SYSTEM AND METHOD FOR OPERATING A ROTORCRAFT

The present disclosure provides methods and systems for operating a rotorcraft (100) comprising a plurality of engines (102, 104) configured to provide motive power to the rotorcraft (100). A request to enter into an asymmetric operating regime (AOR), in which at least one first engine of the plural...

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Bibliographische Detailangaben
Hauptverfasser:	MANOUKIAN, Patrick, BEAUCHESNE-MARTEL, Philippe
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The present disclosure provides methods and systems for operating a rotorcraft (100) comprising a plurality of engines (102, 104) configured to provide motive power to the rotorcraft (100). A request to enter into an asymmetric operating regime (AOR), in which at least one first engine of the plurality of engines (102, 104) is an active engine (102) and is operated in an active mode to provide motive power to the rotorcraft (100) and at least one second engine of the plurality of engines (102, 104) is a standby engine (104) and is operated in a standby mode to provide substantially no motive power to the rotorcraft (100), is obtained. A power capability of the active engine (102) of the rotorcraft (100) is determined. The power capability is compared to a current power demand for the rotorcraft (100). When the current power demand is greater than the power capability of the active engine (102), a standby-engine power output of the standby engine (104) of the rotorcraft (100) is reduced, and the reduction in the standby-engine power output is compensated for by adjusting an active-engine power output of the active engine (102) and/or at least one flight control of the rotorcraft (100).