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High Specific Power Primary Fuel Cell System

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC20C0193
Agency Tracking Number: 193829
Amount: $744,472.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: Z1
Solicitation Number: SBIR_19_P2
Solicitation Year: 2019
Award Year: 2020
Award Start Date (Proposal Award Date): 2020-07-07
Award End Date (Contract End Date): 2022-07-06
Small Business Information
410 Sackett Point Road
North Haven, CT 06473-3106
United States
DUNS: 178154456
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Christian Junaedi
 (203) 287-3700
Business Contact
 Rose Anderson
Title: roconnor
Phone: (203) 287-3700
Research Institution

Precision Combustion, Inc. (PCI) proposes to further mature a Primary Fuel Cell (PFC) System that will meet NASArsquo;s lunar mission target specifications of (i) high specific power (gt;2,000 W/kg), (ii) high current density (gt;200 mA/cm2), (iii) long service life (a final operational life of gt;10,000 hrs is targeted), and (iv) operability with H2/O2, CH4/O2, and other propellants.nbsp; The PFC system contains multiple innovations and will comprise SOFC and internal reforming catalyst that permit a potential for high fuel utilization and very high specific power, while allowing SOFC operation with hydrocarbon fuels (e.g., CH4 and scavenged propellants). The innovative design and integration of at-anode reforming elements have been demonstrated for effective internal heat exchange and moderate the operating temperature of the stack. The approach also offers the potential to operate with a wide range of input fuels without forming carbon. At the end of Phase I, a clear path towards a 1 kW PFC system prototype demonstration in Phase II was described. In a follow on Phase III, a complete modular SOFC system will be developed, demonstrated, and delivered to a NASA facility for demonstration testing in a relevant environment. PCIrsquo;s approach will result in a system that will be much smaller, lighter, more thermally effective and efficient than current technology or prospective alternative technologies. This effort would be valuable to NASA as it would significantly reduce the known long-duration mission technical risks and increase mission capability/durability/efficiency while at the same time increasing the TRL of the solid oxide systems for lunar/Mars power generation and ISRU application.

* Information listed above is at the time of submission. *

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