Human Mars Architecture

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1 National Aeronautics and Space Administration Human Mars Architecture Tara Polsgrove NASA Human Mars Study Team 15 th 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

2 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

3 EXPLORATION CAMPAIGN

4 Gateway Initial Configuration (Notional) Lunar Orbital Platform-Gateway Orion 4

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6 NationalA er onautics and Space Administration A Brief History of Human Exploration Beyond LEO National Commission on Space NASA Case Studies America at the Threshold First Lunar Outpost DPT / NEXT Constellation Program Lunar Architecture Team Review of U.S. Human Spaceflight Plans Committee Pathways to Exploration Challenger Bush 41 Speech Columbia Bush 43 Speech 7k Obama Speech HAT/EMC MSC Report of the 90-Day Study on Human Exploration of the Moon and Ma rs Leadership and America s Future in Space November Day Study Mars Design Reference Mission 1.0 Mars Design Reference Mission 3.0 Exploration Blueprint Exploration System Architecture Study Mars Design Reference Architecture 5.0 Global Exploration Roadmap NASA s Journey to Mars

7 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-ofsystems 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 Primary Program Focus Mission Class Mission Architecture / End State Level of Human Earth Based TransportationPropellant Activity Mission Support Cost Emphasis Reusability Crew Launch

8 Design Choices Primary Program Focus Mission Class Mission Architecture / End State Level of Human Earth Based TransportationPropellant Activity Mission Support Cost Emphasis Reusability Crew Launch and/or Logistics Vehicle Launch Vehicle Cis-Earth Infrastructure Transportation Earth-to-Orbit Element Launch Vehicle Launch Earth-to-Orbit Vehicle Flights per Shroud Size / Expedition SLS 2B Deep Fairing Space Opposition Class - Supporting 8.4 m Flags & Footprints / Robotic / Continual Low Cost / In-Space No. of Short Stay (1-60 Long-Term Space In-Space Earth Return None Cis-Lunar SLS/Orion Mars Orbit SLS Chemical SLS In-Space Diameter, 2 1 per year Lewis & Clark Initial Orbit Telerobotic Control Orion Gradual Build-Up Habitat Crew to Pathway sols) Staging Infrastructure Refueling Mode Propulsion Propulsion Propellant Habitation Short Length Mass Transportation Duration Orbit Research Base / Conjunction Class m Moderate High Cost / In-Space Antarctic Field Long Stay (300+ Expeditions Take Orion All Chemical DRO Cis-Lunar Hab < 50 mt International International International Diameter, 4 per year Intervention Gradual Yes Build-UpDirect Habitation Entry Deep / All Space Chemical / NTO / Monolithic DSG > 2-year Flyby > 600 days 2 Earth Return Analog sols) to Mars Cryogenic Cryogenic Hydrazine Transit Long Hab Length Long-Stay Surface Primary Activity: Near All-Up vs. Split No Daily Low Mars Cost Orbit / Fast Mars Orbit 10 m In-Space Human-Tended Science & Research Mission Intervention Build-Up Transportation Commercial Mars Commercial Ascent Vehicle Commercial Ascent Vehicle MAV Earth Earth Descent to Mars Parking Mars Orbit Diameter, 6 3 per year Mars Pre- Earth Entry Rectilinear No Cis-Lunar Destination Leave Orion Insertion - Insertion Earth Orbit - All Chemical Descent / All Chemical Propellant / -LOX Propellant / Modular - Payload Capture Return DSG > 2-year Flyby > Earth's mt Orbit No Operations Halo Orbit Infrastructure in Orbit Capture Storable Short Length1000 days 3 Deployment Vehicle Human Cargo Health Crew Propellant Storable From Earth Methane From ISRU Transit HabUp Orbit Surface Scheme Short-Stay Surface Surface 10 m Primary Activity: (NRHO) Continuous High Cost / Fast Minimal EDL and Ascent Combination Combination Combination Diameter, Direct 8 Entry 6 per year Resource Utilization Presence Build-Up Lunar Orbit LOX / DSG > 3-year Orbital > LEO mt NTR NTR Combination Long Length1200 days (with Landed Mass Mars Orbit 1-sol Propulsive Propulsive 4 Capture Minimal Storables Cryogenic Hydrogen LOX Only 0 Lander Direct Design First Surface Crew Surface No. of Crew to kg Transit hab per Entry Lander Long-Stay Consumables Entry Surface Direct Landing Orion Landing Radiation Countermeasures Payload Size Lander Altitude Primary Activity: Human Considerations Mission Date Stay Time Surface Surface Systems 12 m Diameter flyby) Crewmember Type Location Accuracy (Metric Tons) 10 + DSG > 3-year Orbital > Human Expansion HEO Settlements > 200 mt SEP OCT 5 Short-Stay Surface Phobos 5-sol Aerobrake Aerobrake Rendezvous / (Metric Surface Tons) Propulsive Separate Infrastructure Cryogenic Hypergol LOX Methane 250 kg DRO None Human Transfer Capture System Commercial Hybrid SEP / Hybrid SEP Short / Stay Passive Zero-G w/exercise for Permanent Psychology 6 Colonization Vehicle 2035 Excursion 18 mt lander: 2 18 Blunt Body Near Equator - 6 km MOLA Chem Chem (1-60 sols) mt Landing < 100 m Habitation Habitat Life Planetary Radius/ Length of Planetary Laboratory Cargo Surface Mars' Surface 500 km Circular None ISRU None Refurbishmen Power Other LOX/Hydrogen > 250 kg NHRO Landers ECLSS Trash Combination Robotics Zone Hybrid t SEP / TypeHybrid Support SEP / Outpost Exploration Surface Stay Sciences Sciences Handling Communication Long Stay 20 mt lander: > 6 Surveys Active Artificial Short Arm Medical Hypergols 2037Hypergols Zone 3 20 Mid L/D Polar 0 km MOLA 100 m - 1 km (300+ sols) mt Earth Return Combination Areosynchronous Other HEO Split SEP / Split SEP / Different Teleoperation of Propellant Lunar First Artificial Long Arm Dust Chem 2039 Chem 22 mt lander: Low Latency Crane/ None Solar Monolithic Open for Each < 10 4 km 7 sols 22 Instrument / None Inflatable Open Mid-Latitude Containers+ 2 km MOLA Orbital > 1 km Line of Sight mt Telerobotics Hoist Q-Drive Q-Drive Expedition Networks Areosynchronous SEP / Chem / SEP / Chem / Demonstration 25 mt lander: Northern Mars Flyby Aerobrake 2041 Aerobrake + Single Nuclear Modular Closed 5 25 Deployable Only Outpost km 14 sols Recon Geology / Basic Analysis 50-75% mt Hemisphere Recycle Autonomous Robotic Ramp Relay Satellite Geophysiology / No Lab Closed NEP NEP Backflip Bimodal NTR Bimodal NTR 27 mt lander: Moderate Southern Grand Tour Atmospheric Multiple 6 27 All Propulsive 75-90% RTG Inflatable > 100 km 30 sols Field Oxygen Outposts 9.0 -Work 54.0 mt Geochemical Closed Hemisphere Combination Crew ATHLETE Partnered Fast + Life Science Water from Regolith Water from from Subsurface Ice Fabrication / Manufacturing Combination Export Combination Rigid > 6 90 sols 30 Local Features and Resources sols sols > 1000 sols, overlapping crews Launch Vehicle Rate 30 Drilling mt lander: / Full-Scale Life Geophysical Tests mt Science 40 mt lander: mt > 90% Different for Closed each mission The current big picture design choices offers up 5.3 x possible combinations Other

20 Questions - End State, Reusability Primary Program Focus Flags & Footprints / Lewis & Clark Research Base / Antarctic Field Analog Primary Activity: Science & Research Primary Activity: Resource

Split Mission Mission Architecture / End State Level of Human Earth Based Cost Emphasis Activity Mission Support Reusability Robotic / Telerobotic Expeditions Human-Tended Continuous Presence Human

Build-Up None In-Space Habitation In-Space Transportation EDL and Ascent Surface Systems Infrastructure for Permanent Habitation A single surface site lends itself to a field station approach for

9 20 Questions - End State, Reusability Primary Program Focus Flags & Footprints / Lewis & Clark Research Base / Antarctic Field Analog Primary Activity: Science & Research Primary Activity: Resource Utilization Primary Activity: Human Expansion Mission Class Opposition Class - Short Stay (1-60 sols) Conjunction Class - Long Stay (300+ sols) All-Up vs. Split Mission Mission Architecture / End State Level of Human Earth Based Cost Emphasis Activity Mission Support Reusability Robotic / Telerobotic Expeditions Human-Tended Continuous Presence Human Settlements Human Colonization Continual Control Moderate Intervention No Daily Intervention Minimal Low Cost / Gradual Build-Up High Cost / Gradual Build-Up Low Cost / Fast Build-Up High Cost / Fast Build-Up None In-Space Habitation In-Space Transportation EDL and Ascent Surface Systems Infrastructure for Permanent Habitation A single surface site lends itself to a field station approach for development of a centralized habitation zone / landing site. The first mission to this site would deploy habitation, power, and other infrastructure that would be used by at least two subsequent surface missions. Reusable surface elements (first 3 landed missions) Provides some infrastructure for missions to follow Reusable in-space transportation and habitation (at least 3 missions) Based in cis-lunar space Cost can be spread via gradual buildup of transportation/orbital capability à 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

10 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 mt payload to Mars surface delivery (E/D/L) Surface nuclear power Atmospheric ISRU, evolving to atmosphere + water Affordability and sustainability: TBD Target milestones: First human orbital mission 2033, first human landed mission

11 Beyond Cis-lunar Space First Human Mission to Mars Sphere of Influence Deep Space Transport (DST)

12 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 cislunar space Deep Space Gateway Deep Space Transport Crew operations in

13 Mars Orbital Mission Elements and Systems Earth Launch System Deliver payloads to cislunar space Deep Space Gateway Deep Space Transport Crew operations in Martian vicinity Earth Moon Mars Orion Transfer crew and cargo from Earth to cislunar space and back to Earth Communications System Earth-to-Mars communication

Mars Orbital 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

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

14 Mars Orbital 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 5 Earth-Mars Transit (early phase) DST DST powered return to HEO (available for 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 11 Lunar Gravity Assist #3 DST None continue mission 11 Lunar Gravity Assist #4 DST None continue mission days 12 Orion Launch SLS/Orion HEO Loiter 12 Earth Return via Orion Orion HEO Loiter days 291 days 10 Deep Space Gateway High-Earth Orbit 1 Checkout before each mission 3 Orion return (no crew) Launch Loiter High Thrust Chemical Low Thrust Electric

15 Mars Surface Mission

16 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 Deep Space Transport 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

powered return to HEO (available for limited time post departure - TBD) 9 6 Earth-Mars Transit Thrusting SEP None continue to Mars 7 Mars Orbit

ascend to orbit 10 Mars orbit reorientation SEP None continue mission 11 Trans-Earth Injection Chem None continue mission 12 Mars-Earth Transit

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 Deep

17 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 5 Earth-Mars Transit (early phase) DST DST powered return to HEO (available for limited time post departure - TBD) 9 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 9 Mars Ascent Ascent None must ascend to orbit 10 Mars orbit reorientation SEP None continue mission 11 Trans-Earth Injection Chem None continue mission 12 Mars-Earth Transit Thrusting SEP None continue mission days High-Mars Orbit 13 Lunar Gravity Assist #3 DST None continue mission 13 Lunar Gravity Assist #4 DST None continue mission days 370 days Orion Launch SLS/Orion HEO Loiter 14 Earth Return via Orion Orion HEO Loiter Deep Space Gateway High-Earth Orbit 1 Checkout before each mission 3 Orion return (no crew) Launch Loiter High Thrust Chemical Low Thrust Electric

18 Mars Surface Mission Key Elements and Systems Phase 4 Mission Elements Earth Space Launch System Deliver payloads to cislunar space Deep Space Gateway Moon Deep Space Transport, Hybrid SEP Cargo Transport Transport t aggregated payloads and crew between Earth and Mars Mars Entry-Descent Lander Land t payloads on Mars Crew Operations on Mars Surface Orion Mars Ascent Vehicle Transfer crew and cargo from Earth to cislunar space and back to Earth Communications System Earth-to-Mars, Mars surface-to-mars orbit, and Mars surface-to-surface communication Transfer crew and cargo from the Mars surface to Mars orbit Legend: Surface Systems MSC Phase 1 elements Phase 2/3 elements Phase 4 elements Surface Habitat and Laboratory Surface Mobility Surface Utilities Logistics Carrier

20 Human Landers: A Leap in Scale Viking 1 & 2 Pathfinder MER A/B Phoenix MSL Human Scale Lander (Projected) Diameter, m Entry Mass, kg t Landed Mass, kg t Landing Altitude, km Peak Heat Rate, W/cm ~120 ~ Landing Ellipse, km 280x x70 150x20 100x20 20x x0.1 Steady progression of in family EDL New Approach Needed for Human Class Landers

21 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

22 Concept Quad Chart HIAD: Hypersonic Inflatable Aerodynamic Decelerator ADEPT: Adaptable Deployable Entry & Placement Technology Capsule Mid L/D

23 HIAD EDL Sequence Deorbit & Deploy Powered Descent Initiation Mach = 3.0, Alt = 8.3 km Pitch to 0 deg AOA Entry AOA= -10 deg Velocity = 4.7 km/s FPA = 10.6 deg Approach 8x100kN engines 80% throttle Touchdown HIAD Retract Surface Ops

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NASA s Exploration Plans and The Lunar Architecture

National Aeronautics and Space Administration NASA s Exploration Plans and The Lunar Architecture Dr. John Olson Exploration Systems Mission Directorate NASA Headquarters January 2009 The U.S. Space Exploration