1 Introduction

Drilling is a conventional machining process for producing round holes of different sizes and depths in aeronautical structures. The number of holes can vary from 300,000 up to three million in commercial aircraft [1,2,3,4]. At the same time, poor hole quality is responsible for around 60% of all parts rejection [1, 5, 6]. Poorly machined holes usually lead to costly corrective manufacturing measures and increase the required inspection time [3, 4, 7]. Holes are produced to allow for fastener installation for assembly purposes. Failure to produce acceptable hole quality can lead to excessive preloads, fatigue and may cause cracks in the assembly. Hole quality is often evaluated by several parameters which must meet tolerances depending on their final application, customer specification or current standards. Hole size, circularity, cylindricity and perpendicularity error are some of the most inspected hole quality parameters in aerospace applications.

Fibre metal laminates (FMLs) are made from thin layers of composites materials and sheets of metallic alloys bonded together using adhesive epoxies [8,9,10,11]. The metallic sheets are usually made from aluminium alloys, while the composite layers are usually made from glass (GLARE®), aramid (ARALL®) or carbon fibres (CARALL®) [11]. The typical thickness of the metallic sheets can be anything between 0.25 and 0.5 mm, and the total material thickness is typically less than 1 mm but can be as thick as 20 mm [9, 12, 13]. GLARE® offers weight savings between 15 and 30% and improved fatigue resistance over standard aeronautical aluminium alloys [10, 14, 15]. The first utilisation of GLARE® panels was in the Boeing 737, 757 and 777 cargo floors and liners, in the Learjet 45 and on the C-17 Globemaster III cargo doors [8, 11, 16,17,18,19]. Currently, GLARE® is installed in parts of the Airbus A380 fuselage skin, lateral shells and the vertical stabiliser [9, 20, 21].

Drilling and milling operations are applied to GLARE® structures for assembly and riveting purposes [9, 21]. Experimental machining studies on GLARE® laminates have been increasing in the last 20 years [2, 4, 6, 9, 21,22,23,24,25,26,27,28,29,30,31,32,33,34,35,36,37,38,39]. Previous studies on drilling GLARE® studied the impact of machining parameters, drill geometry, workpiece thickness, fibre orientation and cooling strategy on several hole quality parameters [2,3,4, 6, 9, 21,22,23,24,25,26,27,28,29,30,31,32,33,34,35,36,37,38,39,40]. A smaller number of studies also investigated the influence of drill geometry and coating on the generated drilling forces and hole quality [4, 26, 40,41,42]. Reported findings suggest that carbide drills perform better than uncoated and high-speed steel drills due to the abrasive glass fibre layers [9, 21, 41]. Other studies investigated the influence of machining coolants [3, 9, 22, 23]. It was found that cryogenic and minimum quantity lubrication cooling technologies tended to reduce burrs, surface roughness and workpiece temperature when compared to dry conditions [3, 9, 22, 23]. The laminate thickness and fibre orientation were also found to impact the hole quality [6, 22, 23, 27].

In comparison with more traditional engineering materials, only a few studies looked into the impact of drilling parameters, drill coating and geometry on specific hole quality metrics, i.e. hole size, circularity and perpendicularity, when drilling FMLs [2,3,4, 22,23,24]. For these studies, the measured hole parameters and their values are summarised in Table 1. Also, this table reports such results for studies that focussed on the drilling of the constituent materials used in FMLs. Based on this body of literature, it can be said that none of the previous work on the hole drilling in FMLs investigated the impact of drill coating when the drill geometry is fixed (i.e. point angle, helix angle, diameter). For this reason, the work reported here investigates the impact of three drill coatings on hole quality parameters (hole size, circularity, cylindricity and perpendicularity) under different spindle speeds and feed rates while using same drill geometry (i.e. drill size, helix and angles). In this way, it is possible to evaluate specifically the influence of drill coating on hole quality. The analysis reported in this work is carried out using design of experiments (DoE) and ANOVA is implemented to study the impact of the feed rate, the spindle speed and their interactions on the studied outputs.

Table 1 Previous drilling studies reporting on hole size, circularity, perpendicularity, and cylindricity when drilling different aeronautical materials [2]
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2 Materials and method

2.1 Workpiece details

The workpiece material utilised in this research is a GLARE® 2B laminate as shown in Fig. 1a. The laminate is made up of Al2024-T3 aluminium sheets and S2/FM94 glass fibre-epoxy layers [3, 4, 6]. The distance between the centres of two holes drilled adjacent to each other was kept constant as illustrated in Fig. 1b [49]. The workpiece dimensions were 200 mm × 150 mm and approximately 7.13 mm thick. Each glass fibre layer was made up of two plies oriented at 90°/90° with respect to the aluminium rolling direction (0°) as represented with Fig. 1c.

Fig. 1
figure 1

Details of the GLARE® workpiece used in the current study. a Side view. b Front view. c Laminate configuration [3, 50]

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2.2 Machining setup and drill details

A Geo Kingsbury three-axis milling machine was used to drill the holes in the GLARE® workpiece [49]. The sample was placed on the top of a 20-mm-thick support plate made from stainless steel to restrict the movement or bending of the laminate similarly to previous studies [3, 4, 6, 22, 49]. The complete setup is shown in Fig. 2. The drilling tests were conducted without the use of any coolants (dry drilling). Additional drilling tests were conducted on a Quaser MV 154-C-CNC milling machine to measure the thrust force. The thrust force was measured using a KISTLER 9257B dynamometer. A DynoWare software, KISTLER 5697A data acquisition system and 5070A 8-channel charge amplifier were used for measurement and data acquisition.

Fig. 2
figure 2

Setup of the GLARE® laminate inside the CNC machine [49]

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The drilling tools were made from coated carbide material with a Ø6-mm nominal diameter. All drills had a fixed 140° point angle, and a 30° helix angle which was based on previous studies and literature [2,3,4, 6, 22,23,24,25,26, 41, 50]. The three types of coatings investigated in this work were TiAlN, TiN and AlTiN/TiAlN. The drills had an M7 tolerance which means that their actual diameter was between Ø6 mm + 0.004 mm and Ø6 mm + 0.016 mm. The full details of dimensions, geometry and other properties of the drills employed are given in Table 2.

Table 2 General information about the drill bits used and their coatings [49]
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2.3 Machining parameters and design of experiments

Three feed rates (f) and three spindle speeds (n) were used in the current study according to previous literature on drilling GLARE® laminates [3, 4, 6, 22, 23, 26, 27, 47, 51]. A design of experiments (DoE) approach was implemented using a full factorial design composed of three levels and with a total of 27 runs (L27 orthogonal array). The proposed orthogonal array can determine the influence of the spindle speed, feed rate and drill coating and their linear interactions on the studied hole parameters. The analysis of variance (ANOVA) was carried out to determine the percentage contribution of the drilling parameters and drill coating on the studied hole quality parameters. Each trial was repeated three times resulting in drilling a total of 81 holes and the reported results represent the average of the three drilling tests. For each coating, each set of corresponding nine holes was drilled with a fresh drill to minimise any impact arising from drill wear [25]. A summary of the drilling parameters used in this study is provided in Table 3.

Table 3 Drilling parameters used in the study showing the structure of the design of experiments
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2.4 Measurement of hole geometrical tolerances

The hole geometrical tolerances (hole size, circularity, perpendicularity and cylindricity) were measured using a Sheffield Cordax-D8 Discovery III Coordinate Measurement Machine (CMM) [2,3,4]. The workpiece was clamped on the CMM table as shown in Fig. 3, and the measurements were taken at two locations at the top and the bottom of each hole (1 mm and 6 mm, respectively). A Leitz stylus equipped with a 2-mm ruby probe was employed to scan the borehole with an average of 30 contacts per mm at a scanning speed of 0.5 mm/s using an LSP-X1s probe head. The machine accuracy factory specification is 4.9 + 5 L/1000 μm; the maximum uncertainty reported in the calibration report of the machine was 0.97 μm. A Mitutoyo Crysta-Apex S776 CMM was used to measure a set of drills sizes before drilling. The MPEE (maximum permissible error) of the CMM used to measure the sizes of the drills was 1.7 + 3 L/1000, while the MPEE of the CMM is used to measure hole tolerances was 4.9 + 5 L/1000 μm. MPEE follows the form of MPEE = A + L/K, where A is a constant (μm) specified by the manufacturer, K is a dimensionless constant specified by the manufacturer and L is the measured length (mm) in this case is 6 mm. Therefore, the accuracies at which the CMM measures the distance between any two points up to a distance of 6 mm for the two CMM machines used in this study were 0.0349 μm and 0.0197 μm. The drill diameters for TiN-, TiAlN- and AlTiN/TiAlN-coated tools were found to be 6.0146 mm, 5.994 mm and 5.9965 mm, respectively.

Fig. 3
figure 3

Measurement of hole geometrical tolerances

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2.5 Scanning electron microscopy

SEM was employed to inspect the machined hole surface for any drilling-induced damage. Each hole was cut in half and was then subjected to an ultrasonic bath to eliminate any unwanted debris from the borehole surface as shown in Fig. 4a. The sectioned holes were then sputter-coated before the inspection with the SEM (Fig. 4b). They were then secured on a platform using a copper double-sided tape before inspecting them as shown with Fig. 4 c and d. Magnifications (× 35–500) and 10 keV voltage were applied to visualise the borehole walls as necessary.

Fig. 4
figure 4

Sample preparation for SEM analysis. a Ultrasonic bath with acetone. b Sputter coating. c Mounting base. d Interlock chamber. e Carl Zeiss 1540 XB SEM

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3 Results and discussion

3.1 Thrust force analysis

Figure 5 shows the average thrust force from the three runs for each tool coating under different cutting parameters. It is noticeable that the TiAlN drills consistently produced the largest thrust force under all cutting parameters, followed by the TiN and AlTiN/TiAlN drills, respectively. It is also observed from this figure that increasing the feed rate increased the thrust force, while increasing the spindle speed decreased it, which is in agreement with previous studies on the drilling of GLARE® laminates [3, 6]. The thrust force recorded using TiAlN drills was between 9.87 and 21.86% higher than that recorded using TiN tools under the same cutting parameters. Similarly, the thrust force recorded using TiAlN drills was between 49.26 and 62.27% higher than that recorded using AlTiN/TiAlN tools.

Fig. 5
figure 5

Thrust force results for different types of drill coating

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A previous study also reported that the cutting forces generated using TiN-coated drills were lower than those generated by TiAlN-coated drills [52]. It could be speculated that the AlTiN/TiAlN coating provided a better self-lubricating effect due to its multilayer coating structure, but this needs to be confirmed in a future study. AlTiN/TiAlN tools combine two coatings in a micro-layered structure that is harder and more wear resistant than the two alone. As reported in Table 2, the TiAlN coating has an oxidation temperature of approximately 800 °C, a nano-hardness of 3300 (HV 0.05) and a friction coefficient of 0.5. The AlTiN/TiAlN coating, on the other hand, has an oxidation temperature of approximately 900 °C with a 0.6 friction coefficient. Although such coating’s parameters are fairly close to those of TiAlN’s, AlTiN/TiAlN still has the highest thermal stability between the two coatings thus providing exceptional oxidation resistance and extreme hardness when used in multilayer coating system and performing better in dry drilling.

The ANOVA analysis shown in Table 4 reveals that the cutting parameters and tool coating contributed somewhat equally towards the thrust force with each contributing around 30%. In addition, their linear interaction had some minor impact on the thrust force. This could indicate that a proper combination of cutting parameters and tool coating would result in reduced thrust force and drilling-induced damage in the glass fibre layers of the laminate.

Table 4 ANOVA results for thrust force
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3.2 Hole size analysis

Figure 6 shows the average hole size obtained when drilling the GLARE® sample under different drilling parameters and drill coatings for both the top and bottom regions of the hole. Overall, the hole size at the top ranged between 6.010 and 6.028 mm, while this range decreased between 5.98 and 6.014 mm at the bottom. Similar results were reported in previous studies in drilling GLARE® and Al2024 alloy [3, 22, 25, 53]. Oversized holes were produced at the top regardless of the type of drill coating or drilling parameters used. It should be noted that all drills were produced with a tolerance range of +4 μm to +16 μm. In addition, there was a significant variation in the drill diameters as shown previously in Sect. 2.4. For this reason, it is argued that no firm conclusion may be made from the direct observation of Fig. 6 in terms of which drill coating resulted in the largest hole oversize. Instead, one can use data in Fig. 6 to analyse the relative reduction in the hole diameter between the top and the bottom region for a given type of coating. The average reduction in hole size between the top and the bottom region was 15.86 μm, 17.78 μm and 18.19 μm for TiN-, TiAlN- and AlTiN/TiAlN-coated drills, respectively. Hole shrinkage is common when drilling composites due to the relaxation of the lamina [22, 54]. Therefore, the lower coefficient of friction of TiN-coated drills compared to the other two coatings might have caused a lower temperature at the cutting zone leading to reduced hole shrinkage with depth. If the actual drill size for each coating is considered when comparing the measured hole sizes obtained by the three coatings, then TiN-coated drills produced holes with least deviation from the drill original size followed by AlTiN/TiAlN and TiAlN coatings, respectively. However, this requires further investigation which will be carried out in a future study.

Fig. 6
figure 6

Hole size for different types of coating at top and bottom location

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The largest hole deviation from the nominal value on the top region took place when drilling at the highest spindle speed, i.e. n=6000 rpm, with the lowest feed rate, i.e. f=300 mm/min. This may be due to increased drill vibration at higher spindle speed values [55]. On the contrary, the smallest hole deviation at the top occurred when drilling at the lowest spindle speed, i.e. n=3000 rpm, and with the highest feed rate, f=600 mm/min, except for the drills with TiN coating where the smallest deviation was achieved at n=4500 rpm and f=450 mm/min. On the bottom region, the largest hole deviation from the nominal value occurred for a different set of drilling conditions for each of the drill coating. This may indicate that the impact of drill coating on hole size becomes more significant with the increase in hole depth.

From the data presented in Fig. 6, it can also be said that, generally, the hole size on the top increased with the increase of spindle speed and decreased on the bottom surface with the increase of the spindle speed when drilling at constant feed rate. Thus, different phenomena, related to the increase in spindle speed, occur at the entrance and exit of the holes. For the bottom region, the continuous rubbing of the drill and evacuated hot chips increase the temperature at the cutting zone leading to thermal shrinkage [56]. This does not happen at the top surface as the more dominant influence in this region is the drill vibration. Finally, it can also be noted that drilling at the following combinations of feed rates and spindle speeds of 300/3000, 450/4500 and 600/6000 ((mm/min)/rpm) showed that hole size at top tended to increase, while at the bottom, it tended to decrease with the reduction of drilling time.

The ANOVA analysis provided in Table 5 shows that the parameters drill coating and spindle speed had a significant impact on hole size on the top region with 52.4% and 15.0% contribution, respectively. For the bottom region, the ANOVA results imply that all three input parameters had a significant impact on hole size. However, the dominant contribution came from the parameter drill coating with 42.4%, thus confirming an earlier comment made when discussing the results of Fig. 6.

Table 5 ANOVA results for hole size on the top and bottom regions
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Ideally, holes drilled in aeronautical structures should be close to their required nominal diameter for optimum rivet joint performance [3]. Having an oversized or undersized hole would imply additional post-machining operations such as reaming process to achieve desired hole size. In the current study, the variation of hole size did not exceed the interval [− 16.0 μm + 26.2 μm] which is within the upper range of H9 (0 to + 30 μm) hole tolerance recommended by aerospace manufacturers [3, 57]. Besides, industrial reports of drill manufacturers indicate that hole tolerances in aeronautical materials including GLARE® could vary between ± 20 and ± 40 μm [3, 58]. This means that hole sizes obtained in this study are within the allowable range and would only require a reaming process to enlarge the undersized holes.

3.3 Hole circularity analysis

Figure 7 shows the average hole circularity in the GLARE® sample under different drilling parameters and drill coatings at the top and bottom regions. Overall, the average hole circularity on the top was better as it ranged between 3.08 and 10.6 μm, while at the bottom, it was between 13.3 and 28.8 μm. The results are in line with circularity data reported in previous studies on drilling same grade and thickness of GLARE® laminates, particularly the fact that hole circularity is likely to worsen with depth due to the gradual increase in thermal load while cutting through the material and the non-isotropic nature of the coefficient of thermal expansion of the glass fibre layers [3, 22, 25]. However, this observation disagrees with previous studies on drilling metals which report that the deviation from circularity at the hole inlet is worse than that at the hole outlet due to the dynamic instability of the drill during its initial contact with the workpiece. The better values observed at the outlet in holes drilled in metallic materials were reportedly due to self-pointing guidance action of the hole to the drill with increasing depth [59,60,61]. Other studies on drilling aluminium alloys reported that there are highly non-linear variations in hole circularity throughout the depth of the hole due to the presence of other factors such as fixture/machine drill vibration/drill deflections and damping characteristics [25, 53]. In addition, there was a significant variation in the drill diameters as shown previously in Sect. 2.4. For this reason, it is argued that no firm conclusion may be made from the direct observation of Fig. 7 in terms of which drill coating resulted in the least hole circularity. Instead, one can use data in Fig. 7 to analyse the relative difference in the hole circularity between the top and the bottom region for a given type of coating. The variation in repetitions was significant at the bottom which could be due to the weakening of the hole structure with the reduction in material thickness to be removed from the hole as the drill progresses towards the exit side of the hole. It is also speculated that there might be some other factors affecting those holes tolerances such as the location of the hole and the clamping technique. Such factors will be considered for investigation in future studies.

Fig. 7
figure 7

Hole circularity for different types of coating at top and bottom

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When considering all the experimental data, the worst hole circularity on the top region occurred when drilling at n=4500 rpm, f=450 mm/min using TiN coating, while the best hole circularity was achieved when drilling at n=4500 rpm, f=600 mm/min using TiAlN coating. Generally, for TiN-coated drills, hole circularity at the top region deteriorated with the increase of the spindle speed. For both TiAlN- and AlTiN/TiAlN-coated drills, hole circularity on the top region became better with the increase in spindle speed except for the lowest feed rate value considered.

Regarding the circularity of holes on the bottom region, for TiN coating, it tended to worsen with the increase of the spindle speed at all feed rates. For AlTiN/TiAlN coating, the hole circularity at the bottom tended to worsen with the increase of the feed rate when drilling at n= 3000 rpm, while it tended to worsen then become better with the increase of the feed rate when drilling at spindle speeds of n= 4500 and n= 6000 rpm. Drilling at feed rate/spindle speed ratios of 0.1 (0.1 mm/rev) showed that hole circularity at the top tended to be worst when drilling at of n= 4500 and f= 450 mm/min. However, at the bottom, the hole circularity tended to worsen with the reduction of drilling time which indicates that drilling at faster rates will be on the expense of worsening hole circularity.

The ANOVA analysis provided in Table 6 shows that only the drill coating had a major impact on hole circularity for the top surface while it was only the spindle speed which was identified as the significant contributor for the bottom surface, with 13.79% and 25.22%, respectively. This is somewhat different from previous studies which showed that the spindle speed and the feed rate had a significant effect on hole circularity on both surfaces with a higher contribution by the spindle speed [2, 6]. This is because the current study also considered drill coating as one of the input parameters. Also, this may be due to the presence of non-linear trend in the model, as indicated by the large error present in the model, i.e. from 36.43 to 58.04%.

Table 6 ANOVA results for hole circularity
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3.4 Hole cylindricity and perpendicularity

Figure 8 shows the average values of hole cylindricity and perpendicularity under different drilling parameters for the three types of drill coatings used. The average hole cylindricity ranged between 16.5 and 45.2 μm as shown in Fig. 8a. The worse hole cylindricity occurred using TiN coating when drilling at a spindle speed of n= 3000 rpm and a feed rate of f= 450 mm/min. The best hole cylindricity occurred using TiN coating when drilling at a spindle speed of n= 3000 rpm and a feed rate of f= 300 mm/min. Hole cylindricity tended to worsen with the increase of the feed rate when drilling at spindle speeds of n= 4500 and 6000 rpm using TiN-coated drills. For TiAlN- and AlTiN/TiAlN-coated drills, hole cylindricity tended to deteriorate and then improve with the increase of feed rate at spindle speeds of n= 4500 and 6000 rpm.

Fig. 8
figure 8

Hole. a Cylindricity. b Perpendicularity

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Hole perpendicularity became worse with the increase of the feed rate when drilling at a spindle speed of n=3000 rpm for TiN and AlTiN/TiAlN coatings. A similar trend is observed with the increase of the feed rate when drilling at a spindle speed of n=6000 rpm for TiAlN and AlTiN/TiAlN coatings, which could be due to the increase in feed force and vibrations with the increase of the feed rate [4]. The average hole perpendicularity ranged from 0.015 to 0.089 mm; the highest and lowest perpendicularity was found to occur when drilling using AlTiN/TiAlN coating at n= 6000 rpm and f= 300 mm/min and n= 3000 rpm and f= 600 mm/min, respectively.

It is also worth to mention that the poor repeatability in hole perpendicularity data suggest that other input factors/parameters might have had an influence on hole perpendicularity which were not investigated in the current study [4]. One of the suggested factors is the location of the hole within the workpiece and the clamping setup of the laminate inside the CNC machine which will be investigated in a future study. In addition, the large errors in hole cylindricity and perpendicularity are common when measured for drilled holes in GLARE laminates as reported by previous studies [2, 3].

The R2 (coefficient of determination) obtained from ANOVA analysis is low as shown in Table 7. Thus, the ANOVA analysis might not be suitable here to judge the impact of drilling parameters and drill coating on hole perpendicularity. ANOVA results show that the drill coating was the only contributing parameter on hole cylindricity, while the spindle speed was the only contributing factor on hole perpendicularity.

Table 7 ANOVA results for hole cylindricity and Perpendicularity
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3.5 Scanning electron microscopy analysis

SEM images reported with Figs. 9 and 10 reveal that minor metal chipping, interlayer burrs, broken fibres and deformation marks on the surface of aluminium sheets can be observed due to contact with the drill. The types of damage resemble those observed in previously reported studies on drilling GLARE® under dry conditions [2, 3, 50]. The SEM inspection showed that the damage on the hole surface increased with hole depth. Smearing (plastic deformation) and other forms of deformation marks were observed on the surfaces of aluminium sheets which seemed to occur more frequently at higher feed rates which is in line with observations reported in a previous study [50]. Those deformation marks shown in Figs. 9 and 10 may be due to two distinct contact scenarios. The first type of deformation marks is speculated to be caused by the rubbing action of the metallic chips colliding with the hole walls while they are leaving the workpiece as shown in Fig. 9. In this case, the marks are helical in shape which resembles the profile of the flute of the twist drill and is of several millimetres in length. This type of deformation marks could be also caused by the fierce rubbing on the hole walls due to vibrations and loss of drill eccentricity while it cuts through the material.

Fig. 9
figure 9

SEM image of a borehole wall at f = 300 mm/min and n = 3000 rpm using a TiN-coated drill

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Fig. 10
figure 10

SEM image of a borehole wall at af = 300 mm/min and n = 4500 rpm using a AlTiN/TiAlN-coated drill b at f = 300 mm/min and n = 6000 rpm for TiAlN-coated drill

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The second type of deformation marks is speculated to be caused by broken fibres which are trapped between the drill and borehole surface, causing them to be stressed onto the aluminium sheets and plastically deform their outer surface. In this case, the deformation marks appear to be parallel to the fibres as shown in Fig. 10a. Multiple instances of this type of marks were observed on the aluminium sheet. Some of the aluminium chips and broken glass fibres are not evacuated through the drill flutes and are eventually stressed into the edges of the aluminium sheets or into the voids formed in the glass fibre layers due to fibre pull-outs [50] as shown in Fig. 10b.

Interlayer burrs were observed around the borehole and through its thickness which might have caused further erosion in the glass fibre layers. Besides, the erosion in glass fibre layers might have been caused by the evacuated metallic chips [3, 50]. Powdery glass fibre chips and broken metallic chips were stressed into the laminate layers forming what is known as waste material as shown in Fig. 11a. The waste material—whether metallic or composite—is caused by the subsequent removal and adherent of laminate constituent materials debris during the drilling process [3]. The damage in borehole surface increased with the increase of both cutting parameters similar to previously reported studies [3, 50]. The results also showed that the edge of the last aluminium sheet is likely to be more deteriorated than the first aluminium sheet as reported in Fig. 11b. This could be attributed to the increased contact area between the drill and workpiece leading to higher frictional heat and plastic deformation. Therefore, burr formations tend to be higher at the bottom of the laminate than at the top as reported in previous literature [2, 3, 50]. The burrs formed at the entry of the hole were uniform around its edge, while burrs formed at the exit had an irregular appearance and heights.

Fig. 11
figure 11

SEM image of a borehole wall at af = 300 mm/min and n = 3000 rpm using a AlTiN/TiAlN-coated drill. b The upper and lower aluminium sheets edges at f = 300 mm/min and n = 3000 rpm using a TiN-coated drill. cf = 300 mm/min and n = 3000 rpm using a AlTiN/TiAlN-coated drill d showing fibres with different uncut lengths at f = 450 mm/min and n = 3000 rpm using a TiN-coated drill

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Delamination (type I) was present in the machined holes which takes place due to the progression of the drill into the laminate causing the peeled layers to bend either permanently due to plastic deformation or temporarily like a cantilever beam [3, 62]. A type II fibre buckling is seen in Fig. 11c due to compressive loading acting along their direction. Some chunks of fibres end with varying lengths were pointing out due to cutting by fracture as shown in Fig. 11d [3, 50, 62].

The SEM images did not show any signs of ply separation in composite layers or de-bonding between the laminate constituents. It is speculated that the sandwiched glass fibre layers between two metallic sheets from the top and bottom mimic the effect of support plates placed on the top or the bottom of a composite sample to reduce delamination, especially when drilling at higher feed rates [3, 63].

4 Conclusions

The machinability of GLARE® fibre metal laminates was investigated using twist drills to analyse the hole size, circularity, cylindricity and perpendicularity. The objective was to study the influence of drilling and three types of drill coatings (TiAlN, TiN and AlTiN/TiAlN) on the stated hole quality parameters. The influence of drill coatings had been previously studied in different GLARE® grades to evaluate the hole quality, but no study was previously carried out using the same drill geometry. The influence of drill coatings is a crucial factor in drilling aeronautical multimaterials made from composites and metals since they can prolong drill life and improve surface finish. However, only a handful number of researches had been conducted on drilling of GLARE® laminates in general and the influence of drill coating in particular. The following conclusions can be drawn from the study:

  • The thrust force generated using AlTiN/TiAlN multilayer-coated drills was the lowest among the three coatings tested, followed by TiN and TiAlN coatings, respectively.

  • The average reduction in hole size between the top and the bottom region was 15.86 μm, 17.78 μm and 18.19 μm for TiN-, TiAlN- and AlTiN/TiAlN-coated drills, respectively.

  • Hole circularity at the bottom was worse than that at the top regardless of drill coating or drilling parameters. TiN-coated drills produced worst hole circularity at the top among the three coatings.

  • Hole cylindricity was worst when using AlTiN/TiAlN- and TiN-coated drills; whole hole perpendicularity worsened with the increase of the feed rate.

  • The ANOVA results showed that the spindle speed and drill coating had a significant influence on hole size and circularity, while drill coating was the only contributing parameter on hole cylindricity, and spindle speed was the only contributing factor on hole perpendicularity.

  • SEM inspection showed that the damage generated on the walls of the hole are strongly influenced by the drilling parameters but not the drill coating. Fibre buckling, smearing, interlayer burr formation and deformation marks due to evacuated metallic chips and broken glass fibres were observed from the SEM images.