A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.


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    Title :

    AUTOPILOT CONTROL ARRANGEMENT AND METHODS


    Additional title:

    AUTOPILOTSTEUERANORDNUNG UND VERFAHREN
    AGENCEMENT ET PROCÉDÉS DE COMMANDE DE PILOTE AUTOMATIQUE


    Contributors:
    ALBION NICK (author) / FEIFEL MARK (author) / MARVIN MARK (author) / MERCER JOHN (author)

    Publication date :

    2019-12-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / B64C AEROPLANES , Flugzeuge



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