System and method for thermal mitigation for tire pressure measurement electronics

• US 20140010264A1
• Filed: 07/09/2012
• Published: 01/09/2014
• Est. Priority Date: 07/09/2012
• Status: Active Grant

• Current Assignee: Meggitt Safety Systems, Inc. (Meggitt PLC)
• Original Assignee: Meggitt Incorporated (Amphenol Corporation)
• Inventors: Smith, Gary Thomas
• Granted Patent: US 9,381,779 B2
• Time in Patent Office: Days
• US Class Current: 374/143
• CPC Class Codes: B60C 2200/02 for aircrafts
• CPC Class Codes: B60C 23/0498 for rim attachments B60C23/0494, B60C23/0496 take precedence
• CPC Class Codes: B64C 25/36 Arrangements or adaptations of wheels, tyres or axles in general
• CPC Class Codes: G01K 1/12 for preventing damage due to heat overloading
• CPC Class Codes: G01K 13/08 in rotary movement

Abstract

A thermal pressure measurement assembly coupled to a rim of an aircraft wheel. A housing is configured to be fastened to a wheel face. An electronics enclosure is positioned in the housing. Electronics are positioned in the electronics enclosure and configured to process a signal received from a remote sensor that measures tire pressure and temperature. Internal insulation is positioned in an interior of the housing. The internal insulation is configured to reduce the temperature of the electronics sufficiently to permit use of low temperature electronics rated to 125 degrees C.

Claims

1. A thermal pressure measurement assembly coupled to a rim of an aircraft wheel, comprising:

a housing configured to be fastened to a wheel face;

an electronics enclosure positioned in the housing;

electronics positioned in the electronics enclosure and configured to process a signal received from a remote sensor that measures tire pressure and temperature; and

internal insulation positioned in an interior of the housing, the internal insulation configured to reduce the temperature of the electronics sufficiently to permit use of low temperature electronics rated to 125 degrees C.

2. The assembly of claim 1, wherein the internal insulation is of a quantity and positioned to provide that an interior temperature of an enclosure for the low temperature electronics does not exceed 125 degrees C.

3. The assembly of claim 1, wherein the housing includes a main body housing, a lower body housing, an intermediate housing, an electronics enclosure and a separate or integral cap.

4. The assembly of claim 1, further comprising:

external insulation positioned at an external surface of the housing.

5. The assembly of claim 4, wherein the internal and external insulation are of a quantity and positioned to provide that an interior temperature of an enclosure for the low temperature electronics does not exceed 125 degrees C.

6. The assembly of claim 1, wherein the insulation is made of a material selected from among materials exhibiting thermal insulating properties greater than the material of construction of the main housing.

7. The assembly of claim 1, wherein the insulation provides insulation greater than that provided by the main housing material.

8. The assembly of claim 1, wherein the internal insulator is in the form of a ring, or some other profile matching the TPM mounting interface on the wheel.

9. The assembly of claim 1, wherein the internal insulator is positioned near the top of the hubcap.

10. The assembly of claim 1, wherein the remote sensor is coupled to a rim of the wheel and is electrical coupled to the electronics.

11. The assembly of claim 1, wherein the housing includes a top cap.

12. The assembly of claim 1, wherein the internal insulator retards a transfer of heat by radiation, conduction and convention, from the hub cap, wheel and brakes of the aircraft, into the electronics.

13. The assembly of claim 1, wherein the remote sensor is coupled to the electronics with a conduit.

14. The assembly of claim 1, wherein at least a portion of the internal insulation is positioned between a housing main body and a housing cover.

15. The assembly of claim 1, wherein the remote sensor is a pressure sensor.

16. The assembly of claim 1, wherein the remote sensor is a piezoresistive, piezoelectric or MEMS pressure sensor.

17. The assembly of claim 4, wherein internal and external insulator 16s are provided on a same lower housing body element.

18. The assembly of claim 17, wherein the lower housing body element is coupled to the hubcap main body via fasteners.

19. The assembly of claim 18, wherein the fasteners are thermally isolated from the electronics.

20. The assembly of claim 1, wherein at least a portion of the internal insulator 16 includes collet insulation.

21. The assembly of claim 4, wherein the internal insulator include at least one of, a ring, one or more insulator collets and an insulator positioned at the intermediate housing body element.

22. The assembly of claim 4, wherein the thermal pressure measurement assembly is positioned over an axial opening of the wheel. An external thermal insulation is provided at an external surface of the hubcap.

23. The assembly of claim 1, wherein the electronics includes an ASIC that conditions a signal generated by the pressure sensor to obtain a first analog pressure output signal.

24. The assembly of claim 23, wherein the electronics includes an analog signal line coupled to a corresponding pressure input port of an ECU microprocessor.