Research On Modeling And Active Vibration Control Of Flexible Solar Wing Support Structure

With the increase of manned spaceflight,flexible solar wings with various advantages have become a new development trend.Compared with a rigid spacecraft body,this flexible solar wing has the characteristics of large span,low stiffness,and small damping.Under the conditions of spacecraft orbital adjustment and other conditions,it will be subject to transient impact and generate vibration that is difficult to self-attenuate.This kind of vibration will affect the accuracy of the solar wing and the spacecraft,and even cause the failure of the function of the spacecraft and the instruments on it.Therefore,it is necessary to study the vibration control of the flexible solar wing.In this paper,a "ladder-type" flexible solar wing support structure is used as the research object.The piezoelectric sensor and piezoelectric actuator attached to the place where the structural strain is the largest are used to control the vibration of the support structure.To control the vibration of this structure,we must first analyze its structure,establish a dynamic model of the system according to the characteristics of the system,design a controller based on the obtained dynamic model,control the vibration of the system,and finally design and build an experiment The platform verifies the accuracy of the model and the effectiveness of the algorithm through experimental results.This paper focuses on the vibration control research of flexible solar wing support structures that are subject to transient impact and difficult to rapidly decay during orbital adjustment.The main research contents of the paper include:(1)Firstly,the related literatures were reviewed,and the research status of piezoelectric intelligent materials,flexible structure modeling,and active control algorithms at home and abroad was summarized.Based on this,an active vibration control scheme for flexible solar wing support structures was proposed.(2)Finite element analysis of flexible support structuresFinite element analysis of flexible support structures.HyperMesh software is used to establish a finite element model of the flexible support structure,and the frequency and mode shapes are obtained by modal analysis,and the frequency response curve is obtained by frequency response analysis;the characteristics of the support structure are obtained based on the analysis results,and The main mode simplifies the model.(3)Dynamic modeling of piezoelectric flexible support structure system.The mathematical model of the piezoelectric sensor and piezoelectric sensor is derived based on the piezoelectric principle.The Euler-Bernoulli beam model is used to describe the deformation of the flexible support structure model.The Hamilton principle is used to establish the dynamic model of the active vibration control system.Time-domain and frequency-domain simulations verify model accuracy and analyze system characteristics.(4)The control algorithm is simulated using the dynamic model of the piezoelectric flexible support structure system.Four control algorithms,namely PD Control,Active Damping Control,Linear Quadratic Regulator Control,and Robust H∞ Control,are designed to perform vibration control simulation and compare and analyze the control results,and analyze and evaluate the four controllers in combination with actual operating conditions..(5)The mechanical structure of the experimental platform is processed,and the hardware scheme of the experiment is purchased,and the software code part based on the digital microcontroller is designed to complete the experimental platform of the piezoelectric flexible support structure system.Based on the simulation design of the PID Controller and the Robust H∞ Controller,vibration control experiments were performed on the flexible support structure system,and the experimental results were compared to verify the accuracy of the dynamic model and the effectiveness of the control algorithm.