KETEP 세계에너지시장정보

Hybrid propulsion system (10, 20) for aircraft, comprising at least a fuel cell unit (13) for providing power to drive an aircraft (100) by using hydrogen in a redox reaction; at least a gas turbine (11) for providing power to drive the aircraft (100) by burning hydrogen; a hydrogen source (12) for providing the hydrogen to the fuel cell unit (13) and/or to the gas turbine (11); and at least an electric propulsion unit (14, 24) for driving the aircraft (100), the electric propulsion unit (14, 24) comprising a first electric machine (15a, 15b) connected to a first propeller (16a, 16b), the first electric machine being electrically powered by the fuel cell unit (13) and mechanically powered by the gas turbine (11) in at least two different propulsion modes (M1, M2); and a control unit (27) to control the power supply to the electric propulsion unit (14, 24), wherein the control unit (27) is configured to apply a first propulsion mode (M1) for a first flight phase in which the electric propulsion unit (14, 24) is essentially or only electrically powered by the fuel cell unit (13), and to apply a second propulsion mode (M2) for a second flight phase in which the electric propulsion unit (14, 24) is essentially or only mechanically powered by the gas turbine (11).