HYBRID MULTIROTOR PROPULSION SYSTEM FOR AN AIRCRAFT

摘要

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) is configured according to a predetermined operating mode: to cause said mechanical power source (MPS) to output total mechanical power and to cause said total mechanical power to be split into first and second mechanical power components; to cause said main distributor gearbox (MDG) to distribute said first mechanical power component to said plurality of driving elements (PDS) for providing each driving element (PDS) with a direct mechanical propeller power; to cause said electric machine (EM) to convert said second mechanical power component into electric power and to cause at least a part of said electric power to be distributed to said plurality of electromotors (EU) for providing each electromotor (EU) with an electric propeller power; to cause each driving element (PDS) to output said direct mechanical propeller power to said peripheral differential gearbox (PDGU) of said propulsion unit (PU) to which said driving element (PDS) is coupled; to cause each electromotor (EU) to convert said electric propeller power into an indirect mechanical propeller power and to output said indirect mechanical propeller power to said peripheral differential gearbox (PDGU) of said propulsion unit (PU) comprising said electromotor (EU); and to cause said peripheral differential gearbox (PDGU) of each propulsion unit (PU) to aggregate said direct mechanical propeller power and said indirect mechanical propeller power to a total mechanical propeller power and to drive said propeller (Pr) of each propulsion unit (PU) based on said total mechanical propeller power.