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Home , Human mission to Mars, Mars flyby, Sol (day on Mars)

National Aeronautics and Space Administration

Human 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 new knowledge and opportunities.

Beginning with missions beyond low-Earth , 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 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- Study on Human 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 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 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 > 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 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 & 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- 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 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 5-sol Aerobrake Aerobrake Cryogenic Hypergol LOX 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 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 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 elements and technological capabilities: – Reusable, refuelable in-space propulsion (SEP and chemical) – Long-lifetime, high reliability in-space habitation – 20-25 mt payload to Mars surface delivery (E/D/L) – Surface – Atmospheric ISRU, evolving to atmosphere + water • Affordability and sustainability: TBD • Target milestones: First human orbital mission 2033, first human landed mission 2037

10 Beyond Cis-lunar Space First Sphere of Influence

Deep Space Transport (DST) Orbital Mission to Mars Sphere of Influence

• Emphasis on first human mission to Mars’ sphere of influence • First long duration flight with self sustained systems • Autonomous mission with extended communication delay • First crewed mission involving limited abort opportunities

• Example Assumptions • 8.4 m Cargo Fairing for SLS launches • Crew of 4 for Mars class (1000+ day) mission independent of Earth • Orion used for crew delivery and return to/from cislunar space • Re-usable DST/Habitat and Propulsion Stage • Hybrid (SEP/Chemical) In-Space Propulsion System • Gateway used for aggregation and re-fueling of DST Mars Orbital Mission Elements and Systems

Earth Launch System

Deliver payloads to Deep Space cislunar space Transport

Deep Space Crew operations in Gateway vicinity

Earth Moon Mars

Orion

Transfer crew and cargo from Earth to cislunar Communications space and back to Earth System Earth-to-Mars communication Mars Orbital Mission Example Operational Concept

# Crew Phase Critical Event System Return to Earth Options

4 Lunar #1 DST/Orion DST powered return to HEO / Orion return

5 Lunar Gravity Assist #2 DST DST powered return to HEO

5 Earth-Mars Transit (early phase) DST powered return to HEO (available for DST limited time post departure - TBD)

6 Earth-Mars Transit Thrusting SEP None – continue to Mars

7 Mars Orbit Insertion Chem Backflip (TBD) – continue mission

8 Mars orbit reorientation SEP None – continue mission 9 Trans-Earth Injection Chem None – continue mission 7 9 High-Mars Orbit 10 Mars-Earth Transit Thrusting SEP None – continue mission 8 11 Lunar Gravity Assist #3 DST None – continue mission

11 Lunar Gravity Assist #4 DST None – continue mission 438 days

12 Orion Launch SLS/Orion HEO Loiter

12 Earth Return via Orion Orion HEO Loiter 6 306 days 291 days 10

13 2 Deep Space Gateway 5 11 4 High-Earth Orbit Checkout before 1 3 each mission Orion return 12 12 (no crew)

Launch Loiter High Thrust Chemical Low Thrust Electric Mars Surface Mission Mars Surface Mission

• Emphasis on establishing Mars surface field station • First human landing on Mars’ surface • First three missions revisit a common landing site

• Example Assumptions • Re-use of for crew transit to Mars • 4 additional, reusable Hybrid SEP In-Space Propulsion stages support Mars cargo delivery • 10 m cargo fairing for SLS Launches • Missions to Mars’ surface include the following: • Common EDL hardware with precision landing • Modular habitation strategy • ISRU used for propellant (oxidizer) production • Fission Surface Power • 100 km-class Mobility (Exploration Zone) Mars Surface Mission Example Operational Concept

# Crew Phase Critical Event System Return to Earth Options

4 Lunar Gravity Assist #1 DST/Orion DST powered return to HEO / Orion return

5 Lunar Gravity Assist #2 DST DST powered return to HEO 9 5 Earth-Mars Transit (early phase) DST powered return to HEO (available for DST limited time post departure - TBD)

6 Earth-Mars Transit Thrusting SEP None – continue to Mars

7 Mars Orbit Insertion Chem Backflip (TBD) – continue mission 8 Rendezvous & Mars Descent Lander Remain in Mars orbit for return 8 9 Mars Ascent Ascent None – must ascend to orbit 7 11 High-Mars Orbit 10 Mars orbit reorientation SEP None – continue mission 10 11 Trans-Earth Injection Chem None – continue mission

12 Mars-Earth Transit Thrusting SEP None – continue mission 300 days

13 Lunar Gravity Assist #3 DST None – continue mission

13 Lunar Gravity Assist #4 DST None – continue mission 6 390 days 370 days 12

14 Orion Launch SLS/Orion HEO Loiter

14 Earth Return via Orion Orion HEO Loiter 15 2 Deep Space Gateway 5 13 4 High-Earth Orbit Checkout before 1 3 each mission Orion return 14 14 (no crew)

Launch Loiter High Thrust Chemical Low Thrust Electric Mars SurfacePhase Mission 4 Mission KeyElements Elements and Systems

Space Launch Entry-Descent System Lander Deep Space Deliver payloads to cislunar space Transport, Hybrid SEP Deep Space Cargo Transport Gateway Transport 100-200t aggregated Land 20-30 t payloads payloads and crew between Earth on Mars and Mars Crew Operations Earth Moon Mars on Mars Surface

Mars Ascent Vehicle Orion

Transfer crew and cargo Communications Transfer crew and cargo from Earth to cislunar System from the Mars surface to space and back to Earth Mars orbit Earth-to-Mars, Mars surface-to-Mars orbit, and Mars surface-to-surface communication

Surface Systems Legend: Phase 1 elements Surface Surface Surface Logistics Phase 2/3 elements Habitat and Mobility Utilities Carrier Laboratory MSC Phase 4 elements

Human Landers: A Leap in Scale

Viking Pathfinder MER A/B MSL Human 1 & 2 Scale Lander (Projected) Diameter, m 3.505 2.65 2.65 2.65 4.5 16-19 Entry Mass, kg 930 585 840 602 3151 47-62 t Landed Mass, kg 603 360 539 364 1541 36-47 t Landing Altitude, km -3.5 -1.5 -1.3 -3.5 -4.4 + 2 Peak Heat Rate, 24 106 48 56 ~120 ~120-350 W/cm2 Landing Ellipse, km 280x130 200x70 150x20 100x20 20x6.5 0.1x0.1

New Approach Needed Steady progression of “in family” EDL for Human Class Landers Human Mars Lander Challenges

• 20x more payload to the surface • 200x improvement in precision landing • Dynamic atmosphere; poorly characterized • New engines; performing Supersonic RetroPropulsion • Terrain hazard detection - improving, but not perfect • Surface plume interaction - debris ejecta could damage vehicles

21 21 Concept Quad Chart

HIAD: Hypersonic Inflatable Aerodynamic Decelerator ADEPT: Adaptable Deployable Entry & Placement Technology

Capsule Mid L/D HIAD EDL Sequence

Deorbit & Deploy Entry AOA= -10 deg Velocity = 4.7 km/s FPA = 10.6 deg Powered Descent Initiation Mach = 3.0, Alt = 8.3 km Pitch to 0 deg AOA

Approach 8x100kN engines 80% throttle

Touchdown HIAD Retract Surface Ops 24 25