NEAR SYNCHRONOUS CONTROLLED INDUCTION MOTOR DRIVE ACTUATION SYSTEM

• US 20120018578A1
• Filed: 07/21/2011
• Published: 01/26/2012
• Est. Priority Date: 07/22/2010
• Status: Active Grant

• Current Assignee: Parker Intangibles LLC (Parker-Hannifin Corporation)
• Original Assignee: Parker-Hannifin Corporation
• Inventors: Polcuch, Eric A.
• Granted Patent: US 9,190,942 B2
• Time in Patent Office: Days
• US Class Current: 244/99.2
• CPC Class Codes: H02P 8/40 Special adaptations for controlling two or more stepping motors

Abstract

A distributed electromechanical actuation system including multiple electromechanical actuators intended to operate together in a synchronous (or near synchronous) manner. Each individual actuator is powered by one or more induction motors or other appropriate motor such as a stepper motor. The induction motors are designed to have a very high pullout torque with very low slippage to the pull out point. The group of actuators is controlled from a single controller (e.g., an induction motor controller) that utilizes a Volts per Hertz type of open loop control where the bus voltage and frequency are controlled to assure that the motors always operate on the low slip side of the pull out point performance curve.

Claims

1. A control system for controlling a plurality of actuators, the system comprising:

a plurality of actuators for actuating movement of one or more adjustable components of an aircraft, wherein each actuator has a first end coupled to a structure of the aircraft and a second end coupled to one of the one or more adjustable components and each actuator additionally includes a motion control assembly that includes a drive path from a motion provider to the one adjustable component, wherein the one or more components is configured to move along a respective drive path; and

a controller operable to output motor drive power through a common bus to a plurality of the motion providers in a synchronous manner to actuate movement of the one or more adjustable components.

2. The system of claim 1, wherein each motion provider is an induction motor.

3. The system of claim 2, wherein the induction motor is controlled by the controller to operate on a low slip side of a pull out point on a performance curve.

4. The system of claim 1, wherein the controller utilizes a Volts per Hertz open loop control.

5. The system of claim 4, wherein the Volts per Hertz open loop control utilizes voltage and frequency to control the motion providers.

6. The system of claim 1, wherein the controller sends a command to re-synchronize each actuator every retract cycle by driving each actuator into a calibrated retract stop at a controlled speed and torque capability.

7. The system of claim 6, wherein the controller controls the output of each of the actuators and the output is maintained near synchronous over the applied load range within a slip error of the motion provider characterized between a no-load and an operating point maximum load.

8. The system of claim 1, wherein at least one actuator includes a no-back mechanism for preventing the applied load from backdriving the actuator.

9. The system of claim 1, wherein at least one actuator includes an independent brake to prevent motion when not commanded.

10. The system of claim 1, wherein at least one actuator includes an adjustable stop along the drive path.

11. The system of claim 1, wherein at least one actuator includes a mechanical overload protection device.

12. The system of claim 11, wherein the mechanical overload protection devices is one selected from a group of a slip clutch and a load limiter.

13. The system of claim 1, wherein a pair of the plurality of actuators are coupled to one adjustable component.

14. The system of claim 13, wherein another pair of the plurality of actuators are coupled to a different one of the adjustable components.

15. The system of claim 11, wherein the controller outputs controlled motor drive power to the pair of actuators and another pair of actuators in a synchronous manner to actuate movement of the common component and the another common component.

16. The system of claim 15, wherein the common component is one selected from the group consisting of:

a flap, a slat, a spoiler, an aileron and an elevator.

17. The system in claim 1, wherein each motion provider is a stepper motor.

18. The system in claim 17, further including a single stepper motor controller for providing controlled open loop stepper motor drive power to the stepper motor.

19. The system in claim 1 where each motion provider is a switched reluctance motor (SRM).

20. The system in claim 19, further including g a single SRM motor controller for providing controlled open loop SRM motor drive power to the SRM.

21. A method for controlling a plurality of actuators for actuating movement of one or more adjustable components of an aircraft, the system comprising:

receiving a command for adjusting the one or more adjustable components;

controlling a plurality of actuators for actuating movement of the one or more adjustable components of the aircraft by a controller that outputs controlled motor drive power over a common bus in a synchronous manner to the plurality of actuators;

adjusting the one more adjustable components based on the command information.

22. The method of claim 21, further including re-synchronizing each of the plurality of actuators every retract cycle by driving each actuator into a calibrated retract stop at a controlled speed and torque capability.

23. The method of claim 21, further including controlling the output of each of the actuators by maintaining near synchronous output signals over an applied load range within a slip error of the motion provider characteristic between a no-load and an operating maximum load point.

24. The method of claim 21, further including the controller utilizing a Volts per Hertz open loop control for the step of controlling.

25. The method of claim 24, further including modifications to the Volts per Hertz open loop control to provide torque and/or speed modifications to the plurality of actuators.