Is this project an undergraduate, graduate, or faculty project?
Undergraduate
Project Type
group
Campus
Daytona Beach
Authors' Class Standing
Nnamdi Adi,Senior Luke Behringer, Senior Gabriel De Oliveira, Senior Dylan Nagowski, Senior Paul Koffi, Senior
Lead Presenter's Name
Nnamdi Adi
Lead Presenter's College
DB College of Engineering
Faculty Mentor Name
Kimberly Heinzer
Abstract
This project focuses on the preliminary design of a hybrid-electric aircraft with short takeoff and landing (STOL) capabilities tailored for the rapidly expanding hybrid-electric market. This aircraft distinguishes itself from its competition through multi-mission capabilities, distributed electric propulsion (DEP) for quiet takeoff and landing, and advanced safety systems. The geometric design was developed using computer-aided design (CAD). The development of weight, lift, drag, and thrust models dictated the aircraft's performance characteristics while stability and control models were derived from the geometric design. Iterative refinement of the performance, stability, and geometric design were conducted to meet design requirements set by federal, international, and internal entities. The continued refinement produced a hybrid-electric aircraft capable of 500-foot takeoff and landing distances in multiple terrains with a maximum payload capacity of 9 passengers or 3,000 pounds and a maximum range of 1,100 nautical miles. This project demonstrates key methodologies required to design an aircraft, including performance, structural, financial, and human factor considerations.
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
Preliminary Design of Hybrid-Electric STOL Aircraft with Multi-Mission Capabilities
This project focuses on the preliminary design of a hybrid-electric aircraft with short takeoff and landing (STOL) capabilities tailored for the rapidly expanding hybrid-electric market. This aircraft distinguishes itself from its competition through multi-mission capabilities, distributed electric propulsion (DEP) for quiet takeoff and landing, and advanced safety systems. The geometric design was developed using computer-aided design (CAD). The development of weight, lift, drag, and thrust models dictated the aircraft's performance characteristics while stability and control models were derived from the geometric design. Iterative refinement of the performance, stability, and geometric design were conducted to meet design requirements set by federal, international, and internal entities. The continued refinement produced a hybrid-electric aircraft capable of 500-foot takeoff and landing distances in multiple terrains with a maximum payload capacity of 9 passengers or 3,000 pounds and a maximum range of 1,100 nautical miles. This project demonstrates key methodologies required to design an aircraft, including performance, structural, financial, and human factor considerations.