본 발명은, 피치축(pitch axis)의 r/R에 따른 x축 방향 위치는 아래 [식 1]로 표현되고, 상기 피치축의 r/R에 따른 z축 방향 위치는 아래 [식 2]로 표현되는 것을 특징으로 하는 쿼드틸트로터 무인기의 블레이드를 제공한다. [식 1][식 2]본 발명은 쿼드틸트로터 블레이드 형상을 최적 설계함으로써, 소요동력을 최소화하고 성능효율을 증가시키면 무인기의 성능 증가를 향상시킨 효과가 발생한다.

    The present invention relates to a blade of a quad tilt rotor unmanned aerial vehicle. A position in an X-axis direction of a pitch axis in accordance with an r/R is expressed by the below formula 1. A position in a Z-axis direction of the pitch axis in accordance with an r/R is expressed by the below formula 2. [Formula 1] [Formula 2] The present invention is able to draw an optimal design of the shape of the blade for the quad tilt rotor, to minimize a used power, to increase a performance efficiency, and to improve an increase in performance of the unmanned aerial vehicle.


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    Titel :

    BLADE FOR QUAD-TILT ROTOR UNMANNED AERIAL VEHICLES


    Weitere Titelangaben:

    쿼드틸트로터 무인기의 블레이드


    Erscheinungsdatum :

    28.08.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Koreanisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge




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