The embodiment of the invention provides a low-orbit satellite with a flat structure. Thelow-orbit satellite includes a satellite body, wherein amain envelope of the satellite body is a flat cuboid, and satellite equipment is respectively distributed on the front surface and the back surface of a-Z plate; solar cell wings which are curled and folded on one side of the satellite before being unfolded and are elastically unfolded through the framework when being unfolded; a comprehensive electronic system which is used for the coordination and control of each satellite device, and carries out the information interaction with each satellite device through RS422, RS485, a CAN bus, GPIO and a sensor collection interface. The overall size of the satellite is greatly reduced, the requirement for enveloping in a fairing of a current mainstream carrier rocket can be met, and the space utilization rate in the rocket fairing is greatly increased.
本发明实施例提出一种具有扁平式结构的低轨卫星,所述卫星本体主包络呈现扁平的长方体,卫星设备分别分布于所述‑Z板的正面和反面;还包括太阳电池翼,展开前卷曲收拢在卫星一侧,展开时靠骨架弹性展开;还包括综合电子系统,用于卫星各设备的协调和控制,通过RS422、RS485、CAN总线、GPIO和传感器采集接口与卫星各设备进行信息交互。本申请实施例提出的卫星整星体积大大缩小,可以适应当前主流运载火箭的整流罩内包络要求,极大提高火箭整流罩内的空间利用率。
Low-orbit satellite with flat structure
一种具有扁平式结构的低轨卫星
2021-07-16
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
Satellite orbit semi-major axis flat root long period term modeling method
European Patent Office | 2024
|NTRS | 1979
|NTRS
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