| 摘要 |
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). |
