INTEGRITY CONTROL FOR HIGH-TEMPERATURE STRUCTURAL APPLICATIONS

被引：0
|
作者：
BECKER, W
KERFIN, W
PRADIER, A
TRABANDT, U
VOGEL, WD
机构：
[1] DORNIER LUFTFAHRT GMBH,FRIEDRICHSHAFEN,GERMANY
[2] EUROPEAN SPACE AGCY,EUROPEAN SPACE RES & TECHNOL CTR,F-75738 PARIS,FRANCE
来源：
JOURNAL DE PHYSIQUE IV | 1993年 / 3卷 / C7期
关键词：
D O I：
10.1051/jp4:19937305
中图分类号：
O4 [物理学];
学科分类号：
0702 ;
摘要：
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.
引用
收藏
页码：1911 / 1916
页数：6
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