Aircraft and deployable vision systems for aircraft

Patent metadata

Field	Value
Publication number	US-10414515-B2
Application number	US-201615359987-A
Country	US
Kind code	B2
Filing date	Nov 23, 2016
Priority date	Nov 23, 2016
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

Aircraft, vision sensor systems, and methods of operating deployable vision systems are provided. An aircraft includes a fuselage and a vision sensor system. The fuselage defines an outer mold line and the vision sensor system includes a housing and a vision sensor package. The housing is selectively deployable between a retracted position and a deployed position and is disposed within the outer mold line in the retracted position and outside of the outer mold line in the deployed position. The vision sensor package is associated with the housing and is positioned to collect imaging information when the housing is in the deployed position.

First claim

What is claimed is:

1. An aircraft comprising:
a fuselage defining an outer mold line; and
a vision sensor system comprising;
a housing selectively deployable between a retracted position and a deployed position, the housing disposed within the outer mold line in the retracted position and outside of the outer mold line in the deployed position,
a vision sensor package associated with the housing and positioned to collect imaging information when the housing is in the deployed position, and
a controller configured to deploy and retract the vision sensor system.

2. The aircraft of claim 1 , wherein the housing is disposed in an upper portion of the fuselage and includes an outer surface that lies flush with the outer mold line when the housing is in the retracted position.

3. The aircraft of claim 2 , wherein the fuselage includes an opaque aircraft skin and encloses a flight deck that defines a design eye point of a pilot, and wherein the opaque aircraft skin is disposed forward of the design eye point with respect to the aircraft.

4. The aircraft of claim 3 , wherein the housing is positioned substantially directly in front of the design eye point.

5. The aircraft of claim 1 , wherein the housing is disposed in a lower portion of the fuselage.

6. The aircraft of claim 5 , further comprising a landing gear assembly, wherein the housing is secured to the landing gear assembly and is deployable with the landing gear assembly.

7. The aircraft of claim 6 , wherein the landing gear assembly is a nose gear assembly.

8. The aircraft of claim 1 , further comprising a first pilot seat and a second pilot seat, wherein the housing is a first housing associated with the first pilot seat, the vision sensor package is a first vision sensor package associated with the first pilot seat, and wherein the vision sensor system further includes a second housing associated with the second pilot seat and a second vision sensor package associated with the second pilot seat.

9. The aircraft of claim 8 , further comprising a landing gear assembly, wherein the vision sensor system further includes a third housing and a third vision sensor package secured to the landing gear assembly.

10. The aircraft of claim 1 , wherein the controller is configured to deploy and retract the housing based on an altitude of the aircraft.

11. The aircraft of claim 10 , wherein the controller is configured to retract the vision sensor system when the altitude exceeds 18,000 feet and to deploy the vision sensor system when the altitude of the aircraft drops below 18,000 feet.

12. The aircraft of claim 1 , wherein the controller is configured to generate a signal that causes a display to present the imaging information as an image of an environment in which the aircraft is located.

13. The aircraft of claim 1 , wherein the vision sensor package includes a visible spectrum camera.

14. The aircraft of claim 1 , wherein the vision sensor package includes an infrared spectrum camera.

15. The aircraft of claim 1 , wherein the vision sensor package includes a radar sensor.

16. The aircraft of claim 1 , wherein the vision sensor package includes a low light camera.

17. A vision sensor system for an aircraft, the vision sensor system comprising:
a housing selectively deployable between a retracted position and a deployed position, wherein the housing is configured to be disposed within an outer mold line of the aircraft in the retracted position and outside of the outer mold line in the deployed position;
a vision sensor package associated with the housing and positioned to collect imaging information when the housing is in the deployed position, and
a controller configured to deploy and retract the vision sensor system.

18. The vision sensor system of claim 17 , wherein the housing is configured to be disposed in an upper portion of a fuselage and includes a first surface that is configured to lie flush with the outer mold line when the vision sensor system is in the retracted position.

19. A method of operating a deployable vision system for an aircraft, the method comprising:
deploying, outside of an outer mold line of the aircraft with a controller, a housing and a vision sensor package associated with the housing;
displaying, on a display, an image of an environment outside of the aircraft based on an output from the vision sensor package.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Michaels Charles
• Knight Michael
• Klutzke Douglas

Classifications

• B64D43/00

  Arrangements or adaptations of instruments · CPC title

• B64C1/14

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title

• H04N7/183

  for receiving images from a single remote source · CPC title

• H04N23/54

  Mounting of pick-up tubes, electronic image sensors, deviation or focusing coils · CPC title

• H04N23/63

  by using electronic viewfinders · CPC title