National Aeronautics and Space Administration Overview of Current Advanced Mission Studies at JSC February 1, 2017 Joe Caram Exploration Mission Planning Office Exploration Integration and Science Directorate - JSC
Exploration Integration and Science Directorate Vanessa Wyche, Director Dr. Eileen K. Stansbery, Deputy Director & Center Chief Scientist* Glenn Lutz, Associate Director Chris Culbert, Center Chief Technologist* Strategic Business and Partnerships Integration (XB) Integrated Cost/Schedule Analysis Performance Management EISD Business Integration Center Risk Management Center Partnership Representative Exploration Communications Strategy Exploration Mission Planning Office (XM) HEO Architecture and Mission Planning/Studies Mars Study Capability HAB Formulation Exploration Development Integration Office (XS) Exploration Programs SE&I Exploration Mission Integration HEO Systems Protection Analysis Exploration Technology Office (XT) AES STMD IRAD SBIR STTR Tech Transfer Tech Partnerships Astromaterials Research and Exploration Science Division (XI) Mission Support Science Curation EVA Office (XX) ISS EVA Operations ISS EVA Sustaining Engineering Advanced Suit Development & Integration Mission: We make Human Space Exploration Happen
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Human Space Exploration Phases Today Phase 0: Exploration Systems Testing on ISS Ends with testing, research and demos complete* Asteroid Redirect Crewed Mission Marks Move from Phase 1 to Phase 2 Phase 1: Cislunar Flight Testing of Exploration Systems Ends with one year crewed Mars-class shakedown cruise Phase 2: Cislunar Validation of Exploration Capability * There are several other considerations for ISS end-of-life Proving Ground Phase 3: Crewed Missions Beyond Earth-Moon System Phase 4a: Development and robotic preparatory missions Phase 4b: Mars Human Landing 2016 2020 2030 Missions 42
Human Exploration of Mars Capability Needs Launch Multiple launches Short spacing Large mass: 130 t Large Volume 10 x 30 m Space Transportation Advanced propulsion to reduce mass Fast Transits for Crew (180 days) Limited / lack of quick aborts Entry Descent and Landing Large mass (40 t) / Large volume Abort to surface Precision landing Crew Surface Health and Support Crew acclimation post landing Human Support (radiation, hypogravity, dust, behavior) Planetary protection Operations Automated, rendezvous and docking Pre-deploy cargo No logistics Reliability, maintenance and repair Autonomous operations post landing Infrastructure emplacement (power) High continuous power (40-400 kwe) ISRU oxygen production - atmosphere Multiple EVAs, long-range roves, routine exploration
Deep-Space Habitation Development Strategy Phase 0: SYSTEMS DEVELOPMENT AND TESTING ON ISS / LEO LEO COMMERCIALIZATION Bigelow Expandable Activity Module Habitation System Projects Spacecraft Fire Safety Human Research and Performance Life Support Systems Advanced Avionics Exercise Systems Phase 1: DEEP SPACE TESTING Docking / berthing Systems EVA Phase 2: DEEP SPACE VALIDATION Gateway NextSTEP Habitation / Int. Partners Deep Space Transport Shakedown Cruise 4
NextSTEP Habitation Overview NextSTEP Phase 1: 2015-2016 NextSTEP Phase 2: 2016-2018 BIGELOW AEROSPACE LOCKHEED MARTIN ORBITAL ATK NANORACKS Cislunar habitation concepts that leverage commercialization plans for LEO LOCKHEED MARTIN BIGELOW AEROSPACE ORBITAL ATK BOEING Partners develop required deliverables, including concept descriptions with concept of operations, NextSTEP Phase 2 proposals, and statements of work. SIERRA NEVADA CORPORATION FIVE GROUND PROTOTYPES BY 2018 ORBITAL ATK BOEING Partners refine concepts and develop ground prototypes. NASA leads standards and common interfaces development. ONE CONCEPT STUDY Initial discussions with international partners FOUR SIGNIFICANTLY DIFFERENT CONCEPTS RECEIVED Define reference habitat architecture in preparation for Phase 3. Phase 3: 2018+ Partnership and Acquisition approach, leveraging domestic and international capabilities Development of deep space habitation capabilities Deliverables: flight unit(s) 7 6
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Mars Trajectory Classes A trip to Mars with a return back to Earth is a double rendezvous problem Mars round-trip missions are flown in heliocentric space Relative planetary alignment is a key driver in the mission duration and propulsion required Opposition Class ( Short-Say ) Missions: Non-optimum transfers which result in greater energy requirements Stay times at Mars short (typically 30-60 days) Total transfer energy increases as stay time is increased Conjunction Class ( Long-Stay ) Missions: Minimum Energy transfers both outbound to, and inbound from, Mars Stay times at Mars ( typically 500 days) adjusted to minimize energy of the transfers Example Short-Stay Opposition Class Mission MARS ARRIVAL MARS ARRIVAL Selected Conjunction Class base on strategic principles of sustained presence Example Long-Stay Conjunction Class Mission MARS DEPARTURE EARTH RETURN SUN g SUN g MARS DEPARTURE EARTH RETURN VENUS SWING-BY EARTH DEPARTURE EARTH DEPARTURE 9