The invention discloses a horizontal-tail-free high-stealth aerodynamic layout pitching moment pitch-up suppression method, and belongs to the technical field of aerodynamic design of aviation aircrafts. Edging is conducted on the lateral edge of the front fuselage, rounding is conducted along the lateral edge line of the front fuselage, small-radius smooth transition is achieved, and the edging effect of the lateral edge of the front fuselage is reduced; the plane shape of the wing adopts a Lamda wing, the Lamda wing comprises an inner wing section and an outer wing section, and the inner wing section and the outer wing section form a lambda shape; the trailing edge of the inner wing section of the Lamda wing is swept forward, the inner side area of the trailing edge of the wing is increased, the effect of partially replacing a horizontal tail is achieved, and the aerodynamic focus is changed by designing parameters of the Lamda wing. According to the invention, the edging of the fuselage edge is realized by rounding the lateral edge of the front fuselage, and the flowing characteristic of the upper surface of the wing is changed, so that the pitch angle of pitch moment is delayed by 1 degree when the aircraft is at a low speed and a large angle of attack; the designed Lamda wings can generate larger head lowering torque at a large incidence angle, so that the pitching moment and the pitching incidence angle are delayed by more than 1 degree at the low speed and the large incidence angle of the aircraft; and the stealth performance of the whole aircraft is not influenced.

    无平尾高隐身气动布局俯仰力矩上仰抑制方法,属于航空飞行器气动力设计技术领域。前机身侧棱去边条化,并沿前机身侧棱线倒圆,实现小半径光滑过渡,减少前机身侧棱的边条效应;机翼平面形状采用兰姆达机翼,所述的兰姆达机翼包括内翼段和外翼段,二者构成“λ”形状;兰姆达机翼内翼段后缘前掠,增大机翼后缘内侧面积,部分代替平尾的作用,通过设计兰姆达机翼参数,改变气动焦点。本发明采用前机身侧棱倒圆的方式实现机身边缘的去边条化,改变了机翼上表面的流动特征,使飞机低速大迎角时俯仰力矩上仰迎角推迟1°;所设计的兰姆达机翼,在大迎角时产生更大的低头力矩,使飞机低速大迎角时俯仰力矩上仰迎角推迟1°以上;对全机隐身性能无影响。


    Access

    Download


    Export, share and cite



    Title :

    Flat-tail-free high-stealth aerodynamic layout pitching moment pitch-up suppression method


    Additional title:

    无平尾高隐身气动布局俯仰力矩上仰抑制方法


    Contributors:
    CHENG SHIXIN (author) / GE CHANGJIE (author) / TAO XIAOYANG (author) / WANG XIAO (author) / MEI XIAOYIN (author) / LIU JIANG (author) / WANG KELONG (author) / LI XIANKAI (author)

    Publication date :

    2025-01-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    Aerodynamic layout of supersonic high-maneuverability stealth target

    HAN SHANSHAN / FENG XIAOQIANG / QUAN JINGGE et al. | European Patent Office | 2022

    Free access

    Pitching moment due to rotation in pitch

    Halliday, Alfred S. / Bryant, L. W. / Burge, C. H. | TIBKAT | 1933


    Unsteady Aerodynamic Characteristics of Pitching Flat Plates at Low Reynolds Numbers

    Badrya, Camli / Govindarajan, Bharath / Medina, Albert et al. | AIAA | 2021


    LOW REYNOLDS NUMBER UNSTEADY AERODYNAMIC OVER A PITCHING-PLUNGING FLAT PLATE

    Hart, A. / Ukeiley, L. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2010


    Dynamic Pitching Moment Measurement of a Wing Executing Pitch and Plunge Motion

    Goal, Kevin / Sun, Daniel / Raghav, Vrishank et al. | AIAA | 2012