星载遥感器的精密热控设计

Precise thermal design for a satellite-based sensor

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.