Is this project an undergraduate, graduate, or faculty project?
Undergraduate
Project Type
group
Campus
Daytona Beach
Authors' Class Standing
Lohit Talachutla, Senior Giorgio Landonko, Senior Joshua Beltrame, Senior Camron Allen, Senior Nicolas Volberg, Senior Yug Patel, Senior Ian Keene, Senior
Lead Presenter's Name
Lohit Talachutla
Lead Presenter's College
DB College of Engineering
Faculty Mentor Name
Alberto Mello
Abstract
The focus of this project is to size the wing structure of HEX-1 to withstand the aerodynamic loadings that result from Distributed Electric Propulsion (DEP) effects and blown lift. Furthermore, the design must be able to pass electricity and fuel through the wing structure without compromising the structural integrity. To analyze and size the wing, idealized wing analysis was performed by hand, coupled with Finite Element Analysis (FEA) to validate results. After the sizing was validated, damage tolerance analysis was performed to ensure the system can survive its entire life cycle. The wing structure was proven to withstand the various loadings that are encountered, while not losing integrity throughout its lifespan. It stays within the allotted weight of the wing found during the conceptual and preliminary design stage, which is essential for ensuring the aircraft can meet its rigorous performance requirements and meet the mission. This project involved the process of applying structural analysis and damage analysis, and ensuring that the design is safe, strong and reliable, while staying within a set of constraints.
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
HEX-1 Hybrid Electric Military Logistics Vehicle
The focus of this project is to size the wing structure of HEX-1 to withstand the aerodynamic loadings that result from Distributed Electric Propulsion (DEP) effects and blown lift. Furthermore, the design must be able to pass electricity and fuel through the wing structure without compromising the structural integrity. To analyze and size the wing, idealized wing analysis was performed by hand, coupled with Finite Element Analysis (FEA) to validate results. After the sizing was validated, damage tolerance analysis was performed to ensure the system can survive its entire life cycle. The wing structure was proven to withstand the various loadings that are encountered, while not losing integrity throughout its lifespan. It stays within the allotted weight of the wing found during the conceptual and preliminary design stage, which is essential for ensuring the aircraft can meet its rigorous performance requirements and meet the mission. This project involved the process of applying structural analysis and damage analysis, and ensuring that the design is safe, strong and reliable, while staying within a set of constraints.