高超飞行器尖前缘材料发展及相关气动热试验

宇航材料工艺 , 2012, 42(5): 1-4.

1.中国航天空气动力技术研究院,北京 100074

2.中国航天空气动力技术研究院,北京 100074

3.中国航天空气动力技术研究院,北京 100074

4.中国航天空气动力技术研究院,北京 100074

Development and Aero-Heating Tests of Sharp Leading Edge in Hypersonic Vehicles

回顾了高超声速飞行器建立的几种热防护系统,简要分析了吸气式发动机高超声速飞行器尖前缘的热环境特点及相应防热材料发展的趋势,介绍了近20年来美国在吸气式发动机高超声速飞行器相关研究中所开展的Hytech、X43A及NGLT等三个研究项目,重点介绍这些研究项目中尖前缘材料的发展以及进行的气动热试验.

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[2]	Walker S P .Sharp refractory composite leading edges on hypersonic vehicles[R].American Institute of Aeronautics and Astronautics,2003.
[3]	Glass D E .Ceramic matrix composite (CMC) thermal protection systems (TPS) and hot structures for hypersonic vehicles[R].American Institute of Aeronautics and Astronautics,2008.
[4]	Moses P L .X-43C plans and status[R].American Institute of Aeronautics and Astronautics,2003.
[5]	Dialing R B .Progress in materials and structures evaluation for the HyTech program[R].American Institute of Aeronautics and Astronautics,1998.
[6]	Bruce W E;Horn D D .Arc heater development at AEDC[R].American Institute of Aeronautics and Astronautics,1994.
[7]	Ohlhorst C W.Development of X-43A mch 10 leading edges[A].Fukuoka,Japan,2005
[8]	Max E L;Jeremiah J M .Boundary layer transition protuberance tests at NASA JSC arc-jet facility[R].American Institute of Aeronautics and Astronautics,2010.
[9]	Ohlhorst C W .Arc jet results on candidate high temperature coatings for NASA' S NGLT refractory composite leading edge task[NASA 20040040337][R].,2004.

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