High fidelity simulation of low velocity impact behavior of CFRP laminate

Masaya Ebina, Akinori Yoshimura, Kenichi Sakaue, Anthony M. Waas

研究成果: Article

4 引用 (Scopus)

抄録

In this paper, a finite element (FE) model which simulates damage extent of CFRP laminate subjected to low velocity face-on impact is proposed. The validity of the model is demonstrated by comparing experimental and numerical results for two different CFRPs with different stacking sequence and boundary conditions. Experimental damage extent were obtained from the drop-weight test and non-destructive inspections (C-scan, radiograph and X-ray CT). Numerical results were obtained from FE analyses done on Abaqus/Explicit 2016. In the present model, each damage mode is modeled separately. Fiber damage is modeled by smeared crack model (SCM). In-plane ply cracks are modeled by the enhanced continuum damage mechanics (ECDM) model, which is composed of continuum damage mechanics (CDM) and SCM. Delamination between laminae is modeled by cohesive behavior based on the contact formulation. For both CFRPs, numerical results obtained from the present model show reasonable agreement with experimental results.

元の言語English
ページ(範囲)166-179
ページ数14
ジャーナルComposites Part A: Applied Science and Manufacturing
113
DOI
出版物ステータスPublished - 2018 10 1

Fingerprint

Carbon fiber reinforced plastics
Laminates
Continuum damage mechanics
Cracks
carbon fiber reinforced plastic
Delamination
Inspection
Boundary conditions
X rays
Fibers

ASJC Scopus subject areas

  • Ceramics and Composites
  • Mechanics of Materials

これを引用

High fidelity simulation of low velocity impact behavior of CFRP laminate. / Ebina, Masaya; Yoshimura, Akinori; Sakaue, Kenichi; Waas, Anthony M.

:: Composites Part A: Applied Science and Manufacturing, 巻 113, 01.10.2018, p. 166-179.

研究成果: Article

@article{dac3733dd1d74869947368b06a570952,
title = "High fidelity simulation of low velocity impact behavior of CFRP laminate",
abstract = "In this paper, a finite element (FE) model which simulates damage extent of CFRP laminate subjected to low velocity face-on impact is proposed. The validity of the model is demonstrated by comparing experimental and numerical results for two different CFRPs with different stacking sequence and boundary conditions. Experimental damage extent were obtained from the drop-weight test and non-destructive inspections (C-scan, radiograph and X-ray CT). Numerical results were obtained from FE analyses done on Abaqus/Explicit 2016. In the present model, each damage mode is modeled separately. Fiber damage is modeled by smeared crack model (SCM). In-plane ply cracks are modeled by the enhanced continuum damage mechanics (ECDM) model, which is composed of continuum damage mechanics (CDM) and SCM. Delamination between laminae is modeled by cohesive behavior based on the contact formulation. For both CFRPs, numerical results obtained from the present model show reasonable agreement with experimental results.",
keywords = "B. Impact behavior, B. Transverse cracking, C. Damage mechanics, C. Finite element analysis (FEA)",
author = "Masaya Ebina and Akinori Yoshimura and Kenichi Sakaue and Waas, {Anthony M.}",
year = "2018",
month = "10",
day = "1",
doi = "10.1016/j.compositesa.2018.07.022",
language = "English",
volume = "113",
pages = "166--179",
journal = "Composites - Part A: Applied Science and Manufacturing",
issn = "1359-835X",
publisher = "Elsevier Limited",

}

TY - JOUR

T1 - High fidelity simulation of low velocity impact behavior of CFRP laminate

AU - Ebina, Masaya

AU - Yoshimura, Akinori

AU - Sakaue, Kenichi

AU - Waas, Anthony M.

PY - 2018/10/1

Y1 - 2018/10/1

N2 - In this paper, a finite element (FE) model which simulates damage extent of CFRP laminate subjected to low velocity face-on impact is proposed. The validity of the model is demonstrated by comparing experimental and numerical results for two different CFRPs with different stacking sequence and boundary conditions. Experimental damage extent were obtained from the drop-weight test and non-destructive inspections (C-scan, radiograph and X-ray CT). Numerical results were obtained from FE analyses done on Abaqus/Explicit 2016. In the present model, each damage mode is modeled separately. Fiber damage is modeled by smeared crack model (SCM). In-plane ply cracks are modeled by the enhanced continuum damage mechanics (ECDM) model, which is composed of continuum damage mechanics (CDM) and SCM. Delamination between laminae is modeled by cohesive behavior based on the contact formulation. For both CFRPs, numerical results obtained from the present model show reasonable agreement with experimental results.

AB - In this paper, a finite element (FE) model which simulates damage extent of CFRP laminate subjected to low velocity face-on impact is proposed. The validity of the model is demonstrated by comparing experimental and numerical results for two different CFRPs with different stacking sequence and boundary conditions. Experimental damage extent were obtained from the drop-weight test and non-destructive inspections (C-scan, radiograph and X-ray CT). Numerical results were obtained from FE analyses done on Abaqus/Explicit 2016. In the present model, each damage mode is modeled separately. Fiber damage is modeled by smeared crack model (SCM). In-plane ply cracks are modeled by the enhanced continuum damage mechanics (ECDM) model, which is composed of continuum damage mechanics (CDM) and SCM. Delamination between laminae is modeled by cohesive behavior based on the contact formulation. For both CFRPs, numerical results obtained from the present model show reasonable agreement with experimental results.

KW - B. Impact behavior

KW - B. Transverse cracking

KW - C. Damage mechanics

KW - C. Finite element analysis (FEA)

UR - http://www.scopus.com/inward/record.url?scp=85050668650&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85050668650&partnerID=8YFLogxK

U2 - 10.1016/j.compositesa.2018.07.022

DO - 10.1016/j.compositesa.2018.07.022

M3 - Article

AN - SCOPUS:85050668650

VL - 113

SP - 166

EP - 179

JO - Composites - Part A: Applied Science and Manufacturing

JF - Composites - Part A: Applied Science and Manufacturing

SN - 1359-835X

ER -