AIRCRAFT ELECTRICAL ACTUATOR ARRANGEMENT

• US 20100252691A1
• Filed: 03/25/2010
• Published: 10/07/2010
• Est. Priority Date: 04/01/2009
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: MALKIN, Peter, TRAINER, David R.
• Granted Patent: US 8,698,444 B2
• Time in Patent Office: Days
• US Class Current: 244/76.R
• CPC Class Codes: F16H 25/20 Screw mechanisms with automatic reversal F16H25/12
• CPC Class Codes: H02J 2310/44 for aircrafts
• CPC Class Codes: H02J 3/14 by switching loads on to, or off from, network, e.g. progressively balanced loading
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

An aircraft (40) electrical actuator arrangement comprises a plurality of electrical actuators (11) coupled to an electrical power distribution network, the electrical power distribution network has a master power converter (1) to convert electrical power from the electrical power distribution network for supply to each electrical actuator (11). The electrical actuators (11) comprise an environmental control system actuator (68), an aileron actuator (78), a flap actuator (70), a slat actuator (72), a landing gear actuator (76), a thrust reverser actuator (74), a brake actuator (80) and a taxiing actuator (82). A controller is coupled to the master power converter (1). The controller is arranged to allow the supply of electrical power from the master power converter (1) to the environmental control system actuator (68) during a first mode of operation of the aircraft (40). The controller is arranged to allow the supply of electrical power from the master power converter (1) to at least one of the aileron, the flap, the slat, the landing gear, the thrust reverser, the brake actuator or the taxiing actuator (78, 70,72, 76, 74, 80, 82) during a second mode of operation of the aircraft (40).

Claims

1. An aircraft electrical actuator arrangement comprising a plurality of electrical actuators coupled to an electrical power distribution network, the electrical power distribution network having at least one master power converter to convert electrical power from the electrical power distribution network for supply to each electrical actuator, the electrical actuators comprising at least one environmental control system actuator, at least one aileron actuator, at least one flap actuator, at least one slat actuator, at least one landing gear actuator, at least one thrust reverser actuator, at least one brake actuator and at least one taxiing actuator, a controller being coupled to the master power converter coupled, the controller being arranged to allow the supply of electrical power from the master power converter to the at least one environmental control system actuator during a first mode of operation of the aircraft, the controller being arranged to allow the supply of electrical power from the master power converter to at least one of the at least one aileron actuator, the at least one flap actuator, the at least one slat actuator, the at least one landing gear actuator, the at least one thrust reverser actuator, the at least one brake actuator or the at least one taxiing actuator during a second mode of operation of the aircraft.

2. An aircraft electrical actuator arrangement as claimed in claim 1 wherein the first mode of operation is cruise or high speed flight and the second mode of operation is landing, take off or taxiing.

3. An aircraft electrical actuator arrangement as claimed in claim 1 wherein in the second mode of operation the controller being arranged to allow the supply of electrical power sequentially from the master power converter to the at least one flap actuator and/or the at least one slat actuator, the at least one landing gear actuator, the at least one thrust reverser actuator, the at least one brake actuator and the at least one taxiing actuator.

4. An aircraft electrical actuator arrangement as claimed in claim 1 wherein in the second mode of operation the controller being arranged to allow the supply of electrical power sequentially from the master power converter to the at least one taxiing actuator, the at least one brake actuator, the at least one flap actuator and/or the at least one slat actuator and the at least one landing gear actuator.

5. An aircraft electrical actuator arrangement as claimed in claim 1 wherein there is a plurality of electrical actuators arranged in functional groups.

6. An aircraft electrical actuator arrangement as claimed in claim 5 wherein the functional groups are defined by potential use sequence or lack of likelihood of simultaneous demand or a similar electrical actuator demand requirement.

7. An aircraft electrical actuator arrangement as claimed in claim 6 wherein the functional groups can be prioritised.

8. An aircraft electrical actuator arrangement as claimed in claim 1 wherein the electrical power distribution network is coupled to electrical power generators having different electrical supply values.

9. An aircraft electrical actuator arrangement as claimed in claim 1 wherein the electrical actuators have individual and specific electrical power requirements achieved by reconfiguration of the master power converter.

10. An aircraft electrical actuator arrangement as claimed in claim 1 wherein the electrical actuators are provided with electrical power in a sequence determined by the controller in the second mode of operation.

11. An aircraft electrical actuator arrangement as claimed in claim 1 wherein the at least one electrical actuator is provided with electrical power by the master power converter for a fixed time period.

12. An aircraft electrical actuator arrangement as claimed in claim 11 wherein the fixed time period is one second.

13. An aircraft electrical actuator arrangement as claimed in claim 1 wherein an electrical actuator is provided with a mechanical lock to retain position.

15. An aircraft electrical actuator arrangement as claimed in claim 1 wherein an actuator comprises an electrical motor.

16. An aircraft electrical actuator arrangement as claimed in claim 15 wherein the electric motor is a stepping motor and the master power converter provides electrical power for each step of the stepping motor.

17. An aircraft electrical actuator arrangement as claimed in claim 1 wherein the master power converter comprises an AC to DC converter and a DC to AC converter.

14. An aircraft electrical actuator arrangement as claimed in 13 wherein the mechanical lock is releasable by the controller.

18. A method of operating an aircraft electrical actuator arrangement, the aircraft electrical actuator arrangement comprising a plurality of electrical actuators coupled to an electrical power distribution network, the electrical power distribution network having at least one master power converter to convert electrical power from the electrical power distribution network for supply to each electrical actuator, the electrical actuators comprising at least one environmental control system actuator, at least one aileron actuator, at least one flap actuator, at least one slat actuator, at least one landing gear actuator, at least one thrust reverser actuator, at least one brake actuator and at least one taxiing actuator, the method comprising supplying electrical power from the master power converter to the at least one environmental control system actuator during a first mode of operation of the aircraft and supplying electrical power from the master power converter to at least one of the at least one aileron actuator, the at least one flap actuator, the at least one slat actuator, the at least one landing gear actuator, the at least one thrust reverser actuator, the at least one brake actuator and the at least one taxiing actuator in a second mode of operation of the aircraft.

19. A method as claimed in claim 18 wherein the first mode of operation is cruise or high speed flight and the second mode of operation is landing, take off or taxiing.

20. A method as claimed in claim 18 wherein the second mode of operation comprises supplying electrical power sequentially from the master power converter to the at least one flap actuator and/or the at least one slat actuator, the at least one landing gear actuator, the at least one thrust reverser actuator, the at least one brake actuator and the at least one taxiing actuator.

21. A method as claimed in claim 18 wherein the second mode of operation comprises supplying electrical power sequentially from the master power converter to the at least one taxiing actuator, the at least one brake actuator, the at least one flap actuator and/or the at least one slat actuator and the at least one landing gear actuator.

22. A method as claimed in claim 18 comprising supplying electrical power from the master power converter to the electrical actuators in a sequence determined by a controller.

23. A method as claimed in claim 18 comprising supplying electrical power from the master power converter to the electrical actuators for a fixed time period.

24. A method as claimed in claim 23 wherein the fixed time period is one second.