The invention discloses a flexible solar wing applied to a satellite and a high-orbit satellite, and the flexible solar wing comprises a flexible solar wing array plane which is rectangular; the at least two first supporting frames are located on the two opposite sides of the flexible solar wing array plane respectively, and the first supporting frames are fixedly connected with the flexible solar wing array plane; the central connecting piece is arranged at the central position of the flexible solar wing array plane; the number of the second supporting frames is four, the first ends of the four second supporting frames are connected to the four corners of the center connecting piece respectively, and the second ends of the four second supporting frames extend to the four corners of the flexible solar wing array plane and are fixedly connected with the flexible solar wing array plane; the two second supporting frames on the same diagonal line are arranged to be capable of being folded and unfolded around the center of the center connecting piece. According to the solar wing, the problems of large folding envelope, large occupied space, heavy weight and weak structural stability of the solar wing in the related technology are solved.
本申请公开了一种应用于卫星的柔性太阳翼及高轨卫星,其中柔性太阳翼包括:柔性太阳翼阵面,柔性太阳翼阵面呈矩形;第一支撑框架,至少设置为两个并分别位于柔性太阳翼阵面上相对的两侧,第一支撑框架与柔性太阳翼阵面固定连接;中心连接件,设于柔性太阳翼阵面的中心位置;第二支撑框架,设置为四个,四个第二支撑框架的第一端分别连接于中心连接件的四角,其第二端延伸至柔性太阳翼阵面的四角并与柔性太阳翼阵面固定连接;在同一对角线上的两个第二支撑框架设置成能够绕中心连接件的中心对折和展开。本本申请解决了相关技术中的太阳翼存在收拢包络大、空间占用高、重量重、结构稳定性弱的问题。
Flexible solar wing applied to satellite and high-orbit satellite
应用于卫星的柔性太阳翼以及高轨卫星
2024-10-01
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
On-orbit unfolding and folding mechanism of satellite-borne flexible solar wing
European Patent Office | 2024
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