A progressive failure model for composite laminates subjected to low velocity impact damage

By M. Donadon, L. Iannucci, Brian G. Falzon, J. Hodgkinson, S. D. Almeida. 2008

432 citations recorded by the source corpus.

Subfields: Civil and Structural Engineering, Mechanics of Materials

View Paper: https://www.semanticscholar.org/paper/b311c7fea0070f362b1ffbd57ee651b16b539cb2

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In Civil and Structural Engineering

In Mechanics of Materials

Citations in the corpus

The role of interfacial properties on the intralaminar and interlaminar damage behaviour of unidirectional composite laminates: Experimental characterization and multiscale modelling (2018, methodology): “5 , which is very close to published experimental data [29] and has been used by many CDM models based on Puck’s failure criteria [26].”
Experimental and numerical studies on the impact response of damage-tolerant hybrid unidirectional/woven carbon-fibre reinforced composite laminates (2018, neutral): “Donadon et al. [19,20], Faggiani et al. [21] and Falzon et al. [22,23] proposed a three-dimensional (3D) computational damage mechanics (CDM) based material damage model to capture the intralaminar degradation of composite laminates with nonlinear shear behaviour.”
Low velocity impact modeling in composite laminates capturing permanent indentation (2012, neutral): “[23] will make it possible to capture the permanent dent depth.”
Validation of low velocity impact modelling on different stacking sequences of CFRP laminates and influence of fibre failure (2013, methodology): “For FE modelling, an alternative method is to dissipate the energy release rate of fibre failure spreading over the volume finite element such as the modelling of [8] [1] [13] [12] [11].”
Numerical analysis of intralaminar failure mechanisms in composite structures, Part I: FE implementation (2011, background): “[7] improved and extended this model to include 3D effects.”
Predicting low velocity impact damage and Compression-After-Impact (CAI) behaviour of composite laminates (2015, background): “Page 10 of 53 fracture plane orientation, f θ , is typically found to be approximately 53° for unidirectional composites [6] under uniaxial transverse compressive loading.”