航天器在轨全周期热变形分析方法

发布时间：2018-05-02 13:39

  本文选题：航天器 + 在轨全周期　； 参考：《航天器工程》2016年06期

【摘要】：提出一种适应于在轨全周期热变形的分析方法,采用基于热传导算法进行"热分析模型-结构分析模型"全周期温度场映射,利用数学拟合算法开展对各类结果数据的分析,通过相关程序实现全周期多工况温度场映射、计算、数据分析的自动化。对某遥感卫星进行全周期热变形分析,结果表明:全周期温度场映射时间由天缩短至小时量级,温度场映射精度可控制在1%以内,相对于以往基于极端工况的热变形分析方法,可显著地提升分析精度与验证覆盖性,获得在轨热变形量级、全周期变化规律。文章的研究结果可为航天器热稳定设计提供参考。
[Abstract]:In this paper, a method for analyzing thermal deformation in orbit is proposed. Based on heat conduction algorithm, the whole period temperature field mapping of "thermal analysis model-structure analysis model" is carried out, and the analysis of all kinds of result data is carried out by means of mathematical fitting algorithm. The temperature field mapping, calculation and data analysis of the whole cycle and multi-working condition can be realized by the related program. The whole period thermal deformation analysis of a remote sensing satellite is carried out. The results show that the mapping time of the whole period temperature field is shortened from days to hours, and the mapping precision of temperature field can be controlled within 1%, compared with the previous thermal deformation analysis method based on extreme working conditions. The accuracy and coverage of the analysis can be improved significantly and the order of thermal deformation in orbit and the law of variation of the whole period can be obtained. The results of this paper can be used as a reference for the design of spacecraft thermal stability.
【作者单位】： 北京空间飞行器总体设计部;
【基金】：基金项目:国家民用空间基础设施(发改高技[2015]2429号)
【分类号】：V414;V443.5
，

本文编号：1834177