Design of a Wing Structure for a Single Turboprop Normal Category Aircraft

Abstract

This paper presents the wing design and structural analysis of a single turboprop aircraft with a maximum takeoff weight of 2,200 lbs. The wing structure of the aircraft is a conventional mid-wing configuration of a twisting trapezoidal planform with an aspect ratio of 0.6. The analysis involved determining the loads acting on the wing structure. That is the aircraft’s flight envelope and the wing’s critical loading condition according to Title 14 Code of Federal Regulations Part 23 (14 CFR Part 23). The wing CAD model, composed of the aircraft wing components of the spar, ribs, and skins including its layout, was developed, and analyzed based on available 7075T6 Aluminum sheets using the SolidWorks software. The results for the wing’s critical loading condition showed that the wing tip displacement was less than 5% of the half-wingspan with a margin of safety of 0.5 and mass of 117.97 lbs which was less than the expected mass of 132 lbs.

Keywords

• Wing structural design
• Finite element analysis
• Normal category aircraft
• 14 CFR part 23
• Single turboprop aircraft

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