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Lightweight, Low-Cost Ceramic Matrix Composite Combustion Chambers for DACS

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: HQ0147-09-C-7114
Agency Tracking Number: B083-005-0636
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: MDA08-005
Solicitation Number: 2008.3
Timeline
Solicitation Year: 2008
Award Year: 2009
Award Start Date (Proposal Award Date): 2009-03-27
Award End Date (Contract End Date): 2009-09-27
Small Business Information
12173 Montague Street
Pacoima, CA 91331
United States
DUNS: 052405867
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Arthur Fortini
 Director of Science & Technology
 (818) 899-0236
 art.fortini@ultramet.com
Business Contact
 Craig Ward
Title: Engineering Administrative Manager
Phone: (818) 899-0236
Email: craig.ward@ultramet.com
Research Institution
N/A
Abstract

In this project, Ultramet will design, build, and hot-fire test a lightweight, low-cost, high-temperature 5-lbf combustion chamber. The system will be designed for the AF-315 family of monopropellants, which have specific impulse values ranging from 263 to 288 sec, and the combustion chamber material will be based on Ultramet’s proven zirconium-silicon carbide ceramic matrix composite (CMC) technology. This material system allows the zirconium carbide-to-silicon carbide ratio in the matrix to be adjusted, thus enabling the material to be optimized for different combustion environments. To date, Ultramet CMC chambers have been hot-fire tested with both O2/H2 (flame temperature of ~3000°C) and AF-315e. Ultramet will work closely with a leading supplier of spacecraft propulsion systems that will provide the chamber design and perform hot-fire testing with AF-315e. The fabrication process and the survivability of the material system will be demonstrated in Phase I. Phase II will include longer duration testing of the Phase I chamber to quantify life margin with respect to MDA mission requirements, and it will include design, fabrication, and testing of a chamber in the 100-lbf thrust class suitable for high accelerations and high-velocity change applications. It is anticipated that Phase II chambers will be tested with an AF-315 blend (for MDA applications) and with Earth-storable bipropellants (for commercial applications).

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

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