| 基于系统辨识方法的航天器热真空试验热传递模型 |
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| 引用本文： | 于涛,崔俊峰.基于系统辨识方法的航天器热真空试验热传递模型[J].航天器环境工程,2005,22(4):202-203. |
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| 作者姓名： | 于涛 崔俊峰 |
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| 作者单位： | 北京卫星环境工程研究所,北京100094 |
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| 摘 要： | 航天器及其部件的热真空试验是航天器研制过程保证其可靠性的重要环节。由于复杂的物理和边界条件,单纯从传热的角度得到的航天器传热模型与真实情况存在差别。基于传热理论的基本方法,文章提出结合系统辨识的方法得到航天器热真空试验传热数学模型。这种方法可以推广到相似的试验中去,将加快试验进程和节省大量的试验经费。
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| 关 键 词： | 航天器 热真空试验 系统辨识 传热模型 |
| 文章编号： | 1673-1379(2005)04-0202-02 |
| 收稿时间： | 2005/6/24 0:00:00 |
| 修稿时间： | 2005年6月24日 |
THERMAL MODEL BASED ON METHOD OF SYSTEM IDENTIFICATION IN SPACECRAFT THERMAL VACUUM TEST |
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| YU Tao,CUI Jun-feng.THERMAL MODEL BASED ON METHOD OF SYSTEM IDENTIFICATION IN SPACECRAFT THERMAL VACUUM TEST[J].Spacecraft Environment Engineering,2005,22(4):202-203. |
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| Authors: | YU Tao CUI Jun-feng |
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| Abstract: | Thermal vacuum test of spacecrafts or their parts is one of the crucial processes during spacecraft design.Due to the complexity of thermal boundary conditions and physical features,however,thermal model solely obtained from heat analysis aspect is somehow not as precise as expected by comparison with real test data.Based on basic thermal analysis,a new thermal model is obtained by means of system identification.In addition,thermal test process will be shortened and expenses will be decreased with the similar thermal test requirements. |
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| Keywords: | spacecraft thermal vacuum test system identification thermal model |
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