A Flexible Path of Human and Robotic Exploration Developed for the Review of U.S. Human Space Flight Plans Committee NASA Analysis Summary for FISO Team Feb 10, 2010 Dr. David Korsmeyer Intelligent Systems Division (Code TI) NASA Ames Research Center Phone: (650) 604-3114 [email protected] Scenario E (FlexPath) Team David Korsmeyer (ARC) Gabe Merrill (LaRC) Rob Landis (ARC) Rob Falck (GRC) Dan Mazanek (LaRC) Rob Adams (MSFC) Leon Gefert (LaRC) Dan Adamo (JSC) Frank Bauer (HQs) John Casani (JPL) Richard Mattingly (JPL) Steve Oleson (GRC) 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 2 NASA Engineering Analysis Team (EAT), support to HSF Committee Flexible Path Study Background • Engineering Analysis Team (NASA) support to the HSF committee was kicked off on May 21st 2009. • EAT Spent the next month collecting background studies and waiting. • June 26th, Ed Crawley released the first draft of the Study Analysis guidance for the EAT to do • June 30th, Scenario Leads are chosen for the 5 Scenarios with 1 month until Briefing the Committee subteam on initial results on July 22nd, 2009 Scenario A is the Lunar Base, Scenario B is the Lunar Global, Scenario C is Moon as a testbed for Mars, Scenario D is Mars First (and only) Scenario E is the Flexible Path 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 3 Previous Exploration Studies influencing the Scenarios 1988 Evolutionary 1989 90-Day Study 1991 Synthesis Report Strategy 1989 Case Study 2004 ESAS Lunar Base (Approaches A through (Moon to Stay and Mars (Lunar Outpost to Early (Lunar Evolution) 2005+ Constellation D) Exploration) Mars) 1993 First Lunar 1991 Synthesis Report 1988 Case Study Outpost Lunar Global (Science Emphasis for (Lunar Observatory) (Note: Design the Moon and Mars) Reference Mission) 1990 90-Day Study 1991 Synthesis Report Moon to Mars (Approach E) (Mars Exploration) Mars DRM 1988 Case Study 1989 Case Study 1989 Case Study 1.0,3.0,4.0,&5.0 Mars First (Human Expeditions to (Mars Evolution) (Mars Expedition) (Note: Design Mars) Reference Mission) 2007 Exploration 2007 & 2008 NEO 1988 Case Study Blueprint - SEL2 Feasibility Studies Flexible Path (Human Expedition to (Note: Design (Note: Design Phobos) Reference Mission) Reference Mission) 1991 Synthesis Report Other (Space Resource Utilization) Note: Some studies do not correspond exactly to our scenarios 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 4 A Flexible Path of Human and Robotic Exploration ! A Flexible Path for Exploration • Frequent, measured, and visible human exploration of space beyond Earth orbit • Cross-leverage the human and robotics capabilities • Gain operational experience and system validation - For long duration missions (90 – 600 days) beyond low-Earth orbit (LEO) - In vicinity of low-gravity planetary bodies ! Key Scientific Return • Exploration while producing exciting new science each step of the way • Understanding human impacts of - long-term radiation environment in deep space - extended exposure to micro-gravity environment • Multi-kilogram sample return from solar system bodies. Some radically different from Moon/Mars • Telerobotic exploration and sampling of the surface of Mars ! Public Engagement and Inspiration • Cultivate and maintain public support by taking on demonstrably new, visible and different space missions • Unprecedented deep space missions with dramatic perspective of the Itokawa. Earth-Moon system and voyages to NEOs, Mars and Venus Courtesy JAXA 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 5 Scenario E) Flexible Path • Piloted missions to many places in the inner solar system • Orbit planets with deep gravity wells; Rendezvous with small bodies • Tele-robotically explore and sample planetary surfaces NEOs Sun - Earth L 2 L Moon 2 L4 L1 Mars L5 Earth Phobos L3 & Deimos Sun - Earth L1 Venus • Visible exploration progress to interesting destinations • Regular return of new scientific knowledge • Minimizes destination specific systems (landers, etc) Sun2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 6 !"#$#%&'(")*%+',*-./'0'1//*234)%/' Ground Rules • Piloted missions to many different venues is a key metric • Planetary surfaces within a deep gravity well will be accessed telerobotically by the Crew • Robotic precursors to NEO missions, and for Mars surface sample collection • TransHab or equivalent habitat space is commercially / IP available • Using Constellation launch vehicle capabilities as baseline; Ares I & V • Orion capsule used for crew launch from Earth, Earth entry, descent and landing (EDL), and in-space piloted missions. No changes other than block upgrades Assumptions • 1 crewed flight, plus 1-2 cargo missions, per year • 3-5 person crew with closed-loop Environmental Control & Life Support System (ECLSS) mass which varies with mission duration • EELV upper stage with low boil-off available in 2015 • Cryogenic oxygen/hydrogen Earth Departure Stage (EDS) with low boil-off available initially and on- orbit “Topping-off” of EDS in LEO available (not necessarily a depot) • Nuclear Thermal Rocket (NTR) propulsion available in late 2020’s • Mission maximum duration of approximately 2 years • Earth entry velocity not to exceed 12 km/s • Chemical Isp = 448 sec; NTR Isp = ~900 sec 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 7 Scenario E Analysis Process LV Architecture #2 Mission Analysis for crew various destinations Scenario E) LV Architecture #1 G & A Trajectory Analysis of Flexible Missions Develop Transportation Manifest of Flexible Missions Assess and Determine Enabling Technologies Robotic Precursors 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 8 Scenario E) Flexible Path Mission Sequence Sequence for Scenario 1. Unpiloted mission to Sun-Earth L1 for system test (or lunar flyby) 2. Piloted mission to lunar flyby and/or to Earth-Moon L1 3. Mission to Sun-Earth L2 to service science assets 4. Mission to Sun-Earth L1 to experience the interplanetary radiation environment 5. Several missions to NEOs to rendezvous and return samples 6. Flyby mission to Mars with telerobotic operation of surface assets 7. Mars Phobos rendezvous and Mars/Phobos surface sample return 8. ?Venus orbital mission, and balloon teleoperation Initial Operational Capability (IOC) is human presence in orbit of Mars or Venus 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA 9 Flexible Path Architecture Flexible Path Scenario E is a sequence of Inner Solar System missions with increasing capability into >365 day duration the inner solar system Limited Inner Solar System Mars ~200 day duration Phobos Sun-Earth Vicinity NEOs Near Earth 30-90 day duration NEOs Mars 21+ day duration Sun – Earth Flyby Earth’s L2 Minimum Lagrange L Capability Points 2 7-14 day duration Sun – Earth L Lunar 1 L1 Flyby Zero boil off & Refueling 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 10 Scenario E Milestones, Destinations & Capabilities Humans in Humans in First Humans to Humans in Cislunar Interplanetary Humans to Mars Mars Orbit Space Space NEOs Vicinity & Sample Return 7 10 21 32 90 155 190 440 780 491 Days Days Days Days Days Days Days Days Days Days Unpiloted Earth Sun Sun NEO NEO Lunar Lunar Moon Earth Earth (2008 (2007 Mars Phobos Venus Test Flyby L1 L2 L1 EA9) UN12) Flyby Flyby Year 1 2 3 4 5 6 7 8 9 10 11 Minimal Near Earth Sun Earth Limited Inner Inner Solar Vicinity Solar System System MSR Sample NEO Telescope Phobos Capture at Precursor Servicing Precursor Mars Sampler Phobos 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 11 Orion Support of Flexible Path Missions ! “Lunar” Orion Capabilities • Support of 4 crew for 18 days • Provides ~1,550 m/s total delta-v* • ~1,500 We power to other elements ! Flexible Path Mission Modifications • Support of crew for 90+ days Example: The CEV can perform 1,700 m/s with - Consumables ~1,350 kg mass savings - Habitation / exercise Example: The CEV can push an additional 3,200 • Radiation protection for longer kg through 1,300 m/s duration deep-space mission * Total delta-v available dependent on propellant load and vehicle mass 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 12 In-space Propulsion and Propellant Resupply Trades With propellant resupply, an EDS could perform transfer mission injection for Flexible Path missions ! Trade EDS use/resupply vs NTR development costs/use ! Trade EDS staging vs EDS propellant resupply for missions EELV Centaur Upper Stage Ares V Earth Departure Stage (EDS) DRA 5 Nuclear Thermal Rocket (NTR) 2/10/10 Korsmeyer :: Flexible Path Concept :: Pre-decisional NASA Page 13 Flexible Path Transportation Elements Initial and then Modest Capability Full Capability (NTR = 3.5 launch) or (Chemical = 5.5 launch) • !"#$%&'#()&*++,"&-(./,&01,%(.2"&.%3&(),%&45-6& • 7."8&E".%8#(&F,)#G@,&07EF6&3,H%,3&D$"&IJJK&5LMN& 7."8&M"G)#(,G(2",&-(23=&01),?#G.@&O8&>EL6& • 7#88#$%8&($&92%."&!":#(;&9./".%/,&<$#%(8&.%3& %,.":=&>4!8& • -2++$"(8&?#88#$%8&($&7."8&!":#(&0<)$:$86;&F,%28&!":#(& • 1$?+@,(,@=&4A+,%3.:@,& .%3&@,88&.GG,88#:@,&>4!8& • B%(,/".C$%&#%&4."()&!":#(;&#%3,+,%3,%(&$D&B--& • <$(,%C.@@=&",28.:@,&3,8#/%&0,AG,+(&D$"&!"#$%&,@,?,%(8& .%3&3"$+&(.%P86& • *++,"&8(./,&3,+@$=,3&#%&$":#(& O#.&449F;&(),%&M",8&F&$"&),.O=&@#Q& ,R2#O.@,%(& • 1",'&.%3&!"#$%&3,+@$=,3&O#.& M",8&B&$"&,R2#O.@,%(& • M@(,"%.(,&#8&)2?.%S".(,3&M",8&FS Infrastructure required for Mission [email protected]&O,)#G@,&($&/.#%&8#%/@,&