Application study of a correction method for a spacecraft thermal model with a Monte-Carlo hybrid algorithm

作     者：CHENG WenLong LIU Na LI Zhi ZHONG Qi WANG AiMing ZHANG ZhiMin HE ZongBo 

作者机构：Department of Thermal Science and Energy Engineering University of Science and Technology of China Hefei 230027 China Research and Development Center China Academy of Space Technology Beijing 100094 China Beijing Institute of Spacecraft System Engineering Chinese Academy of Space Technology Beijing 100094 China 

出 版 物：《Chinese Science Bulletin》 (Chin. Sci. Bull.)

年 卷 期：2011年第56卷第13期

页      面：1407-1412页

核心收录：

学科分类：080703[工学-动力机械及工程] 082502[工学-航空宇航推进理论与工程] 08[工学] 0807[工学-动力工程及工程热物理] 0825[工学-航空宇航科学与技术] 

主　　题：校正方法 混合算法 热模型 蒙特卡洛 航天器 敏感性分析 应用 模型修正 

摘      要：The correction of a thermal model for a thermally controlled satellite in ground test conditions is studied using a Monte Carlo hybrid ***,the global and local parameters are summarized according to sensitivity analyses on uncertain parameters,and then the model correction is treated as a parameter optimization problem to be solved with a hybrid ***,the correction of the thermal model is completed using a layered correction *** sensitivity analysis showed that the effective emissivities across the multi-layer insulation (MLI) and the emissivities of the thermal control coating are global parameters,while the contact heat transfer coefficients are local *** correction,the deviations between the calculated and test values were all within ± 3 ℃.The final results prove that the method in this study is superior to traditional methods and satisfies the requirements for thermal model correction.