A clutch actuator assembly operably integrated with a clutch assembly in a drive system, and a method of use. The drive system may be an electric taxi drive system mounted completely within wheel walls of an aircraft landing gear wheel (see fig. 5). The actuator includes: a rotatable actuator mounting element 12 in torque transfer connection with a clutch assembly (e.g. clutch 40, fig. 3); and, mounted on the plate 12, a pair of prime mover solenoids 16, 18 and a (third) locking solenoid 20. The first and second solenoids 16, 18 are selectively activatable by power supply and control elements to cause said rotatable actuator element to rotate in a selected opposite rotational directions and transfer torque through a mechanical linkage (e.g. a bell crank 30) to said clutch assembly, for example to a bi-directional clutch selector plate. The locking solenoid 20 comprising a locking element engaging said rotatable mounting element to lock said rotatable mounting element in a default neutral disengaged position and prevent torque transfer through said mechanical linkage to said clutch assembly when said prime mover solenoids are not activated.


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    Title :

    Clutch actuator assembly


    Contributors:

    Publication date :

    2024-04-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F16D COUPLINGS FOR TRANSMITTING ROTATION , Nicht schaltbare Kupplungen / B64C AEROPLANES , Flugzeuge



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