Abstract :

Aircraft Fuselage Structures Are Among The Most Critical Load-bearing Components In Aerospace Engineering, As They Must Safely Withstand Internal Pressurization, Aerodynamic Forces, Vibration, And Repeated Cyclic Loading Throughout Service Life. Traditionally, Aircraft Fuselages Were Manufactured Using Conventional Metallic Materials, Particularly Aluminum Alloys, Because Of Their Favourable Strength-to-weight Ratio, Ease Of Fabrication, And Widespread Industrial Acceptance. Over Time, However, Increasing Demands For Lightweight Structures, Improved Fatigue Resistance, And Reduced Maintenance Have Driven The Aerospace Industry Toward Advanced Composite And Hybrid Materials. Despite The Longstanding Use Of Conventional Alloys, Fuselage Structures Remain Highly Susceptible To Fatigue Damage, Stress Concentration, And Deformation Under Dynamic Operating Conditions, Which Can Reduce Structural Life And Compromise Safety. Traditional Material Systems Such As Aluminum Alloy Fuselages Often Exhibit Higher Cyclic Damage Accumulation, Greater Stress Levels, And Lower Long-term Durability Under Fluctuating Loads, Making Them Less Suitable For Nextgeneration Aircraft Applications. Hence, There Is A Growing Need To Identify And Evaluate Alternative Fuselage Materials That Offer Improved Structural Efficiency, Fatigue Performance, And Dynamic Stability. This Study Presents A Comparative Finite Element Analysis Of An Aircraft Fuselage Structure Using Three Different Materials: Aluminum Alloy 7075, Carbon Fiber, And GLARE (Glass Laminate Aluminum Reinforced Epoxy). A Three-dimensional Fuselage Model Was Developed In SolidWorks And Imported Into ANSYS For Detailed Finite Element Evaluation. Static, Fatigue, And Transient Dynamic Analyses Were Carried Out To Assess Deformation, Equivalent Stress, Hoop Stress, Longitudinal Stress, Strain, Fatigue Damage, And Safety Factor Under Varying Operating Conditions. The Proposed System Aims To Identify The Most Suitable Material For Aircraft Fuselage Applications By Comparing Structural Behavior Across All Three Materials. Results Demonstrate That GLARE Exhibits Lower Deformation, Reduced Stress Concentration, Lower Fatigue Damage, And Higher Safety Factor Than Aluminum Alloy 7075 And Carbon Fiber. The Study Establishes GLARE As A Superior Material For Fuselage Applications, Offering Enhanced Structural Reliability, Longer Service Life, And Improved Performance For Modern Aerospace Structures.

Published:

21-6-2026

Issue:

Vol. 26 No. 6 (2026)

Page Nos:

1940-1950

Section:

Articles

License:

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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