Characterization of high-velocity impact damage in CFRP laminates: Part II – prediction by smoothed particle hydrodynamics

A welding window is one of the key concepts used to select optimal regimes for high-velocity impact welding. In a number of recent studies, the method of smoothed particle hydrodynamics (SPH) was used to find the welding window. In this paper, an attempt is made to compare the results of SPH simulation and classical approaches to find the boundaries of a welding window. The experimental data on the welding of 6061-T6 alloy obtained by Wittman were used to verify the simulation results. Numerical simulation of high-velocity impact accompanied by deformation and heating was carried out by the SPH method in Ansys Autodyn software. To analyze the cooling process, the heat equation was solved using the finite difference method. Numerical simulation reproduced most of the explosion welding phenomena, in particular, the formation of waves, vortices, and jets. The left, right, and lower boundaries found using numerical simulations were in good agreement with those found using Wittman’s and Deribas’s approaches. At the same time, significant differences were found in the position of the upper limit. The results of this study improve understanding of the mechanism of joint formation during high-velocity impact welding.

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Damage of Hygrothermally Conditioned Carbon Epoxy Composites under High-Velocity Impact

Materials ◽

10.3390/ma11122525 ◽

2018 ◽

Vol 11 (12) ◽

pp. 2525 ◽

Cited By ~ 3

Author(s):

Xiang Liu ◽

Weimin Gu ◽

Qiwen Liu ◽

Xin Lai ◽

Lisheng Liu

Keyword(s):

High Velocity ◽

Impact Test ◽

Impact Damage ◽

Fiber Reinforced Polymer ◽

High Velocity Impact ◽

Velocity Impact ◽

Cfrp Laminates ◽

Reinforced Polymer ◽

Digital Microscope ◽

The Impact

The influence of hygrothermal aging on high-velocity impact damage of carbon fiber-reinforced polymer (CFRP) laminates is investigated. Composite laminate specimens were preconditioned in water at 70 °C. The laminates were subsequently impacted by flat-, sphere-, and cone- ended projectiles with velocities of 45, 68, and 86 m/s. The incident and residual velocities were collected during the impact test. The impact-induced damages were measured by ultrasonic C-scan, a digital microscope system, and a scanning electron microscope. The results show that the hygrothermally conditioned laminates offer a higher energy absorption during high-velocity impact. Due to the weakening of the interlaminar properties, the hygrothermally conditioned laminates are more susceptible to delamination failure, and shear-induced debonding dominates. The projected delamination area increases with the increment of impact velocity. The damaged region becomes close to a circular shape after hydrothermal conditioning, and close to a rhomboidal shape for the dry specimens.

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High-velocity impact damage in CFRP laminates

Dynamic Deformation, Damage and Fracture in Composite Materials and Structures ◽

10.1016/b978-0-08-100080-9.00007-5 ◽

2016 ◽

pp. 169-191 ◽

Cited By ~ 2

Author(s):

S. Yashiro ◽

K. Ogi

Keyword(s):

High Velocity ◽

Impact Damage ◽

High Velocity Impact ◽

Velocity Impact ◽

Cfrp Laminates

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Effect of strain rate, off-axis loading and high-velocity impact damage on the compressive strength of C/SiC composite

Journal of Composite Materials ◽

10.1177/0021998318787618 ◽

2018 ◽

Vol 53 (4) ◽

pp. 535-546 ◽

Cited By ~ 1

Author(s):

M Altaf ◽

S Singh ◽

VV Bhanu Prasad ◽

Manish Patel

Keyword(s):

Compressive Strength ◽

Strain Rate ◽

High Velocity ◽

Impact Damage ◽

The Other ◽

High Velocity Impact ◽

Fibre Bundles ◽

Velocity Impact ◽

Kink Bands ◽

Other Hand

The compressive strength of C/SiC composite at different strain rates, off-axis orientations and after high-velocity impact was studied. The compressive strength was found to be 137 ± 23, 130 ± 46 and 162 ± 33 MPa at a strain rate of 3.3 × 10−5, 3.3 × 10−3, 3.3 × 10−3 s−1, respectively. On the other hand, the compressive strength was found to be 130 ± 46, 99 ± 23 and 87 ± 9 MPa for 0°/90°, 30°/60° and 45°/45° fibre orientations to loading direction, respectively. After high-velocity impact, the residual compressive strength of C/SiC composite was found to be 58 ± 26, 44 ± 18 and 36 ± 3.5 MPa after impact with 100, 150 and 190 m/s, respectively. The formation of kink bands in fibre bundles was found to be dominant micro-mechanism for compressive failure of C/SiC composite for 0°/90° orientation. On the other hand, delamination and the fibre bundles rotation were found to be the dominant mechanism for off-axis failure of composite.

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