ELECTRICAL CONVERSION AND DISTRIBUTION SYSTEM FOR AN AIRCRAFT

The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising at least one synchronous starter-generator (S/G1, S/G2) intended to be coupled to an engine (Engine1) of the aircraft, at least one conversion path comprising a plurality of power convert...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Hadjidj Djemouaï, Casimir Roland, Giorgis Vincent
Format:	Patent
Sprache:	eng
Schlagworte:	CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER CONVERSION OR DISTRIBUTION OF ELECTRIC POWER ELECTRICITY GENERATION SYSTEMS FOR STORING ELECTRIC ENERGY
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Beschreibung
Zusammenfassung:	The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising at least one synchronous starter-generator (S/G1, S/G2) intended to be coupled to an engine (Engine1) of the aircraft, at least one conversion path comprising a plurality of power converters (CVn, CV′n) associated with switching means suitable for supplying at least one charge (CAC1, CAC2, CAC3, CAC4, P1, P2) from at least one source (S/G1, S/G2, AUX S/G1, AUX S/G2, GPU1, GPU2), and at least one distribution path suitable for supplying electrical charges (CT1n, SW1n, CT2n, SW2n).