星外快旋部件的热设计方法  

Thermal Design Methods for Fast Spin Components on Satellites

作　　者：彭方汉[1] 耿利寅[1] 王甜甜[1] 李国强[1] 

机构地区：[1]北京空间飞行器总体设计部空间热控技术北京市重点实验室,北京100094

出　　处：《航天器工程》2013年第6期53-58,共6页Spacecraft Engineering

摘　　要：文章分析了星外快旋部件的热设计特点和难点,包括整体散热能力较小、热管工作条件苛刻、散热面外热流复杂、加热回路资源有限等多个方面;结合HY-2卫星散射计探测头部和辐射计探测头部的热设计方案,描述了星外快旋部件的热设计方法和热设计要点;最后对散射计探测头部和辐射计探测头部,采用"机-电-热"一体化的设计方法,得出了合理可行的星外快旋部件的热设计方案。This article analyzes the characteristics and difficulties of thermal design for fast spin components such as low heat radiating capacity of the system, seious heat pipe working condi- tion, complicated external heat flow on radiator, and restricted heating circuit resources, etc. Based on the HY-2 satellite＇s thermal design program of the scatterometer and radiometer probe heads, the article describes the thermal design methods and key points for the spin components on the satellite. A reasonable thermal design scheme for spin components outside the satellite is reached by using the ＂mechanical-electrical-thermal＂ integration design method.

关 键 词：快旋 热设计 方法 特点 

分 类 号：V423.4[航空宇航科学与技术—飞行器设计]