Architecture and a multiple function power converter for aircraft

A method and apparatuses are implemented for electric power systems. An apparatus for power conversion according to one embodiment comprises: a multiple function power converter (77), the multiple function power converter (77) being capable of performing functions of a static inverter, and being cap...

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Bibliographische Detailangaben
Hauptverfasser:	PEARSON WAYNE T, MCGINLEY RAY M, DIVITO ROCCO, ANGHEL CRISTIAN E
Format:	Patent
Sprache:	eng
Schlagworte:	CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER CONVERSION OR DISTRIBUTION OF ELECTRIC POWER ELECTRIC EQUIPMENT OR PROPULSION OF ELECTRICALLY-PROPELLEDVEHICLES ELECTRICITY ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES, IN GENERAL GENERATION MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES PERFORMING OPERATIONS SYSTEMS FOR STORING ELECTRIC ENERGY TRANSPORTING VEHICLES IN GENERAL
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Beschreibung
Zusammenfassung:	A method and apparatuses are implemented for electric power systems. An apparatus for power conversion according to one embodiment comprises: a multiple function power converter (77), the multiple function power converter (77) being capable of performing functions of a static inverter, and being capable of at least one of performing functions of a motor controller, and performing functions of a start converter to use a generator as a starter. An architecture system for aircraft according to another embodiment comprises: one or more rectifiers (408), wherein the one or more rectifiers (408) receive at least one high frequency AC power input; and a plurality of power conversion devices (78) optionally connectable to drive at least one high frequency generator (105) as a starter and at least one load, the input of each power conversion device (78) being connected to at least one rectifier (408).