Nonlinear Vibration Response Analysis Of Bolted Composite Plate Under Thermo Acoustic Loading

With the development of Aeronautics and Astronautics,the requirement of aircrafts is also improved.This makes the working environment of aircrafts very serious.When high-speed aircrafts enter the atmosphere,the airflow makes the panels on the surface of the aircrafts bear high temperature and strong noise,which is an important reason for the destruction of the panels.In addition,the bolt connection is a very common boundary condition in the practical application of projects,so the dynamic analysis of composite panels with the bolt connected under the effect of thermo-acoustic loads is carried out,and the dynamic response model of the structure is established in this paper.The bolt connection boundary is treated as the elastic support boundary firstly,that is to say,tensile springs and torsion springs are evenly distributed on the boundary of the laminate panel,and the bolt boundary can be simulated by changing the spring stiffness.By using Rayleigh Ritz method,the natural frequencies and analytical vibration modes of the elastically supported laminate panel are solved and compared correctness of the model is verified.Based on the analytical vibration modes of the elastic support laminated plate model,the nonlinear random vibration problem of the structure under acoustic load is studied.The low freedom nonlinear dynamic equation of the structure under the acoustic load is established by the Hamilton principle,and the dynamic response of the structure under the noise load is solved,and the influence of the sound pressure level on the response of the panel is studied.The nonlinear random vibration response of structures under thermo-acoustic loads is proposed.The thermal load is loaded by introducing it into the strain relationship of the structure.The critical temperature of the thermal buckling of the structure is calculated,and the influence of the support stiffness on the critical temperature of the thermal buckling is studied in this paper.Then the low freedom nonlinear dynamic equation of the panel under thermo-acoustic loads is established by the Hamilton principle.The dynamic response of the laminated panel is obtained,and the stress and strain distribution of the panel is solved,which lays a foundation for the fatigue life prediction.