星载遥感器的精密热控设计  

Precise thermal design for a satellite-based sensor

作　　者：王永宪[1] 王志宏[1] 高明辉[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

出　　处：《长春工业大学学报》2011年第2期115-120,共6页Journal of Changchun University of Technology

基　　金：国家863计划基金资助项目(863-2-5-1-13B)

摘　　要：针对某型星载遥感器光学系统和支撑结构几何尺寸及外形尺寸大、通光口径大、轨道外热流变化大、易产生较大的轴向和径向温度梯度等特点,采用热隔离、热疏导及温度补偿等手段,针对该星载遥感器进行了热控设计。通过建立遥感器结构有限元模型,利用有限元分析软件I-DEAS进行了轨道外热流和高、低温稳态工况及瞬态工况仿真分析,结合热平衡试验验证热设计的有效性和正确性。结果表明,热控设计方案合理、可行,且满足设计要求。According to the features of large geometry structure,large aperture,big change of heat flow at external orbit,big axial and radial temperature gradient in a certain type of satellite-based sensor,we make a precise thermal design for the sensor with some thermal compensation,heat isolation and heat grooming.Here the finite element model is established for the sensor structure,and the simulation of heat flow,stable high-low temperature condition and transient conditions are carried with I-DEAS software.The thermal balance tests verify the effectiveness and accuracy of thermal design and results show that the design meets the requirements.

关 键 词：星载遥感器 热设计 热平衡试验 

分 类 号：V445.8[航空宇航科学与技术—飞行器设计]