1 Delamination of Glass Fiber Reinforced Epoxy Plastic (GFRP) Composite Laminates of Different Orientation 1 Mayuresh Bhosale, 2 Rajvardhan Mane, 3,* Lokavarapu Bhaskara Rao, 1,2,3 School of Mechanical and Building Sciences, VIT Chennai, Vandalur-Kelambakkam Road, Chennai-600127, Tamil Nadu, 1 E-mail:[email protected], 2 E-mail: [email protected], 3 E-mail:[email protected]( * Address for correspondence) Abstract Objectives: Our main objective is to study comparison of delamination factor of [0/90/0] as shown in Figure.4, [0/60/0] as shown in Figure.5 and [0/45/0] as shown in Figure.6 oriented GFRP composite laminates. Finding includes-Variation of delamination factor with respect to process parameters,Variation of delamination factor with respect to drilling geometry,Variation of delamination factor with respect to fiber orientation. Methods: To have functional outputs from composite, machining is very important. Out of various machining operations drilling is one of the most important operations. Findings: This paper correlate delamination of [0/90/0], [0/60/0] and [0/45/0] GFRP composite with drilling process parameters viz cutting speed and feed rate respectively. Improvements/Applications: This paper gives a clear view of different behaviours of GFRP plates with different orientations. Keywords : GFRP, Delamination, Machining, Process Parameters Introduction: Composites are proved to be the effective constructive materials for present day industry due to their excellent properties. The major advantages in terms of mechanical properties such as high stiffness-to-weight and strength-to-weight ratios of composite materials led them to replace conventional materials like metals in broad range of applications such as aircraft, sea vehicles, automobile, aerospace and defence. Producing error free précised holes is desired to ensure high joint strength during assembling of materials by riveting or bolting. Damages like fiber push out as shown in Figure 1. fiber peel up as shown in Figure 2 and delamination as shown in Figure 3. are induced by drilling operation which severely affect fatigue strength so reduce performance of composite for long term needs. Out of above mentioned damages delamination induced due to drilling is main area of concern in machining. In aircraft industries 60-65% parts of composite laminates are rejected due to delamination induced by drilling. The thrust force is primary reason of delamination. The composites consists of two primary phases: matrix and reinforcement Matrix- Matrix is important and first phase in manufacturing of composite. It enhances properties of material. Reinforcement: It is stronger, stiffer and harder than matrix. It modifies thermal and wear resistance and also thermal conductivity. Extrusion, rolling, forging and drilling are done in this phase. Single filament fiber such as carbon fiber, glass fiber and silicon fiber are used in continuous reinforcement. Physical identification is combination of both phases. Due to increase in demand from industries for better materials in terms of mechanical properties as compared to metals but they should be light in weight. For this reason composite materials are developed which are light in weight but with enhanced mechanical properties. But at the same time it was also noticed that by using traditional machining processes machining become more difficult. Those processes can affect composite materials and induces problems like fiber pullout,
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Delamination of Glass Fiber Reinforced Epoxy Plastic (GFRP)
Composite Laminates of Different Orientation
1Mayuresh Bhosale,
2Rajvardhan Mane,
3,*Lokavarapu Bhaskara Rao,
1,2,3 School of Mechanical and Building Sciences, VIT Chennai, Vandalur-Kelambakkam Road,