The invention discloses a vertical landing type recoverable solid rocket booster. A combustion chamber comprises a descending section and an ascending section; the descending section comprises a descending section combustion chamber shell, a descending section combustion chamber heat insulation layer is arranged on the inner wall of the descending section combustion chamber shell, descending section charge is arranged in the descending section combustion chamber shell, and a descending section igniter is arranged in the descending section combustion chamber shell; an air rudder is arranged outside the descending section combustion chamber shell; the ascending section comprises an ascending section combustion chamber shell, an ascending section combustion chamber heat insulation layer is arranged on the inner wall of the ascending section combustion chamber shell, and ascending section charge is arranged in the ascending section combustion chamber shell; a soft pulse isolation layer is installed between the descending section combustion chamber shell and the ascending section combustion chamber shell, and the descending section combustion chamber shell and the ascending section combustion chamber shell are connected through flanges. The method is high in drop point precision, small in landing impact and good in environmental adaptability; the booster is simple in overall structure, easy to disassemble and assemble and low in cost of repeated use after being recycled, and better energy distribution is achieved.

    本发明公开一种垂直着陆式可回收固体火箭助推器,燃烧室包括下降段和上升段;下降段包括下降段燃烧室壳体,下降段燃烧室壳体内壁设有下降段燃烧室绝热层,下降段燃烧室壳体内装有下降段装药并配置有下降段点火器;下降段燃烧室壳体外设有空气舵;上升段包括上升段燃烧室壳体,上升段燃烧室壳体内壁设有上升段燃烧室绝热层,上升段燃烧室壳体内装有上升段装药;下降段燃烧室壳体与上升段燃烧室壳体之间安装软质脉冲隔离层,并通过法兰连接。本发明落点精度高、落地冲击小、环境适应性好;助推器整体结构简单,容易拆卸和装配,回收后重复使用的代价较低,实现了较优的能量分配。


    Access

    Download


    Export, share and cite



    Title :

    Vertical landing type recoverable solid rocket booster


    Additional title:

    垂直着陆式可回收固体火箭助推器


    Contributors:
    LI WENTAO (author) / ZHANG YIYI (author) / ZHENG HANYUN (author) / HE YUNQIN (author) / GUO HONGJIE (author) / LIANG GUOZHU (author)

    Publication date :

    2025-03-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen / B64U / F02K JET-PROPULSION PLANTS , Strahltriebwerke




    ROCKET BOOSTER STAGE LANDING APPARATUS

    NJAH MOUNIR | European Patent Office | 2024

    Free access

    Rocket booster stage landing apparatus

    NJAH MOUNIR | European Patent Office | 2023

    Free access

    Ignition reverse thrust deceleration landing system for recoverable rocket

    CHEN KERU | European Patent Office | 2024

    Free access

    Emergency Solid Rocket Booster

    Stojkovic, Branko / Brown, Jonathan | AIAA | 2024