Oxidation catalyst detector for aircraft components

Patent metadata

Field	Value
Publication number	US-9678029-B2
Application number	US-201414466714-A
Country	US
Kind code	B2
Filing date	Aug 22, 2014
Priority date	Aug 22, 2014
Publication date	Jun 13, 2017
Grant date	Jun 13, 2017

Abstract

The exposure of an aircraft component to an oxidation catalyst, such as a deicing solution, may be detected with the aid of an electrical conductivity sensor. In some examples, a system includes an aircraft component, an electrical conductivity sensor mechanically connected to the aircraft component and configured to generate an output, and a processor configured to detect an oxidation catalyst exposure event based on the output generated by the electrical conductivity sensor. The electrical conductivity sensor may be configured and positioned to generate a signal indicative of electrical conductivity of a substance to which the aircraft component is exposed. The processor may be configured to detect an oxidation catalyst exposure event by at least determining whether the electrical conductivity indicated by the signal is greater than or equal to a predetermined conductivity threshold value.

First claim

What is claimed is:

1. A system comprising:
an aircraft brake assembly;
an electrical conductivity sensor mechanically connected to the aircraft brake assembly and configured to generate an output; and
a processor configured to detect an oxidation catalyst exposure event based on the output generated by the electrical conductivity sensor by at least:
determining an electrical conductivity value based on the output of the electrical conductivity sensor,
comparing the electrical conductivity value to a predetermined conductivity threshold value, and
detecting the oxidation catalyst exposure event in response to determining the electrical conductivity value is greater than or equal to the predetermined conductivity threshold value.

2. The system of claim 1 , further comprising a memory, wherein the processor is configured to store an indication of the oxidation catalyst exposure event in the memory.

3. The system of claim 1 , wherein the threshold conductivity value is 30 millisiemens/centimeter (mS/cm).

4. The system of claim 1 , wherein the electrical conductivity sensor comprises a conductivity meter and two electrodes, the conductivity meter being configured to generate the output, the output being a function of an impedance of a substance positioned between the two electrodes.

5. The system of claim 1 , wherein the electrical conductivity sensor comprises an array of electrical conductivity sensors mechanically connected to the aircraft brake assembly, and wherein the processor is configured to detect the oxidation catalyst exposure event based on the output of at least one electrical conductivity sensor of the array.

6. The system of claim 1 , further comprising a plurality of aircraft components including the aircraft brake assembly, wherein the electrical conductivity sensor comprises a plurality of electrical conductivity sensors, wherein each aircraft component of the plurality of aircraft components is mechanically connected to at least one electrical conductivity sensor of the plurality of electrical conductivity sensors, and wherein the processor is configured to detect the oxidation catalyst exposure event based on the output generated by at least one of the electrical conductivity sensors.

7. The system of claim 1 , wherein the aircraft brake assembly includes a piston housing, and wherein the electrical conductivity sensor is mechanically connected to the piston housing.

8. The system of claim 1 , wherein the electrical conductivity sensor is a first electrical conductivity sensor, and wherein the output of the first electrical conductivity sensor is a first output, the system further comprising:
an aircraft component, wherein the aircraft component is a wheel well, a landing gear component, or an aircraft fuselage; and
a second electrical conductivity sensor mechanically connected to the aircraft component and configured to generate a second output,
wherein the processor is configured to detect an oxidation catalyst exposure event based on the first output and the second output.

9. A method comprising:
receiving, by a processor, an output of an electrical conductivity sensor mechanically connected to an aircraft brake assembly;
detecting, by the processor, an oxidation catalyst exposure event based on the output, wherein detecting the oxidation catalyst exposure event based on the output comprises:
determining an electrical conductivity value based on the output of the electrical conductivity sensor;
comparing the electrical conductivity value to a predetermined conductivity threshold value; and
detecting the oxidation catalyst exposure event in response to determining the electrical conductivity value is greater than or equal to the predetermined conductivity threshold value;
generating, by the processor, an indication of the oxidation exposure event; and storing the indication of the oxidation exposure event in a memory of a device.

10. The method of claim 9 , wherein the aircraft brake assembly includes a piston housing, and wherein the electrical conductivity sensor is mechanically connected to the piston housing.

11. The method of claim 9 , wherein the predetermined conductivity threshold value is 30 millisiemens/centimeter.

12. The method of claim 9 , wherein the electrical conductivity sensor comprises a conductivity meter and two electrodes, the conductivity meter being configured to generate the output, the output being a function of an impedance of a substance positioned between the two electrodes.

13. The method of claim 9 , wherein receiving the output of the electrical conductivity sensor comprises receiving outputs from an array of electrical conductivity sensors mechanically connected to the aircraft brake assembly, and wherein detecting the oxidation catalyst exposure event based on the output comprises detecting the oxidation catalyst exposure event based on the output of at least one electrical conductivity sensor of the array.

14. The method of claim 9 , wherein receiving the output of the electrical conductivity sensor comprises receiving outputs from a plurality of electrical conductivity sensors, wherein at least two electrical conductivity sensors of the plurality of electrical conductivity sensors are mechanically connected to different aircraft components including the aircraft brake assembly, and wherein detecting the oxidation catalyst exposure event comprises detecting the oxidation catalyst exposure event based on the output generated by at least one electrical conductivity sensor of the plurality of electrical conductivity sensors.

15. The method of claim 9 , wherein the electrical conductivity sensor is a first electrical conductivity sensor, and wherein the output of the first electrical conductivity sensor is a first output, the method further comprising:
receiving, by the processor, a second output of a second electrical conductivity sensor mechanically connected to an aircraft component, wherein the aircraft component is at least one of: a carbon aircraft component, a wheel well, a landing gear component, or an aircraft fuselage;
detecting, by the processor, an oxidation catalyst exposure event based on the first output and the second output.

16. A system comprising:
means for sensing electrical conductivity of a substance to which an aircraft brake assembly is exposed; and
means for detecting an oxidation catalyst exposure event based on an output of the means for sensing electrical conductivity, wherein the means for detecting the oxidation catalyst exposure event comprises:
means for determining an electrical conductivity value based on the output of the means for sensing electrical conductivity; and
means for comparing the electrical conductivity value to a predetermined conductivity threshold value,
wherein the means for detecting detects the oxidation catalyst exposure event in response to determining the electrical conductivity value is greater than or equal to the predetermined conductivity threshold value.

17. The system of claim 16 , further comprising:
means for generating an indication of the oxidation catalyst exposure event, based on an output of the means for sensing electrical conductivity; and
means for storing the indication.

18. The system of claim 16 , wherein the aircraft brake assembly includes a piston housing, and wherein the means for sensing electrical conductivity is mechanically connected to the piston housing.

Assignees

• Honeywell Int Inc

Inventors

• Rateick Richard

Classifications

• F16D66/00

  Arrangements for monitoring working conditions, e.g. wear, temperature · CPC title

• B60T17/22

  Devices for monitoring or checking brake systems; Signal devices · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B60T17/18 Primary

  Safety devices; Monitoring · CPC title

• G01N27/20

  Investigating the presence of flaws · CPC title