RESEARCH ON POST⁃BUCKLING DESIGN OF HAT⁃STRINGER STIFFENED FUSELAGE PANELS
YUAN Fei
LIN GuoWei
LI XinXiang
CHEN XiangMing
Abstract：Composite stiffened panel structure is widely used in modern aircraft,which is prone to buckling under working conditions.A large number of tests show that the aircraft composite stiffened thin⁃wall structure has considerable post⁃buckling bearing capacity.The design scheme of the stiffened fuselage curved panel with inner cladding and without inner cladding was proposed.The buckling load,bearing capacity and failure mode of the two kinds of curved panels with inner cladding and without inner cladding were calculated by using Abaqus under axial compressive load,pure shear load and compressive shear combined load.In the model,the Tsai⁃Wu criterion was used as the failure criterion of composite materials,and the damage evolution was realized by the subroutine Usdfld.It is found that the inner cladding of the hat stringer can significantly improve the post⁃buckling capacity of the structure and prolong the post⁃buckling process.
Keywords：CompositeCurved fuselage panelInner cladding layerHat⁃stringer stiffenedPost⁃buckling
Publication Date：2024-12-15
Online Publishing Date：2026-09-12(First online date of this platform, not the publication date of the document)
Pages：11( 1408-1418 )