A rotor speed indication system configured to communicate a rotor speed operating range for a twin engine rotorcraft (10) having a rotor (12) during one engine inoperable conditions. The rotor speed indication system includes a governing reference indicator (70) located on a display (40) and configured to communicate an upper operating range threshold. A droop reference indicator (100) located on the display (40) and configured to communicate a lower operating range threshold. A sensor (32) configured to measure a current rotor speed of the rotor (12). A dynamic rotor speed indicator (68) located on the display (40) and configured to communicate the current rotor speed of the rotor (12) such that when the dynamic rotor speed indicator is positioned between the governing reference indicator (70) and the droop reference indicator (100) on the display, the current rotor speed of the rotor is within the rotor speed operating range.


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    Title :

    ROTOR SPEED INDICATION SYSTEMS FOR ROTORCRAFT


    Additional title:

    ROTORGESCHWINDIGKEITSANZEIGESYSTEME FÜR DREHFLÜGLER
    SYSTÈMES D'INDICATION DE VITESSE DE ROTOR DE GIRAVION


    Contributors:

    Publication date :

    2020-06-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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