The present invention includes a hybrid propulsion system for an aircraft (300) comprising: one or more turboshaft engines (306) that provide shaft power and are capable of providing thrust; at least one of: one or more electrical generators (310a, 310b, 310c) or one or more hydraulic pumps (410a, 410b, 410c) connected to a shaft of the one or more turboshaft engines (306); and at least two rotatable nacelles (304a, 304b), each nacelle (304a; 304b) housing at least one of: one or more electric motors (313a, 313b, 313c; 320a, 320b, 320c; 324a, 324b, 324c) or one or more hydraulic motors (413a, 413b, 413c; 420a, 420b, 420c; 424a, 424b, 424c) each connected to a proprotor, wherein the electric motor (313a, 313b, 313c; 320a, 320b, 320c; 324a, 324b, 324c) is electrically connected to the electric generator (310a, 310b, 310c), or the hydraulic motor (413a, 413b, 413c; 420a, 420b, 420c; 424a, 424b, 424c) is connected to the hydraulic pump (410a, 410b, 410c), respectively, wherein the proprotors provide lift whenever the aircraft (300) is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft (300) is in forward flight.
HYBRID PROPULSION DRIVE TRAIN SYSTEM FOR TILTROTOR AIRCRAFT
HYBRIDANTRIEBSSYSTEM VON KIPPROTORFLUGZEUGEN
SYSTÈME DE PROPULSION HYBRIDE POUR UN AVION À ROTOR BASCULANT
2020-01-08
Patent
Electronic Resource
English
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