A device is provided for attenuating the vortex wake created in the zone behind an aircraft, the aircraft having at least one wing and an afterbody having a strong upward asymmetrical reduction of section of the rear fuselage. The device is positioned downstream of the wing of the aircraft symmetrically relative to the longitudinal plane of the aircraft. The device includes vortex-generating aerodynamic appendages capable of being deployed between a folded-down position in which the aerodynamic appendages are folded down substantially in the direction of the fuselage, capable of switching from a folded-down position in which they are folded down substantially in the direction of the fuselage, and a deployed position calculated to generate vortex structures having an intensity and a trajectory which modify the local pressure field in order to interact with the vortex wake to attenuate it and separate the upsweep vortices from the longitudinal plane of the aircraft.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    VORTEX WAKE ATTENUATION DEVICE


    Beteiligte:
    BURY YANNICK (Autor:in)

    Erscheinungsdatum :

    24.09.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



    Wake Vortex Attenuation Flight Tests: A Status Report

    Barber, Marvin R. / Tymczyszyn, Joseph J. | NTRS | 1981


    Wake vortex attenuation flight tests - A status report

    Barber, M. R. / Tymczyszyn, J. J. | NTRS | 1982



    Wake Vortex Attenuation Control of Receiver UAV in Autonomous Aerial Refueling

    Yu, Ziquan / Qu, Yaohong / Zhang, Youmin et al. | IEEE | 2018


    Wake Vortex

    Bryant, W. / Henke, R. / International Council of the Aeronautical Sciences | British Library Conference Proceedings | 2006