Assessment on Selection of Appropriate Materials for Fuselage of an Aircraft

Abstract

Considering composites, after treatments like heat processing, and the creation of composite substances in addition to pure components, the range of engineering components is steadily expanding. It is crucial to choose the best material from such a huge material source for each unique part that needs to be made. The picking of acceptable composition for the fuselage, A critical aircraft component, its importance lies in its lightweight and cost-effective nature, along with its thermal and mechanical characteristics. The criteria and options in this study, which attempts to choose components for the fuselage of a commercial airplane, have first been established following expert viewpoints. During the research, the COPRAS technique was employed to evaluate various materials, considering factors such as "density, tensile strength, shear strength, and cost." According to the ranking of options using the COPRAS approach, CFRP is the best option, followed by GFRP, AISI 4130, Al 2024-T3, Al 5052-H32, Al 6061-T6, Al 7075-T6, and AZ31B. In comparison to other chosen materials, CFRP recorded the highest importance with the tensile strength of 1240 MPa, shear strength of 740 MPa, and elastic modulus of 145 Gpa, whereas AZ318 recorded the lowest relevance with the tensile strength of 290 MPa, shear strength of 130 MPa, and elastic modulus of 45 Gpa. The order is summarized as " CFRP> GFRP>AISI 4130> Al 7075-T6> Al 2024-T3> Al 6061-T6> Al 5052-H32> AZ31B ".As per the result of the COPRAS approach, the three choices that were most suited for the fuselage were "CFRP, GFRP, and AISI 4130", with "AZ318 being the least appropriate.