Research on Compression Buckling and Failure Characteristics of Composite Fuselage Cap-stringer Stiffened Panel

Abstract

Carbon fiber reinforced polymer(CFRP)is widely used in the design of aircraft fuselage panel.It is important to study the buckling and failure characteristics of panel to improve the efficiency of structural design.The compression buckling load,failure mode and failure load of composite capstringer stiffened panel under compression load are studied by engineering analysis,finite element analysis and panel test.The buckling modes and loads of panels under compression are studied by engineering method and finite element method.The loading capacity of the panel under compression load is studied by the column instability method modified by Von Karman method.Based on the advanced multiload panel test rig,the 3m×2m panel test are completed under compression load and pressure load.The engineering analysis method and finite element analysis method are verified and modified by test.T he results show that the engineering analysis and finite element method need to be modified in buckling analysis,and the results of the modified column instability method are slightly conservative than the test results.

Keywords

• composite material
• fuselage panel
• cap-stringer
• compression load
• stability