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.


    Access

    Download


    Export, share and cite



    Title :

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


    Contributors:

    Publication date :

    2018-11-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



    Flow control device and method for aircraft and missile forebody

    SOWLE ZAK / VASUDEVAN SRIKANTH / STUCKE RUSSELL et al. | European Patent Office | 2016

    Free access

    Numerical investigation of subsonic flow over a typical missile forebody

    Tuncer, Ismail / Marvin, Ron / Platzer, Max | AIAA | 1996




    Physics of forebody flow control

    Font, Gabriel I. | NTRS | 1993