COMPOSITE THERMAL PROTECTION MATERIAL

HEAT SHIELDS FOR EARTH ORBITING, REENTRY VEHICLES REQUIRE A LOW WEIGHT, DURABLE THERMAL PROTECTION SYSTEM THAT CAN OPERATE AT HIGH TEMPERRATURES IN AN OXIDIZING ATMOSPHERE. THE OBJECTIVE OF THIS RESEARCH PROJECT IS TO INVESTIGATE A NEW CERAMIC MATRIX COMPOSITE MATERIAL THAT MAY MEET THOSE REQUIREMENTS. THE MATERIAL IS MADE BY INFILTRATING SILICON CARBIDE IN THE GAS PHASE INTO A CERAMIC REINFORCEMENT PERFORM. THE PHASE I PROGRAM INCLUDES THE FABRICATION OF A NUMBER OF TEST SAMPLES AND THE EAMINATION OF MECHANICAL AND THERMAL PROPERTIES. THE RESULTS SHOULD DEMONSTRATE THE SHOULD DEMONSTRATE THE FEASABILITY OF THE MATERIAL APPROACH AND SUGGEST SPECIFIC APPLICATION AREAS.