The invention discloses a flap aileron linkage system and an aircraft, the flap aileron linkage system comprises two flap ailerons, two push-pull flexible shafts, a flap aileron control mechanism and a flap aileron linkage mechanism; the two push-pull flexible shafts are used for being installed on a vehicle body, and the two push-pull flexible shafts are in one-to-one transmission connection with the two flap ailerons. The flap aileron control mechanism is in driving connection with the two push-pull flexible shafts and used for driving the two flap ailerons to rotate around the corresponding axis through the two push-pull flexible shafts, and the rotating directions and angles of the two flap ailerons are different so as to control the steering of the aircraft; and the flap aileron linkage mechanism is in driving connection with the two push-pull flexible shafts and used for driving the two flap ailerons to synchronously rotate around an axis through the two push-pull flexible shafts, and the synchronous rotation directions and angles of the two flap ailerons are the same so as to assist in adjusting the lifting pressure of the aircraft. According to the technical scheme, the problem that an existing aircraft cannot take off and land in a short distance is solved.

    本发明公开一种襟副翼联动系统和飞行器,其中,襟副翼联动系统包括两襟副翼、两推拉软轴、襟副翼控制机构以及襟副翼联动机构;两推拉软轴用于安装于机体上,两所述推拉软轴与两所述襟副翼一对一传动连接;襟副翼控制机构与两所述推拉软轴驱动连接,用于通过两所述推拉软轴驱动两所述襟副翼各自绕一轴线转动,两所述襟副翼转动的方向和角度不同,以控制飞行器的转向;襟副翼联动机构与两所述推拉软轴驱动连接,用于通过两所述推拉软轴驱动两所述襟副翼绕一轴线同步转动,且两所述襟副翼同步转动的方向和角度相同,以辅助调节飞行器的升降压力。本发明技术方案解决现有飞行器无法实现短距起飞和降落的问题。


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    Title :

    Flap aileron linkage system and aircraft


    Additional title:

    襟副翼联动系统和飞行器


    Contributors:
    CHEN MO (author)

    Publication date :

    2021-04-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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