INTEGRITY CONTROL FOR HIGH-TEMPERATURE STRUCTURAL APPLICATIONS

High temperature composite materials in combination with advanced desi gn and manufacturing concepts are becoming more and more important for space transportation systems like hypersonic flight and reusable reen try vehicles. In order to meet the challenging demands for thermostruc tural applications Carbon/Carbon and Ceramic Matrix Composites are the most promising materials with respect to weight, stiffness, strength and heat resistance. An ESA supported study has been undertaken to def ine an Integrity Control Methodology for thermostructural elements mad e from these high temperature composite materials.