### Abstract

Explicit finite element code (LS-DYNA3D program) simulation is used to investigate the penetration and perforation behaviour of 6061-T6 aluminum plate and C12K33 carbon fiber reinforced 6061-T6 aluminum metal matrix composite plate when impacted by a tungsten projectile. The plate is impacted by the projectile at the angle of incidence of 0° (i.e. normal direction), and three impact velocities are used, 500m/s, 1000 m/s and 1500m/s. The composite plate has a laminate stacking sequence of (0°/90°)_{2} and is tested at fiber volume fractions of 5%, 10% and 15%. The carbon fiber laminate is modeled as Hughes-Liu shell elements, whereas the projectile, aluminum plate and composite's aluminum matrix are modeled as 8-node hexahedron elements. The material model for the tungsten projectile, aluminum plate and composite's aluminum matrix is elastic-plastic-hydrodynamic, while the model for the carbon fiber laminate is the Chang-Chang composite failure model. Plate perforation is found to occur under all studied impact conditions. Deformation behaviour of plate and projectile as well as projectile post-perforation velocity and deceleration of the projectile depend strongly on plate properties and impact velocity.

Original language | English |
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Pages (from-to) | 185-194 |

Number of pages | 10 |

Journal | Structures and Materials |

Volume | 8 |

Publication status | Published - 2000 |

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### All Science Journal Classification (ASJC) codes

- Engineering(all)

### Cite this

*Structures and Materials*,

*8*, 185-194.

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*Structures and Materials*, vol. 8, pp. 185-194.

**Simulation of perforation behaviour of carbon fiber reinforced 6061-T6 aluminum metal matrix composite by a tungsten projectile.** / Lee, Woei-Shyan; Lai, C. H.; Chiou, S. T.

Research output: Contribution to journal › Article

TY - JOUR

T1 - Simulation of perforation behaviour of carbon fiber reinforced 6061-T6 aluminum metal matrix composite by a tungsten projectile

AU - Lee, Woei-Shyan

AU - Lai, C. H.

AU - Chiou, S. T.

PY - 2000

Y1 - 2000

N2 - Explicit finite element code (LS-DYNA3D program) simulation is used to investigate the penetration and perforation behaviour of 6061-T6 aluminum plate and C12K33 carbon fiber reinforced 6061-T6 aluminum metal matrix composite plate when impacted by a tungsten projectile. The plate is impacted by the projectile at the angle of incidence of 0° (i.e. normal direction), and three impact velocities are used, 500m/s, 1000 m/s and 1500m/s. The composite plate has a laminate stacking sequence of (0°/90°)2 and is tested at fiber volume fractions of 5%, 10% and 15%. The carbon fiber laminate is modeled as Hughes-Liu shell elements, whereas the projectile, aluminum plate and composite's aluminum matrix are modeled as 8-node hexahedron elements. The material model for the tungsten projectile, aluminum plate and composite's aluminum matrix is elastic-plastic-hydrodynamic, while the model for the carbon fiber laminate is the Chang-Chang composite failure model. Plate perforation is found to occur under all studied impact conditions. Deformation behaviour of plate and projectile as well as projectile post-perforation velocity and deceleration of the projectile depend strongly on plate properties and impact velocity.

AB - Explicit finite element code (LS-DYNA3D program) simulation is used to investigate the penetration and perforation behaviour of 6061-T6 aluminum plate and C12K33 carbon fiber reinforced 6061-T6 aluminum metal matrix composite plate when impacted by a tungsten projectile. The plate is impacted by the projectile at the angle of incidence of 0° (i.e. normal direction), and three impact velocities are used, 500m/s, 1000 m/s and 1500m/s. The composite plate has a laminate stacking sequence of (0°/90°)2 and is tested at fiber volume fractions of 5%, 10% and 15%. The carbon fiber laminate is modeled as Hughes-Liu shell elements, whereas the projectile, aluminum plate and composite's aluminum matrix are modeled as 8-node hexahedron elements. The material model for the tungsten projectile, aluminum plate and composite's aluminum matrix is elastic-plastic-hydrodynamic, while the model for the carbon fiber laminate is the Chang-Chang composite failure model. Plate perforation is found to occur under all studied impact conditions. Deformation behaviour of plate and projectile as well as projectile post-perforation velocity and deceleration of the projectile depend strongly on plate properties and impact velocity.

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M3 - Article

VL - 8

SP - 185

EP - 194

JO - Structures and Materials

JF - Structures and Materials

SN - 1462-6055

ER -