An aircraft system is provided that includes a first propulsor rotor (42A), a second propulsor rotor (42B), a drivetrain (40) and an intermittent combustion engine (68). The first propulsor rotor (42A) is rotatable about a first propulsor axis (48A). The second propulsor rotor (42B) is rotatable about a second propulsor axis (48B). The drivetrain (40) includes a drive structure (100) and a transmission (106). The drive structure (100) is rotatable about a drive axis (110) that is angularly offset from the first propulsor axis (48A) and the second propulsor axis (48B). An output (119) of the transmission (106) is coupled to the first propulsor rotor (42A) and the second propulsor rotor (42B) through the drive structure (100). The intermittent combustion engine (68) is configured to drive rotation of the first propulsor rotor (42A) and the second propulsor rotor (42B) through the drivetrain (40).
AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSION ENGINE(S)
FLUGZEUGANTRIEBSSYSTEM MIT INTERMITTIERENDEM VERBRENNUNGSMOTOR/-VORRICHTUNGEN
SYSTÈME DE PROPULSION D'AÉRONEF AVEC MOTEUR(S) À COMBUSTION INTERMITTENTE
2024-01-17
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
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|AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
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|AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
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|AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
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