Air data sensing probe with icing condition detector

Patent metadata

Field	Value
Publication number	US-10132824-B2
Application number	US-201715625323-A
Country	US
Kind code	B2
Filing date	Jun 16, 2017
Priority date	Jun 28, 2016
Publication date	Nov 20, 2018
Grant date	Nov 20, 2018

Abstract

A system includes a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface, a first current monitor configured to sense a first measurement value representing electrical current flow through the first self-compensating heater, one or more processors, and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to receive aircraft flight condition data and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.

First claim

The invention claimed is:

1. A system comprising:
a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface;
a first current monitor configured to produce a first measurement value representing electrical current flow through the first self-compensating heater;
one or more processors; and
computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to:
receive aircraft flight condition data; and
produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.

2. The system of claim 1 , wherein the computer-readable memory is further encoded with instructions that, when executed by the one or more processors, cause the system to produce the icing condition signal to include an indication of an amount of liquid water content within the airflow.

3. The system of claim 1 , wherein the computer-readable memory is further encoded with instructions that, when executed by the one or more processors, cause the system to:
determine one or more parameters of expected electrical current flow through the first self-compensating heater based on the received aircraft flight condition data; and
determine whether the first measurement value exceeds a first threshold deviation from the one or more parameters of expected electrical current flow,
wherein the computer-readable memory is further encoded with instructions that, when executed by the one or more processors, cause the system to produce the icing condition signal based upon the first measurement value and the aircraft flight condition data responsive to determining that the first measurement value exceeds the first threshold deviation from the one or more parameters of expected electrical current flow.

4. The system of claim 3 , further comprising:
a second current monitor;
wherein the device comprises a second surface exposed to the airflow about the exterior of the aircraft and a second self-compensating heater configured to heat the second surface;
wherein the second current monitor is configured to sense a second measurement value representing electrical current flow through the second self-compensating heater;
wherein the computer-readable memory is further encoded with instructions that, when executed by the one or more processors, cause the system to:
determine whether the first measurement value exceeds a second threshold deviation from the second measurement value;
produce the icing condition signal to include an indication of a solid water icing condition in response to determining that the first measurement value exceeds the second threshold deviation from the second measurement value; and
produce the icing condition signal to include an indication of a solid water icing condition in response to determining that the first measurement value exceeds the second threshold deviation from the second measurement value.

5. The system of claim 1 , wherein the one or more parameters of expected electrical current flow through the first self-compensating heater comprise an expected electrical current draw.

6. The system of claim 1 , wherein the one or more parameters of expected electrical current flow through the first self-compensating heater comprise an expected rate of change of electrical current draw.

7. The system of claim 1 ,
wherein the device comprises an air data sensing probe; and
wherein the first self-compensating heater is disposed in a probe head portion of the air data sensing probe.

8. The system of claim 7 , wherein the second self-compensating heater is disposed in a strut portion of the air data sensing probe that extends between the probe head portion and a mounting plate configured to mount the air data probe to an aircraft exterior.

9. The system of claim 7 , wherein the air data sensing probe comprises a total air temperature probe.

10. The system of claim 1 , further comprising:
one or more communication devices configured to send and receive data over an aircraft data bus;
wherein the computer-readable memory is further encoded with instructions that, when executed by the one or more processors, cause the system to output the icing conditions signal over the aircraft data bus via the one or more communication devices.

11. A method comprising:
receiving a first measurement value representing electrical current flow through a first self-compensating heater that heats a first surface of a device exposed to airflow about an exterior of an aircraft;
receiving aircraft flight condition data; and
producing an icing condition signal based upon the first measurement value and the aircraft flight condition data.

12. The method of claim 11 , wherein producing the icing condition signal comprises producing the icing condition signal to include an indication of an amount of liquid water content of the airflow about the device.

13. The method according to claim 11 , further comprising:
determining one or more parameters of expected electrical current flow through the first self-compensating heater based on the received aircraft flight condition data; and
determining whether the first measurement value exceeds a first threshold deviation from the one or more parameters of expected electrical current flow, wherein producing the icing condition signal based upon the first measurement value and the aircraft flight condition data is responsive to determining that the first measurement value exceeds the first threshold deviation from the one or more parameters of expected electrical current flow.

14. The method according to claim 13 , further comprising:
receiving a second measurement value representing electrical current flow through a second self-compensating heater that heats a second surface of the device exposed to the airflow about the exterior of the aircraft; and
determining whether the first measurement value exceeds a second threshold deviation from the second measurement value;
wherein producing the icing condition signal comprises:
producing the icing condition signal to include an indication of a liquid water icing condition in response to determining that the first measurement value does not exceed the second threshold deviation from the second measurement value; and
producing the icing condition signal to include an indication of a solid water icing condition in response to determining that the first measurement value exceeds the second threshold deviation from the second measurement value.

15. The method according to claim 11 , wherein the one or more parameters of expected electrical current flow through the first self-compensating heater comprise an expected electrical current draw.

16. The method according to claim 11 , wherein the one or more parameters of expected electrical current flow through the first self-compensating heater comprise an expected rate of change of electrical current draw.

17. The method according to claim 11 , wherein the first self-compensating heater is disposed in a probe head portion of an air data sensing probe.

18. The method according to claim 17 , wherein the second self-compensating heater is disposed in a strut portion of the air data sensing probe that extends between the probe head portion and a mounting plate configured to mount the air data probe to the exterior of the aircraft.

19. The method according to claim 17 , wherein the air data sensing probe compr

Assignees

• Rosemount Aerospace Inc
• Rosemount Aerospace Inc

Inventors

• Benning Kevin
• Heuer Weston Daniel Clarence

Classifications

• G01P5/165 Primary

  Arrangements or constructions of Pitot tubes · CPC title

• G01K13/028

  for use in total air temperature [TAT] probes · CPC title

• B64D15/20

  Means for detecting icing or initiating de-icing · CPC title