Wireless tire pressure and/or wheel speed sensing system for aircraft

• US 7,397,353 B2
• Filed: 07/27/2005
• Issued: 07/08/2008
• Est. Priority Date: 08/25/2003
• Status: Expired due to Fees

• Current Assignee: Rosemount Aerospace, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Rosemount Aerospace, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Williams, Wade W., Norlien, John A., Kunik, William G., Myhre, Douglas C., Buenz, Mark J.
• Primary Examiner(s): Swarthout; Brent
• Application Number:
  US11/190,404
• Publication Number:
  US 20050264406A1
• Time in Patent Office: 1,077 Days
• Field of Search: 340442-448, 340/945, 73146-1465
• US Class Current: 340/448
• CPC Class Codes: B60C 2200/02 for aircrafts
• CPC Class Codes: B60C 23/0428 using passive wheel mounted resonance circuits
• CPC Class Codes: B60C 23/043 using transformer type signal transducers, e.g. rotary transformers
• CPC Class Codes: G01P 3/44 for measuring angular speed G01P3/56 takes precedence
• CPC Class Codes: G01P 3/48 by measuring frequency of generated current or voltage in general G01R23/00

Abstract

A wireless tire pressure sensing system for an aircraft comprises: dual resonant circuits mounted to a wheel of the aircraft, each resonant circuit comprising: a variable capacitance sensor and a wire loop of a predetermined inductance coupled thereto, one capacitance sensor for monitoring the pressure of a tire mounted to the wheel, and the other capacitance sensor operative as a reference to the one capacitance sensor; an interrogating circuit magnetically coupleable to the dual resonant circuits and operative to induce magnetically a variable frequency current in the dual resonant circuits, the one resonant circuit responding to the induced current with an E-field signal at a first resonant frequency commensurate with the capacitance of the one sensor, and the other resonant circuit responding to the induced current with an E-field signal at a second resonant frequency commensurate with the capacitance of the other sensor; a receiving circuit E-field coupleable to the dual resonant circuits and operative to receive the E-field signals at the first and second resonant frequencies and to generate first and second signals representative thereof, and a processing circuit coupled to the receiving circuit for processing the first and second signals to generate a compensated pressure reading of the tire. The pressure sensing system may be modified to provide and/or include wheel speed sensing.

Claims

1. A wireless tire pressure and wheel speed sensing system for an aircraft, said system comprising:

a resonant circuit mounted to a wheel of the aircraft for monitoring the pressure of a tire mounted to said wheel, said resonant circuit comprising a wire loop of a predetermined inductance;

an interrogating circuit magnetically coupleable to said resonant circuit and operative to induce magnetically a variable frequency current in the wire loop of said resonant circuit, said resonant circuit generating a corresponding variable frequency electric field in response to said induced current, said variable frequency electric field including a resonant frequency commensurate with the pressure of said tire;

a magnetic field altering apparatus for alternating the magnetic coupling between said wire loop and said interrogating circuit to cause a rate of amplitude modulations of said variable frequency electric field commensurate with said wheel speed;

a receiving circuit E-field coupleable to said resonant circuit and operative to receive said amplitude modulated variable frequency electric field of said resonant circuit and to generate a signal representative thereof;

a first processing circuit coupled to said receiving circuit for processing said signal to generate a pressure reading of said tire based on the resonant frequency thereof; and

a second processing circuit coupled to said receiving circuit for processing said signal to generate a wheel speed reading based on the rate of amplitude modulations thereof.

2. The system of claim 1 wherein the magnetic field altering apparatus comprises a plurality of magnetic field gratings disposed on the wheel about the perimeter of the wire loop at predetermined intervals for rotation therewith, said gratings acting as shutters to the magnetic coupling at the predetermined intervals during wheel rotation.

3. The system of claim 2 wherein the gratings are electrically grounded to prevent the radiation of a magnetic field therefrom.

4. The system of claim 1 wherein the magnetic field altering apparatus comprises first and second concentrically disposed pluralities of magnetic field gratings, said first plurality of gratings disposed on the wheel about the perimeter of said wire loop at predetermined intervals for rotation therewith, and said second plurality of gratings mounted stationary with respect to said first plurality of gratings, said first and second pluralities of gratings acting as shutters to the magnetic coupling at the predetermined intervals during wheel rotation.

5. The system of claim 1 wherein the magnetic field altering apparatus comprises a plurality of elements of ferro-magnetic material disposed on the wheel about the perimeter of said wire loop at predetermined intervals for rotation therewith.

6. The system of claim 1 wherein the magnetic field altering apparatus comprises a plurality of permanent magnets disposed on the wheel about the perimeter of said wire loop at predetermined intervals for rotation therewith.

7. The system of claim 1 including an aircraft bus;

and wherein the first and second processing circuits are coupled to said aircraft bus for conducting the tire pressure reading and wheel speed reading over the aircraft bus.

8. A wireless wheel speed sensing system for an aircraft, said system composing:

a wire loop mounted to a wheel of the aircraft and rotating therewith;

an interrogating circuit magnetically coupleable to said rotating wire loop and operative to induce magnetically a current signal in said rotating wire loop, said rotating wire loop generating a corresponding electric field in response to said induced current;

a magnetic field altering apparatus for alternating the magnetic coupling between said wire loop and said interrogating circuit to cause a rate of amplitude modulations of said electric field commensurate with said wheel speed; and

a receiving circuit statically mounted with respect to the rotating wheel, said receiving circuit operative to receive said amplitude modulated electric field and to generate a signal representative of wheel speed.

9. The system of claim 8 wherein the magnetic field altering apparatus comprises a plurality of magnetic shield gratings disposed about the perimeter of the wire loop at predetermined intervals and insulated therefrom, said magnetic shield gratings acting as shutters to the magnetic coupling at the predetermined intervals during wheel rotation.

10. The system of claim 9 wherein the magnetic shield gratings are electrically grounded to prevent the radiation of a magnetic field therefrom.

11. The system of claim 8 including a support layer mounted to the rotating wheel;

wherein the wire loop is disposed at the support layer; and

wherein the altering apparatus includes a plurality of magnetic shield gratings disposed on a first side of the layer about the perimeter of the wire loop at predetermined intervals, each grating attached at one end to the first side of the support layer and cantilevered over the wire loop, said gratings acting as shutters to the magnetic field at the predetermined intervals during wheel rotation.

12. The system of claim 11 wherein the altering apparatus includes a second plurality of magnetic shield gratings disposed on a second side of the layer about the perimeter of the wire loop at predetermined intervals, each grating of the second plurality attached at one end to the second side of the support layer and cantilevered over the wire loop.

13. The system of claim 11 wherein the wire loop is embedded in the support layer.

14. The system of claim 11 wherein the support layer is mounted to a hub of the wheel.

15. The system of claim 11 including a supporting ring for coupling together the unattached ends of the plurality of gratings.

16. The system of claim 11 wherein the receiving circuit comprises a statically mounted wire loop concentric with the rotating wire loop;

and wherein the altering apparatus includes a second plurality of magnetic shield gratings disposed at predetermined intervals about a static perimeter concentric with the rotating perimeter of the wire loop.

17. The system of claim 16 wherein the static wire loop and second plurality of magnetic shield gratings are mounted to an axle of the wheel.

18. The system of claim 8 including an aircraft bus;

and wherein the receiving circuit is coupled to said aircraft bus for conducting the wheel speed signal over the aircraft bus.

19. The system of claim 8 wherein the altering apparatus includes forming shaped extensions from the periphery of the wire loop at predetermined intervals about the periphery, said shaped wire loop extensions causing a rate of amplitude modulations of the electric field commensurate with the wheel speed.

20. The system of claim 19 wherein the wire loop is shaped in the form of a multi-pointed star with said star apexes at the predetermined intervals about the periphery.

21. The system of claim 19 including a support layer mounted to the rotating wheel;

wherein the wire loop is disposed at the support layer.

22. The system of claim 8 including a support layer mounted to the rotating wheel;

wherein the wire loop is disposed at the support layer; and

wherein the altering apparatus includes a plurality of elements of ferro-magnetic material disposed on a first side of the layer about the perimeter of the wire loop at predetermined intervals, said elements acting to distort the magnetic field at the predetermined intervals during wheel rotation.