Dynamic inversion and singular perturbation methods are employed for medium-range air-to-air missile to obtain a near-optimal midcourse guidance law. The midcourse guidance stage is separated into two phases. In phase 1, which the rocket engine working, a dynamic inversion guidance law is used to guide the missile flight along a nominal trajectory. In the second gliding phase, singular perturbation technique is employed to develop a guidance law which maximum terminal specific energy. A terminal correction is made to ensure the seeker intercept the target. The result obtained from numerical simulation shows that, the guidance law can conserve energy for terminal interception, and the flight path error is small enough at the end of midcourse stage.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    A Near Optimal Midcourse Guidance Law for Air-to-Air Missile


    Beteiligte:
    Qiao, Qing-Qing (Autor:in) / Chen, Wan-Chun (Autor:in)


    Erscheinungsdatum :

    2013


    Format / Umfang :

    6 Seiten




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    A Near Optimal Midcourse Guidance Law for Air-to-Air Missile

    Qiao, Qing Qing ;Chen, Wan Chun | Trans Tech Publications | 2013


    On optimal stochastic midcourse guidance.

    Jazwinski, A. H. | NTRS | 1968


    Near Optimal Midcourse Guidance Law for Flight Vehicle

    Poh Eng Kee / Dong, L. / Chai Joo Siong et al. | British Library Conference Proceedings | 1998


    Midcourse Guidance and Control for Pulse Motor Boost Missile

    Tang, Mao / Gong, Yinghui / Xie, Jia et al. | British Library Conference Proceedings | 2022


    Midcourse Guidance and Control for Pulse Motor Boost Missile

    Tang, Mao / Gong, Yinghui / Xie, Jia et al. | Springer Verlag | 2021