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Article

Evaluation of XD 10 Polyamide Electrospun Nanofibers to Improve Mode I Fracture Toughness for Epoxy Adhesive Film Bonded Joints

by
Stefania Minosi
*,
Fabrizio Moroni
and
Alessandro Pirondi
Department of Engineering and Architecture, University of Parma, Parco Area delle Scienze 181/A, 43124 Parma, Italy
*
Author to whom correspondence should be addressed.
Processes 2023, 11(5), 1395; https://doi.org/10.3390/pr11051395
Submission received: 30 March 2023 / Revised: 20 April 2023 / Accepted: 25 April 2023 / Published: 4 May 2023
(This article belongs to the Special Issue Design of Adhesive Bonded Joints)
Browse Figures
Versions Notes

Abstract

:
The demand for ever-lighter structures raises the interest in bonding as a joining method, especially for materials that are difficult to join with traditional welding and bolting techniques. Structural adhesives, however, are susceptible to defects, but can be toughened in several ways: by changing their chemical composition or by adding fillers, even of nanometric size. Nanomaterials have a high surface area and limited structural defects, which can enhance the mechanical properties of adhesives depending on their nature, quantity, size, and interfacial adhesion. This work analyzes the Mode I fracture toughness of joints bonded with METLBOND® 1515-4M epoxy film and XantuLayr electrospun XD 10 polyamide nanofibers. Two joint configurations were studied, which differed according to the position of the nanomat within the adhesive layer: one had the nanofibers at the substrate/adhesive interfaces, and the other had the nanofibers in the center of the adhesive layer. Double cantilever beam joints were manufactured to evaluate the Mode I fracture toughness of the bonding with and without nano-reinforcement. The nanofibers applied at the substrate/adhesive interface improved the Mode-I fracture toughness by 32%, reaching the value of 0.55 N/mm. SEM images confirm the positive contribution of the nanofibers, which appear stretched and pulled out from the matrix. No fracture toughness variation was detected in the joints with the nanofibers placed in the middle of the adhesive layer.

1. Introduction

Advanced composite materials are commonly used for various applications due to their high strength-to-weight ratio. Glass fiber-reinforced polymers (GFRPs), carbon fiber-reinforced polymers (CFRPs), and sandwich structures are widely used in the aerospace, automotive, marine, and railway industries, as well as in the production of wind blades and sports equipment. The development of these materials has led to the advancement of structural adhesives and bonding techniques [1,2,3,4,5] used to join complex and multi-material structures, replacing traditional mechanical fastening [6,7,8]. Composite materials, metal fiber laminates, sandwich composites, and adhesive joints are subject to delamination. This refers to interlayer failure in the case of composite laminates, while for metal fiber laminates, sandwiches, and bonded joints, it refers to interface failure [9,10,11]. However, adhesive bonding is prone to delamination failure under high peel loads, which can be improved by developing new adhesive materials and bonding techniques [11].
Epoxy adhesive is widely used as a structural adhesive. However, in its neat formulation, it undergoes brittle fracturing, with a low fracture toughness, which represents a significant limitation for its application in the structural field [11,12]. Joints bonded with brittle epoxy adhesive are defect-sensitive and exhibit broad strength dispersion due to scatter in flaw sizes. To enhance the toughness of structural adhesives, particularly epoxy systems, various methods are commonly employed, such as adding fillers or thermally expandable particles (TEPs), or modifying the chemical resin composition [13,14,15].
The addition of rubber is also a common method used to enhance the fracture toughness of adhesives [16]. The rubbery phase can be introduced in the form of cross-linked [17,18] or core–shell rubbery particles [19], or liquid rubber can be mixed with resin precursors to allow the precipitation of rubbery particles during resin cross-linking [18,20]. To achieve the toughening effect for epoxy systems, a rubbery fraction between 5 and 20 wt. % is added. However, adding a high amount of rubber can lead to a reduction in the glass transition temperature (Tg), elastic modulus, and strength of the resin [21].
Adding organic and inorganic fillers, such as metallic micro- and nano-particles, nano-clays or short fibers, is another method used to improve the fracture toughness of structural adhesives [13,22,23,24]. Nanoparticles can also increase the fracture toughness, strength, and stiffness of bonded joints [13]. However, it is crucial to develop a strong interfacial adhesion to correctly transfer the load from the polymeric matrix to the nano-reinforcement [13]. Carbon-based nanoparticles, such as carbon nanofibers (CNFs), carbon nanotubes (CNTs) and graphene nanoplatelets (GNPs), are widely used for this purpose [25,26,27,28,29,30,31,32,33,34,35,36,37,38,39]. These nanoparticles enhance the fatigue life of bonded joints and can be used for damage detection, as they also improve the electrical properties of the resin they are dispersed in [29,30,31,32,33,34,35,36,37,38,39]. Recently, studies have shown that the application of hybrid nanoparticles is a viable approach to designing tougher, stronger and more durable bonded joints [40,41,42,43,44].
The integration of polymeric nanofibers has been shown to be an effective method for toughening epoxy matrices and composite materials [45]. Many studies have shown that composite laminates reinforced with electrospun polymeric nanofibers exhibit enhanced mechanical properties, including improved fracture toughness and delamination strength, with the interposition of a thermoplastic nanomat between composite layers promoting the ply-to-ply bridging effect [46,47,48,49,50,51,52,53]. Hamer et al. studied laminates of CFRP interleaved with electrospun Nylon 66 nanofibers. They performed DCB tests to evaluate the effects of the nanofibers on Mode I fracture toughness. The mat of naofibers embedded in the midplane improved the toughness by about 3 times [47]. Beckermann and Pickering studied the effects of interleaved nanofiber plies on the mode I and mode II interlaminar fracture toughness of carbon and epoxy resin laminates. Various types of electrospun nanofibers were placed in the midplane planes of the laminates. The results show that the best performance was achieved using 4.5 g/m2 PA66 ply, with fracture toughness improvements of 156% and 69% for Mode I and Mode II, respectively [49]. Saghafi et al. studied the effect of Nylon 6,6 nanofibers interleaved in the midplane of glass/epoxy laminates on mode I and mode II fracture toughness. Nylon 6,6 nanofibers improved the initial GIC and GIIC energy release rates by 62% and 109%, respectively [50]. Daelemans et al. demonstrated that nanofibrous veils of PA 6.9 with different morphologies interleaved in UD carbon/epoxy laminates cause an increase in mode II interlaminar fracture toughness. Mode II interlaminar fracture toughness is doubled by randomly deposited PA 6.9 nanofibers [51]. Goodarz et al. demonstrated that the interfacial incorporation of aramid nanofibers significantly increases the absorbed impact energy, compared to laminates without nanofibers [54].
These results suggest that polymeric nanofibers could be effective in improving crack toughening for bonded joints as well. There have been limited studies on the use of electrospun nanofibers in adhesive bonding, particularly with medium–low-fracture toughness epoxy resins [55,56,57,58]. The works [55,56] analyze the effect of a core/shell structure of electrospun meta-aramid fibers integrated into the adhesive layer of the epoxy-bonded joint. Single-lap shear test results show that electrospun meta-aramid nanofibers decreased joint strength, while those with core/shell structure restored the strength of pure epoxy. Razavi et al. found that incorporating polyacrylonitrile (PAN) nanofibers into an aluminum DCB joint bonded with 2k epoxy resin resulted in a two-fold increase in fracture toughness [57]. Ekrem and Avci demonstrated that incorporating polyvinyl alcohol (PVA) nanofibrous mats into the adhesive layer of single lap joints (SLJ) and DCB joints improved shear strength by 13.5% and increased mode I fracture toughness by about two times that of the neat adhesive [58]. In a previous work, the authors demonstrated that electrospun nylon nanofibers can act as reinforcements and support for the adhesive layer, improving the fracture toughness of low-toughness resins in DCB joints made with pre-impregnated nano-fibers [59,60,61,62]. In a previous work, impregnation of the nanofibers was initially performed with low- and medium-viscosity epoxy resins to facilitate the wetting of the nanomat [59]. Then, an unfilled medium viscosity two-component epoxy adhesive was used before using a high-viscosity, high-strength two-component epoxy adhesive system [60,61,62]. However, tests performed on bonded joints were characterized by extensive areas of adhesive failure, at the interface between substrate and adhesive. The improvement of interfacial adhesion is critical for the evaluation of the effect of nanofibrous structures.
Despite the non-marginal scientific literature on the application of nanofibers for interface toughening, the application to adhesive bonding is still limited, and in-house procedures for the embedding are used, for which the possibility of scaling up to an industrial level is either impractical or unclear. Additionally, home-made electrospun nanofibers are often used, which may have a more limited reproducibility than when manufactured on an industrial scale.
Based on the previous considerations, this study investigates the effect of commercial XD 10 polyamide electrospun nanofibers (XantuLayr™, NANOLAYR LTD, Auckland, New Zealand) on composite joints bonded with epoxy film, commonly used in the aerospace industry. The XantuLayr nanomat is known to improve the interlaminar fracture toughness of composite laminates, resulting in higher delamination resistance and damage tolerance [49,53].
In this work, a XantuLayr electrospun nanomat was used for the first time as a toughening element of composite adhesive joints made by secondary bonding. Furthermore, the joints were produced using bonding techniques employed in the automotive and aerospace industries, and were thus compatible with current industrial practices. The manufacturing technique of these joints is therefore replicable in an industrial environment and not just on a laboratory scale. In this work, two joint configurations were studied: one with nanofibers applied at the adhesive/adherend interfaces, and one with nanofibers placed in the center of the adhesive layer. Double Cantilever Beam (DCB) joints were produced to evaluate the mode-I fracture toughness of the bond with and without nano-reinforcement. A morphological analysis was also performed to understand the phenomena occurring during crack propagation.

2. Materials and Method

2.1. Adherends

In this study, CYCOM® 977-2 prepreg (Solvay Specialty Polymers SpA, Bollate (MI), Italy) was used to fabricate composite adherents. This prepreg is suitable for aerospace and aircraft applications that require impact resistance and light weight. The unidirectional tape used had a nominal thickness of 0.186 mm and a density of 1.55 g/cm3. A quasi-isotropic laminate was produced using 32 layers of prepreg with a lamination sequence of [45/0/–45/90]4s. The panels were prepared for bonding using a peel ply, a sacrificial layer of fabric put on the surface of the composite. The panel was vacuum-bagged and cured in an autoclave using the cycle specified by the prepreg technical datasheet. The vacuum bag was realized as reported in Figure 1. After curing, the part was debagged and cut to size. The peel ply was removed from the panel surface prior to bonding.
The elastic modulus of the laminate was evaluated to be 58 GPa using tensile testing in accordance with the ASTM D3039 standard [63].

2.2. Adhesive

The epoxy adhesive used for the joint fabrication was the METLBOND® 1515-4M (Solvay Specialty Polymers SpA, Bollate (MI), Italy). This adhesive is mainly employed for bonding composites, although it is suitable for various metal bonding applications. The adhesive has a nominal weight of 242 g/m2, with a nylon web carrier accounting for 7.5% of the total weight of the film. The elastic modulus of the adhesive film is closely related to the curing pressure and temperature. Based on recommendations from the supplier and various studies in the literature, the elastic modulus of METLBOND® 1515-4M was determined to be 3.5 GPa [64,65,66]. The yield strength, ultimate strength and strain at failure of the adhesive were not available in the data sheet and, since they are not essential to the purposes of the work and the manufacturing of a tensile test specimen out of a film adhesive is not straightforward, they were not evaluated.
The curing cycle for the bonded joints included an autoclave at 6 bar pressure at 180 °C for 210 min. This cycle is similar to that proposed by the adhesive manufacturer’s datasheet, and is the same as that employed for the adherents’ manufacturing. The chosen cure cycle is of industrial significance as it enables the consolidation and cure of prepreg and secondary bonding simultaneously, leading to time and energy savings, and it is suitable for co-bonded joints.

2.3. Nanofibers

XantuLayr® (NANOLAYR LTD, Auckland, New Zealand) is a thermoplastic nanofiber veil produced using Sonic Electrospinning Technology. It consists of XD10 polyamide nanofibers that form an ultra-thin non-woven web. For this study, a XantuLayr® nanomat with an areal density of 3 g/m2 was used. The thickness of the nanomat was measured using a digital indicator (ALPA, Pontoglio (BS), Italy), with a preload of 0.65 N, and was found to be in the range of 120 to 160 μm.

2.4. Double Cantilever Beam Fabrication

To assess the impact of integrating commercial nanofibers on the fracture toughness of the adhesive system, four series of DCB joints were manufactured. Table 1 and Figure 2 provide details of the various configurations of the DCB joints.
The four configurations chosen were 1S, 2S, 1S–2NF and 2S–1NF. The 1S and 2S configurations refer to the virgin specimens, bonded with one and two layers of adhesive, respectively. The 1S–2NF and 2S–1NF configurations refer to the bonded joints reinforced with nanofibers. The 1S–2NF configuration involves the positioning of nanofibers at the adhesive/support interfaces of joints bonded with one layer of adhesive. The 2S–2NF configuration involves the positioning of nanofibers at the center of the adhesive layer of joints bonded with a layer of epoxy film.
The number of samples was defined in such a way as to derive at least five useful samples for calculating the average fracture toughness value and assessing the repeatability of the failure type.
To manufacture the specimens for testing, two composite panels measuring 190 × 150 mm2 were bonded together and placed in a vacuum bag. A peel-ply was used in the preparation of the panels, which was then removed after the composite had cured, prior to bonding. This method proved to be an effective means of ensuring a strong bond between the composite parts. The joint curing process was carried out in an autoclave at 6 bar pressure and 180 °C temperature for 210 min. During the bonding stage, a 25 mm initial defect was introduced by placing a 0.1 mm-thick Teflon patch on one end of the joint. The nanofibers were placed manually on the adhesive film. Since they were supported on a paper backing, they were easy to handle. Once the nanofibers were properly positioned, the paper backing was removed. After curing, the panels were cut to form DCB joints with a length of 150 mm and width of 25 mm. Two pairs of bonded panels were manufactured for each configuration. Holes were machined for each joint to enable the attachment of steel blocks, which were utilized to secure the specimen in the testing apparatus. Steel blocks were glued to the DCBs using Loctite Hysol 9466 adhesive. To ensure the correct positioning of the blocks, they were fastened to the adherents with screws and bolts. Once the adhesive was polymerized after 24 h at room temperature, screws and nuts were removed, and the DCB was ready to be tested. The adherent dimensions were reduced if compared with ASTM D3433 standards. These dimensions were chosen on the basis of the available material. The DCB geometry is illustrated in Figure 3. Figure 4 and Figure 5 show an example of a tested specimen and the same one mounted on the test machine.
The Table 2 shows the average thicknesses of the tested specimens. The calculation of the adhesive layer’s thickness was carried out using the difference between the average joint thickness and the average thickness, t, of the individual adhesives. The presence of the nylon cloth inside the adhesive layer ensures joints with a constant adhesive cross-section.

2.5. DCB Test

The DCB test was conducted on a servo-hydraulic MTS 810 machine with a 3 kN load cell, using displacement control at a constant crosshead velocity. The loading and unloading rates were 2 mm/min and 5 mm/min, respectively. The correct determination of mode I fracture toughness is crucial to assess the integration effect of the nanomaterial. There are several data reduction methods that can be used to overcome the problem of direct crack length monitoring during the DCB test. The data reduction schemes include the compliance calibration method, in which compliance is calibrated as a polynomial function of crack length, and the compliance-based beam method, which considers the influence of the fracture process zone [67,68,69]. In this paper, according to the same procedure used in the past by the authors, partial unloadings are performed to determine the specimen compliance and actual crack length using Krenk’s model, reported in [70], which accounts for the out-of-plane deformation of the adhesive layer and rotation at the crack tip. The model is represented by Equation (1):
C = δ ′ P = 2 2 λ σ k 1 + λ σ a + a + g 2 λ σ 2 k 1 + 2 λ σ a + a 3 3 E J + g a 2 2 E J
The joint compliance (C (mm/N)) is determined by dividing the Crack Mouth Opening Displacement (CMOD) measurement at the front of the specimen (δ′ (mm)) by the load (P (N)). Other variables in the equation include the actual crack length (a (mm)), Young’s modulus of the adherents (E (MPa)), and area moment of inertia of the adherent (J (mm4)). A clip gage was used to measure the CMOD during testing. The model presented in Equation (1) has been modified from the one proposed by Krenk to account for the distance (g (mm)) between the measurement point and the load axis, as well as the effect of shear.
The joint geometry is shown in Figure 6.
The dimensionless parameters λσ and k are reported in Equations (2) and (3):
λ σ = 6 h 3 t E a E 1 − υ a 2 4
k = 2 E a t t   1 − υ a 2
where all the sizes are expressed in mm, while Ea (MPa) and νa (dimensionless) are the Young’s modulus and the Poisson’s ratio of the adhesive, respectively. The Mode I strain energy release rate G (N/mm) is:
G I = P a 2 t E J 1 + 1 λ σ a 2
Since the fiber volume fraction is negligible, for the rule of mixtures, the Young’s modulus of the nanomat prepreg is also approximately the same as that of the adhesive alone.

3. Results and Discussion

Figure 7, Figure 8 and Figure 9 show the load against CMOD of virgin and nanomodified specimens 1S, 2S, 1S–NF and 2S–1NF, taken as representative. The load peaks of virgin samples are slightly lower than 600 N, and the employment of two layers instead of one does not significantly affect adhesive performance. The nanomodified sample has a slightly higher load peak than the neat joint during crack propagation, and the behavior of the 2S–1NF joint is comparable to that of the virgin samples.
Figure 10 displays the fracture surfaces of 1S, 2S, 1S–2NF, and 2S–1NF samples. As can be seen from the picture, the fibers of the bonded surface are at 45°. This solution was preferred as it represents a more general case of joining. The blue areas highlight the presence of the adhesive on the substrate under examination. The 1S specimens failed cohesively during the first stage of the crack propagation, but the crack deviated inside the composite support generally after 30 mm of propagation inside the adhesive. The failure mode of 2S samples was more scattered, with cohesive failure observed in joints 2S–1, 2S–4, and 2S–5 in the initial stage of crack propagation, interfacial fracture in joints 2S-2 and 2S-3, and cohesive fracture in joints 2S–6, 2S–7, and 2S–8. Figure 11 shows SEM images of the fracture surfaces of the 1S–1 and 2S–6 samples, respectively, which show micro-dimples and broken nylon fibers. The 1S–2NF specimens failed cohesively, but the crack deviated inside the composite supports of the samples 1S–2NF 3, 4 and 5 after 30 mm of propagation inside the adhesive. Samples 2S–1NF exhibited cohesive failure, but half of them were subjected to crack propagation inside the composite layer at Δa values of 10–20 mm, making the results less reproducible. Figure 12 shows SEM images of the fracture surfaces of 1S–2NF–1 and 2S–1NF–5 samples, respectively, which showed micro-dimples, the presence of nylon cloth, and areas rich in nanofibers. The nanofibers in the sample 2S–1NF appear less stretched and were broken inside the matrix without evident pull-out, resulting in fracture toughness values lower than those of 1S–2NF samples and comparable to those of virgin ones.
Figure 13 shows a comparison of the R-Curves of one representative specimen for each configuration. The black markers identify the GIC values used for calculating the average fracture toughness during the steady-state crack propagation phase, while the grey markers represent the excluded ones. Considering all the specimens tested (see Table 1), the average fracture toughness of the neat adhesive is 0.42 ± 0.07 N/mm for 1S and 0.42 ± 0.10 N/mm for 2S. The average fracture toughness of the nanomodified 1S–2NF series is instead 0.55 ± 0.16 N/mm, while for 2S–1NF, it is about 0.44 ± 0.8 N/mm. The average GIC values are reported in Figure 14. The samples 1S–2NF have more scattered values, but higher average GIC than 2S–1NF. The average maximum load values are reported in Figure 15. Again, the highest maximum load was achieved by the 1S–2NF samples with an average maximum load value of 580 N ± 47 N, which is 10% higher than that of the 1S specimens.
The results obtained confirm that the virgin samples exhibit the same fracture toughness values, regardless of the number of adhesive layers used for bonding. The highest values of fracture toughness were obtained by the 1S–2NF samples. Nanofibers placed at the adhesive/adhesive interface deformed and contributed to the joint toughness. The configuration 1S–2NF exhibited a 32% improvement compared to 1S samples. The lower deformation of the nanofibers placed between the two adhesive layers of the 2S–1NF samples resulted in a lower toughness value of the system, which, however, was still comparable with the virgin samples.

4. Conclusions

The effect of commercial XD10 PA (XantuLayr®) nanofibers within composite joints bonded with the epoxy film was studied. Materials and bonding techniques commonly employed in the automotive and aerospace sector were used for joint manufacturing. Since the adhesive was in film form, nanofiber integration could be approached in two ways. The first was to apply the nanofiber at the adherents/adhesive interface. The second was to interleave the nanomat between two layers of adhesive.
The main results are reported below:
  • The behaviors of virgin samples are similar, and are not influenced by the number of adhesive layers used for bonding;
  • The application of commercial XD10 PA nanofibers (XantuLayr®) at the adhesive/adherent interface improves the mechanical performance of the composite joints, which exhibited higher fracture toughness and fracture resistance than virgin samples. In particular, the 1S-2NF specimens exhibited 10% and 32% higher maximum strength and fracture toughness values, respectively;
  • SEM images confirm the contribution of the nanofibers that appear elongated and detached from the matrix. The deformation of the nanomat contributes to the joint toughness;
  • The same nanomaterial applied to the center of the adhesive layer does not contribute to the fracture toughness of the joint, as the nanomodified joints show the same GIC and standard deviation values as the virgin samples.
The application of commercial XD10 PA nanofibers (XantuLayr®) was very simple, and is definitely compatible with materials and bonding techniques used for composite materials.
Further developments of this work will involve evaluating mode II fracture toughness through End-Notched-Flexure (ENF). Further analyses could be conducted on thinner substrate bonds by performing T-Peel tests.

Author Contributions

Conceptualization, S.M. and A.P.; methodology, S.M., F.M. and A.P.; software, N/A; validation, A.P. and F.M.; formal analysis, S.M.; investigation, S.M.; resources, S.M., F.M. and A.P.; data curation, S.M.; writing—original draft preparation, S.M.; writing—review and editing, A.P. and S.M.; visualization, S.M.; supervision, A.P.; project administration, N/A; funding acquisition, N/A. All authors have read and agreed to the published version of the manuscript.

Funding

This research received no external funding.

Data Availability Statement

Data is contained within the article.

Conflicts of Interest

The authors declare no conflict of interest.

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Processes 11 01395 g001 550
Figure 1. Vacuum bag.
Figure 1. Vacuum bag.
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Figure 2. Configurations of the adhesive layers.
Figure 2. Configurations of the adhesive layers.
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Figure 3. Composite DCB geometry.
Figure 3. Composite DCB geometry.
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Figure 4. Example of a DCB specimen.
Figure 4. Example of a DCB specimen.
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Figure 5. Specimen mounted on the testing machine.
Figure 5. Specimen mounted on the testing machine.
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Figure 6. DCB geometry [71,72], where a0 is 25 mm and g is 6 mm.
Figure 6. DCB geometry [71,72], where a0 is 25 mm and g is 6 mm.
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Figure 7. Load against CMOD (δ′) for virgin specimens 1S–1 and 2S–6.
Figure 7. Load against CMOD (δ′) for virgin specimens 1S–1 and 2S–6.
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Figure 8. Load against CMOD (δ′) for both virgin (1S–1) and nylon-nanomodified (1S–2NF–1) specimens.
Figure 8. Load against CMOD (δ′) for both virgin (1S–1) and nylon-nanomodified (1S–2NF–1) specimens.
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Figure 9. Load against CMOD (δ′) for both virgin (2S–6) and nylon-nanomodified (2S–1NF–5) specimens.
Figure 9. Load against CMOD (δ′) for both virgin (2S–6) and nylon-nanomodified (2S–1NF–5) specimens.
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Figure 10. Fracture surface.
Figure 10. Fracture surface.
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Figure 11. SEM images of fracture surfaces of 1S–1 (a) and 2S–6 (b) at 2000×.
Figure 11. SEM images of fracture surfaces of 1S–1 (a) and 2S–6 (b) at 2000×.
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Figure 12. SEM images of fracture surfaces of 1S–NF–1 (a) and 2S–1NF–5 (b) at 10,000×.
Figure 12. SEM images of fracture surfaces of 1S–NF–1 (a) and 2S–1NF–5 (b) at 10,000×.
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Figure 13. Comparison of R-Curves of representative virgin (1S and 2S) and nanomodified (1S–2NF and 2S–1NF) specimens.
Figure 13. Comparison of R-Curves of representative virgin (1S and 2S) and nanomodified (1S–2NF and 2S–1NF) specimens.
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Figure 14. GIC average values for 1S, 2S, 1S–2NF, and 2S–1NF samples.
Figure 14. GIC average values for 1S, 2S, 1S–2NF, and 2S–1NF samples.
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Figure 15. Maximum load average values for 1S, 2S, 1S–2NF, and 2S–1NF samples.
Figure 15. Maximum load average values for 1S, 2S, 1S–2NF, and 2S–1NF samples.
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Table
Table 1. Composite DCB joints configurations.
Table 1. Composite DCB joints configurations.
Series IDAdhesive LayerNumber of Samples
1S METLBOND® 1515-4M7
2S 2 METLBOND® 1515-4M8
1S–2NF XantuLayr® + METLBOND® 1515-4M + XantuLayr®8
2S–1NF METLBOND® 1515-4M + XantuLayr® +
METLBOND® 1515-4M		8
Table
Table 2. Samples thickness.
Table 2. Samples thickness.
Sample IDt (mm)
1S 0.17
2S 0.48
1S–2NF 0.18
2S–1NF 0.52
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Minosi, S.; Moroni, F.; Pirondi, A. Evaluation of XD 10 Polyamide Electrospun Nanofibers to Improve Mode I Fracture Toughness for Epoxy Adhesive Film Bonded Joints. Processes 2023, 11, 1395. https://doi.org/10.3390/pr11051395

AMA Style

Minosi S, Moroni F, Pirondi A. Evaluation of XD 10 Polyamide Electrospun Nanofibers to Improve Mode I Fracture Toughness for Epoxy Adhesive Film Bonded Joints. Processes. 2023; 11(5):1395. https://doi.org/10.3390/pr11051395

Chicago/Turabian Style

Minosi, Stefania, Fabrizio Moroni, and Alessandro Pirondi. 2023. "Evaluation of XD 10 Polyamide Electrospun Nanofibers to Improve Mode I Fracture Toughness for Epoxy Adhesive Film Bonded Joints" Processes 11, no. 5: 1395. https://doi.org/10.3390/pr11051395

APA Style

Minosi, S., Moroni, F., & Pirondi, A. (2023). Evaluation of XD 10 Polyamide Electrospun Nanofibers to Improve Mode I Fracture Toughness for Epoxy Adhesive Film Bonded Joints. Processes, 11(5), 1395. https://doi.org/10.3390/pr11051395

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