National Aeronautics and Space Administration Long Duration Cislunar Habitation Andrea Riley | International Space Station Division | NASA HQ | May 2016

Agenda Brief History Exploration Strategy Long Duration Habitation Capability Goals Habitation Capability Development Efforts 1

A Brief History of Beyond-LEO Spaceflight Architecture Development Leadership and America’s Future in Space National Commission on Space NASA Case Studies America at the Threshold 90-Day Study First Lunar Outpost Mars Design Reference Mission 1.0 Mars Design Reference Mission 3.0 DPT / NEXT Exploration Blueprint Mars Design Reference Architecture 5.0 Review of U.S. Human Spaceflight Plans Committee Challenger Constellation Program Lunar Architecture Team Global Exploration Roadmap Exploration System Architecture Study Bush 41 Speech Bush 43 Speech Columbia Obama Speech Human Journey to Mars – Thoughts on an Executable Program (JPL) Evolvable Mars Campaign Pathways to Exploration 2

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Ends with testing, research and demos complete* Asteroid Redirect Crewed Mission Marks Move from Phase 1 to Phase 2 Ends with one year crewed Mars-class shakedown cruise Today 2030 Mid-2020s *There are several other considerations for ISS end-of-life Transition from ISS to Cislunar Space: Framework 4 Phase 0: Exploration Systems Testing on ISS Phase 1: Cislunar Flight Testing of Exploration Systems Phase 2: Cislunar Validation of Exploration Capability 4

Phase 1: Cislunar Flight Testing of Exploration Systems  Demonstrate that SLS and launch processing systems can insert both Orion and co-manifested payloads into cis-lunar space  Demonstrate that Orion and mission operations can conduct crewed missions in cis-lunar space at least for 21 days  Demonstrate Mars-extensible systems and mission operations that reduce risk for future deep space missions (with EVA) beyond 21 days Phase 1: Cislunar Flight Testing of Exploration Systems  Demonstrate that SLS and launch processing systems can insert both Orion and co-manifested payloads into cis-lunar space  Demonstrate that Orion and mission operations can conduct crewed missions in cis-lunar space at least for 21 days  Demonstrate Mars-extensible systems and mission operations that reduce risk for future deep space missions (with EVA) beyond 21 days Preliminary Top-Level Phase Objectives Phase 0: Exploration Research and Systems Testing on ISS  Test Mars-capable habitation systems – ECLS, environmental monitoring, crew health equipment, exploration generation EVA suit, fire detection/suppression, radiation monitoring  Complete human health & performance research and risk reduction activities  Demonstrate exploration related technologies and operations Autonomous crew operations Docking, prox ops Phase 0: Exploration Research and Systems Testing on ISS  Test Mars-capable habitation systems – ECLS, environmental monitoring, crew health equipment, exploration generation EVA suit, fire detection/suppression, radiation monitoring  Complete human health & performance research and risk reduction activities  Demonstrate exploration related technologies and operations Autonomous crew operations Docking, prox ops Phase 2: Cislunar Validation of Exploration Capability  Validate Mars class habitation and habitation system functionality and performance  Validate Mars class human health and performance  Validate operational readiness to leave Earth-Moon system via one year+ “shakedown cruise” (no resupply/crew exchanges, limited ground interaction, etc.) Phase 2: Cislunar Validation of Exploration Capability  Validate Mars class habitation and habitation system functionality and performance  Validate Mars class human health and performance  Validate operational readiness to leave Earth-Moon system via one year+ “shakedown cruise” (no resupply/crew exchanges, limited ground interaction, etc.)  Validate cislunar as staging orbits  Use of high power SEP for deep space missions  Asteroid related origins of the solar system science objectives  Demonstrate real-time robotic lunar surface activities  In situ resource utilization demonstrations  Validate cislunar as staging orbits  Use of high power SEP for deep space missions  Asteroid related origins of the solar system science objectives  Demonstrate real-time robotic lunar surface activities  In situ resource utilization demonstrations  Robotic manipulation technology and techniques demonstrations  Remote presence technology development and demonstrations  Earth/space science  Enable development of LEO commercial market  Robotic manipulation technology and techniques demonstrations  Remote presence technology development and demonstrations  Earth/space science  Enable development of LEO commercial market Origins of the universe, lunar rover volatile sample return Other scientific or research objectives? Origins of the universe, lunar rover volatile sample return Other scientific or research objectives? enables 5

4 Crew for days Common pressure vessel 15 year lifetime with long dormancy periods Design for reusability across multiple missions 100 m 3 habitable volume and dry mass < 22 t Autonomous vehicle health monitoring and repair Advanced Exploration ECLSS with >98% H 2 O recovery and 75% O 2 recovery from reduced CO 2 ECLSS System (w/o spares): <5 t mass, <9 m 2 volume, <4 kW power Environmental monitoring with >80% detection rate without sample return 14-kW peak operational power and thermal management required Autonomous mission operations with up to 24 minute one-way time delay Autonomous medical care, behavioral health countermeasures, and other physiological countermeasures to counteract long duration missions without crew abort Exercise equipment under 500 kg Provide g/cm 2 of radiation protection EVA pressure garment and PLSS <200 kg Contingency EVA operations with 1 x 2-person EVA per month Communications to/from Earth and between elements Live and operate in microgravity during trip to/from Mars 4 crew for up to 1,100 days 93 m 3 volume for logistics and spares Logistics Mass: 21 t 4 years dormant before use and between uses Live and operate in microgravity at Phobos 4 crew for up to approx. 500 days 48 m 3 volume for logistics and spares Logistics Mass: 10.7 t EVA system with Phobos mobility and dust mitigation 4-5 years dormant before use 3 years dormant between uses Live and operate on the Mars surface in 1/3 g 4 crew for up to approx. 500 days 48 m 3 volume for logistics and spares Logistics Mass: 10.7 t 4 years dormant before use 3-4 years dormant between uses EVA system with surface mobility, dust mitigation, and atmospheric compatibility 6 6

Specific Habitation System Objectives System IncludesTodayDeep Space Goal Life Support Air revitalization, water recovery, waste collection and processing 42% recovery of O2 from CO2; 90% recovery of H2O; <6 mo MTBF for some components >75% recovery of O2 from CO2; >98% recovery of H2O; >2 yr MTBF Environmental Monitoring atmosphere, water, microbial, particulate, and acoustic monitors Limited, crew-intensive on-board capability; rely on sample return to Earth On-board analysis capability with no sample return; identify and quantify species and organisms in air & water Crew Health exercise equipment, medical treatment and diagnostic equipment, long-duration food storage Large, cumbersome exercise equipment, limited on-orbit medical capability, food system based on frequent resupply Small, effective exercise equipment, on- board medical capabilities, long-duration food system EVA Exploration suitISS EMU’s based on Shuttle heritage technology; not extensible to surface ops Next generation spacesuit with greater mobility, reliability, enhanced life support, operational flexibility Fire Non-toxic portable fire extinguisher, emergency mask, combustion products monitor, fire cleanup device Large CO2 suppressant tanks, 2- cartridge mask, obsolete fire products. No fire cleanup other than depress/repress Unified fire safety approach that works across small and large architecture elements Radiation Protection Low atomic number materials including polyethylene, water, or any hydrogen-containing materials Node 2 CQ’s augmented with polyethylene to reduce the impacts of trapped proton irradiation for ISS crew members Solar particle event storm shelter based on optimized position of on-board materials and CQ’s with minimized upmass to eliminate major impact of solar particle event on total mission dose 7

Ends with Industry Developed Concepts – Decision on contract(s) continuation Ends with Industry Developed Concepts – Decision on contract(s) continuation Ends with: 1) Industry Developed Ground Prototype Module performing integrated tests, 2) identified standards, and 3) identified GFE – Decision point on contract continuation and if so, what contractor specific element(s) focus and NASA provided GFE Ends with: 1) Industry Developed Ground Prototype Module performing integrated tests, 2) identified standards, and 3) identified GFE – Decision point on contract continuation and if so, what contractor specific element(s) focus and NASA provided GFE Ends with Deployment and Operational Status of Deep Space Habitat NextSTEP BAA Habitat Development Approach 8 NextSTEP Phase 1 Obtain Innovative Cislunar Habitation Concepts that leverage Commercialization Plans Deliverables include Concept Description with concept of operations, Phase 2 proposal and SOW NextSTEP Phase 1 Obtain Innovative Cislunar Habitation Concepts that leverage Commercialization Plans Deliverables include Concept Description with concept of operations, Phase 2 proposal and SOW NextSTEP Phase 2 Continue Concept refinement and development of ground prototype module(s) and standards, culminating with an integrated test Contractor: Concept description with concept of operations, Phase 3 proposal and SOW, delivery of ground prototype module(s) NASA: Define reference habitat architecture based on contractor concepts and identified GFE in preparation for Phase 3 NextSTEP Phase 2 Continue Concept refinement and development of ground prototype module(s) and standards, culminating with an integrated test Contractor: Concept description with concept of operations, Phase 3 proposal and SOW, delivery of ground prototype module(s) NASA: Define reference habitat architecture based on contractor concepts and identified GFE in preparation for Phase 3 Phase 3 Development of Deep Space Habitat for Proving Ground Phase 1 Objectives Deliverables include Flight Unit (note may be multiple modules integrated via common interfaces and standards) Phase 3 Development of Deep Space Habitat for Proving Ground Phase 1 Objectives Deliverables include Flight Unit (note may be multiple modules integrated via common interfaces and standards)

NextSTEP BAA Phase 1: Habitation Awards (Habitats) 9 Bigelow Aerospace LLC | Las Vegas, NVLockheed Martin | Denver, CO Orbital ATK | Dulles, VA Boeing |Houston, TX 9

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