An aircraft system is provided that includes a first propulsor rotor (42A), a first transmission (106A), a second propulsor rotor (42B), a second transmission (106B) and an intermittent combustion engine (68). The first propulsor rotor (42A) is rotatable about a first propulsor axis (48A). The first transmission (106A) is coupled to the first propulsor rotor (42A). The second propulsor rotor (44) is rotatable about a second propulsor axis (48B). The second transmission (106B) is coupled to the second propulsor rotor (44). The intermittent combustion engine (68) is configured to drive rotation of the first propulsor rotor (42) through the first transmission (106A). The intermittent combustion engine (68) is configured to drive rotation of the second propulsor rotor (44) through the second transmission (106B).
AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
FLUGZEUGANTRIEBSSYSTEM MIT INTERMITTIERENDEM VERBRENNUNGSMOTOR/N
SYSTÈME DE PROPULSION D'AÉRONEF AVEC MOTEUR(S) À COMBUSTION INTERMITTENTE
14.08.2024
Patent
Elektronische Ressource
Englisch
AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
Europäisches Patentamt | 2024
|AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
Europäisches Patentamt | 2024
|AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
Europäisches Patentamt | 2024
|AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
Europäisches Patentamt | 2024
|AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S)
Europäisches Patentamt | 2024
|