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3rd Thermal and Fluids Engineering Conference (TFEC)

ISSN: 2379-1748

A MULTI-PURPOSE UNMANNED AERIAL SYSTEM DESIGN

Mohammed S. Mayeed
Department of Mechanical Engineering, Kennesaw State University, Marietta, GA 30060, USA

Franklin Woods
Kennesaw State University, Marietta, GA 30060, USA

Alexander Bryant
Kennesaw State University, Marietta, GA 30060, USA

DOI: 10.1615/TFEC2018.asp.021494
pages 51-60


KEY WORDS: Unmanned Aerial System, Multi-Purpose, CFD, FEA

Abstract

Firefighters, farmers, and delivery systems workers are constantly looking for a more efficient and faster method for completing tasks. The objective of this study is to design a multi-purpose Unmanned Aerial System (UAS) that would assist in the search and rescue of victims, in fighting fires, in the agriculture industry, and for the transportation of consumer products. Regardless of the provided task, the UAS must be able to support itself in a varying payload, and in lift and horizontal flight. Computer-Aided Design models of the UAS and propeller were created in SolidWorks, and analyzed and evaluated with Finite Element Analysis (FEA) and Computational Fluid Dynamics (CFD) using the state-of-the-art SolidWorks Simulation and Flow Simulation software. Propeller designs utilizing an elliptic cross-section and an airfoil cross-section were examined to determine which provided the most efficient value of thrust. A CFD analysis was performed on the UAS to locate the optimal tip-to-tip distance for the optimized position of the propellers to maximize the combined lift force so that the most efficient placement for the propellers could be achieved. With the FEA and CFD analyses completed, the final UAS was optimized to have a factor of safety between 2-3, maintain a flight for an hour, have a useful life of over ten years, and to maximize the thrust potential of an engine/propeller configuration. Then the UAS design was tested for horizontal motion, the lift force and payload capacity were recalculated under this situation, and the maximum velocity was calculated under the horizontal thrust.

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