A Thermochemical Regenerative Energy Storage System (TRESS)

U.S. Chamber of Commerce Programmatic Workshop on NASA Lunar SurfaceSystems Concepts, Washington DC, 26 February 2009A premier aerospace and defense companyA Thermochemical Regenerative EnergyStorage System (TRESS)Presented by:Dr. Ighor K. UzhinskyATKDr. Anthony CastrogiovanniACEnT Laboratories1This system concept Is protected by US provisional patent 61/092,358

A premier aerospace and defense companyNovember 2012Marketing level data only - non-export controlled.2

ATK Corporate ProfileA premier aerospace and defense company• Revenues in excess of $4.2 billion• Over 17,000 employees in 22 states, Puerto Rico and internationally —Headquartered in Arlington, VA• Emerging provider of precision weapon systems and space systems– Leading U.S. supplier of conventional munitions– World leader in solid rocket motorsSales by CustomerSales by Contract TypeCommercial /International32%US Army30%Subcontractor29%3Other US Govt7%US Navy11%NASA13%US Air Force7%PrimeContractor71%

ATK Current Business OverviewA premier aerospace and defense companyATK is organized into THREE operating groups aligned along product areasATK AerospacePresident: Blake LarsonATK DefensePresident: Mike KahnATK SportingPresident: Ron Johnson• NASA space exploration• Space launch systems• Satellites, subsystems,and components• Strategic missile andmissile defensepropulsion• Ordnance systems• Aerospace structures• Small-, Medium-caliber ammunition• Medium-caliber gun systems• Advanced propellant and energetics• Precision weapon systems• Intelligence, surveillance,reconnaissance (ISR)• Electronic warfare• Tactical propulsion and controls• Ammunition: rimfire,centerfire, rifle and pistol,shot shell• Shooting accessories forsport• Shooting accessories forlaw enforcement4

BAA NNJ08ZBT002. Topic 4: Long-term LunarEnergy Storage Systems ConceptsA premier aerospace and defense companyObjectiveThe primary objective of this study is to identify novel energy storage concepts thatenable longer crewed missions on the lunar surface. The ideal energy storage systemwould be robust to the lunar environment and the system requirements, have low massand volume, and require little or no maintenance or support. The ideal system would alsobe efficient in discharge and recharge and be integrated with the outpost simply and withlittle impact.System Requirements:• 2 - 5 kW net discharge electric power• 100 - 2000 kWhr net energy storage per module• TRL 6 by 2015 - 2018 timeframe• 5 - 10 year calendar life• 10,000 - 15,000 hour operational life• 100 - 2000 charge/discharge cycles• able to withstand high dust, radiation, and widely varying thermal environment.6

BAA NNJ08ZBT002 . BackgroundA premier aerospace and defense company• Staying on the moon for extended periods of time can require significant energystorage. For solar power based systems, energy storage is needed for nighttime poweras well as mobile power and daytime power augmentation. The lunar nighttimeduration is about 350 hours or greater, which h is significantly ifi higher h than Earth andMartian orbit and surface nighttime durations. Some reduction in the lunar nighttimeduration is possible by landing on elevated sites near the poles, but despite this, thenighttime durations are such that even low power levels require significant energystorage.• The high cost of delivering mass to the lunar surface makes mass and volume theprimary drivers for choice of the energy storage approach. Secondary, but stillimportant, design drivers include life-cycle cost, high reliability and long life, little orno maintenance needs, and high discharge and recharge efficiency. All of these canhave significant effects on the overall lunar outpost design and approach.• Batteries have been used for other space missions including short-term lunarmissions but their application for future lunar surface systems carries a substantialmass penalty. Other concepts have not been fully developed and demonstrated in arelevant environment. Fuel cells have been used for manned spaceflight missions buthave not been used regeneratively, where the fluid products are converted back toreactants, in a relevant environment. Other energy storage concepts, as well as newapproaches to battery and fuel cell technology, exist and may be potential solutionsfor the lunar surface application.7

BAA NNJ08ZBT002 . Technical RequirementsA premier aerospace and defense company• The conceptual design(s) and their figures-of-merit, including estimated mass,volume and recharge efficiency.• Qualitative summaries on potential issues affecting cycle and calendar life,reliability, maintainability, and cost.• The sensitivity of the energy storage system design and its requirements on thefigures-of-merit.• The potential impacts on other subsystems including thermal, communications,and logistics needs.• Any concepts for dual use, such as capturing and using waste heat, or otherhybrid approaches.8

NNJ008TA80C Project TeamA premier aerospace and defense companyProgram Manager – Dr. Ighor Uzhinsky (ATK)Principal Engineer and Scientist – Dr. Tony Castrogiovanni (ACEnT Labs)Key Subsystem Principal Investigators:• Florin Girlea, Joe Alifano (ATK)– Provided engineering design data for H 2 generation reactor and 3D models of system• Chris Kogstrom (ATK)– Investigated SOFC, turbine, and MgO recycling systems– Supported by Acumentrics, M-DOT Aerospace, and Boston University• Dr. Akiva aSklar (ATK)– Led H 2 0 2 synthesis efforts supported by Headwaters Technology Innovation9

TRESS Night and Day CyclesA premier aerospace and defense companyNight – Power OutDay – Power In10

TRESS OverviewA premier aerospace and defense companyH 2 O 2H 2 O 2MgH 2MgH 2MgH 2H 2 O 2ReactorH 2 OReactorO 2 + H 2 OH 2MgOSOFCMgOCollectorTurbineH 2 OH 2 O (cooling)H 2 OCollectorH 2 OElectrolyzerO 2H 2H 2 0 2 RecyclingO 2H 2 MgH 2 RecyclingMgOMgH 2Concept based on efficient energy storage in hydrogen peroxide and magnesiumhydride and in leveraging reaction heat release to generate hydrogen, oxygen,and steam for solid oxide fuel cell/steam microturbine power units11

Reactant Volume ComparisonA premier aerospace and defense company581%600%500%400%300%200%100%15%100%0%MgH2 H2 (liquid) H2 (2000psi)591%600%500%400%300%200%100%107%100%0%H2O2(75%) O2 (liquid) O2 (2000psi)12

System Configuration – 5 kW, 2,000 kWhA premier aerospace and defense companyPod configuration:• Sealed from lunar environment in dome(radiation shield)• Readily deployable from lander• Electrical interfaces:– Power in from PV array– Power out• Total system mass ≈ 2,000 kg• Materials consumption:– MgH 2 powder: ~500 gram/hour– H 2 O 2 (75% in water): ~1,800 gram/hour• Fully regenerative closed system13

TRESS Processes Benefits SummaryA premier aerospace and defense company• High temperature chemical processes– High efficiency thermal energy conversion– High grade heat used to generate additional power• High volumetric and gravimetric energy density– High efficiency storage of H 2 and O 2– Scaling-up storage (duration) increases overall system energy density• Low material flow rates– Simplifies material supply subsystem components– Compact energy generation modules• No maintenance required for materials stored for extended time periods– Opportunity to generate and store materials in advance for later use– Materials are safe and easily transportable• Efficient material recycling technologies– System based on tested processes – need to develop lunar-specific designs– Experimental data are available to support system performance estimates• Recycling process synergy with ISRU14– Hydrogen peroxide may be used as a compact /storable water/oxygen source– MgO availability on the Moon

TRESS Unit Design EssentialsA premier aerospace and defense company• Compact size– The system can be delivered in one module to the Moon ready for operations afterintegration with the solar array– Most components (e.g. turbine/SOFC/H 2 and O 2 reactors) are small– The unit is transportable to other lunar locations15

Mobile TRESS – 5 kW, 40 kWh (8-hour scenario)• Encapsulated fueling options– Provide opportunity to fuel mobile/remote units– May be readily transported via hoppers to any lunar locationA premier aerospace and defense company– Standardized recycling interface enables centralized recycling (recharging) pod• System is ~18-in. Φ x 32-in. H + heat rejection panels• Mass ≈ 80 kg (0.5 kWh/kg)16

TRESS Mobile (Rover/Remote Outposts) ApplicationsA premier aerospace and defense company• Mobile units use encapsulatedMgH 2 powder and peroxidecartridges that can be easilyexchanged from a central depotor remote supply caches• No need for on-board recharging• Modular power cartridges maybe distributed to any place on thelunar surface where commonpower generator interfaces areprovided• The cartridges are safe for longtermstorage and may bedelivered to the areas of interestin advance of particular missions17

Applications/Variations of TRESS TechnologyA premier aerospace and defense company• MgH 2 + O 2 system (instead of H 2 O 2 )– Eliminates most complex synthesis process(and contaminants)• Interplanetary Lunar Network (ILN)– 300 sec• Terrestrial vehicle applications – compact H 2for fuel cells and energy generators• Underwater applications (or other sealedenvironments)18

TRESS Relevance to Lunar Exploration ObjectivesA premier aerospace and defense company19

TRESS Relevance to Lunar Exploration ObjectivesA premier aerospace and defense company20

TRESS Relevance to Lunar Exploration ObjectivesA premier aerospace and defense company21

TRESS Program Plan ConceptA premier aerospace and defense company• ATK and ACEnT Laboratories propose a phased program for the developmentof a TRESS system with a TRL of 6 by 2015 to 2018. The program is dividedinto 3 phases as follows:– Phase I: Electrical Energy Generating Module Demo and TRESS SystemAnalysis– Phase II: TRESS Small Scale Prototype Demo Fabrication and Testing– Phase III: Full-scale TRESS Prototype Development, Design, and Testing• Detailed schedules have been developed for each of the program phasesusing Microsoft Project software• All work is expected to be conducted in close cooperation with NASA22

A premier aerospace and defense companyTRESS System Design andConcept of Operation23

TRESS Pod with Heat Rejection ArraysA premier aerospace and defense company245 kW, 2,000 kWh System Depicted5ft9iin. personfor scale

System Block Diagram with OrientationA premier aerospace and defense companyMgH 2 SynthesisMgH2 StorageH 2 O 2SynthesisWater Co ollectionH 2 O 2 StorageH 2 O 2 ReactorElectrolyzerMgH 2 ReactorMgO StorageSOFCTurbineCondenserSOMMgOdecomp25

TRESS System Isometric (Peroxide Tank Removed)A premier aerospace and defense company26

TRESS System Isometric (Peroxide Tank Removed)A premier aerospace and defense company27

Mobile TRESS Block Diagram with OrientationA premier aerospace and defense companyMgH 2 CartridgeH 2 O 2 and H 2 0Bladder CartridgeH 2 O 2 Reactor2 2MgH 2 ReactorSOFCTurbineWaterCollectionMgO CartridgeH 2 O 2 StorageCondenserOnly TRESS Power Generation Components Requiredfor Mobile Applications28

Regeneration Station for Mobile SystemA premier aerospace and defense companyMgH2 SynthesisH 2 O 2SynthesisMgH2 CartridgeWaterCollectionH2O2 StorageElectrolyzerMgO CartridgeMgH 2SynthesisReactorH2O2 and H20Bladder CartridgeSOMMgOdecompMgH 2 Hopper(from mobilesystem)MgO Hopper(from mobilesystem)ElectrolyzerH 2 O 2 SynthesisReactorH 2 O 2 /H 2 OVessel (frommobile system)Mobile Cartridges are Inserted into Regeneration Pod29

A premier aerospace and defense companySubsystems Overviews30

Aqueous Peroxide StorageA premier aerospace and defense company• Toroid-cylinder with bladder• H 2 O 2 + H 2 0 on inside, H 2 O collection on2 2 2 2outside• Largest volume component• Key issue = compatibility with HBr and HCl(from synthesis reactor) and thermalmanagement31

Magnesium Hydride StorageA premier aerospace and defense company• Dry powder hopper• Ultrasonic micro-dispenser• Vibration-assisted flow• Key issues – low gravity and dispense topressurized reactor32

Peroxide Decomposition SystemA premier aerospace and defense companyAqueous Hydrogen Peroxide Decomposition SystemH OIsolationvalve andliquid pumpCatalystBedO 2 (v) + H 2 O (v) +H 2 O (l)H 2 O 2MgH 2LiquidSeparatorO 2 (v) + H 2 O (v)SOFCH 2 O (l)Reactor• Passive transition metal catalyst bed similar toperoxide monopropellant rockets• Exothermic decomposition reaction• At < 67% concentrations, temperature is limitedto saturation at set pressure• Product (

Magnesium Hydride ReactorA premier aerospace and defense companyH 2 O (l)from decomposition reactor ‐ separatorO 2 (v) + H 2 O (v)H 2 O (v)H 2 O (v)O 2 (v) +H 2 O (v)MgH 2 (s)MixerMgH2 ReactorH 2 O (l)(post‐turbine)H 2 (v) +MgO (s)MgO (s)H 2 (v)HEXMgO SeparatorH 2 (v)Products at800°CSOFC• Based on powder/flamespray gun technology• Key is mixing efficiencyand residence time tocomplete reaction34

Solid Oxide Fuel Cell (SOFC)A premier aerospace and defense company• Accumetrics cylindrical configuration is baseline35

Nighttime Waste Heat Recovery - MicroturbineA premier aerospace and defense company• Microturbine has highest power to weight• 40% efficiency today, but we can sacrifice weight for moreefficiency for TRESS• M-DOT 500 W product is selected departure point36

Other Power Generation Options ConsideredA premier aerospace and defense company• Scroll expander offers 70%efficiency, however pressureratio is limited• Multiple units in seriespossible• NASA Stirling engines forradioisotope systems• 38% efficiency for 850°C to 90°Cdemonstrated37

High Pressure Water ElectrolyzerA premier aerospace and defense company• Giner Electrochemical Systems 1,200 psi high pressureelectrolyzer is baseline point of departure– NASA GRC and DARPA funding– Eliminates need for O 2 and H 2 compressors for H 2 O 2synthesis s systemPrototypeSpecific power (W/kg) 386(5100 Watts/13.2 kg)Pressure (kPa gage)8245 (1200 psig)Efficiency at design point 83.20%(at Higher Heat Value basis) (@700 mA/cm2 )Efficiency at 25% Imax 86.40%(HHV basis)Efficiency at 50% Imax 87.60%(HHV basis)Efficiency at 75% mA/cm2 86.00%38(HHV basis)

Aqueous Hydrogen Peroxide SynthesisA premier aerospace and defense company• Headwaters Technology Innovations direct synthesis process is baseline– Industrial process uses methanol as substrate, TRESS uses supercriticalCO 239

MgH 2 Regeneration SystemA premier aerospace and defense company• Boston University solid oxide membrane (SOM) process isbaseline for MgO decompositionMgO from Collector(gravity/ultrasonic feed)H 2 fromElectrolyzerSOM ProcessPower/Heat In Mg (v)MgHMolten Salt2SynthesisSolutionReactor40O 2 to H 2 O 2SynthesisReactorMgH 2 to storage(gravity feed)

Possible Organic Rankine Cycle (ORC) on ReactorA premier aerospace and defense company• ORC bottoming cycle may be used to extract additional energy from H 2 O 2synthesis reactor cooling loop• Use of second fluid and temperature difference from reactor (1,150°C) to shadedlunar heat sink• Low efficiency e cy expected due to indirect heat exchange (~20%), but small systemdoes not add significant weightWaste HeatSource41

Heat Rejection SchemeA premier aerospace and defense company• NASA CR – 2006-214388 1 describes a potential system for heat rejection oftemperatures in the range ~ 450K (177°C)kWt4.54.03.53.02.5202.01.51.00.50.0Daytime Waste Heat, Day = Night(5kW system, 60% efficiencies for turbine and SOFC, 75% H 2 O 2 )Electrolyer Peroxide synthesis MgH2 synthesis SOM w/ORCSubsystem42 1NASA CR – 2006-214388, Heat Rejection Concepts for Lunar Fission Surface Power Applications, J. Siamidis

ATK Deployable Solar ArraysA premier aerospace and defense company• A~6 meter diameter single-wing UltraFlex unit of 14 to 18 kW will be able toprovide the necessary power for the daytime regeneration cycle of TRESS43

Top Subsystem RisksA premier aerospace and defense companyRisk Items Effect(s) Proposed R&D ActivitiesContamination of H 2 O 2 withtrace quantities of HBr and HClIneffective gas phase MgH 2synthesisInefficient mixing of powder andsteamAccurate control of powderdispense in reduced gravity andlow temperatureBackflow of steam due topowder dispense to pressurizedreactorCorrosion of catalyst andreduced life of subsystem.Incorrect chemistryIncorrect chemistry results inlow H 2 yield and undesiredproductsNon-uniform dispensingresults in incorrect chemistryand thermal balance forsystemReaction in powder hopperExperimental verification of material life with tracequantities of the additivesNot typically done with gas phase Mg – bench-scaletests to verifyExtensive design and test of system. Leverageexperience from flame spray industryLeverage experience from pharmaceutical industry.Carefully calibrate systemBackpressure hopper to above steam pressure (notdesired). Supersonic injection (ejector) similar toHVOF flame spray.HBr + HCl contaminants t inPotential ti creation ofAssess with bench-scale teststMgH 2 reactorunwanted compounds (e.g.MgCl 2 and MgBr 2 )SOM Containment VesselCorrosionSOM YSZ Membrane Durabilitymaintenance, lifeLife, efficiency,maintenance, durabilityInvestigate alternatives- material optimization,coatings, g, alloys..; surface temp.Examine post-exposure mechanical and physicalcharacteristics44

Top System Level RisksA premier aerospace and defense companyRisk ItemsEffect(s)Importance/Likely-hoodTechnical RiskProposed R&D ActivitiesInaccuracy inReducedd High High Comprehensive closed-flow control,particularlyduring systemtransientsefficiency,offset thermalbalance,unwantedloop control architecturedevelopment. Extensivetesting and sensitivityexaminationproducts canaccumulatecontaminantsThermal balance System High Med Thermal controlsvariations,particularlyduring transientsefficiency,weight, lifedevelopment and testing –sensitivity assessment.Environmental testsAccumulation ofcontaminantsEfficiency, lifereductionHigh High Subsystem testing toinsure purity, systemtesting to assess impacts45

TRL AssessmentA premier aerospace and defense companySystemTRL Today(on Earth)H 2 O 2 Storage 9 2TRL Today (lunar) Risk to TRL 6by 2015LMgH 2 Storage 9 2LH 2 O 2 DecompositionReactor9 3LMgH 2 + H 2 O Reactor 4 2SOFC and Turbine 5 3Water Electrolysis 9 6MgH 2 Synthesis 3 1 - 2H 2 O 2 Synthesis 9 1 - 2System Integrationand OperationLMLM/HM/HH46

Figure of Merit Sensitivity AnalysisA premier aerospace and defense company• Variables used in parametric analysis:– Percent hydrogen peroxide concentration in water (50% and 75%)– System power level (2, 3.5, and 5 kW)– System energy storage (100 kWh to 2,000 kwh) or up to 400 hours– Regeneration time as a function of power generation time (1X and 2X)– SOFC efficiency (45% to 60%)– Nighttime waste heat efficiency• Key figures of merit:– System flow rates– Overall TRESS system mass– Energy-in/energy-out “round trip” efficiency– Power-in requirements47– System mass distribution by major subsystem

Overall System Energy Efficiency with ORCA premier aerospace and defense company29%System Energy‐Out/Energy‐In Efficiency versus Nighttime Waste HeatUtilization Efficiency5kW ‐ 2000kW‐hr System with ORC (η=20%), 75% H 2 O 2SOFC efficiencies from 45% to 60%Eneergy‐Out/Eneergy‐In (%)27%25%23%21%19%17%15%45% SOFC50% SOFC55% SOFC60%SOFC40% 45% 50% 55% 60%Nighttime Waste Heat Utilization Efficiency48

System Mass Sensitivity (5 kW, 75% Peroxide)A premier aerospace and defense companyMass (kg)System2400230022002100200019001800170016001500Mass vs. Nighttime Waste Heat Utilization Efficiency5kW ‐ 2000kW‐hr System, 75% H 2 O 2Day = Night, SOFC efficiencies from 45% to 60%45% SOFC50% SOFC55%SOFC60% SOFC40% 45% 50% 55% 60%Nighttime Waste Heat Utilization Efficiency49

System Mass Sensitivity (2 kW, 75% Peroxide)A premier aerospace and defense company1050Mass vs. Nighttime Waste Heat Utilization Efficiency2.0kW ‐ 800kW‐hr System, 75% H 2 O 2Day = Night, ih SOFC efficiencies i i from 45% to 60%45% SOFCSystemMass (kg)100095090085050% SOFC55% SOFC60% SOFC80040% 45% 50% 55% 60%Nighttime Waste Heat Utilization Efficiency50

Daytime Waste Heat (75% Peroxide)A premier aerospace and defense company18.0Daytime Waste Heat vs. Waste Heat Utilization Efficiency5kW ‐ 2000kW‐hr System with ORC with η=20%, 75% H 2 O 2Day = Night, SOFC efficiencies from 45% to 60%ste Heat (kW t)Wa17.016.015.014.013.045% SOFC50% SOFC55% SOFC60% SOFC12.040% 45% 50% 55% 60%Nighttime Waste Heat Utilization EfficiencyDaytime Waste Heat vs. Waste Heat Utilization Efficiency2.0kW ‐ 800kW‐hr System with ORC with η=20% , 75% H 2 O 2Day = Night, SOFC efficiencies from 45% to 60%W t)Waste Heat (kW7.06.86.6646.46.26.05.85.65.4525.25.045% SOFC50% SOFC55% SOFC60% SOFC40% 45% 50% 55% 60%Nighttime Waste Heat Utilization Efficiency51

Daytime Waste Heat (55% Peroxide)A premier aerospace and defense company24.0Daytime Waste Heat vs. Waste Heat Utilization Efficiency5kW ‐ 2000kW‐hr System with ORC with η=20%, 55% H 2 O 2Day = Night, SOFC efficiencies from 45% to 60%Waaste Heat (kW t)22.020.018.016.014.045% SOFC50% SOFC55% SOFC60% SOFC12.040% 45% 50% 55% 60%Nighttime Waste Heat Utilization EfficiencyDaytime Waste Heat vs. Waste Heat Utilization Efficiency2.0kW ‐ 800kW‐hr System with ORC with η=20% , 55% H 2 O 2Day = Night, SOFC efficiencies from 45% to 60%9.0kW t)Waste Heat (k8.58.07.57.06.56.05.545% SOFC50% SOFC55% SOFC60% SOFC5.040% 45% 50% 55% 60%Nighttime Waste Heat Utilization Efficiency52

A premier aerospace and defense companySOM MgO decomp0.3%SOFC2.6%Electrolyzer1.7%Pumps, valves04% 0.4%System Mass Distribution, Day = Night(5kW, 2000kWh, 75% H 2 O 2 )MgH2 synth0.2%MgOvessel0.6% Peroxide synthTurbine10.4%0.1%HeatRejection5.6%Separators0.3% Hydridereactor0.1%Peroxidereactor0.1%MgH2Tank0.8%MgH216.9%Peroxide Mixture58.2%Peroxide Tank1.7%53

A premier aerospace and defense companySystem Mass Distribution, Day = Night(5kW, 100kWh, 75% H 2 O 2 )Heat Rejection21.7%Peroxide Mixture11.3%Peroxide Tank0.3%MgH23.3%MgH2 Tank0.2%Peroxide reactor0.4%Hydride reactor0.4%Separators1.1%SOFC10.1%Pumps, valves1.7%Peroxide synth40.4%Electrolyzer6.5%MgOvessel0.1%Turbine0.6%SOM MgO decomp1.3%MgH2 synth0.6%54

A premier aerospace and defense companyReactants as a Percent of System MassDay = Night, 75% H 2 O 2Reaactant (%)80%70%60%50%40%30%20%10%0%2 kW System 5kW System0 500 1000 1500 2000Energy Stored (kWh)55

Key Results SummaryA premier aerospace and defense company• System is characterized by high energy density– ~1.1 kWh.kg for complete TRESS– ~1.4 kWh/kg for power generation only• As expected, high concentrations of peroxide are favorable– Less water to store and regenerate in peroxide mixture• Reactant storage is key mass and volume driver– Efficiency is key for power gen components – mass is secondary (or lower)56

100 W TRESS-derived Power Sources (ILN)A premier aerospace and defense companyOperational Time 336 hoursO 2 O 2H 2 @ 800°CO 2 @ 0°CO 2O 2 @ 800°CPOWEROUTSOFCStirling/ORCMgH 2ReactorMgH 2H 2 @ ~1000°CMgOMgOSteam@~100°CSteam@~1000°CStirling/ EnergyConverterWaterCondenserand CollectorPOWER OUTMgH 2H High PressureSOM + MgH 2 O 22ElectrolyzerO 2RegenerationDaytime Regeneration SystemPOWER IN(FROM SOLAR PV)MgH 2 /O 2 SystemWeight ~35kg; Volume ~140 lTCH/O 2 SystemWeight ~50kg; Volume ~220 l57

100 W MgH 2 /O 2 System ConfigurationA premier aerospace and defense companyO 2 TankMgH 2 SynthesisReactorElectrolyzerMgH 2 ReactorMgO CollectorSOM MgODecompositionReactorMgH 2 HopperSOFCStirlingCondensorShield/Structure58

ILN TRESS Variants – Mass DistributionsA premier aerospace and defense companyMass Distribution for 100W MgH 2 /O 2 based TRESS for ILNSolar ArrayStructure56%5.6% 9.7%O223.1%Heat Rejection13.9%MgH2 SynthesisReactor1.4%SOM6.8%MgH219.0%Mass Distribution for 100W TCH /O 2 based TRESS for ILNElectrolyzerl3.6%CondensorStirling0.7%2.7%SOFCO2 Tank3.9%6.9%MgO collectorMgH2 Reactor0.6%1.4%MgH2Hopper0.8%HydrogenationReactor1.0%Electrolyzer26%2.6%Solar Array4.0% Structure7.0%Heat Rejection10.0%O221.9%Condensor0.5%Stirling2.0%SOFC2.8%DehydrogenationReactor1.0%O2 Tank6.0%TCH39.9%59TCH/Terphenyl Tank1.3%

TRESS SummaryA premier aerospace and defense company• Our Thermochemical Regenerative Energy Storage System (TRESS) is apromising candidate to meet NASA’s requirements in a highly compact,efficient package• The system performance and form factor is superior to batteries and H 2 –O 2regenerative fuel cell based systems• TRESS is highly compatible with future in-situ resource utilization (ISRU) foradded long-term benefits• ATK has committed significant funding to the underlying CHOSS systemdevelopment60

A premier aerospace and defense companyThankYou!61