Surface functionalization of thermoset composite for infrared hybrid welding
Functional Composite Materials volume 2, Article number: 10 (2021)
Fusion assembly is a highly promising technique for joining thermoplastic composite to thermoset composites, enabling the use of both the most affordable composite material and process for each substructure. However, some major challenges need to be addressed such as functionalizing the thermoset composite surface through co-curing with an appropriate thermoplastic interlayer or realizing a fast and robust welding process that meets all quality and mechanical requirements. In this paper, we investigated the potential of polyetheretherketone (PEEK) and its amorphous (PEEK A) and semicristalline (PEEK SC) states as interlayer materials, co-cured onto thermoset composites. A surface preparation involving the atmospheric plasma process demonstrated that both PEEK state materials can be used as interlayer with favorable adhesion properties. The influence of the plasma treatment on surface properties and morphology was also experimentally characterized.
An infrared (IR) welding process, barely studied in the literature, was studied to assemble hybrid structural composite. To avoid the expected thermal degradation of the thermoset matrix, dissimilar infrared heating input power is proposed. Single lap shear tests and failure mode analysis were performed to highlight the promising performance of polyetherimide (PEI) as well as PEEK interlayer based hybrid joint.
Aeronautics have to address two main challenges in the upcoming decade: increasing the expected production rate and reducing the cost of composite manufacturing, assembly and control . Indeed, composite materials are a realistic alternative and a key component for reducing both weight and CO2 emissions without affecting mechanical performance. Composites used to replace metallic parts are composed of a reinforcement, generally glass or carbon fibers and a polymeric matrix, being either a thermoset or a thermoplastic. The use of thermosets over thermoplastics depends on the application, properties and cost. In the aerospace industry, thermoset based composites (TSCs) are currently being used because of their good compression, fatigue and creep resistance as well as their economical production in the form of large parts. Currently, TSCs are mainly assembled by time and labor consuming bonding/riveting techniques. Conversely, thermoplastic based composites (TPCs) demonstrate high ductility, fracture toughness and impact resistance and can be quickly manufactured by stamping and can be joined to other TPCs by welding.
To produce materials in a more efficient and affordable way, the combination of thermoset and thermoplastic composites, defined here as hybrid composites, opens new design possibilities. Indeed, hybrid composites will enable the use of the right material and the right manufacturing process for the right substructure.
Dissimilar TSC/TPC welding
Three main fusion based joining technologies have been explored in the literature to weld together hybrid composites. Resistance welding consists of placing an electrical resistance layer, made of metal or carbon fibers at the interface. The Joule effect is used to heat up the interface up to the point of fusion . Since 1980s, induction welding have been developed for polymer and composite welding and processing. A large range of methods, including static, discontinuous or continuous welding, describe the heat and pressure applications process. Induction heating occurs by transforming electromagnetic energy through a conductive interlayer, called a susceptor, or through the conductive properties of the reinforcement fibers, called a susceptorless approach. Ultrasonic (US) welding is well-known for polymer joining applications, but it is still emerging for structural composite material joining. Heat is generated through high-frequency and low-amplitude vibrations, generally concentrated by design singularities at the interface, called the energy director [6, 21].
Infrared welding is a highly mature welding technology for thermoplastic polymer joining, such as for automotive applications. The relative process simplicity and efficiency and the high level of automation represent strong advantages. Very few authors [4, 15] have explored the ability of this technique to join composites.
Regarding the different solutions proposed to join materials by infrared (IR) welding processes, numerous advantages, such as an ability to quickly heat (typically approximately 20–25 s), and a capacity to attenuate contamination risks, allow high productivity rates of reproducible joints in automated systems involving thermoplastic materials as stated by da Costa et al. .
Hybrid welding was explored by Asséko et al. , by investigating the joining of a glass fiber reinforced polycarbonate composite with carbon black filled polycarbonate. To the best of our knowledge, IR welding has barely been discussed and investigated for joining hybrid high-performance composites.
Thermal degradation during welding
Thermal degradation during welding represents one of the major constraints for process qualification. High-performance materials, such as polyetheretherketone (PEEK), present a sensivity to thermal exposure above their melting temperature. In the neat polymer, a weight loss of 0.5% is observed after 100 min at 400 °C. Both the enthalpy of fusion and the melting temperature were not modified after 10 s exposure to 400 °C. At 420 °C, significant changes were observed after 10 s of exposure in the literatur . More recently, the PEEK thermal stability over a short exposure time have been described by Pascual et al. . The investigation of the through thickness degradation of PEEK indicates that for temperatures below 400 °C, the degradation mechanism is slow. After 50 s at 400 °C, no major changes were observed in the melting temperature, crystallinity, or the glass temperature. Above 430 °C, a faster degradation process was observed.
Thermoset composites are definitely much more sensitive to thermal degradation than thermoplastic. To avoid thermal degradation, very short heating times are required Villegas and Rubio . A heating time well under 1 s is recommended. Such ultrafast heat cycles are only possible by US welding.
TSC surface functionalization
In the literature, many authors have explored the use of polyetherimide (PEI) as an interface material for hybrid welding. PEI has been demonstrated to be a good candidate to act as an interfacial layer for thermoset composite. PEI is generally preferred due to its intrinsic miscibility with epoxy resin, which leads to high resulting adhesion properties. However, this advantage also represents a weak point regarding several in-service applications. PEI polymer presents a limited withstand to aeronautical fluids [12, 26, 25]. Nevertheless, there is another challenge to overcome after co-curing: joining the co-cured TSC bearing a thermoplastic rich layer with the other part efficiently and in a short time. Therefore, the welding process needs to provide concentrated heat in a limited time.
PEEK based interlayers for hybrid welding have barely been investigated in the literature. The PEEK interlayer can be used direct be co-curing or coupled with a PEI interlayer .
The diffusion of thermoset precursors into thermoplastics is well described in the literature and mainly involves the dissolution of thermoplastic fibers, films or fillers into the thermoset precursor, enabling an increase in the thermoset composite toughness. The most popular tougheners are polysulfone (PSF), polyethersulfone (PES) and PEI, which are typically high glass temperature amorphous thermoplastics. Through the experimental analysis of the thermoplastic filament section embedded in the thermoset matrix, swelling kinetics have been observed by measuring the diffusion distance . The diffusion distance is strongly dependent on the isothermal temperature and duration prior to thermoset crosslinking. At 100 °C, the PES thermoplastic is unaffected by RTM6, an event after 180 min. Otherwise, at 140 °C, the PES section reduction was maximal after 20 to 60 min as a function of the PES end group. The diffusion efficiency is predominantly controlled by the thermoplastic Tg . Unlike PES filaments, phenoxy filaments are completely dissolved at 140 °C after 4 min, although PES and phenoxy have similar average molecular weights. The dramatically lower Tg of phenoxy compared to PES (84 °C vs. 220 °C) promotes thermoplastic chain mobility, inducing faster penetration of the thermoset precursor.
Interlayer surface preparation
PEEK is known for its poor wettability and poor adhesive properties. A large range of surface treatment methods have been investigated, such as atmospheric plasma, low pressure plasma , laser treatment or ultraviolet (UV)irradiation . UV irradiation of PEEK induces chemical structure changes, corresponding to higher absorption values by Fourier transform infrared (FTIR) analysis in the range from 1675 cm-1 to 1800 cm-1 and from 2700 cm-1 to 3600 cm-1. Chain scissoring is considered responsible for this change. By atomic force microscopy (AFM), in both height and phase images, the TSC/PEEK interface was analyzed. A clear interface is visible with as-received PEEK, however, a less obvious interface was observed with irradiated PEEK.
Plasma treatment of high-performance polymers, such as PEEK polymers, and the resulting chemical, physical and topological surface modifications are well described in the literature. Surface chemistry analysis has shown an increase in the oxygen content of the surface region, and increases the surface energy, O:C ratio and surface roughness . The plasma treatment induced surface etching of PEEK has been thoroughly studied by a few authors. The resulting roughness of the PEEK surface after plasma treatment is not consistently described. This can be explained by the first representation of the compared roughness parameters and the initial surface roughness. As an example, the arithmetic average roughness (Ra) increases with the plasma treatment time according to Shi et al.  but appears to be unaffected in semicrystalline PEEK according Zhang et al. . The use of less common roughness parameters, such as the total height of profile (Rt)  could provide a clearer view of the plasma induced surface roughness. By measuring the vertical distance between the maximum profile peak height and the maximum profile valley depth along the evaluation length, the potential dual-scale roughness, of namely, the initial roughness of the material surface and the secondary roughness induced by the treatment, is not taken into account.
In the present work, a new approach of hybrid thermoset/thermoplastic composites is proposed by welding both composites by automated fast infrared technology. We propose to study the co-curing of three different thermoplastic interlayers, treated with plasma and investigate how co-cured adhesion is driven by plasma treatment and the waiting time after treatment.
Functionalized TSCs are welded by infrared welding, enabling the production of standard testing samples and mechanical performance for each treatment condition and interlayer material conditions.
Materials for welding
In this work, a carbon fiber-reinforced PEEK consolidated laminate supplied by Toray Advanced Composites was selected. The 1.86 mm thick laminate is made of 6 plies of 5H satin weave from 3 K T300 carbon fiber roving with a quasi-isotropic layup.
Interlayer surface material
Two references of 25 μm PEEK film in an amorphous (PEEK A) and semicristalline (PEEK SC) state (Aptiv®2000 from Victrex®) with matte/gloss finishing were chosen. A 50 μm PEI (ULTEM™ from Sabic) film was also included in this study as a reference interlayer. The DSC analysis presented in Fig. 1 shows that PEEK A presents a low level of cristallinity, 8% as received, compared to the 34,7% crystallinity of PEEK SC as received. As received, PEEK A presents a slightly lower Tg of 143 °C than PEEK SC with a Tg of 148.5 °C. PEEK A starts to recrystallize by heating up to 160 °C. Per convention, the matte surface of the films is in contact with the TSC, and the gloss is welded on the TPC.
TSC surface functionalization
Interlayer surface treatment by plasma
Plasma treatments were performed using an atmospheric pressure dielectric barrier discharge (DBD) reactor. Briefly, plasma was ignited in a DBD (3 mm gap between the electrodes) in which each of the two high voltage aluminum plate electrodes was protected by a 3.25 mm thick glass plate. Plasma discharge was generated by an AC power supply set at 450 W and 6 kHz, with a flow of 80% N2 and 20% O2. The top electrode moved over the bottom electrode at a constant speed of 4 m.min 1. The deposition time was set to 1 min.
Through the proposed surface treatment by N2/O2(80/20) atmospheric plasma , the wettability of the three interlayer films was improved through cleaning and chemical activation. To better understand the time contribution of the treated surface and the hydrophobic recovery that can occur at the surface over time, tests were performed just after plasma treatment and then after 1 and 7 days on samples stored under ambient atmosphere conditions to evaluate their stability. An interlayer film without treatment of each interlayer material was also included. In the present work, a table summarizes the different thermoplastic interlayers used and the treatments performed.
Fricke et al.  reported that plasma treatment can significantly affect the surface roughness of polymer substrates. To quantify the expected surface roughness modification, 3D profilometry measurements were performed on both nontreated and plasma-treated interlayer films. Due to the initial roughness of the selected layer, profilometry was preferred over AFM. The profilometer used was a KAR TENCOR P17, and a scanning area of 50 μm per 50 μm was selected. Plasma treatment is also used industrially to activate polymer surfaces and consequently increase their wettability. Wettability measurements were performed by an OCA 15 contact angle system from Dataphysics. A series of 5 sessile water droplets of 2 μL were deposited on the surface of each sample by means of a syringe pump. The contact angle value was extracted from the droplet shape by using a numerical fit based on the Laplace-Young model. Plasma treatment is also responsible for major surface chemical changes. X-ray photoelectron spectroscopy (XPS) was performed to track chemical surface modifications with a VG SCIENTA SES-2002 spectrometer equipped with a concentric hemispherical analyzer. The incident radiation used was generated by a monochromatic Al Kα X-ray source (1486.6 eV) operating at 420 W (14 kV, 30 mA). Photoemitted electrons were collected at a take-off angle of 90 from the surface substrate, with electron detection in constant analyzer energy mode (FAT). A wide scan spectrum (survey) signal was recorded with a pass energy of 500 eV, and for high-resolution spectra (C1s and O1s), the pass energy was set to 100 eV. The analyzed surface area was approximately 24 mm2, and the base pressure in the analysis chamber during the experiment was approximately 10–9 mbar. The spectrometer energy scale was calibrated using the Ag 3d5/2, Au 4f7/2 and Cu 2p3/2 core level peaks, set at binding energies (BEs) of 368.2, 84.0, and 932.6 eV, respectively. Spectra were subjected to a Shirley background, and peak fitting was performed with mixed Gaussian-Lorentzian components with equal full-widthat-half maximum (FWHM) using CASAXPS version 2.3.18 software. The surface composition, expressed in atom%, was determined using integrated peak areas of each component and took into account the transmission factor of the spectrometer, mean free path and Scofield sensitivity factors of each atom. All the BEs were referenced to the C1s peak at285.0 eV and are presented with a precision of 0.1 eV. The O/C and N/C ratios were obtained by using the values from the surface composition analysis.
In order to better understand the time contribution of the treated surface, three post-treatment time are selected for this study: 1 min, 1 days and 7 days after treatment. An interlayer film without treatment of each interlayer materials is also included in the present work (Table 1).
Functionalized thermoset composite by liquid resin infusion (LRI)
The liquid resin infusion (LRI) process is used to co-cure the thermoplastic interlayer onto the TSC surface. The interlayer is first placed on the molding tool surface. Dry carbon fiber reinforcement, made of 6 plies of carbon fabric layup at 0°, supplied by Hexcel with the following type of yarns: warp, HexTow AS4C GP 3 K; weft: HexTow AS4C GP 3 K. The fabric’s weave style is twill 2/2 for a nominal weight of 200 g/m2. One 600 × 600 mm2 composite plate is injected per interlayer treatment conditions. All three interlayer materials, with an area of 200,600 mm2, are integrated on each plate. Once the dry carbon fiber reinforcement was reached with a peel ply, resin distribution media and a vacuum bag completed the setup. The setup was placed in a 2 m3 oven from SAT Thermique, with an accuracy of +/− 5 °C at 410 °C. An ISOJET injection machine composed of a pressured heated tank of 25 L, a resin flow rate control system and a heated transfer pipe was fully controlled automatically through a Schneider Citect/SQL monitoring automate.
The selected thermoset resin is RTM6–2, a bicomponent supplied by Hexcel. The curing cycle has been adapted to achieve resin polymerization above the PEEK Tg and below the recrystallization temperature of PEEK A. This cycle should promote the interlayer/TSC interface by molecular diffusion . The thermal cycle of 2 h at 150 °C + 2 h @ 180 °C with 5 °C/min heating ramp rate was selected. The applied recipe is described in Table 2.
On Fig. 2 the functionalized TSC surface is shown after demolding. It should be noted that the nontreated PEEK SC configuration presents no adhesion after demolding, which is why no welding tests are possible. The plates are water jets cut to a size of 100 mm × 170 mm and then welded in the next stage.
Infrared welding process for dissimilar join
IR welding principle
IR welding experiments were carried out using a FRIMO Infrared-Welding Machine ECO800 equipped with a welding tool enabling the assembly of two 100 mm long composite plates with an overlap of 12.7 mm. The welding line was 170 mm wide. Single lap shear (SLS) samples were cut in a later stage through water jet cutting with a width of 25 mm.
The welding tool is composed of upper and lower molds (cf. Figure 3), and the plates are positioned through a vacuum gripper. Both molds are fixed on a mobile table, enabling the definition of their position in the vertical direction at each process step. A mobile heating frame was able to move along the horizontal direction. On both sides of the heating frame, a set of infrared lamps was fixed. Each lamp is controlled individually, enabling control of the power as a function of time. By dissimilar material welding, the cycle times of the upper and lower sets of IR lamps are adapted to the thermal profile required by each material melting behavior.
IR welding process for dissimilar material welding
For dissimilar welding, the principle (cf. Figure 4) consists of heating each surface to assemble though an appropriate thermal cycle by individually controlling shortwave infrared emitters on the thermoset composite side and the thermoplastic composite side. Our approach consists of heating the thermoplastic composite up to the decompaction of approximately half of the initial material thickness and heating the thermoset composite side just before the end of the cycle as quickly as possible, enabling the fusion of the thermoplastic film without permanent major degradation of the thermoset composite substrate. In this work, two different heating cycle times are proposed: 27 s at 90% of the maximum infrared lamp power for the TPC and 17 s for the TSC. The TSC heating cycle starts after a 10 s delay compared to the TPC heating cycle start.
Figure 5 shows the thermal profile of both the welded surface and back surface of the TPC and TSC. Type K thermocouples with a 0.25 mm diameter were positioned on the surface to weld of each welding partner, as well as between the welding partner and the tool. A SEFRAM DAS 240 data logger was used for temperature acquisition with a sampling rate of 20 ms.
Thermal degradation of the TS matrix
Prior to the welding of TSC with TPC, a more in-depth study of the effect of IR light on the resin alone needs to be performed, as such materials are sensitive to high-energy light and high temperatures, which cause severe degradation and damage. The modification during the IR treatment was tracked by FTIR in reflection mode to assess the chemical variation. FTIR spectroscopy was performed on the surface of the as-manufactured resin at different IR radiation times from 1 to 15 s. From the spectrum, we can notice an increase in the peaks at 1660 cm 1 and the appearance of a shoulder at 1735 cm 1, which are related to the formation of carbonyl groups linked to thermal degradation when the sample is subjected to IR radiation in the presence of oxygen [7, 24]. Moreover, a decrease in the bond at 1050 cm 1 with increasing irradiation time can be attributed to the epoxy backbone ether bridge. Such a decrease can be assigned to chain scission and indicates the degradation/decomposition of the resin under IR light. By using high-energy IR irradiation, the surface of the resin is modified by a thermal degradation mechanism in which oxidation and chain scission occur. Such an observation can explain the failure in the thermoset composite observed in the next section. For future applications, the control of the power of the IR lamp will be optimized to avoid degradation while applying enough energy to weld the material (Fig. 6).
Results and discussion
Surface functionalization of TS composites
PEEK SC shows a significantly higher effect of plasma treatment on surface roughness than PEEK A or PEI. The root mean square (Sq) value was similar before and after plasma treatment, with values of 0.0213 μm and 0.0209 μm, respectively. In contrast, the kurtosis (Sku) value describing the sharpness of the roughness profile is strongly different. In the case of nontreated PEEK SC, the Sku value is 7.25, which is characteristic of a spiked height distribution. For plasma-treated PEEK SC, the Sku value is much lower, approximately 2.73. Here, the height distribution is skewed above the mean plane. Following plasma treatment, the initial primary roughness of the PEEK SC as received is complemented by a secondary roughness. PEEK A and PEI present a similar trend with a shift of the height distribution towards lower values.
The values of the measured 3D roughness are summarized in Table 3. PEEK SC shows a significantly higher effect of plasma treatment on surface roughness than PEEK A or PEI. The Sq is similar before and after plasma treatment, with values of 0.0213 μm and 0.0209 μm, respectively. In contrast, the Sku describing the sharpness of the roughness profile is strongly different. In the case of nontreated PEEK SC, the Sku is 7.25, which is characteristic of a spiked height distribution. For plasma-treated PEEK SC, the Sku is much lower, approximately 2.73. The analysis of the skewness value, describing the skewness of the topographic height distribution, confirms that following plasma treatment, the initial primary roughness of the PEEK SC as received is complemented by a secondary roughness. An Ssk value comparison between the as-received and plasma-treated interlayers shows a significant decrease for the three interlayer materials. The rate at smaller heights was higher with plasma treatment than without plasma treatment. The Ssk values of PEEK A and PEI present a similar trend with a shift of the height distribution towards lower values.
The analysis of the Abbot-Firestone curve  provides a more complete understanding of the plasma-induced 3D roughness (Fig. 7). For PEEK A and PEI, the height distribution shift is visible. The shift for PEEK SC of the height distribution is dramatic. This phenomenon can be explained by the plasma etching of the amorphous phase only, in accordance with the SEM observations of Zhang et al. , where a plasma-treated surface of PEEK allows the observation of better defined spherulites.
Durability of the surface energy
Surface analysis of the interlayer was performed prior at and after treatment. Water contact angle (WCA) measurements and surface free energy results are depicted in Figs. 8 and 9. Before plasma treatment, PEI, PEEK A and PEEK SC surfaces feature a WCA approximately 90.3°,91.3° and 96.1°, and a SFE of 40.0, 43.5 and 47.0 mN/m respectively. After plasma treatment, WCA decreased significantly to 26.9°, 33.3° and 34.3°, and increased to 65.9, 63.0 and 62.0 mN/m respectively for PEI, PEEK A and PEEK SC. As the WCA and SFE increase in the same manner, plasma treatment mainly introduces polar functions at the surface such as oxygen groups . The dispersive part measured is nearly constant for all surfaces. Moreover, to evaluate the possible hydrophobic recovery of such surfaces, the same analysis was performed after 1 and 7 days. The WCA and SFE go again trend in the same direction, and a decrease is observed, but the values are still higher than the initial values. This clearly demonstrates the formation of stable hydrophile functional groups based mainly on oxygen at the surface of all interlayers and specifically on PEEK. In addition to the contact angle, extreme surface analysis was performed to elucidate the chemical changes occurring during plasma treatment.
Durability of the chemical surface modification investigation
To further investigate the chemical changes occurring at the surface of the interlayer XPS investigation was performed and depicted in Figs. 10 and 11 based on the O/C and N/C ratios. The O/C ratio increased from 0.18 to 0.31 and from 0.05 to 0.08 for PEI. The same trends were observed for PEEK_A and PEEK_SC the ratio is twice that of the initial values after treatment. Such results are in good agreement with the literature highlighting the insertion of oxygen functionality at the surface of the polymer during atmospheric plasma treatment. The incorporation of nitrogen is very low in all samples. After storage of all sample for 1 and 7 days, a decrease in the O/C ratio is observed; however, the ratio is still higher than the initial values. Such results confirm the trend observed previously in WCA and SFE, highlighting the stability of the oxygen functionalities grafted at the surface of all PEI and PEEK samples even a few days of storage. By using plasma treatment, which is a fast (1 min), dry and easy technique to implement, the surface of the three interlayers was modified. This could foster interpenetration with the thermoset, and consequently increase the adhesion with the TS composites during the co-curing process.
Analysis of the surface functionalized TS composites
A pressure-controlled FEI Quanta FEG 200 scanning electron microscope (SEM) from FEI Company was used to obtain information about the microstructure in cross sections of the samples. Samples were embedded in epoxy casting resin and subsequently ground and polished until a scratch-free surface was obtained. Figure 12 highlights a cross-section of a sample with an interlayer at the surface as observed by SEM. The visible interlayer thickness was measured from the SEM image, and the measurement was reproduced five times along the length of the interlayer. The average measured thickness and the associated standard deviation are reported in Table 4. For PEEK A, the standard deviation can be explained by the relative initial surface roughness. For PEI, the standard deviation is mainly due to the difficulty of clearly fixing the limit between the PEI and the thermoset resin. Concerning the PEI interlayer, the average thickness, calculated from 5 interlayer thickness measurements, decreased for each interlayer surface condition. Before co-curing, the as-received PEI thickness was approximately 50 μm. After co-curing, the average visible PEI thickness was approximately 40 μm before and after plasma treatment. As previously discussed, the miscibility/compatibility between the resin and the PEI interlayer explains the changes in the thickness measured by SEM. During the co-curing phase, the resin can, before its gelation point, interpenetrate and interdiffuse through the PEI interlayer and create semi-interpenetrating networks [22, 11, 9]. However, no real difference can be observed and related to plasma treatment. In contrast to PEI, the initial thickness of the PEEK A interlayer does not exhibit any change during co-curing since the same thickness of approximately 25 μm was observed both before and after. Moreover, a clear difference in the grayscale range of the micrograph indicates a small diffusion distance, probably on the submicron-scale, of the thermoset resin into the PEEK interlayer. Although the plasma treatment does not demonstrate any improvement in the diffusion distance at the micron scale between the resin and the PEEK interlayer, the interface is smooth, without any voids or gaps, arguing for good adhesion. Interdiffusion probably occurs at the molecular or nanoscale and is beyond of the resolution of the SEM. Concerning the PEEK SC interlayer without plasma treatment, no adhesion occurs: the PEEK SC interlayer can be easily separated by hand, and no picture is provided. This configuration does not allow interpenetration with the resin during the manufacturing process. Unexpectedly, after plasma treatment, adhesion between the interlayer and the resin during co-curing occurs, as observed by SEM. Furthermore, no decohesion is visible between the two components. The joint line seems smooth and without any defects. The initial thickness was effectively observed by SEM without any additional sample etching preparation and was even on the same order of magnitude as the initial thickness of 25 μm. The surprising effect of plasma on co-cured PEEK SC has to be linked with the drastic change in surface roughness, mainly the height distribution. An explanation could be that the amorphous accessible surface was increased by plasma etching, enabling the interdiffusion of the thermoset onto the amorphous phase of the PEEK SC. The initial roughness of the PEEK SC allowed deeper analysis of the etching mechanism by SEM or AFM.
Welded dissimilar joint performances
Single lap shear (SLS) test result
The double cantilever beam (DCB) test is recognized as the most representative test for characterizing the joint interface of welded joints . The implementation of the DCD test for dissimilar joints is too limiting, as additional devices are required to avoid any sample rotation during the test.
SLS mechanical testing was selected to characterize the mechanical performance of the welded joint. This test is common and is effectively used to address hybrid joint performance. The SLS test was originally developed to investigate the bonding strength of homogeneous joints. In hybrid joints, the stiffness of both weld partners are different, and the constraint along the welding line is not symmetrical. Here, only the calculated shear strength can be compared, as the weld partner combinations are identical.
Figure 13 represents the obtained results from SLS mechanical tests performed on each sample. The value for untreated PEI is approximately 17.5 MPa, and the values for all treated samples are closer to 19 MPa. A slight increase occurs in the plasma-treated sample, which cannot be directly explained by the surface treatment itself, as failure occurs through the TSC instead at the interlayer interface. The same trends were observed for amorphous and semicrystalline PEEK, and a slightly higher value was reached after plasma treatment. Regarding the standard deviation of the lap shear test, this slight trend is considered a component of the welding process uncertainties and does not represent a direct effect of the plasma treatment waiting time after plasma treatment. Surprisingly, the waiting time after plasma treatment has no major impact on the resulting mechanical properties. Except for untreated PEEK SC, where no adhesion occurs with the resin during co-curing, the resulting values of the mechanical performance of both types of PEEK are not far from those of PEI, which means that the IR welding process combined with appropriate surface activation is a powerful technique to strongly bond thermosets to thermoplastic composites.
Failure mode analysis
To investigate the failure mode after the mechanical test, visual observations were performed on the test samples. Three types of failure modes were observed: adhesive failure at the TPC/interlayer interface, adhesive failure at the interlayer/TSC interface and cohesive failure through the TSC.
Figure 14 shows the failure surface of both welded partners using PEEK A material as the interlayer, with and without plasma treatment. It is interesting to note that without plasma treatment, the PEEK A interlayer presents local adhesive failure with the TSC. This failure mode is visible in two of the five tested SLS samples in this configuration. In this configuration, all three failure modes are observed. It is clear that plasma treatment plays a valuable role not only for PEEK SC material but also for PEEK A. With plasma treatment, no adhesive failure at the interlayer/TSC interface was observed. The failure mode was dominated by failure through the TSC composite.
Figure 15 shows the failure mode for both PEEK SC and PEI in the case of plasma treatment of the interlayer. Only cohesive failure through the TSC is observed. The same observation was made in analysis of the nontreated PEI. The first ply of the TSC is still welded after the SLS test.
Time after treatment appears to present no major influence. Similarly, wettability cannot be considered a major driving parameter, as no relationship between surface energy and mechanical performance is observed.
Plasma treatment affects PEEK A and PEI. Local adhesive failure between PEEK A and TSC without plasma treatment is no longer present after plasma treatment. No effect of the time after plasma treatment is observable. PEEK SC shows the dramatic effect of plasma treatment. With no adhesion without plasma treatment, the joints failed to fully cohere through the TSC like they do after plasma treatment, independent of the waiting time after treatment. The interpretation of the results is limited, as cohesive failure through the TSC limits the possibility of conclusions at the interlayer interface level, particularly for the PEI interlayer. The PEEK A interlayer failure analysis highlights how plasma improves the homogeneity of the interlayer adhesion. Plasma etching could explain the gain in both homogeneity and performance. This explanation is also consistent with the observed phenomenon in the PEEK SC interlayer, where plasma etching is assumed to be the main adhesion-driving parameter.
An investigation of plasma chemical surface modification of three interlayer materials is presented. The durability of the chemical surface modification was analyzed. No major link has been shown between chemical modification, durability of this modification and mechanical performance.
Plasma etching of the three interlayers of interest was investigated. The analysis of the 3D topological parameters enables us to better describe plasma surface modification. PEEK SC shows a radical topological change, particularly regarding the height distribution, and a radical increase in adhesion with plasma treatment. The two phenomena are certainly strongly connected. Plasma treatment, through the etching effect, allows the interdiffusion of the thermoset. This assumption must be confirmed in a more dedicated study.
Failure analysis of the nontreated PEEK A interlayer shows miscellaneous failure locations, including through the TSC, at the co-cured interlayer interface and at the welding interface.
Diffusion of the TS matrix in the PEI interlayer was expected and was observed through the reduction of the PEI thickness after co-curing. For both PEEK A and PEEK SC, no thickness variation was observed at the microscale, even if similar levels of SLS strength were measured. Diffusion certainly occurs at the molecular or nanoscale.
Although the obtained mechanical performance is below that of industrial requirements, IR welding has been proven to be suitable for designing hybrid composites without any additional elements, unlike resistive elements and energy directors for resistance and US welding, respectively. Further research on the adhesion between the interlayer and the resin needs to be done to better understand the underlying mechanisms. In addition, the optimization of IR welding process parameters or material combinations must be performed to avoid any TSC degradation.
Availability of data and materials
The datasets used and/or analyzed during the current study are available from the corresponding author on reasonable request.
E. Arikan, J. Holtmannspötter, T. Hofmann, H.J. Gudladt, Vacuum UV of polyetheretherketone (PEEK) as a surface pre-treatment for structural adhesive bonding. J. Adhes. 96(10), 917–944 (2020). https://doi.org/10.1080/00218464.2018.1545646
A.C.A. Asséko, B. Cosson, É. Lafranche, F. Schmidt, Y.L. Maoult, Effect of the developed temperature field on the molecular interdiffusion at the interface in infrared welding of polycarbonate composites. Compos. Part B 97, 53–61 (2016). https://doi.org/10.1016/j.compositesb.2016.04.064
J. Avenet, A. Levy, J.L. Bailleul, S.L. Corre, J. Delmas, Adhesion of high performance thermoplastic composites: development of a bench and procedure for kinetics identification. Compos. A: Appl. Sci. Manuf. 138(April), 106054 (2020). https://doi.org/10.1016/j.compositesa.2020.106054
I.D. Baere, K. Allaer, S. Jacques, W.V. Paepegem, J. Degrieck, Interlaminar behavior of infrared welded joints of carbon fabric–reinforced polyphenylene sulfide. Polym. Composites 33(7), 1105–1113 (2012). https://doi.org/10.1002/pc.22238
W. Ballout, P.V. Velthem, D. Magnin, E. Henry, M. Sclavons, T. Pardoen, C. Bailly, Specific influence of polyethersulfone functionalization on the delamination toughness of modified carbon fiber reinforced polymer processed by resin transfer molding. Polym. Eng. Sci. 59(5), 996–1009 (2019). https://doi.org/10.1002/pen.25055
A.P. da Costa, E.C. Botelho, M.L. Costa, N.E. Narita, J.R. Tarpani, A review of welding technologies for thermoplastic composites in aerospace applications. J. Aerosp. Technol. Manage. 4(3), 255–265 (2012). https://doi.org/10.5028/jatm.2012.04033912
A. Doblies, B. Boll, B. Fiedler, Prediction of thermal exposure and mechanical behavior of epoxy resin using artificial neural networks and Fourier transform infrared spectroscopy. Polymers 11(2), 363 (2019). https://doi.org/10.3390/POLYM11020363
K. Fricke, S. Reuter, D. Schroder, V.S. von der Gathen, K.D. Weltmann, T. von Woedtke, Investigation of surface etching of poly(ether ether ketone) by atmospheric-pressure plasmas. IEEE Trans. Plasma Sci. 40(11), 2900–2911 (2012). https://doi.org/10.1109/TPS.2012.2212463
X. Gao, Z. Huang, H. Zhou, D. Li, Y. Li, Y. Wang, Higher mechanical performances of CF/PEEK composite laminates via reducing interlayer porosity based on the affinity of functional s-PEEK. Polym. Compos. 40(9), 3749–3757 (2019). https://doi.org/10.1002/pc.25236
G. Gardiner, Welding thermoplastic composites : CompositesWorld. Composite World, 1–12 (2018)
M.T. Heitzmann, M. Hou, M. Veidt, L.J. Vandi, R. Paton, Morphology of an interface between Polyetherimide and epoxy prepreg. Adv. Mater. Res. 393-395(September), 184–188 (2012). https://doi.org/10.4028/www.scientific.net/AMR.393-395.184
R.O. Johnson, H.S. Burlhis, Polyetherimide: a new high-performance thermoplastic resin. J. Polym. Sci. Polym. Symp. 70(1), 129–143 (1983). https://doi.org/10.1002/polc.5070700111
J. Kundrak, K. Gyani, V. Bana, Roughness of ground and hard-turned surfaces on the basis of 3D parameters. Int. J. Adv. Manuf. Technol. 38(1–2), 110–119 (2008). https://doi.org/10.1007/s00170-007-10869
A. Kuzminova, A. Shelemin, O. Kylián, A. Choukourov, H. Valentová, I. Krakovský, J. Nedbal, D. Slavínská, H. Biederman, Study of the effect of atmospheric pressure air dielectric barrier discharge on nylon 6,6 foils. Polym. Degrad. Stab. 110, 378–388 (2014). https://doi.org/10.1016/j.polymdegradstab.2014.10.001
J.F. Lamèthe, P. Beauchêne, L. Léger, Polymer dynamics applied to PEEK matrix composite welding. Aerosp. Sci. Technol. 9(3), 233–240 (2005). https://doi.org/10.1016/j.ast.2005.01.008
W. Leahy, V. Barron, M. Buggy, T. Young, A. Mas, F. Schue, T. McCabe, M. Bridge, Plasma surface treatment of aerospace materials for enhanced adhesive bonding. J. Adhes. 77(3), 215–249 (2001). https://doi.org/10.1080/00218460108030739
A. Pascual, M. Toma, P. Tsotra, M.C. Grob, On the stability of PEEK for short processing cycles at high temperatures and oxygen-containing atmosphere. Polym. Degrad. Stab. 165, 161–169 (2019). https://doi.org/10.1016/j.polymdegradstab.2019.04.025
R. Phillips, T. Glauser, J.A.E. Månson, Thermal stability of PEEK/carbon fiber in air and its influence on consolidation. Polym. Composites 18(4), 500–508 (1997). https://doi.org/10.1002/pc.10302
H. Shi, J. Sinke, R. Benedictus, Surface modification of PEEK by UV irradiation for direct co-curing with carbon fibre reinforced epoxy prepregs. Int. J. Adhes. Adhes. 73, 51–57 (2017). https://doi.org/10.1016/j.ijadhadh.2016.07.017
K. Terpi, A.E. Wi, M. Jurak, Influence of nitrogen plasma treatment on the wettability of polyetheretherketone and deposited chitosan layers. Adv. Polym. Technol. 37(6), 1557–1569 (2018). https://doi.org/10.1002/adv.21813
E. Tsiangou, S.T. de Freitas, I.F. Villegas, R. Benedictus, Ultrasonic welding of epoxyto polyetheretherketonebased composites: Investigation on the material of the energy director and the thickness of the coupling layer. J. Compos. Mater. 54(22), 3081–3098 (2020). https://doi.org/10.1177/0021998320910207
L.J. Vandi, M. Hou, M. Veidt, R. Truss, M. Heitzmann, R. Paton, Interface diffusion and morphology of aerospace grade epoxy co-cured with thermoplastic polymers. 28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012 3(January 2012), 1984–1992 (2012)
P.V. Velthem, W. Ballout, D. Daoust, M. Sclavons, F. Cordenier, E. Henry, D. Dumont, V. Destoop, T. Pardoen, C. Bailly, Influence of thermoplastic diffusion on morphology gradient and on delamination toughness of RTMmanufactured composites. Compos. A: Appl. Sci. Manuf. 72, 175–183 (2015). https://doi.org/10.1016/j.compositesa.2015.02.012
I.F. Villegas, P.V. Rubio, On avoiding thermal degradation during welding of high-performance thermoplastic composites to thermoset composites. Compos. A: Appl. Sci. Manuf. 77, 172–180 (2015). https://doi.org/10.1016/j.compositesa.2015.07.002
R. Vodicka, Thermoplastics for airframe applications: a review of the properties and repair methods for thermoplastic composites. (1996)
C. Voto, M. Lannone, Environmental resistance of amorphous bonded thermoplastic joints -the utilization of advanced composites in military aircraft (1992)
X. Xiong, P. Zhao, R. Ren, Z. Zhang, X. Cui, S. Ji, Resistance welded composite joints strengthened by carbon fiber felt: Mechanical properties, failure modes and mechanism. Mater. Res. Express 6(8), 085323 (2019). https://doi.org/10.1088/2053-1591/ab226b
S. Zhang, F. Awaja, N. James, D.R. McKenzie, A.J. Ruys, A comparison of the strength of autohesion of plasma treated amorphous and semi-crystalline PEEK films. Polym. Adv. Technol. 22(12), 2496–2502 (2011). https://doi.org/10.1002/pat.1791
The authors gratefully thank Yves Fleming for 3D-Profilometry measurements and Jerome Guillot, for XPS analysis.
The project leading to this application has received funding from the Clean Sky 2 Joint Undertaking under the European Union’s Horizon 2020 research and innovation programme under grant agreement No 831979. All authors gratefully thank the European Commission and the Clean sky II JU.
The authors have no competing interest.
Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.
About this article
Cite this article
Perrin, H., Mertz, G., Senoussaoui, NL. et al. Surface functionalization of thermoset composite for infrared hybrid welding. Functional Composite Mater 2, 10 (2021). https://doi.org/10.1186/s42252-021-00021-5
- Infrared welding
- Thermoset composite
- Thermoplastic composite
- Dissimilar joining