A dual rotor propulsion system (200, 300) for a tiltrotor aircraft (10, 100) having VTOL and forward flight modes. The dual rotor propulsion system (200, 300) includes an engine (202, 302) operable to provide an input torque to a transmission (206, 306) that, responsive thereto, generates an output torque. A first output shaft (214a, 314a) is coupled to the transmission (206, 306) and is operable to receive a first portion of the output torque. A first rotor assembly (216a, 316a) is coupled to and rotatable with the first output shaft (214a, 314a). A second output shaft (214b, 314b) is coupled to the transmission (206, 306) and is operable to receive a second portion of the output torque. A second rotor assembly (216b, 316b) is coupled to and rotatable with the second output shaft (214b, 314b). In operation, the first and second rotor assemblies (216a, 316a, 216b, 316b) rotate coaxially, the first rotor assembly (216a, 316a) is a different diameter than the second rotor assembly (216b, 316b) and the first rotor assembly (216a, 216b) is stoppable and foldable in the forward flight mode.
DUAL ROTOR PROPULSION SYSTEMS FOR TILTROTOR AIRCRAFT
DOPPELROTORANTRIEBSSYSTEME FÜR KIPPROTORFLUGZEUG
SYSTÈMES DE PROPULSION DE ROTOR DOUBLE POUR AÉRONEF À ROTORS BASCULANTS
2023-08-02
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
TILTROTOR PROPULSION SYSTEM FOR AN AIRCRAFT AND AIRCRAFT HAVING A TILTROTOR PROPULSION SYSTEM
European Patent Office | 2018
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