NASA’S Space Science Missions

Outline

! RPS History ! RPS Technologies Performance Comparison ! RPS Availability Study ! Plutonium Shortage ! Discovery & Scout Mission Capability Expansion - Status ! ASRG Development - Status Radioisotope Power for ! Plans for Discovery 2009 AO NASA’s Space Science Missions

Briefing to Outer Planets Advisory Group March 31, 2008

Leonard A. Dudzinski Program Executive, Radioisotope Power Systems Program NASA Headquarters, Science Mission Directorate

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! RTG’s were used safely in 28 missions since 1961 Radioisotope Missions Radioisotope Power Systems ! 10 Earth orbit (Transit, Nimbus, LES) ! 8 planetary (Pioneer, Voyager, Galileo, Ulysses, Cassini, New Horizons) Technology Evolution ! 6 on lunar surface (Apollo ALSEP) ! 4 on Mars surface (Viking 1& 2) ! 3 RHUs on Mars Pathfinder, 8 RHUs for each MER MHW-RTG

TRL 9 GPHS-RTG

TRL 9

MMRTG

TRL 5-6 TRL 7-8 TRL 9

MSL OPF

123 We 283We 2.8 W/kg 158 We 5.1 W/kg 6.3% Efficiency 4.2 W/kg 6.8% Efficiency 6.6% Efficiency > 14 Year life ASRG > 14 Year life ! Ulysses, Gallileo, TRL 3-4 TRL 5-6 TRL 7-8 TRL 9 ! LES 8/9, Voyager 1 & 2 Cassini, New Horizons Eng Unit Discovery 12

SNAP-19 > 140 We > 7 W/kg TRL 9 > 28% Efficiency

40 We 3 W/kg Advanced Technology

6.2% Efficiency TRL 1-2 TRL 3-4 TRL 5-6 14 Year life !Viking 1 & 2 (8/20/75) NOTE: Graphics not to Scale ATEC, TPV, Advanced Stirling

1970 1980 1990 2000 2005 2010 2015

7 4 May 22, 2007 Pre-decisional / NASA Internal Use Only 5 March 19, 2008 PRE-DECISIONAL. FOR PLANNING PURPOSES ONLY RPS Development History RPS Technology Comparison

Current Technology Flight Development Advanced Technology Specific Fuel Efficiency (W Efficiency Fuel Specific History of success (W Efficiency Fuel Specific Flight system development Radioisotope Power managed by DOE Conversion Technology • Drivers: Multi-mission, Life (RPCT) Project & Reliability, Modular • Additional Drivers: Improved ASRG Performance, Lower Mass Multi-Mission RTG GPHS-RTG (MMRTG) • NRA extended phase

Pu-238 Savings Advanced Concepts • Lower risk, low Pu-238 Savings • 285 We efficiency (8 GPHS) • Improve • 123 W , 6% • 6% Efficiency using e • Efficiency SRG 110 e Efficiency • Specific Power (Redirected) TPV e /kg Pu-238) /kg SiGe Pu-238) /kg (PbTe/TAGS) • Reliability Thermoelectrics • Scalable Generator Efficiency (%) • 18 GPHS • Multi-mission capability Generator Efficiency (%) Advanced Stirling Advanced Thermoelectrics • 4 We/kg (EOL) Radioisotope (Deep space only) Generator (ASRG) MMRTG GPHS RTG • Vacuum applications • ! Pu-238 as MMRTG (2 GPHS) In-house Advanced Research • > 140 We, >28% Efficiency • GRC Stirling Development • GRC Thermophotovoltaics Specific Power (W /kg) • JPL Thermoelectric Development e Mass savings

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Radioisotope Power System Application Origin Of The ASRG and MMRTG in Near Term Planetary Missions

1995 2001 2004 238 New NASA Directives Flagship Mars Projected Power Req’m RPS Pu Usage New Frontiers Lunar Launch (W ) Do smaller missions e Type (kg) Discovery/Scout Year ! (lower power) Mars Science Lab 2009 100 1 MMRTG 3.5 In Development Reduce the cost

! (smaller RPS) Juno (New Frontiers 2) 2011 No RPS requirement In Development

Fly more often Joint NASA / DOE team Discovery 12 2014 250 2 ASRG 1.8 Under Study reviewed: New Frontiers 3 2016 250-600 2-4 ASRG 1.8-3.5 Directed SRG recommended to Non-nuclear ! Missions planned meet a range of space MSL Selects MMRTG ! Available RPS Options Outer Planets Flagship 1 2017 700-850 7 MMRTG 24.5 Under Study and surface missions Development transferred to MSL Discovery 13 2017 at ~ 100 We No RPS requirement Solar Probe 2020 200 2 MMRTG 7.0 Directed MMRTG Non-nuclear recommended as backup ! Out year New Frontier mission opportunities will likely require 250-600 We RPS ! Future odd numbered Discovery mission opportunities may have an RPS option SRG-110 and MMRTG projects started under ! Next Flagship mission will be post 2025 NSI / Prometheus ! Radioisotope heater units may be required on these and other missions ! Other science missions not listed here may also require RPS

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• Usable Pu238 inventory identified ! Assumes all Russian plutonium purchases made ! Does not include new US production ! Enough for MSL, Discovery 12, OPF, and possibly one other mission MMRTG ASRG* • Additional Issue: Losing vendor for Fine Weave Pierced Fabric (FWPF) material used to make GPHS BOM Net Electrical Power 123 We 140 - 160 We ! DOE pursuing either a replacement material or a new Total Mass per Unit 44 kg 22 - 20 kg method of procuring FWPF (Cost & schedule impact uncertain)

Specific Power 2.8 We/kg 6.4 - 8 We/kg ! Limits GPHS available to OPF

Mass for >800 We FS Mission 308 kg (861 We) 132 kg (840 We) • MMRTG production rate: 1 per year (start 2010) ! TRL 7 in Jul 2008 RPS System Efficiency ~ 6.3 % > 28% ! 2 fueled MMRTG per year possible with full scale ASP line 238 We per kg Pu 35 We/kg 159 - 180 We/kg • ASRG production rate: 3 per year (start 2011) Mass of Pu238 per Unit 3.52 kg 0.88 kg ! TRL 6 in Mar 2008, TRL 7 possible in 2010 if “Go Ahead” given Number of GPHS Modules 8 2 • DOE issues Development Cost $94M ~$115M ! Recommends NASA buys remaining Russian fuel ! Recommends NASA funds continued uninterrupted production of Pu pellets after MSL MMRTG is fueled Unit Cost $36M $20M ! DOE seeks authorization for new US Pu238 production (FY09 appropriation) o o o o Hot / Cold-end Temperature 538 C / 210 C 640 - 850 C / 80 C ! First output would be in 2014, with full production by 2016 (Only 1/2 assumed to NASA)

BOM Heat Output 1877 Wt 360 Wt • Plutonium needs must be balanced between Science & Exploration * Range based on ASRG PRE-DECISIONAL. FOR PLANNING PURPOSES ONLY development options 9 PRE-DECISIONAL. FOR PLANNING PURPOSES ONLY 10

Plutonium Supply vs Potential NASA Demand Magnitude of the Potential Shortage RPS Availability Study Results

! SMD has allocated money to purchase all remaining Russian 238Pu, and support DoE efforts to negotiate a new contract • Potential mission roadmap demand exceeds available Pu238 & new Pu238 production rate Future FWPF Limit ! SMD has allocated money to extend current last-production run of FWPF to Flagship 2 • Mission planning will have to reconcile with Demand Discvy 17 meet mission needs for the foreseeable future actual Pu238 availability Exceeds New Frontiers 5 Supply (Venus) . CHANGE ! SMD & ESMD endorse DoE efforts to restart domestic production of 238Pu 238 Pu Supply Exploration Potentially Available Rover Power New Pu238 Production ! The 2015 Outer Planet Flagship mission will use MMRTGs Remaining Russian Mars Mission ! Missions encouraged to reduce power requirements Pu238 Purchases NOTIONAL. FOR PLANNING PURPOSES. SUBJECT TO ! Decision based on risk of large OPF mission with new technology (including ASRG) Lunar Rover Current New Frontiers 4 Exploration Lunar Rover Power FWPF Limit Mission Solar Discovery 15 ! ASRG will be readied for flight as quickly as practical, and SMD will look for Probe Existing Pu238 Inventory -1.8 kg Exploration a mission opportunity to flight validate the new power system Rover Power New ! Competed missions (Discovery & New Frontiers) avoid new technology risk (like ASRG) Frontiers 3 Exploration Discovery 12 Lander Power 238 MSL Flagship 1 Pu Outflows ! Imperative for Discovery & Scout Mission Capability Expansion Program

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! Program Purpose No Target Title Principle Inv Institutions ! Create opportunity for new science on Discovery and Scout budgets 34 Moon ExoMoon: ASRG-Powered Dr Richard Elphic LANL, Ball Aerospace, Honeybee Robotics, UC, GSFC, ARC, CUA, UHi ! Foster exploration of Discovery & Scout class missions enabled by nuclear power in the planetary science community Mobile Lander Lunar Polar Exploration ! Encourage the formation of mission design teams to begin the discussion of necessary engineering trades 6 Moon JEDI: A Lunar Polar Volatile Dr Bradley Jolliff Washington U, SWRI, LANL, LM, ! Inform NASA of the breadth of missions possible with the addition of the ASRG technology to the Discovery and/or Obv. Midi-Pyrenees, U of Guelph Mars Scout programs Rover/Comsat Explorer ! Program Plan 19 Titan Titan Mare Explorer (TiME) Dr Ellen Stofan Proxemy Research, UofAz, CITech, Lockheed Martin, USGS, JHU/APL ! Solicit mission concept proposals for small planetary missions that require a nuclear power source (such as the ASRG) Boat ! Award funding for 6 to 8 six-month detailed mission concept studies. U of Arizona, USGS, SWRI, ! Evaluate these mission concepts to inform decision to expand the mission capabilities of the Discovery and Mars 3 Io Io Volcano Observer (IVO) Dr Alfred McEwen Physikalisches Institut Scout programs to include radioisotope power systems. Fly-Bys ! Groundrules 11 Trojan ASRG-Enabled Trojan Dr Andrew Rivkin JHU/APL, GRC, SETI Institute ! Studies are expected to be led by a scientist serving as Principal Investigator (PI) with a small science team Lander Asteroid Mission (Ilion) ! Mission design is a critical part of these studies to make trades, explore feasibility, & refine the mission concept ! Mission design expertise will be offered from JPL’s Team-X and GSFC IDC 21 Comet Comet Hopper (CHopper) Dr Jessica Sunshine U of Maryland, Cornell, Smithsonian Inst, UWa-Seatle, UTx-Austin, LM ! Short proposals (7 pages) are solicited that clearly summarize : Lander ! The mission concept, 2 Comet Comet Coma Sample Return Dr Scott Sandford ARC, U of Central FL, U of Md, ! Science target(s) and objectives, Lockheed Martin Sample Return Mission ! Relevance to NASA objectives and Decadal Survey science objectives, ! Nature of the science advancement expected from the mission. 32 Mars Kuklos: A tour through Dr Michael Hecht JPL, UC-Berk, LM, CITech, ARC, Geological Survey of Canada ! Justification of the need to use the ASRG Lander Drill martian history ! Missions must fit within Discovery or Scout Mission Class 5 Venus Polar VALOR: Venus Balloon Dr Kevin Baines JPL, UMi, UWi-Madison Balloons (2)

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ASRG Status 2nd Quarter FY 2008 ASRG Development Plan

Draft Integrated DSMCE-ASRG-ASC development schedule ! Advanced Stirling Radioisotope Generator Engineering Unit assembly completed NOTIONAL DISCOVERY SCHEDULE ! Three ASC-E convertors were delivered to LMSSC in October CURRENTLY UNAPPROVED 2007, on-time and exceeding power specification! ! Two convertors have been integrated into the ASRG-EU ! Generator processing completed January 28, 2008 ! Generator testing has begun at LMSSC ! Generator will be delivered to NASA GRC in June 2008 for life testing

ASC-E Convertor Pair of ASC-E Convertors during Integration Completed ASRG Engineering Unit

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! Up to 2 ASRGs will be offered to the mission PI as GFE (no-cost to proposal)

! AO will be open to RPS/ASRG and Non-RPS proposals

! TMCO assessed risk for proposing ASRG will be discounted by selecting official

! If a non-RPS mission is selected, ASRGs will be completed and available for flight on another mission

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RPS Comparisons from a Mission Perspective Thermal Electric Principles of Operation Major Advantage Minor Advantage MMRTG ASRG

123 W BOL 140 W BOL Char- Generic 44 kg 22 kg ATEC Couple Concept acteristic: Requires 8 GPHS modules. Requires 2 GPHS modules. Thermoelectric Couple Heat Source PbTe-TAGS elements were used on RPS missions 1972 to 1975 Cryocoolers have flown with same and similar technology. Flight Principle of Operation New generator design first flight in 2009 on MSL. Gas mgmt and some structure components have RTG heritage N-Leg Heat Collector P-Leg Heat Collector Heritage: Experienced in mission implementation and S/C integration. Ground testing continues on engines/alternators. 10+ yr demo. Design requirement for 14 year mission after 3 year storage. Design requirement for 14 years after 3 year storage Advanced Lifetime: 0.7%/yr loss of power (+0.8%/yr from Pu decay) Negligible from ASC (0.8%/yr from Pu decay) Thermoelectric Predicted power loss 22% over 14 year life Extended ASC ground tests continue. System life test starts 4/08 Converter Passive failure modes with series/parallel/cross-strapping of Same tech terrestrial Stirling coolers have MTBF >500,000hr, Reliability: every TE element w/100s of elements in each RTG. >4000 w/44M cum hrs. 50% power if one converter fails. Controller fault tolerant. To be proven in EU in Q1 FY08

Risk EU tests nearing completion EU assembled and tested by Q2 FY08. N-Leg P-Leg Zintl Mitigation: Extended operation testing will begin in Q3 FY07. Extended operation to begin in Q3 FY08. Waste heat available from 8 GPHS modules at 210 ºC skin Waste heat available from 2 GPHS modules at 80 ºC skin Thermal: More waste heat may require added cooling for aeroshells. Less heat at lower temperature is desirable for aeroshells. Hot N-Leg $94 M development ($11 M remains for QU) $115 M development ($15M remains for EU, $36 M for QU) P-Leg Cost: Electrical Electrical $36M recurring cost for fueled units. $20M recurring cost for fueled units. Contact + + Contact Radiation Materials selected for radiation environments All controller components rated between 500 kRad and 5 Mrad. i N P i hardness: No shielding required to increase radiation tolerance. Standard shielding for higher radiation environments. " T Leg Leg Electro- DC only AC & DC Radiator magnetics: EMI needs to be addressed at the spacecraft level. Requirement EMI needs to be addressed at the spacecraft level. Requirement Attachment below 25 nT at 1 meter. below 25 nT at 1 meter. Shielding possible for lower levels. Assembly Vibration: No moving mechanical components. Meets requirement of < 35 N at 102 Hz with large margin Cold R L V MMOD: Shell pen. results in loss of TE cover gas & rapid power degr. Shell acts as bumper shield for Stirling converter Radiator Shock: Meets 0.2 g2/Hz launch vibration requirement. Meets 0.2 g2/Hz requirement. 0.3 g2/Hz goal.

Backup Reference Slides: 9A, 9B,9C PRE-DECISIONAL. FOR PLANNING PURPOSES ONLY 199 PRE-DECISIONAL. FOR PLANNING PURPOSES ONLY 20 Stirling Convertor Principle of Operation DSMCE Program Overview

GPHS Module ~ 250 Wt Heat Input ! Program solicited mission concept proposals for small planetary Heat In Th Displacer missions that require the ASRG power source ! Two Stirling Engines with ~140 Watts each (as GFE) Regenerator

Sunpower Advanced Stirling Convertor ! Intended to foster science exploration in planetary science by missions T c Free Piston enabled by ASRG Heat The Stirling engine, when Rejection integrated with a load such as a Helium Working Fluid ! Mission design assistance for these 6 month mission concept studies linear alternator, becomes a will be offered by NASA Stirling power convertor Is Converted To

Linear Alternator ! Selected 9 proposals ! With proper masses, spring rates 40 proposals submitted with average budget of $271K and damping (dynamic tuning), the ! NRA directed proposers to budget $200,000-$300,000 convertor will resonate as a Free- Piston Stirling Convertor

• All Wear Mechanisms Have Been Eliminated By Design Electric • Long Life Operation Is Based On Power Out Non-Contacting Operation

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Advanced Stirling Radioisotope Generator Engineering Unit Just Released NRC NOSSE Report

Lockheed Martin/Sunpower ! Operation in space and on surface of atmosphere-bearing planets and moons ! “Opening New Frontiers in Space: Choices for the Next New Frontiers AO” - NASA should: ! Characteristics: ! R1: Emphasize science objectives ! "14 year lifetime ! R2: Expand the list of candidate missions ! Nominal power : 140 We ! R3: Limit to the list below unless compelling science ! Mass ~ 20 kg ! Recommended target list in alphabetic order: ! System efficiency: ~ 30 % ! Asteroid Rover/Sample Return* Possibly RPS Enabled ! 2 GPHS (“Pu238 Bricks”) modules ! Comet Surface Sample Return Possibly RPS Enabled ! Uses 0.8 kg Pu238 ! Ganymede Observer* Likely RPS Enabled ! Final wiring and connections for ASRG ! Io Observer* Likely RPS Enabled engineering unit underway ! Jupiter Polar Orbiter with Probes ! Reliability to be demonstrated by the end of ! Kuiper Belt/Pluto RPS Enabled 2009 ! Lunar South Pole Aitken Basin Sample Return Paired converters ! Mars Network Science* Possibly RPS Enabled with interconnect ! Trojan/Centaur Reconnaissance* Likely RPS Enabled sleeve assembly ! Venus In-Situ Explorer ! Report located at : http://www.nap.edu/catalog/12175.html

* Additions Outboard Housing and Paired ASC-Es PRE-DECISIONAL. FOR PLANNING PURPOSES ONLY 23 PRE-DECISIONAL. FOR PLANNING PURPOSES ONLY 24 Plutonium Supply vs Potential NASA Demand NASA Technology Readiness Levels Baseline

TRL 9: Actual system “mission proven” through successful mission operations Thoroughly debugged software readily repeatable. Fully integrated with operational hardware/software Mission roadmap demand exceeds available Pu238 systems. All documentation completed. Successful operational experience. Sustaining software & new Pu238 production rate TRL 9 engineering support in place. Actual system fully demonstrated. System Test, TRL 8: Actual system completed and “mission qualified” through test and Launch & Operations demonstration in an operational environment Note: Current Agency Roadmap (Excluding ESMD TRL 8 Thoroughly debugged software. Fully integrated with operational hardware and software systems. Requirements) Requires Start of New Domestic 92.4 kg Future FWPF Limit - 6.2 kg 1120W Manufacturing Capability in 2009 Unless Current -3.5 kg e Most user documentation, training documentation, and maintenance documentation completed. All (7 ASRG) functionality tested in simulated and operational scenarios. V&V completed. National Security Set Aside is Made Available or - 5.3 kg System/Subsystem Flagship 2 Additional Russian Material Becomes Available Demand Development TRL 7 TRL 7: Initial system demonstration in high-fidelity environment - 11 kg 640 W Exceeds e Most functionality available for demonstration and test. Well integrated with operational 960 W (4 ASRG) Supply e hardware/software systems. Most software bugs removed. Limited documentation available. Supply (6 ASRG) Discvy 17 238 - 11 kg New Frontiers 5 TRL 6 TRL 6: System/subsystem prototype validated in a relevant end-to-end environment Pu Supply Technology Prototype implementations on full scale realistic problems. Partially integrated with existing - 11 kg Demonstration hardware/software systems. Limited documentation available. TRL 5 Engineering feasibility fully demonstrated. Remaining Russian - 5.3 kg -3.5 kg 2000We TRL 5: Module and/or subsystem qualified in relevant environment Pu238 Purchases Potentially Available (SRG) New Pu238 Production - 11 kg Rover Power Technology Prototype implementations conform to target environment / interfaces. Experiments with realistic 27.1 kg Development TRL 4 problems. Simulated interfaces to existing systems. 19.8 kg 2000We TRL 4: Module and/or subsystem qualified in laboratory environment Current (SRG) for Missions for Standalone prototype implementations. Experiments with full scale problems or data sets. Fuel Available FWPF Limit - 24.6 kg Rover Power 13.2 kg 960 W TRL 3 e Existing Pu238 Inventory (6 ASRG) TRL 3: Analytical & experimental critical function / characteristic proof-of-concept -1.8 kg 2000We Research to Limited functionality implementations. Experiments with small representative data sets. New Frontiers 4 (SRG) -3.5 kg - 1.8 kg Prove Feasibility Scientific feasibility fully demonstrated. 640 We Rover Power 280W (2 ASRG) (4 ASRG) TRL 2 123W (1 MMRTG) e 861We 2000We 238 TRL 2: Technology concept and/or application formulated e Discovery 12 Discovery 15 Pu Outflows MSL (7 MMRTG) (SRG) Basic principles coded. Experiments with synthetic data. Mostly applied research. Flagship 1 Lander Power

Basic Technology Missions for TRL 1 TRL 1: Basic principles observed and reported Research Fuel Unavailable Basic properties of algorithms, representations & concepts. Mathematical formulations. Mix of basic and applied research.

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Plutonium Supply vs Potential NASA Demand Plutonium Supply vs Potential NASA Demand Closing Scenario Supply Constrained Scenario

1) New Frontiers 3 and Solar Probe missions use non-RPS power source Power available to Exploration limited by available Pu238 & new Pu238 production rate 2) New US production of 238Pu starts in 2014 Full Allocation (new start in 2009) of 5kg/yr 3) NASA receives 5kg/yr of new US 238Pu 92.4 kg Future FWPF Limit 4) Discovery 17 and Flagship 2 are deferred 1y - 6.2 kg Potentially Available -3.5 kg New Pu238 Production 1120We - 5.3 kg (7 ASRG)

960 We Flagship 2 (6 ASRG) 238 Annual New Frontiers 5 Pu Supply production 640 W supports - 11 kg e - 2.6 kg 238 (4 ASRG) 480We /yr Pu Supply Discvy 17 Remaining Russian SRG Power 238 - 11 kg - 11 kg Pu Purchases - 11 kg 27.1 kg Remaining Russian Potentially Available - 5.3 kg 238 -3.5 kg 2000We Pu238 Purchases New Pu Production (SRG) 19.8 kg - 11 kg 27.1 kg Rover Power Current 2000We 13.2 kg FWPF Limit - 24.6 kg (SRG)

for Missions for Exploration Power

19.8 kg 2000W Fuel Available e could be limited by Current (SRG) 238

for Missions for Existing Pu Inventory 238 Available Fuel Available FWPF Limit - 24.6 kg Rover Power Pu Availability in 13.2 kg 2020 960 We Existing Pu238 Inventory (6 ASRG) -3.5 kg -1.8 kg 2000We -1.8 kg New Frontiers 4 238 - 1.8 kg (SRG) Pu Outflows -3.5 kg 640 W Rover Power e 861W 280W (2 ASRG) 861W 2000W (4 ASRG) e 123W (1 MMRTG) e e e 238 (7 MMRTG) e Discovery 13 (7 MMRTG) (SRG) Discovery 15 Pu Outflows MSL 280We (2 ASRG) Flagship for Missions for 123W (1 MMRTG) Flagship 1 Lander Power e Discovery Mission

Unavailable Fuel Unavailable MSL for Missions for Unavailable Fuel Unavailable

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