针对常规直升机桨叶不同的桨尖扭转分布设计引起的旋翼动载荷变化的问题，建立旋翼气弹动载荷分析模型并开展不同桨尖扭转分布的动载荷分析和试验分析。针对桨叶典型的细长柔性梁特征，基于柔性多体动力学框架建立旋翼结构动力学模型，并针对桨尖扭转对气动环境的影响，采用双峰自由尾迹方法建立旋翼气动模型，并进行方法验证。以BO105旋翼为研究对象，进行几种桨尖扭转分布下的旋翼气动和结构载荷影响分析。结果表明：增加桨叶线性负扭转有利于提高小速度状态下的旋翼整体气动效率，对旋翼动载荷影响较小。但前飞速度增加后，桨尖产生了负升力，旋翼动载荷增加。采用桨尖正扭设计和后掠布局设计都有利于降低旋翼动载荷水平，且4 m模型旋翼风洞试验结果也验证了采用桨尖正扭设计方案的桨毂垂向力动载荷水平更低。

A rotor aeroelastic loads computing method was adopted and rotor dynamics issue in high speed forward flight was analyzed, aimed at the problem of rotor dynamic load variation caused by different tip twist distribution design of conventional helicopter. With slender and flexible rotor blade, the rotor multi-body dynamics model was built with the Hamilton principle and the middle deformation beam theory. The aerodynamic model was built based on dual free wake model to catch the negative lift at blade tip. The computing method was validated and used in loads characteristic analysis with the influence of blade tip twist design. Taking the BO105 rotor as the research object, analyzed the aerodynamic and structural load effects of several blade tip twist distributions on the rotor. The results indicate that increasing the linear negative twist of the blade is beneficial for improving the overall aerodynamic efficiency of the rotor at low speeds, with minimal impact on the rotor's dynamic load. But as the forward flight speed increases, the blade tip generates negative lift and the rotor dynamic load increases. Both the forward twist design of the blade tip and the swept back layout design are beneficial for reducing the dynamic load level of the rotor, and the wind tunnel test results of the 4 m model rotor also verify that the vertical force dynamic load level of the hub using the forward twist design of the blade tip is lower.