摘要
端齿式折叠机构可以实现尾水平轴系的折叠,增加航空母舰上停靠舰载直升机的数量;同时,端齿式折叠机构对直升机尾传动轴系振动特性也会产生一定影响。建立了舰载直升机端齿式折叠型尾水平轴系动力学模型,求解分析了轴系各支承处振动响应。首先,分别基于有限元法与应变能法对折叠机构中花键连接部分及端齿连接部分进行等效简化,将花键连接部分等效为径向刚度及转角刚度,端齿连接部分等效为等效环,建立端齿式折叠机构的动力学模型,并通过与有限元仿真对比模态分析结果的方法以验证建模方法的准确性;在此基础上,将折叠装置动力学模型耦合到尾水平轴系中,建立折叠型尾水平轴系动力学模型,求解并分析了轴系振动特性。研究结果表明,各支承中,位移响应最大的在关节轴承处,最小的在主减输出端轴承处;振动响应与支承位置及其刚度阻尼特性有关。该研究可为轴系支承配置研究提供理论指导。
An end gear folding mechanism allows for folding of the tail horizontal shaft system,increasing the number of shipboard helicopters that can be docked on aircraft carriers.At the same time,the end gear folding mechanism affects the vibration characteristics of the helicopter tail horizontal shaft system.A dynamic model of a shipboard helicopter end-tooth folding tail horizontal shaft system was established,and the vibration response of each support of the shaft system was solved and analyzed.Firstly,based on the finite element method and the strain energy method,the equivalent simplification of the spline connection part and the end-tooth connection part in the folding mechanism was carried out respectively,the spline connection part was equivalent to the radial stiffness and the corner stiffness,the end-tooth connection part was equivalent to the equivalent ring,the dynamics model of the end-tooth folding mechanism was established,and the accuracy of the modeling method was verified by comparing the modal analysis results with the finite element simulation.On this basis,the folding device dynamics model was coupled to the tail horizontal shaft system,and the folding tail horizontal shaft system dynamics model was established to solve and analyze the vibration characteristics of the shaft system.The results of the study show that in each support,the largest displacement response is at the joint bearing,and the smallest is at the main reduction output end bearing.The vibration response is related to the support position and its stiffness damping characteristics.This study provides theoretical guidance for the study of the shaft system support configuration.
作者
李苗苗
张昭
朱如鹏
王希
梁福东
Li Miaomiao;Zhang Zhao;Zhu Rupeng;Wang Xi;Liang Fudong(National Key Laboratory of Science and Technology on Helicopter Transmission,Nanjing University of Aeronautics and Astronautics,Nanjing 210000,China;Aero Engine Academy of China,Zhuzhou 412000,China)
出处
《机械传动》
北大核心
2024年第10期1-10,共10页
Journal of Mechanical Transmission
关键词
折叠机构
尾水平轴系
振动响应
舰载直升机
Folding mechanism
Tail horizontal shaft system
Vibration response
Shipboard helicopter
作者简介
李苗苗(1981-),女,江苏徐州人,博士,主要研究方向为直升机传动系统设计技术与机械传动,limiaomiao@nuaa.edu.cn。
