共轴刚性旋翼高速直升机旋翼操纵策略分析

摘要

In order to research on the effect of lateral cyclic pitch differential and rotor control phase angle on the flight dynamic characteristics of coaxial rigid rotor high-speed helicopter .By using the validated flight dynamic mod-el of XH-59 helicopter , analyze the influence of lateral cyclic pitch differential and rotor control phase on the trim characteristics , maximum hub bending moment of upper and lower rotors and power required under helicopter mode and compound mode .The results show:with growing up of forward speed , increasing lateral cyclic pitch differential and decreasing rotor control phase angle can augment the trim pitch attitude , reduce the trim collective pitch and power required of helicopter mode and compound mode .Decreasing lateral cyclic pitch differential and increasing rotor control phase angle can lower the maximum hub bending moment .Comparing with lateral cyclic pitch differen-tial, increasing rotor control phase angle cause the trim longitudinal cyclic pitch rapidly increase even exceed the limitation.Meanwhile, lateral cyclic pitch differential can do better in adjusting the power required and hub bending moment.%为研究横向周期变距差动和旋翼控制相位角2种旋翼冗余操纵策略对共轴刚性旋翼高速直升机飞行动力学特性的影响,利用经过验证的XH-59直升机飞行动力学模型,在直升机和复合推进2种飞行模式下,分析了横向周期变距差动和旋翼控制相位角对共轴刚性旋翼高速直升机配平特性;上、下旋翼桨毂最大弯矩以及需用功率的影响.结果表明:随着前飞速度的增加,提高横向周期变距差动和降低旋翼控制相位角会减小直升机模式下的低头姿态,降低直升机和复合推进模式下的配平总距和需用功率.降低横向周期变距差动和提高旋翼控制相位角有利于降低2种模式下的最大桨毂弯矩.随着前飞速度增加,相比于调节横向周期变距差动,改变旋翼控制相位角会明显增加2种模式下配平纵向周期变距,甚至使其超过限幅.同时,采用横向周期变距差动对调节直升机需用功率和桨毂处弯矩的效果更为明显.