Abstract

Composite materials have become fundamental in modern aircraft due to their lightweight properties and high strength-to-weight ratio. This research evaluates the structural performance of carbon fiber aircraft wings under realistic flight loads.

Objectives
Evaluate stress concentration.
Analyze structural deformation.
Compare composite and aluminum structures.
Estimate fatigue life.
Methodology

The aircraft wing was modeled in CATIA and imported into ANSYS Mechanical. Multiple loading conditions including lift, fuel weight, and gust loads were applied. Static structural and fatigue analyses were conducted.

Results

Composite wings showed approximately 28% lower structural weight while maintaining equivalent structural strength. Maximum deformation remained within certification limits, and fatigue life improved significantly compared to conventional aluminum structures.

Findings
Carbon fiber reduces structural weight.
Higher fatigue resistance.
Improved fuel efficiency due to weight reduction.
Better vibration damping characteristics.
Conclusion

Composite wing structures provide superior structural efficiency while reducing aircraft operating costs, making them the preferred choice for next-generation commercial aircraft.