An optimal midcourse guidance law is presented that maximizes the final speed for missiles against a target at far distance or at low attitude in which the final speed is a prime factor. An explicit acceleration command is derived analytically in which the trajectory-dependent optimal control gains are written in terns of thrust, lift, drag, and intercept boundary condition. The optimal guidance law can be implemented either in airframe coordinates or inertia coordinates. It is shown that the acceleration commands with constant control gain are adequate when the range is relatively short; during midcourse guidance, however, the optimal control gains are required to enhance the performance.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Analysis of optimal midcourse guidance law


    Weitere Titelangaben:

    Analyse der Optimalwertregelung für Fernstreckenraketen


    Beteiligte:


    Erscheinungsdatum :

    1996


    Format / Umfang :

    7 Seiten, 12 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    On optimal stochastic midcourse guidance.

    Jazwinski, A. H. | NTRS | 1968



    Analysis of Optimal Midcourse Guidance Law

    Yang, S.-M. | Online Contents | 1996


    Lead Angle Constrained Optimal Midcourse Guidance

    Dwivedi, P. N. / Bhale, Prashant G. / Bhattacharyya, Abhijit et al. | AIAA | 2013


    Optimal Midcourse Guidance against Hypersonic Targets

    Imado, F. / Ichikawa, A. / Kanai, K. | British Library Conference Proceedings | 1993