JET
PROPULSION
LABORATORY
INTEROFFICE
MEMO
DATE: TO: FROM: SUBJECT: Di str ibutio n
24
July
1964
W.
F.
Eichwald2/_ of
_ EPD-180,
_g_ff_
_/_,j'-_. Revision 1
Distribution
Attached Operations Plan,
is the
revised This
Surveyor supplants
Mission the issue
P-42 dated
Space 5 March
Flight 1964..
EPD-180.
This ning for Surveyor for the
document space
reflects,
in general,
the
current will be
state issued
of planas
flight
operations.
Revisions further.
planning
operations
is developed
Individuals receive additions revisions
on
the distribution as they
list (within) become
will
automatically Requests for
to this document be
available.
to the list should
directed
to this office.
WFE:
shc
•
u
EPD-180,
REVISION
1
DISTRIBUTION 7/Z4/64 DISTRIBUTION LIST
A/corn, Aldrich, Anderson, Appleby, Arcand, Ashley, Barnes, Bayley, Beilock, Berglund, Berkowitz, Berman, Bideaux,
H. W. J. A. T. O. R. A. C. F. R. M. L.
Gustavson,
J.
B.
W. H. M. A. Q. H. I. A. R. S. R. L. D. J. J. S. S.
Haglund, H. H. Hall, J. R. Hamilton, T. W. Hansard, M. D. Harrington, T. M. Heller, J. Helms, J. F. Hine, M. G. Hogg, D. F. Holritz, C. A. Holzman, R. E. Hord, C. B. Hornbrook, G. K. James, J. N. Johnson, C. W. Johnson, M. S. Jones, Koukol, Kozak, Kurutz, P. J. F. S. V. M. V.
Montgomery, Morris,
D. B. T.
(4)
Mudgway, D. J. Nea/, J. S. Nevins, S. M. Pirtle, B. A. Polansky, Poulson, Privette, Ralsten, Re chtin, Rehnborg, Rennilson, Renzetti, Reuyl, Rich, J. S. R. G. P. C. W. N. E. E. H. J. J. N. A. S. F. B. I. (6)
Bilbo, T. Blackwell, Blomeyer, Bourquin, Br enkle, Buckley, Butcher, Chandler,
Roberson, Rung, R.
J. R. L. E. C. E.
Chaney, W. D. Chapman, A. K. Christoffel, J. (3) Clark, J. R. Clarke, V. C., Jr. Cruzan, H. (HAC)(44) Curl, F. G. Cushing, G. P. Cutting, E. D'Amore, A. Davis, J. W. Douglas, Downhower, Eichwald, D. W. W. J. W. F. P. R. P. E. V. R. R. T. F. J.
Lairmore, G. E. Larkin, W. E. Lawrence, H. R. Lawson, R. A. Laxdal, A. L. Leflang, W. G. Lesh, F. H. Leslie, R. LeVeau, C. P. Levy, H. N., Jr. (6) Lindsley, J. N. Linnes, K. W. Macomber, H. L. Mallis, R. E. Mamula, D. R. Margraf, H. J. Martin, E. B. M_arxmiller, S. McClure, J. P. McGee, J. F. Meghreblian, R. Mettyear, W. Michal, L. M. Migliori, A. T. Miller, L. W. Miller, T. B. Molloy, M. W. (19)
Rygh, P. J. Scholey, W. Schurmeier, Seafeldt, C.
J. H. A.
M.
Shipley, W. S. Small, J. G. Sparks, B. Sparks, D. B. Spuck, W. H. Squibb, G. Stallkamp, J. A. Stavros, G. N. Steele, J. R. Steinbacher, R. H. Thatcher, J. W. Thompson, G. R. (5) Thornton, T. H., Jr. Trask, D. W. Urban, I. S. Vescelus, G. E. Victor, W. K. Vivian, H. C. Von Allmen, R. Von Ehrensmann, M. Wanczuk, G. E. Watkins, K. S. Westmoreland, P. T. Whitlock, W. Wilson, J. N.
Eyraud, J. Fahnestock, Fearey, J.
O.
Franzgrote, Frey, W. Galleher, Gates, C. Gautschi,
V.
(6)
Gerpheide, J. H. Giber son, W. E. Glenn, M. S. Goddard, F. E.
ii
E NGINEERING
PLANNING NO. 180
DOC
UME
NT
SPACE
FLIGHT
OPERATIONS SURVEYOR
PLAN
MISSION
P-42
EPD-180,
REVISION
1
24
JULY
1964
EPD-
180
5 March
1964
APPROVED: W. F. Eichwald Flight Operations
Space Director
: T. F.
s -4 l 6autschi Project Manager Operations
Assistant for Mission
24 JULY
JET PROPULSION INSTITUTE PASADENA.
1964
LABORATORY OF CALIFORNIA TECHNOLOGY
CALIFORNIA
4
Copyright Jet Propulsion California Institute
_
1964 of Technology
Laboratory
EPD-180,
REVISION
1
FOREWORD
FOREWORD
It is the function of the Space to define the method by which will be conducted in both the
Flight Operations Plan space flight operations standard case and in anSpace necesinforma-
ticipated departures from the standard case. flight operations are defined as the operations sary for obtaining and processing spacecraft
tion and for determining and executing spacecraft commands from launch to the accomplishment of the mission. This Space Flight Operations Plan covers the requirements for the Surveyor P-42 Mission. Operational facilities and support equipment are described, and the flow of data between facilities is outlined. specified standard Required sequences and procedures for the standard case and for certain situations. are non-
°°° Iii
w
EPD-
180,
REVISION
1
CONTENTS
TABLE
OF
CONTENTS
Page FOREWORD SPACE A. B. FLIGHT Mission Launch I. 2. C. D. Mission .............................. OPERATIONS Objectives Vehicle Launch and Vehicle .................... ....................... Spacecraft Descriptions .......... iii I-l I-l I-2 I-2 I-Z I-5 I-9 I-9 ............ I-9 I-ll I-l 1 1-12 I-IZ II- 1 II- 1 II-l II- l II-4 II-ll II-11 II-Z3 II-Z3 in the SFOF ...... II-g3
IB
......................
Spacecraft Profile
........................ ......................... .................... ..................... Director
Operational I. 2. 3. 4. 5. 6. Project Space
Organization Manager Flight
Operations
Advisors SFOF DSIF
......................... Manager Manager Groups ................ ................ ................
Operations Operations Analysis
Technical
OPERATIONAL A. B. General Air I. 2.
C°
FACILITIES
.....................
............................. Eastern Data Test Range ................. ............... ................. Facility (DSIF) ..........
Force
Tracking Telemetry Space DSIF Flight General Control
Requirements
Requirements
Deep I.
Instrumentation Coverage Operations
...................... Facility ................
D°
Space i. Z.
.......................... and Analysis Functions
iv
EPD-180,
REVISION
1
CONTENTS
TABLE
OF
CONTENTS
(CONT'D)
Page
.
Mission-Independent Coverage DSN Ground
Functions
in the SFOF
.......
H-Z8 II- 31
4.
......................... Communications System ..........
5. Ill. DATA A. B. C. IV. FLOW General Data Data
II-31 III- 1 III- l III- l III-l IV- i IV- 1
............................. ............................. ............................ ........................ .....................
Flow
Processing COMMANDS
SPACECRAFT A. B.
Introduction
...........................
Basic Definitions of Terms Relating to Surveyor Spacecraft Commands .....................
l°
IV- 1 IV- l IV- 1 IV-2
Command Command Command
......................... Sequence Message .................... .................... Sequence/Command Transmission Sequence ............. Execution ........
2. 3. 4.
Command/Command Message Return
IV-2 IV-2 IV-2 IV-2 IV-2 IV-2 IV- 3 IV- 3 IV- 3 IV-3
So
Command/Command Command Command Command Command Command Command Command Command Decision Message Request Directive Verification Confirmation System System
6. 7. 8. 9. 10. 11. 1Z. 13.
.................... Preparation .............
.................... ................... .................. .................
.................... Alternative ..............
V
EPD-
180,
REVISION
1
CONTENTS
TABLE
OF
CONTENTS
(CONT'D)
Page
C.
General Policy for Control and System
Governing Utilization
Operational Procedures of the Surveyor Command IV- 3 IV-4 IV-6 IV-6
............................. Command Subsystem System ...............
D.
Spacecraft Ground I. 2.
E.
Command Space Flight
................... Facility (SFOF) ........ and ......
Operations
Deep Space Instrumentation Command and Data Handling System Alternatave Alternative Alternative SEQUENCE Alternatives No. No. No. OF
i°°°°°.°°°°°°°°°°°.°o
Facility Console
(DSIF) (CDC)
IV-8 IV-9
F°
Command
lo
................
IV-9 IV-9
.... °,°°°°°
2. 3. STANDARD A. B. General Legend Glossary VI. NONSTANDARD
_°.°..°,°°.°°°°.°°,°o
3°0°..0°,°
IV-9
V-I V-I V-Z V-61
V.
EVENTS
................
............................ for Table V-I, Standard Sequence of Events .....
............................ OPERATIONS ...................
VI- 1 VI- 1 VI- 1 VI- 3 VI- 3
A°
General Nonstandard Use General
............................ Procedure Isolation Development Trees Operations .............
B. C. D.
of Fault
................. Procedures .........
Nonstandard
vi
EPD- 180, REVISION 1 LIST OF ILLUSTRATIONS
ILLUSTRATIONS
Figure I-I l-Z I-3A I-3B Atlas/Centaur/Surveyor Surveyor Surveyor Configuration Transit Configuration .............
Page I-3 I-4 I-6
..................... ..................
Trajectory
Mission Sequence from Launch to Canopus Acquisition ........................... Surveyor Surveyor Surveyor Tracking Terminal Lunar Space Descent Landing Flight ................... ................. Organization Surveyor Telemetry at AFETR Data System .......... ........ ........ ...... .....
I-6 I-6 I-8 1-10 II-2 II-3 II-14 II-15 II-16 II-24 II-Z5 ........ II-26 II-Z7 II-Z9 II-30
I-3C I-4 I-5 II- 1 11-2 II- 3 II-4 II-5 II- 6 II-7 II-8 II- 9 11-10 11-11 111-1
Areas Operations
Facilities
Supporting Real Time
AFETR/Surveyor Goldstone Johannesburg Canberra Operations Space Pioneer
Station (DSIF
(DSIF
ll) S-Band Conversion
Station Station Area
51) L/S
(DSIF Layout
42) S-Band
...............
..................... Area Layout .............. Layout
Science
Analysis
Spacecraft Flight Data Path
Performance Analysis Area Area
Analysis Layout Plan
Area
............... ............... ............. Areas
Processing
Floor Room
Communications Surveyor in SFOF Surveyor Command
Control
Layout
Data Flow to Control and ............................. Data Word Flow from SFOF
Analysis
III- Z ................ III-3 IV-5
Formats
....................
vii
EPD-
180,
REVISION
1
ILLUSTRATIONS
LIST
OF
ILLUSTRATIONS
(CONT'D)
Figure IV-2 IV- 3 IV-4 IV- 5 Surveyor Command Command Command Command System System System System Alternative Alternative Alternative ................... No. No. No. l ............... 2 ............... 3 ...............
Page IV-7 IV-10 IV-1 IV-I2 1
viii
l i
m
EPD-
180,
REVISION
1
TABLES
LIST
OF
TABLES
Table II-I II- II AFETR AFETR TTY DSIF DSIF TTY Format for Computed Data ............ for
Page II-5
Semi-Raw Transmission Coverage Capabilities and Data Station Condition Station
Tracking Data Format ....................... ......................... for Surveyor
II-8 II- 12 II-13 DSIF ...... II-17 II-19 II-20 II-21 II-22
II-III II- IV II-V II- VI II- VII II- VIII II- IX II-X
................. for the
Acquisition Tracking Ground Data DSIF
Prediction Supplied Tracking Code Used
Information DSIF
by the Modes by
..............
................. DSIF Stations ..........
Tracking
Report
..................
Terrestrial to the First List of Direct Decoder Camera Decoder Decoder Decoder Decoder Decoder Decoder Decoder Standard Fault
Communications Two Surveyor Commands
Capability Available Missions .............. (Tables IV-I through IV-VIII)
II-3g
IV-I
Title: Data Link and TV Approach (No. 4) ....................... Title: Title: Title: Title: Title: Title: Title: of Trees Signal Processing Power and ............. ............. Vehicle .........
IV-13 IV-16 IV- 19 IV-Z1 IV-23 IV-25 IV-_8 (No. 3) .... IV31 V-3 VI-Z
IV- II IV- III IV-IV IV-V IV- VI IV- VII IV- VIII V-I VI-I
Electrical Mechanisms Engineering Engineering Flight
Payload Mechanisms
........... Auxiliary
Control
............... Camera
Television Events
Survey ..................
Sequence Isolation
......................
ix
• EPD-180,
REVISION
1
SECTION
I
SECTION SPACE FLIGHT
I OPERATIONS
A.
MISSION
OBJECTIVES
TO
BE
SUPPLIED
AT
A LATER
DATE.
I-l
EPD-180,
REVISION
1
SECTION
I
B.
LAUNCH I.
VEHICLE Launch Vehicle
AND
SPACECRAFT
DESCRIPTIONS
a Centaur flight path
A two-stage launch vehicle, consisting second stage, will boost the spacecraft into the required translunar trajectory The Atlas propulsion system consists
of an Atlas D first stage and in a direct ascent, powered (see Figure I-l). of twin booster engines, a
single sustainer engine, and two vernier engines for rections. All engines are gimbal-mounted. Guidance controlled from the Centaur inertial guidance system.
attitude and velocity corwill be from an autopilot
The Centaur system is driven by two gimbal-mounted, liquid-hydrogen engines that provide 15,000 pounds of thrust each. Flight control for the Centaur is supplied by an inertial guidance system that also controls the autopilot for the first stage. The first stage telemetry system transmits functional and environon a VHF carrier. The second-stage telemetry system transmits and spacecraft data on a VHF carrier. The Centaur carries a Cto permit ground tracking. Spacecraft
mental data both Centaur band beacon Z.
The Surveyor spacecraft has a nominal weight of Zl00 pounds and is designed to be mounted within an aerodynamic nose fairing atop the Atlas/Centaur launch vehicle. Three extendable legs provide a broad base for touchdown stability (see Figure I-2). The Surveyor spacecraft structure the various spacecraft subsystems. provides mechanical support and
a base
for
The spacecraft has a guidance system that can maintain full attitude stabilization and that can direct the spacecraft through maneuvers in attitude and trajectory in response to commands from the ground. Cold gas jets position the spacecraft craft uses in the required attitude. In the optically stabilized the Sun and Canopus as reference objects. mode, the space-
The spacecraft contains two propulsion systems: I) a solid-propellant, main retro-engine that provides the primary braking during terminal descent, and Z) a variable, low-thrust, liquid-propellant system of three vernier engines capable of executing a midcourse trajectory correction and of providing braking and attitude control during terminal descent. During the terminal sequence, the propulsion by a radar system that measures altitude to the lunar surface. system is controlled and velocity components
automatically with respect
I-2
EPD-180,
REVISION
1
SECTION
I
348.1
NOSE
FAIRING SPACECRAFT
SURVEYOR
SURVEYOR/CENTAUR SEPARATION KNEE JOINT _'_ PLANE
®---4__.
C-BAND BEACON (5635 MC) jI
/
"qI'_'-NOSE
CONE
HINGE
FITTING
PLANE
CENTAUR
LH
TANK
SEPARATION
PLANE
ii IAI
CENTAUR
LO 2
TANK
INTERSTAGE
ADAPTER-------_a_ CENTAUR ENGINES
ATLAS TTLM SUBSYSTEM NO. I, 237. 8mc
D , MODIFIED
®
LM
SUBSYSTEM NO.2,244.3mc
SHARE SAME ANTENNA
TLM 229.9
BOOSTER MC
SUBSYSTEM
NO.I
IIIII
I ¥
I I I1!
FIGURE
I- I.
ATLAS/CENTAUR/SURVEYOR (INFORMATION ONL
CONFIGURATION Y) 1-3
EPD-180,
REVISION
1
------
DATA CONVert
SECTION
I
SECONDARY
SOLAR
SENSOR_
SOLAR
PANEL_
rm;EER
Tm
CAMERA LANDING GEAR MECHANISM, _l[Mlulet FU_ lrallK RE_ 3 REQ.
NO. 3
CAMERA
NO. 4
UE_M3
mr
ASSr-2
IIEO
CRUSHABLE
STRUCTURE
a_'! uc'rr ,r ..... a_, VIq ncrrf SENSING ANTENNA
FIGURE
I-Z.
SURVEYOR
CONFIGURATION
I-4
ti:i
:2-
• EPD-180,
REVISION
1
SECTION
I
The spacecraft has a two-way telecommunications vides: 1) a method of telemetering information to the Earth, receiving and processing commands to the spacecraft, and oneor two-way doppler for orbit determination. Two receivers receivers to decoder power, that flight (for reliability) central command a particular operate continuously. decoder, and subsystem of
system that Z) the capability 3) angle tracking
proof and
through subsystem electrical
the
the
are the
Commands then routed spacecraft,
to
pass the
controls control.
e. g.,
Either of two identical transmitters can be selected by ground commands. Each is capable of operating in either a high-power or a low-power mode in accordance with the bandwidth of the transmitted data. A signal processing system transforms television and engineering data signals into a form suitable for modulating the transmitter. Highly accurate tracking of the spacecraft is obtained by spacecraft transponders that permit two-way doppler shift measurements. In this mode, one of the transmitters is phase-locked to one of the receivers through transponder interconnection circuitry, and the signal transmitted back to Earth is coherent with the received signal. Two transponder interconnection units are used for reliability. There are three telecommunications antennas aboard the spacecraft: a high-gain directional antenna, the planar array, used only for transmission; and two omnidirectional conical antennas. The planar array orientation, with respect to the vehicle, is controlled by Earth commands. Each of the omnidirectional antennas is permanently connected through a diplexer to one of the spacecraft receivers. The omnidirectional antennas are positioned so that commands can be received regardless of spacecraft attitude. The spacecraft derives its electrical batteries. The solar panel furnishes charging during transit and the lunar 1000-ampere-hour periods of peak load power from a solar panel and power for functional use and day. A primary 2640-amperewill supply transit. power during
two for
storage battery
hour battery or a reserve the lunar night and during
battery during
The spacecraft will carry two television cameras: an approach camera, and a survey camera with scanning capability. The approach camera will take pictures during the approach to the Moon starting at an altitude of approximately I000 miles. After touchdown, the survey camera will provide sequential frame s,_,rv_ys _f the lunar surface. The survey camera has a motor-driven lens for focusing, and motor-driven mirrors for pan-and-tilt control. C. MISSION PROFILE
ascent Figure
The spacecraft flight path I-3).
and
will be injected
carried into
by an a nominal
Atlas/Centaur 66-hour
transit
vehicle through trajectory
a (see
direct
I-5
EPD-
180,
REVISION
1
12, II, 17, 16, 15,
PHASE
ALTFrUDiE
EUDCfTY (FPS)
FIGURE
ALIGN RETRO THRUST TRAllSli ,¢_(IS FOI.JJDII[D ISSION WITH BT L0O0 m VELOCITY TELEVtSIOM AmmOAC_ VECTOR,
I-3C.
SURVEYOR
TERMINAL
]3
RETRO GER£O RADAR. TROL
ENGINE e_ wt'rH INERTIAL
trdNITION ATTITUDE
TRIGCON'-
AL'rrruoE VlERNIE_
I_kRKING ENGINES.
mETRO EJECTION.
ENGINE
BURWOU1"
,IWD
25.000
FT.
3SO
VERNIER CONTROL k_lO
D£SC£1Ct BY RADAR
w_'m
nIGHT _,
AJ,.TIIII£TIER
DOmPLI_
VELOCI'Pr
J J
VERNIER LOWED
IENGINE _4UTOFF, FOLBY FREI[FALLTOSURFAC_
LUNAR
SURF_OE
LAUNCH
_
TOSUN
_-INJECTION
/
(o rain) _ _
COAST PHASE--
/
SECTION
I
FIGURE
I- 3B.
MISSION SEQUENCE FROM TO CANOPUS ACQUISITION
LAUNCH
I0, 9, 8,
ESCENT
\ \ \ k
\
16, 17,,
/_11,
12
2-4
9 5-7 EVENTS
L • :
FIGURE
I- 3A.
SURVE YOR TRANSIT TRAJEC TORY (INFORMATION ONLY)
I.
LAUNCH BOOSTER ENGINE CUTOFF AND JETTISON JETTISON
3. 4. 5. 6. T. 8. 9. I0. II. 12. I 3. 14. 15. 16. 17.
CENTAUR
INSULATION
PANELS
NOSE FAIRING SUSTAINER VERNIER
JETTISON
CUTOFF CUTOFF SEPARATION IGNITION CUTOFF CUTOFF
2
ATLAS,"CEMTAUR CENTAUR CENTAUR CENTAUR LANDING ENGINE MAIN
ENGINE
ULLAGE GEAR
ENGINE EXTENSION
OMNIANTENNA
EXTENSION SEPARATION IGNITION RATE NULLED
SURVEYOR/CENTAUR CENTAUR RETRO
SPACECRAFT SPACECRAFT SPACECRAFT
ROTATIONAL SUN
ACQUISITION ACQUISITION
CANOPUS
I
'EPD-
180,
REVISION
1
SECTION
I
The Atlas booster engine cuts off and is jettisoned shortly after launch. Some time before the sustainer and vernier engines burn out, commands from the Centaur programmer will initiate ejection of the Centaur insulation panels and the spacecraft nose fairing. After sustainer and vernier engine burnout, the Centaur separates from the Atlas. The Centaur engines then ignite, drive the vehicle on into the transit trajectory, and cut off. The Centaur programmer commands extension of the spacecraft landing legs and the omnidirectional antennas and finally, separation of the spacecraft and Centaur. The spacecraft nitrogen jets null the rotational rates imparted during separation and maintain the spacecraft in this rate-stabilized mode until the initial Johannesburg DSLF acquisition. After separation, perpendicularly to the sent to the spacecraft orientation in the yaw plished, Canopus must roll. after point from the spacecraft automatically aligns vehicle roll axis; after DSIF acquisition, to acquire the Sun, thereby providing and pitch axes. Before the midcourse be acquired to provide fixed reference the solar cell array commands are a fixed reference for correction is accomfor orientation in
The midcourse correction maneuver injection to bring the spacecraft into on the lunar surface. This maneuver tracking information supplied by the As the first step in the terminal
will be executed approximately 15 hours a trajectory terminating at the desired will be computed at JPL, Pasadena, DSIF. the spacecraft roll axis is
maneuver,
aligned along the velocity vector and the high-gain antenna is aligned toward Earth. Television viewing of the lunar surface begins about 10 minutes before impact. All radars are turned on approximately five minutes before predicted impact. Following a "command enabling" signal to the trigger radar, the landing sequence is automatic. At a slant range of approximately 50 miles from the Moon, the vernier control engines and the main retro-engine are ignited. The retro-engine separates from the spacecraft after burnout at a nominal lunar altitude of 30,000 feet. The vernier engines then operate under control of the doppler radar and the precision altimeter radar so as to slow the spacecraft velocity to about 5 feet per second at a 13-foot altitude. At this time, the vernier engines shut off, and the spacecraft free-falls to the surface. The solar panel and planar array will be unlocked and properly oriented after landing. The post-touchdown condition of the spacecraft will be evaluated by sampling all modes of engineering data, and by attempting to manipulate spacecraft mechanisms. Television survey sequences will then be directed by ground commands. The landing is planned to occur in a region near the Moon's the angle between the unbraked, approach velocity vector and the tical is approximately zero degrees. The spacecraft design provides capabilities for approach angles to 45 degrees with respect to the vertical; thus, landings can be accomplished in other maria in the of the face of the Moon as shown in Figure I-4. It is planned that ing be observed from the Goldstone station and that this visibility for a period of not less than three hours after landing. equator where local Moon verlanding local Moon western region the lunar landbe maintained
I-7
EPD-180,
REVISION
1
SECTION
I
_o
Z
_
[.4
0 Z
I,-,-I
Z; ,.q
;z; ,4 0 ;>., N
! t,--I
O
I--I
0
o
0
_o_
_ZJ
I-8
EPD-180,
REVISION
1
SECTION
I
D.
OPERATIONAL
ORGANIZATION space flight operations organizational structure is shown in mission responsibilities and the authority of the individual are as follows: Manager Manager of the has the responsibility and development and operation Director authority for the of the project.
The Surveyor Figure I-5. Primary organization members I. Project
execution, Z.
The Project to completion, Space Flight
Operations
It is the function of the Space Flight Operations Director to support the Project Manager in the preparation and execution of the standard operating procedure for space flight operations, i.e., the Space Flight Operations Plan (SFOP). The standard operating procedure is defined as the method by which the space anticipated flight operations will be conducted in both departures from the nominal case. a. Preflight Phase the nominal case and in
During the preflight phase, it is the responsibility of the Space Flight Operations Director, supported by appropriate JPL and HAG personnel, to coordinate and integrate requirements that are established by the cognizant divisions for the standard operating procedure to be followed during the inflight phase. The Space Flight Operations Director is empowered to request information and resolve conflicting requirements, within the framework authority sibility.
bl
of existing Laboratory structure and within the of the program, as required to fulfill this respon-
Infli_ht During Flight
Phase the inflight phase, Operations Director it is the to: responsibility of the Space
i)
Interpret the standard operating procedure and place requirements consistent with this SFOP on the various operating groups. any ambiguities directly associated operating procedure arising during with the its exe-
z)
Resolve standard cution.
3)
Make appropriate to ensure success tory Director for Assistant Project not be contacted.
decisions requiring emergency of the mission if the Assistant Projects, Manager the Project for Mission Manager, Operations
action Laboraor the can-
I-9
EPD-
180,
REVISION
1
SECTION
I
I=I
w l.m &mu
i
I
OPERATIONS llAUO(N I. ekU.Lm (,_,J
I
J. n _plJ
I
I
I
NtAL¥SIS & COmll_O elmUP Ul nmuu4sN'# me) II N 1. wuuo aIOUP (talc) | I
I
PREDICTION n a. mima_
I
ANAUnll $ (w_
I---i
L. eE[_
i
[ViLUATIDII, I, Edll • WLUm _J | L a*mJii 1 ATIOH
i
1Y.lll
I
I
I
FIGURE
I-5.
SURVEYOR
SPACE
FLIGHT
OPERATIONS
ORGANIZATION 1-10
EPD-
180,
REVISION
1
SECTION
I
In the fulfillment of this responsibility, the Space Flight Operations Director is accountable to the Assistant Laboratory Director for Projects, the Project Manager, or to the Assistant Project Manager for Mission Operations, and is delegated authority of the Project Manager for placement of requirements on operating groups in accordance with the SFOP. 3. Advisors to be aware subsystem, Manager behavior of the performance and of the DSIF of during
the
It is the function of the advisors spacecraft system, of the instrumentation and to supply judgments of action in the event 4. SFOF Operations to the Project of nonstandard Manager
flight, courses
as to possible future of the spacecraft.
It is the responsibility of the SFOF Operations Manager to direct the operation of the SFOF during space flight operations and to commit and control all functions in the SFOF during the preparation and execution of each flight operation. a. Data Processing Project Engineer Project Engineer conversion, distriduring the prepara-
It is the responsibility of the Data Processing to commit and control the data processing, bution, and display equipment and personnel tion and execution of each flight operation. b. Communications Coordinator
It is the responsibility of the Communications Coordinator to commit and control the operational communications equipment and personnel within the SFOF and the equipment within the Space Flight Operations Complex during the preparation and execution of each flight operation. c. Display Group of this group for mission to display operational and operations control and and techeval-
It is the function nical information
d.
Video
Processing
Group of this group to process suitable for analysis. the spacecraft video
It is the function data into a form
e.
SFOF
Support
Group
This group will supply operational, maintenance, clerical, and other general support as required for the operation.
I-ll
EPD-180,
REVISION 1
SECTION I
5.
DSIF
Operations
Manager
It is the responsibility of the DSIF Operations Manager to direct the operation of the DSIF and to commit and control DSIF personnel and equipment at each station during the preparation and execution of each flight operation. a. DSIF Net Control of this group to be the direct line of contact
It is the function
with the DSIF stations. DSIF Net tions with operational requirements the b. DSIF DSIF Operations Manager
Control will and status status.
supply the staand will inform
of station
Advisors of the informed courses DSIF Advisors of the current of action. to keep the state of the DSIF DSIF
It is the responsibility Operations Manager and to advise future c. DSLF Station Managers
It is the responsibility of the DSLF Station the operation of the DSIF station to which to control the functions of the personnel station. 6. Technical Analysis Groups
Manager to he is assigned, and equipment
direct and of his
Each of the technical analysis groups (FPAC, SPAC, and SSAC) is headed by a Technical Director who is responsible for integrating, directing, and coordinating the preflight, flight, and postflight activities of his group and who will support the SFOD in the planning and conduct of Surveyor space flight operations. It is the responsibility of these groups to assist in defining the standard mission, to recommend courses of action that will provide optimum value from the mission during nonstandard situations, and to perform the intraand intergroup technical liaison required to achieve these objectives. a. Flight It is the Path Analysis and of Command this group (FPAC) to use Group the tracking and
responsibility
telemetry jectory pret the tionally, spacecraft
data to obtain the best estimate of the actual traof the spacecraft and, supported by the DSIF, to intertracking data supplied by the tracking stations. Addiit is the responsibility of this group to determine the commands affecting the flight path by utilizing, to required, FPAC the will support consist Group of of: the SPAC group and the
the degree SSAC group. 1) Z)
Computing Trajectory
Support Group
I-IZ
EPD-180,
REVISION
1
SECTION
I
3) 4) 5)
Do
Tracking Orbit Maneuver
Data Determination
Analysis Group Group Analysis
Group
Analysis
Spacecraft
Performance
and
Command to determine commands behavior
(SPAC)
Group
It is the responsibility craft performance craft as required of the spacecraft. l) 2) 3) Space Performance Engineering Command Science
of this group and to determine by the engineering SPAC will include: Analysis Computer Preparation Group Program Group and Command
to and
the spacethe spaceperformance
Operations
Group
C.
Analysis
(SSAC)
Group
It is the responsibility of this group to control the flow of, and the mathematical operations performed on the data related to the scientific experiments during the interval between its receipt by the DSIF and its transmission to the appropriate scientists. Additionally, it is the responsibility of this group to determine those commands to the spacecraft pertaining to the scientific experiments. This group will consist of:
l) z) 3) 4) s) 6) 7)
Operations Ope SFO rations Coordinator
Engineer Scienti st
Television TV Performance
Evaluation Analysis Science Science
Team
Chairman and and Command Command Team Group Group
Television Touchdown
Analysis Evaluation
1-13
EPD- 180, REVISION 1
SECTION II
SECTION OPERATIONAL
II FACILITIES
A.
GENERAL describes that portion of the Space used by the Surveyor P-42 Mission. Test Range {AFETR), the facilities (DSIF), the Space Flight Operations between these facilities are described. be EASTERN TEST RANGE is fully de3400. The are described Flight The of the Facility Operations Complex facilities at the Deep Space Instru{SFOF), and the
This section (SFOC) that will Air Force Eastern mentation Facility communications B. AIR FORCE
scribed
The support for in the AFETR
the Surveyor P-42 Mission required of AFETR Program Requirements Document (PRD) No. used by AFETR Support Plan information in support (PSP) No. will be of Surveyor 3400. to P-4Z
facilities that will be in the AFETR Program Detailed countdown
forwarded
Pasadena
from
the Additionby AFETR. the JPL/ and
JPL/HAC Operations ally, event information Details regarding the HAC Operations Center Operations Plan.
Center at AFETR during the prelaunch countdown. from launch through separation will be supplied handling of this information at AFETR and within at AFETR will be found in the Surveyor Assembly
After launch, extensive use of the tracking and telemetry facilities at AFETR will be made in support of the mission. Those requirements are described in the following paragraphs. C-band tracking data will be obtained from the launch vehicle by means of the facilities shown in Figure II-l. Trajectory and prediction data will be generated from the raw data and forwarded in nearreal time to the JPL Operations Center at AFETR for relay to the SFOF in Pasadena, California. S-band and VHF telemetry data will be transferred from AFETR to the SFOF in real time as shown in Figure II-Z; recorded S-band and VHF telemetry data will be forwarded to the JPL/HAC Operations Center at AFETR.
i.
Trackin$
Data
Requirements requirements direct a_c_nt for near-real ti'ajectory: time data during the
postinjection
There are three phases of the
ao
It is required that AFETR obtain an spacecraft injection conditions which AFETR, to the JPL/HAC Operations real time for relay to the SFOF.
initial estimate of will be forwarded, Center at AFETR
the by in
II-1
EPD-180,
REVISION 1
SECTION II
_r
.<: .< O
>.,
:>
O 2;
I,--4
0 m
O
o
w
_
u
I
< O Z (J <
l
[q I
!
I
i
D O
0 AVT3,b"_r_ V;A
II-Z
EP'D-
180,
REVISION
1
ANTIGUA
]
SIGNAL VHF RECEIVER CONVERSION
I
DECOMMUTATOR
{
_/
SHIP 1
SIGNAL CONVERSION --_ DECOM S-BAND RECEIVER RECEIVER :__ M UTATOR
HF TRA NSMITTERI_
I
R
H
Or) Z 0 I-,,¢[ I-U_ I¢1 Z <[ R"
1-,,o, I
SHIP
I J
i__
RECEIVER VHF SIGNAL CONVERSION DECOMMUTATOR
i@_
RECEIVER S-BAND
/ I
I
RECEIVER S-BAND 1 ASCENSION __
I I
I
Jo:o°_2L°L -_"'" i
J
/
SECTION
II
SPACECRAFT
AND
JPLIHAC OPERATIONS (A FETR ) AREA
I
RECEIVER
!
H.S, COMMUNICATIONS CENTER m
LINE
l
I
_! _x
RECONVERSION TO SERIAL PCM
.__
DISPLAYcDc
RECONVERSION TO SERIAL PCM
I I
x_ F-
r-
RECONVERSION TO SERIAL PCM l MONITOR
.,o.-S_E_ I J I
KEYER
L_
___J
i
AFETR
-IF
D/A CONVERTER I
FIGURE
II-Z.
AFETR/SURVEYOR TIME TELEMETRY SYSTEM
REAL DATA
II-3
EPD-
180,
REVISION
1
SECTION
II
b.
Initial acquisition The raw tracking
data for the data obtained
DSIF is required from downrange
from AFETR. stations will
be forwarded to the computing center located in the Impact Predictor Building (IPP) at AFETR. This data, in conjunction with pertinent telemetry data, will be used to determine the trajectory of the spacecraft. Table II-I shows the format for all computed data furnished by AFETR to JPL/HAC. The acquisition data shown in Table II-I will be computed and forwarded to the JPL/HAC Operations Center at AFETR for relay to the SFOF in Pasadena and thence to the DSIF stations.
C.
Semi-raw tracking data will be transferred from the Impact Predictor Building to the JPL/HAC Operations Center AFETR for relay to the SFOF. The format of this data is shown in Table II-II. Requirements
Zo
Telemetry
a.
Launch vehicle and spacecraft telemetry obtained through the Centaur VHF link, and spacecraft telemetry obtained through the spacecraft S-band link, are recorded at the AFETR stations. The recorded information will be forwarded to JPL/I-IAC at AFETR in nonreal time. Launch vehicle and spacecraft event information is obtained at AFETR stations and is transmitted by voice lines in real time to the JPL/HAC Operations Center at AFETR for relay to the SFOF. Spacecraft telemetry obtained via the VHF link will be transmitted in real time to the JPL/HAC Operations Center at AFETR for relay to the SFOF from approximately five minutes before injection until immediately prior to spacecraft/Centaur electrical disconnect. Thereafter, spacecraft telemetry obtained via the S-band link will be transmitted in real time to JPL/H_AC. the AFETR reported Additionally, stations, to JPL/I-IAC the telemetry may be monitored spacecraft at and the performance of the in real time by voice line.
b.
c.
11-4
,EPD- 180, REVISION 1
SECTION II
TABLE
II-l.
AFETR
TTY
FORMAT
FOR
COMPUTED
DATA
A.
First Actual
Message launch LIFTOFF time DAY and azimuth. XXX HMS XX XX XX. X GMT AZL XXX. XX
Be
Second Orbital I.
Message elements TTY Format AND YYY. S XX XXXXX. XXX. XXXXX. XX. XXX XXX LAT AZE XX X YY XX.X ECC APF XX. L PLUS TIME INC TA XXX. XXXXX. XXX. XXX. XXX XXX XXX VE XX. XXX ALT C3 XXX. XX. XX XX INJECTION COND OF ACTUAL TRANSFER and injection conditions.
ELEMENTS ORBIT H M
SMA LAN R PTE
X. XXXXXX XXX. XXX XXX. XXX LON XXX
Zo
Nomenclature GMT AZL YYY. YY (HMS) Time Azimuth of launch of launch of computations. The number before is the station ID; the number after indicates the number of the transnumbers 10-99.) from 01-09;
Data source the decimal the decimal
mission. (AFETR is to use JPL is to use numbers from HMS Epoch - Universal Time Seconds); time at which calculated TIME Epoch, Distance seconds above after Earth's
(Hours, Minute_, and osculating conic is
L
PLUS
liftoff surface in kilometers
ALT
(This
table
continued
on
next
page.
)
II-5
EPD-180_
REVISION
1
SECTION
II
TABLE
II-I.
(CONT'D}
Nomenclature SMA
(Cont'd) Semimajor a hyperbola. Eccentricity axis of conic (kilometers) of conic section. Negative for
ECC INC
section
Inclination - Angle between the orbital plane and the Earth's (instantaneous) equator. Degrees, between 0 ° (zero) and 360 ° Twice the total energy in kin2/sec 2. Right ascension from 0 ° (zero) vernal equinox torial plane. per unit mass or vis viva
C3
LAN
of the ascending node. Degrees, to 360 ° . Measured from the of date in the instantaneous equa-
APF
Argument of Perigee. Angle, in the orbital plane, eastward from the ascending node to the perigee point. Degrees, from 0 ° (zero) to 360 ° . True from ward anomaly perigee at epoch. The angle measured to the spacecraft. Measured
TA
east-
in degrees. radius latitude longitude velocity path in kilometers in degrees in degrees in km/sec at injection in degrees
R LAT LON VE PTE AZE
Injection Injection Injection Inertial Inertial Injection
angle
azimuth
(This
table
continued
on
next
page.
)
II-6
EI6D-180, REVISION 1
SECTION II
TABLE
II-L
(CONT'D)
_e
Third
Me
s s age information Format LOOK ANGLES REF XX XX HA XXX. XXX. XXX. S OF XX XX X X X XX.X FREQ XX.X FROM ACTUAL TRANSFER XPONDER XXXXX. DI. X X X XXXXXX XXXXXX XXXXXX XXXXX. ACTUAL 51 XXX D2.51 XXXXXX XXXXXX XXXXXX XXX TRANSFER ORBIT XA. XXXXXX XXXXXX XXXXXX 51 ID LMPQR LMPQR LMPQR FREQ ORBIT XXXXXX for DSIF.
Acquisition I. TTY JPL
XMITTER H H M M S S
XXXXXX RANGE DEC
XXXXXX XXXXXX XXXXXX H M END
XXX. XXX. XXX.
RANGE
LOOK
ANGLESFROM
_e
Nomenclature HMS HA DEC DI. 51 Hours, Hour Minutes, angle, Seconds one-tenth one-tenth degree degree frequency
nearest nearest
Declination,
One-way doppler detector for Station 51, cps Two-way doppler detector for Station 51, cps
output
D2.51
output
frequency
XA.
51
Transmitter
VCO
frequency
for
spacecraft
ID
As LM PQR
listed -
below: Orbit Day number, of year from 01 to 99
II-7
EPD-180,
REVISION
1
SECTION
II
TABLE
il-II. AFETR FORMAT
SEMI-RAW FOR TTY
TRACKING DATA TRANSMISSION
CHARAC TE R TRANSMITTED
INFORMATION
1 2 3 4 5 6 7 8 9 I0 II 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 3O 31 32 33 34 35 36 37 38
Carriage Return Line Feed Figure Shift Data Type Station ID Station ID Radar Type On Track - Code 2 Time - H 20, 19 TimeH 18, 17, 16, 15 Time - M 14, 13, 12 TimeM l l, i0, 9, 8 TimeS 7, 6, 5 TimeS 4, 3, 2, l Az 21, Z0, 19 Az 18, 17, 16 Az 15, 14, 13 Az 12, II, 10 Az 9, 8, 7 Az 6, 5, 4 Az 3, 2, 1 E1 21, 20, 19 E1 18, 17, 16 E1 15, 14, 13 E1 iZ, ll, I0 E1 9, 8, 7 E1 6, 5, 4 E1 3, 2, 1 R 27, 26, 25 R 24, 23, 22 R 21, 20, 19 R 18, 17, 16 R 15, 14, 13 R 12, II, I0 R 9, 8, 7 R 6, 5, 4 R 3, Z, I End of Sample
See
Legend
on next page.
II-8
."
. EPD-180,
REVISION
1
SECTION
II
LE GE ND
1.
Character
4,
Data
Type:
2 - Real Time 3 - Simulated 7 - Last Characters Sample 6,
Data
2o
5 and
Station 70 72 73 74 75 76 77 78 79
ID:
Bermuda San Salvador Grand Turk Antigua Ascension Pretoria Twin Falls ARIS I ARIS Character II 8, On Track: 0 2
o
Off Track On Track Characters 20-Bit
e
e
9 - 14, Binary 15 - ZI,
Time: Coded Azimuth Digit Digit Decimal Data Time Code Character
Characters Most Least
in Binary -
Code: 180 Degrees 0. 000343 Degrees Code: Degrees
Significant Significant 22 - 28,
Bit 20 Bit 1 Data
o
Characters Most Least
Elevation Digit _:-:_ Range Digit Digit Data -
in Binary 20 ' Binary Code: 180
Significant Significant Z9 37,
Bit _'_ in 226 20
e
Characters Most Least Character End
Significant Significant 38, End
67, 108,864 l Yard
Yards
o
of Sample: Oblique Stroke
of Sample
II-9
•
EPD-180,
REVISION 1
SECTION II
SECTION SECTION
II,
C. If,
DEEP D.
SPACE SPACE
INSTRUMENTATION FLIGHT OPERATIONS
FACILITY FACILITY
DEEP
SPACE
NETWORK
The function of the Deep Space Network (DSN) for the Surveyor P-42 Mission is to provide those facilities necessary to meet the space flight operations requirements of the Surveyor Project. The DSN includes the Deep Space Instrumentation Communications System, Facility (SFOF). Facility (DSIF), DSN Ground and the Space Flight Operations
APPROVED: M. DSN S. _ohnson Manager, Surveyor
II-
10
EPD-180,
REVISION
1
SECTION
II
C.
DEEP
SPACE
INSTRUMENTATION
FACILITY
(DSIF)
The and video mission. accordance Instruction Data
function of the DSIF is to obtain angular position, doppler, telemetry, data from the Surveyor spacecraft during the postinjection phase of the Additionally, the DSIF will transmit commands to the spacecraft in with the procedures outlined in Section VI of the Surveyor Tracking Manual (TIM), EPD(to be published). obtained by the DSIF is transmitted to the SFOF in real time or near-
real time by teletype and high-speed data circuits, and by channel (from Goldstone only). The same data is recorded the DSIF station and dispatched to JPL by airmail. 1. DSIF Three Coverage DSLF stations are committed to meet the
wide-band microwave on magnetic tape at
requirements
placed
on the DSLF by the Surveyor Project; these are designated the prime stations. They are Goldstone Pioneer (DSLF ll), Johannesburg (DSIF 51), and Canberra (DSIF 42). The DSIF will provide coverage as specified in Table II-III. The full Goldstone Duplicate Standard (GSDS) S-band system will be used at Goldstone Pioneer (DSIF ll), Canberra (DSIF 42), and for the DSLF 51 acquisition aid. The L-to-S band (L/S) conversion system will be used at Johannesburg (DSIF 51). The parameters and capabilities of the DSIF stations are given in Table H-IV. ures II-3 through II-5. Block diagrams of the stations are presented in Fig-
Acquisition and prediction information required by the DSIF is given in Table II-V. The tracking data to be supplied by the DSIF to the SFOF for orbit determination is shown in Table II-VI. Ground station tracking modes are listed listed in Table in Table H-VII. The II-VIII. reports, data condition codes used by the DSIF stations are
Station mitted by each required within
as detailed to the SFOF.
in Table These
II-IX, reports
will
be
periodically be distributed
transas
DSIF station the SFOF.
will
II-ll
""
.EPD-
180,
REVISION
1
SECTION
II
TABLE
II-HL
DSIF
COVERAGE
PHASE
i
DSIF
COVER_AGE
Transit If landing I. is achieved lunar day and
24-hour/Earth
day
First night Second
Z4-hour/Earth
day
2.
lunar
day;:-"
a.
24-hour/Earth three Earth
day days day
for
first
b.
24-hour/Earth two Earth days
for
last
c,
One ten-hour pass/Earth between a. and b. above 24-hour/Earth three Earth day days day for
day
.
Succeeding and nights*
lunar
days
a,
for first
b,
24-hour/Earth two Earth days
last
co
One ten-hour pass/Earth between a. and b. above 24-hour/Earth day for more than three Earth after encounter 8-hour/Earth day for tional l0 Earth days
day
If no
landing
is achieved
a.
not days
bo
addi-
-r
24-hour/Earth can be provided
day by
coverage spacecraft
required whenever instruments.
valuable
data
II-IZ
_PD-180,
REVISION
1
SECTION
II
A
O
°,.-I -T-I
,-_ o o 0
,-_ o
""4""-4
(D
0
_'_
Oo _'_°
,__0
_
_
,._._ _
_
I_
_3ao_a_
0
o
,.n
m
,-a
ZZ_
°_°_
_'_ o
_'_
> m D O
r_
0
!
_J
,-_ o
tt_ L_
,-_ o oo 4]
.o
+1+1
o_
_
we
_
_
oo
_
m _
_
O0 _ 0 m _
U3
.2
u'5
d
ZZ_
A
¢,.,J
_-4
.o ,_
0 !
<
< O
L0
o_o_
_0_0 O0
°_-_
_
_
o n
,---I
,..,
t_
t_
+'+
0 • 0 .
' _
_ _
_I_ _
o o_ o _0
_
_ _ _ _ _
(',,1
Z
! I--4
>_ _
< ..-
m
_
Z
m
S_
z
• • Ln_
_:0
m
_ .,
m
_ _ _
_
< _ _z m
r_l
N
O
z
_ Z 0 _0 _ Z
<
or]
II-13
+EPD-180,
REVISION
1
SECTION
II
I
A
V
2:
£
M M
0
I I_ :j
Z;
0
o 0
I
M
_
--I z
V'zw w_
i-i
m_
I o
w_
m
,.,z
ooo
_U
Oa.
;+[I
+)
jI_-14
EPD-180,
REVISION
1
SECTION
II
Z 0
> Z O o
r,_
Z 0
I,,,,,4
<
r._
2: 0
m
!
I I_
=-r,D
r,.3_
_
X_
Wf-)W
m
8_
H-15
EPD-180,
REVISION
1
SECTION
II
4t
m
1!
| c
J
|
rT
I
m
I
_n
A
r_
i-i _n
Z_ 0
I-4
E_
[n
<_
m
I
0
i.-i
|I
!i!o
5 TT-16
EPD-
180,
REVISION
1
SECTION
II
TABLE
II-V.
ACQUISITION FOR THE
AND DSIF
PREDICTION
INFORMATION
A.
Format i. Calculated JPL JPL LOOK PREDICTS REF XX XX HA XXX°X XXX. XXX. X X FREQ XX.X at JPL ANGLES (Station Name) Number) FREQ XXX D2. AB XXXXXX XXXXXX XXXXXX XA. XXXXXX XXXXXX XXXXXX AB ID XXX XXX XXX XXXXXX
(Transmission XXXXXX RANGE DEC XXX. XXX. XXX. X X X XPONDER XXXXX. DI.AB XXXXXX XXXXXX XXXXXX
XMITTER H H M M S S
XXXXXX XXXXXX XXXXXX
_m
Calculated See Table
at AFETR II-I.
Bo
Nomenclature HMS HA DEC DI. AB Hours, Hour Minutes, Angle, Seconds one-tenth one-tenth degree degree frequency for
nearest nearest
Declination, One-way Station Two-way Station
B,
doppler Zone
detector A, cps
output
DE.
AB
B,
doppler detector Zone A, cps VCO error frequency for
output
frequency
for
XA.
AB
Transmitter static phase
for B,
spacecraft Zone A,
zero cps
Station
ID
Day
of year
(This
table
continued
on
next
page.
)
II-17
EPD-180,
REVISION
1
SECTION
II
TABLE
II-V.
(CONT'DI
C.
Sample The one rate one will
Rate sample rate sample per will be one sample per be updated for the earlier part of the initial view period will be 2 minutes; for the remainder of the view period the sample per 5 minutes. For all other view periods, 5 minutes will be supplied for each pass. The data each day.
Do
Availability
of Data SAMPLE RATE AND AMOUNT
TIME
ORIGIN
FOR
DSIF
(To
be
supplied
at
a later
date.
)
II- 18
EPD-180, REVISION 1 TABLE II-VI.
SECTION II TRACKING DATA SUPPLIED BY THE DSIF
A.
The tracking data from DSIF II, a data condition code, hour angle thousandth), thousandth), year. The
42, and (decimal
51 will contain time (GMT), degrees, nearest twotwoday of DECLIN-
declination angle (decimal degrees, nearest doppler cycle count (to nearest cycle), and format will be: SPACEDATA CONDITION CODE XXXX GMT XXXX_KX DAY YFA2 XXX OF DOPPLER C0O_T XXXKXXXXXX
HOUR ANGLE (deg) XXXXXX
*
ATION ANGLE (deg) XXXXXX
*
DSIF STATION XX
_-DRMAT I.D. XX
CRAFT I.D. XX
B.
Data
sampling
and
doppler
counting
times:
DSIF STATION
TIME INTERVAL
SAMPLING INTERVAL
DOPPLER COUNTING
TIME
11
and
42
L to Lunar down - i hr Lunar -I hr
Touch-
1 per
min
60
sec
nondestructive
Touchdown to Touchdown +47 min
1 per
10
sec
I0
sec
nondestructive
51
Z
to L
I per I per
I0 sec min
5 sec 60 sec nondestructive
L +47 rain to Lunar Touchdown
The
angle
data
from
DSIF
I I will
not be
the
result
of auto-track
operation.
II- 19
EPD-180,
REVISION 1 TABLE II-VII. GROUND STATION TRACKING MODES
SECTION II
This mode description is used to define the station configuration. The code is broken into two parts. The first defines the Transmit/ Receive mode and the second the Antenna Feed configuration.
TRANSMIT / RECEIVE FEED
GM-O GM1
No
receive
(transmit doppler
only) (receive
Not
Used
One-way only)
Horn feed diplexer combination (receive and transmit up to I0
kw)
GM-2 Two-way, (transmit onestation / r ec eive) Tracking feed tion (receive diplexer and transmit combinaup to
200 w)
GM3 Two-way, coherent two(receive station only) nonAcqui sition ante nna
4
Dipole (receive to Z5 w)
and
transmit
up
Horn only)
feed,
no
diplexer
(receive
Example:
GM-Z-I two-way
; transmitting doppler; will be horn
to spacecraft feed and
and
receiving
diplexer. modes except
Note.
Telemetry GM-0.
available
in all receive
ll-Z0
I_PD-180, REVISION 1
SECTION
II
TABLE
H-VIII.
DATA
CONDITION
CODE
USED
BY
DSIF
STATIONS
DIGIT Doppler Value Digit 0 1 ? 3 4 5 6 7 8 of
NO.
1 Time Receiver Value Time I Sec 5 Sec i0 Sec 20 Sec ? 30 Sec 40 50 60 Sec Sec Sec 4 5 3 1 Digit 0 of
DIGIT & Servo Data
NO. Data
2 Condition
Averaging
Condition Good Data Doppler & Angle
Bad Angle Sense Bad Doppler Sense Bad Doppler Data, Auto Not Used
Data,
Auto
Data,
Auto
& Angle Sense
Nondestructive
Bad Angle Switch
Data,
Manual
6
Bad Doppler Data, Manual Switch Bad Doppler Data, Manual & Angle Switches
7
DIGIT Doppler Value Digit 0 1 2 of Counter Recorder i I I
NO. Mode
3
DIGIT Atomic Value Digit (C2) (CI) Two-Way 0 1 2 of
NO.
4 Standard
Frequency Data Condition In Out Not Lock of Lock
Doppler Mode Two-Way One-Way Pseudo
Applicable
(c3)
4 5 6 2 7 Two-Way One-Way Pseudo (C 3) (Cz} (C 1) Two-Way
II-21
EPD-180,
REVISION 1 TABLE H-IX. DSIF STATION TRACKING REPORT station reports will be submitted: +i hour.
SECTION II
During a tracking period, i) Z)
Every 30 minutes from Launch to Midcourse After Midcourse, period.
on the hour during each station's
tracking
Voice reports will be given from Touchdown -60 minutes to Touchdown. During the first Z4 hours after Launch, each station report will be identified with Launch-referenced time (e. g. , L +60 minutes}. The report will contain the following information:
i) z)
Ground station tracking end time of each mode. mode (GM) as well as start and/or (Table II-VII defines the ground modes. )
Average signal level in dbm and AGC volts plus any variation about this level; also GMT of the signal level reading. Telemetry Equipment channel failures condition. and times of failures. measured
3) 4) S)
Time-labeled transmitter VCO frequency in mc/s, every 5 minutes during the reporting period. Transmitter Time (GMT) Time Time Time e. g., power in watts. events, for example:
6) 7)
of significant of acquisition of loss
a) b) c)
d) e)
of signal changes servo in the bandwidth shifts level corresponding to tracking changes system,
of significant receiver of ahrupt and
Time
frequency in signal
Time of changes c) and d) above
Note.
Report Items l through 6 will be and value. Entries under Report
indicated by item number Item 7 will be defined. II- ZZ
EPD-180, D.
REVISION 1
SECTION II
SPACE FLIGHT OPERATIONS FACILITY
1. General
Control of Space Flight Operations for the Surveyor P-42 Mission will be exercised from the SFOF by the Surveyor Project Office. In addition to providing the capability to exercise this control, the SFOF shall provide the necessary data processing, communications, display, and support capabilities required by the technical groups and the DSIF to perform the analysis, evaluation, and interpretation of spacecraft and/or spacecraft-related data, and to determine and implement the ground control of the spacecraft. Z. Control and Analysis Functions in the SFOF
The space flight operations associated with Surveyor will be directed by the Space Flight Operations Director (SFOD) from the SFOF. The SFOD will operate from Mission Control Room No. i, adjacent to the Operations Area of the SFOF (see Figure II-6). The technical functions that provide the analysis, evaluation, and
interpretation of spacecraft and/or spacecraft-derived information for Surveyor mission direction and evaluation are performed in the Flight Path Analysis Area (FPAA), in the Mission Support Area (which comprises the Space Science Analysis Area (SSAA) and the Spacecraft Performance Analysis Area (SPAA)), and in the Spacecraft Television Analysis Area (STAA). Use of the STAA will be shared with the Lunar Orbiter Project. Layout of the SSAA and STAA is shown in Figure II-7. The SPA_A is illustrated in Figure II-8, and the FPAA in Figure II-9. Normally, the technical functions are performed in the three areas just stated. However, the Operations Area may, at the discretion of the SFOD, be used for this purpose during the critical phases of the mission that require close coordination between technical and operational personnel, and between the SFOD and the Project Manager. In standard originate required the SFOF operations, all commands to the Surveyor spacecraft will be from
in, and be controlled from the SFOF. Approval before any commands or sequences of commands and/or DSIF to the spacecraft.
of the SFOD will are transmitted
Each technical area of the SFOF will be provided with a remote inquiry station of the Data Processing System, including a remote I/O console with an associated administrative printer and card reader to permit direct usage of the Data Processing System from the technical areas. An _'_ JU f %2 _'-_ _ .... ,._%_ xl.L_xx-_1_,,.,,..,,,._ printer will also be provided as well as an Ii" x 17" Dymec plotter and a 30" x 30" Milgo plotter to display the output of the Data Processing System. priate number of receive-only teletype page printers and reperforators provided in each technical area to permit display of the data received directly from the teletype lines. the An approwill be in the SFOF
The Television Ground Data Handling System, with equipment on second floor of the SFOF, will provide the capability for recording spacecraft television data, and will display this data in real time in the SSAA.
II-23
EPb-180,
REVISION
1
SSAA
i
O
PROJECTION
ROOM
STATUS
BOARDS
DATA
PROCESSING
CONTROL
CONSOLES
CARD READER PRINTERS ON 4 22x=2 PLUS ] 5C3070 PR INTER []
[]
FP,4,4
2 REPERFORATORS TABLF..S/EA.
OPERAT/ONS
AREA
I/0
OPS
OPS OPS (P
[]
[]
v1
n
_
m
REC_ER TALKER
PROJ
ASS'T DIR.
[
]
MISSION OIR.
MGR _OF
[]
MGR DSIF
_
MISSION DIR
[_
&SS'T OIR
OO
MCR 2
O
[]
FCR
0
CONTROL
[]
MCR I
[] D
[]
[]
[]
MIS_OmS
[]
COUCH
PLANETARY
OPERATIONS
ROOM
SECTION
II
TV AREA (MEZ)
GALLERY (MEZ)
CONFEREM_ ROOM
!
DOWN PROJECTION ROOM
0
1"4 MONITOR OPN'L VOICE COMM.
FIGURE
If-6.
OPERATIONS LAYOUT
AREA
J._
H-24
EPD-180,
REVISION
1
SECTION
I/
z
.=o
o o
"
_ .............. T_ I
-]
IJ J-_l I
Jz
[_]
C]I:_:
I_---
D 0 <
__L
o_ _J
I
!
"4
/
C] o_= _;oO
IJ
< Z < _3 Z
_-4
./-lo •
!
o
_ I--_-
_3 _3 < 0_
O'3
U
I
p_ o_
n_ i:o
_
._
0
f_.
. _" ]
[3
z
[3
8
U
U
II-25
• EPD-180,
REVISION
1
SECTION
II
_
in.
Y
SiC MOOEL IB ft O
RACK
-
"L->J-_
U
®
FIGURE
II-8.
SPACECRAFT
PERFORMANCE
ANALYSIS
AREA
LAYOUT
II-Z6
EPD-180,
REVISION
1
SECTION
II
TO
SPAA
LEGEND: [] HARD
COPY
TV CAMERA
"
[\
y/
_TRACKIN6 DATA DISPLAY
[]
BOAR/)
4
J
SHI!S
LADDFR
_ S TRACKIN6 TA ANALYSIS -3 ORBIT DETERMINATION
HI ml
STATUS I0 BANKS i DISPLAY i_. MONITORS 60 ira. HIGH OF 3 23
22 I/2 ilt. WIDE 38 in. DEEP GUTTED AGAINST CEILING
OPS DISPLAY M|SS--
PARAMETERS 2ftlilt.X_ft6m
pLOTTER DfSPL PARAMETERS 2ft i i.X I0 ft GieL
6 RECEIVE-ONLY PAGE F_RINTERS 2 REPERFCHRATORS S TABLES 22 I_X22 ON ia.
CHALK
BOARD
-'_
HALL
FIGURE
11-9.
FLIGHT
PATH
ANALYSIS
AREA
LAYOUT
11-27
EPD-
180,
REVISION
1
SECTION
II
The DSIF Net Control Room is located adjacent to the Operations Area (see Figure II-6). trolled and coordinated from this room. A remote
on the first floor of the SFOF, Operation of the DSIF is coninquiry station of the Data
Processing System and a substation of the SFOF Communications System are located in the DSLF Net Control Room to permit monitoring of the tracking and telemetry data obtained by the Deep Space Network (DSN) for operational purposes. The FPAC provides additional support to the DSIF by monitoring the quality of the tracking data in the FPA_A. 3. Mission-Independent Functions in the SFOF are located systems: a) Display Sys-
The relatively mission-independent functions in the SFOF in the operational areas of the SFOF and are divided into four major the Data Processing System, b) the Communications System, c) the tem, and d) the Support System. a. Data The Processing Data System System (DPS) is located
Processing
in the
Data
Proc-
essing Area on the second floor of the SFOF (see Figure LI-10). The major elements of the DPS are the Computer Subsystem, the Telemetry Processing Station Subsystem, the Data Processing Control and Display Subsystem, and the Programming Subsystem. Use of the DPS and of the remote inquiry stations in the SFOF is controlled from the Data Processing Control Console located in the Operations Area. b. Communications System utilized during the Surveyor space flight in the Communications Area in the SFOF.
All communications operations terminate All and and
incoming and outgoing voice, teletype, high-speed data, spacecraft television communications are controlled from, distributed in the Communications Control Room (see All internal communications by this system. in the SFOF will
Figure II-1 I). also be provided c. Display System
The Display System provides the capability of displaying summary, semidetailed, and detailed information about both mission-dependent and mission-independent operations associated with the space flight in the technical and operational areas of the SFOF. The overall status of the Surveyor mission will be maintained on a current basis on the Mission Status Board in the d. Operations System Area.
Support
The Support System provides the services required by the technical and operational personnel during the space flight operations. Maintenance laboratories are provided in the basement.
II-28
"EPD-180,
REVISION
1
SECTION
I/
_UB-COMM FOR BLOCK
CENTER -n_
RANGER
I
23456 IN FEET
SCALE
Illlll
[3
FIGURE
11-10. DATA
PROCESSING
AREA
FLOOR
PLAN
II-29
"EPD-180,
REVISION 1
SECTION II
®
D 0
-7, f_
o.
I
II
11
[I
rl
tI
Jl Ii
u
O O
II II
o u
O 0_
Z
O 0
II
ii
iI I I I
I
Z
0
J r
-o
(.) o
0 Z
I
I[
II
II
il fl tl il
0 0
_
__Q
//-30
• EPD-180,
REVISION
1
SECTION
II
A Standby Room and separate men's are provided on the third floor. The
and women's dormitories SFOF Document Control point data for the obtained
Room, located on the third floor, is the central receipt, indexing, and storage of all operational during the Surveyor mission. 4. Coverage coverage Support, be provided
The SFOF will provide 24-hour-per-day P-4Z Mission from launch to the end of the mission. for the Surveyor space flight operations tests, will the Surveyor SFOS schedule. 5. DSN Ground Communications Ground Communications in Table II-X. System System
to the Surveyor prior to launch, as required in
Mission
The DSN is summarized
for
the Surveyor
P-4Z
ll-31
EPD-180_
REVISION
1
SECTION
II
u u_ o'-
< O O
,o 0
0 _
_n O_ ID-._ o O0 O
111
O
o_,-I
-,, ,,o,1 o o
_,,_. .-.
r/l
o
_
O
O
O
"4-t
_0 O Z
,,D ..o
e¢3 _
O
O
._o
O,--_ o ,,D "_ O
D Z_
O"_
°_',I
O
o,1
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tx]
e,]
_
e¢3 ,---t
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•
? !
Z 0
fT.
0 0
0 U_
O 0
0
O 0
m 0
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m
o _
o_
o N u_ 0 0
O
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[_
Z 0
_D 0
4--* _n
rd
'0 0
0
m_
0.-_
II=32
EPD-180,
REVISION
1
SECTION
III
SECTION DATA A. GENERAL It is the purpose Flight Operations the Air Force Facility (DSIF), are described in DATA FLOW
Ill FLOW
Space includes tation which B.
of this section to describe the flow of data throughout the System (SFOS) for the Surveyor Project. This system Eastern Test Range (AFETR), the Deep Space Instrumenand the Space Flight Operations Facility (SFOF), all of Section II.
Data from AFETR will be obtained from before launch until after spacecraft/launch vehicle separation. This data will provide the information necessary for spacecraft acquisition by the DSIF stations, for computation of the preliminary spacecraft trajectory, and for preliminary evaluation of spacecraft performance. Data that is obtained from the DSIF will be used for real time monitoring of spacecraft performance and status, for near-real time spacecraft performance and flight path analysis, and for determining spacecraft and flight path commands. This data is transmitted from AFETR and the DSIF to the SFOF where computational the SFOF. processing comprises the major effort in data handling by
The nature of Surveyor space flight operations is such that the flow of data in real time is of prime concern. Figure III-1 indicates the types of data that will be obtained during the flights and the types of communications links over which this data may flow from AFETR and the DSIF to the SFOF. It may be seen in Figure III-1 that varied communications capabilities exist for transmitting data to the SFOF; however, this figure does not show specific line assignments or the number of lines available. Each type of data may be traced to its user in the SFOF. Figure ILI-2 details the flow of data from the SFOF to the DSIF. This data comprises spacecraft commands, antenna pointing angles, and administrative information. As in Figure LII-1, this figure does not attempt to indicate information on-line assignments and priorities. C. DATA PROCESSING to
ensure Standard related
Control of data flow and processing is necessary and will be exercised proper receipt and handling of data at the intervals specified in the Sequence of Even_. Thc pr_.cipa! _l._ers of spacecraft and spacecraftdata, and the types of data primarily used are listed below. Group 1} Spacecraft Performance and Command Flight Path Analysis and Analysis Type Engineering of Data Telemetry
2)
Command
Tracking
Data
III- 1
EP.D-180,
REVISION
1
WIDEGAND
CHANNELS
VIDEO
_
BA._EB.4ND
TIM
TIM
HIGH-SPEED
TIM
TTY
COMMAND
VOICE
ADMINISTRATIVE
TTY
ADMINtSTRA77_
TRACKING VOICE S_C INFO
TTY
TIM I
HIGH-SPEED
TIM I
TTY
COMMAND
VOICE
ADMINISTRATIVE
TTY
ADMINISTRATIVE
TTY
TRACKING
VOICE
S/C
//WD
TTY
T/M
HIGH-SPEED
T/M
TTY
COMMAND
VOICE
4_tlINISTRATIV_
ADMINISTRATIVE
TRACKING
VOICE
SIC
/Nr'o
AMR i
!
L_
HIGH-SPEED
T/M
VOICE
ADMINISTP.44_VE
TTY
ADMINISTRATIVE
TTY
TRACKING
NOTE
:
This the each nor types
figure n_er type to of
is of
not intended to circuits available
show of link, of data
communication assignments circuits.
indicate to specific
!
SECTION
III
OPS
AREA
VIDEO
VIDEO
DATA
RE_'_STS D4TA dND SF_D ADMINISTRATIVE
DSIF
CONTROL
RROCESSED
G
I .o. b_
SPAC_CR4FT INFORMATION
I
MISSION
CONTROL
SPAA
J
1
RAW
DATA
B
,ADMINISTRATIVE
TO TrY
RECEIVERS
ADMINISTRATIVE
VOICE
:
L
I
];
•
I
FPAA
i
lid1.
!
FIGURE
SURVEYOR DATA FLOW TO CONTROL AND ANALYSIS AREAS IN SFOF
I
I'
L
III-Z
i)
EPD-180,
REVISION I
343-4RI
DSIF
ADMINISTRATION
8,
CONTROL
SFOD
DSIF
CONTROL
I
|
COMMAND
DECISIONS " I
DIRECTIVES CONTROL COMMAND
AND OF
I
|TTY
I V.OICE
1_1
I
EXECOT,ON ----I" I
COMMAND MESSAGES SPAA
:
COMMAND DECISIONS
_
PREPARATIONS GROUP I I/0 CONSOLE COMMAND 8r CARD READER [A I_
I I,LI
FPAA
TRACKING REQUESTS
PREDICT
SSAA
I ; [1
7288 IN
[
o u
OUT
TRACKING
PREDICTS
I'
7040
I
t
I
PROCESSOR 7090
SECTION
m
COMMUNICATIONS
CONTROL
DSIF
STATIONS
ADM
8= CONTROL PREDICTS
VOICE, TTY VOICE TTY
TTY
TRACKING COMMANDS COMMANDS
v,sos ]-__-_ ,,o
xM,TT _
t
I I
ADM
& CONTROL PREDICTS
VOICE, TTY VOICE TrY
TTY
I "[RACKING COMMANDS COMMANDS
w _l, .,o i sos_--_--._xM,TT_ I
ADM 8_ CONTROL PREDICTS VOICE, TTY VOICE TrY TTY TRACKING COMMANDS COMMANDS
_l_' _J
I I _1 -I sosg,o J---_XM'TTE" 1
FIGURE
m-z.
SURVEYOR DATA FLOW FROM SFOF
III-3
9_
• EPD-180,
REVISION
1
SECTION
IH
3) 4)
Space
Science
Analysis
and
Command
Video Dynamics
and
Touchdown Data and Status
Mission, Operations, Net Control
and
DSIF
Summary Information
It is the responsibility of these groups to interpret, ana/yze, and evaluate the type of data for which they are cognizant. The type of data and the requirements placed by the users determine the types of computation and processing that are performed. A detailed breakdown of data processing within the SFOF may be found in the Surveyor Standard Operating Procedures (SOP) document, EPD":-'.Similarly, additional details concerning internal data flow may be obtain-e-_ from the Surveyor Tracking Instruction Manual (TIM), EPD":-" for the DSIF All and in the Surveyor of data Program by Support the AFETR Control Laboratory Drive Plan will (PSP)::-" for AFETR. be forwarded to:
records
obtained SFOF
Document
Jet Propulsion 4800 Oak Grove Pasadena, All address records within 48
California forwarded to the above
of data acquired by the DSIF will be hours of the time of recording.
Unpublished
this
date.
III-4
EPD-180,
REVISION
1
SECTION
IV
SECTION SPACECRAFT
IV COMMANDS
A.
INTRODUG
TION the operational aspects the Surveyor spacecraft and Surveyor Command System. spacecraft by holding and to increased a minimum the of the states facilities available the general proce-
This section describes for the ground control of dures for their use in the Simplification have of the gained
a mission
been into by for
flexibility the flight
of operation sequences
during that are
preprogrammed to a large extent, is a requirement for the preparation
Be
the spacecraft control system. commands transmitted from highly developed organizational and transmission of commands OF TERMS RELATING
The spacecraft is controlled, ground. Consequently, there and operational procedures to the spacecraft. TO SURVEYOR SPACECRAFT
BASIC COMMANDS I.
DEFINITIONS
Command One of the command when types Direct words listed in the Tables IV-I through produces IV-VII/(see a particular
page IV-13). spacecraft
A command, response. Two a) Type 1.
received by of commands Command
spacecraft, are defined:
A Direct Command Each such command command number, ceed three in value. b) Type A Z. Quantitative
produces an is uniquely the first and
immediate identified third digits
by
spacecraft response. a four-digit octal of which cannot ex-
Command determines by a Command the duration of a particular Direct a fourcannot time
Quantitative
Command response initiated A Quantitative
spacecraft Command. digit, exceed duration Z. Command A spacecraft, Each command command
subsequent associated is represented by digits by the of which desired
octal number (the first and third three) having a value determined of the spacecraft response. Sequence or series of commands which,
when
received series of octal
by
the
produces sequence
aparticular is uniquely
spacecraft identified
response or by a four-digit,
responses. number.
IV-
1
• EPD-180,
REVISION 1
SECTION IV
3.
Command A
Message
instructions quences by by teletype,
statement originating in the SFOF containing commands and/or and concerning the disposition of commands and/or command sethe DSIF. Two command message types, which are transmitted only are:
a)
Type at the Type
I. This DSIF. 2. This
results
in
the
production
of
a CDC
command
tape
b)
.
includes Sequence
all
other
teletype Me
command s sage Return
messages.
Command/Command Transmission The process the DSIF of to
/ Command
transmitting the SFOF. Sequence of
a command/command
sequence/command
message 5.
from
Command/Command The transmission
Execution sequence from the DSIF to
a command/command
the
spacecraft. 6. Command The time. and decision (The from Decision that a particular implementation of the process through Message whereby Preparation a command to message is obtained at the SFOF in series of this decision which the commands be executed is distinct from the decision is reached. ) at a de-
particular cision
itself 7.
Command The process
the proper representation for transmission mand message preparation occurs subsequent mand decision. It is also distinct from the the DSIF, and the disposition of the command establish that the representation so obtained preparation. 8. Command Request to directed occur
the DSIF. (The process of comto, and is distinct from the comcommand message transmission to message after transmission. ) To is correct is part of the comman--'6-
SFOF to the The command pleted. 9.
The request for permission DSIF. This request is request will normally
transmit a command message from a technical area to after command preparation
the is
from SFOD. com-
the
Command The instruction message
Directive by from the the SFOD SFOF to to the the SFOF DSIF. Operations Manager to trans-
mit
a command
IV-Z
EPD-180,
REVISION
1
SECTION
IV
10.
Command A process
Verification whereby to it is determined at the SFOF whether of information message particular is im-
at the correct. portance:
DSIF
pertaining The following
a command/command examples of command
sequence/command verification are
al
Verification at the DSIF
prior to launch are correct. a teletype by the DSIF.
that
preprepared
command
tapes
Verification that rectly received
command
message
has
been
cor-
cl d}
11. Command The or command spacecraft firmation:
Verification cution of Verification CDC
the
that a CDC command tape proper command sequence. that a correct prior to command execution. has
is
in
position
for
exe-
been
entered
on
the
keyboard, Confirmation whereby has
process
it
is
determined
at
the
SFOF
whether and
a command the con-
sequence has responded
been executed correctly correctly. The following
by the DSIF are examples
whether of command
a)
Confirmation Confirmation in the spacecraft.
of of
correct correct
execution storage of
by
the
DSIF. Command
a Quantitative
c}
Confirmation command System
of correct sequences.
spacecraft This is an
response indirect
to process.
commands
or
12.
Command The total implement Command A prese!ected command
available 1 3.
to
means, within the command decisions. System Alternative of
Surveyor
Space
Flight
Operations
System,
implementing
CQ
subsysterp_ decisions.
the
command
system
specified
for
use
in
GENERAL CONTROL
POLICY GOVERNING AND UTILIZATION formulated utilization
OF
OPERATIONAL THE SURVEYOR
PROCEDURES COMMAND to
FOR SYSTEM be is exerdefined
cised in the
The general policy for the control and following paragraphs.
for the Operational of the Surveyor
Procedures Command System
IV- 3
EPD-180,
REVISION
1
SECTION
IV
1)
All command and only by for Surveyor requests.
decisions and command requests will be one of the FPAC, SPAC, or SSAC Directors. details specific responsibilities for these
originated This decisions
by, SFOP and
z)
Transmission of command occur only by Command the SFOD or his designated No commands without the ically noted
messages from the SFOF Directive that must be issued alternate.
to
the DSIF shall by, and only by
3)
or command sequences will be executed approval of the SFOD except in such cases in this document.
by the as are
DSLF specif-
4)
Command System Alternatives those listed in this document; with the specified requirement tered.
shall be selected only from among such selection is to be in accordance for the operational situation encoun-
Utilization of Command System Alternatives in standard operations shall be based, in all cases, on appropriate ating procedures that are prepared prior to, and verified SFO Test Phase.
space flight detailed operduring the
6)
The SFOD shall be responsible general policy stated herein Command Procedure based COMMAND
for interpretation and for the development on this policy.
of the details of the of a Surveyor
D.
SPACECRAFT
SUBSYSTEM of two identical in the command spacecraft subinformation is modulated on a The spacethe central com-
The Surveyor spacecraft command subsystem consists receivers and two central command decoders (for reliability link) and a set of subsystem decoders, located in the various systems (e. g., flight control, electrical power). Command transmitted to the spacecraft as a binary wavetrain, frequency subcarrier that, in turn, phase modulates the DSIF transmitter. craft receiver recovers the binary wavetrain and routes it to mand decoder.
The basic command word is 24 bits in length. Two types of commands are transmitted to the spacecraft: direct and quantitative. (The command word formats are shown in Figure IV-1. Tables IV-I through IV-VIII list direct command words and the proper spacecraft responses.) Direct Commands, most of which initiate some action by the spacecraft, are identified by a four-digit octal number. The centra-r-_-_ecoder routes an ordinary command to the subsystem decoder signified by the first two digits of its octal identification. The subsystem decoder then initiates the spacecraft response called out by the last two digits of the octal command number. A Quantitative Command establishes the length of time over which a spacecraft action initiated by a subsequent Direct Command shall occur. Quantitative Commands are routed by the central command decoder to the flight control subsystem decoder for decoding and storage.
IV-4
EPD-180,
REVISION 1
SECTION IV
O
t
e,]
"_ _
.,4
_o
A
_,_o_
o
u
o
e
_
_2.9o
= _.,4 _._
>,
.,'4
Q)
0 ",4
°,4 .,4
0
U% .--4
0
_u
J o
o
.--4
< 0
f_
.--4
| • _'-_
'-0 M
_ _ o_._° E
4-*
0
A
_
o
_u
• ,4 (D
.,4 u •_ O
,--'4
m C >,
<
_
0 O_
<
o
O
_'-_
0
o-
• -_
O
_>,
O
2
0 "_ o u _>, _n = .,4 U_ > • ,_ ,4
.,4
!
>
D 0
,-.4
u >,
.,4
• ,4
O
mz
O
C_ IV-5
EPD-180,
REVISION
1
SECTION
IV
check coder. mitted rectly fill-in words the E.
As on
protection Direct Quantitative
against error, Command words Commands,
as on
the central a condition the other
decoder performs a complement for entry into a subsystem dehand, are immediately retransthey have been corword synchronization, command words. These however, they violate decoders.
by the spacecraft to the DSIF for confirmation that stored. So that the spacecraft can maintain bit and words are transmitted continuously between actual have a format similar to that of Direct Commands; complement GROUND Figure check and are not entered into subsystem
COMMAND shows, This
SYSTEM in functional diagram shows of command to the DSLF into to the the CDC SFOF at the DSIF form, the the ground capabilities portion for: of the Surveyor
Command 1} 2) 3) 4) 5) 6) 1.
IV-2 System. Preparation
messages
Transmission Entry Return Command Command Space Both of
commands transmission verification confirmation
Fli_ht the
Operations and
Facility the
(SFOF) verification of long or complex the command means
preparation
messages of the
will SCP/CVT
be
implemented Programs. To make tion link electrical
in the Computing These programs up command to the DSIF. interface internally dictionary
Subsystem of have the following
SFOF by capabilities:
a)
messages for output on the communica(The Computing Subsystem has a direct with the TTY link in the SFOF.) that the commands so stored in the Computing prepared Subsystem match
b)
To determine the command disc file. To display examination. the
c) d)
command
message
in
the
user
areas
for
visual
To verify correct transmission of command messages to the DSJ_ through bit-by-bit comparison of the return-transmitted and original messages. (Command messages return-transmitted via TTY will also enter the Computing Subsystem through direct electrical interface with the TTY link. ) Any error is indicated put in the and specifically area identified displays. by English language outtechnical
IV-6
• EPD-180,
REVISION
1
SECTION
IV
]
Ihl
L
=-
_8
!
o
! !
[-4
_O
Z
0 0 0
D
oo.
I
D 0
I'M
I
IV-7
" EPD-180,
REVISION
1
SECTION
IV
e)
To confirm commands transmitted to the spacecraft through bit-by-bit comparison of executed and original sequences. (This information will also enter the Computing Subsystem from the TTY link from DSIF through direct electrical interface. ) messages can be prepared for TTY transpaper tape. Command messages can also verbal instruction over voice line. Verifica-
Additionally, command mission as manually punched TTY be transmitted from the SFOF as
tion can be implemented, if necessary, by the comparison of l_nglish language printouts of transmitted and return-transmitted TTY messages, or by machine comparison of transmitted and return-transmitted TTY tapes. Deep Handling Space Instrumentation (C'DC) Facility (DSIF) and Command and Data
Console
Generation of the command signal that modulates the DSIF transmitter (the modulated subcarrier) is accomplished by the command subsystem of the GDC. Command words are entered in a ten-bit register in the GDC by sequentially depressing four of a set of octal keys, or through a punched mylar tape reader from tapes prepared before the mission or generated from TTY transmission during the mission. The octal command number (or magnitude) is, at this time, displayed on the console for operator examination. In the keyboard entry mode a "transmit" button initiates sequential readout of the register contents to modulate the SCO. The sync signal and the complement bits (in the case of Direct Command words) or address bits (in the case of Quantitative Commands) are generated automatically by the in words from "canned" information. "manual transmit" mode, the tape mitted each time a "proceed" button mode, the tape is time the "proceed" programmed stop that can alternately link to the SFOF. logic. There is advanced is pressed. CDC are The CDC also generates the filltwo modes of tape entry. In the one step and a command is transIn the "automatic transmit" from the a tape readers the TTY
advanced and commands are transmitted continuously button is pressed until a "stop" button is pressed or is reached. The CDC will employ two command tape be switched into the CDG command register or into
characters tified by mode in sequence
The command tapes contain, besides the command words, needed for tape control. In particular, command sequences their sequence numbers. The CDC incorporates an automatic which the tape reader locates the beginning of any specified on the tape. Several features permit close control over any error in
additional are idensearch command
transmission
to
the
spacecraft:
a)
Information on reader directly lating the DSIF
the CDC tape onto the TTY transmitter.
can be entered from the CDC tape link to the SFOF without modu-
IV -8
EPD-180,
REVISION
1
SECTION
IV
b}
Whenever a command word is transmitted the command information is transmitted to the SFOF. The command subcarrier the DSIF station to provide spacecraft. All commands execution, by SYSTEM executed the CDC is also recorded a record of all
to the spacecraft, in real time via
TTY
c)
on magnetic transmission
tape at to the
d)
are recorded, with Command Printer.
the
time
of their
F.
COMMAND
ALTERNATIVES in space flight operations and 3 defined below. The encountered. shall be selection selected will be
Command System Alternatives from among Alternative Nos. 1, Z, specified for the operational situation 1. Alternative Alternative sequence(s} Z. Alternative No. No. exist No. 1
as
command
1 (Figure IV-B) on a preprepared Z
will be used tape at the
whenever DSIF site.
the
required
Alternative No. 2 (Figure IV-4) will be used in command situations for which there are no preprepared command tapes. In this mode, the command message will be return-transmitted in its entirety for verification before transmission to the spacecraft is begun. 3. Alternative No. 3 in those situations for does not permit use of in the CDC by Keyboard
which there Alternative Entry Mode.
Alternative No. 3 (Figure IV-5) will be used are no preprepared command tapes and time No. Z. In this mode, commands are entered
It may be desirable during the mission to use a combination of Alternative Nos. 1 and 3 when the desired command sequence is a minor variation of a sequence that exists on a preprepared tape. The preprepared tape will be entered in the CDC, and special or changed commands will be entered on the CDC keyboard as required.
IV-9
E'PD-180,
REVISION
1
SECTION
IV
E
E
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IV-IO
!
i!i_ •
EPD-180, REVISION 1 SECTION IV
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IV-II
• EPD-180,
REVISION 1
SECTION IV
E
wo _ z_
06
z
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u
d
Z
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t
i
f
< Z
4
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D
IV-12
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER TITLE:
IV-L DATA
LIST LINK
OF AND
DIRECT TV
COMMANDS CAMERA (NO. 4)
APPROACH
OCTAL COMMAND NUMBER
SHORT COMMAND (24 TITLE Characters) SPACECRAFT RESPONSE INITIATED
0100 0101
SPARE XMTR-ALOW - PW R- ON Applies power A for Ibw-power the wide-band tion. Applies filament Transmitter A for high-power to Transmitter operation in (WB) configura-
0102
XMTR-A-
FILA-
PWR-
ON
power to in preparation operation. only 0125 if have
0103
XMTR-
A- HI- VOL
TS- ON
Applies high voltage Commands 010Z and been received. Applies power B for low-power the wide-band to
0104
XMTR-
B- LOW-
PW
R- ON
Transmitter operation configuration.
in
0105
XMTR-
B - FILA-
PW
R- ON
Applies filament power to Transmitter B in preparation for high-power operation. only 0127 if have
0106
XMTR-
B-HI-VOLTS-ON
Applies high voltage Commands 0105 and been received. Removes high ating transmitter(s). voltage
0107
XMTR-HI-VOLTS-OFF
to
oper-
0110
XMTR-
FILA-
PWR-
OFF
Removes high voltage mitter( s):
filament to
power operating
and trans-
0111
XMTR-
LOW-
PWR-
OFF
Removes transmitter(s) ON
power
to and to
operating to VCXO(s).
0112
NARROW
- BAND-
VCXO-
Applies power phase modulator, fier of operating Also turns off
NB VCXO, NB and NB amplitransmitter. WB VCXO.
(This
table
continued
on
next
page.
) IV- 13
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER TITLE: DATA LINK
IV-I. AND
(CONT'D) TV APPROACH CAMERA (NO. 4)
OCTAL COMMAND NUMBER
SHORT COMMAND TITLE
SPACECRAFT RESPONSE INITIATED
0113
NARROW-BAND-VCXO-OFF
Removes NB VCXO ation. Increases of main emergency
power and
to operating allows WB
oper-
0114
HI-
MOD
- GAIN
frequency carrier. TV normal of main Transmitter
deviation Used for
mode. frequency carrier. B to Transmitter
0115
NORM-
MOD-
GAIN
Restores deviation Switches planar A to
0116
XMTR-
B-
TO-
PA
array omniantenna.
and
0117
XMTR-A-
TO-PA
Switches planar B to
Transmitter array omniantenna. and
A Transmitter
to
0120
SE LEC
T- OMNI-A
Switches selected to Omniantenna B Switches selected to Omniantenna Applies A. Applies B. Removes transponder(s). PWR Switches Transmitter amplifier. Switches output power to
transmitter A. transmitter B. Transponder
0121
SE LEC
T- OMNI-
0122
XPONDER-A-PWR-ON
0123
XPONDER-B-PWR-ON
power
to
Transponder
0124
XPONDER-PWR-OFF
power
to
operating
0125
XFR-
SW-A-HI-
antenna A
to final
output power
of
0126
XFR-
SW - A- LOW
- PWK
of
antenna Transmitter
to
low-power A.
(This
table
continued
on
next
page.
)
IV- 14
EPD-180,
REVISION 1
SECTION IV
TABLE DE C ODE R TIT LE: DATA LINK
IV-I. AND
(CONT'D) TV APPROACH CAMERA (NO. 4)
OCTAL COMMAND NUMBER
SHORT COMMAND
TITLE
SPACECRAFT RESPONSE INITIATED
0127
XFR-SW-B-HI-PWR
Switches Transmitter amplifier. - PWR Switches output APRCAM Applies control
antenna to B final
output power
of
01 30
XFR-
SW
- B - LOW
of
antenna Transmitter power system. to to
to
low-power B.
0131
VDN-
TE MP-
C TRL
- ON-
temperature
0132
PWR-ON-APRCH-CAMERA
Applies power 4 electronics. CAMERA Initiates cludes one vertical power
Camera
No.
0133
STR-FRM-APRCH-
frame sync to
which and Camera
invideo. No.
0134
PWR-
OFF-APRCH-
CAMERA
iRemoves !4 electronics. C M
0135
ALL-
TE MP-
C TRL
- OFF
- APR-
Removes power to electronics and vidicon temperature control. Turns on 4 electronics power to heater. Camera No.
0136
ELC
T- TEMP-
C TRL-ON-APR-
CM
0137
SPARE
IV-15
EPIg-180,
REVISION
1
SECTION
IV
TABLE
IV-I/.
LIST
OF
DIRECT
COMMANDS PROCESSING
DECODER
i
TITLE:
SIGNAL
OCTAL C OMMAND NUMBER
SHORT COMMAND
i
TITLE
SPACECRAFT RESPONSE INITIATED
0Z00
LOW-MOD-INDEX-SCO-
ON
Applies power to SCO used for 550 bps transmission following separation and during lunar operation. Applies version Applies version power to clock circuitry. power to circuitry. clock and con-
0201
A/D-
CONV-
1 - PWR-
ON
0202
A/D-CONV-Z-PWR-ON
and
con-
0203
A/D-CONV-PWR-OFF
Removes power A/D converter. C LK-RATE S
to operating
0204
A/D-
COAST-
PH-
Permits bit rate selection of 17.2 bps (OCT. 0505), 137.5 bps (OCT. 0504), or 550 bps (OCT. 0503). Selects bit rate of 1100 bits
0205
A/D-CLK-RATE-
1 i¢#- BPS
per second (100 second, 11 bits 0206 A/DCL K- RATE - 44_k BPS Selects bit rate
words per per word). of 4400 bits
per second (400 second, 11 bits 0207 PRE - SUM - AMPON Applies power ming amplifier. Applies quired power to phase
words per per word). to PM presum-
0Zl0
PHSE-
SUM-AMP-A-ON
to
amplifier modulate
reTrans-
0Zll
PHSE
- S U M-AMP-
B - ON
Applies quired mitter
power to phase B.
to
amplifier modulate
reTrans-
0212
FREQ-
SUM-
AMP
-A- ON
Applies power to amplifier required to frequency modulate Transmitter A. on next page. ) IV-16
(This
table
continued
"EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER TITLE:
IV-IL
(CONT'D) PROCESSING
SIGNAL
OCTAL COMMAND NUMBER
SHORT COMMAND
TITLE
SPACE RESPONSE
C RAF T INITIATED
0213
FRJEQ
- SUM-
AMP-
B - ON
Applies power to amplifier required to frequency modulate Transmitter B. Removes power to presumming, phase and frequency summing amplifier s. Applies power to SCO normally used for 550 bps transmission. Applies power used for II00 Applies power used for 4400 to SCO normally bps transmission. to SCO normally bps transmission.
0214
SUM-AMP-OFF
0215
3.9
KC-A/D-SCO-ON
0216
7. 35 KC-A/D-SCO-ON
0217
33 KC-A/D-SCO-ON
0220
33, 7. 35,
3.9
KC-SCOS-OFF
Removes power to SCO's and isolation amplifier used for transmission of A/D output. -ON Applies power to signal processor used for transmission of gyro speeds. roll, pitch, or yaw gyro
0221
GYRO-
SPE
E D- SIC-
PROC
O222
SE LE
C T - NEXT
- GYRO-
SPD-
C NL
Selects speed.
0223
GYRO-
SPD
- SIC- PROC
- OFF
Removes power essor for gyro Applies summing transmit - OFF Removes amplifier accelerometer
to signal procspeed data.
0224
BASIC-
BUS-ACCEL-
CNLS-ON
power to SCO's and preamplifier used to accelerometer data. power used to SCO's to transmit data. and
0225
BASIC
- BUS-
AC
CE
L - CNLS
(This
table
continued
on
next
page.
)
IV- 17
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER TITLE:
IV-IL
(CONT'D) PROCESSING
SIGNAL
OC TAL COMMAND NUMBER
SHORT COMMAND
TITLE
SPACECRAFT RESPONSE INITIATED
0226
ENGR-
CMTR-
1 - ON
Applies containing midcour Applies required descent planar
power to commutator data required for se correction. power to commutator during terminal when transmitting array.
0227
ENGR-CMTR-2-ON
on
O230
ENGR-CMTR-
3-ON
Applies power to commutator required during terminal de scent when transmitting on omnianterma. Applies power to commutator containing data required during acquisition and lunar operation.
0231
ENGR-CMTR-4-ON
0232
ENGR-
CMTRS-
OFF
Removes power ing commutator Applies SCO to ing via power allow FM/FM power SCO. power provide telemetry. power amplifier.
to all engineers. reject/enable time monitorchannel. from reject/
0233
CMD-REJ/ENBL-SCO-ON
to real
0234
CMD-R.EJ
/ ENBL-
SCO-OFF
Removes enable Applies fier to Centaur
0235
A/D-ISOLTN-AMP-ON
to isolation A/D output
amplivia
0236
A/D-
ISOL
T N- AMP-
OFF
Removes isolation
from
A/D
0237
LOW
- MOD-
INDE
X- SCO-
OFF
Removes power from SCO used for 550 bps transmission following separation and during lunar operation.
IV-18
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER
IV-IIL
LIST TITLE:
OF
DIRECT
COMMANDS POWER
ELECTRICAL
OCTAL COMMAND NUMBER
SHORT COMMAND
TITLE
SPACE RESPONSE
C RAF T INITIATED
0300
FLT-
CTRL-
COAST-
PZ-
PWR-ON
Applies circuits control.
power to for Coast
flight Phase
control attitude
0301
ENBLE-
BATT-
PRESS-
LOGIC
A/lows battery charging discontinued if battery pressure exceeds 65 Disables to permit battery battery
to be manifold psi. logic
0302
DSBLE
- BATT-
PRESS-
LOGIC
pressure charging.
0303 0304
SPARE BYPS-MN-OTC Bypasses circuitry lated bus. Applies regulated sensing overcurrent in nonessential sensing regu-
03O5
ENBLE-MN-OTC
power bus circuitry.
to via
nonessential overcurrent
0306
OCR-ON-&
-BYPS-OFF
Applies mize panel
power to OCR to power transfer from to battery. OCR to permit
maxisolar
0307
OCR-BYPS-ON-&-OCR-OFF
Bypasses
charg-
ing at reduced efficiency but at lower compartment dissipatiom 0310 OCR-OFF Turns solar 0311 ALL-FLT-CTRL-PWR-OFF (I) off panel OCR from and removes power system. con-
Removes power trol regxflated
from flight and unregulated.
0312 0313 0314
SPARE SPARE NONESSENLOADS-OFF (I) Removes power from tial regulated bus. nonessen-
(This
table
continued
on
next
page.
)
IV- 19
EPD-180,
REVISION 1 TABLE IV-IlL DECODER TITLE: (CONT'D) POWER
SECTION IV
ELECTRICAL
OCTAL
COMMAND NUMBER SHORT COMMAND TITLE
,m
SPACE RESPONSE
CRAF T INITIATED
0315 0316 0317
SPARE SPARE AUKBAT T - MODE - ON Connects batteries through main and auxiliary to unregulated bus isolation diodes. directly removes connec-
0320
RE
STORE
- MAIN-
BATT-
MODE
Connects main to unregulated auxiliary battery tion. Disables logic
battery bus and diode
0321
DSBLE-
BATT
-XFR-
LOGIC
which
switches
system to auxiliary battery mode at low main battery voltage. 0322 HI-CUR-MODE-ON Connects rectly Removes between unregulated 0324 to 0337 auxiliary unregulated direct auxiliary bus. battery bus. connection battery and di-
to
0323
Ill-CUR-MODE-OFF
SPARE
IV-Z0
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER
IV-IV. TITLE.
LIST
OF
DIRECT
COMMANDS AND VEHICLE
MECHANISMS
OCTAL COMMAND NUMBER
SHORT COMMAND SPARE S TEPSOLAR-
TITLE
SPACECRAFT RESPONSE INITIATED
0400 0401
PANEL
- PLUS
Pulses solar Pulses solar Pulses polar Pulses polar
stepping panel +0. stepping panel -0. stepping axis +0. stepping axis -0.
motor to move lZ5 degrees. motor to move 125 degrees. motor to move 125 degrees. motor to move 125 degrees.
040Z
STEP-
SOLAR-
PANEL-
MINUS
0403
STEP-
POLAR-AXIS-
PLUS
0404
STEP-
POLAR-AXIS-
MINUS
0405
STEP-ROLL-AXIS-
PLUS
Pulses stepping motor to move roll axis +0. 125 degrees. Pulses stepping roll axis -0. lZ5 Pulses elevation stepping axis stepping axis motor to move degrees. motor 125 motor 125 to move degrees to move degrees. to Com-
0406
STEP-
ROLL-AXIS-MINUS
0407
STEP-ELEV-AXIS-PLUS
+0.
0410
S TE P -E LE V -AXIS-
MINU
S
Pulses elevation Supplies partment Supplies A heater control. Removes Supplies partment
-0.
0411
COMPT
- A - HTR-
PWR-
ON
power directly A heater. power through
0412
COMPT-A-
THRM-CTRL-AUTO
to Compartment a proportional
0413 0414
COMPT-
A-HTR-
PWR-OFF
heater
power. to Com-
COMPT-B-HTR-PWR-ON
power directly B heater.
(This
table
continued
on
next
page.
)
IV-Z1
EPD-180,
REVISION 1
SECTION IV
TABLE IV-IV. DECODER TITLE: OCTAL COMMAND NUMBER
0415 COMPT
(CONT'D)
MECHANISMS AND VEHICLE
SHORT COMMAND - B- THRM-C
TITLE TRL-AU TO
SPACECRAFT RESPONSE INITIATED
Supplies B heater c ontr ol. Removes
power through
to Compartment a proportional
0416 0417 to 0437
COMPT
- B- HTR-
PWR-
OF F
heater
power.
SPARE
IV- ZZ
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER
IV-V. TITLE:
LIST
OF
DIRECT
COMMANDS PAYLOAD
ENGINEERING
OCTAL COMMAND NUMBER SHORT COMMAND TITLE SPACECRAFT RESPONSEINIT_TED
0500
COAST-
PH-
I-A/D-
SCO-
ON
Applies used for Applies used for
power 137.5 power 17.
to SCO normally bps transmission. to Z bps SCO normally
0501
COAST-
PH-II-A/D-
SCO-
ON
transmission.
0502
COAST-PH-A/D-SCO-OFF
Removes power from Coast Phase I and Coast Phase II A/D SCO' s.
0503
A/D-
CLOCK-
RATE-
5 5 @- BPS
Selects bit rate of 550 bits per second (50 words per second, ii bits per word). Selects bit rate of 137.5 bits
0504
A/D-
CLOCK-RATE-
1 37.5- BPS
per second (IZ. 5 words per second, ii bits per word). 0505 A/D-CLOCK-R.ATE17. Z-BPS Selects second bit rate of 17. Z bits per (1.56 words per second, word).
l I bits per 0506 COASTPH-CMTR-ON Applies required CMTR-ON
power to commutator for Coast Phase. commuof com-
0507
TRST-
PH-
BAC
K- UP-
Applies power to backup tator in case of failure
mutators l, 2, 3 during midcourse correction or terminal descent. 0510 AUX-CMTR-OFF Turns off commutator backup 0511 AUX-ACCEL-AMP-ON Applies ometer power and to Coast ThrusL Phase Phase
commutator. power to four acceleramplifiers: one near A, solar one near B panel mast.
Compartment and two on
(This
table
continued
on
next
page.
)
IV-Z
3
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER TITLE:
IV-V.
(CONT'D) PAYLOAD
ENGINEERING
OCTAL COMMAND NUMBER 0512
SHORT COMMAND
TITLE
SPACECRAFT RESPONSE INITIATED
J|, i i
AUX-ACCEL-AMP-OFF
Removes power to four auxiliary accelerometer amplifiers turned on by Octal Command 0511. Applies amplifier transmit data. power to presumming and two SCO's used auxiliary accelerometer
0513
AUX-ACCEL-DATA-CHAN-ON
to
0514
AUX-ACCEL-DATA-CHAN-OFF
Removes power to amplifier and SCO's used to transmit auxiliary accelerometer data. Applies absorber Removes absorber CHNLON power strain to three gage shock amplifiers. three shock amplifiers.
0515
TD-STRN-
GA-PWR-ON
0516
TD-STRN-GA-PWR-OFF
power from strain gage
0517
TD- STRN-
GA- DATA-
Applies power to presumming amplifier and three SCO's to transmit shock absorber gage data.
used strain
0520
TD-STRN-GA-DATA-CHNL-OFF
Removes power from amplifier and SCO's used to transmit shock absorber strain gage data. Applies power to three thrustlevel strain gage amplifiers, one for each vernier engine. Removes power to three thrustlevel strain gage amplifiers.
0521
PROPUL-STRN-GA-PWR-ON
PROPUL-STRN-GA-PWR-OFF
0523 to 0537
SPARE
IV-24
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER TITLE:
IV-VI.
LIST
OF
DIRECT
COMMANDS AUXILIARY
ENGINEERING
MECHANISMS
OC TAL COMMAND NUMBER
SHORT COMMAND TITLE
SPACE RESPONSE
C RAF
T
INITIATED
O6O0
E X TE
ND
- LANDING-
GE
AR
Energizes
squib-actuated
pingear Centaur). pinlatches Centaur).
pullers to extend landing (normally actuated from 0601 EXTEND-OMNI-ANTENNAS Energizes pullers (normally 060Z 06O3 SPARE DUMPNITROGEN-(I) squib-actuated release boom actuated from
to
Energizes squib-actuated dump valve. Removes AMR heater power.
nitrogen
0604 06O5
AMR-HTR-OFF SPARE
0606 0607
SPARE PRE SSURE - VE RNIE R- S YS- (I) Energizes release squib-actuated valve. squib-actuated helium
0610
DUMP-HELIUM-(I)
Energizes dump valve.
helium
0611
t
VER-LINES-Z-TCP-ON
Applies heater power to maintain temperature of Vernier Lines No. 2. Z - TCP-ON Applies temperature No. 2. Removes Vernier Vernier heater of power Vernier to maintain Fuel Tank
0612
VER-
FUEL-
TANK-
0613
VL-Z-&-VFT-Z-TCP-OFF
heater power from Lines No. 2 and Fuel Tank No. g.
(This
table
continued
on
next
page.
)
IV-25
.EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER TITLE:
IV-VL
(CONT'D) MECHANISMS AUXILIARY
ENGINEERING
OCTAL COMMAND NUMBER
SHORT COMMAND
TITLE
SPACECRAFT RESPONSE INITIATED
0614
VER-
LINES-
i - TCP-ON
Applies temperature No. i. ON
heater of
power Vernier
to
maintain Lines
0615
VER-
OXDZ
- TANK-
2 - TCP-
Applies heater temperature Tank No. 2. Removes Vernier Vernier 2. Applies temperature No. 3.
of
power Vernier
to
maintain Oxidizer
0616
VL-
1 -& - VOT-
Z- TCP-OFF
heater power from Lines No. 1 and Oxidizer Tank No.
0617
VER-
LINES-
3- TCP-ON
heater of
power Vernier
to
maintain Lines
0620
VER-OXDZ-
TANK-
3- TCP-ON
Applies heater temperature Tank No. 3. Removes Vernier Vernier 3. Applies ometer Removes amplifiers Command
of
power Vernier
to
maintain Oxidizer
0621
VL-
3- & - VOT
- 3- TCP-OFF
heater power from Lines No. 3 and Oxidizer Tank No.
0622
BB-ACCEL-AMPS-ON
power amplifier power
to
four s.
acceler-
0623
BB-ACCEL-AMPS-OFF
to accelerometer on by Octal
turned 0622. power to
0624
AMR-HTR-ON
Applies package.
preheat
AIVLR
0625
AMR-
PW
R - O N
Applies AMR.
"warm-up"
power
to
(This
table
continued
on
next
page.
)
IV-26
E_D-180,
REVISION 1
SECTION IV
TABLE DECODER TITLE:
IV-VI.
(CONT'D) MECHANISMS AUXILIARY
ENGINEERING
OCTAL COMMAND NUMBER SHORT COMMAND
l
TITLE
SPACE RESPONSE
CKAF T INITIATED
0626
E NABLE
- AMR
"Operate" marking
command radar. power from
to
altitude
0627 0630
AMR-
PWR-OFF-(I) {I)
Removes Energizes which RADVS. L-(T)
AMR. switches from
RADVS-PWR-OFF-
remove
pyrotechnic power
0631
UNLOCK-
SOLAR-
PANE
E ner gize s squibpullers to permit of solar panel.
actuated pinpositioning
0632
UNLK-M_ST-ROLL-AX
Energizes squib-actuated pullers to permit mast axis positioning.
pinroll
0633
SPARE
0634
UNLK-ELEV-AXIS
Energizes pullers to of elevation Energizes pullers of solar GEAR Energizes mechanism rigid. Energizes which apply
squib-actuated permit positioning axis.
pin-
0635
UNLK-SP-(L)
squib-actuated to permit positioning panels.
pin-
0636
LOCK-
LANDING-
squib-actuated locking to hold landing gear
0637 RADVSPWR-ON-(I)
pyrotechnic power
to
switches RADVS.
IV-27
EPD-180,
REVISION
1
SECTION
IV
TABLE
IV-VII.
LIST TITLE:
OF
DIRECT
COMMANDS CONTROL
DECODER
FLIGHT
OCTAL COMMAND NUMBER 0700
SHORT COMMAND
TITLE
ii
SPACECRAFT RESPONSE INITIATED
INERTIAL-
MODE
-ON
Output Sets I, II, and III are to provide inertial reference. Stops craft Initiates pitch with and Sun. motion in all three axes (roll, pitch, automatic yaw search roll
reset
0701
RATE-
LOCK-MODE
-ON
spaceand yaw). in axis
070Z
SUN-
AC Q -MODE
-ON
to align
0703
SUN-
& - STAR-ACQ-
MODE-
ON
Initiates roll
automatic
search after star lock-on if lock-on
in 0702. or
to acquireCanopus Sun and reference are absent.
0704
CRUISE
-MODE-ON
Provide inertial signals
0705
EMER-
P- PRECE
SS-E NABLE
Performs cession gency.
function of pitch preenable in case of emer-
0706
ENABLE INHIBIT-
- GAS-JE GAS-JE
T - AMPS T-AMPS
Enables gas jet amplifiers case of emergency. Inhibits gas jet amplifiers case of an emergency, Establishes command Initiates pre set polarity s. roll attitude
in in
070
0710
POS-
ANGLE
-MANE
U VE R
of attitude
0711
ROLL
maneuver Command.
by Quantitative ' .... "*-'_
071Z
I-'I'I'C bl
Initiates ..... pre set
by Quantitative yaw attitude by Quantitative Sun lockroll attitude on
Command. maneuver Command. and maneuver.
0713
YAW
Initiates preset -ROLL Maintains initiates
0714
SUN-&
(This
table
continued
on
next
page.
) IV-28
EI:'D-180,
REVISION
1
SECTION
IV
TABLE DECODER
IV-VII. TITLE:
(CONT'D) FLIGHT CONTROL
OCTAL COMMAND NUMBER
SHORT COMMAND
TITLE
SPACE RESPONSE
C RAF T INITIATED
0715
MANUAL-
DE
LAY-
MODE
-ON
Prepares programmer ground-controlled
time
to accept interval.
0716 0717 0720 0721
SPARE SPARE RESET-SET-IV-OUTPUTS MVC-OR-EVI-(I)
Resets Initiates rection stored
Set
IV
outputs. increment to the cor-
velocity corresponding magnitude. thrust of lb. total the to Set thrust
0722
SE LE
C T - NOM-
THRU
S T - BIAS
Reduces from 200 Increases engines
vernier to 150 of 200
engines lb. total. vernier lb. total. AMR
0723
RE
SE T - NOM-
THRUS
T - BIAS
nominal IV outputs
0724
RE
TRO-
SE Q- MODE
- ON-
(I)
Enables signal.
and
07_5
0726 0727
SPARE SPARE FLTC TRLTRSTPHZPWRON Applies circuits verniers Performs signal in power to flight control required for control of and retro. function case of Flight of AMR
0730
E MER-
AMR-
SIG
emergency. Control retro Proigni-
0731
EMER-RETRO-IGN
Commands
grammer to deliver tion signal. 0732 EMER-RETRO-EJECT Commands grammer and sets
Flight Control Proto deliver retro eject burnout latch circuit.
(This
table
continued
on
next
page.
)
IV-29
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER
IV-VII. TITLE:
(CONT'D) FLIGHT CONTROL
OCTAL COMMAND NUMBER 0733 EMER-
SHORT COMMAND START-
SPACE TITLE THRUST RESPONSE
CRAF
T
INITIATED
PGRMD-
Sets delayed--post-burnout latch circuit, enabling programmed thrust. Performs "on" gency. signal function in case of of
vernier
07 34
EMER-RADVS-ON-SIG
RADVS emer-
0735
E_ER-
VE
NT-
VERN-
ENG-
SIG
Performs engine
function purge signal
of vernier in case of
emergency. 0736 TERMVERN-ENGVENT Resets latch engine 07 37 THRUS T - PH Z - PWROF F Removes circuits verniers vernier circuit purge engine terminate purge 5-min.
to
cycle.
power to flight control required for control of and retro.
IV- 30
EPD-180,
REVISION 1
SECTION IV
TABLE DECODER
IV-VIII. TITLE:
LIST TELEVISION
OF
DIRECT SURVEY
COMMANDS CAMERA (NO. 3)
OCTAL COMMAND NUMBER
SHORT COMMAND
TITLE
i
SPACE RESPONSE
CRAF T INITIATED
1100
START-FRAME
Gates logic transmission.
to
initiate
video
1101 llOZ 1103
SPARE SPARE SURVE Y- CAMERAPWRON Turns 3. on power to Camera No.
1104
SURVE
Y- CAME
RA-
PWR-
OFF
Turns off electronics Returns Opens light
power for shutter
to TV Survey to under normal
system Camera. mode.
ii05 1106
SHUTTER-NORM SHUTTER-OPEN
shutter conditions.
minimal
1107
E ME
R-
MODE
- ON
Selects emergency and amplitude. Energizes assembly Energizes assembly 1 e ngth. Iris f-stop iris motor to Z5 motor to 100 to mm to mm
scan
rates
1110
SET-25-MM-FOCAL-LGTH
drive focal drive focal
lens length. lens
1111
SET-100-MM-FOCAL-LGTH
1112
IRIS-SERVO-ON
serve loop closed automatically, is not at extreme
to control provided setting.
ili3
STEP-IRIS-
OPEN
.z_"1_° stepper iris one f-stop loop is open. Pulses stepper iris one f-stop loop is open.
meter to open if iris serve
1114
STEP-IRIS-CLOSED
motor if iris
to close serve
(This
table
continued
on
next
page.
)
IV- 31
•
EPD-180,
REVISION 1
SECTION IV
TABLE IV-VIII. DECODER TITLE:
OCTAL COMMAND NUMBER
l
(CONT'D)
CAMERA (NO. 3)
TELEVISION SURVEY
SHORT COMMAND
TITLE
SPACECRAFT RESPONSE INITIATED
1115
S TE
P - MIRROR-
RIGHT
Pulses mirror right. Pulses mirror left.
stepper 3 degrees
motor in
to move azimuth
to
1116
STEP-MIRROR-LEFT
stepper 3 degrees
motor in
to move azimuth
to
1117
2 - STE
PS- MIRROR-
RIGHT
Pulses mirror T Pulses mirror
stepper motor to move 6 degrees to right. stepper 6 degrees motor to to left. move
1120
2 - STE
PS-
MIRROR-
LEF
I121
STEP-
MIRROR-
DOWN
Pulses stepper motor to move mirror 2.5 degrees down in elevation. Pulses mirror tion. stepper motor to move 2. 5 degrees up in eleva-
1122
STEP-
MIRROR-UP
1123
STEP-FOCUS-IN
Pulses stepper in (focus range: 50 steps). Pulses stepper out (focus range: 50 steps). Starts in until stepper command
motor G0 to
one 6 ft.
step in
1124
STEP-FOCUS-OUT
motor 6 ft.
one step to ¢0 in
1125
MULT-STEP-FOCUS-IN
motor is
to run repeated. to run repeated.
focus
1126
MULT-
STE
P- FOCUS-OUT
Starts stepper motor out until command is RIGHT Pulses stepper filter wheel 90 ( 360 ° maximum
focus
1127
STE
P - F LTR
- POSITION-
motor to rotate degrees to right rotation).
(This
table
continued
on
next
page.
)
IV- 32
EPD-180,
REVISION
1
SECTION
IV
TABLE DECODER TITLE:
IV-VIII.
(CONT'D) SURVEY CAMERA (NO. 3)
TELEVISION
OCTAL C OMMAND NUM BE R
SHORT COMMAND
TITLE
SPACECRAFT RESPONSE INITIATED
1130
STEP-
FLTR-
POSITION-
LEF
T
Pulses stepper filter wheel 90 (360 ° maximum
motor to rotate degrees to left rotation).
1131 1132 1133
SPARE SPARE SURVE Y- CAMERAVTC - ON Turns on power to Survey era vidicon heater. Turns off in Survey power Camera. to vidicon Cam-
I134
SURVEY-CAMERA-VTC-OFF
heater
1135 1136
SPARE SURVEY-CAMERA-E TC-ON Turns on electronics power to heater. Camera No. 3
1137
SURVE
Y- CAMERA-
E TC
-OFF
Turns off power to era No. 3 electronics
Survey Camheater,
IV- 33
EPD-180,
REVISION 1
SECTION V
SECTION V STANDARD SEQUENCE OF EVENTS A. GENERAL
Table V-l, the Standard Sequence of Events, specifies an expected sequence of events during normal operation of the Atlas/Centaur vehicle, the Surveyor spacecraft, and the Space Flight Operations System.
This table will be changed the lunar approach and descent change. Subsequent revisions as necessary. portion of the of this document In particular, sequence may will reflect it is expected require considerable these changes. that
V-1
E/Z'D-180,
REVISION
1
SECTION
V
B.
LEGEND
FOR
TABLE
V-l,
STANDARD
SEQUENCE
OF
EVENTS
Time T
of Event Time
Column Before A Comm
Station -
Column Mission Control, SFOF Center, System, SFOF
- Countdown Liftoff - Time
Communications Data SFOF DSIF JPL/HAC Processing
L
of Liftoff Data
I TD
- Time - Time
of Injection of Touchdown Net E FP -
Net
Control, Control,
SFOF AFETR and
Flight Path Analysis Command (FPAC) Spacecraft Space Flight Operations Facility (SFOF) Spacecraft Analysis (SPAC) Performance and Command
S/C SF
-
SP
-
SS
-
Space Science Analysis Command (SSAC) Telemetry
and
TM
-
AFETR AFETR Tel II AFETR 1.16, -
and Cape
DSIF Kennedy
Stations
12
-
Ascension
Island
AFETR
9. 1
-
Antigua
DSIF
11
-
Goldstone California Canberra, Johannesburg,
Pioneer
Station,
DSIF DSIF
42 51
-
Australia South Africa
V-2
EPD-1.80,
REVISION
I
SE_TZON
V
TABLE ITEM TilqE OF EVENT
V-I STATION
STANDARD
SEQUENCE
OF
EVENTS
EVENT
SS
T-IOH
E
|,
SPACECRAFT
READINESS
TESTS
BEGIN.
RR
QQ
T-BH
T-SH2Olq
DATA
coIqM
1.
1.
START..FINAL CHEGKOUT OF DATA R.OCESSiNG SYSTEM.
ESTABL[SHCOMMUNICATIONS SF_-.-DS]F, AND AFETRo BETHEEN
eP (30
T-SHZSM T-SHIOIq
S]L E
COMMAND TAPES. " ]L_, $iI!ART,,PI,_AYBACK TO SF OF, PREPARED LI, REPORT TO A PLANNED GMT LAUNCH TIME AND'START-AND 2o REPO_IF,,,TOA ANNOUNCE AI_)-'NINDON
5_e.-
END STEA-SIC
OF
[JP_UlNCH N|NDOkl. STATUS.TilqE LI, 62,
NN
T,'SHblq
A
1,
PLANNED GIqT LAUNCH TO SF, ANO '_SIF
HH
T.5H
I !
1_
START PLAYBAI;K MAND-_TAPES TQ
OF SFo
PREPREPAREO
CON-.
LL
T-4H45H
42
L.
START PLAYBAGK OF MAND TAPES-TO SFo REPORT TO A START COUNTOOMN. REPORT TO A STATUS
PREPREPARED
COM-
KK
T-4H40H
E
1o
OF
ATLAS/CENTAUR
JJ
T-4H30M
E
,L.
OF
S/C
COUNT-
OOklN.
I[ HH T-Zelt20M T-_H E E |, 1. REPORT TO A STARTOF IU;::!SILEN£E. PROAND
REPORT TO A START OF ATLAS PULSION IGNITER INSTALLATION CONNECTION. REPORT TO A START OF NOSE EXPLOSIVE BOLT INSTALLATZON CONNECTION. REPORT VERIFICAT]ON MAND TAPES TO DSIF OF 5L,
2.
FAIRING AND
GG
T-3H_ON
A
1.
PREPARED 11, 62.
COM-
V-
3
EPD-180,
REVISION
1
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
FF
T-3H40M
E
1o
REPORT DOWN.
TO
A
STATUS
OF
SIC
COUNT-
EE
T-3H30M
E
1.
REPORT TO A PILOT TESTS. REPORT TO PROPULSION CONNECTION° A
START
OF
ATLAS
AUTO-
DD
T-3HIOM
E
1-
COMPLETION OF ATLAS IGNITER INSTALLATION
AND
2.
REPORT TO A ING EXPLOSIVE CONNECTION. REPORT PILOT TO A
COMPLETION OF NOSE BOLT INSTALLATION
FAIRAND
CC
T-2H40M
E
1.
START
OF
CENTAUR
AUTO-
TESTS. TO A ACTIVATION BATTERIES. TO A STATUS OF OF ATLAS AND
2.
REPORT CENTAUR REPORT DOWN.
3.
S/C
COUNT-
BB
T-2H
E
1.
REPORT TO REMOVAL. REPORT TO
A
PREPARATION
FOR
TOWER
AA
T-IHZOM
E
1. 2-
A A
END
OF
RF
SILENCE. ESTABLISHMENT
REPORT TO OF RF LINK REPORT REPORT TO TO
START OF WITH S/C. STATUS REMOVAL OF
3. 4. Z T-IHI3M E 1.
A A
S/C
COUNTDOWN.
OF
TOWER.
REPORT TO A LISHMENT OF
COMPLETION OF ESTABRF LINK WITH S/C. OF SIC TELEMETRY
Y
T-IHI2M
E
1.
START TRANSMISSION TO SF. START PROCESSING VIDE PROCESSED REPORT TO A
X
T-IHI2M
DATA
1.
S/C DATA AND DATA TO SF. OF CENTAUR
PRO-
W
T-IH
1.
START
LOX V-
4
EPD'-180, REVISION 1
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
M
(CONTINUEDI 2.
TANKING. REPORT TO CONDITIONS A REQUIRED S/C ELECTRONICS FOR LAUNCH ESTABLISHED. [OMPLETION OF CENTAUR
V
T-60N
E
1.
REPORT TO A LOX TANKING. REPORT TANKING. REPORT TO A
2o
START
OF
ATLAS
LOX
3° 6.
TO
A
STATUS
OF
SIC
COUNTDOMNo
SEND S/C TRANSMITTER POWER_ FREQUENCY9 AND TEMPERATURE ALSO RECEIVER FREQUENCY AND THRESHOLD MEASUREMENTS TO SP AND FPo REPORT OF S/C TO A GENERAL STATUS. A VERIFICATION
U
T-60M
SP
2o
T
T-35M
E
1°
REPORT TO CHECKED.
ATLAS/CENTAUR
BATTERIES
S
T-35M
SP
1.
REPORT FREQUENCIESt CORRECTIONS. AND
FREQUENCY DRIFT RATES S/C
TO
FP.
R
T-25M
E
1.
REPORT TO A COMPLETION OF NAL PROCESSING, CHECKOUT. SEND INPUT REPORT HELIUM REPORT SAFETY S/C THERMAL PARAMETERS TO A START TANKING. TO A START CHECK. AND POWER TO SP° OF
SIG-
2.
PROGRAM
3°
CENTAUR
LIQUID
6.
OF
FINALRANGE
Q
T-2OM
E
2o
SEND VALUES OF SIC POMER AND FREQUENCY RECEIVER FREQUENCY FPo
TRANSMITTER ALSO TO SP AND
V-
5
EPD-180,
REVISION.
SECTION
V
ITEM
TIME
OF
EV_HT
STATION
EVENT
P
T-17M
E
I.
REPORT TO A RANGE SAFETY REPORT TO POMER ANO POWER. REPORT TO PARAMETERS
COMPLETION CHECK.
OF
FINAL
o
T-ZS_-
E
I.
A TURN_'-OFF TURN-ON OF
CYF SIC EXTERNAL S/C INTERNAL
2.
A
START OF M_NITORING.
SIC
POMER
N
T-ISM
SP
1.
REPORT FREQUENCIESt RECTIONSp AND DRIFT REPORT QUENCY
FREQUENCY RATES TO
CORFP, FRE-
M
T-I$M
Fp _
1.
TO A TRANSMISSION OF INFORMATION TO IPP. A COMPLETION MON|TORING. A TURN-OFF TURN-ON OF OF S/C
L
T--12M
E
I.
REPORT TO PARAMETERS REPORT TO POMER AND POMEfl. REPORT REPORT TOPPING. REPORT CENTAUR REPORT CONTROL REPORT TANKING. REPORT TOPPING, REPORT TO TO
POMER
2.
OF SIC INTERNAL SIC EXTERNAL
K J
T-12M T-IOM
SP E
I. I.
A A
S/C START
POWER OF
SYSTEM CENTAUR
STATUS. LOX
2.
TO A COMPLETION OF AUTOPiLOT TESTS. TO A COMPLETION CHECKS. TO A COMPLETION OP
ATLAS/
3.
SIC
FLIGHT
[
T-SM
E
1o
OF
ATLAS
LOX
2.
TO
A
START
OF
ATLAS
LOX
3. H T-SN FP I,
TO
A
LAUNCH
PLAN, COMPUTATION WITH DIRECT SIMULAT|ON VOF
REPORT TO A START OF INJECTION CONDIIIONS ASCENT POWERED FLIGHT
6
.
°
EPD-IBOI
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
H
(CONTINUED)
PROGRAM TIME (IF FP 1. COMPLETE CONDITIONS
BASED ON REQUIRED)
ESTIMATED (9k X,
LAUNCH Y). INJECTION
G
T-6M
CALCULATION OF IIF REQUIRED). OF
2.
BEGIN COMPUTATION REQUIRED) (94XeY).
PREDICTIONS
(IF
F
T-3M
E
1.
REPORT TO A TURN-OFF OF CENTAUR EXTERNAL POWER AND TURN-ON OF CENTAUR INTERNAL POMERo REPORT 10 A TURN-OFF OF TERNAL POWER AND TURN-ON INTERNAL POWER. REPORT TERNAL REPORT TOPPING. REPORT LIQUID TO A TURN-OFF POWER. TO A COMPLETION OF ATLAS EXOF ATLAS
E
T-2M
E
1.
2.
S/C
EX-
3.
OF
ATLAS
LOX
4.
TO A COMPLETION HELIUM TANKING.
OF
CENTAUR
5.
SEND CRITICAL S/C TEMPERATURE POWER PARAMETER DATA TO SP. REPORT TO A POWER DATA. REPORT REPORT TO TO A A A S/C TEMPERATURE
AND
D
T-2M
SP
1.
AND
C B A
T-IM T-lOS T-17S
E E E
1. 1. 1.
ATLAS START CENTAUR
AND
CENTAUR
ARMED.
OF.ATLAS UPPER
ENGINE. UMBILICAL
REPORT TO REMOVED. LIFTOFF. START IMPACT
E _,PP
1. 1.
REPORT REAL TIME PREDICTION. LIFTOFF
TO
A
LIFTOFF SAFETY
TIME.
RANGE
3
T=O
A
1o
ANNOUNCE
TIME
TO
SF
AND
DSIF V7
EPD-180,
REVISION
1
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
3 6
(CONTINUED) L+30S E 1.
NET. REPORT II. TO A ACQUISITION BY AFETR TEL
2.
REPORT TO A RECEPTION (VHF) FROM AFETR TEL BEGIN AFETR TRANSMISSION OF TEL II TO SF.
OF IT. SIC
S/C
T/M
3.
T/M
FROM
S
L÷2M
FP
I,
COMPLETE BASED ON REQUIRED)
COMPUTATION OF PREDICTIONS ESTIMATED LAUNCH TIME (IF (94 X, Y). OF
2.
REPORT TO A START OF COMPUTATION INJECTION CONDITIONS WITH DIRECT ASCENT POWERED FLIGHT SIMULATION PROGRAM BASED ON ANNOUNCED LAUNCH TIME (94 Xt Y). REPORT CUTOFF TO A ATLAS BOOSTER {BECU). MARK 1. A ATLAS MARK 2. A CENTAUR MARK 3. BOOSTER ENGINE
6
L+
E
I.
7
L+
E
l,
REPORT TO JETTISON. REPORT TO JETTISON. TRANSMIT TO DSIF
ENGINE
8
L+
E
I.
INSULATION
PANEL
9
L+3M
FP
I.
NOMINAL (T-S) PREDICTIONS 51 (IF REQUIRED). OF INJECTION
2.
COMPLETE COMPUTATION CONDITIONS.
3.
BEGIN COMPUTATION OF NOMINAL JECTORY BASED ON ANNOUNCED LAUNCH TIME 194 X, Y). REPORT TO SON. MARK REPORT CUTOFF A SIC 4. NOSE FAIRING
TRA-
10
L÷
E
1.
JETTI-
II
L+
E
I.
TO A ATLAS SUSTAINER (SECO). MARK 5.
ENGINE
V-
8
EPD-[8Ot
REVISION
[
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
12
L÷
E
I.
REPORT TION. REPORT NITION REPORT {VHF) SWITCH MISSION
TO A ATLAS/CENTAUR MARK 7° TO A CENTAUR (MEIG). MARK MAIN 8. OF
SEPARA-
13
L+
E
1.
ENGINE
IG-
14
L+6M9S
E
I.
TO A RECEPTION FROM AFETR 9.I. TO AFETR TO SF. A LOSS qol
S/C
T/M
2.
TIM
FOR
TRANS-
15
L+TM
E
Io
REPORT TO TEL IT. REPORT (VHF) SWITCH TO SF.
OF
SIGNAL
BY
AFEIR
16
L+[OM39S
E
l°
TO A RECEPTION OF FROM AFETR SHIP. TO SHIP T/M FOR
S/C
T/M
2.
TRANSMISSION
17
L÷IIM=I
E
1.
REPORT TO A CENTAUR MAIN ENGINE CUTOFF (MECOI. MARK 9=INJECTION. (TIME OF INJECTION IS VARIABLb. TIMES GIVEN FOR SUBSEQUENT MARK EVENTS ARE BASED ON INJECTION AT L+IIM). REPORT EXTEND REPORT EXTEND REPORT 9. I. TO A SURVEYOR COMMAND SENT. TO A SURVEYOR COMMAND SENT. TO A LOSS OF LANDING GEAR MARK 13. OMNIANTENNAS MARK 14. SIGNAL BY AFETR
18
I÷38S
E
1.
19
I+49S
E
I.
20
I+IM
E
I.
21
I+IM
IPP
I°
BEGIN TRANSMISSION TRACKING DATA TO REPORT TO TRANSMITTER
OF SF.
RAW
AFETR
22
I+IM09S
E
I.
A SURVEYOR ON. MARK
HIGH-PUWER 15. TO S/C TO E. S-BAND
2°
AFETR STATIONS SWITCH T/M FOR TRANSMISSION
V-
9
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
22
(CONTINUED|
3.
REPORT TO A TION BY SHIP. REPORT TRICAL REPORT TION.
S-BAND
SIGNAL
ACQUISI-
23
I_IMISS
E
I.
TO A CENTAUR/SURVEYOR DISCUNNECT. MARK 16. TO MARK A A CENTAUR/SURVEYOR I7. COMPLETION COMPUTATION. OF
ELEC-
24
I+IM20S
E
I.
SEPARA-
25
I÷2M
FP
I.
REPORT TO TRAJECTORY REPORT TO INJECTION REPORT TO I2 HORIZON. REPORT TO HIGH-POWER, REPORT TO CONDITIONS PUTATION. REPORT TO PREDICTIONS TRANSMIT ORBITAL BEGIN DSIF BEGIN
Tn nCtC
NOMINAL
26
I+2M
IPP
I.
A START OF CONDITIONS. A CENTAUR
COMPUTATION
OF
27
I÷5M28S
E
I.
AND
S/C
ON
AFETR
28
I+6M
SP
I.
DSIF 51 LANDING GEAR, SEPARATION STATUS. A COMPLETION AND ORBITAL
OMNIS,
29
I+6M
IPP
I.
OF INJECTION ELEMENTS COM-
2.
A
START OF FOR DSIF
COMPUTATION 51. AND
OF
3.
INJECTION ELEMENTS
TO
CONDITIONS SF. PREDICTIONS
30
I+7M
IPP
I.
TRANSMITTING 5I TO SF. RETRANSMITTING
_!
FOR
3I
I÷7M
COMM
I.
IPP
PREDICTIONS
32
I÷8M
E
I.
REPORT AFETRI2.
TO
A
CENTAUR
ACQUISITION
BY
2.
REPORT TO A SIC BY AFETR I2. SWITCH TO TRANSMISSION AFETR TO
S-BAND
ACQUISITION
3.
12 S/C SF.
T/M
FOR
V-lO
EPD-I80t
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
33
I+9M
IPP
I.
START FROM
TRANSMITTING AFETR 12 TO
RAW SF. ON 51.
TRACKING
DATA
34
I+IOM
FP
I.
REPORT TO PREDICTIONS VISIBILITY
A DECISION AT DSIF BEGINS. OF
USE
OF
AFEIR
35 36
I+12M125 I+12M12S
51 NET
I. I.
REPORT START DSIF 51. REPORT 51. TO
SEARCH
FOR
S/C
BY
37
I+13M30S
NET
I.
A DETECTION
OF
SIC
BY
DSIF
38
I+I5M
NET
I-
REPORT TO WITH S/C.
A DSIF
51
IN
ONE-WAY
LOCK
39
I+ISM
FP
I.
REPORT TO A DETERMINATIDN
STARI 194
OF X,
FIRST YI.
ORBII
40
I+ITM
IPP
I.
REPORT TO A COMPLETION OF TRANSMISSION TO SF OF PREDICTIONS FOR DSIF 51. REPORT TO MARK lB. REPORT TO WITH S/C. BEGIN SF. A CENTAUR RETRO START.
41
I+17M30S
E
l.
42
I+I9M
NET
I.
A DSIF
51
IN
TWO-WAY
LOCK
43
I+IgM
51
I.
TRANSMITTING
TRACKING
DATA
TO
44
I+I9M
IPP
I.
COMPLETE TRACKING REPORT TO TION ORBIT REPORT
TRANSMISSION DATA TO SFA
OF
RAW
AFETR
2.
START OF MULTIPLE COMPUTAIION. PANEL ERECTED.
STA-
45
I+20M
SP
1. 2.
SOLAR
REPORT TO l DECISION TO EXECUTE MAND SEQUENCE 2050 {PRE-SUN SIC ARATION AND BIT RATE SELECTIONI.
COMPREP-
V-II
EPD-180t
REVISION
1
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
46
I÷20M30S
A
I-
DIRECT COMMAND
SP TO CONTROL EXECUTION SEQUENCE 2050.
OF
47
SP
I.
CONTROL BY VOICE DIRECTION DSIF 51 EXECUTION OF COMMAND SEQUENCE 2050. DSIF 51 WILL EXECUTE EACH MINOR SEQUENCE IN 2050 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE TO COMM. EXECUTE (INITIAL COMMAND SEQUENCE IIACCELEROMETER 0040 OFF). (COASI
48
I+21M
5I
I.
49
I÷24M
51
I.
COMMAND SEQUENCE 0041 4400 BPS SELECTION). EXECUTION AND STATUS
50
I÷26M
SP
I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2050, OF S/C RESPONSE. REPORT TO A DECISION TO MAND SEQUENCE 205I (SUN TION). DIRECT SP OF COMMAND [0 CONTROL SEQUENCE
2.
EXECUTE ACQUISI-
COM-
5I
I÷26M30S
A
I.
EXECUTION 205I.
52
SP
I.
CONTROL BY VOICE DIRECTION DSIF 51 EXECUTION OF COMMAND SEQUENCE 2051. DSIF 5I WILL EXECUTE EACH MINOR SEQUENCE IN 2051 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND SEQUENCE ACQUISITION MODE). 0042 (SUN
53
I÷27M
5I
I.
54
I÷34M
IPP
1.
REPORT COMPLETION OF MULTIPLE TION ORBIT COMPUTATION. TRANSMIT BRIEF COMING INJECTION CONDITIONS AFETR DATA. AND
STA-
2. 55 l+40M FP [.
TO
SF.
A ON STATUS OF DSIF TRACKING
IN-
V-12
EPD-I80t
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
56
I+40M
SP
I. 2.
REPORT REPORT PROGRAM EXECUTE MANEUVER
TO
A SUN
ACQUIRED. OF POwER,THERMAL
TO A START UPDATE. COMMAND COMM.4
57
l+40M
51
I.
SEQUENCE 0043 SELECTION). SEQUENCE 0044
{POST
58
I+42M
51
I.
EXECUTE COMMAND 2 SELECTION|.
{COMM.
59
I+42M
IPP
I.
REPORT TO A START OF ELEMENTS COMPUTATION. EXECUTE COMMAND 3 SELECTION).
CENTAUR
ORBITAL
60
I+44M
51
I.
SEQUENCE
0045
ICOMM.
61
I÷45M
SP
I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2051, OF SIC RESPONSE.
EXECUTION AND STATUS
2.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2052 (COAST PHASE PREPARATION-IIOOBPS}. DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE Z052.
COM-
62
I+45M30S
A
I.
OF
63
SP
I°
CONTROL BY VOICE DIRECTION DSIF 51 EXECUTION OF COMMAND SEQUENCE 2052. DSIF 51 WILL EXECUTE EACH MINOR SEQUENCE IN 2052 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE TO 1100 COMMAND SEQUENCE BPS CHANGE)° 0046 (4400
64
I+46M
5I
I.
65
I+46M
IPP
I.
REPORT COMPLETION OF ELEMENTS COMPUTATION. TRANSMIT SF. EXECUTE CENTAUR
CENTAUR
ORBITAL
2.
ORBITAL
ELEMENTS
TO
66
I÷48M
51
I.
COMMAND
SEQUENCE
0047
ILOW V-13
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
66 67
{CONTINUED) I+49M SP I.
POWER/COAST
COMM.). EXECUTION AND STATUS
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2052, OF S/C RESPONSE. REPORT TO A COMPLETION BIT DETERMINATION. BEGIN TRAJECTORY REVISED OF
68
I÷IHJOM
FP
I.
FIRST
OR-
2. 69 I+IH35M FP I.
COMPUTATION PREDICTIONS
(94X). TO
TRANSMIT DSIF 5I. COMPLETE REPORT PROGRAM
70 7I
I+IH40M I+IH40M
FP SP
l. I.
TRAJECTORY TO A START UPDATE. OF
COMPUTATION. POWER, THERMAL
72
I÷IH45M
SP
1.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2055 (COAST PHASE BIT RATE REDUCTION - 550 FROM 4400/II00 BPS). DIRECT SP TO CONTROL EXECUTION COMMAND SEQUENCE 2055. CONTROL EXECUTION EXECUTE BY OF
73
I÷IH45MJOS
A
1.
74
SP
l.
VOICE DIRECTION DSIF 51 OF COMMAND SEQUENCE 2055. SEQUENCE 2055. EXECUTION AND STATUS
75 76
I+lH46M I+lH47M
51 SP
I. I.
COMMAND
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2055, OF S/C RESPONSE.
77
I÷2H
_"rr
1.
REPORT TO A START nc ccrn_n noQIT DETERMINATION (INITIAL CONDITION EVALUATION; {94X, Y). REPORT ORBIT BEGIN TO A COMPLETION DETERMINATION. TRAJECTORY OF SECOND
78
I÷2HJOM
FP
I.
2.
COMPUTATION
(94X). V-14
"
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STAIION
EVENT
79
I+2H40M
FP
I. 2.
COMPLETE GENERATE TAPE FOR REPORT PROGRAM TIONS TO
TRAJECTORY
COMPUTATION. SAVE
TELECOMMUNICATIONS SP. A START OF POWER,
80
I+2H40M
SP
I.
THERMAL
UPDATE, PROGRAM A
AND RUN.
TELECOMMUNICA-
8I
I+3H
FP
I.
REPORT TO TERMINATION ORBIT)
START OF THIRD ORBIT (PRELIMINARY MIDCOURSE Y). OF TELECOMMUNICA-
DE-
(94X,
82
I+3HI5M
SP
I.
BRIEF TIONS REPORT PROGRAM
A ON RESULTS PROGRAM RUN. TO A START
83
I+3H4OM
SP
I.
OF
POWER,
THERMAL
UPDATE. OF THIRD OR-
84
I÷4H
FP
I.
REPORT TO A COMPLETION BIT DETERMINATION. BEGIN IRANSMIT II, 42. TRAJECTORY A START OF COMPUTATION OF TRAJECTORY PREDICTIONS
2. 85 I÷4HO5M FP I.
COMPUTATION IO DSIF
(94X). 5I,
86
I÷4HIOM
FP
I. 2.
COMPLETE REPORT TO MIDCOURSE REPORT PROGRAM REPORT LIMINARY
COMPUTAIION. PRELIMINARY (94Xt Y). POWER, THERMAL
87
I÷4H40M
SP
I.
TO A START UPDATE. TO
88
I÷4H55M
FP
I.
A COMPLETION OF PREMIDCOURSE COMPUTATION. A START OF COMPUTATION. M/C POWER, THERMAL
89
I÷4H55M
SP
I.
REPORT TO PREDICTION GIVE DATA
90
I+5HIOM
FP
I.
PRELIMINARY TO A SP. ON RESULTS
CORRECTION
2.
BRIEF
OF
PRELIMINARY V-15
M/C
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
90 91
(CONTINUED) I÷SH20M FP 1.
STUDY. REPORT TO A START OF FOURTH ORBIT DETERMINATION (DATA CONSISTENCY ORBIT) (94X, Y). REPORT PROGRAM TO A START UPDATE. OF POWER, THERMAL
92
I+SH40M
SP
I.
93
I+5HSOM
SP
I.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2056 (HIGH-POWER ENGINEERING INTERROGATION - 4400 BPS FROM 550 BPS). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2056. OF
94
I÷SHSOM3OS
A
I.
95
SP
I.
CONTROL BY VOICE DIRECTION DSIF 51 EXECUTION OF COMMAND SEQUENCE 2056. DSIF 51 WILL EXECUTE EACH MINOR SEQUENCE IN 2056 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE MITTER EXECUTE TO COMM. COMMAND SEQUENCE B FILAMENT). COMMAND 21. SEQUENCE 0141 (TRANS-
96
I+SHSIM
51
I.
97
I+SHSIM45S
51
I.
0142
(COAST
I+SH53M
51
I.
EXECUTE COMMAND SEQUENCE 0143 POWERI550 TO 4400 BPS CHANGE). EXECUTE COMMAND 4 SELECTION|. EXECUTE COMMAND I SELECTION). SEQUENCE 0144
(HIGH-
98
I+SH56M
51
1.
ICOMM.
99
I+SH58M
51
I.
SEQUENCE
0145
(COMM.
100
I÷6H
SP
I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2056, OF S/C RESPONSE.
EXECUTION AND STATUS
2.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2150 (STAR VERIFI-
COMV-16
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
TO0
(CONTINUED)
CATION/ACQUISITION-TRANSPONDER TWO ROTATIONS). 3. BRIEF A ON PREDICTION DIRECT COMMAND RESULTS OF COMPUTATION. POWER,
OFF,
THERMAL
IOI
I÷6HOOM3OS
A
I.
SP TO CONTROL EXECUTION SEQUENCE 2150.
OF
I02
SP
I.
CONTROL BY VOICE DIRECTION DSIF 51 EXECUTION OF COMMAND SEQUENCE 2150. DSIF 51 WILL EXECUTE EACH MINOR SEQUENCE IN 2150 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISIED. EXECUTE PONDER REPORT EXECUTE MANEUVER EXECUTE (ROLL). COMMAND OFF/DSIF TO A DSIF SEQUENCE 0146 REACQUISITION). REACQUISITION. 0147 {STAR {TRANS-
103
I+6HOIM
5I
I.
104 I05
I+6HO3M I*6HO3M
SP 5I
I. I.
COMMAND SEQUENCE PREPARATION). COMMAND SEQUENCE
I06
I÷6HO4M
51
I.
0240
107
I÷6HI6M
51
I.
EXECUTE COMMAND LECT OMNI A).
SEQUENCE
0241
(SE-
108
I÷6H28M
51
1.
EXECUTE COMMAND SEQUENCE (SUN AND STAR MODE). REPORT PROGRAM REPORT EXECUTE (CRUISE EXECUTE PONDER REPORT TO A START UPDATE. TO A CANOPUS COMMAND MODE). COMMAND ON/DSIF TO A DSIF OF
0243.
109
I÷6HAOM
SP
I.
POWER,
THERMAL
llO 111
I÷6H42M I÷AHAZM
SP 51
I. I.
ACQUIRED. 0244
SEQUENCE
I12
I÷6H43M
51
I.
SEQUENCE 0245 REACQUISITION). REACQUISITIDN.
(TRANS-
I13
I÷6H45M
SP
I.
V-17
EPD-I80,
REVISION I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
lI3
(CONTINUED)
2.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2150, OF S/C RESPONSE.
EXECUTION AND STATUS
3.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2053 {COAST PHASE ARATION - 137.5 BPSI. DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2053.
COMPREP-
114
I+6H45M30S
A
I.
OF
I15
SP
I.
CONTROL BY VOICE DIRECTION DSIF 51 EXECUTION OF COMMAND SEQUENCE 2053. DSIF 51 WILL EXECUTE EACH MINOR SEQUENCE IN 2053 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE RATE TO COMMAND SEQUENCE 0246 137.5 BPS CHANGE). 0047 (HIGH
116
I÷6H#6M
5I
I.
117
I÷6H4BM
51
I.
EXECUTE COMMAND SEQUENCE POWER/COAST COMM.).
(LOW
118
I+6H49M
SP
I.
REPORT TO A COMPLETION OF EXECUTION OF COMMAND SEQUENCE 2053 AND STATUS OF SIC RESPONSE. REPORT PROGRAM REPORT ORBIT TO A START UPDATE. OF POWER, THERMAL
I19
I+7H40M
SP
I.
120
I+8H20M
FP
I.
TO A COMPLETION DETERMINATION.
OF
FOURTH
2.
REPORT TO A START OF u,_ COMPUT_TIn_, (a_v_
I'I#_ " ul, _ I._
INTERMEDIATE v_.
, •
121 122
I+8H30M I+8H40M
FP SP
I. I.
BRIEF REPORT PROGRAM
A ON
RESULTS
OF OF
FOURTH POWER,
ORBIT. THERMAL
TO A START UPDATE.
123
I÷9HO5M
FP
I.
REPORT TO A COMPLETIDN ATE M/C COMPUTATIONS.
OF
INTERMEDI-
V-18
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
I24
I÷9HZOM
FP
I.
GIVE DATA
INTERMEDIATE TO SP. RESULTS
M/C
CORRECTION
2.
BRIEF A ON M/C STUDY. BEGIN
OF
INTERMEDIATE
3. 125 126 I+gH30M I+9H40M FP SP I. I.
TRAJECTORY TRAJECTORY TO A START UPDATE. ENDS.
COMPUTATION COMPUTATION. OF POWER,
(94X).
COMPLETE REPORT PROGRAM
THERMAL
127 128
I+IOH]gM I+IOH40M
51 SP
I. I.
VISIBILITY REPORT PROGRAM
TO A START UPDATE. BEGINS.
OF
POWER,
THERMAL
129 130
I+IOH42M I+lOH42M
11 NET
l. 1.
VISIBILITY
REPORT TO A START BY DSIF II. REPORT If. TO
OF
SEARCH
FOR
S/C
13I
I+IOH44M
NET
I.
A DETECTION
OF
S/C
BY
DSIF
132
I+IOH46M
NET
I.
REPORT TO A DSIF WITH S/C. REPORT TO WITH S/C. A DSIF
II
IN
ONE-WAY
LOCK
133
I÷IOH52M
NET
I.
II
IN
TWO-WAY
LOCK
134
I+IOH52M
II
I.
BEGIN TRANSMITTING TO SF. REPORT TO A DETERMINATION
TRACKING
DATA
135
I÷IIH
FP
I.
START OF FIFTH (94X, Y}.
ORBIT
136
I÷I2HZgM
SP
I.
REPORT TO A DECSION TO EXECUTE COMMAND SEQUENCE 2057 (HIGH-POWER ENGINEERING INTERROGATION-4400 BPS FROM 137°5, 17.2). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2057. OF
137
I+I2H29M30S
A
I.
V-I9
EPD-IBOt
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
I3B
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2057. DSIF II WILL EXECUTE EACH MINOR SEQUENCE IN 2057 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE MITTER COMMAND SEQUENCE B FILAMENT|. OF 0141 (TRANS-
139
I÷I2H3OM
11
1.
I40
I+I2H30M
FP
I.
REPORT TO A COMPLETION BIT DETERMINATION. REPORT EUVER TO A START COMPUTATION COMMAND 21.
FIFTH
OR-
2.
OF FINAL MIC (94X, Y). SEQUENCE 0142
MAN-
141
I+I2H30M45S
II
I.
EXECUTE TO COMM.
(COASI
142
I+12H32M
11
I.
EXECUTE COMMAND POWER/LOW RATE EXECUTE COMMAND 4 SELECTION). EXECUTE COMMAND I SELECTION).
SEQUENCE 0247 TO 4400 BPS). SEQUENCE 0144
(HIGH
143
I*I2H35M
II
I.
(COMM.
144
I+I2H37M
II
I.
SEQUENCE
0145
(COMM.
145
I+I2H39M
SP
I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2057, OF S/C RESPONSE. REPORT COURSE
UtblN
EXECUTION AND STATUS
146
I+I2H50M
FP
I.
TO A COMPLETION OF FINAL MANEUVER COMPUTATION.
IHAJ_GIUK¥ LUMVUIAIIUN
MID-
L.
UAb_U
ON NOMINAL 147 I+13H FP I. COMPLETE BASED ON REPORT PROGRAM MIDCOURSE
MIDCOURSE
MANEUVER
(94X).
TRAJECTORY COMPUTATION NOMINAL MIDCOURSE MANEUVER. OF POWER, THERMAL
148
I÷I3H
SP
1.
TO A START UPDATE. MANEUVER
149
I÷I3HIOM
FP
1.
COMMAND
DEV-Z0
EPD-I8O,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
149 I50
(CONTINUED! I÷I3HZSM SP I.
CISION MIDCOURSE II.
I. MANEUVER COMMAND DECISION
151
I+I3H29M
SP
I.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2057 (HIGH-POWER GINEERING INTERROGATION - 4400 FROM I37.5_ 17.21. DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2057.
COMENBPS
152
I+I3H29M30S
A
I.
OF
153
SP
I.
CONTROL BY VOICE DIRECTION DSIF 1I EXECUTION OF COMMAND SEQUENCE 2057. DSIF IX WILL EXECUTE EACH MINOR SEQUENCE IN 2057 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE MITTER COMMAND SEQUENCE B FILAMENT). SEQUENCE OI4I (TRANS-
I54
I÷I3H30M
IX
I.
155
I+I3H30M45S
11
I.
EXECUTE COMMAND TO COMM. 2). EXECUTE COMMAND POWER/LOW RATE EXECUTE COMMAND 4 SELECTIONI.
0142
(COAST
156
I+13H32M
IX
I.
SEQUENCE 0247 TO 4400 BPS). SEQUENCE 0144
{HIGH
157
I÷13H35M
II
I.
(COMM.
I58
I÷13H35M
SP
1.
REPORT TO A COMPLETION OF MIDCOURSE MANEUVER COMMAND MESSAGE PREPARATION. START EUVER VALIDATION OF MIDCOURSE COMMAND MESSAGE. SEQUENCE 0145 MAN-
I59
I+13H35M
SPtFP
1.
160
I÷13H37M
IX
1.
EXECUTE COMMAND I SELECTION).
(COMM.
I6X
I÷13H39M
SP
I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2057, OF SIC RESPONSE.
EXECUTION AND STATUS
V-21
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
161
(CONTINUED)
2.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2151 (EARLY GYRO CHECK). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2151.
COMSPEED
162
I÷13H39M305
A
I.
OF
163
SP
I.
CONTROL BY VOICE DIRECTION OSIF 1[ EXECUTION OF COMMAND SEQUENCE 2151. DSIF II WILL EXECUTE EACH MINOR SEQUENCE IN 2151 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND GINEERING COMM. SEND MAND SEQUENCE OFF). 0340 (EN-
164
I+I3H40M
ll
Io
165
I+I3H40M
SP
1.
TO A MIDCOURSE REQUEST.
MANEUVER
COM-
166
I+I3H41M
ll
I.
EXECUTE TO GYRO EXECUTE GYRO). COMMAND MANEUVER EXECUTE GYRO). EXECUTE GYRO).
COMMAND SEQUENCE PROCESSING). COMMAND SEQUENCE
0341
(SCO
167
I+13H42M
ll
I.
0342
(NEXT
168
I+13H42M
A
1.
DIRECTIVE COMMAND COMMAND
- SEND MESSAGE SEQUENCE
MIDCOURSE TO DSIF 0342
11.
169
I+I3H43M
ll
1.
(NEXT
170
I+13H44M
ll
I.
COMMAND
SEQUENCE
0342
(NEXT
171
I÷13H45M
ll
1.
EXECUTE COMMAND PROCESSING OFF).
SEQUENCE
0J43
(GYRO
2.
COMMAND VERIFICATION COURSE MANEUVER COMMAND VERIFICATION.
PLAYBACK MIDTAPE FOR
172
I+I3H46M
SP
1.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2151, OF S/C RESPONSE.
EXECUTION AND STATUS
V-22
EPD-180,
REVISION
1
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
172
(CONTINUED)
2.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2152 (POST GYRD CHECK COAST PHASE PREPARATION-|37.5 BPS). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2152o OF
173
I÷13H46M30S
A
I.
174
SP
I°
CONTROL BY VOICE DIRECTION DSIF 11 EXECUTION OF COMMAND SEQUENCE 2152. DSIF IX WILL EXECUTE EACH MINOR SEQUENCE IN 2152 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND BPS SELECTION). SEQUENCE 0344 {137.5
175
I+I3H47M
II
I.
176
I÷I3H48M
II
I.
EXECUTE COMMAND SEQUENCE POWER/COAST COMM°). REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2152, OF SIC RESPONSE. REPORT EUVER REPORT DICTION
0345
(LO_
177
I+I3H49M
SP
I.
EXECUTION AND STATUS
178
I÷I4H
SP
I.
TO A COMPLETION OF MIC MANCOMMAND TAPE VERIFICATION. TO A START OF MIDCOURSE PREORBIT DETERMINATION (94X). BEGINS. START OF SEARCH FUR SIC
179
I÷I4H
FP
1.
180 181
I+I4HITM I+I4HI7M
62 NET
1. I.
VISIBILITY REPORT TO A BY DSIF 42. REPORT 42. TO
182
I÷I4HIBM
NET
1.
A DETECTION
OF
S/C
BY
DSIF
|83
I+I4H2OM
NET
I.
REPORT TO WITH SIC.
A DSIF
42
IN
ONE-WAY
LOCK
186
I+I4H26M
SP
1.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2057 (HIGH-POWER ENGINEERING INTERROGATION-4400 BPS FROM 137.5_ 17.2I. V-23
EPD-I80,
REVISION I
SECTION V
ITEM
TIME
OF EVENT
STATION
EVENT
185
I+I4H26M30S
A
l.
DIRECT COMMAND
SP TO CONTROL EXECUTION SEQUENCE 2057.
OF
I86
SP
I.
CONIROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2057. DSIF II WILL EXECUTE EACH MINOR SEQUENCE IN 2057 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE SMITTER EXECUTE TO COMM. COMMAND SEQUENCE B FILAMENT). COMMAND 2|. SEQUENCE OI4I (TRAN-
187
I÷I4H27M
II
1.
188
I+I4H27M45S
II
I.
0142
(COAST
189
I÷I4H29M
II
I.
EXECUTE COMMAND POWER/LOW RATE REPORT TO PREDICTION
SEQUENCE 0247 TO 4400 BPS).
(HIGH
190
I+I4H30M
FP
I.
A COMPLETION OF MIDCOURSE ORBIT DETERMINATION. SEQUENCE 0144 (COMM.
191
I÷I4H32M
II
I.
EXECUTE COMMAND 4 SELECTION). EXECUTE COMMAND I SELECTION).
192
I+I4H34M
II
I.
SEQUENCE
0145
(COMM.
193
I+I4H36M
SP
I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2057, OF S/C RESPONSE.
EXECUTION AND STATUS
2.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2154 (LATE GYRO SPEED CHECK/4400 BPS RETURN). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2154. OF
194
I+I4H36M30S
A
1.
195
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2154o DSIF II WILL EXECUTE EACH MINOR COMMAND SEQUENCE IN 2154 ON DIRECTION OF SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. V-24
EPD-180t
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
196
I+I4H3?M
II
I.
EXECUTE TO GYRO EXECUTE GYRO). EXECUTE GYRO). EXECUTE GYRO).
COMMAND SEQUENCE PROCESSING). COMMAND SEQUENCE
0341
(SCO
197
I÷I4H38M
ll
I.
0342
(NEXT
198
I+I4H39M
II
I.
COMMAND
SEQUENCE
0342
(NEXT
199
I+I4H40M
ll
I.
COMMAND
SEQUENCE
0342
(NEXT
200
I+I4H40M
FP
1.
TRANSMIT PREDICTIONS BASED INAL MIDCOURSE MANEUVER TO 42t II. EXECUTE COMMAND SEQUENCE PROCESSING TO 33 KC SCO). REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2154, OF S/C RESPONSE.
ON NOMDSIF 51,
201
I÷I4H41M
II
I.
0346
(GYRO
202
I+I4H42M
SP
I.
EXECUTION AND STATUS
2.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2155 (MIDCOURSE CORRECTION PREPARATION). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2155. OF
203
I+I4H42M30S
A
I.
204
SP
I.
CONIROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2155. DSlF II WILL EXECUTE EACH MINOR COMMAND SEQUENCE IN 2155 ON DIRECTION
_DnM S D _ MNM|_AI TIM_ _nD N_T_ _y_
ECUTION LISTED. 205 I+I4H43M II 1.
OF
MINOR
SEQUENCES
ARE
EXECUTE COMMAND SEQUENCE M/C THRUST PREPARATION|. EXECUTE COMMAND SEQUENCE M/C ROLL PARAMETERS). EXECUTE COMMAND SEQUENCE
0347
(PRE-
206
I÷I4H44M
II
I.
0440
(PRE-
207
I+I4H45M
II
I.
0441
(SUN V-25
EPD-18O,
REVISION
!
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
207 208
(CONTINUED) I+I4H46M30S SP 1.
AND
ROLL). TO A COMPLETION OF ROLL MAN-
REPORT EUVER. EXECUTE MIC YAW
209
I+I4H47M505
II
l.
COMMAND (PITCH)
SEQUENCE 0442 PARAMETERS). SEQUENCE 0443
(PRE-
210
I+I4H48M50S
II
I.
EXECUTE COMMAND (YAW(PITCH)). REPORT TO MANEUVER. EXECUTE SET IV EXECUTE (THRUST EXECUTE (STRAIN ETERS).
(0444)
211
I+I4H54MSOS
SP
I.
A COMPLETION
OF
YAW
(PITCH)
212
I+I4H55MSOS
II
I.
COMMAND LATCH).
SEQUENCE
0445
(RESET
213
I+I4H56MSOS
II
I.
COMMAND SEQUENCE PHASE POWER). COMMAND SEQUENCE GAUGES/M/C THRUST
0446
214
I+14H57MSOS
II
I.
0447 PARAM-
215
I+I4H58MSOS
SP
1.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2155, OF S/C RESPONSE.
EXECUTION AND STAIUS
2.
REPORT TO A DECISION TO EXECUIE CUMMAND SEQUENCE 2156 (MIDCOURSE THRUST EXECUTION). DIRECT COMMAND _u,,,_uL EXECUTION SP TO CONTROL EXECUTION SEQUENCE 2156. BY OF
216
I+I4H59M30S
A
I.
217
_" Or
VOI _r_cDIRECT ""''•u, DSIF 11 OF COMMAND SEQUENCE 2156. SEQUENCE 2156. DOP-
ZI8 219
I+ISH I+ISH
11 FP
10 I.
EXECUTE
COMMAND
COMPARE PREDICTED AND OBSERVED PLER SHIFTS IN REAL TIME DURING MIDCOURSE EXECUTION. REPORT TO A COMPLETION OF
220
I÷I5HOIM
SP
I.
EXECUIION V-26
EPD-180,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
220
(CONTINUED)
OF COMMAND SEQUENCE OF S/C RESPONSE. 2.
2156,
AND
STATUS
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2157 (POST-M/C SPACECRAFT RETURN TO COAST). DIRECT SP TO CONTROL EXECUTION COMMAND SEQUENCE 2157. OF
221
I+I5HOIM30S
A
1.
222
SP
1o
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2157. DSIF II WILL EXECUTE EACH MINOR SEQUENCE IN 2157 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF 11 EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND SEQUENCE 0540. {POST-
223 224
I*ISHO2M I*ISHO3M
II II
I. 1.
EXECUTE COMMAND M/C YAW (PITCH) EXECUTE COMMAND (YAW (PITCH)). REPORT (PITCH)
SEQUENCE 0541 PARAMETERS). SEQUENCE 0643
225
I÷I5HO4M
II
l.
(0444)
226
I÷I5HIOM
SP
1-
TO A COMPLETION MANEUVER.
OF
YAW
227
I+ISHIIM
I1
1.
EXECUTE COMMAND SEQUENCE 0542 (POSTM/C ROLL PARAMETERS/VERNIER PURGE TERMINATION). EXECUTE COMMAND AND ROLL). SEQUENCE 0441 (SUN
228
I+I5HI2M
II
1.
229
I+ISHI3M30S
SP
I.
REPORT TO A COMPLETION MANEUVER. EXECUTE COMMAND AND STAR MODE).
OF
ROLL
230
I*ISHI3M30S
II
1.
SEQUENCE
0243
(SUN
231
I+ISHI5M
II
1.
EXECUTE COMMAND SEQUENCE 0543 MANEUVER COMM. 2 SELECTION). EXECUTE COMMAND SEQUENCE 0144
(POST-
232
I+ISHI7M
II
1.
{COMM. V-27
EPD-I80,
REVISION
1
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
232 233
(CONTINUED) I÷ISHI9M SP I.
4
SELECTION). EXECUTION AND STATUS
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2157, OF S/C RESPONSE.
2.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2054. (COAST PHASE PREPARATION-17.2 BPS). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2054. OF
234
I+ISHI9M30S
A
1.
235
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2054. DSIF II WILL EXECUTE MINOR SEQUENCES IN 2054 ON DIRECTION OF SP. NOMINAL TIMES FOR DSIF II EXECUTIUN OF MINOR SEQUENCES ARE LISTED. EXECUTE 1100 [0 COMMAND SEQUENCE 17.2 BPS CHANGE). 0544 (4400/
236
I+ISH20M
11
1.
237
I÷ISHZ2M
11
I.
EXECUTE COMMAND SEQUENCE POWER/COAST COMM.|.
0047
(LOW
238
I+ISH23M
SP
I.
REPORT TO A COMPLETION OF EXECUTION OF COMMAND SEQUENCE 2054 AND STATUS OF SIC RESPONSE. BRIEF SFOD ON INITIAL MIDCOURSE MANEUVER. REPORT PROGRAM TO A START UPDATE. OF EVALUATION OF
239
I+ISH30M
FP
I.
240
I÷ISH30M
SP
I.
POWER,
THERMAL
241
I+I6H
NET
I.
REPORT TO A START FER PROCEDURE. REPORT TO A DSIF AND ONE-WAY LOCK REPORT TO WITH SIC. A DSIF
OF
STATION
TRANS-
242
I÷I6HSM
NET
I.
II TRANSMITTER WITH S/C. 42 IN TWO-WAY
OFF
243
I+I6H6M
NET
I.
LOCK
V-28
EPD-180t
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
244
I÷I6H6M
42
I.
BEGIN SF. REPORT PROGRAM
TRANSMITTING
TRACKING
DATA
TO
245
I+I6H30M
SP
I.
TO A START UPDATE.
OF
POWER,
THERMAL
246
I+ITH
NET
I.
REPORT TO A START FER PROCEDURE. REPORT TO A DSIF AND ONE-WAY LOCK REPORT TO WITH S/C. BEGIN SF. A DSIF
OF
STATION
TRANS-
247
I÷I7HO5M
NET
1.
42 TRANSMITTER WIIH S/C. 11 IN TWO-WAY
OFF
248
I+ITHO6M
NET
X.
LOCK
249
I+ITHO6M
II
I.
TRANSMITTING
TRACKING
DATA
TO
250
I+17H30M
SP
I.
REPORT TO A START OF POWER PROGRAM UPDATE, AND POWER PREDICTION COMPUTATION.
THERMAL THERMAL
2.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2250 (HIGH POWER FORE STAR VERIFICATION). DIRECT COMMAND CONTROL EXECUTION DSIF II IN 2250 NOMINAL OF MINOR EXECUTE MITTER SP TO CONTROL EXECUTION SEQUENCE 2250. BY
COM_E-
25I
I+I7H3OM30S
A
I.
OF
252
SP
I.
VOICE DIRECTION DSIF 11 OF COMMAND SEQUENCE 2250. WILL EXECUTE MINOR SEQUENCES ON DIRECTION FROM SP. TIMES FOR DSIF 11 EXECUTIUN SEQUENCES ARE LISTED. COMMAND SEQUENCE B FILAMENT). SEQUENCE 014I (TRANS-
253
I÷I7H3IM
11
I.
254
I÷17H3IM45S
IX
I.
EXECUTE COMMAND TO COMM. I). EXECUTE COMMAND POWER/LOW RATE
0545
{COAST
255
I÷17H33M
IX
I.
SEQUENCE 0247 TO 4400 BPS).
(HIGH
V-2g
EPD-IBOt
REVISION
1
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
256
I+X7H36M
SP
1.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2250, OF SIC RESPONSE.
EXECUTIUN AND STATUS
2°
REPORT TO A DECISION TO EXECUTE CONHAND SEQUENCE 2150 (STAR VERIFICATION/ACQUISITION - TRANSPONDER OFF( TNO ROTATIONS|. DIRECT SP TO CONTROL EXECUTION COMMAND SEQUENCE 2150. OF
257
I÷X7H36M30S
A
1°
258
SP
1o
CONTROL BY VOICE DIRECTION DSIF 11 EXECUTION OF COMMAND SEQUENCE 2150. DSIF II gILL EXECUTE EACH MINOR SEQUENCE IN 2150 ON DIRECTION FROM SP° NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED° EXECUTE COMMAND SEQUENCE 0146 |TRANSPONDER OFF/DSIF REACQUISETION). REPORT TO A DSIF REACQUISITION. 0167 (STAR
259
I_X7H35M
11
1.
260 261
I÷ITH37M I÷lTH37M
SP 1!
1. l.
EXECUTE COMMAND SEQUENCE MANEUVER PREPARATION). EXECUTE (ROLL). EXECUTE (SELECT COMMAND SEQUENCE
262
I÷XTH38M
11
1.
0260
263
I+X7HSOM
11
1.
COMMAND OMNI AI.
SEQUENCE
0261
266
I+XBHO2M
11
l.
EXECUTE COMMAND AND STAR MODE). REPORT EXECUTE (CRUISE TO
SEQUENCE
0263
(SUN
265 266
I_IBHI6M I÷18HI6M
SP II
1. 1°
A CANOPUS
ACQUIRED. 0266
COMMAND MODE).
SEQUENCE
267
I+IBHI7M
II
l°
EXECUTE COMMAND SEQUENCE 0265 (TRANSPONDER ON/DSIF REACQUISITION)° V-30
).
EPD-180t
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
268
I÷18H19M
SP
I. 2.
REPORT
TO
A DSIF
REACQUISITION. EXECUTION AND STATUS
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2150, OF SIC RESPONSE.
3.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2054 (COAST PHASE PREPARATION-IT.2 BPS). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2054.
COM-
269
I+I8H19M30S
A
I.
OF
270
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2054. DSIF II WILL EXECUTE EACH MINOR SEQUENCE IN 2054 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE 1100 TO COMMAND SEQUENCE I7.2 BPS). 0544 (44001
27I
I÷I8H20M
I1
I.
272
I÷IBH22M
II
I.
EXECUTE COMMAND SEQUENCE POWER/COAST COMM.). REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2054, OF S/C RESPONSE. REPORT TO A START FER PROCEDURE. REPORT
aLm_ rl_
0047
(LOW
273
I÷I8H23M
SP
I.
EXECUTION AND STATUS
274
I÷I8H25M
NET
I.
OF
STATION
IRANS-
275
I÷IBH30M
NET
I.
TO A DSIF
T_A_VT&Ir
II
CT_n_
TRANSMITTER
OFF
276
I÷I8H30M
SP
I.
REPORT PROGRAM
TO A START UPDATE. A DSIF
OF
POWER,
THERMAL
277
I÷I8H31M
NET
I.
REPORT TO WITH S/C.
42
IN
TWO-WAY
LOCK
278
I÷I8H3IM
42
I.
BEGIN TRANSMITTING TO SF.
TRACKING
DATA
V-3I
EPD-I80t
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
279 280
I+I8H49M I+19H
11 SP
1. I.
VISIBILITY BRIEF A ON PREDICTION REPORT PROGRAM REPORT PROGRAM REPORT PROGRAM REPORT MIDCOURSE
ENDS. RESULTS OF COMPUTATION. OF POWER, THERMAL
281
I+I9H30M
SP
1o
TO A START UPDATE. TO A START UPDATE. TO A START UPDATE. TO A START
POWER,
THERMAL
282
I+20H3OM
SP
1.
OF
POWER,
THERMAL
283
I+21H3OM
SP
1.
OF
POWER,
THERMAL
284
I+22H
FP
1.
OF
FIRST
POST(94X). THERMAL
ORBIT TO A START UPDATE. BEGINS. TO 51. TO A A START
DETERMINATION OF POWERt
285
I+22H3OM
SP
1-
REPORT PROGRAM VISIBILITY REPORT BY DSIF
286 287
I÷23H23M I+23H23M
51 NET
1. 1-
OF
SEARCH
FUR
S/C
288
I+23H24M
NET
I.
REPORT 51.
DETECTION
OF
S/C
BY
DSIF
289
I+23H26M
NET
1-
REPORT TO NITH S/C. REPORT PROGRAM TO
A
DSIF
51
IN
ONE-NAY
LOCK
290
I+23H30M
SP
1o
A
START
OF
POWERt
THERMAL
UPDATE. TO A START UPDATE. TO A START OF POHERI THERMAL
291
I+24H30M
SP
1-
REPORT PROGRAM REPORT FER
292
I+24H4OM
NET
1.
OF
STATION
TRANS-
PROCEDURE. DSIF LOCK DSIF 62 TRANSMITTER NIIH S/C. 51 IN TWO-HAY OFF
293
I+26H65M
NET
1o
REPORT TO A AND ONE-WAY REPORT TO WITH S/C. A
294
I+24H46M
NET
1.
LOCK
V-32
EPD-[80,
REVISION
1
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
295
I+24H46M
51
1-
BEGIN TRANSMITTING TO SF.
TRACKING
DATA
296
I÷25H
FP
I.
REPORT TO A COMPLETION OF FIRST POSTMIDCOURSE ORBIT DETERMINATION. BEGIN TRAJECTORY COMPUTATION TO DSIF {94X|. 51,
2. 297 I÷25H05M FP I-
TRANSMIT II, 42. COMPLETE GENERATE TAPE FOR BRIEF BIT.
PREDICTIONS
298
I+25HIOM
FP
I. 2.
TRAJECTORY
COMPUTATION. SAVE
TELECOMMUNICATIONS SP. FIRST POSTMIDCOURSE
299
I+25HISM
FP
I.
A ON
OR-
300
I÷25H3OM
SP
I.
REPORT TO A START OF POWER, THERMAL PROGRAM UPDATE, AND TELECOMMUNICATIONS PROGRAM RUN. REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2251. {LOW-POWER ENGINEERING INTERROGATION). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 225I. UF
30I
I÷25H4OM
SP
I.
302
I÷25Hk0M30S
A
I.
303
SP
I.
CONTROL BY VOICE DIRECTION DSIF 51 EXECUTION OF COMMAND SEQUENCE 225I. DSIF 5I WILL EXECUTE MINOR SEQUENCES IN 225I ON DIRECTION FROM SP. NOMINAL Ti"_Smc ru_.....uoiF EXECUTI UIW _'' OF MINOR SEQUENCES ARE LISTED. EXECUTE TO COMM. COMMAND 21. SEQUENCE 0142 (COAST
304
I÷25H4IM
II
I.
305
I÷25H44M
II
I.
EXECUTE COMMAND 4 SELECTION). EXECUTE COMMAND I SELECTION).
SEQUENCE
0144
{COMM.
306
I÷25H46M
II
I.
SEQUENCE
0145
{COMM.
V-33
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
307
I+25H48M
IX
I.
EXECUTE GINEERING REPORT OF DF
COMMAND SEQUENCE TO COAST COMM.). TO A COMPLETION OF 225I,
0546
(EN-
308
I÷25H4gM
SP
I.
EXECUTION AND SIATUS
COMMAND SEQUENCE S/C RESPONSE. START OF
309
I÷26H
NET
I.
REPORT TO A FER PROCEDURE. BRIEF TIONS
STATION
TRANS-
310
I÷26H
SP
I.
A ON RESULTS PROGRAM RUN. A DSIF LOCK DSIF
OF
TELECOMMUNICA-
3II
I÷26HOSM
NET
1.
REPORT TO AND ONE-WAY REPORT TO WITH SIC. BEGIN SF. REPORT PROGRAM REPORT FER
51 TRANSMITTER WITH S/C. 42 IN TWO-WAY
OFF
312
I+26HO6M
NET
1.
A
LOCK
313
I+26HO6M
42
1.
TRANSMITTING
TRACKING
DATA
TO
314
I÷26H30M
SP
I.
TO A START UPDATE. TO A START
OF
POWER,
THERMAL
315
I+27H20M
NET
I.
OF
STATION
TRANS-
PROCEDURE. TO A DSIF 42 TRANSMITTER OFF
316
I+27H25M
NET
1.
REPORT AND S/C
TRACKING TO A DSIF
STOPPED. 51 IN TWO-WAY LOCK
317
I÷2THZ6M
NET
1.
REPORT WITH
S/C. TRANSMITTING TRACKING DATA TO
318
I÷27H26M
51
I.
BEGIN SF.
319
I÷27H30M
SP
1.
REPORT PROGRAM VISIBILITY REPORT PROGRAM
TO A START UPDATE. ENDS. TO A START UPDATE.
OF
POWER,
THERMAL
320 321
I÷27HSOM I÷28H30M
42 SP
I. I.
OF
POWERt
THERMAL
V-34
EPD-I80,
REVISION
1
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
322
I÷29H30M
SP
X.
REPORT PROGRAM
TO A START UPDATE.
OF
POWER_
THERMAL
323
I+30H30M
SP
1.
REPORT TO A START PROGRAM UPDATE. REPORT TO A START PROGRAM UPDATE. REPORT TO A START PROGRAM UPDATE. REPORT TO A START PROGRAM UPDATE. REPORT TO A START PROGRAM UPDATE. VISIBILITY BEGINS.
OF
POWER,
THERMAL
324
I÷3XH30M
SP
1.
OF
POWER,
THERMAL
325
I+32H3OM
SP
1-
OF POWERt
THERMAL
326
I.33H3OM
SP
1.
OF
POWER,
THERMAL
327
I÷34H30M
SP
1.
OF
POWER,
THERMAL
328 329
I÷34H48M I÷34H4BM
XX NET
I. I.
REPORT TO A START BY DSIF XX.
OF
SEARCH
FOR
S/C
330
I+34H49M
NET
1.
REPORT TO A DETECTION DSIF 11o REPORT TO A DSIF WITH S/C. REPORT TO A START FER PROCEDURE. REPORT TO A DSIF AND S/C TRACKING REPORT TO WITH SIC. BEGIN SF. A DSIF 11 IN
OF
SIC
BY
331
I÷34HSOM
NET
X.
ONE-WAY
LOCK
2.
OF
STATION
TRANS-
332
I+34H55M
NET
X.
42 TRANSMIITER STOPPED. o. IX IN TWO-WAY
OFF
333
I÷34H56M
NET
X.
LOCK
334
I÷34H56M
XX
X.
TRANSMITTING
TRACKING
DATA
TO
335 336
I÷35HXgM I÷35H30M
51 SP
I. I.
VISIBILITY
ENDS. OF POWERtTHERMAL
REPORT TO A START PROGRAM UPDATE.
V-35
EPD-180,
REVISION
!
SECTION
V
IIEM
TIME
OF
EVENT
STATION
EVENT
337
I÷36H3OM
SP
1.
REPORT TO A START OF POWER PROGRAM UPDATE, AND POWER PREDICTION COMPUTATION.
THERMAL THERMAL
338
I*37H
SP
I.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2251 (LOW-POWER ENGINEERING INTERROGATION). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2251.
COM-
339
I÷37HOOM30S
A
1.
OF
34O
SP
1.
CONTROL BY VOICE DIRECTION DSIF 11 EXECUTION OF COMMAND SEQUENCE 2251. DSIF 11 WILL EXECUTE MINOR SEQUENCES IN 2251 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND TO COMM. 2}. EXECUTE COMMAND 4 SELECTION). EXECUTE COMMAND 1 SELECTION). SEQUENCE 0142 (COAST
341
I÷37HO1M
[!
1.
342
I÷37H04M
XL
I.
SEQUENCE
0144
(COMM.
343
I÷37HO6M
IX
I.
SEQUENCE
0145
(COMM.
344
I÷37HOBM
IX
X.
EXECUTE COMMAND SEQUENCE 0546 GINEERING TO COAST COMM.).
(EN-
345
I÷37HOgM
SP
1.
REPORT TO A COMPLETION OF EXECUTION OF COMMAND SEQUENCE 2251, AND STATUS OF SIC RESPONSE. REPORT PROGRAM TO A START UPDATE. OF POWER,THERMAL
346
I÷37H30M
SP
2.
347
I÷3BH
SP
X.
BRIEF A ON PREDICTION REPORT COURSE REPORT PROGRAM TO A ORBIT
RESULTS OF COMPUTATION.
POWER,THERMAL
348
I÷38H
FP
I.
START OF SECOND DETERMINATION OF POWER,
POSTMID194Xl. THERMAL
349
I÷3BH30M
SP
1.
TO A START UPDATE.
V-36
EPD-I8Ot
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
350 351
I÷38H4TM I÷38H47M
42 NET
I. I.
VISIBILITY
BEGINS. OF SEARCH FOR SIC
REPORT TO A START BY DSIF 42.
352
I÷38H48M
NET
I.
REPORT TO A DETECTION DSIF 42. REPORT TO WITH S/C. REPORT PROGRAM A DSIF 42 IN
OF
SIC
BY
353
I÷3BHSOM
NET
I.
ONE-WAY
LOCK
354
I÷39H30M
SP
I.
TO A START UPDATE.
OF
POWERtTHERMAL
355
I÷40H
NET
I.
REPORT TO A START FER PROCEDURE. REPORT TO A DSIF AND ONE-WAY LOCK REPORT TO A DSIF WITH SiC. BEGIN TRANSMITTING TO SF. REPORT PROGRAM TO A START UPDATE.
OF
STATION
TRANS-
356
I÷40HOSM
NET
1.
11 TRANSMITTER WITH S/C. 42 IN TWO-WAY
OFF
357
I÷40HO6M
NET
I.
LOCK
358
I+40HObM
42
I.
TRACKING
DATA
359
I÷40H30M
SP
I.
OF
POWERt
THERMAL
360
I+41H
FP
I.
REPORT TO A COMPLETION OF SECUND POSTMIDCOURSE ORBIT DETERMINATION. BEGIN TRAJECTORY TRAJECTORY COMPUTATION COHPUTATI {94X). "''
Ul_°
2. 36i X+4iHiOM FP i. 2.
COMPLETE
REPORT TO A START TERMINAL MANEUVER (94X). REPORT TO A START FER PROCEDURE.
OF PRELIMINARY COMPUTATIONS
362
I÷41H25M
NET
I.
OF
STATION
TRANS-
363
I÷41H30M
FP
I.
REPORT TO A COMPLETION OF LIMINARY TERMINAL MANEUVER
PRECOMPUTAV-37
EPD-I8O,
REVISION
1
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
363 364
(CONTINUED) I÷4IH30M SP 1.
TIONS. REPORT PROGRAM TO A START UPDATE. DSIF LOCK DSIF UF POWER,THERMAL
365
I+6IH3OM
NET
1.
REPORT TO A AND ONE-WAY REPORT WITH TO S/C. A
42 TRANSMITTER WITH S/C. ll IN TWO-WAY
OFF
366
I+41H31M
NET
I.
LOCK
367
I+41H31M
II
I.
BEGIN TO SF.
TRANSMITTING
TRACKING
DATA
368
I+42H
FP
I.
GIVE EUVER
PRELIMINARY DATA ON IO SP,
TERMINAL SS.
MAN-
2.
BRIEF A MIDCOURSE TERMINAL REPORT PROGRAM
RESULTS OF SECOND ORBIT AND PRELIMINARY MANEUVER COMPUTATIONS. OF
POST-
369
I+62H3OM
SP
l-
TO A START UPDAIE.
POWER,THERMAL
370
I+42H45M
NET
I-
REPORT TO A START FER PROCEDURE. REPORT TO A OFF AND S/C REPORT TO WITH SiC. BEGIN TO SF. A DSIF II TRACKING DSIF
OF
STATION
TRANS-
371
I+42H5OM
NET
1.
TRANSMITTER STOPPED. IN TWO-WAY LOCK
372
I+42HSIM
NET
1.
42
373
I÷42HSIM
62
1.
TRANSMITTING
TRACKING
DATA
374 375
I÷43H25M I+43H30M
11 SP
1. I.
VISIBILITY REPORT PROGRAM REPORT PROGRAM REPORT
ENDS. TO A START-OF UPDATE. TO A START UPDATE. TO A DECISION OF POWERvTHERMAL
376
I÷64H30M
SP
1.
POWERtTHERMAL
377
I÷45H
SP
1.
TO
EXECUTE
CUMV-3B
EPD-I8O,
REVISION
1
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
377
(CONTINUED)
MAND SEQUENCE CONTROL). A I.
2252
(VERNIER
THERMAL
378
I_45HOOM30S
DIRECT SP TO CONTROL EXECUTION COMMAND SEQUENCE 2252.
OF
37?
SP
I.
CONTROL BY VOICE DIRECTION DSIF 62 EXECUTION OF COMMAND SEQUENCE 2252. EXECUTE COMMAND SEQUENCE 2252. EXECUTION AND STATUS
380 38I
I+45HOIM I+45HO2M
42 SP
I. I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2252, OF S/C RESPONSE. REPORT PROGRAM REPORT PROGRAM TO A START UPDATE. TO A START UPDATE. OF
382
I÷65H3OM
SP
I.
POWER,THERMAL
383
I÷46H30M
SP
I.
OF
POWER,THERMAL
384
I_47H30M
SP
I.
REPORT TO A START PROGRAM UPDATE. VISIBILITY BEGINS.
OF
POWER,THERMAL
385 386
I÷67H34M I_47H36M
5I NET
I. I.
REPORT TO A START BY DSIF 5I. REPORT 51, TO
OF SEARCH
FOR
S/C
38T
I÷ATH35M
NET
I.
A DETECTION
OF
S/C
BY
DSIF
388
I_ATH37M
NET
I.
REPORT TO A DSIF WITH S/C. REPORT TO A START PROGRAM UPDATE. REPORT TO A START FER PROCEDURE. REPORT TO A DSIF AND ONE-WAY LOCK REPORT TO A DSIF
51
IN
ONE-WAY
LOCK
389
I÷4BH30M
SP
I.
OF POWER,THERMAL
390
I÷4BH5OM
NET
10
OF STATION
TRANS-
391
I_48H55M
NET
I.
42 TRANSMITTER WITH S/C. 51 IN TWO-WAY
OFF
392
I_48H56M
NET
I.
LOCK V-39
EPD-I8O_ REVISION I
SECTION V
ITEM TIME
392 393
OF
EVENT
STATION
EVENT
(CONTINUED} I÷48H56M 5I 1.
WITH BEGIN SF.
S/C. TRANSMITTING TRACKING DATA TO
394
I_49H
FP
I.
REPORT TO MIDCOURSE
A START OF THIRD POSTORBIT DETERMINATION (94X1.
395
I+49H
SP
I.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2251 (LOW-POWER ENGINEERING INTERROGATION}. DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 225I. OF
396
I÷49HOOM30S
A
I.
397
SP
I.
CONTROL BY VOICE DIRECTION DSIF 51 EXECUTION OF COMMAND SEQUENCE 2251. DSIF 51 WILL EXECUTE MINOR SEQUENCES IN 2251 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION DF MINOR SEQUENCES ARE LISTED. EXECUTE TO COMM. COMMAND 2}. SEQUENCE 0142 (COAST
398
I÷49HOIM
51
I.
399
I÷49HO4M
51
1.
EXECUTE COMMAND 4 SELECTION). EXECUTE COMMAND I SELECTION}.
SEQUENCE
0144
(COMM.
400
I÷49HO6M
51
I.
SEQUENCE
0145
(CUMM.
401
I÷49HO8M
51
I.
EXECUTE COMMAND SEQUENCE 0546 GINEERING TO COAST COMM.). REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 225i, OF SIC RESPONSE. REPORT PROGRAM TO A START UPDATE. OF
(EN-
402
I÷49HO9M
SP
I.
EXECUTIUN AND STATUS
403
I+49H30M
SP
I.
POWER,THERMAL
404
I+50HIOM
NET
1.
REPORT TO A START FER PROCEDURE. REPORT TO A DSIF
OF
STATION
TRANS-
405
I+5OHI5M
NET
1.
51
TRANSMITTER
OFF V-40
EPD-18O,
REVISION
I
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
405 406
[CONTINUED) IeSOHI6M NET I.
AND
ONE-WAY
LOCK A DSIF
WITH 42 IN
S/C. TWO-WAY LOCK
REPORT TO WITH S/C. BEGIN SF. REPORT PROGRAM
407
I÷5OHI6M
42
I.
TRANSMITTING
TRACKING
DATA
TO
408
I÷SOH30M
SP
I.
TO A START UPDATE.
OF
POWER,THERMAL
409
I+51H3OM
NET
1.
REPORT TO A START FER PROCEDURE. REPORT PROGRAM TO A START UPDATE.
OF
STATION
TRANS-
410
I+51H30M
SP
I.
OF
POWER,THERMAL
411
I÷51H35M
NET
I.
REPORT TO A DSIF 42 TRANSMITTER AND SPACECRAFT TRACKING STOPPED. REPORT TO WITH S/C. BEGIN SF. A DSIF 51 IN TWO-WAY
OFF
412
I+51H36M
NET
I.
LOCK
413
I÷51H36M
51
I.
TRANSMITTING
TRACKING
DATA
TO
414 415
I+51HS?M I+52H
42 FP
I. I.
VISIBILITY REPORT TO MIDCOURSE BEGIN COMPLETE
ENDS. A COMPLETION OF THIRD ORBIT DETERMINATION. COMPUTATION COMPUTATION. OF INTERMEDIATE COMPUTATIONS (94X1. INTERCOMPUTAPOST
2. 416 I÷52HlOM FP I. 2.
TRAJECTORY TRAJECTORY
{94X).
REPORT TO A START TERMINAL MANEUVER REPORT MEDIATE TIONS. REPORT PROGRAM
417
I+52H3OM
FP
I.
TO A COMPLETION OF TERMINAL MANEUVER
418
I÷52H30M
SP
I-
TO A START UPDATE.
OF
POWERITHERMAL
V-41
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
419
I*53H
FP
1.
GIVE EUVER
INTERMEDIATE DATA TO ON SP,
TERMINAL SS.
MAN-
2.
BRIEF SFOD ATE TERMINAL REPORT PROGRAM REPORT PROGRAM REPORT PROGRAM REPORT PROGRAM
RESULTS MANEUVER OF
OF INTERMEDICOMPUTATIONS. POWERtTHERMAL
420
I÷53H3OM
SP
I.
TO A START UPDATE. TO A START UPDATE. TO A START UPDATE. TO A START UPDATE.
421
I+54H3OM
SP
I.
OF
POWER,THERMAL
422
I*55H30M
SP
I.
OF
POWER,THERMAL
423
I_56H30M
SP
I.
OF
POWER,THERMAL
424
I÷57H
FP
I.
REPORT TO MIDCOURSE YD.
A START OF FOURTH ORBIT DETERMINATION
POST(94Xt
425
I÷57H4OM
SP
I.
REPORT
TO
A
DECISION 2253
TO {SURVEY
EXECUTE CAMERA
COM-
MAND SEQUENCE WARMUP). 426 I÷57H4OM30S A I. DIRECT COMMAND 427 SP I. CONTROL EXECUTION 428 429 I+57H41M I÷57H42M 51 SP 1. I. EXECUTE SP TO
CONTROL 2253.
EXECUTION
OF
SEQUENCE BY VOICE OF COMMAND
DIRECTION SEQUENCE
DSIF
5I 2253°
COMMAND
SEQUENCE OF 22_3,
2253. EXECUTION ANU STATUS
REPORT TO A COMPLETION OF COMMAND SEQUENCE OF S/C RESPONSE. REPORT TO A MAND SEQUENCE WARMUP). DIRECT COMMAND DECISION 2254
430
I+58H40M
SP
1.
TO EXECUTE COMIAPPROACH CAMERA
631
I+58H40M30S
A
1.
SP TO CONTROL SEQUENCE 2254.
EXECUTION
OF
V-42
EPD-I80t
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
432
SP
1.
CONTROL BY VOICE DIRECTION DSIF 51 EXECUTION OF COMMAND SEQUENCE 2254. EXECUTE COMMAND SEQUENCE 2254. EXECUTION AND STATUS
433 434
I+58H4IM I÷SBH4ZM
5I SP
1. 1.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2254t OF SIC RESPONSE. VISIBILITY BEGINS. OF
435 436
I_58H46M I÷58H46M
11 NET
1. 1.
REPORT TO A START BY DSIF I1. REPORT 11. TO
SEARCH
FOR
SIC
437
I÷58H47M
NET
I.
A DETECTION
OF
SIC
BY
DSIF
638
I÷58H49M
NET
I.
REPORT TO WITH SIC.
A DSIF
II
IN
ONE-WAY
LOCK
2.
REPORT TO A START FER PROCEDURE. REPORT TO A DSIF AND SIC TRACKING REPORT TO WITH SIC. BEGIN SF. A DSIF
OF
STATION
TRANS-
439
I÷58H54M
NET
I.
51 TRANSMITTER STOPPED. II IN TWO-WAY
OFF
440
I+58H55M
NET
I.
LOCK
441
I÷58H55M
II
I.
TRANSMITTING
TRACKING
DATA
TO
442 443
I÷59H28M I÷59H30M
51 SP
II-
VISIBILITY
ENDS.
REPORT TO A _ncrlcvn_'_._,. In._ ....-_.__v_rsIT_ rnM-__.. MAND SEQUENCE 2255 (HIGH-POWER ENGINEERING INTERROGATION - AMR WARMUPIIIOO BPS FROM I37.5, 17.2). DIRECT COMMAND A TO CONTROL EXECUTION SEQUENCE 2255. OF
444
I÷59H30M30S
A
1.
665
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 225b. DSIF II WILL EXECUTE MINOR COMV-43
EPD-ISOt
REVISION
I
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
445
(CONTINUED)
MAND SEQUENCES IN 2255 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. II I. EXECUTE COMMAND SEQUENCE (TRANSMITTER B FILAMENT). EXECUTE TO COMM. COMMAND 21. SEQUENCE 0141
446
I÷SgH31M
447
I+59H31M45S
II
I.
0142
(COAST
44B
I÷59H33M
11
I.
EXECUTE COMMAND POWER/LOW RATE EXECUTE COMMAND 4 SELECTION). EXECUTE COMMAND (AMR WARMUPI. EXECUTE COMMAND I SELECTION).
SEQUENCE 0547 TO 1100 BPS). SEQUENCE 0144
(HIGH
449
I+57H36M
II
I.
(COMM.
450
I+59H37M
II
I.
SEQUENCE
064D.
451
I+59H38M
II
I.
SEQUENCE
0145
(COMM.
452
I+59H40M
SP
I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2255, OF SIC RESPONSE.
EXECUTION AND STAIUS
453
I÷60H
FP
1-
REPORT TO A COMPLETION OF FOURTH POSTMIDCOURSE ORBIT DETERMINATION. REPORT TO A START OF MANEUVER COMPUTATION REPORT TO TERMINATION BEGIN A COMPLETION MANEUVER FINAL (94X, TERMINAL Y)o
2.
454
I+60HISM
FP
I-
OF FINAL COMPUTATION. (94X).
2. 455 456 I+60H25M I÷60H25M FP SP I. I.
TRAJECTORY TRAJECIORY TO A START UPDATE.
COMPUTATION COMPUTATION. OF
COMPLETE REPORT PROGRAM REPORT COMMAND
POWER,THERMAL
457
I+60H30M
SP
I.
TO A DECISION TO EXECUTE SEQUENCE 2256 (HIGH-POWER V-44
EPD-180,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
457
(CONTINUED)
ENGINEERING FROM I37.5t A 1DIRECT COMMAND
INTERROGATION-IIO0 17.2).
BPS
458
I÷6OH3OM3OS
SP TO CONTROL EXECUTION SEQUENCE 2256.
OF
459
SP
I°
CONTROL BY VOICE DIRECTION DSIF 11 EXECUTION OF COMMAND SEQUENCE 2256. DSIF 11 WILL EXECUTE MINOR SEQUENCES IN 2256 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION UF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND SEQUENCE (TRANSMITTER B FILAMENT). EXECUTE TO COMM. COMMAND 2). SEQUENCE 0141
460
I÷60H31M
11
I.
461
I÷60H31M45S
11
I.
0142
(COAST
462
I÷60H33M
11
1.
EXECUTE COMMAND POWER/LOW RATE EXECUTE COMMAND 4 SELECTION). EXECUTE COMMAND I SELECTION).
SEQUENCE 0547 TO 1100 BPS). SEQUENCE 0144
(HIGH
463
I÷60H36M
11
1.
{COMM.
464
I÷60H38M
11
I.
SEQUENCE
0145
(COMM°
465
I_6OH40M
SP
1.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2256t OF SIC RESPONSE.
EXECUTION AND STATUS
2°
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2151 (EARLY GYRO SPEED CHECK|. DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2151o
COM-
466
Ie6OH4OM30S
A
1°
OF
467
SP
|.
CONTROL BY VOICE DIRECTION DSIF 11 EXECUTION OF COMMAND SEQUENCE 2151. DSIF 11 WILL EXECUTE MINOR COMMAND SEQUENCE IN 2151 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. V-45
EPD-1BOt
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
468
I*60H41M
II
1.
EXECUTE COMMAND GINEERING COMM. EXECUTE TO GYRO EXECUTE GYRO). EXECUTE GYRO). EXECUTE GYRO).
SEQUENCE OFFI.
0340
(EN-
469
I+60H42M
II
1.
COMMAND SEQUENCE PROCESSING|. COMMAND SEQUENCE
0341
(SCO
470
I÷60H43M
11
I.
0342
(NEXT
471
I+60H44M
II
1.
COMMAND
SEQUENCE
0342
(NEXT
472
I÷60H45M
IX
I.
COMMAND
SEQUENCE
0342
(NEXT
473
I+60H46M
II
I.
EXECUTE COMMAND PROCESSING OFF).
SEQUENCE
0343
(GYRO
474
I+60H4TM
SP
1.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 21511 OF S/C RESPONSE.
EXECUTION AND STAIUS
2.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2257 (VCXO AND VCO FREQUENCY CHECKS). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2257. OF
475
I÷60H47M30S
A
I.
476
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2257. DSIF ll WILL EXECUTE MINOR SEQUENCES IN 2257 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND SEQUENCE 0146 (TRANSPONDER OFF/DSIF REACQUISlTION;. REPORT TION. TO A DSIF REACQUISI-
477
I+60H48M
11
I.
478
I÷60HSOM
SP
I.
479
I+60HSOM
IX
Io
EXECUTE COMMAND SEQUENCE (NARROW-BAND VCXO OFF).
0641
V-46
EPD-I8O,
REVISION
I
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
480
I÷60HSOM
FP
I.
TERMINAL I.
MANEUVER
COMMAND
DECISION
481
I÷60HSIM
II
I.
EXECUTE COMMAND SEQUENCE 0642 (NARROW-BAND VCXO, TRANSPONDER DSIF REACQUISITION}. REPORT TO A DSIF REACQUISITION.
ON/
482
I÷60H53M
SP
I. 2.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 225?, OF SIC RESPONSE.
EXECUTION AND STATUS
3.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2153 (POST GYRO CHECK COAST PHASE PREPARATION - 17.2 BPS}. DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2153. OF
483
I+60H53M30S
A
I.
484
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2153. DSIF II WILL EXECUTE MINOR SEQUENCES IN 2153 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND SEQUENCE (17.2 BPS SELECTION}. EXECUTE COMMAND SEQUENCE POWER/COAST COMM.). REPORT
........
485
I+60H54M
I1
1.
0643
486
I÷60H56M
II
I.
0345
(LOW
487
I÷60H57M
SP
I.
TO
*-._
A COMPLETION
_=*_L*r_ _I _
OF
EXECUTION
Akin CTATII_
OF 488 I÷61HOSM SP Io
SIC
RESPONSE. MANEUVER COMMAND DECISION
TERMINAL II.
489
I÷61HI5M
SP
I.
REPORT TO A COMPLETION OF TERMINAL MANEUVER COMMAND MESSAGE PREPARATION. START VALIDATION OF TERMINAL MANEUVER V-4T
490
I+61HI5M
SPtFP
I.
EPD-180t
REVISION
I
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
490 691
(CONTINUED) I+61H20M SP 1.
COMMAND SEND MAND
MESSAGE. MANEUVER COM-
TO A TERMINAL REQUEST.
492
I÷6XH22M
A
I.
COMMAND DIRECTIVE - SEND EUVER COMMAND MESSAGE TO
TERMINAL DSIF II.
MAN-
693
I+61H25M
II
I.
COMMAND VERIFICATION - PLAY BACK TERMINAL MANEUVER COMMAND TAPE FOR VERIFICATION. REPORT TO A COMPLETION MANEUVER COMMAND TAPE OF TERMINAL VERIFICATION. COMBPS
494
I+61H60M
SP
I.
495
I÷61H43M
SP
I.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2256 (HIGH-POWER ENGINEERING INTERROGATION-110O FROM 137.5t 17.2). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2256.
696
[÷61H63M30S
A
I.
OF
497
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2256. DSIF II WILL EXECUTE MINOR SEQUENCES IN Z256 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND (TRANSMITTER B EXECUTE TO COMM. COMMAND 2). SEQUENCE FILAMENTI. SEQUENCE 0141
498
I+61H44M
II
I.
699
I+61H66M65S
II
I.
0162
(COAST
500
I÷61H46M
II
I.
EXECUTE COMMAND POWER/LOW RATE EXECUTE COMMAND 4 SELECTION). EXECUTE COMMAND 1 SELECTIONI.
SEQUENCE 0567 TO II00 BPSI. SEQUENCE 0144
(HIGH
501
I*61H69M
II
1.
(COMM.
502
I÷61HSIM
ll
1.
SEQUENCE
0145
|COMM.
V-68
EPD-IBOt
REVISION
[
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
503
I÷61H53M
SP
1.
REPORT TO A COMPLETION OF EXECUTION OF COMMAND SEQUENCE 2256. AND STATUS OF SIC RESPONSE. REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2350 {LATE GYRO SPEED CHECK/llO0 BPS RETURN). DIRECT COMMAND CONTROL EXECUTION DSIF II IN 2350 NOMINAL SEQUENCES EXECUTE TO GYRO EXECUTE GYRO). EXECUTE GYRO). EXECUTE GYRO). SP TO CONTROL EXECUTION SEQUENCE 2350. BY OF
2.
504
I+61H53M30S
A
I.
505
SP
I.
VOICE DIRECTION DSIF II OF COMMAND SEQUENCE 2350. WILL EXECUTE MINOR SEQUENCES ON DIRECTION FROM SP. TIMES FOR EXECUTION OF MINOR ARE LISTED. COMMAND SEQUENCE PROCESSING|° COMMAND SEQUENCE 0341 {SCO
506
I+61H54M
II
I.
507
I÷61H55M
II
I.
0342
(NEXT
508
I+61H56M
II
I.
COMMAND
SEQUENCE
0342
(NEXT
509
I÷61H57M
II
I.
COMMAND
SEQUENCE
0342
(NEXT
510
I÷61HSBM
II
I.
EXECUTE COMMAND SEQUENCE 0664 PROCESSING TO 7.35 KC SCO). REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2350, OF SIC RESPONSE.
(GYRO
511
I+61H59M
SP
1-
EXECUTION ..,.,,.,A_'n STATUS
2.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2351 (PLANAR ARRAY DEPLOYMENTI. DIRECT COMMAND CONTROL SP TO CONTROL EXECUTION SEQUENCE 2351. BY VOICE DIRECTION DSIF
COM-
512
I+61H59M30S
A
I.
OF
513
SP
I.
II V-49
EPD-I80t
REVISION
1
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
513
[CONTINUED;
EXECUTION OF COMMAND SEQUENCE 2351. DSIF II WILL EXECUTE MINOR SEQUENCES IN 2351 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. II I. EXECUTE COMMAND 2 SELECTION). EXECUTE COMMAND POLAR AXIS). EXECUTE COMMAND I SELECTION). SEQUENCE 0044 (COMM.
514
I+62H
515
I+62H01M
II
1.
SEQUENCE
0645
(STEP
516
I+62H05M
II
I.
SEQUENCE
0145
{COMM.
517
I+62HO6M
SP
I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2351, OF S/C RESPONSE.
EXECUTION AND STATUS
2.
REPORT I0 A DECISION TO EXECUTE COMMAND SEQUENCE 2352 (TERMINAL MANEUVER PREPARATION). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2352. OF
518
I+62HO6M30S
A
I.
519
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2352. DSIF 11 WILL EXECUTE MINOR SEQUENCES IN 2352 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE COMMAND SEQUENCE 0646 MINAL FIRST ROLL PARAMETERS). EXECUTE COMMAND AND ROLL;. REPORT TO MANEUVER. SEQUENCE 0441 {TER-
520
I+62HO7M
II
I.
521
I÷62HO8M
11
I.
(SUN
522
2+62HOgM30S
SP
I.
A COMPLETION
OF
ROLL
523
I+62HIOM
IX
I.
EXECUTE COMMAND SEQUENCE 0641 MINAL YAW [PITCH) PARAMETERSI.
(TER-
V-50
EPD-I80t
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
524
I+62HI1M20S
11
I.
EXECUTE COMMAND (YAW (PITCH)). REPORT (PITCH)
SEQUENCE
0443
(0444l
525
I+62HI7M20S
SP
1.
TO A COMPLETION MANEUVER.
OF YAW
526
Ie62H17M50S
II
I.
EXECUTE COMMAND SEQUENCE 0740 MINAL SECOND ROLL PARAMETERSI. EXECUTE (ROLL). COMMAND SEQUENCE 0240
ITER-
527
I÷62HI8M50S
11
I.
528
I÷62H24MSOS
SP
I.
REPORT TO MANEUVER. EXECUTE ERTIAL
A COMPLETION
OF
ROLL
529
I÷62H26M40S
11
I.
COMMAND MODE).
SEQUENCE
0741
(IN-
530
I÷62H27M40S
SP
I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2352, OF S/C RESPONSE.
EXECUTION AND STAIUS
2.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2353 (PRE-APPROACH TELECOMMUNICATIONS PREPARATION|. DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2353.
COM-
53I
I+62H27MSOS
A
I.
OF
532
SP
l.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2353. DSIF II WILL EXECUIE MINOR SEQUENCES IN 2353 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE L,''STED. EXECUTE COMMAND (TRANSMITTER B SEQUENCE TO PLANAR 0742 ARRAY).
533
I÷62H28M
lI
I.
534
I÷62H28MIOS
ll
1.
EXECUTE COMMAND SEQUENCE 0743 (TRANSPONDERt VCXO, SUMMING AMPLIFIERS OFF). EXECUTE QUENCY COMMAND SUMMING SEQUENCE AMPLIFIER 0744 B). (FRE-
535
I÷62H29M00S
ll
I.
V-51
EPD-I8Ot
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
536
I+62H29MIDS
II
1.
EXECUTE TO 4400
COMMAND SEQUENCE 0745 BPSICOMM. 2 SELECTION).
(1100
537
I+62H29MSOS
II
1.
EXECUTE COMMAND SEQUENCE 0746 (APPROACH CAMERA TEMPERATURE CONTROL OFF). EXECUTE COMMAND SEQUENCE 0747° EXECUTION AND STAIUS
538 539
I+62H30M I+62H3OMIOS
II SP
I. I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2353t OF SIC RESPONSE.
2.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2354 (FIRST APPROACH IV SEQUENCE/RETRO SEQUENCE PREPARATIDN). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2354. OF
540
I+62H30M205
A
1.
541
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2354. DSIF II WILL EXECUTE MINOR SEQUENCES IN 2354 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE -PICTURE COMMAND TV). SEQUENCE I040 (FORTY
542
I+62H3OM30S
lI
I.
543
I+62H33M2OS
lI
1.
EXECUTE COMMAND PARAMETERS). EXECUTE SEQUENCE
SEQUENCE
1041
{RETRO
544
i÷62H34H
11
!=
COMMAND SEQUENCE MODE ON}.
I042
{RETRO
545
I+62H34M20S
SP
1.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2354_ OF SIC RESPONSE.
EXECUTION AND STATUS
2.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2355 (FINAL APPROACH SEQUENCE). V-52
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
546
I÷62H34M30S
A
I.
DIRECT COMMAND
SP TO CONTROL EXECUTION SEQUENCE 2355.
OF
547
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2355. DSIF 11 WILL EXECUTE MINOR SEQUENCES IN 2355 ON DIRECTION FROM SP. NOMINAL TIMES FOR DSIF EXECUTION OF MINOR SEQUENCES ARE LISTED. EXECUTE PICTURE ERATURE COMMAND SEQUENCE TV, SURVEY CAMERA CONIROL OFF). SEQUENCE SET IV I043 (TENTEMP-
548
I÷62H34M40S
II
I.
549
I÷62H35M30S
11
I.
EXECUTE COMMAND (AMR POWER/RESET EXECUTE (THREE
I044 LATCH). 0446
550
I+62H35M50S
II
I.
COMMAND SEQUENCE PHASE POWER).
551
I+62H36M
11
I.
EXECUTE COMMAND SEQUENCE 1045 (ACCELEROMETER/STRAIN GAUGE POWER EXECUTE COMMAND (THIRTY-PICTURE SEQUENCE TV}. I046
ON).
552
I+62H36MIOS
11
I.
553
I+62H3BM30S
11
I.
EXECUTE COMMAND SEQUENCE 1047 ABLE BATTERY TRANSFER LOGIC). EXECUTE CURRENT). EXECUTE PICTURE COMMAND SEQUENCE IT40
(DIS-
554
I+62H38M40S
11
I.
(HIGH
555
I+62H38MSOS
II
1.
COMMAND SEQUENCE IV SEQUENCEI.
I141
(TEN-
556
I+62H39M50S
II
l.
EXECUTE COMMAND ENABLE/THREE TV OMETER CHANNELS). AMR TRIGGER. ENGINES
SEQUENCE 1142 PICTURES/ACCELER-
(AMR
557 558 559
I+62H4OM34S I+62H4OM43S I÷62H40M44S
SIC S/C S/C
I. l. I.
VERNIER MAIN
IGNITED.
RETRO
IGNITIDN. V-53
EPD-I80,
REVISION I
SECTION V
ITEM TIME OF EVENT STATION 560
561
EVENT
I÷AZH40M45S
I÷62H4ON55S
SIC
II
I. I.
DOPPLER EXECUTE PICTURE MAIN
AND
ALTIMETER
RADARS I143
ON. [TWO-
COMMAND SEQUENCE TV SEQUENCE). BURNOUT.
562 563
I÷62H4IM42S I÷62H4IM42S
SIC ll
I. I.
RETRO
EXECUTE COMMAND SEQUENCE I144 ILAST TVI TRANSMISSION OF THIS SEQUENCE INITIATED AUTOMATICALLY BY SIC RETRO BURNOUT SIGNAL. MAIN RETRO EJECTED SIGNAL.
564 565
I+62H4IMSIS I÷62H42M
S/C lI
I. I.
EXECUTE COMMAND (TELECOMMUNICATIONS IOOO-FOOT IOFT/SEC 13-FOOT TOUCHDOWN. MARK. MARK. MARK.
SEQUENCE. II_5 TRANSFER).
566 567 568 569 570
I÷62H43MIBS I+62H43M46S I+62H43M54S I÷62H43M56S TD+O
SIC S/C S/C SIC SP
1. I. 1. I. I.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2356 (POSTLANDING OPERATIONS SEQUENCE). REPORT TO A START OF ATTITUDE COMPUTATION. DIRECT COMMAND POSTLANDING
COM-
2.
57I
TD÷30S
A
I.
SP TO CONTROL EXECUTION SEQUENCE 2356.
OF
SP
I.
CONTROL BY VOICE DIRECTION DSIF |I EXECUTION OF COMMAND SEQUENCE 2356. EXECUTE COMMAND SEQUENCE 2366. EXECUTION AND STATUS
572 573
TD+IM TD+5M
11 SP
I. I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2356t OF S/C RESPONSE. REPORT TO A DECISION TO
2.
EXECUTE
CUMV-54
EPD-18Ot
REVISION
I
SECTION
V
ITEM
TIME
OF EVENT
STATION
EVENT
573
{CONTINUED)
MAND SEQUENCE 2357 {TOUCHDOWN SURVIVAL EVALUATION). A I. DIRECT SP TO CONTROL EXECUTION COMMAND SEQUENCE 2357. OF
574
TD÷5M30S
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2351. EXECUIE COMMAND SEQUENCE 235T. EXECUTION AND STAIUS
575 576
TD÷6M TD÷IBM
II SP
I. I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2357t OF SIC RESPONSE.
2.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2450 (SUN/ EARTH ACQUISITIONI. DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2450.
COM-
577
TD÷18M30S
A
I.
OF
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2450. EXECUTE COMMAND SEQUENCE 2450.. POSTLAND-
578 579
TD÷I9M TD÷45M
II SP
I. I.
REPORT TO A COMPLETION OF ING ATTITUDE COMPUTATION. REPORT ORBIT TO A START DETERMINATION OF
580
TD÷45M
FP
I.
POST-TOUCHDOWN (94X).
581
TD÷IHIgM
SP
l-
REPORT TO A COMPLETION OF EXECUTION ur COMMAND SE ni'cLir_ _L_n_ A_n _TATiI_ OF SIC RESPONSE. REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2452 (FIRST WIDE-ANGLE IV MAPPING). DIRECT COMMAND CONTROL SS TO CONTROL EXECUIION SEQUENCE 2452. BY VOICE DIRECTION DSIF OF
582
TD+IH20M
SS
I.
583
TD+IH2OM30S
A
1.
SS
l.
II V-55
EPD-180t
REVISION
[
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
583 584 585
(CONTINUED) TD+IH2IM TD+IH27M II SS 1. l.
EXECUTION EXECUTE
OF
COMMAND
SEQUENCE 2452.
2452.
COMMAND
SEQUENCE
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 24521 OF S/C RESPONSE. REPORT TO A DECISION MAND SEQUENCE 2453. ANGLE TV MAPPING). DIRECT COMMAND CONTROL EXECUTION EXECUTE
EXECUTION AND STATUS
586
TD÷IH35M
SS
1.
TO EXECUTE COM(FIRST NARROW-
587
TD+IH35M30S
A
1°
SS TO CONTROL EXECUTION SEQUENCE 2453. BY
OF
SS
l.
VOICE DIRECTION DSIF ll OF COMMAND SEQUENCE 2453. SEQUENCE 2653. EXECUTION AND STATUS
588 589
TDeIH36M TD÷ZHOIM
11 SS
I. I°
COMMAND
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2653t OF S/C RESPONSE.
5qO
TD÷2HO2M
SP
io
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 245I (ENGINEERING INTERROGATIDNI. DIRECT COMMAND SP TU CONTROL EXECUTION.OF SEQUENCE 2451.
COM-
591
TD÷2HO2M3OS
A
l.
SP
I.
CONTROL BY VOICE DIRECTION DSIF 11 EXECUTION OF COMMAND SEQUENCE 265l. EXECUTE COMMAND SEQUENCE 2451° EXECUTION AND STATUS
592 593
TDe2HO3M TD+2HO?M
ii SP
I. 1.
REPORT TO A COMPLETION UF .OF COMMAND SEQUENCE 2651t OF SIC RESPONSE.
594
TD+2H25M
SP
1.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2451 (ENGINEERING INTERROGATION). DIRECT SP TO CONTROL EXECUTION
COM-
595
TD+2H25M30S
A
l.
OF V-56
EPD-IBOt
REVISION
1
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
595 596
(CONTINUED| TD+2H25M30S SP I.
COMMAND
SEQUENCE
2451.
CONTROL BY VOICE DIRECTION DSIF It EXECUTION OF COMMAND SEQUENCE 2651. EXECUTE COMMAND SEQUENCE 2451. EXECUTION AND STATUS
597 598
TD÷2H26M TD÷2H32M
11 SP
I. I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2451, OF S/C RESPONSE.
599
TD_2H33M
SS
I.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2454 (SECOND WIDEANGLE TV MAPPINGI. DIRECT COMMAND SS TO CONTROL EXECUTION SEQUENCE 2454.
COM-
600
TD+2H33M30S
A
1.
OF
SS
I.
CONIRDL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2454. EXECUTE COMMAND SEQUENCE 2454. EXECUTION AND STAIUS
601 602
TD÷2H34M TD÷2H55M
1[ SS
I. I.
REPORT TO A COMPLETION OF DF COMMAND SEQUENCE 2454, OF S/C RESPONSE.
603
TD÷2HS6M
SP
1.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2451 (ENGINEERING INTERROGATIDNI. DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 2_51.
W_BV_ v* ............
COM-
604
TD÷2H56M30S
A
I.
OF
SP
io
CONTROL BY _anvr_ nIQ_TlnN DSIF [[ EXECUTION OF COMMAND SEQUENCE 2451. EXECUTE COMMAND SEQUENCE 2651.
605 606
TD+2HSTM TD+3HO3M
|l SP
I. I.
REPORT TO A COMPLETION OF EXECUTION OF COMMAND SEQUENCE 265[t AND STATUS OF S/C RESPONSE. REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2451 (ENGINEERING COMV-57
607
TD÷3H25M
SP
].
EPD-IBOt REVISION I
SECTION V
ITEM TIME OF EVENT STATION
607 608 (CONTINUED) TD÷3H25M30S I. INTERROGATION). DIRECT COMMAND
EVENT
SP TO CONTROL EXECUTION SEQUENCE 245I.
OF
SP
I.
CONTROL BY VOICE DIRECTION DSIF IT EXECUTION OF COMMAND SEQUENCE 2451. EXECUTE COMMAND SEQUENCE 2451. EXECUTION AND STATUS
609 610
TD÷3H26M TD÷3H32M
II SP
I. I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2651, OF S/C RESPONSE.
6II
TD÷3H33M
SS
I.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2455 (SECOND NARROWANGLE TV MAPPING SURVEYI. DIRECT COMMAND SS TO CONTROL EXECUTION SEQUENCE 2455. OF
612
TD÷3H33M30S
A
I.
SS
I.
CONIROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2455.. EXECUTE COMMAND SEQUENCE OF 2455. POST-TOUCH-
613 614
TD÷3H34M TD÷3H45M
II FP
I. I.
REPORT TO DOWN ORBIT GIVE BEGIN
A COMPLETION DETERMINATION. SITE DATA
2. 3. 615 616 TD÷3HSSM TD÷4HO4M FP SS I. I.
LANDING
IO
SPy
SS. (94X).
TRAJECTORY TRAJECTORY
COMPUTATION COMPUTATION.
COMPLETE
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2455, OF S/C RESPONSE.
EXECU|iON AND STATUS
617
TD÷4HOSM
SP
I.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 245[ (ENGINEERING TERROGATION). DIRECT COMMAND SP TO CONTROL EXECUTION SEQUENCE 245I.
COMIN-
618
TD÷4HOSM30S
A
I.
OF
V-58
EPD-I8O,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
618
(CONTINUED)
SP
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2451. EXECUTE COMMAND SEQUENCE 2451. EXECUTION AND STATUS
619 620
TD÷4HO6M TD÷4HI2M
IT SP
I. I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2451, OF SIC RESPONSE.
62I
TD÷4HI3M
SS
I.
REPORT TO A DECISION TO EXECUTE COMMAND SEQUENCE 2456 (THIRD NARROWANGLE TV MAPPING)° DIRECT COMMAND SS TO CONTROL EXECUTION SEQUENCE 2456. OF
622
TD+4HI3M3OS
A
I.
SS
I.
CONTROL BY VOICE DIRECTION DSIF II EXECUTION OF COMMAND SEQUENCE 2456. EXECUTE COMMAND SEQUENCE 2456. EXECUTIUN AND STATUS
623 624
TD+4HI4M TD+4H24M
]I SS
I. I.
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2456, OF S/C RESPONSE.
625
TD÷4H25M
SP
I.
REPORT TO A DECISION TO EXECUTE MAND SEQUENCE 2451 (ENGINEERING INTERROGATION). DIRECT COMMAND CONTROL EXECUTION EXECUTE SP TO CONTROL EXECUTION SEQUENCE 245I. BY
COM-
626
TD+4H25M30S
A
I-
OF
SP
I.
VOICE DIRECTION DSIF II OF COMMAND SEQUENCE 2451. SEQUENCE 2451. EXECUTION AND STATUS
627 628
TD÷4H26M TD÷4H32M
II SP
I. I,
COMMAND
REPORT TO A COMPLETION OF OF COMMAND SEQUENCE 2451, OF SIC RESPONSE. VISIBILITY ENDS.
629
TD+SH
II --NOTES--
1. I.
TV SURVEYS TO AVERAGE 24-HOUR DAY UNTIL THE
12 HOURS DAY/NIGHT
PER TERV-59
EPD-I80,
REVISION
I
SECTION
V
ITEM
TIME
OF
EVENT
STATION
EVENT
629
(CONTINUED|
MINATDR. WILL BE 2.
MORE EXACT USAGE SPECIFIED LATER.
PERIODS
ENGINEERING INTERROGATIONS IO BE PERFORMED EITHER CONTINUOUSLY DR AT HALF-HOUR INTERVALS UNTIL THE DAY/ NIGHT TERMINATOR. MORE EXACT USAGE PERIODS WILL BE SPECIFIED LATER. REPOSITION PANEL. REPOSITION PANEL. REPOSITIDN PANEL. REPOSITION PANEL. REPOSITION PANEL. TV CAMERA REACHED. REPOSITION PANEL. DAY/NIGHT MEAN PLANAR ARRAY AND SOLAR
630
TD÷IOH
51
I.
631
TD+21H
ll
I.
PLANAR
ARRAY
AND
SOLAR
632
TD+36H
51
I.
PLANAR
ARRAY
AND
SOLAR
633
TD÷66H
11
I.
PLANAR
ARRAY
AND
SOLAR
634
TD÷57H
51
1.
PLANAR
ARRAY
AND
SOLAR
635
TD+AIH
SIC
1.
LOW-TEMPERATURE
LIMIT
IS
636
TD÷67H
51
1.
PLANAR
ARRAY
AND
SOLAR
637 638
TD÷TIH ID_lllH SIC
1. I.
TERMINATOR. DEPLETION TIME.
BATTERY
V-60
"EPD-180,
REVISION
1
SECTION
V
GLOSSARY DURING
OF COMMAND STANDARD
SEQUENCES SEQUENCE
OF
REQUIRED EVENTS
MAJOR SEQUENCE
MINOR SEQUENCE C OMMANDS DESC RIP TION
2050
Pre-Sun S/C Preparation Rate Selection 0040 0623 0512 0510 0226 Coast to Commutator Bus Acc. Acc. Amp.
and
Bit
I/Accel. Amp. Off Off No. Off
Off
Basic Aux. Aux. Engrg.
Commutators Commutator
1 On
0041 0237 0217
Initial 4400 Low 33 kc A/D
bps
Selection Index On 4400 bps SCO Off
Modulation A/D Clock SCO Rate
0206
0000
Quantitative
Command
2051 0042 0702
Sun Sun
Acquisition Acquisition Sun Acquisition Mode Mode On
0043
Postmaneuver Selection 0704 0231 Cruise Engrg. Mode
Commutator
4
On No. 4 On
Commutator
0044 0227
Commutator Engrg.
Z Selection Commutator No. 2 On
0045 0230
Commutator Engrg.
3 Selection Commutator No. 3 On
(This
table
continued
on
next
page.
)
V-61
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE 2052
MINOR SEQUENCE
COMMANDS
DESCRIPTION
Coast 0046 0220 0216 0205 4400
Phase
Preparation
(ii00
bps)
to Ii00 bps Change 7. 35 kc, 3.9 kc SCOs On II00 bps Off
33 kc,
7. 35 kc, A/DSCO A/D Clock Rate
0O47 0232 O5O6 0107 01 30 0110
Low
Pwr./C oa st Commutator Engrg. Coast Commutators Phase Commutator High Voltage Power Power Off On Off
Transmitter Transfer Sw.
B Low Filament
Transmitter Off
2055
Coast Phase Sequence/550 0140 0220 0215 0204 0503 High Rate
Bit Rate Reduction from 4400, ii00
to 550 bps Change 3.9 kc A/D
33 kc, 7. 35 kc, SCOs Off 3.9 kc A/DSCO A/D A/D Coast Clock Phase Rate
On Clock 550 bps Rates
2056 0141 0105
High Pwr. Engineering gation (4400 bps, from Xmitter B Filament
Interro550 bps)
Transmitter On
B Filament
Power
0142 0510 0227 (This table continued
Coast Aux.
to Commutator Commutators Commutator page. )
2 Off No. 2 On
Engrg. on next
V-62
•EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE COMMANDS DESCRIPTION
0143 0127 0106 0220
High
Power/550 Transfer Transmitter 33 kc, SCOs 33 A/D kc 7. Off A/D Clock 35 Sw.
to
4400
bps Power Voltage kc A/D
Change
B High B High kc, 3.9
On
0217 0206
SCO Rate
On 4400 bps
0144 0Z31
Commutator Engrg.
4 Selection Commutator No. 4 On
0145 0226
Commutator Engrg.
1 Selection Commutator No. 1 On
2150
Star Two 0146 0124
Verification Rotations)
(Transponder
Off,
Transponder Transponder
Off/DSIF Power
Reacquisitio= Off
0147 0704 0715 0710
Star
Maneuver Cruise Manual Positive Mode Delay Angle
Preparation On Mode On
Maneuver
0240 0711
Roll Roll
0241 OIZO
Select Select
Omni
A Omniantenna A
(This
table
continued
on
next
page.
)
V-63
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR i SEQUENCE
MINOR SEQUENCE
COMMANDS
DESCRIPTION Sun and Sun Star and Mode Star Mode On
0243 0703
0244 0704
Cruise Cruise
Mode Mode On
0245 0123
Transponder Transponder
On/DSIF
Reacquisition On
B Power
2053 0246 0220 0500 0204 0504
Coast High
Phase Rate to
Preparation 137.5 bps 3.9
(137. 5 bps) Change kc, A/D On Rates bps
33 kc, 7. 35 kc, SCOs Off Coast A/D A/D Phase Coast Clock
I A/D Phase Rate
SCO Clock
137.5
0047 0232 0506 0107 0130 0110
Low
Pwr./Coast Engrg. Coast
Commutator Off On Off
Commutators Phase Commutator High Sw.
Transmitter Transfer Transmitter
Voltage Power Power
B Low Filament
Off
2057 0141 0105
High-Power _ation (4400 Xmitter
Engineering bps from
Lnterro137.5, 17.2)
B Filament B Filament Power
Transmitter On
(This
table
continued
on next
page.
)
V-64
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
{CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE 0142
COMMANDS Coast 0510 0227 Aux. Engrg.
DESCRIPTION to Commutator Commutators Commutator 2 Off No. Z On
0247 0127 0106 0502 0217 0206
High
Power/Low Sw.
Rate B High B High A/D SCO Rate On 4400
to 4400 Voltage Voltage Off
bps On On
Transfer Transmitter Coast 33 kc A/D
Phase A/D Clock
SCOs
bps
0144 0231
Commutator Engrg.
4 Selection Commutator No. 4 On
0145 0226
Commutator Engrg.
1 Selection Commutator No. 1 On
2151 0 340 0232
Early Engrg.
Gyro
Speed
Check Off Off
Commutator Commutators
Engrg.
0 341 0220 0221 0 342 0222 0 342 022Z
SCO
to Gyro
Processing 3.9 kc A/D
33 kc, 7. 35 kc, SCOs Off Gyro On Next Gyro Select Next Gyro Select Next Gyro Next Gyro Speed Signal
Processing
Speed
Channel
Speed
Channel
(This table continued
on next page. )
V-65
EPD-180,
REVISION 1
SECTION V
GLOSSARY (CONT'D)
MAJOR SEQUENCE IVIINOR SEQUENCE
COMMANDS
DESCRIPTION
m
0 342 0222
Next
Gyro Select Next Gyro Speed Channel
0 343 0223
Gyro
Processing Speed
Off Signal Processing
Gyro Off
2152
Post-Gyro Check Coast Phase Preparation (I 37. 5 bps) 0 344 0500 0204 0504 1 37. 5 bps Coast A/D A/D Selection Phase Coast Clock I A/D Phase Rate SCO Clock 137. On Rates
5 bps
0 345 O5O6 0107 0130 0110
Low
Pwr. Coast
/Coast Phase
Commutator Commutator High Voltage Power Power Off On Off
Transmitter Transfer Transmitter Sw.
B Low Filament
2154
Late Gyro Return 0341 022O SCO to Gyro
Speed
Check/4400
bps
Processing 3.9 kc A/D
33 kc, 7. 35 kc, SCOs _ Gyro Speed Signal
0221
Processing
On
0 342 0222
Next
Gyro Select Next Gyro Speed Channel
(This
table
continued
on next
page.
)
V-66
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE COMMANDS DESCRIPTION
0 342 0222
Next
Gyro Select Next Gyro Speed Channel
0 342 0222
Next
Gyro Select Next Gyro Speed Channel
0 346 0223 0217
Gyro
Processing Gyro 33 kc Speed A/D
to Signal SCO On
33
kc
SCO Off]
Processing
2155
Midcourse Sequence 0 347 3617 0607 Premidcourse Interlock Pressurize (Helium)
Correction
Preparation
Thrust Command Vernier
Preparation
System
0440 0704
Premidcourse Cruise Quantitative 0710 (if required) Positive Mode
Roll On
Parameters
Angle
Maneuver
0441 0714
Sun
and Sun
Roll and Roll
0442
Premidcourse eters 0702 (if required) Quantitative 0710 (if required) (This table continued on next page. ) Positive Sun Acquisition
Yaw
(Pitch)
Param-
Mode
On
Angle
Maneuver
V-67
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE
C OMMANDS
DESCRIPTION
0443 0713
Yaw
(0444 Yaw
- Pitch) - Pitch)
(0712
0445 0720
Reset Reset
Set
IV Set
Latch IV Outputs
0446 0727
Thrust Flight Power
Phase
Power Thrust Phase
Control On
0447
Strain Gauge/Midcourse Parameters 0521 Propulsion On Inertial Quantitative Strain Mode On
Thrust Gauge Power
0700
2156 3617 0721
Midcourse Interlock Midcourse
Thrust
Execution
Velocity
Correction
2157
Postmidcourse to Coast 0540 0737 0522 Flight Power Propulsion Off Control Off
Spacecraft
Return
Thrus£ Strain Gauge
Phase Power
0541
Postmidcourse ere r s
Yaw
(Pitch)
Param-
(This
table
continued
on
next
page.
) V-68
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE
COMMANDS
DESCRIPTION
0700
Inertial
Mode
On
Quantitative 0710 (if 0443 0713 required) Yaw (0444 Yaw (0712 - Pitch) Pitch) Positive Angle Maneuver
0542
Postmidcourse and 0702 0736 Vernier Sun
Roll Purge
Parameters Termination Mode On Engine Vent
Acquisition
Terminate Quantitative
Vernier
0710
Positive
Angle
Maneuver
0441 0714
Sun
and Sun
Roll and Roll
0243 0703
Sun
and Sun
Star and
Mode Star Mode On
0543
Postmaneuver tion 0704 02Z7 Cruise Engrg. Mode
Commutator
2 Selec-
On No. 2 On
Commutator
0144 0231
Commutator Engrg.
4
Selection No. 4 On
Commutator
2054 0544
Coast 4400/1
Phase I00
Preparation to 17.2 bps
(17.2 Change
bps)
(This
table
continued
on
next
page.
)
V-69
EPD-180,
REVISION 1
SECTION V
GLOSSARY (CONT'D) MAJOR SEQUENCE MINOR SEQUENCE
COMMANDS
DESCRIPTION
0220 0501 0204 0505
33 kc, Coast A/D A/D
7. 35 kc, Phase
3. 9 kc SCO Clock 17.2
SCOs On Rates
Off
II A/D Phase Rate
Coast Clock
hps
0047
0232 0506 0107 0130 0110
Low
Pwr. Engrg. Coast
/Coast
Commutator Off On Off
Commutators Phase Commutator High Sw. B Fil.
Transmitter Transfer Transmitter
Voltage Low Power
Power
Off
2250 0141
0105
High
Power
Before
Star
Verification
Xmitter
B Filament B Filament Power On
Transmitter
0545 0510 0226
Coast Aux.
to Commutator Commutators Commutator
1 Off No. I On
Engrg.
0247
High Power/Low Change 0127
t% 1 t% 6, %2_v
Rate
to 4400
bps
Transfer Transmitter Coast 33 kc A/D
Sw. B
B
High High
Power Voltage Off On
0502 0217 0206
Phase A/D Clock
A/D SCO Rate On
SCOs
4400
bps
(This
table
continued
on
next
page.
)
V-70
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE
COMMANDS
DESCRIPTION
2251
Low-Power gation 0142 0510 0227 Coast Aux. Engrg.
Engineering
Interro-
to Commutator Commutators Commutator
2 Off No. 2 On
0144 0231
Commutator Engrg.
4 Selection Commutator No. 4 On
0145 0226
Commutator Engrg.
1 Selection Commutator No. 1 On
0546 0232 0506
Engrg. Engrg. Coast
to Coast
Commutator Off On
Commutators Phase Commutator
2252 0612
Vernier Vernier Thermal
Thermal
Control 2 On No. On No. On 2
Fuel Tank No. Control Power Oxidizer Control Oxidizer Control Tank Power Tank Power
0615
Vernier Thermal Vernier Thermal
0620
2253 1133
Survey
Canncra Temp. Camera
Warmup Control On
Vidicon Survey
1136
Electronics Temp. Survey Camera
Control
On
(This
table
continued
on
next
page.
)
V-71
EPD-180,
REVISION 1
SECTION V
GLOSSARY (CONT'D)
MAJOR SEQUENCE MINOR SEQUENCE
COMMANDS
DESCRIPTION
2254 0131
Approach Vidicon Approach
Camera
Warmup On
Temp. Control Camera Temp. Camera
0136
Electronics Approach
Control
On
2255
High-Power gation (AMR from 137.5, 0141 0105 Xmitter B
Engineering InterroWarmup - II00 bps 17.2) Filament B Filament Power
Transmitter On
0142 0510 0227
Coast Aux.
to
Commutator Commutators Commutator
2 Off No. 2 On
Engrg.
0547
High Pwr. Change 0127 0106 0502 0216 0205 Transfer
/Low
Rate
to II00
bps
Sw.
B
High
Power Voltage Off On
Transmitter Coast Phase A/D
B High A/D SCO Rate
SCOs On If00
7. 35 kc A/D
Clock
bps
0144 0231
Commutator Engrg.
4 Selection Commutator No. 4 On
0640 0624
AMR
Warmup Heater On
AMR
(This
table
continued
on
next
page.
)
V-72
kPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE 0145
COMMANDS Commutator 0226 Engrg.
DESCRIPTION 1 Selection Commutator No. 1 On
2256
Hi_h-Power gation(ll00 0141 0105 Xmitter
Engineering bps from B Filament
Interro137.5, 17.2)
Transmitter
B Filament
Power
On
0142 0510 0227
Coast Aux.
to Commutator Commutators Commutator
2 Off No.
2 On
Engrg.
0547 0127 0106 0502 0Z16 0205
High Power/Low Change Transfer Transmitter Coast Phase A/D Sw.
Rate B High B High A/D SCO Rate
to
1100 Power
bps
Voltage Off
On
SCOs On 1100 bps
7. 35 kc A/D
Clock
0144 0231
Commutator Engrg.
4 Selection Commutator No. 4 On
0!45 0ZZ6
Commutator Engrg.
1 Selection Commutator No. 1 On
2257 0146 0124
VCXO Xponder
and
VCO Off/DSLF
Frequency Reacquisition Power Off
Check
Transponder
(This
table
continued
on
next
page.
)
V-73
EPD-180,
REVISION
i
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE
COMMANDS
DESCRIPTION
0641 0113
Narrow-Band Narrow-Band
VCXO
Off Off
VCXO
0642
Narrow-Band VCXO, DSIF Reacquisition 0112 0123 Narrow-Band Transponder VCXO B
Xponder
on/
On On
Power
2153
Post-Gyro Preparation 0643 0501 0204 0505 17.2 bps
Check Coast (17.2 bps) Selection Phase II A/D Phase Rate
Phase
Coast A/D A/D
SCO Clock
On Rates
Coast Clock
17.2
bps
0345 0506 0107 0130 0110
Low
Pwr. Coast Transmitter Transfer Transmitter
/Coast Phase
Commutator Commutator High Voltage Power Power Off On Off
Sw.
B Low Filament
2350
Late Return 0 341 0220 SCO
Gyro
Speed
Check/ll00
bps
to
Gyro
Processing 3.9 kc A/D
33 kc, 7. 35 kc, SCOs Off Gyro On Next Gyro Next Gyro Speed
0221
Signal
Processing
0 342 0222
Select
Speed
Channel
(This
table
continued
on
next
page.
)
V-74
_.PD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE 0342
COMMANDS Next 0222 Gyro Select
DESCRIPTION
Next
Gyro
Speed
Channel
0342 0222
Next
Gyro Select Next Gyro Speed Channel
0644 0223 0216
Gyro
Processing Speed A/D
to 7.35 Signal SCO
kc
SCO Off
Gyro
Processing On
7. 35 kc
2351 0044 0227
Planar
Array
Deployment 2 Selection Commutator No. 2 On
Commutator Engrg.
0645 0403
Step
Polar (n Times)
Axis
Plus
0145 0226
Commutator Engrg.
1 Selection Commutator No. 1 On
2352 0646 0704
Terminal Terminal Cruise
Maneuver First Mode Roll On
Preparation Parameters
Quantitative 0710 (if required) Positive Angle Maneuver
0441 0714
Sun and Roll Sun and Roll
(This
table continued
on next page. )
V-75
F.PD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE
COMMANDS
DESCRIPTION
0647 0702 (if required)
Terminal Sun
Yaw Acquisition
(Pitch)
Parameters Mode On
Quantitative 0710 (if required) Positive Angle Maneuver
0443 0713
Yaw
(0444 Yaw
- Pitch) - Pitch)
(0712
0740 0700
Terminal Inertial
Second Mode
Roll On
Parameters
Quantitative (if 0710 required) Positive Angle Maneuver
0Z40 0711
Roll Roll
0741 0700
Inertial Inertial
Mode Mode On
Z353
Preapproach _'_par ation 0742 0116 Xmitter
Telecommunications
B to Planar
Array Array
Transmitter
B to Planar
0743 01Z4 0113 0214
Xponder
/ VCXO/Summing Power VCXO Amplifiers ) Off Off
Amps
Off
Transponder Narrow-Band Summing on next page.
Off
(This
table
continued
V-76
tEPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE
COMMANDS
DESCRIPTION
0744 0213
Frequency-Summing Frequency-Summing On
Amp.
B Amplifier B
0745
II00 to 4400 Selection 0220 0217 0206 0227 33 33 A/D Engrg. kc, kc 7. A/D Clock
bps/Commutator
Z
35
kc, SCO Rate
3.9 On 4400
kc
SCOs
Off
bps No. Z On
Commutator
0746
Approach Off 0135 Temperature Camera
Camera
Temp.
Control
Control
Off Approa
0747 0132 0723 Power Select (if On Approach Thrust Camera Bias
Nominal
required)
2354
First Approach TV Sequence Preparation 1040 0220 0133 Forty-Picture 33 kc, TV
Sequence/Retro
7. 35 kc,
3.9
kc
SCOs
Off
(40 Times, 4 Sec. Apart) Frame Approach Camera 33 kc A/D SCO On
Start
0217
1041 0700
Retro
Parameters Mode On
Inertial
Quantitative
(This
table
continued
on
next
page.
)
V-77
EPD-180,
REVISION 1
SECTION V
GLOSSARY (CONT'D) MAJOR SEQUENCE MINOR SEQUENCE
1042 3617 0724
COMMANDS
DESCRIPTION
Retro
Sequence Interlock Retro
Mode Command
On
Sequence
Mode
On
2355
1043
Final
Approach
Sequence Camera
Ten-Picture TV/Survey Temp. Control Off 0220 0133 33 kc, 7. 35 kc,
3. 9 kc Apart) Camera
SCOs Start
Off
(I0 Times, 4 Sec. Frame Approach 33 kc A/D SCO On
0217 1137
Temperature Camera Vidicon Survey
Control
Off Survey
1134
Temperature Camera
Control
Off
1044 0613
AMR
Pwr.
/Reset
Set
IV
Latch Vernier Control
Vernier Lines Fuel Tank No. Pwr. Off Vernier Oxidizer Control Vernier Oxidizer Control Ajtitude Reset Lines Tank Pwr. Lines Tank Pwr. Marking Set IV
No. E and 2 Thermal
0616
No. No. Off No. No. Off
1 and Vernier 2 Thermal
0621
3 and Vernier 3 Thermal
0625 0720
Radar
Pwr.
On
Output
0446 0727
Thrust Thrust
Phase Phase
Power Power On
(This
table
continued
on
next
page.
)
V-78
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE 1045
COMMANDS
DESCRIPTION
Accelerometer/Strain 0622 Basic On Bus Accelerometer Strain
Gauge
Pwr. Amp. Power On
0521 0511
Propulsion On Aux.
Gauge Amp.
Accelerometer
1046 OZZO 0133
Thirty-Picture
TV Off
33 kc, 7. 35 kc, 3.9 kc SCOs (30 Times, 4 Sec. Apart) Frame Approach Camera 33 kc A/D SCO On
Start
0217
1047 0321
Disable
Battery
Transfer
Logic Logic
Disable
Battery
Transfer
1140 0 322
High
Current On 4 Approach
High-CurrentMode TV Sequence No.
1141 0220 0133 0217
Ten-Picture 33 kc,
TV
Sequence Off
7. 35 kc, 3.9 kc SCOs Start
(I0 Times, 4 Sec. Apart) Frame Approach Camera 33 kc A/D SCO On
1142
AMR Accel. 0626 0220
Enable/Three Channels Altitude
TV
Pictures/
Enable
Marking
Radar Off
33 kc, 7. 35 kc,
3.9 kc SCOs
(This table continued
on next
page. )
V-79
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE
C OMMANDS
DESCRIPTION
0133
(3 Times, 4 Sec. Frame Approach 33 Basic Aux. AMR kc A/D Bus Accel. Heater SCO Accel. On
Apart) Camera
Start
0217 0224 0513 0604
Channels On
On
Channels Off
1143 0225 0514 0220 0133
Two-Picture Basic Aux. 33 kc, Bus Accel.
TV Accel.
Sequence Channels Channels 3.9 kc SCOs Off Off Off
Data
7. 35 kc,
(2 Times, 4 Sec. Frame Approach 33 kc Basic Aux. A/D Bus Accel. SCO Accel. On
Apart)Start Camera
0217 0224 0513
Channels On
On
Channels
1144 0225 0514 0220 0133 0217
Last
TV Bus Accel. Accel. Data Channels Channels 3.9 kc SCOs Camera Off Off Off
Basic Aux. 33 kc, Start 33 kc
7. 35 kc, Frame A/D
Approach SCO On
I145 0117 011Z 0ZZ0 0214
Telecommunications Transmitter Narrow-Band 33 kc, 7. 35 kc, A to
Transfer Planar On kc Off SCOs Off Array
VCXO 3.9
Summing
Amplifiers
(This
table
continued
on
next
page.
)
V-80
EPD-180,
REVISION
1
SECTION
V
GLOSSARY
(CONT'D)
MAJOR SEQUENCE
MINOR SEQUENCE
COMMANDS 0Z07 0211 0216 0205 0230 0515
DESCRIPTION
Presumming Phase-Summing 7. 35 kc A/D Engrg. Touchdown On A/D
Amplifier Amplifier SCO Rate On ll00 bps No. Gauge Gauge
On B On
Clock
Commutator Strain
3 On Pwr. Data
0517
Touchdown Strain Channel s On
2356 0226 3617 0630 3617 0311
Postlanding Engrg. Interlock RADVS Interlock All Flight (Interlocked) Power Off
Operations Commutator No. 1 On
Power
Off
(Interlocked)
Control Approach Strain Strain Gear
Pwr.
Off
0134 0516
Camera Gauge Gauge Power Power
Touchdown Off Propulsion Off Lock Interlock Dump Helium Landing
0522
0636 3617 0610 0323
l
(Interlocked) Mode Off
High-Current
EPD-
180,
REVISION
1
SECTION
VI
SECTION NONSTANDARD
VI OPERATIONS
A.
GENERAL
Section V presents, on a certain prescribed level, the normal, or standard, sequence of events. It is recognized that deviations from this standard will occur; therefore, every effort must be made to define various failure modes in anticipation of such events. Several representative situations are included in this Section with a discussion of the methods by which these situations would be handled operationally. B. NONSTANDARD The nonstandard classified as: Prepared Corrective Nonprepared Corrective encountered. A criticalness Class Class Class Class The classification sequences further of A B C D number is action will be determined at the time these situations are action will be available. PROCEDURE situations which DEVELOPMENT may arise during the course of a mission
can
be
breakdown of the time is considered. Nonstandard, Nonstandard, Nonstandard, Nonstandard, of combinations to
categories
may
be
given
in
which
the
degree
of
prepared, prepared, nonprepared, nonprepared, of failures
noncritical critical noncritical critical which result, o.-!y may occur within the above
is practically restricted to be into set
limitless. those cases normally. the which
As a where
development single failures analysis of of occurrence, studied further. for these referred
of nonstandard exist and telemsuch etc., anticipated has reFault isolatrees
etry is assumed situations, taking sulted in a limited tion trees, are identified Procedures
operating consideration of situations Table numbers VI-I,
Exhaustive probability have been devised and are
listed in by the (NSPs).
have 1 through
been 31
situations. The to as Nonstandard
VI-
1
EPD-180,
REVISION 1
SECTION VI
TABLE
VI-I.
FAULT
ISOLATION
TREES
IDENTIFICATION NUMBER Landing gear mechanism/electrical 3 4 5 6
.
DESCRIPTION mechanism;
TITLE omnidirectional antenna
Centaur Flight Coast Flight One-way Two-way Solar
separation control phase control DSIF DSIF panel coast phase
roll control programmer spacecraft spacecraft acquisition acquisition/T/M lockup
7 8 9 I0 ii
J
/
positioning of battery not in transit energy position
Conservation Solar Sun Solar Star panel
/ /13
IZ
acquisition panel electrical
/14
15 16 17 18 19 ZO Zl ZZ Z3 Z4 Z5 Z7
acquisition array as roll attitude maneuver phase soft-land reference
Planar Prethrust Flight Loss Loss
attitude
control
thrust to
of capability of capability attitude
to hit Moon maneuver
Standard Engineering Power Thermal Preretro Terminal Large Loss
interrogation
management management attitude descent injection of signal power errors from the spacecraft maneuver and descent TV
Z9
30 31
Regulated Battery
supply
VI-
2
EPD-180,
REVISION
1
SECTION
Vl
C.
USE
OF
FAULT
ISOLATION
TREES
The Nonstandard Procedures are to serve as the mechanism of operations control during the analysis of spacecraft failures, within the limitations imposed by the assumption of single faults. SPAC has the primary responsibility for the required interpretation of spacecraft data and determination of command decisions. If the single fault limitation does not hold, SPAC may intermesh certain applicable trees, and use any additional techniques necessary to isolate the faults in order to arrive at a satisfactory recommended course of action. The DSIF will use preprepared command tapes according to Detailed Operating Procedures (DOPs), where necessary, in support of SPAC, as directed by Mission Control. When deviations from the standard sequence occur, and anticipated nonstandard procedures exist, the SFOD will direct SPAC to proceed in accordance with the applicable fault isolation tree. A representative tree is shown in Figure VI-1. It should be noted that command sequences are identified by the sequence number associated with the commands on the nonstandard command tape. Corresponding DOP item numbers are given to allow fast cross-reference between the tree and the DOP, primarily for use by DSIF personnel. Branch result of the are developed plished within D. GENERAL choice within a tree is determined by the conditions existing as a fault and as indicated by the current spacecraft telemetry. All trees so that return to the Standard Sequence of Events may be accoma minimum time. NONSTANDARD OPERATIONS PROCEDURES in nonstandard of the Command spacecraft System situations Alternatives
The execution of commands required will generally be implemented through one described in Section IV. For nonstandard Classes A and will be grouped on preprepared of commands in these situations
mands cution
B, above, the required spacecraft CDC command tapes at the DSIF. will be according to Alternative be formulated and transmitted
comExeNo. 1. at to
the the
For nonstandard Class C, the required commands can SFOF manually, or by means of the SCP/CVT program, DSIF via TTY {Command System Alternative No. Z).
Execution of commands in nonstandard Class D (Nonprepared, Time ical} will be negotiated in the framework of Aiternative No. 3. Comn:ands be entered on the CDC keyboard, as directed, by voice from the SFOF.
Critwill
VI-3
EPD-180,
|
REVISION
1
i
,i I_i
I--i!E
ii;ll_
t
@-t !-_
!': :.i!i!
i
II|I
!
"Li:
'..... ,.,;u
" t!._
il
_il | jii!i
jiilt
ii .
,:
IIi
li:Ll ii
i
!_i.;_;: I l_il
|, ii:
:.i|w_] i]
I'_
lI/
.-o__
,: -i_ ,,
E
;_
_;
;_
]
2_
SECTION
Vl
_E
(
/
ib
_:z _
_-i!-_i_.!
÷,,-_!h,
..._ __|Ll_ "' !} _; I;,W
_-_I_" I
-I1_'1 I I_ I
_
_ " _:_
_t-_l
_l___.-"leal I
o I LI_.__I
i_°
---¢-,._0--4i_t >
;i
_s
8_
FIGURE
VI-1.
NSP-8-S/C-DSIF ACQUISITION/TlVi NONSTANDARD
TWO-WAY LOCKUP PROCEDURES
)
VI-4
EPD-180,
REVISION
1
u
u
_0_0 u=Eu:_
z_,_
-o o _-
-;_
_=
_z uZ
Z_Z>_,_ _z a . _zz_Z Z
v =
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oo
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SECTION
Vl
5
o
_<_
_"
z_
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__
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-$g :u_Z_
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a
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Zu 0 o
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l " _ Z
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5o_g_> uZ_Z-_
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FIGURE
VI-3.
NSP-3, CENTAUR TION NONSTANDARD CEDURES
SEPARAPRO-
VI-6
EPD-180,
REVISION
1
.
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--
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x,
3:
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8
z
u_
o uz =o _
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D_u-
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., ,.o_o.... @
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SECTION
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z
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a++i+
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FIGURE
VI-4.
NSP-7-S/C-DSIF ACQUISITION PROCEDURE
ONE-WAY NONSTANDARD
VI-7
EPD-
180,
REVISION
1
_uu u_
u
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Q_o_
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SECTION
Vl
A
o z z_ o = u o _Z-_ o-_ _ ._.O_ _ o_
go6
_az
_o -_)--z_O z-%'_o_ o_O_ _--e_z _z_
0 _Z_z_O_u
z_
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u_
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3
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o.=_.
.ZO _ .
_z_o oS _
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5
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z_z _O_U _Z _o_0 z_o_
0
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u _ZZ OZ Z_Z
z=N_ £ £zO_ o
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:o
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o_ _z FIGURE VI-5. NSP-9, SOLAR PANEL POSITIONING NONSTANDARD PROCEDURES
VI-8
>
top,
EPD180, REVISION 1
IDENTIFICATION N_P-12 SUN
SEQUENCE AQUP31TION
3174 NONSTANDARD _IIC'.CEDUIE
* YAW
ASS_Ft'IO I. 2. 3.
NS : TWO-WAY CO_UNICATIONS MODE 1,550 liPS ESTABLISHED
t
IS ON ENGINEERING SEQUENCE _,_ SECONDARy SUN SENSOR
REQUIRED ,_ ,_ L 2. 3. 4. 5. I 6. 7• 8.
INSTRUMENTATION SUN LOCK-ON SENSOR SIGNAL CELL SIGNALS ERROR SIGNALS - - - -
MODE J, 2, I, I, 2. C 4, C C, T
COMPOSITE SECOI'.IDARy)UN
_ACECRAFT ACQUIRED RY DSIF AND 5OU_q PANEL 4N TIANSIT POSITION INITIAL P, ONITORING A
PRIMARY SL,'t'_ SENSOR I_ITCH AND yAW GYRO PRIMARy SUN PITCH SOLAR MODE SUN SENSOR SIGNAL
PITCH AND yAW ERROR SIGNALS LOCK-ON SIGNAL
AND YAW GYRO PRECESSION CELL ARRAY VOLTAGE
COMMANDS
-
- - -
2, 2,
C, 4,
T C
I
2_
,.Q0 CO--ND=" I ......
_SUN ACQUISiTJON _DtE QH _
I
OBSERVE: SUN MODE QN SIGNAL (FC-59) ) NOTE: USE El)IT CANNOT MADE IS IF LINE TO 550 SFOF RPS.
F
SUN MO_E INDICATED
ACCOMODATE
SUN
MOD_
"NOT
INDICATED
I
L GYRO ERROR SIGNALS (fC-I6, -17) -8, I i) -9, 10_ 2. SECONDAEY SUN SENSOR CELL SIGNALS (FC-7. 3. PRIMARY SUN SENSOR LOCKON SIGNAL _FC-69) )BSERVE: • • COMPOSITE SUN SENSOR LOCKON SIGNAL (FC-
_41
NO SUN INDICATED
ACQUISITION SUN ACQUISITION
I
CONCLUDE:FAILURE CONTROL PROGRAI, SURSYSTEM DECODER IN FLIGHT vI.MER OR
I
REFER TO FLIGHT NSP-6, CONCLUDE: PGMR, CONT.
INDICATID
SUN
MODE
I
SIGNAL
IFC-59)
FALSE
OBSERVE: GYRO VERIFY , FLIGHT ERROR SIGNALS _FC-10, PROPER PERFORMANCE C_NTROL _7) OF
>
SPACECRAFE AS INDICATED ORSER'¢£: -' 2. COMPOSITE LOCKON PRIMARY SUN SENSOR SIGNAL LOCKON (FC-]I) SIGNAl. NOT MANEUVERING A_IOVE BY THE (FC-69)
SPACECRAFT AS INDICATED
MANEUVERING BY THE ABOVE
OBSERVE:
_.T
LOCKON BY BOTH
INDICATED SIGNALS
:. 2.
COMPOSITE LOCK-ON PRIMARY SUN SENSOR
SIGNAL LOCK-ON
(FC-H) (FC-69)
;I
SIGNAL NO SUN LOCK-ON I AFTER
NO BY
LOCKON EITHER
INDICATED SIGNAL
J RETURN
TO
I
REFER TO NSP 4 FLIGHT
CONTROL .... ONE
COAST
SUN LOCK-ON BOTH SIGNALS
INDIC_ATED _Y WITHIN 12 MINUTES.
12 MINUTES
I
CMD: SEQUENCE NO. I) "ENGINEERING NO. 2ON" 0267 COMMUTATOR I J
I
PITCH AND YAW G_O I_ECESSION & 51) COMMAND RECORDINGS (FC-.50
I
I
I
SEQUENCE CMD: I) NO. 0641 COMMUTATOR NO. I ON" J "ENGINEERING
I
I
PITCH AND YAW (FCGYRO 16, ERROR - 17) SIGNAL RECORDINGS
SPACECRAFT
MANEUVERED
AND
STOPPED
I
OlIS_RV_: RECORDINGS PRIMARY ERROR SUN (FC-5, SENSOR -6) PITCH AND YAW
I
WENT TO A MAXlMU_
/
ERROR
SIGNALS
IF TIME
F
I
ERROR ROLL
SIGNALS AXIS NOT
REMAIN_:D POINTED
CONSTANT TOWARD SUN
INDICATES
)ATA CHANNEL
NO. itFC-I1
,t-c- d,, -_7.
_...69 rC-59 _-50, _P-10 -51
SPACECRAFT MANEUVERING CONTINUOUSLY IN PITCH OR YAW OR OSCILLATING IN YAW I. 2. 3. SECONDARY SUN INTERFEREN_ FAILUlIE: SUN SENSO;( LOGIC FI_M EARTH SHINE
ACQUISITION
I F_OBAELE
/ \
OBSERVE SIGNALS
:SECONDAJty TO VERIFY
SUN
SENSOR
CELL
(FC-7,
,..8,
-9,
- 10) /
THE/v_,NEUVERING
IF TIME MINUTES
FIK_M
INJECTION WITH
IS GREATER LAUNCH DAY).
THAN
120
(VARIES
INTERMITTENT COMPOSITE LOCK-.ON
PROBABLE I. 2. 3. 4. 5. PRI_RY CAUSE: SUN SENSOR _ CHANNEL tAILuEE FAILURE . • PRIMARy PRIMARY EARTH SHINE TELEMETRy CELL FAILURE 3. 4. SUb LO( iI'_TT.?,,"E.'E_'!-r_. _(_ CQMPOS_TE LOCKON SECOND_RY ACQUISITION SUN LOGIC SECONDARY SECONDARY SENSE FAILURE
I
\
CMD:
OBSERVE: /SOLAR ARRAy SPACECRAFT
I SEOOENCE"O.0_ I
I) "ENGINEERING COM, MUTATOR VOLTAGE ROLL AX IS (EP-10) TOWARD TO VERIFY
NO.
2ON"
J
\ OF) /
CMO:
fl SEQUENCE '*ENGrf_
ORIENTATION
i
CMD:
1)
EQOENCE O. i
"ENGINEERING CONUTATOR t_. I ON" SENSOR LOCKON OF SPACECRAFT (FC-69) TO VERIFY ROLL AXIS TOWARD SUN
I
SUN
<
J CMD: I) "ENC SEQUEh
PRIMARy SUN OBSERVE: ORIENTATION
b
LOCK-ON _ldl LE CAUSE: :Otv_SITE _CQUISITION LOCK-ON TELEMETRy FAILURE OBSERVE: ERRO_ PRff_AARySIGNALS SENSOR SUN (EC-5, OK INDICATED BY I_TH PROBABLE CAUSE: I. 2. PRIMARY COMPOSITE SUN SENSOR LOCK-ON SIGNALS ERROR CHANNEL FAILURE LOCK_N INDICATED BY ONE SIGNAL VOLTAGE TOWARD LOW ROLL AXIS NOT SUN PROBABLE CAUSE: I. SECONDARY . • SECONDARY INTERFERENCE SUN ORIENTED SENSOR LOGIC FAILED TELEMETR'
I ?
/
I
TELEMETRY
ihITERMITTENT
SUN SENSOR LOCK-ON FROM EARTH SHINE
l
LOGIC
+
.L
-61
I
.:K -.O N COMPO E: ",ISOR LOCK"ON
S I";'.. TELEMETRy FAILED
N(_. CC*'_POSiTE SENSOR LOCK-ON l. 2.
LOCK "ON _IMARY SUN OK PROBABLE CAUSE: COMPOSITE LOCK-ON LOGIC OR TELEMETRY PRIMARY LOCK-ON CELLOR LOGIC FAILED FAILURE
"_ SENSO_ '_ SENSOR ItOM EARTH
LOCK-ON LOCK-ON _Mt_E
LOGIC FAILED TELEMETRy FA_LED
I
ING 02_7 COMMUTATOR ). NO, 2 ON" I
I
J < I
CMD: CMD:
AY
J
\ VOLTAGE (EPI01 ) f
I
ERING 0641 _10. COMMUTATOR NO. I ON"
J
SEOOEOCE_.O_ i I ORS_RVE: ) I SEOOENO I NO._"
I) "ENGINEERING COMMUTATOR NO. 2 ON" SOLAR ARRAY VOLTAGE (EP-10) "ENGINEERING COMMUTATOR NO. I ON"
l
\ //
VOLTAGE ROLL VOLTAGE SUN NORMAL ROLL AXIS ORIENTED LOCK-ON CELL OR LOGIC TOWARD TELEMETR'T PROBABLE FAILURE: I. PRIMARy SUN SENSOR Z. PRIMARy LOCK-ON AXIS ORIENTED FAILURE:
NORMAL TOWARD SUN ROLL LOCK-ON VOLTAGE AXIS NOT SUN LOW ORIENTED
PROBABLE I.
COMPOSITE SECONDARY SIGNALS
<
I
LOGIC SENSOR
OR TELEMETRY
TOWARD PRORASLE I.
i
LOCK,ON CELL OR LOGIC
OBSERVE:
SUN (FC-7, -8,
CELL AND 10)
CAUSE:
-9,
PRIMARY
ALL FOUR CELLS ON:
ONE
OR J
_RE
/ (I _,?
OESEItV1E: SECONDARY SUN SENSOR CELL C_kAp._r, ITF i(_t"l(,.(_N _i_NAI S GNALS (FeII (FC-7 -8,-9
\
-10)_ •
t
SECTION
VI
lil
INDICATESROLL
AXIS
FOtNTED
TOWARD
SUN I. 2. SECONDARY SUN SUN ACQUISITION INTERFERENCE SENSOil LOGIC EARTH SHINF
LOCK NOT
-.O/_
TELEMETRY RESULT OCCUR UNLESS
3.
FROM
A POSSIBLE FAILURES
MULTIPLE
I
OBSERVE: SIGNALS SECONDARY SPACECRAFT SUN SENSOR CELL TO VERIFY ATTITUDE. (FC-7, -B, -9 -10)} SPA, TO
SEQUEI_ I _D: I) 3) I 4) "INEI 'FOSI "XAW
IF TIME MINUTES
FROM
iNJECTION WITH
IS LESS LAUNCH
THAN DAY)
I_ (VARIES WITH LAUNCH DAY_
(VARIES
I
_OBABLE INTERFERENCE FROM EARTH IHIIGHTNESS f_OILAIILE .. FAILURE: SUN SENSOe LOGIC SECONDARy ACGUISETION
I
,
ERROR SIGF CAUSE: OPERATIOt SIGNAL CONTROL (SPACECRAFT TELEI El
SUN
LOCK-ON
OBTAINED
NO
SUN
LOCK-.ON
SUN
LOCX
-ON
SIGNAL
ORTAINED
WAIT
UNTILII2O
MINUTES
ONE NORMAL) _OBAIILE I. NORMAL ERROR FLIGHT 2.
(
ERROR AND SIGNALS WENT TO A MAXIMUM LOCK-ON PROEAgLE I. 2. 3. 4. 5. NORMAL LOC_-_N PRtMARY CAUSE: LOCK-ON, CIRCUIT SUN ERRORS HAPPENED FAILED. ROLL AXIS FAILED FAILED FAILED SENSOR LOGIC TO NOT BE ZERO POINTED TOWARD SUN 4. BOTH ERROR SIGNALS ALWAYS ZEE RETLIRNED TO VERIFIES ZERO REAL
I
SENSOR
SECONDARY SUN SUN ACQUIS(TION
I
/ OBSERVE: SECONDAR'_SUN SENSOR CELL = SIG .... (FC -7, -8 ...... \ O) /
DOES
NOT
MANEUV
I ; - SEC6-N_I_y'stJ
N
SENSOR
I
SUN IF SPACECRAFT MANEUVERING CONTINUOUSLY:
LOCK-ON OBTAINED
NO
SUN
LOCK-ON ORTAiNED ALL 4 CELLS ON PROEABLE I. 2. FAILURE: SENSOR TELE/_ETRY
I
!CRAFT PROIABLY ATTEMPTING WHEN TWO OR MORE
I
CELLS A_E ILLUMINATED
SIGNAL
SIGNAL
I
SEQUENCE CMD: IVE ANGLE MANEUVER' (UNTIL TWO OR MORE )i CELLS AJtE ILLU_INAFED) IAL MODE ON" t)
I
NO. 1242 MODE ON" "INERTIAL
'v
(
NOT
FAILURES
A POSSllE OCCI_
RESULT
UNLESS
MULTIPLE
)
P_IM_eJ{y SUN INTERMITTENT
OESERVE: SECONDARy SUN ERROR
F_IMARy
SUN ;FC-5
SENSOR
SIGNALS
& -6)
F
l
MINUTES ERROR SIGNALS AND RETURNED WENT TO A MAXIMU_ TO ZERO o
+
ERR'OR SIGNA r CONSTANT CONCLUDE: PRIMARy SENSC_ SUN FAILURE
F_LE
1
SUN
ACQUISITION'MANEUVERS COi_MAND
IN
TI_E _ESENCE
OF EARTH
ERIGHTNESS RESULT
INTERFERENCE COMMAND
TABLE
2 SUN
ACQUISITION
_OCEI[_
I
CONCLUDE: TELEMETRy FAILURE
C LL ON
CO_41_AND
G "tl_O SIGNALS ERROR
PRECESSION AND GYRO SIGNALS.
,,_ _o, _EENS'_
I A A C I +Y +Y i CANDDON A AND l ON C OR A AND 3 A C I +y• D L_oES 4 A B AND A AND LO 5 6 A C I -L_ ÷Y g GOES OFF OFF CON D ON A GOES B ON -.F" OFF
INDICATE
I
PROCEED WITH USING MANUAL SECONDAIEY MISSION MODE KEEP AXIS AND SUN SENSOR
_
LO
tO
CONTINUOUS LO
÷ YAW
CELL CELL CELL
A GC D GC C AN
2
_o ND_o'_ _
LO
CELL SIGNALS TO SPACECRAFT ROLL POINTED AT SUN
I
:,_ -T
_
--_
_o
LO LO CELL B GO C AW OSCILLATIONS CELL B GO
C AND D ON I OR D GOES C AND A AND DON R ON
OFF
LO
co
LO
CELL l ON LO CELL CELL ONTINUOUS PITCH CELL
A AND
7
C
-Y
B AN] A AN B ANI
g
C
I
-Y*
LO C GOES in A GOES A AND OFF D ON C ON OFF jLO
9
A
J LO
÷y• C D -_
J
CELL ON COMI_AND _ROBADL
10
|
AND
D(_'-ON J_AIN_D NONE D &T UNLESS MULTIPL_ C • WHEN SUN LOCK-ON SIGNAL APPEARS gfi B B A A NSP SER. 12 A A A A D CC D E B C C C C D D D SEE NSP +YAW -YAW - PITCH" - YAW .... -YAW" - * YAW ÷ YAW .... - yAW" * PITCH • 28 .OGIC .OGIC - :ELL .OGtC .OGtC :ELL A O .OGIC :ELL O A
SUN SEQUENCE NO. 0046 "000g" MODE ON"
ACQUISITION
NONSTANDARD
_OCEDURE DATE: NUMIIER: IDENT.
P
,_L ALWAYS ZERO (ONE ONE ERROR SIGNAL NOT ZERO (ONE NOILMAL)
CMD:
1) 2)
QUANTITY COMMAND "SUN ACQUISITION
3174
•
I
rtRY HAPIqENED TO OUTPUT FAILED liE ZERO) FeOlU_ELE CAUSE: 1. BIAS IN FLIGHT 2. FAILED 3. 4. 5. PALLED (SPACECRAFT 6. BIAS IN CONTROL TELEMETRY PRIMARY SUN FAILED USE THE FOLLOWING SEQUENCE OF COMMANDS, YAW) BUT ONLY CALLED THE OUT
IIMA_y SUN SENSOR _"TRONICS FAILED f_NOt MANEUVER)
TELEMETRY FAILED THAT CHANNEL OF SENSOR FAILED.
FLIGHT CONTROL ELECTRONICS (SPACECRAFT DOES NOT/_kNEL_) FLIGHT CONTROL OOES LOGIC NOT FAILURE MANE_) (SPACECIU_FT
ONE MANEUVER COMMAND (ROLL, IN THE "COMMAND" COLU/_N OF
PITCH, OR THE TABLE.
!
[FC-7,-10) -8, -9,
TELEMETRY
I
INTERMITTENT
u_
LUL_
P_RIUD SUN WITH
_ONCLUDt: ERROR / USING CHANNEL MANUAL FAILED MODE TO
PRIMARY PROCEED
SENSOR MtSSI_N SUN ROLL
I
AND SECONDARY KEEP SPACECItAFT
SENSOR CELL AXIS POINTED
SIGNALS AT SUN
®
ONE OR I. . • MORE CELLS CAUSE: FROM EARTH SHINE PAILL_E OFF PROBABLE _NTERFERENCE SECONDARY ACQUISITION SUN SENSOR LOGIC
I
f .
RE,
SPACECRAFT
_NEUVERI_C
WHEN
CELL
J P_OBABLE J FAILUQE
GOES OFF COM/_AND S ON S ON AND AND OFF, OFF, BOFF B OFF A, D, A, D, II GOES ON AND OFF B, C, R, C, B, C, A ON A OFF B, B, A, C GOES ON AND OFF, DON DOFF AND OFF, BOPF _ PITCH - PITCH + PITCH PITCH • e • • • •
I
CELL
B
I CELL C J LOGIC I LOGIC
+ PITCH -PITCH
I LOGIC J LOGIC J CELL I CELL A D
S ON •_ ON ON ON
AND AND AND AND ON ON
OFF, OFF, OFF, OFF, AND AND
A OFF D OFF A ON D ON OFF, OFF,
+ PITCH e - PITCH"
÷ P_TCH e J LOGIC - PITCH • I LOGIC yAW e YAW" * YAW • w e J CELL A J LOGIC J J I j LOGIC CELLD LOGIC LGGIC
C GOES C GOES
C,-yAW !C,-yAW !_n, _y_._t_
CGOESONANDOFF, I D GOES ON
r SPACECRAFT ° IF AhK)THER *
NOT
MANEUVERING
CELL
IF CELL GOES OFF RETURN TO ORIGINAL ATTITU0_ THEN COMMAND
-PITCH ° . PITCH• _ITCH o
PITCH"
SUN-MODE SUN-MODE
: ,_TCH.+ PITCH •
I
• RETURN POINT 1"O
LOCK-ON
SIGNAL
OK
ALL
4 CELLS
ON.
LOCK-ON ONE CELL
SIGNAL OK NOT ON _. 2. C_LL HAS FAILED GROSS MISALIGNM CAUSE: IS OUT OTHER OF
J POSSIBLE RECORD ALIGNMENT SUN WHICH CELL FAILED OR ON
FOR
REFERENCE
ACQUISITIONS
I
SPACECRAFT INDICATED
NOT
MANEUVERING
AS
SPACECRAFT INDICATED
MANEUVERING BY AIIOVE
AS
BY ABOVE
+
IF POINT WHILE IOE HAS SPACECRAFT _EEN REACHED _RE MANEUVERS=
1
WHILE ON"
I
SPACECRAFT MAN
4
"SUN ACC_
I
SPACECRAFT
"°+°+°"+ +_°+ II .... + +
CMD: 1) "CRUISE/vIODE E'_T MANEUVERING SPACECRAFT MANEUVERING NOT A POSSIBLE RESULT UNLESS MULTIPLE FAILURES OCCUR
I
L
i
IF POINT I IA HAS BE:EN PERFORMED I_FORE IF POINT I IA HAS NOT BEEN PERFC_MED g_FORE,
I %Y"Y 'o
I
RETURN POINT TO
LOCKON_IGNAL
OFF
ALL
4 CEUiS
m
ON RESULT UNLESS
,
NOT
A POSSIBLE
MULTIPLE
FAILL,kRE S 0 CCUR
,/'T;
V
_FC_RE
SEO_J_t'K_ C3_D: I) "I_OSITIVE
NO.
0360 M,ANEUVER _
ANGLE
1
"N REACHED
I
3.0046 _VA'IA ;ITION N D "00(_" MODE ON" ( OI_RVE: . SECONDARY 2. COMFOSITE
Y
SUN SENSOR CELL LOC¢ ..ON SIGNAL S GNALS IFC. i1 ' {PC-7 -B, ...... )_
A
IF tF AS SPACECIAFT INDICATED MANEUVERS bY AIlOVE, AS COMMANDED,
SPACECRAFT
DOES AS
NOT
MANEUVER
AS
COMMANDED,
INDICATED
BY ABOVE,
I
REFER TO ATTITUDE
I
NSP-20, STANOA.RO MANEUVER,
PITCH ONE OR MORE CELLS OFF tF ALL 4 CELLS ON NOT
ERRO(_R SIGNAL ZERO
I
PROBABLE FAILURE: L SECON_y SUN 2. 3. SUN ACQUISITION CIRCUIT LOCK-ON PROI_RLE SENSOR LOGIC F_qLED SEQUENCE C_D: 11 2) 3) 4) 5) 6) "INERTIAL "MANUAL "YAW" I 2 NOItlWAL PRtlMA_qy CAUSE SUN
I
LOCK-ON SENSOR FAILED
I
NO. 0362 ON" MODE SEQUENCE ON" CLAD: I) 3) 3) 4) S) ON" 6) "INERTIAL "MANUAL "FITCH" MODE DELAy FO_ 5 SEC. '*POSITIVE ANGLE MANEUVER" "YAW" FOR 5 SEC MODE " INERTIAL
I
NO. 0363 MODE DELAY FOE ON" MODE CMD: ON" SEQUENCE I) 2) 3) 4) 5) 6) "INERTIAL "MANUAL "YAW" FC "POSITIVE "yAw" FC "INERTIAl t 5 SEC MODE ON"
"IwCISITIVIE ANGLE MANEUVER" "PITCH" FOR 5 SEC *'INERTIAL
I
OBSERVE: DETERMINE ERIMARY IF LOOP SUN CLOSED SENSOR IS YAW (FC-6) ERROR SIGNAL TO
I 1 /
_. OBSERVE: TH_ _O DETEL_INE CORRES_ND|NG IF THE LOOP P_lhe_RY SUN SENSOR IS CLOSED IFC -5 OR -6_ ERI_OR !
A,
SIGNAL
INCREASES
SIGNAL
REMAINS
ZERO
1
PROBABLE I. 2. PRIMARY CAUSES: SUN SPACECRAFT
SIGNAL
INCREASES
I
SENSOR FAILED MANEUVER INDICATES L_F NOT /
I
CLOSED LOCK-ON OK
I. 2. 4.
ERROR SIGNAL THAT CHANNEL FLIGHT CONTROL
TELEMETRY Of PRIMA LOGIC
DIID
ET
NG_
J
dO|SERVE:, O|SERVE: CELL SECONDA=RY (FC-7, -8, SUN -9, SENSOR -10)
YAW
.GYRO(FC-17)EJUIO_ SIGNAL
RECORDI
SIGNALS
IF ALL
4 CELLS ON VERIFIES: . •
SENSOR
OK
SECONDARY NO SENSOR
SUN SENSOR MISALIGNMENT
OK
t
tf ONE CELL NOT ON CAUSE: CELLHAS POSSIBLE i. THAT 2. GROSS FAILED MISALIGNMENT MAINTAIN OF ALIGNI_ENT FOR
SIGNAL
V_I_D DID MANEUVER SIGNAL REMA} f_
SPACECRAFT PROIABL_ PRIMARY SENSOR
CAUSE: SUN FAILED OF SPACECRAFT
SPACECRAFT
DI[
I
RECORD WHICH REFERENCE ON CELL HAS FAILED OR IS OUT OTHER SUN ACQUISITIONS
REFER TO FLIGHT C(
I ORIENTATION TOWARD USING
ROLL AXIS MANEUVERS SENSOR
SUN BY MANUAL SECONDARY SUN
I
CELL
SIGNAILS REFER TO ROINT
Y
ERROR SIGNAL f_)T ZERO INITIALLY BUT GOES TO ZERO
J i
4
OUTPUT FAILED INDICATES ORIENTATIO_ MANEUVER F U_
I
INDICATES TELEMETRY ERROR CHANNEL OK
I
I
CMD: j
1) "INEIIIAL _¢-,,autlr, lc¢
MODE ON" Nu. iz_1,¢
j
_D_, ,,_DELAY_DEON" _._O_.__S.*_,NOLEMA_=0'
_D_
•0362
ON" MODE ON" CMD: ON"
SEQUENCE 1) 2) 3) 4) 5) 6) "INERTIAL "MANUAL "PITCH" "POSITIVE "PITCH" "INERTIAL
NO.
0363 ON" _DE ON" CAA_:
SEQUENCE I) 2) 3) 4) 5) 6) _NEETIAL "MANUAL
NO.
0362 ON" MODE ON" ONE OF THE FOLLOWING:
DELAy
MODE DELAY
MODE DELAY
t 5 SEC. ANGLE MANEUVER" i MODE
FOR 5 SEC ANGLE MANEUVER" FOR S SEC. MODE ON"
"YAW _ FOR 5 SEC "POSITIVE ANGLE
MANEUVEE"
"yAW" FC_ 5 SEC "INER1"IAL MODE ON"
I
Ct_D: t) "_LL" C_D: I)
AND
ONLY
i (, DEE, LOO L ,_ ,;
"PITCH
_
'
t
NOT
'VARy
SIGNAL
VAriES
_UTPUT SUN
FAILED SENSOR DID F_dLED NOT MANEUVER) I. 2. LOOP CLOSED BUT BIAS
I
IN FLIGHT CONTROL OR TM LOO_'IIDPEN
_PACECRAFT
I
SEQUENC_ NO. 0C46 "0000" MODE ON" 11 QUANTIFY COMMAND 2) "SU_ ACQUISITION
u._eCO_0tNG T_
ANEUVERED (FC16 17)
\
/
CMD:
i
OBSB_VE SIGNAL PRIR_ARY SUN SENSOR [FC-5 ERROI RECORDINGS t -6_
5
/
SPACECRAFT
DID
SFACECEAFT
DID
MANEUVER
SIGNAL
REMAINS
CONSTANT LOOP OPEN
SIGNAL
RETUtRNS
TO
ORIGINAL
VALUE
CONCLUSION
1
NOt NSI'-4 FLIGHT CONTROL j _AINTAIN TOWARD ORIENTATION SUN BY MANUAL OF SPACECRAFT ROLL AXIS PROCEED COAST PHASE NOT REF_ MANEUVER TO NSp-4,
LOOP CLOSED CONTROL OR
IMAS IN TM
FLIGHT
I
WITH IN MISSION TM. CHECK A_SIJ_ING THIS LATER CANOPtJ'_ THAT BY BIAS IS PERFORMING V_IFICATION IN
i
IV, ANEUVIERS
CMD: E
I)
2) "SUN SEQUENCE
ALLOW SETTLING PRIVY
_ANTII'Y
CO.AND ACQUISITION NO. 0046 _klNUTE SENSOR
"_" EAODE
ON*
ONE TN. SUN
[:RBOR THE
CHANNEL SHOULD SMALL PE_TUI_IATK)N
NULL
)
ERROR SIGNAL REA4AINS ZERO
I
LU_E OF OF T_AT CHANNEL° ROLL SUN AXIS SENSOR MAINTAIN TOWARD CELL SUN BY MANUAL SIGNALS SPACECRAFT SECOND_'_Y
,
I
;2.
_:
I)"YAW"
__J
FIGURE
VI-6.
NSP-IZ SUN NONSTANDARD
ACQUISITION PROCEDURE
VI-9
EPD-180,
REVISION I
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u
u
I
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i,i
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I
SECTION
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zzg=_|
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FIGURE
VI-7.
NSP-13, SOLAR ELECTRICAL ARD PROCEDURE
PANEL NONSTAND-
Vl-lO
t
EPD-180,
REVISION
1
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