Numerical FEA parametric analysis of CAI behaviour of CFRP stiffened panels

Gaitanelis, D. G.; Giannopoulos, Ioannis K.; Theotokoglou, Efstathios E.

doi:10.1016/j.tws.2019.106231

Cited by 11 publications

(2 citation statements)

References 34 publications

(69 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…However, they are commonly modeled using buckling mode shapes. (Anyfantis and Tsouvalis, 2012;ANyfantis, 2019;Gaitanelis, et al, 2019;Tran, et al, 2014). In this study, a sensitivity analysis is performed to study the effects of geometric imperfections on the postbuckling of the composite stiffened plates.…”

Section: Buckling Mode Shape As Initial Geometric Imperfectionmentioning

confidence: 99%

Postbuckling of Marine Stiffened Composite Plates with Initial Geometric Imperfections Using Progressive Failure Analysis

Morshedsolouk

Karimirad

2021

J. Marine. Sci. Appl.

View full text Add to dashboard Cite

This work explores the postbuckling behavior of a marine stiffened composite plate in the presence of initial imperfections. The imperfection shapes are derived from buckling mode shapes and their combinations. Thereafter, these imperfection shapes are applied to the model, and nonlinear large deflection finite element and progressive failure analyses are performed in ANSYS 18.2 software. The Hashin failure criterion is employed to model the progressive failure in the stiffened composite plate. The effect of the initial geometric imperfection on the stiffened composite plate is investigated by considering various imperfection patterns and magnitudes. Results show that when the magnitude of the imperfection is 20 mm, the ultimate strength of the stiffened composite plate decreases by 31%. Moreover, global imperfection shapes are found to be fundamental in determining the ultimate strength of stiffened composite plates and their postbuckling. Article Highlights• The effect of initial geometric imperfection mode shapes and magnitude on the ultimate strength of the stiffened composite panels are studied.• The 11 th first buckling mode shapes and a series of combinations of them are assumed as initial geometric imperfections.• The postbuckling and damage are modeled using the progressive damage method and nonlinear finite element method.

show abstract

Section: Buckling Mode Shape As Initial Geometric Imperfectionmentioning

confidence: 99%

Postbuckling of Marine Stiffened Composite Plates with Initial Geometric Imperfections Using Progressive Failure Analysis

Morshedsolouk

Karimirad

2021

J. Marine. Sci. Appl.

View full text Add to dashboard Cite

show abstract

“…They believed that this FEM could describe the delamination of the sub‐component more precisely, and the relative error between their simulation results and the experimental results was lower than 6%. Gaitanelis et al [ 35 ] discussed the influence of the property of the cohesive elements in the FEM on the prediction results of the residual compression strength of the I‐shaped stiffened CFRP laminate after LVI load, and thought that enlarging the number of the cohesive elements appropriately could ensure the accuracy of the simulation results of the residual compressive strength. Ouyang et al [ 36 ] and Sun et al [ 37 ] presented an equivalent damage FEM based on the virtual crack closure technique and softened inclusion in ABAQUS software to improve the prediction results of the final failure load of the composite stiffened panel with double L‐shaped and multiple T‐shaped stiffener subjected to the compression after LVI load respectively.…”

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

View full text Add to dashboard Cite

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.

show abstract

Effect of impact position on the mechanical response and viscoelastic behavior of double‐blade composite stiffened structures

Hu,

Xu,

Cai

et al. 2024

Polymer Composites

View full text Add to dashboard Cite

This paper focuses on the mechanical response and viscoelastic properties of double‐blade composite stiffened structure (DCSS) under low‐velocity impact (LVI). Firstly, the impact resistance and viscoelastic behavior of the DCSS are revealed by LVI testing at four different locations using the same initial velocity. Next, the damage morphologies at the impact locations are observed with ultrasonic A‐ and C‐scan equipment and optical microscopy. At last, the DCSS containing impact damage is implemented for axial compression and the strain values of the DCSS surface are obtained using a strain testing system to reveal its residual properties and buckling behavior. The results show that there are significant differences in the impact damage modes at the four different locations. The maximum impact resistance is observed at location D, while location A has the opposite. The DCSS has a certain viscoelastic behavior at LVI and conforms to an exponential decay model. Moreover, position B presents interface debonding damage due to stiffness discontinuities at the flange and skin bonding and severely weakens the load carrying performance of the DCSS.Highlights The impact resistance of different positions is analyzed by LVI experimental results. Viscoelastic properties exist at different impact locations and obey the exponential decay model. Impact damage alters the buckling load and residual strength of the DCSS. The damage mechanism of the triangular zone is revealed by damage morphology.

show abstract

Numerical FEA parametric analysis of CAI behaviour of CFRP stiffened panels

Cited by 11 publications

References 34 publications

Postbuckling of Marine Stiffened Composite Plates with Initial Geometric Imperfections Using Progressive Failure Analysis

Postbuckling of Marine Stiffened Composite Plates with Initial Geometric Imperfections Using Progressive Failure Analysis

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

Effect of impact position on the mechanical response and viscoelastic behavior of double‐blade composite stiffened structures

Contact Info

Product

Resources

About