Wireless Power Transmission System and Method for an Aircraft Sensor System

• US 20120234971A1
• Filed: 03/14/2011
• Published: 09/20/2012
• Est. Priority Date: 03/14/2011
• Status: Active Grant

• Current Assignee: Simmonds Precision Products, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Simmonds Precision Products, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Bugash, Robert S., Fusare, Scott T.
• Granted Patent: US 8,686,590 B2
• Time in Patent Office: Days
• US Class Current: 244/102.R
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: H02J 2310/44 for aircrafts
• CPC Class Codes: H02J 50/12 of the resonant type
• CPC Class Codes: H02J 50/80 involving the exchange of data, concerning supply or distribution of electric power, between transmitting devices and receiving devices
• CPC Class Codes: H02J 7/00034 Charger exchanging data with an electronic device, i.e. telephone, whose internal battery is under charge

Abstract

An aircraft sensor system including a primary module configured to be attached to an aircraft portion and operative to transmit electrical power wirelessly. A secondary module configured to be attached to an aircraft component, the secondary module operative to receive electrical power wirelessly from the primary module. At least one sensor configured to be operatively attached to a portion of the aircraft component and electrically coupled to the secondary module, wherein the at least one sensor is operative to measure a desired parameter of the aircraft component.

Claims

1. An aircraft sensor system, the system comprising:

a primary module configured to be attached to an aircraft portion, the primary module operative to transmit electrical power wirelessly;

a secondary module configured to be attached to an aircraft component, the secondary module operative to receive electrical power wirelessly from the primary module; and

at least one sensor configured to be operatively attached to a portion of the aircraft component and electrically coupled to the secondary module, wherein the at least one sensor is operative to measure a desired parameter of the aircraft component.

2. The aircraft sensor system of claim 1, wherein the primary module and secondary module are operative to transfer electrical power wirelessly by inductive coupling.

3. The aircraft sensor system of claim 1, wherein the primary module and secondary module are operative to transfer electrical power wirelessly by resonant inductive coupling.

4. The aircraft sensor system of claim 1, wherein the aircraft component is a retractable landing gear assembly.

5. The aircraft sensor system of claim 1, wherein the primary module is configured to be mounted in close proximity to the secondary module.

6. The aircraft sensor system of claim 1, further including a power storage module configured to be mounted in close proximity to the aircraft component and being electrically coupled to the at least one sensor, the power storage module operative to provide electrical power to the at least one sensor.

7. The aircraft sensor system of claim 6, wherein the power storage module includes at least one rechargeable battery configured to store electrical power.

8. The aircraft sensor system of claim 6, wherein the power storage module includes at least one capacitor configured to store electrical power.

9. The aircraft sensor system of claim 6, wherein the power storage module is configured to provide electrical power to the at least one sensor during periods when the secondary module is not receiving electrical power from the primary module.

10. The aircraft sensor system of claim 6, wherein the secondary module is configured to charge the power storage module with electrical power received from the primary module.

11. An aircraft sensor system, the system comprising:

a primary module configured to be attached to an aircraft portion, the primary module operative to transmit electrical power wirelessly and operative to receive data wirelessly;

a secondary module configured to be attached to an aircraft component, the secondary module operative to receive electrical power wirelessly from the primary module and transmit data wirelessly to the primary module; and

at least one sensor configured to be operatively attached to a portion of the aircraft component and electrically coupled to the secondary module, wherein the at least one sensor is operative to measure a desired parameter of the aircraft component and provide corresponding data to the secondary module.

13. The aircraft sensor system of claim 11, wherein the primary module and secondary module are operative to transfer electrical power wirelessly by resonant inductive coupling.

14. The aircraft sensor system of claim 11, wherein the primary module is operative to transmit data wirelessly and the secondary module is operative to receive data wirelessly.

15. The aircraft sensor system of claim 11, wherein the aircraft component is a retractable landing gear assembly.

16. The aircraft sensor system of claim 11, wherein the primary module is configured to be mounted proximal to the secondary module.

17. The aircraft sensor system of claim 11, further including a power storage module configured to be mounted proximal to the aircraft component and being electrically coupled to the at least one sensor, the power storage module operative to provide electrical power to the at least one sensor.

18. The aircraft sensor system of claim 16, wherein the power storage module includes at least one rechargeable battery configured to store electrical power.

19. The aircraft sensor system of claim 16, wherein the power storage module includes at least one capacitor configured to store electrical power.

20. The aircraft sensor system of claim 16, wherein the power storage module is configured to provide electrical power to the at least one sensor during periods when the secondary module is not receiving electrical power from the primary module.

21. The aircraft sensor system of claim 16, wherein the secondary module is configured to charge the power storage module with electrical power received from the primary module.

12. (canceled)

22-24. -24. (canceled)