Heater power modulation based on outside air temperature and aircraft velocity

Patent metadata

Field	Value
Publication number	US-2021300571-A1
Application number	US-202016828666-A
Country	US
Kind code	A1
Filing date	Mar 24, 2020
Priority date	Mar 24, 2020
Publication date	Sep 30, 2021
Grant date	—

Abstract

A system for heating an aircraft component of an aircraft includes a heater mat located adjacent the aircraft component and to generate heat. The system further includes a controller coupled to the heater mat and configured to receive an aircraft speed of the aircraft and an outside air temperature (OAT), and to control the heater mat based on the OAT and the aircraft speed.

First claim

What is claimed is:

1 . A system for heating an aircraft component of an aircraft, the system comprising:
a heater mat located adjacent the aircraft component and to generate heat; and a controller coupled to the heater mat and configured to receive an aircraft speed of the aircraft and an outside air temperature (OAT), and to control the heater mat based on the OAT and the aircraft speed.

2 . The system of claim 1 , wherein the controller is configured to control the heater mat by increasing power to the heater mat in response to the aircraft speed increasing and by decreasing power to the heater mat in response to the aircraft speed decreasing.

3 . The system of claim 2 , wherein the controller is further configured to control the heater mat by increasing power to the heater mat in response to the OAT decreasing and by decreasing power to the heater mat in response to the OAT increasing.

4 . The system of claim 3 , wherein the controller is configured to control the heater mat by increasing or decreasing a duty cycle of power provided to the heater mat.

5 . The system of claim 4 , wherein the controller is configured to use the OAT to determine a main duty cycle and to use the aircraft speed as an additive to the main duty cycle.

6 . The system of claim 4 , wherein the controller is configured to use the aircraft speed to determine a main duty cycle and to use the OAT as an additive to the main duty cycle.

7 . The system of claim 1 , further comprising a temperature sensor located adjacent or in the heater mat and configured to detect the OAT.

8 . The system of claim 1 , wherein the controller is configured to receive the OAT from an aircraft computer of the aircraft.

9 . The system of claim 1 , further comprising a speed sensor located adjacent or in the heater mat and configured to detect the aircraft speed.

10 . The system of claim 1 , wherein the controller is configured to receive the aircraft speed from an aircraft computer of the aircraft.

11 . The system of claim 1 , wherein the controller is further configured to receive a liquid water content (LWC) of air outside the aircraft, and to control the heater mat further based on the LWC.

12 . The system of claim 1 , wherein the controller is further configured to receive an angle of attack (AOA), and to control the heater mat further based on the AOA.

13 . A system for heating an aircraft component of an aircraft, the system comprising:
a heater mat located adjacent the aircraft component and to generate heat; a temperature sensor configured to detect an outside air temperature (OAT); and a controller coupled to the temperature sensor and the heater mat and configured to receive an aircraft speed of the aircraft and to control the heater mat based on the OAT and the aircraft speed.

14 . The system of claim 13 , wherein the controller is configured to control the heater mat by increasing power to the heater mat in response to the aircraft speed increasing and by decreasing power to the heater mat in response to the aircraft speed decreasing.

15 . The system of claim 14 , wherein the controller is further configured to control the heater mat by increasing power to the heater mat in response to the OAT decreasing and by decreasing power to the heater mat in response to the OAT increasing.

16 . A method for heating an aircraft component of an aircraft, the method comprising:
receiving, by a controller, an aircraft speed of the aircraft and an outside air temperature (OAT); and controlling, by the controller, a heater mat located adjacent the aircraft component based on the aircraft speed and the OAT.

17 . The method of claim 16 , wherein controlling the heater mat further includes controlling the heater mat by increasing power to the heater mat in response to the aircraft speed increasing and by decreasing power to the heater mat in response to the aircraft speed decreasing.

18 . The method of claim 17 , wherein controlling the heater mat further includes controlling the heater mat by increasing power to the heater mat in response to the OAT decreasing and by decreasing power to the heater mat in response to the OAT increasing.

19 . The method of claim 18 , wherein controlling the heater mat further includes controlling the heater mat by increasing or decreasing a duty cycle of power provided to the heater mat.

20 . The method of claim 19 , wherein controlling the heater mat further includes using the OAT to determine a main duty cycle and using the aircraft speed as an additive to the main duty cycle.

Assignees

• Goodrich Corp

Inventors

• Zadell Alex
• Botura Galdemir Cezar
• Selvaraj Sugumaran
• Ridouane El Hassan
• Debbadi Karthik

Classifications

• B64D15/12 Primary

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

• B64D15/22

  Automatic initiation by icing detector · CPC title

• G01P13/025

  indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw · CPC title

• B64D15/00

  De-icing or preventing icing on exterior surfaces of aircraft · CPC title