Wing Structure Design for YF-27 Shrike Homeland Defense Interceptor

Abstract

This project focuses on designing the wing structure of an interceptor aircraft to withstand sustained supersonic flight and provide sufficient fuel storage for extended operations. The aircraft and structure were designed according to the AIAA Homeland Defense Interceptor request for proposal (RFP). Sizing of structural components was performed utilizing hand calculations and an idealized shear box approach focused on maximum aircraft limit loads. Based on these preliminary calculations, different wing structural components such as spars, ribs, stringers, and attachment points were designed using computer aided design (CAD) software. Finite element analysis was used to verify results and structural integrity of these components. Additionally, critical failure points were further analyzed using crack propagation theory to prevent structural failure concerns. The wing structure withstands limit loads of +7/-3 g while remaining lightweight. Components can operate without failure for 2,000 hours between inspections. This project demonstrates that structural design of high-speed interceptor is feasible while minimizing material and manufacturing cost and weight