An aircraft (800) comprising a hybrid electric aircraft propulsion system (200). The system (200) comprises a first sub-assembly (1502A) having a first electric propulsor assembly (808A) and a first thermal propulsor assembly (810A), the first thermal propulsor assembly (810A) having a first thermal engine (201A), a first generator (202A) and a first rotating structure (206C), the first electric propulsor assembly (808A) attached to the aircraft (800) at a first location and the first thermal propulsor assembly (810A) attached to the aircraft (800) at a second location. The system (200) also comprises a second sub-assembly (1502B) having a second electric propulsor assembly (808B) and a second thermal propulsor assembly (810B), the second thermal propulsor assembly (810B) having a second thermal engine (201B), a second generator (202B) and a second rotating structure (206F), the second electric propulsor assembly (808B) attached to the aircraft (800) at a third location and the second thermal propulsor assembly (810B) attached to the aircraft (800) at a fourth location.
HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM
HYBRIDES ELEKTRISCHES FLUGZEUGANTRIEBSSYSTEM
SYSTÈME DE PROPULSION D'AÉRONEF ÉLECTRIQUE HYBRIDE
2020-03-11
Patent
Electronic Resource
English