火星进入器气动热环境模拟及热防护试验综述  

Review of aerothermal environmental simulations and thermal protection tests for Mars entry vehicles

作　　者：欧东斌[1] 曾徽 张智[1] 杨国铭[1] 文鹏 OU Dongbin;ZENG Hui;ZHANG Zhi;YANG Guoming;WEN Peng(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：《航天器环境工程》2022年第5期522-532,共11页Spacecraft Environment Engineering

摘　　要：文章简述典型火星进入器所面临的气动热环境,阐明在火星大气CO_(2)介质下进行试验的重大需求以及建立火星热环境模拟及热防护试验方法的必要性;并对国内外进行的相关火星进入器热防护工程性和研究性试验进行综述,指出研究空气和CO_(2)介质下的电弧加热器运行特性将对火星热防护试验提供必要的支撑,CO_(2)介质下防热材料催化特性研究和先进测试技术(如TALIF、OES、HSC等)是未来发展的方向。In this paper,the aerodynamic thermal environment of a typical Mars entry vehicle is analyzed,and the major requirements for conducting tests in the Martian atmosphere are highlighted,as well as the necessity of establishing a thermal environment simulation and thermal protection test method for Mars probes.The thermal protection tests for the Mars entry vehicle performed at home and abroad are reviewed.The importance of the ground thermal protection tests is shown,as well as the importance of studying the operation characteristics of the arc heaters in air and CO_(2),to provide a necessary support for Mars thermal protection tests.It is suggested that the basic researches of the catalytic properties of the thermal protection materials in CO_(2) and some advanced testing techniques(such as TALIF,OES,HSC,etc.)are the directions of the future development.

关 键 词：火星进入器 气动热 热防护 电弧风洞 

分 类 号：P185.3[天文地球—天文学] V416.5[航空宇航科学与技术—航空宇航推进理论与工程]