AIRCRAFT SECONDARY ELECTRIC LOAD CONTROLLING SYSTEM

A method of controlling electrical load power consumption during operation of an aircraft (12) includes determining current operating conditions of the aircraft (12). An engine secondary power extraction limit is determined in response to the current operating conditions. Engine secondary power extr...

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Bibliographische Detailangaben
Hauptverfasser:	BOWMAN, MICHAEL D, CURRIER, THOMAS F, NOZARI, FARHAD
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION CONVERSION OR DISTRIBUTION OF ELECTRIC POWER COSMONAUTICS ELECTRIC EQUIPMENT OR PROPULSION OF ELECTRICALLY-PROPELLEDVEHICLES ELECTRICITY ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES, IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS GENERATION MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES PARACHUTES PERFORMING OPERATIONS SYSTEMS FOR STORING ELECTRIC ENERGY TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE TRANSPORTING VEHICLES IN GENERAL
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Beschreibung
Zusammenfassung:	A method of controlling electrical load power consumption during operation of an aircraft (12) includes determining current operating conditions of the aircraft (12). An engine secondary power extraction limit is determined in response to the current operating conditions. Engine secondary power extraction is determined. Multiple secondary loads (18) are operated in response to the engine secondary power extraction limit and the engine secondary power extraction.