A fourth-order extended Kalman filter is described which generates an estimate of target lateral acceleration. This is used with the sensed rate of change of bearing, the missile lateral acceleration, and its first derivative to generate a demanded lateral missile acceleration according to a precomputed suboptimal control law. Single-plane analysis is used throughout. The simulation results show that a substantial improvement in miss distance is achieved. This work concerns only target maneuver detection and no conclusions can be drawn about the effects of errors in the measurement of range and its rate of change.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Missile guidance based on Kalman filter estimation of target maneuver


    Additional title:

    Flugkoerperlenkung mit der Kalman-Filter-Abschaetzung der lateralen Zielbeschleunigung


    Contributors:
    Tang, Y.M. (author) / Borrie, J.A. (author)

    Published in:

    Publication date :

    1984


    Size :

    6 Seiten, 5 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





    Target maneuver detection and estimation (missile guidance)

    Williams, D.E. / Friedland, B. | Tema Archive | 1988


    Passive homing missile guidance law based on new target maneuver models

    SPEYER, JASON L. / KIM, KEVIN D. / TAHK, MINJEA | AIAA | 1990



    Target Maneuver Adaptive Guidance Law for a Bounded Acceleration Missile

    Atir, Ronen / Hexner, Gyorgy / Weiss, Haim et al. | AIAA | 2009