Research Of The Aeroelastic Thermal Flutter And Control Of The Panel

With the continuous improvement of technology, toward a higher, faster, strongergoal, people conform to the trend of the times of low-carbon, energy saving,environmental protection, livable society. In the mechanical structure of lightweight andultimate design, the thin-wall structure is widely used in high-speed trains, aircraftwings, missile ramjets and so on. As the elastomer, in the initial installation statemicrobending geometry, boundary tension and compression load, the temperatureincrement generated stress environment, due to the aerodynamic force, the elastic forceand inertial force coupling, the unstable vibration of the thin-wall panel will occur,which is often an important reason of the ones that cause damage to the panel structure.So far, the impact of factor which is considering geometric nonlinearity andaerodynamic nonlinearity, initial geometric micro-bending curve configuration, pre-loadand temperature increments lead to stress in the model of the thin-wall panel structure,the papers taking all the factor above are no published, the papers about non-linearstability analysis and structural vibration control of the slightly curved thin-wall panelhave not been published, the main work of this paper is as follows:1、 The establishment of the kinetic equation of the two-dimensional flat panel in thetransverse vibration of nonlinear large deflection, approximate subsonic low-speed aerodynamic expressions are used. Included in the coupling of the filmforce and the lateral vibration, considering the pre-applied load and stress causedby temperature increments, the analysis of the characteristics of the vibrationresponse of the large deflection, is done, such as pre-load and temperatureincrements, the critical flutter vibration instability points, limit cycles.2、 The establishment of the kinetic equation of the lateral vibration of the geometricnonlinear large deflection of the three-dimensional curved thin-wall structure,respectively, using the approximate expression of the subsonic low-speedaerodynamic and supersonic third-order nonlinear piston theory aerodynamicexpression. Included the coupling of the film force and the lateral vibration,considering a pre-load and stress caused by temperature increments, the study ofits large deflection vibration response characteristics, such as the impact ofmicrobending, pre-load and temperature increment, the critical flutter instabilitypoint and limit cycle.3、 The establishment of state equation using the LQR control of3D panels usingpiezoelectric thin film is done to improve the critical flutter instability point, toreduce harmful vibration response. The main task of this paper is to predict the response of the panel structure quicklyand accurately and control of the harmful vibration to the thin-wall structure, this subjecthas important reference value of the engineering design.