Glenn Research Center 
Marshall Space Flight Center
1993 Phase II

Oxidation Resistant Rocket Thrusters for High Performance Propellants

Ceramic Composites, Inc.

Millersville, MD

Chemical vapor infiltration process to fabricate low-cost, functionally graded ceramic matrix composites

• Developed rapid chemical vapor infiltration (CVI) process that leads to reduction in processing time and higher matrix densities. Fabrication times reduced by a factor of seven with up to a ten fold reduction in the fabrication cost
• Rapid CVI leads to directional matrix growth and to functional grading through the fiber preform. Lightweight C(f)/C graded Ceramic Matrix Composites (CMCs) were fabricated which behave like Re or HfC, with density of ~ 3g/cm³
• Thrust cells tests with O₂&H₂propellants at operating conditions for 30 seconds showed no erosion at the throat
• Tested components in air at 4300F for 6 minutes. Excellent thermal stability was shown

• Patent applied for February 2000-Docket Number 1388
• Received $140K Phase III from MSFC
• Collaborating with commercial partners to design and test propulsion components for Divert and Attitude Control, Scramjet and Satellite station keeping/orbit transfer systems

• CMC technology developed under the NASA Glenn SBIR is being modified and evaluated as hypersonic scramjet propulsion components under a DARPA Phase 2 SBIR
• This new family of lightweight materials will provide oxidation and erosion resistance for next generation NASA and DoD propulsion applications
• CMC thruster technology developed under the NASA Glenn SBIR is being extended to the development of an integrated ceramic injector-CMC thruster for satellite propulsion being funded under an AF Phase 2 SBIR

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