A thermal stabilization criterion determination method for spacecraft thermal balance test

被引：0
|
作者：
Meng F.-K. [1 ]
Zhao L. [1 ]
Qing H.-X. [1 ]
Fan Y.-F. [1 ]
Man G.-L. [1 ]
Fan H.-L. [1 ]
机构：
[1] Beijing Institute of Spacecraft System Engineering, Beijing
来源：
| 1600年 / China Spaceflight Society卷 / 37期
关键词：
Thermal balance test; Thermal control; Thermal stabilization criterion; Thermal time constant;
D O I：
10.3873/j.issn.1000-1328.2016.10.015
中图分类号：
学科分类号：
摘要：
A transient coupling lumped heat transfer model is proposed for the internal avionics and external spacecraft structure, which is consistent with the heat transfer characteristics of a general spacecraft thermal control system. The determination method for thermal stabilization criterion is developed, which is based on the thermal time constant. The spacecraft thermal time constant is achieved analytically for dual-node coupling heat transfer process. The relation between the thermal stabilization temperature difference and the temporal change rate of the temperature is derived. The real-time correction method for the thermal time constant is proposed, which is based on the temperature curve fitting technology by using the Levenberg-Marquardt algorithm and least squares method. Furthermore, the real-time correction method is able to meet the demand of the thermal stabilization criterion determination for the multi-node coupling heat transfer spacecraft system. The validity of the actual thermal stabilization criterions is discussed. The determination method of the thermal stabilization proposed in this paper can be applied to the spacecraft thermal balance tests. © 2016, Editorial Dept. of JA. All right reserved.
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页码：1263 / 1270
页数：7
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