Fatigue damage growth monitoring for composite structures with holes

Muc, Aleksander; Barski, Marek; Chwał, Małgorzata; Romanowicz, Paweł; Stawiarski, Adam

doi:10.1016/j.compstruct.2018.01.065

Cited by 39 publications

(20 citation statements)

References 40 publications

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“…However, it is impossible to characterize the influence of material properties on the buckling resistance with the use of simple analytical formulas. The above problems have also been discussed by Muc et al [ 37 , 38 , 39 ] and Seif and Kabir [ 34 ].…”

Section: Comparison Of Theoretical Predictions and The Finite Elemmentioning

confidence: 85%

“…Since experimental research shows the simultaneous existence of different failure modes (see e.g., Muc et al [ 37 , 38 , 39 ]), the detailed first-ply failure (FPF) and delamination (the use of fracture criteria) analysis should be carried out to determine and optimize the dominant failure modes (buckling, FPF or delamination) for perforated laminated plates or shells. Such an analysis should precede the experimental verification of buckling loads for stretched laminated panels.…”

Section: Discussionmentioning

confidence: 99%

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Peculiarities in the Material Design of Buckling Resistance for Tensioned Laminated Composite Panels with Elliptical Cut-Outs

Muc

2018

Materials

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The results of analytical and numerical studies of the buckling behavior of laminated multilayered tensioned sheets with circular and elliptical openings are presented. The analysis shows the significant influence of stress concentration effects on buckling modes and loads, particularly taking into consideration variations in the E1/E2 and E1/G12 ratios. The results of finite element (FE) computations prove that the buckling mode cannot be described by a single buckle localized at the apex of the hole. The optimal design of such structures seems to be much more complicated than classical buckling problems of compressed laminated panels without holes. However, the obtained results indicate that the optimal laminate configurations occur at the boundaries of the feasible regions of the introduced design space. Both continuous and discrete fibre orientations are considered. For continuous fibre orientations, the optimal stacking sequence corresponds to angle-ply symmetric laminates.

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Section: Comparison Of Theoretical Predictions and The Finite Elemmentioning

confidence: 85%

Section: Discussionmentioning

confidence: 99%

Peculiarities in the Material Design of Buckling Resistance for Tensioned Laminated Composite Panels with Elliptical Cut-Outs

Muc

2018

Materials

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“…For laminated multilayered plates with a cut-out more information about the stress concentration problems can be found in Refs [65][66][67].…”

Section: Buckling Of Cylindrical Shells With Domed Headsmentioning

confidence: 99%

Evolutionary Design of Engineering Constructions

Muc

2018

Lat. Am. j. solids struct.

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The basic information required to utilize one of possible computation tools/algorithms (mainly the evolution strategy) to solve a wide class of real practical engineering optimization problems is presented and discussed in the present paper. The effectiveness of the considered method is demonstrated by the possibility of the use of different form of objective functions, various and numerous nonlinear constraints and different types of design variables (continuous, discrete, real, integer). The sensitivity of the algorithm to the choice of the evolution strategy parameters is also discussed herein. The generality of the evolution strategy is illustrated by the analysis of various examples dealing with: the design of helical springs, the buckling of cylindrical composite panels and the buckling of pressure vessels with domed heads. Keywords optimal design; evolutionary algorithms, buckling; plated and cylindrical composite panels; pressure vessels, helical springs, strength of laminates.

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“…When damage reached a critical condition, the laminate fails catastrophically [ 29 , 30 , 31 , 32 , 33 ]. The open hole geometry is also used in fatigue studies [ 34 , 35 , 36 , 37 , 38 ], where it is proved that longitudinal strain, stiffness and surface temperature can provide valuable information regarding damage progression, fatigue life, and also for predicting notched fatigue performance.…”

Section: Introductionmentioning

confidence: 99%

An Experimental and Numerical Investigation to Characterize an Aerospace Composite Material with Open-Hole Using Non-Destructive Techniques

Feito

Calvo

Belda

et al. 2020

Sensors

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In this study, the open-hole quasi-static tensile and fatigue loading behavior of a multidirectional CFRP thick laminate, representative of laminates used in the aerospace industry, is studied. Non-destructive techniques such as infrared thermographic (IRT) and digital image correlation (DIC) are used to analyze the behavior of this material. We aim at characterizing the influence of the manufacturing defects and the stress concentrator through the temperature variation and strain distribution during fatigue and quasi-static tests. On the one hand, the fatigue specimens were tested in two main perpendicular directions of the laminate. The results revealed that manufacturing defects such as fiber waviness can have a major impact than open-hole stress concentrator on raising the material temperature and causing fracture. In addition, the number of plies with fibers oriented in the load direction can drastically reduce the temperature increment in the laminate. On the other hand, the quasi-static tensile tests showed that the strain distribution around the hole is able to predict the crack initiation and progression in the external plies. Finally, the experimental quasi-static tests were numerically simulated using the finite element method showing good agreement between the numerical and experimental results.

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Fatigue damage growth monitoring for composite structures with holes

Cited by 39 publications

References 40 publications

Peculiarities in the Material Design of Buckling Resistance for Tensioned Laminated Composite Panels with Elliptical Cut-Outs

Peculiarities in the Material Design of Buckling Resistance for Tensioned Laminated Composite Panels with Elliptical Cut-Outs

Evolutionary Design of Engineering Constructions

An Experimental and Numerical Investigation to Characterize an Aerospace Composite Material with Open-Hole Using Non-Destructive Techniques

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