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Ceramic Matrix Composite Combustion Chamber for HAN-Based Monopropellants

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX09CE13P
Agency Tracking Number: 085365
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: N/A
Solicitation Number: N/A
Solicitation Year: N/A
Award Year: 2009
Award Start Date (Proposal Award Date): N/A
Award End Date (Contract End Date): N/A
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
 Principal Investigator
 (818) 899-0236
Business Contact
 Craig Ward
Title: Engineering Administrative Mgr
Phone: (818) 899-0236
Research Institution

Ultramet will design and fabricate a lightweight, high temperature 5-lbf combustion chamber. The system will be designed for use with the AF-315 family of monopropellants, which have specific impulse values well in excess of 240 sec, and the combustion chamber material will be based on Ultramet's proven [Zr,Si]C 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, hot-fire testing has been done on Ultramet CMC chambers with both O2/H2 and AF-315e propellants. Ultramet will work closely with a leading supplier of spacecraft propulsion systems that will provide the chamber design and perform the hot-fire testing. The fabrication process and the survivability of the material system will be demonstrated in Phase I. Phase II would include long-duration life testing of the Phase I chamber as well as the design, fabrication, and testing of a chamber in the 100- to 500-lbf thrust class suitable for a payload ascent vehicle.

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

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