Requirement No. Ref. Status Requirement

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Requirement No. Ref. Status Requirement Powered By Docstoc
					Hi George,

I must admit that the requirement tree is a bit confusing for LTP as there are "concurrent" specifications to be

LTP RS:
To start with the LTP RS as the easiest one, from your viewpoint at least. This is the specification according to which
we at ASD have to close-out all LTP requirements against the Customer. Subsystem or unit level responsibles have
no obligation in this respect. Provision of this spec to you is meant to make available an informational source. When
you have spottet discrepancies with other specs, however, we would appreaciate your comments. Be aware that the
existing official issue of the LTP RS is under major revision currently.

OMS RS and OMS Units RS:
The OMS RS is the "translation" (flow-down) of system level req to OMS level. The verification close-out
responsibility is with the OMS subsystem responsible, which formally is ASD. As the close-out of OMS req in most
cases will require verif close-out information from unit level as input and thus this tasks heavily relies on unit

In general this support should be already sufficiently covered if the unit level specifications have been properly
broken down from OMS level requirements to the final technical req on units. Then verificational close-out of these
RS leads nearly completely to OMS level close-outs. Unit level RS verification is in responsibility of unit suppliers, as
UoG for OBI and KT for Laser Assembly. Some of the OMS unit PFM specifications (PM RS, OBI RS) are in statu
nascendi, to say the best. For LTP historical reasons as well the establishment of the unit level specifications based
on EM/TRP program results and on newly defined PFM OMS requirements is expected to be performed by the
"traditional suppliers" (not really the usual way around). So for final agreement on verification close-out of OMS RS
and how far the unit supplier takes a share in responsibility is open till finalization of unit RSs. We will address this

GDIR (= EID-A Annex):
This set of requirements is complementary to each subsystem and unit level RS and needs to be covered within unit
suplliers verification program. However, the GDIR in most cases is only directly applicable for units directly mounted
to the S/C panels. Thus e.g. the OBI is not constrained by GDIR resp. Only in those cases explicetly stated in the
OMS spec. For phasemeter, e.g., the GDIR is fully applicable.

EID-A (Main Body):
The EID-A is sent to subsystem and unit suppliers as informational RS. It has importance only in so far, as unit
suppliers might need this source for establishing their unit level RS. As soon as Subsystem and unit RS have been
established the EID-A requirments should be reflected in the SS/unit RS and verif close-out again is needed only

What RS supersedes which RS:
In general the LTP RS is superseding OMS RS which in turn is superseding OMS Unit RS. GDIR in theory should be
completely complementary to OMS RS and OMS Unit RS, so that contradictional statement should be minimized.
EID-A requirements should be sufficiently covered by the OMS RS and if necessary OMS Unit RS and afterwards is
no longer directly applicable. In summary, the OMS unit level RS at a minimum must comply with GDIR and OMS

As you wrote that you have spottet contradictionary information the following. Different development status of RS
documents and of course human errors might cause contradictionary statements. In case that someone has spottet
such ones the normal procedure is to bring that to the attention of the higher level responsibility or to LTP Architect

By the way:
For (detailed) discussion of verification issues I like you to address Peter Luetzow-Wentzky (see Cc:) who is dealing
with AIV issues at LTP System level. Of course you may contact me directly as well if you like, but in this case please
keep Peter in copy for AIV issues. For all OMS related aspects please keep as well Rainer Sesselmann (see Cc:) at
least in copy who cares at our site as responsible engineer for the OMS. He in general is point of contact for all
technical aspects of OMS.

I hope that this clarifies what you are concerned about.

Cheers,
Rüdiger.



-----Original Message-----
From: George Dixon [mailto:gd@star.sr.bham.ac.uk]
Sent: Donnerstag, 7. April 2005 16:31
To: Gerndt, Ruediger
Cc: 'Ray Carvell'; 'David Robertson'; 'David Hoyland'
Subject: Verification Clarification Required (LTP OB & PMS)




Ruediger,

I am currently compiling verification requirements lists for verification control for both the phasemeter and the optical
bench. I am struggling to understand the philosophy of the requirements specifications 'family'. Currently, there are;

GDIRS
LTP RS
OMS RS
and if I understand correctly, there will be distinct OB and PMS requirement specs arriving soon.

Together, these documents contain thousands of requirements. Sometimes these requirements overlap, or
contradict, sometimes a requirement is repeated verbatim in more than one requirements document.

Which requirements documents *must* the PMS and OB comply with?

In the case of overlap or contradiction, which requirements document takes priority?

Thank you,

George Dixon


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            This list has been generated from the following document



Worksheet   Document ID          Document                                Issue     Date

GDIR        S2-ASU-RS-2031       General Design & Interface Requirements Issue 4    12/1/2004

LTP_RS      S2-ASD-RS-3001       LTP Requirement Specification           Issue 3    12/7/2004

OMS RS      S2-ASD-RS-3010       Optical Metrology System R. S.          Issue 1     2/3/2005
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 Requirement No. Ref. Status                                                   Requirement                                                        i   n
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                                                                                                                                                                          Contamination is the
                                                                                                                                                                                                         MICD?
GDI-31/CREATED/R               The on-ground lifetime of flight hardware is defined as the duration between unit delivery and satellite launch.   O                   R   only possible lifetime
                                                                                                                                                                                                        Statement
                                                                                                                                                                          limiting factor
                                                                                                                                                                                                          MICD?
                               The Unit shall meet the requirements of this specification after a minimum on-ground lifetime of 3 years
GDI-32/CREATED/A,R                                                                                                                                O           A       R                              Refer to GEO600
                               including up to 1.5 years in storage.
                                                                                                                                                                                                         evidence
                               The in-orbit lifetime of the satellite is defined as the duration from launcher seperation until the end of the                                                            MICD?
GDI-33/CREATED/R                                                                                                                                  O                   R
                               mission.                                                                                                                                                                 Statement
                                                                                                                                                                          Radiation hardening     Considering radiation
                               The unit shall be designed with positive margins of safety to meet the requirements of this specification for a
GDI-34/SRS-753/SRD-                                                                                                                                                       of optics and coatings        testing
                               minimum in-orbit lifetime of 11 months with all other consumables able to meet an in-orbit lifetime of 17          O           A       R
MAS-1/A,R                                                                                                                                                                 Fibre Injector critical  possibly using EM
                               months.
                                                                                                                                                                          part                          spares
                               Maintenance during storage shall be as limited as possible and, if required, shall be identified by the supplier                                                    Specification of final
GDI-35/CREATED/R                                                                                                                                  O                   R
                               for approval by the customer.                                                                                                                                         dry-gas dust?
                               The unit shall be designed and fabricated with compatible materials in such a manner that all hazards                                                               Declared Materials
GDI-37/CREATED/A                                                                                                                                  O           A
                               associated with the unit are eliminated, minimised and controlled.                                                                                                          List
                               General safety requirements for electronic units are as following:
                               * All guards and covers provided for personal protection shall be clearly marked to indicate the voltage
GDI-38/CREATED/A               potential.                                                                                                                     A           Not Applicable
                               * Adequate shielding of control equipment and critical equipment is needed to prevent initiation of explosive
                               devices from induced currents.
                                                                                                                                                                          Cannot be tested at
                               The unit shall be able to operate within a pressure range of 1 bar to < 1E-10 bar. It shall have a suitable                                this pressure.
GDI-41/CREATED/A,R             venting provision that is >= 2mm² venting hole area per litre volume. Outgassing vents shall be < 5mm              O           A       R   Outgassing                     Drawing
                               diameter and > 1.5mm diameter. They shall be located close to but not within the unit mounting plane.                                      requirements (fibre
                                                                                                                                                                          injector)
                               For all relevant thermal hardware, explicitly MLI, tapes and heatermats, venting provisions shall be
GDI-42/CREATED/R                                                                                                                                                      R   Not Applicable
                               incorporated.
                                                                                                                                                                          Fibre injector strain
                               Unless a cavity is hermetically sealed adequate means of venting shall be provided in the design. The method                               relieving epoxy sealed
GDI-43/CREATED/R               of venting shall prevent the contamination of the cavity by the external environment and prevent the release of    O                   R   - hence this
                               contaminants from the cavity.                                                                                                              requirement not
                                                                                                                                                                          applicable
                               Structural members (honeycomb panels, in particular) shall include provisions to enable venting of any
                               hermetically sealed volumes during lauch ascent. Any items that do not include venting provisions shall be
GDI-44/CREATED/ T,A                                                                                                                                       T   A
                               treated as sealed containers, and adequate safety margins shall be demonstrated by analysis or by a 1.5 atm
                               proof test.
                                                                                                                                                                                                    Post manufacture
                               All spacecraft units of the same part or configuration number shall be interchangeable in terms of form, fit and                                                    measurement (PFM &
GDI-46/CREATED/R               functions. The units must be of the same qualification status and reliability in order to meet the                 O                   R                               Flight Spare)
                               interchangeability requirement.                                                                                                                                     Post Build Inspection
                                                                                                                                                                                                        Document
GDI-48/CREATED/I               Deleted
GDI-49/CREATED/I               Deleted




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                                                                                                                                                c   c       Y   E                                   Method
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                               For the particular case of connector identification, the following requirements shall apply:
                               * Each unit or bracket is required to bear visible connector labels closely adjacent to the appropriate
                               connector in order to allow a correct mating of the corresponding harness connector.
                                                                                                                                                                        Fibre leads require
                               * For each unit or bracket, the connector identification shall be three alphanumeric characters:
GDI-50/CREATED/I                                                                                                                                                I       identification - method
                               a. The first character is "J" for fixed (hard-mounted) connectors and "P" for mobile connectors.
                                                                                                                                                                        to be determined?
                               b. The two last characters consist of a 2 digits sequential number starting from 01.
                               * The location and content of the above described connector identification labels shall be included in the ICD
                               of the relevant unit.
                               The design of the unit, the position of the connectors, grounding studs and of the attachments etc. shall
                               provide sufficient accessibility to enable the mounting and removal of the unit with standard tools. The unit                            Optical Bench only
GDI-52/CREATED/R               configuration itself shall not hinder the installation and removal of the attachment bolts. Where this           O                   R   demountable with             Drawing
                               requirement cannot be applied, the unit supplier shall provide a kit of tools as a part of the unit MGSE such                            fibre tails
                               that the mounting bolts can be tightened from an accessible position.
                               The equipment shall be designed to require a minimum of special tools and test equipment to maintain
GDI-53/CREATED/R                                                                                                                                O                   R   No tools required            Drawing
                               calibration, perform adjustments and accomplish fault identification.
                                                                                                                                                                         Specification of pre-
                                                                                                                                                                          launch particulate
                                                                                                                                                                                levels
GDI-54/CREATED/R               No field maintenance, servicing or adjustment shall be required within three months of launch                    O                   R
                                                                                                                                                                        Question on Astrium
                                                                                                                                                                        to warrant particulate
                                                                                                                                                                                levels
GDI-57/CREATED/R               Deleted
GDI-58/CREATED/R               Deleted
GDI-59/CREATED/R               Deleted
GDI-60/CREATED/R               Deleted
GDI-62/CREATED/I               Deleted
GDI-63/CREATED/I               Deleted
GDI-65/CREATED/I               Deleted
GDI-66/CREATED/I               Deleted
GDI-68/CREATED/R               Deleted
                               Unless justified and agreed beforehand, any thermally conducting interface filler, used between a unit and the
GDI-70/CREATED/I,R             surface on which it is mounted, shall be of non-curing gasket type rather than a grease or curing                                    R   Not applicable
                               rubber/adhesive. Units must use a bonding strap even if the gasket is electrically conducting.
GDI-72/CREATED/R               Deleted.
                               Deleted
GDI-73/CREATED/R
                               Requirements on magnetic materials can be found in the PA Requirements document for subcontractors.
                               Any seals used shall comply with all the applicable requirements of this specification, particularly regarding
GDI-75/CREATED/R                                                                                                                                                    R   No Seals                     Drawing
                               propellant and simulant compatibility and out-gassing.
                               Any seals requiring periodic replacement during ground activities, and especially prior to launch, shall be
GDI-76/CREATED/R               identified to the Customer. The Unit supplier shall provide any procedures and special tooling required for                          R   No Seals                     Drawing
                               replacement of seals.
GDI-78/CREATED/R               No lubricants shall be used without the prior written agreement of the Customer.                                                     R   No Lubricants                Drawing
GDI-80/CREATED/I,R             All screw type hardware used on the unit shall be locked by adequate measures.                                   O               I   R   PD Mount Only                Drawing
                               All drawings, specifications and engineering data shall only use the International System of Units (SI units),
GDI-82/CREATED/R                                                                                                                                O                   R                                Drawing
                               with the exception of accelerations which may be expressed in terms of multiples of g (gravity).
GDI-83/CREATED/R               Units shall be compatible with mechanical testing.                                                               O                   R                                Drawing




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 Requirement No. Ref. Status                                                  Requirement                                                            i   n
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                                                                                                                                                                         I   COMMENT
                                                                                                                                                     c   c       Y   E                                     Method
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                               Following testing the unit shall be inspected to confirm no physical damage. In order to avoid unrealistic over-
GDI-84/CREATED/I               testing of units/assemblies vibration spectra may be adjusted by notching according to the results of coupled         O               I                                  Post Test Inspection
                               analyses.
                               Any need for notching shall be notified to the Customer as soon as identified. It shall be justified by a technical
                               note. The Customer reserves the right to reject any notching that is not technically justified or possible, due to                            No notching required
                               system constraints.                                                                                                                           owing to high
GDI-86/CREATED/T,A                                                                                                                                   O           A
                               Appendix G: Notching Guidelines for Mechanical Tests gives the guidelines for raising a notching request. It                                  predicted natural
                               defines both the technical way to establish notching levels and the rules to manage associated waivers. In                                    frequencies
                               any case, the decision to accept or reject this waiver is under Customer authority.
                                                                                                                                                                                                              MICD
GDI-87/CREATED/A,R             No unit shall generate microvibration loads at its baseplate interface.                                               O           A       R   Passive design
                                                                                                                                                                                                             Drawings
GDI-2042/CREATED/A,R           Deleted
                               Any unit (excluding propellant reservoirs) whose anticipated total mass loss in orbit exceeds 0.3% of the unit
GDI-2058/CREATED/A,R           total mass shall be identified to the prime contractor, so that an assessment of the effect on gravitational field                A       R   Not Applicable                    MICD
                               of this mass loss can be made, and mitigation strategies identified if required.
                               The following failure modes, for units at all levels of integration, shall be prevented:
                               * Permanent deformation,
                                                                                                                                                                                                      Structural Analysis
                               * Yield,
                                                                                                                                                                             Bolted joint analysis          Report
                               * Rupture,
                                                                                                                                                                             on PD mounts              Refer to previous
                               * Instability,
                                                                                                                                                                             Clarify Astrium's          experience Re
                               * Buckling,
GDI-91/CREATED/A                                                                                                                                     O           A           responsibility for          bonded joints
                               * Gaping of bolted joints, of storage devices,
                                                                                                                                                                             bolted joint design        Glued joints via
                               * Degradation of bonded joints,
                                                                                                                                                                             (Optical Bench to Side referenceto procedure
                               * Vibration induced mounting interface slip,
                                                                                                                                                                             Plates)                     and previous
                               * Loss of alignment of units that are subjected to alignment stability requirements, distortion violating any
                                                                                                                                                                                                          experience
                               specified envelope,
                               * Distortion causing functional failure or short circuit.
                               The unit shall be designed to withstand the environments it will encounter during its lifetime without
                               degradation of its performance, and without detrimental influence on the spacecraft or any other unit. The
                               following shall be taken into account:
                               * Fabrication and assembly loads (e.g. welding, interference fitting)
                               * Handling and transportation loads,                                                                                                                                     Structural Analysis
GDI-92/CREATED/A,R                                                                                                                                   O           A       R
                               * Test loads (including thermal stresses),                                                                                                                                     Report
                               * Launch loads (vibration (including shock), thermal and depressurisation),
                               * Operational loads (including thermal, attitude and orbit control induced loads).
                               * Structural dimensioning of the units shall consider critical combination of simultaneously acting loads (e.g.
                               mechanical and thermal).
                               For sine and random vibrations, the mechanical sizing shall be performed with peak values. For random                                                                    Structural Analysis
GDI-93/CREATED/A                                                                                                                                     O           A
                               vibrations, the peak value is equal to 3 times the rms value unless otherwise specified.                                                                                       Report
                               Wherever practical a fail safe design based on redundant structural elements shall be used. A design                                          Fail Safe Design not
                               implementation is considered fail safe if the failure of one structural element in the load path does not affect                              feasible for main OB
GDI-94/CREATED/A                                                                                                                                     O           A                                             MICD
                               the stiffness of the structure significantly and does not cause remaining structural elements to fail under the                               structure - possible for
                               new load distribution.                                                                                                                        PD mounts?




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                               In cases where a failsafe design cannot be implemented, the load path shall be verified to be safe life.
                               Corresponding structural elements shall be tracked as potential fracture critical items (PFCI's). The following
                                                                                                                                                                         Proving of test bonds
                               items are PFCI's:
                                                                                                                                                                         Proving of as built
                               * pressurised systems;
                                                                                                                                                                         items over a
GDI-95/CREATED/A               * rotating machinery;                                                                                             O           A
                                                                                                                                                                         temperature range
                               * fasteners in safe life design implantations;
                                                                                                                                                                         Consider possible
                               * items fabricated using welding, forging or casting used at limit stress levels 25% of the ultimate tensile
                                                                                                                                                                         analysis?
                               strength;
                               * non-metallic structures.
                               All potential fracture critical items shall be subject to a fracture control programme in accordance with the
GDI-2045/CREATED/A                                                                                                                               O           A
                               requirements of 'Space Engineering - Fracture Control', ECSS-E-30-01A.
                               All mass estimations shall be accompanied by the definition of the design maturity of the concerned item. The
                               margin to be added to each item estimated mass for budget consolidation shall follow the rules expressed in
                               Table 3.2-1. The mass budget shall be reported to the customer through the datasheet as defined in
                               APPENDIX A: MICD.

GDI-98/SRS-753/SRD-                                                                                                                                                                                 Mass Budget
                                                                                                                                                 O       T   A
MAS-1/T                                                                                                                                                                                          Post Build Inspection




                               The mass of an item must be measured with the following accuracy:
                               * Item mass up to 10 kg : 0.005 kg
                               * Item mass from 10 to 20 kg : 0,010 kg                                                                                                   method to be
GDI-100/CREATED/T                                                                                                                                O       T                                       Post Build Inspection
                               * Item mass from 20 to 50 kg : 0,020 kg                                                                                                   determined
                               * Item mass from 50 to 100 kg : 0,050 kg
                               * Item mass from 100 to 350 kg : 0,100 kg
                               All COG and MOI estimates shall be accompanied by the definition of the design maturity of the concerned
                               item. The uncertainty of each item COG and MOI calculation for budget consolidation shall follow the rules
                               expressed in Table 3.2-2. They shall be reported to the customer through the relevant mass, CoG and inertia
                               properties data sheet defined in APPENDIX A: MICD.

                                                                                                                                                                         MOI and c of g data
                                                                                                                                                                         may be calculated
GDI-102/CREATED/A                                                                                                                                O           A                                   Gravitational Model
                                                                                                                                                                         from gravitational
                                                                                                                                                                         model




                                                                                                                                                                         Wording of this
GDI-104/CREATED/T              The unit centre of gravity shall be measured with an accuracy of + or - 1mm.                                      O       T               requirement to be
                                                                                                                                                                         questioned
                                                                                                                                                                         Wording of this
GDI-105/CREATED/A              The unit moment of inertia shall be measured with an accuracy of + or - 5%.                                       O           A           requirement to be
                                                                                                                                                                         questioned


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 Requirement No. Ref. Status                                                 Requirement                                                         i   n
                                                                                                                                                         s
                                                                                                                                                                 P
                                                                                                                                                                     I   COMMENT
                                                                                                                                                 c   c       Y   E                   Method
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                               Unless otherwise specified, units shall have their first main resonant frequency above 140 Hz when fixed on a
                                                                                                                                                                                   Structural analysis
GDI-113/CREATED/T,A            rigid interface. Any exceptions shall be identified to the Customer. Main resonance frequency is defined as       O           A
                                                                                                                                                                                         report
                               frequency such that associated effective mass is greater or equal to 10% of the total unit mass
                               The stiffness requirements shall be demonstrated taking into account definition and analysis uncertainties as
                               follows:
                               * A margin of 15% shall be taken into account for frequency computation with finite element software (e.g.
                                                                                                                                                                                      FE models &
                               NASTRAN), and more than 30% for hand calculations. Special care shall be emphasized on the boundary
GDI-114/CREATED/T,A                                                                                                                              O       T   A                     Structural Analysis
                               conditions representativity.
                                                                                                                                                                                         Report
                               * Assumptions shall be presented taking into account the worst cases for material data base characteristics
                               (e.g. Young Modulus or thickness) or proven measurements from the manufacturer.
                               * Mass figures shall include the actual predicted margins as per Section 3.2.1.2.
                               The safety factors in Table 3.2-3 are minimum values applicable for a qualification model approach. If a proto-
                               flight approach is chosen, then all factors shall be multiplied by 1.1 to cover additional risks.




                                                                                                                                                                                      FE models &
GDI-2057/SRD-STRE-
                                                                                                                                                 O       T   A                     Structural Analysis
3/T,A
                                                                                                                                                                                         Report




                               The units shall be designed with positive margins of safety under the yield and ultimate load conditions as
                                                                                                                                                                                      FE models &
                               defined below. These loads will be combined with potential thermal loads deduced by analysis from the
GDI-129/CREATED/A                                                                                                                                O           A                     Structural Analysis
                               environment seen during the entire on-ground and in-orbit life. The mechanical and thermal environment
                                                                                                                                                                                         Report
                               applicable to the mechanical sizing of the units are defined in Section 4.


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 Requirement No. Ref. Status                                                 Requirement                                                         i   n
                                                                                                                                                         s
                                                                                                                                                                 P
                                                                                                                                                                     I   COMMENT
                                                                                                                                                 c   c       Y   E                              Method
                                                                                                                                                         t   S       E
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                                                                                                                                                                                                 FE models &
                               The design loads for the structure elements are to be derived by the unit manufacturer according to the loads
GDI-130/CREATED/A                                                                                                                                O           A                                Structural Analysis
                               as defined in Section 3.2.1.5 and the dynamic behaviour of the unit/assembly.
                                                                                                                                                                                                    Report
                               The internal loads (thermo elastic, pre-stressed mounting,...) shall be defined by the unit manufacturer. The                                                     FE models &
                                                                                                                                                                         Thermal
GDI-131/CREATED/A              applied loads shall be those imposed by worst-case mass distribution i.e. accounting for mass uncertainties       O           A                                Structural Analysis
                                                                                                                                                                         Side plate loading
                               and design maturity.                                                                                                                                                 Report
                                                                                                                                                                                                 FE models &
                               For the computation of the design loads the maximum margin shall be included in the unit mass and inertia
GDI-132/CREATED/A                                                                                                                                O           A                                Structural Analysis
                               properties as defined in Section 3.2.1.2 and Section 3.2.1.3.
                                                                                                                                                                                                    Report
                               The spacecraft equipment shall be able to withstand the worst-case expected combination of the required
                               loads as per Section 3.2.1.5.1 and associated environments as specified in Section 4. These include
                               manufacturing, assembly, testing, transport, launch and in-orbit operations. All mechanical elements shall
                               demonstrate positive margins of safety. In addition, the factors of safety defined in the Table 3.2-3 and Table                                                Loading Document
GDI-136/CREATED/A,R            3.2-4 below shall be applied to derive the margins of safety.                                                     O           A       R                        Structural Analysis
                               The margin of safety is defined as the ratio between the material allowable yield or ultimate load (or stress)                                                      Repoort
                               and the design yield or ultimate load (or stress) minus 1.
                               The loads/stresses resulting from the application of the design yield loads shall be compared to the yield or
                               0.2% proof stress appropriate to the structural component.
                               No significant permanent deformation or deformation detrimental to the specified performances shall result                                                        FE models &
                               from the application of the qualification load (QL) multiplied by the appropriate safety factor.                                                               Structural Analysis
GDI-2112/CREATED/A,R                                                                                                                             O           A       R
                               The loads/stresses resulting from the application of design ultimate loads shall be compared to the ultimate or                                                      Report
                               failure load/stress appropriate to the structural component.                                                                                                   PA Material Specs




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                               Failure is defined as structural collapse, rupture or other inability to sustain the ultimate loads, or for
                               mechanisms permanent inability to ensure their function. No failure shall result from the application of the
                               ultimate load (Qu) multiplied by the appropriate safety factor as given below.




                                                                                                                                                                                           Loading Document
GDI-2113/CREATED/A,R                                                                                                                                   O           A       R               Structural Analysis
                                                                                                                                                                                                Repoort




                               A summary of the margins of safety for the structural elements of the unit to all design loads shall be prepared                                            Structural analysis
GDI-147/CREATED/A                                                                                                                                      O           A
                               in a single document.                                                                                                                                             report
                               All bolts shall be sized to prevent sliding under mechanical & thermal environments. Initially, a friction
                                                                                                                                                                                           Structural analysis
GDI-148/CREATED/A              coefficient of 0.2 shall be considered for preliminary sizing of the bolts, unless an actual friction coefficient has   O           A           PD mounts
                                                                                                                                                                                                 report
                               been measured.
                               Wherever applicable, rules for general design of bolts, screws and inserts, from ESA PSS-01-303, ESA PSS-                                                   Structural analysis
GDI-149/CREATED/R                                                                                                                                      O                   R   PD mounts
                               03-1202 and ESA PSS-03-208 shall be used.                                                                                                                         report




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                                                                                                                                                     c   c       Y   E                           Method
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                               In addition, in case of combined loads due to thermal differential loading the unit internal allowable loads shall
                               be considered to verify bolts, nuts and inserts strength and evaluated as follows;




                                                                                                                                                                                               Structural analysis
GDI-150/CREATED/A                                                                                                                                    O           A
                                                                                                                                                                                                     report



                               where T, S, and M are actual vaules, and Tm, Sm, and Mm are maximum allowable tension, shear, and
                               moment respectively. Instead of tension (T,Tm), values for compression may be used (C,Cm) if more
                               onerous.
                               Method for evaluation of dimensioning loads/stresses to be considered to verify mechanical sizing takes into
                               account that applied loads (i.e. design yield/ultimate loads multiplied by additional safety factors) are sum                                                   Structural analysis
GDI-153/CREATED/A                                                                                                                                    O           A
                               vectors applied along the worst spatial direction at the unit or part of unit c-o-g. (GD note - effectively                                                           report
                               combines stresses using SRSS method)
                               For the preliminary determination of the requested number of bolt for the attachment of a unit, it will be                                    PD Mounts
GDI-160/CREATED/A              considered that under a 1g environment in any direction, the tensile load per interface bolt of that unit shall not   O           A           InsertsAstrium
                               exceed 10 N.                                                                                                                                  Responsibility
                               The attachment points shall provide a controlled surface contact between the units and the structure to allow
                                                                                                                                                                             PD Mounts
                               control of thermal conditions on the units as well as electrical bonding. This contact shall be maintained under
GDI-161/CREATED/I,R                                                                                                                                  O               I   R   InsertsAstrium
                               all operating conditions, taking into account loading resulting from the different thermal coefficient of
                                                                                                                                                                             Responsibility
                               expansion between dissimilar materials.
                               The interface plane flatness of a unit shall be better than 0.1mm, i.e. all attachment points shall be in a
GDI-162/CREATED/I                                                                                                                                    O               I                        Post Build Inspection
                               common plane within + or - 0.05 mm.
                               The mechanical mounting interface shall be consistent with the thermal and EMC design requirements. In                                                               MICD
GDI-163/CREATED/R                                                                                                                                    O                   R
                               particular, the contact area shall be free of paint.                                                                                                                Drawings
                               The unit bolts type and number shall be defined to withstand the worst-case environmental conditions as
                                                                                                                                                                             PD Mounts
                               defined in Section 4. Sizing rules of Section 3.2.1 shall be applied. For the attachment on the support, units
GDI-164/CREATED/R                                                                                                                                    O                   R   InsertsAstrium
                               shall use M5 bolts preferably. The use of other bolt types might be acceptable, but shall be reviewed and
                                                                                                                                                                             Responsibility
                               agreed on a case-by-case basis.
                               Except otherwise specified, all units shall be through bolted into threaded inserts. The interface bolts
                               clearances of Table 3.2-5 shall be respected.




                                                                                                                                                                             PD Mounts
GDI-165/CREATED/I,R                                                                                                                                  O               I   R   InsertsAstrium
                                                                                                                                                                             Responsibility




                               Thermally dissipative units shall have proper provisions to allow implementation of interface filler between their
GDI-167/CREATED/I,R                                                                                                                                                  I   R   Not applicable
                               base-plate and the supporting structure.


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GDI-168/CREATED/I,R            Unless special conditions override, the thickness of the unit mounting feet shall be at least 3.0 mm.                               I   R   Not applicable
                               For the unit mounting, provision shall be made for under head for flat washers of :-
                               * 12.0 mm diameter for M6 bolts and above;                                                                                                  Not Applicable
GDI-169/CREATED/I,R                                                                                                                                                I   R
                               * 10.0 mm diameter for M5 bolts;                                                                                                            Astrium responsibility
                               * 8.0 mm diameter for M4 bolts.
                               Sufficient clearance shall be allowed between mechanical parts to cover design, manufacturing, assembly
GDI-170/CREATED/I,R                                                                                                                                O               I   R   why inspect?                  Drawings
                               tolerances, alignment translation/rotation ranges and environmental displacements.
GDI-171/CREATED/A              Fasteners shall be verified similarly to other structural items.                                                    O           A           Fibre connectors?
                                                                                                                                                                                                     Structural Analysis
GDI-172/CREATED/A              All units shall be designed allowing for the failure of any single attachment bolt.                                 O           A
                                                                                                                                                                                                           Report
                               Fasteners shall be procured and tested according to approved aerospace standards. After proof-testing or non-                                                        Assembly Inspection
GDI-173/CREATED/I                                                                                                                                  O               I
                               destructive inspection, they shall be marked and stored separately.                                                                                                         (TBC)
                               The Flight equipment shall be able to survive :-
                               * 2 times all mechanical acceptance tests                                                                                                   Refer to fracture
GDI-174/CREATED/A                                                                                                                                  O           A
                               * plus 2 times all mechanical qualification tests (to cover System PFM testing)                                                             control plan
                               * plus one launch
                               Units requiring alignment with an accuracy better than + or - 0.25° shall carry reflecting mirrors. These mirrors
                               constitute the unit optical reference. The optical reference design shall be such to comply with Table 3.2-6
                               requirements.
                               Fixed mirrors shall be delivered with easily mountable/dismountable protective covers for AIV acitivities.
                               Dismountable mirrors shall demonstrate the repeatability of their orientation accuracy.




                                                                                                                                                                           Astium input to design        Drawings
GDI-176/CREATED/R                                                                                                                                  O                   R
                                                                                                                                                                           iterations required         As built report




                               Optical references are required to withstand all the environments supported by the unit with stability better                                                              MICD
GDI-177/CREATED/R                                                                                                                                  O                   R   Fixed mirror design
                               than + or - 15 µrad with respect to each of the 3 unit axes.                                                                                                              Drawings
                               Location of optical references for units shall be agreed between customer and subcontractor through the
GDI-178/CREATED/R              MICD. In particular, the useful faces of the optical reference shall be clearly visible at higher-level assembly    O                   R                                   MICD
                               integration and identified in top assembly drawings that shall form a part of MICD.
                               The alignment errors shall be included in pointing and localisation errors as established in the unit alignment                                                      Alignment Tolerance
GDI-179/CREATED/R                                                                                                                                  O                   R
                               and pointing error budget.                                                                                                                                                  Study




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                               Units which require alignment accuracy of + or - 0.25° or better shall be equipped with adjustment means (or
                               suitable interface for the incorporation of such means) as part of the unit. When the unit alignment is achieved
                                                                                                                                                                              Astrium Responsibility
                               by the use of angled brackets, screw adjusters, and/or shims, they shall be designed and supplied as parts of
GDI-180/CREATED/R                                                                                                                                     O                   R   No internal
                               the unit, unless provided as an integral part of the unit. When shims have to be machined at end of alignment,
                                                                                                                                                                              adjustments possible
                               5 sets of spare shims with maximum possible thickness shall be provided to account for possible iteration or
                               mistake.
                               The mechanical and optical configuration and its interface requirements and dimensions, shall be fully detailed
                               in one (or more) Interface Control Drawing(s) that shall be fully referenced by the unit supplier. This drawing
GDI-183/CREATED/A                                                                                                                                     O           A                                      Drawings
                               shall detail all co-ordinate systems utilised and their relationship to each other, together with the principal unit
                               interfaces. The content of the mechanical and optical ICD shall conform to appendices A and D respectively.
                                                                                                                                                                              Question to Astrium -
                               Interfaces will be subjected to a formal inspection, using interface data sheets in respect to mechanical,
                                                                                                                                                                              content of OICD and
                               thermal, electrical and optical properties and any other details that proves useful (see appendices A, B, C and
                                                                                                                                                                              MICD - alignment            MICD +
GDI-184/CREATED/T,I            D respectively). These data sheets, specimens of which will be provided in MICD, TICD, EICD and OICD,                  O       T       I
                                                                                                                                                                              issues where no             OICD?
                               respectively, will be completed by the unit contractors and then brought together into ICDs, for the various
                                                                                                                                                                              adjustment possible
                               units.
                                                                                                                                                                              internal to OB
                                                                                                                                                                              Question to Astrium -
GDI-185/CREATED/A              The issues of ICDs have to be released as defined in the relevant unit Statement of Work.                              O           A           what is Statement of
                                                                                                                                                                              Work?
                               One of the attachment holes on a unit shall be specified as the reference hole and must carry the identification
                                                                                                                                                                              Design iteration with
GDI-186/CREATED/R              letter R. This shall be clearly indicated on the mechanical interface drawings The reference hole shall support        O                   R                              Drawings
                                                                                                                                                                              Astrium required
                               the Unit Reference Frame.
                               The unit reference frame shall have its origin at the unit reference hole (R) and shall be in accordance with
                               Figure 3.2-2.




                                                                                                                                                                              Design iteration with
GDI-187/CREATED/R                                                                                                                                     O                   R                              Drawings
                                                                                                                                                                              Astrium required




                               The unit alignment reference frame shall have its origins at the centre of the optical cube and shall be in                                    Design iteration with
GDI-188/CREATED/R                                                                                                                                     O                   R
                               accordance with Figure 3.2-2.                                                                                                                  Astrium required




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 Requirement No. Ref. Status                                                Requirement                                                          i   n
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GDI-190/CREATED/A              The dimensioning of the attachment hole pattern shall be specified with respect to the Unit Reference Frame.      O           A                                      Drawings
                               Interface Control Drawings shall be provided to the customer, with the following media and file formats:
                               * Operating system: HP-UX compatible
                               * Media type: CD-ROM (other media to be agreed on a case-by-case basis
                               * File format (by order of preference):
GDI-191/CREATED/R              a. CATIA EXP                                                                                                      O                   R   3D IGES                      ICDs
                               b. 3D IGES
                               c. STEP
                               d. 2D DXF
                               e. 2D IGES
                               Finite elements models shall be provided for all items which have principal modes of vibration at frequencies
                               less than:-
                               - 140 Hz actual or,
GDI-197/CREATED/A              - 161 Hz if predicted by FE model (i.e. +15% margin) or,                                                          O           A                                   Analysis Report
                               - 182 Hz if predicted by hand calculation (i.e. +30% margin).
                               The supplied FEM shall represent all significant modes, i.e. modes with an effective modal mass equal to or
                               larger than 5% of the total equipment mass.
GDI-198/CREATED/T              Deleted
GDI-2075/CREATED/R             The use of duplicate element numbers for elements of different types is to be avoided.                            O                   R                           Analysis Report
                               The model shall be prepared using NASTRAN Software Version 70.5 or later with all elements compatible with
GDI-200/CREATED/R                                                                                                                                O                   R                           Analysis Report
                               70.5. The NASTRAN version shall be indicated as part of the model data.
                               Finite elements models shall be provided for all units which have principal modes of vibration at frequencies
                               less than 140 Hz or when specifically requested in the unit SoW. It shall be provided, with the following media
                                                                                                                                                                         Specifically Required
GDI-201/CREATED/R              and file formats:                                                                                                 O                   R                           Analysis Report
                                                                                                                                                                         Fracture Control
                               * Operating system: HP-UX compatible
                               * Media type: CD-ROM (other media type might be agreed on a case-by-case basis).
                               For the FEM delivery, the following list of information's shall be provided by the subcontractor:
                               * A document describing the models and containing as a minimum:
                               a. Description of the reference frames (a drawing is required),
                               b. GRID points, element numbering and connectivity co-ordinate systems,
                               c. Modelling assumptions/boundary conditions,
                               d. Plots of the deformation-free shape,
                               e. Status of compliance with the present specification,
GDI-202/CREATED/R              f. Mass breakdown and distribution in the models in accordance with the unit detailed mass budget and the         O                   R                           Analysis Report
                               gravitational control requirements.
                               * Output listings including the BULK data echo from eigen-value analysis for the full model. Associated model
                               plots shall also be provided with a description of the modes. The main dynamic parameters resulting from the
                               modal analysis (effective masses) shall be delivered.
                               * The model files shall include:
                               a. The complete set of BULK data for each model.
                               b. The complete set of BULK data corresponding to the zero stress test of the thermo-elastic model.
                               S.I. units are to be used:
                               * Newton (N) for force
                               * Kilograms (kg) for mass
GDI-204/CREATED/R                                                                                                                                O                   R                           Analysis Report
                               * Meters (m) for length
                               * Seconds (s) for time
                               * Degrees Celsius (°C) for temperature



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 Requirement No. Ref. Status                                                Requirement                                                        i   n
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                               The FEM shall use the Units/assembly Reference Frame (see Section 3.2.3) as the primary local coordinate
                               system for the building of the model. The following reference frames shall be used for interface description:
                               * Mechanical reference frame
                               * Assembly/Units reference frame
GDI-206/CREATED/R              Each part can be moved by changing only the primary local coordinate system. Definition and displacement        O                   R             Analysis Report
                               system for each grid (and also elements which need one) must be defined relative to a coordinate system
                               dependant on the primary local coordinate frame of the unit/assembly. In one assembly, one can define as
                               many different coordinate systems as necessary but they must depend on the primary local coordinate
                               system.
                               The model name, issue and date must be included at the beginning of the structural data. Sufficient comments
                               must be included to ensure complete understanding of the model by the customer. As a minimum, interface
GDI-208/CREATED/R                                                                                                                              O                   R             Analysis Report
                               GRID points with their associated coordinate systems must be shown clearly in the comment part. The
                               boundary conditions shall be completely defined.
                               The model description shall refer to a configured issue of the following documents:
                                                                                                                                                                                 Analysis Report
                               * Mass, Inertia and Centre of Gravity budget
GDI-209/CREATED/R                                                                                                                              O                   R              Mass Budget
                               * Mechanical ICD of the assembly/unit. In the BULK data, the reference of the interface drawing shall be
                                                                                                                                                                                     MICD
                               introduced as comment with the last version and last revision.
                               The following comment cards must be included in the model:
                               * Model name, issue and date,
                               * Boundary conditions (clamped DoF)
                               * Interface GRID points description (number, location)
GDI-210/CREATED/R                                                                                                                              O                   R             Analysis Report
                               * Mass properties and frequency of the model,
                               * GRIDs included in the ASET (if necessary)
                               * GRIDs included in the CSUPEXT, if necessary)
                               * Restitution node (if needed).
                               Each Nastran BULK card will have a unique identifier number in the range allocated for each model.
GDI-212/CREATED/R              Continuation card identifiers should contain letters from the identification number. It is requested that no    O                   R             Analysis Report
                               duplicate number among Nastran BULK data cards exists in each model.
                               All data cards used to define default values for a set of cards are excluded, namely:
                               * PARAM, Bailout
                               * PARAM, K6ROT
                               * PARAM, ERROR…
                               * PARAM, EPZEO..
GDI-213/CREATED/R                                                                                                                              O                   R             Analysis Report
                               The only PARAM card authorized to affect a set of cards is "PARAM, AUTOSPC, YES", but the listing of
                               degrees of freedom affected must be delivered. Also, no DoF perpendicular to the plate elements can be
                               clamped by special card (SPC).
                               Note: If the model is created using NASTRAN v2001 rev 4, then the default PARAM card SNORM is to be
                               overridden with PARAM, SNORM, 0.0
                               The authorised NASTRAN elements are the following:
                               * 1D: ROD, BAR, BEAM
                               * 2D: TRIA3, QUAD4
                               * 3D: CPENTA, CTETRA, CHEXA
GDI-214/CREATED/R                                                                                                                              O                   R             Analysis Report
                               * Masses: CONM2, CMASSSS2
                               * Interfaces: CELASi
                               * Others: PLOTEL, RBE2, RBAR, MPC,
                               Agreement with the Prime Contractor will be necessary for the use of any other kind of elements.




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                               The use of MSG-MESH data cards is prohibited. A punched output shall be provided instead. Some
GDI-215/CREATED/R              connections, coordinate and load cards using GRID points to orient vectors in space must be excluded from             O                   R             Analysis Report
                               the BULK. The alternate valid method is to use the point location in space.
                               For the structural mass, the density field of the MAT card will be used or a non-structural mass number will be
GDI-216/CREATED/R                                                                                                                                    O                   R             Analysis Report
                               set in the PSHELL cards.
                               When necessary, equipments may be represented by CONM2 elements located at their centre of gravity. The
                               CONM2 card will have the mass and inertia moments given in the local coordinate system of the sub-system.
GDI-217/CREATED/R              The concentrated mass will be connected to the support points with the adequate element representing an               O                   R             Analysis Report
                               equivalent stiffness and the thermal expansion behaviour. In case another modellisation is used, the supplier
                               shall explain and justify the method.
                               The mass distribution check performed thanks to the NASTRAN "Grid Point Weight Generator (GPWG)"
                               provides:
                               * Mass matrix of the structure (M0) at the reference point in the primary local coordinate system;
                               * Mass of the structure and position of the centre of gravity with respect to the reference point in the primary
                               local coordinate system;
                               * Inertia matrix at the centre of gravity and in the primary local coordinate system of the reference point [I(S)]
GDI-221/CREATED/A                                                                                                                                    O           A                     Analysis Report
                               or in the principal axis of inertia [I(Q)]. Reference frame transformation matrix (Q) between local coordinate
                               system of the reference point and principal axis of inertia.
                               The outputs of the NASTRAN "Grid Point Weight Generator (GPWG)" shall be used to check whether the
                               mass of the model is in good accordance with the unit mass budget.
                               * Mass figures shall be the same for axes X, Y, and Z;
                               * The diagonal terms of the centre of gravity matrix must be zero.
                               Strain energy and stiffness maxratio are requested to check the good mathematical conditioning of internal
                               loads of the model. This check is made with a classical NASTRAN dynamic analysis (SOL 103) with nominal
                               boundary conditions of the model. The strain energy is calculated and given in the "*.f06" file at every support
                               point. During this check, the maximum ratio between the stiffness matrix terms (called "MAXRATIO") is also
                               presented in the "*.f06" file.
                               Success criteria are the following:
                               * The value of the strain energy must be limited to 5.0E-3 J.
                               * The maximum ratio represents the ratio between the higher and the lower value of the stiffness matrix. The
                               maximum allowed value for the MAXRATIO is 1.0E7.
GDI-223/CREATED/A              It should be noted that MSC Nastran calculates an equivalent internal strain energy (work) for each rigid body        O           A                     Analysis Report
                               vector. The rigid body error and the strain energy should be zero if a set of statistically determinate SUPORT
                               DoFs is chosen. Round off error may lead to computational zero values for these quantities ('computational
                               zero' is a very small number that is normally 0.0 except for numerical round off). The rigid body error ratio and
                               strain energy may be significantly non zero for any of the following reasons:-
                               • Round off error accumulation.
                               • The ur set is overdetermined leading to redundant supports. This condition gives high strain energy.
                               • The ur set is underspecified leading to a singular reduced stiffness matrix and a MAXRATIO error. This
                               condition gives a high rigid error ratio.
                               • The multipoint constraints are statically indeterminate. This condition gives high strain energy and a high rigid




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                               Delivered models will be expected to meet the conditioning requirements when checked by the customer.
                               The purpose of the conditioning check is to identify regions of the structure, which are potential mechanisms
                               that can cause numerical rounding errors in the stiffness matrix that can lead to errors in results. The
                               procedure for this check is based on the identification of singularities in the model when constrained with
                               SUPORT bulk data at six degrees of freedom representative of the constraints to be used in the static and
                               frequency analysis. In the solution the stiffness matrix, KFF, is partitioned:
                               [KFF] = [ KFRFR | KFRR ]
                               [ KFRR | KRR ]
                               KRR contains the SUPORT degrees of freedom. KFRFR contains the unconstrained degrees of freedom and
                               is subject to matrix decomposition. Degrees of freedom on the diagonal of the decomposed stiffness matrix
GDI-225/CREATED/A                                                                                                                                    O           A                     Analysis Report
                               less than unity are identified in a matrix DLFR. These are points of low stiffness and potential singularity. The
                               ratios of the terms on the diagonal of KFRFR to those on the diagonal of the decomposed matrix maximum
                               are computed and terms greater than 1.0E7 identified in a matrix MECHFR. These indicate the presence of
                               potential mechanisms in the model.
                               The acceptance criteria are:
                                 DLFR values : > 1.0E-3 and >0.0
                                 MECHFR values : < 1.0E7 and > 0.0
                               Those GRID points and dofs not compliant with the criteria shall be identified and a justification provided.
                               Remark: the MECHFR values are the definition of the NASTRAN MAXRATIO values.
                               An alternative method of checking for mechanisms can be used with approval of the Project Prime.

                               The purpose of the constraint check is to verify the model internal loads. This verification is made with a
                               NASTRAN SOL 103 analysis with the model in free-free conditions and
                               with DMAP commands. The results of this check are given in the "*.f06" file.
                               Four matrix called KRBi are calculated by: (KRBi) = (f)t (K) (f), where (K) is the stiffness matrix and (f) a rigid
                               body mode vector calculated thanks to the geometry.
                               Matrix KRBi are performed at various model sizes:
                                 G set (KRGB matrix): all structural degrees of freedom;
                                 N set (KRBN matrix): all structural degrees of freedom not constrained by multi-point constraints;
                                 F set (KRBF matrix): all unconstrained (free) degrees of freedom;
GDI-227/CREATED/R                                                                                                                                    O                   R             Analysis Report
                                 A set (KRBA matrix): analysis set.
                               Success criteria is the following:
                               The resultant matrix KRBi are equal to twice the strain energy in the structure following its motion as a rigid
                               body. With units of metre and the terms on the diagonal of the respective energy matrix, KRBi, shall be
                                 G set: <1.0E-3 Nm translation dof <1.0E-3 Nm Rotational dof
                                 N set: <1.0E-3 Nm translation dof <1.0E-3 Nm Rotational dof
                                 F set: <1.0E-3 Nm translation dof <1.0E-3 Nm Rotational dof
                                 A set: <1.0E-3 Nm translation dof <1.0E-3 Nm Rotational dof
                               If this cannot be achieved the associated grid and dof shall be identified and justification provided.

                               The purpose of the "Free-Free" check is to verify the rigid body modes of the model. This verification is made
                               with a NASTRAN SOL 103 dynamic analysis with the model in free-free conditions. Success criteria is the
GDI-229/CREATED/R              following:                                                                                                            O                   R             Analysis Report
                               * The computed frequencies of first 6 modes shall be below 1E-3 Hz.
                               * Supplementary rigid body modes (such as mechanisms) shall be justified on a case-by-case basis.




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                               The purpose of the static load check is to confirm that total forces at the interface of the model divided by the
                               excitation acceleration must be equal to the unit/model mass. This check consists in exciting the model with
                               1g accelerations along the 3 orthogonal directions separately. Interface reaction forces will be computed using
                               the NASTRAN command
GDI-231/CREATED/R                                                                                                                                  O                   R              Analysis Report
                               SPCFORCES=ALL.
                               Success criteria is the following:
                                 The total force computed at the interface shall be equal to the unit mass multiplied by g (gravity factor).
                                 No constraint forces should occur at points other than legitimate boundary condition locations.

                               The purpose of the "Zero" stress check is to verify that the model to be used for the thermo-elastic analysis is
                               well conditioned.
                               This is achieved, assuming the model characteristics shown below, when the model check results presented
                               below are obtained:-
                               Model Characteristics
                                The model is isostatically constrained
                                All the materials used in the model have been replaced by a fictitious homogenous and isotropic one with the
                               following properties:-
GDI-233/CREATED/R                 Young's Modulus = 100 GPa                                                                                        O                   R              Analysis Report
                                  Poisson's Ratio = 0.3
                                  Coefficient of Thermal Expansion (CTE) = 10-5 m/m/°C
                                All elements have the same reference temperature TREF = 20°C
                                A uniform elevation in temperature is applied to all GRIDs of the complete model of ∆T=100°C.
                               Model Results
                               The resulting maximum stresses and rotations anywhere in the model should comply with the following values:-
                                  Maximum stress s 100 Pa
                                  Maximum rotation 10-4 Rad
                               Full finite element models shall be correlated with the test results, and a dedicated report shall be issued and
GDI-235/CREATED/T,A            delivered with the correlated FEM.                                                                                  O           A                      Analysis Report
                               Correlation shall demonstrate compliance with the following criteria:-
                                                                                                                                                                                      Analysis Report
                               For modes with effective masses > 10% of the total mass, the measured forces and moments shall deviate
GDI-2102/CREATED/T,A                                                                                                                               O       T   A                     Environmental Test
                               from predictions by <10%
                                                                                                                                                                                           Report
                               Damping shall take measured values as input for the response analysis and use realistic test inputs for this
GDI-2101/CREATED/R                                                                                                                                 O                   R              Analysis Report
                               purpose.
                               The cross-orthogonality checks shall comply with;                                                                                                      Analysis Report
GDI2100/CREATED/T,A            * diagonal terms shall be >0.9                                                                                      O       T   A                     Environmental Test
                               * off-diagonal terms shall be < 0.1                                                                                                                         Report
                               For other significant modes                                                                                                                            Analysis Report
GDI-2099/CREATED/T,A           * MAC shall be > 0.85                                                                                               O       T   A                     Environmental Test
                               * Eigen frequency deviation between measured and FEM results shall be <5%                                                                                   Report
                               For modes with effective masses > 10% of the total mass                                                                                                Analysis Report
GDI-2098/CREATED/T,A           * MAC shall be > 0.90                                                                                               O       T   A                     Environmental Test
                               * Eigen frequency deviation between measured and FEM results shall be <5%                                                                                   Report
                               For fundamental modes                                                                                                                                  Analysis Report
GDI-2097/CREATED/T,A           * MAC shall be > 0.95                                                                                               O       T   A                     Environmental Test
                               * Eigen frequency deviation between measured and FEM results shall be <3%                                                                                   Report




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 Requirement No. Ref. Status                                                  Requirement                                                            i   n
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                               The difference between the the Centre of Gravity position of the FEM and the measured unit shall be within                                                           Analysis Report
GDI-2096/CREATED/T,A                                                                                                                                 O       T   A
                               the measurement tolerance stated in section 3.2.1.3                                                                                                                   Mass Budget
                                                                                                                                                                                                    Analysis Report
GDI-2095/CREATED/T,A           The mass difference between the measured and FEM figure shall be <1% of the totla unit mass.                          O       T   A
                                                                                                                                                                                                     Mass Budget
                               If Reduced Distortion Analysis Models are requested, they shall be delivered as simplified static models which
                               are derived by removing elements from the full static model that do not have a significant effect on the
                               distortion of the instrument baseplate or are rigid elements connecting non-coincident grids.
                               Typically the model will include:
                               1. Full instrument baseplate with all interface locations
                               2. Instrument shear walls mounted to the baseplate which affect the baseplate stiffness locally                                               Not Applicable
                               3. Instrument equipments mounted to the instrument baseplate adding stiffness locally                                                         Detail Thermo -
GDI-2074/CREATED/T,I                                                                                                                                         T       I
                               The purpose of producing this reduced model is to minimise the effort required by the instrument supplier in                                  Mechanical Analysis
                               detailing the thermal properties of all components in the full static model, and to reduce the size of model used                             to be carried out.
                               for determining the thermo-elastic behaviour at system level.
                               The elements remaining in the model shall have the thermal properties of each of the component materials
                               added, and shall be checked using the procedures detailed in Section 3.2.4.7.
                               The models shall be delivered in a state which allows thermal distortion analysis to be carried out ( i.e. no rigid
                               elements connecting non-coincident grids).
                               The Reduced Model Model delivery shall include the following:-
                               1. In order to retain the full numeric accuracy of the data, the reduced model is to be supplied as mass and
                               stiffness matrices.
                               2. Any NASTRAN DMAP statements used to read in these matrices are also required.
                               3. Separate files containing all the bulk data cards required to be able to run the dynamic analysis using the                                Not Applicable
                               modal matrices, including (for example) the following:-                                                                                       Detail Thermo -
GDI-2072/CREATED/A,R                                                                                                                                             A       R
                                 Interface file. GRID and CORD definition cards for the interface points.                                                                    Mechanical Analysis
                                 Partition file. SPOINT cards showing the identification numbers used to create the reduced matrices.                                        to be carried out.
                               4. Separate 'example' run ('.dat') and output ('.f06') files required to be able to run the dynamic analysis using
                               the modal matrices. These will be used to perform a check run of the model in order to verify the models for
                               correct function.
                               This information shall be delivered as ASCII files (see Section 3.2.4.1 for media formats)
                                                                                                                                                                                                    Analysis Report
                               For other modes within the frequency range of interest, the total effective mass shall be >90% of the total unit
GDI-2071/CREATED/T,A                                                                                                                                 O       T   A                                 Environmental Test
                               mass.
                                                                                                                                                                                                         Report
                                                                                                                                                                                                    Analysis Report
                               For other significant modes measured during test that have effective mass >5% of the total unit mass, the
GDI-2070/CREATED/T,A                                                                                                                                 O       T   A                                 Environmental Test
                               eigenfrequency deviation between measured and FEM results shall be <20%.
                                                                                                                                                                                                         Report
                                                                                                                                                                                                    Analysis Report
                               For fundamental modes with effective mass >5% of the total unit mass, the eigenfrequency deviation between
GDI-2069/CREATED/T,A                                                                                                                                 O       T   A                                 Environmental Test
                               measured and FEM results shall be <3%.
                                                                                                                                                                                                         Report
                                                                                                                                                                                                    Analysis Report
                               The difference between the Centre of Gravity position of the FEM and the measured unit shall be within the
GDI-2068/CREATED/A,I                                                                                                                                 O           A   I                               Post Assembly
                               measurement tolerance stated in Section 3.2.1.3.
                                                                                                                                                                                                       Inspection
                               The mass difference between the measured and FEM figure shall <1% of the total unit mass.
                                                                                                                                                                                                    Analysis Report
                               Reduced finite element models shall be correlated with the test results, and a dedicated report shall be issued
GDI-2067/CREATED/T,A                                                                                                                                 O       T   A                                 Environmental Test
                               and delivered with the correlated FEM.
                                                                                                                                                                                                         Report
                               Correlation shall demonstrate compliance with the following criteria:-




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 Requirement No. Ref. Status                                                 Requirement                                                         i   n
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                               For gravitational modelling purposes, the mass distribution of each element of the unit shall be defined in a
                               FEM model as follows:
                               - For each element of the unit the following items shall be specified
                               - A unique node number
                               - Mass
GDI-2043/CREATED/A,R           - X, Y, Z location in the Unit Reference Frame (as specified in GDI-186)                                          O           A       R                          Analysis Report
                               - The mesh size shall be no greater than 40 mm cubed
                               - The mass at a node representing a given volume of the equipment should be within 1% of the actual mass
                               inside that same volume. The mesh size shall be reduced as appropriate to meet this criteria.
                               - The mesh shall be chosen to align with components of the equipment (e.g. at the mid-plane of equipment
                               casings or circuit boards). This distribution information shall form part of the ICD.
                               In the frame of LISA Pathfinder, all units with the exception of the LTP and DRS sensors shall be conductively
                                                                                                                                                                         Not Applicable -
                               controlled units (see Section 3.3.1.2) with the exception of low power units for which the power density on the
GDI-239/CREATED/R                                                                                                                                                    R   Negligible Power
                               total skin area is less than 70W/m². For these low power units thermal control which relies on radiative
                                                                                                                                                                         dissipation on bench
                               coupling is allowed.
                                                                                                                                                                         Not Applicable -
                               All units with a power density on the total skin higher than 70W/m² will be mounted so that the base plate is
GDI-241/CREATED/R                                                                                                                                                    R   Negligible Power
                               conductively coupled with the spacecraft with a full base plate (without holes).
                                                                                                                                                                         dissipation on bench
                                                                                                                                                                         Not Applicable -
                               As far as possible thermal gradients across the baseplate shall be minimised i.e. the unit shall be designed to
GDI-243/CREATED/R                                                                                                                                                    R   Negligible Power
                               be isothermal.
                                                                                                                                                                         dissipation on bench
                                                                                                                                                                         Not Applicable -
                               For radiative units the temperature difference between all points of the unit case and baseplate shall be less
GDI-244/CREATED/R                                                                                                                                                    R   Negligible Power
                               than 3oC.
                                                                                                                                                                         dissipation on bench
                                                                                                                                                                         Not Applicable -
                               For conductive units the temperature difference between all points of the unit baseplate shall be less than
GDI-245/CREATED/R                                                                                                                                                        Negligible Power
                               3oC.
                                                                                                                                                                         dissipation on bench
                                                                                                                                                                         Not Applicable -
GDI-246/CREATED/R              For non-isothermal units a reference temperature shall be defined for each thermal node.                                              R   Negligible Power
                                                                                                                                                                         dissipation on bench
                               The temperature reference point (TRP) shall be selected on the unit external surface, preferably close to a
                               mounting bolt, such that its temperature reflects the average unit housing temperature (no hot or cold spot).                             Responiblity of
GDI-248/CREATED/R              The temperature reference point shall be used as reference for the thermal acceptance and qualification tests.                        R   Environmental
                               The temperature reference point will be maintained within the specified temperature limits by the S/C thermal                             monitoring package
                               control during flight.
                                                                                                                                                                         No EMC requirements
GDI-252/CREATED/A              The mounting interface shall comply with the mechanical and EMC requirements.                                     O           A           Claify mechanical
                                                                                                                                                                         requirements
                               Unit mounting areas shall not be painted or anodised, in order to obtain a good conductive thermal contact
GDI-253/CREATED/R                                                                                                                                O                   R                             Drawings
                               with the Spacecraft.
                                                                                                                                                                         Not Applicable -
GDI-254/CREATED/R              All units shall have a smooth and plane baseplate to give full contact for the thermal control requirements                           R   Negligible Power
                                                                                                                                                                         dissipation on bench
                               Local heat flux shall not be greater than 1.5x specified base plate average heat flux. The base plate heat flux                           Not Applicable -
GDI-255/CREATED/A              is defined as the ratio of the thermal dissipation versus effective contact area when the unit is in the test                 A           Negligible Power
                               configuration                                                                                                                             dissipation on bench




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                                                                                                                                                                             Not Applicable -
                               The heat exchange and the desired internal unit temperature are achieved by the selection of finishes.
GDI-258/CREATED/R                                                                                                                                                        R   Negligible Power
                               Units shall be designed with an emittance > 0.8 (black)
                                                                                                                                                                             dissipation on bench
                               Temperature monitoring of selected points within a unit shall be provided by the Unit Supplier to cover the
                                                                                                                                                                             Responiblity of
                               following cases:
GDI-260/CREATED/R                                                                                                                                                        R   Environmental
                               * Unit operational health and safety monitoring.
                                                                                                                                                                             monitoring package
                               * Unit operational temperature and performance monitoring.
                                                                                                                                                                             Responiblity of
                               The location, type and electrical interface of all devices used for unit temperature measurement shall be
GDI-261/CREATED/R                                                                                                                                                        R   Environmental
                               defined in the ICD.
                                                                                                                                                                             monitoring package
                               The units shall be designed such that all internal heat sources have the required thermal couplings to the
                               external surfaces of the unit to comply with the interface requirements of Section 3.3.2.1 and Section 3.3.2.2
                                                                                                                                                                             Not Applicable -
                               and their own unit requirements in terms of temperature and heat exchange. Hot spots on the external
GDI-263/CREATED/A                                                                                                                                                A           Negligible Power
                               surface of the unit are to be taken into account at the unit level. In designing the unit and ascertaining the
                                                                                                                                                                             dissipation on bench
                               optimum flow paths, the unit design will take due account of the method of mounting and the relative
                               exchanges with the environment by both conduction and radiation.
                               Hot spots on the external surface of the unit are to be taken into account at the unit level. In designing the unit
                               and ascertaining the optimum flow paths, the unit design shall take due account of the method of mounting
                                                                                                                                                                             Not Applicable -
                               and the relative exchanges with the environment by both conduction and radiation.
GDI-264/CREATED/A,R                                                                                                                                              A       R   Negligible Power
                               The objective of the unit thermal analysis is to demonstrate that internal components have acceptable
                                                                                                                                                                             dissipation on bench
                               temperatures when the unit itself (i.e. case or base plate) is at its operating temperature limits, with a
                               reasonably representative distribution of the heat flow to the external environment.
                               Average dissipation of the unit operating with stable external load over any time period between 10 seconds
GDI-2079/CREATED/A,R                                                                                                                                             A       R   Not connected to bus
                               and 2000 seconds shall not vary by more than 0.5% when bus voltage varies by up to 0.5%
                               All thermal hardware mounted on the unit shall be identified in the ICD, for example:
                               * Heaters
                                                                                                                                                                             Data to be supplied if
GDI-267/CREATED/R              * Temperature Sensors                                                                                                 O                   R
                                                                                                                                                                             required
                               * Low Emissivity Tape
                               * Multi Layer Insulation Blanket
                               All unit thermal interfaces shall be described within a unit thermal interface control document as per                                        Data to be supplied if
GDI-269/CREATED/R                                                                                                                                    O                   R
                               APPENDIX B: TICD.                                                                                                                             required
                               The use of the ESARAD and ESATAN software packages is recommended for all thermal analyses and shall                                          Data to be supplied if
GDI-2091/CREATED/A,R                                                                                                                                 O           A       R
                               be required for all deliverable thermal mathematical models.                                                                                  required

                               The Thermal mathematical model shall be provided for non-isothermal units in accordance with the following
                               rules:
                               * Reduced model of maximum 7 nodes (or otherwise agreed between the unit supplier and the customer)
                                                                                                                                                                             Data to be supplied if
GDI-272/CREATED/A              * Node definition and heat capacity                                                                                   O           A
                                                                                                                                                                             required
                               * Conductive coupling
                               * External geometry, thermal characteristics and radiative coupling
                               * Heat dissipation for each node and operating modes, including significant transient cases and failure cases




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                               All units used in thermal models (geometrical and thermal mathematical models) will conform to the
                               International System units (SI units). In particular for:
                               * Radiative coupling: square meters
                               * Temperature: Kelvin (or Celsius)
                                                                                                                                                                             Data to be supplied if
GDI-273/CREATED/A              * Power: Watts                                                                                                        O           A
                                                                                                                                                                             required
                               * Energy: Joules
                               * Dimensions: meters
                               * Mass: Kg
                               For all other parameters, measurement units shall be declared by the supplier.
                               The detailed thermal model of a unit shall be verified and correlated with a thermal test. The correlation criteria
                                                                                                                                                                             Not Applicable -
                               shall be:
GDI-275/CREATED/T,A                                                                                                                                          T   A           further integration
                               * ± 3°C on the temperatures
                                                                                                                                                                             level
                               * ± 10 % on the required heater power
                               The consistency between reduced and detailed thermal model shall be demonstrated by:                                                          Not Applicable -
GDI-277/CREATED/A              * The temperature difference less than ± 2 degrees.                                                                               A           further integration
                               * The required heater power less than ± 10%.                                                                                                  level
                                                                                                                                                                             Not Applicable -
GDI-278/CREATED/A              The convergence of the thermal models shall be demonstrated.                                                                      A           further integration
                                                                                                                                                                             level
                               For each optical surface, the physical dimension shall be oversized with regard to the useful optical dimension
GDI-282/CREATED/R                                                                                                                                    O                   R                                  Drawings
                               by at least 1mm along both axes.
                               Glass types and material quality shall be selected to comply with the performance requirement in terms of
                                                                                                                                                                                                       Design Description /
GDI-284/CREATED/R              spectral transmittance and spatial environment. Glass selection and related optical configuration optimisation        O                   R
                                                                                                                                                                                                             Report
                               shall be performed in accordance with the environment requirements (as defined in Section 4).
                                                                                                                                                                                                       Design Description /
GDI-285/CREATED/R              The use of stain sensitive glasses shall be avoided.                                                                  O                   R
                                                                                                                                                                                                             Report
                               The use of optical cements shall be avoided as far as possible. If their use is nevertheless necessary, the
                                                                                                                                                                                                       Declared Materials
GDI-286/CREATED/R              contractor shall demonstrate their qualification to LISA Pathfinder requirements (ageing, thermal cycles,             O                   R
                                                                                                                                                                                                              List
                               radiation dose, etc...). Reference to their use for other space programmes shall also be mentioned.

                                                                                                                                                                                                            Drawings
                               Coating shall be designed such that performance, as measured at ambient conditions on ground, are
GDI-288/CREATED/T,R                                                                                                                                  O       T           R                             Mirror Specification
                               maintained in the space environment.
                                                                                                                                                                                                      Thermal Vacuum Test
                                                                                                                                                                                                       Declared Materials
                                                                                                                                                                                                              List
GDI-289/CREATED/R              Metallic layers of the coatings, if any, shall be grounded.                                                           O                   R   No mettalic Coatings
                                                                                                                                                                                                       Design Description
                                                                                                                                                                                                            Rerport
                                                                                                                                                                             Coatings performance
                                                                                                                                                                                                       Design Description /
GDI-290/CREATED/R              Thermo-optical properties of the coatings shall be compatible with the thermal control design requirements.                               R   statement for
                                                                                                                                                                                                             Report
                                                                                                                                                                             temperature range
GDI-291/CREATED/R              Deleted
GDI-292/CREATED/R              High efficiency anti-reflective coating shall be applied to all free refractive surfaces.                             O                   R   TBC                            Drawings




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                                                                                                                                                                                                                      Manufacturer's testing
                               Sensitivity of coatings to polarisation effects associated to the incidence angle shall be determined and                                                                                report included in
GDI-293/CREATED/T,R                                                                                                                                                 O       T           R   OBI RS
                               validated.                                                                                                                                                                              desiign description
                                                                                                                                                                                                                              report
                                                                                                                                                                                            To be tested under
                               The optical performance of the unit shall be verifiable on ground under ambient pressure and Earth gravity                                                   vacuum                      TV test with PFM
GDI-295/CREATED/T                                                                                                                                                   O       T
                               conditions.                                                                                                                                                  Functional Test               phasemeter
                                                                                                                                                                                            possible
                               Alignment and interface with regard to other optical units shall be maintained between clean room conditions
                               and space environment. Note that residual defocus or misalignment induced by ambient air or gravity
                                                                                                                                                                                            Not applicable -
GDI-296/CREATED/T              conditions remains acceptable as long as it has been clearly identified and as removable means to                                            T
                                                                                                                                                                                            focussing
                               compensate it during alignment and test on ground are provided. Compensation means shall not affect
                               performed alignment nor measured performance.
                               The unit supplier shall provide the optical interface data in the optical data sheet format as provided in
GDI-298/CREATED/R                                                                                                                                                   O                   R                                     OICD
                               APPENDIX D: OICD.
                               The free mechanical aperture of optical surfaces shall be oversized with respect to the minimum clear
                                                                                                                                                                                            Requirement not
                               aperture by at least 2 mm along both axes to avoid any stray reflection on the mechanical parts. The minimum
GDI-299/CREATED/R                                                                                                                                                                       R   appropriate - specified
                               clear aperture is determined according to the input beam characteristics, specified FOV, pupil (dimensions,
                                                                                                                                                                                            in OBI RS
                               location and decentring if any), alignment and long term stability.
                               In addition to specific requirements mentioned in the relevant unit specification, any unit shall be designed to                                                                        Design Description
GDI-300/CREATED/R                                                                                                                                                   O                   R
                               minimise the internal stray light.                                                                                                                                                           Report
                               The unit supplier shall use an optical model for numerical simulation of the unit. This model shall be
                               established using the complete set of latest specifications and tolerances that are available about the unit. The
GDI-302/CREATED/A                                                                                                                                                   O           A                                        Analysis Report
                               model shall include not only the actual optical elements but also intermediate image planes, intermediate pupil
                               imaging planes wherever applicable.
                                                                                                                                                                                            Zemax software
GDI-303/CREATED/A              The numerical model shall be developed in Code V (r)                                                                                 O           A
                                                                                                                                                                                            (TBD)
                               The numerical model shall be used for the evaluation of the unit's optical performance. Actual glass
                                                                                                                                                                                            Moelling of as built
GDI-304/CREATED/A              characteristics as measured by the glass supplier shall be included. Performance analyses shall take into                            O           A                                        Analysis Report
                                                                                                                                                                                            unit
                               account the diffraction effects, misalignments and manufacturing tolerances.
                               All electrical performances are specified under Worst-Case End-Of-Life conditions, unless otherwise explicitly
GDI-308/CREATED/R                                                                                                                                                                       R   Not Applicable
                               notified.



                                                        Interface Code   Interface Designation                                        Current   Section


                                                        LCA (LCL)        Regulated Latching Current Limiter Power Class A:            1A        Section 3.5.2.1
                                                        LCB (LCL)        Regulated Latching Current Limiter Power Class B:            2A        Section 3.5.2.1
                                                        LCC (LCL)        Regulated Latching Current Limiter Power Class C:            3A        Section 3.5.2.1
                                                        LCD (LCL)        Regulated Latching Current Limiter Power Class D:            5A        Section 3.5.2.1
                                                        LCE (LCL)        Regulated Latching Current Limiter Power Class E:            8A        Section 3.5.2.1
                                                        LCF (LCL)        Regulated Latching Current Limiter Power Class F:            10A       Section 3.5.2.1
                                                        FCA (FCL)        Regulated Foldback Current Limiter Power Class A:            1A        Section 3.5.2.1
                                                        FCB (FCL)        Regulated Foldback Current Limiter Power Class B:            2A        Section 3.5.2.1
                                                        MIL              MIL-STD-1553B Interface                                                Section 3.5.5.1
                                                        SBDL             Standard Balanced Digital Link                                         Section 3.5.5.2
                                                        USL              UART Serial Link Interface                                             Section 3.5.5.3
                                                        PPS              Pulse Per Second Interface                                             Section 3.5.5.4.1
                                                        SYNC             Synchronization Clock Interface (TBC)                                  Section 3.5.5.4.2
                                                        AN1              Analogue TM Acquisition -5V to +5V                                     Section 3.5.5.5.1
                                                        AN2              Analogue TM Acquisition 0V to +5V                                      Section 3.5.5.5.2
                                                        AN3              Analogue TM Acquisition -10V to +10V                                   Section 3.5.5.5.3
                                                        ANY              Temperature Acquisition Type 1: YSI 44907/YSI-44908) (TBC)             Section 3.5.5.6.1
                                                        ANP              Temperature Acquisition Type 2: PT-1000                                Section 3.5.5.6.2
                                                        ANF              Temperature Acquisition Type 3: Fenwall (TBC)                          Section 3.5.5.6.3
                                                        SHP              Standard High Power On/Off Command                                     Section 3.5.5.7.1
                                                        EHP              Extended High Power On/Off Command                                     Section 3.5.5.7.2
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                                                                         Standard Low Power On/Off Command (TBC)                Section 3.5.5.7.3                                                                                 Page 23 of 335
                                                        RSA              Relay Status Acquisition                                               Section 3.5.5.8
                                                        BLD              Digital Bi-Level TM Acquisition (TBC)                                  Section 3.5.5.11
                                                        DTC              X-Band Digital TC Channel IF                                           Section 3.5.5.9.1
                                                        RLS              Receiver Lock Status IF                                                Section 3.5.5.9.2
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                               Beginning-Of-Life criteria shall be derived by the Unit Supplier from the specified parameters for testing and
                               acceptance of all on-board units. All interfaces are referenced by a specific Interface Code. Table 3.5-1 lists
                               all the standard interfaces:
                                                        Interface Code   Interface Designation                                        Current   Section


                                                        LCA (LCL)        Regulated Latching Current Limiter Power Class A:            1A        Section 3.5.2.1
                                                        LCB (LCL)        Regulated Latching Current Limiter Power Class B:            2A        Section 3.5.2.1
                                                        LCC (LCL)        Regulated Latching Current Limiter Power Class C:            3A        Section 3.5.2.1
                                                        LCD (LCL)        Regulated Latching Current Limiter Power Class D:            5A        Section 3.5.2.1
                                                        LCE (LCL)        Regulated Latching Current Limiter Power Class E:            8A        Section 3.5.2.1
                                                        LCF (LCL)        Regulated Latching Current Limiter Power Class F:            10A       Section 3.5.2.1
                                                        FCA (FCL)        Regulated Foldback Current Limiter Power Class A:            1A        Section 3.5.2.1
                                                        FCB (FCL)        Regulated Foldback Current Limiter Power Class B:            2A        Section 3.5.2.1
                                                        MIL              MIL-STD-1553B Interface                                                Section 3.5.5.1
                                                        SBDL             Standard Balanced Digital Link                                         Section 3.5.5.2
                                                        USL              UART Serial Link Interface                                             Section 3.5.5.3
                                                        PPS              Pulse Per Second Interface                                             Section 3.5.5.4.1
                                                        SYNC             Synchronization Clock Interface (TBC)                                  Section 3.5.5.4.2
                                                        AN1              Analogue TM Acquisition -5V to +5V                                     Section 3.5.5.5.1
                                                        AN2              Analogue TM Acquisition 0V to +5V                                      Section 3.5.5.5.2
                                                        AN3              Analogue TM Acquisition -10V to +10V                                   Section 3.5.5.5.3
                                                        ANY              Temperature Acquisition Type 1: YSI 44907/YSI-44908) (TBC)             Section 3.5.5.6.1
GDI-309/CREATED/R                                       ANP              Temperature Acquisition Type 2: PT-1000                                Section 3.5.5.6.2                          R   Not Applicable
                                                        ANF              Temperature Acquisition Type 3: Fenwall (TBC)                          Section 3.5.5.6.3
                                                        SHP              Standard High Power On/Off Command                                     Section 3.5.5.7.1
                                                        EHP              Extended High Power On/Off Command                                     Section 3.5.5.7.2
                                                        SLP              Standard Low Power On/Off Command (TBC)                                Section 3.5.5.7.3
                                                        RSA              Relay Status Acquisition                                               Section 3.5.5.8
                                                        BLD              Digital Bi-Level TM Acquisition (TBC)                                  Section 3.5.5.11
                                                        DTC              X-Band Digital TC Channel IF                                           Section 3.5.5.9.1
                                                        RLS              Receiver Lock Status IF                                                Section 3.5.5.9.2
                                                        DTM              X-Band Digital TM Channel IF                                           Section 3.5.5.9.3
                                                        RSU              X-Band Transponder Uplink Interface                                    Section 3.5.5.9.4
                                                        RSD              X-Band Transponder Downlink Interface                                  Section 3.5.5.9.5
                                                        PYR              Pyro Interface                                                         Section 3.5.5.10.2
                                                        LVC              Latch Valve Command Interface                                          Section 3.5.5.13.1.1
                                                        LVS              Latch Valve Status Interface                                           Section 3.5.5.13.1.2
                                                        FCVC             Flow Control Valve Command Interface                                   Section 3.5.5.13
                                                        MEC              Main Engine Flow Control Valve Command Interface                       Section 3.5.5.13
                                                        PTS              Pressure Transducer Supply Interface                                   Section 3.5.5.13
                                                        PTA              Pressure Transducer Acquisition Interface                              Section 3.5.5.13
                                                        PBA              Battery Power Interface                                                TBD
                                                        PSA              Solar Array Power Interface                                            TBD
                                                        SCS              Solar Cell Sensor Interface (TBC)                                      Section 3.5.5.12




                               All PROM's shall be accessible and removeable after the unit has been integrated to the spacecraft without
GDI-2024/CREATED/R                                                                                                                                                                         R
                               the need to de-integrate the unit from the spacecraft.
GDI-2046/                      The design of all essential loads (i.e those supplied from FCL's) shall not be prone to any lock-up
                                                                                                                                                                                           R
Derived from SRS-529/R         phenomenon requiring recovery via the removal of external power.
                               All units connected to the sunlight regulated bus shall ensure full performance for a power bus voltage at the
                               unit power input as specified in Table 3.5-2 and Table 3.5-3.
                               When the spacecraft is in sunlight the the spacecraft power bus voltage will be regulated to 28V at the main
GDI-338/CREATED/T,A                                                                                                                                                            T   A
                               regulation point.
                               When the spacecraft is in sunlight the spacecraft power bus voltage will keep its nominal value at the main
                               regulation point to within +/-0.14V in steady state.
                               The spacecraft sunlight regulated bus shall have a nominal ripple voltage in the time domain below 1% peak
GDI-2104/SRS-539/T,R                                                                                                                                                           T           R
                               to peak of the nominal bus voltage.
                               For load transients of upto 50% of the nominal load, bus transients shall not exceed 2% and the bus voltage
GDI-2103/SRS-538/T,R           shall remain within 5% of its nominal value during all source transients and load transients in nominal                                         T           R
                               operation with a recovery time of 2ms.




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                               For information - When the spacecraft is in sunlight the spacecraft power bus voltage shall be regulated to
GDI-1269/CREATED/T                                                                                                                                        T
                               28V at the main regulation point.
                               For information - When the spacecraft is in sunlight the spacecraft power bus voltage shall keep its nominal
GDI-1270/CREATED/T,A                                                                                                                                      T   A
                               value at the main regulation point to within +/-0.14V in steady state.
                               If undervoltage protection is implemented by the load, the load shall not switch off its DC/DC converter for
                               voltages in the specified operating range:
GDI-339/CREATED/T              * V > minimum specified operating Voltage - 1V.                                                                            T
                               Appropriate Hysteresis shall be implemented for switch on. Detailed timing of automatic switch-on after under
                               voltage switch-off if implemented shall be defined and agreed via unit Interface Control Document.
                               In case of an inductive load, when considering the bus impedence mask, the load shall prevent an overvoltage
GDI-340/CREATED/T,A            generation to the power source. The maximum over voltage emission shall not exceed 0.5V above the                          T   A
                               maximum specified DC. bus voltage.
                               The load shall not be irreversibly degraded for any standing or fluctuating voltage as defined in Table 3.5-3
                               (point -27).
GDI-341/CREATED/R                                                                                                                                                     R
                               Note: If required by the load, primary power under-voltage and over-voltage protection has to be provided by
                               the load.
GDI-342/CREATED/R              No fuse protection shall be implemented.                                                                                               R
                               No primary current protection shall be implemented on the DC/DC converter of a load, which is connected to
GDI-343/CREATED/R              an LCL output. Note: Exceptions from this requirement may be granted on the basis of unit inrush current                               R
                               measurements even after power loss and recovery.
                               The contractor shall design the load side of the LCL interface to be compliant to the characteristics as defined
GDI-344/CREATED/T,R                                                                                                                                       T           R
                               in Table 3.5-2 and Table 3.5-3 below:
GDI-345/CREATED/I,R            Deleted
GDI-346/CREATED/T              All power converters shall be designed to allow operation in either free-running or synchronised mode.                     T
GDI-347/CREATED/T              The free-running frequency shall be limited to ±10% of the nominal frequency.                                              T
                               The as designed free-running frequency and frequency variations shall be defined and agreed in the unit
GDI-348/CREATED/T                                                                                                                                         T
                               Interface Control Document.




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                               The units shall be designed taking into account the source impedance depicted in Figure 3.5-1 and defined in
                               Table 3.5-2 and Table 3.5-3 for primary power lines.




GDI-349/CREATED/A                                                                                                                                         A




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GDI-349/CREATED/A                                                                        A




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                               At the point of regulation, the impedance of the voltage-regulated bus, operating with one source (battery or
GDI-1273/CREATED/T,R                                                                                                                                   T           R
                               solar array) shall be below the impedance mask shown in Figure 3.5-1.




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                               The contractor shall design his side of the Regulated FCL interface to be compliant to the characteristics as
                               defined in the Interface Datasheet "FCL", Table 3.5-4 below.




GDI-352/CREATED/T,R                                                                                                                                    T           R




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                               Following switch-ON, and during input filter charging, the user shall ensure that the instantaneous load
                               characteristic never crosses the foldback region (see Figure 3.5-2):




GDI-354/CREATED/T,R                                                                                                                                         T           R




                               The power allocation for each unit is given in the unit specification, it covers all the operating modes and the
                               mean and peak (long and short) figures. Note that:
                                Mean represents the average consumption over 5 minutes (inclusive of heater power)
GDI-361/CREATED/T,A             Short peak represents the power demand within 1 msec                                                                        T   A
                                Long peak represents the power demand within 100 msec
                               The compliance versus the power allocations shall be established by taking into account the worst-case
                               conditions within the qualification temperature range and the in-orbit lifetime including radiation effects.

                               For each power interface circuit, the following consumption shall be calculated:
GDI-362/CREATED/T,A            * Nominal consumption using nominal component values calculated at the estimated operational temperature                     T   A
                               * Worst case consumption using worst case component values and temperature
                               A power consumption test shall be required at temperature extremes during environmental testing on flight
GDI-363/CREATED/T,R                                                                                                                                         T           R
                               equipment with the unit running in operationally representative state.
                               When a unit is internally redundant, and the supply to one of the internal redundant modules fails, the unit shall
GDI-365/CREATED/T,A                                                                                                                                         T   A
                               be able to fulfil all its performances and functionality when switched to the redundant part.



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                               Upon application of power in nominal conditions all electronic equipment shall have a safe initial configuration
GDI-367/CREATED/T                                                                                                                                           T
                               and electrical status that is fully defined, reproducible and reported in the ICD’s.
                               The following requirements apply only in the case where an electrical unit supplies secondary power lines to
                               another unit.
GDI-370/CREATED/T              It shall be possible to switch on the source unit without having to connect an external load to its power outputs.           T
                               The output voltages shall correspond to their nominal values under these conditions. (If unit Supplies Power to
                               Secondary Device Only)
                               The source unit shall be protected against short-circuits on the secondary power lines (either differential or to
GDI-371/CREATED/T                                                                                                                                           T
                               the mechanical ground). (If unit Supplies Power to Secondary Device Only)
                               The supplied unit and Electrical I/F shall withstand without damage the supply voltages generated in case of
GDI-372/CREATED/T,A            source unit failure, as specified in the unit technical specification. (If unit Supplies Power to Secondary Device           T   A
                               Only)
                               The signal provider is referred to as Driver. In the case where the signal is provided by a passive device, this
                               device is more particularly called Source (see Figure 3.5-3).
                               The signal user is referred to as Receiver. In the case where the signal is used by a passive device, this
                               device is more particularly called Load (see Figure 3.5-3).




GDI-378/CREATED/R                                                                                                                                                       R




                               Specified driver (or source) characteristics shall be considered at the output of the driver (or source), with the
                               specified load.
                               All data and signal interface drivers shall survive a short circuit to driver ground, receiver ground or structure
GDI-379/CREATED/T,A                                                                                                                                         T   A
                               without permanent degradation.
GDI-380/CREATED/T,A            The unit shall tolerate active signal I/Fs when unpowered without any permanent degradation.                                 T   A
                               In case the electrical architecture does foresee cross strapping on interface level the interfaces shall ensure
GDI-381/CREATED/T,R                                                                                                                                         T           R
                               proper function with 'both interfaces powered' and 'one interface unpowered'.
GDI-382/CREATED/R              In case no load is specified, the characteristics are to be considered with the driver output in open circuit.                           R



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                               Signal duration and rise and fall times are defined as follows:
                               Signal duration:The signal pulse width is defined as the time between the voltage crossing points of fall and
                               rise time to 50 % of the measured full amplitude. See Figure 3.5-4.
                               Signal rise and fall time: The rise and fall time of a digital signal are defined as the time duration between 10%
                               and 90% of the nominal voltage swing. See Figure 3.5-5.
                               The delay between two signals is defined as the time between the voltage crossing points 50% at the full
                               amplitude level.




GDI-391/CREATED/A                                                                                                                                               A

                               Interface signal drivers shall consider the capacitive loading by the harness; the worst-case design
                               performance shall comply with the values as specified in Figure 3.5-6 for a Twisted Shielded Pair.




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                               performance shall comply with the values as specified in Figure 3.5-6 for a Twisted Shielded Pair.                    l               T
                                                                                                                                                                 S




                               Cables falling into different EMC classifications shall be assembled to different (separate) cable bundles and
GDI-395/CREATED/I,R            connectors. If this is not feasible and wires of different classifications use the same connector, the separation                     I   R
                               shall be implemented by a row of grounded pins in between.
                               All cable bundles shall be routed as close as possible to the structure ground plane/ground rail respectively, in
GDI-396/CREATED/I,R                                                                                                                                                  I   R
                               order to reduce the common mode noise.
                               In wiring through connectors all leads shall be kept as close as possible to their return (i.e. twisted wires shall
GDI-397/CREATED/I,R                                                                                                                                                  I   R
                               be routed on adjacent pins), to obtain good self cancellation and to minimize the wire loop.
                               The DC resistance between the single cable shield and the shield ground point (at the connector, unit case,
GDI-398/CREATED/T                                                                                                                                            T
                               PCB or intermediate points) shall be <= 10 m
                               The structure termination of shields shall be made via connector housing. When multiple shielding is used,
GDI-399/CREATED/I,R                                                                                                                                                  I   R
                               each shield shall be grounded separately.
                               All connectors mounted on units shall be D*MA** connectors except for coaxial links which shall use SMA type
                               connectors. For power lines with currents greater than 15Amps circular connectors shall be used, e.g.
GDI-401/CREATED/R                                                                                                                                                        R
                               according ESA SCC 3401/056 25-19 (AWG 12). Exception to this requirement may be granted for High
                               voltage connectors.
                               The number of times flight connectors are mated / demated shall not exceed 5, up to unit delivery and shall be
GDI-402/CREATED/R                                                                                                                                                        R
                               designed to cope with a further 50.




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                               Different connector classes shall be implemented in order to separate the different type of links: Power,
                               Signal, and Pyros.
                               Classifications: Power and signal lines shall be gathered into the following EMC classes:
                                  class 1 : power (primary / secondary)
                                  class 2 : digital signals , high level analogue signals (except RF)
                                  class 3 : pyrotechnics
                                  class 4 : low level analogue signals (except RF)
GDI-403/CREATED/R                 class 5 : RF signals (via coaxial lines , waveguides , microwave transmission lines)                                                 R
                               Signals falling into different EMC classifications shall be assembled to separate connectors and cable
                               bundles.
                               If not feasible, the separation shall be achieved by a row of grounded pins.
                               Sensitive, "high quality" secondary power should not be routed with primary power in the same bundle.
                               In case of such power a distinction as follows is recommended:
                               - Class 1a : Primary Power
                               - Class 1b : Secondary Power
                               Connectors at interfaces shall be clearly identified in particular in the ICD and GA drawing. This applies to
GDI-405/CREATED/R                                                                                                                                                      R
                               equipment connectors as well as to interface brackets connectors.
GDI-406/CREATED/R              Connectors shall not be a source of single point failures.                                                                              R
                               Equipment or structure-mounted connectors shall be male, except those supplying or distributing power or
GDI-407/CREATED/R                                                                                                                                                      R
                               coaxial cable connectors, which shall be female.
GDI-408/CREATED/R              Male and female connectors shall be mechanically locked together to prevent inadvertent disconnection.                                  R

GDI-409/CREATED/I              Active lines together with their return shall be on adjacent contacts to facilitate cable twisting and shielding.                   I
GDI-410/CREATED/R              Connectors shall be made of Non magnetic material                                                                                       R
                               For any unit connector which contains a number of free pins:
                                 At least one free pin shall be internally connected to the mechanical chassis of the unit by a resistance lower
GDI-411/CREATED/T,R                                                                                                                                        T           R
                               than 10m .
                                 At least one connector free pin shall be internally connected to the secondary 0V of the unit (if applicable).
                               Nominal and redundant lines shall have separated connectors. If not feasible, connector pins carrying
GDI-412/CREATED/R                                                                                                                                                      R
                               redundant functions shall be physically separated and isolated from each other.
                               All electrical connectors shall be located at a minimum distance of 25mm from the unit-mounting plane in
                               order to avoid problems with cable routing and cable harness support fixation. When connectors are located
GDI-414/CREATED/R                                                                                                                                                      R
                               above 80mm from the unit interface, the equipment supplier shall define tie-wraps on the unit sides to support
                               the harness. The mechanical ICD's shall clearly identify the tiewraps and the associated harness routings.
                               Connectors shall be arranged in such a way that the harness connectors can be mated and demated easily
GDI-415/CREATED/R              without special tools and without touching any neighbouring connectors. The minimum free space around                                   R
                               each connector shall be 10mm to allow for installation of spacers and covers.
                               Mechanical methods in conjunction with identification markings shall be employed to prevent incorrect mating
GDI-416/CREATED/I,R                                                                                                                                                I   R
                               of connectors.
                               Connector savers shall be utilized on all flight standard connectors to minimize the number of times a flight
GDI-417/CREATED/R              connector is mated/demated during the unit and subsystem integration activities. The unit manufacturer shall                            R
                               provide these savers.
                               The connection shield ground pin to case shall be as short as possible in order to minimize its effectiveness to
GDI-418/CREATED/R                                                                                                                                                      R
                               act as an antenna, receiving and/or transmitting shield currents. The maximum allowable length is 6 cm.



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                               Test connectors shall have sufficient protection to prevent from any potential hazards to the unit during testing
                               via the unit test set. The protection shall be in the form of current limiting resistors, diodes or protection via the
GDI-420/CREATED/R                                                                                                                                                           R
                               test set when other forms of protection are not practical. The unit supplier is responsible for the protection
                               provided.
GDI-421/CREATED/I,R            Test connectors shall be protected by EMC metal covers attached to fixation bolts                                                        I   R
GDI-422/CREATED/R              The metallic protection cover shall be capable of flight operation.                                                                          R
                               The MIL-STD-1553 Bus features 2 different Buses, one Nominal and one Redundant. Only one bus is active
                               at any time. A single Bus Controller (BC) supported by the OBC manages each bus. All the other units are
GDI-426/CREATED/R                                                                                                                                                           R
                               connected to the bus as Remote Terminals (RT).
                               Each data bus subscriber equipment shall comply with MIL-STD-1553 B + Notice 3 standard.
GDI-427/CREATED/R              All units (BC or RT) shall be configured in long stub connection.                                                                            R
GDI-428/CREATED/R              Each RT (N&R) shall be connected to both 1553 buses (N&R). See Figure 3.5-8.                                                                 R
GDI-429/CREATED/R              Each stub shall be grounded inside each RT or BC derivation by a redunded resistor.                                                          R
GDI-430/CREATED/R              The RT address shall be programmable on an external connector.                                                                               R
GDI-431/CREATED/R              The 1553-bus shall be connected on separate connectors. No other signals shall be on these connectors.                                       R
                               Unless otherwise agreed with the Prime Contractor, the remote terminal address definition shall be performed
                               on a dedicated Cannon 9 S equipment connector, according to the following pin function :
                               pin 1 remote terminal address bit n° 4 (MSB)
                               pin 2 remote terminal address bit n° 3
                               pin 3 remote terminal address bit n° 2
                               pin 4 remote terminal address bit n° 1
                               pin 5 remote terminal address bit n° 0 (LSB)
                               pin 6 remote terminal address parity bit
                               pin 7 secondary OV
                               pin 8 secondary OV
                               pin 9 not connected
                               Concerning remote terminal address definition pins (bits 4 to 0 and parity), a logical " 1 " level shall be
                               obtained by floating the corresponding pin (no connection at harness connector level) ; adequate filtering shall
                               be provided inside the unit on those signals. A logical " 0 " level shall be obtained by connecting the
                               corresponding pin to the secondary OV pin at harness level ; the current in each remote terminal address
                               definition pin shall not exceed 10 mA when programmed to logical level " 0 ".




GDI-1198/CREATED/R                                                                                                                                                          R




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GDI-1198/CREATED/R                                                                                                                              R


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                               The 1553-Bus Protocol shall be compliant to LISA Pathfinder Data Bus Specification.




GDI-432/CREATED/R                                                                                                                               R




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                               The unit shall be compatible with the setup as defined in Figure 3.5-9.




GDI-434/CREATED/R                                                                                                                                 R




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                               The SBDL link interface is dedicated to serial digital links or synchronisation signals. This link is based on the
                               RS422 standard.
                               The SBDL Link interface is shown in Figure 3.5-10.




GDI-438/CREATED/T,R                                                                                                                                         T           R




                               Although the line is symmetrical the two wires are identified as true line and complementary line.
                               The true line is the non-inverted output of the driver. The complementary line is the inverted output of the
                               driver.
                               The status (Vdiff = Vtrue - Vcomp) of the signal is defined High (Logic “1”) when the true line has a positive « 1
                               » level w.r.t the ground and the complementary line has a« 0 » level versus the ground. The low level of the
                               SBDL (logic “0”) is conversely when the true line has a « 0 » level and the complementary
                               line has a « 1 » level.




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                               The contractor shall design his side of the Standard balanced Digital Link (SBDL) interface to be compliant to
                               the characteristics as defined in Interface Datasheet "SBDL", Table 3.5-5 and Table 3.5-6 below.




GDI-1201/CREATED/T,R                                                                                                                                    T           R




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GDI-1201/CREATED/T,R                                                                                                                                  T           R




                               The UART RS-422 serial link shall be composed of two 2 signals, one Transmit Data Line (TD) and one
                               Receive Data Line (RD) as seen from the OBC (see Figure 3.5-11).




GDI-450/CREATED/R                                                                                                                                                 R




                               The UART RS-422 Serial Link Interface shall be implemented using Standard Balanced Link (SBDL) interface.
GDI-451/CREATED/R              The contractor shall design his part of the interface to be compliant to the characteristics as given by the                       R
                               Interface Data Sheet "SBDL".


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                               The contractor shall design his part of the UART RS-422 Serial Link interface to be compliant to the following
                               data transmission characteristics:
                               - Asynchronous protocol (according to RS232 but SBDL signal-levels)
                               - Data flow control by software
GDI-452/CREATED/R              - Start Bit                                                                                                                          R
                               - 8 Data Bits
                               - no Parity Bit
                               - 1 Stop Bit
                               - Data Rate (each link): selectable 19.2k / 38.4k / 57.6k / 76.8k Bauds.
                               Figure 3.5-12 shows an example for data transmission via the UART Serial Link (AB hex):
                               When no data is being transmitted, the line status shall be "Logical 0".
                               The line status (TD, RD) of the Asynchronous protocol shall correspond to the SBDL signal levels as follows:
                               "Logical 0": SBDL true line at high level, comp line at low level.
                               "Logical 1": SBDL true line at low level, comp line at high level.




GDI-453/CREATED/R                                                                                                                                                   R




                               The OBC shall be able to send commands on the Transmit Data Line (TD) even during data reception on the
GDI-1274/CREATED/T                                                                                                                                      T
                               Receive data Line (RD).
GDI-1275/CREATED/T             No data repetition mechanism in both directions shall be supported by the OBC and the user, respectively.                T
                               Command messsages sent by the OBC to the user and HK measurement data received by the OBC shall be
GDI-1276/CREATED/T                                                                                                                                      T
                               transmitted in continuous blocks without time gaps between the bytes of a block.




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                               The Pulse Per Second (PPS) Interface shall be implemented using Standard Balanced Link (SBDL) interface.
                               The contractor shall design his part of the interface to be compliant to the characteristics defined in Table 3.5-
                               7 (Interface Data Sheet "PPS"):




GDI-460/CREATED/R                                                                                                                                                       R




GDI-462/CREATED/R              The active level shall be High level                                                                                                     R
GDI-463/CREATED/R              The synchronisation edge shall be the rising edge                                                                                        R
                               The pulse width shall be >= 900 ns




GDI-464/CREATED/T                                                                                                                                           T




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                               Analogue acquisition interfaces are used for the acquisition by the OBC of information from Users in the form
                               of a voltage varying between two defined limits. This voltage is sampled on a regular basis, converted from
                               analogue to digital and coded as an 11 or 12 bit word (unipolar or bipolar acquisition). The interface shall
                               consist of a differential link (single ended emitter, differential receiver). See Figure 3.5-14.




GDI-471/CREATED/R                                                                                                                                                  R




                               Analogue Telemetry Acquisition -5V to +5V Interface.
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "AN1", Table 3.5-8 and Table 3.5-9 below.




GDI-1205/CREATED/T,R                                                                                                                                   T           R


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GDI-1205/CREATED/T,R                                                                 T           R




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                               Analogue Telemetry Acquisition 0V to +5V Interface.
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "AN2", Table 3.5-10 and Table 3.5-11 below.




GDI-1210/CREATED/T,R                                                                                                                                T           R




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GDI-1210/CREATED/T,R                                                                                                                               T           R




                              Analogue Telemetry Acquisition -10V to +10V Interface.
                              The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                              Interface Datasheet "AN3", Table 3.5-12 and Table 3.5-13 below.




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GDI-1211/CREATED/T,R                                                                                                                               T           R
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GDI-1211/CREATED/T,R                                                                                                                                    T           R




                               Temperature Acquisitions (ANY, ANP, ANF)
                               These acquisitions are used for thermal control (control and monitoring) and also for unit monitoring.
                               There are three options:
                               - Type 1 (IF-Code "ANY"):
                               Thermistor type: YSI-44907/-44908 (10KOhm @25°C)
GDI-482/CREATED/R              - Type 2 (IF-Code "ANP"):                                                                                                            R
                               Thermistor type: PT-1000 (1000 Ohm @ 0°C)
                               - Type 3 (IF-Code "ANF"):
                               Thermistor type: Fenwell (15KOhm @25°C)
                               The signal shall be transmitted via twisted shielded pairs. The cable shield is connected at both sides of the
                               interface to chassis ground.




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                               The temperature aquisition interface circuitry, as well as the interconnecting harness, shall be as shown in
                               Figure 3.5-15.




GDI-483/CREATED/R                                                                                                                                                 R




                               Temperature Acquisition Type 1: YSI 44907/YSI-44908 (ANY) Interface.
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "ANY", Table 3.5-14 and Table 3.5-15 below.




GDI-1215/CREATED/T,R                                                                                                                                  T           R
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GDI-1215/CREATED/T,R                                                                                                                                T           R




                               Temperature Acquisition Type 2: PT-1000 (ANP) Interface.
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "ANP", Table 3.5-16 and Table 3.5-17 below.




GDI-487/CREATED/T,R                                                                                                                                 T           R


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GDI-487/CREATED/T,R                                                                                                                                 T           R




                               Temperature Acquisition Type 3: Fenwall (ANF) Interface.
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "ANF", Table 3.5-18 and Table 3.5-19 below.




GDI-1216/CREATED/T,R                                                                                                                                T           R



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GDI-1216/CREATED/T,R                                                                                                                                 T           R




                               The purpose of the Standard High Power On/Off Command interface is to transfer a pulse from the driver to
                               the user, which can be used to switch/drive high power loads such as relays or optocoupler, e.g. for
GDI-493/CREATED/R                                                                                                                                                R
                               decentralised power switching or unit configuration purposes.
                               The High Power On/Off Command source shall be referenced to driver signal ground.
GDI-494/CREATED/R              The High Power On/Off Command receiver shall be isolated from any user electrical reference.                                      R
                               The High Power On/Off Command receiver shall be equipped with appropriate circuits in order to suppress
GDI-495/CREATED/R              any switching transients, in particular those due to inductive loads such as relays, which may cause the                          R
                               current drive capability, or the over voltage capability of the source to be exceeded.
                               The High Power On/Off Command source shall be short circuit proof for short circuits to source or receiver
GDI-496/CREATED/R                                                                                                                                                R
                               signal ground and structure.
                               The Standard High Power On/Off Command interface shall implement diodes at the level of the driver (e.g. by
GDI-1220/CREATED/R                                                                                                                                               R
                               means of 2 serial diodes or equivalent ) to allow unit external Or-ing of commands.




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                               Standard High Power On/Off Command:
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "SHP", Table 3.5-20 and Table 3.5-21 below.




GDI-497/CREATED/T,R                                                                                                                                 T           R




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GDI-497/CREATED/T,R                                                                                                                                 T           R




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                               Extended High Power On/Off Command:
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "EHP", Table 3.5-22 and Table 3.5-23 below.




GDI-502/CREATED/T,R                                                                                                                                 T           R


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GDI-502/CREATED/T,R                                                                                                                                   T   S       R




                               The purpose of the Low Power On/Off Commands interface is to transfer a pulse from the driver to the user.
GDI-509/CREATED/R                                                                                                                                                 R
                               The Low Power On/Off Command source shall be referenced to driver signal ground.
GDI-510/CREATED/R              The Low Power On/Off Command receiver shall be isolated from any user electrical reference.                                        R
                               The Low Power On/Off Command receiver shall be equipped with appropriate circuits in order to suppress any
GDI-511/CREATED/R              switching transients, in particular those due to inductive loads such as relays, which may cause the current                       R
                               drive capability, or the over voltage capability of the source to be exceeded.
                               The Low Power On/Off Command source shall be short circuit proof for short circuits to source or receiver
GDI-512/CREATED/R                                                                                                                                                 R
                               signal ground and structure.




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                               Standard Low Power On/Off Command:
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "SLP", Table 3.5-24 and Table 3.5-25 below.




GDI-1252/CREATED/T,R                                                                                                                                T           R




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                               Relay Status Acquisitions (RSA) The status is provided by users in the form of a relay dry contact or
                               optocoupler.
                               The open/closed status of a relay/switch contact (or optocoupler) shall be acquired via the Relay Status
                               Acquisition inputs for conversion into one bit being "1" or "0", respectively using a pull-up resistor. The
                               comparing input is referenced to signal ground. A closed contact corresponds to a "0" level and an open
                               contact to a "1" level.




GDI-1229/CREATED/R                                                                                                                                               R




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                               Relay Status Acquisition
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "RSA", Table 3.5-26 and Table 3.5-27.




GDI-516/CREATED/T,R                                                                                                                                     T           R




                               The X-Band Digital TC Channel shall consist of 3 signals. (For these signals the following abbreviations shall
                               be used):
GDI-527/CREATED/R              · Data (DCD)                                                                                                                         R
                               · Clock (DCC)
                               · Data Valid (DCE) [Enable/Channel Active]




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                               The X-Band Digital TC Channel shall be transmitted via Standard Balanced Digital Link Interfaces (TBC) as
GDI-1283/CREATED/R                                                                                                                                              R
                               defined in Section 3.5.5.2.
                               This Requirement has been deleted.
                               For information the relationship between the Data Valid, Clock and Data signals within the X-Band DTC
                               channel is as shown in the typical timing diagram shown in Figure 3.5-18.




GDI-528/CREATED/T,R                                                                                                                                 T           R




                               T1 =< 128 bit
                               T2 between 1 bit and 128 bit
                               T3 = 500ms
                               T4 = 100ms
                               Tc = 500µs +/- 5% (for a 2kbps uplink)
                               Ts = 10µs min
                               Th = 20µs min
                               Note 1: The clock is running as soon as the LOCK STATUS is ”high” and it will run until LOCK STATUS falls
                               to ”low”.
                               Note 2: The bit clock stability shall be better than +/- 5% as soon as DATA VALID is ”high” and until DATA
                               VALID falls to ”low”.
                               Note 3: The ESA standard requires an acquisition sequence of 128bits. This value can be increased by
                               adding an idle sequence (min. 8 bits) after the acquisition sequence.

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GDI-528/CREATED/T,R                                                                                                                                        T           R
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                               T1 =< 128 bit
                               T2 between 1 bit and 128 bit
                               T3 = 500ms
                               T4 = 100ms
                               Tc = 500µs +/- 5% (for a 2kbps uplink)
                               Ts = 10µs min
                               Th = 20µs min
                               Note 1: The clock is running as soon as the LOCK STATUS is ”high” and it will run until LOCK STATUS falls
                               to ”low”.
                               Note 2: The bit clock stability shall be better than +/- 5% as soon as DATA VALID is ”high” and until DATA
                               VALID falls to ”low”.
                               Note 3: The ESA standard requires an acquisition sequence of 128bits. This value can be increased by
                               adding an idle sequence (min. 8 bits) after the acquisition sequence.


                               For information the relationship between the Data Valid, Clock and Data signals within the Xband DTC
GDI-530/CREATED/T                                                                                                                                          T
                               channel is as shown in the typical timing diagram shown in Figure 3.5-18.
                               The X-Band Receiver Lock Status signal shall be transmitted via Standard Digital Link interface (TBC) as
GDI-535/CREATED/T,R                                                                                                                                        T           R
                               defined in Section 3.5.5.2.
                               The X-Band Digital TM Channel shall consist of 2 signals. (For these signals the following abbreviations
                               shall be used):
GDI-538/CREATED/R                                                                                                                                                      R
                               · Data (DMD)
                               · Clock (DMC)
                               The X-Band Digital TM channel shall be transmitted via Standard Balanced Digital Link interfaces (TBC) as
GDI-539/CREATED/R                                                                                                                                                      R
                               defined in Section 3.5.5.2.
                               Items which require pyrotechnic release shall incorporate Electro-Explosive Devices (EED's) as an integral
GDI-1255/CREATED/R                                                                                                                                                     R
                               part of the item.
GDI-1256/CREATED/T,R           All EED's shall be initiated via the spacecraft dedicated pyrotechnic circuitry.                                            T           R
GDI-1257/CREATED/R             Only qualified initiators shall be accepted for use, subject to Prime/ESA approval.                                                     R
GDI-1258/CREATED/T,R           Only one firing command to a single filament shall be provided at a time.                                                   T           R
GDI-1259/CREATED/R             Redundancy shall be provided for each function by duplication up to at least the initiators.                                            R
                               The Pyro electronic interface, as well as the interconnecting harness including Antistatic Resistor, shall be as
GDI-1260/CREATED/R                                                                                                                                                     R
                               shown in Figure 3.5-19. (The safe plug configuration is indicated by dashed lines.)
                               Pyro Firing Characteristics. The contractor shall design his side of the interface to be compliant to the
GDI-1264/CREATED/T,R           characteristics as defined in                                                                                               T           R
                               Interface Datasheet "PYR", Table 3.5-33.
                               Each bi-level digital channel shall be used to acquire one of a number of discrete status signals from the OBC
GDI-523/CREATED/R                                                                                                                                                      R
                               users.
                               The OBC shall acquire via the Bi-Level Digital Acquisition inputs the "High"/"Low" status of a user for
GDI-1232/CREATED/R                                                                                                                                                     R
                               conversion into one bit being "1" or "0", respectively.
                               Each channel shall be allocated to a specific bit position within an 8-bit telemetry word in such a way, that the
GDI-1233/CREATED/R                                                                                                                                                     R
                               channel which has the lowest address number is put at the MSB location (bit 0).




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                               Bi-level Digital Interface The contractor shall design his side of the interface to be compliant to the
                               characteristics as defined in Interface Datasheet "BLD", Table 3.5-29 and Table 3.5-30.




GDI-524/CREATED/T,R                                                                                                                              T           R




                               The driver function shall implement an arming and firing mechanism to avoid an FCV or LV command
GDI-1775/CREATED/T,R                                                                                                                             T           R
                               activation in case of single failure or inadvertent command.
GDI-1776/CREATED/T,R           The arming and firing commands shall be implemented by segregated function.                                       T           R
GDI-1777/CREATED/A             There shall be no failure propogation from the driver function to any PT, LV or FCV.                                  A
GDI-1778/CREATED/T             The Driver shall implement free wheeling diodes in the electrical command I/F's with the FCV and LV.              T



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                               Each Latch Valve has 2 coils for commanding (1 for open command / 1 for close command) and a
GDI-1287/CREATED/R             corresponding status switch.                                                                                                      R
                               The Latch Valve Command outputs shall provide redundant freewheeling diodes at the output lines.
                               Each Latch Valve Command interface, main and redundant, shall be able to be cross-strapped with the same
GDI-1288/CREATED/A             Latch Valve coil interface. Therefore protection features shall be implemented to avoid failure propagation               A
                               between the main and the redundant command type interface respectively..
                               The contractor shall design his part of the Latch Valve Open / Close Command interface to be compliant to
                               the characteristics as defined in Table 3.5-31. (Interface Data Sheet "LVC"; Driver: OBC, Receiver: Latch-
                               Valve):




GDI-1289/CREATED/T,R                                                                                                                                 T           R




                               Latch Valve Status
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
11/8/2012                                                                            3.5-27.
                               Interface Datasheet "RSA", Table 3.5-26 and Table b5155b8c-4151-4881-83aa-65d2b0a4eb36.xls                                                             Page 62 of 335
GDI-1289/CREATED/T,R                                                                                                                                  T           R


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                               Latch Valve Status
                               The contractor shall design his side of the interface to be compliant to the characteristics as defined in
                               Interface Datasheet "RSA", Table 3.5-26 and Table 3.5-27.

GDI-1436/CREATED/R             The Flow Control Valve Command outputs shall provide redundant freewheeling diodes at the output lines.                            R
                               The contractor shall design his part of the Flow Control Valve Command interface to be compliant to the
                               characteristics as defined in Table 3.5-32. (Interface Data Sheet "FCV"; Driver: OBC, Receiver: Flow Control
                               Valve):




GDI-1437/CREATED/T,R                                                                                                                                  T           R




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GDI-1437/CREATED/T,R                                                                                                                                T           R




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                               Internal test acquisitions shall be provided to allow the OBC processor module to check the health of the
GDI-1590/CREATED/R                                                                                                                                              R
                               reference voltages and the good functioning of the analogue/digital-converter.
                               Pressure Transducer Acquisition Interface (PTA):
                               The contractor shall design his part of the interface to be compliant to the characteristics as defined in
                               Table 3.5-33 (Interface Data Sheet "PTA"):




GDI-1591/CREATED/T                                                                                                                                  T




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GDI-1591/CREATED/T                                                                                                                               T




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                               The contractor shall design his part of the Pressure Transducer Supply Interface to be compliant to the
                               characteristics as defined in Table 3.5-34 (Interface Data Sheet "PTS"; Driver: OBC, Receiver: Pressure
                               Transducer):




GDI-1790/CREATED/T,R                                                                                                                             T           R




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                               Main Engine Flow Control Valve Interface (MEC):
                               The contractor shall design his part of the interface to be compliant to the characteristics as defined in Table
                               3.5-35 (Interface Data Sheet "MEC"):




                               Interfaces will be formally controlled within the Electrical Interface Control Documents. The Electrical Interface
GDI-558/CREATED/R              Control Document will present all the electrical properties and additional useful details for each unit through                            R
                               the electrical datasheets of APPENDIX C: EICD.
                               Bonding is the method by which adjacent conductive elements are electrically connected in order to minimise
                               any potential differences and flow of electrical currents. If dissimilar materials are bonded, the relative areas of
GDI-562/CREATED/R              the anode and the cathodes are important and finishing should be applied on both materials.The bond shall be                               R
                               resistant against corrosion and shall have an adequate cross section to carry fault currents of 1.5 times the
                               unit/circular protection device for an indefinite time.



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                               Metallic parts of each electrical equipment chassis (case) shall be mutually bonded together by direct metal
GDI-563/CREATED/T              contact (preferred method) or bonding strap. Bonding interfaces shall be designed to achieve a contact                    T
                               resistance of 2.5 m or less per bonding junction (including strap, if used).
                               Joint faces shall be flat and clean before assembly; the only permitted surface finishes for joint faces are
                               (preference order) :
GDI-564/CREATED/I,R                                                                                                                                              I   R
                               * alodine 1200 for aluminium alloys,
                               * clean metal except for Aluminium alloys.
GDI-565/CREATED/T              All non-electrical equipment shall be bonded to the structure by direct metallic contact with less than 1kOhm.            T
                               Each electrical equipment chassis (case) shall be bonded to the GRR by means of a bonding strap or direct
GDI-566/CREATED/T              metal contact. The bonding interfaces shall not exceed a chassis to GRR bonding resistance of 5mOhm The                   T
                               bond strap shall have a maximum length to width ratio of 5:1.
                               Metallic receptacles of connectors shall be electrically bonded to the equipment case with a DC resistance of
GDI-567/CREATED/T                                                                                                                                        T
                               2.5mOhm or less.
                               Electrical bonding throughout CFRP structure shall be achieved by means of a continuous metallic Ground
GDI-569/CREATED/R                                                                                                                                                    R
                               Reference Rail (GRR).
GDI-570/CREATED/T,R            The resistance between any adjacent parts of the GRR shall never exceed 2.5 mOhm (DC).                                    T           R
GDI-571/CREATED/T,R            The resistance between any point of the GRR shall be lower than 10 mOhm.                                                  T           R
                               Where shielded wires are used, the shield shall be of a braided construction, selected to provide an optical
GDI-573/CREATED/R                                                                                                                                                    R
                               coverage of at least 85%.
                               The maximum unshielded length of any shielded wire shall not exceed 2.5cm. Cable shields shall be
GDI-574/CREATED/R              grounded at both ends. Where shielded cable pass through intermediate connectors, the shield shall pass                               R
                               through the interface on dedicated pins.
                               Daisy chaining of shield terminations shall be avoided. If this is not feasible due to connector limitations, a
GDI-575/CREATED/R                                                                                                                                                    R
                               maximum of three shields of similar electrical interfaces are allowed for daisy chaining.
                               Shields shall not be used as an intentional current carrying conductor and not as return lines for power and
GDI-576/CREATED/R                                                                                                                                                    R
                               signal with the exception of the RF coaxial lines.
                               Conducive struture components shall be electrically bonded to each other by direct metal to metal contact, or
GDI-578/CREATED/I,R                                                                                                                                              I   R
                               via the use of a bond strap
                               The DC resistance between two mating metal struture parts shall be <2.5 mOhm. The minimum size of the
GDI-1990/CREATED/T,R                                                                                                                                     T           R
                               contact area shall be 1cm^2
                               Across moveable parts, a bond strap shall be applied to ensure an electrical contact is made between those
GDI-1991/CREATED/T,R                                                                                                                                     T           R
                               parts with a DC resistance of <25 mOhm.
                               For CFRP structure without shielding function, the bonding resistance between any CFRP parts and the local
GDI-1992/CREATED/T,R                                                                                                                                     T           R
                               GRR shall be less than 100 Ohm measured at DC.
GDI-2093/CREATED/T,R           Aluminium honeycomb shall be bonded to the structure with a DC resistance of < 10 mOhm                                    T           R
                               For CFRP structure used for electromagnetic shielding, the bonding resistance shall be less than 100mOhm
GDI-2092/CREATED/T,R                                                                                                                                     T           R
                               between any adjacent parts and the local GRR.
GDI-1989/CREATED/T,R           Metal fittings shall be bonded to the structure with a DC resistance of < 10 Ohm.                                         T           R
GDI-579/CREATED/T,R            Metal fittings shall be bonded to CFRP with a DC resistance of < 10 Ohm.                                                  T           R
                               The DC resistance from any metal structure part and the structure ground reference located close to the
GDI-2105/CREATED/T,R                                                                                                                                     T           R
                               separation plane shall be <25mOhms
                               The DC resistance between any other conductive component that does not perform an electrical function, i.e
GDI-2094/CREATED/T,R                                                                                                                                     T           R
                               CFRP, CFK, conductive coatings etc and the spacecraft structure shall be < 1 kOhm
                               The GRR shall be attached at less than or equal to every 150mm to the panels by an M4 bolt. Further
GDI-1993/CREATED/T,R           mechanical fixings may be required at the ends of the rails. The DC resistance between the rail and the local             T           R
                               CFRP shall be < 100 mOhm.
GDI-1994/CREATED/T,R           The resistance between any adjacent parts of the GRR shall never exceed 2.5 mOhm.                                         T           R



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GDI-1995/CREATED/T,R           The resistance between any point of the GRR shall be < 10 mOhm.                                                            T           R
                               Mechanical Parts without electrical nor shielding function shall show a bonding resistance of less than 1 kOhm
GDI-581/CREATED/T,R                                                                                                                                       T           R
                               between any adjacent parts and the local GRR.
                               Mechanical Parts used for electromagnetic shielding shall show a bonding resistance of less than 2.5 mOhm
GDI-582/CREATED/T,R                                                                                                                                       T           R
                               between any adjacent parts and the local GRR (or connector bracket)
                               Each unit shall provide a grounding point, which is easily accessible even when all harness connectors have
GDI-585/CREATED/I                                                                                                                                                 I
                               been installed.
GDI-586/CREATED/R              CFRP and SiC shall not be used as an electrical bonding path. Grounding rails shall be used as bonding path                            R
                               The structure of electrical and electronic unit shall form a continuous conductive metallic shield for the
GDI-588/CREATED/T              electronics with a resistance between the different covers and the bonding stud at the box side not exceeding              T           R
                               2.5mOhm (DC).
                               Openings for drainage, ventilation, etc... shall never exceed 5mm diameter per hole and distances between
                               screws for lids, etc... shall never exceed 30mm for flat mounted lids. Conductive surfaces are required on
GDI-589/CREATED/I                                                                                                                                                 I
                               each bonding surface (each screw). Lids with an overlap of more than one centimetre require only a maximum
                               10-centimetre distance between the bond screws.
GDI-590/CREATED/I              All units shall have a M4 bonding stud                                                                                             I
                               The design of this bonding stud shall allow the connection of a bonding strap with length to width ratio of less
GDI-591/CREATED/I                                                                                                                                                 I
                               than 5 to 1 with a contact area of more than 1cm^2.
GDI-593/CREATED/R              Space exposed Insulating material having a bulk resistivity higher than 1E10    m/micron shall not be used.                            R
                               MLI shall carry at least 1 conductive layer and each conductive layer shall be bonded to structure to avoid
GDI-595/CREATED/I                                                                                                                                                 I
                               electrical charge differential.
                               MLI: The grounding points shall be in a minimum of 2 locations (opposite corners), such that no piece of
GDI-596/CREATED/I,R            blanket is >1m away from a grounding point. No blanket shall exceed 2 sq m in size, each blanket shall be                          I   R
                               individually grounded to the structure.
GDI-597/CREATED/T              MLI: The resistance between each bonding point and the structure shall be lower than 100mOhm.                              T
                               MLI: The resistance between each bonding point and each point of a metallic conductive layer shall be lower
GDI-598/CREATED/T                                                                                                                                         T
                               than 100 Ohm.
GDI-599/CREATED/R              PAINTS: Refer to Section 3.5.7.2.3 above.                                                                                              R
                               HEATERS & THERMISTORS: Heaters, thermistors and other discrete thermal components shall be isolated
                               from structure with:
GDI-600/CREATED/T,R                                                                                                                                       T           R
                                 Resistance >= 10M .
                               Heater mats shall be designed to produce a minimum magnetic field.
                               Isolation: Within all units the primary power buses shall be isolated. There shall be no direct connection
GDI-605/CREATED/R                                                                                                                                                     R
                               between the primary power bus zero volt and the unit's chassis.
                               Isolation: All units (except PCDU) shall maintain a galvanic isolation of at least 1MOhm shunted by not more
                               than 50 nF between:
                               * Primary power positive and chassis,
                               * Primary power return and chassis
                               * Primary power and secondary power (line and return).
GDI-606/CREATED/T,R            * Regulated power positive and Unregulated power positive                                                                  T           R
                               * Regulated power negative and Unregulated power negative
                               The insulation requirements shall be measured at 5 Vdc and 5V 10 kHz for the capacitance.
                               It is recommended to use static shields between primary and secondary windings of transformers to reduce
                               the capacitive coupling between primary and secondary side. This static shield should be connected to the
                               primary power return line by means of a low inductance strap.
GDI-609/CREATED/I,R            Grounding: All secondary supplies, inside a unit, shall be connected to unit structure.                                            I   R



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                               Equipment with its own dedicated DC - DC converter shall ground the secondary power return at a
GDI-1988/CREATED/T                                                                                                                                        T
                               single location.
                               Isolation: prior to connection of the unit internal starpoint, the isolation between the secondary power return
GDI-610/CREATED/T,R                                                                                                                                       T           R
                               and unit chassis shall be at least 1M in parallel with a capacitance of less than or equal to 50nF.
                               After grounding, the impedance between the unit secondary zero volt taken at the level of the transformer and
GDI-2106/CREATED/T,R                                                                                                                                      T           R
                               the unit structure (bonding stud) shall be less than 5m . To be tested at board level.
                               Secondaries distributed between units (1 supplier; 1 receiver): The distribution shall be at ONE point only. In
                               the baseline, the grounding point is located at the supplier. However, Both units (supplier and receiver) shall
GDI-611/CREATED/R              provide the capability of this grounding point. Implementation of this point will be defined at Project level.                         R
                               Specific care shall be taken to avoid grounding loops between these units (isolation of other interface signals:
                               differential type have to be taken into account)
                               Secondaries distributed between units (1 supplier; several receivers): The distribution shall be a starpoint
GDI-612/CREATED/R              system for power line and return. Specific care shall be taken to avoid grounding loops between these units                            R
                               (isolation of other interface signals: differential type have to be taken into account)
                               Grounding diagram including zero volts interconnection and detailed implementation shall be described in the
                               EICD
GDI-614/CREATED/I                                                                                                                                                 I
                               * For each unit,
                               * For each assembly.




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                               The symbols below shall be used in the production of grounding diagram in order to obtain unified drawings




GDI-615/CREATED/R                                                                                                                                                       R




                               Signal circuits interfacing between Satellite equipment shall follow the distributed star point grounding concept,
GDI-617/CREATED/R                                                                                                                                                       R
                               see Figure 3.5-21.
                               Where single-ended signal transmitters are used, independent signal returns are required. Ground reference
GDI-618/CREATED/R              lines shall not be used as signal returns. The signal receivers shall insulate the signal lines from power ground                        R
                               (differential amplifier, opto-coupler, solid state relay, transformer).
                               The use of common signal return paths is only permitted for groups of signals belonging to the same family
GDI-619/CREATED/R                                                                                                                                                       R
                               (analogue, digital, etc.) and originating from the same unit.




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                               EGSE signal and power circuits interfacing with flight hardware shall simulate the original flight interfaces w.r.t.
                               Impedance, power and signal characteristics, timing, grounding and isolation (See Figure 3.5-21) and test
                               harness design.




GDI-621/CREATED/R                                                                                                                                                         R




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                               Each equipment shall be designed and fabricated to preclude or minimise both permanent and stray magnetic
GDI-1997/CREATED/T,R           fields (due to DC current loops). The use of magnetic materials is strictly forbidden except where required for            T           R
                               correct operation of the equipment. In these cases full details shall be provided to prime before they are used.
                                                                                                                                                                          Test of Optical Bench
                                                                                                                                                                          Complete with PD
GDI-1998/CREATED/T             All equipments shall provide magnetic dipole moment data (test results).                                           O       T               systems                     TBD
                                                                                                                                                                          or test of PD mounts
                                                                                                                                                                          and cables alone
                               In all project specific documentation including commented code, the following convention shall be applied:
                               * Bit 0 in a byte shall be the most significant bit and bit 0 shall be transmitted first.
                               * Byte 0 in data fields shall be the most significant byte, and byte 0 shall be transmitted before byte 1.
                               Figure 3.6-1 below shall apply




GDI-632/CREATED/T,R                                                                                                                                       T           R




                               During file transfer, within any data type structure, bytes shall be transmitted in ascending order, i.e. byte 0
GDI-634/CREATED/T,R                                                                                                                                       T           R
                               before byte 1 etc.
                               An operational mode/state represents an operationally well defined and, within certain limitations, a stable
                               configuration as concerns mechanical, thermal, electrical and functional conditions. Modes/States are defined
                               on satellite, instrument, subsystem and unit level as appropriate and form operational entities, which are
                               defined by a list of conditions. A repetitive but fixed sequence of functions may define a mode/state, provided
                               that other conditions remain stable.
GDI-638/CREATED/R              Convention: The terminology “mode” is to be used when mode management is provided by SW, while the                                     R
                               terminology “state” is to be used when the functionality is provided by HW.
                               Mode/State transitions: Transitions from one mode/state to another are initiated by defined events and depend
                               only on source and destination mode/state and on actual conditions. The transition time from one mode/state
                               to another is defined by the time triggering the event and the time where all conditions for the new mode/state
                               are fulfilled
GDI-639/CREATED/R              The unit supplier shall identify appropriate modes/states and transitions between them for the unit.                                   R
                               At all times, equipment and units shall be in a clearly identified operational mode/state of both hardware and
GDI-640/CREATED/T,R            software. The unit shall provide sufficient telemetry to allow unambiguous identification of its mode/state and            T           R
                               transitions.
                               In addition, modes and the mode transitions managed by on-board software shall be observable and the
GDI-641/CREATED/T,R                                                                                                                                       T           R
                               necessary data shall be available in the telemetry
GDI-642/CREATED/R              The unit supplier shall identify all internal and external events triggering a mode/state transition.                                  R



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GDI-643/CREATED/R              The unit supplier shall identify all transition times between modes/states.                                                                R
GDI-644/CREATED/R              Mode/State transitions with duration longer than 10 seconds shall be indicated in the telemetry.                                           R
GDI-645/CREATED/T,R            It shall be possible to command the unit into each of its operation states by means of a single telecommand.                   T           R

                               Commandability is characterised by the set of commands to a system, satellite, instrument, subsystem or unit,
                               which allows modification of its configuration (i.e. status, parameters, settings and/or mode). The correct level
GDI-648/CREATED/T                                                                                                                                             T
                               of commandability allows the Operational Ground Segment to set the satellite, instrument, subsystem or unit in
                               the hardware and software configuration appropriate to fulfil the mission.
                               In operating states of the unit, it shall be possible to command all on-board devices, switchable elements (e.g.
GDI-649/CREATED/T                                                                                                                                             T
                               relays), equipment and sub-units individually and externally.
                               In addition, in non-operating states of the unit, especially if the unit is OFF, it shall be possible to command all
GDI-650/CREATED/T                                                                                                                                             T
                               on-board devices and switchable elements (e.g. relays), individually and directly from external.
                               Individual switching of switchable elements (e.g. relays) shall be possible even in the case that automatic
GDI-651/CREATED/T                                                                                                                                             T
                               switching is implemented for nominal operation
                               The on-board reception, processing and execution of a telecommand to on-board devices, equipment and
GDI-652/CREATED/T,R                                                                                                                                           T           R
                               units shall not affect the performance of other ongoing processes within the item.
                               The function of a command shall not change throughout the mission and shall not depend of any previous
                               command history. Flip/flop or toggle commands as well as multi-stable commands (i.e. commands for which
GDI-653/CREATED/T,R                                                                                                                                           T           R
                               effect depends on previous state of the function) are not allowed. This applies to switchable elements as well
                               as memory/register loads.
                               A single command may be used to initialise a change in configuration via on-board logic only if the individual
                               switching elements are accessible by external commands. For example: one command can switch two units if
GDI-654/CREATED/T,R                                                                                                                                           T           R
                               the individual unit switches are also commandable from external. Exceptions to this rule shall be agreed with
                               the customer on a case-by-case basis.
GDI-655/CREATED/R              Commands with variable bit-fields meaning shall not be used.                                                                               R
                               Nominal and the redundant functions or equipments of a unit shall be commanded by the same number, type
GDI-656/CREATED/T                                                                                                                                             T
                               and format of telecommand.
                               The unit design shall avoid any conflict between a command register update by the S/W and the command
GDI-657/CREATED/T              acquisition by the unit. The register update shall be possible at any time according to the communication                      T
                               protocol.
                               Observability is characterised by the set of telemetry (housekeeping information) that is provided by a system,
                               satellite, instrument, subsystem or unit, which allows information about its overall status. The correct level of
GDI-660/CREATED/R                                                                                                                                                         R
                               observability allows the Operational Ground Segment to get the appropriate data for the satellite, instrument,
                               subsystem or unit for taking any action if required.
                               The unit shall provide in its housekeeping telemetry all data required for the monitoring and execution of all
GDI-661/CREATED/T,R                                                                                                                                           T           R
                               nominal and foreseen contingency operations throughout the entire mission.
                               The unit shall provide the necessary instrumentation to allow the ground or the next higher operational level to
GDI-662/CREATED/T,R                                                                                                                                           T           R
                               determine at any time the precise and current status of the unit including software parameters (if applicable)

                               Telemetry measurement sensors shall be designed such that they provide the full performance range with a
GDI-663/CREATED/T              suitable resolution compatible with the parameter to be measured. This resolution shall be determined taking                   T
                               into account the needs for real time control and for performances and lifetime evaluation.
                               It shall be possible to determine the status of the unit (w.r.t. HW and SW), without the need of any older data
GDI-664/CREATED/T                                                                                                                                             T
                               knowledge (e.g. telecommand history, history of autonomous processes).




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                                                                                                                                                                       I   COMMENT
                                                                                                                                                   c   c       Y   E                   Method
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                               Essential (high-priority) telemetry data enabling a reliable determination of the current status of onboard vital
GDI-665/CREATED/T,R                                                                                                                                        T           R
                               equipment under all circumstances shall be provided by the unit irrespective of its mode/status
                               Telemetry shall always be provided to identify unambiguously the conditions required for execution of all
GDI-666/CREATED/T,R            possible configuration dependent telecommands. Note: A configuration dependent telecommand is defined                       T           R
                               as a telecommand that should only be executed if a particular subsystem or instrument condition is satisfied.
                               Status information in telemetry shall be provided from direct measurements from operating units rather than
GDI-667/CREATED/T,R                                                                                                                                        T           R
                               from secondary effects. This is in particular essential for the status of all on-board relays.
GDI-668/CREATED/R              Any TM processing required at a higher operational level shall be defined.                                                              R
                               Telemetry shall always be available to determine the health status of all units that manage the generation and
GDI-669/CREATED/R                                                                                                                                                      R
                               routing of (other) telemetry data.
                               When a key parameter is derived on-board from several inputs, each input shall be available in the telemetry
GDI-670/CREATED/T,R                                                                                                                                        T           R
                               in addition to the parameter itself
                               The TM acquisition process by the data bus shall neither modify the contents of the telemetry H/W register (no
GDI-672/CREATED/T                                                                                                                                          T
                               status re-initialisation) nor the unit configuration; acquisitions with a commanding effect are forbidden.
                               The unit design shall avoid any conflict between the acquisition of a telemetry register by the S/W and the
GDI-673/CREATED/T              register update by the unit. The register acquisition shall be possible at any time according to the                        T
                               communication protocol.
GDI-674/CREATED/R              TM acquisitions with conditional meaning shall not be used.                                                                             R
GDI-675/CREATED/R              The value of a telemetry parameter shall be transmitted in contiguous bits within one packet.                                           R
                               Analog TM acquisitions shall have a measurement range and an accuracy (w.r.t. time, sampling frequency,
GDI-676/CREATED/T,R                                                                                                                                        T           R
                               resolution, etc.) appropriate to allow handling of nominal operation and detection of anomalies.
GDI-677/CREATED/R              Acquisition of safety critical analog parameters of a unit shall be possible even when the unit is OFF.                                 R
                               The values of currents or voltages readings shall be representative and valid irrespective of the status of the
GDI-678/CREATED/R                                                                                                                                                      R
                               unit.
                               The calibration curve of an analog parameter shall be unique: it shall not depend on the status of the unit nor
GDI-679/CREATED/R                                                                                                                                                      R
                               on the value of another parameter.
                               At switch on, the configuration of the unit at elementary function level shall be clearly defined and observable
GDI-681/CREATED/T                                                                                                                                          T
                               and available under a single telemetry identifier.
                               In case a unit includes several elementary functions (i.e. converter, bus coupler etc..) the detailed
GDI-682/CREATED/R                                                                                                                                                      R
                               configuration shall be available in a single telemetry identifier.
                               The configuration of any on-board device and any switching element shall be known in a nonambiguous way,
GDI-683/CREATED/T,R                                                                                                                                        T           R
                               without the need of any older data knowledge.
GDI-684/CREATED/R              Any configuration command register shall be observable by a corresponding telemetry parameter.                                          R
GDI-685/CREATED/R              The acquisition of the unit configuration/state shall be possible irrespective of the unit status.                                      R
GDI-686/CREATED/R              The acquisition of an ON/OFF status for a relay shall be independent of the unit status.                                                R
                               If the unit controls the redundancy configuration or the power of its sub-units, the redundancy setting or power
GDI-687/CREATED/T                                                                                                                                          T
                               status shall be identified in an unambiguous way in the telemetry.
GDI-688/CREATED/R              Nominal and redundant functions shall be observable by the same number, type and format of telemetry.                                   R
                               Commands to the unit shall be acknowledged in an unambiguous manner. The acknowledgement shall either
                               be performed:
GDI-690/CREATED/R              * On bus protocol level (e.g. MIL-STD 1553B)                                                                                            R
                               * On Packet Utilisation Standard (PUS) level if unit SW is involved
                               * Or on a level, where the effect of the command can be identified unambiguously




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                               Acknowledgement of commands shall be direct (i.e. not relying on the operation of other units or on the
GDI-691/CREATED/T,R                                                                                                                                      T           R
                               previous commanded state) and accurately relevant.
                               The association between command acknowledgement acquisition and respective command shall be clearly
GDI-692/CREATED/I                                                                                                                                                I
                               identified by the unit supplier.
GDI-693/CREATED/T,R            Successful execution of a command to the unit shall be notified to the next higher operational level                      T           R
                               Failures in the acceptance and /or the execution of commands to the unit shall be notified to the next higher
GDI-694/CREATED/T,R                                                                                                                                      T           R
                               operational level
                               Sufficient data to monitor the converters shall be available in the telemetry as:
                               * Secondary voltage
GDI-696/CREATED/T              * Primary current                                                                                                         T
                               * Relay status
                               * Temperature
                               Hazardous functions are those that could cause loss of mission, mission degradation or damage to unit,
                               equipment, facilities or personnel, when being executed at the incorrect time. Critical commands are defined
                               as commands which invoke hazardous functions and for which inadvertent execution (erroneous
                               transmission), incorrect execution (aborted transmission or transmission in wrong order), or loss of function
                               may cause loss of nominal mission or, during the ground phase, presents hazards
GDI-700/CREATED/A                                                                                                                                            A
                               for personnel. For instance, critical commands include pyrotechnics firing, propulsion (hydrazine) activation,
                               etc.

                               All critical commands shall be identified at equipment, subsystem or unit level for further analyses at system
                               level.
                               The execution of any command or command sequence shall not lead to permanent equipment or unit
GDI-701/CREATED/A              damage. This applies also for incorrect commands or command sequences. Exceptions to this requirement                         A
                               shall be approved by the Satellite Prime and shall be included in a Critical Command List.
                               Commanding of critical commands shall be implemented by at least 2 separate and independent commands.
GDI-702/CREATED/A,R                                                                                                                                          A       R
                               The level of implementation shall be discussed on a case-by-case basis
                               The status of inhibition of safety critical functions shall be monitored and readable in a non-ambiguous way
GDI-703/CREATED/T                                                                                                                                        T
                               even if the function is not powered.
                               Units shall provide an unambiguous health status of potentially hazardous functions in a dedicated TM
GDI-704/CREATED/T                                                                                                                                        T
                               identifier.
GDI-706/CREATED/T              Any part of installed RAM's shall be readable by memory read commands.                                                    T
GDI-707/CREATED/T              Any part of installed RAM's shall be overwriteable by memory load commands.                                               T
GDI-708/CREATED/T              Any part of installed ROM's shall be readable by memory read commands.                                                    T
                               For failure investigation, it shall be possible to switch the equipment into a mode in which the memory can be
GDI-709/CREATED/T                                                                                                                                        T
                               dumped and sufficient to identify errors as appropriate.
                               Apart from failure situations, the unit shall operate autonomously, including nominal data acquisition and data
GDI-711/CREATED/T                                                                                                                                        T
                               transmission.
                               All parameters used for autonomous operations and processes, including FDIR functions, shall be updateable
GDI-712/CREATED/T                                                                                                                                        T
                               by command and available in telemetry.
                               It shall be possible to inhibit and to override all automatic functions including FDIR functions and the
GDI-714/CREATED/T                                                                                                                                        T
                               necessary data to monitor these functions must be available in the telemetry.
                               All actions generated by automatic on-board logic (hardware or software) shall be inhibitable, reversible, by
GDI-715/CREATED/T                                                                                                                                        T
                               command. Exceptions shall be discussed on a case-by-case basis.
                               The automatic function design shall be such that no single point failure can cause the loss of the primary
GDI-716/CREATED/A,R                                                                                                                                          A       R
                               function and of the automatic function provided as back up.




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                               Telemetry shall be associated to all automatic functions enabling the ground to be informed of all the actions
GDI-717/CREATED/T              of the automatic function and of their enabled/inhibited status. In addition, any input used by the automatic                   T
                               function shall be observable.
                               For all the automatic logic using several criteria in an "OR" configuration inhibition shall be possible individually
GDI-718/CREATED/T                                                                                                                                              T
                               and independently for each criteria.
GDI-719/CREATED/T,R            The capability to change all on board logic (hardware and software) thresholds at any time shall be provided.                   T           R
                               If the unit has operationally not been synchronised to the on-board Master clock after a power reset or switch-
GDI-721/CREATED/R                                                                                                                                                          R
                               on this shall be indicated to the next higher operational level.
                               If the unit has the function, all information on how to synchronize a units internal clock to an external clock
GDI-722/CREATED/R                                                                                                                                                          R
                               shall be supplied.
                               Timing information provided in Housekeeping telemetry of the unit shall allow the correlation from onboard
GDI-723/CREATED/T,R            time to UTC with an accuracy necessary for command & control operations and compliant with any unit                             T           R
                               datation requirements.
                               Any unit shall be able to withstand (i.e. remain in a safe state, without any requirement on performances, and
GDI-726/CREATED/T,R            except in case of unit failure due to another cause), interruptions of the cyclic management by the OBSW for                    T           R
                               an indefinite period, regardless of the configuration it was left.
                               Any unit shall be able to withstand (i.e. remain in a safe state, without any requirement on performances, and
GDI-727/CREATED/T,R            except in case of unit failure due to another cause), interruptions of the data bus operation for an indefinite                 T           R
                               period, regardless of the configuration it was left.
                               It shall be possible to repeat any command several times without disturbing its nominal execution, even in
GDI-728/CREATED/T,R            case of timing constraints. No configuration change, no temporary or permanent degradation of the function                      T           R
                               performance must result from any command repeatability that would respect data bus constraints.
GDI-730/CREATED/R              All units that perform regular self-tests shall report the result in a single TM identifier.                                                R
                               FDIR functions are those functions, which implement the failure detection, isolation and recovery actions. The
                               FDIR functionality is set up at both unit and system levels and is defined within the overall Operations Concept
                               of the Lisa Pathfinder spacecraft. The implementation of the FDIR function is based on specific system needs,
                               e.g. the time to react, which is the maximum time to end a recovery action guaranteeing the hardware
GDI-733/CREATED/A,R                                                                                                                                                A       R
                               integrity.

                               FDIR functions shall be implemented in a hierarchical manner, i.e. failure detection, isolation and recovery
                               shall be implemented to a certain degree on unit level.
                               The unit shall automatically detect any failure, which makes it deviate from its nominal configuration and
GDI-734/CREATED/T,R                                                                                                                                            T           R
                               operating status. This includes HW and SW failures.
                               At unit level failures shall be detectable by adequate and comprehensive monitoring (e.g. for switchable
GDI-735/CREATED/A                                                                                                                                                  A
                               elements) and the capability for failure isolation and recovery action shall be provided.
                               Failure detection algorithms shall report in event telemetry all parameter values considered necessary for the
GDI-736/CREATED/A,R                                                                                                                                                A       R
                               ground analysis of the failure.
                               Failures which require a reaction time less than 10s shall be monitored through a hardware device (Watchdog,
GDI-737/CREATED/T,A                                                                                                                                            T   A
                               current limiter etc..)
                               Failure which requires a reaction time between 10s and 48h shall be monitored by on board software
GDI-738/CREATED/A,R                                                                                                                                                A       R
                               implemented in the unit or by SW in the higher operational level.
GDI-739/CREATED/T,A            Failure isolation shall be performed at switchable items level                                                                  T   A
                               Any FDIR actions on unit level shall be reported to the next higher operations level. This includes in particular
GDI-740/CREATED/T,R                                                                                                                                            T           R
                               redundancy switching.




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                               The need for intervention of higher levels to react on failure situations which cannot be handled at unit level
GDI-741/CREATED/T,A,R          shall be clearly identified and communicated to the next higher operational control level. The reaction time for           T   A       R
                               such a higher-level intervention shall be identified.
                               The unit supplier shall provide a design justification for the operations relevant part. For each
                               telemetry/telecommand and their parameters a functional description shall be given with the reason of the
GDI-744/CREATED/R              choice. It shall be proved that the location of the acquisition and its characteristics (dynamic, bandwidth,                           R
                               resolution, frequency variation in case of failure) can satisfy the operational requirements and is appropriate
                               for all modes (normal and contingency modes, safe modes..)
                               The unit supplier shall provide inputs to the Operational Database or fill in a customer provided Database. This
GDI-746/CREATED/R              data shall be provided through a defined and agreed numerical format (based on Excel or ASCII files). The                              R
                               detailed format is to be defined by the Customer.
                               Data to be provided (the list is not exhaustive):
                               * For TM: Mnemonic, description, addressing, coding, calibration, bandwidth, validity conditions, monitoring
GDI-747/CREATED/R                                                                                                                                                     R
                               limits.
                               * For TC: Mnemonic, description, addressing, coding, calibration, execution conditions, execution checking.
                               The unit supplier shall provide an Operations Manual covering all operational aspects (in-flight and onground)
                               for the unit. As a minimum, the following information shall be provided:
                               * Functional Description of the unit (HW and SW)
                               * Description of modes, states and transitions
GDI-749/CREATED/R              * Commandability (TC list) and Observability (TM list)                                                                                 R
                               * Nominal and Contingency Operations
                               * Operational Constraints
                               * FDIR implementation
                               * On-Ground Handling




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                               The following standardization (Table 3.6-1) shall be used for the coding of 2-state status:




GDI-750/CREATED/R                                                                                                                                              R




                                                                                                                                                                   Photo Diodes           Design Description
                                                                                                                                                                   add statement to            Report
GDI-771/CREATED/R              The unit shall be designed to withstand a relative humidity of 60% maximum during testing and transport.    O                   R
                                                                                                                                                                   design description     Declared Materials
                                                                                                                                                                   report                        List
                                                                                                                                                                   Cleanliness
                                                                                                                                                                                        Cleanliness Plan for
                                                                                                                                                                   requirement on
GDI-773/CREATED/R              The cleanliness design requirements on the unit H/W shall be as defined in the PA requirements              O                   R                           Glasgow work
                                                                                                                                                                   Astrium OBI RS check
                                                                                                                                                                                              process
                                                                                                                                                                   with Dave Smith

GDI-775/CREATED/R              The S/C units flight H/W shall be designed to withstand a storage duration as specified in Section 3.1.1.                       R                        Declared Materials list




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                               Decreasing atmospheric pressure from launch pad level conditions down to vacuum will occur at a rate
                               dependent on the flight profiles and venting schedule. For Rockot, the typical slope of the static pressure
                               within the fairing is shown in Figure 4.1-1.




                                                                                                                                                                                             Environmental Tests
GDI-780/CREATED/T                                                                                                                            O       T               Check vacuum facility
                                                                                                                                                                                                   Reports




                               Units mounted on the S/C shall be designed to withstand without degradation, a de-pressurization rate of
                               70mbar/s maximum and a Delta-P of 150mbar over ambient.
                                                                                                                                                                     OBI RS contain the
                               Cleanliness requirements are as defined in the Section 3.7 of S2.ASU.RS.1005 (PA Requirements For Sub-                                most appropriate
GDI-782/CREATED/T,R                                                                                                                          O       T           R
                               contractors) for LPF spacecraft units and S2-ASD-RS-3006 for the LTP.                                                                 cleanliness
                                                                                                                                                                     requirements
GDI-788/CREATED/T,A            Deleted                                                                                                               T   A
                               The equipment/assembly and associated transport containers shall be sized to survive transportation and
                               handling loads as defined in Table 4.2-1.
                               Vertical and horizontal loads shall be considered as acting simultaneously (un-attenuated input to MGSE).

                                                                                                                                                                     check who has           Environmental Test
GDI-790/CREATED/T,A                                                                                                                          O       T   A           responsibility for            Report
                                                                                                                                                                     building the box         Analysis Report




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                                                                                                                                                                 S
                               During ground transportation the equipments shall withstand without damage the limit shock loads defined in
                               Table 4.2-2.


                                                                                                                                                                                       Environmental Test
GDI-793/CREATED/T,A                                                                                                                                  O       T   A                           Report
                                                                                                                                                                                        Analysis Report




                                                                                                                                                                                       Environmental Test
                               The design of transport containers shall be such to resist to a shock generated by a 100mm fall onto concrete
GDI-795/CREATED/T,A                                                                                                                                  O       T   A                           Report
                               floor when one corner is already lying on the floor.
                                                                                                                                                                                        Analysis Report
                               For all equipments/assemblies:-
                                tests in the in plane axis refers to quasi-static, vibration or shock testing in a direction parallel to the
                               equipment mounting plane,
                                tests in the out of plane axis refers to quasi-static, vibration or shock testing in a direction orthogonal to the
                               equipment mounting plane.

                               The quasi-static and low frequency flight limit accelerations that all units on the SCM Structure will encounter
                               during launch and early orbit phase are compiled in Table 4.2-4.
                               The loads are applied:
                                At the unit c-o-g,
                                Along the worst spatial direction w.r.t resulting reactions/stresses (Section 3.2.1.5).
                               Structural dimensioning of units shall consider critical combination of simultaneously acting loads. The safety
                               factors to be used for design dimensioning purpose are defined in Section 3.2.1.5.
                                                                                                                                                                                       Environmental Test
GDI-799/CREATED/T,A                                                                                                                                  O       T   A                           Report
                                                                                                                                                                                        Analysis Report




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                               All units mounted on the SCM Structure shall be designed to withstand without degradation the sinusoidal
                               environment as defined in Table 4.2-5.



                                                                                                                                                                  Test or analysis
                                                                                                                                                                  missing ?
                                                                                                                                                                                             Environmental Test
                                                                                                                                                                  Qual testing on sub
GDI-808/CREATED/R                                                                                                                         O                   R                                    Report
                                                                                                                                                                  units
                                                                                                                                                                                              Analysis Report
                                                                                                                                                                  acceptance level
                                                                                                                                                                  testing on built up init




                               Units mounted on the SCM Structure shall be designed to withstand without degradation the random
                               environment as defined in Table 4.2-6.




                                                                                                                                                                  Test or analysis
                                                                                                                                                                  missing ?
                                                                                                                                                                                             Environmental Test
                                                                                                                                                                  Qual testing on sub
GDI-812/CREATED/R                                                                                                                         O                   R                                    Report
                                                                                                                                                                  units
                                                                                                                                                                                              Analysis Report
                                                                                                                                                                  acceptance level
                                                                                                                                                                  testing on built up init




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                               Units mounted on the SCM Structure shall be designed to withstand without degradation the qualification
                               shock response spectrum (SRS) defined in Table 4.2-7. The SRS is applicable to each axes X, Y and Z
                               (independently).




GDI-818/CREATED/A,R                                                                                                                               O           A       R                              Analysis Report




                               During orbit and attitude correction manoeuvres, units shall be able to withstand the following dynamic
                               environments:
                               Linear Acceleration:-
                                 In S/C +Z axis 1.20 m/s²
                                 All other axes 0.03 m/s²                                                                                                                                           Environmental Test
GDI-823/CREATED/T,A,R          Angular Velocity:-                                                                                                 O       T   A       R   Unit Operational limits         Report
                                 About all S/C axes 10.0°/s                                                                                                                                          Analysis Report
                               Angular Acceleration:-
                                 About S/C X & Y axes 10.0°/s²
                                 About S/C Z axis 1.5°/s²
                               These accelerations can act simultaneously, and are applied at unit CoG.
                               During transportation and storage, the spacecraft units shall be kept within their non-operational acceptance
                               temperature limits as specified in Table 4.3-1.




                                                                                                                                                                                                    Declared Materials
                                                                                                                                                                                                           List
                                                                                                                                                                          TBD to be checked by
GDI-838/CREATED/R              During the assembly, integration and test (AIT) and ground operations on launch pad, the spacecraft units will     O                   R                             Video of bond test
                                                                                                                                                                          D Robertson
                               be kept within their non-operational acceptance temperature limits.                                                                                                   under very cold
                               Notes: the temperature ranges presented are the worse cases that the equipment units could experience                                                                    conditions
                               during the launch campaign
                               1) ambient temperature at Baikonour
                               2) ambient temperature at cosmodrome
                               3) temperature range during active temperature control
                               During transportation and storage, the spacecraft units shall be kept within their non-operational acceptance
                               temperature limits. For the majority of units, these are specified in Table 4.3-2. Where unit temperature limits
                               deviate from these, and specific constraints on ground handling exist, they shall be treated individually (for
                               example, in the equipment specifications or EID-A's).



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                                                                                                                                                                       I   COMMENT
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                               This requirement applies to external items only.
                               Peak Aerothermal Flux
                               The aerothermal flux, at and after fairing jettisoning, shall not exceed 1135 W/m² in the worst case whatever
                               the ‘LV’ trajectory and atmospheric model errors.
                               The flux is calculated as a free molecular flow acting on a plane surface perpendicular to the velocity. The
GDI-2051/CREATED/A,R                                                                                                                                           A       R   Not Applicable
                               thermal flux formula is




                               This requirement applies to external items only.
                               Mean Aerothermal Flux:
                               The mean aerothermal flux absorbed after fairing jettisoning, calculated on a sliding period of 300 sec shall not
                               exceed the following values in worst case whatever the ‘LV’ trajectory and atmospheric model errors.
                               1) 600 W/m² during the sun eclipse period
                               2) 300 W/m² when exposed to the sun
GDI-2052/CREATED/A,R                                                                                                                                           A       R   Not Applicable
                               The mean absorbed flux is:




                               During the In Orbit phase, the spacecraft units will be kept within their acceptance temperature limits. Unless
                               otherwise specified in an EID or equipment specification, the levels of Table 4.3-2 shall apply.




GDI-841/CREATED/A,R                                                                                                                                O           A       R   Operational Values




                               The radiation environment for the mission is shown in Section 4.4.3.1. Each unit shall be designed to
                               withstand a radiation exposure that is twice the expected radiation environment during the mission (i.e.
                                                                                                                                                                           Possibility of radiation
                               Radiation Damage Margin (RDM) = 2). This applies to all types of radiation damage, including ionising dose
                                                                                                                                                                           testing of fibre
GDI-847/CREATED/A,R            (total and low dose) and displacement damage. Protective shielding by the outer panels of the satellite of          O           A       R                              Design Description
                                                                                                                                                                           injector, PD and glue
                               1.42mm Al equivalent shall be assumed.
                                                                                                                                                                           interface TBD
                               See GDIRs for graphs & Tables
                               Protective shielding by the outer panels of the satellite of 1.42mm Al equivalent over 4pi steradians shall be
GDI-876/CREATED/R                                                                                                                                  O                   R                              Design Description
                               assumed.




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                                                                                                                                                                P
                                                                                                                                                                    I   COMMENT
                                                                                                                                                c   c       Y   E                   Method
                                                                                                                                                        t   S       E
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                               The data provided for 0.66 g/cm2 shielding shall be used for all component level analyses unless it can be
                               demonstrated that the component has additional shielding equivalent to >2.28 mm of Aluminium, in which
                               case, the 1 g/cm2 data may be used (i.e. a total of 3.70mm including the spacecraft shielding). The LISA PF
                               structure provides only 1.42 mm Aluminium equivalent shielding to components mounted inside the
GDI-2087/CREATED/R             spacecraft. Therefore, the generic figure of 1 g/cm2 Aluminium shielding is too high for many components.                            R
                               Additional data is provided for shielding corresponding to 0.66 g/cm2 Aluminium, which assumes 1.42 mm
                               Aluminium equivalent shielding provided by the spacecraft plus 1 mm Aluminium equivalent shielding
                               provided by the unit box. The 1 g/cm2 data may only be used where the unit box or internal shielding gives an
                               additional 2.28 mm Aluminium equivalent shielding.
                               The integral LET spectra generated using CREME96 (excluding proton effects) are shown in Figure 4.4-1 and
                               Table 4.4-2 for 1 g/cm2 Aluminium shielding and Figure 4.4-2 and Table 4.4-3 for 0.66 g/cm2 Aluminium
GDI-1946/CREATED/R             shielding. This data should be used for analysis of Single Event Effects in most components not susceptible to                       R
                               proton induced upset, typically those which have a sensitivity threshold above 15
                               MeV - cm2/mg. Full tabulated values are given in Appendix H: Radiation Tables (13.1).
                               The proton flux data generated using CREME96 are shown in Figure 4.4-3 and Table 4.4-4 for 1 g/cm2
                               Aluminium shielding and Figure 4.4-4 and Table 4.4-5 for 0.66 g/cm2 Aluminium shielding. All devices which
GDI-2088/CREATED/R             may be susceptible to proton induced upset, typically those with LET threshold below 15 MeVcm2/ mg, must                             R
                               also be analysed using this data. Full tabulated values are given in Appendix H:
                               Radiation Tables (13.1).
                               The radiation environment for the mission shall be as shown in Figure 4.4-8 and each unit shall be designed to
                               withstand a radiation exposure as described in Section 4.4.




GDI-1966/CREATED/A,R                                                                                                                                        A       R




GDI-877/CREATED/A,R            Any unit shall take into account the shielding provided by the spacecraft.                                                   A       R
                               The Subcontractor shall implement a Radiation Hardness Assurance programme at his level, documented by
GDI-1969/CREATED/R             a Radiation Hardness Assurance plan, including specific additional de-rating and design rules. It shall be                           R
                               submitted to ASTRIUM for approval.
                               All parts shall be reviewed by the Subcontractor to establish their ability to meet the hardness criteria
GDI-1970/CREATED/R                                                                                                                                                  R
                               according to the radiation environment as defined in Section 4.4.




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                               The Subcontractor shall issue a Radiation Assessment document identifying all sensitive components with
GDI-1971/CREATED/R             regard to relevant radiation effects(total dose, heavy ions, protons), their impact and giving the adequate                             R
                               solution (local shielding, design solution, specific test, RVT, ...) for the relevant equipment.
                               The total dose to be taken into account is defined in Section 4.4.3 of this specification for the lifetime of the
                               mission. Comparison between component type Total Dose Sensitivity (TDS) and Total Dose Level (TDL) to be
                               received by parts within equipment is required for all active EEE part types used by Subcontractor.
GDI-1975/CREATED/A,R           * Parts are considered suitable if their Total Dose Sensitivity is greater than twice the dose received.                        A       R
                               * Other parts shall be submitted to a RVT (Radiation Verification Test). If the part parametric tolerance and
                               the functional hardness are larger than 1.5 times the dose level, the part is accepted.
                               A sector analysis shall be performed in order to determine the TDL at part level.

                               Parts are considered SEE immune when the LETth is greater than 100MeV.cm²/mg. Parts are considered
GDI-1977/CREATED/R                                                                                                                                                     R
                               sensitive to heavy ion and proton induced SEE when the LETth is lower than 15 MeV.cm²/mg.
                               The component shall be designed to tolerate GCR, proton and heavy ion induced SEEs in accordance with the
                               fluxes given in Section 4.4.2.1, Section 4.4.2.3 and Section 4.4.2.4. Parts subject to SEE shall be analysed
GDI-
                               and/or tested for latchup and/or Single Event Upset (SEU). Where EEE parts are not compliant with the                       T   A       R
1978/CREATED/T,A,R
                               radiation requirements specified in this section, the design must compensate for or tolerate the effects (e.g. by
                               latch-up switches and/or autonomous software recovery methods).
                               Devices with a LETth for SEL less than 60 MeV-cm2/mg shall not be used. Devices with a LETth for SEL
                               between 60 and 100 MeV-cm2/mg may be used if the Latch Up Rate (LUR) follows:
                               LUR < 10% ldev.
GDI-1980/CREATED/A,R                                                                                                                                           A       R
                               where ldev: intrinsic device failure rate, as determined using MIL HDBK217, or based on experimental set of
                               reliability data to be submitted to ASTRIUM for approval. Latch up protection circuitry can be used only after
                               project acceptance.
                               Part types shall be acceptable according to the acceptance criteria for SEP, i.e. the error rate is compatible
                               with the mission. If this is not the case, part replacement or implementation of proper countermeasure is
GDI-1982/CREATED/A,R                                                                                                                                           A       R
                               required: error correction, design hardening, any solutions at equipment or system level lowering the
                               maximum error rate are acceptable so that part types will be acceptable.
                               For SEB and SEGR, error rate prediction techniques are not mature and require project approval before use.
                               Radiation assurance is then based on de-rating rules of maximum operating values. If no acceptable SEGR
                               and SEB data exist.
                               For MOS Power Transistors, the Vds voltage must be at least 50% lower than the maximum Vds (with VDS
                               max<200V) and Vgs>0V (N-channel MOSFETs) or Vgs<0V (P-channel MOSFETs).
                               In any other cases, an acceptable evaluation phase data are required. If SEGR and SEB acceptable data
                               exist.
GDI-1984/CREATED/A,R                                                                                                                                           A       R
                               Acceptable evaluation phase data will give drain to source threshold voltages (Vdsth) versus LET and gate to
                               source voltage (Vgs), for static ON and static OFF case temperature. Worst case Vdsth(WC) will be defined.
                               The derating is to maintain Vds over the full design life time as:
                               Vds 0,80*Vdsth(WC)
                               with
                               a) IVgsI < IVgsmaxI used during testing for Vdsth(WC) estimate
                               b) Ttest<Tcase where Ttest is the case temperature used during testing, for Vdsth(WC) estimate.




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                                                                                                                                                          s
                                                                                                                                                                  P
                                                                                                                                                                      I   COMMENT
                                                                                                                                                  c   c       Y   E                   Method
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                                                                                                                                                              S
                               Parametric and functional sensitivity of an EEE part will be estimated for X MeV equivalent proton fluence
                               level. X usually being 1 or 10, any other value should be submitted to project approval before use. All types
                               shall be categorized as follows, displacement damage equivalent fluence being compared to displacement
                               damage sensitivity fluence:
GDI-1986/CREATED/R             * Group 1: 2 x proton fluence level < sensitivity fluence level - No generic requirements.                                             R
                               * Group 2: 1.5 x proton fluence level < sensitivity fluence level < 2 x proton fluence level - Lot testing.
                               * Group 3: Sensitivity fluence level < 1.5 x proton fluence level - Part not acceptable as is.
                               Shielding of parts, replacement, or any other solutions shall be found in order to transfer part from group 3 to
                               group 1 or 2.
                               The reset or data corruption occurrence rate due to Single Event Upset (SEU) shall not exceed 1E-4 per day.
GDI-1987/CREATED/A,R                                                                                                                                          A       R
                               Any exceptions shall be subjected to Astrium for approval on a case by case basis.
GDI-1973/CREATED/R             Deleted                                                                                                                                R
                               Inrush current at unit switch on shall not exceed the following characteristics:
GDI-895/CREATED/T,R            * dI/dt < 2 A/µs                                                                                                           T           R
                               * Q < 4ms*IL, for the input filter setting time of t < 4ms (I = LCL Trip-Off Class in [A])
                               The transient on the primary power bus distribution during switch-ON/OFF of a unit shall stay within the limits
                               of the voltage transient envelope (see Figure 4.5-1)




GDI-897/CREATED/T                                                                                                                                         T




                               Conducted voltage transients on the primary power bus, appearing during nominal mode switching (excluding
GDI-899/CREATED/T                                                                                                                                         T
                               ON / OFF) shall be 1 Vpp when measured with at least 10 MHz bandwidth.




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                                                                                                                                                                   I   COMMENT
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                                                                                                                                                           S
                               Conducted narrow band current emissions (differential mode) in the frequency range 30 Hz - 50 MHz
                               appearing on the unit's primary power lines shall not exceed the limits of Figure 4.5-2.




GDI-902/CREATED/T                                                                                                                                      T




                               Conducted narrow band current emissions (common mode) in the frequency range 30 Hz - 50 MHz appearing
                               on the unit's primary power lines shall not exceed the limits of Figure 4.5-3.




GDI-904/CREATED/T                                                                                                                                      T




                               Time domain conducted differential mode voltage ripple at the primary power bus distribution outlets from any
                               power user, measured between positive and return lines, shall be <= 100 mVpp. Time domain conducted
GDI-907/CREATED/T              differential mode voltage ripple from the PCDU measured at the primary power bus distribution outlets when              T
                               connected to a dummy load, shall be <= 140 mVpp. The voltage ripple shall be measured with at least 50 MHz
                               bandwidth.



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                                                                                                                                                                  P
                                                                                                                                                                      I   COMMENT
                                                                                                                                                  c   c       Y   E                   Method
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                                                                                                                                                  a   h           C
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                                                                                                                                                              S
                               Time domain conducted voltage spikes on the primary power bus distribution outlets, measured between
GDI-908/CREATED/T              positive and return lines, shall be <= 150 mVpp. The voltage spikes shall be measured with at least 50 MHz                 T
                               bandwidth
                               The maximum voltage emission levels for secondary power supplies shall be less than:
                               * 20mV RMS from 30Hz up to 50MHz in differential mode,
                               * 20mV RMS from 5 kHz up to 50 MHz in common mode.
GDI-918/CREATED/T                                                                                                                                         T
                               The secondary supplies will be loaded by the representative (R, L, C) loads specified in the unit interface
                               specifications. Grounding of the load networks shall be representative of the flight configuration for these
                               measurements.
                               The voltage ripple and spikes on secondary power supplies shall be less than:
                               * 50mVpp in a 50 MHz bandwidth, in differential mode,
                               * 50mVpp in a 50 MHz bandwidth, in common mode.
GDI-920/CREATED/T                                                                                                                                         T
                               The secondary supplies will be loaded by the representative (R, L, C) loads specified in the unit interface
                               specifications. Grounding of the load networks shall be representative of the flight configuration for these
                               measurements.
                               The unit shall not exceed the specified limits in the range 14 kHz - 20GHz. Testing above 1GHz is not required
                               if the unit does not employ any intentional frequencies above 100MHz and if the emissions at frequencies
                               between 0.5 and 1GHz are at least 20dB below the limit. The limit of the downlink frequency is relaxed 75dB
                               V/m for the SSPA. The launcher radiated emission limits only apply to those units that are powered at launch.




GDI-922/CREATED/T                                                                                                                                         T




                               The radiated H field generated by Units, shall be below the following limit: 110dBpT at 50Hz falling linearly on
GDI-926/CREATED/T                                                                                                                                         T
                               a log frequency scale to 70dBpT at 50KHz.
GDI-2013/CREATED/              Any specific requirements on E-field will be detailed in the individual equipment specification



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                                                                                                                                                                     I   COMMENT
                                                                                                                                                 c   c       Y   E                   Method
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                                                                                                                                                             S
GDI-2022/CREATED/              Any specific requirements on H-field will be detailed in the individual equipment specification

                               The unit shall not show any malfunction or deviation from the specified performance when irradiated with the
                               following E-fields:
                                 Payloads: 10kHz to 18GHz: 2V/m rms
GDI-928/CREATED/T                Platform: 10kHz to 18GHz: 2V/m rms (unit suppliers may alternatlvely prefer to verify non susceptability to             T
                               low frequencies by a combination of analysis and design and to only test over the range 30MHz to 18GHz. If
                               such an approach were to be proposed by the supplier it shall be agreed in advance with Astrium UK).
                               The radiated E-field shall be amplitude modulated by a sine wave at 1kHz with a modulation depth of 30%.

                               No unit that is powered On at launch shall show any malfunction or deviation from the specified performance
                               when irradiated with the launcher E-fields as listed in Table 4.5-2. No unit shall show any malfunction or
                               deviation from the specified performance when irradiated with the XBS transmitter E-field as listed in Table
                               4.5-2.



GDI-929/CREATED/T                                                                                                                                        T




                               Units shall not be susceptible when submitted to the following perturbation:
GDI-932/CREATED/T                                                                                                                                        T
                               * 50Hz to 50kHz: 140 dbpT
                               When secondary lines power a unit, the unit shall be tested with twice the maximum noise (or ripple) identified
GDI-934/CREATED/T                                                                                                                                        T
                               in the relevant power specification between these 2 units.
                               When a unit delivers secondary lines, the unit shall demonstrate under all EMC susceptibility tests (especially
GDI-935/CREATED/T              conducted susceptibility on PPB) that the maximum noise (or ripple) identified in the relevant power                      T
                               specification between these 2 units is not exceeded.
                               Primary power bus powered units shall not exhibit any failures, malfunctions or unintended responses when
                               sine wave voltages of 1 Vrms in the frequency range 30 Hz - 50 MHz (modified combination of MIL-STD-461C
                               CS01 and CS02 requirements) are developed across the power input terminals (differential mode).
                               The applied sine wave shall be amplitude modulated (30% AM) with a modulation frequency of 1 kHz in the
                               frequency range from 50 kHz - 50 MHz.
                               The frequency sweep rate shall be adjusted based on the characteristics of all unit’s internal frequencies but
                               not be faster than 3 min/decade.
GDI-938/CREATED/T                                                                                                                                        T
                               The requirement shall also be considered met when:
                               1) Frequency range 30 Hz - 50 kHz:
                               The specified test voltage levels cannot be generated but the injected current has reached 1A (rms), and the
                               equipment is still operating nominally
                               2) Frequency range 50 kHz - 50 MHz:
                               A 1-watt source of 50W impedance cannot develop the required voltage at the unit’s power input terminals,
                               and the unit is still operating nominally.




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                                                                                                                                                            S
                               The unit shall not exhibit any malfunction, degradation of performance or deviation beyond the tolerance
                               indicated in its individual specification when a sinusoidal common mode current is injected in both the
                               equipment power leads via Bulk Current Injection (BCI). The injected power shall be limited to 1 watt across a
                               50 ohm resistor.
                               The injected signal shall be in accordance with the following adjustable limits.
                               1) For nominal DC input current less than 1A, use the curve shown in Figure 4.5-5
                               2) For nominal DC input current greater than 1A, increase the level of the curve shown in Figure 4.5-5 by
                               10log[I(A)]




GDI-2000/CREATED/T                                                                                                                                      T




GDI-2006/CREATED/T             Deleted                                                                                                                  T




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                                                                                                                                                                              I   COMMENT
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                                                                                                                                                                      S
                               The unit shall not exhibit any malfunctions, degradation of performance or deviation beyond the tolerance
                               indicated in its individual specification when transient voltages typically shaped as shown in (Figure 4.5-6) are
                               applied to the unit power leads.




GDI-2007/CREATED/T                                                                                                                                                T




                               Transient Type 1
GDI-2009/CREATED/T             With reference to (Figure 4.5-6), T shall be 10 us +-10%. The pulse repetition frequency of the waveform shall                     T
                               range from 5Hz - 10 Hz and the test duration shall be at least 3 minutes. Vmax shall be +-28V
                               Transient Type 2
                               With reference to (Figure 4.5-6), T shall be 700 us +-10%. The pulse repetition frequency of the waveform
GDI-2010/CREATED/T                                                                                                                                                T
                               shall range from 5 Hz to 10 Hz and the test duration shall be at least 3 minutes. Vmax shall be +- 2.5 V for
                               differential mode.
                               No unit shall exhibit any malfunction, degradation of performance or deviation beyond the tolerance indicated
                               in its individual specification when subjected to the conducted and radiated susceptibility tests defined in
                               Section 4.5. In particular:
                               * Signal levels at unit signal outputs shall remain within the tolerances defined in Section 3.5 for each signal
GDI-944/CREATED/T                                                                                                                                                 T
                               interface type when subjected to the susceptibility tests.
                               * Units shall continue to meet their performance requirements in the presence of levels of noise induced by
                               the susceptibility testing appearing additionally at their signal inputs for all valid levels of signal input defined in
                               Section 3.5 (i.e. maximum/minimum source signal level plus induced signal).
                               The unit shall not exhibit any malfunction, degradation of performance or deviation beyond the tolerance
                               indicated in its individual specification when sinusoidal currents with an amplitude as defined in Figure 4.5-5
GDI-2089/CREATED/T             are applied to the signal lines. The test signals may be applied to a harness associated with an individual                        T
                               connector or to groups of such harnesses as dictated by the physical configuration of the unit. The injected
                               power shall be limited to 1 Watt injected into a 50 Ohm resistor.
                               (Only applies if unit supplies secondary power to other unit/s) The conducted susceptibility specification for
GDI-949/CREATED/T,R            secondary power supplied units shall be at least: 200 mV RMS from 30 Hz up to 50 MHz in differential mode,                         T           R
                               100 mV RMS from 5 kHz up to 50 MHz in common mode.
                               (Only applies if unit supplies secondary power to other unit/s)In addition, a margin of at least +6dB shall be
GDI-951/CREATED/T,R            demonstrated in frequency domain between the supplier highest emission levels and the supplied unit                                T           R
                               susceptibility level.




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                               The use of ferro-magnetics shall be avoided for parts, components, and equipment structure. Materials shall
                                                                                                                                                                                                    Declared Materials
                               be used which are non-magnetic or, if magnetic characteristics cannot be avoided, have the lowest residual
                                                                                                                                                                                                            List
                               field. In particular soft magnetic material shall be avoided whenever possible. The requirement to use ferro-
GDI-954/CREATED/I,R                                                                                                                                    O               I   R                         Magnetic Control
                               magnetic materials shall be referred to prime prior to use. Aluminium and its alloys, fibreglass, CFRP,
                                                                                                                                                                                                        Document
                               magnesium and its alloys, titanium and its alloys are all nonmagnetic. These are among the most desirable
                                                                                                                                                                                                   Post Build\Inspection
                               materials to be used structurally.
                                                                                                                                                                                                    Declared Materials
                               Steel or other magnetic materials shall be avoided for use in the mechanical hardware, and their use shall be
                                                                                                                                                                                                            List
                               minimised in any support equipment. If the use of steel in the mechanical hardware is unavoidable, it shall be
GDI-956/CREATED/I,R                                                                                                                                    O               I   R                         Magnetic Control
                               stainless steel of proven non-magnetic characteristics. It is not intended to use high permeable shielding foil
                                                                                                                                                                                                        Document
                               for the harness.
                                                                                                                                                                                                   Post Build\Inspection
                               The use of relays shall be limited to the most critical functions, which cannot be handled by solid state
GDI-958/CREATED/R                                                                                                                                                          R   Not Applicable
                               switching.
                                                                                                                                                                               To Comply with
GDI-959/CREATED/               The permitted magnetic moment of equipments shall be detailed in the individual equipment specification                                         specification
                                                                                                                                                                               undefined

                               The unit shall not be susceptible when submitted to the following perturbations:
                               * Radiated discharges (10 kV, 10 mJ, Test Duration > 3 min, with a repetition rate of 10 arcs/min) at 30 cm
GDI-962/CREATED/T                                                                                                                                              T               Photo-Diodes Only
                               * Conducted discharges into the ground plane or structure / unit (case(10 kV, 10 mJ, Rise time (10%-90%)
                               <10nsec,Duration (half amplitude) 100nsec, Test Duration > 3 min, with a repetition rate of 10 arcs/min).


                               Qualification of the design shall be accomplished using representative flight configuration hardware and
                               software. The objective of the qualification shall be to demonstrate the capability of all hardware items to
                               provide all specified performances under all environment and interface conditions and to survive their full
                                                                                                                                                                                                   Environmental Test
                               operational life. The test specimen shall be subjected to qualification loads. The test conditions shall not
GDI-967/CREATED/T,A                                                                                                                                    O       T   A                                     Report
                               exceed design margins of safety nor excite unrealistic failure modes. Items which can be qualified by an
                                                                                                                                                                                                    Analysis Report
                               applicable qualification history, by similarity to qualified items, or purely by analysis, may require only limited
                               qualification testing or even none. However, all safety critical items must be fully qualified by test. Qualification
                               testing shall be conducted at the relevant level according to the requirements defined in this section.
                               Environmental acceptance testing shall be performed on all deliverable flight and flight spare hardware. The
                               objectives of acceptance testing are:
                               * Demonstrate freedom from manufacturing and workmanship errors.
                                                                                                                                                                                                   Environmental Test
GDI-969/CREATED/T,A,R          * Demonstrate that hardware and software performance comply with design specifications.                                 O       T   A       R
                                                                                                                                                                                                         Report
                               * During environmental acceptance testing, conditions or effects, similar to the mission environment shall be
                               simulated. Acceptance testing shall be conducted at the relevant level according to the requirements defined
                               in this section.




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                               The objective of the test item functional performance test is to verify the performance of the item/unit during
                               the test program. Satisfactory and un-degraded functional performance before, during and after the specified
                               environmental loads are required prior to approval for qualification or acceptance.
                               An initial and a final functional performance test shall be conducted at the beginning and at termination of each
                               environmental test. A functional performance test may run continuously for such tests, where the unit would
                               be active, when this environment occurs (e.g. thermal). The test shall be conducted under standard laboratory
                               conditions.
                               The tests shall be performed in compliance with approved test procedures, which reflect the verification
                               criteria of the particular test item/unit specification. Beside electrical performance, all mechanical functions
                               operated electrically shall be commanded and shall function. Failure detection, isolation and recovery                                                               Environmrntal Test
                               functions shall be tested to the maximum extent possible without destroying the test article. Functional test will                                                         Report
GDI-971/CREATED/T,A                                                                                                                                 O       T   A
                               be performed by operating all required operational modes. Unit interface functions will be simulated. Unit                                                            Functional Test
                               performance will be checked considering at least:                                                                                                                          Report
                                 All required modes
                                 Begin/end of life power
                                 Maximum/minimum load
                                 Effects of power and subsystem switching
                                 Redundancies
                                 Emergency/safety modes
                                 Power protection
                                 Variation of input parameters
                                 Software if applicable
                               Any test facility to be used within the instrument assembly or unit test programme shall be capable to perform                                                       Design Description
GDI-973/CREATED/A,R            the required test within the specified limits and shall not impact the test objective or degrade the test article                A       R   Temperature Stability        Report
                               performance.                                                                                                                                                            Test Facility
                               The accuracy of instrument and test equipment used to control or measure the test parameters shall be in
                               general, one order of magnitude better than the tolerance for the variable to be measured Exceptions shall be                                                           Instrument
                               specified in the relevant specifications and shall be agreed by the customer. All instrumentation to be used for                                                      Specification &
GDI-975/CREATED/A,R                                                                                                                                 O           A       R
                               qualification and acceptance tests shall be subjected to approved calibration procedures and shall be within                                                            Calibration
                               the normal calibration periods at the time of test. Instrumentation which will run out of calibration during the                                                     Test Specification
                               planned test time shall be not used.




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                               The allowed test condition tolerances shall be applied to the specified nominal test values. Unless otherwise
                               specified, the maximum allowable tolerances on test conditions or measurements shall be as per Table 5.1-1
                               and Table 5.1-2. The tolerance on test parameters specifies the maximum allowable range within which the
                               specified test level (input level) or measurement (output) may vary and excludes instrument accuracy.




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GDI-977/ECSS-E-10-                                                                                                                                                     Verification Method is
                                                                                                                                                           A   I   R                            Test Specification
03A/A,I,R                                                                                                                                                              inappropriate
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GDI-977/ECSS-E-10-                                                                                   Verification Method is
                                                                                         A   I   R                            Test Specification
03A/A,I,R                                                                                            inappropriate




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GDI-977/ECSS-E-10-                                                                                   Verification Method is
                                                                                         A   I   R                            Test Specification
03A/A,I,R                                                                                            inappropriate
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                               Unless otherwise specified herein, all measurements and tests shall be made at room ambient atmospheric
                               pressure, temperature and relative humidity conditions, whereby 22 3°C and 55 10% RH shall not be
                               exceeded. Whenever these conditions must be closely controlled in order to obtain reproducible results a
                               reference temperature of 21°C, a relative humidity of 50 % and an atmospheric pressure of 1013 hPa shall be                                    Waiver Required for
GDI-981/CREATED/A,I,R                                                                                                                                 O           A   I   R                           Test Reports
                               used together with whatever tolerances are required to obtain the desired precision of measurement. Actual                                     Glasgow Facility
                               ambient test conditions should be recorded periodically during the test period. The cleanliness requirements
                               for the test items during assembly, integration, transport and test shall be in accordance with the PA
                               requirements.




GDI-983/CREATED/A,I,R          ########################################################################################                               O           A   I   R                           Test Reports




                               The test is successfully performed if all measurement results are in accordance with the design requirements
                               as stated in the particular unit design and performance specification and transformed into test requirements
                               listed in the test specification.                                                                                                              Phasemeter
                               Modifications, repair, replacement or refurbishment of an item, which failed an initial test, shall be subject to a                            Procedure
                               retest. When it can be shown that the test interruption was caused by a GSE or software problem the retest                                     Interface with          Test Reports
GDI-985/CREATED/T,A                                                                                                                                   O       T   A
                               shall be started from that point of GSE or software failure after appropriate repair has taken place and positive                              Materials Review            TBD
                               confirmation can be given for the nominal performance of the GSE item. Any repetition of qualification or                                      Board
                               acceptance test needs the prior decision of the MRB responsible. If not, the corrective action substantially                                   NRB?
                               affects the significance of results of previously completed tests in the sequence, such tests shall also be
                               repeated.
                               The unit under test shall be mounted (to a rigid fixture, see below) as in flight configuration. The unit
                               attachment hardware (bracket, cabling, tubing, etc.) shall be included in the tests (to a reasonable extent) to
                                                                                                                                                                                                    Test Specification
GDI-989/CREATED/T              achieve dynamic similarity of the unit to actual installation. Cabling, tubing etc. shall be attached to the unit as   O       T               Method?
                                                                                                                                                                                                      Test Report
                               required for operating or monitoring functions; but fixed in such a way to the fixture or auxiliary supports that
                               no higher loads are excited than in actual installation configuration.
GDI-990/CREATED/T              At least one triaxial sensor shall be mounted on the unit under test to monitor the response on the units.             O       T               Method?                  Test Report
                               At least two axis aligned sensors shall be mounted on the test fixture adjacent to the unit to monitor the test
GDI-991/CREATED/T                                                                                                                                     O       T               Method?                  Test Report
                               level input.
                               All units powered on during launch shall be powered on during mechanical equipment testing in the same
GDI-992/CREATED/T                                                                                                                                     O       T               Not Applicable
                               operational configuration. The unit electrical performance shall be monitored during the test.
                               The test item shall be attached to the vibration exciter table by means of a rigid test fixture capable of                                     Contradicts GDI-
GDI-995/CREATED/T              transmitting the vibration conditions specified herein. The test fixture shall be designed to minimise fixture         O       T               989/CREATED/T            Test Report
                               response at resonance within the test frequency range.                                                                                         Transducer on Table




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                               The variation of transmissibility between test item mounting points shall not exceed a factor of + 3 dB between
                                                                                                                                                                            Definition of
GDI-996/CREATED/T              5 and 500 Hz and + 6 dB between 500 and 2000 Hz, provided that the total cumulative bandwidth, which                 O       T
                                                                                                                                                                            transmissibility
                               exceeds + 3 dB does not exceed 300 Hz. Cross talk shall not exceed the input.
                               Adequate fixture design and specimen installation are the responsibility of the unit subcontractor as part of the
GDI-997/CREATED/T                                                                                                                                   O       T                                  Test Procedure
                               verification activities. The fixture shall be described in the test procedure.
                               A pre-test of the empty fixture shall be performed to verify the correct dynamic behaviour of the fixture and the
GDI-998/CREATED/T                                                                                                                                   O       T                                  Test Procedure
                               proper function of the control loop.
                               Frequency search tests shall be conducted In order to:
                               * Identify the unit frequency content and correlate results with FEM predictions,
                               * Estimate the Q_factors associated to the main modes,
GDI-1000/CREATED/T             * Establish a basis for frequency content comparison between test runs and allow eventual interface settling         O       T                                  Test Procedure
                               anomaly evaluation, In particular, the knowledge of the results of the main unit frequencies and associated
                               Q_factors measured during the first frequency search test along each axis is of prime importance to lead
                               properly higher level tests.
                               Frequency search tests shall be conducted along each of the three mutually perpendicular axes one at a time
                               at least prior to and after performing the tests. The frequency search tests are defined in Table 5.2-1. In
                               order to allow better Q_factor estimation, the frequency search test level shall be adjusted in order to avoid
                               notching on the main eigen modes.



GDI-1002/CREATED/T                                                                                                                                  O       T                                  Test Procedure




                               For units the vibration test levels that are applied at the unit interface are identified, both for acceptance and
                               qualification and shall be as:
                               * In Table 4.2-5 for sinusoidal vibration
                               * In Table 4.2-6 for random vibration
GDI-1005/CREATED/A,R                                                                                                                                O           A       R                      Test Procedure
                               * In Table 4.2-7 for shock
                               When necessary, these levels can be reduced in accordance with the notching philosophy defined in
                               APPENDIX G: NOTCHING GUIDELINES FOR MECHANICAL TESTS. Any notching must be formally
                               requested as a waiver/deviation to a specification and submitted for customer agreement.
GDI-1011/CREATED/T             Sine and random vibration tests shall be performed separately on the three axis.                                     O       T                                  Test Procedure
                               Prior and after sine and random vibration qualification and acceptance tests a low level sine frequency search
                               test shall be performed according to requirements GDI-1000 and GDI-1002. Care shall be taken in adjusting
GDI-1012/CREATED/T                                                                                                                                  O       T                                  Test Procedure
                               the level before test such that resonant modes do not lead to unit overstress or Q-factors erroneous
                               estimation.
                               Before applying full levels, a test at intermediate level shall be applied. For qualification testing, the
                               intermediate levels shall be set as the acceptance (flight limit) levels. For acceptance testing, the intermediate
GDI-1013/CREATED/T                                                                                                                                  O       T                                  Test Procedure
                               levels shall be the acceptance levels divided by 2 for sine vibrations and by 4 the power spectral densities for
                               random vibrations.




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                               A notching of sine and random vibrations may be applied to decrease the impact of resonant modes, keeping                                 To be reviewed post
                               load below the specified quasistatic qualification load as per Section 4.2.2.1 . Guidelines for notching are                              analysis, but prior to
GDI-1014/CREATED/T                                                                                                                               O       T                                        Test Procedures
                               defined in APPENDIX G: NOTCHING GUIDELINES FOR MECHANICAL TESTS. The notching shall be                                                    writing test
                               justified by the Subcontractor, discussed on a case-by-case basis and submitted to the customer for approval.                             procedures
                                                                                                                                                                                                   Test Facility
                               The vibration facility shall include a shock free abort device mounted onto the shaker to prevent the unit from
GDI-1015/CREATED/T                                                                                                                               O       T                                         Requirement
                               hazardous over testing potentially induced by facility failure.
                                                                                                                                                                                                  Test Procedure
                               Units shall demonstrate by test their ability to withstand the shock acceleration levels as defined in Section
GDI-1017/CREATED/T                                                                                                                               O       T                                        Test Procedure
                               4.2.2.2.3 of this document.
                               Prior and after shock tests a low level sine frequency search test shall be perform according to requirements
                                                                                                                                                                         Visual Inspection
GDI-1018/CREATED/T             GDI-1000 and GDI-1002. Care shall be taken in adjusting the level before test such that resonant modes do         O       T                                        Test Procedure
                                                                                                                                                                         Between Tests
                               not lead to unit overstress or Q-factors erroneous estimation.
                                                                                                                                                                         Operational?
                                                                                                                                                                         Quantifying loads fed
                               Static tests shall be performed by applying the specified sinusoidal level defined in the low frequency range,
GDI-1020/CREATED/T                                                                                                                               O       T               in from surrounding      Test Procedure
                               whose amplitude generates acceptance/qualification quasi-static loads.
                                                                                                                                                                         structure at higher
                                                                                                                                                                         levels of integration
                               The temperatures shall be selected and controlled such that the test item experiences actual temperatures                                 No Temperature
                               equal to or beyond the minimum and maximum qualification/acceptance temperatures. This shall be                                           Reference Point
GDI-1024/CREATED/R                                                                                                                               O                   R                            Test Procedure
                               guaranteed by temperature monitoring at the temperature reference point and additional points as agreed with                              Astrium to be
                               the customer.                                                                                                                             consulted




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                               The test arrangement shall be as shown in Figure 5.2-1.




GDI-1025/CREATED/R                                                                                                                             O                   R                      Test Procedure




GDI-1026/CREATED/R             The unit shall be bolted to a thermally controlled heat sink using the flight design.                                               R   Not Applicable
GDI-1027/CREATED/R             On all external surfaces flight representative thermal hardware shall be applied.                                                   R   Not Applicable
GDI-1028/CREATED/R             The heat sink (HS) plates shall be black painted (except for the contact area) as well as the chamber shroud.                       R   Not Applicable
                               The conductive heat sink temperature and the chamber shroud temperature shall be controlled in order to give
GDI-1029/CREATED/R                                                                                                                             O                   R                       Test Report
                               as a minimum qualification/acceptance temperatures at the unit temperature reference point(s).
                                                                                                                                                                       TV Chamber
GDI-1030/CREATED/R             For vacuum tests the pressure inside the chamber shall be less or equal than 1E-5 torr                          O                   R   Capability          Test Report
                                                                                                                                                                       Why the extreme?




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                               Unit's suppliers shall perform Thermal Vacuum (TV) qualification tests at unit level to demonstrate the
                               performance of the units in an extreme thermal vacuum environment by simulating minimum and maximum
                               qualification temperatures. (See Table 5.2-3 for test parameters) The thermal qualification test could be used
                               for the unit thermal model verification and correlation purpose.




GDI-1034/CREATED/T                                                                                                                              O       T                         Test Procedure




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                               The TV test on unit level shall be performed as in Table 5.2-2.




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                                                                                                                                                      Qualification tests of
                                                                                                                                                      fibre injector to include
GDI-1036/CREATED/R                                                                                                                                R                               Test Procedure
                                                                                                                                                      performance test
                                                                                                                                                      aspects




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                               The qualification temperatures for the different units are defined in Table 4.3-2. All temperatures refer to the
GDI-1037/CREATED/R                                                                                                                                O                   R             Test Procedure
                               temperature reference point.
                               The units shall be tested following the thermal vacuum test sequence, as shown in Figure 5.2-2.




                                                                                                                                                  O




                                                                                                                                                                                    Test Procedure
GDI-1038/CREATED/T,R                                                                                                                                      T           R
                                                                                                                                                                                     Test Report




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                                                                                                                                                                                   Test Procedure
GDI-1038/CREATED/T,R                                                                                                                                     T           R
                                                                                                                                                                                    Test Report




                                                                                                                                                 O




                               Unit suppliers shall perform thermal vacuum (TV) acceptance tests on unit level in order to detect material and
GDI-1044/CREATED/T                                                                                                                               O       T                         Test Procedure
                               workmanship defects prior to installation.
                               The thermal vacuum acceptance test shall be performed in the same way as specified above for the thermal
                               vacuum qualification test, with the following modifications:
                               * Acceptance temperatures shall be applied instead of qualification temperatures. The acceptance
                               temperatures for the different units are defined Table 4.3-2.
                               * The number of thermal cycles applicable to the TV acceptance test is n = 4
GDI-1045/CREATED/T,R           * Step 30 in the test sequence is modified to:"Repeat steps 24 to 29 two times"                                   O       T           R             Test Procedure
                               On a case-by-case basis, and after approval of the customer, thermal vacuum can be replaced by thermal
                               tests at ambient pressure. This will however be forbidden if calibrations of flight parameters are necessary
                               during thermal tests. In any case, this replacement shall require demonstration of consistency between
                               thermal vacuum measurements and thermal at ambient pressure ones. Specific acceptance criteria for the
                               performance measurements shall be computed.
GDI-1049/CREATED/T             Unit suppliers shall perform thermal vacuum (TV) protoflight tests on unit level in order to qualify the unit.            T




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                               The thermal vacuum protoflight test shall be performed in the same way as specified above for the thermal
                               vacuum qualification test, with the following modifications:
                               * The number of thermal cycles applicable to the TV protoflight test is n = 4
                               * Step 30 in the test sequence is modified to:"Repeat steps 24 to 29 two times"
                                                                                                                                                                           Acceptance Level
GDI-1050/CREATED/T,R           On a case-by-case basis, and after approval of the customer, thermal vacuum can be replaced by thermal              O       T           R                      Test Procedure
                                                                                                                                                                           Testing
                               tests at ambient pressure. This will however be forbidden if calibrations of flight parameters are necessary
                               during thermal tests. In any case, this replacement shall require demonstration of consistency between
                               thermal vacuum measurements and thermal at ambient pressure ones. Specific acceptance criteria for the
                               performance measurements shall be computed.
GDI-1053/CREATED/R             Deleted                                                                                                                                 R
                               Development tests may be performed to evaluate the design approach, indicate critical areas where design
GDI-1057/CREATED/T,R           improvement is required, assure compliance with the design requirements, confirm and support analytical                     T           R   Not Applicable
                               methods or generate essential design data at an early stage.
GDI-1059/CREATED/T,R           Qualification tests for PFM shall be performed as specified in the applicable equipment SOW.                                T           R   SOW?
GDI-1061/CREATED/T,R           Acceptance tests for FM shall be performed as specified in the applicable equipment SOW.                                    T           R   SOW?
                               In order to ensure the proper grounding of the secondary power to the unit structure (refer to Section 3.5.7.3.2)
GDI-1063/CREATED/T,R                                                                                                                                       T           R   Not Applicable
                               a bonding test shall be performed during unit assembly.
                               A retest may be required in case a test result is not as expected resulting in an NCR. The retest of the test
                                                                                                                                                                                              Test Procedure
GDI-1065/CREATED/R             article shall be defined by the Non-conformance Review Board (NRB) in accordance with the                           O                   R
                                                                                                                                                                                              NCR documents
                               Nonconformance Control Procedure as defined in the PA requirements.
GDI-1067/CREATED/R             The pre- and post-test inspection is specified in the Product Assurance Requirements                                                    R   Not Applicable
                               The following test sequence is recommended, but not mandatory. It can be changed to fulfil schedule or cost
                               requirements if it does not affect the overall validity of the EMC test program. Recommended EMC test
                               sequence:
                                 Bonding and grounding
                                 Isolation
GDI-1069/CREATED/R               Conducted emission                                                                                                                    R
                                 Conducted susceptibility
                                 Radiated emission
                                 Radiated susceptibility
                                 Radiated ESD
                                 Conducted ESD
GDI-1072/CREATED/R             All EMC tests shall be conducted at standard ambient conditions as specified in Section 4.                                              R
                               The test facilities used for the EMC test program shall be capable to perform the required tests within the
                               specified limits and shall not impact the test objectives or degrade the performance of the test specimen. For
GDI-1074/CREATED/R                                                                                                                                                     R
                               the radiated EMC tests the terrestrial electromagnetic noise levels shall be better than 6dB lower than those
                               needed for the specified levels to be measured.
                               The maximum allowable tolerance for the test parameters shall be as follows unless otherwise specified within
                               this specification or the applicable equipment specification.
                               * Voltage magnitude: ± 5 % of peak value
                               * Current magnitude: ± 5 % of peak value
                               * RF amplitude: ± 2 dB
GDI-1077/CREATED/R                                                                                                                                                     R
                               * Frequency: ± 2 % (except for notches)
                               * Distances: ± 5 % or ± 5 cm, whichever is greater
                               * Test time: 0 - 10 %
                               The tolerance specifies the allowable range within which the specified test parameter / level may vary and is
                               exclusive of measurement equipment accuracy.




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                               The accuracy of measurement equipment and test equipment used to control or measure the EMC test
                               parameters shall be
                               * ± 2 dB for levels
GDI-1079/CREATED/R                                                                                                                                                     R
                               * ± 2 % for frequencies.
                               All instrumentation to be used for qualification and acceptance tests shall be subjected to approve calibration
                               procedures and shall be within the normal calibration periods at the time of test.
                               Measurement equipment shall use an isolation transformer on the AC power lines and a separate ground
GDI-1081/CREATED/R                                                                                                                                                     R
                               cable to the central ground point. The ground cable shall consist of braided cable.
                               For radiated emission measurements no part of the measuring antenna shall be less than 1 m from any
GDI-1082/CREATED/R             obstructions. For radiated susceptibility tests no parts of the field generating and field-measuring antenna (for                       R
                               calibration purposes) shall be less than 1 m from any obstructions.
                               The following receiver bandwidth shall be used if not otherwise specified (Table 5.2-5): Any deviation from the
                               proposed bandwidths shall be recorded in the test report.




GDI-1083/CREATED/R                                                                                                                                                     R




                               The primary power for unit level tests shall be adjusted for emission and susceptibility tests To 28 Volts for
GDI-1085/CREATED/R                                                                                                                                                     R
                               regulated power bus
                               For the conducted emission and susceptibility tests on unit level a LISN, simulating the primary power bus
GDI-1087/CREATED/R                                                                                                                                                     R
                               impedance, shall be used as shown in the relevant test set-up.
                               The LISN has to be designed and provided by the company responsible for the test. Prior to test the network
GDI-1090/CREATED/T                                                                                                                                         T
                               impedance shall be measured in the relevant frequency range and attached to the test report.




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                               Derivation of the bus impedance is as follows:
                               The maximum bus impedance at the low frequency end may be derived from dividing the maximum voltage
                               drop from the appropriate LCL by its current rating (see GDI-350) and adding 20 milliohms plus a 20% margin.
                               The minimum value (to be used for test purposes) may be significantly less and is TBC. This value is
                               intercepted by the sloping portion of the graph which is determined by the harness impedance and reaches a
                               maximum value of 100 Ohms at 10 MHz, thereafter remaining constant. A typical bus impedance is shown in
                               Figure 5.2-3.




GDI-2116/CREATED/T                                                                                                                                         T




                               The purpose of the test is to demonstrate the compliance with the EMC performance requirements of Section
GDI-1094/CREATED/R                                                                                                                                                     R
                               4.5.1 of this document.
                               The equipment under test shall be switched on in the normal switch-on sequence and shall operate in suitable
GDI-1095/CREATED/R                                                                                                                                                     R
                               operational modes w.r.t. the particular EMC test purpose.
                               For emission testing the unit shall operate within a mode, which allows the maximum amount of generated
GDI-1096/CREATED/R                                                                                                                                                     R
                               interferences (voltage, current, field).
                               For susceptibility testing the suitable operational mode shall be that mode which maximises the response of
GDI-1097/CREATED/R                                                                                                                                                     R
                               the equipment under test to the particular environment being created.
GDI-1098/CREATED/R             After testing the equipment shall be switched off using the normal switch-off sequence.                                                 R
                               Both operational modes shall provide operational conditions, which result in an adequate test data profile of
GDI-1099/CREATED/R             the generated interference and susceptibility of unwanted signal outputs or degradation of equipment                                    R
                               performance that could exist during unit functional operation.
                               The particular test set-up shall represent the flight configuration as close as possible. Power, signal and other
GDI-1100/CREATED/R             circuits grounding shall be in compliance with the grounding requirements as described in Section 3.5.7.2 of                            R
                               this document.
GDI-1106/CREATED/R             This test shall verify the DC resistance of bonding interfaces specified in Section 3.5.7.1.                                            R
                               The bonding test shall be performed with the unit under test (UUT or EUT) switched off. The measurements
GDI-1107/CREATED/R                                                                                                                                                     R
                               shall be done with the four-wire method and with both directions of polarity.
GDI-1108/CREATED/R             The bonding test shall be performed without any harness connection.                                                                     R


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                               The purpose of this test is to measure the isolation of primary and secondary power lines from ground in order
GDI-1110/CREATED/R                                                                                                                                                  R
                               to verify the requirements of Section 3.5.7.2.
                               The isolation test shall be performed with the UUT switched off, but all interfaces connected (i.e. EGSE, unit
                               interconnection for subsystem level). The measurement shall be done with both directions of polarity. Figure
                               5.2-4 shows the principle test set-up for isolation measurements.




GDI-1111/CREATED/R                                                                                                                                                  R




                               This test shall demonstrate the compliance of the differential and common mode conducted emissions on
GDI-1115/CREATED/R                                                                                                                                                  R
                               primary power lines with the requirements defined Sections GDI-601 and Section 4.5.1.




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                               UUT operation shall be selected in order to maximise the level of conducted interference appearing on the
                               power lines, while remaining within the normally expected operating range. The test set-ups are shown in
                               Figure 5.2-5 (frequency domain) and Figure 5.2-6 (time domain).




GDI-1116/CREATED/R                                                                                                                                             R




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GDI-1116/CREATED/R                                                                                                                                              R




                               Ripple and transient interference tests on the power lines shall be performed using standard current probe
GDI-1118/CREATED/R                                                                                                                                              R
                               measurement techniques for each DC power lead.
                               This test shall measure the conducted emissions (ripple) and demonstrate the compliance with the
                               requirements defined in Section 4.5.9.
GDI-1122/CREATED/R                                                                                                                                              R
                               * On the secondary power input of a unit.
                               * On the secondary power output of a unit providing power to another unit.
                               UUT operation shall be selected in order to maximise the level of conducted interference appearing on the
GDI-1123/CREATED/R                                                                                                                                              R
                               power lines, while remaining within the normally expected operating range.




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                               When the secondary power provider and user need to be tested individually, the secondary power output shall
                               be terminated with a load, representing the load impedance of the nominal secondary power user.
                               Alternatively the test can be performed when the secondary power provider and user are connected together
                               and operating. The test set-ups are shown in Figure 5.2-7 (unit secondary power input) and Figure 5.2-8 (unit
                               secondary power output). For frequency domain measurements replace oscilloscope with EMI receiver and
                               differential amplifier




GDI-1124/CREATED/R                                                                                                                                                 R




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                               The mode selection for susceptibility testing shall be such as to maximise the response of the UUT to the
GDI-2090/CREATED/T,R           particular environment created. The test set-up is shown in Figure 5.2-12, with the exception that the current           T           R
                               probes are located around the appropriate signal harness(es).
                               This test shall demonstrate the noise immunity of primary power lines to the specified interference levels of
GDI-1132/CREATED/R                                                                                                                                                  R
                               Section 4.5.11.
                               The mode selection for susceptibility testing shall be such as to maximise the response of the UUT to the
GDI-1133/CREATED/R                                                                                                                                                  R
                               particular environment being created.
                               The test set-ups are shown in Figure 5.2-9 (CS01; Continuous Wave 30Hz...50 kHz), Figure 5.2-10 (CS02;
                               Continuous Wave 50 kHz... 50 MHz), Figure 5.2-11 (CS06; Transients) and Figure 5.2-12 (Bulk Current
                               Injection). Note: Use Figure 5.2-12 for common mode voltage, but locate current probes on connection
GDI-1134/CREATED/T                                                                                                                                      T
                               between equipment signal reference (0V) and ground plane.

                               See GDIRS for Drawings
                               This test shall demonstrate the noise immunity of primary power lines to the specified interference levels of
GDI-1139/CREATED/R                                                                                                                                                  R
                               Section 4.5.10.
                               The mode selection for susceptibility testing shall be such as to maximise the response of the UUT to the
GDI-1140/CREATED/R                                                                                                                                                  R
                               particular environment being created.




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                               The test set-ups are shown in Figure 5.2-13 (CS01; Continuous Wave 30Hz...50 kHz), Figure 5.2-14 (CS02;
                               Continuous Wave 50 kHz... 50 MHz).




GDI-1141/CREATED/T                                                                                                                               T




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                               UUT operation shall be selected in order to maximise the level of radiated interference appearing on the
                               power lines, while remaining within the normally expected operating range. The test set-up is shown in Figure
                               5.2-15.




GDI-1151/CREATED/R                                                                                                                                                 R




GDI-2015/CREATED/T             Deleted




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                               UUT operation shall be selected in order to maximise the level of radiated interference appearing on the
                               power lines, while remaining within the normally expected operating range. The test set-up is shown in Figure
                               5.2-16.




GDI-1155/CREATED/R                                                                                                                                                 R




                               The test method to determine the fluctuations of the H-field in the instrument measurement bandwidth is
GDI-2017/CREATED/T             shown in GDI-1152 with the exception that the antenna and receiver are replaced by an appropriate sensor                T
                               and detection system.
GDI-1158/CREATED/R             Deleted




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                               UUT operation shall be selected in order to maximise the response of the test specimen to the particular
                               environment being created. The test set-up is shown in Figure 5.2-17.




GDI-1159/CREATED/R                                                                                                                                            R




GDI-1162/CREATED/R             Deleted




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                                                                                                                                          l               T
                                                                                                                                                      S
                               UUT operation shall be selected in order to maximise the response of the test specimen to the particular
                               environment being created. The test set-up is shown in Figure 5.2-18.




GDI-1163/CREATED/R                                                                                                                                            R




GDI-1166/CREATED/R             Deleted




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                                                                                                                                              O           A   I
                                                                                                                                                          N       R
                                                                                                                                              p   B           N
                                                                                                                                                      T   A       E
                                                                                                                                              t   e           S
                                                                                                                                                      e   L       V             Verification
 Requirement No. Ref. Status                                                Requirement                                                       i   n
                                                                                                                                                      s
                                                                                                                                                              P
                                                                                                                                                                  I   COMMENT
                                                                                                                                              c   c       Y   E                   Method
                                                                                                                                                      t   S       E
                                                                                                                                              a   h           C
                                                                                                                                                          I       W
                                                                                                                                              l               T
                                                                                                                                                          S
                               UUT operation shall be selected in order to maximise the response of the test specimen to the particular
                               environment being created. Figure 5.2-19 shows principle test set-up for radiated ESD test and Figure 5.2-20
                               for conducted ESD test.




GDI-1167/CREATED/R                                                                                                                                                R




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                                                                                                                                                 O           A   I
                                                                                                                                                             N       R
                                                                                                                                                 p   B           N
                                                                                                                                                         T   A       E
                                                                                                                                                 t   e           S
                                                                                                                                                         e   L       V                     Verification
 Requirement No. Ref. Status                                                 Requirement                                                         i   n
                                                                                                                                                         s
                                                                                                                                                                 P
                                                                                                                                                                     I   COMMENT
                                                                                                                                                 c   c       Y   E                           Method
                                                                                                                                                         t   S       E
                                                                                                                                                 a   h           C
                                                                                                                                                             I       W
                                                                                                                                                 l               T
                                                                                                                                                             S
GDI-1167/CREATED/R                                                                                                                                                   R




                               This test shall be used in order to show the compliance of the test specimen with the referring magnetic
                               requirement as given in the equipment specification. If accepted by the customer, verification by similarity is
                                                                                                                                                                         Magnetic Moment
GDI-1171/CREATED/T,R           possible. It is recommended to measure the test specimen in a magnetic coil facility or to use other adequate     O       T           R                      Test Report
                                                                                                                                                                         Test
                               test methods in order to show compliance with the requirement. The selected test method has to be accepted
                               by the customer.




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                                                                                                                                                   O           A   I
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                                                                                                                                                           T   A       E
                                                                                                                                                   t   e           S
                                                                                                                                                           e   L       V                             Verification
 Requirement No. Ref. Status                                                  Requirement                                                          i   n
                                                                                                                                                           s
                                                                                                                                                                   P
                                                                                                                                                                       I   COMMENT
                                                                                                                                                   c   c       Y   E                                   Method
                                                                                                                                                           t   S       E
                                                                                                                                                   a   h           C
                                                                                                                                                               I       W
                                                                                                                                                   l               T
                                                                                                                                                               S
                               Verification by similarity may be applied to equipment or subsystems coming from other programs, where re-
                               use as it is or re-use with only little modification is proposed. An analysis of the test results of the previous
                               programme shall be carried out against the unit requirement. For information the following evaluations are
                               given:
                               A mean magnetic field will be derived for each measurement axes according to the equation




                               The total magnetic field (magnitude of magnetic field vector) can be calculated according to the equation



                                                                                                                                                                           Not Applicable
                               For comparison with the specified limit the result shall be referred to 1 m using the equation                                              Testing to be carried
GDI-1173/CREATED/A,R                                                                                                                                           A       R   out of complete optical
                                                                                                                                                                           Bench + PD - Not
                                                                                                                                                                           Applicable




                               A life test shall be required for all the assemblies concerned by wear-out phenomenon during the operation
GDI-1185/CREATED/T,R                                                                                                                                       T           R
                               lifetime (on-ground and on board).
                               Space conditioning shall be performed whenever design choices for a unit or an assembly induce behaviour
GDI-1187/CREATED/T,R                                                                                                                                       T           R   Not Applicable
                               differences between in flight environment and on-ground environment.
GDI-1188/CREATED/R             The contractors shall propose the corresponding tests program, submitted to customer approval.                                          R   Not Applicable
                               For example, but without limitation to, materials moisture release, outgassing & strain releases shall be
GDI-1189/CREATED/T                                                                                                                                         T               Not Applicable
                               conducted whenever necessary




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Requirement No. Ref. Status                                                Requirement


                              The LTP instrument shall be fully compatible with the following primary main mission phases:
                              · Ground operations, handling and transport
                              · Launch and early orbit phase
   RS 4.2.2-1/R               · Transfer and injection to the final orbit
                              · LTP demonstration phase
                              · DRS demonstration phase
                              · Joint LTP/DRS demonstration phase
                              During the LEOP the LTP shall not need any primary power.
   RS 4.2.2-2/R T
                              The maximum duration of this phase will not exceed TBD days
                              During the transfer and final orbit injection the LTP shall be in a passive mode and require no more than TBD
                              W primary power.
                              The maximum duration until final orbit acquisition will not exceed TBD days
                              Note:
   RS 4.2.2-3/R T
                              During transfer LTP shall be passive as baseline. However, some calibrations could be performed in this
                              phase, if these can be separated from the activities of the demonstration phase. (TBD)
                              Furthermore, there is a radiation monitor that could be used during the apogee orbit manoeuvres to measure
                              the radiation TBC.
                              The LTP design shall support a complete in-orbit commissioning of the instrument within equal or less than 10
                              days.
                              Note: This requirement must also be imposed on S/C and LTP operational SW, i.e. charge management
                              control and release procedure controlled by S/C need to support this requirement.

                              The total duration of the nominal LTP demonstration phase will be 3 months. During this phase the LTP will be
   RS 4.2.2-4/R A
                              operated in various modes to be tested on all parameters. These modes will include:
                              -the basic LTP operational mode (M1) (with and without optical readout)
                              - the Laser signal locking mode (M3)
                              - the drift mode
                              - the charge measurement mode
                              - the stiffness measurement mode
                              During the DRS demonstration phase the maximum duration until final orbit acquisition will not exceed TBD
  RS 4.2.2-5 /R T
                              days.
                              During the LTP/DRS joint operational modes the LTP shall support following combined operations:
                              - Simultaneous operation of LTP and DRS at full functionality for both packages
   RS 4.2.2-6/R T
                              - Use of one Test Mass of the DRS as A source of gravitational signal for the LTP
                              - 2-axes 2-test-masses control with full functionality for both packages and one axis controlled by DRS
                              The total duration of the LTP/DRS joint demonstration phase shall be 24 days, included in the individual
   RS 4.2.2-7/R
                              periods of the LTP and DRS demonstration phases.
                              The in-orbit design lifetime shall be 12 months. This shall also concern all consumables, if any required.
   RS 4.2.3-1/ R
                              The LTP shall be designed such that it can be stored on ground for 1 year, under controlled environment
   RS 4.2.3-2/ R              conditions, with minimum need for preventive maintenance.
                              Note: Refer as well to Chapter 5.1.5.
                              S/C orbit maintenance operations will not be performed during the LTP measurement cycle.
                              Protection of the LTP from any excessive disturbances during orbit maintenance or other non-LTP related S/C
   RS 4.2.4-1/ R              operational phases (outside the LTP measurement phase) may require TM re-caging.
                              The LTP shall implement means by with the TM is re-caged during S/C orbit maintenance operations, if so
                              commanded by the S/C.
                              The Instrument design shall be compatible with the spacecraft being under dragfree control using the LTP,
                              DRS and other sensors information for attitude and position control via any micro-propulsion subsystem
   RS 4.2.5-1/ R              provided by the S/C. That is, cold-gas thrusters or FEEP thrusters.
                              Note:
                              During joint operations the colloid thrusters will be switched off.
                    The LTP shall be functionally broken down into subsystems and units as identified in the Product Tree shown
                    in Figure 4.3-1.




  RS 4.3.1-1/R




                    It shall be possible for the LTP team on-ground to override each individual fault management function within
 RS 4.3.2-1/R T
                    the LTP by telecommand.
                    LTP internal software inspection and modification during flight through the LPF S/C OBC shall be possible.
RS 4.3.3.1-1/R T    Adequate safety mechanisms for modifications of LTP internal S/W shall be implemented in the LTP internal
                    S/W.
                    LTP S/W shall be able to receive and accept new S/W parameters via the LPF S/C OBC from ground while an
                    operation phase is running, without interrupting operations. Adequate safety mechanisms for modifications of
RS 4.3.3.1-2 /R T
                    LTP internal S/W parameters shall be implemented in the LTP internal S/W in order not to disturb running
                    procedures and to validate the parameters' evidence.
                    LTP internal software and LTP general design shall support changing LTP missionmodes and mission-profiles
                    at ground-defined times, including periods of no ground visibility, according to the mission definition.
                    Commanding of mode and profile changes will be through the S/C OBC (this can be done using e.g. time-
RS 4.3.3.1-3/R T
                    tagged commands or higher level applications executing, e.g. Macro-Commands or Onboard Control
                    Procedures, to be selected upon principles of simplicity, safety, robustness and economic use of resources).

                    All functions (TBD in detail) that are required for Command and Control of the LTP instrument shall be
                    implemented within the Data Management & Diagnostics Subyystem for all S/C Modes with some exceptions
                    concerning the IS FEE. The C&C Router shall handle all TCs received from the OBC and all TM data to the
                    OBC. The module shall precompile telemetry packages relevant to LTP operations and route them to the
                    OBDH for storing and later downlink.
RS 4.3.3.2-1/R T
                    Note:
                    Which functions specifically have to be implemented is TBD in detail, including potential split in responsibility
                    between S/C OBC and LTP DMU (compare initial note of the current Chapter). This requirement is more
                    meant in a way that those functions to be handled on LTP level shall be implemented in the DMU (and not
                    elsewhere inside LTP).
                    All functions (TBD in detail) that are required for Optical Metrology Subsystem operations including Laser
                    Assembly Laser frequency stabilization, Optical Pathlength Stabilization, and Phasemeter digital signal
RS 4.3.3.2-2/R T
                    acquisition and postprocessing shall be implemented in the DMU. The OMS Manager module shall be able to
                    process the raw Optical Metrology signal and deliver, in SCIENCE mode
                    All LTP functions interfacing with SCM control include Drag Free Control, Charge Management, Sensing,
RS 4.3.3.2-3/R T
                    Actuation, and Low Frequency Suspension only.
                    Data and Diagnostics Subsystem software shall support the charge management control and the UV lamp
RS 4.3.3.2-4/R T
                    operational control based on software control being performed by S/C OBC.
                    Data and Diagnostics Subsystem software shall perform Data processing from diagnostics boards:
                    § Magnetometer
                    § Radiometer (TBC)
RS 4.3.3.2-5/R T    § Radiation monitor
                    § Magnetic coil drive
                    § Heaters drive
                    § Laser diagnostics
                    Data and Diagnostics Subsystem software shall drive the required excitation of the Test Mass by external
                    forces. It includes:
RS 4.3.3.2-6/R T    · Magnetic coil drive
                    · Heaters drive
                    · Others (TBD)
RS 4.3.3.2-7/R T    The peak usage of the on-board processor shall not exceed 75%.
RS 4.3.3.2-8/R T    The peak usage of on-board RAM and EEPROM shall not exceed 75%.
RS 4.3.3.2-9/R T    The predicted OBC processor utilisation at PDR shall be less than 50%
RS 4.3.3.2-10/R T   The predicted usage of on-board RAM and EEPROM at PDR shall be less than 50%
                    The DMU SW shall provide the following services to comply with its function as per RS 4.3.3.1.1-1 (LTP C&C).
RS 4.3.3.2-11/R T
RS 4.3.3.3-1/R T    The thermal controller module shall autonomously control all LTP elements
                    The CMA (Caging Mechanisms Assembly) Manager shall be able to apply the realcontrol law used for detailed
                    actuation of the separation system. The CMA Manager shall be able to autonomously implement the control
RS 4.3.3.3-2/R T
                    sequence necessary to release the Test Masses from their caged state to the free-floating state as per the
                    definition of the POSITIONING mode
                    The CMS (Charge Management Subsystem) module shall be able to command the application of a voltage
                    dithering on the voltage test masses TBC to measure the charge. The CMS module shall be able to use and
RS 4.3.3.3-3/R T    process the output of the voltage / position readings from the IS TM control (DFACS). The CMS module shall
                    include a logic able to autonomously decide the necesssity for, and magnitude of, possible discharge actions.

                    The LTP Mode Logic module shall keep track of the actual health status of all the hardware units required for
                    any mode start. The LTP Mode logic module shall provide an internal safety logic to autonomously prevent
RS 4.3.3.3-4/R T
                    inadvertent commanding of forbidden or unsafe LTP or LTP subsystems mode transitions.

                    The Data Management module's main function shall be to compile the LTP data reported from the C&C router
RS 4.3.3.3-5/R T
                    module and others from a Software Data Pool.
                    SCIENCE mode shall be operated at "Run" command level. A run is defined as a sequence of operations
                    leading to the performing of a particular, complete experiment. As a goal, Run commands will be implemented
RS 4.3.3.3-6/R T    by means of On-Board Control Procedures residing in the SCM OBDH subsystem as part of the DHSW. On-
                    board procedures are essentially generators of TC's with limited flow control logic and are normally adequate
                    for the purpose of commanding.
                    Operational data exchanges necessary for IS TM Drag-Free control as commanded by the SCM DFACS
RS 4.3.3.3-7/R T    application shall be conducted directly between the LTP FEE and the SCM OBC. This comprises of voltage
                    readings and voltage commands only. (cross refer to LTP IRD)
                    The DMU Basic Software (BSW) shall include Boot Software for Start-Up, Application Interface (API) Software
RS 4.3.3.4-1/R T
                    and – if deemed necessary – the Real-Time Operating System.
                    The Boot SW shall be stored in PROM (with a 50% margin at PDR, and a 25% margin in flight for memory
RS 4.3.3.4-2/R T
                    usage) and shall be executed when the processor is first time powered or is reset.
                    The Boot SW shall provide a Start-Up sequence with the following actions as a minimum:
                    · Log ERC32 registers (for caus of reset detection)
                    · Start Watchdog
RS 4.3.3.4-3/R T    · Perform ERC32 initialisation
                    · Perform ERC32 basic tests
                    · Log test results
                    · Initialize processor HW (memory etc)
                    The ERC32 basic tests shall perform the following actions as a minimum:
                    · ERC32 self-test
RS 4.3.3.4-4/R T    · RAM test
                    · EEPROM test
                    · PROM rest
RS 4.3.3.4-5/R T    Load application SW from EEPROM to RAM, check checksum and raise alarm in case of failure
                    The Boot SW report log shall contain the results of all the tests and shall be stored in memory at a defined
RS 4.3.3.4-6/R T
                    location
                    The Boot SW shall pass control to the application SW after the software has been loaded into RAM
RS 4.3.3.4-7/R T
                    successfully.
RS 4.3.3.4-8/R T    The BSW shall include a Target Monitor to be used only during ground testing
                    The API SW shall be a library of interface routines that will allow the application software to access the
RS 4.3.3.4-9/R T    hardware without having detailed knowledge of the exact HW/SW interface – e.g. for MIL-Std 1553 Bus
                    interfaces, Serial RS422 inerfaces (TBC), Discrete Input and Output Interfaces.
                    The API SW shall be stored in EEPROM with the Application SW, and shall require a maximum of 100kBytes
RS 4.3.3.4-10/R T
                    (TBC) of EEPROM space, with a 50% margin at PDR and a 25% margin in flight.
                    LTP IS Subsystem shall comprise
                    · 2 Inertial Sensor Heads each of which being constituted by the following functional modules:
                    § 1 electrode housing
                    § 1 Test Mass
                    § 1 vacuum enclosure (with autonomous pumping (getter) and optical windows etc.)
                    § the necessary number of (2 TBC) mounting flanges
                    § 1 Caging Mechanism (caging and release mechanism acting in +Z and –Z)
                    · 1 IS FEE implementing:
  RS 4.3.4-1/R
                    § 6 to 7-channel motion sensing front-end electronics (FEE) per IS Head
                    § 12 to 14-channel actuation AC and DC voltage generator per IS Head
                    § 1-channel injection per IS Head
                    § interfaces to DMU and S/C , especially a DFACS data related data bus in/out
                    · 1 Caging Control Unit containing the circuitry to drive motors of the Caging Mechanism with associated
                    power supplies and control electronics.
                    · 1 UVLA including the necessary number of UV lamps and optics together with associated power supplies
                    and control electronics.
                     The test mass (TM) has to perform the following functions:
                    · It shall serve as the end mirror for the optical metrology interferometer
 RS 4.3.4-2/R T     · It shall be the reference body to perform the S/C translation and attitude control (as specified in Chapter
                    TBD).
                    · The TM has to accommodate the requested interface features to the CM.
                 The electrode housing shall:
                 · host the appropriate set of electrodes to allow for the capacitive sensing of the motion of TM along all DOF
                 and to apply the required forces in line with the needs of the DFACS,
                 · host a proper set of bias electrodes to allow to ac-bias the TM,
                 · host the proper holes for allowing the input/output of the laser beams along x,
                 · guarantee proper mechanical and electrical accuracy to allow for aligning the TM by electrical forces as
                 requested by optical metrology operation:
RS 4.3.4-3/R T   a) during optical metrology initialization
                 b) during science operation,
                 · guarantee proper mechanical accuracy and stability to allow aligning the TM as requested for testing optical
                 metrology operation on ground,
                 · host the requested features for caging the TM,
                 · transmit and withstand the caging mechanism loads,
                 · host the proper interface for allowing UV-light carrying optical fibers to illuminate the TM and the selected
                 surfaces with the requested UV light intensity.
                 The Front End Electronics (FEE) has to perform the following functions:
                 · biasing the TM with the requested ac-voltages,
                 · detecting capacitance variation between the TM and the proper set of electrodes,
                 · applying the selected voltages to the electrodes to perform actuation for:
                 o TM initial capture after release from CM
                 o TM attitude and position control
RS 4.3.4-4/R T   o TM charge detection
                 o DC-voltage compensation,
                 · A/D- and D/A-converting signals from and to the LTP controller/computer and the S/C OBC,
                 · biasing the caging mechanism plunger in contact with the TM, when this is caged but not in contact with any
                 of the electrodes or housing, to allow for position detection and initial acquisition of TM,
                 · allowing the measurement of diagnostics parameters on the FEE itself for science data debugging
                 · provide HK information to the LTP DMU.
                 The vacuum enclosure shall:
                 · guarantee the proper vacuum during science operation,
                 · guarantee the proper vacuum during integration and testing,
                 · provide for all the mechanical interfaces of the IS
                 · guarantee proper mechanical accuracy to allow for aligning the TM as requested by optical metrology
                 operation:
                 a) during optical metrology initialization
                 b) during science operation,
                 · guarantee proper mechanical accuracy and stability to allow aligning the TM as requested for testing optical
RS 4.3.4-5/R T
                 metrology operation on ground,
                 · provide for the caging mechanism mounting points,
                 · carry the vacuum feed-through connectors for the FEE cables, CM actuator cables, and any other diagnostic
                 sensors located inside the VE (e.g. pressure sensor, CM monitoring, magnetometer heads (TBC),
                 thermometers, heaters, etc.)
                 · allow laser beam from optical metrology to reach the TM faces through optical windows
                 · carry the interfaces for the UV fibers inlet to the vacuum enclosure
                 · carry the mechanical interfaces to the balance masses required to null the gravitational fields and its gradient
                 tensor
                 The charge management system shall perform the following main functions:
                 · measure the charge accumulated on the TM because of cosmic rays; this function is performed:
                 a) by applying a dither voltage to a proper sub-set of the available electrodes via the FEE and
RS 4.3.4-6/R T
                 b) by measuring the motion of the TM, as available from the FEE, at the frequency of the dither.
                 · illuminate the TM and selected parts of the electrode housing with amplitude regulated UV light so that the
                 extracted photoelectrons neutralize the TM.
                 The Caging Mechanism shall perform the following multiple functions:
                 · cage the TM in a safe position during the launch,
                 · release the TM at the beginning of the measurement (commissioning) phase, i.e. transition from launch lock
                 mode to free floating mode of TM
                 · re-capture (grabbing) the TM everywhere and from whatever orientation within the electrode housing and
RS 4.3.4-7/R T   bring it to a safe position.
                 · Re-centering the TM in the electrode nulling position during in-orbit operational phases
                 · holding the TM in an position suitable for in-flight and on-ground optical metrology testing,
                 · hold and position the TM during ground testing and handling in a safe position
                 The total failure of one CM (e.g. for TM 1) shall not influence / reduce the information, which can be provided
                 by the other test mass (e.g. TM 2) for the operation of the DFACS
                 The Optical Metrology Subsystem (OMS) shall comprise all major hardware elements required to perform
                 following functions:
                 - Mechanical support of two Inertial Sensor Heads
                 - measurement of the relative displacement between the two Test masses (TM) along the measurement axis
                 (main science measurable; called x2-x1)
RS 4.3.5-1/R T   - measurement of the motion of one Test Mass (labelled TM1) relative to A defined point on the Optical
                 Bench, i.e. relative to the S/C
                 - measurement of the relative angular motion between the Test-masses about two axes (? ? and ? ?in Figure
                 4.1-1)
                 - measurement of the relative angular motion of TM1 versus an OB Reference system (resp. vs. S/C) about
                 two axes (? ? and ? ?in Figure 4.1-1)
                  The LTP Optical Metrology Subsystem shall be constituted by the following functional modules:
                  · the Laser Assembly with
                  § 1 Laser Unit
                  § 1 Acousto-Optical Modulation Unit (including 1 beam splitter, 2 AOMs and 2 OPDAs)
                  § AOM and OPDA control electronics
                  § LA Harness
 RS 4.3.5-2/R
                  · the Optical Bench with
                  § 4 two-beam interferometers
                  § photodiodes (8 quadrants and 2 single-elements)
                  § mechanical supports
                  § harness
                  · the Phasemeter Front End Electronics
                  ########################################################################################




RS 4.3.5-3/R T




                  The optical bench shall:
                  · carry all the optical components needed to implement the interferometry,
                  · support 8 quadrant photodiodes that collect the light and generate the interferometer output signals,
                  · support 2 single-element photodiodes for laser power monitoring
                  · include 4 interferometers based on quadrant photo-diodes, in detail:
                  o two for the metrology proper,
RS 4.3.5-4/R T    o one for phase-reference, and
                  o one for laser frequency noise measurement
                  · provide the mechanical interface for both IS
                  · guarantee the proper alignment tolerances for the use of the IS TM as the OMU end mirrors during:
                  o ground testing
                  o in-flight initialisation
                  o science operation
                  The LTP interferometer as part of the OB shall:
                  o use a non-polarizing interferometer with non-normal incidence
                  o use heterodyne Mach-Zehnder interferometry
RS-4.3.5-5/R I
                  o allow unequal pathlengths and include a frequency stabilization
                  o make optical paths otherwise as similar as possible.
                  o minimize pathlength in transmission through optical components.
                  Four interferometers shall be implemented on the OBA:
                  1. x1 - x2 shall provide the main measurement: the distance between the two test masses and their differential
                  alignment.
RS-4.3.5-6/R I    2. x1 shall provide as auxiliary measurement the distance between one test mass and the optical bench and
                  the alignment of that test mass.
                  3. Reference shall provide the reference phase for x1 - x2 and x1.
                  4. Frequency shall measure laser frequency fluctuations with intentionally unequal pathlengths.
                  The phasemeter frontend shall provide interface to the 8 quadrant diodes at the OB:
                  1. Accept 32 channels of analogue photodiode current
                  2. Provide stabilized bias voltage to the photodiode of no more than 5 V (TBC)
                  3. Produce raw output data (single bin discrete Fourier transform output) at 100 Hz data rate (TBC) for each of
                  the 32 channels to be further processed in the DMU (phasemeter backend)
RS 4.3.5-7/R T    The phasemeter shall be compatible with:
                  1. Heterodyne frequency between 500 and 5000 Hz
                  2. An optical power on the photodiodes of 1 mW (nominal operation) to 2 mW (absolute maximum rating)
                  3. A fringe rate of up to 40 Hz without loosing track of the integer number of fringes (corresponding to a
                  testmass motion of 20 µm/s). Reduced noise performance is allowed at this speed.

                  The OB shall be delivered with fibre-launchers fixed and aligned and ready to accept the fibre connectors from
RS-4.3.5-8/ R I
                  the LA
RS-4.3.5-9/ R I   The Laser Assembly shall be delivered with optical fibres and harness.
                  The optical signal from laser head to AOMU and from AOMU to OB respectively will be delivered by fibre
                  optical connections. For these connections the following components shall be adopted:
RS-4.3.5-10/R I
                  Fiber: polarization maintaining fiber Fujikura PANDA SW.98-P-6/125UV/UV-400
                  Connector: Diamond AVIM PM8°
RS-4.3.5-11/R I   Phasemeter front end electronics shall be delivered with harnesses.
                  The electrical interface between the phase meter and each four-quadrant photodiode on the optical bench
RS-4.3.5-12/R I   shall consist of a shielded 5-thread cable with a nano-D connector on the diode side and a sub-D connector on
                  the phase meter side (TBC).
RS-4.3.5-13/R T   The Data and Diagnostics Subsystem shall perform the Laser Assembly diagnostics tasks.
                     The Data and Diagnostics Subsystem shall be composed of the following main functional modules:
                     · the Data Management Unit (DMU), accommodating
                     § Processor Control board
                     § the Phasemeter back-end (reduced to PM data acquisition and SW task)
                     § and the DMU DC/DC conversion block
                     · Diagnostic Units, in detail:
                     § Two 3-axes Magnetometers
                     § Radiation Monitor (former Particle Counter)
                     § high precision Thermometers
   RS 4.3.6-1/R      § high precision Heaters for:
                     · optical fiber heating to adjust for OPD (tbc, only an option)
                     · and others within the LCA (specified herafter)
                     § Two sets of 3-axes Magnetic Coils
                     § Diagnostics Harness
                     · Software to operate all the above elements on functional level, defined as “The LTP software resident on the
                     LTP DMU (DMU SW)”
                     · Software to operate the whole LTP, being the LTP controller for Command & Control performing the LTP
                     TM/TC to /from the S/C OBC
                     · DDS harness to the LTP internal users
                     The DMU SW shall perform the following tasks:
                     · Optical metrology final data processing (Phasemeter Back-end function)
                     · Laser frequency stabilisation and optical path difference (OPD) stabilisation
                     · Thermometers data processing
                     · Magnetometer data processing
                     · Particle detector data processing (TBC. this item may be part of the S/C)
  RS 4.3.6-2/R T     · data processing to operate the diagnostics elements:
                     § magnetometer,
                     § radiometer (solar pressure fluctuation),
                     § Radiation Monitoring (particle detector),
                     · The software needed to drive the required excitation of the TM by external forces. It includes:
                     o Magnetic coils drives
                     o Heaters drive
                     The Data and Diagnostics Subsystem DMU shall provide the LTP data and command I/F to the S/C
  RS 4.3.6-3/R T
                     computer..
                     The Data and Diagnostics Subsystem DMU shall provide the command and control interfaces for the following
                     LTP equipments:
                     · IS CCU,
  RS 4.3.6-4/R T     · IS UVLA,
                     · IS FEE SAU.
                     · Phasemeter
                     · Laser Assembly
                     The Data and Diagnostics Subsystem DMU shall manage and command the creation of the following
                     controlled perturbations:
                     o oscillating magnetic field and gradient on TM (using the magnetic coils being attached to the IS vacuum
  RS 4.3.6-5/ R T
                     enclosure)
                     o oscillating heat flux at selected places on optical bench and inertial sensors (the latter using the DMU
                     heaters being attached to the electrode housing of IS)
                     The Data and Diagnostics Subsystem DMU shall provide the drives for:
  RS 4.3.6-6/R T     · the magnetic coils
                     · the heaters.
                     The DMU software shall support the S/C OBC in charge management control to an extend operating the UV
RS 4.3.6-7/R T TBC   lamp with command distribution from the S(C OBC at a rate of 1 Hz and TM acquisition at a rate of 1 Hz

                     The DMU software shall support the S/C OBC in the caging and de-caging control management to an extend
RS 4.3.6-8/R T TBC   with command (also as macro-command) distribution from the S/C OBC at a rate of 1 Hz and TM acquisition
                     at a rate of 1 Hz
                     The DDS Command & Control functions shall apply the Packet Utilisation Standard with selected PUS
  RS 4.3.6-9/R T
                     services from / to the S/C OBC
                     The DDS shall perform acquisition of LTP HK data and perform monitoring of essential parameters for
 RS 4.3.6-10/R T     anomalies (out of bounds and anolog / digital status signals). These essential data are to be identified on LTP
                     subsystems according to their needs for health monitoring
 RS 4.3.6-11/R T     The DDS shall create an event report in case of an identified anomaly
                     The Data and Diagnostics Subsystem shall perform the following DDS internal tasks:
                     · It shall comprise the Power Conditioning for the data and diagnostic subsystem.
                     · It shall perform the data and diagnostic subsystem internal housekeeping data acquisition and monitoring.of
 RS 4.3.6-12/R T
                     their essential HK data subsets and shall report anomalies in an event report
                     · It shall comprise calibration and validation circuitries allowing for calibration of the different measurements.
                     The high precision temperature measurement and high precision heating shall be performed at least at:
                     · locations on each inertial sensor
                     · locations on the optical bench
                     · locations on the LTP/Spacecraft mechanical interface
                     · according to RD 34 above, listed and shown in positions indicated below in Figure 4.3-6: and Figure 4.3-7.
                     (these positions are to be consolidated after thermal analysis with the System Architect)
                     Note on optics related thermistors and heater positions (reference in RD 34):
                     Temperature sensors should be placed at points where thermal fluctuations result in potential damage to LTP
                     measurement performance. A total of 5 temperature sensors should be placed in the Optical Bench, see
 RS 4.3.6-13/R T     Figure 4.3-6:
                     · One in the optical fibre inlets
                     · Two in diagonally opposite photodiode sets
                     · Two in other points of the optical bench, as far as possible from the rest
                     8 more thermometers are required:
                     · Two thermometers near each optical window, for a total of four
                     · Four in the struts’ attachments
                     The following heater positions are required, see Figure 4.3-7:
                     · Two per optical window, on diametrically opposite sides of lens, for a total of four
                     · Two more in each side slab, for a total of four: one in strut attachment and one near the centre of the slab.
                     A 3-D magnetic field measurement shall be performed at least at two positions as close as possible to the
 RS 4.3.6-14/ R T
                     inertial sensor.
                     The Data and Diagnostics Subsystem shall host the front-end electronics for all diagnostic items. An exception
                     from this RQMT is:
 RS 4.3.6-15/ R T
                     From magnetometer harness length restrictions it might be necessary that the two related E-units need to be
                     separately mounted to the S/C walls near to each of the IS Heads as separate boxes (tbc)
  RS 4.3-7.3         covered by RS 4.3.7.-4
  RS 4.3.7-4         deleted
  RS 4.3.7-7         covered by RS 4.3.7-8
  RS 4.3.7-10        deleted
 RS 4.3.7-12         covered by RS 4.3.7-2
  RS 4.3.7-13        covered by RS 4.3.7-12
RS 4.3.7-14…16       deleted, covered by AIE subsystem spec
RS 4.3.7-17…19       covered by RS 4.3.7-15…17
 RS 4.3.7-20         deleted
                     The Assembly and Integration Equipment shall be constituted by the following main functional modules:
                     · the Thermal Shield (including TS Support Structure & Thermal Equipment)
  RS 4.3.7-1/ R      · LCA Support Structure
                     · Gravitational Balance Equipment

                     The LCA Support Structure and the Thermal Shield shall provide the mechanical and thermal interface
  RS 4.3.7-2/R
                     interface between the S/C and the LTP Core Assembly (LCA).
                     The design of both, the LCA support structure and the TS support structure shall consider symmetric mass
  RS 4.3.7-3/ R
                     distribution w.r.t. the YZ plane of the Science Module axes system.
                     The LCA Support Structure shall be composed of:
                     · Struts including fixation provisions (screws, washers, etc.)
  RS 4.3.7-4/ R
                     · LCA Brackets (Brackets between struts and Optical Bench side walls) incuding fixation provisions
                     · I/F Brackets (Brackets between struts and S/C support walls) including fixation provisions
                     The design of the LCA Support Structure shall aim for an optimum between the two contradicting
                     requirements a) to minimise thermo-mechanical deformations of the LCA (OB), and b) to reduce LCA rigid
 RS 4.3.7-5/ R T
                     body motions according to DFACS needs. The design shall also withstand the launch loads without any
                     buckling, permanent deformation, slippage or gapping.
                     The design of the LCA Support Structure shall consider minimisation of the conductive heat transfer between
 RS 4.3.7-6/ R T     the S/C and the LCA, i.e. the total thermal conductance of the LCA Support Structure (between the Optical
                     Bench I/F and the S/C support walls I/F) shall be lower than 5*10-3 W/K.
                     The thermal capacity of the LCA Support Structure shall be maximised as far as possible, i.e. within the frame
  RS 4.3.7-7/R
                     of other design constraints such as mass and conductivity.
                     The design of the LCA support structure shall consider translational and rotational adjustment capabilities (for
 RS 4.3.7-8/ R T     assembly & integration in the S/C) at both LCA support structure internal I/Fs (strut – LCA bracket, strut – I/F
                     bracket).
                     The Thermal Shield shall be composed of:
                     · The LCA Thermal Shield Support Structure (framework) including rivets, bolts, etc. for connection of
  RS 4.3.7-9/R
                     structure elements and for fixation at the S/C inner cylinder and the LCA support walls
                     · The Thermal Shield MLI (insulating foils) including grounding and fixation equipment
                     The design of the Thermal Shield shall take into account the overall integration procedure for the LCA, i.e.
 RS 4.3.7-10 /R
                     allow TS integration consistent with struts and harness integration.
                     The Thermal Shield shall support the thermal stability required for the LCA operation, i.e. the attenuation w.r.t.
RS 4.3.7-11/ R T A   external disturbances at S/C level has to be maximised. For this purpose the effective emissivity shall be <
                     0.03 (TBC by thermal analysis on LCA level).
                     The Thermal Shield shall provide the proper interface to route the optical harnesses for:
 RS 4.3.7-12/R T     · fibers from UV lamps to IS housing
                     · fibers from Laser Assembly to Optical Bench
                     The Gravitational Balance Equipment shall be composed of
 RS 4.3.7-13 /R      · Gravitational Balance Mass and
                     · Fixation provisions to attach the Gravitational Balance Mass to the IS Head
                     The location and the mass of the Gravitational Balance Equipment have to be defined by gravitational
  RS 4.3.7-14/R
                     analyses on LCA and S/C level.
                     The external balancing mass shall cope with limitations in available space for VE internal balancing masses
  RS 4.3.7-15/R
                     and with late changes on S/C level taking place after IS manufacturing.
                     The Gravitational Balance Equipment shall minimize gravitational static fields and gravitational gradients
                     resulting from remaining LCA mass imbalances, which cannot be compensated by the IS internal balancing
RS 4.3.7-16/R T A
                     masses, to fulfil the requirements for the TM as defined in RS 4.5.1-31 and RS 4.5.1-25 (TBC).
                         The Gravitational Balance Equipment shall minimize gravitational static fields and gravitational gradients
                         resulting from remaining LCA mass imbalances, which cannot be compensated by the IS internal balancing
 RS 4.3.7-17 /R T A      masses, to fulfil the requirements for the TM gravitational gradients resulting from remaining unsymmetrical
                         S/C mass distribution around LTP to the limits defined by RS 4.5.1-31 and RS 4.5.1-25 (TBC).

                         The Inertial Sensor Subsystem must achieve the noise acceleration performance, relative to a free falling
                         frame (inertial system), whose Amplitude Spectral Density (ASD; being the square root of the Power Spectral
                         Density) is less than




RS 4.4-1/ A T (partly)



                         in the range 0.1 mHz = f = 0.1 Hz
                         f is the frequency of the measurement.
                         Relaxation from this performance can be accepted only if due to the different test environment of LPF
                         compared to LISA




    RS 4.4-2/A T




                         No LTP instrument design feature must be introduced that permanently suppresses the sensitivity to one of
    RS 4.4-3 / R
                         the disturbances that may affect LPF.
                         Drag-free and actuation control schemes must guarantee that all disturbances that affect LPF TM are
                         detectable at the required levels on LTP.
                         The following main force noise sources [AD1] are identified to be the performance drivers for the various
                         intended measurement modes defined in Chapter 6.2:
                         - is readout displacement noise being converted into A force noise via the drag-free control loop and the
                         difference between parasitic stiffness that couples both TM to the S/C (in mode M3 for TM1 only, in mode M1
                         IS2 sensor noise is converted into a force noise via the low frequency suspension gain)
                         - Correlated part of readout back-action (readout noise from disturbance sources, that produce a back-action
                         force at readout, is called correlated if the back-action force causes both, an additional displacement noise
    RS 4.4-4 / R         and a direct force disturbance onto the TM)
                         - Uncorrelated part of readout/actuation back-action (back-action forces from readout that have no
                         displacement noise as counterpart and actuation force noise)
                         - forces due to Thermal effects within the is
                         - Thermal noise due to various dissipation mechanisms
                         - Cross-talk between various is axes, i.e. forces applied to different DOF that leak into the sensitive axis
                         - Magnetic disturbances within S/C and due to interplanetary field fluctuation
                         - RANDOM charging. force shot noise
                         - Laser radiation pressure fluctuation
                         - fluctuation of local gravitational field




   RS 4.4-5/ A T
RS 4.4-6/ A T
RS 4.4-7/ A T




RS 4.4-8/ A T




 RS 4.4-9 / A




RS 4.4-10/ A T




 RS 4.4-11/A



                 Operation of low frequency suspension (lfs) in Mode M1 (see Chapter 6.2 for mode definition) shall be
                 possible with an open loop gain resulting in:


RS 4.4-12 /A




RS 4.4-13/ A T
 RS 4.4-14/ A T



                    The requirements derived from System level driven pre-conditions as being stated in this Chapter shall be
                    fulfilled taking into account all subsystem individual contributions. Thus for the development of the subsystems
  RS 4.5.1-1/R
                    these requirements form a-priori conditions, depending on fields generated anywhere on the S/C.

  RS 4.5.1-2 /T     Each test-mass (TM) shall have a nominal mass of 1.96 kg.
  RS 4.5.1-3 /T     Each test-mass shall have a nominal size of 46mm × 46mm × 46mm.



  RS 4.5.1-4 /T




  RS 4.5.1-5 /T




  RS 4.5.1-6/T




 RS 4.5.1-8/A T




 RS 4.5.1-9/A T




RS 4.5.1-10/A T



                    The contractor shall ensure that force noises within the MBW on the LTP testmasses due to down-conversion
                    of magnetic field forces generated inside the spacecraft (including those of the DRS and the LTP), for
RS 4.5.1-11a /A T
                    frequencies above the MBW and below 10 KHz (TBC), shall be within the allocation given to magnetic noise.




RS 4.5.1-12/R T
 RS 4.5.1-13 / T



                    For the purpose of calculating electric force disturbances onto the test-masses due to down-conversion of
 RS 4.5.1-14 / T    fluctuating electric field at frequencies > 50 Hz, it shall be assumed that among electrodes there is a sine-
                    wave voltage at any frequency between 50 Hz and 100 kHz with amplitude of 4 V p.p.
                    The single charge (positive or negative) deposit rate on the TM to be assumed for the LTP design (especially
 RS 4.5.1-15 / T
                    CMS) is Ie = 2000 s-1.
                    The net charging rate, in the absence of any discharging, to be assumed for the LTP design (especially CMS)
 RS 4.5.1-16 / T
                    is Ie = + 2.5×10-17 A..



 RS 4.5.1-17 / T




 RS 4.5.1-18 / T




 RS 4.5.1-19 / T




 RS 4.5.1-20 / T




 RS 4.5.1-21 / T




 RS 4.5.1-22 / T




 RS 4.5.1-23 / T




                    The LFS (low frequency suspension system) shall be able to apply a force and /or a torque to the TM of up to
RS 4.5.1-23a /T A   TBD without exceeding the actuation acceleration noise.
                    Note: applicable for science mode
RS 4.5.1-24/A T
RS 4.5.1-25/ A T




RS 4.5.1-26 / T




RS 4.5.1-27 / T




RS 4.5.1-28 / T
   RS 4.5.1-29 / T




   RS 4.5.1-30 / T




  RS 4.5.1-31/ A T




  RS 4.5.1-32/ A T




                          The Inertial Sensor Subsystem must achieve the noise acceleration performance required for LISA as defined
RS 4.5.2-1/A T (partly)
                          by RS 4.4-1.
                    ########################################################################################




RS 4.5.2-2/ R A T




 RS 4.5.2-3 / T     The mass of each test-mass (TM) shall be as stated by requirement RS 4.5.1-2.
                    Materials used for the Electrode Housing shall comply with RS 4.5.1-12, i.e. they shall be paramagnetic or
 RS 4.5.2-4/R T
                    diamagnetic.
                    CMS design shall comply with the assumed single charge (positive or negative) deposit rates and net charging
 RS 4.5.2-5/A T
                    rates defined by RS 4.5.1-15 and RS 4.5.1-16


 RS 4.5.2-6/A T




 RS 4.5.2-7/A T



                    IS design shall comply with the total force noise requirement RS 4.5.1-24 if relaxations according to RS 4.2.2-
RS 4.5.2-8/A +T     1 apply.
                    Note: H/W level for tests and feasibility of tests TBD.
                    IS design shall comply with the requirement on stiffness contributed by different stiffness sources as defined
RS 4.5.2-9/A +T     by RS 4.5.1-25 if relaxations according to RS 4.2.2-1 apply.
                    Note: H/W level for tests and feasibility of tests TBD.




RS 4.5.2-10/A +T
RS 4.5.2-11/A +T




RS 4.5.2-12/A T     IS generated magnetic field shall comply with RS 4.5.1-26.
RS 4.5.2-13/T A     Gradient of IS generated magnetic field shall comply with RS 4.5.1-27.
                    The second derivative of the IS generated magnetic field shall comply with RS 4.5.1-28.
 RS 4.5.2-14/A
                    Note: H/W level for tests and feasibility of tests TBD.
                    The peak value of the AC magnetic field above the MBW as generated by IS shall comply with RS 4.5.1-29.
RS 4.5.2-15/A T     Note: H/W level for tests and feasibility of tests TBD.

                    The contribution of IS to the system level DC-electric field requirement shall comply with RS 4.5.1-30.
RS 4.5.2-16/A T
                    Note: H/W level for tests and feasibility of tests TBD.
                    The Inertial Sensor Subsystem shall comply with DC force differences ?Fx (y,z) levels defined in RS 4.5.1-31.
RS 4.5.2-17/A T     Note: H/W level for tests and feasibility of tests TBD.

                    The Inertial Sensor Subsystem shall comply with torques levels defined in RS 4.5.1-32.
RS 4.5.2-18/A T
                    Note: H/W level for tests and feasibility of tests TBD.
                    The inertial sensors shall be delivered with:
                    - free-end harness and UV optical Fibres
RS 4.5.2-19/R I
                    - Getter-Pump maintained vacuum inside the VE
                    - TM held in caged mode with tbd limited load on it




RS 4.5.2-20/ R, I




                    The low frequency suspension control loop overall stability shall be = 1%. {Ref. to [RD-29, Chap. 3-8)}.
                    Note:
RS 4.5.2-21/ R, I   This is no req on metrology subsystem nor is it in the hand of LTP alone. Rather it is a req. on S/C Control
                    Laws and S/W. This req. and the location in this document is to be reconsidered. Currently in as placeholder.
RS 4.5.3-1/ A, T




RS 4.5.3-2/ A, T




                   The Differential Wavefront Sensing (DWS) alignment metrology shall produce monotonous valid signals for
RS 4.5.3-3/ A, T   Test Mass misalignments smaller than +/-300 µrad, referred to the DWS alignment metrology zero position.

                    For Test Mass misalignments between +/- 300 µrad and at least +/- 1000 µrad, referred to the Differential
                   Wavefront Sensing (DWS) alignment metrology zero position, the phasemeter DC alignment metrology shall
RS 4.5.3-4/ A, T
                   provide monotonous valid signals indicating the magnitude and direction of the Test Mass misalignment.

RS 4.5.3-5 / A T   deleted
RS 4.5.3-6/ A, T   deleted




RS 4.5.3-7/ A, T




 4.5.3-8/ A, T     deleted
 4.5.3-9/ A, T     deleted
                    The straylight contribution within each interferometer beam shall be attenuated to at least 10-6 of the signal
 4.5.3-10/ A, T
                   amplitude.
 4.5.3-11/ A, T    deleted
                   The processor shall cope with the specified functions from section 4.3.6 keeping a margin of 50% (TBC) for:
                   · computational performance
RS 4.5.4-1/R T
                   · memory sizing

 RS 4.5.4-2/R      Deleted
 RS 4.5.4-3/R




                  See extra notes in Requirements Specification
                  All drawings, specifications and engineering data shall use exclusively the International System of Units (SI
RS 5.1.1-1/R T
                  units), with the exception of gravity.
                   The in-orbit design lifetime shall be 12 months operational plus 4 months of nonoperational. This shall also
 RS 5.1.2-1/ R
                  concern all consumables, if any required
                  The LTP shall be designed such that it can be stored after delivery to S/C on ground for at least 1 year, under
RS 5.1.2-2/ R
                  controlled environment conditions, with minimum need for preventive maintenance.
                  The possibility to have for the IS an ionic pump connected to the vacuum enclosure shall be considered.
                  Note:
                  Currently during the LTP-S/C integration phases, at least 3 TBC months before launch, the vacuum inside IS
 RS 5.1.2-3/ R
                  Vacuum enclosure shall be re-pumped the last time by means of an ionic pump. TBC shall be removed after
                  the EM test in progress.

                  The LTP hardware shall be designed to achieve reasonable robustness and a high probability of flight mission
RS 5.1.3-1/ R
                  success. No numerical reliability figure shall be established
RS 5.1.3-2/ A     deleted
                  It shall be possible to reconfigure the instrument to be fully operational after a single failure wherever possible.
                  Redundancy shall be implemented wherever possible up to the Test Mass.
                  Note:
RS 5.1.3-3/ R A
                  Physical limitations, e.g. for IS, that cannot be easily avoided by alternative designs, may compel
                  compromising the requirement. This shall be justified case-by-case and shall be discussed with Industrial
                  Prime and if necessary with LMO.
RS 5.1.3-4/ R     If single point failures cannot be avoided, it shall only be implemented after approval of the Agency.
RS 5.1.3-5/ A     Failure propagation from one function to another shall be avoided.
RS 5.1.4-1/ A     Failure propagation from one function to another shall be avoided.
                  The LTP equipment shall be designed in such a way that any failure cannot be propagated inside the unit (e.g.
RS 5.1.4-2/R A
                  to redundant chain).
                  The LTP equipment shall be designed in such a way that any failure cannot be propagated inside the unit (e.g.
RS 5.1.4-3/R A
                  to redundant chain).
                  The equipment shall be designed in such a way that nominal and redundant functions are electrically
RS 5.1.4-4/R T
                  separated, i.e. use separate electrical components.
                  The LTP design minimise, to a reasonable extent, single point failures. If single point failure exists, it shall be
RS 5.1.4-5/R A    clearly identified together with all the necessary precautions required to minimise its consequences.

                  Redundant functions located in the same housing shall be separated by a metallic wall to prevent failure
RS 5.1.4-6/R A
                  propagation due to thermal or EMC effects.
                  All LTP constituents subject to planned maintenance shall be designed, selected and installed to facilitate the
RS 5.1.5-1/ R     execution of such tasks with minimum hazard to the equipment and personnel. The design shall provide
                  maximum use of standard tools and test equipment.
                  The LTP shall be designed such that it routine checks and maintenance operations will not be required later
RS 5.1.5-2/ R
                  than 3 months before launch.
RS 5.1.5-3/ R     Identical units shall be exchangeable.
                  The LTP equipment shall be designed to minimize the generation of loose particulate matter or liquid or
                  gaseous contamination. The hardware shall be manufactured, handled and controlled within an environment
RS 5.1.6-1/ R
                  of increased cleanliness and low contamination levels. Outer surfaces shall be cleaned to a level “visible
                  clean” and shall require standard cleaning equipment only.
RS 5.1.6-2/ R     The environment during assembly of the equipment shall meet class 100.000.
                  Particulate contamination shall not exceed 200 ppm (TBC) at instrument delivery on sensitive optical surfaces.
RS 5.1.6-3/ R I
                  Other surfaces shall be visibly clean. The cleanliness shall be controlled according AD 04.
                  Molecular contamination shall not exceed 1*10-7 (TBC) at instrument delivery on sensitive optical surfaces.
RS 5.1.6-4/ R I
                  Other surfaces shall be visibly clean. The cleanliness shall be controlled according AD 04.
                    Each unit shall be designed to withstand a radiation exposure that is twice the expected radiation environment
                    during the mission (i.e. RDM = 2). This applies to all types of radiation damage, including ionising dose (total
RS 5.1.7-1/R TBC
                    and low dose) and displacement damage. A protective shielding by the outer panels of the satellite of 1 [TBC]
                    mm Al equivalent shall be assumed.
                    The component shall be designed to tolerate proton and heavy ion induced SEEs in accordance with the
                    particle flux as given in Figure TBD. Parts subject to SEE shall be analyzed and/or tested for latchup and/or
RS 5.1.7-2 /R TBC   SEU. Where EEE parts are not compliant with the radiation requirements specified in this section, the design
                    must compensate for or tolerate the effects (e.g. by latch-up switches and/or autonomous software recovery
                    methods).
RS 5.1.7-3 /R TBC   deleted
                    Single Event Latch-Up (SEL): Microcircuits containing CMOS technologies shall be evaluated to withstand an
RS 5.1.7-4 /R TBC   LET greater than 60 MeVcm2/mg without latchup. This requirement is imposed to account for the maximum
                    solar flare activity.
                    Single Event Burnout (SEB) & Single Event Gate Rupture (SEB/SEGR): All power MOSFETs shall be
                    evaluated for SEB and SEGR vulnerability. An LET threshold of 20 MeVcm2/mg for SEB and SEGR shall be
RS 5.1.7-5/R TBC    considered insensitive. For SEB and SEGR vulnerability, further radiation hardness assurance shall be
                    achieved by derating to less than 75% of the voltage at which the SEB/SEGR occurred at 20 MeVcm2/mg.
                    This range may very from 60%-75%, depending on the specific part and vendor used.
                    The units shall be able to operate within a pressure range of 1 bar to 1*10-10 mbar. It shall have a suitable
                    venting provision compliant with above pressure range and variation of fairing static pressure during ascent
                    phase as defined by the GDIR. A typical value is 2 mm² venting hole area per litre volume (except IS). Out
RS 5.1.8-1/R TBC
                    gassing vents shall be < 5mm diameter and shall be located closest to but not within the unit mounting plane.
                    For EMC reasons, there shall be no other openings than necessary for connectors and venting holes.

  RS 5.1.9-1/R      deleted
                    The units shall be designed to withstand a relative humidity of 60% maximum during testing and transport (no
  RS 5.1.10-1/R
                    condensation is allowed ). TBC
                    Each LTP element shall include a mass contingency margin, depending on its development status, as follows:




 RS 5.2.1-1/R A




                    Total LTP mass shall not exceed 100 kg including margin. The mass allocation to S/Ss is




  RS 5.2.1-2/R




                    The mass of the LTP elements shall be controlled such that all masses are known to accuracy better than
  RS 5.2.1-3/A T    0.5% (TBC) of the final mass for gravitational control purposes. The final mass is understood as in-orbit mass,
                    any difference shall be indicated.
                    The location of the CoG of the main LTP physical blocks, including the Optical Metrology Subsystem, the
  RS 5.2.1-4/A      sensor assembly, and the electronic assembly, shall be known to accuracy better than +/- 0.5 mm TBC.

  RS 5.2.1-5/T      The CoG shall be measured with an accuracy of +/- 0.5 mm (TBC).
                    All LTP components sited outside the SCM central cylinder shall provide their mass distribution with a
  RS 5.2.1-6 /R     granularity of 40 mm, granularity being defined as the minimum size of a constant mass cube in which the
                    item can be discretised with accuracy.
  RS 5.2.1-7 /T     A best engineering estimate of the CoG shall be given latest 2 months after the contract ATP (TBC).
                    The structural interfaces of LTP to the Spacecraft shall be such that the mechanical environmental
  RS 5.2.2-1/T A
                    requirements are fulfilled.
                    The LTP shall be designed against loads as specified in section 8.2: Error! Reference source not found.. The
  RS 5.2.2-2/A T
                    LCA design load are given by Table 8-4: LCA Quasi-Static Requirements.
                    The definitions in [RD31] are applicable. For limit loads (see [RD32]) the probability shall be more than 99%
 RS 5.2.2-3/A R
                    with a confidence level of 95% during the service life.
                    Materials and material A-level properties shall be used in accordance with [RD31]. This requirement is also
 RS 5.2.2-4/A R
                    applicable for the material and material properties of mechanisms.
RS 5.2.2-5/A R




RS 5.2.2-6/ A




                 Fundamental frequencies are defined as structural eigenfrequencies with effective mass greater than 10% of
RS 5.2.2-7/R A
                 the total unit mass..
RS 5.2.2-8 /R    deleted
                 The LTP payload shall achieve a structural stiffness ensuring that the first fundamental frequency of the
RS 5.2.2-9/R     launch configuration with effective mass greater than 10% is at least 140 Hz in hard mounted conditions.

                 The resonance frequencies of compact equipment and boxes (not located at the LTP core) shall be above 140
RS 5.2.2-10 /R
                 Hz in hard mounted conditions.
RS 5.2.2-11 /R   deleted
                 Stiffness margin on every part of the LTP payload shall cover design, material and mass Design
RS 5.2.2-12 /R
                 Requirements uncertainties.
                 The design shall guarantee, under the worst combinations of mechanical and thermal loads as derived from
                 the analysis :
                 a. survival and functionality of the structure
                 b. positive margins of safety for yield and for ultimate loads, such that it shall not result in permanent
RS 5.2.2-13 /R
                 deformation and loss of functionality or rupture
                 c. positive margins of safety for buckling loads, such that it shall not result in buckling or collapse, taking into
                 account a non-perfect geometry of the failing elements.

                 The following structural failure modes, for LTP units at all levels of integration, shall be prevented:
                 · Permanent deformation,
                 · Yield,
                 · Rupture,
                 · Instability,
                 · Buckling,
RS 5.2.2-14 /R
                 · Gaping of bolted joints, of storage devices,
                 · Degradation of bonded joints,
                 · Vibration induced mounting interface slip,
                 · Loss of alignment of units that are subjected to alignment stability requirements,
                 - distortion violating any specified envelope,
                 · Distortion causing functional failure or short circuit.
RS 5.2.2-15 /R   For sine vibrations, the mechanical sizing should be performed with peak values.
RS 5.2.2-16 /R   For random vibrations, the mechanical sizing should be performed with 3 times the rms value.
                 All safety factors shall be applied in accordance with [RD32] and shall be applicable also to subsystems and
RS 5.2.2-17/R
                 equipments.
                 The LTP payload shall be designed to withstand the mechanical loadings encountered during its entire life,
RS 5.2.2-18 /R
                 including ground handling, transportation, testing, launch, and operation phases.
                 The LTP payload must be designed and operated so as to minimise thermal transients and associated thermo-
RS 5.2.2-19 /R
                 elastic structural distortions.
RS 5.2.3-1 /R    The lifetime of a mechanism shall be demonstrated by test in the appropriate environment.
                 The adequacy of the lifetime of Commercial Off the Shelf (COTS) items with respect to the previous
RS 5.2.3-2 /R
                 requirement shall be demonstrated.
                 The contractor responsible for the development of the model shall establish an operation log for tracking of the
RS 5.2.3-3 /R    performed number of operations starting from mechanism level tests onwards. The log shall be maintained on
                 all integration levels by the respective bodies in charge for the level.
                 The CM after delivery to ISS shall be capable of completing the following number of cycles during on-ground
                 integration and testing:

                 On-ground subsystem (ISS) integration and testing:

                 Operations at unit level (in air /vacuum):                                       cycles
                   Caging Mode (launch lock, high preload)                                            5 (tbc)
                   On-Ground Storage Mode (medium preload)                                             5 (tbc)
RS 5.2.3-4/A T
                   S/C Safe Mode /Re-Caging Mode (low preload):                                       30 (tbc)
                   grabbing and positioning/centring incl. centring under 1 g:                        50 (tbc)

                 Operation at LTP system level:                                                cycles
                    Caging Mode (launch lock, high preload)                                         5 (tbc)
                    On-Ground Storage Mode (medium preload)                                          5 (tbc)
                    S/C Safe Mode /Re-Caging Mode (low preload):                                    30 (tbc)
                    grabbing and positioning/centring incl. centring under 1 g:                     15 (tbc)
                 The CM shall be capable of completing the following number of cycles during operation based on a 12 (TBC)
                 month mission life (6 months of LTP plus 6 months of DRS operational time):
                 The minimum number of re-caging operations (deemed necessary only in case of safe mode situations) up to
                 the end of flight operations is at least 15 (TBC, 2 per month during LTP operational phase plus 1 during DRS
RS 5.2.3-5/A T   operations plus contingency). The mechanism design shall comply with this boundary condition.
                 The minimum number of grabbing and re-centering operations at LTP system level shall be at least 360 (TBC;
                 2 per day of LTP operation over 6 months). The mechanism design shall comply with this boundary condition.


                 The LTP payload shall be designed to withstand all thermal environment encountered during its entire life,
 RS 5.3-1 /R
                 including ground handling, transportation, testing, launch, and operation phases.
 RS 5.3-2 /R     The LTP design shall permit analysis by a thermal mathematical model.
 RS 5.3-3 /R     The LTP thermal design shall be testable on ground.
                 The thermal analyses on LTP unit level shall prove that for the temperature limits, as specified in RS 5.3-16
 RS 5.3-4 /R
                 and considering RS 5.3-14, the LTP units provide full performance.
                 The thermal design and analyses shall support the definition of the thermal stability requirements to be fulfilled
 RS 5.3-5 /R     by the spacecraft at the LTP units thermal interface locations for all the applicable mission phases and taking
                 into account the required LTP operational profile.
                 The thermal design and analyses shall also demonstrate that the internal thermal stability requirements of the
 RS 5.3-6 /R     LTP units are fulfilled during all the applicable mission phases and taking into account the required LTP
                 operational profile.
                 Deviations and temporal degradations from the nominal values of external and internal fluxes, thermo-optical
 RS 5.3-7 /R     properties, heat capacitances and conductive and radiative couplings shall be taken into account in the
                 thermal analysis.
                 The use of the ESARAD and ESATAN software packages is recommended for all thermal analyses and it is
                 required for all deliverable interface thermal mathematical models (TIMM, as defined in RS 10.2-3 and RS
 RS 5.3-8 /R
                 10.2-7), excluding geometrical models if not otherwise specified. For time resolved analysis in the frequency
                 domain special tools shall be made available.
                 For verification and validation of the thermal performance of the design selected, analysis results obtained in
 RS 5.3-9 /R     the time domain have to be transferred into the frequency domain by means of spectral analysis tools (Fourier
                 transformation).
                 A thermal reference point located on the unit surface preferably close to a mounting bolt and representing the
RS 5.3-10 /R     unit´s average temperature at the I/F shall be defined and instrumented for all units during ground testing and
                 shall be used for all analyses as “interface temperature”.
                 The thermal control function shall include sufficient thermistors for telemetry with the purpose of evaluation of
RS 5.3-11 /R
                 the performance of the thermal control in-orbit.




RS 5.3-12 /R




RS 5.3-13 /R




                 The design limits of a unit are equal to the qualification limits decreased at both ends by a margin of 10 °C
RS 5.3-14 /R
                 and/or equal to the acceptance temperature limits decreased at both ends by a margin of 5 °C
 RS 5.3-15 /R




RS 5.3-16 /R T A




                   To support the thermal stability required for the LTP Core Assembly (LCA) operation the Thermal Shield shall
RS 5.3-17/R T A
                   have an effective emissivity of eeff< 0.03 (TBC).
                   All electrical performances are specified under Worst-Case End-Of-Life conditions, unless otherwise explicitly
                   notified.
                   Beginning-Of-Life criteria shall be derived by the Unit Supplier from the specified parameters for testing and
  RS 5.4-1 /R      acceptance of all on-board units.
                   Note:
                   All interfaces are referenced by a specific Interface Code. The standard interfaces are listed in AD 03, Table
                   3.5-1.
                   The contractor shall design the load side of the LCL interface to be compliant to the characteristics as defined
 RS 5.4-2/R T
                   in AD3 § 3.5.2.
                   All electronic logic units/circuits shall assume a defined and safe configuration upon application of power in
  RS 5.4-3 /R
                   nominal conditions.
                   All power converters shall work either in free-running or synchronized mode. (TBC – mode will be chosen at a
  RS 5.4-4 /R
                   later stage pending detail assessment)
                   The free-running frequency shall be limited to ± 10% of the nominal frequency. Frequency shall be agreed with
  RS 5.4-5 /T
                   LTP industrial architect.
 RS 5.4-6/R T      deleted
 RS 5.4.1-1/R      Power budgets shall be compiled, in accordance with the guidelines and requirements of AD3 § 3.5.2.




 RS 5.4.1-2 /R




                   Total LTP maximum peak power absorption shall not exceed 185 W including margin.
RS 5.4.1-3/R T
                   (Note that this exceeds the EID-A figure of 150 W max., refer to AD5).
                   For the development of the LTP units and subsystems the power budget (28 V regulated) for LTP shall be
                   applied as provided in the following table (items breakdown and values are TBC)




 RS 5.4.1-4/R




                   The Diagnostics and Data Management System shall be composed of a Data Management Unit (DMU) and
 RS 5.4.2-1 /R
                   Diagnostics End Items.
 RS 5.4.2-2 /R     The DMU shall be designed as a redundant unit.
                   No single failure shall cause the loss of mission, degraded function and/or performance can be tolerated.
RS 5.4.2-3/R T
                   The DMU shall be a box able to host electrical boards:
                   - the so-called PCU for power conversion and distribution to the external LTP is FEE
                   - for LTP Command & control with A processor, memory, and Remote Terminal Interface and its own power
RS 5.4.2-4/R T
                   DC/DC converter
                   - the so-called optical metrology Subsystem (OMS) back-end
                   - and for diagnostic end Items sensors conditioning, data acquisition and processing
                   The DMU main task shall be:
                   · - Interfacing with LPF OBC with MIL STD 1553B I/Fand acquisition of clocks, 1 PPS and 8 MHz
                   - Interfacing with OMS front end with · phasemeter via MIL Bus
                   · Two set point of former analog signals now as digital information via MIL Bus
                   · Six monitor analog signals (I)
RS 5.4.2-5/ R T    · Two fiber actuators. Former analog now as digital information via MIL Bus
                   · Two laser frequency control. Former analog, now as digital information via MIL Bus
                   · TBD Status and control signals (I/O)
                   · distribution of clocks, PPS, 8 MHz ,2clocks for fheterodyne
                   - Interfacing (performing data acquisition and actuation) with the diagnostics subsystem,
                   - Receiving as input two +28V regulated power lines from S/C PCU
 RS 5.4.3-1 /R     The LTP design shall comply with the spacecraft EPSS that will provide a power bus regulated at 28 V.
                   The LTP design shall comply with a spacecraft power bus that will keep its nominal voltage value at the main
                   regulation point within ±0.14 V in steady state. For load transients of up to 50 % of the nominal load, bus
 RS 5.4.3-2 /R
                   transients will not exceed 1 % and the bus voltage will remain within 5 % of its nominal value during all source
                   transients and load transients in nominal operation with a recovery time of 2ms. (TBC)
                   Units shall be designed taking into account the power interface requirements defined in AD3 § 3.5.2 for
RS 5.4.3-3/R T
                   Regulated primary power lines.
                   The LTP design shall comply with a spacecraft regulated bus that will have a nominal ripple voltage in the time
RS 5.4.3-4 /R T
                   domain below 0.5 % peak to peak of the nominal bus voltage.
                   Units shall be designed taking into account the source impedance defined in AD3 § 3.5.2 for Regulated
RS 5.4.3-5 /R T
                   primary power lines.
                   No single point failure in the LTP payload, including failure of wiring and connectors, shall short the main
RS 5.4.3-6 / R A
                   electrical power bus or cause any over voltage.
 RS 5.4.4-1 /R     The local grounding concept of LTP shall be “Distributed Single Point Grounding” (DSPG) system.
                   The user of the primary power shall be prohibited from grounding the power line to structure and shall maintain
                   a DC isolation of at least 1 MOhm between the primary power input leads and chassis and between the
RS 5.4.4-2/ R T
                   primary power input and secondary power.
                   This shall be verified by an isolation measurement.
RS 5.4.4-3 /R T    Equipment EGSE and subsystem EGSE shall reference their structure to the test ground plane.
                   Definition:
                   Power which is transformer isolated from the primary power bus is called secondary power.
                   Equipment containing dedicated power converters shall reference their secondary power return directly to the
RS 5.4.4-4 /R T
                   unit chassis. The bonding resistance shall be <= 5 mOhm.
                   This shall be verified by measurement of the resistance between secondary power ground and unit housing.

                   Signal circuit receivers shall be isolated from secondary power and chassis. The isolation resistance shall be >
 RS 5.4.4-5 /R
                   150 kOhm.
                   Where single-ended signal transmitters are used, independent signal returns are required.
 RS 5.4.4-6 /R
                   Ground reference lines shall not be used as signal returns. Exception: All coaxial cables / connections.
                  The unit bonding resistance between all unit metallic parts shall be < 10 mOhm. The unit shall be delivered
RS 5.4.4-7/R T    with a bonding stud with a resistance < 5 mOhm. The bonding stud shall be a M4 bolt, minimum length is
                  10mm. Small items may provide a grounding insert instead of a bonding stud.
                   Connectors location and harness routing shall be agreed upon between the LPF and the LTP contractors
RS 5.4.5-1 / R
RS 5.4.5-2 / R    Power harness to each LTP unit shall be provided by the LPF Contractor.
                  Non-magnetic connectors and shells shall be used, not used contacts shall be equipped, too. All connectors
                  shall be normal density DxMA types, special connectors or connectors at of-the-shelf equipment may be from
                  other type. In this case, the connector counterpart shall be delivered together with the unit.
                  Cable shields are to be connected to the outside of the box, i.e. via the connector shell. The connection must
                  be of low impedance. A pigtail connection from shield to connector shell is not allowed.
RS 5.4.5-3 /R I
                  In no case it is allowed to route a cable shield via a pin into the unit housing, to be terminated to ground inside.
                  If a high current, low DC impedance termination of the shield is required, the shield may be additionally
                  grounded via a low impedance pigtail wire to the outside of the unit.


RS 5.4.5-4 /R     deleted
                  The LTP software design and development lifecycle shall be based on AD16. This requirement shall be
RS 5.5.1-1 /R
                  applicable for both space and ground segment software.
RS 5.5.1-2 /R     The programming language shall be ADA, C++ or C.
                  The software architecture shall be defined as a series of views using the Unified Modeling Language (UML):
                   Use case view: detailing the most relevant use-cases realisation explaining how the software works and
                  describing the different software elements involved by means of sequence and collaboration diagrams.
                  · Logical view: discomposing the system into packages, and for each package the related software elements
                  that contain and their main functionality and behavior by means of ‘class’ diagrams and state machine
                  diagrams.
RS 5.5.1-3 /R     · Process view: discomposing the system into processes and describing the main modes of communication.
                  · Code view: describes the relationship between the logical view and the actual code (i.e. source files, libraries.
                  . . ).
                  · Data view: describe the data to be stored in the system memory/database, if any.



                  The modeling of thermo-elastic distortions, self-gravity disturbances, optodynamics of the optical metrology
RS 5.5.2-1/ R T
                  system, and the electrostatic actuation system are required.
                  The End-to-End (E2E) simulations shall allow verifying the performance of the complete system (i.e. LTP and
RS 5.5.2-2/R T
                  spacecraft) demanding a highly integrated modeling approach
                  The simulator shall include the drag-free system composed of inertial sensors, the optical metrology, the µ-
RS 5.5.2-3/R T
                  propulsion system, and the onboard computer.
                  Detailed and accurate models of these systems and their disturbances shall be developed. Four rather
                  unconventional models including temporal resolution are required:
                  · Thermo-elastic distortion analysis and its modeling within the E2E simulation.
RS 5.5.2-4/R T
                  · Self-gravity model accounting for thermo-elastic distortions.
                  · Opto-dynamical model of the optical metrology system accounting for thermo-elastic distortions.
                  · 6DOF electrostatic test mass actuation model using 12 electrodes
                  SW Validation shall be performed according to the standards as given in ECSS-E-40A, Software Engineering
RS 5.5.3-1/R T
                  Standard [AD16].
                  The LPF Prime Contractor SVF shall support modular testing, allowing for validation of the individual LPT
RS 5.5.3-2/R T
                  Experiment software modules
                  The LPF Prime Contractor SVF shall allow for Hardware in the Loop testing, and shall include selectable
RS 5.5.3-3/R T
                  software simulation of any LTP units.
                  The LPF Prime Contractor SVF shall include all the features necessary to support both validation tests and
RS 5.5.3-4/R T    acceptance tests of both the Drag Free Attitude Control and the Electrostatic Suspension S/W once integrated
                  on the S/C and the LTP flight processors.
                  The LTP design shall support operations (only through the SCM data and command links to the ground
  RS 6.1-1/R      station) by the LPF Mission Operations Centre (S2MOC). This centre shall do the scheduling and monitoring
                  of the spacecraft, the payload and the stations and shall perform the control tasks.
                  The LTP shall be compatible with all mission phases as defined in Chapter 4.2.2 in the following manner:
                  · In LEOP the LTP shall be maintained in OFF mode.
                  · In TRAN the LTP shall be used in OFF, STANDBY or ACTIVATION mode, able to relay single commands
  RS 6.1-2/R
                  and test sequences.
                  · In IOOP the LTP shall be used in all modes.

                  LTP design shall support all instrument modes commanded from ground or S/C OBC, as long as they are
  RS 6.1-3/R
                  compatible with the operating sequence of the LTP
                  The LTP shall be operated either at single-command level (for commissioning, testing and anomaly
 RS 6.1-4/R T     management), or at “run” level, where a run represents a given experimental protocol, as defined in [AD1].

                  Runs as defined per RS-6.1-4 shall be implemented on-board the OBC via On-Board Control Procedures
 RS 6.1-5/R T
                  (OBCP) TBC as per service 18 in section 4.3.3.1.3.
                   LTP shall be operated in either of the subsequent modes defined in the following table




RS 6.2.1-1/R T




                   The LTP shall support a measurement science mode. This mode shall allow all the functions necessary for the
RS 6.2.1-2/R A T   DFACS modes M1, M3, and M4 indifferently and for the runs 1, 2, 3, 4, 5, 6, 8, 9, and 10 as per [AD01].

                   The LTP shall support a discharge and sensitivity science mode. This mode shall allow all the functions
RS 6.2.1-3/R A T
                   necessary for the DFACS modes M1, M3, and M4 indifferently and for the runs 7 & 10 as per [AD01].
                   The LTP shall support a Joint Ops science mode (TBC). This mode shall allow all the functions necessary for
RS 6.2.1-4/R A T
                   the DFACS mode Joint Ops and for the run 12 as per [AD01].
                  The LTP S/S´s shall support the transitions between LTP modes as depicted in Figure 6.2-1 and Table 6.2-1
                  Note: Nominal transitions are commanded by Telecommands, but may be initialized automatically by fulfilling
                  certain conditions.




RS 6.2.2-1/R T




                  The LTP mode transitions shall be commandable from ground by means of realtime or time-tagged
                  telecommands (if not done automatically)
                  Note:
RS 6.2.2-2/R T
                  Mode transfer is controlled by S/C OBC so that the ground TC primarily goes to this OBC. This requirement
                  shall ensure that LTP itself through its DMU and by its elements is supporting this approach.

                  Autonomous LTP operations shall be restricted to basic start-up sequences initiated from Power-On of the
  RS 6.3-1/R
                  units
                  The DMU shall provide the following on-board autonomy capabilities as a minimum
                  · a reliable boot up sequence
                  · DMU/DDS (re)configuration after boot up/re-boot
 RS 6.3-2 /R
                  · DMU/DDS initialisation
                  The start up sequence shall end up in the DMU Switch On/Software Maintenance Mode
                  Note: Transitions to higher modes are commanded by Telecommands
                  The LTPA shall provide detection of the anticipated failures which are credible and have major consequences,
RS 6.4.1-1/ R T   and report the results to S/C OBC. Ltp shall provide the execution of pre-defined failure isolation controlled by
                  S/C OBC.
                  The LTPA shall provide recovery from the credible anticipated failures with major consequences. Recovery
                  shall be achieved by (in order of preference):
RS 6.4.2-1/ R T
                  1. selection of redundant functional paths
                  2. selection of alternative operational modes
                  Failures, configuration changes, recoveries, and recovery attempts shall be recorded and included in the
RS 6.4.3-1/ R T
                  status telemetry data.
RS 6.4.4-1/ R T   It shall be possible to inhibit and by-pass automated functions by external commands.
                  Following failure detection, the on-board system shall verify that this is not caused by a failure of a sensor or
RS 6.4.5-1/ R T
                  the failure detection.
 RS 6.5-1 / A     deleted
RS 6.5-2 / R T    In case of a failure, restoring to operational mode shall be performed by redundancy switching.
                 The overall LTP envelope dimensions (without its mounting elements e.g. struts to S/C) shall be:
                 · x = 640 mm
                 · y = 375mm
                 · z = 375 mm
                 The LTP accommodation envelope is shown in Figure 7.1-1.




RS 7.1.2-1 /R




RS 7.1.2-2 /R    deleted
RS 7.1.2-3 /R    The dimensions of each LTP item shall be known to accuracy better than TBD mm. (0.5 mm TBC).
                 For the preliminary determination of the requested number of bolt for the attachment of a LTP unit to the S/C,
RS 7.1.3-1/T A   it will be considered that under a 1g environment in any direction, the tensile load per interface bolt of that unit
                 shall not exceed 10 N.
                 The interface plane flatness of a unit interfacing directly with the S/C shall be better than 0.1 mm, i.e. all
RS 7.1.3-2 /T
                 attachment points shall be in a common plane within ±0.05 mm. (TBC)
                 The interface bolts from LTP core assembly to S/C shall be M8x1 (TBC) and their clearances shall be:
                 · Hole size: 8.3 +/- 0.1mm
                 · Positional tolerance of diameter: 0.1 mm
                 · Positional tolerance of inserts: 0.2 mm (TBC)
RS 7.1.3-3 /T    The LTP core assembly shall be mounted to the S/C by an (quasi) isostatic mounting system (TBC)
                 Other equipment like electronic units shall be fixed with M5 bolts respecting the following clearances:
                 · Hole size: 5.3 +/- 0.1mm
                 · Positional tolerance of diameter: 0.1 mm
                 · Positional tolerance of inserts: 0.2 mm (TBC)
                 Unless special conditions override, the thickness of the mounting feet of LTP units directly interfacing with the
RS 7.1.3-4 /T
                 S/C shall be at least 3.0 mm. (TBC)
                 S/C interfacing LTP units requiring alignment (beyond the accuracy provided by the fixation bolt clearances)
RS 7.1.3-5 /R    on the S/C shall provide the means for the alignment (alignment pins, optical reference cubes etc.)

RS 7.2.1-1/T A   LTP unit power values according to RS 5.3-15 shall be considered for the S/C thermal control design.
                 OB photodiodes and wires coming from LCA external equipments shall be the only power sources inside LCA.
RS 7.2.1-2/T A   Note: Any Dissipation from Diagnostics inside LCA TBD

                 The average power dissipation on the OB due to photodiodes shall be less than 50 mW. (TBC). Remaining
RS 7.2.1-3/T A   LCA dissipation budget of 50 mW (compared to RS 5.3-15) is reserved to cover peaks and any other sources
                 inside the LCA.
                 OB Photodiodes power fluctuation shall be in accordance with the following figures:




RS 7.2.1-4/T A




                 Thermal analysis of LTP electronic units shall comprise analysis of I/F temperature fluctuations due to
RS 7.2.1-5 /A
                 dissipation fluctuations resulting from bus voltage fluctuations.
                 The following cables shall be considered and modeled in the LCA TMM (as a conservative approach, as mass-
                 less nodes and with zero capacity, TBC) and in the GMM (as nodal surfaces for evaluating their radiative
                 coupling to the LCA)
                 o Laser optic (OB) optical fibers
RS 7.2.2-1/T A
                 o Phasemeter & AOMU wires
                 o IS optical fibers
                 o IS FEE coaxial cables
                 o IS CM motor signals cables
                 The S/C thermal control system is required to reduce the heat flow through the LTP core assembly as far as
                 possible. The LCA thermal design shall provide full performance if the corresponding requirements (IRD TCS-
RS 7.2.3-1/T A
                 6, to be reasonably updated and to be implemented in the EID-A/B documents) boundary conditions are met
                 by the S/C.
                 The S/C thermal control system has to guarantee that any heat flux across the LTP core assembly (OB with
                 IS) will be stable to within a PSD 1%/vHz within the MBW (IRD TCS-7 in its actual, preliminary meaning). The
RS 7.2.3-2/T A
                 LCA thermal design shall provide full performance if this boundary condition is met by the S/C.
                   LTP units thermal I/Fs shall comply with the mechanical and EMC requirements.
RS 7.2.3-3/R T     Remark: The following are LTP internal requirements for the Core Assembly, which have to be more detailed
                   in future issues or to be placed in the subsystem specifications.
RS 7.2.3-4/R T A   The overall interface conductance at the IS/OB interface flanges shall be less than TBD W/K
RS 7.2.3-5/R T A   The overall interface conductance between Thermal Shield and OB shall be less than TBD W/K
                   The overall thermal radiative coupling between IS vacuum enclosure and OB shall be less than TBD W/K^4
RS 7.2.3-6/R T A
                   The overall thermal radiative coupling between IS vacuum enclosure and Thermal Shield shall be less than
RS 7.2.3-7/R T
                   TBD W/K^4
RS 7.2.3-8/R T     The overall thermal radiative coupling between Thermal Shield and OB shall be less than TBD W/K^4
                   The LTP instrument thermal control system of the single LTP units shall follow the guideline established in
                   Figure 7.2-1.




 RS 7.2.4-1/T A




                   All LTP units except the LCA shall be conductively controlled, i.e. all electronic units shall have excellent
                   conductive coupling (I/F filler to be applied) to the S/C via their base plate together with a high emissive
RS 7.2.4-2/R T A
                   surface (e > 0.85) in order to reduce thermal gradients between the electronic units housing and the S/C as far
                   as possible.
                   The temperature reference point (TRP) shall be selected on the unit external surface, preferably close to a
                   mounting bolt, such that its temperature reflects the average unit housing temperature (no hot or cold spot).
 RS 7.2.4-3/T A
                   The temperature reference point will be used as reference for the thermal testing and shall be maintained
                   within the specified temperature limits during flight.
                   The temperature reference point (TRP) temperature range of LTP units shall be agreed between the customer
 RS 7.2.4-4 /R
                   and the supplier and defined in an ICD.
RS 7.2.4-5/R T     For non-isothermal units the number of temperature reference points shall be increased accordingly.
                   All thermal hardware mounted in the unit shall be identified in the ICD, e.g. heaters, temperature sensors,
 RS 7.2.4-6 /R
                   tapes, MLI.
                   Temperature monitoring of selected points within a unit shall be provided by the unit supplier to cover the
                   cases:
 RS 7.2.4-7/R
                   a) Unit operational safety monitoring
                   b) Unit operational temperature and performance monitoring.
 RS 7.2.5-1 /R     LTP unit I/F temperatures according to RS 5.3-16 shall be applied.
                   Specifically, the temperature experienced by the optical bench, at the IS/OB interface flanges, shall be inside
 RS 7.2.5-2/R
                   the range 20°C ± 10°C during operation.
                   The temperature fluctuations experienced by the optical bench, at the IS/OB interface flanges, shall be less
 RS 7.2.5-3 /R
                   than 10-4 K/Hz0.5 in the frequency range of 1 – 30 mHz.
                   The temperature fluctuations experienced by the IS at its thermal I/Fs (mechanical, electrical, optical , shall be
 RS 7.2.5-4 /R
                   less than 10-4 K/Hz0.5 in the frequency range of 1 – 30 mHz
                   The temperature experienced by LTP units measured at the TRP(s), temperature reference point(s), shall be
 RS 7.2.5-5 /R
                   inside the range as defined in RS 5.3-16.
                   The OMS reflection points on the Test Mass center shall be located absolutely within an uncertainty cube of
RS-7.3-1 / A, T
                   length of smaller 100 µm.
                   The angle mismatch between the interferometer axis frame (IAF) and the FRF shall be smaller than +/- 300
RS-7.3-2 / A, T
                   µrad.
                   For the optical window providing the laser beam access from optical metrology to the TM a diameter of not
RS-7.3-3 / R, I
                   more than 30mm (TBC) shall be assumed.
                   The maximal change of optical path length between OMS and TM (due to an optical I/F) shall be not more
                   than 1pm / vHz @ MBW.
  RS-7.3-4/ T
                   Note: E.g. applying a window thickness of 6 mm, window tilt angle of 2.5º and coefficient of refraction n = 1.6
                   the transfer function is 10-4 m/rad leading to a stability of 10nrad/vHz @ MBW.
                    A reference point (e.g. optical cube) shall be introduced in the OB design being accessible for optical and
                   mechanical position and attitude measurements during integration of IS Heads with OB. A co-ordinate transfer
                   matrix from the OBF and IAF to this location shall be established. The reference point shall be defined in
 RS-7.3-5/ R, T    terms of translational and rotational coordinates to a precision of smaller TBD µm in y- and z-axes and smaller
                   TBD µm in x-axis and tbd µ rad, respectively.
                   Note: The actual alignment requirement figures as well as the methods to be adopted are presently still under
                   detailed study.
                   Note: Each power interface will be provided from a regulated bus with a nominal bus voltage of 28V, regulated
                   within a range of 25.5V to 28V +0.14V at the LTP input (including harness drop), refer to AD3 §
                   The S/C will provide and the LTP shall acquire 8 (TBC) redundant power feeders as listed below to power on
                   and off each single LTP. Commanding is exclusively performed by the spacecraft computer which controls the
                   power feeders inside the spacecraft PCDU. No unit pulse commands are used. The Power feeders (LCL’s)
                   are specified in AD3 § 3.5.2.




RS 7.4.1-1/R T




                   The S/C shall make 2 redundant spare power feeders available for usage by LTP units. These spare power
RS 7.4.1-2 / R T
                   feeders are included in reqt. RS 7.4.1-1 and the accompanying table.
RS 7.4.1-3 / A T   Bus voltage ripple and spikes: as defined in the EMC paragraphs of AD3 § 4.5
                   Whenever an interface is referred to as MIL-STD-1553B RT, the interface requirements of AD3 shall apply.
 RS 7.4.2-1/RT
                   For the 1 PPS signal the interface requirements of AD3 shall apply.
                   Note: Assumption: To allow for cross-coupling between spacecraft platform and DDS, the LPF is expected to
                   provide two one-pulse-per-second (1 PPS) signals (two each from its nominal and from its redundant 1PPS
 RS 7.4.2-2/RT
                   drivers) (GD Note & 8MHz?) for the Synchronisation of Timing between the spacecraft and the LTP/ DDS. At
                   DDS inputs the signals from the nom and the red. LPF divers are to be ored (tbc). This topic is not yet covered
                   from the EID-A
                   For the 1 PPS (GD Note 8MHz?) signal the interface requirements of AD3 shall apply.
RS 7.4.2-3/R T     Note: The 8 MHz clock is still under discussion. If agreed the interface requirements will be included and
                   referenced to AD3. This will also be extended to the redundancy and cross-coupling requirements
                   The maximum telemetry data rate shall not exceed 1715 bps (TBC) according to S/C IRD
                   Comment:
RS 7.4.2.2-1/A T
                   It is too early to freeze this requirement finally. It needs to be revisited when EID-A will be discussed after its
                   release by LPF prime.
RS 7.4.2.2-2 /A    deleted
                   The LTP to LPF I/F shall be implemented via single redundant interface between S/C OBC and LTP as MIL-
                   STD 1553 B Remote Terminal in the DMU for Command and Control and non-critical timing demands at a
                   total sum of < 10 kbps mean maximum in TM direction to the S/C OBC and < 5 kbps in the TC direction from
                   S/C OBC to LTP.
RS 7.4.2.2-3 /A
                   The real-time critical data for IS closed loop control and the delta data rate which is required for DFACS,
                   charge detection, and suspension shall be implemented by MIL-STD 1553 B RT on LTP IS FEE SAU. (Note:
                   this data rate is < 4 kbps for TM and < 6.5 kbps for TC, each at 10 Hz packet cycles).

                   The LTP data exchanged through this standard I/F to the LPF OBC shall be capable for a transfer rate of at
                   least 2230 bit/s in total (TBC, see comment on data rate requirement in RS 7.4.2.2-1).
RS 7.4.2.2-4/A T
                   This value represents the data transmitted (1715 bit/s TBC) plus 30% margin for additional communication
                   operations.
                   The SW device driver for IS displacement measurement data transfer to the LPF OBC for DFACS real-time
RS 7.4.2.2-5/R T   control shall support a control loop sampling rate of 10 Hz with a maximum allowed latency of TBD
                   milliseconds to the 10 Hz samples.
RS 7.4.2.3-1/R T   deleted
                   DMU shall interface with the phasemeter front-end with one MIL-STD-1553 B RT each in 2 sparately operable
RS 7.4.2.3-2/R T
                   PM modules.
RS 7.4.2.3-3/R T   DMU shall interface internally the DDS with the Diagnostics S/Ss units
                   The DMU shall interface with the Optical Metrology Subsystem for the managing of the following signals:
                   · Frequency Stabilization,
                   · Optical Pathlength Stabilization
                   · Phasemeter Back-end Data Processing
                   · analog and digital signal in and out
RS 7.4.2.3-4/R T   · digital control,
                   · monitors,
                   · setpoint,
                   · flags,
                   · various clocks.

                   The LTP shall provide mechanical interfaces for handling, testing and transport, e.g.
                   · interfaces to transport container
  RS 7.7-1/R
                   · interfaces to handling frames, trolley, lifting devices
                   · interfaces to test adapters (vibration test, thermal test)
                   Wherever possible interfaces intended for flight shall be used. Unavoidable mechanical integration and test
  RS 7.7-2 /R
                   interfaces shall be removed for flight.
                   The LTP shall provide interfaces for alignment measurements, e.g.
  RS 7.7-3 /R      · alignment cubes or alignment mirrors at locations accessible at all relevant integration stages and after
                   environmental testing.
              The LTP shall provide interfaces for system electrical integration and functional testing, e.g.,
              · electrical interfaces (connectors) to test equipment
RS 7.7-4 /R
              · stimuli / feedback interfaces to spacecraft (if any)
              Electrical connections to test equipment shall be made vi a connector savers.
              The LTP shall provide mechanical and electrical interfaces for inertial sensor vacuum maintenance as
              necessary, e.g.
RS 7.7-5 /R
              · vacuum pumping ports
              · getter pumps electrical supply and monitoring connectors
RS 7.7-6 /R   Integration and test interfaces shall be compliant with LTP cleanliness requirements.
              The LTP shall be designed and manufactured to meet the system requirements when subjected to the
RS 8.1-1/R    environmental conditions existing during all periods from ground activities till the end of in-orbit operation.

              No induced environment shall lead to a degradation of the mission product. Where necessary, special
RS 8.1-2 /R
              provisions shall be taken to ensure this requirement.
RS 8.1-3 /R   The applicable terrestrial and in-orbit space environment is specified in[AD3].
RS 8.1-4 /A   The LTP components shall perform within specification in the environment of the final orbit.
RS 8.1-5 /R   Handling, transportation loads and test loads shall not be design drivers.
              The LTP shall be able to withstand the following sinusoidal excitation along the three axes in hard mounted
              conditions as defined by Table 8-1 : SCM Sinusoidal Vibration Requirement




RS 8.2-1 /R




              Notching of the vibration sine excitation may be allowed in order not to exceed the design load interface forces
RS 8.2-2 /R
              after agreement with the Customer.
              The acceptance levels could be applied after agreement with the Customer if retesting has to be performed to
RS 8.2-3 /R
              avoid overstressing of H/W.
              The LCA shall demonstrate compliance with the random vibration requirements defined in Table 8-2: Random
              Vibration Excitation.




RS 8.2-4 /R




              Notching of the vibration random excitation may be allowed in order not to exceed the design load interface
RS 8.2-5 /R
              forces after agreement with the Customer.
              The LTP shall be able to withstand the following mechanical shock along the three axes in hard mounted
              conditions as given by Table 8-3 : SCM Shock Spectra Requirements



RS 8.2-6 /R




              The LCA shall be able to withstand the following quasi-static requirement as summarised in Table 8-4: LCA
              Quasi-Static Requirements.


RS 8.2-7/R




              The system, subsystem and unit design and the test programme shall be adequate to ensure that the
RS 8.4-1 /R   combined conducted and radiated emissions from all sources shall not adversely affect the correct operation
              of the payload nor degrade the performance of elements of the subsystems.
              The EMC programme shall demonstrate margins of at least 6 dB (TBC) between susceptibility and emission in
RS 8.4-2 /R
              conducted and radiated mode at spacecraft level.
RS 8.4-3 /R




                Permanent magnets shall be avoided where possible. Non-magnetic materials shall be used wherever
                possible, especially a non-magnetic unit housing shall be used.
RS 8.4-4 /A T
                In case of existing hardware with magnetic components the contractor is requested to indicate the type and
                magnetic properties of relevant components for individual disposition.
                A maximum electric field, relative to the location of the LTP test masses are required:
                Editorial note: values have been changed; this table needs updating!




RS 8.4-5 /A T




                For a period of 20 ms after switch-on (applying DC power to the unit), the inrush current will be limited to twice
                the nominal current at 28V by the latching current limiter in the PCDU. This will cause the bus voltage to ramp
                up. The switch-on current shall return to nominal current level within these 20 ms otherwise it is deemed as a
RS 8.4-6 /R
                short circuit and switched off by the PCDU.
                This requirement shall be verified by unit switch-on with current limitation to twice the nominal current for 20
                ms. After this period, the inrush current shall be lower than the specified nominal current at 28 V
RS 8.5-1/R      deleted
RS 8.6-1 /R     Definitions and requirements of AD-TBD shall apply.
                The equipment shall withstand the environmental impact referenced in the ENVIRONMENTAL
RS 8.6-2 /R
                SPECIFICATION [AD TBD].
                A Detailed Mechanical Stress Analysis shall be established for LTP and its major units. This shall include at
                least:
                - A description of the configuration analysed with Reference to interface Controlled drawings,
                - A description of the mathematical finite element model and/or of the assumptions taken to verify the
                structure,
                - A description of all possible loading cases and an identification of the design driving load cases or load
                combinations,
RS 10.1-1 /R
                - detailed description of the most loaded elements listed with relevant stresses, and the loading cases that
                generated them,
                - A list of the materials and structural Components with characteristics data sheets (including long-life effects
                under space environment),
                - A set of tables showing, for each structural element, the maximum value on each type of stress or
                combination of them with the allowable value, and the load case that determines it, together with its margin of
                safety.
                A structural mathematical model of the instrument and its major units shall be established that is detailed
                enough to predict the loads to size the structure elements, and the interface loads in particular, with sufficient
RS 10.1-2 /R
                accuracy. This means that it shall be able to reproduce the low frequency modes with an upper limit to the
                frequency range to be defined on a case-by-case basis.
                The LTP industrial Architect shall be provided by the responsible subsystem and unit contractors with a
                structural mathematical model of the major LTP units. The models shall be able to reproduce the low
                frequency modes with an upper limit to the frequency range to be defined on a case-by-case basis. (derived
                from GDIR GDI-197/CREATED/A)
                Finite elements models shall be provided for all items which have principal modes of vibration at frequencies
RS 10.1-3 /A    less than:
                - 140 Hz actual or,
                - 161 Hz if predicted by FE model (i.e. +15% margin) or,
                - 182 Hz if predicted by hand calculation (i.e. +30% margin).
                The supplied FEM shall represent all significant modes, i.e. modes with an effective mass equal to or larger
                than 10% of the total equipment mass.
RS 10.1-4 /A    deleted
                The finite element model shall be prepared using NASTRAN Software Version 70.7 or later with all elements
RS 10.1-5 /R
                compatible with 70.7. The NASTRAN version shall be indicated as part of the model data.
                The physical finite element model shall be accompanied by a clear description of the model itself and of the
                assumption made in the model, particularly concerning the boundary conditions at the spacecraft interfaces.
RS 10.1-6 /R
                For mechanisms, two or more models (stowed, deployed, general position, engaged, etc.), may be required.
                  A thermo-elastic model shall be established for LTP system level. The LTP industrial Architect shall be
 RS 10.1-7 /R     provided by the responsible subsystem and unit contractors with the necessary input concerning their units
                  and equipment.
 RS 10.1-8 /R     All mathematical models shall be maintained in current configuration.
 RS 10.1-9 /R     deleted, covered by 10.1-17
                  Mechanism Functional Analysis - Each mechanism shall be analysed functionally and the following information
                  shall be at least supplied:
                  - A detailed description of the mechanisms, with particular Reference to its discrete components (bearings,
                  actuators, switches) and to its operational/safety features,
                  - A detailed description of the operating modes with Reference to ground and orbital activations,
                  - A definition of operating loads in various configurations with A clear definition of analysis assumptions, in
RS 10.1-10 /A R
                  particular, the functional analysis shall include the effects of the worst environmental conditions that could
                  produce distortions or changes in clearance between movable parts (e.g. thermal gradient through bearings),
                  - A Failure modes, effects and Criticality Analysis (FMECA) defining the Failure modes and the functional
                  margins of safety against each of them,
                  - A performance description of the control system that the mechanisms form a part of.

                  S.I. units are to be used for the mechanical models:
                  · Newton (N) for force
                  · Kilograms (Kg) for mass
RS 10.1-11 /A R   · Meters (m) for length
                  · Seconds (s) for time
                  · Degrees Celsius (°C) for temperature
                  Further unit definitions are given in [AD6].
                  Coordinate systems shall be according to Chapter4.1.
RS 10.1-12 /R
                  Additional reference CS shall be in accordance with [AD6].
                  The following post-run checks shall be performed on each model in accordance with [AD6]
                  Mass Proprty Check
                  Conditioning Check
                  Gravity Load Check
                  Constraint Check
RS 10.1-13 /A R   Rigid Body Frequency Check
                  Thermo elastic stress check
                  Constraint check
                  Rigid Body Frequency Check
                  Thermo elastic stress check
                  Details over each of such tests are to be found in [RD33].
RS 10.1-14/A R    For the Thermo-Elastic Stress Check, the conditions given in [AD6] shall be satisfied
RS 10.1-15 /R     Model size and identification numbering (TBD)
RS 10.1-16 /R     Models shall be full models with no symmetry assumptions made to reduce the size.
                  The structural mathematical model description (report) shall be in accordance with [AD6].
                  An abstract, of what it shall include at least is given below:
                  - A description of the configuration analysed with Reference to interface Controlled drawings,
                  - A description of the mathematical finite element model and/or of the assumptions/reductions introduced in
                  the analysis,
                  - a description of the checks performed on the model to verify its quality (e.g. rigid body modes, residual
RS 10.1-17 /A R   forces),
                  - A list of eigenfrequencies with relevant mode type and associated modal effective masses,
                  - plots and listings of eigenvectors.
                  - Description of the reference frame used (a drawing, the rotation and translation matrixes with respect to a
                  single coordinate frame are require
                  - Mass breakdown and distribution in the models
                  - Electronic files saved on CD-ROM containing all BULK data for the analyses and the model checks
                  The thermal performance of LTP and each of its unit shall be calculated by means of time resolved thermal
                  mathematical models. If necessary to verify thermal requirements defined in the frequency domain, special
 RS 10.2-1 /R
                  analysis tools have to be set up. The contractor shall use models for design purposes and shall also provide
                  interface models for use during the system/spacecraft design.
                  The degree of detail (i.e. number of nodes and conductors, etc.) shall be sufficient to allow verification of the
                  requirements and validation of test results. In addition is has to be shown that all interface requirements are
                  met. The model shall allow performing transient analyses; hence a thermal capacity must be allocated to each
 RS 10.2-2 /R
                  node. Heat dissipation shall be identified, along with indication of the appropriate operating mode. The number
                  of operating modes considered for thermal modelling purposes may be a reduced set of the total number.

                  A Thermal Interface Mathematical Model (TIMM) shall be set up for each LTP electronic unit with respect to
                  the S/C, meeting following requirements:
                  - The minimum number of isothermal nodes shall be three, representing the unit's housing, base plate and
                  interior. More nodes up to ten shall be generated if considerable temperature gradients along the base plate or
                  the housing must be expected.
                  (Note: For the latter case GDIR specifies seven nodes maximum).
 RS 10.2-3 /R
                  - the TIMM shall be in ESATAN format.
                  - the TIMM temperature predictions shall be Correlated with the predictions of the detailed TMM of the unit.
                  This correlation is to be considered successfully obtained, if the node temperatures of the TIMM are within ± 3
                  K of the corresponding nodes of the detailed TMM.
                  - the Thermal Test results (temperature distribution at hot and cold levels) shall be used to update the TIMM.

                  A Geometrical Mathematical Model (GMM) shall be established for each LTP electronic unit if not otherwise
 RS 10.2-4 /R
                  agreed. The GMM shall preferably be in ESARAD format.
                  The thermal model of a unit shall be verified and correlated with a thermal test. The correlation criteria shall
                  be:
RS 10.2-5/T A
                  +/- 2 K on the temperatures
                  +/- 10 % on the required heater power
                  For thermal analysis of the LCA special software tools shall be made available, which allow analysis and
 RS 10.2-6 /R
                  verification in the frequency domain.
                 LCA Thermal Interface Mathematical Models (TMM & GMM) shall be established for implementation into the
                 S/C thermal models. These models shall be in ESARAD & ESATAN format. Correlation criteria and / or
RS 10.2-7 /R     correlation analysis cases are TBD.
                 Nevertheless the reduced models shall represent the thermal behaviour of the LCA to the extent, to allow
                 performance validation & verification of the LCA thermal I/Fs at S/C thermal analysis level.
                 For optical units of LTP an optical mathematical model (OMM) for numerical simulation of the unit shall be
 RS 10.3-1 /A    established. This model shall be based on the complete set of latest specifications and tolerances that are
                 available about the unit.
                 The OMM shall include not only the actual optical elements but also intermediate image planes, intermediate
 RS 10.3-2 /A
                 pupil imaging planes wherever applicable.
 RS 10.3-3 /A    The numerical model shall be developed on Code V.
                 The OMM shall be based on the complete set of latest specifications and tolerances that are available about
 RS 10.3-4 /A
                 LTP.
                 The numerical model shall be used for the evaluation of the unit’s optical performance. Actual glass
 RS 10.3-5 /A    characteristics as measured by the glass supplier shall be included. Performance analyses shall take into
                 account the diffraction effects, misalignments and manufacturing tolerances.
                 A numerical model shall be established describing the gravitational static field and gravitational gradient at the
 RS 10.4-1/A
                 location of the TMs resulting from LTP internal and S/C environment mass distribution.
                 The gravitational model shall be based on the complete set of latest specifications and tolerances that are
 RS 10.4-2 /A
                 available about LTP and S/C.
                 The gravitational model shall be used to derive requirements for mass and position of gravitational balance
 RS 10.4-3/A
                 masses to be implemented inside the Inertial Sensor.




RS 10.4-4 /R T




RS 10.4-5 /R T




                 For LTP and for its major elements influencing the Scientific Performance a Performance Model models shall
RS 10.5-1/R A
                 be established.
                 Performance models shall be used to evaluate the performance values of critical LTP functions and
RS 10.5-2 /R A
                 parameters.
                 General verification definitions such as
                 · model definition
                 · unit development status (i.e. categories A through D)
RS 11.1-1 /R
                 · verification methods, levels and stages as defined in ECCS-E-10-02A [AD14] shall be used in the LTP
                 project.

                 Verification specific definitions for LTP as defined in the LTP Design, Development and Verification Plan,
RS 11.1-2 /R
                 [RD30] shall be used consistently throughout the LTP project.
                 The LTP verification programme shall be defined in accordance with ECCS-E-10-02A [AD14]. The
RS 11.2.1-1 /R   requirements of this standard may be tailored for LTP, in accordance with the general ECSS tailoring
                 guidelines (ref. ECSS-M-00-02).
                 The verification program shall achieve for full complement of the flight H/W and S/W:
                 - Demonstration of design qualification
RS 11.2.1-2 /R   - Demonstration of flight acceptance
                 - Demonstration of system performance for the mission DURATION, including all ground H/W, S/W and
                 associated support equipment
                 On unit level for each item a qualification and acceptance program shall be established by the supplier, which
RS 11.2.1-3 /R   demonstrates compliance with all system-derived requirements as given in the relevant lower level
                 specifications or in this document.
RS 11.2.1-4 /R   All applicable requirements shall be verified by the relevant supplier.
                 The supplier shall establish, maintain and deliver verification documentation in accordance with ECSS-10-02
RS 11.2.1-5 /R
                 and shall submit the documentation in due time for LTP Architect approval.
RS 11.2.1-6 /R   For all testing activities, the requirements and terminology specified in ECSS-E-10-03 shall apply.
                 The supplier shall establish, maintain and deliver test documentation in accordance with ECSS-10-03 and
RS 11.2.1-7 /R
                 shall submit the documentation in due time for LTP Architect approval.
                 Testing - if necessary in combination with analysis (or simulation) - shall be the preferred method of
RS 11.2.1-8 /R
                 verification.
                  Simulation models used for verification activities shall be validated (preferably by test) against the simulated
RS 11.2.1-9 /R
                  equipment.
                  The assignment of verification methods and verification levels shall take into account:
                  - level of confidence
RS 11.2.1-10 /R   - practicality
                  - safety
                  - cost efficiency
                  Qualification and acceptance w.r.t. mechanical loads shall be achieved by test at unit level as detailed in the
RS 11.2.2-1 /R
                  Test Matrix.
                  Qualification and acceptance w.r.t. the thermal environment shall be achieved by test at unit level as detailed
RS 11.2.2-2 /R
                  in the Test Matrix.
                  Qualification and acceptance w.r.t. EMC shall be achieved by test at unit level as detailed in the Test Matrix.
RS 11.2.2-3 /R
RS 11.2.2-4 /R    Qualification of mechanisms lifetime shall be achieved by test.
RS 11.2.2-5 /R    Qualification of lifetime critical items shall be achieved by test.
RS 11.2.3-1 /R    Verification of interfaces shall be achieved by test at unit level.
RS 11.2.3-2 /R    Verification of physical properties shall be achieved by test at unit level.
RS 11.2.3-3 /R    Verification of alignment shall be achieved by test at unit level.
RS 11.2.4-1 /R    Functional verification shall be achieved by test at unit level.
                  Performance verification shall be achieved by test at unit level, complemented by analysis as far as necessary.
RS 11.2.4-2 /R
                  The Verification Requirements shall be derived from the system performance requirements and shall consist
RS 11.2.5-1 /R    of the system level parameters requiring verification in order to demonstrate that the overall programme
                  objectives are met.
                  The LTP verification program shall provide system-wide visibility on compliance of flight H/W and S/W design
                  and performance with the LTP top level requirements, which has to be accomplished by a complete and
                  redundant-free verification sequence from unit to system level.
                  This compliance shall be shown in a verification control document, which contains a verification matrix with all
                  relevant information:
RS 11.2.5-2 /R
                  - type of verification
                  - model for verification
                  - level of verification
                  - Method of verification
                  - Closeout notification
 RS 12.1-1 /R     The unit shall be delivered packed in a dedicated transport container.
 RS 12.1-2 /R     The transport container shall be part of the delivery to the Industrial Architect.
 RS 12.1-3 /R     The transport container shall be reusable and marked as such.
                  The transport container shall be designed to support the surface and air transport of the unit under the
 RS 12.1-4 /R
                  specified transportation environments.
                  The transport container shall be designed to support the storage of the unit under the specified storage
 RS 12.1-5 /R
                  environment.
                  The transport container shall be compatible with the requirements specified for the contained hardware, e.g.
 RS 12.1-6 /R
                  cleanliness, magnetic properties.
 RS 12.1-7 /R     The transport container shall fulfil the requirements of [AD 3], §§ 3.1.7.1, 3.1.7.2, 3.1.7.3
 RS 12.1-8 /R     The transport container shall fulfil the general MGSE requirements.
                  For every unit with mass in excess of 10 kg, a hoisting / offload device shall be designed and built which shall
 RS 12.2-1 /R     support the integration of the unit on the S/C panel when the S/C is horizontal and the mounting panel is
                  vertical.
 RS 12.2-2 /R     The hoisting / offload device shall be packed in a reusable container.
 RS 12.2-3 /R     The hoisting / offload device and its container shall be part of the delivery to the Industrial Architect.
                  The hoisting / offload device shall be compatible with the cleanliness requirements specified for the hardware
 RS 12.2-4 /R
                  to be handled.
 RS 12.2-5 /R     The hoisting / offload device shall be non-magnetic.
 RS 12.2-6 /R     The hoisting / offload device shall be clearly marked for its identity.
                  The hoisting / offload device shall be fully tested and certified in accordance with applicable European,
 RS 12.2-7 /R
                  German and UK statutory and regulatory requirements.
 RS 12.2-8 /R     The hoisting / offload device shall fulfil the general MGSE requirements.
                  EGSE, including test equipment, test harness, and EGSE software modules for measurement data evaluation,
 RS 12.3-1 /R     needed to operate and test the unit shall be made available by the supplier or subcontractor to the Industrial
                  Architect for use during the LTP level AIT phases.
 RS 12.3-2 /R     EGSE shall be supported and maintained by the supplier or subcontractor.
 RS 12.3-3 /R     EGSE shall be compatible with the flight hardware interfaces.
                  EGSE software shall be structured in a modular way such that databases and automated test sequences are
 RS 12.3-4 /R
                  compatible to each other.
 RS 12.3-5 /R     EGSE shall provide automatic self test capability.
 RS 12.3-6 /R     EGSE shall fulfil the general GSE requirements.
                  Equipment which needs alignment shall be equipped with alignment reference targets (e.g. alignment cube) in
 RS 12.4-1 /R
                  accordance with the applicable ICD.
                  Dedicated optical ground support equipment, jigs or tools needed for alignment or alignment checks shall be
 RS 12.4-2 /R     made available by the supplier or subcontractor to the Industrial Architect for the LTP level AIT phases. Such
                  items shall be supported and maintained by the supplier or subcontractor.
 RS 12.4-3 /R     Optical ground support equipment shall be supported and maintained by the supplier or subcontractor.
                  Optical ground support equipment shall fulfil cleanliness requirements to be compatible with the flight
 RS 12.4-4 /R
                  hardware.
 RS 12.4-5/R      Optical ground support equipment shall fulfil the general GSE requirements.
                  All equipment required for IS vacuum maintenance shall be made available by the IS supplier to the Industrial
 RS 12.5-1/R      Architect for all higher level AIT phases, including S/C level. This requirement shall include any purging
                  equipment eventually required for IS vacuum maintenance
 RS 12.5-2 /R     The vacuum maintenance equipment shall be supported and maintained by the IS supplier.
 RS 12.5-3 /R     The vacuum maintenance equipment shall fulfil the general GSE requirements.
        O           A   I
                    N       R
P   m   p   B           N
                T   A       E
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                e   L       V             Verification
a   t   i   n
                s
                        P
                            I   COMMENT
s   e   c   c       Y   E                   Method
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Requirement No. Ref. Status                                                Requirement


                              The OMS shall be fully compatible with the following primary main mission phases:
                              • Ground operations, handling and transport
                              • Launch and early orbit phase
OMS-4.2.1-1/R                 • Transfer and injection to the final orbit
                              • OMS demonstration phase
                              • DOMS-demonstration phase
                              • Joint OMS/DOMS-demonstration phase
                              During the LEOP the OMS shall not need any primary power.
OMS-4.2.1.1-1/R T
                              During the transfer and final orbit injection the OMS shall be in a passive mode and shall not require primary
                              power.
OMS-4.2.1.2-1/R T
                              Note: During transfer OMS shall be passive as baseline. However, some calibrations could be performed in
                              this phase, if these can be separated from the activities of the demonstration phase.
                              The OMS shall be functionally broken down into assemblies and units as identified in the Product Tree shown
                              in Figure 4.3-1.
OMS-4.3.1-1 /R
                              All primary instrument functional requirements can be allocated to the various subsystems and units as
                              specified in the following sections
                              The Optical Metrology Subsystem (OMS) shall comprise all major hardware elements required to perform
                              following functions:
                              - Mechanical support of two Inertial Sensor Heads
                              - Measurement of the relative displacement between the two test masses (TM) along the measurement axis
                              (main science measurable; called x2-x1)
                              - Measurement of the motion of one test mass (labelled TM1) relative to a defined point on the Optical Bench,
OMS-4.3.2.1-1 /R T            i.e. relative to the S/C

                              4.1-1)
                              - Measurement of the relative angular motion of TM1 versus an OB reference system (resp. vs. S/C) about

                              Parts of the necessary data processing of the optical read-out (Phasemeter data products) will be performed
                              within the Data Management Unit
                              The OMS Optical Metrology Subsystem shall be constituted by the following functional modules:
                              • the Laser Assembly with
                              -- 1 Laser Unit
                              -- Laser Interface Electronics
                              -- 1 Acousto-Optical Modulation Unit (including 1 beamsplitter, 2 AOMs and 2 OPDAs)
                              -- AOM and OPDA control electronics
                              -- LA Harness
                              • the Optical Bench with
OMS-4.3.2.1-2 /R              -- 4 two-beam interferometers
                              -- photodiodes (8 quadrants and 2 single-elements)
                              -- 2 fibre coupled beam launchers
                              -- mechanical supports
                              -- Harness
                              • the Phasemeter Assembly consisting of
                              -- interface to photodiodes (8 quadrants)
                              -- Phasemeter Unit
                              -- Phasemeter Harnesses incl. cables/connectors to photodiodes
                              ########################################################################################




OMS-4.3.2.2-1 /R T




                              The optical signal from laser head to AOMU and from AOMU to OB respectively shall be delivered by fibre
                              optical connections. For these connections the following components shall be adopted:
OMS-4.3.2.2-2 R, I
                              -- Fiber: polarization maintaining fiber Fujikura PANDA SM.98-P-6/125UV/UV-400
                              -- Connector: Diamond AVIM PM8° (103-026-604V001)
                      Laser Assembly shall be delivered with optical fibres and harness for following signals:
                      • 8 MHz clock
                      • MIL Bus
OMS-4.3.2.2-3/ R, I
                      • Serial data TBD
                      • Cables between single element photodiodes on OB and AOMU for power monitoring
                      Note: The Data and Diagnostics Subsystem will perform the Laser Assembly diagnostics tasks.
                      The Optical Bench Assembly (OBA) shall:
                      • carry all the optical components needed to implement the interferometry,
                      • support 8 quadrant and 2 single-element photodiodes that collect the light and generate the interferometer
                      output signals,
                      • use 2 single-element photodiodes for laser power monitoring
                      • include 4 interferometers based on quadrant photo-diodes, in detail:
                      o two for the metrology proper,
                      o one for phase-reference, and
                      o one for laser frequency noise measurement
                      • provide the mechanical interface for both IS
                      • guarantee the proper alignment tolerances for the use of the IS TM as the OMU end mirrors during:
                      o ground testing
                      o in-flight initialisation
                      o science operation
                      • provide optical alignment devices (flight items and non-flight items) to support positioning and alignment
                      verification of ISHs versus the OBA as well as of the LCA on the S/C.

                      The OBA will consist of the optical bench interferometer OBI, the reinforcement structure and interfaces. The
                      most recent design of the OBA mechanical layout is shown in Fig. 4.3.2.3-1 below.




OMS-4.3.2.3-1 /R T




                      The OBI ( Optical Bench Interferometer) shall:
                      o use non-polarizing interferometers with non-normal incidence on the TM surfaces
                      o use heterodyne Mach-Zehnder interferometry
OMS-4.3.2.4-1/ R, I
                      o provide 3 interferometers with equal pathlengths and one with intentionally large pathlength difference
                      o make optical paths otherwise as similar and symmetric as possible.
                      o avoid unnecessary pathlengths in transmission through optical components.
                      Four interferometers shall be implemented on the OB:
                      1. x1 - x2 shall provide the main measurement: the distance between the two test masses and their differential
                      alignment.
                      2. x1 shall provide as auxiliary measurement the distance between one test mass and the optical bench and
OMS-4.3.2.4-2/ R, I
                      the alignment of that test mass.
                      3. Reference shall provide the reference phase for x1 - x2 and x1.
                      4. Frequency shall measure laser frequency fluctuations with intentionally unequal pathlengths.

                      The OB shall be delivered with fibre launchers fixed and aligned and ready to accept fibre connections from
OMS-4.3.2.4-3/ R, I
                      the LA.
                      The phasemeter shall provide interface to the 8 quadrant diodes at the OB:
                      1. Accept 32 channels of analogue photodiode current
                      2. Provide stabilized bias voltage to the photodiode of no more than 5 V (TBC)
                      3. Produce raw output data (single bin discrete Fourier transform output) at 100 Hz data rate (TBC) for each of
                      the 32 channels to be further processed in the DMU (phasemeter backend)
                      The phasemeter shall be compatible with:
OMS-4.3.2.5-1/ R, I
                      1. Heterodyne frequency between 500 and 5000 Hz with a nominal value of 1 kHz and a resolution of TBD Hz
                      2. An optical power on the photodiodes of 1 mW (nominal operation) to 2 mW (absolute maximum rating)
                      3. A fringe rate of up to 40 Hz without loosing track of the integer number of fringes (corresponding to a
                      testmass motion of 20 µm/s). Reduced noise performance is allowed at this speed.


                      The Phasemeter shall be delivered with electrical harnesses for the following signals:
                      - 8 MHz clock
OMS-4.3.2.5-3/ R, I   - MIL Bus
                      - Serial data TBD
                      - Bias to and photo current from photodiodes
                      The electrical interface between the phasemeter and each four-quadrant photodiode on the optical bench shall
OMS-4.3.2-12/ R, I    consist of a shielded 5-thread cable with a nano-D connector on the diode side and a sub-D connector on the
                      phase meter side (TBC).
                      The longitudinal metrology noise in the x1-x2 and x1 interferometers shall be smaller than the expression
                      below.
                      This refers to optical pathlength and corresponds to 4.5 10-12 m/√Hz for the Test Mass position/distance
                      noise. This allocation includes;
                      o Laser and AOMU related noise sources (power, frequency, etc.)
                      o Phasemeter related noise (digitization noise, electronics noise, etc.)
                      o Thermal effects of the OB
                      But does not include interface-related noise such as;
                      o Optical window
                      o TM tilt-to-shift coupling etc.
OMS-4.3.3-1/A, T      Note: The allocation of the noise contributions to the particular sources is TBD.




                      The Differential Wavefront Sensing (DWS) alignment metrology noise shall be smaller than the expression
                      below
                      This refers to TM tilt angle and shall be applicable for well-aligned test masses (+/- 50 µrad as determined by
                      the DWS alignment metrology).


OMS-4.3.3-2/A, T




                      The Differential Wavefront Sensing (DWS) alignment metrology shall produce monotonous valid signals for
OMS-4.3.3-3/A, T      Test Mass misalignments smaller than +/-300 µrad, referred to the DWS alignment metrology zero position.

                      For Test Mass misalignments between +/- 300 µrad and at least +/- 1000 µrad, referred to the Differential
                      Wavefront Sensing (DWS) alignment metrology zero position, the phasemeter DC alignment metrology shall
OMS-4.3.3-4/A, T
                      provide monotonous valid signals indicating the magnitude and direction of the Test Mass misalignment.

                      Laser power fluctuations (on Test Mass ) shall be smaller than given by the expression below, relaxing as
                      1/f^2 up to 30 mHz. (TBC, see detailed budget)




OMS-4.3.3-5/A, T




                      The straylight contribution within each interferometer beam shall be attenuated to at least 10-6 of the signal
OMS-4.3.3-6/A, T
                      amplitude (TBC).
                      All drawings, specifications and engineering data shall use exclusively the International System of Units (SI
OMS-5.1.1-1/R T
                      units).
                    The in-orbit design lifetime shall be 24 months. This shall also concern all consumables, if any required.
                    In detail the OMS shall be designed to meet the needs of the operational phases in the environmental
                    condition defined in section 8 of this document of:
                    • 2 months LEOP and transfer
                    • 1 month commissioning phase
OMS-5.1.2-1/ R
                    • 4 months operational lifetime
                    • 2.5 months not operational
                    • 0.5 months operational lifetime
                    • 3 months extended operational phase

                    The OMS shall be designed such that it can be stored on ground for at least 1 year, under controlled
OMS-5.1.2-2/R
                    environment conditions, with minimum need for preventive maintenance.
                    The OMS design shall be compatible with an instrument reliability >0.9 for the overall in-orbit mission life.
OMS-5.1.3-1/ A
OMS-5.1.3-2/R       If single point failures cannot be avoided, it shall only be implemented after approval of the Agency.
OMS-5.1.3-3/ R      Fracture control analysis shall be performed as required by the Fracture Control Plan AD TBD.
OMS-5.1.4-1/ A      Failure propagation from one function to another shall be avoided.
                    The OMS equipment shall be designed in such a way that any failure cannot be propagated inside the unit
OMS-5.1.4-2 / R A
                    (e.g. to redundant chain).
                    The OMS equipment shall be designed in such a way that any failure cannot be propagated towards other
OMS-5.1.4-3 /R A
                    equipment, through electrical harness or by thermal or mechanical effects.
                    The equipment shall be designed in such a way that nominal and redundant functions are electrically
OMS-5.1.4-4 /R T
                    separated, i.e. use separate electrical components.
                    The OMS design shall minimise, to a reasonable extent, single point failures. If single point failure exists, it
OMS-5.1.4-5 /R A
                    shall be clearly identified together with all the necessary
                    All OMS constituents subject to planned maintenance shall be designed, selected and installed to facilitate the
OMS-5.1.5-1/ R      execution of such tasks with minimum hazard to the equipment and personnel. The design shall provide
                    maximum use of standard tools and test equipment.
                    The OMS shall be designed such that it routine checks and maintenance operations will not be required later
OMS-5.1.5-2/ R
                    than 3 months before launch.
OMS-5.1.5-3/ R      Identical units shall be exchangeable.
                    The OMS equipment shall be designed to minimize the generation of loose particulate matter or liquid or
                    gaseous contamination. The hardware shall be manufactured, handled and controlled within an environment
OMS-5.1.6-1/ R
                    of increased cleanliness and low contamination levels. Outer surfaces shall be cleaned to a level “visible
                    clean” and shall require standard cleaning equipment only.
OMS-5.1.6-2/ R      The environment during assembly of the equipment shall meet class 100.000 as a minimum.
                    Particulate contamination shall not exceed 200 ppm (TBC) at instrument delivery on sensitive optical surfaces.
OMS-5.1.6-3/ R I    Other surfaces shall be visibly clean. The cleanliness shall be controlled according the requirements defined in
                    GDIR AD1 and the Contamination Control Plan AD TBD.
                    Molecular contamination shall not exceed 1*10-7 unit ? (TBC) at instrument delivery on sensitive optical
OMS-5.1.6-4/ R I    surfaces. Other surfaces shall be visibly clean. The cleanliness shall be controlled according the requirements
                    defined in AD2 TBD
                    The units shall be able to operate within a pressure range of 1 bar to 1*10-10 mbar. It shall have a suitable
                    venting provision, that is 2 mm² venting hole area per litre volume. Outgassing vents shall be < 5mm diameter
OMS-5.1-1 /R TBC
                    and shall be located closest to but not within the unit mounting plane. For EMC reasons, there shall be no
                    other openings than necessary for connectors and venting holes.
                    The units shall be designed to withstand a relative humidity of 60% maximum during testing and transport (no
OMS-5.1-1 / R
                    condensation is allowed ).
                    Each OMS element shall include a mass contingency margin, depending on its development status, as
                    follows:
                    Completely New Developments                            - 20% Margin
OMS-5.2.1-1 /R A
                    New Developments derived from existing hardware - 15% Margin
                    Existing units requiring minor modification             - 5 % Margin (10% TBC)
                    Existing units requiring no modification                - 0% Margin
                    The mass of the particular units of the OMS shall be not greater than stated in the table below (TBC).
                    The specified mass values include margin according to OMS 5.2.1-1
                    Optical Metrology S/S
                    Optical Bench Assy. Including optical bench interferometer (4.2kg) 14.00kg
OMS-5.2.1-2 /R
                    Laser Assembly                                                       3.90kg
                    Acouso-Optic Modulator (AOMU)                                          1.90kg
                    Laser unit                                                           1.03kg
                    Phasemeter Front End Electronics                                       4.17kg
OMS-5.2.1-3 /T      A best engineering estimate of the CoG shall be given latest 2 months after the contract ATP (TBC).
OMS-5.2.1-4 /T      The CoG shall be measured with an accuracy of +/- 0.5 mm (TBC).
                    The mass and moment of inertia of the payload shall be controlled such that they are known with accuracy
OMS-5.2.1-5 /R      better than 0.5%. During early design phases larger uncertainties are allowed on the mass, as per OMS-5.2.1-
                    1.
                    The structural interfaces of the OMS to LTP and/or spacecraft shall be such that the mechanical
OMS-5.2.2-1 /T A
                    environmental requirements are fulfilled.
                    The optical bench interferometer (OBI) shall be designed against a design load of 64g quasi-static load (TBC).
OMS-5.2.2-2 /A
                    The definitions in AD3 are applicable. For limit loads (see AD3, AD4) the probability shall be more than 99%
OMS-5.2.2-3 /A R
                    with a confidence level of 90% during the service life.
                    Materials and material A-level properties shall be used in accordance with AD5. This requirement is also
OMS-5.2.2-4 /A R
                    applicable for the material and material properties of mechanisms.
                   The definitions in AD3 are applicable.
                   The following Factors of Safety (FoS) are to be applied on Design Loads:




OMS-5.2.2-5 /A R




                   In addition to the safety factors identified for the analysis of a structure the following shall be used for
                   mechanisms:




OMS-5.2.2-6 /A




                   Fundamental frequencies are defined as structural eigenfrequencies with effective mass greater than 10% of
OMS-5.2.2-7 /R A
                   the total unit mass.
OMS-5.2.2-8 /R     deleted
                   The OBI shall achieve a structural stiffness ensuring that the first fundamental frequency of the launch
                   configuration with effective mass greater than 10% is at least 250 Hz (TBC) in hard mounted conditions fixed
OMS-5.2.2-9 /R     at its 8 inserts (fixation points for side slabs, four at each side). The inserts will be manufactured and mounted
                   by the customer.
                   Note: Optical bench assembly will be tested on LCA level.
                   OMS electronic units fixed to the S/C on a rigid interface shall have their first main resonant frequency above
OMS-5.2.2-10 /R
                   140 Hz (TBC). Any exceptions shall be identified to the customer.
OMS-5.2.2-11 /R    deleted
OMS-5.2.2-12 /R    Stiffness margin on every part of the OMS shall cover design, material and mass uncertainties
                   The design shall guarantee, under the worst combinations of mechanical and thermal loads as derived from
                   the analysis :
                   a. survival and functionality of the structure
OMS-5.2.2-13 /R    b. positive margins of safety for yield and for ultimate loads, such that it shall not result in permanent
                   deformation and loss of functionality or rupture
                   c. positive margins of safety for buckling loads, such that it shall not result in buckling or collapse, taking into
                   account a non-perfect geometry of the failing elements.
                   The following structural failure modes, for OMS units at all levels of integration, shall be prevented:
                   • Permanent deformation,
                   • Yield,
                   • Rupture,
                   • Instability,
                   • Buckling,
OMS-5.2.2-14 /R
                   • Gaping of bolted joints, of storage devices,
                   • Degradation of bonded joints,
                   • Vibration induced mounting interface slip,
                   • Loss of alignment of units that are subjected to alignment stability requirements, distortion violating any
                   specified envelope,
                   • Distortion causing functional failure or short circuit.
OMS-5.2.2-15 /R    For sine vibrations, the mechanical sizing should be performed with peak values.
OMS-5.2.2-16 /R    For random vibrations, the mechanical sizing should be performed with 3 times the rms value.
                   All safety factors shall be applied in accordance with AD3 and shall be applicable also to subsystems and
OMS-5.2.2-17 /R
                   equipments.
                   The OMS shall be designed to withstand the mechanical loadings encountered during its entire life, including
OMS-5.2.2-18 /R
                   ground handling, transportation, testing, launch, and operation phases.
                   The OMS must be designed and operated so as to minimise thermal transients and associated thermo-elastic
OMS-5.2.2-19 /R
                   structural distortions.
                   The OMS payload shall be designed to withstand all thermal environment encountered during its entire life,
OMS-5.3-1 /R
                   including ground handling, transportation, testing, launch, and operation phases.
OMS-5.3-2 /R       The OMS payload design shall permit analysis by a thermal mathematical model.
OMS-5.3-3 /R       The OMS thermal design shall be testable on ground.
                   The thermal analyses on OMS unit level shall prove that for the temperature limits, as specified in OMS 5.3-16
OMS-5.3-4 /R
                   and considering OMS 5.3-14 the LTP units provide full performance.
                   The thermal design and analyses shall support the definition of the thermal stability requirements to be fulfilled
OMS-5.3-5 /R       by the spacecraft at the OMS thermal interface locations for all the applicable mission phases and taking into
                   account the required OMS operational profile.
                The thermal design and analyses shall also demonstrate that the internal thermal stability of the OMS payload
OMS-5.3-6 /R    is fulfilled during all the applicable mission phases and taking into account the required OMS operational
                profile.
                Deviations and temporal degradations from the nominal values of external and internal fluxes, thermo-optical
OMS-5.3-7 /R    properties, heat capacitances and conductive and radiative couplings shall be taken into account in the
                thermal analysis.
                The use of the ESARAD and ESATAN software packages is recommended for all thermal analyses and it is
                required for all deliverable interface thermal mathematical models (TIMM as defined in OMS-10.2-3 and OMS
OMS-5.3-8 /R
                10.2-7), excluding geometrical models if not otherwise specified.
                For time resolved analysis special tools shall be made available.
                For verification and validation of the thermal performance of the design selected, analysis results obtained in
RS 5.3-9 /R     the time domain have to be transferred into the frequency domain by means of spectral analysis tools (Fourier
                transformation).
                A thermal reference point located on the unit surface preferably close to a mounting bolt and representing the
OMS-5.3-10 /R   unit´s average temperature at the I/F shall be defined and instrumented for all units during ground testing and
                shall be used for all analyses as “interface temperature”.
                The thermal control function shall include sufficient thermistors for telemetry with the purpose of evaluation of
OMS-5.3-11 /R
                the performance of the thermal control in-orbit.
                The temperatures identified through the steady state thermal analysis shall be corrected for each equipment
                node with uncertainty values, called UFP (Uncertainty Flight Prediction), from the following expression:
                UFP = SQRT (Us^2+Ufe^2)+Ui
                Where;
                US is the RSS (Root Sum Square) uncertainty due to OMS parameters.
                UFE is the RSS uncertainty due to flight environment parameters.
                UI is the expected uncertainty due to idealisation (analytical modelling) errors.
                The UFP shall be calculated via sensitivity analyses for major parameteOMS-affecting the complete payload
OMS-5.3-12 /R   and the selected flight cases. UFP is not applicable to thermal stability.
                The Test-Predicted Temperature deviation (TTi) for each node i is defined as:
                TTi = TTMi - TTPi
                Where;
                TTMi is the measured test temperature.
                TTPi is the predicted test temperature.
                The temperatures calculated by the thermal analysis and corrected with the UFP must be within the unit
                design temperature limits.

                The following three correlation criteria shall be applied:
                - For model test correlation, the histogram centroid of TTi shall be within +/- 1.5 °C of zero.
OMS-5.3-13 /R
                - The standard deviation shall be less than: (UFP-1.5)/3
                - For each individual Measurement point, TTi shall be less than or equal to UFP.
                The design limits of a unit are equal to the qualification limits decreased at both ends by a margin of 10 °C
OMS-5.3-14 /R
                and/or equal to the acceptance temperature limits decreased at both ends by a margin of 5 °C
                Depending on the operational status, the OMS unit dissipations shall not exceed the following range, values
                TBC, no margins applied: (detailed power (dissipation) budget depending on operation modes, etc. to be
                established)




OMS-5.3-15 /R
                   The applicable OMS units (“physical boxes”) temperature limits shall be (unit item list in table top rows is
                   TBC), values TBC:




OMS-5.3-16 /R




                   All electrical performances are specified under Worst-Case End-Of-Life conditions, unless otherwise explicitly
                   notified.
                   Beginning-Of-Life criteria shall be derived by the Unit Supplier from the specified parameters for testing and
                   acceptance of all on-board units.
                   Note:
                   All interfaces are referenced by a specific Interface Code. Table 5.4-1 below lists all the standard interfaces:




OMS-5.4-1 /R




                   The contractor shall design the load side of the LCL interface to be compliant to the characteristics as defined
OMS-5.4-2 /RT
                   in EID-A TBC
                   All electronic logic units/circuits shall assume a defined and safe configuration upon application of power in
OMS-5.4-3 /R
                   nominal conditions.
                   All power converters shall work in both synchronized and free-running mode. The converters shall be capable
OMS-5.4-4 /R
                   of free-running in case the synchronisation signal is OFF.
OMS-5.4-5 /T       The free-running frequency shall be limited to ± 10% of the nominal frequency.
                   Units shall be designed taking into account the source impedance defined in Figure TBD for Regulated
OMS-5.4-6 /RT
                   primary power lines.
                   The OMS shall interface with the DMU handling the following signals:
                   - Phasemeter raw data via the MIL bus
                   - Laser frequency control via the MIL bus
OMS-5.4.2-1 /R T   - Set points For the LA/AOMU control via the MIL bus
                   - Monitor, status and control signals via the MIL bus
                   - Master cloch and heterodyne frequency as both SBDL signals via SMA
                   (TBC) connectors
                   The OMS design shall comply with the spacecraft EPSS that will provide a power bus regulated at 28 V.
OMS 5.4.3-1 /R
                     The nominal voltage to be delivered to OMS is:
                     Voltage: 28V -1.14 V +0.14 V DC nominal.
                     Current: 1 A max.
OMS 5.4.3-2 /R
                     For load transients of up to 50 % of the nominal load, bus transients will not exceed 1 % and the bus voltage
                     will remain within 5 % of its nominal value during all source transients and load transients in nominal operation
                     with a recovery time of 2ms. (TBC)
                     The OMS design shall comply with a spacecraft regulated bus that will have a nominal ripple voltage in the
OMS 5.4.3-3 /R T
                     time domain below 0.5 % peak to peak of the nominal bus voltage.
                     No single point failure in the OMS payload, including failure of wiring and connectors, shall short the main
OMS 5.4.3-4 /R A     electrical power bus or cause any over voltage.
                     For requirements on power consumption, refer to § 7.4.1
                     Unconditioned power distributed from the Power Control and Distribution Unit (PCDU) is called primary power.
                     The satellite grounding scheme is a distributed star-point grounding (DSPG). In the integrated spacecraft the
OMS-5.4.4-1 /R       primary power MINUS will be referenced to structure at the Star Point (within the S/C PCDU).
                     The local grounding concept of OMS shall be “Distributed Single Point Grounding” (DSPG) system.

                     The user of the primary power shall be prohibited from grounding the power line to structure and shall maintain
                     a DC isolation of at least 1 MΩ between the primary power input leads and chassis and between the primary
OMS-5.4.4-2 /RT
                     power input and secondary power.
                     This shall be verified by an isolation measurement.
OMS-5.4.4-3 /RT      Equipment EGSE and subsystem EGSE shall reference their structure to the test ground plane.
                     Power which is transformer isolated from the primary power bus is called secondary power.
                     Equipment containing dedicated power converters shall reference their secondary power return directly to the
OMS-5.4.4-4 /RT      unit chassis. The bonding resistance shall be ≤ 20 mΩ.
                     This shall be verified by measurement of the resistance between secondary power ground and unit housing.

                     Signal circuit receivers shall be isolated from secondary power and chassis. The isolation resistance shall be >
OMS-5.4.4-5 /R
                     150 kΩ.
                     Where single-ended signal transmitters are used, independent signal returns are required. Ground reference
OMS-5.4.4-6 /R
                     lines shall not be used as signal returns. Exception: All coaxial cables / connections.
                     The unit bonding resistance between all unit metallic parts shall be < 100 mΩ. The unit shall be delivered with
OMS-5.4.4-7 /RT      a bonding stud with a resistance < 20 mΩ. The bonding stud shall be a M4 bolt, minimum length is 10mm.
                     Small items may provide a grounding insert instead of a bonding stud.
                     Connectors location and harness routing shall be agreed upon between the LPF and the OMS contractors
OMS-5.4.5-1 /R
OMS-5.4.5-2 / R      Power harness to each OMS unit shall be provided by the LPF Contractor.
                     Non-magnetic connectors and shells shall be used, not used contacts shall be equipped, too.
                     All connectors shall be normal density DxMA types, special connectors or at of-theshelf equipment may be
                     from other type. In this case, the connector counterpart shall be delivered together with the unit.
                     Cable shields are to be connected to the outside of the box, i.e. via the connector shell. The connection must
                     be of low impedance. A pigtail connection from shield to connector shell is not allowed.
OMS-5.4.5-3 /R I     In no case it is allowed to route a cable shield via a pin into the unit housing, to be terminated to ground inside.
                     If a high current, low DC impedance termination of the shield is required, the shield may be additionally
                     grounded via a low impedance pigtail wire to the outside of the unit.



                     The OB envelope dimensions shall be compatible with the LCA overall envelope:
                     x ≤ 640 mm
                     y ≤ 375mm
OMS 7.1.1-1 /R
                     z ≤ 375 mm
                     The LTP accommodation envelope is shown in Figure 7.1-1 for information.
                     The actual OMS envelope figures are TBD, pending on the design of the thermal shield.
OMS-7.1.1-2 /R       The dimensions of each OMS item shall be known to accuracy better than TBD mm. (0.5 mm TBC).
OMS 7.1.2-1 /T A R   The requirements of AD1 (GDIR Issue 4) GDI 160 to 191 are fully applicable
                     The OBA side slabs shall provide I/Fs to the IS head according to AD6. For tolerances and dimensions see
                     AD7 and AD8.
OMS-7.1.3-1 /R, T    Note:
                     The IS Head shall be fixed to the optical bench using the I/F flanges defined by AD6 with 2 points on one side
                     each. Two flanges are part of each IS housing (CGS deliverables).
                      The OBA side slabs shall provide I/Fs to the strut brackets according to AD10
OMS-7.1.3-2 /R, T    Note: For the optical interface between OMS and ISS (window etc.) refer to paragraph 7.3 of this specification.

                     Except otherwise specified, when OMS units are fixed to the S/C on a rigid interface shall have their first main
                     resonant frequency above 140 Hz (TBC). Any exceptions shall be identified to the customer.
OMS-7.1.4-1 /T A
                     Main resonant frequency is defined as frequency such that associated effective mass is greater or equal to 10
                     % of the total unit mass.
                     OMS unit dissipated thermal power values according to OMS-5.3.15 shall be considered for the S/C thermal
OMS-7.2.1-1 /T A
                     control design.
                     OB photodiodes and wires coming from LCA external equipments shall be the only power sources on the OB.
OMS-7.2.1-2 /T A     Remark: Any Dissipation from Diagnostics inside LCA TBD

OMS-7.2.1-3 /T A     The power dissipation on the OB due to photodiodes shall be less than 50mW. (TBC)
                   OB Photodiodes power fluctuation shall be in accordance with the following figures:
                   • DP/P = 4*10-3 /Hz1/2 for frequencies ≥1.8* 10-3 Hz
                   • DP/P = 6*10-5 /Hz1/2 for frequencies <1.8* 10-3 Hz




OMS-7.2.1-4 /T A




                   Thermal analysisof OMS electronic units shall comprise analysis of I/F temperature fluctuations due to
OMS-7.2.1-5 /A
                   dissipation fluctuations resulting from bus voltage fluctuations.
OMS-7.2.2-1 /T A   deleted
OMS-7.2.3-1 /R T   OMS units thermal I/Fs shall comply with the mechanical and EMC requirements.
                   The overall interface conductance at the IS/OB interface flanges (between interface flange and titanium insert)
OMS-7.2.3-2 /R T
                   shall be less than TBD W/m²K.
                   The overall interface conductance between OB (titanium insert) and Strut Brackets shall be less than TBD
OMS-7.2.3-3 /R T
                   W/m²K
                   The overall thermal radiative coupling between IS vacuum enclosure and OB shall be less than TBD W/K^4
OMS-7.2.3-4 /R T
OMS-7.2.3-5 /R T   The overall thermal radiative coupling between Thermal Shield and OB shall be less than TBD W/K^4
                   The OMS thermal control system of the single OMS units shall follow the guideline established in Figure 7.2-1.
                   (below)




OMS-7.2.4-1 /T A




                   OMS electronic units (boxes) shall be conductively controlled, i.e all electronic units shall have excellent
                   conductive coupling (I/F filler to be applied) to the S/C via their base plate together with a high emissive
OMS-7.2.4-2 /R T
                   surface (ε > 0.85) in order to reduce thermal gradients between the electronic units housing and the S/C as far
                   as possible.
                   The temperature reference point (TRP) shall be selected on the unit external surface, preferably close to a
                   mounting bolt, such that its temperature reflects the average unit housing temperature (no hot or cold spot).
OMS-7.2.4-3 /T A
                   The temperature reference point will be used as reference for the thermal testing and shall be maintained
                   within the specified temperature limits during flight.
                   The temperature reference point (TRP) temperature range of OMS units shall be agreed between the
OMS-7.2.4-4 /R
                   customer and the supplier and defined in an ICD.
OMS-7.2.4-5 /R T   For non-isothermal units the number of temperature reference points shall be increased accordingly.
                   All thermal hardware mounted in the unit shall be identified in the ICD, e.g. heaters, temperature sensors,
OMS-7.2.4-6 /R
                   tapes, MLI.
                   Temperature monitoring of selected points within a unit shall be provided by the unit supplier to cover the
                   cases:
OMS-7.2.4-7 /R
                   a) Unit operational safety monitoring
                   b) Unit operational temperature and performance monitoring.
OMS-7.2.5-1 /R     OMS unit I/F temperatures according to OMS-5.3.16 shall be applied
                   Specifically, the temperature experienced by the optical bench at its mechanical interfaces (IS flange / OB and
OMS-7.2.5-2 /R
                   OB / Strut bracket) shall be inside the range 20°C ± 10°C during operation.
                   The temperature fluctuations experienced by the optical bench at its mechanical interfaces, shall be less than
OMS-7.2.5-3 /R
                   10-4 K/Hz0.5 in the frequency range of 1 – 30 mHz.
                    The temperature experienced by OMS electronic units measured at the TRP (temperature reference point)
OMS-7.2.5-4 /R
                    shall be inside the range as defined in OMS 5.3-16.
OMS-7.3-1 /A, T     • Alignment of IS Head wrt. Optical Bench incl. window effects: 50 (TBC) µm
                    The angle mismatch between the interferometer axis frame (IAF) and the FRF shall be smaller than +/- 300
                    µrad.
OMS-7.3-2 /A, T     This includes the following contributions:
                    • Optical bench alignment: TBD µrad
                    • Alignment of IS Head wrt. Optical Bench incl. window effects: TBD µrad
                    For the optical window providing the laser beam access from optical metrology to the TM a diameter of (tbc)
OMS-7.3-3 / R,I
                    30 + 0mm / -0.2mm shall be assumed.
                    The maximal change of optical path length between OMS and TM (due to an optical I/F) shall be not more
                    than 1pm / √Hz @ MBW.
OMS-7.3-4/ T
                    Note: E.g. applying a window thickness of 6 mm, window tilt angle of 2.5º and coefficient of refraction n = 1.6
                    the transfer function is 10-4 m/rad leading to a stability of 10nrad/√Hz @ MBW.
                    A reference point (e.g. optical cube) shall be introduced in the OB design being accessible for optical and
                    mechanical position and attitude measurements during integration of IS Heads with OB. A co-ordinate transfer
                    matrix from the OBF and IAF to this location shall be established. The reference point shall be defined in
OMS-7.3-5/ R,T      terms of translational and rotational co-ordinates to a precision of smaller TBD µm in y- and z-axes and
                    smaller TBD µm in x-axis and tbd µ rad, respectively.
                    Note: The actual alignment requirement figures as well as the methods to be adopted are presently still under
                    detailed study and be included in this specification not before the next issue.
                    For the development of the OMS units the power budget (28 V regulated) for LTP shall be applied where
                    applicable as provided in the following table (items breakdown and values are TBC):




OMS -7.4.1-1 /R




OMS 7.4.1-2 / A T   Bus voltage ripple and spikes: as defined in the EMC paragraphs of AD1
                    LTP payload design shall have included a power contingency margin, depending on its development status, as
                    follows:




OMS 7.4.1-3 /R




                    The OMS shall provide mechanical interfaces for handling, testing and transport, e.g.
                    • interfaces to transport container
OMS-7.5-1 /R
                    • interfaces to handling frames, trolley, lifting devices
                    • interfaces to test adapters (vibration test, thermal test)
OMS-7.5-2 /R        Wherever possible mechanical integration and test interfaces shall be removed for flight.
                    The OMS shall provide interfaces for alignment measurements, e.g. alignment cubes or alignment mirrors at
OMS-7.5-3 /R        locations accessible at all relevant integration stages and after environmental testing. Please refer especially
                    to req. OMS-7.3-5
                    The OMS shall provide one permanent mount near each ISH on the OBI base plate which shall be able to
                    reproducibly position and fix a removable optical element (e.g. a 45 ° mirror). The removable optical element
OMS-7.5-4 /R        shall allow optical alignment measurements on the optical axis towards the EH and the TM using additional
                    external OGSE(e.g. an autocollimator). At least one item of the removable optical element (non-flight item)
                    shall be provided. Please refer especially to req. OMS-7.3-5
                    The OMS shall provide interfaces for system electrical integration and functional testing,
                    e.g.
OMS-7.5-5 /R        - electrical interfaces (connectors) to test equipment
                    - stimuli / feedback interfaces to spacecraft (if any)
                    Electrical connections to test equipment shall be made via connector savers.
OMS-7.5-6 /R        Integration and test interfaces shall be compliant with LTP cleanliness requirements.
                    The OMS shall be designed and manufactured to meet the subsystem requirements after being subjected to
OMS-8.1-1 /R        the environmental conditions existing during all periods from ground activities till the end of in-orbit operation.
OMS-8.1-2 /R      The applicable in-orbit and terrestrial space environment is specified in AD1.
OMS-8.1-3 /A      The OMS components shall perform within specification in the environment of the final orbit.
OMS-8.1-4 /R      Handling, transportation loads and test loads shall not be design drivers.
                  The OMS shall comply with the requirements as defined in GDIR section 4.2 (AD1). The laser assembly (LA)
OMS-8.2-1 /A
                  as well as the phasemeter unit at TBD locations at the shear walls.
OMS-8.2-2 /R      The OBI shall comply with the requirements for random and sinus vibration as given by tables xy below.
OMS-8.4-1 /R      The design of the OMS shall comply with the requirements of section 4.5 of AD1
OMS-8.4-2 /R      For the Optical Bench a magnetic cleanliness program shall be applied. Details see AD10.
OMS-8.4-3 /T      The magnetic moment of the Phasemeter unit shall be ≤30 (TBC) mAm².
                  Magnetic Moment Test - The magnetic moment shall be measured in all three axes with rotational
                  measurements over 360° in 10° steps, either with one rotation using a threeaxes magnetometer (preferred
                  measurement method), or with three measurements in different orientations using a simple magnetometer.
                  - The measurements shall be performed with unit OFF
                  − initial measurement, as built, at standard measurement distance
                  − deperm unit in three axes with 50 Gauss, 3 Hz, 10 min
                  − after perm, measurement at standard distance
                  − perm unit in three axes with 3 Gauss
OMS-8.4-4 /T      − after perm, measurement at standard distance
                  − final deperm in three axes unit with 50 Gauss, 3 Hz, 10 min
                  − after final deperm, measurement at standard distance
                  − the last measurement shall be repeated using the standard measurement distance increased by 10 cm.
                  − strayfíeld measurement (measurement at standard distance with the unit operating in nominal mode)
                  The unit shall be located in the center of the Helmholz coil system. Standard measurement distance shall be 1
                  … 2x of the largest unit dimension. ².


                  Magnetic Multipole Model - From the data measured a multipole model shall be calculated with at least 3
OMS-8.4-5 /A      magnetic dipoles, using e. g. the Ganew-Model. The multipole model shall comprise the magnetic dipole
                  vectors as well as the location of the dipoles within the unit coordinate system.
OMS-8.5-1 /R      Definitions and requirements of AD1 shall apply.
                  A Detailed Mechanical Stress Analysis shall be established for LTP and its major units. This shall include at
                  least:
                  - a description of the configuration analysed with reference to interface controlled drawings,
                  - a description of the mathematical finite element model and/or of the assumptions taken to verify the
                  structure,
                  - a description of all possible loading cases and an identification of the design driving load cases or load
                  combinations,
OMS 10.1-1 /R
                  - detailed description of the most loaded elements listed with relevant stresses, and the loading cases that
                  generated them,
                  - a list of the materials and structural components with characteristics data sheets (including long-life effects
                  under space environment),
                  - a Set of tables showing, For each structural element, the maximum value on each type of stress or
                  combination of them with the allowable value, and the load case that determines it, together with its margin of
                  safety.
                  A structural mathematical model of the instrument and its major units shall be established that is detailed
                  enough to predict the loads to size the structure elements, and the interface loads in particular, with sufficient
OMS 10.1-2 /R
                  accuracy. This means that it shall be able to reproduce the low frequency modes with an upper limit to the
                  frequency range to be defined on a case-by-case basis.
                  The LTP industrial Architect shall be provided by the responsible subsystem and unit contractors with a
                  structural mathematical model of the major LTP units. The models shall be able to reproduce the low
                  frequency modes with an upper limit to the frequency range to be defined on a case-by-case basis. (derived
                  from GDIR GDI-197/CREATED/A)
                  Finite elements models shall be provided for all items which have principal modes of vibration at frequencies
OMS 10.1-3 /A     less than:
                  - 140 Hz actual or,
                  - 161 Hz if predicted by FE model (i.e. +15% margin) or,
                  - 182 Hz if predicted by hand calculation (i.e. +30% margin).
                  The supplied FEM shall represent all significant modes, i.e. modes with an effective mass equal to or larger
                  than 10% of the total equipment mass.
                  The finite element model shall be prepared using NASTRAN Software Version 70.7 or later with all elements
OMS 10.1-4 /R
                  compatible with 70.7. The NASTRAN version shall be indicated as part of the model data.
                  The physical finite element model shall be accompanied by a clear description of the model itself and of the
                  assumption made in the model, particularly concerning the boundary conditions at the spacecraft interfaces.
OMS 10.1-5 /R
                  For mechanisms, two or more models (stowed, deployed, general position, engaged, etc.), may be required.

                  A thermo-elastic model shall be established for LTP system level. The LTP industrial Architect shall be
OMS 10.1-6 /R     provided by the responsible subsystem and unit contractors with the necessary input concerning their units
                  and equipment.
OMS 10.1-7 /R     All mathematical models shall be maintained in current configuration.
                  Mechanism Functional Analysis - Each mechanism shall be analysed functionally and the following information
                  shall be at least supplied:
                  - a detailed description of the mechanisms, with particular reference to its discrete components (bearings,
                  actuators, switches) and to its operational/safety features,
                  - a detailed description of the operating modes with reference to ground and orbital activations,
                  - a definition of operating loads in various configurations with a clear definition of analysis assumptions, in
OMS 10.1-8 /A R
                  particular, the functional analysis shall include the effects of the worst environmental conditions that could
                  produce distortions or changes in clearance between movable parts (e.g. thermal gradient through bearings),
                  - a Failure modes, Effects and Criticality Analysis (FMECA) defining the Failure modes and the functional
                  margins of safety against each of them,
                  - a performance description of the control system that the mechanisms form a part of.
                   S.I. units are to be used for the mechanical models:
                   • Newton (N) for force
                   • Kilograms (Kg) for mass
OMS 10.1-9 /A R    • Meters (m) for length
                   • Seconds (s) for time
                   • Degrees Celsius (°C) for temperature
                   Further unit definitions are given in [AD1].
                   Coordinate systems shall be according to Chapter4.1.
OMS 10.1-10 /R
                   Additional reference CS shall be in accordance with [AD1].
                   The following post-run checks shall be performed on each model in accordance with [AD1];
                   - Mass Property Check
                   - Conditionioning Check
                   - Gravity Load Check
                   - Constraint Check
OMS 10.1-11 /A R   - Rigid Body Frequency Check
                   - Thermo-Elastic Stress Check
                   - Constraint Check
                   - Rigid Body Frequency Check
                   - Thermo Elastic Stress Check
                   Details over each of such tests are to be found in [AD29]
OMS 10.1-12 /A R   For the Thermo-Elastic Stress Check, the conditions given in [AD1] shall be satisfied
OMS 10.1-13 /R     Model size and identification numbering (TBD)
OMS 10.1-14 /R     Models shall be full models with no symmetry assumptions made to reduce the size.
                   The structural mathematical model description (report) shall be in accordance with [AD1]. An abstract, of what
                   it shall include at least is given below:
                   - a description of the configuration analysed with reference to interface controlled drawings,
                   - a description of the mathematical finite element model and/or of the assumptions/reductions introduced in
                   the analysis,
                   - a description of the checks performed on the model to verify its quality (e.g. rigid body modes, residual
OMS 10.1-15 /A R   forces),
                   - a list of eigenfrequencies with relevant mode type and associated modal effective masses,
                   - plots and listings of eigenvectors.
                   - Description of the reference frame used (a drawing, the rotation and translation matrixes with respect to a
                   single coordinate frame are required
                   - mass breakdown and distribution in the models
                   - Electronic files saved on CD-ROM containing all BULK data For the analyses and the model checks
                   The thermal performance of the OMS and each of its unit shall be calculated by means of time resolved
OMS-10.2-1 /R      thermal mathematical models. The contractor shall use models for design purposes and shall also provide
                   interface models for use during the system/spacecraft design.
                   The degree of detail (i.e. number of nodes and conductors, etc.) shall be at least sufficient to show that all
                   interface requirements are met. The model shall allow performing transient analyses; hence a thermal
OMS-10.2-2 /R      capacity must be allocated to each node. Heat dissipation shall be identified, along with indication of the
                   appropriate operating mode. The number of operating modes considered for thermal modelling purposes may
                   be a reduced set of the total number.
                   A Thermal Interface Mathematical Model (TIMM) shall be set up for each OMS unit and for OMS with respect
                   to the S/C meeting following requirements:
                   - The minimum number of isothermal nodes shall be three, representing the unit's housing, baseplate and
                   interior. More nodes up to ten shall be generated if considerable temperature gradients along the baseplate or
                   the housing must be expected.
OMS-10.2-3 /R      - the TIMM shall be in ESATAN format.
                   - the TIMM temperature predictions shall be correlated with the predictions of the detailed TMM of the unit.
                   This correlation is to be considered sucessfully obtained when the node temperatures of the TIMM are within ±
                   3 K of the corresponding nodes of the detailed TMM.
                   - the thermal test results (temperature distribution at hot and cold levels) shall be used to update the TIMM.

                   A Geometrical Mathematical Model (GMM) shall be established for each OMS unit if not otherwise agreed.
OMS-10.2-4 /R
                   The GMM shall be in ESARAD format.
                   The thermal model of a unit shall be verified and correlated with a thermal test. The correlation criteria shall
                   be:
OMS-10.2-5 /T A
                   +/- 2 K on the temperatures
                   +/- 10 % on the required heater power
                   For the OMS an optical mathematical model (OMM) for numerical simulation of the units shall be established.
OMS-10.3-1 /A
                   This model shall be based on the complete set of latest specifications and tolerances that are available about
                   The OMM shall include not only the actual optical elements but also intermediate image planes, intermediate
OMS-10.3-2 /A
                   pupil imaging planes wherever applicable.
OMS-10.3-3 /A      The numerical model shall be developed on Code V
OMS-10.3-4 /A      The OMM shall be based on the complete set of latest specifications and tolerances that are available about
                   The numerical model shall be used for the evaluation of the unit’s optical performance.
                   Actual glass characteristics as measured by the glass supplier shall be included.
OMS-10.3-5 /A
                   Performance analyses shall take into account the diffraction effects, misalignments and manufacturing
                   tolerances.
                   For the purposes of the Gravitational Modelling of LTP the OMS suppliers need to deliver a mass distribution
                   FEM model of the items. The granularity of the mass distribution models will be defined in detail in the
                   respective item specifications. The general approach shall be:
                   Accuracy of the model data is TBC and preliminary set to:
                   The maximum size of the body’s part approximated by one mass should follow the following role:
OMS-10.4
                   - for a distance from the TM less than 50 mm the maximum body size shall be 4mm
                   - for a distance from the TM between 50mm and 100mm the maximum body size shall be 12mm
                   - for a distance from the TM greater than 100mm the maximum body size shall be 0.2 time the distance
                   The model shall use the FRF (TBC) reference frame.

                   For the OMS and for its major elements influencing the Scientific Performance a Performance Model shall be
OMS-10.5-1 /R A
                   established. (TBD)
                  Performance models shall be used to evaluate the performance values of critical OMS functions and
OMS-10.5-2 /R A
                  parameters. (TBD)
        O           A   I
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                        P
                            I   COMMENT
s   e   c   c       Y   E                           Method
                t   S       E
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                    I       W
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