Experimental And Simulation Study On Structure Stability Of Tail Composite Panels

With the development of composite molding and manufacturing technology,thetechnical advantages of application platform is brought for the design of aircraftstructures. And the amount and application status of advanced composite materials isincreasing in structural components of large aircraft increase. However, the failure isdue to structure buckling subject to compression or shear loads normally. In order toreduce its weight and improve the efficiency of the structure significantly, it is verynecessary to analyze the stability of the structure and study the bearing capacity oftail panels of composite materials.The object of this thesis is the stiffened composite laminated plate structure usedin large aircraft tail. After the recent progress of the stiffened composite platestructures researched, the stability of the stiffened composite laminated plate isanalyzed and studied through three ways, the test, the finite element simulationanalysis and engineering simplified calculation.This paper first studies the overall and partial stability of the rear wing wallplate by the theoretical solution and there are the different results in differentboundary conditions analysis results comparing with the finite element numericalcalculation results. Then the influence of geometric parameters of stringer of wallplate for its buckling load is discussed and analyzed, and the optimal geometricparameter in the same weight is selected. Four different configurations is studied bysimulation calculation. And four finite element models four subject to reasonableboundary conditions are established, the linear buckling analysis under uniaxialcompress load and the nonlinear buckling analysis under shear load are analyzedrelatively. The numerical results and theoretical solution are compared. Finally, staticdamage experiment study of composite wall plate is conducted. The overall andpartial stability, failure mode and bearing capacity of rear wing wall plate arediscussed and compared with the finite element simulation analysis results.Composite wall plate is applied in large aircraft for the first time in China andthe existing design manual is not perfect. The results of the study show that the beststringer andHskinHof the axial stiffness matching relation is1.33for the stability ofrear wing wall plate; dealing with finite element model, it should impose theconstraint on the directionθ y; In the same stringer’s weight, the bearing capacity oftail panels is the largest under the condition of scaling factor η width of0.7.