Embedded thermal sensing within electrical power harness

Patent metadata

Field	Value
Publication number	US-2025033790-A1
Application number	US-202318359676-A
Country	US
Kind code	A1
Filing date	Jul 26, 2023
Priority date	Jul 26, 2023
Publication date	Jan 30, 2025
Grant date	—

Abstract

Systems and methods for an overheating control system for an electrical power harness disposed within an enclosure of an aircraft. The system includes a temperature sensor disposed within the enclosure and communicatively coupled to an electronic processor. The electronic processor is configured to monitor, via the temperature sensor, a temperature within the enclosure, compare the temperature to a predetermined threshold, and adjust a power output provided to one or more supply lines of the harness based on an amount in which the temperature exceeds the predetermined threshold.

First claim

What is claimed is:

1 . A control system for an electrical power harness disposed within an enclosure of an aircraft, the system comprising:
a temperature sensor disposed within the enclosure; an electronic processor configured to:
monitor, via the temperature sensor, a temperature within the enclosure;
compare the temperature to a predetermined threshold; and
adjust a power output provided to one or more power supply lines of the harness in response to the temperature exceeding the predetermined threshold.

2 . The system of claim 1 , wherein the enclosure is a rotor shaft of the aircraft.

3 . The system of claim 1 , wherein the one or more power supply lines includes a high-voltage power supply line.

4 . The system of claim 3 , wherein the high-voltage power supply line is a 270 VDC line.

5 . The system of claim 2 , wherein the electrical power harness provides power to a de-icing system of the aircraft.

6 . The system of claim 1 , wherein the temperature sensor is disposed within the electrical power harness.

7 . The system of claim 1 , wherein the electronic processor is configured to adjust the power output by adjusting a duty cycle of the power output.

8 . The system of claim 1 , wherein the electronic processor is configured to adjust the power output by adjusting the power output based on amount in which the temperature exceeds the predetermined amount.

9 . The system of claim 1 , wherein the electronic processor is configured to adjust the power output by adjusting a power usage profile of a de-icing system of the aircraft.

10 . A method of controlling an electrical power harness disposed within an enclosure of an aircraft, the method including:
monitoring, via a temperature sensor, a temperature within the enclosure; comparing, via an electronic processor, the temperature to a predetermined threshold; and adjusting a power output provided to one or more power supply lines of the electrical power harness based on an amount in which the temperature exceeds the predetermined threshold.

11 . The method of claim 10 , wherein the enclosure is a rotor shaft of the aircraft.

12 . The method of claim 10 , wherein the one or more power supply lines include a high-voltage power supply line.

13 . The method of claim 12 , wherein the high-voltage power supply line is a 270 VDC line.

14 . The method of claim 10 , wherein the one or more power supply lines of the electrical power harness provides power to a de-icing system of the aircraft.

15 . The method of claim 10 , wherein the temperature sensor is disposed within the electrical power harness.

16 . The method of claim 8 , wherein adjusting the power output includes adjusting a duty cycle of the power output.

17 . An electronic controller installed in an aircraft, the electronic controller comprising:
an input-output interface configured to receive a signal from a temperature sensor disposed within an enclosure of the aircraft including an electrical power harness; an electronic processor configured to:
monitor, via the signal received from the temperature sensor, a temperature within the enclosure;
compare the temperature to a predetermined threshold; and
adjust a power output provided to one or more power supply lines of the harness based on an amount in which the temperature exceeds the predetermined threshold.

Assignees

• Lockheed Corp

Inventors

• Bourne Frederick L
• Andrews Bernard J
• Eisenhauer Mark P
• Massaquoi Hans R
• Asaro Carlo
• Crespo Elvis Arturo
• Budd Timothy R

Classifications

• G01K3/005

  Circuits arrangements for indicating a predetermined temperature (fire detection G08B17/00) · CPC title

• B64D15/12 Primary

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title

• B64C27/04

  Helicopters · CPC title

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title