The invention provides an aircraft nose fairing structure and an aircraft attitude control method. The front end of a fairing is of a conical cover structure, a fairing body is a cylindrical cover, radial rectification wings are arranged on the outer side of the rear end of the cylindrical cover and comprise fixed wings and movable wings, and the fixed wings and the movable wings are connected through transmission shafts; a driving device of the movable wing is arranged in the cylindrical cover and drives the movable wing to deflect relative to the fixed wing through the transmission shaft, so that pitching-up, pitching-down, left turning, right turning, clockwise turning and anticlockwise turning of the nose of the aircraft are realized, and the maneuverability of the aircraft is improved.

    本申请提供一种飞机机头整流罩结构及飞机姿态控制方法,整流罩的前端为锥形罩结构,整流罩主体为圆柱形罩,在圆柱形罩的后端外侧设有放射状的整流翼,该整流翼含有固定翼和活动翼,固定翼和活动翼通过传动轴连接,在圆柱形罩内设有活动翼的驱动装置,驱动装置通过传动轴驱动活动翼相对固定翼发生偏转,实现飞机机头的上仰、下俯、左转、右转、顺时针翻转、逆时针翻转运动,提高飞机的机动性。


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    Title :

    Aircraft nose fairing structure and aircraft attitude control method


    Additional title:

    一种飞机机头整流罩结构及飞机姿态控制方法


    Contributors:
    DU KUNPENG (author) / NIU BOYA (author) / YANG CHENGLI (author) / CHEN YONG (author)

    Publication date :

    2021-08-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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