中国空间科学技术

中国空间科学技术 ›› 2025, Vol. 45 ›› Issue (3): 185-191.doi: 10.16708/j.cnki.1000.758X.2025.0050

• 空间科学与试验专栏 • 上一篇    

木星系任务新型热控技术

李金岳1，2，苏若斌3，杨金1，*，段晓闻1，2，何春黎1，2，陆希1，2，牛俊坡1，2   

  1. 1.上海卫星工程研究所，上海201109
    2.上海市深空技术重点实验室，上海201109
    3.上海航天技术研究院，上海201109
  • 收稿日期:2023-10-30 修回日期:2024-01-16 录用日期:2024-02-05 发布日期:2025-05-15 出版日期:2025-06-01

New thermal control technology for jovian mission

LI Jinyue1，2，SU Ruobin3，YANG Jin1,*，DUAN Xiaowen1，2， HE Chunli1，2，LU Xi1，2，NIU Junpo1，2    

  1. 1.Shanghai Institute of Satellite Engineering，Shanghai 201109，China
    2.Shanghai Key Laboratory of Deep Space Exploration Technology，Shanghai 201109，China
    3.Shanghai Academy of Spaceflight Technology，Shanghai 201109，China
  • Received:2023-10-30 Revision received:2024-01-16 Accepted:2024-02-05 Online:2025-05-15 Published:2025-06-01

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摘要： 木星系探测器通常采用金星-地球-地球等借力序列实现地木转移，由于大范围的器日距离变化引起太阳光照强度大尺度变化，进而导致探测器舱外热控部组件温度交变范围宽，不仅要适应金星附近达2938W/m2以上的高太阳热流，还需适应木星附近50W/m2直至阴影区为0W/m2的超低太阳热流，对热控设计的极端高低温适应性带来挑战。目前传统方式主要采用流体回路、百叶窗及多层组件等热控措施进行控温，增加了热控系统的复杂度和设计难度，本文提出一种新型热控设计方法，使用三维隔热太阳翼实现对阳光的遮挡，并采用闭环解耦控制算法来调节太阳翼与星体的位置关系，从而减小太阳对探测器外表面单机设备的热辐射并维持固定的散热面，同时减少探测器的温度波动，通过仿真分析太阳翼离星体1.5m情况下，星体遮挡处的散热能力可以达到170W/m2，用于金星处高太阳热流的遮挡；当太阳翼离星体0.5m情况时，散热能力减少到50W/m2，能起到在木星处保温作用，减少散热面的漏热。具有简化热控设计和适应性强的优点，为后续深空探测器热控设计提供一种新思路。

关键词: 木星及行星穿越探测器, 热控技术, 三维隔热太阳翼, 闭环解耦控制, 太阳翼遮日

Abstract: Usually the Jovian probe uses Venus-Earth-Earth gravity-assist mission sequences to achieve Earth-Jupiter transfer. due to a wide range of changes in the daily distance caused by large-scale changes in solar light intensity， which in turn leads to the drastic temperature variation of the probe's external thermal control components， which not only needs to adapt to the high solar heat flow of up to about 2，938W/m2 near Venus， but also needs to adapt to the low solar heat flow of 50W/m2 near Jupiter， which poses a challenge to the extreme high and low temperature adaptability of the thermal control design. Currently， the traditional approach mainly adopts thermal control measures such as fluid loops， shutters and multi-layer components to control temperature， which increases the complexity and design difficulty of the thermal control system. In this paper， we proposed a new type of thermal control design method We used a three-dimensional heat-insulating solar panel to orbstruct the sunlight， and adopted a closed-loop decoupling control algorithm to regulate the positional relationship between the solar wing and the star body. By deminishing the solar thermal radiation to the detector's external surface of the stand-alone device and maintaining a fixed heat-sinking surface， the temperature fluctuation of the detector is reduced. Through simulation analysis， it has been shown that when the solar panel is positioned 1.5 meters away from the star body， the heat dissipation capacity at the shaded area can reach 170W/m2， suitable for blocking high solar heat flux near Venus. When the solar panel is positioned 0.5 meters away from the star body， the heat dissipation capacity decreases to 50W/m2， providing insulation and reducing heat loss at the heat-sinking surface near Jupiter. Our design has the advantages of simple thermal control design and high adaptability， and provides a new idea for the thermal control design of the subsequent deep space detectors.

Key words: Jovian probes, thermal control technology, three-dimensional insulated solar panel, closed-loop decoupling control, solar wing occlusion sunny