The present invention includes an aircraft drive system (200) comprising a main rotor gearbox (214) comprising a first and a second input; a first drive system comprising a first engine reduction gearbox (216a) connecting a first engine to the first input of the main rotor gearbox (214) at a reduced shaft speed; and a second drive system independent from and redundant with the first drive system, the second drive system comprising a second engine reduction gearbox (216b) connecting a second engine to the second input of the main rotor gearbox (214) at the reduced shaft speed.
AIRCRAFT DRIVE SYSTEM
FLUGZEUGANTRIEBSSYSTEM
SYSTÈME DE TRANSMISSION POUR AÉRONEF
27.07.2022
Patent
Elektronische Ressource
Englisch