The invention discloses a sub-stage recovery landing mechanism of a carrier rocket. The mechanism comprises a plurality of shape-preserving supporting structures arranged in the circumferential direction of a rocket body. One end of each shape-preserving supporting structure is rotatably connected to the rocket body, and the shape-preserving supporting structures have a folding state of being folded on the outer surface of the rocket body when locked by an initial locking structure and a landing supporting state of being unfolded outwards after unlocked by the initial locking structure. The sublevel recovery landing mechanism also comprises a telescopic rod structure and an interstage locking part. One end of the telescopic rod structure is hinged to the rocket body, and the other end of the telescopic rod structure is hinged to the shape-preserving supporting structures; and the telescopic rod structure comprises at least two sections of hollow struts which are movably sleeved sequentially. The interstage locking part is used for locking the two adjacent sections of hollow struts which extend to the extreme position, so that the telescopic rod structure, the shape-preserving supporting structure in the landing supporting state and the rocket body form a triangular framework. According to the recovery landing mechanism, the telescopic rod structure can provide powerful and reliable support for the shape-preserving struts structures, so that the sub-stage of the carrier rocket can land stably, and guarantee is provided for recycling the rocket sub-stage and reducing the launching cost.

    本发明公开了一种运载火箭的子级回收着陆机构,包括:保型支撑结构,围绕箭体的周向设有多个,其一端转动连接于箭体,具有被初始锁定结构锁定时收拢于箭体外表面的收拢状态和在初始锁定结构解除锁定后向外展开的着陆支撑状态;伸缩杆结构,一端铰接于箭体、另一端铰接于保型支撑结构,包括至少两节依次活动套接的空心支杆;级间锁定部件,用于锁定伸开到极限位置后的相邻两节空心支杆、以使伸缩杆结构、处于着陆支撑状态下的保型支撑结构和箭体形成三角形架构。这种回收着陆机构,伸缩杆结构可以为保型支撑结构提供有力可靠支撑,使运载火箭的子级可以平稳着陆,为火箭子级的回收再利用、降低发射成本提供保障。


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    Title :

    Sub-stage recovery landing mechanism of carrier rocket


    Additional title:

    一种运载火箭的子级回收着陆机构


    Contributors:
    PENG XIAOBO (author) / ZHENG LIWEI (author) / WANG YONGKUN (author)

    Publication date :

    2020-07-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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