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Human Mars Architecture National Aeronautics and Space Administration Human Mars Architecture Tara Polsgrove NASA Human Mars Study Team 15th International Planetary Probe Workshop June 11, 2018 Space Policy Directive-1 “Lead an innovative and sustainable program of exploration with commercial and international partners to enable human expansion across the solar system and to bring back to Earth new knowledge and opportunities. Beginning with missions beyond low-Earth orbit, the United States will lead the return of humans to the Moon for long-term exploration and utilization, followed by human missions to Mars and other destinations.” 2 EXPLORATION CAMPAIGN Gateway Initial ConfigurationLunar Orbital Platform-Gateway (Notional) Orion 4 5 A Brief History of Human Exploration Beyond LEO America at DPT / NEXT NASA Case the Threshold Constellation National Studies Program Lunar Review of Commission First Lunar Architecture U.S. Human on Space Outpost Team Spaceflight Plans Committee Pathways to Exploration Columbia Challenger 1980 1990 2000 2010 Bush 41 Bush 43 7kObama HAT/EMC MSC Speech Speech Speech Report of the 90-Day Study on Human Exploration of the Moon and Mars NASA’s Journey to National Aeronautics and November 1989 Global Leadership Space Administration Mars Exploration and 90-Day Study Mars Design Mars Design Roadmap America’s Reference Mars Design Reference Future in Reference Mission 1.0 Exploration Architecture Space Mission 3.0 System 5.0 Exploration Architecture Blueprint Study 6 Exploring the Mars Mission Design Tradespace • A myriad of choices define the “Architecture” of a human Mars mission • A large menu of human Mars architecture choices can be organized into three distinct segments – End State: Describing long-term architecture goals and objectives – Transportation: Getting crew and cargo to Mars and back – Surface: Working effectively on the surface of Mars • Human exploration of Mars may represent one of the most complex systems-of- systems engineering challenges that humans will undertake – Multiple systems must work seamlessly together • Work will continue to define the optimal human Mars architecture, and the following is ONE possible solution. Design Choices Transportation Mission Architecture / End State Earth-to-Orbit The current big picture design Launch Propellant Element Earth-to-Orbit Launch Primary Program Level of Human Earth Based TransportationCrew Launch Vehicle Mission Class Cost Emphasis Reusability and/or Logistics Launch Flights per Vehicle Focus Activity Mission Support Vehicle Shroud Size / 37 Launch Vehicle Vehicle Expedition Rate Cis-Earth Infrastructure SLS 2B FairingDeep Space choices offers up 5.3 x 10 Supporting Opposition Class - 8.4 m In-Space No. of Flags & Footprints / Long-Term Robotic / Space Continual Low Cost / In-Space Earth Return Cis-Lunar Mars Orbit Chemical In-Space Initial OrbitShort Stay (1-60 Orion None SLS/Orion SLS SLS Diameter, Habitat 2 Crew to 1 per year Pathway Lewis & Clark StagingTeleroboticInfrastructure Control GraDual BuilDRefueling-Up Mode Propulsion Propulsion Propellant Habitation possible combinations sols) Short LengthDuration Orbit Mass Transportation Research Base / Conjunction Class - 8.4 m MoDerate High Cost / In-Space Antarctic FielD Long Stay (300+ ExpeDitions Take Orion All Chemical / InternationalAll Chemical / International InternationalNTO / Monolithic Diameter, 4 2 per yearDSG > 2-year Flyby > DRO Cis-Lunar Hab < 50 mt Intervention GraDual BuilDYes -UpDirect EntryHabitation Deep Space 600 Days 2 Earth Return Analog sols) to Mars Cryogenic Cryogenic HyDrazine Transit HabLong Length Long-Stay Surface Near Mars Orbit Mars Orbit Mars Ascent Vehicle Ascent Vehicle 10 m MAV Earth Earth Descent to Primary Activity: All-Up vs. Split Mars Parking No Daily Low Cost / Fast In-Space Mars Orbit Mars Pre- Earth Entry Rectilinear No Cis-Lunar HumanDestination-TenDeD Leave Orion Insertion - Insertion Earth Orbit - All Chemical / CommercialDescent All Chemical / CommercialPropellant Commercial-LOX / Propellant MoDular Diameter, - PayloaD Capture 6 3 per yearReturn DSG > 2-year Flyby > Earth's Science & Research Mission 50 - 100 mtInterventionOrbit BuilDNo-Up TransportationOperations 1000 Days 3 Deployment Vehicle Halo Orbit Infrastructure in Orbit Human HealthCargo CrewCapture StorablePropellantStorableFrom EarthMethaneFrom ISRUTransit HabShort LengthUp Orbit SurfaceScheme Short-Stay SurfaceSurFace 10 m Primary Activity: (NRHO) Continuous High Cost / Fast Minimal EDL anD Ascent Combination Combination Combination Diameter, Direct Entry8 6 per year Resource Utilization Presence BuilD-Up Lunar Orbit LOX / Landed Mass DSG > 3-year Orbital > LEO 100 - 200 mt NTR NTR CombinationLong LengthLander 1200 Days(with 4Direct Mars Orbit 1-sol Propulsive PropulsiveCaptureDesign Minimal First Surface Storables CryogenicCrew Surface HyDrogenNo. of Crew to LOX Only 0 kg per Lander Entry LongConsumables-Stay Surface DirectLanding Orion Landing Radiation Countermeasures Payload SizeTransit hab Entry Lander Altitude Primary Activity: Human Considerations Mission Date Stay Time Surface Crewmember Type Location Accuracy Surface Systems 12 m Diameter(Metric Tons)flyby)10 + DSG > 3-year Orbital > Human Expansion HEO Settlements> 200 mt SEP OCT (Metric Tons)Surface5 Rendezvous / Propulsive Short-Stay SurfaceSeparate Phobos 5-sol Aerobrake Aerobrake Cryogenic Hypergol LOX Methane 250 kg DRO None Commercial Infrastructure Transfer Capture System Human HybriD SEP / HybriD SEP / Short Stay 18 mt lander: Passive Zero-G w/Exercisefor Permanent Psychology 2035 Excursion 2 18 6 Blunt Body Near Equator - 6 km MOLA < 100 m Colonization Vehicle Chem Chem (1-60 sols) 6.0 - 36.0 mt Landing Habitation Habitat Life Planetary Radius/ Length of Planetary Laboratory Cargo Surface Mars' Surface 500 km Circular NoneISRU None RefurbishmenPower Other LOX/Hydrogen > 250 kg NHRO Landers ECLSS TrashCombinationRobotics Zone HybriD SEP / TypeHybriD SEP / Support Outpost Exploration Surface Stay Sciences Sciences Handling Communication t Long Stay 20 mt lander: > 6 Surveys Active Artificial Short Arm MedicalHypergols 2037Hypergols Zone3 20 Mid L/D Polar 0 km MOLA 100 m - 1 km (300+ sols) 6.7 - 40.0 mt Earth Return Combination Areosynchronous Other HEO Split SEP / Split SEP / Different Teleoperation of Propellant 22 mt lander: Low Latency Crane/ Lunar First Artificial Long ArmNone DustSolarChem Monolithic2039 ChemOpen for Each < 10 km4 7 sols22 Instrument / NoneInflatable OpenMid-LatitudeContainers+ 2 km MOLAOrbital > 1 km Line of SiGht 7.3 - 44.0 mt Telerobotics Hoist Q-Drive Q-Drive Expedition Networks Areosynchronous SEP / Chem / SEP / Chem / Demonstration SinGle Recon GeoloGy / 25 mt lander: Basic Analysis 50 - 75%Northern NuclearAerobrakeModular2041 +AerobrakeClosed 10 - 100 km5 14 sols25 Deployable Recycle Autonomous Robotic Ramp Relay Satellite Mars Flyby Only Outpost GeophysioloGy8.3 - 50.0 mt / No Lab ClosedHemisphere NEP NEP Backflip BimoDal NTR BimoDal NTR Moderate Atmospheric Multiple 27 mt lander: 75 - 90%Southern Crew Grand Tour RTG Inflatable > 100 km6 30 sols27 Field Work Geochemical All Propulsive Combination ATHLETE OxyGen Outposts 9.0 - 54.0 mt ClosedHemisphere Partnered Fast + Life Science Water from 30 mt lander: DrillinG / Full-Scale Life > 90%Different for Combination RiGid > 6 90 sols30 Other ReGolith Geophysical Tests10.0 - 60.0 mt Science Closedeach mission Local 40 mt lander: 40 Water from from Features 300 - 500 13.3 - 80.0 mt Subsurface Ice and sols Resources Fabrication / 500 - 1000 ManufacturinG sols > 1000 sols, Combination overlappinG crews Export 20 Questions - End State, Reusability • A single surface site lends itself to a “field station” approach for Mission Architecture / End State development of a centralized habitation zone / landing site. The first mission to this site would deploy habitation, Primary Program Level of Human Earth Based Mission Class Cost Emphasis Reusability Focus Activity Mission Support power, and other infrastructure that would be used by at least two Opposition Class - Flags & Footprints / Robotic / Continual Low Cost / subsequent surface missions. Short Stay (1-60 None Lewis & Clark Telerobotic Control GraDual BuilD-Up sols) • Reusable surface elements (first 3 Research Base / Conjunction Class - Moderate High Cost / In-Space landed missions) Antarctic FielD Long Stay (300+ ExpeDitions Intervention GraDual BuilD-Up Habitation Analog sols) – Provides some infrastructure for Primary Activity: All-Up vs. Split No Daily Low Cost / Fast In-Space Human-TenDed missions to follow Science & Research Mission Intervention BuilD-Up Transportation • Reusable in-space transportation and Primary Activity: Continuous High Cost / Fast Minimal EDL anD Ascent Resource Utilization Presence BuilD-Up habitation (at least 3 missions) Primary Activity: Human – Based in cis-lunar space Surface Systems Human Expansion Settlements • Cost can be spread via gradual buildup Infrastructure Human for Permanent of transportation/orbital capability à Colonization Habitation short surface stay à long surface stay SUMMARY – NASA Example Mission • End State: First 3 human Mars mission visit a common “Field Station” – Single landing site for first 3 (min) surface missions – Long-distance (100 km-class) surface mobility • Major decisions that “frame” this example architecture – Reusable in-space transportation and habitation* – Split mission architecture (predeploy) – Conjunction-class, long-stay, minimum energy – Hybrid in-space propulsion – Use of ISRU from the very first landed mission • Priority
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