摘要
文章通过对一个典型的单机热分析和热试验的研究,提出了一种小型单机热平衡试验方法,模拟单机在整星环境下的热平衡试验,以避免只为验证其热设计而再次补做整星热平衡试验。为准确模拟单机在星内的辐射和导热过程,通过灰体间辐射热网络法和仪器安装板处单元体热平衡法,给出了等效辐射特征点和等效导热特征点的确定方法;并结合试验结果,对模型修正的合理性、局限性进行了分析,提出了在实际应用过程中应注意的问题。
By means of heat analysis and test of a typical device onboard spacecraft, a small scale heat balance test method was introduced to verify the device heat design, so that the repeated whole satellite＇s heat balance test can be avoided, and just need to verify the changed design of the key device. An equivalence radiation characteristic node and conductive characteristic node were presented to simulate the whole satellite boundary conditions in which the device existed. In addition, a revised model was introduced to analyze the errors resulted under the hypothetic boundary conditions. The rationality and limits of the method were dissassed, and suggestions in application were presented.
出处
《中国空间科学技术》
EI
CSCD
北大核心
2008年第1期35-40,共6页
Chinese Space Science and Technology
关键词
等效特征点
热平衡试验
单机测试
热环境
仿真
卫星
Equivalent characteristic node Heat balance test Single machine testing Ther-mal environment Simulation Satellite
作者简介
姜军1971年生，1996年获哈尔滨工业大学能源与动力工程系硕士学位。高级工程师，主要研制方向为载人航天器热控制、空间用流体回路。
满广龙1977年生，2002年获哈尔滨工业大学能源学院工程热物理硕士学位。主要研究方向为：大型载人航天器热管理技术。
