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Bibliographies thématiques / Interlaminar and intralaminar damage

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Littérature scientifique sur le sujet « Interlaminar and intralaminar damage »

Auteur : Grafiati

Publié le 7 avril 2023

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Articles de revues sur le sujet "Interlaminar and intralaminar damage"

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Keršienė, Neringa, and Antanas Žiliukas. "INTERLAMINAR AND INTRALAMINAR DAMAGE MECHANISMS OF IMPACT RESISTANT AIRCRAFT MATERIALS UNDER LOW‐ENERGY IMPACT." Aviation 10, no. 3 (2006): 3–8. http://dx.doi.org/10.3846/16487788.2006.9635933.

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For low-velocity impact, drop‐weight impact tests performed by EADS (European Aeronautic Defence and Space Company) Corporate Research Center Germany have been carried out for 2‐D woven E‐Glass/epoxy composite systems to determine material response as a function of absorbed energy and damaged area. Nondestructive techniques like visual inspection and analysis of impact response of the woven fabric laminates at different energy levels are utilized to assess the initiation and progression of interlaminar and intralaminar damage. The dominant damage modes for woven reinforced composite systems we

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Bruno, Domenico, Fabrizio Greco, and Paolo Lonetti. "Interaction Between Interlaminar and Intralaminar Damage in Fiber-Reinforced Composite Laminates." International Journal for Computational Methods in Engineering Science and Mechanics 9, no. 6 (2008): 358–73. http://dx.doi.org/10.1080/15502280802365824.

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Li, N., P. H. Chen, and Q. Ye. "A damage mechanics model for low-velocity impact damage analysis of composite laminates." Aeronautical Journal 121, no. 1238 (2017): 515–32. http://dx.doi.org/10.1017/aer.2017.6.

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ABSTRACTA method was developed to predict numerically the damage of composite laminates with multiple plies under low-velocity impact loading. The Puck criterion for 3D stress states was adopted to model the intralaminar damage including matrix cracking and fibre breakage, and to obtain the orientation of the fracture plane due to matrix failure. According to interlaminar delamination mechanism, a new delamination criterion was proposed. The influence of transverse and through-thickness normal stress, interlaminar shear stress and damage conditions of adjacent plies on delamination was conside

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Liao, BB, and PF Liu. "Finite element analysis of dynamic progressive failure properties of GLARE hybrid laminates under low-velocity impact." Journal of Composite Materials 52, no. 10 (2017): 1317–30. http://dx.doi.org/10.1177/0021998317724216.

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This paper aims to study dynamic progressive failure properties of glass fiber composite/aluminium hybrid laminates under low-velocity impact. Intralaminar damage models using Puck failure criteria and strain-based damage evolution laws for composite layers are implemented by developing finite element codes using ABAQUS-VUMAT (user dynamic material subroutine), the interface delamination is simulated by bilinear cohesive model in ABAQUS and the mechanical properties of aluminium layers are described using the Johnson-Cook model. Effects of different layer thickness and impact energy on the imp

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Duplessis Kergomard, Y., J. Renard, A. Thionnet, and C. Landry. "Intralaminar and interlaminar damage in quasi-unidirectional stratified composite structures: Experimental analysis." Composites Science and Technology 70, no. 10 (2010): 1504–12. http://dx.doi.org/10.1016/j.compscitech.2010.05.006.

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Hassoon, Omar H., Mayyadah S. Abed, Jawad K. Oleiwi, and M. Tarfaoui. "Experimental and numerical investigation of drop weight impact of aramid and UHMWPE reinforced epoxy." Journal of the Mechanical Behavior of Materials 31, no. 1 (2022): 71–82. http://dx.doi.org/10.1515/jmbm-2022-0008.

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Abstract Due to their characteristics such as weight/strength ratio and absorbed energy, the widespread use of composite materials in the last decades engorged the companies to exploit these materials invariant applications like the aerospace, automobile, and marine hull. However, there are some obstructs to the use of these materials that may constrain that. This came from the fact, that composite materials suffer from different damages modes that occur during loading and can be lead to catastrophic failure in their structure, such as intralaminar and interlaminar damage. Consequently, this m

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Zou, Z., S. R. Reid, S. Li, and P. D. Soden. "Modelling Interlaminar and Intralaminar Damage in Filament-Wound Pipes under Quasi-Static Indentation." Journal of Composite Materials 36, no. 4 (2002): 477–99. http://dx.doi.org/10.1177/0021998302036004539.

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BALZANI, CLAUDIO, and WERNER WAGNER. "NUMERICAL TREATMENT OF DAMAGE PROPAGATION IN AXIALLY COMPRESSED COMPOSITE AIRFRAME PANELS." International Journal of Structural Stability and Dynamics 10, no. 04 (2010): 683–703. http://dx.doi.org/10.1142/s0219455410003683.

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In the design phase of stringer-stiffened composite airframe panels, it is a key issue to exploit material reserves as far as possible to create lighter and safer aircraft. A recent approach is to apply postbuckling design — standard for metallic panels — also to composite parts. This work focusses on the development of a simulation procedure which accurately predicts the postbuckling response of composite panels while accounting for damage propagation. For this purpose we employ a robust shell element formulation which allows for arbitrary stacking sequences as well as a variable location of

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Meon, M. S., N. H. Mohamad Nor, S. Shawal, J. B. Saedon, M. N. Rao, and K. U. Schröder. "On the Modelling Aspect of Low-Velocity Impact Composite Laminates." journal of Mechanical Engineering 17, no. 2 (2020): 13–25. http://dx.doi.org/10.24191/jmeche.v17i2.15297.

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Composites suffer a degradation of structural stiffness due to various types of impact loading resulting in damage which is difficult to observe from the surface of the structure. The paper deals with the finite element model (FEM) to study the possible modelling procedures in low-velocity impact (LVI) and failure mechanism of carbon fiber reinforced polymer (CFRP) composite laminate of CCF300/epoxy and its structural responses. In finite element calculation, a proposed three-dimensional progressive damage model is used to determine the intralaminar damage, whereas the cohesive contact formula

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Townsend, Patrick, Juan Carlos Suárez, Paz Pinilla, and Nadia Muñoz. "Insertion of a Viscoelastic Layer to Reduce the Propagation of Energy by Vertical Impacts of Slamming in Planing Hull Vessels." Key Engineering Materials 889 (June 16, 2021): 65–70. http://dx.doi.org/10.4028/www.scientific.net/kem.889.65.

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For the design of vessels built by GFRP laminates, an insert with a viscoelastic layer is proposed to reduce the spread of damage produced by the vertical impact of the ship's bottom with the sea or slamming phenomenon. Using vertical drops-weight impact machine that reproduce the energy inferred to the panel during navigation, the propagation of the damage of OoA cured prepreg panels is studied comparing it with modified panels with insertion of viscoelastic layer. The use of acceleration data reading allows the benefits of viscoelastic modification during impact to be quantified through the

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