The invention discloses a tilt rotor aircraft and a control method thereof, and belongs to the technical field of rotorcrafts, the tilt rotor aircraft comprises a fuselage, wings are respectively arranged on two sides of the middle position of the fuselage, head rotor groups are respectively arranged on two sides of the head position of the fuselage, tail rotor groups are respectively arranged on two sides of the tail position of the fuselage, and the wings are provided with middle rotor groups. Comprising three control modes including a helicopter mode, a transition mode and a fixed wing mode, by designing a tilt rotor scheme with a high safety coefficient, the design difficulty and the structural complexity of the rotor aircraft in a flight control system are reduced, and then the stability and the safety of the rotor aircraft are improved.

    本发明公开了一种倾转旋翼飞行器及其控制方法,属于旋翼机的技术领域,包括机身,机身中部位置的两侧分别设有机翼,机身头部位置的两侧分别设有头部旋翼组,机身尾部位置的两侧分别设有尾部旋翼组,机翼设有中部旋翼组。包括直升机模式、过渡模式和固定翼模式三种控制模式,通过设计一种高安全系数的倾转旋翼方案,降低旋翼飞行器在飞行控制系统设计的难度和结构的复杂性,进而提高旋翼飞行器的稳定性和安全性。


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    Title :

    Tilt-rotor aircraft and control method thereof


    Additional title:

    一种倾转旋翼飞行器及其控制方法


    Contributors:
    CHENG CHENG (author) / LI TAOLIN (author)

    Publication date :

    2025-04-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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