Distributed hybrid electric propulsion system optimization method and device

The invention belongs to the technical field of engine design, and particularly relates to a distributed hybrid electric propulsion system optimization method and device. The method comprises the following steps: giving an initial aircraft layout; determining a thrust demand of the propulsion system...

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Bibliographische Detailangaben
Hauptverfasser:	SU GUIYING, HE JIAQIAN, RUI CHANGSHENG
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR PARACHUTES PERFORMING OPERATIONS TRANSPORTING
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Beschreibung
Zusammenfassung:	The invention belongs to the technical field of engine design, and particularly relates to a distributed hybrid electric propulsion system optimization method and device. The method comprises the following steps: giving an initial aircraft layout; determining a thrust demand of the propulsion system; giving an initial ratio of the main thrust to the auxiliary thrust; determining the main thrust of a turbofan engine and the auxiliary thrust of each electric drive fan; determining the power of the electrically driven fan; according to the power of the electric drive fan, determining the extraction power obtained from the turbofan engine; determining the oil consumption rate of the turbofan engine; determining the oil consumption rate of the propulsion system; and judging the reduction degree of the oil consumption rate of the propulsion system compared with the oil consumption rate of the original turbofan engine, and if the reduction degree of the oil consumption rate of the propulsion system compared with the