滑橇式直升机地面共振非线性时域仿真  

Nonlinear Time-Domain Simulation for Skid Helicopter Ground Resonance

作　　者：吴靖 刘湘一 宋山松 WU Jing;LIU Xiangyi;SONG Shansong(School of Basic Science for Aviation,Naval Aviation University,Yantai 264001,China)

机构地区：[1]海军航空大学航空基础学院,烟台264001

出　　处：《南京航空航天大学学报》2024年第2期234-241,共8页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：为研究非线性因素对滑橇式直升机地面共振的影响,针对滑橇式起落架弹性结构及机体阻尼器连接方式的特点,建立了简洁有效的直升机地面共振当量平面模型。该模型不仅计入了桨叶减摆器以及机体阻尼器的非线性,还考虑了机体阻尼器非比例阻尼对机体固有特性的影响。通过激振法激出机体模态稳态响应,并采用模态阻尼识别法对瞬态响应进行模态阻尼识别。分析可知,机体阻尼器提供的非比例非线性阻尼使得机体模态阻尼在时域上呈现较复杂的变化,系统稳定时,激出的阻尼器稳态响应速度幅值越大,其变化就越滞后。In order to study the influence of non-linear factors on skid helicopter ground resonance,a concise and effective equivalent planar model of helicopter ground resonance is established based on the characteristics of elastic skid landing gear and the connection type of fuselage damper.This model not only considers the nonlinearity of blade damper and fuselage damper,but also considers the influence of the non-proportional damping of fuselage damper on fuselage inherent characteristics.The stable fuselage modal responses are excited by the excitation method,and the modal damping identification method is used to identify the modal damping of the transient response.The results show that the change in time domain is complex because of the non-linear and non-proportional fuselage damping.When the system is stable,the larger the amplitude of the steady-state response speed of the excited damper is,the more lagged its variation will be.

关 键 词：滑橇式直升机 地面共振 非线性 非比例阻尼 时域仿真 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]