Ice protection system including frequency dependent susceptor

Patent metadata

Field	Value
Publication number	US-12037121-B2
Application number	US-202217731926-A
Country	US
Kind code	B2
Filing date	Apr 28, 2022
Priority date	Apr 28, 2022
Publication date	Jul 16, 2024
Grant date	Jul 16, 2024

Abstract

An aircraft ice protection system includes a frequency a frequency dependent susceptor coupled to a critical surface of an aircraft. A radio frequency (RF) energy source is configured to apply RF energy to the frequency dependent susceptor. The aircraft ice protection system is configured to selectively operate in a susceptor absorbing mode and a water absorbing mode. The aircraft ice protection system operates in the susceptor absorbing mode until a Faraday layer associated with ice formed on the critical surface reaches a target characteristic. When the target characteristic is met, the aircraft ice protection system initiates the water absorbing mode.

First claim

What is claimed as:

1. An aircraft ice protection system comprising:
a frequency dependent susceptor coupled to a critical surface of an aircraft;
a radio frequency (RF) energy source configured to apply RF energy to the frequency dependent susceptor,
wherein the aircraft ice protection system is configured to selectively operate in a susceptor absorbing mode and a water absorbing mode.

2. The aircraft ice protection system of claim 1 , wherein the RF energy source delivers the RF energy having a first frequency to the frequency dependent susceptor in response to operating in the susceptor absorbing mode, and delivers the RF energy having a different second frequency to the frequency dependent susceptor in response to operating in the water absorbing mode.

3. The aircraft ice protection system of claim 2 , wherein the RF energy having the first frequency attenuates the frequency dependent susceptor to emit heat therefrom, and wherein the RF energy having the second frequency is transmitted from the frequency dependent susceptor to attenuate a Faraday layer defining a layer of liquid water formed on ice present on the critical surface.

4. The aircraft ice protection system of claim 3 , wherein the first frequency falls within a frequency range that includes a first attenuation frequency of a material of the frequency dependent susceptor, and wherein the second frequency falls within a second range that includes a second attenuation frequency of the liquid water.

5. The aircraft ice protection system of claim 4 , wherein the first frequency is different from the second frequency.

6. The aircraft ice protection system of claim 4 , further comprising a controller in signal communication with the radio frequency (RF) energy source, the controller configured to selectively invoke the susceptor absorbing mode and the water absorbing mode.

7. The aircraft ice protection system of claim 6 , wherein the controller is configured to switch from the susceptor absorbing mode to the water absorbing mode in response to determining the Faraday layer has a target characteristic.

8. The aircraft ice protection system of claim 7 , wherein the controller determines a time period during which the RF energy having the first frequency is delivered to the frequency dependent susceptor, and determines the Faraday layer has the target characteristic in response to the time period exceeding a time period threshold.

9. The aircraft ice protection system of claim 6 , wherein the controller determines scattering parameters of the RF energy having the first frequency and determines one or both of a transmission coefficient and a reflection coefficient of the RF energy having the first frequency, and wherein the controller determines the Faraday layer has the target characteristic in response to one or both of the transmission coefficient being less than a transmission coefficient threshold or the reflection coefficient being greater than a reflection coefficient threshold.

10. The aircraft ice protection system of claim 1 , further comprising at least one dielectric layer covering the critical surface.

11. The aircraft ice protection system of claim 1 , wherein the frequency dependent susceptor includes a thin dielectric layer having an upper surface and an opposing lower surface, and wherein at least one of the upper and lower surfaces includes a patterned metallic structure configured to define an absorbance and transmittance response with respect to a frequency of applied RF energy.

12. A method of removing ice from a critical surface of an aircraft, the method comprising:
applying, by a radio frequency (RF) energy source, RF energy to a frequency dependent susceptor coupled to the critical surface;
selectively operating the aircraft ice protection system in a susceptor absorbing mode and a water absorbing mode; and
removing the ice from the critical surface based on the susceptor absorbing mode and a water absorbing mode.

13. The method of claim 12 , further comprising:
delivering, by the RF energy source, the RF energy having a first frequency to the frequency dependent susceptor in response to operating in the susceptor absorbing mode; and
delivering the RF energy having a different second frequency to the frequency dependent susceptor in response to operating in the water absorbing mode.

14. The method of claim 13 , further comprising:
attenuating the frequency dependent susceptor using the RF energy having the first frequency attenuates to emit heat therefrom; and
transmitting the RF energy having the second frequency from the frequency dependent susceptor to attenuate a Faraday layer defining a layer of liquid water formed on ice present on the critical surface.

15. The method of claim 14 , wherein the first frequency falls within a frequency range that includes a first attenuation frequency of a material of the frequency dependent susceptor, and wherein the second frequency falls within a second range that includes a second attenuation frequency of the liquid water.

16. The method of claim 15 , wherein the first frequency is different from the second frequency.

17. The method of claim 15 , further comprising:
determining a target characteristic of the Faraday layer;
detecting the Faraday layer achieves the target characteristic in response to delivering the RF energy having a first frequency during the susceptor absorbing mode; and
switching from the susceptor absorbing mode to the water absorbing mode in response to detecting the Faraday layer has the target characteristic.

18. The method of claim 17 , further comprising:
determining a time period during which the RF energy having the first frequency is delivered to the frequency dependent susceptor; and
determining the Faraday layer has the target characteristic in response to the time period exceeding a time period threshold.

19. The method of claim 17 , further comprising:
determining scattering parameters of the RF energy having the first frequency;
determining one or both of a transmission coefficient and a reflection coefficient of the RF energy having the first frequency; and
determining the Faraday layer has the target characteristic in response to one or both of the transmission coefficient being less than a transmission coefficient threshold or the reflection coefficient being greater than a reflection coefficient threshold.

20. The method of claim 12 , wherein the frequency dependent susceptor includes a thin dielectric layer having an upper surface and an opposing lower surface, and wherein at least one of the upper and lower surfaces includes a patterned metallic structure configured to define an absorbance and transmittance response with respect to a frequency of applied RF energy.

Assignees

• Rohr Inc

Inventors

• Kestler Steven
• Mantese Joseph V
• Gok Gurkan

Classifications

• B64D15/12 Primary

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