Controller for Electromechanical Braking System with Power Demand Control and Method

• US 20080284358A1
• Filed: 11/15/2006
• Published: 11/20/2008
• Est. Priority Date: 11/30/2005
• Status: Abandoned Application

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Ralea, Mihai
• Application Number:
  US12/092,172
• Publication Number:
  US 20080284358A1
• Time in Patent Office: Days
• US Class Current: 318/14
• CPC Class Codes: B60T 13/741 acting on an ultimate actuator
• CPC Class Codes: B60T 8/1703 for aircrafts

Abstract

A system and method for limiting peak power demand of a controller (26) for an electromechanical actuator A motor current command is limited to at least one of a positive current limit or a negative current limit, the positive and negative current limits being a function of motor velocity. A motor drive signal is output to the motor in accordance with the limited motor current command.

Claims

1. An aircraft, comprising:

at least one electromechanical actuator including a motor for applying a force to a moveable item in response to a motor drive signal;

a power supply; and

an electromechanical actuator controller for generating the motor drive signal based on a motor current command and with electrical power from the power supply, the electromechanical actuator controller including;

a motor current limiter for limiting the motor current command to at least one of a positive current limit or a negative current limit, the positive and negative current limits being a function of motor velocity by which the positive current limit and negative current limit are inversely related to the motor velocity; and

a current driver for outputting the motor drive signal to the motor in accordance with the limited motor current command.

2. The aircraft of claim 1, wherein the moveable item is an actuator for applying a braking force to perform a braking operation of a wheel of the aircraft.

3. The aircraft of claim 1, wherein the moveable item is an actuator for positioning a flight control surface of the aircraft.

4. The aircraft of claim 1, wherein the moveable item is an actuator for a landing gear.

5. The aircraft of claim 1, wherein the current driver provides closed loop current control of the motor drive signal.

6. The aircraft of claim 1, wherein the positive current limit is established by the equation:

Positive Current Limit=PSP×

(1−

K_p(V_m/V_pmax))

wherein PSP is a predetermined positive current limit set point, K_p is a predetermined gain constant, V_m is the velocity of the motor and V_pmax is a predetermined positive motor velocity limit.

7. The aircraft of claim 1, wherein the negative current limit is established by the equation:

Negative Current Limit=NSP×

(1+K_n(V_m/V_nmax))

wherein NSP is a predetermined negative current limit set point, K_n is a predetermined gain constant, V_m is the velocity of the motor and V_nmax is a predetermined negative motor velocity limit.

8. The aircraft of claim 1, wherein the controller further includes a closed loop feedback element for generating the motor current command based on an input command received by the controller.

9. The aircraft of claim 8, wherein the closed loop feedback element includes a velocity servo compensator that provides closed loop velocity control of the motor current command.

10. The aircraft of claim 1, wherein the closed loop feedback element includes a force servo compensator that provides closed loop force control of the motor current command.

11. The aircraft of claim 10, wherein the force servo compensator receives the braking input command and generates an intermediate motor current command input to the velocity servo compensator.

12. The aircraft of claim 1, wherein the positive current limit is established by a power demand controller that includes a motor velocity limiter for limiting a motor velocity value to a positive motor velocity limit and a function block that derives the positive current limit as a function of the limited motor velocity value and a positive motor current limit setpoint.

13. The aircraft of claim 1, wherein the negative current limit is established by a power demand controller that includes a motor velocity limiter for limiting a motor velocity value to a negative motor velocity limit and a function block that derives the negative current limit as a function of the limited motor velocity value and a negative motor current limit setpoint.

14. The aircraft of claim 1, wherein the positive and negative current limits are established with a power demand controller that is embodied as executable logic.

15. The aircraft of claim 1, wherein values used to determine the positive current limit and the negative current limit as functions of motor velocity are set based on an aircraft condition.

16. The aircraft of claim 15, wherein a first set of values for determining the positive and negative current limits are associated with normal power supply operation and a second set of values for determining the positive and negative current limits are associated with emergency power supply operation.

17. A controller for an electromechanical actuator having a motor that is driven in response to a motor drive signal generated by the controller, comprising:

a motor current limiter for limiting a motor current command to at least one of a positive current limit or a negative current limit, the positive and negative current limits being a function of motor velocity by which the positive current limit and negative current limit are inversely related to the motor velocity; and

a current driver for outputting the motor drive signal to the motor in accordance with the limited motor current command.

18. The controller of claim 17, wherein the current driver provides closed loop current control of the motor drive signal.

19. The controller of claim 17, wherein the positive current limit is established by the equation:

Positive Current Limit=PSP×

(1−

K_p(V_m/V_pmax))

wherein PSP is a predetermined positive current limit set point, K_p is a predetermined gain constant, V_m is the velocity of the motor and V_pmax is a predetermined positive motor velocity limit.

20. The controller of claim 17, wherein the negative current limit is established by the equation:

Negative Current Limit=NSP×

(1+K_n(V_m/V_nmax))

wherein NSP is a predetermined negative current limit set point, K_n is a predetermined gain constant, V_m is the velocity of the motor and V_nmax is a predetermined negative motor velocity limit.

21. The controller of claim 17, further comprising a closed loop feedback element for generating the motor current command based on an input command received by the controller.

22. The controller of claim 21, wherein the closed loop feedback element includes a velocity servo compensator that provides closed loop velocity control of the motor current command.

23. The controller of claim 21, wherein the closed loop feedback element includes a force servo compensator that provides closed loop force control of the motor current command.

24. The controller of claim 23, wherein the force servo compensator receives a braking input command and generates an intermediate motor current command input to the velocity servo compensator.

25. The controller of claim 17, wherein the positive current limit is established by a power demand controller that includes a motor velocity limiter for limiting a motor velocity value to a positive motor velocity limit and a function block that derives the positive current limit as a function of the limited motor velocity value and a positive motor current limit setpoint.

26. The controller of claim 17, wherein the negative current limit is established by a power demand controller that includes a motor velocity limiter for limiting a motor velocity value to a negative motor velocity limit and a function block that derives the negative current limit as a function of the limited motor velocity value and a negative motor current limit setpoint.

27. The controller of claim 17, wherein the positive and negative current limits are established with a power demand controller that is embodied as executable logic.

28. The controller of claim 17, wherein values used to determine the positive current limit and the negative current limit as functions of motor velocity are set based on an aircraft condition.

29. The controller of claim 28, wherein a first set of values for determining the positive and negative current limits are associated with normal power supply operation and a second set of values for determining the positive and negative current limits are associated with emergency power supply operation.

30. A method of limiting peak power demand of a controller for an electromechanical brake actuator having a motor, the electromechanical brake actuator operative to apply a braking force to brake a wheel of a vehicle, comprising:

limiting a motor current command to at least one of a positive current limit or a negative current limit, the positive and negative current limits being a function of motor velocity by which the positive current limit and negative current limit are inversely related to the motor velocity; and

outputting the motor drive signal to the motor in accordance with the limited motor current command.

31. The method of claim 30, wherein the outputting the motor drive signal includes carrying out closed loop feedback control of the motor drive signal.

32. The method of claim 30, further comprising receiving a braking input command and carrying out closed loop feedback control with respect to at least one of motor velocity or force applied by the electromechanical brake actuator to generate the motor current command.

33. The method of claim 30, wherein the positive current limit is established by limiting a motor velocity value to a positive motor velocity limit and deriving the positive current limit as a function of the limited motor velocity value and a positive motor current limit setpoint.

34. The method of claim 30, wherein the negative current limit is established by limiting a motor velocity value to a negative motor velocity limit and deriving the negative current limit as a function of the limited motor velocity value and a negative motor current limit setpoint.

35. The method of claim 30, wherein the vehicle comprises an aircraft.

36. The method of claim 30, wherein the motor is driven to control the displacement of a force applicator relative to a brake stack.

37. The method of claim 30, further comprising adjusting values used to determine the positive current limit and the negative current limit as functions of motor velocity based on an aircraft condition.

38. The method of claim 37, wherein a first set of values for determining the positive and negative current limits are associated with normal power supply operation and a second set of values for determining the positive and negative current limits are associated with emergency power supply operation.