Speed, weight, height of an aircraft change during the flight and the parameters of the process vary. The process can be modelled by multiple linear models (multi-model). A robust flight system was designed by two different state-space methods. According to the first method the feedback coefficients were optimised iteratively by non-linear programming till the poles of the closed-loop system achieved a given region (performance trapezium). The second method provides a robust design for a highly flexible aircraft with significant cross-coupling between flight mechanics and structural dynamics modes. This new approach optimises the eigenvalue assignment within a chosen domain in order not to excite the flexible modes. No change in the law structure was envisaged; the problem was solved by optimising the feedback gains (i.e., the eigenvalue assignment). No decoupling was considered during the optimisation phase because of the degrees-of-freedom limitation. However, by initialising the algorithm with a feedback obtained by eigenstructure assignment (making the desired coupling) and by limiting the feedback gain variations at each step, the feedback which was finally obtained, provides acceptable performance. Computer simulations show the performance of the control.


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    Title :

    Robust flight control design with respect to delays, control efficiencies and flexible modes


    Additional title:

    Entwurf einer robusten Flugregelung unter Berücksichtigung der Parameteränderungen und Totzeiten bzw. der Elastizität


    Contributors:
    Livet, T. (author) / Kubica, F. (author) / Magni, J.F. (author)

    Published in:

    Control Engineering Practice ; 3 , 10 ; 1373-1384


    Publication date :

    1995


    Size :

    12 Seiten, 15 Bilder, 3 Tabellen, 13 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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