Gain compensation of aerodynamic missile control systems operating over dynamic pressure (q) range of 10 to 1 is discussed and engineering compromise struck between control surface sizing and low dynamic pressure performance when employing q 1/2 compensation is pointed out; illustrative example, controlling small, high-performance missile frame is developed; stability and transient response of system are evaluated at extremes of 10 to 1 dynamic pressure range; limitations of approach, restricting it in application to missiles with predictable control surface center-of-pressure and low actuation torque requirements, are presented.


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    Titel :

    Missile autopilot adaption using control-surface hinge-moment feedback


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Leondes, C.T. (Autor:in) / Pearson, J.L. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1968


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



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