Nonlinear Dynamic Response And Flutter Analysis Of Folded Rudder Structure Of High Speed Aircraft

In the process of design and manufacture,in order to reduce the volume and store and transport,rudder surface is often designed as folding structure.In engineering practice,the influence of clearance is ignored in design stage,and the analysis is carried out according to linear method.However,it is well known that the connecting part of folding rudder surface structure is designed,processed and processed The joint part of the assembly will inevitably lead to the gap.Because of the existence of the hinge mechanism with clearance,the stiffness,mode,dynamic response and flutter characteristics of the hinge mechanism are different from those of the conventional rudder surface.In order to make the rudder desi gn more reasonable and fit the actual situation,a new method must be adopted to explore.This paper analyzes the nonlinear dynamic response and flutter of the folding rudder surface structure of high-speed aircraft.It mainly studies the modeling of the nonlinear parameters of the structure clearance and its influence on the structural dynamics characteristics,and focuses on the nonlinear characteristics of the rudder surface structure,and focuses on the nonlinear modeling of the folded rudder surface and the flutter of the folding rudder surface.In this paper,the ground vibration test and nonlinear modeling of the folded rudder surface are studied.The gap nonlinearity is the most important nonlinear link of the folding rudder surface structure,and it is the main research content of the nonlinear dynamic response and flutter of the rudder surface.Therefore,this paper focuses on the nonlinear modeling of the clearance of the folding rudder surface structure.The experimental model parameters of the rudder surface are obtained through the ground vibration test,which is the basis for accurate modeling.The nonlinear and time-varying characteristics of multiple parameters should be considered in the dynamics modeling and analysis of rudder system.The modeling methods of these parameters are not perfect,whether it is theoretical research or test determination,and it is difficult to evaluate the error or accuracy or even effectiveness of the other side as a reference.Therefore,the method used in the study is the close combination and mutual support of nonlinear theory and ground vibration test.Based on the understanding of the structure characteristics,the mathematical model is established and the model structure is given.The model parameters are determined by experiments,so the mixed modeling effect of theory and experiment is obtained.Considering the joint of hinge,the contact force model is selected and the dynamic equation of nonlinear folding rudder surface with clearance concentration is established.The relationship among design parameters,actual clearance and dynamic response characteristics is explored.At the same time,the nonlinear vibration analysis of the folding rudder surface is carried out.This paper extracts the main nonlinear links in rudder surface,and gives the research design for the important links,changes the influence parameters and studies the independent influence of the nonlinear of different links.Based on the accurate modeling,the nonlinear dynamic response and flutter analysis of the folded rudder surface are carried out.Based on the influence of clearance,the paper studies the aeroelastic response characteristics of the folding rudder under the action of high supersonic aerodynamic force,and studies the influence of the nonlinear link of clearance on the nonlinear dynamic response and flutter of the folding rudder.The aerodynamic elastic equation of folded rudder surface is established to analyze the flutter of rudder surface.