Apparatus and method pertaining to light-based power distribution in a vehicle

• US 7,880,325 B2
• Filed: 04/27/2009
• Issued: 02/01/2011
• Est. Priority Date: 10/16/2006
• Status: Active Grant

• Current Assignee: Lightspeed Technologies, LLC (Professional Trading Solutions, Inc.)
• Original Assignee: Embedded Control Systems Inc.
• Inventors: Stoner, Paul Douglas
• Primary Examiner(s): DeBeradinis; Robert L.
• Application Number:
  US12/430,437
• Publication Number:
  US 20090230784A1
• Time in Patent Office: 645 Days
• Field of Search: 307/9.1
• US Class Current: 307/9.1
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: G02B 6/2808 using a mixing element which evenly distributes an input signal over a number of outputs
• CPC Class Codes: G02B 6/4298 coupling with non-coherent light sources and/or radiation detectors, e.g. lamps, incandescent bulbs, scintillation chambers
• CPC Class Codes: H04B 10/807 Optical power feeding, i.e. transmitting power using an optical signal

Abstract

A vehicle (400) such as an aircraft is provided (101) with a source of light (401). An optical conduit is then used to couple (104) this source of light to a light-to-electricity conversion apparatus (408). So configured, the optical conduit delivers light from this source of light to the light-to-electricity conversion apparatus such that the light source then serves as a source of electricity in the vehicle.

Claims

1. A method comprising:

in an aircraft;

providing a source of light within the aircraft such that the source of light will accompany the aircraft when the aircraft is in flight;

using an optical conduit to couple the source of light to a light-to-electricity conversion apparatus;

such that light from the source of light is delivered to the light-to-electricity conversion apparatus via the optical conduit and is used to provide a source of electricity in the aircraft to components of the aircraft.

2. The method of claim 1 wherein providing a source of light comprises providing a source of light that is powered, at least in part, by an aircraft engine.

3. The method of claim 1 wherein providing a source of light comprises providing at least two independent sources of light.

4. The method of claim 3 wherein using an optical conduit to couple the source of light to a light-to-electricity conversion apparatus comprises:

using a first optical conduit to couple a first source of light to the light-to-electricity conversion apparatus;

using a second optical conduit that is independent of the first optical conduit to couple a second source of light that is different than the first source of light to the light-to-electricity conversion apparatus;

such that the light-to-electricity conversion apparatus receives a redundant supply of light to be converted to electricity.

5. The method of claim 1 wherein providing a source of light comprises, at least in part, providing a source of infrared light.

6. The method of claim 1 wherein the light-to-electricity conversion apparatus comprises an infrared light-to-electricity conversion apparatus.

7. The method of claim 1 wherein the optical conduit comprises, at least in part, an optical fiber.

8. The method of claim 7 wherein the optical conduit comprises, at least in part, a plurality of the optical fibers.

9. The method of claim 8 wherein the plurality of the optical fibers comprises a plurality of optical fibers that are each comprised of polymer materials.

10. The method of claim 9 wherein the plurality of optical fibers comprises a plurality of optical fibers that are each about 0.1 to 5 millimeter in diameter.

11. The method of claim 10 wherein the plurality of optical fibers comprises from about 2 to about 100 optical fibers.

12. The method of claim 1 wherein using an optical conduit to couple the source of light to a light-to-electricity conversion apparatus comprises using a plurality of optical conduits to couple the source of light to a corresponding plurality of light-to-electricity conversion apparatuses.

13. The method of claim 12 wherein using a plurality of optical conduits to couple the source of light to a corresponding plurality of light-to-electricity conversion apparatuses comprises using a star-based architecture to couple the source of light to the plurality of light-to-electricity conversion apparatuses.

14. The method of claim 13 wherein separate whole sets of light sources and sinks are cross-coupled for fail-functional operation.

15. The method of claim 1 wherein the light-to-electricity conversion apparatus is further operably coupled to at least one electrically powered aircraft component.

16. The method of claim 15 wherein the light-to-electricity conversion apparatus comprises an integral part of the electrically powered aircraft component.

17. The method of claim 15 wherein the aircraft is configured and arranged to optically distribute data to and from the electrically powered aircraft component.

18. The method of claim 17 wherein the aircraft is configured and arranged to optically distribute data to and from the electrically powered aircraft component independent of the optical conduit.

19. The method of claim 1 wherein providing a source of light comprises:

providing a source of a first component of the light;

providing a source of a second component of the light, wherein the first and second components are different from one another.

20. The method of claim 19 wherein the first component of the light comprises a power component and the second component of the light comprises a visible marker.

21. The method of claim 20 wherein the power component comprises an infrared light component.

22. The method of claim 21 wherein the visible marker comprises a visible light component.

23. The method of claim 22 wherein the visible light component comprises a white light component.

24. The method of claim 20 wherein providing a source of light further comprises providing at least a third component of the light that is different from the first and second components, wherein the third component comprises at least one of:

a data-bearing component;

a heating component;

a surface illumination end use component.

25. An aircraft power distribution system comprising:

a source of light disposed within an aircraft such that the source of light will accompany the aircraft when the aircraft is in flight;

an optical conduit that is operably coupled between the source of light and a light-to-electricity conversion apparatus;

such that light from the source of light is delivered to the light-to-electricity conversion apparatus via the optical conduit and is used to provide a source of electricity in the aircraft.

26. The aircraft power distribution system of claim 25 wherein the source of light is operably coupled to an aircraft engine to thereby facilitate powering the source of light.

27. The aircraft power distribution system of claim 25 wherein the source of light is operably coupled to an aircraft main battery to thereby facilitate powering the source of light.

28. The aircraft power distribution system of claim 25 wherein the source of light comprises at least two independent sources of light.

29. The aircraft power distribution system of claim 28 wherein the optical conduit comprises:

a first optical conduit that is operably coupled between a first source of light and the light-to-electricity conversion apparatus;

a second optical conduit that is independent of the first optical conduit and that is operably coupled between a second source of light and the light-to-electricity conversion apparatus, wherein the second source of light is different from the first source of light;

such that the light-to-electricity conversion apparatus receives a redundant supply of light to be converted to electricity.

30. The aircraft power distribution system of claim 25 wherein the source of light comprises, at least in part, a source of infrared light.

31. The aircraft power distribution system of claim 25 wherein the optical conduit comprises, at least in part, an optical fiber.

32. The aircraft power distribution system of claim 31 wherein the optical conduit comprises, at least in part, a plurality of the optical fibers.

33. The aircraft power distribution system of claim 32 wherein the plurality of the optical fibers comprises a plurality of optical fibers that are each comprised of a polymer material.

34. The aircraft power distribution system of claim 33 wherein the plurality of optical fibers comprises a plurality of optical fibers that are each about 0.1 to 5 millimeter in diameter.

35. The aircraft power distribution system of claim 34 wherein the plurality of optical fibers comprises from about 2 to about 100 optical fibers.

36. The aircraft power distribution system of claim 25 wherein the optical conduit that is operably coupled between the source of light and a light-to-electricity conversion apparatus comprises a plurality of optical conduits that are each operably coupled between the source of light and a corresponding plurality of light-to-electricity conversion apparatuses.

37. The aircraft power distribution system of claim 36 wherein the plurality of optical conduits that are each operably coupled between the source of light and a corresponding plurality of light-to-electricity conversion apparatuses are so coupled using a star-based architecture.

38. An aircraft comprising:

a plurality of electrically powered aircraft components;

a source of light;

a plurality of optical conduits, wherein at least one of the plurality of optical conduits is operably coupled between the source of light and a corresponding light-to-electricity conversion apparatus that is operably coupled to at least one of the plurality of electrically powered aircraft components;

such that light from the source of light is delivered to the light-to-electricity conversion apparatus via the optical conduit and is used to provide a source of electricity to the plurality of electrically powered aircraft components.