A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal associated therewith, the at least one sensor being used for determining or estimating flow separation or side forces on the missile forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.


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    Titel :

    Aircraft and missile forebody flow control device and method of controlling flow


    Beteiligte:
    PRINCE TROY (Autor:in) / LISY FREDERICK J (Autor:in) / PATEL MEHUL P (Autor:in) / DICOCCO JACK M (Autor:in) / CARVER REED (Autor:in) / SCHMIDT ROBERT N (Autor:in)

    Erscheinungsdatum :

    27.11.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen



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