scholarly journals NUMERICAL SIMULATION OF A MASSIVE IMPACTOR FALLING ONTO A REINFORCED CONCRETE BEAM

2020 ◽  
Vol 82 (1) ◽  
pp. 5-15
Author(s):  
S.M. Gertsik ◽  
Yu.V. Novozhilov
Keyword(s):  
Finite Elements ◽  
Concrete Beam ◽  
Time Integration ◽  
Volumetric Strain ◽  
Failure Criteria ◽  
Tensile Failure ◽  
Low Velocity Impact ◽  
Isotropic Hardening ◽  
Elastoplastic Material ◽  
Low Velocity

The paper presents the results of numerically modeling the dynamics of a concrete beam reinforced by longitudinal rods and transversal frames of rods under the effect of a falling massive impactor. The dynamic behavior of the material of concrete is described using the Holmquist - Johnson - Cook model. The reinforcement of the beam is modeled by beam elements, using the bilinear model of elastoplastic material with isotropic hardening. Binding between the reinforcement and concrete is described by introducing additional kinematic equations that couple degrees of freedom of the related nods of the beam and volumetric finite elements. The mathematical model makes it possible to introduce additional failure criteria to predict propagation of tensile cracking. Pressure lower than the minimal one (failure only in the tension zone) and volumetric strain higher than the threshold value are taken as a criterion of tensile failure. Failure is modeled by removing elements from the computational pattern, when the above failure criteria are satisfied. The effect of accounting for failure on the response of the beam is analyzed. Numerical modeling is done using the finite-element method with explicit time integration in the LOGOS and LS-DYNA systems. Concrete is modeled using linear four-node finite elements with one integration point. The impactor is modeled as an absolutely solid body with a detailed description of the impacting end. The obtained results are compared with experimental data. It is demonstrated that the Holmquist - Johnson - Cook material model developed for analyzing high-velocity impacts can also be applied to problems of low-velocity impact.

Failure Analysis of CCF300/5428 Laminates under Low Velocity Impact Based on Properties of Advanced Composite Material

2013 ◽  
Vol 387 ◽  
pp. 185-188
Author(s):  
Jian Yu Zhang ◽  
Ming Li ◽  
Li Bin Zhao ◽  
Bin Jun Fei
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
Damage Model ◽  
Failure Criteria ◽  
Low Velocity Impact ◽  
Material System ◽  
Low Velocity ◽  
3D Fem ◽  
Velocity Impact ◽  
The Impact

A progressive damage model (PDM) composed by 3D FEM, Hashin and Ye failure criteria and Changs degradation rules was established to deeply understand the failure of a new material system CCF300/5428 under low velocity impact. User defined subroutines were developed and embedded into the general FEA software package to carry out the failure analysis. Numerical simulations provide more information about the failure of composite laminates under low velocity impact, including initial damage status, damage propagation and final failure status. The history of the impact point displacement and various damage patterns were detailed studied.

Impact of Fiber Metal Laminates - Literature Research

2020 ◽  
Vol 22 (4) ◽  
pp. 1355-1370
Author(s):  
Bartłomiej Lisowski
Keyword(s):  
Experimental Tests ◽  
Failure Criteria ◽  
Low Velocity Impact ◽  
General Idea ◽  
Tensile Fracture ◽  
Low Velocity ◽  
Fiber Metal Laminates ◽  
Basic Parameters ◽  
Fiber Metal ◽  
Composite Contact

AbstractThe paper refers the general idea of composite materials especially Fiber Metal Laminates (FMLs) with respect to low-velocity impact incidents. This phenomenon was characterized by basic parameters and energy dissipation mechanisms. Further considerations are matched with analytical procedures with reference to linearized spring-mass models, impact characteristics divided into energy correlations (global flexure, delamination, tensile fracture and petaling absorbed energies) and set of motion second order differential equations. Experimental tests were based on analytical solutions for different types of FML - GLARE type plates and were held in accordance to ASTM standards. The structure model reveals plenty of dependences related to strain rate effect, deflection represented by the correlations among plate and intender deformation, separate flexure characteristics for aluminium and composite, contact definition based on intender end-radius shape stress analysis supported by FSDT, von Karman strains as well as CLT. Failure criteria were conformed to layers specifications with respect to von Misses stress-strain criterion for aluminium matched with Tsai-Hill or Puck criterion for unidirectional laminate. At the final stage numerical simulation were made in FEM programs such as ABAQUS and ANSYS. Future prospects were based on the experiments held over 3D-fiberglass (3DFG) FMLs with magnesium alloy layers which covers more favorable mechanical properties than FMLs.

scholarly journals Effect of friction and shear strength enhancement on delamination prediction

2020 ◽  
Vol 54 (23) ◽  
pp. 3329-3342
Author(s):  
Marwah A Hameed ◽  
Ghalib R Ibrahim ◽  
A Albarbar
Keyword(s):  
Friction Coefficient ◽  
Composite Structures ◽  
Enhancement Factor ◽  
Damage Model ◽  
Failure Criteria ◽  
Matrix Cracking ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Shell Elements ◽  
New Model

This study considers the intra-laminar damage mode in composite structures and its effect on delamination prediction. The progressive damage models for matrix cracking and fibre failure in ABAQUS, based on Hashin's model, are only available for shell elements. The results presented here show that the predicted matrix cracking based on the damage model presently available in ABAQUS diverges from experimental results. A new model based on strain failure criteria, which can be used with both shell elements and 3D solid elements, has been developed. The effect of friction coefficient and enhancement factor on the delamination lobes within the delamination area was investigated, and it is shown that the intact zone can be captured in laminate [03/903]s and [903/03]s subjected to low-velocity impact, by using an enhancement factor of η = 0.75, and friction coefficient [Formula: see text], together with the new model proposed here.

Simulations of Delamination Propagation in Composite Laminates under Static and Low-Velocity Impact Transverse Loads Using a New Cohesive Model

2008 ◽  
Vol 32 ◽  
pp. 137-140
Author(s):  
Ning Hu ◽  
Yutaka Zemba ◽  
Hisao Fukunaga
Keyword(s):  
Composite Laminates ◽  
Time Integration ◽  
Low Velocity Impact ◽  
Integration Scheme ◽  
Initial Stiffness ◽  
Low Velocity ◽  
Cohesive Model ◽  
Transverse Loads ◽  
Time Integration Scheme ◽  
Set Up

In this paper, we have proposed a new cohesive model to stably and accurately simulate delamination propagations in composite laminates under transverse loads. In this model, we set up a pre-softening zone in front of the original softening zone. In this pre-softening zone, the initial stiffness is gradually reduced as the interface strength decreases. However, the onset displacement for starting the real softening process is not changed in this model. The fracture toughness of materials for determining the final displacement of complete decohesion is not changed too. This cohesive model is implemented in the explicit time integration scheme. A DCB problem is employed to analyze the characteristics of the present cohesive model. Moreover, an experimental example of laminates under impact loads is employed to illustrate the validity of the present method.

Effect of intra-yarn hybridisation and fibre architecture on the impact response of composite laminates: Experimental and numerical analysis

2021 ◽  
pp. 095440622110373
Author(s):  
Hussein Dalfi
Keyword(s):  
Numerical Analysis ◽  
Composite Laminates ◽  
Composite Structures ◽  
Damage Mechanics ◽  
Failure Criteria ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Element Analysis ◽  
Velocity Impact ◽  
The Impact

Advanced composite laminates (i.e. glass composite laminates) are highly susceptible to low velocity impact, and the induced damage failures substantially reduced their residual mechanical properties and safe-service life during their application. Therefore, experiments and simulation efforts to predict their low-velocity impact damages and energy absorbing have significant importance in composite structures design. In this regards, experimental and finite element analysis (FEA) with aiding Abaqus software were respectively performed to investigate the influence of yarn hybridisation on the response of composite laminates under low velocity impact. The hybrid yarns, which consisted of S-glass and polypropylene yarns have been used to manufacture two types of composites; non-crimp cross-ply hybrid yarns and twill hybrid fabric composites. Additionally, for comparison, the non-crimp cross-ply and twill fabric composite laminates have been made from glass fibres only. The vacuum infusion resin process has been adopted to manufacture these composite laminates. The impact performance of composite laminates has been investigated using low-velocity impact at 15 J, 35, and 50 impact energy levels. The numerical analysis was executed using Abaqus/Explicit and Hashin failure criteria and continuum damage mechanics by using homogenous shell were adopted to simulate the intra-laminar damage in layers. Meanwhile, standard cohesive inter-laminar interfaces that inserted between composite layers with quadratic stress failure criteria have been used to model delamination failures. The numerical results regarding impact force-time, displacement–time and energy-time histories plots, as well as the damage evolution behaviour of matrix crack and fibre fracture, presented an agreement with experimental results.

Finite Element and Experimental Study of the Fiber-Reinforced Composite Laminates under Low-Velocity Impact

2013 ◽  
Vol 535-536 ◽  
pp. 505-508
Author(s):  
Han Yang Liu ◽  
Xin Ming Qiu ◽  
Deng Yu Zhang ◽  
Yu Huai He ◽  
Jin Juan Fan
Keyword(s):  
Composite Laminates ◽  
Failure Modes ◽  
Failure Criteria ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Velocity Impact ◽  
Damage Level ◽  
Nondestructive Examination ◽  
The Matrix ◽  
The Impact

Experimental and numerical studies of the 2D woven composite laminates under low-velocity impact with different energy are discussed in this paper. The traditional Hashin failure criteria are improved to cover the failure modes of fiber rupture and delamination. It is found that the damage level depend on the impact energy. The matrix deformation is the main reason of delamination. The simulating results are in good agreement with the experimental phenomenon observed by nondestructive examination (ultrasonic C scanning) and cross-section examination

Progressive damage modeling and interface delamination of cross-ply laminates subjected to low-velocity impact

2018 ◽  
Vol 53 (6) ◽  
pp. 435-445 ◽  
Author(s):  
Sanan H Khan ◽  
Ankush P Sharma
Keyword(s):  
Material Model ◽  
Element Model ◽  
Failure Criteria ◽  
Low Velocity Impact ◽  
Absorbed Energy ◽  
Low Velocity ◽  
Damage Development ◽  
Velocity Impact ◽  
Interface Delamination ◽  
Post Impact

In this study, Hashin failure criteria were enhanced with Puck’s action plane concept to develop a user material model that can accurately predict the damage development inside the composite laminate when it is subjected to low-velocity impact. A simple cross-ply laminate [0/90]s was chosen to demonstrate the applicability of the material model. Experiments were also performed to observe the real behavior of the laminate. A good correlation between the experiment and simulation results was obtained in terms of peak force and displacement. However, the model under-predicted the absorbed energy, but the discrepancy decreased with the increase in impact energy. Moreover, the interface delamination study was performed by comparing the signatures in post-impact samples of the experiment and numerical simulation. It was observed that the experimentally detected delamination area was closely predicted by the simulation. It was further noticed that the top interface delamination increases faster than bottom interface delamination. Furthermore, the total energy absorbed by the laminates in intralaminar and interlaminar damage modes and friction effects were found to be closely matching with the final absorbed energy of the laminate. Hence, it was seen that the developed finite element model was able to closely capture the behavior occurring in experiments.

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