太阳同步轨道卫星热控分系统分析及优化  

Analysis and Optimization of SSO Satellite Thermal Control Subsystem

作　　者：吴文瑞[1] 黄海[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航天器工程》2012年第2期44-49,共6页Spacecraft Engineering

摘　　要：定义地心日照轨道坐标系,并在此坐标系下简化卫星与地球相对位置的复杂计算,以及卫星轨道外热流分析过程中相关角度的计算,使轨道外热流的分析仿真更加快速、简洁。以正六棱柱形卫星为例,建立热网络模型,对其表面在一圈轨道内所受的轨道外热流进行仿真,并结合仿真结果计算进出地影区时卫星内部的温度。在此基础上,建立以热控分系统多层隔热材料质量最小化为目标的优化问题;在满足高低温工况卫星内部温度在-10～+35℃范围内的约束下,对多层隔热材料厚度和散热窗大小进行了优化。An Earth-original sunshine orbital coordinate system is defined.In this coordinate system,the complex computation of the relative position between satellite and the Earth can be bypassed,so the calculations of related angles in satellite orbital heat flux analysis become simple,and the satellite thermal analysis can be quickly accomplished.A thermal network model of a six-prism shaped satellite is built.The orbital heat flux on the surfaces of the satellite is simulated and applied in the model to obtain the satellite internal temperature at the start and end of eclipse period.Based on the model,an optimization of thermal control system to minimize multi-layer insulations mass in limitation of the satellite internal temperatures between-10℃ and ＋35℃ in both cold and hot cases is established.Multi-layer insulations thickness and radiator window area are optimized.

关 键 词：太阳同步轨道卫星 热控 轨道外热流 优化 

分 类 号：V444.3[航空宇航科学与技术—飞行器设计]