Is this project an undergraduate, graduate, or faculty project?
Undergraduate
Project Type
group
Campus
Daytona Beach
Authors' Class Standing
Michael Roden, Senior, RODENM@my.erau.edu Karl Pongase, Senior, PONGASEK@my.erau.edu Sungje Park, Senior, PARKS48@my.erau.edu Adrian Fanjoy, Senior, FANJOYA1@my.erau.edu Alexander Antonakos, Senior, ANTONAKA@my.erau.edu Sergio Chinchilla-Ordonez, Senior, CHINCHS2@my.erau.edu Maurya Jandyala, Senior, JANDYALM@my.erau.edu
Lead Presenter's Name
Maurya Jandyala
Lead Presenter's College
DB College of Engineering
Faculty Mentor Name
Alberto Mello
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.
Did this research project receive funding support (Spark, SURF, Research Abroad, Student Internal Grants, Collaborative, Climbing, or Ignite Grants) from the Office of Undergraduate Research?
No
Included in
Wing Structure Design for YF-27 Shrike Homeland Defense Interceptor
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.