Carbon Fiber-reinforced Polymer Composite Laminates Research Articles

Damage detection and classification of carbon fiber-reinforced polymer composite materials based on acoustic emission and convolutional recurrent neural network

Carbon fiber-reinforced polymer (CFRP) composite laminates generate acoustic emission signals during the tensile process, which can be used to identify the type of acoustic emission (AE) signal at a given moment and determine the current damage condition. However, due to the large number and complexity of AE signals generated during the tensile process of carbon fiber composite laminates, it is challenging to manually identify and annotate them. To address this issue, we propose a low-complexity classification and detection network model based on the convolutional recurrent neural network (CRNN) architecture. First, we construct a dataset of composite damage signals for a single damage category and use log-mel spectrogram features to train the model for that specific category of damage signals. Then, we utilize the trained model to recognize the AE signals of CFRP composite laminates. The proposed method achieves an accuracy of 99.02% in classifying single damage modes in the test set and effectively distinguishes the types of AE signals generated during the damage process of CFRP composite laminates. Compared with the classic classification model using AE signals, the number of parameters in our proposed low-complexity CRNN model is reduced by 94.42%. It also demonstrates that 19.4% of the AE signals during the damage process are in a superimposed state, indicating the simultaneous occurrence of multiple damage modes in CFRP composite laminates.

Enhancing the Longitudinal Compressive Strength of Freeform 3D-Printed Continuous Carbon Fiber-Reinforced Polymer Composite Laminate Using Magnetic Compaction Force and Nanofiber Z-Threads.

Low fiber-direction compressive strength is a well-recognized weakness of carbon fiber-reinforced polymer (CFRP) composites. When a CFRP is produced using 3D printing, the compressive strength is further degraded. To solve this issue, in this paper, a novel magnetic compaction force-assisted additive manufacturing (MCFA-AM) method is used to print CFRP laminates reinforced with carbon nanofiber (CNF) z-threads (i.e., ZT-CFRP). MCFA-AM utilizes a magnetic force to simultaneously levitate, deposit, and compact fast-curing CFRP prepregs in free space and quickly solidifies the CFRP laminate part without any mold nor supporting substrate plate; it effectively reduces the voids. The longitudinal compressive test was performed on five different sample types. ZT-CFRP/MCFA-AM samples were printed under two different magnetic compaction rolling pressures, i.e., 0.5 bar and 0.78 bar. Compared with the longitudinal compressive strength of a typical CFRP manufactured by the traditional out-of-autoclave-vacuum-bag-only (OOA-VBO) molding process at the steady-state pressure of 0.82 bar, the ZT-CFRP/MCFA-AM samples showed either comparable results (by -1.00% difference) or enhanced results (+7.42% improvement) by using 0.5 bar or 0.78 bar magnetic rolling pressures, respectively.

Study of the dynamic response and damage evolution of carbon fiber/ultra-thin stainless-steel strip fiber metal laminates under low-velocity impact

Two configurations of carbon fiber/ultra-thin stainless-steel strip fiber metal laminates (CUSFML) with differing metal volume contents (35.3% and 18.2%) and carbon fiber-reinforced polymer (CFRP) composite laminates were selected for tests. The impact response and the effect of metal volume content on the impact resistance of CUSFML were assessed via experiment and FEM. Inducing damage by drop-weight test within the impact energy range of 18.60–46.23 J, two types of CUSFML and CFRP composite laminates were compared. In particular, the bearing capacity, impact deflection, failure modes, and energy dissipation were considered. The impact modeling using the VUMAT subroutine refines the relationship between energy-dissipating mechanism and damage evolution. The results indicate that CUSFML are characterized by higher impact resistance than CFRP composite laminates under low-velocity impact. The effect of metal volume content on the impact resistance increases gradually with impact energy increasing. Under 46.23 J impact, the CUSFML with higher metal volume content exhibits more concentrated damaged area with severe penetration failure, which is more dominated by metal failure features with a higher proportion of plastic energy dissipation. For CUSFML with lower metal volume content, extensive delamination and damage expansion occurs under the dominance of fiber damage behaviors.

On the mechanical behavior of carbon fiber/epoxy laminates exposed in thermal cycling environments

Carbon fiber reinforced polymer (CFRP) composites are commonly used for reflectors of artificial satellites operating in low earth orbit (LEO). The decay of the modulus of the CFRP composite varies under different thermal cycling environments, which can lead to a reduction in the accuracy of the reflector panels, affecting the transmission of signals. This paper investigates the impact of different thermal cycling conditions on the mechanical behavior of carbon fiber/epoxy laminated composites experimentally. Three kinds of thermal cycling conditions involving continuous temperature changes are employed to explore the influence of temperature range on the residual tensile and in-plane shear moduli of the laminates. Test results indicate that the upper temperature limit and the temperature span of the thermal cycling conditions jointly affect the mechanical properties of CFRP composite laminates, but the responses of the residual tensile and in-plane shear moduli are different under the variation of each temperature parameter alone. The residual tensile and in-plane shear moduli of the laminates under thermal cycling decrease with an expansion of the temperature span having the same upper limit. If the temperature span remains constant, an increase in the upper temperature limit leads to an increase in the residual tensile modulus, but a decrease in the residual in-plane shear modulus. The main damages causing the decay of residual tensile and in-plane shear moduli of unidirectional laminates were investigated by scanning electron microscopy (SEM) technology. Observations of the microscopic fracture of the material show that the post-curing reaction factor predominantly influences the residual tensile modulus of unidirectional laminates, while the fiber/matrix interface damage factor dominates the residual in-plane shear modulus of the unidirectional laminates. Furthermore, an increase in the fiber tensile modulus decreases both residual tensile and residual in-plane shear moduli. Notably, the residual in-plane shear modulus exhibits greater sensitivity to thermal cycling compared to the residual tensile modulus. The findings reported in this paper would provide valuable insights and guidance for the design and application of carbon fiber/epoxy composites subjected to thermal cycling conditions.

Integrated composite electrothermal de-icing system based on ultra-thin flexible heating film

Icing is a serious threat to the flight safety of aircraft. Lightweight and efficient electrothermal de-icing systems for carbon fiber reinforced polymer components are expected to contribute to the lightweighting and electrification of aircraft. This study presents the development and test of a novel, integrated, multifunctional composite electrothermal ice protection system. The system achieves this by incorporating a carbon-based ultra-thin flexible heating film into a carbon fiber-reinforced polymer composite laminate. T700 and M40 carbon fiber prepregs were used. The system composition and configuration were designed based on the anisotropic mechanical and thermal properties of the carbon fiber-reinforced polymer composite. The effects of ply stacking sequence, presence of insulation layer, ply angle, heating area, and prepreg type on thermal response and de-icing performance were investigated. Thermal response experiments were carried out in both room temperature and low temperature environments. A one-dimensional thermal response analysis model was developed for a representative heating structure. Comparative de-icing experiments were conducted on different samples in a low-temperature test chamber. A numerical model, based on the modified enthalpy-porosity method, was developed to simulate the de-icing process, and showed good agreement with the experimental results. Experiments and numerical calculations show that the arrangement of the heater close to the deicing surface improves the performance of the electrothermal deicing system while maintaining the overall mechanical properties of the multi-layer structure. While the insulation layer helps marginally with heat loss during de-icing, it significantly increases the system’s thermal inertia, which delays the de-icing’s start. It is recommended to minimize or eliminate insulation layer thickness. Rapid de-icing effects, combined with energy conservation, can be achieved through a short-term, high-power heating strategy.

Cyclic aging analysis of CFRP and GFRP composite laminates

When a composite laminate is subjected to humidity, moisture diffusion occurs depending on the number and thickness of the lamina. Water diffusion changes the mechanical response of laminates and usually causes a significant reduction of the mechanical properties of the composite specimens in ocean structures. One of the most important mechanical properties of laminates is flexural stiffness which should be considered in the design procedure. Despite the extensive research on single cycle aging of composites, cyclic aging of these materials is less explored. The aim of the current research is to investigate the variation of mechanical properties of carbon fiber reinforced polymer (CFRP) and glass fiber reinforced polymer (GFRP) composites as a substrate in adhesive joints with the same initial flexural stiffness values subjected to cyclic wet/dry aging conditions for long-term structural applications. The matrix used in the CFRP and GFRP composites are based on epoxy and vinyl ester, respectively. Both unaged and cyclically aged samples were characterized by tensile and three-point bending tests. In order to simulate the moisture absorption condition of composites in adhesive joints, one side of the composite laminates was sealed with aluminum foils and three sides were exposed to humidity. The interaction between the composite thickness and the number of aging cycles was also investigated. The experimental results show that in cyclic aging condition, the reduction of flexural stiffness in CFRP is more than GFRP laminates and GFRP laminates is more suitable for ocean applications.

Low velocity impact behavior of auxetic CFRP composite laminates with in-plane negative Poisson’s ratio

Introducing auxeticity or negative Poisson’s ratio is one potential solution to mitigate the low velocity impact damage of fiber reinforced polymer matrix composites, which can be achieved by tailoring the layup of an anisotropic composite laminate. This study aims to investigate the effect of laminate-level in-plane negative Poisson’s ratio on the low velocity impact behavior of carbon fiber reinforced polymer (CFRP) matrix composites using numerical simulations. The layups of the auxetic composites that allow them to produce negative Poisson’s ratios are identified based on the Classical Lamination Theory and verified through fundamental coupon-level experimental tests. To ensure meaningful comparisons, the non-auxetic counterpart composites are designed by allowing them to produce positive in-plane Poisson’s ratio while closely matching the longitudinal effective modulus of the auxetic laminate. The simulation results indicate that the auxetic laminates suffer smaller (12.6% on average) delamination area in top and bottom interfaces, much smaller (38% on average) matrix compressive damage in the top and bottom plies, and smaller (14.6% on average) fiber tensile damage area in each ply of the laminate at relatively higher impact energies (5 and 8 J).

Effect of hygrothermal aging on moisture diffusion and tensile behavior of CFRP composite laminates

Carbon Fiber Reinforced Polymer (CFRP) composites are widely used in aircraft structures, because of their superior mechanical and lightweight properties. CFRP composites are often exposed to hygrothermal environments in service. Temperature and moisture can affect the material properties of composites. In order to make clear the moisture diffusion behavior and the properties degradation of composites, the TG800/E207 composite laminates with four stacking sequences [0]16, [90]16, [±45]4s, and [(+45/0/0/–45)s]s are designed and manufactured. Moisture absorption tests are carried out at 80 ℃, 90 %RH. It is shown that the moisture absorption curves of composite laminates present a three-stage. A modified Fickian model was proposed to capture the diffusion behavior of TG800/E207 composite laminates. The relationships among the non-Fickian parameters, the environmental parameters and the stacking sequences of CFRP were correlated and compared. Results showed that the modified Fickian curve is sensitive to the diffusivity of Stage I and Stage II. Compared with unaged specimens, the maximum tensile stress for [0]16, [90]16, [±45]4s, and [(+45/0/0/–45)s]s decreased by 14.94 %, 28.15 %, 11.96 %, and 26.36 %, respectively. The strains at failure for [0]16, [90]16, [±45]4s, and [(+45/0/0/–45)s]s decreased by 55.38 %, 62.65 %, 46.41 %, and 31.71 %, respectively. The elastic modulus for [0]16, [90]16, [±45]4s, and [(+45/0/0/–45)s]s increased by 90.93 %, 94.57 %, 49.22 %, and 8.22 %, respectively. [90]16 sample has the minimum saturated moisture content and the maximum strength degeneration.

Structural health monitoring of carbon fiber reinforced polymer composite laminates for offshore wind turbine blades based on dual maximum correlation coefficient method

Structural health monitoring (SHM) of offshore wind turbine blades (OWTBs) is critical to the safety of wind turbines, which can avoid catastrophic failures and reduce offshore wind turbine operation and maintenance costs. Combined with the damage imaging algorithm based on the reconstruction algorithm for the probabilistic inspection of defects (RAPID), a Lamb wave baseline-free detection method based on maximum similarity of forward-path is proposed to detect the damage of OWTB carbon fiber-reinforced polymer composite laminates. Damage can introduce nonlinearity into the structure, affecting the correlation of the response signal in the forward path with the original input signal. A new method for calculating the baseline-free damage index (DI) based on the dual maximum correlation coefficient method (DMCCM) is proposed by analyzing the maximum correlation coefficient between the forward path response signal and the original excitation signal. The proposed DMCCM compensates the DI by twice comparing the local maximum correlation coefficients and reducing the errors caused by the interference of the reflected wave to the direct wave and the offset of the peak point when intercepting the response signal. Experimental studies are performed using OWTB composite laminates to validate the proposed method further. The detection results of DMCCM are more reliable, accurate, and require less time than existing methods, which is a very promising baseline-free method for visual SHM of OWTB composite laminates.

Significantly improving thermal conductivity of carbon fiber polymer composite by weaving highly conductive films

This paper significantly improved the transverse thermal conductivity (TC) of unidirectional carbon fiber reinforced polymer (CFRP) laminates by a simple and effective method of weaving highly conductive films (HCFs), including Copper (Cu) film and highly oriented graphite film (HOGF). The TC and interlaminar shear strength (ILSS) of HCF enhanced CFRP (HCF-CFRP) composite laminates were measured. The results show that the HCF-CFRP composite with a larger geometric undulation of HCF has a higher through-thickness TC. And the through-thickness and in-plane transverse TCs can be regulated by the undulation of HCF. The maximum through-thickness TCs of HCF-CFRPs are up to 49.19 W m−1 K−1 for HOGF-CFRP with 1.97 vol% HOGF, and up to 21.45 W m−1 K−1 for Cu-CFRP with 1.74 vol% Cu film, which are 11029% and 4753% higher than that of CFRP, respectively. Numerical simulation and infrared thermography demonstrate that the geometric undulation and ultrahigh in-plane TC of HOGF lead to the formation of a rapid through-thickness heat transfer path. In addition, the ILSSs of HOGF-CFRP and Cu-CFRP are 44.01 and 40.91 MPa, respectively, which are 13.76% and 19.77% lower than that of CFRP.

Flexural Strengthening of Prestressed Girders with Partially Damaged Strands Using Enhancement of Carbon Fiber Laminates by End Sheet Anchorages

This paper examines the impact of flexural strengthening on the percentage of damaged strands in internally unbonded tendons in partially prestressed concrete beams (0, 14.28%, and 28.57%) and the recovering conditions using CFRP composite longitudinal laminates at the soffit, and end anchorage U-wrap sheets to restore the original flexural capacity and mitigate the delamination of the soffit of longitudinal Carbon Fiber Reinforced Polymer (CFRP) laminates. The composition of the laminates and anchors affected the stress of the CFRP, the failure mode, and thus the behavior of the beam. The experimental results revealed that the usage of CFRP laminates has a considerable impact on strand strain, particularly when anchors are employed. The EB-CFRP laminates increased the flexural capacity by approximately 13%, which corresponds to strand damage of 14.28%, while flexural capacity increased by 9.3%, strand damage increased by 28.57% for members strengthened with laminates only, and around 21.58% and 16.85% for members reinforced with laminates and end anchorings. Quasi-experimental equations have been proposed to estimate the actual stress of untethered tendons considering the effect of CFRP laminates and final fixation winding.

Influence of the different surface treatments on fracture property of CFRP adhesive joint

Surface treatment before the bonding process for carbon fiber reinforced polymer composite (CFRP) laminate is an effective method to improve the adhesive bonding strength of the joint. In this paper, UV laser treatment and mechanical treatment were implemented to regulate the surface condition of CFTP laminate, and then the treated zone was characterized to research the reasons why adhesive joints exhibit different mechanical properties under various surface treatments. The surface resin was thoroughly and evenly removed by UV laser while the carbon fibers remained intact. Additionally, the UV laser treatment could reduce the contact angle of the CFRP surface, leading to an improvement in wettability and surface free energy. The CFRP adhesive joints treated by UV laser reach an average shear strength of 31.51 MPa, which is 42.32% greater than joints treated by mechanical grinding with an average shear strength of 22.14 MPa. The main fracture mode of the adhesive joint with UV laser treatment is the cohesive failure of adhesive film, as compared to the joint with mechanical treatment, whose fracture mode includes cohesive failure and adhesion failure between the adhesive film and CFRP laminate.

Linear-Nonlinear Stiffness Responses of Carbon Fiber-Reinforced Polymer Composite Materials and Structures: A Numerical Study.

The stiffness response or load-deformation/displacement behavior is the most important mechanical behavior that frequently being utilized for validation of the mathematical-physical models representing the mechanical behavior of solid objects in numerical method, compared to actual experimental data. This numerical study aims to investigate the linear-nonlinear stiffness behavior of carbon fiber-reinforced polymer (CFRP) composites at material and structural levels, and its dependency to the sets of individual/group elastic and damage model parameters. In this regard, a validated constitutive damage model, elastic-damage properties as reference data, and simulation process, that account for elastic, yielding, and damage evolution, are considered in the finite element model development process. The linear-nonlinear stiffness responses of four cases are examined, including a unidirectional CFRP composite laminate (material level) under tensile load, and also three multidirectional composite structures under flexural loads. The result indicated a direct dependency of the stiffness response at the material level to the elastic properties. However, the stiffness behavior of the composite structures depends both on the structural configuration, geometry, lay-ups as well as the mechanical properties of the CFRP composite. The value of maximum reaction force and displacement of the composite structures, as well as the nonlinear response of the structures are highly dependent not only to the mechanical properties, but also to the geometry and the configuration of the structures.

Strength degradation and fractographic analysis of carbon fiber reinforced polymer composite laminates with square / circular hole using scanning electron microscope micrographs

AbstractIn this article, experimental study has been carried out to obtain comparative information intended for designing and assembly of structural components made of carbon fiber reinforced polymer (CFRP) composite. Investigation on tensile strength has been done on unidirectional CFRP composite laminates with hole. Effect of stacking sequence, hole size, and hole shape on tensile strength has been examined independently by open hole tensile (OHT) test. Reduction in OHT strength is observed when stacking sequence is changed from [0]8 to [0/90]2s and when the hole size is increased. However, OHT strength is noticed to get increased when hole shape is changed from circular to square. Laminates containing square shaped hole demonstrate less sensitiveness towards tensile strength and show negligible effect of stacking sequences on the normalized strength than the circular hole. Fractographic analysis figures out the failure mechanism of tested specimens by correlating their mechanical properties. SEM micrographs and data analysis reveal that axial splits and local delamination effectively blunt the stress concentration around the hole resulting in higher OHT strength and less notch sensitiveness towards tensile strength.

Progressive failure analysis of CFRP composite laminates under uniaxial tension using a discrete element method

This study presents a 3D Discrete Element Method (DEM) model for the progressive failure analysis of Carbon Fiber Reinforced Polymer (CFRP) composite materials subjected to uniaxial tensile loading. Particles in the model are packed and bonded in regular patterns (hexagonal or square). The relationship between the bond stiffness and material properties is established based on the average strain energy method. The random distribution of bond strengths calibrated from experiments with a variation of 30% and 10% following a normal distribution law is assigned to the bonds in 0∘ and 90∘ plies to capture random cracks, respectively. Tsai-Hill failure criterion is utilized for the calibration of bond strength of [Formula: see text] plies to predict their failures in composite laminates. Quantitative and qualitative analyses were conducted for predicting the damage initiation and propagation of the cross-ply and Quasi-Isotropic (QI) composite laminates under tensile loading, respectively. Two interface stiffnesses were utilized in the failure prediction of cross-ply composite laminates, and it was found that the numerical results with the interface stiffness calculated from fracture energy are in good, quantitative agreements with the experiments. All the four stages of the failure process of QI composite laminates are well captured by the 3D DEM model, including isolated cracks, inner delamination cracks, outer delamination cracks and final failure.

Global sensitivity analysis of low-velocity impact response of bio-inspired helicoidal laminates

The preform architectures and the variability of the constituents of carbon fiber reinforced polymer (CFRP) composites materials can affect their mechanical behaviors significantly. This paper describes a systematic analysis of the low-velocity impact response and energy absorption capacity of biomimetic architected CFRP laminates. High-fidelity multiscale Finite Element (FE) models considering constituent material property uncertainties are developed to evaluate the effect of pitch angles on the impact performance of Bouligand architected composite laminates. Experimental results extracted from open literature have been used to validate the low velocity impact response of the CFRPs predicted by the numerical model. Constituent material property uncertainties are identified as parametric variables, and the peak impact load and energy absorption responses of the bio-inspired CFRPs are obtained with the verified numerical models. The main effect sensitivity indices of the parameters are then calculated based on a variance-based global sensitivity analysis model. The presented studies clearly shows that smaller pitch angles and larger fiber longitudinal elastic modulus achieve more desirable impact resistance and better energy-absorption characteristics. This study aim to open up new possibilities for improving low velocity impact performance of CFRP composite laminates by adopting bionic design approach and considering constituent materials effect.

Analysis of boundary condition in modelling the low-velocity impact carbon-fiber reinforced polymer composite laminates

The effect of modelling strategy on boundary condition and impact energy of low-velocity impact laminate has been investigated. The paper deals with the finite element model (FEM) to study the structural responses of carbon fibre reinforced polymer (CFRP) composite laminate of CCF300/epoxy. In FE calculation, a proposed three-dimensional progressive damage model is used to determine the intralaminar damage, while cohesive contact formulation is employed to analyse the interlaminar damage. The failure model performances are validated and verified based on different boundary conditions and impact energies. Through experiment and simulation, it can be said that variation in boundary condition as well as impact energy, significantly change the force-time, displacement-time, energy-time, and load-displacement histories.

Thermo-elastic behaviour of carbon-fiber reinforced polymer and the effect of adding nanoparticles at elevated heat intensity

Thermal stress development in materials could lead to structural failure in engineering applications. Carbon-fiber reinforced polymer composite (CFRP) have gained wide acceptance in the manufacturing industry. However, its thermo-elastic behaviour at elevated temperatures still remains an open question. Heat transfer analysis coupled with material layer-wise arrangement technique of the CFRP was implemented to investigate the thermo-elastic behaviour of these composites. A finite element model (FEM) was built and studied using COMSOL Multiphysics software. The heat energy applied in the simulation was sourced from a heat beam model. The deposited beam power was varied from 10 to 200W, and focused at the centre of the laminate (yp = 0.15 m). The laminates considered were made up of six layers with distinctly different stacking sequences. The thermal stresses and strains obtained from the finite element analysis were assessed to observe the material's behaviour when subjected to increasing thermal load. Results revealed that thermal stresses are intense along fiber-direction of the composite laminates. The CFRP material was found to give good thermo-elastic characteristics at lower deposited heat power, however, this was not the case for higher deposited heat power (e.g. 200 W). The anisotropic property of the laminate had a significant influence in managing the thermal stresses. The study was repeated for carbon fibers doped with nanoparticles of silicon carbide (CFSiC) and resin bonded glass fiber (RBGF). It was found that the results were distinctly different when compared with the CFRP laminate. CFSiC showed to exhibit an ehanced thermo-elastic behaviour, due to the high thermal stability of SiC nanoparticles in the composite.

Effect of hygrothermal aging on static behavior of quasi-isotropic CFRP composite laminate

Abstract The Carbon fiber reinforced polymer (CFRP) composites used in offshore and marine industries tend to deal with high temperatures and humid conditions throughout its life. This work investigates the effect of long term hygrothermal aging on the physical and mechanical properties of CFRP composites. The IMA/M21 carbon fiber epoxy quasi-isotropic Multidirectional laminate with stacking sequence [±45, 0, 90] 2S was fabricated using vacuum assisted resin transfer moulding . The static specimens were immersed in room temperature (RT) and comparatively high temperature (HT) tap water at 70 °C up to saturation. The kinetics of moisture absorption was monitored up to saturation as a function of time which followed a two-stage model. The static strength of virgin, RT aged and HT aged specimens were determined with a constant cross-head speed of 1 mm/min. The post-saturation static strength showed a major drop however reduction in compressive strength was higher than tensile strength in a matrix dominated failure. Similarly, the hygrothermal aged specimen showed higher moisture absorption and strength reduction as compared to RT aging. The SEM and FESEM micrographs clearly revealed matrix erosion and fiber-matrix interfacial debonding after saturation. The TGA analysis of the moisture absorbed specimen showed a degraded physical property.

The effect of hybridization on high-velocity impact response of carbon fiber-reinforced polymer composites using finite element modeling, Taguchi method and artificial neural network

In this paper, the effect of hybridization of carbon fiber-reinforced polymer (CFRP) composite laminates was investigated on the high-velocity impact responses of laminates using a validated finite element model, the Taguchi and the artificial neural network methods. The CFRP laminates were hybridized by replacing half of the carbon layers with glass and Kevlar laminae. It was found out that employing the right hybrid materials on the right position of the laminate can considerably change the damage pattern and consequently reduce the projectile residual velocity by increasing the energy absorbed by the CFRP laminate. Introducing four Kevlar laminae on the back of the CFRP composite laminate instead of the four carbon layers resulted the highest improvement in the laminate energy absorption by 67%. The hybrid laminates experienced wider damage zone and more extensive delamination compared to the CFRP laminate. Introducing the hybrid materials with high strength and strain to failure material such as Kevlar on the back of the laminate in the presence of CFRP front face can be considered as an appropriate hybrid composite laminate when exposed to high-velocity impact loading.