An integrated spoiler may comprise a side tube having a tube wall, wherein the tube wall has a first edge and a second edge, wherein the first edge is disposed proximate a portion of the tube wall; a seam proximate the first edge and the portion of the tube wall; a coupling across the seam configured to inhibit the exchange of gas across the seam; a flap comprising the second edge and extending outward of the seam; and a ligament. The flap may further comprise an angle θ between the flap and an outer surface of the tube wall wherein the ligament is configured to restrain angle θ at a maximum. The flap may be configured to pivot about the seam through angle θ in response to an aerodynamic force.


    Access

    Download


    Export, share and cite



    Title :

    Aircraft evacuation system with an integrated spoiler


    Contributors:
    VOLNY JARO S (author) / HARTMAN DREW (author)

    Publication date :

    2021-03-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / A62B DEVICES, APPARATUS OR METHODS FOR LIFE-SAVING , Vorrichtungen, Geräte oder Verfahren zur Lebensrettung



    AIRCRAFT EVACUATION SYSTEM WITH AN INTEGRATED SPOILER

    VOLNY JARO S / HARTMAN DREW | European Patent Office | 2019

    Free access

    AIRCRAFT SPOILER LOCKOUT

    SILVERSTEIN MITCHELL / PAVLETICH KEN / LIMON MARK NOEL C | European Patent Office | 2019

    Free access

    Integrated spoiler

    HUANG SHIFENG / HUANG YUNHUI / JIN XING et al. | European Patent Office | 2022

    Free access

    Aircraft spoiler lockout

    SILVERSTEIN MITCHELL / PAVLETICH KEN / LIMON MARK NOEL C | European Patent Office | 2020

    Free access

    AIRCRAFT WING WITH SPOILER

    HANSEN HEINZ / KIRN JOHANNES / MACHUNZE WOLFGANG et al. | European Patent Office | 2017

    Free access