Aircraft may be considered as systems with nonlinear dynamics, affected by several variables. The aircraft's response characteristics vary and depend on several factors and conditions, such as type of the aircraft, flight condition, aircraft configuration, and presence of atmospheric turbulence or gusts. Designing an automatic flight control system for such an aircraft, which maintains good flying performance over the entire operational flight envelope of the aircraft, is a difficult and time consuming task, as parameters vary with each condition. Currently, to overcome this problem, the design is done using gain-scheduling technique, where the controller gains or parameters are scheduled using air data variables to adjust to variation of those conditions. However, this technique becomes cumbersome when the number of possible operating conditions is very large. Furthermore, this technique may not be appropriate to solve the problem when the aircraft configuration changes drastically, as when sudden malfunction of or damage to the flight control system occurs. In this thesis, prospects of one particular adaptive control scheme are evaluated for possible application, which is the Self-Tuning Controller (STC) method. This method consists of a recursive parameter estimation algorithm combined with a control law design algorithm. The recursive parameter estimation uses the Recursive Least-Squares method with an adaptive forgetting factor which is calculated through the multiple model (XAFMM) approach. In addition, a switching algorithm is used to overcome the identifibility problem whenever aircraft experiences non-persistently exciting input signals.


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    Title :

    Adaptive Self-Tuning Flight Control systems. The Multiple Model Approach


    Contributors:
    Z. Abidin (author)

    Publication date :

    1998


    Size :

    244 pages



    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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