Design Space Exploration for Electrically Powered Vertical Take-Off and Landing Unmanned Aerial Vehicles

摘要

This paper addresses the current lack of detailed, published investigation into optimal Vertical Take-Off and Landing (VTOL) Unmanned Aerial Vehicle (UAV) configuration design. For purposes of this current study, the scope is limited to electrical power provided by Commercial Off-The-Shelf Li-Ion batteries, and a 0-25kg gross vehicle weight UAV sector. Presented are details on the systems design focused on three primary types of VTOL aircraft: a tail-sitter, ducted fan, and hybrid/dual propulsion system, and their optimality in regards to multiple flight and static parameters. These configurations have been modeled systematically using current aerodynamic and electrical representations to develop a more complete understanding of the parameters and tradeoffs involved between hover, and cruise flight profiles for these basic VTOL designs. To the extent possible, this work will be verified against existing VTOL systems as well as the prototype testing of the VSTAR(C) UAV of Frontline Aerospace.