Hung D. Nguyen and Gynelle C. Steele

Glenn Research Center, Cleveland, Ohio

An Overview of 2014 SBIR Phase II 

Power, Energy Storage, and Storage

NASA/TM—2015-218902

December 2015
NASA STI Program . . . in Profi le

Since its founding, NASA has been dedicated 

to the advancement of aeronautics and space science. 

The NASA Scientifi c and Technical Information (STI) 

Program plays a key part in helping NASA maintain 

this important role.

The NASA STI Program operates under the auspices 

of the Agency Chief Information Offi cer. It collects, 

organizes, provides for archiving, and disseminates 

NASA’s STI. The NASA STI Program provides access 

to the NASA Technical Report Server—Registered 

(NTRS Reg) and NASA Technical Report Server—

Public (NTRS) thus providing one of the largest 

collections of aeronautical and space science STI in 

the world. Results are published in both non-NASA 

channels and by NASA in the NASA STI Report 

Series, which includes the following report types:

• TECHNICAL PUBLICATION. Reports of 

completed research or a major signifi cant phase 

of research that present the results of NASA 

programs and include extensive data or theoretical 

analysis. Includes compilations of signifi cant 

scientifi c and technical data and information 

deemed to be of continuing reference value. 

NASA counter-part of peer-reviewed formal 

professional papers, but has less stringent 

limitations on manuscript length and extent of 

graphic presentations.

• TECHNICAL MEMORANDUM. Scientifi c 

and technical fi ndings that are preliminary or of 

specialized interest, e.g., “quick-release” reports, 

working papers, and bibliographies that contain 

minimal annotation. Does not contain extensive 

analysis.

• CONTRACTOR REPORT. Scientifi c and 

technical fi ndings by NASA-sponsored 

contractors and grantees.

• CONFERENCE PUBLICATION. Collected 

papers from scientifi c and technical 

conferences, symposia, seminars, or other 

meetings sponsored or co-sponsored by NASA.

• SPECIAL PUBLICATION. Scientifi c, 

technical, or historical information from 

NASA programs, projects, and missions, often 

concerned with subjects having substantial 

public interest.

• TECHNICAL TRANSLATION. Englishlanguage translations of foreign scientifi c and 

technical material pertinent to NASA’s mission.

For more information about the NASA STI 

program, see the following:

• Access the NASA STI program home page at 

http://www.sti.nasa.gov

• E-mail your question to help@sti.nasa.gov

• Fax your question to the NASA STI 

Information Desk at 757-864-6500

• Telephone the NASA STI Information Desk at

 757-864-9658

• Write to:

NASA STI Program

 Mail Stop 148

 NASA Langley Research Center

 Hampton, VA 23681-2199
Hung D. Nguyen and Gynelle C. Steele

Glenn Research Center, Cleveland, Ohio

An Overview of 2014 SBIR Phase II 

Power, Energy Storage, and Storage

NASA/TM—2015-218902

December 2015

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135
Available from

Level of Review: This material has been technically reviewed by technical management. 

NASA STI Program

Mail Stop 148

NASA Langley Research Center

Hampton, VA 23681-2199

National Technical Information Service

5285 Port Royal Road

Springfi eld, VA 22161

703-605-6000

This report is available in electronic form at http://www.sti.nasa.gov/ and http://ntrs.nasa.gov/
Contents 

Abstract ......................................................................................................................................................... 1

High-Volume Production of Lightweight Multijunction Solar Cells ..................................................... 3

Active High-Temperature Heat Pipes .................................................................................................... 4

Thermal Management System for Long-Lived Venus Landers ............................................................. 5

Optimization of the Roll-Out Solar Array (ROSA) and Mega-ROSA ................................................... 6

Modular Ultra-High-Power Solar Array Architecture ............................................................................ 7

PV Concentrator Blanket Assembly for Ultralightweight Solar Arrays ................................................ 8

Lightweight IMM PV Flexible Blanket Assembly ................................................................................. 9

Advanced Passive Liquid Feed PEM Electrolyzer ............................................................................... 10 

Thin, Flexible IMM Solar Array .......................................................................................................... 11

High Radiation Resistance IMM Solar Cell ......................................................................................... 12 

High-Temperature, Wirebondless, Ultracompact Wide Bandgap Power Semiconductor Modules ..... 13

Mesoporous Silicon-Based Anodes ...................................................................................................... 14 

Autonomous Instrumentation and Control Maintenance and Health Monitoring System ................... 15

High-Speed Neutron and Gamma Flux Sensor .................................................................................... 16

Wrapped Multilayer Insulation ............................................................................................................. 17

High-Performance Elastically Self-Deployed Roll-Out Solar Array ................................................... 18

InGaN High-Temperature Photovoltaic Cells ...................................................................................... 19

Titanium Heat Pipe Thermal Plane ...................................................................................................... 20

Advanced Cathode Electrolyzer ........................................................................................................... 21

SiLix-C Nanocomposites ..................................................................................................................... 22 

Advanced Radiative Emitters ............................................................................................................... 23

NASA/TM—2015-218902 iii

An Overview of 2014 SBIR Phase II 

Power, Energy Storage, and Storage 

Hung D. Nguyen and Gynelle C. Steele 

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 44135 

Abstract 

NASA’s Small Business Innovation Research (SBIR) program focuses on technological innovation 

by investing in the development of innovative concepts and technologies to help NASA mission 

directorates address critical research and development needs for Agency programs. 

This report highlights 21 of the innovative SBIR Phase II projects from 2007 from 2012 that focus on 

one of NASA Glenn Research Center’s six core competencies—Power, Energy Storage, and Conversion. 

The technologies cover a wide spectrum of applications such as multijunction solar cells, roll-out solar 

arrays, photovoltaic concentrator blanket assemblies, wide bandgap power semiconductor modules, and 

indium-gallium nitride high temperature photovoltaic cells. Each article describes an innovation, technical 

objective, and highlights NASA commercial and industrial applications. 

This report provides as an opportunity for NASA engineers, researchers, and program managers to 

learn how NASA SBIR technologies could help their programs and projects, and lead to collaborations 

and partnerships between small SBIR companies and NASA that would benefit both. 

NASA/TM—2015-218902 1

MicroLink Devices, Inc. photo

NASA 

} Solar electric propulsion 

programs

Commercial and Military

} Electric-powered unmanned 

aerial vehicles (UAVs)

} Commercial and military 

satellites

} Portable solar electric power 

chargers

High-Volume Production of 

Lightweight Multijunction 

Solar Cells 

Reduces the cost of cells via a 6-inch gallium arsenide 

(GaAs) epitaxial lift-off and substrate reclaim process

MicroLink Devices, Inc., has transitioned its 6-inch epitaxial lift-off (ELO) 

solar cell fabrication process into a manufacturing platform capable of 

sustaining large-volume production. This Phase II project improves the ELO 

process by reducing cycle time and increasing the yield of large-area devices. 

In addition, all critical device fabrication processes have transitioned to 6-inch 

production tool sets designed for volume production. An emphasis on automated cassette-to-cassette and batch processes minimizes operator dependence 

and cell performance variability. MicroLink Devices established a pilot production line capable of at least 1,500 6-inch wafers per month at greater than 80 

percent yield. The company also increased the yield and manufacturability of 

the 6-inch reclaim process, which is crucial to reducing the cost of the cells.

Firm Contact

MicroLink Devices, Inc.

Christopher Youtsey

cyoutsey@mldevices.com

6457 West Howard Street

Niles, IL 60714–3301

Phone: 847–588–3001

Proposal Number: 11-2 X8.04-9001 

Phase II Objectives

} Improve the manufacturability 

and reduce the cost of the 6-inch 

ELO process for fabricating 

high-efficiency, large-area 

multijunction solar cells 

} Optimize the 6-inch ELO process 

for high throughput and yield 

(greater than 80 percent)

} Use automated process tool sets 

capable of more than 1,500 6-inch 

wafers per month

} Establish a production-ready 

6-inch GaAs substrate reclaim 

process

Benefits

} Produces lightweight and high 

specific power multijunction solar 

cells

} Offers an inexpensive and 

streamlined manufacturing process 

Applications

MicroLink Devices, Inc., photo

NASA/TM—2015-218902 3
NASA 

} Space fission nuclear reactors that 

utilize Stirling or thermoelectric 

converters for power conversion:

•	 1 kWe fission power system 

with a 15-year design life:

– The alkali metal heat 

pipes would be capable of 

transporting the reactor 

heat to the Stirling or 

thermoelectric converters 

for power generation.

•	 Lower temperature radiator 

heat pipes

Commercial and Military

} Waste heat energy recovery 

and utilization, specifically for 

automotive engines and military 

generator sets:

•	 The exhaust heat generated 

in these applications is 

considered high-grade heat 

and would require alkali metal 

heat pipes for collection and 

transportation.

•	 The high-temperature heat 

pipes could be used to collect 

the high-grade exhaust heat 

and transfer it to either a 

catalyst converter to reduce 

the energy needed for 

vehicle startup or to Stirling 

engines for electrical energy 

generation.

} High-temperature solar receivers:

•	 Thermochemical reduction 

processes used to generate 

alternate energy must be 

performed at very high 

temperatures. The hightemperature heat pipes 

developed could be used to 

transfer the thermal energy 

collected by a solar receiver to 

a reactor to aid in the thermochemical reduction process.

Active High-Temperature 

Heat Pipes 

For spacecraft nuclear fission systems

Future space transportation and surface power applications require small fission 

reactors for power generation. To support future NASA science missions, the 

reactors must have an 8- to 15-year design life. Heat pipes are being examined 

to transfer the thermal energy from the reactor to the electric conversion 

systems. Arterial heat pipes are the default design for spacecraft nuclear reactors; however, depriming of the artery due to radiation is a serious potential 

problem. Grooved and self-venting arterial heat pipes are less susceptible to 

depriming because the liquid in the grooves is open to the vapor space and 

the self-venting arterial heat pipe has venting pores in the evaporator to allow 

trapped vapor to escape. Advanced Cooling Technologies (ACT) examined the 

tradeoffs between the three types of heat pipe wicks—grooved, self-venting 

arterial, and sintered arterial—and determined an optimum wick design that is 

suitable for fission reactor applications.

Firm Contact

Advanced Cooling Technologies

Kara L. Walker

kara.walker@1-act.com

1046 New Holland Avenue

Lancaster, PA 17601–5688

Phone: 717–295–6081

Proposal Number: 11-2 X8.03-9866

Phase II Objectives

} Develop low-mass alkali metal heat 

pipes for space fission reactors, 

examining the tradeoffs between 

grooved, conventional arterial, 

and self-venting arterial heat pipe 

wicks

} Demonstrate the feasibility of alkali 

metal grooved and self-venting 

heat pipes for a space fission 

reactor 

} Fabricate and test full-length 

versions of the sintered arterial 

and self-venting arterial heat pipe 

wicks for both the Stirling and 

thermoelectric energy conversion 

systems

Benefits

} Ensures long design life

} Identifies optimum wick design for 

fission reactor applications

Applications

NASA photo

NASA/TM—2015-218902 4
NASA photo

NASA 

} Venus missions:

•	 Thermal management for a 

long-lived Venus lander cooled 

with a Stirling system 

•	 High-powered radioisotope 

systems that require a large 

number of GPHS modules

•	 Smaller systems that use the 

less-efficient americium-241–

based GPHS modules

} Deep space missions powered by 

alternate radioisotopes

} Missions to other hightemperature locations in the solar 

system

Commercial and Military

} Pressure-controlled isothermal 

furnace liners:

•	 An isothermal furnace liner is 

an annular alkali metal heat 

pipe. Replacing the current 

heat pipe with a pressurecontrolled VCHP will allow 

much tighter temperature 

control.

} Fuel cell reformers:

•	 In a fuel cell reformer, diesel 

fuel and air pass through a 

series of high-temperature 

reactors to generate hydrogen. 

The operating temperature of 

the reactors must be closely 

controlled to maintain their 

chemical equilibrium. Alkali 

metal VCHP heat exchangers 

can replace the current heat 

exchanger and control system 

with a passive system that 

automatically maintains 

the output stream from the 

heat exchanger at a constant 

temperature.

Thermal Management System for 

Long-Lived Venus Landers 

For more efficient thermal management on deep space 

missions

The thermal management system for a long-lived Venus lander is critical for 

mission success. This project is developing a passive high-temperature thermal 

management system (HTTMS) for the radioisotope power conversion system 

that energizes the refrigeration system for Venus missions. The innovation 

consists of a high-temperature alkali metal variable conductance heat pipe 

(VCHP) integrated with a two-phase heat collection/transport package from 

the general purpose heat source (GPHS) stack to the Stirling converter heater 

head. The HTTMS collects the heat from the GPHS modules and delivers 

heat, as required, to the Stirling system. The VCHP removes any excess heat 

when the Stirling system is shut down or in the early stages of a mission 

powered by a short-life radioisotope. A full-scale HTTMS has been designed 

and a representative multisegment of the full-scale HTTMS built and tested. 

This multisegment contains two or three parallel/redundant heat paths from 

the simulated GPHS stack to the heater head simulator in addition to the 

VCHP backup cooling system. The full-scale multisegment HTTMS has been 

integrated and tested with the corresponding full-scale multisegment of the 

intermediate-temperature thermal management system of the Venus lander. 

Firm Contact

Advanced Cooling Technologies

Calin Tarau

calin.tarau@1-act.com

1046 New Holland Avenue

Lancaster, PA 17601–5688

Phone: 717–295–6061

Proposal Number: 09-2 S3.03-8061

Phase II Objectives

} Develop an HTTMS for the 

long-lived Venus lander

} Develop a full-scale design 

} Fabricate a single-segment system 

for 650 °C that can be tested with 

a Stirling converter

} Fabricate and test a multisegment 

system operating at 1,000 °C, 

including tests in the Venus 

Chamber

Benefits

} Efficiently collects heat from the 

GPHS modules and delivers it to 

the Stirling engine

} Allows the Stirling converters and 

cooling to be shut off during the 

transit to Venus, saving heater 

head life

} Allows the use of alternative 

isotopes with a shorter half-life 

than plutonium-238

Applications

NASA photo

NASA/TM—2015-218902 5
NASA 

} Solar electric propulsion:

•	 Appropriate for NASA 

missions that require highefficiency photovoltaic power 

production through deployment of an ultralightweight 

and highly modular structural 

system

Commercial

} Solar electric propulsion

} Low Earth orbit (LEO) 

surveillance, reconnaissance, 

communications, commercial 

mapping, and other critical 

payload/equipment satellites

} Medium Earth orbit (MEO) 

satellites and space tugs

} Geosynchronous orbit (GEO) 

communications and critical 

payload/equipment satellites

} Fixed-ground and deployable/

retractable mobile ground-based 

systems

Optimization of the Roll-Out Solar 

Array (ROSA) and Mega-ROSA 

High-efficiency photovoltaic power production

The Mega-ROSA is a new, highly modularized, and extremely scalable selfdeployed solar array that provides immense power level range capability, from 

100 kilowatts to several megawatts. Mega-ROSA, an enhancement of NASA’s 

ROSA, will enable extremely high power spacecraft and solar electric propulsion powered missions, including space tug and large-scale planetary science 

and lunar/asteroid exploration missions. Mega-ROSA/ROSA is adaptable to all 

photovoltaic and concentrator flexible blanket technologies.

This Phase II project optimized the Mega-ROSA/ROSA technology and 

deployable structural system. More specifically, the project optimized the 

elastically deployable slit-tube thin-shell boom structures through advanced 

composites design, development and analytical modeling, materials design 

and development, innovative and affordable manufacturing processes, and 

the development of accurate engineering methodologies to rapidly allow for 

new material properties and design performance characterizations. The team 

developed new and innovative structural sections/configurations, such as 

section closeout and root reinforcement. Finally, the team developed and 

refined innovative and affordable composite structure fabrication processes.

Firm Contact

Deployable Space Systems, Inc.

Brian Spence

Brian.Spence@DeployableSpaceSystems.com

75 Robin Hill Road, Building B2

Goleta, CA 93117–3108

Phone: 805–722–8090

Proposal Number: 11-2 T3.01-9785

Phase II Objectives

} Optimize Mega-ROSA/ROSA solar 

array materials and structures

} Characterize creep/relaxation 

phenomena 

} Perform analytical modeling

} Optimize the array’s manufacturing 

process

Benefits

} Inexpensive

} Ultralightweight

} Compact stowage volume 

(< 50 kW/m3

 for very large arrays)

} High strength and stiffness

} Capable of providing power levels 

from 60 kW to more than 300 kW

} Operates in high-voltage and highor low-temperature environments

} Radiation tolerant

} Scalable

Applications

NASA photo NASA photo NASA photo

NASA/TM—2015-218902 6
NASA 

} PV power production

} High-power spacecraft

} Solar electric propulsion (SEP) 

spacecraft

} Space tugs

} Large-scale planetary science 

applications:

•	 Mega-ROSA’s potential 

to reduce launch vehicle 

needs could provide a step 

function in large NASA SEP/

Exploration mission cost 

savings. 

Commercial

DSS has formed a strategic 

relationship with Orbital Sciences 

Corporation and Space Systems 

Loral for this program and the 

Mega-ROSA technology to help 

expedite commercialization/technology infusion into their high-power 

applications, including: 

} High-power spacecraft

} Space tugs

} Power stations

} Other large-scale applications

} Low Earth orbit (LEO) 

surveillance, reconnaissance, 

communications, mapping, and 

other critical payload/equipment 

satellites

} Medium Earth orbit (MEO) 

satellites and resupply space tugs

} Geosynchronous Earth orbit 

(GEO) communications satellites

Modular Ultra-High-Power Solar 

Array Architecture 

Novel hardware for photovoltaic (PV) power production

Deployable Space Systems (DSS) has developed hardware for the Mega RollOut Solar Array (Mega-ROSA), a highly-modularized and scalable solar array 

that provides immense power level range capability. The Mega-ROSA technology can package much more power into a given launch vehicle envelope than 

any other solar array, potentially enabling new missions. The stowed package 

of an ultra-high-power array can fit within the compact stowage volume of a 

smaller, less expensive, and more readily available launch vehicle.

This Phase II project validated and demonstrated key Mega-ROSA hardware 

scale-up through the design, development, manufacture, and test of a very 

large, representative-scale Mega-ROSA engineering development unit (EDU) 

solar array wing system.

Firm Contact

Deployable Space Systems

Brian Spence

Brian.Spence@DeployableSpaceSystems.com

75 Robin Hill Road, Building B2

Goleta, CA 93117–3108

Phone: 805–722–8090

Proposal Number: 10-2 X8.04-9339

Phase II Objectives

} Validate and demonstrate key 

Mega-ROSA hardware scale-up 

} Design, develop, manufacture, 

and test a very large, representative-scale Mega-ROSA EDU solar 

array wing system

Benefits

} Low cost (25-50 percent cost 

savings, depending on PV and 

blanket technology)

} High specific power 

(>200 W/kg to 400 W/kg 

beginning of life [BOL] at the wing 

level, depending on PV and blanket 

technology)

} Compact stowage volume 

(>50 kW/m3

 for very large arrays)

} Platform simplicity (low parts 

count and reduced potential failure 

modes)

} High deployed strength/stiffness 

(>5 times stiffer and stronger than 

rigid panel arrays of similar sizes)

} High-voltage operations capability

} Scalable to ultrahigh power 

(100 kW to several megawatts)

} Unique environment operation 

(high/low illumination, high/low sun 

intensity, and high radiation)

Applications

NASA photo

NASA/TM—2015-218902 7
NASA 

} Advanced solar array systems 

Commercial

} Low Earth orbit (LEO)

surveillance, reconnaissance, 

communications, commercial 

mapping, and other critical 

payload/equipment satellites

} Medium Earth orbit (MEO) 

satellites and space tugs

} Geosynchronous Earth orbit 

(GEO) communications and 

payload/equipment satellites

} Dual-use opportunities for 

ground and roof-mount 

applications

} Mobile power production for 

terrestrial applications

PV Concentrator Blanket Assembly 

for Ultralightweight Solar Arrays 

Highly affordable, lightweight blanket assembly can be 

rolled or z-folded

The Flexible Array Concentrator Technology (FACT) is a lightweight, 

high-performance reflective concentrator assembly that can be used on solar 

array blankets. FACT replaces alternating rows of solar cells on a solar array 

blanket, significantly reducing the cost of the array. The modular design is 

highly scalable for the array system designer, and it exhibits compact stowage, 

good off-pointing acceptance, and mass/cost savings. The assembly’s relatively 

low concentration ratio, accompanied by a large radiative area, provides for a 

low cell operating temperature and eliminates many of the thermal problems 

inherent in designs with a high concentration ratio. Unlike other reflector 

technologies, the FACT modules function on both z-fold and rolled flexible 

solar array blankets as well as on rigid array systems.

This Phase II project demonstrated the FACT concentrator flexible blanket 

technology, with EMCORE Corp. standard third-generation triple junction 

(ZTJ) photovoltaic (PV) and advanced inverted metamorphic multijunction 

(IMM) PV, and integrated it onto the ultralightweight Roll-Out Solar Array 

(ROSA) system. The relevant tests and environments included ambient/

hot/cold functional deployments, thermal life cycle, vibration survivability, 

deployed strength/stiffness, mass properties, thermal balance in vacuum 

(forward bias), and high-voltage operation (water immersion). 

Firm Contact

Deployable Space Systems, Inc.

Brian Spence

Brian.Spence@DeployableSpaceSystems.com

75 Robin Hill Road, Building B2

Goleta, CA 93117–3108

Phone: 805–693–1313

Proposal Number: 10-2 S3.03-8462

Applications

Phase II Objectives

} Demonstrate the technology and 

integrate it onto the ultralightweight 

ROSA system

} Conduct detailed design and 

analysis

} Validate risk mitigation component/

breadboard hardware 

} Validate multiple FACT flight-like 

panel assembly hardware coupons 

} Validate large functional engineering 

development unit FACT/ROSA wing 

assembly hardware 

Benefits

} High specific power (>260 W/kg 

beginning of life [BOL] with 

ZTJ/NeXt triple-junction and 

~400 W/kg BOL with IMM PV 

when coupled to ROSA array)

} Affordable (>40 percent cost savings 

when coupled to ROSA array)

} Flexible blanket compatibility and 

architecture flexibility (accommodates rolled or z-folded blankets)

} Compact stowage volume 

(>50 kW/m3

)

} High radiation tolerance 

} High-voltage operation capability

} Adaptable to standard rigid honeycomb panel arrays

NASA photo

NASA/TM—2015-218902 8
NASA photo

NASA 

} Near- to medium-term NASA 

Discovery, Flagship OuterPlanets, and New Frontiers–class 

science missions

} Interplanetary comet rendezvous 

and solar electric propulsion 

science missions

} Low Earth orbit (LEO), 

geosynchronous Earth orbit 

(GEO), planetary or celestial-body lander, planetary 

orbiter, and/or deep space 

applications

Commercial and Military

} Power and energy production for 

fixed-ground, mobile, and roofmounted consumer applications

} High-altitude airship applications 

} LEO surveillance, reconnaissance, communications, 

commercial mapping, and other 

critical payload/equipment 

satellites

} GEO commercial and Defense 

Department communications 

and critical payload/equipment 

satellites

Lightweight IMM PV Flexible 

Blanket Assembly 

For high-voltage solar electric propulsion missions

Deployable Space Systems (DSS) has developed an inverted metamorphic 

multijunction (IMM) photovoltaic (PV) integrated modular blanket assembly 

(IMBA) that can be rolled or z-folded. This IMM PV IMBA technology 

enables a revolutionary flexible PV blanket assembly that provides high specific 

power, exceptional stowed packaging efficiency, and high-voltage operation 

capability. DSS’s technology also accommodates standard third-generation 

triple junction (ZTJ) PV device technologies to provide significantly improved 

performance over the current state of the art. 

This SBIR project demonstrated prototype, flight-like IMM PV IMBA 

panel assemblies specifically developed, designed, and optimized for NASA’s 

high-voltage solar array missions.

Firm Contact

Deployable Space Systems

Brian Spence

Brian.Spence@DeployableSpaceSystems.com

75 Robin Hill Road, Building B2

Goleta, CA 93117–3108

Phone: 805–805–1313

Proposal Number: 09-2 S3.03-8863

Phase II Objectives

} Demonstrate and validate 

prototype IMM PV IMBA panel 

assemblies specifically developed, 

designed, and optimized for 

NASA’s high-voltage solar array 

missions

} Develop scalable analytical models 

and correlate with test results to 

validate IMM PV IMBA prototype 

hardware

} Develop technology and 

manufacture infrastructure 

Benefits

} High-voltage operability

} High specific power 

(>1,000 W/kg beginning of life 

[BOL] at the blanket subsystem 

level; >500 W/kg BOL at the array 

level)

} Compact stowage volume 

(>50 kW/m3

)

} Rollable or z-foldable for stowage

} Flexible and durable

} Adaptable to all existing industry 

flexible blanket solar array 

products

Applications

NASA photo

NASA/TM—2015-218902 9
Phase II Objectives

} Evaluate and develop critical 

aspects of the advanced 

passive liquid cathode feed PEM 

electrolyzer

} Increase technical readiness level 

of the design

} Compare four water feed 

approaches

} Conduct data analysis and system 

modeling

} Design/Develop system and stack

} Test short stack performance and 

endurance

Benefits

} Reduces system weight

} Offers high operational efficiency

} Enhances current density capability

NASA 

} Energy storage

} High energy density systems for 

long-term space travel as well as 

lunar and Mars bases:

•	 Oxygen produced at high 

pressure can be used to meet 

life support needs, including 

recharge of the extravehicular 

mobility unit (EMU).

} Hydrogen recovery systems:

•	 Substantial savings are possible 

due to hydrogen loss resulting 

from cryogenic boil-off.

Commercial and Military

Successful development of efficient, 

high-pressure water electrolysis 

systems is critically important in 

meeting developing needs in the 

hydrogen economy:

} Refineries

} Ammonia production

} Chemical plants

} Vehicle refueling applications 

(require higher pressures, up to 

12,000 psi)

Advanced Passive Liquid Feed 

PEM Electrolyzer 

Reduces system weight while offering high operational 

efficiency

Proton Exchange Membrane (PEM) water electrolyzers have undergone 

continuous development for commercial, military, and space applications since 

the 1970s. Unfortunately, conventional technology requires a complex balance 

of plant components that add weight to the overall system package. This SBIR 

project is developing a high-pressure electrochemical cell architecture that 

uses novel water management technology to generate a passive liquid feed 

electrolyzer capable of operating at 2,000 psi and scalable to higher pressures. 

This new technology can substantially reduce system weight while offering high 

system operational efficiency and enhanced current density capability.

Firm Contact

Sustainable Innovations, LLC 

Trent Molter

trent.molter@sustainableinnov.com

160 Oak Street

Glastonbury, CT 06033–2336

Phone: 860–652–9690

Proposal Number: 10-2 X8.01-8730

Applications

Department of Energy photo

NASA/TM—2015-218902 10
NASA 

} Solar electric propulsion (SEP)

} Electric and magnetic field 

instruments used on NASA 

science spacecraft:

•	 Time History of Events and 

Macroscale Interactions 

during Substorms (THEMIS)

•	 Magnetospheric Multiscale 

(MMS) mission

•	 Mars Atmosphere and Volatile 

Evolution (MAVEN) space 

probe

•	 Direct-drive SEP approaches

Commercial 

} Commercial spacecraft 

Thin, Flexible IMM Solar Array 

Offering higher efficiencies and lower mass and flexibility

NASA needs solar arrays that are thin, flexible, and highly efficient; package 

compactly for launch; and deploy into large, structurally stable high-power 

generators. Inverted metamorphic multijunction (IMM) solar cells can enable 

these arrays, but integration of this thin crystalline cell technology presents 

certain challenges. The Thin Hybrid Interconnected Solar Array (THINS) 

technology allows robust and reliable integration of IMM cells into a flexible 

blanket comprising standardized modules engineered for easy production. The 

modules support the IMM cell by using multifunctional materials for structural 

stability, shielding, coefficient of thermal expansion (CTE) stress relief, and 

integrated thermal and electrical functions. The design approach includes total 

encapsulation, which benefits high voltage as well as electrostatic performance. 

In Phase I of this project, the THINS design was refined for enhanced 

environmental durability and integration into a large deployment structure 

such as Mega Roll-Out Solar Array (Mega-ROSA) or MegaFlex. Phase II 

advanced the THINS technology, incorporating advanced IMM solar cells 

into THINS modules and then integrating these modules into the MegaFlex 

deployable structure where it underwent environmental testing, including 

launch vibration, thermal vacuum deployment, and electrostatic discharge/

plasma testing. The THINS technology is further enhanced by automated 

manufacturing activities being performed under a Phase II SBIR with NASA, 

focusing on reducing manufacturing costs and scale-up. This technology is 

expected to provide tens to hundreds of kilowatts to enable outer planetary 

missions, allow improved solar electric propulsion performance during cruise, 

and provide significant power (i.e., hundreds of watts) despite the minimal 

sunlight available at the asteroid belt, Jupiter, and beyond.

Firm Contact

Vanguard Space Technologies, Inc.

Nicholas Walmsley

nwalmsley@vst-inc.com

9431 Dowdy Drive

San Diego, CA 92126–4633

Phone: 858–587–4200 ext. 1849

Proposal Number: 10-2 X8.04-9431

Applications

Phase II Objectives

} Fabricate and performance test a 

full-scale module

} Test module coupons in the 

most stressing simulated space 

environments

} Develop and fabricate a deployment 

demonstration of a THINS MegaFlex 

array containing a complete photovoltaic array blanket comprising THINS 

modules with some active cells

} Demonstrate full-scale deployment at 

ambient, hot, and cold temperatures

Benefits

} Designed for manufacturability using 

mature semiconductor industry 

standard equipment and processes

} Fits tens of kilowatts in a compact 

stowage envelope

} Improves process control

} Enables smaller, more economical 

launch vehicles

} Uses total encapsulation and 

continuity of cover glass materials 

to create a continuous grounded, 

shielded enclosure

NASA illustration

NASA/TM—2015-218902 11
NASA 

} Medium Earth orbit missions

} Outer planet missions

} Satellite power systems

Commercial

} Concentrator photovoltaic 

(CPV) systems to provide 

terrestrial solar power

High Radiation Resistance 

IMM Solar Cell 

For efficient, lightweight, radiation-resistant solar power

Due to high launch costs, weight reduction is a key driver for the development 

of new solar cell technologies suitable for space applications. This project is 

developing a unique triple-junction inverted metamorphic multijunction 

(IMM) technology that enables the manufacture of very lightweight, low-cost 

InGaAsP-based multijunction solar cells. This IMM technology consists 

of indium (In) and phosphorous (P) solar cell active materials, which are 

designed to improve the radiation-resistant properties of the triple-junction 

solar cell while maintaining high efficiency. The intrinsic radiation hardness of 

InP materials makes them of great interest for building solar cells suitable for 

deployment in harsh radiation environments, such as medium Earth orbit and 

missions to the outer planets. NASA Glenn’s recently developed epitaxial lift-off 

(ELO) process also will be applied to this new structure, which will enable the 

fabrication of the IMM structure without the substrate. 

Firm Contact

MicroLink Devices, Inc.

Noren Pan

npan@mldevices.com

6457 West Howard Street

Niles, IL 60714–3301

Phone: 847–588–3001 ext. 13

Proposal Number: 09-2 S3.03-8143

Phase II Objectives

} Reduce efficiency degradation to 

less than 10 percent

} Develop solar cells with efficiency 

greater than 30 percent

} Maintain high end-of-life 

performance 

Benefits

} Suitable for harsh environments

} Reduces or eliminates the heavy 

cover glass materials as required 

on conventional gallium-arsenide 

(GaAs)-based cells

} Uses the quaternary InGaAsP 

subcell rather than the GaAs 

subcell, allowing the use of a set 

of bandgaps that better match the 

solar spectrum

} Reuses multiple times, and 

ultimately recycles, the GaAs 

substrate on which the solar cell is 

grown via the ELO process 

Applications

NASA photo

NASA/TM—2015-218902 12
NASA 

} Wide operating temperature 

power semiconductors for space 

power systems and science 

missions:

•	 Spacecraft orbiting Earth, 

Venus, Europa, and Titan

•	 Lunar Quest Program 

Commercial 

} Power electronics, along with 

computer and microprocessor 

technology:

•	 Automobiles, electric utilities, 

pollution controls, communications, computer systems, 

consumer electronics, and 

factory automation

} Hybrid electric vehicles

} Renewable energy conversion

} Power supplies

High-Temperature, Wirebondless, 

Ultracompact Wide Bandgap Power 

Semiconductor Modules 

For space and commercial power systems

Silicon carbide (SiC) and other wide bandgap semiconductors offer great 

promise of high power rating, high operating temperature, simple thermal 

management, and ultrahigh power density for both space and commercial 

power electronic systems. However, this great potential is seriously limited by 

the lack of reliable high-temperature device packaging technology. 

This Phase II project developed an ultracompact hybrid power module 

packaging technology based on the use of double lead frames and direct 

lead frame-to-chip transient liquid phase (TLP) bonding that allows device 

operation up to 450 °C. The new power module will have a very small form 

factor with 3–5X reduction in size and weight from the prior art, and it will 

be capable of operating from 450 °C to –125 °C. This technology will have a 

profound impact on power electronics and energy conversion technologies and 

help to conserve energy and the environment as well as reduce the 

nation’s dependence on fossil fuels.

Firm Contact

Advanced Power Electronics Corp. (ApECOR) 

John Elmes

jelmes@apecor.com

3259 Progress Drive, Suite A

Orlando, FL 32826–2930

Phone: 407–275–1174

Proposal Number: 09-2 S3.05-8550

Applications

Phase II Objective

} Develop an ultracompact hybrid 

power module packaging technology 

based on the use of double lead 

frames and direct lead frame-to-chip 

TLP bonding

Benefits

} Device operation up to 450 °C

} Very high current-carrying capability

} Low package parasitic impedance

} Low thermomechanical stress at high 

temperatures

} Double-side cooling

} Modularity for easy system-level 

integration

NASA photo

NASA/TM—2015-218902 13
NASA 

} Power for landers, rovers, and 

extravehicular activities (EVAs)

} Space-related applications in 

Moon and other planetary 

habitats 

Commercial 

The new anodes will result in 

high-performance Li-ion batteries 

suitable for the following 

commercial applications: 

} Electric vehicle propulsion

} Portable consumer products:

•	 Cellular phones

•	 Portable power tools

•	 Cameras

•	 Laptop computers

Mesoporous Silicon-Based Anodes 

For high-capacity, high-performance lithium-ion batteries

A new high-capacity anode composite based on mesoporous silicon is being 

developed. With a structure that resembles a pseudo one-dimensional phase, 

the active anode material will accommodate significant volume changes 

expected upon alloying and dealloying with lithium (Li). The mesoporosity is 

created without the aid of a surfactant template using a novel, high-volume 

synthetic process. The anode composite based on this material is designed to 

have a reversible Li-ion capacity exceeding 600 mAh/g—or nearly twice that 

obtainable with graphite anodes—and much higher capacities could be attainable. Phase I successfully demonstrated the synthesis of this new meso-silicon 

(Si) material as well as its high electrochemical activity and rechargeability. 

Phase II expanded the investigation of the development of mesoporous 

Si-based Li-ion anodes. The optimum anode was evaluated in Li-ion cells 

containing 4-V oxide cathodes.

Firm Contact

EIC Laboratories, Inc.

Dharmasena Peramunage

pera@eiclabs.com

111 Downey Street

Norwood, MA 02062–2612

Phone: 781–769–9450

Proposal Number: 09-2 X7.01-8568

Applications

Phase II Objectives

} Expand the investigation of the 

development of a mesoporous, 

Si-based Li-ion anode 

} Evaluate the optimum anode in Li-ion 

cells containing 4-V oxide cathodes

Benefits

} Reversible Li-ion capacity exceeding 

600 mAh/g (nearly twice that 

obtainable with graphite anodes)

} Nonflammable

} Subambient temperature operation

NASA/TM—2015-218902 14
NASA 

} Space nuclear reactors

} Nonnuclear test systems used 

for component- and system-level 

validation

} Aircraft structural and system 

health monitoring

} Chemical propulsion systems

} Ground test facilities for liquid 

fuel rocket motor testing and 

development

Commercial 

} Nuclear power utilities for health 

monitoring

} Small modular reactors for 

autonomous health monitoring 

systems

} Aircraft structural and system 

health monitoring

} Chemical propulsion systems

Autonomous Instrumentation and 

Control Maintenance and Health 

Monitoring System 

For fission surface power (FSP)

The primary goal of this project is to design and develop an autonomous 

instrumentation and control (I&C) health monitoring system for space nuclear 

power applications. The system will be able to detect anomalies based on 

analytical modeling techniques that use data from existing sensors in the power 

generator.

This Phase II project is extending the software and algorithm design into a fully 

functional software module for the health monitoring system. In designing and 

building the system, Analysis and Measurement Services Corp. (AMS) worked 

with NASA to determine the specific number and types of sensors, sensor interfaces, and data transfer protocols to be used. Researchers used data collected at 

the AMS labs and NASA historical test loop data to perform final validation 

testing of the developed health monitoring system. This autonomous I&C and 

health monitoring technology can be applied to a wide range of applications, 

including other space applications, propulsions systems, and next-generation 

designs of nuclear reactors.

Firm Contact

Analysis and Measurement Services Corp.

Brent Duane Shumaker

bshumaker@ams-corp.com

9119 Cross Park Drive

Knoxville, TN 37923–4505

Phone: 865–691–1756 ext. 113

Proposal Number: 09-2 X7.02-8908

Applications

Phase II Objectives

} Design and develop the prototype 

health monitoring system:

•	 Establish software and hardware 

requirements

•	 Design and build software 

modules and hardware

•	 Integrate software and hardware 

components into a complete, 

self-contained prototype system

} Demonstrate functionality of the 

system:

•	 Test integrated system on the AMS 

test loop

•	 Test system on simulated or 

historical data from FSP test loop 

and operational FSP test loop

Benefits

} Detects system anomalies using 

analytical modeling techniques

} Provides online calibration monitoring

} Provides sensor validation and fault 

detection capabilities

} Enables automated diagnosis of 

sensor and process anomalies

NASA/TM—2015-218902 15
NASA 

} Lunar surface power reactors

} Mars surface power reactors

} Nuclear thermal propulsion for 

Mars manned missions

Commercial 

} Nuclear power plants

} Nuclear waste storage facilities

} Monitoring spent fuel

High-Speed Neutron and Gamma 

Flux Sensor 

For monitoring surface nuclear reactors

NASA needs compact nuclear reactors to power future bases on the Moon and 

Mars. These reactors require robust automatic control systems using low-mass, 

rapid-response, in–core reactor power monitoring sensors and radiationtolerant sensor interrogation systems that do not yet exist. Luna Innovations 

developed a new type of fiber optic miniature sensor of neutron flux and 

gamma flux that will have significantly faster response than recently developed 

fiber optic radiation sensors. Luna has optimized the sensor design and the 

interrogation system for high-temperature, in-core monitoring of both gamma 

flux and neutron flux with internal thermal compensation and in situ thermal 

calibration. Luna is delivering a lightweight sensor interrogation system, using 

experimentally verified radiation-hardened components wherever possible, 

including an analog output signal for interfacing with standard reactor control 

electronics. While the sensor development was focused on nuclear space power 

needs, the sensors also can be directly used for monitoring terrestrial nuclear 

power reactors.

Firm Contact

Luna Innovations

Matthew Davis

davism@lunainc.com

3157 State Street

Blacksburg, VA 24060–6604

Phone: 540–961–6731

Proposal Number: 09-2 X7.02-9116

Applications

Phase II Objectives

} Demonstrate the feasibility of fiber 

optic gamma thermometer sensors

} Continue development of the novel 

fiber optic neutron flux sensors

} Develop a strategy for the sensor 

interrogation system to operate in 

space radiation

Benefits

The new sensors will maintain the 

advantages of current fiber optic reactor 

sensor technology, including:

} Small size for in-core sensor 

distributions

} High-temperature performance 

(>600 °C)

} High-speed performance

} Immunity to electrical noise in the 

presence of ionizing radiation

NASA/TM—2015-218902 16
NASA 

} New NASA vehicles

} Orbiting fuel depots

} Vacuum-insulated pipe used to 

transfer cryogens

Commercial 

} Food, research, medical, and 

industrial applications:

•	 Transfers of cryogenic liquid 

into and from cryogenic 

dewars for liquid nitrogen 

(LN2

), hydrogen (LHe), and 

oxygen (LOX)

} Industrial:

•	 Handling LN2

, LOX, and 

liquefied natural gas (LNG)

•	 Handling piping, automatic 

filling equipment, dewar 

manifolds, and gas panels

} LNG:

•	 High-performance insulated 

cryogenic transfer piping 

to reduce LNG losses from 

vaporization during liquid 

transfer

} LN2 equipment:

•	 Semiconductor, electronics, 

and aerospace environmental 

temperature testing

•	 Special effects (fogging), 

biological freezing applications, inerting of food and 

beverage containers, container 

pressurization, and food 

freezing

Wrapped Multilayer Insulation 

Thermal insulation for cryogenic piping

New NASA vehicles, such as Earth Departure Stage (EDS), Orion, landers, and 

orbiting fuel depots, need improved cryogenic propellant transfer and storage 

for long-duration missions. Current cryogen feed line multilayer insulation 

(MLI) performance is 10 times worse per area than tank MLI insulation. 

During each launch, cryogenic piping loses approximately 150,000 gallons 

(equivalent to $300,000) in boil-off during transfer, chill down, and ground 

hold. Quest Product Development Corp., teaming with Ball Aerospace, 

developed an innovative advanced insulation system, Wrapped MLI (wMLI), 

to provide improved thermal insulation for cryogenic feed lines.

wMLI is high-performance multilayer insulation designed for cryogenic piping. 

It uses Quest’s innovative discrete-spacer technology to control layer spacing/

density and reduce heat leak. The Phase I project successfully designed, built, 

and tested a wMLI prototype with a measured heat leak 3.6X lower than 

spiral-wrapped conventional MLI widely used for piping insulation. A wMLI 

prototype had a heat leak of 7.3 W/m2

, or 27 percent of the heat leak of 

conventional MLI (26.7 W/m2

). 

The Phase II project is further developing wMLI technology with custom, 

molded polymer spacers and advancing the product toward commercialization 

via a rigorous testing program, including developing advanced vacuuminsulated pipe for ground support equipment.

Firm Contact

Quest Product Development Corporation 

Scott A. Dye

sdye@quest-corp.com

6833 Joyce Street

Arvada, CO 80007–7570

Phone: 303–670–5088 ext. 12

Proposal Number: 09-2 X8.01-8258

Applications

Phase II Objectives

} Design and develop a custom, 

molded polymer spacer

} Further develop assembly and 

installation processes

} Develop and test wMLI for three 

different piping diameters

} Conduct testing to optimize spacer 

and wrap geometries

} Perform thermal testing on 12 

different wMLI test configurations

} Perform thermal testing on 

advanced ”clam-shell” netting MLI

} Design, develop, and test MLI in a 

vacuum-insulated pipe prototype for 

use in ground support equipment

Benefits

} Low heat leak (3.6X less than 

conventional MLI)

} Easy assembly

} Few layers

} Low cost

} Less mass

NASA/TM—2015-218902 17
NASA photo

Firm Contact

Deployable Space Systems

Brian Spence

Brian.Spence@DeployableSpaceSystems.com

75 Robin Hill Road, Building B2

Goleta, CA 93117–3108

Phone: 805–693–1319

Proposal Number: 08-2 S3.03-8644

Phase II Objectives

} Establish technology validation and 

demonstrate technology readiness 

level (TRL) 5–6 of an optimized and 

scaled-up ROSA solar array with thin 

IMM PV and ZTJ PV 

} Validate technology through requirements definition, detailed design and 

development, analytical modeling, 

hardware risk mitigation, and build/

test of a very large (10 kW size) ROSA 

engineering development unit wing 

system

} Correlate analytical models with test 

results

Benefits

} High specific power (up to 400 W/kg 

beginning of life [BOL] with IMM and 

~200 W/kg with ZTJ)

} Lightweight

} High deployed strength and stiffness

} Compact stowage volume 

(>50 kW/m3

 BOL)

} Reliable

} Affordable

NASA photo

NASA 

} Direct replacement for standard 

solar array technologies in space

} Low Earth orbit (LEO), geosynchronous Earth orbit (GEO), 

interplanetary, deep space, 

outer planets, lunar surface, and 

planetary lander missions

Commercial and Military

} Direct replacement for terrestrial 

solar array technologies

} LEO, GEO, medium Earth orbit 

(MEO), fixed-terrestrial, and 

mobile-terrestrial applications:

•	 Operational responsive space, 

nanosatellite, military satellite 

communications systems, 

space-based radar, solar 

electric tugs, military space 

and/or terrestrial applications, 

and Army mobile power 

applications

High-Performance Elastically 

Self-Deployed Roll-Out Solar Array 

Lightweight, compact, flexible solar arrays

Deployable Space Systems has developed an ultralightweight elastically 

self-deployable Roll-Out Solar Array (ROSA) structural platform. When 

combined with ultrathin 33 percent inverted metamorphic multijunction 

(IMM) photovoltaic (PV) or 29.5 percent standard third-generation 

triple-junction (ZTJ) PV solar cell, flexible blanket technologies can produce 

a near-term and low-risk solar array system that provides revolutionary performance. ROSA’s predicted performance metrics are significant improvements 

over current state of the art, and in many cases they are mission-enabling for 

future applications. The ROSA technology innovation is applicable to 

practically all NASA and non-NASA missions as a direct replacement for 

current solar array technologies. 

The Phase II project was uniquely structured to develop a feasible scaled-up 

ROSA system specifically configured for NASA’s outer-planets missions. This 

project will rapidly enable the ROSA technology for commercial infusion into 

future programs.

Applications

NASA/TM—2015-218902 18
NASA 

} Missions near the Sun:

•	 Solar Orbiter

•	 Solar Sentinels in the Living 

with a Star (LWS) Program 

} Missions in high-radiation 

environments

Commercial and Military

} Terrestrial DoD applications

InGaN High-Temperature 

Photovoltaic Cells 

For high-temperature, high-radiation environments

This Phase II project developed Indium-Gallium-Nitride (InGaN) photovoltaic 

cells for high-temperature and high-radiation environments. The project 

included theoretical and experimental refinement of device structures produced 

in Phase I as well as modeling and optimization of solar cell device processing. 

The devices have been tested under concentrated air mass zero (AM0) sunlight, at temperatures from 100 °C to 250 °C, and after exposure to ionizing 

radiation. The results are expected to further verify that InGaN can be used for 

high-temperature and high-radiation solar cells. 

The large commercial solar cell market could benefit from the hybridization 

of InGaN materials to existing solar cell technology, which would significantly 

increase cell efficiency without relying on highly toxic compounds. In addition, 

further development of this technology to even lower bandgap materials for 

space applications would extend lifetimes of satellite solar cell arrays due to 

increased radiation hardness. This could be of importance to the Department 

of Defense (DoD) and commercial satellite manufacturers.

Firm Contact

Integrated Micro Sensors, Inc. 

David Starikov 

dstarikov@imsensors.com

10814 Atwell Drive

Houston, TX 77096–4934

Phone: 713–748–7926

Proposal Number: 08-2 S3.03-9731

Applications

Phase II Objectives

} Refine single-junction device 

structures

} Optimize the processing of 

single-junction devices

} Demonstrate two-junction devices

} Verify the stability of InGaN solar 

cells at high temperatures and high 

radiation environments

Benefits

} Remains stable in high-temperature 

and high-radiation environments

} Extends lifetime of satellite solar cell 

arrays

NASA/TM—2015-218902 19
NASA 

} Passive fuel cell or electrolysis cell 

heat removal/thermal control

} Spacecraft onboard electronics 

cooling

} Isothermal panels for heat 

radiation into space

} Radiator demonstration unit 

(RDU) panels

Commercial

} Electronics cooling

Titanium Heat Pipe Thermal Plane 

For thermal management of fuel cells

This Phase II project is completing the development of a titanium heat pipe 

thermal plane for thermal management of fuel cells for space applications as 

well as commercial applications. Modern electronic components are small in 

size and generate heat fluxes that cannot be handled by pure conduction or 

direct forced convection cooling technologies. This planar heat pipe can be 

integrated with a printed circuit board (PCB), allowing it to stay at nearuniform temperature. As a result, several components can be cooled utilizing a 

single cooling device located at the edge of the PCB.

In Phase I, three thermal plane units were produced and thermally tested. One 

unit was shipped to NASA Glenn, and one unit is currently in a “burn-in” 

setup for noncondensable gas (NCG) generation prevention. NCG generation 

still remains the most important issue to be resolved before the heat pipe will 

be ready for production. Another limiting factor for wide commercial application of the titanium heat pipes is their high manufacturing cost. These issues 

have been addressed in the Phase II project.

Phase II involved requirements review, thermal plane design, alternative 

materials development, design optimization, and NCG abatement. Researchers 

also are establishing all necessary steps for production of this heat pipe.

Firm Contact

Thermacore

Sergey Y. Semenov

s.y.semenov@thermacore.com

780 Eden Road

Lancaster, PA 17601–4275

Phone: 717–519–3133

Proposal Number: 08-2 X6.01-8889

Applications

Phase II Objectives

Develop titanium heat pipe thermal plane 

with the following parameters:

} Heat pipe thickness: 

0.045±0.005 inches

} Bulk density: ≤ 3 g/cm3

} Effective thermal conductivity: 

≥ 2,000 W/m∙K

} Electrical resistivity: ≤ 0.2 Ω∙cm

} Operation against gravity: ≥ 6 inches

} Operating temperature range: 

+20 °C to +90 °C

} Maximum heat flux: ≥ 0.5 W/cm2

} Evaporator area: ≥ 150 cm2

} Condenser area: ≤ 9 cm2

} Life cycle: ≥ 10 years

} Manufacturing cost: ≤ $1,000 each

} Compression strength: ≥ 400 psi

Benefits

} High thermal conductivity

} Low effective density

} Coefficient of thermal expansion (CTE) 

match with titanium round heat pipes

NASA/TM—2015-218902 20
NASA 

} Lunar and planetary fixed-base 

energy storage

} Recharge of lunar rovers and 

portable power fuel cells

} Generation of oxygen for crew 

life support

Commercial

} Recharge of fuel cells for 

telecommunications backup 

power

} Remote off-grid power

} Undersea fuel cell systems

} Aircraft and airship energy 

storage systems

Advanced Cathode 

Electrolyzer 

Based on proton exchange membrane (PEM) 

electrolysis technology

This Phase II project developed a static, cathode-fed, 2,000 psi, balancedpressure Advanced Cathode Electrolyzer (ACE) based on PEM electrolysis 

technology. It electrolyzes water vapor supplied to the hydrogen-evolving 

electrode and eliminates the need to circulate hydrogen and water on the 

cathode side of the cell. Infinity Fuel Cell and Hydrogen’s proprietary cellsealing technology is applied to electrolysis to minimize high-pressure seals. In 

addition, innovative passive current-control techniques are used to eliminate 

potential hydrogen gas in feedwater chambers. ACE produces hydrogen and 

oxygen that is free of liquid water droplets without using dynamic product 

gas/liquid water phase separation or other motorized equipment. 

Firm Contact

Infinity Fuel Cell and Hydrogen, Inc. 

William Smith

wsmith@infinityfuel.com

431A Hayden Station Road

Windsor, CT 06095–1373

Phone: 860–688–6500

Proposal Number: 08-2 X6.01-9321

Applications

Phase II Objectives

} Prove the concept of a gravityindependent primary cathode vapor 

feed electrolysis cell

} Define and assess the benefits of ACE 

technology when incorporated into a 

complete system

Benefits

} Eliminates the need to circulate 

hydrogen and water on the cathode 

side of the cell

} Minimizes high-pressure seals

} Eliminates potential hydrogen gas in 

feedwater chambers

NASA photo

NASA/TM—2015-218902 21
NASA 

} Ascent module of the Altair 

Lunar Lander 

} Lunar extravehicular activity 

(EVA) suit and integrated 

portable life support systems

} Lunar surface systems and 

mobility systems 

} Uninterruptable power systems 

(UPS) for Orion spacecraft, the 

International Space Station (ISS), 

and other spaceflight vehicles

Commercial and Military

} Power sources for hybrid 

electric and electric vehicles 

(HEV and EV)

} Portable consumer electronics

} Handheld military equipment, 

exploration robots, and drones

SiLix-C Nanocomposites 

For high energy density Li-ion battery anodes

For this Phase II project, Superior Graphite Co., in collaboration with the 

Georgia Institute of Technology and Streamline Nanotechnologies, Inc., 

developed, explored the properties of, and demonstrated the enhanced 

capabilities of novel nanostructured SiLix-C anodes. These anodes can retain 

high capacity at a rapid 2-hour discharge rate and at 0 °C when used in Li-ion 

batteries. 

In Phase I, these advanced anode materials had specific capacity in excess of 

1,000 mAh/g, minimal irreversible capacity losses, and stable performance 

for 20 cycles at C/1. The goals in Phase II were to develop and apply a variety 

of novel nanomaterials, fine-tune the properties of composite particles at the 

nanoscale, optimize the composition of the anodes, and select appropriate 

binder and electrolytes. In order to achieve a breakthrough in power characteristics of Li-ion batteries, the team developed new nanostructured SiLix-C 

anode materials to offer up to 1,200 mAh/g at C/2 at 0 °C.

Firm Contact

Superior Graphite Co.

Francois Henry

FHenry@superiorgraphite.com

10 South Riverside Plaza, Suite 1470

Chicago, IL 60606–3700

Phone: 773–209–4793

Proposal Number: 08-2 X6.02-8492

Applications

Phase II Objectives

} Identify ideal combination of binder 

and electrolyte material to maximize 

performance for silicon-carbon (SiC) 

nanocomposite powder at 0 °C using 

a charge/discharge rate of C/2

} Identify and adjust optimum parameters of SiC nanocomposite powder, 

such as particle size, thickness, and 

morphology of the carbon coating; 

porosity of the adaptive carbon matrix; 

size of Si crystals; and Si content

} Determine origin of irreversible 

capacity loss 

} Plan and build small pilot plant 

} Optimize synthesis process of SiC 

nanocomposite powders to maximize 

uniformity and reproducibility

} Develop an anode-based on the novel 

SiC nanocomposite powder that offers 

1,200 mAh/g at C/2 at 0 °C and a 

long cycle life

Benefits

} High energy density

} Dramatically improved capacity

} Cycling performance

NASA illustration

NASA/TM—2015-218902 22
NASA 

} Deep space power systems

} Exploration of the outer solar 

system for both spacecraft and 

rovers

Commercial and Military

} Military sensing 

} Power for deep sea monitoring 

instruments

} Monitoring stations in remote 

locations

Advanced Radiative Emitters 

For radioisotope thermophotovoltaic (RTPV) power systems

Radioisotope power systems (RPS) are critical for future space and planetary 

exploration missions. Small improvements in RPS performance, weight, size, 

and reliability can have a dramatic effect on the scientific capability of the vehicle and the overall mission costs. RTPV energy converters are a particular type 

of RPS that directly convert the heat produced by a general purpose heat source 

to electrical power using a specialized photovoltaic (PV) cell. A key element 

in an RTPV system is the radiative emitter that converts thermal energy into 

radiative energy to illuminate the PV cell. 

In this project, Creare and the Massachusetts Institute of Technology have 

advanced the development of a two-dimensional photonic crystal radiative 

emitter optimized for RTPV systems. The technology provides high emittance 

matched to the bandgap of the PV cell with low emittance elsewhere, providing 

high system efficiency. In Phase I, the team designed, fabricated, and tested 

prototype emitters. In Phase II, they improved and scaled up the fabrication 

processes. They also fabricated larger, improved test samples to be fully 

characterized for high-temperature emittance and durability. The project also 

assessed the impact of this new emitter on the overall RTPV system design and 

performance.

Firm Contact

Creare, Inc.

Richard W. Kaszeta

rwk@creare.com

P.O. Box 71

Hanover, NH 03755–0071

Phone: 603–643–3800 ext. 2441

Proposal Number: 08-2 T3.01-9974

Applications

Phase II Objectives

} Develop an improved design of the 

photonic crystal for RTPV applications

} Improve high-temperature stability

} Match performance to current RTPV 

operating constraints

} Develop and demonstrate techniques 

for fabricating larger photonic crystals

} Quantify the advantages that the 

fabricated crystals provide to overall 

system efficiency

Benefits

} High mass-specific power

} High system efficiency

NASA photo

NASA/TM—2015-218902 23