Modelling High Velocity Impact on Aluminium Alloy 7075-T6 under Axial Pretension

This paper explains the utilisation of finite element model to analyse the ballistic limit of aluminium alloy 7075-T6 impacted by 8.33 g with 12.5 mm radius rigid spherical projectiles. This numerical study was compared with the results obtained experimentally. During impact, the targets were subjected to either non- or uniaxial- pretension and the projectile travelled horizontally to the target. It was observed that pretensioned targets were more vulnerable, which reduced the ballistic limit. The existence of harmful failures owing to pretension impact was ascertained and compared with the non-pretension targets.

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High Velocity Impact Modelling of Sandwich Panels with Aluminium Foam Core and Aluminium Sheet Skins

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.553.745 ◽

2014 ◽

Vol 553 ◽

pp. 745-750 ◽

Cited By ~ 4

Author(s):

Cheng Jun Liu ◽

Yi Xia Zhang ◽

Qing Hua Qin ◽

Rikard Heslehurst

Keyword(s):

Finite Element ◽

Finite Element Model ◽

High Velocity ◽

Sandwich Panels ◽

Material Model ◽

Element Model ◽

Aluminium Foam ◽

Foam Core ◽

High Velocity Impact ◽

Velocity Impact

A finite element model is developed in this paper to simulate the perforation of aluminium foam sandwich panels subjected to high velocity impact using the commercial finite element analysis software LS-DYNA. The aluminum foam core is governed by the material model of crushable foam materials, while both aluminium alloy face sheets are modeled with the simplified Johnson-Cook material model. A non-linear cohesive contact model is employed to simulate failure between adjacent layers, and an erosion contact model is used to define contact between bullets and panels. All components in the model are meshed with 3D solid element SOLID 164. The developed finite element model is used to simulate the dynamic response of an aluminium foam sandwich panel subjected to projectile impact at velocity ranging from 76 m/s to 187m/s. The relationship between initial velocity and exit velocity of the projectile obtained from numerical modelling agrees well with that obtained from experimental study, demonstrating the effectiveness of the developed finite element model in simulating perforation of sandwich panels subjected to high velocity impact.

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Linking of Lagrangian particle methods to standard finite element methods for high velocity impact computations

Nuclear Engineering and Design ◽

10.1016/0029-5493(94)90143-0 ◽

1994 ◽

Vol 150 (2-3) ◽

pp. 265-274 ◽

Cited By ~ 80

Author(s):

Gordon R. Johnson

Keyword(s):

Finite Element ◽

Finite Element Methods ◽

High Velocity ◽

Particle Methods ◽

High Velocity Impact ◽

Lagrangian Particle ◽

Velocity Impact

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Probabilistic Finite-Element Analysis of S2-Glass Epoxy Composite Beams for Damage Initiation Due to High-Velocity Impact

ASCE-ASME J Risk and Uncert in Engrg Sys Part B Mech Engrg ◽

10.1115/1.4033575 ◽

2016 ◽

Vol 2 (4) ◽

Cited By ~ 9

Author(s):

Shivdayal Patel ◽

Suhail Ahmad ◽

Puneet Mahajan

Keyword(s):

Finite Element Analysis ◽

Finite Element ◽

High Velocity ◽

Laminated Composite ◽

Composite Plates ◽

High Velocity Impact ◽

Element Analysis ◽

Fiber Failure ◽

Velocity Impact ◽

Damage Initiation

The safety predictions of composite armors require a probabilistic analysis to take into consideration scatters in the material properties and initial velocity. Damage initiation laws are used to account for matrix and fiber failure during high-velocity impact. A three-dimensional (3D) stochastic finite-element analysis of laminated composite plates under impact is performed to determine the probability of failure (Pf). The objective is to achieve the safest design of lightweight composite through the most efficient ply arrangement of S2 glass epoxy. Realistic damage initiation models are implemented. The Pf is obtained through the Gaussian process response surface method (GPRSM). The antisymmetric cross-ply arrangement is found to be the safest based on maximum stress and Yen and Hashin criteria simultaneously. Sensitivity analysis is performed to achieve the target reliability.

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Development of a Finite Element Model for Progressive Damage Analysis of Composite Laminates Subjected to Low Velocity Impact

Polymers and Polymer Composites ◽

10.1177/096739111402200111 ◽

2014 ◽

Vol 22 (1) ◽

pp. 73-78 ◽

Cited By ~ 1

Author(s):

Yuequan Wang ◽

Shuhua Zhu ◽

Junwei Qi ◽

Jun Xiao

Keyword(s):

Finite Element ◽

Finite Element Model ◽

Composite Laminates ◽

Element Model ◽

Low Velocity Impact ◽

Progressive Damage ◽

Damage Analysis ◽

Low Velocity ◽

Velocity Impact

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Modeling inflatable fabric with undevelopable surfaces by motion folding method

Journal of Engineered Fibers and Fabrics ◽

10.1177/1558925019886408 ◽

2019 ◽

Vol 14 ◽

pp. 155892501988640

Author(s):

Xiao-Shun Zhao ◽

He Jia ◽

Zhihong Sun ◽

Li Yu

Keyword(s):

Finite Element ◽

Finite Element Model ◽

Numerical Study ◽

Technical Problem ◽

Three Dimensional ◽

Element Model ◽

Model Errors ◽

Folding Model ◽

Study Results ◽

The Stability

At present, most space inflatable structures are composed of flexible inflatable fabrics with complex undevelopable surfaces. It is difficult to establish a multi-dimensional folding model for this type of structure. To solve this key technical problem, the motion folding method is proposed in this study. First, a finite element model with an original three-dimensional surface was flattened with a fluid structure interaction algorithm. Second, the flattened surface was folded based on the prescribed motion of the node groups, and the final folding model was obtained. The fold modeling process of this methodology was consistent with the actual folding processes. Because the mapping relationship between the original finite element model and the final folding model was unchanged, the initial stress was used to modify the model errors during folding process of motion folding method. The folding model of an inflatable aerodynamic decelerator, which could not be established using existing folding methods, was established by using motion folding method. The folding model of the inflatable aerodynamic decelerator showed that the motion folding method could achieve multi-dimensional folding and a high spatial compression rate. The stability and regularity of the inflatable aerodynamic decelerator numerical inflation process and the consistency of the inflated and design shapes indicated the reliability, applicability, and feasibility of the motion folding method. The study results could provide a reference for modeling complex inflatable fabrics and promote the numerical study of inflatable fabrics.

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