An explicit closed-form formula of a discrete guidance law for a linear time-invariant, acceleration commanded, arbitrary-order missile and a linear, time-invariant arbitrary-order, maneuvering target is derived. The formula is given in terms of the missile and target transfer functions and responses to initial conditions. Examples are explicitly solved for zero-lag and a first-order missile. As an example, it is shown that the discrete proportional navigation ratio is higher than 3 and time varying in contrast to the continuous case.<>


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    Titel :

    Discrete optimal guidance for high-order missile and maneuvering target


    Beteiligte:
    Rusnak, I. (Autor:in)


    Erscheinungsdatum :

    01.11.1991


    Format / Umfang :

    232934 byte




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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