# Unidirectional Cordenka Fibre-Reinforced Furan Resin Full Biocomposite: Properties and Influence of High Fibre Mass Fraction

Authors: Talent Malaba; Jiajun Wang
Journal: Journal of Composites
 (2015)

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## Abstract

A full biocomposite was fabricated from Cordenka CR fibre and furan resin. High fibre mass fractions (FMF) were achieved by pressing the CR fibres into unidirectional sheets prior to incorporation into the resin. Results of testing indicated that the tensile properties of the biocomposite were improved by the initial increase of FMF from 51 to 64%, with a subsequent increase of FMF to 75% resulting in a deterioration of those properties. Examination of the tensile fracture surfaces with a scanning electron microscope (SEM) revealed moderate deterioration in fibre-matrix adhesion after the initial increase of FMF. Further increase of the FMF to 75% was shown by SEM to result in worse fibre-matrix adhesion. On the other hand, the flexural, interlaminar-shear, and dynamic mechanical properties were adversely affected by the increase in fibre-mass fraction from 51 through 75%. These effects were mainly attributed to reduced fibre wetting that resulted in weakened fibre-matrix interfacial bonding and subsequent poor stress exchange at the fibre-matrix interface. Observations made with a digital microscope revealed normal crack behaviour in the laminated composite, and the shear fracture modes were I and II. This biocomposite has mechanical properties comparable to those of flax and glass fibre-reinforced furan resin biocomposites.


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## Body

## 1. Introduction

Biocomposites are composite materials that consist of either a bio-derived matrix or biofibre reinforcement or both. Companies and research institutions are developing biocomposites mainly because of heightening environmental conscience amongst the public, government legislation, the depletion of raw materials for synthetic polymers, and price increases [1].A bio-derived matrix is known as a bioresin [2]. One type of thermosetting bioresin is called furan resin. At room temperature, furan resin is a reddish-brown liquid consisting of prepolymers of furfuryl alcohol (2-furanmethanol), which can cross-link into a solid thermoset polymer called polyfurfuryl alcohol (PFA). This cross-linking is accelerated by heat and acid catalysts [3]. To produce furfuryl alcohol, plant-sourced hemicellulose is hydrolysed in acidic conditions into pentose sugars [4]. The five-carbon sugars are then hydrolysed under the same conditions into the aldehyde furfural (furan-2-carbaldehyde), which is then reduced into furfuryl alcohol [5]. Furan resins are used in the manufacture of corrosion resistant fibre-reinforced plastics (FRPs) because the polymer has excellent chemical resistance and is particularly good at handling solvents and aggressive service environments [6]. Some FRP manufacturers also select furan resins due to their high temperature performance, which has been found to exceed 200°C in some furan based laminates [6].The adoption of long unidirectional natural fibres as reinforcement in bioresins can result in “full biocomposites” with enhanced mechanical properties and the potential for use in more structural applications [7]. Natural fibres, however, tend to possess poorer mechanical properties when compared to their synthetic counterparts. They are also prone to large variations in measurable parameters, such as length, diameter, and strength, even within the same batch [2]. These naturally occurring variations are almost inevitable and can make the design and quality control of natural fibre-reinforced biocomposites challenging.To continue relying on biomass as raw material, rayon fibre is a viable option to overcome some challenges posed by natural fibres [8]. Rayon fibre is made from purified cellulose sourced from plant material, particularly wood pulp. A variant of the manufacturing process yields high tenacity rayon (HTR) which, as its name suggests, exhibits high tensile strength. Cordenka GmbH & Co. KG (Obernburg, Germany) make a type of HTR called CR fibre for composite applications [9]. The CR fibre has tensile strength of 850 MPa, an elastic modulus of 19.5 GPa, and an elongation at break of 12% [9, 10]. Due to these properties, thermoplastics reinforced with this fibre possess a significant energy absorption capacity, which translates to a high degree of impact resistance [10]. The research into the application of CR fibres in thermoset based composites is still ongoing [10].In most previous studies of furan based natural fibre-reinforced composites, the proportion of the fibre reinforcement has been below 50% [7, 11, 12]. However, it has been suggested that to attain high mechanical strength levels (>200 MPa), the fibre proportion must exceed 50% [12]. One proposed technique for achieving a high fibre proportion in these laminates is to compact the natural fibres into unidirectional sheets before their incorporation into the resin [12]. Thus, in the current study, a full biocomposite has been fabricated through wet lay-up and compression moulding using CR fibre sheets and furan resin. Composite specimens with high fibre proportions are obtained and tested to evaluate the properties of the composite, as well as the influence of the high fibre proportion on the tensile, flexural, and interlaminar shear strengths of the composites. Digital microscope and scanning electron microscope (SEM) are employed to analyse the fractured specimens. In addition, the viscoelastic behaviour of the composite is studied using dynamic mechanical analysis (DMA), whilst thermogravimetric analysis (TGA) is conducted for an evaluation of the thermostability of the biocomposite. The results of these tests will also serve to assess the feasibility of applying the CR fibre-reinforced furan resin full biocomposite in the relevant industries.


## 2. Materials and Methods

### 2.1. Materials

High tenacity rayon of the type (Cordenka) CR fibre with a linear density of 1840 dtex and zero twist was obtained in wound package form from Cordenka GmbH & Co. KG (Obernburg, Germany). Furan resin was sourced from Hangzhou Tianyu Chemicals Co. Ltd. (Xiaoshan, Hangzhou, China). The resin had the molecular formula (C5H6O2)n, wheren ≥ 2; the purity was 80% with about 20% moisture, 30 mPa·s viscosity (20°C), 1.16 g/cm3 density, and a pH of 7. The resin manufacturer also provided the resin’s curing agent: p-toluenesulphonic acid (4-methylbenzenesulphonic acid).


### 2.2. Fibre Preparation

The CR fibres were unwound from the package, cut, and evenly laid into 36 individual sheets with dimensions of 280 × 70 mm2; each sheet had a mass of approximately 10 g. The sheets were separately wrapped in aluminium foil and compacted in a hot press at 10 MPa and 80°C for 2 hours to form flat and firm sheets consisting of unidirectional fibres. The compacted fibre sheets were finally arranged into three discrete sets, where in the first set the sheets were layered into double plies, triple plies in the second set, and quadruple plies in the third set. Each set had four stacks of the sheets, with the mass of a stack in set 1 being 20 g, 30 g in set 2, and 40 g in set 3.


### 2.3. Resin Preparation

350 mL of the furan resin was poured into a 500 mL glass beaker and stirred without heating using a magnetic stirrer. The curing agent was then gradually added into the beaker in five 3 g partitions to avoid the potentially violent cross-linking reaction. The mixture was continuously stirred for approximately 20 minutes, or until its temperature reached 45°C, as indicated by a mercury thermometer.


### 2.4. Composite Laminates Fabrication

The composite laminates were prepared inside a 2 mm thick aluminium mould with dimensions 300 × 300 × 20 mm3. The mould had first been sprayed with mould release agent (Daifree GA 7550, Daikin Fluorochemicals China Co. Ltd.). The four fibre stacks from set 1 were laid side by side inside the mould. The hot resin/curing agent mixture was then poured into the mould to thoroughly wet the fibres. The moulding of furan resin is done in two steps: drying and then curing. Thus, prior to curing, the wet laminates were placed inside a vacuum oven at 45°C for 1 hour to remove the moisture from the resin [7]. The aluminium mould was then placed inside a compression moulding machine to cure the laminates.


### 2.5. Curing the Laminates

Curing was done at 10 MPa pressure using an adapted multistep sequence [13]. The temperature was kept at 40°C for 12 hours, then raised to 60°C to remain there for another 12 hours, and then increased to 80°C and kept there for 6 hours. The temperature was finally increased to 110°C and the pressure released to 0 MPa to postcure the laminates for 1 hour. The temperature was increased gradually in order to slowdown the polymerisation process to facilitate the release of water produced during the cross-linking of the prepolymers [11]. If curing is too rapid the trapped water may cause matrix cracking and delamination [11].The above resin preparation, laminate fabrication, and curing procedures were repeated with the stacks of fibre sheets from the second and third sets, respectively.


### 2.6. Preparation of Test Specimens

After cooling to room temperature, each of the three cured composite plaques was cut into four smaller strips; each strip was approximately 2 mm thick and had dimensions of 280 × 70 mm2 in order to correspond with the initial fibre sheet stacks of the same dimensions. The densities of the fibre and cured resin were obtained from their manufacturers as 1.5 and 1.8 g/cm3, respectively. The composite strips were weighed to determine the fibre mass fraction (FMF) and to calculate the fibre volume fraction (FVF). Table 1 displays the outcomes.Table 1
Fibre mass and volume proportions in the composite strips.
Mass of fibres (g)
Mass of resin (g)
FMF (%)
Volume of fibres (cm3)
Volume of resin (cm3)
Volume of voids (cm3)
FVF (%)
Percentage of porosity
Set 1
20
19.35
51
13.33
10.75
15.12
34
38.6
Set 2
30
16.60
64
20.00
9.22
9.98
51
25.5
Set 3
40
13.41
75
26.67
7.45
5.08
68
13.0


### 2.7. Evaluation of Mechanical Properties

The composite strips were cut into the appropriate shapes for tensile, flexural, and interlaminar shear strength (ILSS) testing. For each test, a minimum of 5 specimens were tested for each category of FMF shown in Table1. Specimen dimensions were measured to the nearest 0.05 mm with a sliding vernier. The specimens were conditioned at room temperature for at least 24 hours prior to testing, which was then carried out under the same conditions using a Universal Testing Machine (Shenzhen Reger Instrument Co. Ltd., Shenzhen, China). The tensile strength test was done in accordance with ASTM D3039 at a cross-head speed of 2 mm/min on specimens with dimensions of 250 × 15 mm2. The flexural strength test was done in accordance with ASTM D790 at a cross-head speed and was 2 mm/min on specimens with dimensions of 100 × 13 mm2. The short-beam shear method specified in ISO 14130 was used for the ILSS test. The specimens had dimensions of 20 × 10 mm2 and the cross-head speed was 1 mm/min.


### 2.8. Tensile Fracture Surface Analysis with Scanning Electron Microscope (SEM)

The tensile fracture surfaces of specimens that attained tensile strength values closest to the mean were gold-sputter coated for 20 minutes in a JEOL JFC-1600 Auto Fine Coater (JEOL Ltd., Japan). The fracture surfaces were then observed in a JEOL JSM-5610LV SEM (JEOL Ltd., Japan) with acceleration voltage of 5 kV.


### 2.9. Interlaminar Fracture Analysis with Digital Microscope

A Hirox KH-7700 digital microscope (Hirox Co. Ltd., Japan) was used to observe the damaged specimens of 51% FMF after the ILSS test. The cracked specimens with values of ILSS close to the mean were cut cross-wise 5 mm below the cracks and placed on the microscope slide to observe the cracks and to determine the shear mode(s).


### 2.10. Study of Viscoelasticity with Dynamic Mechanical Analysis (DMA)

DMA was carried out to evaluate the storage and loss moduli and the damping properties (tan⁡δ) of the composites using a DMA Q800 instrument (TA Instruments Inc., United States). In addition to the specimens from the three categories of FMF in Table 1, a similarly cured control specimen with FMF of 0% was included in the analysis. All the specimens had dimensions of 50 × 13 mm2 and they were clamped in the 3-point bend mode. The strain amplitude and frequency were 15 μm and 1.0 Hz, respectively. The temperature was increased from 0 to 240°C at a heating rate of 5°C/min.


### 2.11. Evaluation of Thermostability with Thermogravimetric Analysis (TGA)

The thermostability of the composites was assessed using a Perkin Pyris 1 TGA (PerkinElmer Inc., United States) instrument. Composite specimens from the three categories of FMF in Table1 and a similarly cured control specimen with FMF of 0% were heated from 25 to 600°C at 20°C/min under nitrogen flow rate of 20 mL/min.


## 2.1. Materials

High tenacity rayon of the type (Cordenka) CR fibre with a linear density of 1840 dtex and zero twist was obtained in wound package form from Cordenka GmbH & Co. KG (Obernburg, Germany). Furan resin was sourced from Hangzhou Tianyu Chemicals Co. Ltd. (Xiaoshan, Hangzhou, China). The resin had the molecular formula (C5H6O2)n, wheren ≥ 2; the purity was 80% with about 20% moisture, 30 mPa·s viscosity (20°C), 1.16 g/cm3 density, and a pH of 7. The resin manufacturer also provided the resin’s curing agent: p-toluenesulphonic acid (4-methylbenzenesulphonic acid).


## 2.2. Fibre Preparation

The CR fibres were unwound from the package, cut, and evenly laid into 36 individual sheets with dimensions of 280 × 70 mm2; each sheet had a mass of approximately 10 g. The sheets were separately wrapped in aluminium foil and compacted in a hot press at 10 MPa and 80°C for 2 hours to form flat and firm sheets consisting of unidirectional fibres. The compacted fibre sheets were finally arranged into three discrete sets, where in the first set the sheets were layered into double plies, triple plies in the second set, and quadruple plies in the third set. Each set had four stacks of the sheets, with the mass of a stack in set 1 being 20 g, 30 g in set 2, and 40 g in set 3.


## 2.3. Resin Preparation

350 mL of the furan resin was poured into a 500 mL glass beaker and stirred without heating using a magnetic stirrer. The curing agent was then gradually added into the beaker in five 3 g partitions to avoid the potentially violent cross-linking reaction. The mixture was continuously stirred for approximately 20 minutes, or until its temperature reached 45°C, as indicated by a mercury thermometer.


## 2.4. Composite Laminates Fabrication

The composite laminates were prepared inside a 2 mm thick aluminium mould with dimensions 300 × 300 × 20 mm3. The mould had first been sprayed with mould release agent (Daifree GA 7550, Daikin Fluorochemicals China Co. Ltd.). The four fibre stacks from set 1 were laid side by side inside the mould. The hot resin/curing agent mixture was then poured into the mould to thoroughly wet the fibres. The moulding of furan resin is done in two steps: drying and then curing. Thus, prior to curing, the wet laminates were placed inside a vacuum oven at 45°C for 1 hour to remove the moisture from the resin [7]. The aluminium mould was then placed inside a compression moulding machine to cure the laminates.


## 2.5. Curing the Laminates

Curing was done at 10 MPa pressure using an adapted multistep sequence [13]. The temperature was kept at 40°C for 12 hours, then raised to 60°C to remain there for another 12 hours, and then increased to 80°C and kept there for 6 hours. The temperature was finally increased to 110°C and the pressure released to 0 MPa to postcure the laminates for 1 hour. The temperature was increased gradually in order to slowdown the polymerisation process to facilitate the release of water produced during the cross-linking of the prepolymers [11]. If curing is too rapid the trapped water may cause matrix cracking and delamination [11].The above resin preparation, laminate fabrication, and curing procedures were repeated with the stacks of fibre sheets from the second and third sets, respectively.


## 2.6. Preparation of Test Specimens

After cooling to room temperature, each of the three cured composite plaques was cut into four smaller strips; each strip was approximately 2 mm thick and had dimensions of 280 × 70 mm2 in order to correspond with the initial fibre sheet stacks of the same dimensions. The densities of the fibre and cured resin were obtained from their manufacturers as 1.5 and 1.8 g/cm3, respectively. The composite strips were weighed to determine the fibre mass fraction (FMF) and to calculate the fibre volume fraction (FVF). Table 1 displays the outcomes.Table 1
Fibre mass and volume proportions in the composite strips.
Mass of fibres (g)
Mass of resin (g)
FMF (%)
Volume of fibres (cm3)
Volume of resin (cm3)
Volume of voids (cm3)
FVF (%)
Percentage of porosity
Set 1
20
19.35
51
13.33
10.75
15.12
34
38.6
Set 2
30
16.60
64
20.00
9.22
9.98
51
25.5
Set 3
40
13.41
75
26.67
7.45
5.08
68
13.0


## 2.7. Evaluation of Mechanical Properties

The composite strips were cut into the appropriate shapes for tensile, flexural, and interlaminar shear strength (ILSS) testing. For each test, a minimum of 5 specimens were tested for each category of FMF shown in Table1. Specimen dimensions were measured to the nearest 0.05 mm with a sliding vernier. The specimens were conditioned at room temperature for at least 24 hours prior to testing, which was then carried out under the same conditions using a Universal Testing Machine (Shenzhen Reger Instrument Co. Ltd., Shenzhen, China). The tensile strength test was done in accordance with ASTM D3039 at a cross-head speed of 2 mm/min on specimens with dimensions of 250 × 15 mm2. The flexural strength test was done in accordance with ASTM D790 at a cross-head speed and was 2 mm/min on specimens with dimensions of 100 × 13 mm2. The short-beam shear method specified in ISO 14130 was used for the ILSS test. The specimens had dimensions of 20 × 10 mm2 and the cross-head speed was 1 mm/min.


## 2.8. Tensile Fracture Surface Analysis with Scanning Electron Microscope (SEM)

The tensile fracture surfaces of specimens that attained tensile strength values closest to the mean were gold-sputter coated for 20 minutes in a JEOL JFC-1600 Auto Fine Coater (JEOL Ltd., Japan). The fracture surfaces were then observed in a JEOL JSM-5610LV SEM (JEOL Ltd., Japan) with acceleration voltage of 5 kV.


## 2.9. Interlaminar Fracture Analysis with Digital Microscope

A Hirox KH-7700 digital microscope (Hirox Co. Ltd., Japan) was used to observe the damaged specimens of 51% FMF after the ILSS test. The cracked specimens with values of ILSS close to the mean were cut cross-wise 5 mm below the cracks and placed on the microscope slide to observe the cracks and to determine the shear mode(s).


## 2.10. Study of Viscoelasticity with Dynamic Mechanical Analysis (DMA)

DMA was carried out to evaluate the storage and loss moduli and the damping properties (tan⁡δ) of the composites using a DMA Q800 instrument (TA Instruments Inc., United States). In addition to the specimens from the three categories of FMF in Table 1, a similarly cured control specimen with FMF of 0% was included in the analysis. All the specimens had dimensions of 50 × 13 mm2 and they were clamped in the 3-point bend mode. The strain amplitude and frequency were 15 μm and 1.0 Hz, respectively. The temperature was increased from 0 to 240°C at a heating rate of 5°C/min.


## 2.11. Evaluation of Thermostability with Thermogravimetric Analysis (TGA)

The thermostability of the composites was assessed using a Perkin Pyris 1 TGA (PerkinElmer Inc., United States) instrument. Composite specimens from the three categories of FMF in Table1 and a similarly cured control specimen with FMF of 0% were heated from 25 to 600°C at 20°C/min under nitrogen flow rate of 20 mL/min.


## 3. Results and Discussion

Table2 displays the results of the mechanical tests carried out on the composites. The strength and moduli values are shown plotted in Figures 1(a) and 1(b), respectively, with the error bars inserted at the respective standard deviations.Table 2
Mean values of the mechanical properties of the composites.
Fibre mass fraction (%)
Tensile strength (MPa)
Tensile modulus (GPa)
Flexural strength (MPa)
Flexural modulus (GPa)
Interlaminar shear strength (MPa)
51
77.2
4.32
95.4
6.96
11.2
64
121
5.58
87.4
5.91
8.89
75
86.6
4.78
48.8
3.12
5.77Figure 1
(a) Tensile, flexural, and interlaminar shear strengths. (b) Tensile and flexural moduli.
(a)
(b)


### 3.1. Tensile Properties

The mean tensile strength and modulus were significantly improved by the increase of FMF from 51 to 64%. The tensile strength of 121 MPa at 64% FMF is almost twice that of a unidirectionally stitched flax fabric-reinforced furan biocomposite, which attained tensile strength of 64 MPa at 60% FMF [14]. However, the tensile modulus of the flax-furan composite was much higher at 8.5 GPa, compared to just 5.6 GPa in the current study. This can be attributed to the greater stiffness of the flax fibre, which has just one quarter (3.3%) of the elongation at break of the CR fibre [15]. In PLA based composites, it has also been indicated that Cordenka fibre improves tensile strength, whilst flax fibre improves the tensile modulus [16]. Similar findings were obtained using Cordenka and flax fabrics in epoxy composites [17]. In the current study, further increase of the FMF from 64 to 75% resulted in a decrease of about 34 MPa in the mean tensile strength. In another study, unidirectionally aligned kenaf fibre-reinforced furan biocomposite attained tensile strength and modulus of approximately 40 MPa and 1.3 GPa, respectively [18]. In that study, the FMF was restricted to a considerably low 20%, above which the tensile properties were observed to decrease sharply. The deterioration of the tensile properties above a certain FMF in that study correlates with the results of the current study. The decrease in tensile strength is caused by poor dispersion, which is a consequence of the high degree of proximity of the fibres to each other [19]. Poor dispersion leads to unreinforced matrix-only areas through which the stress of testing concentrates, leading to rapid crack propagation and ultimately rupture [20]. The tensile strength is also affected by the alignment of the fibres during fabrication [21]. In the current study, the fibres were manually aligned and stacked unidirectionally, a technique that becomes less reliable as the quantity of the fibres increases and may result in misalignment of some fibres. The misaligned fibres do not contribute enough support during testing [21].


### 3.2. Flexural Properties

The flexural properties deteriorated with the increase of FMF from 51 through 75%. The greatest mean flexural strength and modulus were approximately 95 MPa and 7.0 GPa, respectively, attained at 51% FMF. The flexural strength in this case (where the FVF is 34%) compares well with a value of 99 MPa obtained with unidirectionally stitched flax fabric-reinforced furan resin at 41% FVF [7]. The flexural modulus in that study, however, was significantly higher at 9.6 GPa. For reference, a glass plain weave fabric-reinforced furan resin composite with 47% FVF attained flexural strength and modulus of 105 MPa and 9.0 GPa, respectively [7]. In the current study, the flexural properties decrease at increasing fibre proportions because the flexure test has a compressive component in it, and the compressive strength of a composite is determined by the properties of the matrix and the fibre-matrix interface [17]. Furthermore, there was an increase in weak spaces in the composite due to reduced fibre wetting that occurs at higher FMF, which consequently reduced the flexural strength [22]. The weak areas consist of fibre sheet regions that have the least amount of resin wetting [11]. This effect is apparent in Table 1, where resin uptake is observed to decline as the fibre loading is increased. Thus, the furan matrix clearly dominates the flexural properties of this composite. However, it appears that the CR fibre of the current study could still compete well with the already established glass and flax fibres in furan composites, especially where the flexural strength is of prime interest. The optimum FMF that results in the best flexural strength and modulus has to be found through further research.


### 3.3. Interlaminar Properties

The ILSS decreased with the increase of FMF from 51 through 75%. The greatest mean value was 11.2 MPa at 51% FMF. For reference, a commercially available flax twill fabric-reinforced epoxy prepreg was found to have ILSS of 10.7 MPa [17]. In the short-beam shear test, the ratio (support span length/specimen thickness) is much smaller (10/2 = 5), compared to 80/2 = 40 in the flexural strength test. The smaller ratio in the ILSS test causes the specimen to fail through shearing of its layers, as intended. These results indicate that the fibre-matrix interfacial adhesion deteriorated steadily with increased FMF.


### 3.4. Results of Analysis with SEM

Figure2 shows SEM images of the tensile fracture surfaces. Figure 2(a) shows a fracture surface from a specimen of 51% FMF. The matrix appears prominently and exhibits signs of porosity, some of which can be attributed to water that got trapped during curing. Some fibres have been pulled out from the matrix and they appear to be smeared with matrix material, which is indicative of good fibre-matrix adhesion [8]. Figure 2(b) shows a fracture surface from a specimen that had 64% FMF. The matrix shows a high level of porosity and signs of brittle fracture, revealing some fibres still embedded within the matrix, whilst many were pulled out. Some fibres were also misaligned. The tensile properties were still improved, however, which means these adverse effects were outweighed by the reinforcing effect of the CR fibres. A high level of porosity was also observed in a unidirectional flax-furan resin biocomposite with 60% FMF, which was attributed to excessive resin bleed-out [14]. Figure 2(c) shows a fracture surface from a specimen that had 75% FMF. The fibre-matrix interaction was not optimal, as there are many short pulled-out fibres in proximity to each other. For comparison, a Cordenka fibre-reinforced PLA composite with 30% FMF was found to have poor fibre-matrix adhesion due to long and clean pulled-out fibres [16]. In Figure 2(c) the fibres appear to have huddled together into bundles that led to dry spots and became interfacial weak areas; the huddling of the fibres can be attributed to hydrogen bonds that formed between them [17, 23]. This is one major consequence of the high FMF. The large gaps between the fibres and the matrix are also the result of poor dispersion during fabrication [16].Figure 2
(a) SEM image of tensile fracture surface (51% FMF). (b) SEM image of tensile fracture surface (64% FMF). (c) SEM image of tensile fracture surface (75% FMF).
(a)
(b)
(c)


### 3.5. Results of Analysis with Digital Microscope

Figure3 shows cross section images of some specimens of 51% FMF from the short-beam shear test. In Figure 3(a), an intralaminar or matrix crack is seen extending from the edge of the specimen towards the interlaminar crack. The crack propagation was transferred from the matrix or the fibre-matrix interface towards the fibre plies, causing delamination [24, 25]. This type of crack behaviour signals satisfactory fibre-matrix compatibility [26]. Matrix cracks are one of the main causes of the commencement of delamination [27]. The cracks may initiate in the matrix due to its lower failure strain. The release of cure pressure can also result in fractures within the matrix [17]. Despite the extensive cracking, the specimens exhibited minimal deformation to their overall shapes, which is typical of a brittle material [28]. This can be seen in Figure 3(b), where the delamination crack runs in a fairly straight line across the specimen, and the outer edges of the specimen remained parallel to each other. The shear fracture modes are II and III.Figure 3
(a) Matrix cracking. (b) Delamination.
(a)
(b)


### 3.6. Results of Viscoelastic Behaviour Study

Table3 displays the data outputted by the DMA instrument. The viscoelastic behaviours of the composites and control specimen are shown in Figure 4.Table 3
Storage modulus, damping coefficient and glass transition temperature values of the composites and control specimen.
Fibre mass fraction (%)
Storage modulus at 25°C (GPa)
tanδ at 25°C
Glass transition temperature (°C)
tanδ at glass transition temperature
0
0.5
0.028
90.3
0.092
51
4.6
0.032
128
0.123
64
4.1
0.033
122
0.109
75
4.0
0.033
119
0.093Figure 4
(a) Storage moduli of the composites and control specimen. (b) Loss moduli of the composites and control specimen.
(a)
(b)In Figure4(a), the storage moduli (E′) decreased with increasing temperature due to the deterioration of the elasticity of the furan matrix. The highest storage modulus at room temperature (25°C) was approximately 4.6 GPa, which was attained by the specimens with 51% FMF. For the three tested composites, the value of E′ is observed to decrease with increasing FMF, a trend that is consistent with the flexural and interlaminar shear strengths. The three composites, however, had much higher values of E′ than the control specimen of 0% FMF, which is an indication of the increased stiffness of the composites due to the reinforcing properties of the CR fibres. In addition, the curves of E′ do not exhibit any increase in the value of E′ in the tested temperature range, suggesting that the resin was cured sufficiently [29]. In Figure 4(b), the loss moduli (E′′) are observed to reach maximum values corresponding with the respective glass transition temperatures (Tg). Incorporating the fibre reinforcement elevated the Tg of the resin. Amongst the three composites, however, the Tg decreased with increasing FMF. At higher FMF, it has been noted that the furan matrix becomes less reinforced as the fibres tend to huddle together. The data in Table 3 indicate that the three composites had similar damping coefficients (tan⁡δ) at 25°C. Above 25°C, the specimen with 51% FMF maintained the highest values of tan⁡δ, which means it was the most efficient at absorbing and dissipating energy. This is due to the adequate wetting of the fibres by the resin, which enhanced the damping effect at the fibre-matrix interface during cyclic loading [30]. This is an important consideration for automotive applications, where the biocomposite is expected to absorb and dissipate vibrational energy safely and efficiently.


### 3.7. Results of Thermostability Study

Figure5 shows the TGA curves of the specimens. The three composites and the control specimen each lost about 7% mass at 200°C. Above 200°C, the thermostability of the three composites appears to be improved over that of unreinforced furan resin. A mass loss of 10% corresponds with a temperature of approximately 260°C for the composites, whilst for unreinforced furan resin it is lower at approximately 220°C. The three composites show rapid mass loss at approximately 275°C, which can be attributed to the degradation of the cellulosic structures of the CR fibres [31]. This degradation became worse with the increase of FMF since although the fibres are completely enclosed within the furan matrix, at higher FMF there is less matrix material to protect the fibres from degrading [12]. Between 280 and 320°C, the specimen with 51% FMF lost 5% less mass compared to the other two specimens with the higher FMFs. The specimen with 51% FMF also retained the greatest mass residue (41.1%) at 600°C, whilst the specimens with 64% FMF and 75% FMF retained mass residues of 34.0% and 13.5%, respectively.Figure 5
Thermogravimetric curves of the composites and control specimen.


## 3.1. Tensile Properties

The mean tensile strength and modulus were significantly improved by the increase of FMF from 51 to 64%. The tensile strength of 121 MPa at 64% FMF is almost twice that of a unidirectionally stitched flax fabric-reinforced furan biocomposite, which attained tensile strength of 64 MPa at 60% FMF [14]. However, the tensile modulus of the flax-furan composite was much higher at 8.5 GPa, compared to just 5.6 GPa in the current study. This can be attributed to the greater stiffness of the flax fibre, which has just one quarter (3.3%) of the elongation at break of the CR fibre [15]. In PLA based composites, it has also been indicated that Cordenka fibre improves tensile strength, whilst flax fibre improves the tensile modulus [16]. Similar findings were obtained using Cordenka and flax fabrics in epoxy composites [17]. In the current study, further increase of the FMF from 64 to 75% resulted in a decrease of about 34 MPa in the mean tensile strength. In another study, unidirectionally aligned kenaf fibre-reinforced furan biocomposite attained tensile strength and modulus of approximately 40 MPa and 1.3 GPa, respectively [18]. In that study, the FMF was restricted to a considerably low 20%, above which the tensile properties were observed to decrease sharply. The deterioration of the tensile properties above a certain FMF in that study correlates with the results of the current study. The decrease in tensile strength is caused by poor dispersion, which is a consequence of the high degree of proximity of the fibres to each other [19]. Poor dispersion leads to unreinforced matrix-only areas through which the stress of testing concentrates, leading to rapid crack propagation and ultimately rupture [20]. The tensile strength is also affected by the alignment of the fibres during fabrication [21]. In the current study, the fibres were manually aligned and stacked unidirectionally, a technique that becomes less reliable as the quantity of the fibres increases and may result in misalignment of some fibres. The misaligned fibres do not contribute enough support during testing [21].


## 3.2. Flexural Properties

The flexural properties deteriorated with the increase of FMF from 51 through 75%. The greatest mean flexural strength and modulus were approximately 95 MPa and 7.0 GPa, respectively, attained at 51% FMF. The flexural strength in this case (where the FVF is 34%) compares well with a value of 99 MPa obtained with unidirectionally stitched flax fabric-reinforced furan resin at 41% FVF [7]. The flexural modulus in that study, however, was significantly higher at 9.6 GPa. For reference, a glass plain weave fabric-reinforced furan resin composite with 47% FVF attained flexural strength and modulus of 105 MPa and 9.0 GPa, respectively [7]. In the current study, the flexural properties decrease at increasing fibre proportions because the flexure test has a compressive component in it, and the compressive strength of a composite is determined by the properties of the matrix and the fibre-matrix interface [17]. Furthermore, there was an increase in weak spaces in the composite due to reduced fibre wetting that occurs at higher FMF, which consequently reduced the flexural strength [22]. The weak areas consist of fibre sheet regions that have the least amount of resin wetting [11]. This effect is apparent in Table 1, where resin uptake is observed to decline as the fibre loading is increased. Thus, the furan matrix clearly dominates the flexural properties of this composite. However, it appears that the CR fibre of the current study could still compete well with the already established glass and flax fibres in furan composites, especially where the flexural strength is of prime interest. The optimum FMF that results in the best flexural strength and modulus has to be found through further research.


## 3.3. Interlaminar Properties

The ILSS decreased with the increase of FMF from 51 through 75%. The greatest mean value was 11.2 MPa at 51% FMF. For reference, a commercially available flax twill fabric-reinforced epoxy prepreg was found to have ILSS of 10.7 MPa [17]. In the short-beam shear test, the ratio (support span length/specimen thickness) is much smaller (10/2 = 5), compared to 80/2 = 40 in the flexural strength test. The smaller ratio in the ILSS test causes the specimen to fail through shearing of its layers, as intended. These results indicate that the fibre-matrix interfacial adhesion deteriorated steadily with increased FMF.


## 3.4. Results of Analysis with SEM

Figure2 shows SEM images of the tensile fracture surfaces. Figure 2(a) shows a fracture surface from a specimen of 51% FMF. The matrix appears prominently and exhibits signs of porosity, some of which can be attributed to water that got trapped during curing. Some fibres have been pulled out from the matrix and they appear to be smeared with matrix material, which is indicative of good fibre-matrix adhesion [8]. Figure 2(b) shows a fracture surface from a specimen that had 64% FMF. The matrix shows a high level of porosity and signs of brittle fracture, revealing some fibres still embedded within the matrix, whilst many were pulled out. Some fibres were also misaligned. The tensile properties were still improved, however, which means these adverse effects were outweighed by the reinforcing effect of the CR fibres. A high level of porosity was also observed in a unidirectional flax-furan resin biocomposite with 60% FMF, which was attributed to excessive resin bleed-out [14]. Figure 2(c) shows a fracture surface from a specimen that had 75% FMF. The fibre-matrix interaction was not optimal, as there are many short pulled-out fibres in proximity to each other. For comparison, a Cordenka fibre-reinforced PLA composite with 30% FMF was found to have poor fibre-matrix adhesion due to long and clean pulled-out fibres [16]. In Figure 2(c) the fibres appear to have huddled together into bundles that led to dry spots and became interfacial weak areas; the huddling of the fibres can be attributed to hydrogen bonds that formed between them [17, 23]. This is one major consequence of the high FMF. The large gaps between the fibres and the matrix are also the result of poor dispersion during fabrication [16].Figure 2
(a) SEM image of tensile fracture surface (51% FMF). (b) SEM image of tensile fracture surface (64% FMF). (c) SEM image of tensile fracture surface (75% FMF).
(a)
(b)
(c)


## 3.5. Results of Analysis with Digital Microscope

Figure3 shows cross section images of some specimens of 51% FMF from the short-beam shear test. In Figure 3(a), an intralaminar or matrix crack is seen extending from the edge of the specimen towards the interlaminar crack. The crack propagation was transferred from the matrix or the fibre-matrix interface towards the fibre plies, causing delamination [24, 25]. This type of crack behaviour signals satisfactory fibre-matrix compatibility [26]. Matrix cracks are one of the main causes of the commencement of delamination [27]. The cracks may initiate in the matrix due to its lower failure strain. The release of cure pressure can also result in fractures within the matrix [17]. Despite the extensive cracking, the specimens exhibited minimal deformation to their overall shapes, which is typical of a brittle material [28]. This can be seen in Figure 3(b), where the delamination crack runs in a fairly straight line across the specimen, and the outer edges of the specimen remained parallel to each other. The shear fracture modes are II and III.Figure 3
(a) Matrix cracking. (b) Delamination.
(a)
(b)


## 3.6. Results of Viscoelastic Behaviour Study

Table3 displays the data outputted by the DMA instrument. The viscoelastic behaviours of the composites and control specimen are shown in Figure 4.Table 3
Storage modulus, damping coefficient and glass transition temperature values of the composites and control specimen.
Fibre mass fraction (%)
Storage modulus at 25°C (GPa)
tanδ at 25°C
Glass transition temperature (°C)
tanδ at glass transition temperature
0
0.5
0.028
90.3
0.092
51
4.6
0.032
128
0.123
64
4.1
0.033
122
0.109
75
4.0
0.033
119
0.093Figure 4
(a) Storage moduli of the composites and control specimen. (b) Loss moduli of the composites and control specimen.
(a)
(b)In Figure4(a), the storage moduli (E′) decreased with increasing temperature due to the deterioration of the elasticity of the furan matrix. The highest storage modulus at room temperature (25°C) was approximately 4.6 GPa, which was attained by the specimens with 51% FMF. For the three tested composites, the value of E′ is observed to decrease with increasing FMF, a trend that is consistent with the flexural and interlaminar shear strengths. The three composites, however, had much higher values of E′ than the control specimen of 0% FMF, which is an indication of the increased stiffness of the composites due to the reinforcing properties of the CR fibres. In addition, the curves of E′ do not exhibit any increase in the value of E′ in the tested temperature range, suggesting that the resin was cured sufficiently [29]. In Figure 4(b), the loss moduli (E′′) are observed to reach maximum values corresponding with the respective glass transition temperatures (Tg). Incorporating the fibre reinforcement elevated the Tg of the resin. Amongst the three composites, however, the Tg decreased with increasing FMF. At higher FMF, it has been noted that the furan matrix becomes less reinforced as the fibres tend to huddle together. The data in Table 3 indicate that the three composites had similar damping coefficients (tan⁡δ) at 25°C. Above 25°C, the specimen with 51% FMF maintained the highest values of tan⁡δ, which means it was the most efficient at absorbing and dissipating energy. This is due to the adequate wetting of the fibres by the resin, which enhanced the damping effect at the fibre-matrix interface during cyclic loading [30]. This is an important consideration for automotive applications, where the biocomposite is expected to absorb and dissipate vibrational energy safely and efficiently.


## 3.7. Results of Thermostability Study

Figure5 shows the TGA curves of the specimens. The three composites and the control specimen each lost about 7% mass at 200°C. Above 200°C, the thermostability of the three composites appears to be improved over that of unreinforced furan resin. A mass loss of 10% corresponds with a temperature of approximately 260°C for the composites, whilst for unreinforced furan resin it is lower at approximately 220°C. The three composites show rapid mass loss at approximately 275°C, which can be attributed to the degradation of the cellulosic structures of the CR fibres [31]. This degradation became worse with the increase of FMF since although the fibres are completely enclosed within the furan matrix, at higher FMF there is less matrix material to protect the fibres from degrading [12]. Between 280 and 320°C, the specimen with 51% FMF lost 5% less mass compared to the other two specimens with the higher FMFs. The specimen with 51% FMF also retained the greatest mass residue (41.1%) at 600°C, whilst the specimens with 64% FMF and 75% FMF retained mass residues of 34.0% and 13.5%, respectively.Figure 5
Thermogravimetric curves of the composites and control specimen.


## 4. Conclusions

A full biocomposite has been successfully fabricated from high tenacity rayon fibre and furan resin. Study of the laminate cracking behaviour revealed the two materials to be compatible as a composite system. The comparisons made with related furan resin-based biocomposites indicated that the CR fibres are a viable reinforcement in such composites. In particular, the CR fibres will be a suitable candidate to replace flax fibres if the tensile strength is of prime interest. Furthermore, the tensile properties benefit from a fibre mass fraction that is just above 60%; for additional improvements, it will be necessary to find means to stall the loss of fibre-matrix adhesion. One way to achieve this could be the incorporation of coupling agents to enhance the fibre-matrix adhesion. Since the CR fibres provided similar flexural strength as glass fibres in furan resin biocomposites, the CR fibres may be a suitable substitute for glass fibres in these biocomposites. This would add the advantage of reduced weight, which is necessary in the automotive sector. More research is required to determine the optimum fibre mass fraction corresponding with the best flexural and dynamic mechanical properties. For better control of resin bleed-out to improve fibre wetting and reduce porosity, alternative fabrication techniques have to be investigated, for example, vacuum bagging. The fibres can also be stitched into a unidirectional fabric for better alignment.



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*Source: 707151-2015-09-09.xml*