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Abstract
GLARE (GLAss REinforced), is a fibre metal laminate that consists of aluminum layers and glass fibre/ epoxy composites. The analysis of this composite structure is non-linear and very complex. Its analysis can be carried out though simulation exercises employing numerical tools/techniques such as finite element modeling. The present paper describes finite element modeling of the GLARE laminates. The deformation characteristics of such hybrid materials are non-linear. In this paper, the numerical analysis based on finite element modeling is used to predict the deformation behavior of various GLARE configurations. The results of numerical analysis obtained are then compared with experimental results for verification and validation.
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References
- Vogelesang, L.B. and Volt, A., "Development of Fiber Metal Laminates for advanced Aerospace Structures", Journal of Materials Processing Technology, 103, 2000, pp.1-5.
- Fernando Rastellini., Sergio Oller., Omar Salomon and Eugenio Onate., "Composite Materials Non-linear Modeling for Long Fiber-reinforced Laminates Continuum Basis, Computational Aspects and Validations", Computers and Structures, 2007, pp.1-18.
- Nam, H.W., Hwang, W. and Han, K.S., "Stacking Sequence Design of Fiber Metal Laminate for Maximum Strength", Journal of Composite Materials, Vol.35, No.18, 2001, p.1654.
- Kant Tarun and Menon, M.P, "A Finite Element-difference Computational Model for Stress Analysis of Layered Composite Cylindrical Shells", Finite elements Analysis and Design, 14, 1993, pp.55-71.
- Michel Hagenbeck., "Characterization of Fiber Metal Laminates Under Thermo Mechanical Loadings", GLARE Data Hand Book, 2005.
- Nam, H.W., Hwang, W. and Shan, K., "Stacking Sequence Design of Fiber Metal Laminate for Maximum Strength", Journal of Composite Materials, Vol.35, No.18, 2001, p.1654.
- Guocal Wu and Jenn-Ming Yang., "Analytical Modeling and Numerical Simulation of the Non-linear Deformation of Hybrid Fiber Metal Laminates", Modeling Simulation Material Science Engineering, 13, 2005, pp.413-425.
- Goh, K.L., Aspden, R.M. and Hukins, D.W.L., "Reviews Finite Element Analysis of Stress Transfer in Short-fiber Composite Materials", Composites Science and Technology, 64, 2004, pp.1091-1100.
- Onkar, A.K., Upadhyay, C.S. and Yadav, D., "Probabilistic Failure of Laminated Composite Plate Using the Stochastic Finite Element Method", Composite Structures, 77, 2007, 79-91.
References
Vogelesang, L.B. and Volt, A., "Development of Fiber Metal Laminates for advanced Aerospace Structures", Journal of Materials Processing Technology, 103, 2000, pp.1-5.
Fernando Rastellini., Sergio Oller., Omar Salomon and Eugenio Onate., "Composite Materials Non-linear Modeling for Long Fiber-reinforced Laminates Continuum Basis, Computational Aspects and Validations", Computers and Structures, 2007, pp.1-18.
Nam, H.W., Hwang, W. and Han, K.S., "Stacking Sequence Design of Fiber Metal Laminate for Maximum Strength", Journal of Composite Materials, Vol.35, No.18, 2001, p.1654.
Kant Tarun and Menon, M.P, "A Finite Element-difference Computational Model for Stress Analysis of Layered Composite Cylindrical Shells", Finite elements Analysis and Design, 14, 1993, pp.55-71.
Michel Hagenbeck., "Characterization of Fiber Metal Laminates Under Thermo Mechanical Loadings", GLARE Data Hand Book, 2005.
Nam, H.W., Hwang, W. and Shan, K., "Stacking Sequence Design of Fiber Metal Laminate for Maximum Strength", Journal of Composite Materials, Vol.35, No.18, 2001, p.1654.
Guocal Wu and Jenn-Ming Yang., "Analytical Modeling and Numerical Simulation of the Non-linear Deformation of Hybrid Fiber Metal Laminates", Modeling Simulation Material Science Engineering, 13, 2005, pp.413-425.
Goh, K.L., Aspden, R.M. and Hukins, D.W.L., "Reviews Finite Element Analysis of Stress Transfer in Short-fiber Composite Materials", Composites Science and Technology, 64, 2004, pp.1091-1100.
Onkar, A.K., Upadhyay, C.S. and Yadav, D., "Probabilistic Failure of Laminated Composite Plate Using the Stochastic Finite Element Method", Composite Structures, 77, 2007, 79-91.