A linearizing transformation technique developed for the control of nonlinear systems is applied to the autopilot design of air-to-air missile systems. The plant inversion characteristic of this methodology is clearly displayed, and stability problems associated with nonminimum-phase plants are identified. To avoid the difficulty associated with the non-minimum-phase dynamics of missile acceleration, the plant inversion is first applied to the control of angle-of-attack and sideslip. Owing to simplifications made by the plant inversion, a point design is enough to provide the desired closed-loop responses for all fight conditions. Normal and lateral accelerations are then controlled by the classical integral feedback. The gain-scheduling required is minimal and transparent. The procedure is applied to the autopilot design of skid-to-turn and bank-to-turn missiles to obtain satisfactory performance of both missile designs.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Applications of plant inversion via state feedback to missile autopilot design


    Additional title:

    Anwendung der Zustandsruckfuehrung beim Entwurf eines Raketen-Autopilots


    Contributors:
    Tahk, M. (author) / Briggs, M.M. (author) / Menon, P.K.A. (author)


    Publication date :

    1988


    Size :

    6 Seiten, 8 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Missile autopilot designs using full state feedback

    Inaishi, Sadamu / Obana, Kazumitsu / Aizawa, Yasutaka | TIBKAT | 1992


    BTT missile autopilot design based on dynamic inversion

    Yan, Z. / Chaoyang, D. / Ping, Z. et al. | British Library Online Contents | 2007




    A Missile Autopilot Based on Feedback Linearization

    Devaud, E. / Siguerdidjane, H. | British Library Online Contents | 2002