The paper presents the application of linear quadratic regulator (LQR) theory to the control of change of state of an aircraft turbine engine from rated to maximum. On the basis of the engine digital simulator, an optimal regulator of change of state is designed. The results of simulation of the optimal control system show that: during transient process, maximum rotor speed deviation is decreased from 148 rpm to 4.5 rpm, thrust settling time is shortened from 7 seconds to 4 seconds, and transient response of turbine outlet temperature is refined from small overshot to monotonic, as compared with the original hydromechanical control system, thus, the improvement is apparent.


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    Title :

    Optimal control of change of state of aircraft turbine engine


    Additional title:

    Optimale Steuerung der Zustandsaenderung einer Flugzeugturbine


    Contributors:

    Published in:

    ASME-Papers ; Sep ; 1-8


    Publication date :

    1985


    Size :

    8 Seiten, 6 Bilder, 14 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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