北京航空航天大学学报 ›› 2019, Vol. 45 ›› Issue (8): 1544-1551.doi: 10.13700/j.bh.1001-5965.2018.0679

• 多相流测量 • 上一篇    下一篇

空间光学遥感器真空热试验工装模块化设计

周泽鑫1, 孙志强1, 徐冰1,2, 洪扬1,2   

  1. 1. 中南大学 能源科学与工程学院, 长沙 410083;
    2. 北京空间机电研究所, 北京 100076
  • 收稿日期:2018-11-21 出版日期:2019-08-20 发布日期:2019-09-06
  • 通讯作者: 孙志强 E-mail:zqsun@csu.edu.cn
  • 作者简介:周泽鑫 男,硕士研究生。主要研究方向:热设计与传热优化;孙志强 男,博士,教授,博士生导师。主要研究方向:多相流理论与测试、热设计与传热优化、能源新技术及应用等。
  • 基金资助:
    国家自然科学基金(51576213);中南大学中央高校基本科研业务费专项资金(2018zzts495)

Modularization design of vacuum thermal test frock for space optical remote sensor

ZHOU Zexin1, SUN Zhiqiang1, XU Bing1,2, HONG Yang1,2   

  1. 1. School of Energy Science and Engineering, Central South University, Changsha 410083, China;
    2. Beijing Institute of Space Mechanics and Electricity, Beijing 100076, China
  • Received:2018-11-21 Online:2019-08-20 Published:2019-09-06
  • Supported by:
    National Natural Science Foundation of China (51576213); the Fundamental Research Funds for the Central Universities of Central South University (2018zzts495)

摘要: 针对空间光学遥感器在空间环境地面模拟试验中舱板温度分布不均的问题,运用模块化思想对某型号空间光学遥感器工装的舱板结构开展了优化设计。将舱板按照温度分布进行分块,提出模块化拼装和模块化热控2种设计方案,模块化拼装是对舱板及其表面加热片进行独立分块划分,模块化热控则是将舱板视为整体,仅对其表面的加热片进行分块设计。结果表明:模块化热控的舱板平均温度偏差为0.205 K,低于未模块化设计的0.87 K和模块化拼装的0.30 K,提高了舱板的温度均匀性。同时,模块化拼装改善了舱板温度分布,使得符合热控要求的测点比例由34.8%提高到96.7%,但独立划分的模块之间仍存在一定温差;模块化热控则消除了模块间的温差,将符合热控要求的测点比例进一步提高到100%,完全满足热控要求。

关键词: 空间光学遥感器, 工装, 真空热试验, 辐射, 模块化设计

Abstract: To solve the problem of uneven temperature distribution in the ground simulation experiment of space environment by space optical remote sensor, the modular design is used to optimize the cabin plate structure frock of a certain space optical remote sensor, and the cabin plates are divided according to the temperature distribution. In this paper, modular assembly and modular thermal control are proposed. The modular assembly is to divide the cabin plates and its surface heating sheets independently; the modular thermal control considers the cabin plates as a whole, and only the heating sheets are divided. The results show that the average temperature deviation of the modular thermal control is 0.205 K, which is lower than 0.87 K of the unmodulated design and 0.30 K of the modular assembly, and improves the temperature uniformity of the cabin plates. Modular assembly improves the temperature distribution of the cabin plates, and the proportion of measuring points that meet the thermal control requirements is increased from 34.8% to 96.7%. However, there is still a certain temperature difference between the modules, and modular thermal control eliminates the temperature difference. The proportion of measuring points meeting the thermal control requirements is further increased to 100%, which fully meets the thermal control requirements.

Key words: space optical remote sensor, frock, vacuum thermal test, radiation, modularization design

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