An electric fuse for an aircraft solid-state power controller comprising at least one electric conductor, which is connected between an electric input terminal and an electric output terminal, and which is configured to blow when an electric current (I) flowing through the at least one electric conductor exceeds a predefined threshold (Imax). The at least one electric conductor is encapsulated in a potting and at least one outer surface of the potting is covered with a polymeric coating.
ELECTRIC FUSE FOR AN AIRCRAFT SOLID STATE POWER CONTROLLER AND AIRCRAFT SOLID STATE POWER CONTROLLER COMPRISING AN ELECTRIC FUSE
2024-10-10
Patent
Electronic Resource
English
AIRCRAFT SOLID STATE POWER CONTROLLER AND METHOD OF TESTING AN AIRCRAFT SOLID STATE POWER CONTROLLER
European Patent Office | 2024
|Aircraft solid sate power controller and aircraft electric power supply system
European Patent Office | 2025
|AIRCRAFT SOLID SATE POWER CONTROLLER AND AIRCRAFT ELECTRIC POWER SUPPLY SYSTEM
European Patent Office | 2024
|