星載大型旋轉(zhuǎn)部件的熱平衡試驗方法

A method ofthermal balance test for space large rotating payloads

摘要: 星載大型旋轉(zhuǎn)部件因其構(gòu)型復(fù)雜和相對星體其他部分轉(zhuǎn)動的特性，給熱設(shè)計的驗證帶來諸多難題,。文章以“海洋二號”衛(wèi)星的微波散射計為例,，分別采用通過地面試驗直接獲取在軌預(yù)示溫度的直接驗證方法，以及驗證熱分析模型,、再由熱分析模型預(yù)示在軌溫度的間接驗證方法進行熱平衡試驗,。通過對試驗結(jié)果、熱分析結(jié)果和在軌飛行結(jié)果的對比,，驗證了這2種試驗方法正確,、有效。

Abstract: Space large rotating payloads, being complex in structure and constantly rotating, are a challenge to the test validation of their thermal characteristics. A case study of the thermal balance test method of the microwave scatterometer in Haiyang-2 satellite is presented. A direct validation method is used in the engineering model phases, which Call used to forecast the in-orbit temperature directly from the ground test result. Meanwhile, all indirect validation method is used in the flight-model phases, which may used to predict the in-orbit temperature through the thermal analytical model. A comparison between the thermal test results, the thermal analytical results and the flight results shows the correctness and the effectiveness of the thermal balance test.