POWER SUPPLY APPARATUS FOR AEROSPACE ACTUATOR

Abstract

A power supply apparatus for an aerospace actuator includes motor drive electronics for actuation of a motor for control of the aerospace actuator, and an energy storage device. The motor drive electronics are configured to receive input electrical energy from an aircraft power grid, receive electrical energy from the energy storage device and provide electrical energy from the grid and/or from the energy storage device to the motor. The energy storage device is configured to store at least one of: excess electrical energy supplied to the motor drive electronics from the grid and regenerated electrical energy from the motor drive electronics. The energy storage device is configured to discharge the stored energy as electrical energy to the motor drive electronics when required.

Claims

1. A power supply apparatus for an aerospace actuator, comprising: motor drive electronics for actuation of a motor for control of the aerospace actuator; and an energy storage device; wherein the motor drive electronics are configured to: receive input electrical energy from an aircraft power grid; receive electrical energy from the energy storage device; and provide electrical energy from the grid and/or from the energy storage device to the motor; and wherein the energy storage device is configured to store at least one of: excess electrical energy supplied to the motor drive electronics from the grid; and regenerated electrical energy from the motor drive electronics; and wherein the energy storage device is configured to discharge the stored energy as electrical energy to the motor drive electronics when required.

2. A power supply apparatus as claimed in claim 1, wherein the energy storage device comprises a battery.

3. A power supply apparatus as claimed in claim 2, wherein the battery comprises a lithium ion battery.

4. A power supply apparatus as claimed in claim 1, wherein the energy storage device comprises a supercapacitor.

5. A power supply apparatus as claimed in claim 1, comprising a bi-directional power converter for controlling the flow of power between the motor drive electronics and the energy storage device.

6. A power supply apparatus as claimed in claim 1, configured such that motor drive electronics can: (i) receive input electrical energy from the aircraft power grid at the same time as receiving electrical energy from the energy storage device, (ii) receive input electrical energy only from the aircraft power grid, or (iii) receive input electrical energy only from the energy storage device.

7. An aircraft comprising: at least one actuator; and a power supply apparatus as claimed in claim 1, for supplying power to the actuator.

8. An aircraft as claimed in claim 7, comprising multiple actuators with each actuator having associated motor drive electronics and an energy storage device being connected with each of the motor drive electronics.

9. A method for supplying power to an aerospace actuator of an aircraft using a power supply apparatus comprising motor drive electronics and an energy storage device; the method comprising: receiving input electrical energy from a grid at the motor drive electronics; storing in the energy storage device at least one of: excess electrical energy supplied to the motor drive electronics from the grid; and regenerated electrical energy from the motor drive electronics; discharging electrical energy from the energy storage device to the motor drive electronics when required; and using the motor drive electronics to provide electrical energy from the grid and/or from the energy storage device to a motor for control of the aerospace actuator.

10. A method as claimed in claim 9, further comprising: using a power supply that includes: motor drive electronics for actuation of a motor for control of the aerospace actuator; and an energy storage device; wherein the motor drive electronics are configured to: receive input electrical energy from an aircraft power grid; receive electrical energy from the energy storage device; and provide electrical energy from the grid and/or from the energy storage device to the motor; and wherein the energy storage device is configured to store at least one of: excess electrical energy supplied to the motor drive electronics from the grid; and regenerated electrical energy from the motor drive electronics; and wherein the energy storage device is configured to discharge the stored energy as electrical energy to the motor drive electronics when required.

11. A method as claimed in claim 9, further comprising preventing discharged energy from the energy storage device from leaking into the grid.

12. A method as claimed in claim 9, wherein the energy supplied by the energy storage device to the motor for control of the aerospace actuator is in addition to or in excess of energy already supplied by the grid.

13. A method as claimed in claim 12, wherein the energy supplied by the energy storage device to the motor for control of the aerospace actuator is in addition to energy regenerated in the motor drive electronics.

14. A method as claimed in claim 12, comprising using the energy storage device to provide higher peak power levels to the aircraft actuator than the power levels that are possible without the energy storage device.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Preferred embodiments of the present disclosure will now be described by way of example only and with reference to the accompanying drawing, in which:

[0030] FIG. 1 shows a power supply apparatus for an actuator, the power supply apparatus including an energy storage device.

DETAILED DESCRIPTION

[0031] As shown in FIG. 1, an aircraft comprises a prime mover 2, in the form of an engine. The prime mover 2 causes a generator 4 to generate power, which is supplied to a grid 6. The power is distributed to multiple actuator power supplies 10, 20, 30 in the grid 6 via single phase or 3-phase power distribution lines 8. The distributed power is usually 3-phase AC power at 115V, or single-phase AC power at 230V AC. In the latter case, the power distribution lines 8 are a voltage bus.

[0032] In each actuator power supply 10, 20, 30, there is an AC/DC converter 11 to convert the input power into DC power. This DC power can be passed via motor drive electronics 12 to an electric motor 13 of an actuator 14. Connected to the motor drive electronics 12 is a bi-directional power converter 15. This controls the flow of power between the motor drive electronics 12 and an energy storage device 17, which takes the form of a battery in this example. The bi-directional power converter 15 also allows for power to pass from the grid 6 to the energy storage device 17 as well as permitting power to flow in the opposite direction from the energy storage device 17 to the motor drive electronics 12. A circuit breaker 16 is provided to ensure that the motor drive electronics 12 are not overloaded by a power surge from the energy storage device 17 as it discharges.

[0033] The bi-directional power converter 15 allows movement of electrical energy from the input energy supplied by the grid 6 to the energy storage device 17 for storage in the energy storage device 17. This occurs for example when the energy supplied by the grid 6 to the motor drive electronics exceeds the requirements of the motor drive electronics 12, such as when there is no requirement to drive the motor 13, or when the motor 13 requires a smaller electrical current than can be provided from the grid 6. In this case, the excess electrical energy can pass through the bi-directional power converter 15 to be stored in the energy storage device 17. If the energy storage device 17 is already at full capacity then the bi-directional power converter 15 may prevent further excess energy passing to the energy storage device 17.

[0034] The bi-directional converter 15 allows flow of power in the reverse direction, when it is desired to drive the motor 13 without drawing energy from the grid 6 and/or when the energy being supplied by the grid 6 to the motor drive electronics 12 is insufficient for the requirements of the motor 12 and should be supplement by energy from the energy storage device 17. In this case, previously stored energy from the energy storage device 12 is discharged through the bi-directional power converter 15 and delivered to the motor drive electronics 12 for powering the motor 13 as required.

[0035] The term about is intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application.

[0036] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms a, an and the are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms comprises and/or comprising, when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof.

[0037] While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.