Aircraft electric power distribution systems and methods 80 of operating aircraft electrical power distribution systems are provided. One such method 80 comprises determining a measure of an electrical power demand of a power and propulsion system 300 of the aircraft; setting a target operating voltage of the aircraft electrical power distribution system based at least in part on the measure of the electrical power demand; and controlling the operating voltage in accordance with the set target operating voltage. In some embodiments the measure of the electrical power is a measure of an operating parameter of a gas turbine engine 101, 201 or propulsor 204 of the aircraft. The operating parameter may include one or more of: a speed of an airflow through the gas turbine engine 101, 201 or propulsor 204; a rotational speed of a spool of the gas turbine engine 101, 201 or propulsor 204; a rate of fuel flow into a combustor of the gas turbine engine 101, 201; a pressure in the gas turbine engine 101, 201 or propulsor 204; and a temperature in the gas turbine engine 101, 201 or propulsor 204.
AIRCRAFT ELECTRICAL POWER DISTRIBUTION
ELEKTRISCHE ENERGIEVERTEILUNG EINES FLUGZEUGS
DISTRIBUTION D'ÉNERGIE ÉLECTRIQUE D'UN AÉRONEF
19.10.2022
Patent
Elektronische Ressource
Englisch
ADAPTIVE AIRCRAFT ELECTRICAL POWER DISTRIBUTION SYSTEM
Europäisches Patentamt | 2024
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