独立桨叶变距对旋翼振动载荷影响规律分析  

Analysis on Rotor Vibration Load in Individual Blade Pitch Control

作　　者：顾景轶 李清龙[1] 高亚东[1] 王华明[1] GU Jingyi;LI Qinglong;GAO Yadong;WANG Huaming(National Key Laboratory of Science and Technology on Rotorcratt Aeromechanics,Nanjing University of Aeronautics&Astronautics,Nanjing,210016,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,南京210016

出　　处：《南京航空航天大学学报》2018年第2期239-243,共5页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：中央高校基本科研业务费专项资金(NS2015013)资助项目

摘　　要：独立桨叶控制技术(Individual blade control,IBC)能够改善旋翼气动环境,降低桨毂振动载荷。本文采用Leishman-Beddoes动态失速模型和动态入流模型计算旋翼非定常气流下的气动响应;通过动力学软件ADAMS建立旋翼气弹动力学模型计算桨毂载荷;在周期变距基础上施加二阶和三阶谐波变距进行控制仿真,研究独立桨叶高阶谐波变距对桨毂载荷减振作用的规律。仿真结果表明,通过改变相应变距谐波的幅值和相位,能够使得振动水平大幅降低并达到最优。Independent blade control(IBC)technology can improve the rotor aerodynamic environment and reduce the vibration load of hub.The rotor aerodynamic response in unsteady flow is calculated by using Leishman-Beddoes dynamic stall model and dynamic inflow model.The rotor aeroelastic dynamic model by software ADAMS is built to calculate the hub loads.By periodic variable pitch control applied with two-and three-order harmonic,the law of vibration reduction can be studied on the simulation of individual blade rotor.It is shown that the vibration level can be lower by changing the amplitude and the phase of the pitch harmonics.

关 键 词：直升机旋翼 桨毂载荷 独立桨距控制 减振 

分 类 号：V214.1[航空宇航科学与技术—航空宇航推进理论与工程]