The invention discloses a super-heat-conduction variable satellite structure based on memory alloy and a machining method, and relates to the field of spacecraft structures, the super-heat-conduction variable satellite structure comprises a satellite variable structure, a compression device and solar wings connected to the two opposite sides of the satellite variable structure; the satellite variable body structure is in a cylinder shape with a polygonal section, each side face of the satellite variable body structure comprises a plurality of arc-shaped plates which are sequentially and integrally connected, and the middle portions of the arc-shaped plates protrude in the direction away from the center line of the satellite variable body structure. The compression device is used for driving the satellite variable body structure to be compressed in the center line direction of the satellite variable body structure. And multi-state conversion of the spacecraft structure can be realized.
本申请公开了一种基于记忆合金的超导热可变体卫星结构与加工方法,涉及航天器结构领域,包括卫星可变体结构、压缩装置、以及连接于卫星可变体结构相对两侧的太阳翼;卫星可变体结构为截面为多边形的筒形,其每一个侧面均包括多个依次一体连接的弧形板,弧形板的中部向远离卫星可变体结构中心线的方向凸出;压缩装置用于驱动卫星可变体结构沿着卫星可变体结构中心线方向压缩。能够实现航天器结构多状态转换。
Super-thermal-conductivity variable satellite structure based on memory alloy and processing method
一种基于记忆合金的超导热可变体卫星结构与加工方法
2023-09-01
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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