An apparatus and method for controlling a yaw moment of a flight vehicle, such as an aircraft. A wing structure of the flight vehicle has a first opening or actuator positioned by a first apex section of a first side of the wing, and has a second opening or actuator positioned away from or at a distance from a second apex section of a second side of the wing. The first side and the second side can each be positioned or located opposite a centerline of the wing or wing structure. A pressure source or other pressure supply device is in communication with the first opening or actuator and the second opening or actuator to which a pressurized fluid, such as air, is controlled and delivered to control or vary the yaw moment of the flight vehicle.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Pneumatic yaw control effector for aircraft


    Beteiligte:
    WILLIAMS DAVID R (Autor:in) / SEIDEL JÜRGEN (Autor:in)

    Erscheinungsdatum :

    17.04.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    PNEUMATIC YAW CONTROL EFFECTOR FOR AIRCRAFT

    WILLIAMS DAVID R / SEIDEL JÜRGEN | Europäisches Patentamt | 2017

    Freier Zugriff

    Pneumatic inflatable end effector

    Clark, K. H. / Johnston, J. D. | NTRS | 1981


    Pneumatic Inflatable End Effector

    K. H. Clark / J. D. Johnston | NTIS | 1978



    AIRCRAFT PNEUMATIC SYSTEM

    OLVER BRYAN W / ALECU DANIEL / STINA NICK | Europäisches Patentamt | 2021

    Freier Zugriff