The invention provides an aircraft tail structure for stability augmentation and drag reduction, the aircraft tail is a ship-shaped tail, double-triangle empennages are distributed around the aircrafttail, and each empennage comprises an inner wing and an outer wing; the inner wing is fixedly connected with the tail part of the aircraft into a whole, and the outer wing is connected with the innerwing and is a movable control surface. The ship-shaped aircraft tail can be basically not limited by a steering engine, effective contraction from the engine body to the nozzle is completed, and thepurpose of reducing the bottom area and bottom resistance of an aircraft is achieved. Effective contraction is completed, the length of the tail of the aircraft does not need to be increased, and thelength of the aircraft can be reduced or the installation space of other parts can be increased. The steering engine bulges and the empennage inner wings are integrally designed, so that the lift force and the stability of the whole aircraft are improved, the flight resistance of the steering engine bulges is reduced, and the lift-drag ratio of the whole aircraft is increased.

    本发明提供一种增稳减阻的飞行器尾部构型,飞行器尾部为船型尾部,飞行器尾部的周身分布有“双三角”尾翼,所述尾翼包括:内翼和外翼;所述内翼与所述飞行器尾部固连一体,所述外翼与所述内翼连接,为可动舵面。本发明提供的船型飞行器尾部,可以基本不受舵机限制,完成发动机主体到喷口的有效收缩,达到减小飞行器底部面积与底阻的目的。完成有效收缩,不需要不延长飞行器尾部长度,可以减小飞行器长度或增大其它部件安装空间。舵机鼓包与尾翼内翼一体设计,既增加全飞行器升力与全飞行器稳定性,又减小舵机鼓包的飞行阻力,从而提高全飞行器升阻比。


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    Title :

    Aircraft tail configuration for stability augmentation and drag reduction


    Additional title:

    一种增稳减阻的飞行器尾部构型


    Contributors:
    LUO SHUAI (author) / ZHAO XIAOYONG (author) / ZHOU XIAOHUA (author) / QI LONG (author) / YANG HUILIN (author) / LI JUANJUAN (author) / LI LI (author) / XIE LIYUN (author) / CHENG YI (author)

    Publication date :

    2021-02-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge




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