System for powering and controlling a device associated with a rotating component on aircraft

• US 6,851,929 B2
• Filed: 03/19/2002
• Issued: 02/08/2005
• Est. Priority Date: 03/19/2002
• Status: Expired due to Term

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Goldberg, Joshua I.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): MCALEENAN, JAMES M
• Application Number:
  US10/101,908
• Publication Number:
  US 20030180145A1
• Time in Patent Office: 1,057 Days
• Field of Search: 416/1, 416/95, 416/61, 415/118, 318/811, 318/599, 318/139
• US Class Current: 416/1
• CPC Class Codes: B64C 11/00 Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
• CPC Class Codes: B64D 15/14 controlled cyclically along length of surface
• CPC Class Codes: F01D 7/00 Rotors with blades adjustable in operation; Control thereof for reversing F01D1/30
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A system for providing power and communication signals to a device associated with a rotating component on an aircraft includes a communication strategy that allows power and command signals to be propagated along the same conductors. A stationary controller provides power and command signals to a controller that is supported for rotation with the rotating device. Only two slip rings are required to communicate power and command signals between the stationary and rotating controllers. Synchronous modulation preferably is used for sending the command signals to avoid interference from noise inherent in slip ring electrical couplings. A multi-zone propeller deicing heater is one example device that is controllable using the inventive approach.

Claims

1. A system for providing power and control information to a device associated with a rotating component of an aircraft, comprising:

a power supply supported on the aircraft that remains stationary when the rotating component rotates;

an electrical coupling that accommodates relative rotation between the device and the power supply and conducts electrical power from the power supply to the device;

a device controller supported to rotate with the device; and

a stationary controller supported on the aircraft to remain stationary when the rotating component rotates, the stationary controller communicating with the device controller using synchronously modulated communication signals that are transmitted through the electrical coupling.

2. The system of claim 1, wherein the electrical coupling has only two slip rings and a plurality of conductive brushes associated with each ring.

3. The system of claim 1, wherein the device controller and the stationary controller each include a communication portion that sends and receives the communication signals, each communication portion provides a reference signal with a selected frequency ω

and a message signal having a frequency ω

/N, where N is an integer, and wherein the synchronously modulated communication signals comprise a sum of the message signal and the reference signal.

4. The system of claim 3, wherein the synchronously modulated communication signals comprise binary ones or zeros and wherein the ones comprise a sum of the positive phase of the message signal and the reference signal and the zeros comprise a sum of the negative phase of the message signal and the reference signal.

5. The system of claim 1, wherein the device comprises an electric heater used to prevent ice build up on a propeller having a plurality of zones and wherein the synchronously modulated communication signals comprise commands to activate at least one of the zones.

6. The system of claim 5, wherein the stationary controller issues at least one command to the device controller to selectively activate or deactivate at least one of the zones and the device controller issues confirmation messages to the stationary controller indicating that the device controller has received the command and has responsively activated or deactivated the corresponding zone.

7. The system of claim 5, wherein the stationary controller includes a transformer that provides an indication of an amount of current draw across the electrical coupling and wherein the stationary controller determines whether the device is being operated consistent with the command by determining the amount of current draw.

8. The system of claim 5, wherein the rotating component comprises a propeller assembly having a plurality of propeller blades and the electrical coupling has only two slip rings and a plurality of conductive brushes associated with each ring and wherein the heater zones are each associated with a corresponding one of the propeller blades and there are only two electrical leads between each blade and the slip rings.

9. A method of powering and controlling a device associated with a rotating component on an aircraft, comprising the steps of:

providing an electrical coupling that accommodates relative rotation between the device and another portion of the aircraft;

supplying power to the device across the electrical coupling; and

sending synchronously modulated communication signals to the device across the same electrical coupling including at least one command signal indicative of a desired operation of the device.

10. The method of claim 9, wherein the electrical coupling has only two slip rings and a plurality of conductive brushes associated with each slip ring.

11. The method of claim 9, including synchronously demodulating the communication signals at the device and controlling the device responsive to the command signals and sending at least one confirmation signal back across the electrical coupling indicating that the command signal was received and responsive action taken.

12. The method of claim 9, including synchronously modulating the communication signals by adding a reference signal having a selected frequency ω

to a selected phase of the command signal having a frequency ω

/N, where N is an integer.

13. A propeller assembly for use on an aircraft, comprising:

a plurality of propeller blades supported to rotate relative to another portion of the aircraft;

at least one electrical device supported to rotate with the propeller blades;

a power supply supported on the aircraft that remains stationary when the propeller blades rotate;

an electrical coupling that accommodates relative rotation between the electrical device and the power supply and conducts electrical power from the power supply to the device;

a device controller supported to rotate with the device; and

a stationary controller supported on the aircraft to remain stationary when the propeller blades rotate, the stationary controller communicating with the device controller using synchronously modulated communication signals that are transmitted through the electrical coupling.

14. The assembly of claim 13, wherein the electrical coupling has only two slip rings and a plurality of conductive brushes associated with each ring.

15. The assembly of claim 13, wherein the device controller and the stationary controller each include a communication portion that sends and receives the communication signals, each communication portion provides a reference signal with a selected frequency ω

and a message signal having a frequency ω

/N, where N is an integer, and wherein the synchronously modulated communication signals comprise a sum of the message signal and the reference signal.

16. The assembly of claim 15, wherein the synchronously modulated communication signals comprise binary ones or zeros and wherein the ones comprise a sum of the positive phase of the message signal and the reference signal and the zeros comprise a sum of the negative phase of the message signal and the reference signal.

17. The assembly of claim 13, wherein the device comprises an electric heater used to prevent ice build up on the blades, the heater having a plurality of zones at least one of the zones being associated with each of the propeller blades and wherein the synchronously modulated communication signals include a command to activate at least one of the zones.

18. The assembly of claim 17, wherein the stationary controller issues at least one command to the device controller to selectively activate or deactivate at least one of the zones and the device controller issues a confirmation message to the stationary controller indicating that the device controller has received the command and has responsively activated or deactivated the corresponding zone.

19. The assembly of claim 17, wherein the stationary controller includes a transformer that provides an indication of an amount of current draw across the electrical coupling and wherein the stationary controller determines whether the heater is being operated consistent with the command by determining the amount of current draw.

20. The assembly of claim 17, wherein the electrical coupling has only two slip rings and a plurality of conductive brushes associated with each ring and wherein the heater zones are each associated with a corresponding one of the propeller blades and there are only two electrical leads between each blade and the slip rings.