The design and analysis of the electromechanical actuator (EMA) being developed for the NASA/Marshall Space Flight Center as part of the National Launch System (NLS) Propellant Control Effector Advanced Development Program (ADP) are addressed. The EMA design uses several proven technologies combined into a single modular package which includes single stage high ratio gear reduction, redundant electric motors mounted on a common drive shaft, redundant drive and control electronics, and digital technology for performing the closed loop position feedback, communication, and health monitoring functions. Results of tests aimed at evaluating both component characteristics and overall system performance demonstrated that the goal of low cost, reliable control in a cryogenic environment is feasible.


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    Titel :

    Electromechanical actuation for cryogenic valve control


    Beteiligte:
    Lister, M. J. (Autor:in) / Reichmuth, D. M. (Autor:in)

    Kongress:

    AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit ; 1993 ; Monterey, CA, United States


    Erscheinungsdatum :

    1993-06-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Electromechanical actuation for cryogenic valve control

    LISTER, M. / REICHMUTH, D. | AIAA | 1993


    Electromechanical flight control actuation

    Bird, D.K. | Tema Archiv | 1977


    Electromechanical Flight Control Actuation

    Bird, Daniel K. | SAE Technical Papers | 1977



    Electromechanical Flight Control Actuation Update

    BIRD, DANIEL K. | SAE Technical Papers | 1978