The Analysis Of Mechanical Properties On Composite Laminated Plate And Honeycomb Panel Under The Environment Of High Temperature

Losing its weight, withstanding the mechanical load and the high temperature generated by air friction, if aircraft wants to take the further step. How to meet the requirements above, composite structures resolve these question, it’s advantages in high specific strength and modulus can make the aircraft do better, which makes the study on the composite structure’s mechanical properties in high temperature condition become the hotspot.In this paper, it focus on the mechanical properties’ experimental study and simulation analysis of the carbon fiber-reinforced epoxy composite, carbon fiber/BMI laminated plates and honeycomb panel composed by carbon fiber-reinforced epoxy composite and honeycomb core layer made by aramid paper in the environment of high temperature. Through the efforts above, the law of its mechanical properties changing with temperature can be get, which can provide references for its application in the engineering practiceFirstly, the static tensile tests of the carbon fiber-reinforced epoxy composite and carbon fiber/BMI laminated plates in the environment of high temperature have been made, through the experiments, getting the law of the tensile modulus changing with temperature, which lays the foundation for the mechanical characteristics’ study of the composite honeycomb panel; Then making the modal test in the high temperature condition and the simulation calculation corresponding to the former, comparing the result of test and simulation, the law of the honeycomb panel’s natural frequency and vibration mode changing with the temperature can be get. Analyzing this result combining the law getting from the tensile test, the conclusion on the change of the honeycomb panel’s structural stiffness can be inferred qualitatively. Besides, combining vibration table test in the environment of high temperature and the dynamic response calculation based on the modal superposition method, getting the law of the honeycomb panel’s natural frequency and vibration response amplitude changing with the temperature. Finally, the equivalent sandwich and original model of honeycomb panel have been compared in modal and dynamic response simulation calculations, the sandwich model’s advantages in calculation have been clarified.