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Evaluation of In-Orbit Thermal Performance of X-Ray Astronomy Satellite 'Hitomi'

机译：X射线天文学“ Hitomi”在轨热性能评估

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摘要

This study presents the evaluation results of the thermal performance for Japan Aerospace Exploration Agency's X-ray astronomy satellite (Hitomi) ASTRO-H mission. Hitomi was successfully launched on 17 February 2016. The thermal design of the spacecraft and scientific instruments was challenging because the high-energy resolution and the sensitivity needed to achieve the desired scientific objectives required small thermal distortion and a strict temperature range, in spite of large heat dissipation. Hitomi housed four telescopes and six detectors. Each detector had its own radiator and heat pipes for heat dissipation. The most essential mission instrument, the soft X-ray spectrometer, had four loop heat pipes to transfer heat from two sets of compressors and the cold heads of two-stage Stirling coolers. Six fans were mounted close to six cryocoolers for ground cooling in the fairing until just before launch. The heat pipes were operated properly in orbit. Two loop heat pipes for the cryocooler compressors continued operating from the time of launch, thereby maintaining cryocooler temperatures within the allowable temperature range. Comparing the thermal analysis results and flight data, the difference between the predicted and measured temperatures was less than 4 degrees C for more than 95% of all measured temperatures. The thermal control system functioned properly in both launch operation and in orbit, and the thermal mathematical model simulated the actual thermal design of Hitomi.
机译：这项研究提出了日本航空航天局X射线天文学卫星（Hitomi）ASTRO-H任务热性能的评估结果。 Hitomi于2016年2月17日成功发射升空。航天器和科学仪器的热设计具有挑战性，因为尽管达到了很高的能量分辨率和达到预期科学目标所需的灵敏度，但仍需要较小的热变形和严格的温度范围散热。瞳内装有四架望远镜和六个探测器。每个探测器都有自己的散热器和热管以散热。最重要的任务仪器是软X射线光谱仪，它具有四个回路热管，用于从两组压缩机和两级斯特林冷却器的冷头传热。在整流罩附近，六个风扇安装在六个低温冷却器附近，用于地面冷却，直到发射前。热管在轨道上运行正常。自启动之日起，用于低温冷却器压缩机的两个回路热管继续运行，从而将低温冷却器温度保持在允许的温度范围内。比较热分析结果和飞行数据，对于超过95％的所有测得温度，预测温度和测得温度之间的差异小于4摄氏度。热控制系统在发射操作和在轨运行中均正常运行，并且热数学模型模拟了瞳的实际热设计。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2018年第1期|77-84|共8页
  • 作者

    Iwata Naoko; Usui Takashi; Ikeda Mizuho; Takei Yoh; Okamoto Atsushi; Ogawa Hiroyuki; Yumoto Takahiro; Ono Yukari; Kokubun Motohide; Takahashi Tadayuki;

  • 作者单位

    Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Chuo Ku, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 2528505, Japan;

    NEC Corp Ltd, Space Technol Dept, Space Syst Div, 1-10 Nisshin Cho, Fuchu, Tokyo 1838551, Japan;

    NEC Corp Ltd, Space & Satellite Syst Dept, Space Syst Div, 1-10 Nisshin Cho, Fuchu, Tokyo 1838551, Japan;

    Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Chuo Ku, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 2528505, Japan;

    Japan Aerosp Explorat Agcy, Res & Dev Div, 2-1-1 Sengen, Tsukuba, Ibaraki 3058505, Japan;

    Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2528505, Japan;

    NIPPI Corp, Space Design Grp, Engn Dept, Aerosp Div,Kanazawa Ku, 3175 Showa Cho, Yokohama, Kanagawa 2368540, Japan;

    NIPPI Corp, Space Design Grp, Engn Dept, Kanazawa Ku, 3175 Showa Cho, Yokohama, Kanagawa 2368540, Japan;

    Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Chuo Ku, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 2528505, Japan;

    Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Chuo Ku, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 2528505, Japan;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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