高超声速飞行器一体化防热与热控设计方法

王浚; 王佩广

高超声速飞行器一体化防热与热控设计方法

王浚,
王佩广

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

中图分类号: V 245
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出版历程
- 收稿日期: 2006-05-30
- 网络出版日期: 2006-10-31

Integrated thermal protection and control system design methodology for hypersonic vehicles

School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 围绕高超声速飞行器所遭遇的"热障"问题,阐述了防热与热控系统一体化设计的思想,指出将机身结构、防热与热控系统、推进系统耦合在一起进行一体化设计是解决"热障"问题的有效途径,并提出了不同任务需求的高超声速飞行器防热与热控系统方案思路.介绍了部分防热材料的性能,指出了在设计中选择防热材料的原则.对防热与热控系统的优化方法进行了探讨,指出了防热与热控系统一体化设计中涉及的关键技术,举例说明了防热与热控一体化设计的基本流程.
- 高超声速流动 /
- 飞行器 /
- 防热 /
- 热控
Abstract: To solve the problem of heat barrier which a hypersonic vehicle would encounter during its mission,the idea that thermal protection system design should be integrated with thermal control system design was described. It was concluded that the airframe structure design should be coupled with design of thermal protection system, thermal control system and propulsion system. It was regarded as an effective solution to heat barrier problem. Considerations of thermal protection and control concepts for hypersonic vehicles which had different missions were put forward. Properties of some thermal protection materials were introduced and principles to select thermal protection materials in a design were addressed. Optimization of integrated thermal protection and thermal control system was discussed. Key technologies concerning the integrated design methodology were put forward. An example was put forth to illustrate the essential approach of the integrated design methodology.
- hypersonic flow /
- vehicle /
- thermal protection /
- thermal control

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参考文献(1)

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