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.
Optimal control of change of state of aircraft turbine engine
Optimale Steuerung der Zustandsaenderung einer Flugzeugturbine
ASME-Papers ; Sep ; 1-8
1985
8 Seiten, 6 Bilder, 14 Quellen
Aufsatz (Konferenz)
Englisch
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