本文選題：航天器 + 在軌全周期�。� 參考：《航天器工程》2016年06期

【摘要】：提出一種適應(yīng)于在軌全周期熱變形的分析方法,采用基于熱傳導(dǎo)算法進(jìn)行"熱分析模型-結(jié)構(gòu)分析模型"全周期溫度場映射,利用數(shù)學(xué)擬合算法開展對各類結(jié)果數(shù)據(jù)的分析,通過相關(guān)程序?qū)崿F(xiàn)全周期多工況溫度場映射、計算、數(shù)據(jù)分析的自動化。對某遙感衛(wèi)星進(jìn)行全周期熱變形分析,結(jié)果表明:全周期溫度場映射時間由天縮短至小時量級,溫度場映射精度可控制在1%以內(nèi),相對于以往基于極端工況的熱變形分析方法,可顯著地提升分析精度與驗證覆蓋性,獲得在軌熱變形量級、全周期變化規(guī)律。文章的研究結(jié)果可為航天器熱穩(wěn)定設(shè)計提供參考。
[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.
【作者單位】： 北京空間飛行器總體設(shè)計部;
【基金】：基金項目:國家民用空間基礎(chǔ)設(shè)施(發(fā)改高技[2015]2429號)
【分類號】：V414;V443.5
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本文編號：1834177