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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。
Using the coaxial rigid rotor helicopter flight dynamics model and the XH-59A coaxial rigid rotor helicopter as the research object, the influence of the rotor phase angle control on the longitudinal trim characteristics, the required power and the bending moments of the upper and lower rotor hubs is analyzed. Based on the analysis results, a method of configuring the phase angle of rotor control for a coaxial rigid rotor helicopter is proposed. This configuration method aims to reduce the helicopter required power and to ensure that the upper and lower rotor hub bending moments and trim characteristics meet the requirements. By this method, the XH-59A helicopter can meet the requirements of the maximum hub bending moment and the longitudinal maneuvering limit of the upper and lower rotor blades in the range of 0 ~ 80 m / s flight speed, and can reduce the required power of the helicopter by up to 8% , Provides a reference for the design of coaxial rigid rotor helicopters.