Explicit formulas of optimal guidance laws for an acceleration-constrained, arbitrary-order missile and maneuvering target are derived. These formulas are given in terms of the transfer function and acceleration constraint of the missile and the transfer function/shaping filter of the target. Optimal full-state feedback guidance law is synthesized against a target performing a barrel roll maneuver, and compared with the performance of proportional navigation (PN) for minimum and nonminimum phase missile. Simulation of a third-order missile shows the relative gain from using the full-order guidance law.<>


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    Titel :

    Optimal guidance for acceleration constrained missile and maneuvering target


    Beteiligte:
    Rusnak, I. (Autor:in) / Meir, L. (Autor:in)


    Erscheinungsdatum :

    1990-07-01


    Format / Umfang :

    370712 byte




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch