全复合材料翼面振动主动控制技术研究  

Active Vibration Control of Full Composite Wing

作　　者：雷鸣[1] 李阳[1] 寇宝智 LEI Ming;LI Yang;KOU Bao-zhi(Aircraft Flight Test Technology Institute,Chinese Flight Test Establishment,Xi凷an 710089,China)

机构地区：[1]中国飞行试验研究院飞机所,西安710089

出　　处：《装备环境工程》2018年第9期26-31,共6页Equipment Environmental Engineering

摘　　要：目的减小复合材料结构振动响应。方法以全复合材料翼面为研究对象,结合该翼面结构有限元模型,建立带有压电作动器的结构动力学仿真模型。利用PID(Proportional,Integral and Differential)控制理论设计主动控制律,基于Simulink仿真平台设计控制律程序,通过控制律变参分析得出PID控制各参数的设计规律,基于仿真模型进行主动控制仿真试验。以仿真试验结果为基础,在复合材料翼面上进行振动主动控制地面试验。结果有效地控制了复合材料翼面振动响应,振动响应减小了79.74%,验证了模型和控制律设计的有效性。结论以压电作动器作为控制作动器,通过PID控制理论设计控制律,能够有效控制全复合材料翼面振动,使振动减小。Objective To reduce vibration response of composite structure.Methods With the composite wing as the object of study,a structure dynamic simulation model with piezoelectric actuator was established in combination with the finite element model of the wing structure.Active control law was designed with the PID(Proportional,Integral and Differential)control theory.The control law program was developed based on the Simulink simulation software.The design rules of each parameter for PID control were obtained by analysis of variable parameters for control laws.The simulation experiment of vibration active control was conducted based on simulation model.Based on the result of the simulation experiment,ground test of vibration active control was conducted for full composite wing.Results The control laws were demonstrated to be effective in controlling vibration.The vibration response was reduced by 79.74%.The model and control laws were effective.Conclusion With the piezoelectric actuator as the control actuator,the control laws designed based on the PID control theory could effectively control vibration of composite wing and reduce the vibration.

关 键 词：全复合材料翼面 振动主动控制 PID控制 变参分析 地面试验 

分 类 号：V216.21[航空宇航科学与技术—航空宇航推进理论与工程]