The invention provides a vertical recovery method of a liquid injection rocket under a sublevel route and related equipment, and belongs to the field of aerospace. The method comprises the following steps: in a high-altitude reentry attitude adjustment section, adjusting a pitch angle of a sublevel to 110-130 degrees by utilizing a cold air attitude control device or other auxiliary attitude control devices at the head of the sublevel; in the reentry power deceleration section, the engine at the tail part of the first sub-stage is used for controlling the first sub-stage to decelerate; in the grid speed reduction section, a grid rudder and aerodynamic resistance of a rocket body are used for controlling first sublevel speed reduction, and the grid rudder is used for controlling the pitch angle of the first sublevel to be adjusted to 80-100 degrees; in the landing deceleration section, a single engine at the tail of the first substage is used for controlling the first substage to decelerate, the pitch angle and the yaw angle of the first substage are controlled through bidirectional swing of the engine, and the roll angle of the first substage is controlled through a cold air attitude control device or other auxiliary attitude control devices so that the first substage can land in the vertical attitude. According to the technical scheme provided by the embodiment of the invention, one sublevel can be recycled with relatively low structural cost and cost, so that the recycling cost is reduced.

    本发明提供了液体入轨火箭的一子级航线下垂直回收方法及相关设备,属于航空航天领域。方法包括:在高空再入调姿段,利用一子级头部的冷气姿控或其他辅助姿态控制装置将一子级俯仰角调整至110‑130°;在再入动力减速段,利用一子级尾部的发动机控制一子级减速;在栅格减速段,利用栅格舵和箭体的气动阻力控制一子级减速以及利用栅格舵控制一子级俯仰角调整至80‑100°;在着陆减速段,利用一子级尾部的单台发动机控制一子级减速,利用发动机双向摆动控制一子级的俯仰角和偏航角,利用冷气姿控或其他辅助姿态控制装置控制一子级的滚转角,以使一子级以垂直姿态落地。实施本发明实施例的技术方案,一子级可以以较小的结构代价和成本,实现回收,降低回收成本。


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    Titel :

    Vertical recovery method of liquid injection rocket under sublevel route and related equipment


    Weitere Titelangaben:

    液体入轨火箭的一子级航线下垂直回收方法及相关设备


    Beteiligte:
    ZHENG ZE (Autor:in) / HUO LIANG (Autor:in) / REN TAN (Autor:in)

    Erscheinungsdatum :

    18.04.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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