The invention relates to a helicopter rotor wing type stall control method and system. The helicopter rotor wing type stall control method is characterized in that synthetic jet vibration exciters arearranged within the range of 0.7 R to0. 9R on propeller blades and at positions of 15% c away from the front edges of the propeller blades, the distance between the synthetic jet vibration exciters is about 2.6% R, wherein the R is the span of the propeller blade, and the c is the chord length. The method comprises the steps: acquiring current operation parameters of a driver and current flight state parameters of an airplane; determining an instantaneous attack angle of a helicopter rotor wing according to the current operation parameters of the driver and the current flight state parametersof the aircraft; determining a stall angle of attack according to the current flight state parameters of the aircraft; judging whether the instantaneous angle of attack is greater than the stall angle of attack or not, if so, starting the synthetic jet vibration exciters, and controlling the trailing edge winglet at 0.7 R-0. 9R on the paddle to deflect upwards by 0-5 degrees; and if not, turningoff the synthetic jet vibration exciters, and controlling the trailing edge winglet at the 0.7 R-0. 9R position on the paddle to deflect downwards by 0-5 degrees. With the control method and system provided by the invention, the aerodynamic characteristics of the rotor wing can be efficiently improved and the dynamic stall of the rotor wing can be controlled.

    本发明涉及一种直升机旋翼翼型失速控制方法及系统。所述直升机旋翼翼型失速控制方法,在桨叶上的0.7R~0.9R范围内和距离桨叶前缘15%c处布置合成射流激振器,合成射流激振器的间距约为2.6%R,R为桨叶的展长,c为弦长,包括:获取驾驶员当前操作参数以及飞机当前飞行状态参数;根据驾驶员当前操作参数以及飞机当前飞行状态参数确定直升机旋翼的瞬时迎角;根据飞机当前飞行状态参数确定失速迎角;判断瞬时迎角是否大于失速迎角,若是,开启合成射流激振器,并同时控制桨叶上0.7R~0.9R处后缘小翼向上偏转0~5度;若否,关闭合成射流激振器,并同时控制桨叶上0.7R~0.9R处的后缘小翼向下偏转0~5度。采用本发明所提供控制方法及系统,能够高效提升旋翼气动特性及控制旋翼动态失速。


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    Title :

    Helicopter rotor wing dynamic stall control method and system


    Additional title:

    一种直升机旋翼动态失速控制方法及系统


    Contributors:
    SHI YONGJIE (author) / LI CONGCONG (author) / XU GUOHUA (author) / LI RONGHAI (author)

    Publication date :

    2020-07-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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