The invention discloses a solid rocket booster with an adjustable thrust line structure. The solid rocket booster comprises a combustion chamber shell, a booster charge, a front top cover, a spray pipe assembly and an ignition assembly. A front connecting support is arranged on the side wall of the front end of the combustion chamber shell, and a rear connecting support is arranged on the side wall of the middle of the combustion chamber shell. A fixed shaft connecting hole is horizontally formed in the upper end of the front connecting bracket; a group of optional shaft connecting holes which are vertically distributed are horizontally formed in the upper end of the rear connecting bracket; the front connecting support is hinged to the front end of the belly of the unmanned aerial vehicle through a fixing shaft connecting hole, and the rear connecting support is hinged to the rear end of the belly of the unmanned aerial vehicle through a selectable shaft connecting hole. The angle between the axis of the rocket booster and the positioning surface of the belly of the unmanned aerial vehicle is adjusted by selecting the selectable shaft connecting holes in different vertical positions in the rear connecting support to be connected with the rear end of the belly of the unmanned aerial vehicle. According to the rocket booster, connection of the rocket booster and the rear connecting support optional shaft connecting holes is adjusted under different working conditions, and rapid adjustment of the thrust line is achieved.

    本发明公开了一种推力线可调结构固体火箭助推器,燃烧室壳体、助推器装药、前顶盖、喷管组件和点火组件;所述燃烧室壳体的前端侧壁设有前连接支架,所述燃烧室壳体中部侧壁设有后连接支架;所述前连接支架的上端水平开有一个固定轴连接孔,所述后连接支架的上端水平开有一组竖直分布的可选轴连接孔;所述前连接支架通过固定轴连接孔铰接在无人机机腹前端,所述后连接支架通过可选轴连接孔铰接在无人机机腹后端;通过选择所述后连接支架上不同竖直位置的可选轴连接孔与无人机机腹后端连接,实现调节所述火箭助推器的轴线与无人机机腹定位面的角度。本发明的火箭助推器,在不同工况下调整与后连接支架可选轴连接孔的连接,实现推力线快速调整。


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    Title :

    Solid rocket booster with thrust line adjustable structure


    Additional title:

    一种推力线可调结构固体火箭助推器


    Contributors:
    WEN ZHIWEI (author) / QU MANYI (author) / WEI XIAOLIN (author) / WANG QINGHUA (author) / LI WANHUI (author) / REN XIAOBIN (author) / GAO KANGJIAN (author) / MA XIAOKAO (author) / HAO YANJUN (author) / WANG YAN (author)

    Publication date :

    2024-02-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64U





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