The invention discloses a micro-nano satellite and rocket unlocking and separating mechanism which comprises a center rotating wheel structure, N extension sliding arms and N satellite locking and releasing structures, one end of each extension sliding arm is connected with the center rotating wheel structure, and the other end of each extension sliding arm is connected with one satellite locking and releasing structure; the central runner structure controls the plurality of connecting rods to realize synchronous opening and closing; the satellite locking and releasing structure adopts a steel ball for locking and releasing, so that the satellite is prevented from popping up in advance, and the satellite locking and releasing structure has higher loading capacity; the invention provides a satellite separation speed and separation force value solving method aiming at a satellite and rocket separation speed requirement; the unlocking separation mechanism is high in synchronism, large in load, light in weight, small in size, high in reliability and capable of ensuring that a satellite is safely separated from a rocket after entering an orbit.

    本发明公开了一种微纳卫星星箭解锁分离机构,包括中心转轮结构、N条延展滑动臂以及N个卫星锁定与释放结构,每条延展滑动臂均一端与中心转轮结构连接,另一端连接一个卫星锁定与释放结构;中心转轮结构控制多个连杆实现同步开合;卫星锁定与释放结构采用钢珠进行锁定与释放,防止卫星提前弹出,具备较高载重能力;本发明针对卫星与火箭分离速度要求,提出卫星分离速度以及分离力数值的求解方法;该解锁分离机构具备同步性高,载重大,质量轻,体积小,可靠性高,可保证卫星进入轨道后安全与火箭分离。


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    Title :

    Star-rocket unlocking and separating mechanism for micro-nano satellite


    Additional title:

    一种微纳卫星星箭解锁分离机构


    Contributors:
    ZHANG XIANG (author) / MAO RONGLEI (author)

    Publication date :

    2025-03-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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