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TAAT Study Team Applications and Plans

Satellite Servicing. ISRU. SBSP. Solar Electric Propulsion. Propellant Depot. MMSEV. TAAT Study Team Applications and Plans. Mack Henderson FISO/January 26, 2011. Edward.M.Henderson@nasa.gov. TAAT OBJECTIVES. Identify key technologies that can advance Space Exploration

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TAAT Study Team Applications and Plans

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  1. Satellite Servicing ISRU SBSP Solar ElectricPropulsion Propellant Depot MMSEV TAAT Study Team Applications and Plans Mack Henderson FISO/January 26, 2011 Edward.M.Henderson@nasa.gov

  2. TAAT OBJECTIVES • Identify key technologies that can advance Space Exploration • Determine technology interaction to achieve common goals • Define technology demonstrations that can be done soon - what are affordable - what can be partnered Maximize use of existing Assets- facilities, H/W, FSW, skills, etc.

  3. TAAT Activity • The Technology Applications Assessment Team selected several applications that would add value for Exploration • The Team is independently assessing these applications for future implementation • The Team is supporting similar technology assessments in other areas: • DARPA/NASA tasks • MacGyver team • Human Exploration Framework Team (HEFT) • Office of the Chief Technologist (OCT)CISS Commercial In-Space Servicing • Future in Space Operations (FISO)

  4. Technology Applications (Leads) 1. Satellite Servicing Mission(s) (Ted Talay) 2. ISRU Lunar Mission (Paul Spudis/Bill Rothschild) 3. Space Based Solar Power Demo (Bill Rothschild) 4. Solar Electric Propulsion Vehicle (Larry Schmidt/Sonny White) 5. Propellant Depot (Wally Twichell) 6. Multi-Mission Space Exploration Vehicle (Mark Holderman) Lead Develops Plan

  5. Satellite Servicing Assessments Description: • To support satellite servicing studies underway in the Agency (HQ, GSFC, JSC) and DARPA. • Identify transportation options, human habitation, and space vehicle options that can support satellite servicing scenarios. • Identify technologies (e.g. heavy-lift launch) that can enable or enhance human and robotic servicing missions • Examine the commercial viability of satellite servicing for ops scenarios, concepts & technologies identified. • Define a near-term, servicing demonstration mission Schedule/Cost: Approach: • Support NASA/DARPA Manned GEO Servicing Study thru April 2011 • Support GSFC Servicing Study thru April 2011 • Demonstration Mission Definition - Large, multi-satellite GEO servicing (provide life extension via end-of-life relocations) • Interface with NASA/DARPA study teams to provide support in areas noted • Conduct Notional Mission trades and definition especially in human GEO servicing and use of heavy-lift launch systems. • Identify key technologies, ops scenarios, and system concepts • Integrate into a near-term servicing demonstration mission definition • Supports requests from NASA, GSFC, JSC, SOMD, OCT, DARPA stakeholders • Provides data to same to support decision-making Justification:

  6. ISRU Water Processing Demo • Find, extract, process, and store water on the Moon • Single launch on an Atlas V-551 • 6,420 kg Lunar Lander (GLOW) • Landing near a crater at the Moon’s North Pole • Prospecting rover in crater where water ice exists • Dig lunar feed stock and haul to processing plant • Demonstrate water extraction and storage Multiple sources provide clear evidence of water in this crater 11 12 13 14 15 16 17 18 Rozhdestvensky N ATP Launch PDR CDR TRR • Key Demo Technologies • Precision navigation and landing near • the crater rim at the Moon’s North Pole • Pair of Comm/Nav Sats in lunar orbit • High power PV array • Deployable Rover; rechargeable batteries • Prospecting sensor suite to find water • Diggers suitable for lunar regolith • ISRU processing plant • Water storage on the Moon F A F B F C F D FRR PRELIMINARY F E Prog Mgmt / SE&I $120M Comm/nav sats $ 70 M Lunar Lander (1655 kg) $250M Rover (530 kg) $100M ISRU Processor (210 kg) $ 50M Launcher (Atlas V) $180M Operations Segment $ 20M Mgmt Reserve (300 kg) $100M Total $900M ROM Cost

  7. Pilot Beam Rectenna Space Based Solar Power Beaming Demo • Proof of concept for wireless power transmission from space • Significant power levels > 25 kW to users • Safe and controllable power beaming from space to ground (Microwave) • Growth paths for exploration, military and commercial applications • Proof of concept for Ground to Space Laser power beaming • Closely coupled with solar power concept • Growth paths for space to space power beaming applications Ground to Space Laser Solar Dynamic Satellite Space to Ground Microwave Solid State Laser Atlas V Demo Schedule / ROM Cost • Key Demo Technologies • Retrodirective phase lock beam control • High power solid state laser • Inflatable solar power concentrator • Solar dynamic power generator • High energy flywheels • High efficiency microwave converters • Large deployable rectenna farm Prog Mgmt / SE&I $185M Satellite Bus (330 kg) $115M SBSP Payload (6,200 kg) $470M Launcher (Atlas V) $175M Ground Segment $150M Operations Segment $ 40M Other (250 kg) $ 25M Mgmt Reserve (850 kg) $145M Total $1.3 B PRELIMINARY Bill Rothschild wjrothschild@yahoo.com713-248-2882

  8. SEP Demo Description: • Perform high power SEP demonstration • 30kW solar power • Battery augmentation to facilitate 200kW short duration • Total system delta-v: ~15km/sec • System will demonstrate two high power EP engine technologies: VASIMR & Hall_or_ION • Demo will also make use of mini free flying inspection spacecraft • Utilize emerging advanced solar technologies such as DARPA’s FAST or SOLAROSA. Approach Schedule/Cost: • Vehicle can launch to LEO on Falcon 9 • Vehicle can achieve Mars orbit • Delta-v split between two EP technologies • Design, Development, Test, & Evaluation ~4 years • Launch Vehicle Categories: Falcon 9, Atlas V, Delta IV – final variant depends on final SEP tug mass and cargo • Cost estimate: ~$500 million (includes launch cost on F9) Justification: • All future exploration plans beyond LEO will make use of SEP technology elements in the architectures. • SEP is a requirement for manned exploration beyond CIS-Lunar space. • SEP is orders of magnitude more efficient than chemical and will result in smaller vehicle architectures, and allow selection of smaller (and cheaper) launch vehicles

  9. Depot at GEO Description and Objectives • Provide storage for satellite pressurants and propellants in orbit in close proximity to multiple users. • Provide docking and replenishment service to robotic satellite servicing vehicle. • Enable extension of service life to on orbit satellites. • Enable multiple servicing missions by robotic servicing vehicle. • Reduce cost of satellite servicing missions. Approach Cost and Schedule • Maximize use of existing satellite technology • Mature AR&D and on orbit fluid transfer technologies • System includes depot and tanker • Robotic Servicing Vehicle developed in separate joint DARPA/NASA program • Allow commercial delivery of fluids to Depot by commercial operators. Justification • Provides significant national capability • Expands opportunities for commercial space Phase 1 DDT&E: $150M

  10. MMSEV (Multi-Mission Space Exploration Vehicle) Technology Applications Assessment Team M.L. Holderman JSC/SSP Description and Objectives: • Long-duration space journey vehicle for crew of 6 for periods • of 1 -24 months • CIS-lunar would be initial Ops Zone [shakedown phase] • Exo-atmospheric, Space-only vehicle • Integrated Centrifuge for Crew Health • ECLSS in deployed Large Volume w/ shirt-sleeve servicing • Truss & Stringer thrust-load distribution concept (non-orthogird) • Capable of utilizing variety of Mission-Specific • Propulsion Units [integrated in LEO, semi-autonomously] • Utilizes Inflatable & Deployed structures • Incorporates Industrial Airlock for construction/maintenance • Integrated RMS • Supports Crewed Celestial-body Descent/Return • Exploration vehicle(s) • Utilizes Orion/Commercial vehicles for crew rotation Non – Atmospheric Universal Transport Intendedfor Lengthy United States - - - - - - - X-ploration Approach: Justification: • Multiple HLV (2-3) & Commercial ELV launches • On-orbit LEO Integration/Construction • First HLV payload provides Operational, self-supporting Core • Centrifuge utilizes both inflatable & deployed structures • Provides Order-of-Magnitude increase in long duration journey • capability for sizeable Human Crews • Exploration & Discovery • Science Packages • Meets the requirement of Sec. 303 MULTIPURPOSE CREW VEHICLE • Title III Expansion of Human Space Flight Beyond the International • Space Station and Low-Earth Orbit, of the “National Aeronautics and • Space Administration Authorization Act of 2010” Collaborators/Roles: • JPL:Deployment Integ., Communications/Data Transmission • AMES: ECLSS, Bio-Hab • GSFC: GN&C, Independent System Integrator • GRC: PowerPumps, PMD, External Ring-flywheel • LaRC: Hoberman deployed structures & Trusses • MSFC: Propulsion Unit(s) & Integration platform , Fluids Transfer & Mgmt. • JSC: Proj. Mgmt – SE&I , ECLSS, Centrifuge, Structures, Avionics, • GN&C, Software, Logistics Modules • NASA HQTRS: Legislative & International Lead COST: $ 3.7 B DCT & Implementation 64 months M.L. Holderman - JSC/SSP

  11. Applications Concept Definition Plan • Brief description of the Application, including a quad chart • Identify launch systems and existing assets being used • Concept of Operations and Design Reference Mission • Design description including configurations, main subsystems, and performance sensitivities • Identify Challenges and key risks • Identify Partnering Opportunities: Other Centers, Contractors, Government Agencies, Internationals, etc. • Who are the potential Customers • How Application interacts with other technologies to support Exploration plans • Define a rough development schedule, including the projected first flight date and a Development cost “Swag”

  12. TAAT Milestones OCT NOV DEC JAN ‘11 FEB MAR Weekly Reviews MacGyver Brief SSPReview JSCReview SOMD Review Preliminary Plans CISSBrief FISOBrief JSC Review Final Plans SSPReview SSP Review HQ Review

  13. Technology Applications Roadmap 2011 2015 2020 Retire 2011 Shuttle EELV Falcon 9 Taurus II 70-100 mT 130 mT Super Heavy ISS Human Sat. Servicing Robotic Sat. Servicing Satellite Servicing ISS Dextre Demo ISRU Small Scale Full Scale SBSP ISRU SBSP High Orbit Demo ISS Demo SEPDemo Sojourner-X 200 SEP Aurora ISS Demo LP Depot Depot GEO Depot Fluid Transfer ISS MMSEV MMSEV Vac. Chamber Demo AG ISS

  14. Space Exploration Infrastructure Concept

  15. TAAT Interactivity EELV COM/COTS HLV HLLV 2010 2020 HEFT NASA/DARPA MacGyver OCT/CISS FISO MMSEV SEP Sat. Serv. SBSP ISRU Depot GEO Moon LP NEO Mars Break Point Analysis EELV Falcon 9 Taurus II 70-100 mT 130 mT Super Heavy 15

  16. Summary • The team has identified six technology applications for assessment • Technologies were selected based the collective benefits for future Exploration • Leads for each application are assigned to develop a plan • Preliminary plans ready for review • TAAT overview has been shared with other teams • The team will continue to assess recommended applications for further development

  17. Forward Plans • Share preliminary plans with SOMD and Center(s) management • Continue to refine and mature plans consistent with management direction • Perform necessary trade studies to determine the best application demonstrations • Continue to coordinate with other teams on common goals • Brief candidate partners on TAAT concepts and solicit participation agreements • Update plans for formal review with appropriate NASA management by March

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