You are here

TaC/TaC CMCs for Aluminized Propellant SRMs

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: N00167-04-C-0039
Agency Tracking Number: B041-035-1048
Amount: $99,771.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: MDA04-035
Solicitation Number: 2004.1
Solicitation Year: 2004
Award Year: 2004
Award Start Date (Proposal Award Date): 2004-06-22
Award End Date (Contract End Date): 2004-12-21
Small Business Information
31304 Via Colinas, Suite 102
Westlake Village, CA 91362
United States
DUNS: 869308346
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Edward A. Pope
 (818) 991-8500
Business Contact
 Edward A. Pope
Title: President
Phone: (818) 991-8500
Research Institution

In this proposed MDA Phase I SBIR Program, MATECH seeks to develop woven TaC ceramic fiber reinforced TaC matrix CMCs for aluminized propellant solid rocket motors (SRMs). Aluminized propellant SRMs constitute the most eroding environment when compared to non-aluminized SRMs and liquid SRMs. Both theoretically and experimentally, it has been shown that the reaction initiation temperature of TaC is 1000oC higher than that of carbon and 400oC higher than HfC, thus making it a prime candidate for thrusters used in the next generation of higher performance, hypersonic missile defense systems. Moreover, it has been demonstrated that the erosion rate of TaC is significantly less that HfC and carbon under comparable conditions. Of all the refractory metal carbide systems, TaC holds the most promise for the unique conditions of aluminized propellant SRMs.

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

US Flag An Official Website of the United States Government