ROTOR SPEED INDICATION SYSTEMS FOR ROTORCRAFT

ROTOR SPEED INDICATION SYSTEMS FOR ROTORCRAFT

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 configu...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: HALVERSON, Aaron Thomas, OLTHETEN, Erik John
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
AIRCRAFT
ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVEREDIN A SINGLE OTHER SUBCLASS
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
COSMONAUTICS
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
MEASURING
MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE
MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
PARACHUTES
PERFORMING OPERATIONS
PHYSICS
TARIFF METERING APPARATUS
TESTING
TRANSPORTING
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Beschreibung
Zusammenfassung: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.