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Thermal-Catalytic Ignition Source for Ionic Liquid Monopropellants

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX12CD85P
Agency Tracking Number: 115102
Amount: $125,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: S3.04
Solicitation Number: N/A
Solicitation Year: 2011
Award Year: 2012
Award Start Date (Proposal Award Date): 2012-02-13
Award End Date (Contract End Date): 2012-09-13
Small Business Information
12173 Montague Street
Pacoima, CA -
United States
DUNS: 052405867
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Matthew Wright
 Principal Investigator
 (818) 899-0236
Business Contact
 Craig Ward
Title: Engineering Administrative Mgr
Phone: (818) 899-0236
Research Institution

Ultramet recently demonstrated rapid, reliable, and repeated ignition of hydroxylammonium nitrate (HAN)-hydroxyethylhydrazinium nitrate (HEHN) monopropellant mixtures. Before this milestone was achieved, the feasibility of using this advanced ionic liquid monopropellant was distant. In this project, Ultramet will build on that success and develop novel architectures and the related processing to render a thermal ignition source based on resistive heating of refractory monolithic open-cell foam. In Phase I, prototype igniters and an oxide-iridium/rhenium thruster appropriate for an attitude control system will be designed and fabricated. Engine testing with AF-315E and ammonium dinitramide (ADN) monopropellants will be performed at the Jet Propulsion Laboratory (JPL) at no cost to the project. In Phase II, longer hot-fire testing would be performed with both monopropellants at JPL and/or industry partners Aerojet, AMPAC-ISP, Northrop Grumman, or ATK, all of which have expressed interest in the technology. ADN and HAN/HEHN green monopropellants offer many improvements over hydrazine, including increased specific impulse and density specific impulse, as well as greater safety in terms of toxicity and insensitivity, which will significantly decrease overall propulsion volume, mass, and cost. Because the thermal bed is nondiscriminate to the propellant, additional propellants may be included in follow-on testing.

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

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