The invention relates to an optical satellite light load cabin, which comprises an equipment mounting plate which is a bottom plate of the optical satellite light load cabin, and the bottom surface of the equipment mounting plate is fixedly connected with a satellite platform cabin; the multifunctional frame is fixed on the top surface of the equipment mounting plate; the thermal control multi-layer heat insulation assembly is mounted on the multifunctional frame; an optical device is fixed on the device mounting plate and located in the multifunctional frame. According to the invention, the structural form of a tetrahedral plate-type load cabin formed by an existing aluminum honeycomb structural plate and a plurality of thermal control layers is changed, and the thermal control weight of the light load cabin structure can be reduced by 50%.
本发明涉及一种光学卫星轻型载荷舱,包括:设备安装板,为所述光学卫星轻型载荷舱的底板,所述设备安装板的底面与卫星平台舱固定连接;多功能框架,固定于所述设备安装板的顶面;热控多层隔热组件,安装在所述多功能框架上;光学设备固定于所述设备安装板上,位于所述多功能框架内。本发明改变了现有的铝蜂窝结构板和热控多层组成四面体板式载荷舱结构形式,轻型载荷舱结构热控重量可降低50%。
Light load cabin of optical satellite
光学卫星轻型载荷舱
2025-03-21
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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|NTIS | 1969
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