Electrical distribution system for aircraft and associated method
AssigneeSafran Electrical & Power
InventorsVincent CHAPERON, Florence GIRAULT
Life of this patent
Estimating the term…
Abstract
An electrical distribution system configured to supply power to at least a first electric motor and a second electric motor from at least a first electrical source and a second electrical source, including at least a first switch and a second switch, each switch including at least a first power supply bus and a second power supply bus, at least one electrical reconfiguration line connecting the first switch to the second switch, the electrical reconfiguration line including at least one reconfiguration switch configured to be switched into the closed position in the event of a fault in one of the electrical sources.
Claims11
An electrical distribution system configured to supply power to at least a first electric motor and a second electric motor from at least a first electrical source and a second electrical source, each of the electric motor motors being a propulsion motor of an aircraft, each of the electric motors motor comprising at least a first electrical star and a second electrical star configured to be independently power supplied, each of the electrical sources having a defined nominal power, each of the electrical sources comprising at least a first power supply output and a second power supply output having a defined elementary power lower than the defined nominal power, the electrical distribution system comprising:
- at least a first commutator and a second commutator, each of the commutators being associated with one of the electrical sources and one of the electric motors,
- each of the commutators comprising at least a first power supply bus and a second power supply bus configured to supply power respectively to the first electrical star and the second electrical star of the electric motor associated with the commutator,
- the first power supply bus and the second power supply bus of each of the commutators being configured to be power supplied respectively by the first power supply output and by the second power supply output of the electrical source associated with the commutator, the power supply buses being power supplied independently with the elementary power,
- at least one electrical reconfiguration line connecting the first commutator to the second commutator, the electrical reconfiguration line comprising at least one reconfiguration switch configured to be active in a closed position in an event of a fault in one of the electrical sources.
Dependencies are inferred from the claim text.