Abstract
The finite element model of integral wing panels with central penetration cracks under bending load was established, and the crack propagation process of the aircraft panel was simulated. The stress intensity factor (SIF) of the crack tip during crack propagation under varying conditions of crack length and panel structural parameters was determined. The effects of the panel structure parameters and crack size on the crack tip SIF were obtained. The regression analysis of the finite simulation element results has been performed and a regression model of SIF at the crack tip of the integral panel has been established, the determination coefficient of the regression model is 0.955.
Highlights
The panel is one of the main structural parts of the fuselage, wing and tail of the aircraft
The influence of rib spacing on stress intensity factor (SIF) at the crack tip was analyzed by using a finite element
The influence of rib spacing on SIF at the crack tip was analyzed by using a finite element model of integral panel with center penetration crack
Summary
The panel is one of the main structural parts of the fuselage, wing and tail of the aircraft. Many scholars have studied the repairing techniques of aircraft structural of cracks in the bossstress and field rib during the growth process and the crack arrest performance [7]. Fossati demonstrated application numerical to usingFASTRAN finite element [11], Liao studied the the residual fatigueoflife of repairmethods structures evaluate the behavior of the longitudinal cracked plate on the whole machined surface, introduced the under different shapes, sizes, positions and stress levels [12]. The study of the influence of different elementon methods single cracked andaproposed method structuralfinite parameters the SIFfor at athe crack tip canplate, provide basis for an the“analytical structural cycle optimization for crack growth residual strength andpredicting the improvement of theand fracture resistance of in theintegral integralstructures”. The change of the the structural parameters of the integral panel will affect bearing capacity
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