The influence of hygrothermal aging on the fatigue behavior and residual strength of post-buckled co-bonded stiffened panels subjected to compressive loading

Akker, Bart P.H. van den; Donadon, Maurício Vicente; Loendersloot, Richard; Oliveira, Lucas Amaro de; Arbelo, Mariano A.

doi:10.1016/j.compositesb.2020.108023

Cited by 21 publications

(6 citation statements)

References 42 publications

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“…The AS4/3501‐6 graphite/epoxy material system has been considered since the constants required for the application of the “generalized residual material property degradation model” are available 34 . On the contrary, the Paris parameters coefficient related to such material system is not known, instead values have been considered from a material with similar fatigue behavior 35 . The details on mechanical properties of the material have been taken from References 34,36 and are listed in Table 2.…”

Section: Numerical Applicationmentioning

confidence: 99%

A numerical investigation of the interaction between interlaminar and intralaminar damages in a fatigued composite panel

Russo

Palumbo

Riccio

2023

Fatigue Fract Eng Mat Struct

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The fatigue behavior of composite materials is still a very challenging issue for the scientific community. So far, several numerical methodologies allow us to faithfully simulate the propagation of delamination due to fatigue. However, the reduction of material properties due to the applied cyclic load should be considered. The main objective of this work is to investigate the role of the material property degradation and the intralaminar damages on the propagation of delamination in composite laminates under fatigue loads. The numerical tool FT‐SMXB, based on the Paris Law and virtual crack closure technique, for the mimic of fatigue‐driven delamination, has been integrated with a user material subroutine, based on the generalized residual material property 7degradation model and the Hashin fatigue failure criteria. Typical aeronautical stiffened panel has been considered as test case. Matrix damages and strength degradation due to fatigue cycles have been found to influence the propagation of delamination.

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Section: Numerical Applicationmentioning

confidence: 99%

A numerical investigation of the interaction between interlaminar and intralaminar damages in a fatigued composite panel

Russo

Palumbo

Riccio

2023

Fatigue Fract Eng Mat Struct

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“…Carbon fiber reinforced polymer (CFRP) composites have been widely utilized in the field of the aviation industry as a consequence of their outstanding mechanical behaviors such as high strength/stiffness to weight ratio, high specific modulus and excellent fatigue resistance, and they are gradually replacing the conventional metallic materials like aluminum alloy to achieve the light-weight of the structure and enhance the maneuverability of the aircraft. [1][2][3][4][5] The composite stiffened panel, which is made up of the skin panel and the stiffener with a certain stacking sequence of the composite prepreg, [6,7] is one of the most common used structural components in the manufacturing process of the airplane, and it is going to sustain complicated loading conditions like axial compression during the process of the service, [8][9][10][11][12] which may directly trigger the emergence of the buckling. [13,14] However, these structural components are very vulnerable to the low velocity impact (LVI) loading while the airplane is flying.…”

Section: Introductionmentioning

confidence: 99%

A novel methodology to research the residual compressive mechanical properties of composite stiffened panel after low velocity impact based on quantification damage simulation

Xiao

et al. 2022

Polymer Composites

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Composite stiffened panels have become one of the most usual components in the design process of the aircraft's structure due to their splendid mechanical properties in the last decades. The main purpose of this work is investigating and presenting a more precise method to forecast the residual compressive mechanical behavior of the composite stiffened panel. First of all, an axial compression after impact (CAI) test is performed to understand the failure mechanism of different type of L‐shaped stiffened carbon fiber reinforced polymer panels with barely visible impact damage, which is introduced by the low velocity impact test. Subsequently, a finite element model, which contains a quantification damage model, is established in ABAQUS software based on the CAI test results to predict the mechanical behavior of these composite stiffened panels during the CAI test process. Both of the experimental and predicted results demonstrate that the propagation of the delamination caused by LVI is going to exert a destructive influence on the total failure of the composite stiffened panel, and the prediction results of the residual compressive strength of these composite stiffened panels are well consistent to that measured in the CAI test.

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“…Depending on the state of the composite adherend, adhesive bonding can be classified as three categories, including secondary bonding [4,5], co-bonding [6,7] and co-curing [8,9] (see Fig. 1).…”

Section: Introductionmentioning

confidence: 99%

Co-curing bonding of carbon fibre/epoxy composite joints with excellent structure integrity using carbon fibre/PEEK tapes

Zhao

Scarselli

Alderliesten

2022

Composites Science and Technology

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The influence of hygrothermal aging on the fatigue behavior and residual strength of post-buckled co-bonded stiffened panels subjected to compressive loading

Cited by 21 publications

References 42 publications

A numerical investigation of the interaction between interlaminar and intralaminar damages in a fatigued composite panel

A numerical investigation of the interaction between interlaminar and intralaminar damages in a fatigued composite panel

A novel methodology to research the residual compressive mechanical properties of composite stiffened panel after low velocity impact based on quantification damage simulation

Co-curing bonding of carbon fibre/epoxy composite joints with excellent structure integrity using carbon fibre/PEEK tapes

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