Control of electric pump-driven deicer

Patent metadata

Field	Value
Publication number	US-12097963-B2
Application number	US-202117495260-A
Country	US
Kind code	B2
Filing date	Oct 6, 2021
Priority date	Oct 6, 2021
Publication date	Sep 24, 2024
Grant date	Sep 24, 2024

Abstract

Examples described herein provide a computer-implemented method that includes receiving static data about an aircraft. The method further includes receiving dynamic data about flight conditions for a flight of the aircraft. The method further includes determining, based on the static data and the dynamic data, an amount of air pressure and a volumetric air flow to apply from an electric pump to a deicing device. The method further includes controlling the electric pump to cause the electric pump to apply the amount of air pressure and the volumetric air flow to the deicing device.

First claim

What is claimed is:

1. A method comprising:
receiving static data about an aircraft;
receiving dynamic data about flight conditions for a flight of the aircraft;
determining, based on the static data and the dynamic data, an amount of air pressure and a volumetric air flow to apply from an electric pump to a deicing device, wherein the amount of air pressure and volumetric air flow is an amount determined to maintain a threshold difference between an ambient pressure and a pressure within the deicing device, such that the pressure within the deicing device is maintained at least the threshold difference below the ambient pressure when the pressure within a device is below the ambient pressure and such that the pressure within the deicing device is maintained at least the threshold difference above the ambient pressure when the pressure within the device is above the ambient pressure; and
controlling the electric pump to cause the electric pump to apply the amount of air pressure and the volumetric air flow to the deicing device, wherein the amount of air pressure is negative thereby creating a vacuum effect.

2. The method of claim 1 , wherein the static data do not change during the flight of the aircraft.

3. The method of claim 1 , wherein the dynamic data change during the flight of the aircraft.

4. The method of claim 1 , wherein the dynamic data is received in real-time from a sensor of the aircraft.

5. The method of claim 1 , wherein the amount of air pressure is based at least in part on a pressure difference between a desired pressure and the ambient pressure.

6. A controller comprising:
a memory storing processor-executable instructions; and
a processor to execute the processor-executable instructions to cause operations to be performed, the operations comprising:
receiving static data about an aircraft;
receiving dynamic data about flight conditions for a flight of the aircraft;
determining, based on the static data and the dynamic data, an amount of air pressure to apply from an electric pump to a deicing device, wherein the amount of air pressure and volumetric air flow is an amount determined to maintain a threshold difference between ambient pressure and pressure within the deicing device, such that the pressure within the deicing device is maintained at least the threshold difference below the ambient pressure when the pressure within a device is below the ambient pressure and the pressure within the deicing device is maintained at least the threshold difference above the ambient pressure when the pressure within the device is above the ambient pressure; and
controlling the electric pump to cause the electric pump to apply the amount of air pressure to the deicing device, wherein the amount of air pressure is negative thereby creating a vacuum effect.

7. The controller of claim 6 , wherein the static data do not change during the flight of the aircraft.

8. The controller of claim 6 , wherein the dynamic data change during the flight of the aircraft.

9. The controller of claim 6 , wherein the dynamic data is received in real-time from a sensor of the aircraft.

10. The controller of claim 6 , wherein the amount of air pressure is based at least in part on a pressure difference between a desired pressure and an ambient pressure.

11. A system comprising:
a deicing device;
an electric pump in fluid communication with the deicing device; and
a controller communicatively coupled to the electric pump, the controller comprising:
a memory storing processor-executable instructions; and
a processor to execute the processor-executable instructions to cause operations to be performed, the operations comprising:
receiving static data about an aircraft;
receiving dynamic data about flight conditions for a flight of the aircraft;
determining, based on the static data and the dynamic data, an amount of air pressure to apply from the electric pump to the deicing device, wherein the amount of air pressure and volumetric air flow is an amount determined to maintain a threshold difference between an ambient pressure and a pressure within the deicing device, such that the pressure within the deicing device is maintained at least the threshold difference below the ambient pressure when the pressure within a device is below the ambient pressure and the pressure within the deicing device is maintained at least the threshold difference above the ambient pressure when the pressure within the device is above the ambient pressure; and
controlling the electric pump to cause the electric pump to apply the amount of air pressure to the deicing device, wherein the amount of air pressure is negative thereby creating a vacuum effect.

12. The system of claim 11 , wherein the static data do not change during the flight of the aircraft.

13. The system of claim 11 , wherein the dynamic data change during the flight of the aircraft.

14. The system of claim 11 , wherein the dynamic data is received at least in part from an ice detection system associated with the aircraft.

Assignees

• Goodrich Corp

Inventors

• Slane Casey
• Werbelow Jeffrey Martin
• Shen Guangqing
• Botura Galdemir Cezar

Classifications

• B64D15/166 Primary

  using pneumatic boots · CPC title

• B64D15/04

  Hot gas application · CPC title

• B64D15/22 Primary

  Automatic initiation by icing detector · CPC title