The invention provides a launch vehicle upper-stage propulsion system and a launch vehicle. The system is characterized in that an outlet end of a supercharging device is connected with an air inlet end of a propellant storage tank, a control air inlet end of an upper-stage orbit control engine and an inlet end of a basic-stage control air separation connector; a liquid outlet end of the propellant storage tank is connected with a propellant inlet end of the upper-stage orbit control engine, a propellant inlet end of the upper-stage attitude control engine and an inlet end of a basic-stage propellant separation connector; an outlet end of the basic-stage control air separation connector is connected with a control air inlet end of the basic-stage attitude control engine; and an outlet end of the basic-stage propellant separation connector is connected with the propellant inlet end of the basic-stage attitude control engine. According to the launch vehicle upper-stage propulsion system and the launch vehicle, the weight of the upper stage is reduced, the carrying capacity of the launch vehicle is remarkably improved, connecting assemblies are reduced, and the reliability of the launch vehicle is improved.

    本发明提供一种运载火箭上面级推进系统及运载火箭,其中系统包括:增压装置的出口端分别与推进剂贮箱的进气端、上面级轨控发动机的控制气入口端和基础级控制气分离接头的入口端连接;推进剂贮箱的出液端分别与上面级轨控发动机的推进剂入口端、上面级姿控发动机的推进剂入口端和基础级推进剂分离接头的入口端连接;基础级控制气分离接头的出口端与基础级姿控发动机的控制气入口端连接;基础级推进剂分离接头的出口端与基础级姿控发动机的推进剂入口端连接。本发明提供的运载火箭上面级推进系统及运载火箭,降低了上面级的重量,显著地提高了运载火箭的运载能力,减少了连接组件,提高了运载火箭的可靠性。


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    Titel :

    Launch vehicle upper-stage propulsion system and launch vehicle


    Weitere Titelangaben:

    运载火箭上面级推进系统及运载火箭


    Erscheinungsdatum :

    18.06.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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