Series hybrid-electric propulsion for fixed-wing VTOL UAV

Abstract

This paper investigates feasibility of series hybrid-electric propulsion for a fixed-wing VTOL UAV. The experimental derivation of the piston engine map, alternator and battery parameters are considered and configured in Matlab Simulink program for a MTOW 60 kg VTOL UAV. The typical intelligence, surveillance, and reconnaissance mission profile is analysed. The series hybrid-electric propulsion have been represented to take advantage of the synergy between engines, battery and motors to improve overall performance. The series hybrid electric propulsion configuration is 10% lighter than a simple piston engine propulsion system, and also predict to have 3 times longer endurance with 10kg payload than electric only propulsion system. It is believed that present results can have potential advantages including fuel savings, lower pollution, reduced take-off noise, and increased short-term power. These characteristics will produce a much more community-friendly class of vehicles.