An actuation system for an aircraft piston engine includes a controller and an actuator. The controller selectively supplies motor control signals to a motor. The actuator includes a housing, a motor, a main rod, a control handle, and an inner rod. The main rod receives a drive torque from the motor and translates in either a first axial direction or a second axial direction. The main rod is responsive to an axial drive force to translate in either the first axial direction or the second axial direction. The inner rod is disposed within the main rod and is movable between a first position, in which main rod rotation causes the main rod to translate, and a second position, in which main rod rotation does not cause the main rod to translate, but application of the axial force to the control handle causes the main rod to translate.


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    Title :

    ACTUATOR FOR USE IN A PISTON ENGINE POWERED AIRCRAFT ACTUATION CONTROL SYSTEM


    Contributors:
    NOVOSAD BORIS (author) / JASA ZDENEK (author)

    Publication date :

    2022-10-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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