低轨道低能量空间光学遥感器热设计

Thermal design of a low-energy space optical remote sensor in LEO

为了保证空间光学遥感器所需温度条件,以被动热控为主、主动热控为辅的原则对其进行了热设计。分析了其轨道环境特点,计算了遥感器轨道寿命内原子氧通量,选择了一种玻纤增强聚四氟乙烯复合膜(β布)作为多层隔热组件面膜。根据其工作模式和外热流特点,确定了三个极端工况,以对日低温工况热设计为主要对象。热试验结果表明:热设计满足遥感器光学系统温度指标,热控方案可行。热设计方法对其它低轨道、低能量航天器热设计具有一定的指导和借鉴作用。

In order to maintain the temperature of a space optical remote sensor in orbit,a thermal control system is designed.The thermal control strategy is primary passive thermal control and assistant active thermal control.A simple simulation of the complicated orbital environment is made,and beta cloth is chosen to prevent AO.Three extreme conditions are confirmed based on its work patterns and heat fluxes.Thermal control design is primary concentrated on the sun-oriented work pattern in low temperature condition.The result of thermal balance test show that the thermal control system meets the requirement of mission,and the thermal design is feasible.Some guidance and reference are gotten from the research jobs for other analogous spacecraft.