1. MinMars Project Surface Infrastructure Update A DevelopSpace Project June 15 th, 2008

2. Overview Ongoing process to size all surface infrastructure elements based on previous literature – This presentation is not to detail surface infrastructure element sizes, but to discuss several key points and ask opinions on overall concept Key questions being analyzed – What infrastructure is needed? – Can this be done in 5 – 10 mt landed payloads No analysis of landing systems Focused on two types of elements – Cargo Either pre-deployed or re-supply – Pre-deployed must survive 2+ years on the surface – How much autonomous construction is required? – Crewed 30-day surface survival capability EVA Suits and Mobility included No consideration for in-space transit

3. Surface Infrastructure Categories Structures – Pressurized & Unpressurized – Habitation – Rigid & Inflatable Power – Minimal integrated power (for keep alive of pre-deployed elements) – Deployed surface power Thermal – Minimal integrated thermal – Deployed surface radiators Communication & Navigation – Mars surface network – Mars-Earth network Life Support – Based on Wilfried’s assessment In-situ Resource Utilization – Basic vs. extended capability Crew Systems – Medical – Hygiene Maintenance & Repair – Facilities, Spare Parts, Raw Materials Science & Exploration – Facilities & Tools Extra Vehicular Activities – EVA Suits & Spares Surface Mobility – Unpressurized Crew Mobility – Pressurized Crew Mobility – Asset Mobility Consumables & Logistics – Initial cache & resupply

4. Cargo Landers – Individual units that are able to sustain initial period without interaction with other systems Common structure (5m by 5m rigid cylinder) (~1mt) Basic power, thermal, communications, avionics (~ 1mt) Each element can carry ~3mt of payload Approximately five cargo landers required – Deployable power & thermal systems – Central life support and ISRU – Logistics & cargo lander – Habitat lander(s) – Mobility asset (pressurized and unpressurized rovers & asset mobility)

5. Crewed Lander Deliver crew to Martian surface – Maintain crew for 30-days Requires consumables for 30-days without ISRU capability Requires fully functioning power, thermal, and life support systems – Provide EVA capability to enable base assembly and initialization Mass will be very tight on this element – Structures (1mt) – Crew & EVA Suits (1mt) – Consumables (0.5mt) – Life Support (0.5mt) – Power & thermal (1mt) – Avionics, communications (0.5mt)

6. Questions/Discussion Currently creating sizing sheets to better flush out details of the elements Pre-deployed assets – At what point does the infrastructure have to be to send crew? Successful landings vs fully-functioning Crew lander – How does the crew lander interact with the in-space habitat? – How is this achieved

7. BACK-UP SLIDES

8. Structures Common 5m by 5m rigid cylinder (~100 m 3 ) – Baseline: Al 6061 T6 & MLI – Two floors: ~39 m 2 (420 ft 2 ) of floor area – Mass: ~1 mt Inflatable Structures – Used to add habitable volume – Free-standing vs. attached

9. Power Baseline: Non-Tracking Solar & RFC – Volume Specific Power 0.0019P 3 -0.3882P 2 +29.933P+955.28 – Mass Specific Power 0.00004P 3 -0.0082P 2 +0.6887P+6.1184 – Valid from 35kW – 80kW – 50kW requires ~2mt & 30m 3 How densely can this be packed? Concept one dedicated cargo lander with power systems (including deployment assets) with connections to all other units All other assets will require integrated power to survive for period between landing and connection

10. Thermal Each element will be required to have plumbing, cold plates, heat exchangers, and survival radiators – Will also require deployable radiators on the Martian surface to handle operational heat loads Not considering Thermal Protection System for landing

11. Communication & Navigation Each element requires low-data rate surface network and Earth-Mars network System will require high-data rate networks for operation Avionics in NASA’s DRM is ~150 kg per element – (from Exploration Blueprint) – 1.5 mt in DRM-1

12. Life Support/ISRU Baseline: Components from Wilfried’s presentation – 4BMS – Solid state compressor – Sabatier reactor – Methane pyrolysis reactor – Electrolysis unit – Multi-filtration – Vapor compression distillation Hardware mass is approximately 250 kg/person One system could be deployed and attached to all elements – Each element would require plumbing, fans, sensors, etc.

13. Crew Systems Hardware for basic survival – Food preparation & storage – Hygiene – Sleep provisions – Housekeeping – Washing machine Total system mass can vary greatly Components can be spread out between elements

14. Near-Term Mars Colonization -A DevelopSpace Project- June 15 th, 2008

15. Mars Results

16. Mars Results Continued

17. Mars Solar Surface Power Issues to be resolved – RFC performance may be significantly reduced compared to our assumptions 300 Wh/kg or less Could possibly be enhanced by generating oxygen for RFC in-situ (~ 25% of RFC mass) – Effect of wind speed on roll-out arrays Would they be blown away? – Degradation, dust removal – Robotic deployment

18. Mars Surface Infrastructure (1) DRM 1.0: infrastructure after 1 st opportunity

19. Mars Surface Infrastructure (2) DRM 1.0: infrastructure after 2 nd opportunity

20. Mars Surface Infrastructure (3) DRM 1.0: infrastructure after 3 rd opportunity

21. Mars Surface Infrastructure (4) DRM 1.0: hab or lab module final landing

22. Mars Surface Infrastructure (5) DRM 1.0: mobile hab and lab modules connected

23. Mars Surface Infrastructure (6) DRM 3.0: hab-module with inflatable extension

24. Mars Surface Infrastructure (7) Hab module for dual landers DRM

25. Mars Surface Infrastructure (8) DRM 1.0:MAV under-slung cargo delivery and deployment

26. Mars Surface Infrastructure (9)

27. Mass allocations for Mars Direct components on surface of Mars ERV componentsmTHabitat componentsmT ERV cabin structure3Habitat structure5 Life Support System1 3 consumables3.4Consumables7 Solar Arrays (5 kW)1 1 Reaction Control System0.5Reaction Control System0.5 Communications and Information Management0.1Communications and Information Management0.2 Furniture and Interior0.5Furniture and Interior1 Space Suits (4)0.4Space Suits (4)0.4 Spares and Margin (16%)1.6Spares and margin (16%)3.5 Aeroshell (for Earth Return)1.8Pressurized Rover1.4 Rover0.5Open Rovers (2)0.8 Hydrogen Feedstock6.3Lab Equipment0.5 ERV Propulsion stages4.5Field Science Equipment0.5 Propellant Production Plant0.5Crew0.4 Nuclear reactor (100 kW)3.5 Total Mass28.6 25.2

28. Mass Budget for Habitat-1 Mars DirectDRM-3MSMExplanation for MSM figures Habitat Module Structure55.54.8Scaled from DRM-3 Furniture and Interior101.5 Life Support System34.73.8NASA model for crew of six Comm/Info0.20.3 DRM-3 Hydrogen and Hab ISRU0.400 Health Care1.300 Thermal00.60.5DRM-3 Scaled Crew accommodation011.50 Spares and Margin3.500Included in individual listings Science100 Crew0.40.50.4 Surface power (reactor)01.75At least 25 kWe needed Power Distribution00.3 DRM-3 Scaled EVA Suits0.411DRM-3 Open Rovers0.80.50Mass budgeted with surface power Pressurized Rover1.400 Consumables703.298% closed H20/02 + food (=0.630 kg/per/day for 600 days) EVA Consumables02.30Produced by ISRU on MAV and Hab Descent fuel cell131.3 Reaction Control System0.50 Mars Direct Total Landed26.931.922.6Total of Above

29. Mars Wish List

30. Transportation Automated Mars landing and hazard avoidance navigation systems Mars in-situ propellant production friendly rocket combustion / performance characterization (C2H4/LOX; CH4/LOX); more important if people want to come back Large-scale (20mt+) Mars aero-entry (and EDL more generally) technology Low mass, cost, power and ideally autonomous deep-space (out to at least ~2 AU) navigation systems (software, hardware)

31. Power Automated, large scale (football field+) solar array transport, surface deployment, and maintenance systems High energy density electrical power storages systems (aiming in particular towards high energy density relative to Earth imported mass) Mars surface internal combustion engines (LOX, plus various fuels, e.g., C2H4, CH4, CO, etc), possibly with water exhaust reclamation.

32. Life Support, Logistics, ISRU Mars atmosphere collection systems (at minimum CO2; adding N2 and Ar is useful; H2O depends on energy/mass intensity relative to other options) Mars permafrost mining systems (for varying wt% H2O); note, this is much easier than mining putative lunar ice Good, high capacity Mars surface cryocoolers (options for just soft/medium cryogens (e.g., LOX, CH4, C2H4), or also for hard cryogen (LH2)) Earth-Mars hydrogen transport systems (not necessarily as LH2) Basic ISRU chemical processing systems (e.g., H2O electrolysis, Sabatier, RWGS, CO2 electrolysis, ethylene production, etc.) High closure physical-chemical life support systems (e.g., air revitalization, water recycling) "Food system" for food supplied from Earth. Consider being able to survive on food shipped 5 years ago. Mars surface food production systems Simple in-situ manufacturing systems (e.g., for spare parts) Simple raw materials production (e.g., plastics such polyethylene, epoxies, ceramics, etc.)

33. Outpost Ops and Surface Exploration Mars surface communication and navigation systems (e.g., for rovers), sans extensive satellite constellation Very high data rate Mars-Earth back-haul comm system Good Mars surface EVA suits Data collection, analysis in support of landing site / outpost location selection Very long distance surface mobility systems (including with people) Solar flare / SPE warning systems