The invention provides a heat dissipation device for a fixed solar wing of a spacecraft, which comprises an insulating material (1), a heat conduction film (2) and a secondary surface mirror (3), the insulating material (1) is attached to the back surface of a to-be-cooled area of the fixed solar wing of the spacecraft, one end of the heat conduction film (2) is attached to the insulating material (1), and the other end of the heat conduction film (2) is attached to the secondary surface mirror (3). The other end of the heat conduction film (2) is attached to the other side face, not directly irradiated by the sun, of the spacecraft body, and the secondary surface mirror (3) is attached to the heat conduction film (2). The heat dissipation device has the beneficial effects that on the premise that the structural design of the body is not changed, the fixed solar wing is cooled through the flexible graphene film, the temperature index requirement after the number of the fixed solar wing cloth pieces is reduced can be met, and the output voltage of the solar wing meets the specific requirement.
本发明提供了一种航天器固定太阳翼的散热装置,包括绝缘材料(1)、导热膜(2)、二次表面镜(3),所述绝缘材料(1)贴装在航天器固定太阳翼需要散热区域的背面,所述导热膜(2)一端贴装在所述绝缘材料(1)上,所述导热膜(2)另一端贴装在航天器本体其它非太阳直接照射的侧面,所述二次表面镜(3)贴装在所述导热膜(2)上。本发明的有益效果是:本发明的散热装置在不改变本体结构设计的前提下,通过柔性石墨烯膜对固定太阳翼进行降温,可满足固定太阳翼布片数量减少后的温度指标要求,让太阳翼输出电压满足特定要求。
Heat dissipation device for fixed solar wing of spacecraft
一种航天器固定太阳翼的散热装置
20.12.2022
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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