The invention discloses a satellite-rocket separation structure for marine satellite launching. The satellite-rocket separation structure comprises a launcher body and a satellite body, a fixing ringis arranged on the upper side of the launcher body, arc-shaped grooves are formed in the upper side of the fixing ring, spring grooves are formed in the upper side of the launcher body, a first springis connected with the bottom of each spring groove, and arc-shaped protrusions are arranged on the lower part of the satellite body; sliding parts are slidably arranged on the outer ring side of thefixing ring, an annular pipe is arranged on the outer side of the fixing ring, arc-shaped sliding bodies are slidably arranged in the annular pipe, and the sliding bodies are fixedly connected with the sliding parts through connecting blocks; and baffles are fixedly arranged in the annular pipe, a second spring is connected between each baffle and the corresponding sliding body, electric telescopic rods are fixedly arranged on the outer side of the annular pipe, and limiting grooves are formed in the outer sides of the sliding bodies. The satellite-rocket separation structure is compact in structure, small in space occupation, small in satellite structure transformation, stable in connection structure, convenient to operate, small in action in the separation process, safe, reliable and recyclable, the satellite launching efficiency is effectively improved, and the launching cost is reduced.

    本发明公开了一种海上卫星发射用星箭分离结构,包括发射器本体和卫星本体,发射器本体上侧设置有固定环,固定环上侧设置有弧形凹槽,发射器本体上侧设置有弹簧槽,弹簧槽底部连接有第一弹簧,卫星本体下部设置有弧形凸起,固定环外环侧滑动设置有滑动件,固定环外侧设置有环形管,环形管内滑动设置有弧形的滑动体,滑动体与滑动件之间通过连接块固定连接,环形管内固定设置有挡板,挡板与滑动体之间连接有第二弹簧,环形管外侧固定设置电动伸缩杆,滑动体外侧设置有限位槽;本发明结构紧凑,减少空间占用,对卫星结构改造小,连接结构稳定,操作方便、分离过程动作较小、安全可靠,可回收利用,有效提高卫星发射效率,降低发射成本。


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    Title :

    Satellite-rocket separation structure for marine satellite launching


    Additional title:

    一种海上卫星发射用星箭分离结构


    Contributors:
    YANG JIANDONG (author) / MA YINGLIANG (author) / FU MINHUI (author) / XU XIANCHUN (author) / JIN DONG (author) / ZHANG TAO (author)

    Publication date :

    2020-12-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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