摘要
地球同步卫星工作过程中法兰底座所受的辐射加热对法兰上的控制开关等零件的安全有重要影响。为此,建立了节点网络法计算发动机和隔热屏对卫星法兰底座及控制开关的辐射加热,比较了发动机、隔热屏和羽流3种辐射源的作用大小,还研究了发动机位置的平移对底部法兰及控制开关辐射加热的影响。研究表明:羽流对法兰和控制开关的辐射热流最小,发动机对法兰和控制开关的辐射热流最大;法兰和控制开关上不同侧面受到的辐射加热很不均匀,面向发动机正面的侧面辐射加热最强,面向发动机头部的侧面辐射最小;发动机向后平移可以显著降低法兰和控制开关上辐射热流的最大值。
The radiation heating on the base flange concerns the safety of the jointing switch in satellites. The node and network method and the IRTE method are used to calculate the radiative flux of the engine,the heat shield radiation and the plume radiation on the base flange and the jointing switch. The effects of the three radiation sources on the heating of the base flange and the jointing switch are compared. Also,the effect of parallel moving of the engine's position on the radiative heating is studied. It is shown that the effect of plume radiation on the radiative heating of the base flange and the jointing switch is the smallest,while that of engine radiation is the most important. The radiation flux varies in a large range on the surfaces of the base flange and the jointing switch,which is the largest on the surfaces towards the front face of the engine,and the smallest is on the surfaces towards the head face of the engine. Parallel moving of the engine's position backwards can reduce the maximum radiation flux on the base flange and the jointing switch remarkably.
出处
《航天器环境工程》
2008年第2期148-151,98-99,共4页
Spacecraft Environment Engineering
