This paper discusses the choice of drive topologies for the electrical actuation of aircraft flaps and slats. The paper first discusses the potential benefits of replacing electro-hydraulic actuation with distributed electrical actuation of the flight control surfaces. It then demonstrates why fault tolerance is essential in order to meet the reliability requirements of these systems. A range of different modular drive structures are compared, examining performance requirements at all speeds. It is shown how a shorted phase will exert substantial braking torque at low speed, and this strongly influences the choice of drive topology. (6 pages)


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    Title :

    Choice of drive topologies for electrical actuation of aircraft flaps and slats


    Contributors:
    Bennett, J.W. (author) / Mecrow, B.C. (author) / Jack, A.G. (author) / Atkinson, D.J. (author) / Sewell, C. (author) / Mason, G. (author) / Sheldon, S. (author) / Cooper, B. (author)

    Publication date :

    2004-01-01



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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