Abstract
High temperature composite materials in combination with advanced design and manufacturing concepts are becoming more and more important for space transportation systems like hypersonic flight and reusable reentry vehicles. In order to meet the challenging demands for thermostructural 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 define an Integrity Control Methodology for thermostructural elements made from these high temperature composite materials
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