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.


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    Title :

    AIRCRAFT EVACUATION SYSTEM WITH AN INTEGRATED SPOILER


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

    Publication date :

    2019-03-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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