Active pilot flight control stick system with passive electromagnetic feedback

• US 20080156939A1
• Filed: 01/03/2007
• Published: 07/03/2008
• Est. Priority Date: 01/03/2007
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Abel, Stephen G., Hanlon, Casey, Wilkens, Dean R., Potter, Calvin C., Wingett, Paul T.
• Application Number:
  US11/649,011
• Publication Number:
  US 20080156939A1
• Time in Patent Office: Days
• US Class Current: 244/223
• CPC Class Codes: B64C 13/507 with artificial feel

Abstract

A pilot flight control stick haptic feedback mechanism provides variable force feedback to the pilot flight control stick. The flight control stick is movable to a control position in a displacement direction. A motor control unit is operable to selectively supply motor feedback signals to a motor that is coupled to the flight control stick. The motor is responsive to the motor feedback signals to supply a variable feedback force to the flight control stick in a direction that opposes the displacement direction. A passive electromagnetic damping mechanism is electrically coupled to the motor and is at least selectively and passively supplies a non-braking damping force to the flight control stick.

Claims

1. An aircraft flight control surface actuation haptic feedback system, comprising:

a flight control stick adapted to receive an input force supplied by a pilot and configured, upon receipt of the input force, to move at least a portion thereof to a control position in a displacement direction;

a motor control unit operable to selectively supply motor feedback signals;

a motor coupled to the flight control stick and to receive the motor feedback signals, the motor operable, upon receipt of the motor feedback signals, to supply a variable feedback force to the flight control stick in a direction that opposes the displacement direction; and

a passive electromagnetic damping mechanism electrically coupled to the motor and operable to at least selectively and passively supply a non-braking damping force to the flight control stick.

2. The system of claim 1, wherein the motor comprises:

a rotationally mounted permanent magnet rotor coupled to the flight control stick; and

a multi-phase drive stator at least partially surrounding the permanent magnet rotor and coupled to receive the variable force feedback signals.

3. The system of claim 2, wherein the passive electromagnetic damping mechanism comprises a plurality of electrical resistor circuits, each electrical resistor circuit (i) having a substantially fixed amount of electrical resistance and (ii) electrically coupled in parallel with one phase of the multi-phase drive stator.

4. The system of claim 2, wherein:

each phase of the multi-phase drive stator includes a first number of turns; and

the passive electromagnetic damping mechanism comprises a multi-phase damping stator at least partially surrounding the permanent magnet rotor, each phase of the multi-phase damping stator having a second number of turns that is less than the first number of turns.

5. The system of claim 4, wherein each phase of the damping stator is short-circuited to each other.

6. The system of claim 4, wherein each phase of the damping stator is selectively short-circuited to each other.

7. The system of claim 6, further comprising:

a plurality of switches, each switch electrically coupled between two phases of the multi-phase damping stator and movable between a first position, in which the two phases are short-circuited to each other, and a second position, in which the two phases are not short-circuited to each other.

8. The system of claim 1, wherein:

the flight control stick is further configured, upon movement thereof to the control position, to supply a flight control stick position signals representative of the control position; and

the motor control unit is coupled to receive the flight control stick position control signals and is further operable, in response thereto, to supply one or more flight control surface position commands.

9. The system of claim 8, further comprising:

one or more flight control stick position sensors configured to sense the control position of the flight control stick and operable to supply the flight control stick position signals.

10. The system of claim 8, further comprising:

a plurality of flight control surface actuators, each actuator adapted to couple to a flight control surface and configured, upon being energized, to supply a drive force;

a flight control unit coupled to receive the flight control surface position commands and operable, in response thereto, to selectively energize one or more of the flight control surface actuators.

11. The system of claim 8, wherein:

the flight control unit is further coupled to receive one or more signals representative of aircraft flight conditions and is further operable, in response thereto, to supply force influence feedback signals; and

the motor control unit is further coupled to receive the force influence feedback signals and is further operable, in response thereto, to supply the motor feedback signals based at least in part on the force influence feedback signals.

12. The system of claim 1, further comprising:

a gear set coupled between the motor and the flight control stick.

13. The system of claim 1, wherein the motor is a brushless DC motor.

14. An aircraft flight control surface actuation haptic feedback system, comprising:

a flight control stick adapted to receive an input force supplied by a pilot and configured, upon receipt of the input force, to move at least a portion thereof to a control position in a displacement direction;

a motor control unit operable to selectively supply motor feedback signals;

a passively damped brushless DC motor coupled to the flight control stick and to receive the motor feedback signals, the motor operable, upon receipt of the motor feedback signals, to supply a variable feedback force to the flight control stick in a direction that opposes the displacement direction, the motor including;

a rotationally mounted permanent magnet rotor coupled to the flight control stick,

a multi-phase drive stator at least partially surrounding at least a portion of the permanent magnet rotor and coupled to receive the motor feedback signals, each phase of the multi-phase drive stator includes a first number of turns, and

a multi-phase damping stator at least partially surrounding at least a portion of the permanent magnet rotor, each phase of the multi-phase damping stator having a second number of turns that is less than the first number of turns.

15. The system of claim 14, wherein each phase of the damping stator is short-circuited to each other.

16. The system of claim 14, wherein each phase of the damping stator is selectively short-circuited to each other.

17. The system of claim 16, further comprising:

a plurality of switches, each switch electrically coupled between two phases of the multi-phase damping stator and movable between a first position, in which the two phases are short-circuited to each other, and a second position, in which the two phases are not short-circuited to each other.

18. An aircraft flight control surface actuation haptic feedback system, comprising:

a flight control stick adapted to receive an input force supplied by a pilot and configured, upon receipt of the input force, to move at least a portion thereof to a control position in a displacement direction;

a motor control unit operable to selectively supply motor feedback signals;

a motor coupled to the flight control stick and to receive the motor feedback signals, the motor operable, upon receipt of the motor feedback signals, to supply a variable feedback force to the flight control stick in a direction that opposes the displacement direction, the motor including a rotationally mounted permanent magnet rotor coupled to the flight control stick, a multi-phase stator at least partially surrounding the permanent magnet rotor and coupled to receive the motor feedback signals; and

a plurality of electrical resistor circuits, each electrical resistor circuit having a substantially fixed amount of electrical resistance and electrically coupled in parallel with one phase of the multi-phase stator, whereby the motor is passively damped.