Architektur eines Elektrischen Antriebssystems

Details

Veröffentlichungs-Nr.

EP4797484

Anmeldetag

4. Februar 2026

Veröffentlichung

26. August 2026

Rechtsraum

EP

IPC

H02J4/00, B64D27/35, H02H7/26

Abstract

An electric distribution architecture is described herein. In some embodiments, the electric distribution architecture (300) for an aircraft (100) includes at least one electrical source (314, 324), a plurality of loads (348) including at least one high energy load (350) and at least one low energy load (354) and a power distribution system (332). The power distribution system (332) includes a plurality of contactors (338, 340, 342) configured to selectively distribute electrical power from each of the at least one electrical source (314, 324) to each of the plurality of loads (348). In some approaches, at least one first fast acting high energy protection device (316, 326) is electrically coupled in series with each at least one electrical source (314, 324), and at least one second fast acting high energy protection device (358) is electrically coupled in series with each of the at least one high energy loads (350). In some approaches, the power distribution system (332) is devoid of any high energy protection devices (316, 326, 352).

Anmelder

Firma

GE Aviation Systems Limited

Land

🇬🇧 Großbritannien

Fachgebiete