Stress intensity factor for multiple cracks on curved panels

Kastratović, Gordana; Aldarwish, Mustafa; Grbović, Aleksandar; Vidanović, Nenad; Eldwaib, Khalid Ahmed

doi:10.1016/j.prostr.2018.12.078

Cited by 8 publications

(1 citation statement)

References 3 publications

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“…Early analytical studies have been conducted by Folias, 6 Jeong et al 7 Chen et al 8 presented experimental and semi-analytical expressions for the bulging factor of a crack in pressurized cylindrical shells with large radii. Finite element analysis (FEA) based studies were conducted by several authors often leading to semi-analytical expressions for the bulging factor such as Bakuckas et al, 5,9 Furukawa et al 10 and Tavares et al 11 Bulging factor studies in a nonlinear geometry framework have been conducted by Rose et al [12][13][14][15][16][17] The bulging factor in the presence of multiple cracks have been treated by Refs 18,19 .…”

Section: Introductionmentioning

confidence: 99%

Effect of hexagonal stringer design on bulging factor and stress intensity factor of cracks in the skin of pressurized aircraft fuselage

Zayati

Lazghab

Soula

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Aircraft structural fatigue is a serious issue. Untreated, it could lead to failure. Several aircraft accidents were caused by widespread fatigue damage. For cracks in the fuselage, the stress state is due to the bulging around the crack caused by applied internal pressure. This condition is characterized by a parameter called the bulging factor; it compares the stress intensity factor of a crack in curved shell to its counterpart in a plate. Bulging factor expressions are available for longitudinal and circumferential cracks but less for slanted cracks. The underlying structure that stiffens the skin of the fuselage has a direct impact on the stress intensity factor and the bulging factor of the crack. A hexagonal grid stiffening pattern has been shown to provide sufficient stiffening to the fuselage skin while using a lesser amount of material compared to the traditional orthogonal grid design. However, the response of this grid pattern in the presence of a cracked fuselage has not been studied. The current paper aims to estimate the effect of the hexagonal grid pattern on the bulging factor and stress intensity factor of cracks of various lengths and orientations in the skin of the fuselage. Results obtained are compared to the conventional orthogonal grid stiffening pattern of a fuselage structure. Several patterns were considered. Results show that cracks of different lengths and orientations in hexagonal grid stiffened panels had stress intensity factors and bulging factors that are comparable to the base case within a margin of 2%–8%.

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Section: Introductionmentioning

confidence: 99%

Effect of hexagonal stringer design on bulging factor and stress intensity factor of cracks in the skin of pressurized aircraft fuselage

Zayati

Lazghab

Soula

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Fatigue Life Evaluation of the Damaged Passenger Boarding Bridge Supports

Balac

Grbović

Kastratović

et al. 2021

Current Problems in Experimental and Computational Engineering

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Bridge constructions are developing rapidly as they are necessity in the transport network. The Passenger Boarding Bridge (PBB) provides passengers with means to embark and disembark a ship through weather protected tunnels. It is obvious that the endurance and safety of such structures are of paramount importance. It has been shown that forces and moments at three-tunnel boarding bridge supports were high in the critical cases, as well as stresses in pins and lugs. The aim of this research is to analyze crack propagation in the damaged supporting part of the PBB. After determination of critical components to demonstrate how dangerous the appearance of the crack could be and to evaluate the fatigue life of the damaged supporting part, numerical simulations based on the improved finite element method (FEM) were carried out. To do this, the determination of actual loads was conducted with special consideration. The predicted number of cycles to complete failure was low, indicating the fact that special attention has to be paid on the design of PBB's critical supporting components.

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