The invention provides a supersonic low-resistance and low-sonic-boom configuration adopting a double-wing double-fuselage layout form, and belongs to the technical field of supersonic aircraft design. The problem that a traditional supersonic civil aircraft layout is limited in shock wave resistance reducing effect is solved. The aircraft comprises a left fuselage, a right fuselage, a front middle wing, wings, an end plate, a rear middle wing, an air inlet channel, an engine and a T tail. The inner sides of the left fuselage and the right fuselage are contracted into non-axisymmetric structures and are fixedly connected through the front middle wing and the rear middle wing; the front middle wing is a single wing, and the rear middle wing is double wings; the wing and the rear middle wing are fixed into a double-wing structure, upper and lower wing bottom edges are parallel, vertex angles are opposite, and wing tips are fixed through an end plate; the air inlet channel is rectangular and is arranged between the upper wing and the lower wing, and an engine is arranged in the air inlet channel; the tails of the left and right fuselages are fixed through a T tail. The problem that the shock wave resistance reduction effect of a traditional supersonic civil aircraft layout is limited is solved, the shock wave resistance generated in the flight process is reduced, and the sound detonation intensity influence can be reduced.

    本发明提出一种采用双翼双机身布局形式的超声速低阻低声爆构型,属于超声速飞行器设计技术领域。目的是解决传统超声速民机布局对于降低激波阻力效果有限问题。本发明包括左机身、右机身、前中间翼、机翼、端板、后中间翼、进气道、发动机、T尾;左、右机身内侧收缩为非轴对称结构,通过前、后中间翼固定连接;前中间翼为单翼,后中间翼为双翼;机翼与后中间翼固定为双翼结构,上、下翼底边平行,顶角相对,翼尖通过端板固定;进气道为矩形安装在上、下翼之间,进气道内安装有发动机;左、右机身尾部有尾翼通过T尾固定。本发明解决了传统超声速民机布局对于降低激波阻力效果有限问题,降低飞行过程中产生的激波阻力,有利于减小声爆强度影响。


    Access

    Download


    Export, share and cite



    Title :

    Supersonic-speed low-resistance low-sonic-explosion configuration adopting double-wing double-fuselage layout form


    Additional title:

    一种采用双翼双机身布局形式的超声速低阻低声爆构型


    Contributors:
    LI QI (author) / WANG DI (author) / QIAN ZHANSEN (author) / DUAN JIAXIN (author) / ZHANG SHENG (author)

    Publication date :

    2025-03-25


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Double-fuselage tandem rotor wing composite wing aircraft layout

    YANG WEI / YU LEI / WU WENHUA et al. | European Patent Office | 2021

    Free access

    Hybrid laminar flow wing suitable for double-fuselage layout demonstrator

    WANG ZHONGYU / ZHANG JIAN / GENG JIANZHONG et al. | European Patent Office | 2020

    Free access

    Supersonic speed jet adopting supersonic speed double wings and variant design

    ZHAO CHANGHUI / YANG YANTONG / TANG MINGYUAN et al. | European Patent Office | 2025

    Free access


    Aircraft with double-fuselage tandem wing vertical take-off and landing layout

    YANG XIAOCHUAN / FU ZHI / XIAO HANSHAN et al. | European Patent Office | 2020

    Free access