旋翼激励下直升机振动响应预计及实测对比  

Prediction and comparing with measurement of helicopter vibration response excited by rotors

作　　者：王影 王文涛[1] 习娟[1] WANG Ying;WANG Wentao;XI Juan(China Helicopter Research and Development Institute,333001 Jingdezhen,China)

机构地区：[1]中国直升机设计研究所,景德镇333001

出　　处：《应用力学学报》2023年第2期253-258,共6页Chinese Journal of Applied Mechanics

基　　金：民用飞机专项科研基金资助项目(No.KT-20210259-HK009)。

摘　　要：旋翼激励是直升机振动的主要源头,影响直升机驾驶员操纵性、机上人员舒适性及结构疲劳寿命。振动问题一般在试飞过程中暴露出来,问题处理和解决往往需要大的周期和代价,影响直升机研制。直升机振动响应预计是解决振动问题的主要手段之一,可以在早期发现振动问题,方便在型号研制早期开展优化设计或解决预案。本研究基于机体动力学仿真模型,以固定坐标系下的桨毂中心振动载荷作为输入,得到机体关键位置的振动响应,形成旋翼激励下直升机振动响应预测的方法。通过某直升机在尾桨激励下关键位置响应预计与实测数据对比分析,表明该方法得到的振动响应随速度的变化规律与实测数据一致,精度满足工程需要。该方法在新机振动响应分析、振动问题排查及振动控制方案制定等工作中具有较高的工程价值。Rotor exitation is the main source of helicopter vibration,which effects pilot manipulation,comfortability as well as structural fatigue.Vibration problems are generally exposed during test flights,and problem handling and solution often require large cycles and costs,that affecting helicopter development.The prediction of helicopter vibration response is a major way to deal with vibration problems,which can be found in the early stage,convenient to carry out optimization design or solution plan in the early development stage of the helicopter.In this paper,a method to predicting vibratory response excited by rotors was presented,which takes vibratory loads of rotor center in nonrotating coordinate system as input,and based on the structural dynamic model.The method was proved to be effective,whose results had coordinated variation patterns as measured data,as well as satisfying accuracy of the engineering needs,through comparing analysis of predicted vibration response and measured ones excited by tail-rotor of the important positions of a certain helicopter.The method has high engineering value in vibration response analysis,vibration problem investigation and vibration control scheme formulation.

关 键 词：桨毂振动载荷 动力学模型 振动响应 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]