Numerical Simulation of Compression-After-Impact Process of Composite Laminates

2012 ◽  
Vol 525-526 ◽  
pp. 265-268
Author(s):  
Biao Li ◽  
Ya Zhi Li ◽  
Xi Li ◽  
Zhen Hua Yao
Keyword(s):  
Composite Laminates ◽  
Element Model ◽  
Low Velocity Impact ◽  
Cohesive Elements ◽  
Low Velocity ◽  
Velocity Impact ◽  
Impact Process ◽  
Compression After Impact ◽  
Out Of Plane ◽  
Plane Compression

The residual compressive strength of composite laminates subjected to low-velocity impact (CAI) was analyzed using the ABAQUS/Explicit package through a two-step calculation. The finite element model was composed of solid elements and interfacial cohesive elements. The out of plane low-velocity impact process was simulated in the first step and the results of which were taken as the input for the second step of the in-plane compression, until the collapse of the laminate. The usefulness of the explicit solution algorithm in dealing with the quasi-static procedure of the in-plane compression was investigated by examining the effect of different initial velocities of the compression loading on CAI values. The simulation results agree well with the experimental results.

Study on low-velocity impact and residual strength at high temperatures of composite laminates

2017 ◽  
Vol 233 (3) ◽  
pp. 1106-1123 ◽  
Author(s):  
Jingmeng Weng ◽  
Weidong Wen ◽  
Hongjian Zhang
Keyword(s):  
Compressive Strength ◽  
High Temperatures ◽  
Residual Strength ◽  
Composite Laminates ◽  
Impact Damage ◽  
Element Model ◽  
Low Velocity Impact ◽  
Cohesive Elements ◽  
Low Velocity ◽  
Velocity Impact

In this paper, low-velocity impact characteristics and residual tensile/compressive strength of composite laminates at high temperatures are experimentally and analytically investigated. Low-velocity impact tests at room temperature were performed using a drop-weight apparatus, and residual strength tests at high temperatures were performed using a hydraulic MTS machine. The experimental results show that both residual tensile and compressive strength decrease monotonically with the increase of impact energy, while the variation trend of residual tensile/compressive strength of composite laminates keeps the same with longitudinal tensile/compressive strength with the increase of temperature. In addition, a new stress-based delamination failure criterion was established, in which the delamination is considered to be controlled by the difference between through-thickness stresses of adjacent layers. Once delamination occurs, only the elements below the interface are marked with delamination, whereas the material properties of the elements on both sides of the interface are reduced simultaneously. In this way, delamination can be defined more precisely without cohesive elements, and a considerable reduction in CPU time can be achieved. Combined with extended Hashin failure criteria, an integrated finite element model was established to simulate low-velocity impact damage and to predict residual tensile and compressive strength of composite laminates. The numerical results show good agreements with experimental data.

Modelling damage evolution and CAI strength of composite laminates under biaxial compression

2021 ◽  
pp. 002199832199842
Author(s):  
Bin Yang ◽  
Kunkun Fu ◽  
Yan Li
Keyword(s):  
Residual Strength ◽  
Composite Laminates ◽  
Failure Modes ◽  
Compressive Loading ◽  
Element Model ◽  
Low Velocity Impact ◽  
Biaxial Compression ◽  
Low Velocity ◽  
Damage Initiation ◽  
Compression After Impact

In this paper, a finite element model (FEM) was developed to investigate failure mechanism and compression after impact (CAI) strength of woven carbon fibre reinforced polymer (CFRP) after low-velocity impact (LVI) subjected to biaxial compressive loading. A built-in VUMAT user-defined material subroutine was adopted to take into account the in-plane damage and intralaminar delamination under LVI loading and in-plane compression. The LVI response, failure pattern, and residual mechanical properties under uniaxial compression were compared to the available experimental data to verify the numerical model. The damage initiation, subsequent evolution, final failure modes, and residual strength of the composite laminates with LVI damages subjected to biaxial compressive loading are presented by numerical methods, and the effects of impact energy and impactor diameter on the residual strength of the laminates are discussed.

Bridging the low-velocity impact energy versus impact damage and residual compression strength for composite laminates

2020 ◽  
pp. 073168442097064
Author(s):  
Di Zhang ◽  
Xitao Zheng ◽  
Jin Zhou ◽  
Wenxuan Zhang
Keyword(s):  
Impact Energy ◽  
Composite Laminates ◽  
Damage Model ◽  
Low Velocity Impact ◽  
Fe Model ◽  
Material System ◽  
Cohesive Elements ◽  
Low Velocity ◽  
Velocity Impact ◽  
Damage Area

A finite element (FE) model based on fiber kinking and a transversal fracture angle damage model with cohesive elements are proposed to simulate the low-velocity impact (LVI) and compression after impact (CAI), and build a relationship between LVI energy and CAI strength of composites. The proposed FE model is validated by a comprehensive experimental work conducted using a high strength carbon fiber/epoxy material system i.e. CCF300/BA9916II and underwent LVI and CAI experimentation.  The relative errors between numerical and experimental results of LVI damage area, maximum impact force, impact time, as well as CAI strength are less than 5%. The FE analysis results of LVI show that the dominant damage mode is delamination, and the CAI results demonstrate a brittle behavior with almost no loss of stiffness before failure. It is further deduced that the relationship of LVI energy and damage induced is directly proportional initially; however, after a threshold level of impact energy, the curve turns horizontal so that the increase in further impact energy does not increase the damage area substantially. A similar relationship is developed between impact energy and CAI strength.

Studies on Low-Velocity Impact Damage of Metal Ion Implanted Composite Laminates

2011 ◽  
Vol 311-313 ◽  
pp. 37-42
Author(s):  
Li Yan ◽  
Xue Feng An ◽  
Hai Chao Cui ◽  
Xiao Su Yi
Keyword(s):  
Ion Implantation ◽  
Composite Laminates ◽  
Metal Ion ◽  
Impact Damage ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Velocity Impact ◽  
Compression After Impact ◽  
Dent Depth ◽  
Metal Ion Implantation

composite laminates, metal ion implantation, low-velocity impact damage, BVID Abstract. Metal ion implantation was carried out on composite laminates to modify the surface properties, so that after low-velocity impact barely visible impact damage (BVID) was easy to realize. Surface topography of laminates was observed by SEM. Microhardness and drop-weight impact was tested on composite laminates. The results showed that after metal ion implantation microhardness of laminates increased obviously and resin was easy to generate plastic deforming. Dent depth had been improved so as to realize visible impact damage more easily. And compression-after-impact (CAI) had not decreased. Comparison with Ti ion implantation, Cu ion implantation had better influence on realizing visible impact damage (VID).

Analysis of Patch Bonded Repair to Carbon Fiber Composite Laminates with Low Velocity Impact Damage

2011 ◽  
Vol 335-336 ◽  
pp. 226-229
Author(s):  
Lun Wang ◽  
Wan Lin Zhou ◽  
Xue Gang Shi
Keyword(s):  
Carbon Fiber ◽  
Composite Laminates ◽  
Impact Damage ◽  
Fiber Composite ◽  
Element Model ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Carbon Fiber Composite ◽  
Velocity Impact ◽  
Bonded Repair

In this paper, low-velocity impact residual tensile strength of carbon fiber composite laminates are investigated by experiment. The triple-plate-string-element finite element model was used to calculate the strength of repaired structures of the damage. The corresponding strength tests were conducted to verify the computational results. According to the computational and experimental results, the influence of the repair parameters on the repair efficiency was analyzed, such as the overlap length and the thickness of the patch.

Development of a mathematical model to analyze residual strength of composites after low-velocity impact

2018 ◽  
Vol 53 (8) ◽  
pp. 738-745 ◽  
Author(s):  
Camila Medeiros Dantas de Azevedo ◽  
Rayane Dantas da Cunha ◽  
Raimundo Carlos Silverio Freire Junior ◽  
Wanderley Ferreira de Amorim Junior
Keyword(s):  
Residual Strength ◽  
Composite Laminates ◽  
Repair Process ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Velocity Impact ◽  
Three Point Bending ◽  
Compression After Impact ◽  
Strength And Stiffness ◽  
The Impact

This study aimed to develop a model to analyze the residual strength of composites after low-velocity impact, using three-point bending and compression after impact tests. Two types of composite laminates with an orthophthalic polymer matrix were used: one reinforced with bidirectional E-glass fabric and the other reinforced with bidirectional Kevlar-49 fabric. To that end, an equation was developed to assess loss of strength and stiffness after impact at different distances from the impact point, and this equation was not found in any previously searched article. The results demonstrate that the laminate based in glass fiber is more appropriate for the repair process.

scholarly journals Investigation of damage to thick composite laminates under low-velocity impact and frequency-sweep vibration loading conditions

2020 ◽  
Vol 12 (10) ◽  
pp. 168781402096504
Author(s):  
Miaomiao Duan ◽  
Zhufeng Yue ◽  
Qianguang Song
Keyword(s):  
Composite Laminates ◽  
Energy Levels ◽  
Experimental Tests ◽  
Element Model ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Internal Damage ◽  
Frequency Sweep ◽  
Velocity Impact ◽  
The Impact

A detailed investigation of damage and failure mechanisms of composite laminates under low-velocity impact (LVI) by experimental tests and numerical modeling is presented. Five impact energy levels were investigated on composite laminates by drop-weight tests. Permanent indentations were measured, and delamination areas of each interface induced by each LVI event were captured using an ultrasonic C-scan. The 3D volume elements with a user-defined, material-based finite element model (FEM) has been applied to predict the LVI event considering damage modes, including intra-ply damage and inter-ply damage. The results of the FEM were found to agree well with experimental observations. Internal damage of the laminate during the impact process was analyzed. For thick laminates, the initiation of damage is observed at the first layer, and then spreads from the impact surface to the back, leading to a pine-type damage pattern as the thickness increases. Frequency-sweep vibration tests of composite laminates subjected to LVI events were studied under a “fixed ends” boundary condition. Our results show that it is reasonable to use frequency-sweep vibration experiments to evaluate the damage of laminates subjected to LVI events.

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