Aircraft Electrical System Operating Method

A method of controlling an aircraft electrical system (40). The electrical system (40) comprises an alternating current electrical machine (56, 58) comprising a plurality of phases, each phase having a power rating, the electrical machine (56, 58) being configured to operate on failure of one or mor...

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Bibliographic Details
Main Authors Edwards, Huw, Vyas, Parag
Format Patent
LanguageEnglish
French
German
Published 29.07.2020
Subjects
CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORSOR DYNAMO-ELECTRIC CONVERTERS
CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
ELECTRICITY
GENERATION
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Summary:A method of controlling an aircraft electrical system (40). The electrical system (40) comprises an alternating current electrical machine (56, 58) comprising a plurality of phases, each phase having a power rating, the electrical machine (56, 58) being configured to operate on failure of one or more phases. The method comprises: determining a power requirement; sensing a fault of one or more phases of the electrical machine (56, 58), and controlling the electrical machine (56, 58) to operate in a fault condition, in which the remaining phases of the electrical machine (56, 58) provide the electrical power requirement; and providing an overrating signal to a flight computer (66) of the aircraft (2) where the power provided by each phase exceeds the power rating of the respective phase.
Bibliography:Application Number: EP20140163813