An aircraft leading edge flight control surface comprising an actuation mechanism configured to independently translate and rotate the flight control surface relative to an aircraft aerofoil structure on which the flight control surface is mounted. An aerofoil assembly 2 comprises an aerofoil structure 20 and a leading edge flight control surface 21. The flight control surface includes an actuation mechanism that enables the control surface to be moved between a stowed position 21a to a first intermediate position 21b by a translation movement 201. The mechanism then enables the control surface to move to a second intermediate position 21c by a translation movement 202. The mechanism further enables the control surface to move to a high lift position 21d by means of a rotational movement 203. The control surface can be moved to a spoiling position (21e, fig 3a) by means of an additional translation movement 204. The control surface can also be moved to a braking position (21f, fig 4) from the high lift position 21d by means of a rotation movement (205, fig 4).


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    Titel :

    Leading edge flight control surfaces


    Beteiligte:
    HENRY EDWARDS (Autor:in)

    Erscheinungsdatum :

    2019-09-25


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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    FISCHER, M. / WRIGHT, JR., A. / WAGNER, R. | AIAA | 1983


    A flight test of laminar flow control leading-edge systems

    Fischer, M. C. / Wright, A. S., Jr. / Wagner, R. D. | NTRS | 1983


    A flight test of laminar flow control leading-edge systems

    Fischer, M. C. / Wright, A. S., Jr. / Wagner, R. D. | NTRS | 1983