Asteroid Redirect Mission Concept Overview
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1 National Aeronautics and Space Administration Asteroid Redirect Mission Concept Overview Michele Gates 13th Meeting of the NASA Small Bodies Assessment Group June 29, 2015
2 Asteroid Redirect Mission: Three Main Segments IDENTIFY Ground and space based assets detect and characterize potential target asteroids NEOWISE Pan-STARRS Goldstone Arecibo Infrared Telescope Facility REDIRECT The Asteroid Redirect Robotic Mission (ARRM) uses solar electric propulsion (SEP) based system to redirect asteroid to cis-lunar space. EXPLORE Crew launches aboard SLS rocket, travels to redirected asteroid in Orion spacecraft to rendezvous with redirected asteroid, studies and returns samples to Earth 2 22
3 Key Aspects of ARM Moving large objects through interplanetary space using SEP Integrated crewed/robotic vehicle operations in lunar distant retrograde orbit (LDRO) Integrated attitude control, e.g., solar alignment Multi hour EVAs Lean implementation Clean interfaces, streamlined processes Common rendezvous sensor procurement for robotic vehicle and Orion Integrates robotic mission and human space flight (HSF) capabilities HSF hardware deliveries to and integration and test with robotic spacecraft Joint robotic spacecraft and HSF mission operations 3
4 Asteroid Redirect Mission: 2015 Advancements IDENTIFYING CANDIDATE ASTEROIDS MISSION DESIGN AND SIMULATION OF CRITICAL MISSION OPERATIONS PROTOTYPING AND TESTING CAPTURE OPTIONS INTERNATIONAL DOCKING SYSTEM VACUUM PRESSURE INTEGRATED SUIT TESTING SOLAR ELECTRIC PROPULSION 4
5 Objectives of Asteroid Redirect Mission 1. Conduct a human spaceflight mission involving in-space interaction with a natural object, providing systems and operational experience required for human exploration of Mars. 2. Demonstrate an advanced solar electric propulsion system, enabling future deep-space human and robotic exploration with applicability to the nation s public and private sector space needs. 3. Enhance detection, tracking and characterization of Near Earth Asteroids, enabling an overall strategy to defend our home planet. 4. Demonstrate basic planetary defense techniques that will inform impact threat mitigation strategies to defend our home planet. 5. Pursue a target of opportunity that benefits scientific and partnership interests, expanding our knowledge of small celestial bodies and enabling the mining of asteroid resources for commercial and exploration needs. 5
6 External Engagement (1) June 2013: NASA issued a Request for Information (RFI) to seek new ideas on how to implement the ARM and AGC, alternative ARM concepts, and innovative approaches to broaden participation from partners and the public. Fall 2013: Ideas Synthesis workshop for public synthesis of highest rated responses March 2014: NASA issued the Asteroid Redirect Mission Broad Agency Announcement (BAA), soliciting proposals for concept studies in areas including asteroid capture systems, rendezvous sensors, adapting commercial spacecraft for the Asteroid Redirect Mission and feasibility studies of potential future partnership opportunities for secondary payloads and the crewed mission. In June 2014, NASA announced it selected 18 of the 108 BAA proposals for six-month studies, totaling $4.9 million in awards. 6
7 External Stakeholder Engagement (2) Other assessments, information during pre-formulation Several briefings with feedback SBAG Special Action Team August 2014 CAPTEM input December 2014 May 2015: NASA issued another RFI for Spacecraft Bus Concepts to Support the Asteroid Redirect Robotic Mission and In-Space Robotic Servicing June 2015: Formulation Assessment and Study Team invitation Sept 2015: Community workshop 7
8 ARRM Mission Concept Overview NEA LDRO Moon 4) SEP thrusting to NEA 5) NEA Characterization and Boulder Collection 1) Launch on Delta IV Heavy or SLS 6) Measurable Planetary Defense Demonstration on PHA Sized NEA 7) SEP thrusting to Earth 3) Lunar Gravity Assist 8) Lunar Gravity 2) Phasing Assists 9) SEP Thrusting to Lunar Distant Retrograde Orbit (LDRO) ~ 180 days 10) Crew Visit to Returned Boulder in LDRO EARTH
9 ARRM Capture Phase Introduction Approach 14 days Characterization 72 days Boulder Collection 69 days Planetary Defense Demo 150 days (30 deflection hold & verify) Characterization Approach Note: Asteroid operations timeline varies depending on target asteroid. Times shown are for 2008 EV 5 : total stay time of 305 days with 95 days of margin. Boulder Collection Departure Planetary Defense Demo 9
10 Current Candidate Parent Asteroids ITOKAWA BENNU 2008 EV JU3 Muses C Hayabusa landing Radar OSIRIS-REx target Radar boulders and extremely pronounced bulge at equator suggests movement of loose material Expected valid target - Hayabusa 2 target Comparison of current candidate parent asteroids Asteroids not to scale Itokawa Bennu 2008 EV JU 3 Size 535 x 294 x 209 m 492 x 508 x 546 m 420 x 410 x 390 m 870 m diameter V 5.68 km/s 6.36 km/s 4.41 km/s 5.08 km/s Aphelion 1.70 AU 1.36 AU 1.04 AU 1.42 AU Spin Period hr hr hr hr Type S B (C-grp volatile rich) C (volatile rich) C (volatile rich) Precursor Hayabusa (2005) OSIRIS-REx (9/2016 launch, 8/2018 arrival) NASA continues to look for additional targets in accessible orbits. None currently planned (boulders implied from 2008 radar imaging) Hayabusa 2 (launched 12/4/2014, 7/2018 arrival) Reference ARRM Target 10
11 ARRM Formulation Guidance Capture option B Draft Level 1 requirements Target robotic mission launch date Dec 2020 Cost cap $1.25B not including launch vehicle and mission operations (Phase E) Internal and external dependencies Define capability demonstration implementation approach Target crewed mission launch date Dec 2025 NASA Approval to Proceed to begin Phase A Formulation for Robotic Mission 11
12 Pre-formulation of Crewed Mission Will continue through FY2016 Will involve community and potential partnerships The ARRM Flight System will support visits by crewed missions: 1. Carry GFE hardware to make docking and EVA possible, such as International Docking Mechanism (passive) with: FRAM-type connectors for data and power transfer Retro-reflectors 24 EVA Handrails mounted to the spacecraft exterior Attach for Orion-to-ARRM Telescopic Boom Attach for EVA Boom Installation EVA Telescoping Booms EVA Tool Box with tools 2. Carry robotic systems which could have multiple purposes 3. Provide resources to crewed and future vehicles 125 V unregulated power Data transfer to Earth via X-band or Optical Communications demonstration 4. System is crew safe 12
13 ARM Investigation Team Introduction The Investigation Team will operate similar to a science team Will provide input on the following four areas: science benefit planetary defense deflection demo in-situ resources utilization benefit technology demonstrations International partners and/or commercial partners may wish to have membership on the investigation team also. Supports the robotic mission project manager, and early formulation of the crewed mission, concept of operation, mission requirements, partnerships development, etc. Dan Mazanek, of LaRC is the lead, and Paul Abell, of JSC, is deputy Dan is calling the first phase the FAST (Formulation assessment and support team) 13
14 ARM milestones ARRM Implementation Approach Agency discussion #1 Jun 22 Formulation investigation team* courtesy letter released Jun 24 Spacecraft bus Request for Information responses due Jun 29 Small Bodies Assessment Group June 29 ARRM Implementation Approach Agency discussion #2 Jul 6 NewSpace Conference Jul NASA Advisory Committee HEO Committee Meeting Jul Draft common visible/infra-red camera spec release Jul 30 ARRM lean implementation approach action due Jul 31 SEP 2nd thruster test unit fab and assembly complete Aug 3 ARRM Acquisition Strategy Meeting Aug 4 Exec Session management structure discussion Aug 5 Requirements Closure Technical Interchange Meeting Dec 15 * Formulation Assessment and Support Team (Sept - Dec 2015) June 26,
15 ARM: A Capability Demonstration Mission High Efficiency Large Solar Arrays Solar Electric Propulsion IN-SPACE POWER & PROPULSION: High efficiency 40kW SEP extensible to Mars cargo missions Power enhancements feed forward to deep-space habitats and transit vehicles EXTRAVEHICULAR ACTIVITIES: Primary Life Support System design accommodates Mars Sample collection and containment techniques Follow-on missions in DRO can provide more capable exploration suit and tools Exploration EVA Capabilities Deep-Space Rendezvous Sensors & Docking Capabilities TRANSPORTATION & OPERATIONS: Capture and control of noncooperative objects Rendezvous sensors and docking systems for deep space Cis-lunar operations are proving ground for deep space operations, trajectory, 15 and navigation 15
16 SEP Module Extensibility Concept for Mars Asteroid Redirect Mission SEP/Chemical Hybrid 50-kW Solar Array 40-kW EP System 10-t Xenon Capacity with Refueling Capability 190-kW Solar Array 150-kW EP System 16-t Xenon Capacity 250 to 400-kW Solar Array 150 to 300-kW EP System 24-t Xenon Capacity With Xe Refueling Capability 16
17 A Sustainable Exploration Approach Mars Split Mission Concept 17 17
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