Low-velocity impact analysis of composite laminates using linearized contact law

Choi, Ik-Hyeon; Lim, Chang Hwy

doi:10.1016/j.compstruct.2004.04.030

Cited by 105 publications

(58 citation statements)

References 13 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The compression law for this spring was the indentation law previously computed in paragraph 3. This proposition is similar to the approach of Choi [32] for laminated plates. An implicit finite element model was made using the same software as in paragraph 3.2.…”

Section: Accepted Manuscriptsupporting

confidence: 51%

Modelling of low-energy/low-velocity impact on Nomex honeycomb sandwich structures with metallic skins

Castanié¹,

Bouvet²,

Aminanda

et al. 2008

International Journal of Impact Engineering

101

View full text Add to dashboard Cite

Abstract.In the aircraft industry, manufacturers have to decide quickly whether an impacted sandwich needs repairing or not. Certain computation tools exist at present but they are very time consuming and they also fail to perfectly model the physical phenomena involved in an impact. In a previous publication, the authors demonstrated the possibility of representing the NomexTM honeycomb core by a grid of nonlinear springs and have pointed out both the structural behaviour of the honeycomb and the influence of core-skin boundary conditions. This discrete approach accurately predicts the static indentation on honeycomb core alone and the indentation on sandwich structure with metal skins supported on rigid flat support. In this study, the domain of validity of this approach is investigated. It is found that the approach is not valid for sharp projectiles on thin skins. In any case, the spring elements used to model the honeycomb cannot take into account the transverse shear that occurs in the core during the bending of a sandwich. To overcome this strong limitation, a multi-level approach is proposed in the present article. In this approach, the sandwich structure is modelled by Mindlin plate elements and the computed static contact law is implemented in a non linear spring located between the impactor and the structure. Thus, it is possible to predict the dynamic structural A c c e p t e d m a n u s c r i p t response in the case of low-velocity/low-energy impact on metal-skinned sandwich structures.A good correlation with dynamic experimental tests is achieved. Keywords.Sandwich structures, low velocity/low energy impact, finite element nonlinear analysis, indentation. 1-IntroductionSandwich structures exhibit static properties such as high stiffness-to-weight ratio and high buckling loads which are of great importance in the aeronautics field. Nevertheless, the current applications on commercial airplanes remain mainly limited to secondary structures like control surface or floor panels. In the field of helicopters where stress levels are lower, full sandwich structures are already in flight. In fact, one of the main limitations is linked to a lack of knowledge on the effects induced by impact damages [1]. However, in service, such structures are exposed and are often impacted during taxiing manoeuvres or take-off. They can also be damaged by tool drops during maintenance operations [2] and [3]. In such circumstances, the aircraft manufacturer has to inform the users very quickly of whether the impacted structure needs a repair or not. The study presented in this article is a step toward the final objective, which is to provide the aerospace industry with an inverse method. In this method, a 3D picture of the damage is first made by the airline company. Then, based on the shape of the impact, the impactor's shape is found and both the impact damage and the residual strength would be computed. All the approaches presented have a common feature which is to consider the honeycomb as a homogeneous material. Recent...

show abstract

Section: Accepted Manuscriptsupporting

confidence: 51%

Modelling of low-energy/low-velocity impact on Nomex honeycomb sandwich structures with metallic skins

Castanié¹,

Bouvet²,

Aminanda

et al. 2008

International Journal of Impact Engineering

101

View full text Add to dashboard Cite

show abstract

“…Yang and Sun [10] presented the experimental indentation law through static indentation tests on composite laminates. Choi and Lim [11] proposed a linearized contact law for low-velocity impact analysis of composite laminates and compared it with the modified Hertzian contact law. Sun and Chattopadhyay [12], Dobyns [13], Ramkumar and Chen [14] employed the first-order shear deformation theory developed by Whitney and Pagano [15] in conjunction with the Hertzian contact law to study the impact behavior of laminated composite plates.…”

Section: Methodsmentioning

confidence: 99%

The effects of stacking sequence on the penetration-resistant behaviors of T800 carbon fiber composite plates under low-velocity impact loading

Ahmad¹,

Hong²,

Choi³

et al. 2015

Carbon letters

View full text Add to dashboard Cite

Impact damages induced by a low-velocity impact load on carbon fiber reinforced polymer (CFRP) composite plates fabricated with various stacking sequences were studied experimentally. The impact responses of the CFRP composite plates were significantly affected by the laminate stacking sequences. Three types of specimens, specifically quasi-isotropic, unidirectional, and cross-ply, were tested by a constant impact carrying the same impact energy level. An impact load of 3.44 kg, corresponding to 23.62 J, was applied to the center of each plate supported at the boundaries. The unidirectional composite plate showed the worst impact resistance and broke completely into two parts; this was followed by the quasi-isotropic lay-up plate that was perforated by the impact. The cross-ply composite plate exhibited the best resistance to the low-velocity impact load; in this case, the impactor bounced back. Impact parameters such as the peak impact force and absorbed energy were evaluated and compared for the impact resistant characterization of the composites made by different stacking sequences.

show abstract

“…F is the contact force, m 1 =m p and m 2 =m i represents respectively the mass of the impactor and the FML plate, z 1 and z 2 are respectively the relative displacements of the structure and the impactor masses, K 1 = K bs is the bending-shear stiffness the plate. Using of the Choi's linearized model (Choi, and Lim, 2004), instead of nonlinear Hertzian contact law, the contact force can be obtained as:…”

Section: Contact Force Analysismentioning

confidence: 99%

Analytical and Mathematical Modeling and Optimization of Fiber Metal Laminates (FMLs) subjected to low-velocity impact via combined response surface regression and zero-One programming

Ghasemi

Raissi

Malekzadehfard

2013

Lat. Am. j. solids struct.

View full text Add to dashboard Cite

This paper presents analytical and mathematical modeling and optimization of the dynamic behavior of the fiber metal laminates (FMLs) subjected to low-velocity impact. The deflection to thickness (w/h) ratio has been identified through the governing equations of the plate that are solved using the first-order shear deformation theory as well as the Fourier series method. With the help of a two degrees-of-freedom system, consisting of springs-masses, and the Choi's linearized Hertzian contact model the interaction between the impactor and the plate is modeled. Thirty-one experiments are conducted on samples of different layer sequences and volume fractions of Al plies in the composite Structures. A reliable fitness function in the form of a strict linear mathematical function constructed. Using an ordinary least square method, response regression coefficients estimated and a zero-one programming technique proposed to optimize the FML plate behavior subjected to any technological or cost restrictions. The results indicated that FML plate behavior is highly affected by layer sequences and volume fractions of Al plies. The results also showed that, embedding Al plies at outer layers of the structure significantly results in a better response of the structure under low-velocity impact, instead of embedding them in the middle or middle and outer layers of the structure.

show abstract

Low-velocity impact analysis of composite laminates using linearized contact law

Cited by 105 publications

References 13 publications

Modelling of low-energy/low-velocity impact on Nomex honeycomb sandwich structures with metallic skins

Modelling of low-energy/low-velocity impact on Nomex honeycomb sandwich structures with metallic skins

The effects of stacking sequence on the penetration-resistant behaviors of T800 carbon fiber composite plates under low-velocity impact loading

Analytical and Mathematical Modeling and Optimization of Fiber Metal Laminates (FMLs) subjected to low-velocity impact via combined response surface regression and zero-One programming

Contact Info

Product

Resources

About