scholarly journals Energy absorption of composite materials under high velocity impact

2021 ◽  
Author(s):  
Ramin Amid
Keyword(s):  
High Velocity ◽  
Composite Laminates ◽  
Hybrid Composites ◽  
Surface Damage ◽  
Stacking Sequence ◽  
High Velocity Impact ◽  
Threshold Velocity ◽  
Velocity Impact ◽  
Graphite Composites ◽  
The Impact

Many studies were directed toward understanding damage patterns in composite laminates and determining the damage development sequence upon high velocity impact. Damage accumulation depends on projectile velocity and on a number of other parameters, so that it is not possible to set strict limits between the different regimes. However, experiments show that, for a given set of experimental conditions where the impact speed is the only variable, there is a certain threshold velocity below which no detectable damage occurs. Above the threshold velocity, no surface damage is observed except for a small indentation at the contact point, but significant internal damage consisting of delaminating and matrix cracks is introduced. As the impact velocity increases further, surface damage due mainly to fiber breakage is introduced. For very high speeds, the target does not have time to deform, and perforation occurs, leaving a clean hole in the sample. The objective of this study is to develop a mathematical model that corresponds to the deformed geometry under high velocity impact applications for composite laminates. A total of 100 tests were conducted on composite laminates, struck by cylindrohemispherical projectiles at normal incidents with velocities up to about 100 mls. The types of materials, used this study, are AS4/3051, IM7/5250 CarbonlEpoxy and TI003 Glass/Epoxy. The strain energy was obtained by derivation of the proposed deflection function. The strain energy was plotted with respect to the deflection of the mid-plane and, then correlated through dynamic correlation factors to actual kinetic energy during the impact. The dynamic correlation factors were determined using a genetic algorithm regression analysis. Two types of materials were tested, namely plain graphite composites and hybrid composites. The growth of the delamination and also the effect of varying the stacking sequence were investigated for the different type of materials and various orientations. The mathematical model appears to provide a reasonable representation of the deformation of composite laminates during the penetration by a cylindro-hemispherical projectile. Furthermore, hybrid composites appear to provide more resistance to the impact, whereas plain composites have less resistance with respect to the higher velocities. It was concluded that, the change of the material in a hybrid composite affects the growth of the damaged area and also reduces the impact penetration resistance. Hence, IM7/E-Glass hybrid has a higher resistance to the penetration. Measurements of the energy levels of the hybrid composites indicated that they offer the highest resistance to ballistic perforation. The hybrid composites perforated at velocities between 77 mls and 83 (mls), whereas the graphite composites perforated at velocities between 48 m/s and 59 (mls). The higher perforation resistance is attributed to the reduced level of delamination generated during the impact, and also the addition of the E-Glass, which was capable of absorbing more energy during the impact. In studying the graphite composites, the best orientation in terms of the stacking sequence was found to be [(45, -45, 0, 90) 2 ] S , which indicates that this stacking sequence withstand higher velocity and hence absorbs more energy during the impact. Therefore, the quasi-isotropi corientation [(45, -45, 0, 90) 2 ] S is best for impact resistance if a laminate is not combined with E-Glass. The ballistic-limit velocity prior to perforation for the Quasi-isotropic laminate was measured as 58.9 m/s. This is a significant increase compared to the other plain graphite samples. The energy required for the complete perforation is approximately 48% higher in this stacking sequence as compared to other plain Graphite specimens. It was also found that the energy absorption capability is reduced significantly in the cross-ply laminates. The penetration resistance of the [(0,90,0,90) 2 ] S laminate and the energy required for perforation are approximately 50% less than the other plain graphite specimens.

scholarly journals Energy absorption of composite materials under high velocity impact

2021 ◽  
Author(s):  
Ramin Amid
Keyword(s):  
High Velocity ◽  
Composite Laminates ◽  
Hybrid Composites ◽  
Surface Damage ◽  
Stacking Sequence ◽  
High Velocity Impact ◽  
Threshold Velocity ◽  
Velocity Impact ◽  
Graphite Composites ◽  
The Impact

Many studies were directed toward understanding damage patterns in composite laminates and determining the damage development sequence upon high velocity impact. Damage accumulation depends on projectile velocity and on a number of other parameters, so that it is not possible to set strict limits between the different regimes. However, experiments show that, for a given set of experimental conditions where the impact speed is the only variable, there is a certain threshold velocity below which no detectable damage occurs. Above the threshold velocity, no surface damage is observed except for a small indentation at the contact point, but significant internal damage consisting of delaminating and matrix cracks is introduced. As the impact velocity increases further, surface damage due mainly to fiber breakage is introduced. For very high speeds, the target does not have time to deform, and perforation occurs, leaving a clean hole in the sample. The objective of this study is to develop a mathematical model that corresponds to the deformed geometry under high velocity impact applications for composite laminates. A total of 100 tests were conducted on composite laminates, struck by cylindrohemispherical projectiles at normal incidents with velocities up to about 100 mls. The types of materials, used this study, are AS4/3051, IM7/5250 CarbonlEpoxy and TI003 Glass/Epoxy. The strain energy was obtained by derivation of the proposed deflection function. The strain energy was plotted with respect to the deflection of the mid-plane and, then correlated through dynamic correlation factors to actual kinetic energy during the impact. The dynamic correlation factors were determined using a genetic algorithm regression analysis. Two types of materials were tested, namely plain graphite composites and hybrid composites. The growth of the delamination and also the effect of varying the stacking sequence were investigated for the different type of materials and various orientations. The mathematical model appears to provide a reasonable representation of the deformation of composite laminates during the penetration by a cylindro-hemispherical projectile. Furthermore, hybrid composites appear to provide more resistance to the impact, whereas plain composites have less resistance with respect to the higher velocities. It was concluded that, the change of the material in a hybrid composite affects the growth of the damaged area and also reduces the impact penetration resistance. Hence, IM7/E-Glass hybrid has a higher resistance to the penetration. Measurements of the energy levels of the hybrid composites indicated that they offer the highest resistance to ballistic perforation. The hybrid composites perforated at velocities between 77 mls and 83 (mls), whereas the graphite composites perforated at velocities between 48 m/s and 59 (mls). The higher perforation resistance is attributed to the reduced level of delamination generated during the impact, and also the addition of the E-Glass, which was capable of absorbing more energy during the impact. In studying the graphite composites, the best orientation in terms of the stacking sequence was found to be [(45, -45, 0, 90) 2 ] S , which indicates that this stacking sequence withstand higher velocity and hence absorbs more energy during the impact. Therefore, the quasi-isotropi corientation [(45, -45, 0, 90) 2 ] S is best for impact resistance if a laminate is not combined with E-Glass. The ballistic-limit velocity prior to perforation for the Quasi-isotropic laminate was measured as 58.9 m/s. This is a significant increase compared to the other plain graphite samples. The energy required for the complete perforation is approximately 48% higher in this stacking sequence as compared to other plain Graphite specimens. It was also found that the energy absorption capability is reduced significantly in the cross-ply laminates. The penetration resistance of the [(0,90,0,90) 2 ] S laminate and the energy required for perforation are approximately 50% less than the other plain graphite specimens.

An experimental and numerical study of epoxy-based Kevlar-basalt hybrid composites under high velocity impact

2021 ◽  
pp. 152808372199090
Author(s):  
Azizolrahman Amirian ◽  
Hossein Rahmani ◽  
Hossein Moeinkhah
Keyword(s):  
Energy Absorption ◽  
High Velocity ◽  
Hybrid Composites ◽  
Numerical Study ◽  
Energy Levels ◽  
High Velocity Impact ◽  
Residual Velocity ◽  
Velocity Impact ◽  
The Impact ◽  
Ballistic Apparatus

In this paper, the high velocity impact (HVI) behavior of epoxy-based Kevlar-Basalt hybrid composites was studied experimentally and numerically. The composite specimens were manually placed in nine layers classified into six types of stacking sequences: non-hybrid, sandwich hybrid, and intercalated hybrid. The impact tests were conducted by using a ballistic apparatus at three different energy levels: 150 J, 200 J, and 250 J, and the amount of absorbed energy was calculated based on input velocity and residual velocity of the projectile. The results demonstrated that hybridization improves the behavior of composites in high velocity impacts compared to that of specimen that are not hybridized. The absorption of sandwich hybrids on average increased 23.25% and 11.3% compared to pure Basalt and Kevlar, respectively. Moreover, the intercalated hybrids showed an efficiency of about 35.6% and 21.76% better than that of pure Basalt and Kevlar, respectively, in absorbing energy. The same energy absorption pattern was observed in numerical simulation performed in ABAQUS/Explicit. Also, the highest amount of energy absorption and the lowest residual velocity as well as damage occurred when Kevlar was attacked by the projectile and the layers were intercalated.

scholarly journals High-velocity impact behavior of hybrid fiber-reinforced epoxy composites

2021 ◽  
Vol 43 (9) ◽  
Author(s):  
Clifton Stephen ◽  
B. Shivamurthy ◽  
Abdel-Hamid I. Mourad ◽  
Rajiv Selvam
Keyword(s):  
Energy Absorption ◽  
High Velocity ◽  
Composite Laminates ◽  
Epoxy Composite ◽  
Matrix Cracking ◽  
Impact Behavior ◽  
Stacking Sequence ◽  
High Velocity Impact ◽  
Velocity Impact ◽  
Hybrid Fabric

AbstractIn this study, non-hybrid and hybrid (Kevlar, carbon and glass) fabric epoxy composite laminates were fabricated with different stacking sequences by hand lay-up followed by hot-compression molding. Experimental tests were conducted to investigate tensile, flexural, and hardness characteristics. It was found that the stacking sequence did not significantly affect the tensile strength and hardness values of the composites; however, it affected their flexural strength. Damage morphology of the specimens through SEM images showed that the major damage mechanisms in the composites were delamination, fiber breakage, pull-out, and matrix cracking. Based on the static experimental results, the high-velocity impact behavior was investigated through simulation study using LS-DYNA finite element analysis (FEA) software. To study the ballistic impact, a steel projectile with a hemispherical penetrating edge at impact velocities of 100 m.s−1, 250 m.s−1, and 350 m.s−1 was considered. Among non-hybrid fabric epoxy composite specimens, Kevlar/epoxy specimen was found to have the highest impact energy absorption followed by carbon/epoxy and glass/epoxy, respectively. Regarding the hybrid fabric epoxy composite specimens, the ones with Kevlar plies in the rear face exhibited better energy absorption compared to other stacking sequences. The non-hybrid glass/epoxy specimen had the lowest energy absorption and highest post-impact residual velocity of projectile among all specimens. From the FEA results, it was noted that impact resistance of hybrid composites improved when Kevlar fabric was placed in the rear layer. Thus, the stacking sequence was observed to be of substantial importance in the development of fabric-reinforced composite laminates for high-velocity impact applications.

The Behaviour of Fibre-Metal Laminates under High Velocity Impact Loading with Different Stacking Sequences of Al Alloy

2012 ◽  
Vol 225 ◽  
pp. 213-218 ◽  
Author(s):  
A.A. Ramadhan ◽  
Abdul Rahim Abu Talib ◽  
Azmin Shakrine Mohd Rafie ◽  
R. Zahari
Keyword(s):  
Impact Loading ◽  
High Velocity ◽  
Stacking Sequence ◽  
Ballistic Limit ◽  
High Velocity Impact ◽  
Velocity Impact ◽  
Limit Velocity ◽  
Fibre Metal ◽  
Ballistic Limit Velocity ◽  
The Impact

The high velocity impact response of composite laminated plates has been experimentally investigated using a nitrogen gas gun. Tests were undertaken on fibre-metal laminate (FML) structures based on Kevlar-29 fiber/epoxy-Alumina resin with different stacking sequences of 6061-T6 Al plates. Impact testing was conducted using a cylindrical shape of 7.62 mm diameter steel projectile at 400m/s velocity, which was investigated to achieve complete perforation of the target. The numerical parametric study of ballistic impacts caused by similar conditions in experimental work is undertaken to predict the ballistic limit velocity, energy absorbed by the target, and comparisons between simulations by using ANSYS AUTODYN 3D v.12.1 software and experimental work to study the effects of the shape of the projectile with different (4, 8, 12, 16 and 20mm) thicknesses on the ballistic limit velocity. While only one thickness was used with 24mm of back stacking sequence, it was not penetrated. The sequence of the Al plate position (front, middle and back) inside laminate plates of the composite specimen was also studied. The Al back stacking sequence plate for the overall results obtained was the optimum structure to resist the impact loading. The simulation results obtained of the residual velocity hereby are in good agreement with the experimental results with an average error of 1.8%. The energy absorption was obtained with 7.3% and 2.7% of the back to front and back to middle of the Al stacking sequence respectively. Hence, the back Al stacking sequence is considered the optimum position for resisting the impact loading. The data showed that these novel sandwich structures exhibit excellent energy-absorbing characteristics under high-velocity impact loading conditions. Hence, it is considered suitable for aerospace applications.

Simulations of High Velocity Impacts of Ice on Carbon/Epoxy Composite Laminates

2014 ◽  
Vol 566 ◽  
pp. 505-510 ◽  
Author(s):  
Jesús Pernas-Sánchez ◽  
José Alfonso Artero-Guerrero ◽  
David Varas ◽  
Jorge López-Puente
Keyword(s):  
Mechanical Behavior ◽  
High Velocity ◽  
Composite Laminates ◽  
Epoxy Composite ◽  
Experimental Tests ◽  
High Velocity Impact ◽  
Velocity Impact ◽  
Wide Range ◽  
High Velocity Impacts ◽  
The Impact

In this work simulations of high velocity impacts of ice spheres on carbon/epoxy laminates are accomplished. The Drucker-Prager model has been chosen to describe the mechanical behavior of the ice under high velocity impact conditions. Results have been validated by means of experimental tests performed in a wide range of impact velocities. The delaminated area was chosen as comparison variable, and reflects that the model predicts adequately the impact process.

The High Velocity Impact Response of Novel Fiber Metal Laminates

2001 ◽  
Author(s):  
Wesley J. Cantwell ◽  
Graham Wade ◽  
J. Fernando Guillen ◽  
German Reyes-Villanueva ◽  
Norman Jones ◽  
...  
Keyword(s):  
High Velocity ◽  
Impact Resistance ◽  
High Velocity Impact ◽  
Fiber Metal Laminates ◽  
Velocity Impact ◽  
Glass Fiber Reinforced ◽  
Fiber Metal ◽  
Energy Absorbing ◽  
Dynamic Loading Conditions ◽  
The Impact

Abstract The impact resistance of a range of novel fiber metal laminates based on polypropylene, polyamide and polyetherimide matrices has been investigated. Initial attention focused on optimizing the interface between the composite and aluminum alloy constituents. Here, it was shown that composite-metal adhesion was excellent in all systems examined. In addition, tests at crosshead displacement rates up to 3 m/s indicated that the interfacial fracture energies remained high under dynamic loading conditions. High velocity impact tests on a series of 3/2 laminates (3 layers of aluminum/2 layers of composite) highlighted the outstanding impact resistance of a number of these systems. The glass fiber reinforced polypropylene system offered a particularly high impact resistance exhibiting a perforation energy of approximately 160 Joules. Here, failure mechanisms such as extensive plastic drawing in the aluminum layers and fiber fracture in the composite plies were found to contribute to the excellent energy-absorbing characteristics of these systems.

The fracture properties of fiber metal laminates based on a 3D printed glass fiber composite

2020 ◽  
pp. 089270572097617
Author(s):  
B Yelamanchi ◽  
E MacDonald ◽  
NG Gonzalez-Canche ◽  
JG Carrillo ◽  
P Cortes
Keyword(s):  
3D Printing ◽  
Glass Fiber ◽  
High Velocity ◽  
Metal Composite ◽  
High Velocity Impact ◽  
Fiber Metal Laminates ◽  
Velocity Impact ◽  
Impact Performance ◽  
Fiber Metal ◽  
The Impact

Fiber Metal Laminates (FML) are structures that contain a sequential arrangement of metal and composite materials, which are of great interest to the aerospace sector due to the superior mechanical performance. The traditional manufacturing process for FML involves considerable investment in manufacturing resources depending on the design complexity of the desired components. To mitigate such limitations, 3D printing enables direct digital manufacturing to create FML with customized configurations. In this work, a preliminary mechanical characterization of additively-manufacturing-enabled FML has been investigated. A series of continuous glass fiber-reinforced composites were printed with a Markforged system and placed between layers of aluminum alloy to manufacture hybrid laminate structures. The laminates were subjected to tensile, interfacial fracture toughness, and both low-velocity and high-velocity impact tests. The results showed that the FMLs appear to have a good degree of adhesion at the metal-composite interface, although a limited intralaminar performance was recorded. It was also observed that the low and high-velocity impact performance of the FMLs was improved by 9–13% relative to that of the constituent elements. The impact performance of the FML appeared to be related to the fiber fracture, out of plane perforation and interfacial delamination within the laminates. The present study can provide an initial research foundation for considering 3D printing in the production of hybrid laminates for static and dynamic applications.

Study of the Impact Performance of Solder Joints by High-Velocity Impact Tests

2010 ◽  
Vol 39 (12) ◽  
pp. 2536-2543 ◽  
Author(s):  
Ning Zhang ◽  
Yaowu Shi ◽  
Fu Guo ◽  
Fuqian Yang
Keyword(s):  
High Velocity ◽  
Solder Joints ◽  
High Velocity Impact ◽  
Velocity Impact ◽  
Impact Performance ◽  
Impact Tests ◽  
The Impact

THE MECHANISM OF SHOCK COMMINUTION OF 3D C/SIC COMPOSITE SUBJECTED TO HIGH VELOCITY IMPACT

2008 ◽  
Vol 22 (09n11) ◽  
pp. 1510-1517
Author(s):  
QINGMING ZHANG ◽  
FENGLEI HUANG ◽  
LI CHEN ◽  
LIMING HAN ◽  
JINZHU LI
Keyword(s):  
Experimental Investigation ◽  
High Velocity ◽  
Ceramic Matrix Composite ◽  
Three Dimensional ◽  
Ceramic Matrix ◽  
Impact Point ◽  
High Velocity Impact ◽  
Velocity Impact ◽  
Sic Ceramic ◽  
The Impact

In this paper, experimental investigation and theoretical analysis are carried out in an attempt to study the response of SiC ceramic matrix composite reinforced with three dimensional braided fabric(3 D C/SiC ) under high velocity impact. The results show that 3 D C/SiC composite will be turned into comminution if the pressure of the impact point resulted from the projectile impacting 3 D C/SiC composite sample is larger than 780Mpa. Based on the analysis of the mechanism of composite comminution, a theoretical model has been developed.

Sign in / Sign up

Export Citation Format

Share Document