Power transmission for aircraft flight testing

• US 8,672,258 B1
• Filed: 08/21/2009
• Issued: 03/18/2014
• Est. Priority Date: 08/21/2009
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Tillotson, Brian J., Loudiana, Michael A.
• Primary Examiner(s): Lee, Benjamin P
• Assistant Examiner(s): GOMBERG, BENJAMIN S
• Application Number:
  US12/545,551
• Time in Patent Office: 1,670 Days
• Field of Search: 343/708, 343/715
• US Class Current: 244/1.R
• CPC Class Codes: B64C 1/1484 Windows B64C1/1492 takes precedence
• CPC Class Codes: B64D 47/00 Equipment not otherwise provided for
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems

Abstract

Systems and methods for transferring power through an aircraft window and thereby powering temporary externally mounted equipment, such as flight test instrumentation, without cutting or drilling holes in the airplane to run wire for a flight test or experiment. One embodiment uses a light source and a photovoltaic cell to transfer power from inside to outside the aircraft. Another embodiment uses an RF source and a rectenna to transfer power from inside to outside the aircraft.

Claims

1. A system comprising:

a fuselage of an aircraft containing a pressurized volume, said fuselage comprising a transparent portion which is transparent to the passage of an electromagnetic beam therethrough;

a source of electromagnetic radiation that emits electromagnetic radiation as an electromagnetic beam, said source being mounted inside said fuselage within said pressurized volume;

a portion of the aircraft disposed outside said fuselage and having an external surface;

an electrical device attached to said portion of the aircraft;

a receiver configured to convert an impinging electromagnetic beam from said source into electrical power, said receiver being mounted on said external surface at a location which is separated from said transparent portion of said fuselage by air along the path of an electromagnetic beam emitted from said source and received by said receiver; and

an electrical connection between said receiver and said electrical device for carrying electrical power from said receiver to said electrical device.

2. The system as recited in claim 1, wherein said electromagnetic radiation is light.

3. The system as recited in claim 2, wherein said receiver comprises at least one photovoltaic cell.

4. The system as recited in claim 1, wherein said electromagnetic radiation is microwaves.

5. The system as recited in claim 4, wherein said receiver is a rectenna.

6. The system as recited in claim 1, wherein said transparent portion of said fuselage is a window.

7. The system as recited in claim 1, wherein said transparent portion of said fuselage is a cockpit canopy.

8. The system as recited in claim 1, wherein said electromagnetic radiation is microwaves and said transparent portion comprises a composite of electrically nonconductive fibers and resin.

9. The system as recited in claim 1, further comprising a plate into which said source is integrated, said plate being attached to the inside of a window of said aircraft.

10. The system as recited in claim 9, said plate comprising an optical data transceiver.

11. The system as recited in claim 1, wherein the transparent portion through which the electromagnetic beam passes is not an optical fiber.

12. A system comprising:

an electrical device attached to an exterior surface of an aircraft;

a source of electromagnetic radiation that produces a beam of electromagnetic radiation, said source being mounted inside a fuselage of the aircraft;

a receiver configured to convert electromagnetic radiation from said source into electrical power, said receiver being mounted outside said fuselage and electrically connected to said electrical device;

means for tracking the location of said receiver relative to said source while said aircraft is in flight; and

means for steering said beam of electromagnetic radiation so that it is directed toward said receiver while said aircraft is in flight.

13. A system comprising:

an electrical device attached to an exterior surface of an aircraft;

a source of electromagnetic radiation that produces a beam of electromagnetic radiation, said source being mounted inside a fuselage of the aircraft;

a receiver configured to convert electromagnetic radiation from said source into electrical power, said receiver being mounted outside said fuselage and electrically connected to said electrical device; and

a plate into which said receiver is integrated, said plate being attached to the outside of a portion of the fuselage that surrounds a cabin window of the aircraft.

14. The system as recited in claim 13, said plate comprising an optical data transceiver electrically connected to said electrical device.

15. The system as recited in claim 13, further comprising sealant material arranged to prevent water from encroaching between said plate and said fuselage.

16. A system for providing electrical power to an electrical device mounted outside an aircraft, comprising:

a first plate attached to the inside of a portion of a fuselage that surrounds a cabin window of said aircraft;

a source of electromagnetic radiation integrated into said first plate;

a second plate attached to the outside of said window; and

a receiver configured to convert electromagnetic radiation from said source into electricity, said receiver being integrated into said second plate and electrically connected to said electrical device.

17. The system as recited in claim 16, said first plate comprising a first optical data transceiver, and said second plate comprising a second optical data transceiver optically coupled to said first optical data transceiver and electrically connected to said electrical device.