A method and control system for an aircraft engine comprising a gas turbine driving a fan propeller with a mechanical gear-train and a dedicated pitch change mechanism for the fan propeller includes a fuel flow signal input; a pitch change mechanism signal input; a controlled plant for relating a pitch change mechanism pitch angle (BetaP) and a fuel flow (Wf) to at least two controlled outputs and a set of constraints. A decoupling control decoupling the controlled plant and/or the constraints into two separate single-input single-output (SISO) control loops for the first and second controlled outputs and a decoupling control decoupling the constraints from the decoupled controlled outputs and the constraints from one another provide gas turbine and fan propeller coordinate control while coordinately controlling constraints and outputs. A feedforward control can compensate the load change effect on engine speed and fan propeller rotor speed control.
METHOD AND SYSTEM FOR MODEL BASED CONTROL FOR VARIABLE PITCH FAN ENGINES AND TURBO-SHAFT, TURBO-PROPELLER ENGINES
METHODE ET SYSTEME DE COMMANDE FONDEE SUR UN MODELE POUR REACTEURS A DOUBLE FLUX A PAS VARIABLE ET TURBOMOTEURS TURBOPROPULSEURS
2016-03-30
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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