An investigation was made to determine if the dynamics of an aerospace vehicle might be identified more readily if represented in some other form than a z-transform. An analysis and simulation performed indicate that a representation in terms of linear band-pass filters is preferable. An investigation was made of an implicit response matching technique applicable to both identification and synthesis, which form the bases for self-adaptive control. In a digital simulation the implicit technique was able to simultaneously identify five parameters of a typical aerospace vehicle within 2 seconds without noise, and within 5 seconds with 30 percent noise. An investigation and digital simulation was made of a hybrid digital adaptive flight control system which uses the implicit technique. The system identified 4 parameters of a typical vehicle, and adjusted 2 parameters of the flight control system to provide optimum response. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Digital Adaptive Flight Control System, Phase II


    Contributors:

    Publication date :

    1964


    Size :

    2 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Digital adaptive flight control

    Andeen, R.E. | Engineering Index Backfile | 1963


    DIGITAL ADAPTIVE FLIGHT CONTROL SYSTEM FOR AEROSPACE VEHICLES

    ANDEEN, R. E. / SHIPLEY, P. P. | AIAA | 1963


    Digital adaptive flight control system for aerospace vehicles

    Andeen, R.E. / Shipley, P.P. | Engineering Index Backfile | 1963


    Digital Adaptive Model following Flight Control

    Gurbux S. Alag / Howard Kaufman | AIAA | 1975


    Digital adaptive model following flight control

    ALAG, G. / KAUFMAN, H. | AIAA | 1974