Solid State Power Controller For An Aircraft

A solid state power controller 100 for an aircraft has a solid state switching device 110 for activating an electrical power bus 160, a control unit 120 for controlling the solid state switching device 110, and a current sensing circuit 150 for monitoring current flowing in the bus 160. The current...

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Bibliographic Details
Main Author JULIAN PETER MAYES
Format Patent
LanguageEnglish
Published 27.05.2015
Subjects
CONTROL OR REGULATING SYSTEMS IN GENERAL
CONTROLLING
FUNCTIONAL ELEMENTS OF SUCH SYSTEMS
MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS ORELEMENTS
PHYSICS
REGULATING
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Summary:A solid state power controller 100 for an aircraft has a solid state switching device 110 for activating an electrical power bus 160, a control unit 120 for controlling the solid state switching device 110, and a current sensing circuit 150 for monitoring current flowing in the bus 160. The current sensing circuit 150 includes a sensing fuse 140, and may measure the voltage across the fuse 140. The fuse 140 may comprise a fuse wire connected to a solder joint. An amplifier 130 may boost the current sense signal. The fuse 140 provides an additional failsafe in the event that the solid state switching device 110 fails to disconnect the power bus 160 in an over-current or surge event. A current sensing resistor is not therefore required and fewer components are used. An aircraft comprising such a power controller and a method of use are disclosed.
Bibliography:Application Number: CN201410670949