多体变构卫星在轨柔顺重组机构设计与仿真  

Design and simulation of compliant reassembly mechanism for multi⁃body variable configuration satellite in orbit

作　　者：夏鲁瑞 徐升 李森 杨程 XIA Lurui;XU Sheng;LI Sen;YANG Cheng(Space Engineering University,Beijing 101416,China)

机构地区：[1]航天工程大学,北京101416

出　　处：《航天工程大学学报》2025年第2期24-31,共8页

摘　　要：多体变构卫星在轨重组时,捕获碰撞力过大或动量传递过快都易对原空间机器人和卫星基座的平衡状态造成破坏,甚至导致捕获后复合体系统失稳。对此,设计了一种解耦的在轨柔顺重组机构,既可以根据捕获任务的不同阶段实现刚/柔双模转换操作,同时可以利用阻尼缓冲组件实现空间六维碰撞力缓冲和动量卸载,实现了多体变构卫星在轨柔顺重组操作。在Adams虚拟样机分析软件中建立了多体变构卫星在轨柔顺重组仿真模型,通过模拟实际空间捕获任务,验证了机构的缓冲卸载性能和在解决复合体失稳问题时的有效性。When a multi-body variable configuration satellite is reassembled in orbit,excessive capture impact forces or rapid momentum transfer can easily disrupt the balance state between the original space robot and the satellite base,and even lead to instability of the captured composite system.A compliant reassembly mechanism has been designed to address this issue.It can achieve dual-mode conversion between rigid and flexible modes according to different stages of the capture mission,and can also use damping buffering components to achieve six dimensional collision force buffering and momentum unloading in space,thereby realizing the flexible reassembly operation of multi-body variable configuration satellite in orbit.A simulation model for the compliant in orbit recombination of multi-body variable configuration satellite was established in Adams virtual prototyping analysis software.By simulating actual space capture tasks,the buffering and unloading performance of the mechanism and its effectiveness in solving complex instability problems were verified.

关 键 词：柔顺重组 碰撞缓冲 多体变构卫星 在轨服务 

分 类 号：V423[航空宇航科学与技术—飞行器设计]