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A Lunar Fission Surface Power (FSP) System Presented to: Nuclear and Emerging Technologies for Space NETS 2009

A Lunar Fission Surface Power (FSP) System Presented to: Nuclear and Emerging Technologies for Space NETS 2009. James Werner/INL, Project Lead June 15, 2009. History of Space Nuclear Power. SNAP-10A (Agena). Fission Reactor Systems SNAP-10A (launched 1965) SP-100 (cancelled 1992)

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A Lunar Fission Surface Power (FSP) System Presented to: Nuclear and Emerging Technologies for Space NETS 2009

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  1. A Lunar Fission Surface Power (FSP) SystemPresented to:Nuclear and Emerging Technologies for SpaceNETS 2009 James Werner/INL, Project Lead June 15, 2009 Pre-Decisional, For Discussion Purposes Only

  2. History of Space Nuclear Power SNAP-10A (Agena) • Fission Reactor Systems • SNAP-10A (launched 1965) • SP-100 (cancelled 1992) • Jupiter Icy Moons Orbiter (cancelled 2005) • Fission Surface Power (Present) • Radioisotope Power Systems • 44 Successful U.S. Radioisotope Thermoelectric Generators (RTG) Flown Since 1961 • Some Examples: • Apollo SNAP-27 (1969-72) • Viking SNAP-19 (1975) • Voyager MHW-RTG (1977) • Galileo GPHS-RTG (1989) • New Horizons GPHS-RTG (2005) SNAP-27 (Apollo) SNAP-19 (Viking) Pre-Decisional, For Discussion Purposes Only

  3. Recent interest in Fission Surface Power (FSP) to support moon / Mars exploration Continuous Day/Night Power for Robust Surface Ops Same Technology for Moon and Mars Suitable for any Surface Location Lunar Equatorial or Polar Sites Permanently Shaded Craters Environmentally Robust Lunar Day/Night Thermal Transients Mars Dust Storms Operationally Robust Multiple-Failure Tolerant Long Life Highly Flexible Configurations Excavation Shield Permits Near-Habitat Siting Option for Above-Grade System or Mobile System (with shield mass penalty) Option for Process Heat Source (for ISRU or habitat) Pre-Decisional, For Discussion Purposes Only 3

  4. Safe During All Mission Phases Launched Cold, No Radiation Until Startup Safe after Shutdown with Negligible Residual Radiation Scalable to Higher Power Levels (kWs to MWs) Competitive Cost with PV/RFC Detailed, 12-month “Affordable” Fission Surface Power System Cost Study Performed by NASA & DOE LAT2 FSP and PV/RFC Options had Similar Overall Cost Modest Unit Cost Enables Multiple Units and/or Multiple Sites Technology Primed for Development Terrestrial Reactor Design Basis No Material Breakthroughs Required Lineage to RPS Systems (e.g. Stirling) and ISS (e.g. Radiators, Electrical Power Distribution) Recent interest in Fission Surface Power (FSP) to support moon / Mars exploration Pre-Decisional, For Discussion Purposes Only 4

  5. Affordable Fission Surface Power System Study Reference Concept • Modular 40 kWe system with 8-year design life suitable for global lunar and Mars surface applications • Emplaced configuration with regolith shielding augmentation permits near-outpost siting (<5 rem/yr at 100 m separation) • Approximately 7 metric tons and <60 m3 volume is a good match for Altair capability Deployed Stowed 3 x 3 x 7 m Pre-Decisional, For Discussion Purposes Only

  6. Keys to Affordability • Reactor: low temperature, well known UO2 fuel, stainless steel construction, liquid metal NaK coolant well-tested • Stirling power conversion: high efficiency at low temperature, 1980’s test experience, RPS leverage • Heat rejection: ISS mechanical design heritage, simple water heat pipes • System: Power density of nuclear reactor allows heavier, simpler, more robust components Pre-Decisional, For Discussion Purposes Only

  7. 07 08 09 10 11 12 13 14 15 16 17 18 19 20 Notional FSP Flight Development Schedule Task FY Tech Demo. Unit (TDU) ETDP Study Design Fab Test 1/2 Power, Full-Scale System Test Environ. Eval. (Radiation, Vib, etc.) Physics Core Criticals Ref. Concept Selection LSS MCR Non-nuclear TRL6 Devt. Test Models (DTM) 1/4 Power, Full-Scale System Test Prim. & Sec. Fluid Test Loops Coupon/Component Radiation Tests Study Des Fab Test Life Test ≤5 yrs Full Power, Full-Scale System Test Structural & Environ. Qualification Engineering Core Criticals LSS SRR Prime Contract Engineering Models (EM) Form, Fit & Function Design Fab Test Life Test ≤3 yrs PDR/NAR Subsystem, Module, and System Flight Acceptance Testing Flight Models (FM) Design Fab Test KSC ATP CDR ATLO Ship Launch Revised 8/1/08 Pre-Decisional, For Discussion Purposes Only

  8. Fission Surface Power Project 1.0 Fission Surface Power Systems Project Management Project Manager: Don Palac (GRC) Principal Investigator: Lee Mason (GRC) DOE Lead: Scott Harlow MSFC Lead: Mike Houts Business Analyst: Annie Delgado-Holton (GRC) 2.0 Concept Definition 2.1 Concept Selection Lead: Lee Mason (GRC) 2.2 Modeling and Tool Development Lead: Scott Harlow (DOE) 4.0 Risk Reduction 4.1 System Risk Reduction Lead: Lee Mason (GRC) 4.2 Primary Test Circuit Risk Red. Lead: Mike Houts (MSFC) 4.3 Reactor Component & Irradiation Testing Lead: Scott Harlow (DOE) 4.4 Power Conversion Risk Reduction Lead: Lee Mason (GRC) 4.5 Heat Rejection Risk Reduction Lead: Don Jaworkse (GRC) Pre-Decisional, For Discussion Purposes Only

  9. FSP Technology Project:Concept Definition Reactor Heat Transport Loop Integration Stirling CFD Modeling Stirling Convertor Concept Radiator Model Validation Reactor Core Modeling Radiator & Deployment System Pre-Decisional, For Discussion Purposes Only

  10. FSP Technology Project: Component Pathfinders Power Conversion Heat Rejection Reactor 2 kWe NaK Stirling System 10 kWe Stirling Alternator Test Rig 20 kWt NaK Reactor Simulator Ti-H2O Heat Pipe Life Test 1 kWt Radiator Demo Unit NaK Electromagnetic Pump 2 kWe Direct Drive Gas Brayton Pre-Decisional, For Discussion Purposes Only

  11. Demonstrate system-level technology readiness in an operational environment ¼ power, full scale hardware demonstration Technology Demonstration Unit – The Core of the Fission Surface Power Systems Project Notional TDU Test Layout in GRC Vacuum Facility #6 Pre-Decisional, For Discussion Purposes Only

  12. Lunar Surface Systems Architecture Planning FSP Off-Loaded & Buried Notional Concept for FSP-Lander Delivery FSP Remains on Lander Pre-Decisional, For Discussion Purposes Only

  13. FSP has many advantages Day/night power Location independence Environment tolerance Moon/Mars commonality High power, low mass Mission integration options are plentiful Buried or Landed, Early or Later, With or without PV Minimal impact on crew Major impact on surface capabilities Affordability = Conservative, Simple, Robust Known materials, generous margins Modest requirements Self-regulating controls Fault tolerant, designed to recover from anomalies Hardware-rich test program Low risk, accept mass penalties if necessary Summary FSP Technology Development Project is addressing the fundamental issues Pre-Decisional, For Discussion Purposes Only

  14. NASA News Release “NASA Developing Fission Surface Power Technology” Katherine Martin (9/10/08) Picked up by Dozens of Internet Sites including SpaceRef and Science Daily 100’s of Blogs… mostly supportive and positive DiscoveryChannel.com “NASA Eyes Nuclear Reactor for Moon Base” Irene Klotz (9/15/08) Space.com “NASA Eyes Nuclear Power for Moon Base” Jeremy Hsu (9/17/08) Athens Post “Athens Business to Develop Power Converter for NASA” Amanda Liles (10/6/08) Popular Science Magazine “Gone Fission” Dawn Stover (Dec 2008 Issue) Positive Press Pre-Decisional, For Discussion Purposes Only

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