Systeme und Verfahren zum Fehlerschutz

Details

Veröffentlichungs-Nr.

EP4790860

Anmeldetag

19. Januar 2026

Veröffentlichung

12. August 2026

Rechtsraum

EP

IPC

H02H3/16, // H02H7/26

Abstract

A system and method for fault protection are described herein. An electrical power system architecture (100) for an aircraft includes at least one electrical source (102), at least one electrical load (112), and a power distribution system (106) connecting the at least one electrical source (102) to the at least one electrical load (112). The power distribution system (106) is grounded to an electrical ground (118) of the aircraft through a high impedance grounding circuit (108) and a plurality of protection devices (124) are coupled electrically upstream and downstream of the high impedance grounding circuit (108). In some approaches, the electrical power system architecture (100) includes a fault detection circuit (126) configured to detect a fault and a controller (128) to selectively open or close the plurality of protection devices (124) based on the detected fault. In some approaches, an electrical wiring interconnection system separates positive power 1(114) and negative power lines (116) of the power distribution system (106) for reducing line-to-line faults.

Anmelder

Firma

GE Aviation Systems Limited

Land

🇬🇧 Großbritannien

Fachgebiete