Research On The Dynamic Response Of A Typical Aircraft Structure In The Thermal Environment And Under Random Loading

High speed flight vehicle subjected to high temperature and strong noise environment,many field coupling in this harsh environment under the surface of the high speed flight vehicle structure will undergo a series of continuously high tensile stress,the changing of stress for the destruction of the structure is very serious.If the surface structure of the high speed aircraft is not properly designed,it will have an adverse effect.At present there is a general room temperature related experimental methods for the new type aircraft research and development to play a supporting role,it is necessary for us to do some relevant experimental work associated with high temperature and noise.This paper studies the dynamic response of simple structure and complex structure.In this paper,a series of theories about the multi-degree of freedom system are carried out with the mobile response.The key to the random response analysis of multi-degree of freedom system is to find the frequency response function of the system.In general,the solution of the frequency response function of a multi-degree-of-freedom system is divided into direct and modal superposition.Then compare the two approaches.In this paper,the plain all matte aramid fiber honeycomb plate under the action of a single noise field excitation of dynamic response test,high temperature and noise under the field excitation of dynamic response test,in the high temperature and the dynamic responses of the vibrator excitation test.We obtained the honeycomb plate a series of natural frequency,dynamic response change rules and other relevant information.Under the same noise excitation conditions,as the temperature increases,the modal frequency values of the structure will gradually decrease,and the trend will decrease obviously.In this paper,complex aircraft structure finite element model is established,through the model correction method to obtain relatively accurate finite element model,and then make use of the ground wind tunnel,fluctuating pressure test data according to the empirical coefficient into heaven and earth simulation aerodynamic load and flight state of external applied to structural model,in practical engineering structure under the multi-point excitation of the random dynamic response calculation,complex aircraft structure subjected to fluctuating pressure response law awareness,for complex aircraft structure design,dynamic environment and load analysis to provide technical basis.