The invention discloses a control method, system and device for a rotor blade of a variable sweepback wing, and relates to the field of rotor blades. The method comprises the following steps: acquiring azimuth angles of first and second paddles; judging whether the azimuth angles of the first blade and the second blade are not within a preset range or not to obtain a first judgment result; if the first judgment result is yes, returning to the previous step; if the first judgment result is no, the sweepback device of the paddle corresponding to the azimuth angle set in the preset range is a to-be-adjusted sweepback device, and the resistance value of the to-be-adjusted sweepback device is obtained; judging whether the resistance value is greater than a preset resistance threshold value or not to obtain a second judgment result; if the second judgment result is yes, the blade tip speed and the forward flying speed generated by rotation of the to-be-adjusted sweepback device are obtained, and the sweepback control angle is calculated; performing sweepback control on the to-be-adjusted sweepback device according to the sweepback control angle; and returning to obtain the resistance value of the to-be-adjusted sweepback device until the azimuth angle is not within the preset range, and performing sweepback on the local high-speed region to realize noise reduction of the high-speed pulse noise.

    本发明公开一种可变后掠翼的旋翼桨叶的控制方法、系统及装置,涉及旋翼桨叶领域;方法包括:获取第一、二桨叶的方位角;判断第一、二桨叶的方位角是否均不在预设范围内,得第一判断结果;第一判断结果为是,返回上一步骤;第一判断结果为否,设在预设范围内的方位角对应的桨叶的后掠器为待调整后掠器,获取待调整后掠器的阻力值;判断阻力值是否大于预设阻力阈值,得第二判断结果;第二判断结果为是,获取待调整后掠器的旋转产生的桨尖速度和前飞速度,计算后掠控制角度;根据后掠控制角度对待调整后掠器进行后掠控制;返回“获取所述待调整后掠器的阻力值”,直到方位角不在预设范围内,本发明对局部高速区进行后掠,实现高速脉冲噪声的降噪。


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    Titel :

    Control method, system and device for rotor blade of variable sweepback wing


    Weitere Titelangaben:

    一种可变后掠翼的旋翼桨叶的控制方法、系统及装置


    Beteiligte:
    CHEN XI (Autor:in) / SHI NAIRUI (Autor:in) / ZHAO QIJUN (Autor:in) / BAO WEICHENG (Autor:in) / ZHAO GUOQING (Autor:in) / CHEN ZHE (Autor:in) / LIN MUYANG (Autor:in)

    Erscheinungsdatum :

    2023-07-04


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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