Optimal Material Selection for Aircraft Components using The COPRAS Method

Abstract

Abstract

Material selection for aircraft components is a fundamental aspect of aerospace engineering because it directly influences structural performance, operational safety, durability, and fuel efficiency. Aircraft parts are subjected to demanding service conditions, including high mechanical loads, temperature variations, and corrosive environments. Therefore, selecting an appropriate material requires balancing multiple properties such as low density, high stiffness, adequate elongation, and elevated temperature resistance. The present study investigates the material selection problem for aircraft parts by evaluating five candidate materials: aluminum, Aluminum 7075-T6, maraging steel, steel, and titanium. A structured decision-making methodology is employed to compare these alternatives based on key engineering criteria, namely density (kg/m³), elastic modulus (GPa), elongation (%), and temperature limit (°C). The evaluation process integrates material property analysis with multi-criteria assessment techniques to identify the most suitable material for aerospace applications. The results indicate that Aluminum 7075-T6 achieves the highest overall ranking due to its favorable combination of lightweight characteristics, mechanical strength, and performance under operational conditions. In contrast, conventional aluminum receives the lowest ranking among the evaluated alternatives because of its comparatively lower performance across the selected criteria. The findings demonstrate the importance of systematic material evaluation in optimizing aircraft design and performance. Effective material selection contributes to enhanced reliability, reduced structural weight, improved fuel economy, and lower maintenance requirements, thereby supporting the development of safer and more sustainable aerospace systems.