The invention discloses an attitude controllable module unit, an aircraft and an attitude control method. The attitude controllable module unit comprises a jet thrust device, a direction regulation and control device, a bent pipe and a rack; the air injection thrust device is installed on the rack, the bent pipe is connected with an air injection opening of the air injection thrust device, air flow can be sprayed out along the bent pipe, and the bent pipe can be driven by a direction adjusting and controlling device arranged on the rack and can rotate around the axis of the end face in butt joint with the air injection opening. The attitude control method comprises the following steps: pitching motion control: enabling the first bent pipe and the second bent pipe to deflect forwards or backwards at the same time; transverse rolling motion control is conducted, specifically, the first bent pipe and the fourth bent pipe are made to deflect towards the two sides correspondingly; and yawing motion control: enabling the first bent pipe and the fourth bent pipe to deflect backwards at the same time, and enabling the second bent pipe and the third bent pipe to deflect forwards at the same time. The requirement for driving is reduced, the streamline of the fuselage is not damaged, pitching, yawing and rolling three-axis attitude control is achieved in a new mode, rapid maneuvering in the vertical take-off and landing stage can be achieved, and high-speed cruising can also be achieved.

    姿态可控模块单元、飞行器及姿态控制方法,姿态可控模块单元包含喷气推力装置、方向调控装置、弯管和机架;喷气推力装置安装在机架上,弯管与喷气推力装置的喷气口相连,气流可沿弯管喷出,弯管可由设置在机架上的方向调控装置驱动,弯管可绕与喷气口对接的端面轴线旋转,姿态控制方法包含俯仰运动控制:使第一弯管和第二弯管同时向前或向后偏转;横滚运动控制:使第一弯管和第四弯管分别向两侧偏转;偏航运动控制:使第一弯管和第四弯管同时向后偏转,第二弯管和第三弯管同时向前偏转。本发明降低了对驱动的需求,不会破坏机身的流线型,以新的方式实现俯仰、偏航、横滚三轴姿态控制,既可以实现垂直起降阶段时快速机动,也可以实现高速巡航。


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    Titel :

    Attitude controllable module unit, aircraft and attitude control method


    Weitere Titelangaben:

    姿态可控模块单元、飞行器及姿态控制方法


    Beteiligte:
    ZHAO JIE (Autor:in) / LIU BENSHAN (Autor:in) / GAO LIANG (Autor:in) / ZHU YANHE (Autor:in) / ZHANG JUNMING (Autor:in) / GAO YONGSHENG (Autor:in)

    Erscheinungsdatum :

    2022-06-03


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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