摘要
可重复使用运载器的防热瓦故障会使航天器的局部结构产生热源,并在结构中形成温度场。应用热源温度场迭加法的解函数,解得结构温度历程,然后据此温度的变化率趋势判断出热源位置,在此基础上依据多点测量值构造出辨识参数用于热强度识别,通过对一薄壁结构模型算例的计算仿真,证明了本文所提方法的有效性。论文工作为进一步开展热源诊断技术研究,提供了可资工程实践应用的数值算法体系以及有益的数值计算结论。
The malfunction of thermal protection system on reusable launch vehicle will generate a heat source on the part of vehicle. The heat souse will lead to a temperature field. The change of structural temperature can be calculated by the heatsource method, and the heat source position can be found out. Based upon this approach, a parameter which can be used to evahuate the intensity of the heat source can be obtained hy using measured values on certain points. By analyzing a sheet structure model, the methods are testified effective. The methods and the numerical calculations of this paper can be applied to further astronautical heat-source researches.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2006年第1期41-44,共4页
Journal of Astronautics
关键词
可重复使用运载器
热源法
热源定位
热强度识别
Reusable launch vehicle
lleat-source method
Thermal source
Heat-source position
Heat-source intensity
