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理论计算和实验测量表明,共轴式直升机在悬停、前飞状态下,上下旋翼桨盘处轴向诱导速度分布与单旋翼直升机的相类似,本文根据共轴式直升机双旋翼这一特点,引入气动力相互干扰因子,将单旋翼直升机一阶谐波形式的Pitt-Peters静态非均匀入流模型推广到共轴式直升机,建立了一种共轴双旋翼载荷计算模型,为共轴式直升机飞行动力学建模作前期准备。以某共轴双旋翼为研究对象进行载荷计算,并与国外计算结果进行了对比,两者吻合较好。
Theoretical calculations and experimental measurements show that the axial induced velocity distribution of the co-axial helicopters in the hovering and pre-fly state is similar to that of the single-rotor helicopters. According to the characteristics of the coaxial helicopter twin-rotor, By introducing the aerodynamic interference factor, the Pitt-Peters static inhomogeneous inflow model of the first-order single-rotor helicopter harmonic is extended to the coaxial helicopter. A co-axial twin-rotor load calculation model is established for co-axial helicopter flight Kinetic modeling for pre-preparation. Taking a coaxial double-rotor as the research object, the load calculation is carried out and the results are compared with those obtained from foreign countries. The two agree well with each other.