开普勒轨道航天器凸表面外热流通用计算方法研究  

Study on General Calculation Method for External Heat Fluxon of Convex Surfaces on Spacecraft in Keplerian Orbit

作　　者：易桦[1] 黄兴 周宇鹏[1] YI Hua;HUANG Xing;ZHOU Yupeng(National Key Laboratory of Spacecraft Thermal Control,Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部航天器热控全国重点实验室,北京100094

出　　处：《航天器工程》2024年第5期59-64,共6页Spacecraft Engineering

摘　　要：空间外热流对航天器热设计有重要影响,因此必须开展外热流分析,以确定热设计方案和热分析极端工况。使用开普勒轨道航天器凸表面外热流通用计算方法,将其应用于常用的平面、圆柱面、圆锥面和球面,采用解析法或数值积分法计算太阳直射热流,采用数值积分或随机法求解行星红外和行星反照热流,能有效简化计算过程。根据此方法分析了上述常用凸表面在常用姿态(+Z对地,-Z对日,偏航和复杂机动)的瞬态外热流结果。此外,以复杂机动姿态下的瞬态外热流分析为例,将基于此方法的圆柱面、圆锥面和球面的瞬态外热流分析结果与热分析软件计算结果进行了对比,对比结果表明计算结果相差不超过6 W/m^(2),相对误差不超过5%,充分说明了此方法的准确性。The external heat flux has asignificant impact on the thermal design of spacecraft,therefore it is necessary to conduct the external heat flux analysis to determine the thermal design scheme and external thermal analysis.A general calculation method for external heat flux of common convex surfaces(such as plane,cylinder,cone and sphere)on spacecraft in Keplerian orbit is advanced.In this method,the solar heat flux is calculated by analytical or numerical integration method,while the planet infrared and albedo heat flux is calculated by numerical integration or random method,and the process can be simplified effectively.The transient external heat flux is analyzed based on this method for the above convex surfaces in common attitude(+Z pointing nadir,-Z pointing sun,yaw and complicated maneuver).Moreover,the transient results of the cylinder,cone and sphere surfaces in the attitude with complicated maneuver based on the method are compared with the results solved by thermal analysis software.The comparison result shows that the absolute difference of the external heat flux does not exceed 6W/m^(2),and the relative error does not exceed 5%,fully demonstrating the accuracy of the method.

关 键 词：开普勒轨道 外热流 解析法 数值积分法 随机法 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]