# Mechanical Properties of Epoxy and Its Carbon Fiber Composites Modified by Nanoparticles

Authors: Fang Liu; Shiqiang Deng; Jianing Zhang
Journal: Journal of Nanomaterials
 (2017)

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## Abstract

Compressive properties are commonly weak parts in structural application of fiber composites. Matrix modification may provide an effective way to improve compressive performance of the composites. In this work, the compressive property of epoxies (usually as matrices of fiber composites) modified by different types of nanoparticles was firstly investigated for the following study on the compressive property of carbon fiber reinforced epoxy composites. Carbon fiber/epoxy composites were fabricated by vacuum assisted resin infusion molding (VARIM) technique using stitched unidirectional carbon fabrics, with the matrices modified with nanosilica, halloysite, and liquid rubber. Testing results showed that the effect of different particle contents on the compressive property of fiber/epoxy composites was more obvious than that in epoxies. Both the compressive and flexural results showed that rigid nanoparticles (nanosilica and halloysite) have evident strengthening effects on the compression and flexural responses of the carbon fiber composite laminates fabricated from fabrics.


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## Body

## 1. Introduction

With extensive applications of polymer and its composites, the demand for materials that possess excellent mechanical properties is increasing. It is well known that most advanced fiber composites are stronger in tension (in the fiber direction) than in compression. This behavior is due to fact that the compressive strength of unidirectional composites is governed by microbuckling of fibers embedded in the matrix [1, 2], with the fiber waviness being the major factor [3]. Compressive properties are commonly weak parts in structural application of composites, particularly for the composite laminates prepared using fiber fabrics. The similar situation also exists for mechanical performance of the composites under flexural loads. The reductions in compressive and flexural behaviors of the composite laminates using fabrics are greatly attributed to the presence of fiber waviness [4, 5]. Currently, cost-effective manufacture methods, such as resin transfer molding (RTM) and vacuum assisted resin infusion molding (VARIM), are being extensively used for mass production of composite structures, which use fiber fabrics or preform as reinforcements, instead of prepregs. Therefore, improvements in compression and flexural properties via proper methods can definitely benefit composite structural design and lead to the wider applications of the materials in different areas. Obviously, matrix strengthening is primarily one of the approaches among the methods to improve the compression and flexural properties of the composites manufactured from fiber fabrics [6–8].Addition of a small amount of rigid nanoparticles in a polymer matrix has been proved to increase its mechanical properties significantly [9–13]. Some attempts have been made to take this advantage of nanoparticle reinforced matrix to enhance the mechanical performance of fiber composites [8, 14–16]. Many published studies extensively focused on tensile properties, fracture toughness, and interfacial strength of carbon fiber composite [17–21] with modified matrices using nanoparticles. Only a limited number of studies were conducted to investigate the influence of nanoparticles on the compressive and flexural properties of fiber/epoxy composites, particularly, for the composites prepared by RTM and VARIM.Cho et al. [22] reported 10% and 16% improvement in longitudinal compressive strength of carbon/epoxy composites with 55% fiber volume fraction by adding 3 wt.% and 5 wt.% graphite nanoparticles in epoxy matrices. He et al. [23] investigated compressive strength of nano-calcium carbonate/epoxy and its fiber composites, revealing a noticeable improvement of 13.5% and 14.1%, increases in compressive strength, for the cured bulk epoxy matrix and its fiber composites filled with 4 wt.% nano-CaCO3. Sánchez et al. [24] also observed large rises in the flexural strength when functionalized carbon nanotubes were added, with the improvement of 12% in flexural strength at CNT–NH2 content of 0.3 wt.%.In the present study, carbon fiber/epoxy composites with their matrices modified by rigid nanoparticles and CTBN liquid rubber were manufactured using the unidirectional fiber fabrics by means of VARIM. Different amounts of nanofillers (silica, CTBN liquid rubber, and halloysite particles) were incorporated into the epoxy matrices reinforced by carbon fiber fabrics, which were impregnated by resin infusion with the help of vacuum bag. Curing of the impregnated laminate was completed using a hot pressing device. Characterizations of compressive and flexural properties were conducted to elaborate the mechanical properties of the modified matrices and the resulting composites and to verify the influence of the nanoparticle types in order to explore the possibility of using rigid nanofillers to improve compressive and flexural performance of the composite laminates fabricated from fiber fabrics.


## 2. Experimental

### 2.1. Materials

A DGEBA epoxy resin (Araldite-F, Huntsman) was used as matrices for carbon fiber reinforced composites. A hardener, piperidine (Sigma–Aldrich, Australia), was used at a ratio of 100 : 5 by weight for curing the epoxies. The modifiers of the matrices were silica nanoparticles dispersed in epoxy (Nanopox XP, Nanoresins, Germany), a CTBN liquid rubber (Hycar CTBN 1300X13), and halloysite particles (Imerys Tableware New Zealand Limited). Nanopox XP consists of surface-modified silica nanoparticles (40 wt.%) with an average particle size of 20 nm. Halloysite particles were first washed using acetone and then mixed with the Araldite-F epoxy to form epoxy-based nanocomposites (Halloysite/epoxy). The halloysite particles used in this study are mainly tubular shapes with a length of 100–500 nm and a diameter of approximately 10–50 nm [12]. Unidirectional carbon fabrics (T300), 500 mm in width, (FGI Fiber Glass International, Australia) with a dry weight of 205 g/m2 per layer, were used for fabricating carbon fiber reinforced epoxy composites (CF/EP composites). Carbon fibers in the fabrics were held together by transversal polyester stitching filaments, so that the displacement of fibers in the fabric sheets is generally constrained.


### 2.2. Fabrication of Bulk Cured Matrix Resins and CF/EP Composites

The matrix mixtures were first prepared and later used in fabrication of CF/EP composites. The designated amount of Nanopox XP, CTBN liquid rubber, and halloysite particles were blended with the DGEBA epoxy resin to obtain homogeneous mixtures by means of a mechanical mixer, stirring at 80°C for 1 h. After that, the hardener was added to the mixtures in a ratio of 100 : 5 (epoxy/hardener) by weight and stirred slowly with the mechanical stirrer for about 5 mins. In order to remove the bubbles, the mixtures were then degassed in a vacuum oven (about −100 KPa) for about 30 mins.The liquid mixtures were cast into specimen cavities in preheated silicone rubber molds and cured at 120°C for 16 h. Once the cured specimens were cooled and removed from the molds, compressive specimens were prepared according to ASTM D695. The top and bottom surfaces of a compressive specimen were kept parallel by the use of a grinding machine in order to obtain reliable compression properties during compression tests.The unidirectional CF/EP composites were fabricated by VARIM. The laminates consisted of 10 unidirectional carbon fiber fabrics, which were stacked on a metal platform in the longitudinal direction of the fibers, with one resin flow medium screen sheet and a peel ply being placed on top and bottom of the carbon fabric stacks. Then, the whole stack was sealed within a vacuum bag. Prior to the resin infusion process, vacuum was applied up to −100 KPa. The metal platform with the vacuum bag on it was positioned on top of a heating plate, so that the temperature of the vacuum bag was maintained at ~100°C to ensure that the viscosity of the resin mixture will be low enough to infiltrate into the fiber fabrics from one end to another. A heat-resistant plastic hose was embedded in the vacuum bag to allow resin transferring from the resin pot into the fabrics. The hose had precut holes in equal distance, so that the resin can flow equally out of the holes and advance simultaneously to expel any trapped air in the fabrics. Because of the tiny sizes of the nanoparticles (nanosilica and halloysite), they did not dramatically increase the viscosity of the resin mixtures, so that basically no difficulty was encountered during the resin infusion process. The final curing of the laminate was carried out in a hot press with a uniform pressure of 400 kPa under vacuum for about 16 h at 120°C. The composite laminates after curing have a fiber volume fraction of about 65%, calculated on the basis of the laminate dimensions, the weights of fabrics, and the laminate, as well as the densities of the carbon fibers and the epoxy matrix.


### 2.3. Mechanical Testing

#### 2.3.1. Compression Test for the Cured Matrix Resins

Compression tests of the cured matrix resins were conducted using an Instron 5567 universal testing machine. A specially designed fixture was used for the tests. The fixture consists of a semisphere and a support block with a half sphere hollow on it, both made of tool steel. Siting in the half sphere hollow, the semisphere was separated with the support block by a thin layer of lubricant oil, so that slight adjustment can be made automatically by the fixture during compression tests. Based on ASTM D695, a cross head speed of 1.3 mm/min was adopted.


#### 2.3.2. Compression and Flexure Tests for Composite Laminates

Longitudinal compressive tests were carried out using a MTS 810 Materials Testing System with a pair of hydraulic grips, which allow griping pressures uniformly applied on the gripping surfaces of a compression specimen, and also ensure a good alignment of the specimen with the loading axis to prevent specimen buckling during the compression tests.Compressive tests were performed according to ASTM D3410 standard. The specimens were cut from a unidirectional composite panel and tabbed with the same composite laminate coupons using a high strength epoxy glue. A compression specimen has 120 mm in overall length, 20 mm in width, and 10 mm in gage length. A clip gage was attached in between the tabs to measure the deformation of the specimen within the gage length region, so as to find out the compression modulus. All compression tests were performed at a cross head speed of 1.5 mm/min.Flexural tests were conducted using the Instron 5567 testing machine with a three-point bend fixture, which is in compliance with the ASTM D790-97 standard. Typical specimen dimensions were 55 mm in length, 13 mm in width, and 2 mm in thickness and the loading span was 40 mm.All tests were conducted at room temperature (23°C) with a humidity of 50% RH. For all mechanical tests, five specimens were successfully tested to determine failure strength and modulus in flexure and compression characterizations.For simplicity, the CF/EP composite specimens with silica (10 wt.% and 20 wt.%) were denoted as “10S” and “20S”, those specimens with rubber (10 wt.% and 20 wt.%) as “10R” and “20R,” and those with halloysite (5 wt.% and 10 wt.%) as “5H” and “10H.” All the test results obtained from the cured bulk epoxies and the composite laminates with their matrices modified nanoparticles and CTBN rubber were compared to the corresponding specimens with neat epoxy matrix.


## 2.1. Materials

A DGEBA epoxy resin (Araldite-F, Huntsman) was used as matrices for carbon fiber reinforced composites. A hardener, piperidine (Sigma–Aldrich, Australia), was used at a ratio of 100 : 5 by weight for curing the epoxies. The modifiers of the matrices were silica nanoparticles dispersed in epoxy (Nanopox XP, Nanoresins, Germany), a CTBN liquid rubber (Hycar CTBN 1300X13), and halloysite particles (Imerys Tableware New Zealand Limited). Nanopox XP consists of surface-modified silica nanoparticles (40 wt.%) with an average particle size of 20 nm. Halloysite particles were first washed using acetone and then mixed with the Araldite-F epoxy to form epoxy-based nanocomposites (Halloysite/epoxy). The halloysite particles used in this study are mainly tubular shapes with a length of 100–500 nm and a diameter of approximately 10–50 nm [12]. Unidirectional carbon fabrics (T300), 500 mm in width, (FGI Fiber Glass International, Australia) with a dry weight of 205 g/m2 per layer, were used for fabricating carbon fiber reinforced epoxy composites (CF/EP composites). Carbon fibers in the fabrics were held together by transversal polyester stitching filaments, so that the displacement of fibers in the fabric sheets is generally constrained.


## 2.2. Fabrication of Bulk Cured Matrix Resins and CF/EP Composites

The matrix mixtures were first prepared and later used in fabrication of CF/EP composites. The designated amount of Nanopox XP, CTBN liquid rubber, and halloysite particles were blended with the DGEBA epoxy resin to obtain homogeneous mixtures by means of a mechanical mixer, stirring at 80°C for 1 h. After that, the hardener was added to the mixtures in a ratio of 100 : 5 (epoxy/hardener) by weight and stirred slowly with the mechanical stirrer for about 5 mins. In order to remove the bubbles, the mixtures were then degassed in a vacuum oven (about −100 KPa) for about 30 mins.The liquid mixtures were cast into specimen cavities in preheated silicone rubber molds and cured at 120°C for 16 h. Once the cured specimens were cooled and removed from the molds, compressive specimens were prepared according to ASTM D695. The top and bottom surfaces of a compressive specimen were kept parallel by the use of a grinding machine in order to obtain reliable compression properties during compression tests.The unidirectional CF/EP composites were fabricated by VARIM. The laminates consisted of 10 unidirectional carbon fiber fabrics, which were stacked on a metal platform in the longitudinal direction of the fibers, with one resin flow medium screen sheet and a peel ply being placed on top and bottom of the carbon fabric stacks. Then, the whole stack was sealed within a vacuum bag. Prior to the resin infusion process, vacuum was applied up to −100 KPa. The metal platform with the vacuum bag on it was positioned on top of a heating plate, so that the temperature of the vacuum bag was maintained at ~100°C to ensure that the viscosity of the resin mixture will be low enough to infiltrate into the fiber fabrics from one end to another. A heat-resistant plastic hose was embedded in the vacuum bag to allow resin transferring from the resin pot into the fabrics. The hose had precut holes in equal distance, so that the resin can flow equally out of the holes and advance simultaneously to expel any trapped air in the fabrics. Because of the tiny sizes of the nanoparticles (nanosilica and halloysite), they did not dramatically increase the viscosity of the resin mixtures, so that basically no difficulty was encountered during the resin infusion process. The final curing of the laminate was carried out in a hot press with a uniform pressure of 400 kPa under vacuum for about 16 h at 120°C. The composite laminates after curing have a fiber volume fraction of about 65%, calculated on the basis of the laminate dimensions, the weights of fabrics, and the laminate, as well as the densities of the carbon fibers and the epoxy matrix.


## 2.3. Mechanical Testing

### 2.3.1. Compression Test for the Cured Matrix Resins

Compression tests of the cured matrix resins were conducted using an Instron 5567 universal testing machine. A specially designed fixture was used for the tests. The fixture consists of a semisphere and a support block with a half sphere hollow on it, both made of tool steel. Siting in the half sphere hollow, the semisphere was separated with the support block by a thin layer of lubricant oil, so that slight adjustment can be made automatically by the fixture during compression tests. Based on ASTM D695, a cross head speed of 1.3 mm/min was adopted.


### 2.3.2. Compression and Flexure Tests for Composite Laminates

Longitudinal compressive tests were carried out using a MTS 810 Materials Testing System with a pair of hydraulic grips, which allow griping pressures uniformly applied on the gripping surfaces of a compression specimen, and also ensure a good alignment of the specimen with the loading axis to prevent specimen buckling during the compression tests.Compressive tests were performed according to ASTM D3410 standard. The specimens were cut from a unidirectional composite panel and tabbed with the same composite laminate coupons using a high strength epoxy glue. A compression specimen has 120 mm in overall length, 20 mm in width, and 10 mm in gage length. A clip gage was attached in between the tabs to measure the deformation of the specimen within the gage length region, so as to find out the compression modulus. All compression tests were performed at a cross head speed of 1.5 mm/min.Flexural tests were conducted using the Instron 5567 testing machine with a three-point bend fixture, which is in compliance with the ASTM D790-97 standard. Typical specimen dimensions were 55 mm in length, 13 mm in width, and 2 mm in thickness and the loading span was 40 mm.All tests were conducted at room temperature (23°C) with a humidity of 50% RH. For all mechanical tests, five specimens were successfully tested to determine failure strength and modulus in flexure and compression characterizations.For simplicity, the CF/EP composite specimens with silica (10 wt.% and 20 wt.%) were denoted as “10S” and “20S”, those specimens with rubber (10 wt.% and 20 wt.%) as “10R” and “20R,” and those with halloysite (5 wt.% and 10 wt.%) as “5H” and “10H.” All the test results obtained from the cured bulk epoxies and the composite laminates with their matrices modified nanoparticles and CTBN rubber were compared to the corresponding specimens with neat epoxy matrix.


## 2.3.1. Compression Test for the Cured Matrix Resins

Compression tests of the cured matrix resins were conducted using an Instron 5567 universal testing machine. A specially designed fixture was used for the tests. The fixture consists of a semisphere and a support block with a half sphere hollow on it, both made of tool steel. Siting in the half sphere hollow, the semisphere was separated with the support block by a thin layer of lubricant oil, so that slight adjustment can be made automatically by the fixture during compression tests. Based on ASTM D695, a cross head speed of 1.3 mm/min was adopted.


## 2.3.2. Compression and Flexure Tests for Composite Laminates

Longitudinal compressive tests were carried out using a MTS 810 Materials Testing System with a pair of hydraulic grips, which allow griping pressures uniformly applied on the gripping surfaces of a compression specimen, and also ensure a good alignment of the specimen with the loading axis to prevent specimen buckling during the compression tests.Compressive tests were performed according to ASTM D3410 standard. The specimens were cut from a unidirectional composite panel and tabbed with the same composite laminate coupons using a high strength epoxy glue. A compression specimen has 120 mm in overall length, 20 mm in width, and 10 mm in gage length. A clip gage was attached in between the tabs to measure the deformation of the specimen within the gage length region, so as to find out the compression modulus. All compression tests were performed at a cross head speed of 1.5 mm/min.Flexural tests were conducted using the Instron 5567 testing machine with a three-point bend fixture, which is in compliance with the ASTM D790-97 standard. Typical specimen dimensions were 55 mm in length, 13 mm in width, and 2 mm in thickness and the loading span was 40 mm.All tests were conducted at room temperature (23°C) with a humidity of 50% RH. For all mechanical tests, five specimens were successfully tested to determine failure strength and modulus in flexure and compression characterizations.For simplicity, the CF/EP composite specimens with silica (10 wt.% and 20 wt.%) were denoted as “10S” and “20S”, those specimens with rubber (10 wt.% and 20 wt.%) as “10R” and “20R,” and those with halloysite (5 wt.% and 10 wt.%) as “5H” and “10H.” All the test results obtained from the cured bulk epoxies and the composite laminates with their matrices modified nanoparticles and CTBN rubber were compared to the corresponding specimens with neat epoxy matrix.


## 3. Results and Discussion

### 3.1. The Compressive Properties of Cured Bulk Matrix Resins

To determine the effects of nanoparticles on the mechanical properties of the cured epoxy resins, the compressive tests were performed on the nanocomposite coupon specimens that contain different loadings of particles. Figure1 demonstrates the load and displacement curves for the epoxy and particle/epoxy systems with the piperidine curing agent, which shows the same tendency of load-displacement curves for different types of particles. When it comes to the first peak, load decreases rapidly and then increases until specimen failure. From the compressive properties of the matric resins (shown in Table 1), it can be seen that the addition of the rigid nanoparticles increases compressive yield strength of the matric resins. The maximum strength for silica/epoxy and halloysite/epoxy is 94.78 MPa at 20 wt.% and 91.33 MPa at 15 wt.%, respectively. From Figure 2 and Table 1, it can be seen that there is a fluctuation for the strength improvement with the increment of rigid particle loading. The fluctuation could be due to the defect generated during the fabrication process. It was found that when nanoparticles were introduced into the brittle matrix, the compound became very sticky, making it difficult to uniform nanoparticles dispersing in the matrix and eradiate the embedded bubbles. No significant differences were found regarding the effect of nanoparticles on the compressive modulus of these matrix systems. For hybrid systems, compressive properties of matrix resins with 10 wt.% Silica and 5 wt.% CTBN increase most obviously. Hybrid strengthening mechanism is a more complicated issue. As shown in Figure 3, strength enhancement of hybrid systems is not simply the sum of the two improvements for each component. From the testing results, it can be seen that introducing nanofillers can influence the compressive property of epoxies.Table 1
Compressive properties of bulk matrix resins cured by piperidine.
Filler type
Weight fraction
Compressive yield strength(MPa)
Compressive modulus(GPa)
Tensile strength(MPa) [25]
Tensile modulus(GPa) [25]
Neat epoxy
89.1 ± 1.2
2.62 ± 0.05
65.8 ± 1.9
2.94 ± 0.10
Silica
2 wt.%
91.6 ± 0.4
2.63 ± 0.02
—
—
4 wt.%
91.5 ± 0.2
2.55 ± 0.03
—
—
6 wt.%
91.9 ± 0.5
2.46 ± 0.05
—
—
8 wt.%
92.3 ± 0.3
2.58 ± 0.03
—
—
10 wt.%
91.1 ± 0.2
2.71 ± 0.02
69.0 ± 0.5
3.36 ± 0.12
20 wt.%
94.8 ± 0.5
2.89 ± 0.07
—
—
Halloysite
2 wt.%
90.8 ± 0.2
2.43 ± 0.05
—
—
5 wt.%
89.3 ± 0.3
2.40 ± 0.01
68.1 ± 0.3
3.03 ± 0.13
7 wt.%
90.9 ± 0.2
2.55 ± 0.03
—
—
10 wt.%
90.4 ± 0.1
2.49 ± 0.01
68.2 ± 0.4
3.11 ± 0.08
15 wt.%
91.3 ± 0.2
2.58 ± 0.02
—
—
CTBN liquid rubber
5 wt.%
92.4 ± 0.6
2.61 ± 0.03
67.3 ± 0.7
2.09 ± 0.10
10 wt.%
89.3 ± 0.5
2.42 ± 0.06
60.1 ± 1.0
2.61 ± 0.10
Hybrid system
10 wt.% halloysite + 5 wt.% CTBN
93.0 ± 0.3
2.72 ± 0.03
65.9 ± 0.3
3.05 ± 0.11
10 wt.% silica + 5 wt.% CTBN
96.2 ± 0.9
2.77 ± 0.05
65.5 ± 0.4
3.17 ± 0.10
10 wt.% silica + 10 wt.% CTBN
90.1 ± 0.3
2.69 ± 0.04
59.2 ± 0.7
2.83 ± 0.09Figure 1
Load-displacement curves for pure epoxy and particle/epoxy systems cured by piperidine.Figure 2
Compressive yield strength improvement with the increment of silica particle loading.Figure 3
Comparison of compressive strengths of the cured epoxy systems.Compared with tensile properties [25] for the corresponding modified epoxy systems in Table 1, it can be seen that compressive yield strength is much higher than tensile strength, while compressive modulus is lower. It may be caused by fracture failure in tensile specimens. Bubbles and aggregations in matric resins will lead to stress concentration.Figure4 gives the compression damage mode of neat epoxy, which is similar to failures of the other nanoparticle/epoxy systems cured by piperidine. It can be seen that the failure specimen is box-like with an opening side.Figure 4
Comparison of pure epoxy specimens before and after compression tests.The compression failure process of pure epoxy is shown in Figure5. Side damage occurs at first, and then a damage point at bottom appears at the strain of 0.47 (Figure 5(b)). After that, the damage point propagates at bottom along the direction of 45° (Figure 5(c)) until the moment of failure at the strain of 0.56 (Figure 5(d)).Figure 5
Compression failure process of pure epoxy: (a) at beginning; (b) side damage and a damage point at bottom occur; (c) the damage point propagates at bottom along the direction of 45°; (d) at the moment of failure.
(a)
(b)
(c)
(d)


### 3.2. Compressive Properties of Unidirectional CF/Epoxy Composite Laminates

Most engineering applications of carbon fiber reinforced composites are based on multidirectional laminates. However, if the mechanism of fracture was to be fully understood, a systematic study of unidirectional composites should be first made. Hence, unidirectional composites were investigated in this study.Figure6 demonstrates the compressive load-displacement curves of carbon fiber/epoxy composites with their matrices modified by nanoparticle and CTBN rubber. As shown in Figure 6, all the specimens exhibit relatively nonlinear behaviors. The specimens failed rapidly after reaching the maximum load. When a composite, especially for unidirectional fiber reinforced composites, is subjected to a longitudinal compressive load, several main failure modes are involved [26]. These failure modes may include microbuckling, kinking, fiber failure, and longitudinal cracking (synonymous with delamination failure in general laminates) and shear failure [27]. Fiber microbuckling and kinking are considered as the dominant mechanisms of failure. Scanning electron microscopy (SEM) images of CF/epoxy composites with their matrices modified by nanoparticles and rubbers are shown in Figures 7 and 8. Fiber microbuckling and kinking can be easily seen from the specimen surface and the fracture surfaces of the compressive specimens.Figure 6
Compressive load-displacement curves of CF/epoxy composites.Figure 7
SEM images of the specimen surfaces around the failure locations for the tested CF/epoxy composite specimens.Figure 8
SEM images of fracture surfaces for CF/epoxy composite specimens after compressive tests.The compressive test results are summarized in Table2. It can be clearly seen that compressive properties of the unidirectional composite test coupons are obviously enhanced with the use of the nanoparticle reinforced epoxy matrix, while, for the composites with their matrices modified with the CTBN liquid rubber, both compressive strength and modulus are reduced. Particularly, compared with the properties of the composite specimens with the unmodified matrix, the longitudinal compressive strength was significantly increased by 22.3% with the addition of 10 wt.% of halloysite nanoparticles. The reason is believed to be the unique strengthening effect of the halloysite nanotubes as indicated in previously published research papers [12].Table 2
Compressive properties of unidirectional CF/epoxy composites.
Composite
wt.% of filler
Compressive strength(MPa)
Relative increase(%)
Compressive modulus(GPa)
Relative increase(%)
CF/EP
0
367 ± 53
—
34.9 ± 10.3
—
CF/EP-silica
10
382 ± 42
4.1
50.5 ± 6.7
44.7
CF/EP-silica
20
388 ± 36
5.7
47.9 ± 6.2
37.2
CF/EP-halloysite
5
385 ± 26
4.9
35.1 ± 4.1
0.6
CF/EP-halloysite
10
449 ± 3
22.3
38.8 ± 6.0
11.2
CF/EP-rubber
10
361 ± 14
−1.6
32.1 ± 12.1
−8.0
CF/EP-rubber
20
322 ± 13
−12.3
33.5 ± 10.0
−4.0It is noted that the compressive properties of carbon fiber composites prepared in this study are much lower than those of the composites manufactured by autoclaving using the commercial carbon fiber/epoxy prepregs. This is obviously attributed to some factors that exist in the manufacturing process of CF/EP composites by VARIM, such as the effect of the shape of the flow media screen sheet and the waviness of the fibers in the fabrics due to the use of the stitching filaments and also fabric handling during lay-ups. During the process of hot pressing, the flow media screen sheet on top and bottom of the laminate can clearly cause fiber waviness as shown in Figure9. Fiber waviness and fiber misalignment have been proved to significantly reduce the compressive properties of carbon fiber composites [4].Figure 9
Microscope images of the longitudinal cross-section of the composite laminates fabricated by VARIM, showing obvious waviness of the fabrics.However, as a compression for the effect of nanofillers on the compressive properties of composite laminates between the composite laminates with different matrix modifiers, the results are still meaningful.


### 3.3. Flexural Properties of Unidirectional CF/Epoxy Composite Laminates

Flexural load-displacement curves obtained from flexural tests of carbon fiber/epoxy composites with different matrix fillers are shown in Figure10. The curves show a linear deformation zone followed by a second zone with irregularities which can be attributed to out-plane fiber breakage during loading. However, some differences can be observed before and after reaching the maximum flexure load when nanoreinforcement is added. For composites with neat resin, there is no obvious plastic zone before reaching the peak load, and specimens failed rapidly after reaching the peak load. When 10 wt.% silica nanoparticles are added, a slight plastic zone in load before the maximum value is observed. In the case of adding 10 wt.% halloysite nanoparticles, an evident plain appears after peaking then load falls sharply. These load drops are believed to be attributed to the fiber breakage and matrix cracking, accompanied by the extension of the local delamination. Flexural properties are shown in Table 3. The increase of flexural properties for the composite laminates with the matrices modified by halloysite particles is the most pronounced, with strength improvement of 19.6% at content of 10 wt.% and the modulus enhancement of 27% at 5 wt.%. The flexural failure locations of the flexural specimens tested in this study were mainly on the top surface of the specimens under the loading nose, which should be accompanied by the compressive failure of the laminate in the first few plies, rather than interlaminar shear failure, as shown in Figure 11, which shows the cross-section of the laminate in thickness direction under the loading nose, indicating compressive failure mode near the top surface of the laminate.Table 3
Flexural properties of unidirectional CF/epoxy composites.
Composite
wt.% of filler
Strength(MPa)
Relative increase(%)
Modulus(GPa)
Relative increase(%)
CF/EP
0
701 ± 48
—
57.1 ± 1.3
—
CF/EP-silica
10
728 ± 54
3.9
62.9 ± 0.9
10.2
CF/EP-silica
20
818 ± 24
16.7
70.8 ± 2.4
24.0
CF/EP-halloysite
5
728 ± 12
3.9
72.5 ± 2.2
27.0
CF/EP-halloysite
10
838 ± 22
19.6
68.0 ± 1.9
19.1
CF/EP-rubber
20
554 ± 75
−20.9
58.5 ± 1.0
2.6Figure 10
Flexural load-displacement curves of CF/epoxy composites.Figure 11
Microscopic images of cross-sections of composite laminate specimens in thickness direction of specimens with different matrices.Experimental results from the compressive and flexural tests show that the rigid-particles (silica and halloysite) provide an effective mechanism of matrix strengthening.


## 3.1. The Compressive Properties of Cured Bulk Matrix Resins

To determine the effects of nanoparticles on the mechanical properties of the cured epoxy resins, the compressive tests were performed on the nanocomposite coupon specimens that contain different loadings of particles. Figure1 demonstrates the load and displacement curves for the epoxy and particle/epoxy systems with the piperidine curing agent, which shows the same tendency of load-displacement curves for different types of particles. When it comes to the first peak, load decreases rapidly and then increases until specimen failure. From the compressive properties of the matric resins (shown in Table 1), it can be seen that the addition of the rigid nanoparticles increases compressive yield strength of the matric resins. The maximum strength for silica/epoxy and halloysite/epoxy is 94.78 MPa at 20 wt.% and 91.33 MPa at 15 wt.%, respectively. From Figure 2 and Table 1, it can be seen that there is a fluctuation for the strength improvement with the increment of rigid particle loading. The fluctuation could be due to the defect generated during the fabrication process. It was found that when nanoparticles were introduced into the brittle matrix, the compound became very sticky, making it difficult to uniform nanoparticles dispersing in the matrix and eradiate the embedded bubbles. No significant differences were found regarding the effect of nanoparticles on the compressive modulus of these matrix systems. For hybrid systems, compressive properties of matrix resins with 10 wt.% Silica and 5 wt.% CTBN increase most obviously. Hybrid strengthening mechanism is a more complicated issue. As shown in Figure 3, strength enhancement of hybrid systems is not simply the sum of the two improvements for each component. From the testing results, it can be seen that introducing nanofillers can influence the compressive property of epoxies.Table 1
Compressive properties of bulk matrix resins cured by piperidine.
Filler type
Weight fraction
Compressive yield strength(MPa)
Compressive modulus(GPa)
Tensile strength(MPa) [25]
Tensile modulus(GPa) [25]
Neat epoxy
89.1 ± 1.2
2.62 ± 0.05
65.8 ± 1.9
2.94 ± 0.10
Silica
2 wt.%
91.6 ± 0.4
2.63 ± 0.02
—
—
4 wt.%
91.5 ± 0.2
2.55 ± 0.03
—
—
6 wt.%
91.9 ± 0.5
2.46 ± 0.05
—
—
8 wt.%
92.3 ± 0.3
2.58 ± 0.03
—
—
10 wt.%
91.1 ± 0.2
2.71 ± 0.02
69.0 ± 0.5
3.36 ± 0.12
20 wt.%
94.8 ± 0.5
2.89 ± 0.07
—
—
Halloysite
2 wt.%
90.8 ± 0.2
2.43 ± 0.05
—
—
5 wt.%
89.3 ± 0.3
2.40 ± 0.01
68.1 ± 0.3
3.03 ± 0.13
7 wt.%
90.9 ± 0.2
2.55 ± 0.03
—
—
10 wt.%
90.4 ± 0.1
2.49 ± 0.01
68.2 ± 0.4
3.11 ± 0.08
15 wt.%
91.3 ± 0.2
2.58 ± 0.02
—
—
CTBN liquid rubber
5 wt.%
92.4 ± 0.6
2.61 ± 0.03
67.3 ± 0.7
2.09 ± 0.10
10 wt.%
89.3 ± 0.5
2.42 ± 0.06
60.1 ± 1.0
2.61 ± 0.10
Hybrid system
10 wt.% halloysite + 5 wt.% CTBN
93.0 ± 0.3
2.72 ± 0.03
65.9 ± 0.3
3.05 ± 0.11
10 wt.% silica + 5 wt.% CTBN
96.2 ± 0.9
2.77 ± 0.05
65.5 ± 0.4
3.17 ± 0.10
10 wt.% silica + 10 wt.% CTBN
90.1 ± 0.3
2.69 ± 0.04
59.2 ± 0.7
2.83 ± 0.09Figure 1
Load-displacement curves for pure epoxy and particle/epoxy systems cured by piperidine.Figure 2
Compressive yield strength improvement with the increment of silica particle loading.Figure 3
Comparison of compressive strengths of the cured epoxy systems.Compared with tensile properties [25] for the corresponding modified epoxy systems in Table 1, it can be seen that compressive yield strength is much higher than tensile strength, while compressive modulus is lower. It may be caused by fracture failure in tensile specimens. Bubbles and aggregations in matric resins will lead to stress concentration.Figure4 gives the compression damage mode of neat epoxy, which is similar to failures of the other nanoparticle/epoxy systems cured by piperidine. It can be seen that the failure specimen is box-like with an opening side.Figure 4
Comparison of pure epoxy specimens before and after compression tests.The compression failure process of pure epoxy is shown in Figure5. Side damage occurs at first, and then a damage point at bottom appears at the strain of 0.47 (Figure 5(b)). After that, the damage point propagates at bottom along the direction of 45° (Figure 5(c)) until the moment of failure at the strain of 0.56 (Figure 5(d)).Figure 5
Compression failure process of pure epoxy: (a) at beginning; (b) side damage and a damage point at bottom occur; (c) the damage point propagates at bottom along the direction of 45°; (d) at the moment of failure.
(a)
(b)
(c)
(d)


## 3.2. Compressive Properties of Unidirectional CF/Epoxy Composite Laminates

Most engineering applications of carbon fiber reinforced composites are based on multidirectional laminates. However, if the mechanism of fracture was to be fully understood, a systematic study of unidirectional composites should be first made. Hence, unidirectional composites were investigated in this study.Figure6 demonstrates the compressive load-displacement curves of carbon fiber/epoxy composites with their matrices modified by nanoparticle and CTBN rubber. As shown in Figure 6, all the specimens exhibit relatively nonlinear behaviors. The specimens failed rapidly after reaching the maximum load. When a composite, especially for unidirectional fiber reinforced composites, is subjected to a longitudinal compressive load, several main failure modes are involved [26]. These failure modes may include microbuckling, kinking, fiber failure, and longitudinal cracking (synonymous with delamination failure in general laminates) and shear failure [27]. Fiber microbuckling and kinking are considered as the dominant mechanisms of failure. Scanning electron microscopy (SEM) images of CF/epoxy composites with their matrices modified by nanoparticles and rubbers are shown in Figures 7 and 8. Fiber microbuckling and kinking can be easily seen from the specimen surface and the fracture surfaces of the compressive specimens.Figure 6
Compressive load-displacement curves of CF/epoxy composites.Figure 7
SEM images of the specimen surfaces around the failure locations for the tested CF/epoxy composite specimens.Figure 8
SEM images of fracture surfaces for CF/epoxy composite specimens after compressive tests.The compressive test results are summarized in Table2. It can be clearly seen that compressive properties of the unidirectional composite test coupons are obviously enhanced with the use of the nanoparticle reinforced epoxy matrix, while, for the composites with their matrices modified with the CTBN liquid rubber, both compressive strength and modulus are reduced. Particularly, compared with the properties of the composite specimens with the unmodified matrix, the longitudinal compressive strength was significantly increased by 22.3% with the addition of 10 wt.% of halloysite nanoparticles. The reason is believed to be the unique strengthening effect of the halloysite nanotubes as indicated in previously published research papers [12].Table 2
Compressive properties of unidirectional CF/epoxy composites.
Composite
wt.% of filler
Compressive strength(MPa)
Relative increase(%)
Compressive modulus(GPa)
Relative increase(%)
CF/EP
0
367 ± 53
—
34.9 ± 10.3
—
CF/EP-silica
10
382 ± 42
4.1
50.5 ± 6.7
44.7
CF/EP-silica
20
388 ± 36
5.7
47.9 ± 6.2
37.2
CF/EP-halloysite
5
385 ± 26
4.9
35.1 ± 4.1
0.6
CF/EP-halloysite
10
449 ± 3
22.3
38.8 ± 6.0
11.2
CF/EP-rubber
10
361 ± 14
−1.6
32.1 ± 12.1
−8.0
CF/EP-rubber
20
322 ± 13
−12.3
33.5 ± 10.0
−4.0It is noted that the compressive properties of carbon fiber composites prepared in this study are much lower than those of the composites manufactured by autoclaving using the commercial carbon fiber/epoxy prepregs. This is obviously attributed to some factors that exist in the manufacturing process of CF/EP composites by VARIM, such as the effect of the shape of the flow media screen sheet and the waviness of the fibers in the fabrics due to the use of the stitching filaments and also fabric handling during lay-ups. During the process of hot pressing, the flow media screen sheet on top and bottom of the laminate can clearly cause fiber waviness as shown in Figure9. Fiber waviness and fiber misalignment have been proved to significantly reduce the compressive properties of carbon fiber composites [4].Figure 9
Microscope images of the longitudinal cross-section of the composite laminates fabricated by VARIM, showing obvious waviness of the fabrics.However, as a compression for the effect of nanofillers on the compressive properties of composite laminates between the composite laminates with different matrix modifiers, the results are still meaningful.


## 3.3. Flexural Properties of Unidirectional CF/Epoxy Composite Laminates

Flexural load-displacement curves obtained from flexural tests of carbon fiber/epoxy composites with different matrix fillers are shown in Figure10. The curves show a linear deformation zone followed by a second zone with irregularities which can be attributed to out-plane fiber breakage during loading. However, some differences can be observed before and after reaching the maximum flexure load when nanoreinforcement is added. For composites with neat resin, there is no obvious plastic zone before reaching the peak load, and specimens failed rapidly after reaching the peak load. When 10 wt.% silica nanoparticles are added, a slight plastic zone in load before the maximum value is observed. In the case of adding 10 wt.% halloysite nanoparticles, an evident plain appears after peaking then load falls sharply. These load drops are believed to be attributed to the fiber breakage and matrix cracking, accompanied by the extension of the local delamination. Flexural properties are shown in Table 3. The increase of flexural properties for the composite laminates with the matrices modified by halloysite particles is the most pronounced, with strength improvement of 19.6% at content of 10 wt.% and the modulus enhancement of 27% at 5 wt.%. The flexural failure locations of the flexural specimens tested in this study were mainly on the top surface of the specimens under the loading nose, which should be accompanied by the compressive failure of the laminate in the first few plies, rather than interlaminar shear failure, as shown in Figure 11, which shows the cross-section of the laminate in thickness direction under the loading nose, indicating compressive failure mode near the top surface of the laminate.Table 3
Flexural properties of unidirectional CF/epoxy composites.
Composite
wt.% of filler
Strength(MPa)
Relative increase(%)
Modulus(GPa)
Relative increase(%)
CF/EP
0
701 ± 48
—
57.1 ± 1.3
—
CF/EP-silica
10
728 ± 54
3.9
62.9 ± 0.9
10.2
CF/EP-silica
20
818 ± 24
16.7
70.8 ± 2.4
24.0
CF/EP-halloysite
5
728 ± 12
3.9
72.5 ± 2.2
27.0
CF/EP-halloysite
10
838 ± 22
19.6
68.0 ± 1.9
19.1
CF/EP-rubber
20
554 ± 75
−20.9
58.5 ± 1.0
2.6Figure 10
Flexural load-displacement curves of CF/epoxy composites.Figure 11
Microscopic images of cross-sections of composite laminate specimens in thickness direction of specimens with different matrices.Experimental results from the compressive and flexural tests show that the rigid-particles (silica and halloysite) provide an effective mechanism of matrix strengthening.


## 4. Conclusions

In this study, we have demonstrated that compressive and flexural properties of carbon fiber/epoxy composites manufactured by a VARIM process are significantly enhanced by reinforcing the matrix with rigid nanoparticles. Particularly, due to the strengthening effect of the unique halloysite nanotubes, both the compressive and flexural properties of the bulk matrices and the composite laminates are remarkably increased as a result of the incorporation of the halloysite nanoclay. The effect of different particle contents on the compressive property of fiber/epoxy composites was more obvious than that in epoxies.Compressive and flexural properties of CF/epoxy composites are more sensible to the matrix behavior. Both their strength and their modulus increase with the rigid particle loading, while they decrease with soft particle (CTBN liquid rubber).



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