A guidance-to-collision law is presented. The guidance law is derived, using the optimal control methodology, for an accelerating exoatmospheric interceptor. It is dependent on a unique zero-effort heading angle error and on a variable denoted as the zero-effort angle of attack. The guidance law enables an accelerating interceptor to fly toward the interception point along a straight line, after the initial heading error is nulled. In addition, the guidance-to-collision law enables interception of the target with a terminal body angle. Moreover, the trajectory imposed by this guidance law enables an accelerating interceptor to estimate the target’s acceleration by using bearings-only measurements. This is possible due to the imposed line-of-sight rotation, making the range between the two vehicles observable. Using a nonlinear two-dimensional simulation, the performance of the guidance law is analyzed, showing superior performance compared to that of classical proportional navigation.


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    Titel :

    Optimal Guidance-to-Collision Law for an Accelerating Exoatmospheric Interceptor Missile


    Beteiligte:
    Reisner, Daniel (Autor:in) / Shima, Tal (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.11.2013




    Medientyp :

    Aufsatz (Konferenz) , Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






    Optimal Guidance-to-Collision for an Accelerating Exo-Atmospheric Interceptor Missile

    Reisner, D. / Shima, T. / American Institute of Aeronautics and Astronautics; Conferderation of European Aerospace Societies | British Library Conference Proceedings | 2011



    Optimal Guidance Law for an Accelerating Exo-Atmospheric Interceptor Missile

    Reisner, D. / Shima, T. / Tekhniyon, Makhon tekhnologi le-Yisra'el | British Library Conference Proceedings | 2011