Active HUD alignment

Patent metadata

Field	Value
Publication number	US-9541763-B1
Application number	US-201514812508-A
Country	US
Kind code	B1
Filing date	Jul 29, 2015
Priority date	Jul 29, 2015
Publication date	Jan 10, 2017
Grant date	Jan 10, 2017

Abstract

An active HUD boresight alignment system for correcting a boresight of a HUD in an aircraft relative to an aircraft boresight is described. The system has an aircraft IRU, a HUD angular orientation detector and a detector. The aircraft IRU is rigidly coupled with the aircraft and configured to define an aircraft boresight indicative of a three axis angular orientation of the aircraft. The HUD angular orientation detector is rigidly arranged relative to at least one component of the HUD in the aircraft, and configured to determine a HUD boresight indicative of a three axis angular orientation of the HUD. The processor is coupled with the aircraft IRU and the HUD angular orientation detector and configured to determine a boresight angular offset of the HUD boresight to the aircraft boresight for at least one axis of the three axis angular orientation, and to correct for the boresight angular offset based on the determined boresight angular offset.

First claim

What is claimed is:

1. An active head up display (HUD) boresight alignment system, comprising:
an aircraft inertial reference unit (IRU) rigidly coupled with the aircraft and configured to define an aircraft boresight indicative of a three axis angular orientation of the aircraft;
a HUD angular orientation detector rigidly arranged relative to at least one component of a HUD in the aircraft, and configured to determine a HUD boresight indicative of a three axis angular orientation of the HUD during flight of the aircraft; and
a processor coupled with the aircraft IRU and the HUD angular orientation detector, the processor configured to determine a boresight angular offset of the HUD boresight to the aircraft boresight for at least one axis of the three axis angular orientation, and to correct for the boresight angular offset based on the determined boresight angular offset.

2. The active HUD boresight alignment system of claim 1 , wherein the HUD angular orientation detector is at least one of a HUD IRU and at least one position sensor.

3. The active HUD boresight alignment system of claim 1 , wherein the HUD comprises:
a combiner arranged to combine information and an image of the view outside the aircraft; and
a projector arranged to project an image onto the combiner.

4. The active HUD boresight alignment system of claim 3 , wherein the HUD angular orientation detector is rigidly attached to the combiner.

5. The active HUD boresight alignment system of claim 3 , wherein the HUD angular orientation detector is rigidly attached to the projector.

6. The active HUD boresight alignment system of claim 1 , wherein the three axis orientation of the aircraft and of the HUD is characterized by yaw, pitch, and roll parameters.

7. An active head up display (HUD) for correcting a boresight of the HUD in an aircraft relative to an aircraft boresight, the aircraft having an aircraft inertial reference unit (IRU) rigidly coupled with the aircraft and configured to define an aircraft boresight indicative of a three axis angular orientation of the aircraft, the HUD comprising:
a HUD angular orientation detector rigidly arranged relative to at least one component of the HUD in the aircraft, and configured to determine a HUD boresight indicative of a three axis angular orientation of the HUD during flight of the aircraft; and
a processor coupled with the aircraft IRU and the HUD angular orientation detector, the processor configured to determine a boresight angular offset of the HUD boresight to the aircraft boresight for at least one axis of the three axis angular orientation, and to correct for the boresight angular offset based on the determined boresight angular offset.

8. The active HUD of claim 7 , wherein the HUD angular orientation detector is at least one of a HUD IRU, or at least one position sensor.

9. The active HUD of claim 7 , wherein the HUD comprises:
a combiner arranged to combine information and an image of the view outside the aircraft; and
a projector arranged to project an image onto the combiner.

10. The active HUD of claim 9 , wherein the HUD angular orientation detector is rigidly attached to the combiner.

11. The active HUD of claim 9 , wherein the HUD angular orientation detector is rigidly attached to the projector.

12. The active HUD of claim 9 , wherein the combiner and the projector are separated.

13. The active HUD of claim 7 , wherein the three axis orientation of the aircraft and of the HUD is characterized by yaw, pitch and roll parameters.

14. A method of correcting a boresight of an active head up display (HUD) in an aircraft relative to an aircraft boresight, the method comprising:
determining a HUD boresight indicative of a three axis angular orientation of the HUD via a HUD angular orientation detector rigidly arranged relative to at least one component of the HUD in the aircraft during flight of the aircraft, wherein an aircraft inertial reference unit (IRU) is rigidly attached to the aircraft and configured to define the aircraft boresight indicative of a three axis angular orientation of the aircraft;
determining, via a processor, a boresight angular offset of the HUD boresight to the aircraft boresight for at least one axis of the three axis angular orientation;
correcting, via the processor, for the boresight angular offset based on the determined boresight angular offset; and
displaying an image on the HUD based on correcting for the boresight angular offset.

15. The method of claim 14 , wherein the HUD angular orientation detector is at least one of a HUD IRU and at least one position sensor.

16. The method of claim 14 , wherein the HUD comprises:
a combiner arranged to combine information and an image of the view outside the aircraft; and
a projector arranged to project an image onto the combiner.

17. The method of claim 16 , wherein the HUD angular orientation detector is rigidly attached to the combiner.

18. The method of claim 16 , wherein the HUD angular orientation detector is rigidly attached to the projector.

19. The method of claim 14 , wherein the three axis orientation of the aircraft and of the HUD is characterized by yaw, pitch, and roll parameters.

20. The method of claim 14 wherein the HUD angular orientation detector is integrated with an inertial reference unit (IRU) attached to the aircraft.

Assignees

• Heberlein Ronald E
• Roethler Byron B
• Burns Lincoln J
• Rockwell Collins Inc

Inventors

• Heberlein Ronald E
• Roethler Byron B
• Burns Lincoln J

Classifications

• G01C23/00

  Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration · CPC title

• G02B27/0179 Primary

  Display position adjusting means not related to the information to be displayed · CPC title

• G02B2027/014

  comprising information/image processing systems · CPC title

• G02B27/01

  Head-up displays · CPC title