中国空间科学技术

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防热层表面突起物及内部结构的温度场分析

唐功跃,吴国庭   

  1. 北京空间飞行器总体设计部!北京100086,北京空间飞行器总体设计部!北京100086
  • 发布日期:2000-02-25

Analysis of the Temperature of Protuberance on the Surface of Thermal Layer and Inner Complex Structure

Tang Gongyue Wu Guoting (Beijing Institute of Spacecraft System Engineering,Beijing 100086)   

  • Published:2000-02-25

摘要： 阐述了高超声速和超声速流动条件下， 返回式航天器防热层表面的突起物所引起局部过热问题； 分析了突起物对其周围防热层表面的局部热环境的影响及其本身表面所处的热环境。以ＡＲＩＥＳ前后处理软件和ＮＡＳＴＲＡＮ 分析程序为工具， 分别计算了在试验热环境条件下及轨道热环境条件下突起物上的温度分布， 并与试验结果进行对比， 计算结果与试验结果吻合得相当好， 从而证明了对防热层表面突起物所引起的局部过热问题所采用的分析方法和途径的合理性与先进性。同时也证明了对突起物周围及其本身的热流密度的工程简化是合理的。

关键词: 热环境, 突出物, 航天器, 返回, 分析

Abstract: Local overheat causing by the protuberance on the surface of reentry spacecraft in the condition of hypersonic and supersonic flow is discussed briefly.Using the pre processing and after processing software ARIES and calculation program NASTRAN,the distributions of temperature on the protuberance under the test thermal environment and trajectory thermal environment condition are calculated respectively.Then the result of calculation are compared with the result of the test and they are very identical,which is proved that the way treating local overheat causing by the protuberance is practicable and advanced.