Docstoc

Mars Exploration Group “MarsX”

Document Sample
Mars Exploration Group “MarsX” Powered By Docstoc
					Mars
          ploration Group




               InDRA
In-situ Diagnostic of Regional Atmosphere
Mars
                 Overview
 Overview
 Science                        • What is Indra?
  Objectives
  MEP Relationship                    – The Hindu god of thunder and rain
 Baseline Mission
  Launch                              – A great warrior, a symbol of courage and
  Cruise Stage
  Critical Events
                                        strength
  Separation
  Aeroshell                                                   NASA
  Landing Site
  Landing Events     • Mars Exploration              Science Mission Directorate

  Footprints
  Lander               Group                         Principle Investigator
  Communications
  Power                                              Project Management
 Risk Mitigation
 Descope Options                                       Ryan Solomon
 Schedule
 Cost                                   Project Systems
 Summary
                                          Engineering
 Questions
                                         Chris Tanner

                             Science Payload           Spacecraft Flight                 Mission
                           Systems Engineering       Systems Engineering           Systems Engineering
                               Cissie Ogle                Julie Sapp               Jonathan Skolrood

                                                                                                8 July 2011
Mars
                 Science Objectives
 Overview            •   “Follow the water…” Super!
 Science
  Objectives
                     •   “Follow the carbon…” Fabulous!
  MEP Relationship   •   BIG hole in Mars science
 Baseline Mission
  Launch
  Cruise Stage       •   Don’t follow – LEAD science
  Critical Events    •   Climate Investigations
  Separation
  Aeroshell               –   Determine long-term climate variations over a region
  Landing Site            –   Validate circulation models by investigating Martian atmospheric
  Landing Events              photochemistry
  Footprints              –   Track diurnal changes in atmospheric composition
  Lander
                          –   Profile surface-atmosphere interactions
  Communications
  Power              •   Geological Investigations
 Risk Mitigation          –   Determine absorption characteristics of Martian interior
 Descope Options
 Schedule            •   Human Exploration Investigations
 Cost                     –   Determine surface radiation environment
 Summary
 Questions
                     “Under the current NASA Mars Exploration Program, the only avenue
                        for surface meteorology experiments is through the Mars Scout
                        program…”



                                                                                                 8 July 2011
Mars
                                 Traceability
                 Instrumentation Traceability
 Overview
 Science              Science                                Measurement
                                                                                        Baseline
                                                                                                               Baseline     Baseline Instrument
  Objectives                     Science Rationale                                    Measurement
                     Objective                                Objective                                         Inst.         Requirement(s)
                                                                                     Requirement(s)
  MEP Relationship
 Baseline Mission                                                                     Orthogonal wind                         140-350 K (±0.1K)
  Launch                         Determine circulation    In-situ meteorological       measurements                          2-12 mbar (±4 mbar)
                        1                                                                                        EMS
                                   patterns on Mars           measurements           Proper instrument                      0 to 80 m/s (±0.2 m/s)
  Cruise Stage                                                                            spacing                             0-100% RH (±1%)
  Critical Events
  Separation                      Determine surface       In-situ determination     Measurements of UV                         200-400 nm (8 bit
                        2                                                                                        EMS
                                      radiation             of daily radiation           spectra                                   precision)
  Aeroshell
  Landing Site                   Characterize variation
                                                          In-situ measurement
                                                                                   Opacity measurement
                                                                                                                            Optical filters @ 440 nm
  Landing Events        3           of atmospheric                                  twice daily - Sun on        Pancam
                                                             of optical depth                                                     and 880 nm
                                        opacity                                    horizon, Sun at peak
  Footprints
  Lander                          Determine surface-
                                                          Relate atmosphere to        360o stereoscopic                      360o range of motion
  Communications        4            atmosphere                                                                 Pancam
                                                           surrounding surface       image of landscape                         Two cameras
                                     interactions
  Power
 Risk Mitigation         5
                                  Hydrogen's role in
                                                           In-situ measurement
                                                                                    Mass spectra of OH,
                                                                                                                             Mass range of at least
 Descope Options                    atmospheric                                     H2O2, H2O, CO, CO2,         GC/MS
                      Descope                             photochemical species                                                   16-48 amu
                                   photochemistry                                        O, and O3
 Schedule
 Cost                               Track seasonal
                                                          Measurement of noble
                                                                                   Direct measurement of
 Summary                 6            changes in                                          noble gas                         Mass range to at least 2-
                                                            gases and O, N, C,                                  GC/MS
                      Descope        atmospheric                                     concentrations and                            131 amu
 Questions                           composition
                                                           and H isotope ratios
                                                                                        isotope ratios
                                 Determine absorption                                Broadband sensors
                         7                                In-situ measurement                                     3-axis
                                   characteristics of                              Greater sensitivity than                      0.05 to 100 Hz
                      Descope                               of seismic activity                               Seismometer
                                    Martian interior                                Viking seismometers




                                                                                                                                  8 July 2011
Mars
               Relationship to MEP Roadmap
 Overview
                                    1996                                   2001                                    2005
 Science
  Objectives
  MEP Relationship
 Baseline Mission
  Launch
  Cruise Stage
  Critical Events
  Separation             Mars Global Surveyor                         Mars Odyssey                  Mars Reconnaissance Orbiter
  Aeroshell            Studying weather and climate, in        Measuring mineral and subsurface      Will study atmospheric transport of
                     addition to role of water and dust and     water distribution as well as the   dust and water and help characterize
  Landing Site
                           composition of surface and         radiation environment around Mars.              climate variability.
  Landing Events                  atmosphere.
  Footprints
  Lander                            2007                                   2009                                    2011
  Communications
  Power
 Risk Mitigation
 Descope Options
 Schedule
 Cost
 Summary
 Questions
                                  Phoenix                     Mobile Science Laboratory                 In-situ Diagnostic of
                      First weather station in Mars polar      Will analyze soil/rock samples for       Regional Atmosphere
                                    region.                   organic compounds and search for       First Martian meteorological station.
                                                              subsurface water. Meteorological       Will fully characterize weather over
                                                                    package for basic climate                      large area.
                                                                        measurements.


                                                                                                                          8 July 2011
Mars
                 Baseline Definition
 Overview
 Science             • Platform
  Objectives
  MEP Relationship      – 3 independent landers
 Baseline Mission
  Launch                – Triangular configuration
  Cruise Stage
  Critical Events       – ~1000 km separation distance
  Separation
  Aeroshell
  Landing Site
                     • Duration
  Landing Events        – One Martian year (Two Earth years)
  Footprints
  Lander
  Communications
                     • Location
  Power
 Risk Mitigation
                        – Elysium Region and Utopia Basin
 Descope Options
 Schedule            • Instruments:
 Cost
 Summary                – Environmental Monitoring System (EMS)
 Questions
                        – Stereoscopic Pancam
                        – Miniature Gas Chromatograph / Mass
                          Spectrometer
                        – 3-Axis VBB Seismometer
                                                                  8 July 2011
Mars
                 Launch
 Overview            •                     Launch
 Science                                   –   Vehicle: Delta II 7925H
  Objectives
  MEP Relationship                         –   Window: 10 Oct 2011 – 11 Nov 2011
 Baseline Mission
  Launch
                                           –   Optimum Date: 7 Nov 2011
  Cruise Stage                             –   Optimum C3: 9 km2/s2
  Critical Events
  Separation         •                     Arrival
  Aeroshell
  Landing Site                             –   Window: 10 Aug 2012 – 21 Oct 2012
  Landing Events                           –   Optimum Date: 22 Aug 2012
  Footprints
  Lander                                   –   Arrival C3: 8 km2/s2
  Communications                          14                                               40%
  Power
                                          12                                               35%
 Risk Mitigation




                                                                                                 Launch Mass Margin
                     C3 Energy (km2/s2)




 Descope Options                          10                                               30%
 Schedule
                                           8                                               25%
 Cost
 Summary                                   6                                               20%
 Questions
                                           4                          Launch C3            15%
                                                                      Arrival C3
                                           2                          Launch Mass Margin   10%

                                           0                                               5%
                           11 011

                           11 011

                           11 011

                           11 011

                                      1
                                      1

                                      1

                                      1

                                      1

                             /2 11

                                      1

                              /1 1




                                      1
                                    11
                          11 201
                          10 201

                          10 201

                          10 201

                          10 201



                          10 201

                                    1




                          11 201
                                 20



                                 20




                                 20
                                /2

                                /2

                                /2

                                /2

                                /
                               8/

                               0/

                               2/

                               4/

                               6/

                               8/

                               0/




                               1/

                               3/
                              /3

                              /5

                              /7

                              /9
                             /1

                             /2

                             /2

                             /2

                             /2



                             /3




                             /1

                             /1
                           11
                     10




                          10




                                                        Launch Date                                                   8 July 2011
Mars
                 Cruise Stage                   Subsystem          CBE
                                                                                  30%
                                                                                                    Total
                                                                               Contingency
                                           Payload (Landers x3)                                    686.3 kg

                     • 3-Axis Stabilized
 Overview                                  Propulsion              47.7   kg         11.9   kg      59.7 kg
 Science                                   ADCS                    19.7   kg          3.0   kg      22.6 kg
  Objectives                               Communications          16.1   kg          4.0   kg      20.1 kg
  MEP Relationship
 Baseline Mission    • Bi-propellant       C&DH
                                           Power
                                                                    5.0
                                                                    7.4
                                                                          kg
                                                                          kg
                                                                                      1.3
                                                                                      1.9
                                                                                            kg
                                                                                            kg
                                                                                                     6.3 kg
                                                                                                     9.3 kg
  Launch
  Cruise Stage
  Critical Events
                     • Redundant ADS       Thermal
                                           Structures/Mechanisms
                                                                    1.0
                                                                   35.7
                                                                          kg
                                                                          kg
                                                                                      0.3
                                                                                      8.9
                                                                                            kg
                                                                                            kg
                                                                                                     1.3 kg
                                                                                                    44.6 kg
                                           Total                                                   850.1 kg
  Separation
  Aeroshell          • Articulated HDR     Propellant
                                           Max Boosted Total
                                                                                                    81.0 kg
                                                                                                  949.8 kg
  Landing Site
  Landing Events       Antenna             Optimum Margin                                            35%
  Footprints
  Lander
  Communications     • UHF Relay
  Power
 Risk Mitigation       Capabilities w/
 Descope Options
 Schedule              Landers
 Cost
 Summary
 Questions
                     • >77% DV Margin



                                                                                                 8 July 2011
Mars
                 Critical Events
 Overview                                                               Lander Sep Sequence - EI
 Science                                                                      T-56 hours
  Objectives
  MEP Relationship
 Baseline Mission
  Launch
  Cruise Stage
  Critical Events
  Separation
  Aeroshell
  Landing Site              Transfer Duration: 289 days
  Landing Events            Vehicle: 3-axis stabilized cruise
  Footprints                         DV = 250 m/s budgeted for trajectory augmentation
  Lander
                                     Comm = 40 bps for command and telemetry
  Communications
  Power
 Risk Mitigation
 Descope Options         Launch: 7 November 2011
 Schedule                Vehicle: Delta II 7952H             Arrival: 22 August 2012
 Cost                    Departure C3 = 9 km2/s2             Arrival C3 = 8 km2/s2
 Summary
 Questions




                                                                                         8 July 2011
Mars
                 Separation Sequence
 Overview
 Science
                     1                Deceleration
  Objectives                          DV = 35 m/s
  MEP Relationship
 Baseline Mission
  Launch
                                                       3
  Cruise Stage
  Critical Events            Plane Change
  Separation                   Di = < 1o
  Aeroshell
  Landing Site
  Landing Events
  Footprints
  Lander
  Communications
  Power
 Risk Mitigation
 Descope Options     2
 Schedule
 Cost
 Summary
                                 Plane Change
 Questions                         Di = < 1o


                                            Deceleration
                                            DV = 30 m/s
                                                           8 July 2011
Mars
                 Aeroshell
                     • 72% Battery Power Margin
 Overview
 Science
  Objectives
  MEP Relationship      – Single-string fault tolerant
 Baseline Mission
  Launch
  Cruise Stage
                        – Can support well over 56-hrs of autonomous operation
  Critical Events                                   Backshell        Radiators
  Separation                     Parachute Mortar    Height 0.48 m    Area 0.3 m2
  Aeroshell                       Diameter 0.1 m     Mass 47 kg       Mass 1.0 kg
  Landing Site                    Length 0.3 m
                                  Mass 3.3 kg                                       Radar Altimeter
  Landing Events                                                                     Mass 1.4 kg
  Footprints                                                                         Power 16 W
  Lander                      Accelerometers
  Communications               Mass 71 g                                                Cold-Gas Thrusters
  Power                        Power 480 mW                                              Thrust 3.6 N
 Risk Mitigation
                                                                                         DV 0.4 m/s
 Descope Options
 Schedule              RAD Rockets
                                                                                           Heatshield
 Cost                   Thrust 3969 N
                                                                                            Diameter 1.33 m
 Summary                Burn Time 1.1 sec
                                                                                            Nose Radius 0.33 m
 Questions              Mass 5.1 kg
                                                                                            Mass 37 kg

                         Li-Ion Batteries
                          Capacity 1034 Wh
                          Mass 8.5 kg



                                                                                                             8 July 2011
Mars
                Landing Site
                    • Landing Site: Elysium
Overview
Science
 Objectives
 MEP Relationship
Baseline Mission
 Launch                               Phoenix                                                Viking 2
 Cruise Stage                  (65-70oN, 100-140oW)                                       (48oN, 134oE)
 Critical Events
 Separation
 Aeroshell                                                     Pathfinder
                               Viking 1
 Landing Site                                               (19.5oN, 32.8oW)
                            (22.5oN, 50oW)
 Landing Events
 Footprints
 Lander
 Communications
 Power                                                                       InDRA
                                                MER-B
Risk Mitigation                                                          (~20oN, ~104oE)
                                             (2oS,354oE)
Descope Options                                                                                          MER-A
Schedule                                                                                             (14.6oS, 175oE)
Cost
Summary
Questions




                               -Courtesy of the Institute for Space Sensor Technology and Planetary Exploration, DLR, Berlin


                                                                                                          8 July 2011
Mars
                 Landing Events
 Overview            •    Heritage entry architecture reduces both risk and cost
 Science
  Objectives             Atmospheric Interface: Alt = 125 km, V = 5671 m/s, Landing T-9.7 min
  MEP Relationship
 Baseline Mission             Peak Heating: Q = 95 W/cm2, Alt = 92 km, Landing T-9.4 min
  Launch                      Peak Loads: n = -11.6 G’s, Alt = 73 km, Landing T-9.2 min
  Cruise Stage                   Parachute Deployment: q = 701 N/m2, Alt = 39.8 km, Landing T-7.8 min
  Critical Events
  Separation                            Heatshield Separation: V = 133.2 m/s (0.60 Mach), Alt = 31.8 km, Landing T-7.5 min
  Aeroshell
  Landing Site
  Landing Events
  Footprints
                                              Lander Separation / Bridle Deployment: Alt = 17.5 km, Landing T-7.0 min
  Lander
                                                    Ground Radar Acquisition: Alt = 2.44 km, Landing T-50.4 sec
  Communications
  Power
 Risk Mitigation                                           Airbag Inflation: Alt = 489.17 m, Landing T-12.8 sec
 Descope Options
 Schedule
 Cost                                                            RAD Ignition: V = 49.6 m/s, Alt = 37.7 m, Landing T-3.7 sec
 Summary
 Questions


                                                                       Bridle Cut: V = 0 m/s, Alt = 14.4 m, Landing T-2.8 sec



                                                          Landing: Vel = 10.5 m/s, n = -10.6 G’s, Alt = 0 km, Landing T-0 sec
                                                                                                                  8 July 2011
Mars
                 Lander                 Solar Arrays
                                                                               Electronics Box
                                         Area 1.4 m2                                             UHF Antennae
                                         Mass 5.5 kg                                              Height 0.23 m
 Overview                       Pancam                                                            Mass 0.203 kg
 Science                         Mass 0.3 kg each                                                 Gain 5 dBi
  Objectives                     Power 5.9 W
  MEP Relationship
 Baseline Mission                   EMS Mast                                                                      VBB Seismometer
  Launch                             Mass 1.1 kg                                                                   Mass 0.2 kg
  Cruise Stage                       Power 3.0 W                                                                   Power 0.1 W
  Critical Events
  Separation
  Aeroshell
  Landing Site                  0.8 m
  Landing Events
  Footprints
                                                                              GC/MS
  Lander                                                                       Mass 2.5 kg
  Communications                                                               Power 15 W
  Power
 Risk Mitigation                                                                      2.0 m
 Descope Options
 Schedule
 Cost
                                                               30%
 Summary                  Subsystem             CBE                           Total
                                                            Contingency
 Questions
                     Instruments                 4.5   kg          1.4   kg     5.9 kg
                     Power                      12.7   kg          3.8   kg    16.5 kg
                     Communications              3.3   kg          2.0   kg     5.3 kg
                     C&DH                        2.8   kg          0.8   kg     3.7 kg
                     Thermal                     4.4   kg          1.3   kg     5.7 kg
                     Structures/Mechanisms      13.2   kg          3.9   kg    17.1 kg
                     Airbags                    14.4   kg          3.6   kg    18.0 kg
                     Landed Total                                             72.1 kg
                                                                                                                                8 July 2011
Mars
                Communications
                                                Ka-Band: 4 Mbits/s                   Mars Telecommunications
                                                                                     Orbiter
 Overview                                                                            Altitude: 4450 km
 Science
  Objectives
  MEP Relationship
 Baseline Mission
  Launch




                                                                                    UHF Ba
  Cruise Stage
  Critical Events
  Separation




                                                                     s
                                                                     bp
  Aeroshell




                                                                                      nd: 4.2
                                                                   2k
  Landing Site




                                                               .8 9
  Landing Events




                                                             t4
  Footprints



                                                            sa




                                                                                              Mbi
  Lander

                                                        bit
  Communications




                                                                                           ts at 4.8
  Power                                                M
                                                     4 .2
 Risk Mitigation
                                                  d:


 Descope Options
                                                an




                                                                                                     92 kbps
                                             FB




 Schedule
 Cost
                                           UH




 Summary
 Questions


                     Lander
                     UHF Antenna                                          1000 km
                     Beamwidth: 98.6°
                     Transmission Rate: 4.892 kbps
                                                                                                               8 July 2011
Mars
                 Power
                     • Allow for year-long solar power operation
 Overview
 Science
  Objectives
  MEP Relationship
 Baseline Mission
                     • Angled solar panels provide larger power margin
  Launch
  Cruise Stage         over flat panels
  Critical Events
  Separation
  Aeroshell
                     • Better long-term science return
  Landing Site                      160
  Landing Events
  Footprints                        140                              0 deg Inclination
  Lander                                                             45 deg Inclination
  Communications                    120                              Power Required
  Power
 Risk Mitigation                    100
                        Power (W)




 Descope Options
 Schedule                            80
 Cost
 Summary                             60
 Questions
                                     40

                                     20

                                      0
                                          0   200   400        600     800            1000
                                                      MET (Days)                             8 July 2011
Mars
                 Risk Mitigation
 Overview
 Science
  Objectives
                              Risk Element                          Mitigation Strategy                        Impact     Likelihood
  MEP Relationship
 Baseline Mission                                  Broad simulation and wind tunnel testing of various entry
  Launch                 Entry/Descent/Landing     conditions
                     1                                                                                           High        Low
  Cruise Stage           Failure                   Heritage EDL architecture
  Critical Events                                  Robust system performance
  Separation
                                                   Extensive simulation of separation dynamics
  Aeroshell              Aeroshell Separation
  Landing Site       2                             Thorough testing of separation mechanisms                   Moderate    Moderate
                         Complications
  Landing Events                                   Redundant pyrotechnics
  Footprints                                       Rigorous testing of deployment mechanisms
  Lander             3   Solar Power Degradation   Dust-mitigating solar array configuration                   Moderate    Moderate
  Communications
                                                   Contingency science & communications options
  Power
 Risk Mitigation                                   Thorough testing of subsystem performance in relevant
 Descope Options         Single Lander Subsystem   environment
                     4                                                                                         Moderate      Low
 Schedule                Failure                   Redundant communications and C&DH systems
 Cost                                              Network architecture creates inherent redundancy
 Summary
                         Component Development     Apply cost and schedule margins
 Questions           5                                                                                         Moderate      Low
                         Complications             Performance Floor consists of only heritage components




                                                                                                                        8 July 2011
Mars
                 Descope Options
 Overview                                              ΔLaunch             ΔCost
                             Descope Option                                                                             Science Impact
 Science                                               Mass (kg)         (M$FY07)
  Objectives         1   Eliminate Seismometer           -1.8              -3.4           Unable to conduct seismology experiment
  MEP Relationship
 Baseline Mission    2   Eliminate GC/MS                 -36.8             -12.1          Unable to track atmospheric isotope and photochemical behavior
  Launch                 Reduce mission length
                                                         -24.3             -20.1          Unable to determine annual climate variation
  Cruise Stage       3   to 3/4 Martian year
  Critical Events
                         Reduce mission length
  Separation         4   to 1/2 Martian year
                                                         -40.9             -31.1          Unable to determine annual climate variation
  Aeroshell
  Landing Site       5   Eliminate 3rd Lander           -263.2             -38.1          Inability to correlate data along a single longitude or latitude line
  Landing Events     6   Performance Floor              -305.6             -86.4          2 Landers, 1/2 Martian year, Full payload minus GC/MS and seismometer
  Footprints
  Lander                                                                                                                                                  Eliminate
                         Perf. Floor
  Communications                                                                                                                                          Seismometer
                          Option 13
  Power                   Option 12                                                                                                                       Eliminate GC/MS
 Risk Mitigation          Option 11
 Descope Options          Option 10
 Schedule                  Option 9                                                                                                                       Reduce mission
                                                                                                                                                          length to 3/4
 Cost                      Option 8
                                                                                                                                                          Martian year
                           Option 7
 Summary                                                                                                                                                  Reduce mission
                           Option 6
 Questions                 Option 5
                                                                                                                                                          length to 1/2
                                                                                                                                                          Martian year
                           Option 4                                                                                                                       Eliminate 3rd
                           Option 3                                                                                                                       Lander
                           Option 2
                           Option 1
                                   0.0          50.0             100.0            150.0           200.0         250.0          300.0          350.0
                                                                                      Mass (kg)


                                                                                                                                                      8 July 2011
Mars
                 Design and Mission Schedule
 Overview
 Science
                     • InDRA uses a dynamic schedule that meets all AO
  Objectives
  MEP Relationship
                       requirements and leaves substantial margin
 Baseline Mission                  Year            2006           2007        2008     2009       2010       2011   2012       2013    2014
  Launch             Phase                         A                     B                C              D                 E
  Cruise Stage       Project Planning
  Critical Events    Project Management
  Separation         Instrument Development
  Aeroshell          Instrument I, A, & T
  Landing Site       Lander Development
                     Lander I, A, & T
  Landing Events
                     Cruise Stage Development
  Footprints         Cruise Stage I, A, & T
  Lander             ATLO and Launch
  Communications     Descopes Unfeasable              1,2 3,4,5      1,2         3,4          5
  Power              E/PO
 Risk Mitigation     Science Return/Distribution
 Descope Options      Green = ~30% Margins
 Schedule
                      Blue = Cost Descope
 Cost
                      Red = Mass Descope
                                                                           Phase A     10 Months
 Summary
 Questions                                                                 Phase B     24 Months
                                                                           Phase C     20 Months
                                                                           Phase D 12 Months
                                                                           Phase E     34 Months
                                                                                                                               8 July 2011
Mars
                 Cost Breakdown
                     Instruments                     $35.1M                                Cruise
 Overview                                                                                            EDL
 Science
                     Landers (3)                     $77.2M                 Landers
                                                                                           Stage
                                                                                                    System
  Objectives         Cruise Stage                    $31.7M
  MEP Relationship
 Baseline Mission    EDL System                      $29.2M   Instruments
  Launch                                                                                             Launch Vehicle
  Cruise Stage       ATLO                             $7.1M
  Critical Events
  Separation         Management                       $8.0M        Other
  Aeroshell
  Landing Site       Operations and Data Analysis    $19.3M                                     Reserves
                                                                                  Margin
  Landing Events
                     Phase A Concept Study            $1.0M
  Footprints
  Lander             Planetary Protection             $4.5M
  Communications
  Power              E/PO and Technology Transfer     $3.1M
 Risk Mitigation
 Descope Options     Launch Vehicle                  $89.0M                 Phase A            $1.0M
 Schedule
 Cost                Total Reserves                  $58.2M                 Phase B          $23.9M
 Summary                                                                    Phase C        $173.6M
 Questions
                     Other Costs                     $13.5M
                     Total Cost                     $376.9M                 Phase D          $62.7M
                     Margin (25.4%)                  $73.1M                 Phase E          $26.7M
                     Maximum NASA Cost              $450.0M


                                                                                                     8 July 2011
Mars
                 Summary
 Overview
 Science              Relevant and applicable science objectives
  Objectives
  MEP Relationship       Compliments Mars Exploration Program
 Baseline Mission
  Launch                 Extends previous missions
  Cruise Stage
  Critical Events        Meets a variety of science themes
  Separation
  Aeroshell
  Landing Site
                      Robust mission architecture
  Landing Events         Three networked landers
  Footprints
  Lander                 One Martian year
  Communications
  Power
 Risk Mitigation
                      Feasible engineering solution
 Descope Options
 Schedule
                         Ambitious platform goals
 Cost
 Summary
                         Use of Heritage and qualified technologies
 Questions
                         Strategic risk mitigation and descope options
                         Good mass, power, schedule and cost margins (≥30%)


                                                                     8 July 2011
Mars
                 Questions?
 Overview
 Science
  Objectives
  MEP Relationship
 Baseline Mission
  Launch
  Cruise Stage
  Critical Events
  Separation
  Aeroshell
  Landing Site
  Landing Events
  Footprints
  Lander
  Communications
  Power
 Risk Mitigation
 Descope Options
 Schedule
 Cost
 Summary
 Questions




                              8 July 2011
Mars
       Lander Deployment
                                       Springs Provide Reliable Source of Torque to
                                                Ensure Panel Deployment.




         Overlapping Stowed Configuration Allows for
                 High Packaging Efficiency.




                                                                               Fail-Safe Latch Prevents Panel
                                                                                         Collapse.
                  Contingency Line Prevents Panel Over-
                               Rotation.

                                                                                                     8 July 2011
Mars
       Planetary Protection
        • InDRA is a Category IV A mission
          – Class-100 clean room, stopping 99.97% of
            microbial organisms
          – Hydrogen-peroxide sterilization process
          – Surfaces cleaned with alcohol wipes
          – Assay procedures ensuring < 300 parts per
            million
          – NASA inspection and verification
          – Enclosed in bioshield
        • InDRA uses RHUs
          – Launch services certification
          – Emergency response teams on site
                                                 8 July 2011
Mars
       E/PO & Technology Transfer
        • K-12 Education
           – Interactive website
           – Educational packets
           – Educator workshops
        • College Education
           – Research grants
           – Traveling lecture series
        • Public Outreach
           – Press releases and mass media
           – Library VHS
        • Technology Infusion and Transfer
           – Work with NASA in marketing new technologies
        • Small Disadvantaged Businesses
           – Participation a priority at all management levels




                                                                 8 July 2011
Mars
                 Landing Footprints
 Overview
 Science
  Objectives
  MEP Relationship
 Baseline Mission
  Launch
  Cruise Stage
  Critical Events
  Separation
  Aeroshell
  Landing Site
  Landing Events
  Footprints
  Lander
  Communications
  Power
 Risk Mitigation
 Descope Options
 Schedule
 Cost
 Summary
 Questions




                                      8 July 2011