The invention provides an integrally-designed satellite-rocket separation mechanism. The integrally-designed satellite-rocket separation mechanism comprises a satellite end separation base, a carrier end separation base, a release spring and a pyrotechnic separation nut, wherein the satellite end separation base is connected with a satellite bottom plate; the carrier end separation base is connected with a carrier; the release spring is accommodated in inner space of the carrier end separation base to provide elasticity between the satellite end separation base and the carrier end separation base; a connection screw rod of the pyrotechnic separation nut penetrates through insides of the carrier end separation base and the release spring to be connected with the satellite end separation base, and a nut body of the pyrotechnic separation nut is connected with the carrier end separation base. A satellite-rocket connection mechanism, the satellite-rocket separation mechanism and a satellite-rocket separation signal acquisition mechanism are integrated in one structure, the spring is accommodated in the separation base, the screw rod of the pyrotechnic separation nut penetrates through the carrier end separation base and the release spring, so that the design is simplified and compact, the occupied space is greatly reduced and the integrally-designed satellite-rocket separation mechanism is simpler and smaller than an existing separation mechanism.


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    Title :

    Integrally-designed satellite-rocket separation mechanism


    Contributors:
    CHEN YINXIN (author) / XIN QIANG (author) / XU YUNFEI (author) / GAO YONGXIN (author)

    Publication date :

    2015-08-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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