Active human-machine user interface feedback system with spherical motor

Patent metadata

Field	Value
Publication number	US-11009892-B2
Application number	US-201916358409-A
Country	US
Kind code	B2
Filing date	Mar 19, 2019
Priority date	Mar 19, 2019
Publication date	May 18, 2021
Grant date	May 18, 2021

Abstract

An active human-machine interface feedback system includes a user interface, a pitch angle sensor, a roll angle sensor, a spherical motor, and a control circuit. The user interface adapted to receive user input and is configured, upon receipt of the user input, to move, about one or both of a pitch axis and a roll axis, to a user interface position. The pitch angle sensor is configured to sense the pitch angle component of the user interface position. The roll angle sensor is configured to sense the roll angle component of the user interface position. The spherical motor is coupled to the user interface and is symmetrically disposed about the origin. The control circuit determines a polar angle (θ) of the user interface relative to the origin, determine an azimuthal angle (φ) of the user interface relative to the origin, and supply current to the first, second, and third coils.

First claim

What is claimed is:

1. An active human-machine interface feedback system, comprising:
a user interface adapted to receive user input and configured, upon receipt of the user input, to move, about one or both of a pitch axis and a roll axis, to a user interface position, the user interface position having one or both of a pitch angle component and a roll angle component, wherein the pitch axis and the roll axis are disposed perpendicular to each other and intersect at an origin;
a pitch angle sensor coupled to the user interface and configured to sense the pitch angle component of the user interface position, the pitch angle sensor further configured to supply a pitch angle signal representative of the user interface pitch angle component;
a roll angle sensor coupled to the user interface and configured to sense the roll angle component of the user interface position, the roll angle sensor further configured to supply a roll angle signal representative of the user interface roll angle component;
a spherical motor coupled to the user interface and symmetrically disposed about the origin, the spherical motor including an armature, a spherical stator, a first coil, a second coil, and a third coil, the armature coupled to the user interface, the spherical stator having a first axis of symmetry, a second axis of symmetry, a third axis of symmetry, the first, second, and third axes of symmetry disposed perpendicular to each other, the first coil, the second coil, and the third coil wound on the spherical stator about the first axis of symmetry, the second axis of symmetry, and the third axis of symmetry, respectively; and
a control circuit coupled to receive the pitch angle signal and the roll angle signal and operable, in response to at least these signals, to:
determine a polar angle (θ) of the user interface relative to the origin,
determine an azimuthal angle (φ) of the user interface relative to the origin,
supply current to the first coil that is equal to I 0 *sin(θ)*cos(φ),
supply current to the second coil that is equal to I 0 *sin(θ)*sin(φ), and
supply current to the third coil that is equal to I 0 *sin(θ),
wherein I 0 is a current vector magnitude value.

2. The system of claim 1 , wherein the control circuit is further configured to vary the current vector magnitude value (I 0 ), to thereby vary a resistive feedback force on the user interface.

3. The system of claim 2 , wherein the control circuit varies the current vector magnitude value (I 0 ) in response to aircraft operating conditions.

4. The system of claim 3 , further comprising:
an aircraft avionics system in operable communication with the control circuit, the aircraft avionics system configured to supply data representative of the aircraft operating conditions to the control circuit.

5. The system of claim 2 , wherein the control circuit varies the current vector magnitude value (I 0 ) in response to the polar angle (θ) and the azimuthal angle (φ).

6. The system of claim 2 , wherein the control circuit is further configured to restrict movement of the side stick to one or both of a predetermined polar angle (θ) and the azimuthal angle (φ).

7. The system of claim 1 , further comprising:
an aircraft autopilot system in operable communication with the control circuit, the aircraft autopilot system configured to supply data representative of aircraft autoflight control commands to the control circuit,
wherein the control circuit is further configured, upon receipt of the data representative of aircraft autoflight control commands, to supply current to the first, second, and third coils that cause the user interface to move to positions that represent the aircraft autoflight control commands.

8. The system of claim 7 , further comprising:
a first current sensor operable to sense a magnitude and direction of current flow in the first coil and supply a first current signal representative thereof to the control circuit;
a second current sensor operable to sense a magnitude and direction of current flow in the second coil and supply a second current signal representative thereof to the control circuit; and
a third current sensor operable to sense a magnitude and direction of current flow in the third coil and supply a third current signal representative thereof to the control circuit.

9. The system of claim 8 , wherein the control circuit is further configured to:
determine a vector sum of current flow in the first, second, and third coils;
compare the vector sum to a predetermined breakout current; and
supply a disengage signal to the aircraft autopilot system when the vector sum exceeds the predetermined breakout current.

10. The system of claim 9 , wherein the autopilot system is configured, upon receipt of the disengage signal, to disengage and stop supplying the data representative of aircraft autoflight control commands to the control circuit.

11. An active human-machine interface haptic feedback system, comprising:
a user interface adapted to receive user input and configured, upon receipt of the user input, to move, about one or both of a pitch axis and a roll axis, to a user interface position, the user interface position having one or both of a pitch angle component and a roll angle component, wherein the pitch axis and the roll axis are disposed perpendicular to each other and intersect at an origin;
a pitch angle sensor coupled to, and configured to sense the pitch angle component of, the user interface position, the pitch angle sensor further configured to supply a pitch angle signal representative of the user interface pitch angle component;
a roll angle sensor coupled to, and configured to sense the roll angle component of, the user interface position, the roll angle sensor further configured to supply a roll angle signal representative of the user interface roll angle component;
a spherical motor coupled to the user interface and symmetrically disposed about the origin, the spherical motor including an armature, a spherical stator, a first coil, a second coil, and a third coil, the armature coupled to the user interface, the spherical stator having a first axis of symmetry, a second axis of symmetry, a third axis of symmetry, the first, second, and third axes of symmetry disposed perpendicular to each other, the first coil, the second coil, and the third coil wound on the spherical stator about the first axis of symmetry, the second axis of symmetry, and the third axis of symmetry, respectively; and
a control circuit coupled to receive the pitch angle signal, the roll angle signal, and data representative of aircraft operable, in response to at least these signals, to:
determine a polar angle (θ) of the user interface relative to the origin,
determine an azimuthal angle (φ) of the user interface relative to the origin,
supply current to the first coil that is equal to I 0 *sin(θ)*cos(φ),
supply current to the second coil that is equal to I 0 *sin(θ)*sin(φ), and
supply current to the third coil that is equal to I 0 *sin(θ),
wherein I 0 is a variable current vector magnitude value.

12. The system of claim 11 , wherein the control circuit is further configured to vary the current vector magnitude value (I 0 ) in response to the polar angle (θ) and the azimuthal angle (φ).

13. The system of claim 11 , wherein the control circuit is further configured to vary the current vector magnitude value (I 0 ) in response to aircraft characteristics.

14. The system of claim 13 , further comprising:
an aircraft avionics system in operable communication with the control circuit, the aircraft avionics system configured to supply data represent

Assignees

• Honeywell Int Inc

Inventors

• Das Shouvik
• Bandera Pablo
• Kothandaraman Deena Dayalan

Classifications

• G06F3/0338

  with detection of limited linear or angular displacement of an operating part of the device from a neutral position, e.g. isotonic or isometric joysticks · CPC title

• G05D1/0808 Primary

  specially adapted for aircraft · CPC title

• G05G2505/00

  Means for preventing, limiting or returning the movements of parts of a control mechanism, e.g. locking controlling member · CPC title

• G06F3/016

  Input arrangements with force or tactile feedback as computer generated output to the user · CPC title

• B64C13/22

  readily revertible to personal control · CPC title