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Low-Cost, Ultrahigh Temperature Zero-Erosion Ceramic Matrix Composite for SM-3 TDACS Pintles and Throats

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: W9113M-09-C-0129
Agency Tracking Number: B083-007-0638
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: MDA08-007
Solicitation Number: 2008.3
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
 Timothy Stewart
 Research Engineer
 (818) 899-0236
Business Contact
 Craig Ward
Title: Engineering Administrative Manager
Phone: (818) 899-0236
Research Institution

Future performance goals for ballistic missile defense systems necessitate the development of zero-erosion throat materials for boost and tactical solid rocket motors. Increasing demands imposed by advanced solid propellants used in systems such as throttling diverter and attitude control systems (TDACS) require zero-erosion materials for pintles and throats capable of surviving an ultrahigh temperature thermal, chemical, and mechanical environment. Use of robust materials with broad operational capability leads to simpler and lower cost designs. With application and design support provided by Aerojet and thermomechanical modeling and erosion prediction provided by Materials Research & Design, Ultramet will develop ceramic matrix composite materials using its low cost melt infiltration process for a TDACS component that can be used with aluminized and nonaluminized propellants. Tantalum carbide is the current material of choice for use with aluminized propellants, whereas materials including hafnium carbide, zirconium carbide, tungsten, and rhenium have been demonstrated with lower temperature, nonaluminized propellant systems. Ultramet will develop a high-toughness, fiber-reinforced tantalum-hafnium carbide ceramic alloy matrix composite for use with both propellant types using a low cost melt infiltration manufacturing process.

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

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