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Research Papers

Accuracy and Computational Efficiency of Finite Element Models for Low Velocity Impact on Composite Structures Subject to Progressive Damage and Delamination1

[+] Author and Article Information
Ahmed H. A. Ibrahim

Baker Hughes, Inc.,
Ahmadi 61006, Kuwait
e-mail: Ahmed.Hanafy@BakerHughes.com

Ahmet S. Yigit

Department of Mechanical Engineering,
Kuwait University,
Safat 13060, Kuwait
e-mail: ahmet.yigit@ku.edu.kw

1This paper is an expanded version of “Finite Element Modeling and Analysis of Low Velocity Impact on Composite Structures Subject to Progressive Damage and Delamination” by the authors, presented at the ASME 2012 International Mechanical Engineering Congress and Exposition (IMECE), Houston, TX, Nov. 9–15, 2012, Paper No. IMECE2012-86016.

Contributed by the Design Engineering Division of ASME for publication in the JOURNAL OF COMPUTATIONAL AND NONLINEAR DYNAMICS. Manuscript received May 14, 2014; final manuscript received September 4, 2014; published online April 9, 2015. Assoc. Editor: José L. Escalona.

J. Comput. Nonlinear Dynam 10(6), 061009 (Nov 01, 2015) (12 pages) Paper No: CND-14-1126; doi: 10.1115/1.4028504 History: Received May 14, 2014; Revised September 04, 2014; Online April 09, 2015

There has been growing interest to use composites in load carrying structures where high strength and light weight are of major concern, e.g., oil industry (offshore structures and platforms, pipe systems, and tubings), sports equipment, automobiles, and aircraft industries. Despite extensive research in the last two decades, mechanical behavior of composite structures subject to contact and impact loading is still not well understood. It is well known that composites are highly vulnerable to various modes of failure and damage due to impact by foreign objects. Such impact events are not only dependent on the material behavior but also on the dynamics of the structure. Finite element (FE) packages are capable of simulating impact response of composite structures subject to impact. It requires extensive training and in-depth knowledge to obtain an adequate FE model with proper impact response prediction and acceptable computational efficiency. Limited FE models have the ability to capture composite damage due to impact when internal delamination or fiber/matrix failures are present. Severe nonlinearities are encountered during FE analysis to capture composite damage progression or material degradation. This work investigates different FE modeling approaches by analyzing their prediction of force–time history and force–indentation curve occurring in composite plates as a result of low velocity impact. The objective is to provide guidelines on selecting the most appropriate approach for a given impact situation. Moreover, a computationally efficient approach in contact modeling is presented. The proposed approach yields better computation efficiency for contact modeling on both isotropic and composite materials.

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Figures

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Fig. 1

Characterization diagram [16]

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Fig. 2

Layup of the simulated composite structure

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Fig. 3

Mesh of the simulated composite continuum shell mode

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Fig. 4

Transition impact on a clamped structure, λ = 0.2 and ζ = 0.76

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Fig. 5

Force–indentation response of transition impact on a clamped structure, λ = 0.2 and ζ = 0.76

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Fig. 6

Quasi-static impact on a simply supported structure, λ = 0.2 and ζ = 7.6

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Fig. 7

Force–indentation response of quasi-static impact on a simply supported structure, λ = 0.2 and ζ = 7.6

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Fig. 8

Transition impact on a simply supported structure, λ = 2.8 and ζ = 0.13

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Fig. 9

Force–indentation response for transition impact on a simply supported structure, λ = 2.8 and ζ = 0.13

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Fig. 10

Validation of composite FE models by experimental data

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Fig. 11

Validation of composite FE models by experimental data

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Fig. 12

Flexible quasi-static impact on a composite structure, λ = 0.027 and ζ = 99

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Fig. 13

Force–indentation response of flexible quasi-static impact on a composite structure, λ = 0.027 and ζ = 99

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Fig. 14

Flexible transition impact on a composite structure, λ = 0.027 and ζ = 9.9

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Fig. 15

Force–indentation response of flexible transition impact on a composite structure, λ = 0.027 and ζ = 9.9

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Fig. 16

Stiff transition impact on a composite structure, λ = 0.43 and ζ = 1.59

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Fig. 17

Stiff small mass impact on a composite structure, λ = 0.068 and ζ = 0.27

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Fig. 18

Stiff quasi-static impact on a thick composite structure, λ = 5.94 and ζ = 2.7

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