The invention discloses a laterally-arranged single-vertical-fin patrolling device with a vertical fin unfolding device, which is characterized in that a vertical fin is fixedly connected with a vertical fin rotating shaft and a tension spring hook, an elastic check ring is sleeved on the vertical fin rotating shaft, and the tension spring hook can slide in a guide groove of an elastic body side plate; the second end of the tension spring hook is connected with the first end of the tension spring, the second end of the tension spring is fixed in the bomb body, and when the vertical fin is in afolded state, the tension spring is in a stretched state. The single side-mounted foldable vertical fin is adopted in the patrolling device, the number of two vertical fins of a traditional patrolling device is reduced to one, the number of folding wing faces of the patrolling device is reduced while the requirement for course static stability is met, and therefore the structural weight of a missile body is reduced, and the number and complexity of folding mechanisms are reduced; according to the vertical fin unfolding device, a tension spring is adopted for providing driving force, frictionforce in the vertical fin rotating process is reduced by additionally arranging a roller pin end face bearing, vertical fin rotating limiting is achieved by reserving a guide groove in the side wall of the missile body, and the unfolding device is simple, reliable, light in weight and small in installation occupied space.

    本发明公开了一种具有垂尾展开装置的侧置单垂尾巡飞器,垂尾与垂尾转轴和拉簧挂钩固连,弹性挡圈套装在垂尾转轴上,拉簧挂钩可在弹身侧板的导向槽内滑动;拉簧挂钩的第二端与拉簧的第一端连接,拉簧的第二端固定在弹身内部,垂尾处于折叠状态时,拉簧处于拉伸状态。本申请中巡飞器采用单个侧置可折叠垂尾,将传统巡飞器的两个垂尾减少至一个,在保证航向静稳定性要求的同时减少了巡飞器的折叠翼面数量,从而减轻弹体结构重量、减少折叠机构数量和复杂度;垂尾展开装置采用拉簧提供驱动力,通过加装滚针端面轴承减小垂尾转动过程中的摩擦力,并通过在弹身侧壁预留导向槽实现垂尾转动限位,展开装置简单、可靠、重量轻,安装占用空间小。


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    Titel :

    Laterally-arranged single-vertical-fin patrolling device with vertical fin unfolding device


    Weitere Titelangaben:

    一种具有垂尾展开装置的侧置单垂尾巡飞器


    Beteiligte:
    LI YONGZE (Autor:in) / LU YONGGANG (Autor:in) / ZHAO XINLIANG (Autor:in) / TAO JIANGYUAN (Autor:in) / LI YONG (Autor:in) / QIAN LIXIN (Autor:in) / FENG GAOPENG (Autor:in) / CHEN WEI (Autor:in) / YUAN XIAOYA (Autor:in)

    Erscheinungsdatum :

    17.11.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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