The present invention relates to a rotor device for a coaxial counter-rotating aircraft, which operates as at least a part among a collective control input, a cyclic control input, and a yawing control input is co-linked. According to an embodiment of the present invention, the rotor device for a coaxial counter-rotating aircraft can simplify a component of a rotor unit by separating the collective control input and the cyclic control input. According to the present invention, the rotor device for a coaxial counter-rotating aircraft can minimize an additional component composition for yaw control by linking a device for the yaw control of an aircraft to a device for the collective control input. The rotor device for a coaxial counter-rotating aircraft includes a first rotor unit, a second rotor unit, a gearbox, and a link assembly.

    콜렉티브 조종 입력과 사이클릭 조종입력 및 요잉 조종 입력 중 적어도 일부가 co-link 되어 작동되는 동축반전 비행체의 로터장치에 관한 것이다. 본 발명의 일 실시예에 의한 동축반전 비행체의 로터장치는 콜렉티브 조종 입력(Collective Control Input) 및 사이클릭 조종 입력(Cyclic Control Input)을 분리함으로써, 로터유닛의 구성품을 단순화할 수 있게 된다. 본 발명에 따른 동축반전 비행체의 로터장치는 비행체의 요 컨트롤(Yaw Control)을 위한 장치를 콜렉티브 조종 입력(Collective Control Input)을 위한 장치와 연계하여, 요 컨트롤(Yaw Control)을 위한 추가 부품 구성을 최소화할 수 있다.


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    Titel :

    ROTOR APPARATUS OF COAXIAL COUNTER-ROTATING AIRCRAFT


    Weitere Titelangaben:

    동축반전 비행체의 로터 장치


    Beteiligte:
    LEE SEONG HAK (Autor:in)

    Erscheinungsdatum :

    10.01.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Koreanisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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