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.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

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


    Contributors:

    Published in:

    Publication date :

    2013-07-09


    Size :

    14 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    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