基于自由尾迹方法的电控旋翼气动特性分析

摘要

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.%For establishing an aerodynamic characteristics analysis method of the electrically controlled rotor, a free wake model of electrically controlled rotor is developed.The effect of the trailing edge flap on the effective angle of attack and the geometrical structure of rotor wake is considered.The blade flapping model, blade lifting model, wind tunnel trim model are also included in the method.The aerodynamic characteristics of the electrically controlled rotor are compared with that of the baseline rotor.In hover, the amplitude of the flap angle required for trim increases as the thrust increases.In forward flight, because of the large negative lift contribution from the trailing edge flap, the electrically controlled rotor has higher sectional angle of attack than the baseline rotor has.