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.
