Residual life estimation of cracked aircraft structural components

Maksimović, Stevan; Vasovic, V Ivana; Maksimović, Stevan; Trišović, Nataša; Maksimović, Mirko

doi:10.5937/fmet1801124m

Cited by 12 publications

(7 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This energy can be calculated by using cyclic stress-strain curve. As a result, the energy absorbed till failure becomes (Maksimović M. et al 2018…”

Section: Fatigue Crack Growth Methods Model Based On Strain Energy Methodsmentioning

confidence: 99%

See 1 more Smart Citation

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

Maksimović¹,

Boljanović²,

Djuric³

et al. 2019

JSSCM

Self Cite

View full text Add to dashboard Cite

This work deals with fatigue behaviour of cracked aircraft structural components under cyclic loads of constant amplitudes and load spectrum. This investigation is focused on developing efficient and reliable computational methods for fatigue life estimation of cracked aircraft lugs under cyclic loads of constant amplitude and load spectrum. For crack growth analyses and residual lives of damaged lugs two approaches are used: the Strain Energy Density (SED) method and the conventional Forman`s method. A special attention has been focused on the determination of the fracture mechanics parameters of structural components such as stress intensity factors of aircraft cracked lugs. The effects of the shape of lug surface cracks on the residual fatigue life are investigated as well. The SED method uses the low-cycle fatigue (LCF) properties of the material, which are also used for the lifetime evaluation until the occurrence of final failure. Therefore, the experimentally obtained dynamic properties of the material such as Forman`s constants are not required when this approach is concerned. The complete computational procedure for the crack propagation analysis using low-cycle fatigue material properties is illustrated with the cracked structural elements. To determine analytic expressions for stress intensity factors (SIF), singular finite elements are used. The results of the numerical simulations for crack propagation based on the strain energy density method have been compared with the authors' experimental results.

show abstract

“…This energy can be calculated by using cyclic stress-strain curve. As a result, the energy absorbed till failure becomes (Maksimović M. et al 2018…”

Section: Fatigue Crack Growth Methods Model Based On Strain Energy Methodsmentioning

confidence: 99%

“…where f / is cyclic yield strength and f / -fatigue ductility coefficient. Fatigue crack growth rate can be obtained in the next form (Maksimović M. et al 2018;Boljanović S. et al 2014…”

Section: Fatigue Crack Growth Methods Model Based On Strain Energy Methodsmentioning

confidence: 99%

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

Maksimović¹,

Boljanović²,

Djuric³

et al. 2019

JSSCM

Self Cite

View full text Add to dashboard Cite

show abstract

“…The importance of predicting the reliability of the product's functioning is noted in works [4,5]. Such tasks are especially relevant for aviation and critical engineering [6].…”

Section: Setting Objectivesmentioning

confidence: 99%

Application of chemography method to study surface damage phenomena

Federovich¹,

Alexandrovіch²,

Alexandrovich³

et al. 2022

FME Transactions

View full text Add to dashboard Cite

The problems solved by the chemography method based on fixing oxidative reactions of ultra-low concentrations on the surface of solids are discussed. This method makes it possible to fix physical defects (microcracks, destruction, violations of structural homogeneity) and the energy (residual stresses) state of the surface layer of materials under operating conditions under the action of thermobaric loading. The change in these parameters is associated with the degradation of the cutting surfaces and, as a result, with a change in the rate of the reactions taking place. Applied chemography phenomena as a method of visualization of a destructive layer, a network of surface micro cracks in studying the processes of destruction materials, including nonmetallic ones, is shown. The main advantages of this method are the possibility of assessing the level of residual stresses and periodic visualization of surface defects due to the state of the studied materials, including nonmetallic ones. A relationship has been established between the presence of defects, the level of residual stresses, and the intensity of emerging photo molecular fluxes. In the applied aspect, the method makes it possible to evaluate the performance of cutting plates, and to study the formation and development of a network of microcracks by the intensity of the chemographic effect.

show abstract

“…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

View full text Add to dashboard Cite

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.

show abstract

Residual life estimation of cracked aircraft structural components

Cited by 12 publications

References 10 publications

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

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

Application of chemography method to study surface damage phenomena

Postbuckling and failure analysis of layered composite panels

Contact Info

Product

Resources

About