| 一种卫星飞行模拟器的热控分系统模型设计 |
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| 引用本文： | 何治,许晓冬,赵啟伟.一种卫星飞行模拟器的热控分系统模型设计[J].航天器工程,2011,20(1):82-87. |
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| 作者姓名： | 何治 许晓冬 赵啟伟 |
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| 作者单位： | 1. 北京空间飞行器总体设计部,北京,100094
2. 中国空间技术研究院通信卫星事业部,北京,100094 |
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| 摘 要： | 设计了一种飞行模拟器的热控分系统模型,用于仿真卫星在轨正常和故障状态下的温度情况.为了保证热控分系统的仿真功能、速度和精度,构建了一个完整的热控分系统架构,并采用一系列数学模型来描述卫星的热状态变化,尤其是采用了基于偏微分方程的卫星主体热数学模型.最后,根据仿真结果与热分析数据以及卫星在轨数据的对比,对热控分系统设计进...
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| 关 键 词： | 卫星飞行模拟器 热控分系统 偏微分方程 仿真 |
Design of Thermal Control Subsystem for Flying Satellite Simulator |
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| HE Zhi,XU Xiaodong,ZHAO Qiwei.Design of Thermal Control Subsystem for Flying Satellite Simulator[J].Spacecraft Engineering,2011,20(1):82-87. |
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| Authors: | HE Zhi XU Xiaodong ZHAO Qiwei |
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| Institution: | HE Zhi XU Xiaodong ZHAO Qiwei(1 Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)(2 Institution of Communication Satellite,China Academy of Space Technology,China) |
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| Abstract: | The paper developes a high fidelity thermal control subsystem for the flying satellite simulator.To accomplish the goal for building a thermal control model with satisfying ability,speed,and accuracy,thermal subsystem is broken into a series of algorithms that describe the thermal dynamic behavior.Especially,the thermal mathematical model of satellite body is based on partial differential equations.The simulated results produced by the subsystem model are compared with actual satellite data and thermal anal... |
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| Keywords: | flying satellite simulator thermal control subsystem partial differential equation simulation |
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