Conceptual Design of an Electric Propulsion System Based on Fuel Cells for an Ultralight Manned Aircraft

Abstract

The design process of a fuel cell based electric propulsion system an ultralight manned aircraft is presented. Propulsion system consists of electric motor with 60 kW maximum power, 30-35kW proton exchange membrane fuel cell, battery with capacity 1.75 kW and maximum output 30 kW, hydrogen cylinders and other systems. Ultralight aircraft Sigma equipped with such a propulsion system with two pilots can have one our flight duration at maximum takeoff weight 640 kg.