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考虑了襟翼偏转对桨叶剖面有效迎角及旋翼尾迹结构的影响,建立了电控旋翼自由尾迹入流模型,并结合电控旋翼带襟翼翼型气动力模型、桨叶挥舞运动模型、旋翼配平模型,建立了一种电控旋翼气动特性分析方法。利用该方法,对某样例电控旋翼悬停和前飞状态的气动特性进行了计算,并将电控旋翼与常规旋翼的气动特性进行了对比分析。结果表明,悬停时,配平所需的电控旋翼襟翼偏角幅值随拉力增加而增加;前飞时,电控旋翼后行桨叶剖面迎角比常规旋翼更大,更可能发生失速。
Considering the effect of flap deflection on the effective angle of attack and the wake structure of rotor blade, a free-wake inlet model of the electronically controlled rotor is established. Combined with the aerodynamic model of the wing with wings, the waving motion model of the blade, Model, a method of analyzing the aerodynamic characteristics of the electronically controlled rotor is established. By using this method, the aerodynamic characteristics of an electronically controlled rotor hovering and forward flying state are calculated, and the aerodynamic characteristics of the electronically controlled rotor and the conventional rotor are compared. The results show that when hovering, the amplitude of the deflection angle of the electronically controlled rotor blade required for trim increases with the increase of the pulling force. When the rotorcraft is in hovering, the angle of attack of the rear rotor blade is larger than that of a conventional rotor and is more likely to stall .