A method and control system for an aircraft using a gas turbine engine is provided. The control system includes a controller that includes a load and engine control modules and communicates control signals to a plant that includes a gas generator and a rotor load, an engine estimation module that receives engine state measurements and effector feedback/command signals from the controller and communicates a power turbine torque estimate, and a load estimation module that receives signals including the power turbine torque estimate, a first power turbine speed value, a first power turbine torque value, a second power turbine speed value, a second power turbine torque value, and a rotor speed value. The load estimation module generates one or more of a power turbine speed estimate, a power turbine torque estimate, and a rotor load estimate based on the received signals.


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    Title :

    Load estimation for a twin-engine helicopter


    Contributors:

    Publication date :

    2018-07-31


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    LOAD ESTIMATION FOR A TWIN-ENGINE HELICOPTER

    CAI CHAOHONG / CROWLEY TIMOTHY J / MEISNER RICHARD P | European Patent Office | 2018

    Free access




    ICAS2016_0610: ROTORCRAFT SYSTEMS MODELLING FOR TWIN-ENGINE HEAVY HELICOPTER

    Hashim, F. / Lawson, C. P. / Judt, D. M. | British Library Conference Proceedings | 2016