HEAD-MOUNTABLE COCKPIT DISPLAY SYSTEM

• US 20100001928A1
• Filed: 06/30/2008
• Published: 01/07/2010
• Est. Priority Date: 06/30/2008
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Nutaro, Joseph
• Granted Patent: US 9,696,546 B2
• Time in Patent Office: Days
• US Class Current: 345/8
• CPC Class Codes: G02B 2027/0118 comprising devices for improving the contrast of the display / brillance control visibility
• CPC Class Codes: G02B 2027/0123 comprising devices increasing the field of view
• CPC Class Codes: G02B 2027/014 comprising information/image processing systems
• CPC Class Codes: G02B 27/017 Head mounted
• CPC Class Codes: G02B 27/0172 characterised by optical features

Abstract

Systems and apparatus are provided for head-mountable cockpit displays for providing information related to an aircraft system to a user. A cockpit display system comprises an eyeglass frame adapted for wearing on the head of the user. The eyeglass frame has a perimeter defining a field of view. A display element is mechanically coupled to the eyeglass frame and aligned with a bottom portion of the field of view. Display electronics are coupled to the display element, and an avionics system is coupled to the display electronics. The display electronics are configured to render an image of a cockpit instrument panel associated with the avionics system on the display element.

Claims

1. A cockpit display system for providing information related to an aircraft system to a user, the cockpit display system comprising:

an eyeglass frame adapted for wearing on the head of the user, the eyeglass frame having a perimeter defining a field of view;

a display element mechanically coupled to the eyeglass frame, wherein the display element is aligned with a bottom portion of the field of view;

display electronics coupled to the display element; and

an avionics system coupled to the display electronics, wherein the display electronics are configured to render an image of a cockpit instrument panel associated with the avionics system on the display element.

2. The cockpit display system of claim 1, wherein the image is substantially opaque.

3. The cockpit display system of claim 1, further comprising a control element coupled to the display electronics, wherein the display electronics are configured to temporarily cause the image to become substantially transparent in response to the control element being activated.

4. The cockpit display system of claim 1, wherein the display electronics are configured to render a wide-angle image of the cockpit instrument panel.

5. The cockpit display system of claim 1, further comprising optics integral with the display element, the optics and the display element being cooperatively configured to convey the image of the cockpit instrument panel to the user as a wide-angle image.

6. The cockpit display system of claim 1, further comprising:

a second eyeglass frame adapted for wearing on the head of a second user, the second eyeglass frame having a perimeter defining a second field of view; and

a second display element mechanically coupled to the second eyeglass frame and coupled to the display electronics, wherein the second display element is aligned with the bottom portion of the second field of view and has the image of the cockpit instrument panel rendered thereon.

7. The cockpit display system of claim 1, further comprising:

a second display element mechanically coupled to the eyeglass frame and coupled to the display electronics, the second display element being aligned with the bottom portion of the field of view; and

a second avionics system coupled to the display electronics, wherein the display electronics are configured to render a second image of a cockpit instrument panel associated with the second avionics system on the display element.

8. The cockpit display system of claim 1, further comprising a sensor communicatively coupled to the display electronics and integral to the eyeglass frame, wherein the display electronics are configured to temporarily cause the image to become substantially transparent in response to the sensor detecting a first value of the eyeglass frame, relative to a reference plane, that exceeds a threshold value.

9. The cockpit display system of claim 1, further comprising a lens coupled to the eyeglass frame, wherein the lens is aligned with at least a top portion of the field of view.

10. A display system comprising:

a support structure, the support structure being adapted to be worn on a head of a user, the support structure having a perimeter defining a field of view aligned with the eyes of the user, wherein the field of view is substantially transparent;

a display element coupled to the support structure, wherein the display element occupies a bottom portion of the field of view;

a processor coupled to the display element; and

an electronic system coupled to the processor, wherein the processor is configured to display a graphical representation of an instrument panel associated with the electronic system on the display element.

11. The display system of claim 10, further comprising a sensor coupled to the processor and configured to obtain a signal indicative of the graphical representation, wherein the processor is configured to analyze the signal to determine if the display system is operating properly.

12. The display system of claim 10, further comprising optics integral with the display element, wherein the optics are configured such that the user perceives the graphical representation as a wide-angle image.

13. The display system of claim 10, wherein the processor is configured to display a head-up display aligned with a top portion of the field of view.

14. The display system of claim 10, further comprising a sensor communicatively coupled to the processor and integral to the support structure, wherein the processor is configured to temporarily cause the graphical representation to become substantially transparent in response to the sensor detecting an angle of the support structure, relative to a reference plane, that exceeds a threshold value.

15. The display system of claim 14, further comprising a control element coupled to the processor, wherein the processor is configured to temporarily cause the graphical representation to become substantially transparent when the control element is activated.

16. A head-mountable device suitable for wearing during operation of an aircraft, the head-mountable device comprising:

an eyeglass frame adapted to be worn on the head of a user, the eyeglass frame defining a field of view aligned with the eyes of the user, wherein the field of view is substantially transparent;

a display element supported by the eyeglass frame, wherein the display element obstructs a lower portion of the field of view; and

a display controller coupled to the display element, the display controller being configured to;

control rendering of an image on the display element, wherein the image contains information associated with operation of the aircraft; and

present the image rendered on the display element as a wide-angle image.

17. The head-mountable device of claim 16, further comprising a second display element coupled to the processor and supported by the eyeglass frame, wherein the second display element obstructs the lower portion of the field of view, the processor being configured to control rendering of a second image on the second display element.

18. The head-mountable device of claim 16, further comprising a sensor communicatively coupled to the display controller and integral to the eyeglass frame, wherein the display controller is configured to temporarily cause the image to become substantially transparent in response to the sensor detecting an angle of the eyeglass frame, relative to a reference plane, that exceeds a threshold value.

19. The head-mountable device of claim 16, further comprising a button coupled to the processor, wherein the processor is configured to temporarily blank the image on the display element when the button is activated.

20. The head-mountable device of claim 16, further comprising a sensor coupled to the processor and supported by the eyeglass frame, the sensor being configured to obtain a signal indicative of the image, wherein the processor is configured to verify the image accurately reflects information associated with a subsystem of the aircraft.