探月工程三期月地高速再入返回飞行器防热系统设计与验证  

Design and verification of the TPS of the circumlunar free return and reentry flight vehicle for the 3rd phase of Chinese lunar exploration program

作　　者：董彦芝[1] 刘峰[1] 杨昌昊[1] 张高[1] 赵建设[2] 罗晓光[3] 欧东斌[3] 梁馨[2] 郭梅梅[2] 马彬[1] 逯运通[1] 

机构地区：[1]中国空间技术研究院总体设计部,北京100094 [2]航天材料及工艺研究所,北京100076 [3]中国航天空气动力技术研究院,北京100074

出　　处：《中国科学：技术科学》2015年第2期151-159,共9页Scientia Sinica(Technologica)

基　　金：国家中长期科技发展规划重大专项资助项目

摘　　要：本文针对月地高速再入返回的高焓、二次大气层再入、高热流密度峰值与长加热时间耦合的气动加热环境特点,提出了飞行器防热系统设计方案,研制了七种新型碳硅复合烧蚀防热材料,建立了防热系统分析模型,并完成了地面试验验证.经对飞行试验数据的详细分析,结果表明防热系统的实际性能与设计预期一致.The thermal protection system （TPS） of the high speed reentry vehicle is confronted with sever challenges, for the reentry environment has the characteristics such as high enthapy, twice rentry, the coupling of high heat flux and long time heating. This paper brings forward a design of the TPS, develops a new series of carbon-silicon based composite ablative materials, and establishes a simulation method of the entire ablation rate computed by carbon and silicon volume weighted, and an ablation test method for simulation of the whole reentry process through multiple steps and suspension condition. Based on the detailed analysis of test data, the TPS ensured the success of the task.

关 键 词：月地返回 烧蚀 防热系统 设计 验证 

分 类 号：V445.1[航空宇航科学与技术—飞行器设计]