Analytical and Experimental Studies of Crushing Behavior in Composite Laminates

Bolukbasi, Akif O.; Laananen, David H.

doi:10.1177/002199839502900806

Cited by 10 publications

(5 citation statements)

References 15 publications

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“…However, these SEA values are ideal values, only obtained if laminates are crushed entirely in fragmentation mode which is not the case in most of tests available in the literature. Thus, these SEA results are much higher than SEA values (range from 50 to 95 kJ/kg) found in the literature [4,23,24] of other carbon/epoxy types with different geometry configurations. The nearest SEA value found in literature is 194 kJ/kg obtained by Ramakrishna [25], but with a different type of resin: polyetheretherketone (PEEK).…”

Section: Discussioncontrasting

confidence: 68%

Experimental investigation on mean crushing stress characterization of carbon–epoxy plies under compressive crushing mode

Israr

Rivallant

Barrau

2013

Composite Structures

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a b s t r a c tA challenge in numerical simulation of crashworthiness study is to be able to predict the crush damage modes, their evolution during crushing and the energy absorption in any composite structure from elementary material characterisation data. Therefore, it is important to know the behavior of one ply subjected to crushing load, and especially to determine the mean crushing stress that could be used for simulation. For that purpose, quasi-static crushing tests are performed for different configurations of two CFRP materials, UD and fabrics to determine the mean crushing stress of plies alone and inside a laminate. This study shows there is a linear relationship between crushing load and the contact surface of the plies being crushed on a metallic base which enables actually to define a mean crushing stress for a ply. The method to calculate this value is presented in this paper, based on image analysis of specific crushing tests. Experimental results show that for the UD material, the mean crushing stresses in 0°and 90°plies are very close. The value for a balanced fabric is also similar, approximately 270 MPa.⇑ Corresponding author. Address: ISAE/DMSM,

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Section: Discussioncontrasting

confidence: 68%

Experimental investigation on mean crushing stress characterization of carbon–epoxy plies under compressive crushing mode

Israr

Rivallant

Barrau

2013

Composite Structures

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“…Discrete crack propagation using the nodal release approach. The nodal release approach has been proven to be very robust and easy to implement, even in commercial FE codes, and remains a popular technique to model fracture procedure (for details see Yagawa [20], Keegtra [21], and Bolukbasi [22]). In this concept, two element edges, initially constrained to identical displacements, are allowed to separate by releasing the constraints and nodal forces which hold the elements together.…”

Section: Introductionmentioning

confidence: 99%

Development of the DYNA3D simulation code with automated fracture procedure for brick elements

Tabiei

Jin

2003

Numerical Meth Engineering

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SUMMARYNumerical simulation of cracked structures is an important aspect in structural safety assessment. In recent years, there has been an increasing rate of development of numerical codes for modelling fracture procedure. The subject of this investigation is implementing automated fracture models in the DYNA3D non-linear explicit ÿnite element code to simulate pseudo 3D crack growth procedure. The implemented models have the capabilities of simulating automatic crack propagation without user intervention. The implementation is carried on solid elements. The methodology of implementing fracture models is described. An element deletion-and-replacement remeshing procedure is proposed for updating the explicit geometric description of evolving cracks. Fracture parameters such as stress intensity factors, energy release rates and crack tip opening angle are evaluated. The maximum circumferential stress criterion is used to predict the direction of crack advancement. Seven crack problems are presented to verify the e ectiveness of the methodology. Mesh sensitivity and loading rate e ects are studied in the validation of the presented procedure.

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“…Traditionally, in the particular case of aircraft, the energy-absorption devices are steel or aluminum structural elements; these materials allow a controlled collapse of the structure during which they absorb energy by folding or hinging, involving extensive plastic deformation. The current trend of substituting metals with composites, mostly carbon fibers-epoxy resins, can improve the energy absorption performance of the devices [2] and [3], but it introduces several problems due to the complexity of failure mechanisms that can occur within the material [4] to [7].…”

Section: Introductionmentioning

confidence: 99%

Influence of Plying Strategies and Trigger Type on Crashworthiness Properties of Carbon Fiber Laminates Cured through Autoclave Processing

Troiani¹,

Donati²,

Molinari³

et al. 2014

SV-JME

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A small-scale experimental test able to characterize the energy absorption of a material under compression was developed by innovatively introducing self-supporting sinusoidal shape specimens, thus avoiding the complex anti-buckling devices of classical flat specimen tests. Two carbon-fiber-reinforced polymer (CFRP) pre-preg types were tested: 12 plies of unidirectional tape or 8 plies of plain weave fabric for a laminate approximately 1.8 mm thick in both cases. Three stacking sequences were analysed, in order to identify the configuration able to maximize the specific energy absorption (SEA), i.e. the energy absorbed per unit mass of crushed structure is expressed in J/g, with the unidirectional specimen providing the best results.In order to have a controlled crush, the specimens were produced with different auto-triggering configurations. Indeed, the fibers' continuity was interrupted in selected position and to different degrees in order to investigate the SEA of the weakened laminates. For unidirectional specimens, the SEA maximum value and behaviour over the stroke were unaffected by the trigger position. Therefore, the auto-triggering configuration was able to control the position of the initial failure of the specimen without any decrease in safety performance.

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Analytical and Experimental Studies of Crushing Behavior in Composite Laminates

Cited by 10 publications

References 15 publications

Experimental investigation on mean crushing stress characterization of carbon–epoxy plies under compressive crushing mode

Experimental investigation on mean crushing stress characterization of carbon–epoxy plies under compressive crushing mode

Development of the DYNA3D simulation code with automated fracture procedure for brick elements

Influence of Plying Strategies and Trigger Type on Crashworthiness Properties of Carbon Fiber Laminates Cured through Autoclave Processing

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