Overheat sensor system

Patent metadata

Field	Value
Publication number	US-9415882-B2
Application number	US-201414285304-A
Country	US
Kind code	B2
Filing date	May 22, 2014
Priority date	May 22, 2014
Publication date	Aug 16, 2016
Grant date	Aug 16, 2016

Abstract

An overheat sensor system is provided. A controller may create an aircraft temperature profile and may compare temperature sensor data to the profile. The system may provide an output indicating temperatures or fires.

First claim

What is claimed is:

1. An overheat sensor system comprising:
a controller comprising a processor and a tangible, non-transitory memory;
a sensor bus in logical communication with the controller; and
a first sensor in logical communication with the controller via the sensor bus and configured to receive first infrared radiation from a first location under observation;
a second sensor comprising an acoustical sensor in logical communication with the controller via the sensor bus and configured to detect flying debris capable of impeding the operation of the first sensor; and
avionics comprising an aircraft data bus whereby avionics input data indicating a mode of flight is provided to the controller,
wherein the controller is configured to take a first action in response to the mode of flight and a first indication that the first infrared radiation from the first location exceeds a first threshold corresponding to the mode of flight, and
wherein the first sensor comprises a temperature-sensing element configured to detect infrared radiation with a wavelength between 700 nm and 1 mm and a fire-sensing element configured to detect infrared radiation with a wavelength less than that of the temperature-sensing element, whereby each is configured to detect the first infrared radiation from the first location.

2. The overheat sensor system according to claim 1 , wherein the first sensor comprises a temperature-sensing element configured to detect the first infrared radiation from the first location.

3. The overheat sensor system according to claim 1 , further comprising:
a third sensor in logical communication with the controller via the sensor bus and configured to receive a second infrared radiation from a second location under observation,
wherein the overheat sensor system is installed in an aircraft,
wherein the controller is configured to take a second action in response to a second indication that the second infrared radiation from the second location exceeds a second threshold.

4. The overheat sensor system according to claim 3 , further comprising:
an output device comprising a panel located in a cockpit of the aircraft;
wherein the panel is configured to display a graphical depiction of the aircraft having a first zone and a second zone corresponding to the first location and the second location,
wherein the first zone may display a first color in response to the first action; and wherein the second zone may display a second color in response to the second action.

5. The overheat sensor system according to claim 1 , comprising an output device comprising a non-transitory, tangible memory.

6. A method for overheat sensing comprising:
toggling, by an overheat sensing controller, a controller mode to a calibration mode wherein the calibration mode comprises:
receiving, by the overheat sensing controller, an aircraft mode;
receiving, by the overheat sensing controller, a first sensor temperature indication;
receiving, by the overheat sensing controller, a second sensor temperature indication;
building, by the overheat sensing controller, an aircraft profile comprising:
the first sensor temperature indication;
the second sensor temperature indication; and
the aircraft mode;

toggling, by the overheat sensing controller, the controller mode to an operation mode wherein the operation mode comprises:
receiving, by the overheat sensing controller, the aircraft mode;
receiving, by the overheat sensing controller, a third sensor temperature indication;
receiving, by the overheat sensing controller, a fourth sensor temperature indication;
processing, by the overheat sensing controller, the third sensor temperature indication and the fourth sensor temperature indication, wherein the processing comprises:
comparing, by the overheat sensing controller, the third sensor temperature indication and the aircraft mode to the aircraft profile;
comparing, by the overheat sensing controller, the fourth sensor temperature indication and the aircraft mode to the aircraft profile; and

providing an output to an output device in response to the processing.

7. The method for overheat sensing according to claim 6 , wherein the aircraft profile further comprises a first rate of change of the first sensor temperature indication and a second rate of change of the second sensor temperature indication.

8. The method for overheat sensing according to claim 6 , wherein the receiving the first sensor temperature indication is in response to polling a first sensor.

9. The method for overheat sensing according to claim 6 , wherein the receiving the second sensor temperature indication is in response to polling a second sensor.

10. The method for overheat sensing according to claim 6 , wherein the output device comprises a fire extinguisher system and further comprising triggering the fire extinguisher system in response to the output.

Assignees

• Kidde Tech Inc

Inventors

• Kern Mark T
• Bell Ken
• Rogers Aaron Stanley

Classifications

• G01J5/0014

  for sensing the radiation from gases, flames · CPC title

• B64D2045/009

  Fire detection or protection; Erosion protection, e.g. from airborne particles · CPC title

• G01J5/025

  Interfacing a pyrometer to an external device or network; User interface · CPC title

• F05D2260/80

  Diagnostics · CPC title

• F01D21/12

  responsive to temperature · CPC title