Integrated ice protection system

Patent metadata

Field	Value
Publication number	US-12559240-B2
Application number	US-202217568240-A
Country	US
Kind code	B2
Filing date	Jan 4, 2022
Priority date	Oct 18, 2021
Publication date	Feb 24, 2026
Grant date	Feb 24, 2026

Abstract

A system for controlling ice accumulation on a surface of an aircraft, the system includes a carbon nano-tube (CNT) heater comprising: a CNT layer; a first encapsulation layer disposed on a first side of the CNT layer formed of a first encapsulation layer thermoplastic material; and a second encapsulation layer disposed on a second side of the CNT layer formed of a second encapsulation layer thermoplastic material. The system also includes a fore composite structure that includes a fore composite structure thermoplastic material disposed on the first side of CNT heater, an aft composite structure that includes an aft composite structure thermoplastic material disposed on the first side of CNT heater and a sensor layer disposed between the CNT heater and the one of the fore and aft composite structures.

First claim

What is claimed is:

1 . A system for controlling ice accumulation on a surface of an aircraft, the system comprising:
a carbon nano-tube (CNT) heater comprising:
a CNT layer;
a first encapsulation layer disposed on a first side of the CNT layer formed of a first encapsulation layer thermoplastic material; and
a second encapsulation layer disposed on a second side of the CNT layer formed of a second encapsulation layer thermoplastic material;
a fore composite structure that includes a fore composite structure thermoplastic material disposed on the first side of CNT heater;
an aft composite structure that includes an aft composite structure thermoplastic material disposed on the first side of CNT heater; and
a sensor layer that includes a temperature sensor, the layer disposed between the CNT heater and the aft composite structures.

2 . The system of claim 1 , further comprising:
a controller that receives information from sensors in the sensor layer and controls the CNT heater based on the received information.

3 . The system of claim 2 , further comprising a low ice adhesion coating layer disposed on the fore composite structure on a side of the fore composite structure opposite the CNT heater.

4 . The system of claim 1 , further comprising a low ice adhesion coating layer disposed on the fore composite structure on a side of the fore composite structure opposite the CNT heater.

5 . The system of claim 1 , wherein the sensor layer includes both temperature and strain sensors.

6 . The system of claim 1 , wherein the sensor layer includes fiber optic sensors.

7 . The system of claim 1 , wherein the fore and aft composite structure thermoplastic materials are the same thermoplastic material.

8 . The system of claim 7 , wherein the fore and aft composite structure thermoplastic materials are the same as thermoplastic material of the first and second encapsulation layer thermoplastic materials.

9 . A method of forming a multilayer heating structure for controlling ice accumulation on a surface of an aircraft, the structure comprising:
receiving a carbon nano-tube (CNT) heater comprising: a CNT layer, a first encapsulation layer disposed on a first side of the CNT layer formed of a first encapsulation layer thermoplastic material a second encapsulation layer disposed on a second side of the CNT layer formed of a second encapsulation layer thermoplastic material; receiving a fore composite structure that includes a fore composite structure thermoplastic material; receiving a sensor layer that includes one or more temperature sensors; disposing the fore composite structure on the first side of CNT heater; receiving an aft composite structure that includes an aft composite structure thermoplastic material; disposing the sensor layer the second side of the CNT heater structure; disposing the aft composite structure on the second side of CNT heater such that the sensor layer is between the CNT heater and the aft composite structure to form an assembly that includes the fore composite structure, the CNT heater, the sensor layer and the aft composite structure; and heating the assembly to at least partially melt the fore and aft composite structure thermoplastics and the first and second encapsulation layer thermoplastic to bond the assembly together.

10 . The method of claim 9 , wherein heating includes providing heat with the CNT heater.

11 . The method of claim 10 , wherein the fore and aft composite structure thermoplastic materials are the same thermoplastic material.

12 . The method of claim 9 , wherein the fore and aft composite structure thermoplastic materials are the same as thermoplastic material of the first and second encapsulation layer thermoplastic materials.

13 . The method of claim 9 , further comprising:
disposing a low ice adhesion coating layer on the fore composite structure on a side of the fore composite structure opposite the CNT heater.

Assignees

• Goodrich Corp

Inventors

• Hein Brandon
• Slane Casey
• Werbelow Jeffrey Martin
• Botura Galdemir Cezar
• Hamman Matthew

Classifications

• H05B3/145 Primary

  Carbon only, e.g. carbon black, graphite · CPC title

• H05B2214/04

  Heating means manufactured by using nanotechnology · CPC title

• B64D15/20

  Means for detecting icing or initiating de-icing · CPC title

• B32B2605/18

  Aircraft · CPC title

• B32B2457/00

  Electrical equipment · CPC title