NUMERICAL INVESTIGATION OF THE THERMAL BENEFIT OF USING A HIGH THERMAL CONDUCTIVITY CMC FOR THE LEADING EDGE OF HYPERSONIC VEHICLES

Abstract

During atmospheric re-entry high thermal loads are generated on the surface of the entry vehicle with peak loads in the stagnation area. Typical entry vehicles have a blunt shape avoiding sharp tips or leading edges. Recent developments for vehicles in the hypersonic flight regime have concentrated on sharp designs to reduce drag and increase lift. This creates challenges with regard to the materials. Ceramic matrix composites are materials with good high-temperature properties. However, the thermal loads on sharp structures can exceed even their capabilities. One way to relieve the problem could be to use a material with a very high thermal conductivity to distribute the heat load over a wider area and thereby reducing the temperature to an acceptable level. In this work the potential of a new type of CMC material based on the use of carbon pitch fibers was investigated via numerical simulation.