摘要
对各种防热、热控机理基本规律进行了梳理和研究,认为要进一步提高系统性能,需要进行结构、防热、热控一体化设计。基于这种设计思想,提出了一种将航天器防热、热控和结构相结合的"统一热管理的疏导式防热系统",在传统防热机制的基础上,加入原先主要用于热控的各种热传输机制,进行防热、热控和结构等子系统间热的统一管理。应用这种系统,可提高防热效果,减轻飞行器的结构重量,减轻高热流区材料与结构的耐温负担,有可能实现长时间、超高速大气层机动飞行器的前缘尖化,还可使整个防热层趋于等温,易于热控处理,减小结构热应力。文章还分析了疏导式防热系统的应用前景,并针对几种典型的航天器(尖鼻锥和尖翼前缘的高超声速巡航飞行器、返回式航天器和载人飞船)提出若干适用的疏导式防热系统的方案设想。
The analysis and research on basic principle and rule of the thermal-protection system （TPS） and thermal-control system （TCS） are made in the paper. It is considered that further performance improvement of the TPS could be achieved by a kind of leading TPS which is the combination of TPS and TCS of spacecraft and the unified heat management within the systems of thermal-protection, thermal control and structure.
The application of the leading TPS could lighten the total mass of the spacecraft, reduce the local temperature, and therefore make it possible to realize the tine nose cap and wing leading edge of hypersonic aircraft.
The application of the leading TPS is analyzed and some concepts of the TPS for returnable spacecraft, manned spacecraft and hypersonic aircraft are proposed in the paper.
出处
《航天器工程》
2009年第4期13-19,共7页
Spacecraft Engineering
基金
中国空间技术研究院自主研发项目
关键词
航天器
防热
热控制
热疏导
热管理
spacecraft
thermal-protection
thermal-control
leading thermal-protection
heat management
