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CMC for Hot Structures and Control Surfaces of Future Launchers

机译：CMC用于未来发射器的热结构和控制表面

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Test Results on structural components made of "low cost" ceramic matrix composites (CMC) showed that this material can be applied on a wide range of thermal protection systems (TPS) including hot structures and even control surfaces of future reusable space transportation vehicles (RLV). CMC panels and hot structures like leading edges, nose cap or fins require lightweight structures which are resistant to high temperatures and which can be reused for a certain number of flights with a minimum effort of servicing. But as recent design and analyses studies showed, CMC delivers also a suitable material for control surfaces of a RLV with the promising advantage of multi-mission application without a large refurbishment effort after flight. Daimler-Benz Aerospace (Dasa) has developed a CMC manufacturing process that allows the fabrication of complex and large integral hot structures in carbon-silicon carbide (C/SiC) such as nose caps, panels and leading edges. The Polymer Pyrolysis Process applied is more cost efficient and requires only a minimum fabrication period compared to other CMC fabrication methods.rnThis paper reports about present work at Dasa with respect to design, analysis, manufacturing and test of large integral hot CMC structures for future launchers.rnTwo examples are presented: Firtstly the development of a large CMC panel system and secondly the design concept of C/SiC elevator of the current X-33 demonstrator.
机译：由“低成本”陶瓷基复合材料（CMC）制成的结构部件的测试结果表明，该材料可用于多种热保护系统（TPS），包括热结构，甚至是未来可重复使用的太空运输工具（RLV）的控制表面）。 CMC面板和较热的结构（例如前缘，鼻罩或散热片）需要轻巧的结构，这些结构必须能耐高温，并且可以在不花费大量维护工作的情况下重复使用一定的飞行次数。但是，正如最近的设计和分析研究表明，CMC还为RLV的控制面提供了合适的材料，具有多任务应用的有希望的优势，而无需在飞行后进行大量整修。戴姆勒-奔驰航空航天公司（Dasa）开发了一种CMC制造工艺，可以在碳-碳化硅（C / SiC）中制造复杂而大型的整体热结构，例如鼻盖，面板和前缘。与其他CMC制造方法相比，所应用的聚合物热解工艺更具成本效益，并且仅需要最短的制造时间。rn本文报告了Dasa当前在为大型发射器设计，分析，制造和测试大型整体热CMC结构方面的工作。介绍了两个示例：首先是大型CMC面板系统的开发，其次是当前X-33演示器的C / SiC电梯的设计概念。

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