The invention discloses an interstage cold separation structure of a carrier rocket. The interstage cold separation structure comprises a front cabin body, a rear cabin body, and a separation spring assembly. The tail end of the front cabin body is connected with a separation spring ejector rod support. The front end of the rear cabin body is connected with the tail end of the front cabin body through an interstage separation connection unlocking device; and the rear cabin body is connected with a separation spring support base corresponding to the position of a separation spring ejector rod bracket; the interstage separation connection unlocking device is used for locking the front cabin body and the rear cabin body and unlocking the front cabin body and the rear cabin body after receiving a separation instruction. The separation spring assembly is elastically supported between the separation spring support base and the separation spring ejector rod bracket and is provided with an elastic piece for providing a separation impulse for the front cabin body and the rear cabin body. Since the separation spring assembly is arranged between the front cabin body and the rear cabin body, when the interstage separation connection unlocking device is disconnected under fire work, the elastic piece of the separation spring assembly generates an acting force for driving the front cabin body and the rear cabin body to be away from each other, so that the separation speed of the front cabin body and the rear cabin body is increased, and the safety during rocket body separation is improved.

    本发明公开了一种运载火箭的级间冷分离结构,包括前舱体,尾端连接有分离弹簧顶杆支架;后舱体,前端通过级间分离连接解锁装置和前舱体的尾端相连;后舱体上连接有与分离弹簧顶杆支架的位置对应的分离弹簧支座;级间分离连接解锁装置用于锁定前舱体和后舱体,并在接收到分离指令后解除前舱体和后舱体之间的锁定;分离弹簧组件,弹性支撑在分离弹簧支座和分离弹簧顶杆支架之间,具有为前舱体和后舱体提供分离冲量的弹性件。通过在前舱体和后舱体之间设置分离弹簧组件,当级间分离连接解锁装置在火工作用下断开时,分离弹簧组件的弹性件产生驱使前舱体和后舱体相互远离的作用力,可以提高前舱体和后舱体的分离速度,提高箭体分离时的安全性。


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    Titel :

    Interstage cold separation structure of carrier rocket


    Weitere Titelangaben:

    一种运载火箭的级间冷分离结构


    Beteiligte:
    PENG XIAOBO (Autor:in) / ZHENG LIWEI (Autor:in) / CUI SHENSHAN (Autor:in)

    Erscheinungsdatum :

    17.04.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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