Probe heater remaining useful life determination

• US 10,197,517 B2
• Filed: 03/24/2017
• Issued: 02/05/2019
• Est. Priority Date: 03/24/2017
• Status: Active Grant

• 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: Essawy, Magdi A., Fok, Ben Ping-Tao, Onken, Marvin Gary
• Primary Examiner(s): Porta, David
• Assistant Examiner(s): Gutierrez, Gisselle
• Application Number:
  US15/468,860
• Publication Number:
  US 20180275080A1
• Time in Patent Office: 683 Days
• Field of Search: 250340
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B
• 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: B64D 47/08 Arrangements of cameras
• CPC Class Codes: G01J 2005/0077 Imaging
• CPC Class Codes: G01J 5/025 Interfacing a pyrometer to an external device or network; User interface
• CPC Class Codes: G01K 13/028 for use in total air temperature [TAT] probes
• CPC Class Codes: G01K 15/007 Testing
• CPC Class Codes: G01N 25/72 Investigating presence of flaws
• CPC Class Codes: G01N 27/026 Dielectric impedance spectroscopy electrochemical impedance spectroscopy for measuring corrosion G01N17/02
• CPC Class Codes: G01N 27/20 Investigating the presence of flaws
• CPC Class Codes: G01N 27/24 Investigating the presence of flaws
• CPC Class Codes: G01P 13/025 indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
• CPC Class Codes: G01P 5/165 Arrangements or constructions of Pitot tubes
• CPC Class Codes: G01R 19/32 Compensating for temperature change
• CPC Class Codes: G01R 31/008 on air- or spacecraft, railway rolling stock or sea-going vessels
• CPC Class Codes: H05B 1/0236 for vehicles
• CPC Class Codes: H05B 2214/02 Heaters specially designed for de-icing or protection against icing
• CPC Class Codes: H05B 3/44 heating conductor arranged within rods or tubes of insulating material
• CPC Class Codes: H05B 3/56 Heating cables

Abstract

A probe system is configured to receive thermal images of the probe system from a thermal imager and includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe. An operational voltage is provided to the resistive heating element to provide heating for the probe. The control circuit is configured to provide the operational voltage and receive the thermal images from the thermal imager. The control circuit is further configured to monitor the thermal images over time and determine a remaining useful life of the probe system based upon the thermal images over time.

Claims

1. A system for an aircraft, the system comprising:

a probe that includes a heater comprising a resistive heating element routed through the probe, wherein an operational voltage is provided to the resistive heating element to provide heating for the probe;

a thermal imager configured to capture thermal images of the probe; and

a control circuit configured to provide the operational voltage and receive the thermal images from the thermal imager, wherein the control circuit is configured to monitor the thermal images over time to determine a thermal response of the resistive heating element, and wherein the control circuit is configured to normalize the thermal response based upon at least one of a temperature of the probe, a shape of the probe and an external emissivity of the probe, and wherein the control circuit is configured to determine a remaining useful life of the probe based upon the normalized thermal response.

2. The system of claim 1, wherein the thermal images are captured by the thermal imager while the probe is receiving the operational voltage.

3. The system of claim 1, wherein the control circuit monitors the thermal images over time by monitoring a thermal image of the probe over a plurality of flights of the aircraft.

4. The system of claim 3, wherein the control circuit further monitors the thermal images to monitor a thermal response of the resistive heating element over the plurality of flights of the aircraft.

5. The system of claim 4, wherein the control circuit stores and plots the thermal response of the resistive heating element over the plurality of flights and determines a half-life estimate based upon the stored and plotted thermal response.

6. The system of claim 1, further comprising a temperature sensor configured to sense the temperature of the probe and provide the sensed temperature to the control circuit.

7. The system of claim 1, wherein the temperature of the probe is an estimated temperature of the probe.

8. A method for determining a remaining useful life of an aircraft probe, the method comprising:

providing an operational current to a resistive heating element of the aircraft probe;

capturing, by a thermal imager, thermal images of the aircraft probe;

monitoring, by a control circuit, the thermal images of the aircraft probe to determine a thermal response of the aircraft probe over time;

normalizing, by the control circuit, the thermal response based on at least one of a present temperature of the aircraft probe, a shape of the aircraft probe and an external emissivity of the aircraft probe; and

determining, by the control circuit, a remaining useful life of the aircraft probe based upon the normalized thermal response.

9. The method of claim 8, wherein capturing, by a thermal imager, the thermal images of the aircraft probe comprises:

capturing, by the thermal imager, the thermal images during a plurality of flights, wherein the thermal images are captured while the resistive heating element is receiving the operational current.

10. The method of claim 9, wherein monitoring, by the control circuit, the thermal images of the aircraft probe to determine the thermal response of the aircraft probe over time comprises:

determining, by the control circuit, thermal data for the resistive heating element over the plurality of flights of the aircraft; and

storing, by the control circuit, the thermal data over each of the plurality of flights.

11. The method of claim 10, wherein monitoring, by the control circuit, the thermal images of the aircraft probe to determine the thermal response of the aircraft probe over time further comprises:

sensing, by a temperature sensor, the present temperature of the aircraft probe.

12. The method of claim 10, wherein monitoring, by the control circuit, the thermal images of the aircraft probe to determine the thermal response of the aircraft probe over time further comprises:

estimating, by the control circuit, the present temperature of the aircraft probe.

13. The method of claim 12, wherein determining, by the control circuit, the remaining useful life of the aircraft probe based upon the thermal response comprises:

plotting, by the control circuit, the thermal data over the plurality of flights; and

determining a half-life estimate based on the plotted thermal data over the plurality of flights.

14. A probe system configured to receive thermal images of the probe system from a thermal imager, the probe system comprising:

heater comprising a resistive heating element routed through the probe, wherein an operational voltage is provided to the resistive heating element to provide heating for the probe; and

a control circuit configured to provide the operational voltage and receive the thermal images from the thermal imager, wherein the control circuit is configured to monitor the thermal images over time to determine a thermal response of the resistive heating element and determine a remaining useful life of the probe system based upon the thermal response, and wherein the control circuit is further configured to normalize the thermal response based upon at least one of a temperature of the probe, a shape of the probe, and an external emissivity of the probe.

15. The probe system of claim 14, wherein the thermal images are captured by the thermal imager while the probe is receiving the operational voltage.

16. The probe system of claim 14, wherein the control circuit monitors the thermal images over time by monitoring a thermal image of the probe over a plurality of flights of the aircraft.

17. The probe system of claim 16, wherein the control circuit further monitors the thermal images to monitor the thermal response of the resistive heating element over the plurality of flights of the aircraft.

18. The probe system of claim 17, wherein the control circuit stores and plots the thermal response of the resistive heating element over the plurality of flights and determines a half-life estimate based upon the stored and plotted thermal response.