Electrical power supply system for an aircraft

The invention relates to an electrical power supply system for an aircraft comprising at least one main generator (20) feeding at least one technical load and at least one commercial load through at least one electrical power distribution channel comprising at least one electrical distribution busba...

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Bibliographische Detailangaben
Hauptverfasser:	RICHER JULIEN, ALEJO DOMINIQUE, BAUMANN CEDRIC, PRISSE LUCIEN
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC,OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWERSUPPLY SYSTEMS CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION CONTROL OR REGULATION THEREOF CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUTPOWER CONVERSION OR DISTRIBUTION OF ELECTRIC POWER ELECTRICITY GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS GENERATION REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGYGENERATION, TRANSMISSION OR DISTRIBUTION 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
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Beschreibung
Zusammenfassung:	The invention relates to an electrical power supply system for an aircraft comprising at least one main generator (20) feeding at least one technical load and at least one commercial load through at least one electrical power distribution channel comprising at least one electrical distribution busbar (21, 23, 25) and at least one voltage converter (22, 24, 26), wherein the grounding mode of at least one load is an IT type grounding scheme, with an isolated or high impedance neutral.