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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    Title :

    Optimal guidance for acceleration constrained missile and maneuvering target


    Contributors:
    Rusnak, I. (author) / Meir, L. (author)


    Publication date :

    1990-07-01


    Size :

    370712 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English