典型部件疏导式热防护试验技术研究  

Investigation on testing technology of typical component dredging thermal protection

作　　者：朱晓军 李锋[1] 欧东斌[1] 陈连忠[1] 周凯 ZHU Xiao-jun;LI Feng;OU Dong-bin;CHEN Lian-zhong;ZHOU Kai(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《实验力学》2020年第4期681-687,共7页Journal of Experimental Mechanics

摘　　要：疏导式热防护是一种新型非烧蚀热防护技术,对未来高超声速飞行器发展具有十分重要的意义。为了验证疏导式热防护原理的有效性、合理性和优越性,并考核疏导式热防护技术实现途径的可行性,在传统热防护试验模拟技术的基础上,开发了大功率长寿命电弧加热和对流辐射耦合加热等试验技术,并考核了高温热管球柱疏导模型的疏导效果。电弧风洞试验结果表明:在高温热管球柱疏导模型防热层装入快速导热元件后,可以有效降低驻点高热流区的表面温度,提升低温区的表面温度,从而降低整体温差基本实现非烧蚀。由此可知该试验方法能够满足典型部件疏导式热防护机理探索及性能考核研究的需要。Dredging thermal protection is a new concept of non-ablative thermal protection, which is of great significance to the future development of hypersonic vehicle. In order to verify the validity, rationality and superiority of the dredging thermal protection principle and to assess the feasibility of the dredging thermal protection technology, the experimental conditions and testing methods of dredging thermal protection are established based on the traditional simulation technology and testing technology of thermal protection tests, and the dredging effect of high-temperature heat pipe sphere column dredging model is examined. The results show that: as the rapid thermal conduction element is installed into the heat-resistant inner layer, the surface temperature of stagnation point high heat flow area can be effectively reduced, the surface temperature of low-temperature region of the cylinder surface can be increased. So the overall temperature difference is reduced, resulting in the non ablation. It can be concluded that the testing technology can meet the exploration of typical component dredging thermal protection mechanism and the research of performance evaluation.

关 键 词：疏导式热防护 烧蚀 试验条件 防热层 热流 

分 类 号：V411.7[航空宇航科学与技术—航空宇航推进理论与工程]