Is this project an undergraduate, graduate, or faculty project?
Undergraduate
Project Type
group
Campus
Daytona Beach
Authors' Class Standing
Paige Levesque, Senior Jemimah Davies, Senior Carlie Vogt, Senior Melissa Pritchett, Senior Kyle Smothers, Senior Matthew Talty, Senior
Lead Presenter's Name
Paige Levesque
Lead Presenter's College
DB College of Engineering
Faculty Mentor Name
Alberto Mello
Abstract
This project focuses on the structural design of a wing optimized for a significantly larger aspect ratio, aimed at enhancing the efficiency and sustainability of commercial aircraft while ensuring structural integrity and fatigue resistance. As this project focused on the wing structure design, the internal components needed to be sized appropriately to sustain the loading experienced. Some of the important internal components sized and designed included spar caps, webs, stringers, ribs, and fuselage attachment brackets. Along with sizing, fatigue life analysis was completed to ensure the risk of structural failure was reduced over the lifespan of our aircraft. The designed wing structure supports the higher aspect ratio along with the resulting higher stresses and bending moments while maintaining necessary safety margins. This design will undergo Damage Tolerance Analysis and be certified according to FAA structural regulations. The structural design of the wing demonstrates a practical approach capable of balancing the new aspect ratio with the increased shear forces and bending moments, wing weight, and proper damage/fatigue analysis.
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
Commercial Aircraft Wing Structural Design for a High Aspect Ratio
This project focuses on the structural design of a wing optimized for a significantly larger aspect ratio, aimed at enhancing the efficiency and sustainability of commercial aircraft while ensuring structural integrity and fatigue resistance. As this project focused on the wing structure design, the internal components needed to be sized appropriately to sustain the loading experienced. Some of the important internal components sized and designed included spar caps, webs, stringers, ribs, and fuselage attachment brackets. Along with sizing, fatigue life analysis was completed to ensure the risk of structural failure was reduced over the lifespan of our aircraft. The designed wing structure supports the higher aspect ratio along with the resulting higher stresses and bending moments while maintaining necessary safety margins. This design will undergo Damage Tolerance Analysis and be certified according to FAA structural regulations. The structural design of the wing demonstrates a practical approach capable of balancing the new aspect ratio with the increased shear forces and bending moments, wing weight, and proper damage/fatigue analysis.