Disclosed is a hybrid multirotor propulsion system (100) for an aircraft, comprising: a plurality of propulsion units (PU), each propulsion unit (PU) comprising a propeller (Pr), an electromotor (EU) and a peripheral differential gearbox (PDGU); a plurality of driving elements (PDS), each of which being coupled to a respective one of said plurality of propulsion units (PU); a mechanical power source (MPS); a main distributor gearbox (MDG); at least one electric machine (EM); and a power management unit (PMU); wherein said power management unit (PMU). The PMU is configured to cause distribution of mechanical and electrical power within the multirotor propulsion system.
HYBRID MULTIROTOR PROPULSION SYSTEM FOR AN AIRCRAFT
HYBRIDES MULTIROTOR-ANTRIEBSSYSTEM FÜR EIN FLUGZEUG
SYSTÈME DE PROPULSION MULTIROTOR HYBRIDE-POUR AÉRONEF
2023-06-07
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |