The invention discloses a micro unmanned aerial vehicle applying a grid rudder and a control method, and belongs to the field of attitude control of micro aircrafts. The unmanned aerial vehicle adopts a cylindrical shell, four grid rudder surfaces are uniformly distributed at the bottom of the cylindrical unmanned aerial vehicle shell in a horizontal installation mode, the symmetric center of the four grid rudder surfaces and the gravity center of the unmanned aerial vehicle are located on the same vertical line, a propeller of the unmanned aerial vehicle is located above the top of the cylindrical unmanned aerial vehicle shell, and the grid rudder surfaces are installed at the bottom of the unmanned aerial vehicle and used for attitude control of the unmanned aerial vehicle. Compared with a single-plate rudder surface on a conventional small unmanned aerial vehicle, the grid rudder surface has more excellent aerodynamic characteristics, has more excellent control performance when being applied to the small unmanned aerial vehicle, and can effectively reduce the influence of crosswind. Through numerical simulation, flight tests are respectively carried out in windless and windy environments, and simulation calculation and test results both verify that the aerodynamic characteristics and the control performance of the grid rudder surface are better than those of the conventional single-plate rudder surface.

    本发明公开了一种运用栅格舵的微小型无人机及控制方法,属于微小型飞行器姿态控制领域。无人机采用圆筒状外壳,四个栅格舵面以水平安装方式均匀分布在圆筒状无人机外壳底部,四个栅格舵面的对称中心与无人机的重心在同一竖直线上,无人机的螺旋桨在圆筒状无人机外壳顶部上方,栅格舵面安装于无人机的底部用于无人机的姿态控制。本发明栅格舵面与常规小型无人机上的平板舵面相比,具有更加优越的气动特性,运用于微小型无人机具有更加优越的控制性能并能够有效的减少侧风的影响。本发明通过数值仿真、在无风以及有风环境下分别进行飞行测试,仿真计算以及测试结果均验证了栅格舵面的气动特性以及控制性能比常规平板舵面更加优越。


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    Titel :

    Micro-miniature unmanned aerial vehicle applying grid rudder and control method


    Weitere Titelangaben:

    运用栅格舵的微小型无人机及控制方法


    Beteiligte:
    CAI CHENXIAO (Autor:in) / ZHANG YONG (Autor:in) / MENG GAOJU (Autor:in) / YANG YI (Autor:in) / YANG ZHE (Autor:in) / GUO ZIHENG (Autor:in) / XU BEN (Autor:in) / YAO JUAN (Autor:in) / ZOU YUN (Autor:in) / BAI XIANSHUAI (Autor:in)

    Erscheinungsdatum :

    02.11.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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