空间光谱成像仪热设计参数的灵敏度

针对空间光学遥感器在轨运行期间其热物理属性的实际参数与热设计参数之间存在一定的偏差,从而影响整机热设计的问题,本文基于系统灵敏度理论,对空间光学遥感器的热设计进行了分析,并建立了在轨条件下的热平衡方程组.通过分析热平衡方程组的设计变量,总结出影响整机温度分布的热设计参数.以某空间光谱成像仪热设计为例,分析了上述影响整机温度分布的设计参数的灵敏度.灵敏度分析结果表明:整机平均温度对太阳吸收系数的灵敏度几乎为零；对红外半球发射率的灵敏度为2.2～14.55℃；对内部热源的灵敏度为1.8～2℃/W；对导热率的灵敏度为2.25×10-3～4.39×10-2 m℃2/W:对接触导热系数的灵敏度为0～1.1×10-3 m2℃2/W.试验验证结果表明,基于灵敏度分析结果的热控设计方案有效且可行.

Sensitivity of thermal design parameters for space spectral imaging apparatus

As the deviation between the real parameters and the thermal design parameters of a space spectral imaging apparatus in orbit effects on the design accuracy of complete appliances,this paper analyzes the thermal design based on the system sensitivity theory,and establishes the heat balance equations in orbit.Under the design variable analysis of the heat balance equations,thermal design parameters effecting the temperature distributions of complete appliances are given.As an example,the sensitivity of thermal design parameters mentioned above is analyzed for the space spectral imaging apparatus.The analytical results show that the sensitivity of solar absorption coefficient to the mean temperature is equal to zero,and the sensitivities of emissivity,inner heat source,thermal conductivity,and contact thermal conductivity to the mean temperature are 2.2-14.55 ℃,1.8-2 ℃/W,2.25×10-3-4.39×10-2 m℃2/W and 0-1.1×10-3 m2℃2/W,respectively.Test results prove that the sensitivity analysis based proposed thermal design scheme is effective and feasible proved by thermal test results.