An experimental investigation of the impact response and Post-impact shear buckling behaviour of hybrid composite laminates

Damghani, Mahdi; Saddler, John N.; Sammon, Ethan; Atkinson, Gary A.; Matthews, Jason; Murphy, Adrian

doi:10.1016/j.compstruct.2022.116506

Cited by 11 publications

(3 citation statements)

References 33 publications

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“…Numerical analysis was carried out to investigate the buckling and post-buckling behavior on cylindrical panels by varying different radius /thickness ratios, laminated composite materials, ply configurations, and boundary conditions, and compared FE numerical results with experimental results of the cylindrical panel by varying effect of geometric imperfections for the buckling and post-buckling [45]. Damghani et al [46] investigated the influence of impact load on the in-plane shear of laminated composite panels by using experimental studies to find different failure patterns of laminated composite panels. Feng et al [47] presented experimental and FE numerical studies on the stiffened panel under axial load to find the buckling behavior of the panel, buckling capacity, and failure load, and compared experimental results with FE numerical results buckling capacity, failure load, and post-buckling behavior of the panel.…”

Section: Experimental and Numerical Methodsmentioning

confidence: 99%

A review on buckling of the laminated composite panel under in-plane load

Kumar,

Kant,

Poddar

et al. 2024

Eng. Res. Express

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The review paper deals with a literature review on buckling analysis by different methods of laminated plates with different types of stiffeners which has been conducted in recent years. Analytical studies, experimental studies, finite element analysis, and other computational methods have been implemented by researchers on the stiffened panels under compression and shear for determination of the buckling behavior of the panel with I-type, blade-type, T-type, and hat-stiffeners. Some literature has been found on the panel with the influence of variation of the stiffener depth for the determination of buckling capacity. Very few literatures, non-linear finite element (FE) have been implemented for the determination of the effect of debonding damage between plate-stiffener of the panel but have not been reported parametric data about the effect of cohesive parameters of plate-stiffener and delamination of plies of the composites stiffened panel for post-buckling analysis. This paper also provides a literature survey based on the buckling performance of the plates with the application of different shapes of stiffeners.

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Section: Experimental and Numerical Methodsmentioning

confidence: 99%

A review on buckling of the laminated composite panel under in-plane load

Kumar,

Kant,

Poddar

et al. 2024

Eng. Res. Express

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“…Since lightning strike is a threat to all aircraft structures made of metallic or composite material, numerous experimental and numerical studies were covered in the literature to investigate the damage behavior of aircraft structural materials exposed to pressure loading of lightning. Among the experimental studies, Damghani et al [20] examined the effects of transverse impact loading of lightning on two laminate configurations to determine the shear-buckling behavior of the laminate. Boushab et al [21] studied the lightning damage resistance of a carbon-epoxy panel by considering lightning arc channel expansion to find out the cause of the widespread surface damage.…”

Section: Introductionmentioning

confidence: 99%

An Analytical-Based Lightning-Induced Damage Model for an Aircraft Wing Exposed to Pressure Loading of Lightning

Soysal,

Ozkol,

Uzal

2024

Mathematical Problems in Engineering

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Lightning is one of the natural hazards that any aircraft may encounter while navigating. If adequate precautions are not taken against lightning, structural damage, operational disruptions, and loss of life and property can occur. Thus, studying the mechanism of damage caused by lightning strikes in an aircraft’s structural material is necessary to optimize the structure, minimize the damage, and reduce the cost caused by lightning. In the present article, the lightning-induced damage behavior of an aircraft structural material was investigated from an analytical perspective. For this purpose, two analytical-based models were developed: an improved electromagnetic pressure impact model (IEPIM) and the damage model in an aircraft wing. For the IEPIM, the findings of the article showed that the proposed pressure model is in good agreement with the experimental studies, borrowed from the open literature, for 100 and 200 kA lightning current. For the damage model, the findings of the article indicated that (i) even though lightning strikes to the regions with the same characteristics on an aircraft wing in terms of the lightning strike zone, the amount of deflection in the wing increases as the impact point approaches the wing tip and decreases as it approaches the wing root, (ii) without changing the lightning strike point (x0), when the damping coefficient (ξ) is increased in the range of 0,2ξ, the amount of deflection decreases as the amount of damping coefficient increases, and (iii) when lightning with a current of 100 kA hits to the wing root of an aircraft, the pressure impact of the lightning causes more torsion deflection than bending deflection at the wing root; however, when it hits to the mid-wing or wing tip of an aircraft, the pressure impact of the lightning causes more bending deflection than torsion deflection at the mid-wing or wing tip.

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“…Moreover, the hybrid effects significantly enhance the ultimate strength of bonded and bolted FRP-steel (a) Aerospace and marine structures (b) Composite hull size evolution Fig. 1 Large composite structures drawn to scale [24] joints [19,20], as well as the critical buckling load of laminated panels and stiffened plates [21,22]. Through well-designed approaches, hybrid composite materials can maximize the utilization of positive hybrid effects to enhance the fundamental vibration frequency of laminated plates [23].…”

Section: Introductionmentioning

confidence: 99%

Free and Forced Vibration Analysis of Carbon/Glass Hybrid Composite Laminated Plates Under Arbitrary Boundary Conditions

Li,

Guedes Soares,

Liu

et al. 2024

Appl Compos Mater

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This paper presents the theoretical investigations on the free and forced vibration behaviours of carbon/glass hybrid composite laminated plates with arbitrary boundary conditions. The unknown allowable displacement functions of the physical middle surface are expressed in terms of standard cosine Fourier series and sinusoidal auxiliary functions to ensure the continuity of the displacement functions and their derivatives at the structural boundaries. Arbitrary boundary conditions are achieved through the introduction of an artificial spring technique. The first shear deformation theory and Lagrange equations are utilized to derive the energy expression, and the eigenvalue equations associated with free and forced vibration are obtained by Rayleigh-Ritz variational operations. Subsequently, these equations are then solved to determine the natural frequency, mode of vibration, and the steady-state displacement response under forced excitation. The new results are compared with those from references and finite element methods to verify the convergence, accuracy and efficiency of the analytical method. The effects of hybrid ratios, stacking sequences, lamination schemes, fibre orientation, boundary conditions and excitation force on the free and forced vibration behaviours of the carbon/glass hybrid composite laminated plates are analyzed in detail.

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An experimental investigation of the impact response and Post-impact shear buckling behaviour of hybrid composite laminates

Cited by 11 publications

References 33 publications

A review on buckling of the laminated composite panel under in-plane load

A review on buckling of the laminated composite panel under in-plane load

An Analytical-Based Lightning-Induced Damage Model for an Aircraft Wing Exposed to Pressure Loading of Lightning

Free and Forced Vibration Analysis of Carbon/Glass Hybrid Composite Laminated Plates Under Arbitrary Boundary Conditions

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