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.


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    Title :

    DUAL ROTOR PROPULSION SYSTEMS FOR TILTROTOR AIRCRAFT


    Additional title:

    DOPPELROTORANTRIEBSSYSTEME FÜR KIPPROTORFLUGZEUG
    SYSTÈMES DE PROPULSION DE ROTOR DOUBLE POUR AÉRONEF À ROTORS BASCULANTS


    Contributors:

    Publication date :

    2023-08-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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