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SiC Matrix Composite Rocket Thrust Chamber with Integrated SiC Foam Propellant Diffuser/Injector

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: DASG6003P0012
Agency Tracking Number: 022-0788
Amount: $70,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: N/A
Solicitation Number: N/A
Timeline
Solicitation Year: N/A
Award Year: 2002
Award Start Date (Proposal Award Date): N/A
Award End Date (Contract End Date): N/A
Small Business Information
18411 Gothard Street, Unit B
Huntington Beach, CA 92648
United States
DUNS: 798073391
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Wayne Steffier
 President and Technical D
 (714) 375-4085
 wsteffier@htcomposites.com
Business Contact
 Wayne Steffier
Title: President and Technical D
Phone: (714) 375-4085
Email: wsteffier@htcomposites.com
Research Institution
N/A
Abstract

"Liquid rocket engine systems currently in development or being considered for future development will require a variety of subsystems for axial, reaction control, target intercept, and auxiliary propulsion. Recent developments in fiber-reinforced ceramicmatrix composites and porous reticulated ceramics offer promise to increase performance, manufacturability and cost over currently available refractory metal propulsion components. The objective of this Phase I program is to demonstrate the feasibility ofproducing a lightweight SiC matrix composite rocket propulsion thrust chamber incorporating a fully integrated reticulated SiC foam propellant diffuser/injector. A previously developed intraply fiber preform hybridization technique will be utilized for thechamber to mitigate process-induced matrix microcracking and gaseous permeability inherent in C/SiC composites. Optimized hybrid fiber preforms of T300 and Hi-Nicalon will be braided over geometrically contoured mandrels and densified with a SiC matrixproduced by chemical vapor infiltration (CVI). Following partial consolidation of the preform, a reticulated foam diffuser/injector element will be inserted into the forward end of the combustion chamber and CVI-SiC integrated with the composite thrustchamber during final matrix densification. Reticulated open-cell SiC foam specimens of various porosities and densities will be produced and experimentally evaluated to determine their res

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

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