Residual Fatigue Life Estimation of Cracked Aircraft Structural Components Under Load Spectrum

Maksimović, Katarina; Boljanović, Slobodanka; Djuric, Mina; Maksimović, I. Vasović; Maksimović, Mirko

doi:10.24874/jsscm.2019.13.02.01

Cited by 4 publications

(2 citation statements)

References 7 publications

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“…Using strain-life criteria, Neuber's Rule was merged with the finite element method to accurately predict the initiation life of fatigue cracks. [13]. The cumulative damage in the fatigue crack initiation phase was calculated using Miner's rule.…”

Section: Parametersmentioning

confidence: 99%

Characterization of Boeing 777 Nose Landing Gear to Better Withstand Rough Landing

Jinadu,

Olayemi,

Tijani

et al. 2023

JERA

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An important role a landing gear plays is that it aids in the landing and takeoff of aircraft. The landing gear must be designed in such a way that it can take these stresses in static and dynamic situations. This is to accommodate both rough and smooth landings that result from various loads acting upon it, such as drag force, vertical load, and side load. In the aviation industry, landing gear stress is a key concern, and different research in this field has previously yielded excellent results. However, the time has come to raise the bar even higher. This report will focus on the optimization of the Boeing 777's nose landing gear to better withstand rough landings. During the timeframe of this research, SOLIDWORKS was utilized to model and analyze various components of the landing gear. The results summarize that a single material should be avoided throughout the components of the landing gear. Components such as pistons with a larger stress allocation should be made of titanium alloy, while components with a lesser stress allocation should be made from aluminum alloy.Abstract. An important role a landing gear plays is that it aids in the landing and takeoff of aircraft. The landing gear must be designed in such a way that it can take these stresses in static and dynamic situations. This is to accommodate both rough and smooth landings that result from various loads acting upon it, such as drag force, vertical load, and side load. In the aviation industry, landing gear stress is a key concern, and different research in this field has previously yielded excellent results. However, the time has come to raise the bar even higher. This article will focus on the improvement of the Boeing 777's nose landing gear to better withstand rough landings. During the timeframe of this research, motion study in SOLIDWORKS 2020 (Stand-alone license) was utilized to model and analyze various components of the landing gear. The results summarize that a single material should be avoided throughout the components of the landing gear. Components such as pistons with a larger stress allocation should be made of titanium alloy, while components with a lesser stress allocation should be made from aluminum alloy.

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Section: Parametersmentioning

confidence: 99%

Characterization of Boeing 777 Nose Landing Gear to Better Withstand Rough Landing

Jinadu,

Olayemi,

Tijani

et al. 2023

JERA

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“…Higher order shear deformation theory (HOST) with imposed condition on vanishing of the surfaced shear stresses is needed for laminated anisotropic shells [9,10]. In the present work a quadrilateral isoparametric shell finite element is developed based on combining HOST [11,12] and membrane elements with drilling/rotational degrees of freedom (DOF) [13][14][15][16][17][18][19][20][21][22][23]. Membrane elements with drilling DOF are of particular importance as they form the building block of shell facets with full rotational DOFs.…”

Section: Introductionmentioning

confidence: 99%

Postbuckling and failure analysis of layered composite panels

Maksimović¹,

Maksimović²,

Vasović-Maksimović³

et al. 2020

FME Transactions

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This work consideres the buckling and postbuckling behaviour of axially compressed layered composite panels including initial failure analysis. For determination stresses in layered composite panels Finite Element Method (FEM) used. A series of experiments were conducted to verify the FEA-results, but also to address the stability and strength of the composite structure. Combining a geometric nonlinear finite element analysis (FEA) based on the von Karman theory and High Order Shear Deformation Theory (HOST) are used to study the first-ply failure behavior as well as the postbuckling behavior of laminated type composite panels. For this purpose and for the investigation of the failure responses improved 4-node layered shell finite elements are used. The finite element formulation is based on the third order shear deformation theory with four-node shell finite elements having eight degres of freedom per node. A simple method is proposed to predict buckling loads and the post-buckling behaviour together with initial failure analysis of layered composite panels. The experiments carried out on SCHRENK system. Comparisons between numerical and experimental results show quite a good agreement.

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Effect of local laser heating on fatigue crack propagation rate of AA2524 thin plate

Li,

et al. 2024

Engineering Failure Analysis

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Residual Fatigue Life Estimation of Cracked Aircraft Structural Components Under Load Spectrum

Cited by 4 publications

References 7 publications

Characterization of Boeing 777 Nose Landing Gear to Better Withstand Rough Landing

Characterization of Boeing 777 Nose Landing Gear to Better Withstand Rough Landing

Postbuckling and failure analysis of layered composite panels

Effect of local laser heating on fatigue crack propagation rate of AA2524 thin plate

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