共轴刚性旋翼直升机旋翼控制相位角问题分析

Rotor control phase angle analysis for coaxial rigid rotor helicopter

利用共轴刚性旋翼直升机飞行动力学模型,以XH-59A共轴刚性旋翼直升机为研究对象,分析了旋翼控制相位角对纵向配平特性、需用功率以及上、下旋翼桨毂弯矩的影响。基于分析结果,提出了一种针对共轴刚性旋翼直升机的旋翼控制相位角的配置方法。该配置方法以降低直升机需用功率为目标,并保证上、下旋翼桨毂弯矩和配平特性满足要求。通过该方法能使XH-59A直升机在0~80 m/s的飞行速度范围内满足上、下旋翼最大桨毂弯矩和纵向操纵限幅的要求,并且能最多降低8%的直升机需用功率,为共轴刚性旋翼直升机的设计提供了参考依据。

Adopting the flight dynamic model of coaxial rigid rotor helicopter, this paper sets the XH-59A coaxial rigid rotor helicopter as research object and analyzes the influence of rotor control phase angle on longi- tudinal trim characteristics, helicopter power required and hub bending moment of upper and lower rotor. Based on the analysis results, this paper proposes the allocation method of coaxial rigid rotor helicopter＇ s rotor control phase angle. It aims to decrease the helicopter power required and make upper and lower rotor＇ s hub bending moment and trim characteristics meet the requirement. The method can make the XH-59A helicopter satisfy the requirements of hub bending moment of upper and lower rotor and longitudinal cyclic pitch limita- tion within the flight speed scope of 0 -80 m/s, and can minimize up to 8% power required. This method pro- vides reference for design of coaxial rigid rotor helicopter.