Thermal Design and Simulation Verification of High-precision Integrated Star Sensor in Near-Earth Orbit
-
摘要: 某型高精度一体式星敏感器指向精度高，对温度变化非常敏感。其所处近地轨道外热流复杂多变，一体式结构和内热源集中的综合因素不仅导致散热设计困难，而且镜头直接受到内热源发热影响难以保障指向精度。首先，结合轨道参数，安装布局获得星敏感器平均吸收外热流。然后，通过分析外热流与内热源工作情况，采用被动热控和主动热控相结合的热设计方法，并对星敏感器散热面的位置与大小进行设计与计算。最后，根据轨道环境和热控措施并利用热仿真软件进行热分析验证。仿真结果表明，安装法兰温度为19.82℃~20.10℃，镜头轴向温差小于2.23℃，周向温差小于0.48℃，电路盒温度为19.10℃~23.49℃，满足热控指标。通过合理的热控设计保证了极高精度星敏感器的稳定工作条件，星敏感器的热设计合理有效。Abstract: High-precision integrated star sensors have a high pointing accuracy and are highly sensitive to temperature changes. The external heat flow in near-Earth orbits is complex and variable. The comprehensive factors of the integrated structure and the concentration of the internal heat source not only lead to difficulty in the heat dissipation design, but also make it difficult to guarantee the pointing accuracy of the lens directly affected by the internal heat source. First, combined with the orbital parameters, the installation layout provides the average absorbed external heat flux of the star sensor. Subsequently, by analyzing the working conditions of the external and internal heat flows, a thermal design method combining passive and active thermal control is adopted, and the position and size of the heat dissipation surface of the star sensor are designed and calculated. Finally, thermal analysis and verification are performed using thermal simulation software according to the orbital environment and thermal control measures. The simulation results show that the installation flange temperature is 19.82-20.10℃, the axial temperature difference of the lens is less than 2.23℃, the circumferential temperature difference is less than 0.48℃, and the circuit box temperature is 19.10-23.49℃, which meets the thermal control index. The stable working conditions of the extremely high-precision star sensor are ensured by a reasonable thermal control design, and the thermal design of the star sensor is reasonable and effective.
-
Key words:
- high-precision star sensor /
- thermal design /
- thermal analysis
-
图 11 低温工况温度分布云图与温度变化曲线
Figure 11. Low temperature distribution clouds and temperature variation curves
图 12 高温工况温度分布云图与温度变化曲线
Figure 12. High temperature distribution clouds and temperature variation curves
表 1 重要结构热控指标
Table 1. Important structure thermal control index
Structure Index content Thermal control index Installation flange Temperature 20℃±0.5℃ Lens cone Axial temperature difference ＜3℃ Circumferential temperature difference ＜1℃ Power supply chassis Temperature ＜25℃ 
下载: 导出CSV
表 2 极端工况
Table 2. Extreme conditions
Solar position β Heat sink surface coating surface properties High temperature
working conditionWinter
solstice60° End period Low temperature
working conditionSummer
solstice0° Initial period
下载: 导出CSV
-
[1] 吕建伟, 王领华, 苏生, 等. 微型星敏热控设计及仿真[J]. 红外与激光工程, 2022, 51(11): 265-270. https://www.cnki.com.cn/Article/CJFDTOTAL-HWYJ202211025.htmLV Jianwei, WANG Linghua, SU Sheng, et al. Thermal control design and simulation of micro star sensor[J]. Infrared and Laser Engineering, 2022, 51(11): 265-270 https://www.cnki.com.cn/Article/CJFDTOTAL-HWYJ202211025.htm [2] 余成武, 隋杰, 陈超, 等. 高分七号卫星多探头甚高精度星敏感器热设计与验证[J]. 航天器工程, 2020, 29(3): 144-150. https://www.cnki.com.cn/Article/CJFDTOTAL-HTGC202003024.htmYU C W, SUN J, CHEN C, et al. Thermal design and verification of multi-head very high accuracy star sensor onboard GF-7 satellite[J]. Spacecr Eng., 2020, 29(3): 144-150. https://www.cnki.com.cn/Article/CJFDTOTAL-HTGC202003024.htm [3] 江帆, 王忠素, 陈立恒, 等. 星敏感器组件的热设计[J]. 红外与激光工程, 2014, 43(11): 3740-3745. https://www.cnki.com.cn/Article/CJFDTOTAL-HWYJ201411041.htmJIANG FAN, WANG Zhongsu, CHEN Liheng, et al. Thermal design of star sensor assembly[J]. Infrared and Laser Engineering, 2014, 43(11): 3740-3745. https://www.cnki.com.cn/Article/CJFDTOTAL-HWYJ201411041.htm [4] 江帆, 吴清文, 王忠素, 等. 星敏感器支架的结构/热稳定性分析及验证[J]. 红外与激光工程, 2015, 44(11): 6. https://www.cnki.com.cn/Article/CJFDTOTAL-HWYJ201511049.htmJIANG Fan, WU Qingwen, WANG Zhongsu., et al. Analysis and verification of structure stability and thermal stability of a bracket of star sensors[J]. Infrared and Laser Engineering, 2015, 44(11): 6. https://www.cnki.com.cn/Article/CJFDTOTAL-HWYJ201511049.htm [5] 张彧, 赵吉喆, 张翔, 等. 环月轨道一体式星敏感器热设计及仿真验证[J]. 航天器环境工程, 2016, 33(5): 516-520. https://www.cnki.com.cn/Article/CJFDTOTAL-HTHJ201605011.htmZHANG Yu, ZHAO Jizhe, ZHANG Xiang, et al. Thermal design of an integrated star sensor on lunar orbit with simulation validation[J]. Spacecraft Environment Engineering, 2016, 33(5): 516-520. https://www.cnki.com.cn/Article/CJFDTOTAL-HTHJ201605011.htm [6] 訾克明, 吴清文, 李泽学, 等. 空间光学遥感器的热设计实例及其仿真分析[J]. 计算机仿真, 2008, 25(12): 4. DOI: CNKI:SUN:JSJZ.0.2008-12-023 .ZI K M, WU Q W, LI Z X. Simulation analysis of a space optical remote-sensor's thermal design[J]. Computer Simulation, 2008, 25(12): 4. DOI:CNKI:SUN:JSJZ.0.2008-12-023 .[7] 苗建印. 航天器热控制技术[M]. 北京: 北京理工大学出版社有限责任公司, 2018.MIAO J Y. Spacecraft Thermal Control Technology[M]. Beijing: Beijing Institute of Technology Press, 2018. [8] 李强, 陈立恒. 复杂外热流条件下红外探测器组件热设计[J]. 红外与激光工程, 2016, 45(9): 73-79. https://www.cnki.com.cn/Article/CJFDTOTAL-HWYJ201609011.htmLI Qiang, CHEN Liheng. Thermal design of infrared detector components in complex heat flux[J]. Infrared and Laser Engineering, 2016, 45(9): 73-79. https://www.cnki.com.cn/Article/CJFDTOTAL-HWYJ201609011.htm [9] 董奎辰, 郭亮, 黄美娇, 等. 空间相机大功率热源散热设计[J]. 红外技术, 2023, 45(5): 521-526. http://hwjs.nvir.cn/article/id/f7193fd5-4039-46a6-b862-00a13bc28417DONG Kuichen, GUO Liang, HUANG Meijiao, et al. Heat-dissipation design for space camera high-power heat source[J]. Infrared Technology, 2023, 45(5): 521-526. http://hwjs.nvir.cn/article/id/f7193fd5-4039-46a6-b862-00a13bc28417 -
点击查看大图
图(12) / 表(2)
计量
- 文章访问数: 20
- HTML全文浏览量: 10
- PDF下载量: 4
- 被引次数: 0
