AIRCRAFT BRAKE TEMPERATURE MEASUREMENT

• US 20170363482A1
• Filed: 05/15/2017
• Published: 12/21/2017
• Est. Priority Date: 05/16/2016
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE), Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE), Airbus Operations SAS (Airbus SE)
• Inventors: BRUGGEMANN, Kurt, CHERAY, Brice
• Granted Patent: US 10,564,050 B2
• Time in Patent Office: Days
• CPC Class Codes: B60T 17/22 Devices for monitoring or checking brake systems; Signal devices
• CPC Class Codes: B64C 25/42 Arrangement or adaptation of brakes
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: F16D 2066/001 Temperature
• CPC Class Codes: G01K 1/024 for remote indication
• CPC Class Codes: G01K 11/24 of the velocity of propagation of sound
• CPC Class Codes: G01K 13/08 in rotary movement
• CPC Class Codes: H04W 84/18 Self-organising networks, e.g. ad-hoc networks or sensor networks

Abstract

A brake temperature sensing system for an aircraft including a sensor apparatus and an interrogation apparatus. The sensor apparatus includes a temperature sensor for attachment to a brake disc of an aircraft brake, and a relay for attachment to the brake. The temperature sensor is configured to wirelessly transmit a measurement signal containing information relating to a temperature of the brake disc, responsive to receiving a wireless interrogation signal. The relay is configured to receive an interrogation signal from the interrogation apparatus; wirelessly transmit the interrogation signal to the temperature sensor; receive the wireless measurement signal from the temperature sensor; and transmit the received measurement signal. The interrogation apparatus comprises a controller configured to generate an interrogation signal; and a transceiver configured to transmit the generated interrogation signal to the sensor apparatus; and receive the measurement signal transmitted by the sensor apparatus.

Claims

1. A sensor apparatus for use in measuring the temperature of an aircraft brake, the sensor apparatus comprising:

a temperature sensor configured for attachment to a brake disc of an aircraft brake, the temperature sensor being configured to wirelessly transmit a measurement signal containing information relating to a temperature of the brake disc, responsive to receiving a wireless interrogation signal; and

a relay for attachment to the brake, the relay being configured to;

receive an interrogation signal from a remote interrogation apparatus;

wirelessly transmit the received interrogation signal to the temperature sensor;

receive the wireless measurement signal from the temperature sensor; and

transmit the received measurement signal.

2. The sensor apparatus according to claim 1, wherein the relay is configured to wirelessly transmit the received measurement signal, and comprises a first antenna configured for mounting at a first location on the brake, connected by a wire to a second antenna configured for mounting at a second location on the brake.

3. The sensor apparatus according to claim 1, wherein the relay is configured to transmit the measurement signal along a wire, and comprises an antenna for mounting on the brake, the antenna being connectable by a wire to the remote interrogation apparatus.

4. The sensor apparatus according to claim 1, wherein the temperature sensor comprises a transducer configured to transduce the received wireless interrogation signal into a surface acoustic wave, and to transduce the surface acoustic wave into the measurement signal.

5. The sensor apparatus according to claim 4, wherein the transducer comprises a piezoelectric transducer comprising at least one interdigitated electrode.

6. A brake temperature sensing system for an aircraft, the brake temperature sensing system comprising:

a sensor apparatus according to claim 1; and

an interrogation apparatus configured for use in measuring the temperature of an aircraft brake, the interrogation apparatus comprising;

a controller configured to;

generate an interrogation signal configured to cause a remote sensor apparatus to transmit a measurement signal containing information relating to the temperature of a brake disc; and

a transceiver configured to;

transmit the generated interrogation signal to the remote sensor apparatus; and

receive the measurement signal transmitted by the remote sensor apparatus.

7. The brake temperature sensing system according to claim 6, wherein the controller is further configured to determine a temperature of a brake disc based on a received measurement signal.

8. The brake temperature sensing system according to claim 6, wherein the transceiver is one or more of:

configured to receive the measurement signal via a wireless connection to the remote sensor apparatus; and

configured to receive the measurement signal via a wired connection to the remote sensor apparatus.

9. The brake temperature sensing system according to claim 6, wherein the controller is configured to modulate the interrogation signal to minimize interference with other signals which may be present in a signal path between the transceiver and the remote sensor apparatus when the interrogation apparatus is in operation on an aircraft.

10. The brake temperature sensing system according to claim 6, wherein the transceiver comprises a separate unit from the controller, and wherein the transceiver is connected to the controller by a communications link.

11. The brake temperature sensing system according to claim 6, wherein the controller is configured to generate the interrogation signal responsive to receiving a command signal from an aircraft on which the interrogation apparatus is installed.

12. The brake temperature sensing system according to claim 6, wherein the controller is further configured to output, to an aircraft on which the interrogation apparatus is installed, a reporting signal based on a received measurement signal.

13. An aircraft brake comprising a brake disc, a further component located such that it is between the brake disc and a landing gear when the brake is in operation on the landing gear, and the sensor apparatus of claim 1;

wherein the temperature sensor is attached to the brake disc and the relay is attached to the further component.

14. The aircraft brake according to claim 13, wherein the further component comprises a torque tube.

15. The aircraft brake according to claim 13, wherein the temperature sensor is bonded to the brake disc.

16. The aircraft brake according to claim 13, wherein the brake disc comprises a stator.

17. The aircraft brake according to claim 13, wherein the brake disc is located at or near the center of the brake in the axial direction.

18. The aircraft brake according to claim 13, wherein the relay comprises an antenna at a first location on the brake and a wire connected to the antenna and extending between the first location and a second location on the brake;

wherein the brake further comprises a structure configured to impede the transmission of wireless signals through the structure; and

wherein the structure is between the first location and the second location and is not between the first location and the temperature sensor.

19. An aircraft comprising an aircraft brake and the interrogation apparatus of the system of claim 6, wherein the interrogation apparatus is one or more of:

attached to a landing gear on which the aircraft brake is mounted;

attached to a wing of the aircraft;

attached to a fuselage of the aircraft; and

comprised in an avionics box of the aircraft.

20. A brake disc assembly for use in an aircraft brake, the brake disc assembly comprising:

a temperature sensor attached to a brake disc by a mounting element,

wherein the brake disc comprises a first formation and

the mounting element comprises a second formation shaped to interlock with the first formation to prevent relative movement between the brake disc and the mounting element along an axial direction and a circumferential direction of the brake disc.

21. The brake disc assembly according to claim 20, wherein the first formation comprises a recess in a circumferential surface of the brake disc, and wherein the second formation is shaped to be receivable within the recess.

22. The brake disc assembly according to claim 21, wherein the recess comprises a notch configured to receive a spline on a torque tube of the brake pack, wherein the mounting element comprises a clip disposed between the surface of the notch and the spline when the spline is received in the notch, and wherein the second formation comprises a section of the clip having an external profile shaped to match an internal profile of the notch.

23. The brake disc assembly according to claim 21, wherein the mounting element comprises a pin, wherein the stem of the pin is received within the recess, and wherein the temperature sensor is attached to the head of the pin.

24. The brake disc assembly according to claim 23, wherein the brake disc comprises a notch configured to receive a spline on a torque tube of the brake pack, and wherein the recess is in a base of the notch such that the head of the pin is adjacent the base of the notch.

25. The brake disc assembly according to claim 20, wherein the mounting element comprises a portion of adhesive material disposed between the first formation and the temperature sensor, and wherein the second formation is comprised by a surface of the portion of adhesive material in contact with the first formation.

26. The brake disc assembly according to claim 25, wherein the adhesive material comprises a ceramic epoxy material.

27. A method of attaching a temperature sensor to a brake disc for an aircraft brake, the method comprising:

providing a brake disc comprising a first formation;

providing a mounting element on the brake disc such that the first formation is interlocked with a second formation of the mounting element to prevent relative movement between the brake disc and the mounting element along an axial direction and a circumferential direction of the brake disc; and

providing the temperature sensor on the mounting element.

28. The method according to claim 27, wherein providing the temperature sensor on the mounting element comprises bonding the temperature sensor to the mounting element.

29. The method according to claim 27, wherein the mounting element comprises a portion of cured adhesive material, wherein providing the mounting element on the brake disc comprises applying uncured adhesive material to the surface of the first formation to create the second formation, and wherein providing the temperature sensor on the mounting element comprises contacting the temperature sensor with the uncured adhesive material and subsequently curing the adhesive material