Adaptive two-axis acceleration control and roll stabilization of air-to-air missile is analyzed and simulated; adaptive principle consists of relocating open loop zeros to region of S-plane having prescribed damping and frequency characteristics, and cyclically increasing forward loop gain to drive control surface actuator poles across imaginary axis at fixed frequency; factors to consider in application and mechanization of control system are presented.


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    Title :

    Design, analysis and simulation of self-adaptive acceleration flight control system


    Additional title:

    AIAA -- Simulation Aerospace Flight Conference -- Tech Papers


    Contributors:

    Conference:

    AIAA -- Simulation for Aerospace Flight Conference ; 1963 Control



    Publication date :

    1963


    Size :

    9 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English