Višeciljna optimizacija parametara procesa bušenja metalnog laminata ojačanog vlaknima korišćenjem hibridnog GRA-PCA pristupa

Ergün Ekici,Ali Motorcu,Gültekin Uzun

doi:10.5937/fme2102356e

Abstract

This study investigated the effects of drilling parameters and cutting tool coating conditions on the thrust force, surface roughness, and delamination factor in the drilling of fiber-reinforced carbon reinforced aluminum laminate (CARALL) composite, a commercial type of fibermetal laminate. Gray relational analysis (GRA) was used as a multi-objective optimization method to determine optimum processing parameters and principal component analysis (PCA) was used to determine the weights. According to the findings of this experimental study, the most effective control factors for the thrust force, surface roughnes, and delamination factor were the feed rate, tool coating condition-cutting speed interaction, and tool coating condition, with 93.87%, 66.504%, and 29.137% contribution rates, respectively. From the results of the GRA-PCA analysis, the optimum levels of the control factors were determined as 110 m/min cutting speed, 0.1 mm/rev feed rate, and the uncoated tool.

Highlights

In recent years, research interest in the field of engineering applications has increasingly shifted from traditional material to composite material (CM) applications in various engineering industries [1, 2]
Machinability analyses of the carbon reinforced aluminum laminate (CARALL) composites were performed in terms of drilling properties such as the thrust force, surface roughness, and hole exit delamination factor
The probability test plots drawn at 95% confidence interval (CI) for the thrust force, surface roughness and delamination factor reveal that the data points do not exceed the 95% confidence limit and are approximately aligned with the midline

Summary

Introduction

Research interest in the field of engineering applications has increasingly shifted from traditional material to composite material (CM) applications in various engineering industries [1, 2]. Fibermetal laminate (FML) is a composite material system consisting of varying layers of thin metal sheets and composite prepregs These FMLs have seen wide application for structural components in the aerospace and defense industries due to their unique properties that combine fatigue and impact resistance with relatively low density, flame (high burning) and corrosion resistance [3,4,5]. In CARALL, which was developed against ARALL's low compression resistance, carbon fibers are laid between aluminum plates Because of these features of CARALL, aircraft parts can be produced that have the same strength but are lighter than metals [7]. The number of holes required can range from 300,000 holes in a jet fighter to 1.5-3 million holes in a commercial aircraft [8] Throughout their service life, FRP composites lose strength due to delamination [9].

Methods

Results

Conclusion