HEATING ELEMENTS FOR AIRCRAFT HEATED FLOOR PANELS

• US 20150053662A1
• Filed: 02/12/2014
• Published: 02/26/2015
• Est. Priority Date: 08/21/2013
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Rtx Corporation)
• Original Assignee: Goodrich Corporation (Rtx Corporation)
• Inventors: Hu, Jin, Hamm, Richard R., Roach, Kevin E.
• Granted Patent: US 9,623,951 B2
• Time in Patent Office: Days
• US Class Current: 219/202
• CPC Class Codes: B64C 1/18 Floors
• CPC Class Codes: B64D 13/00 Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space , or structural parts of the aircraft treatment rooms with artificial climate for medical purposes A61G10/02; respiratory apparatus in general A62B; for vehicles in general B60H
• CPC Class Codes: F24D 13/024 in walls, floors, ceilings
• CPC Class Codes: F24D 2200/08 Electric heater
• CPC Class Codes: F24D 2220/2081 Floor or wall heating panels
• CPC Class Codes: H05B 2203/003 using serpentine layout
• CPC Class Codes: H05B 2203/013 Heaters using resistive films or coatings
• CPC Class Codes: H05B 2203/017 Manufacturing methods or apparatus for heaters
• CPC Class Codes: H05B 3/16 the conductor being mounted on an insulating base
• CPC Class Codes: H05B 3/26 heating conductor mounted on insulating base for transparent areas H05B3/84, H05B3/86
• CPC Class Codes: H05K 1/167 incorporating printed resistors
• CPC Class Codes: H05K 2201/09263 Meander
• CPC Class Codes: H05K 3/1216 by screen printing or stencil printing
• CPC Class Codes: H05K 3/1283 After-treatment of the printed patterns, e.g. sintering or curing methods
• CPC Class Codes: H05K 3/38 Improvement of the adhesion between the insulating substrate and the metal
• CPC Class Codes: Y02B 30/00 Energy efficient heating, ventilation or air conditioning [HVAC]
• CPC Class Codes: Y10T 29/49155 Manufacturing circuit on or in base
• CPC Class Codes: Y10T 29/49162 by using wire as conductive path

Abstract

A method of forming a heating element includes depositing a conductive ink of silver particles in an epoxy resin on a dielectric film to create a conductive circuit, and heat curing the conductive circuit to achieve a resistivity of the heating element less than 1.68×10⁻⁶ ohm·meter. An aircraft heated floor panel includes at least one floor panel of an aircraft includes a conductive circuit positioned within the floor panel having a conductive ink of silver particles in an epoxy resin on a dielectric film.

Claims

1. A method of forming a heating element, the method comprising:

depositing a conductive ink of silver particles in an epoxy resin on a dielectric film to create a conductive circuit; and

heat curing the conductive circuit to achieve a resistivity of the heating element less than 1.68×

10<sup>−

6</sup> ohm·

meter.

2. A method as recited in claim 1, wherein a 0.001 inch (50.8 microns) to 0.004 inch (101.6 microns) thick post-cure layer of the conductive ink is configured to achieve the resistivity of the heating element and be bent around a ¼

inch (0.635 cm) diameter cylinder rod without experiencing electric resistance degradation.

3. A method as recited in claim 1, wherein the step of heat curing includes curing at a temperature between 155°

C.-200°

C.

4. A method as recited in claim 1, wherein the silver loading is between 65%-95% weight/weight of dry ink.

5. A method as recited in claim 1, wherein the step of heat curing includes curing at a temperature between a glass transition temperature of the conductive ink and a maximum thermal stability temperature of the conductive ink, wherein the glass transition temperature is lower than the maximum thermal stability temperature and the maximum thermal stability temperature is greater than 155°

C.

6. A method as recited in claim 1, wherein the step of depositing includes screen printing the conductive ink onto the dielectric film.

7. A method as recited in claim 1, wherein the step of depositing includes depositing a patterned layer of the conductive ink.

8. A method as recited in claim 1, further including applying the conductive circuit to at least one panel skin of an aircraft floor panel.

9. An aircraft heated floor panel comprising:

at least one floor panel of an aircraft includes a heating element with a conductive circuit positioned within the floor panel, wherein the conductive circuit includes a conductive ink of silver particles in an epoxy resin on a dielectric film.

10. An aircraft heated floor panel as recited in claim 9, wherein the conductive ink is disposed onto the dielectric film in a patterned layer.

11. An aircraft heated floor panel as recited in claim 9, wherein the silver loading is between 65%-95% weight/weight of dry ink.

12. An aircraft heated floor panel as recited in claim 9, wherein the conductive circuit is post-cured at a temperature between a glass transition temperature of the conductive ink and a maximum thermal stability temperature of the conductive ink, wherein the glass transition temperature is lower than the maximum thermal stability temperature and the maximum thermal stability temperature is greater than 155°

C.

13. An aircraft heated floor panel as recited in claim 9, wherein the conductive circuit is post-cured at a temperature between 155°

C. and 200°

C.

14. An aircraft heated floor panel as recited in claim 9, where the resistivity of the heating element is less than 1.68×

10<sup>−

6</sup> ohm·

meter.

15. An aircraft heated floor panel as recited in claim 14, wherein a 0.001 inch (50.8 microns) to 0.004 inch (101.6 microns) thick post-cure layer of the conductive ink is configured to achieve the resistivity of the heating element and be bent around a ¼

inch (0.635 cm) diameter cylinder rod without experiencing electric resistance degradation.