System and method for supplying power for actuators on board an aircraft
AssigneeAirbus France
InventorsOlivier Langlois, Etienne Foch, Lucien Prisse, Xavier Roboam
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Abstract
The invention relates to a system and a method for supplying power to an aircraft comprising several generators supplying alternating current to several different primary electrical master boxes (10, 11, 12 and 13), the various aircraft loads being connected to each of these master boxes. This system comprises conventional master boxes (10, 11, 12 and 13) which supply power loads and at least one master box (40, 41) devoted to actuator loads, this at least one devoted master box being connected to conventional master boxes.
Claims17
A system for supplying power to a plurality of actuators on board an aircraft, the system comprising:
- a plurality of generators to supply alternating current;
- a plurality of conventional electrical master boxes configured to supply power to power loads, the plurality of conventional electrical master boxes having a plurality of power transfer units and being positioned at a first and second side of the aircraft, the power loads including air conditioning units, units to protect against icing and engine starters;
- and
- two devoted master boxes configured
- to each receive power from at least one conventional electrical master box via the plurality of power transfer units, and
- to supply the power only to actuator loads, the two devoted master boxes being connected to the plurality of conventional electrical master boxes at the first and second side of the aircraft, the actuator loads including flight control and wheel brakes.
A method for supplying power to a plurality of actuators on board an aircraft, the method comprising:
- supplying, from a plurality of generators on the aircraft, alternating current;
- supplying, from a plurality of conventional electrical master boxes on the aircraft, power to power loads, the plurality of conventional electrical master boxes having a plurality of power transfer units and being positioned at a first and second side of the aircraft, the power loads including air conditioning units, units to protect against icing and engine starters;
- receiving, at each of two devoted master boxes on the aircraft, power from at least one conventional electrical master box via the plurality of power transfer units;
- and
- supplying, from the two devoted master boxes, the power only to actuator loads, the two devoted master boxes being connected to the plurality of conventional electrical master boxes at the first and second side of the aircraft, the actuator loads including flight control and wheel brakes,
- wherein a first bidirectional power transfer is provided between at least one devoted master box and an electric circuit for the actuators.
An aircraft comprising:
- a system to supply power to a plurality of actuators on board an aircraft, the system including
- a plurality of generators configured to supply alternating current,
- a plurality of conventional electrical master boxes configured to supply power to power loads, the plurality of conventional electrical master boxes having a plurality of power transfer units and being positioned at a first and second side of the aircraft, the power loads including air conditioning units, units to protect against icing and engine starters, and
- two devoted master boxes configured
- to each receive power from at least one conventional electrical master box via the plurality of power transfer units, and
- to supply the power only to actuator loads, the two devoted master boxes being connected to the plurality of conventional electrical master boxes at the first and second side of the aircraft, the actuator loads including flight control and wheel brakes.
Dependencies are inferred from the claim text.