摘要
载人飞船返回舱的烧蚀热防护技术研究和试验表明，碳化烧蚀材料是再入飞行器最有效的热防护层。对典型的碳化烧蚀体的热性能的预测分析模型和计算方法作了阐述。数值计算结果分别与电弧风洞试验和阿波罗的飞行验证试验作了比较，结果符合得很好。
This paper presents the ablative thermal protection techniques of re-entry module of manned spacecraft. Investigations and experiments indicate that charring ablators provide the most efficient thermal protection shield for the re-entry vehicles. An analytical model and calculated method for predicting the thermal performance of typical charring ablators have been described. Good agreement are obtained between the numerical results with arc wind tunnel tests and flight verification testing results.
关键词
载人飞船
返回舱
热防护
碳化烧蚀材料
manned spacecraft
re-entry module
thermal protection
charring ablator
aerothermodynamics
