An afterbody flow control system is used for aircraft or missile flow control to provide enhanced maneuverability and stabilization. A method of operating the flow control system is also described. The missile or aircraft comprises an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

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


    Beteiligte:
    DICOCCO JACK (Autor:in) / PRINCE TROY (Autor:in) / PATEL MEHUL (Autor:in) / NG TSUN MING TERRY (Autor:in)

    Erscheinungsdatum :

    2017-05-02


    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



    Afterbody Flow Control for Low-Alpha Missile Maneuvering

    Patel, Mehul / DiCocco, Jack / Prince, Troy et al. | AIAA | 2003


    Theoretical analysis of aircraft afterbody flow

    DEIWERT, GEORGE S. / ANDREWS, ALISON E. / NAKAHASHI, KAZUHIRO | AIAA | 1987


    Theoretical analysis of aircraft afterbody flow

    Deiwert, George S. / Andrews, Alison E. / Nakahashi, Kazuhiro | NTRS | 1987


    Theoretical analysis of aircraft afterbody flow

    DEIWERT, G. / ANDREWS, A. / NAKAHASHI, K. | AIAA | 1984


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

    PRINCE TROY / LISY FREDERICK J / PATEL MEHUL P et al. | Europäisches Patentamt | 2018

    Freier Zugriff