STRAIN SENSING OF COMPOSITE PLATES SUBJECTED TO LOW VELOCITY IMPACT WITH DISTRIBUTED PIEZOELECTRIC SENSORS: A MIXED FINITE ELEMENT APPROACH

1997 ◽  
Vol 199 (1) ◽  
pp. 17-31 ◽  
Author(s):  
L. Yin ◽  
Y. Shen
Keyword(s):  
Finite Element ◽  
Mixed Finite Element ◽  
Composite Plates ◽  
Piezoelectric Sensors ◽  
Low Velocity Impact ◽  
Strain Sensing ◽  
Low Velocity ◽  
Finite Element Approach ◽  
Velocity Impact ◽  
Element Approach

Simulation of Low Velocity Impact Test on Carbon/Epoxy Composite Plates

2015 ◽  
Vol 1115 ◽  
pp. 523-526
Author(s):  
Ziamah B. Buang ◽  
S.M. Kashif
Keyword(s):  
Numerical Simulation ◽  
Finite Element Analysis ◽  
Finite Element ◽  
Composite Structures ◽  
Composite Plates ◽  
Matrix Cracking ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Element Analysis ◽  
Velocity Impact

Composite materials that have low weight and high strength properties are currently one of the promising materials for a vehicle’s body. However, the effect of low velocity impact on composite may cause failure through matrix cracking, fibre breakage and delamination which may reduce the structure strength. Low velocity impact can be analysed either by experimentation or numerical simulation. Numerical simulation which is also known as finite element analysis can show the degradation of the composite structure properties after an impact loading condition without doing any experimentation. Thus, in this paper, LS-DYNA is the finite element analysis software that is used to simulate a low velocity impact on composite structures.

Multiple Low Velocity Impact on Twisted Composite Stiffened Blade: A Finite Element Approach

2017 ◽  
Author(s):  
Mrutyunjay Rout ◽  
Sasank Shekhar Hota ◽  
Amit Karmakar
Keyword(s):  
Finite Element ◽  
Degrees Of Freedom ◽  
Shell Element ◽  
Low Velocity Impact ◽  
Stiffened Panel ◽  
Low Velocity ◽  
Finite Element Approach ◽  
Element Approach ◽  
Loading And Unloading ◽  
The Impact

This paper presents the numerical modeling of a twisted stiffened cylindrical shell employing finite element approach to investigate the transient response due to impact of multiple masses, wherein the shell and the stiffener are modeled as 8 noded isoparametric shell element with five degrees of freedom per node and 3 noded isoparametric curved beam element having four degrees of freedom per node, respectively. The stiffener element is considered as a discrete beam element and its nodal degrees of freedom are transferred to the corresponding degrees of freedom of the shell element considering curvature and eccentricity. The impact force is predicted by employing modified Hertzian contact law relating the contact force to local indentation. As indentation takes place the impactor induces damage and permanent deformation in the contact zone of stiffened panel, as a result the loading and unloading curves are different. Different mathematical equations are considered for both loading and unloading cases in the stiffened panel during low-velocity impact. The accuracy and effectiveness of the finite element approach is verified by comparing the results with the corresponding solutions of analytical as well as standard computational methods available in the open literature. The optimum design of a structure can only be obtained by understanding the impact behavior and the roles of various parameters affecting the response. Hence, parametric study has been carried out to predict the time histories of contact force, displacement of the impact point and in-plane stresses during low-velocity concurrent/delayed impact at multiple locations of the stationary and rotating stiffened shell.

scholarly journals Experimental and Numerical Analysis of Low-Velocity Impact of Carbon Fibre-Based Non-Crimp Fabric Reinforced Thermoplastic Composites

Polymers ◽  
2021 ◽  
Vol 13 (21) ◽  
pp. 3642
Author(s):  
Muhammad Ameerul Atrash Mohsin ◽  
Lorenzo Iannucci ◽  
Emile S. Greenhalgh
Keyword(s):  
Finite Element ◽  
Carbon Fibre ◽  
Energy Levels ◽  
Composite Plates ◽  
Low Velocity Impact ◽  
Thermoplastic Composites ◽  
Low Velocity ◽  
Velocity Impact ◽  
Extent Of Damage ◽  
The Impact

There has been a lot of interest in understanding the low-velocity impact (LVI) response of thermoplastic composites. However, little research has focussed on studying the impact behaviour of non-crimp fabric (NCF)-based fibre reinforced thermoplastic composites. The purpose of this study was to evaluate the LVI responses of two types of non-crimp fabric (NCF) carbon fibre reinforced thermoplastic laminated composites that have been considered attractive in the automotive and aerospace industry: (i) T700/polyamide 6.6 (PA6.6) and (ii) T700/polyphenylene sulphide (PPS). Each carbon/thermoplastic type was impacted at three different energy levels (40, 100 and 160 J), which were determined to achieve three degrees of penetrability, i.e., no penetration, partial penetration and full penetration, respectively. Two distinct non-destructive evaluation (NDE) techniques ((i) ultrasonic C-scanning and (ii) X-ray tomography) were used to assess the extent of damage after impact. The laminated composite plates were subjected to an out-of-plane, localised impact using an INSTRON® drop-weight tower with a hemispherical impactor measuring 16 mm in diameter. The time histories of force, deflection and velocity are reported and discussed. A nonlinear finite element model of the LVI phenomenon was developed using a finite element (FE) solver LS-DYNA® and validated against the experimental observations. The extent of damage observed and level of impact energy absorption calculated on both the experiment and FE analysis are compared and discussed.

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