A hybrid aircraft power plant (10) has a structure (28); an output shaft (12) connectable to a load (16) and rotatable about an axis (14) relative the structure (28); a thermal engine (18) secured to the structure (28) and having a thermal engine shaft (22); an electric motor (20) having a stator and a rotor shaft (24), the stator secured to the structure (28); an epicyclic gearing (36) having a sun gear (38) coaxial to a ring gear (40), a plurality of planet gears (42) meshed between the sun gear (38) and the ring gear (40), and a carrier (44) coaxial to the sun gear (38) and to the ring gear (40), the sun gear (38), carrier (44), and ring gear (40) being rotatable relative the casing structure (28), the output shaft (12) and the rotor shaft (24) both coupled to the carrier (44), and the thermal engine shaft (22) coupled to sun gear (38) and the carrier (44); and an overrunning clutch (46) operable to prevent the rotation of the ring gear (40) in one angular direction.
HYBRID AIRCRAFT POWER PLANT
HYBRIDFLUGZEUGTRIEBWERK
GROUPE MOTOPROPULSEUR HYBRIDE POUR AÉRONEF
2025-08-13
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |