The EMAS flight test project successfully demonstrated, for the first time, the electrical actuation of a primary flight control surface in flight. This test was a major step toward the realization of the All-Electric Airplane (AEA) concept. An electric actuator was installed in a modified C-141A aircraft to power the left aileron. Testing included ground and flight trials to ensure unchanged control system damping. Aircraft roll performance tests included maximum effort rolls, degraded system rolls, and autopilot rolls. Sideslip and trim test points were also performed. It was verified that EMAS performance was similar to the normal hydraulic actuator. Results include lessons on aircraft modification, general system characteristics, maintenance factors, and compatibility with other aircraft systems that may influence future installations.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Advanced Electromechanical Actuation System (EMAS), Flight Test


    Beteiligte:
    W. J. Norton (Autor:in)

    Erscheinungsdatum :

    1986


    Format / Umfang :

    139 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Electromechanical Flight Control Actuation

    Bird, Daniel K. | SAE Technical Papers | 1977


    Electromechanical flight control actuation

    Bird, D.K. | Tema Archiv | 1977




    Electromechanical Flight Control Actuation Update

    BIRD, DANIEL K. | SAE Technical Papers | 1978