摘要
研究了Johnson提出的倾转旋翼不平衡载荷前飞动力学模型,将其桨叶分析方法应用于直升机旋翼系统模态分析。在刚性条件假设下推导了直升机旋翼弹性阻尼和惯性力综合作用时桨叶的挥舞和摆振运动方程,给出了固定和旋转坐标系下对应的运动方程。通过引入均匀入流和线性扭转假设,获得了运动方程的理论解析解。利用叠加原理,得到了桨毂轴心运动方程;采用Newmark法进行振动微分方程求解,最终得到了直升机旋翼的轴心运动轨迹。以某型直升机旋翼系统为例,验证了本研究所提出旋翼桨叶模态分析方法的准确性,给出了兼顾计算精度和效率的最佳求解步长选取方法;预测了典型飞行状态下的桨毂轴心运动轨迹,为直升机旋翼系统设计提供了基础方法和技术参考。
This paper studies the forward flight dynamic model of tilt rotor unbalanced load proposed by Johnson,and applies its blade analysis method to the modal analysis of helicopter rotor system.Under the assumption of rigidity,the flapping and shimmy motion equations of helicopter rotor blade under the combined action of elastic damping and inertial force are derived,and the corresponding motion equations in fixed and rotating coordinate systems are given.By introducing the assumption of uniform inflow and linear torsion,the theoretical analytical solution of the equation of motion is obtained.Then,using the superposition principle,the axial motion equation of the hub is obtained;Newmark method is used to solve the vibration differential equation,and finally the axis motion trajectory of helicopter rotor is obtained.Taking a helicopter rotor system as an example,the accuracy of the rotor blade modal analysis method proposed in this paper is verified,and the optimal solution step selection method considering both calculation accuracy and efficiency is given.The hub axis trajectory under typical flight state is predicted,which provides a basic method and technical reference for the design of helicopter rotor system.
作者
张永杰
王浩东
曹康
李治权
宋来收
ZHANG Yongjie;WANG Haodong;CAO Kang;LI Zhiquan;SONG Laishou(School of Aeronautics,Northwestern Polytechnical University,710072 Xi'an,China;Chinese Aeronautical Establishment,100029 Beijing,China;School of Aeronautics,Nanjing University of Aeronautics and Astronautics,210016 Nanjing,China)
出处
《应用力学学报》
CAS
CSCD
北大核心
2022年第3期437-444,共8页
Chinese Journal of Applied Mechanics
基金
国家级科项项目(No.2019KF010059)
国家自然科学基金资助项目(No.11972301)。
