航天器转动轴遮热罩设计及仿真  

Design and Simulation for Thermal Shield Installed on Rotating Shaft of Spacecraft

作　　者：杨化彬 吴清文[1] 杨献伟[1] 黄勇[1] 

机构地区：[1]中国科学院长春光学精密机械与物理研究所,吉林长春130033 [2]中国科学院大学,北京100049

出　　处：《计算机仿真》2014年第1期58-63,80,共7页Computer Simulation

摘　　要：在航天器转动遮热罩优化设计问题,为减少航天器转动轴处的能量散失,采用安装遮热罩和包覆多层隔热组件的方法,找到影响转动轴能量散失的主要因索,确定可应用于工程实际的遮热罩设计方案和多层包覆方式的合理性。首先给出遮热罩的基本结构并分析影响转动轴系统能量散失的主要参数。其次运用I-DEAS/TMG进行有限元仿真,得到转动轴系统能量散失与各变量之间的变化规律。最后依据极紫外成像仪俯仰轴上安装和未安装遮热罩的两种应用方案开展热平衡试验。试验和计算结果表明,安装遮热罩并包覆多层隔热组件后,俯仰轴能量散失比无热控措施时减少了53.6%。设计合理的遮热罩并包覆多层隔热组件,既保证转动机构的正常工作,也可有效地减少转动轴处能量的散失。In order to decrease heat loss of the rotating shaft, a valid thermal shield was installed and multi-layer insulation （MLI） was wrapped on the rotating shaft of the spacecraft which can decrease energy loss effectively. First- ly, the structure of thermal shield and its parameters, which affect the energy lost from the rotating shaft, were stud- ied. Secondly, the finite element simulate models were built with I-DEAS/TMG, the energy loss was calculated and the disciplinarian was discovered between energy lost and the parameters of the shaft subassembly. Thirdly, two cases of thermal balance experiment for the pitch shafts of an extreme ultraviolet imager were launched. The shafts were in- stalled with thermal shields in the one case of experiment and uninstalled in another case. It is shown that the total lost energy of the pitch shaft with thermal shields and MLI wrapped can decrease about 53.6%. The thermal shield with optimized parameters and MLI wrapped can decrease energy loss of the rotating shaft and keep it run well in the space.

关 键 词：遮热罩 转动轴 热设计仿真 有限元分析 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]