一种热平衡等温机制的新型热防护及相关技术  

A New Thermal Protection Technology Based on Heat-Balance Isothermal Mechanism

作　　者：李锋[1] 艾邦成[1] 姜贵庆[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《宇航学报》2013年第12期1644-1650,共7页Journal of Astronautics

基　　金：国家自然科学基金重大研究计划资助项目(90505015)

摘　　要：给出了一种适用于高超声速飞行器热防护的新概念——疏导式热防护,其基本理论是利用热平衡等温机制,使防热层趋于一等温体,实现热负载平衡。针对这一概念,进行了较为系统的研究,包括原理、分析方法、实现疏导式热防护的关键技术。研究结果表明,疏导式热防护技术可有效地减少高热流区的温度和热应力,是一种有效的非烧蚀热防护技术。This paper provides a new thermal protection method, heat-balance thermal protection, which is adaptable for thermal protection of hypersonic vehicle. Its principal theory is thermal equilibrium isothermal mechanism. By using heat-balance thermal protection the temperature of thermal protection layer turns into equality. Systematic research has been done directly about heat-balance thermal protection, including principle, analytical methods of the theory and key techniques. It is shown that the temperature and heat stress can be cut down effectively by the heat-balance thermal protection. The heat-balance thermal protection is effective in non-ablating thermal protection of hypersonic vehicle.

关 键 词：疏导式热防护 非烧蚀热防护 高超声速飞行器 

分 类 号：V414.9[航空宇航科学与技术—航空宇航推进理论与工程]