“…The same behavior can be seen in Fig. 14 b, c for AG and GA specimens, respectively, where specimens with significant delamination damage tends to weaken the structures by concentrating too much stress at the hole edge and increasing the risk of rapid matrix cracking 38 . Figure 14 Relation between bearing strength and delamination damage for; ( a ) NG specimen, ( b ) AG specimen, and ( c ) GA specimen.…”
The current study attempted to evaluate the impact of drilling parameters and delamination on the bearing strength of both neat GFRP (NG) and hybrid GFRP/aluminum (Al)-wire mesh with two various configurations, first with Al-mesh in the outer surface of specimen (AG) and the other with Al-mesh in the core of specimen (GA). Drilling procedure is carried out using $$\varnothing$$
∅
6 mm carbide twist drill with three different tip angles (90°, 120° and 135°), as well as Three different speeds and feeds (1000, 2000, and 3000 rpm) and (20, 40, and 60 mm/min), respectively. Taguchi and ANOVA analyses are used to analyze the influence of processing parameters. The findings showed that AG specimen experienced the least delamination damage. The maximum bearing strength refers to NG specimen, which is 9.6% and 8.7% more than AG and GA specimens, respectively. Drill point angle has the major effect on bearing strength for both AG and GA specimens, while for NG feed rate is of the major effect. The developed regression model displayed a high level of fitness with an average prediction error of less than 3%.
“…The same behavior can be seen in Fig. 14 b, c for AG and GA specimens, respectively, where specimens with significant delamination damage tends to weaken the structures by concentrating too much stress at the hole edge and increasing the risk of rapid matrix cracking 38 . Figure 14 Relation between bearing strength and delamination damage for; ( a ) NG specimen, ( b ) AG specimen, and ( c ) GA specimen.…”
The current study attempted to evaluate the impact of drilling parameters and delamination on the bearing strength of both neat GFRP (NG) and hybrid GFRP/aluminum (Al)-wire mesh with two various configurations, first with Al-mesh in the outer surface of specimen (AG) and the other with Al-mesh in the core of specimen (GA). Drilling procedure is carried out using $$\varnothing$$
∅
6 mm carbide twist drill with three different tip angles (90°, 120° and 135°), as well as Three different speeds and feeds (1000, 2000, and 3000 rpm) and (20, 40, and 60 mm/min), respectively. Taguchi and ANOVA analyses are used to analyze the influence of processing parameters. The findings showed that AG specimen experienced the least delamination damage. The maximum bearing strength refers to NG specimen, which is 9.6% and 8.7% more than AG and GA specimens, respectively. Drill point angle has the major effect on bearing strength for both AG and GA specimens, while for NG feed rate is of the major effect. The developed regression model displayed a high level of fitness with an average prediction error of less than 3%.
“…often represent the most suitable choice also taking into account their capability to sustain higher loads as well as their easy of assembly. In order to optimize the use of mechanical connections in composite or hybrid structures, the exploitation of the bearing behavior of pinned composite laminates has been investigated in previous papers concerning polymeric composites reinforced mainly with synthetic fibers such as glass [5][6][7][8][9][10][11] and carbon [12][13][14][15]. Furthermore, the influence of the geometrical configuration of pin-loaded composites on their bearing performances and failure modes 4 was recently investigated also for flax and glass-flax reinforced hybrid structures in our recent papers [16,17].…”
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“…But Abdullah et al. 31 found through experimental investigations that the process of producing hole could affect the strength of the composite laminate. While comparing composite plates with punched and drilled holes, it was observed that failure initiated first from hole-edges in plates with punched holes.…”
Composite panels are widely used as structural members due to their high strength-to-weight ratio. In order to reduce further weight, cutouts or notches are introduced in these members. These cutouts also serve utility requirements such as man-holes for purpose of service as well as for passing electric or fuel lines. An aircraft wing rib is a typical example of such a composite panel. Even while composites with holes or cutouts provide great savings in weight compared to metallic structures, the presence of holes itself leads to strength reduction. The reduction in strength is due to the concentration of stress around the vicinity of the hole while the structure is under loading. Different-sized and shaped holes/cut-outs are used in composites structural members, which may serve for different purposes. They, in turn, introduce their own versions of stress concentrations effects in such members leading to weakening of the structure. The stress concentration effect in fibre composites also depends on other factors like fibre orientation, fibre material, matrix material, etc. Loading can also influence stress concentration. This review pursues vast research done in this area and attempts to compare and summarise the diverse findings for designers to obtain a comprehensive concept on stress concentration factor as an effective tool for composite structure design.
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