宇航学报

宇航学报 ›› 2013, Vol. 34 ›› Issue (6): 866-872.doi: 10.3873/j.issn.1000-1328.2013.06.018

• 环境试验与器件 • 上一篇    下一篇

小卫星最佳温度动态范围热控设计方法研究

张镜洋，常海萍，王立国   

  1. 1. 南京航空航天大学能源与动力学院，南京 210016；
    2.南京航空航天大学高新技术研究院，南京 210016
  • 收稿日期:2012-06-28 修回日期:2013-04-15 出版日期:2013-06-15 发布日期:2013-06-25
  • 基金资助:

    南京航空航天大学天巡一号微小卫星；青年科研基金(Y0834-GXY)

Research on Thermal Control Design Method of Optimum Dynamic Temperature Range in Micro Satellite

ZHANG Jing yang,  CHANG Hai ping,  WANG Li guo   

  1. 1.Coll. of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. Academy of Frontier Science, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
  • Received:2012-06-28 Revised:2013-04-15 Online:2013-06-15 Published:2013-06-25

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摘要：

为探索低热惯性小卫星动态传热下的热控设计方法，首先建立双层集总参数模型，在得到温度时均量解析解的基础上，类比阻尼振荡系统，采用傅里叶变换法求解温度波动量解析解，从而建立周期变化外热流下温度动态变化与热控参数间的解析关系。以此为基础提出“最佳温度动态范围”热控设计新方法。对某型微小卫星进行“最佳温度动态范围”热控设计，并通过其在轨温度遥测量动态变化对该方法的准确性和可行性进行验证。

关键词: 热控, 温度波动, 解析解, 小卫星, 阻尼振荡

Abstract:

In order to research the thermal control design method in Micro\|satellite with dynamic heat transfer, two layer model with lumped parameters is built firstly. Based on analytic solution of average temperature, the analytic solution of temperature fluctuation is gained by means of Fourier transform. Then, the analytic relation between dynamic temperature and thermal control parameters is set up. On basis of the result of derivation, a new method of thermal control design “Optimum Dynamic Temperature Range” is brought forward. The new method is used to design some satellite’s thermal control system, and is qualified as practical and correct through the dynamic variation of temperature in orbit by remote measurement. 

Key words: Thermal control, Temperature fluctuation, Analytic solution, Micro satellite, Damped oscillation

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