Polymer-encapsulated heating elements for controlling the temperature of an aircraft compartment

• US 20050098684A1
• Filed: 03/14/2003
• Published: 05/12/2005
• Est. Priority Date: 03/14/2003
• Status: Abandoned Application

• Current Assignee: Adel Wiggins Group (Transdigm Group Incorporated), Watlow Electric Manufacturing Company
• Original Assignee: Watlow Polymer Technologies
• Inventors: Silva, Mark, Hofmeister, Dane, Marmsoler, Greg, Gullerud, Steven
• Application Number:
  US10/389,399
• Publication Number:
  US 20050098684A1
• Time in Patent Office: Days
• US Class Current: 244/129.1
• CPC Class Codes: B64D 13/08 the air being heated or cooled
• CPC Class Codes: H05B 2203/003 using serpentine layout
• CPC Class Codes: H05B 3/286 the insulating material being an organic material, e.g. plastic
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

The invention relates to polymer-encapsulated heating elements that are suitable for use in an aircraft compartment for modulating the temperature within the compartment. The heating elements can be used, for example, in the cockpit, the passenger compartment, or a cargo bay of an aircraft.

Claims

1. A method of controlling the temperature within an aircraft compartment, the method comprising activating a heating element in the compartment, wherein the heating element comprises an electrical resistance heating material encapsulated in a substantially non-compressible polymer.

2. The method of claim 1, wherein the heating element is activated when the temperature within the compartment is below a selected minimum temperature.

3. The method of claim 2, wherein the heating element is activated when the temperature within the compartment is not greater than a selected maximum temperature.

4. The method of claim 1, wherein the heating element is activated when the temperature within the compartment is not greater than a selected maximum temperature.

5. The method of claim 1, wherein the heating element is activated periodically while the aircraft is in flight.

6. The method of claim 1, wherein the heating material is connected with a voltage source by way of a pair of electrical terminals extending through the polymer.

7. The method of claim 6, wherein the electrical terminals are connected with voltage source by way of wires and the terminals are encapsulated within a second polymer.

8. The method of claim 1, wherein the heating material is connected with a voltage source by way of a pair of wires extending through the polymer.

9. The method of claim 1, wherein the electrical circuit that comprises the heating element further comprises a temperature sensing device.

10. The method of claim 9, wherein the temperature sensing device contacts the polymer.

11. The method of claim 10, wherein the temperature sensing device is fusible at a selected temperature.

12. The method of claim 10, wherein the temperature sensing device deactivates the heating element if the temperature of the polymer exceeds a selected temperature.

13. The method of claim 10, wherein the temperature sensing device deactivates the heating element if the temperature within the compartment exceeds a selected temperature.

14. The method of claim 9, wherein the temperature sensing device does not contact the polymer.

15. The method of claim 14, wherein the temperature sensing device deactivates the heating element if the temperature within the compartment exceeds a selected temperature.

16. The method of claim 14, wherein the temperature sensing device modulates the voltage applied to the heating element in response to the temperature within the compartment.

17. The method of claim 9, wherein the temperature sensing device modulates the duration of the voltage application to the heating element in response to the temperature within the compartment.

18. The method of claim 9, wherein the temperature sensing device is selected from the group consisting of a thermocouple, a temperature switch.

19. The method of claim 9, wherein the temperature sensing device is a temperature switch.

20. The method of claim 1, wherein the polymer is in the form of a sheet.

21. The method of claim 20, wherein two faces of the sheet are composed of different polymers.

22. The method of claim 21, wherein the polymer on one face of the sheet exhibits a significantly greater thermal conductivity than the polymer on the other face of the sheet.

23. The method of claim 20, wherein the heat-reflective material is attached to the sheet on one side of the heating material.

24. The method of claim 23, wherein the sheet of the heat-reflective material is laminated to the polymer sheet.

25. The method of claim 20, wherein a heat conductor is disposed in the polymer in the plane of the sheet.

26. The method of claim 25, wherein a sheet of the heat conductor is laminated to the polymer sheet.

27. The method of claim 20, wherein an insulating material is disposed against one face of the polymer sheet.

28. The method of claim 27, wherein a sheet of the insulating material is laminated to the polymer sheet.

29. The method of claim 20, wherein the heating material is interposed between two polycarbonate layers.

30. The method of claim 20, wherein a plurality of the polymer-encapsulated heating elements are fixedly attached to one another.

31. The method of claim 20, wherein the sheets are attached in an overlapping manner.

32. The method of claim 31, wherein the heating materials of the elements do not occur in overlapping portions of the sheets.

33. The method of claim 31, wherein the sheets are staked.

34. The method of claim 1, wherein a plurality of the heating elements are electrically connected.

35. The method of claim 34, wherein the heating elements are electrically connected in series.

36. The method of claim 34, wherein the heating elements are electrically connected in parallel.

37. The method of claim 1, wherein the compartment is selected from the group consisting of i) a passenger compartment, ii) a crew department, iii) a cargo compartment, and iv) an avionics compartment.

38. The method of claim 1, wherein a plurality of the polymer-encapsulated heating elements are disposed within the compartment and at least two of the heating elements are independently activatable.

39. The method of claim 38, wherein at least two of the independently activatable heating elements are controlled by thermostats disposed in different regions within the compartment.

40. The method of claim 38, wherein at least two of the independently activatable heating elements are disposed near different seats in the passenger compartment and are controlled by thermostats operable by individuals sitting in the corresponding seats.

41. The method of claim 40, wherein each of the independently activatable heaters is disposed in a location selected from the group consisting of i) within the corresponding seat, ii) beneath the leg space of the corresponding seat, iii) in a wall or ceiling of the compartment adjacent the corresponding seat, and iv) on a surface in front of the corresponding seat.

42. An aircraft compartment heater comprising an electrical resistance heating material encapsulated in a substantially non-compressible polymer, wherein the polymer is substantially in the form of a sheet, the heating material is disposed in a serpentine path within the sheet, and the heater is adapted for attachment to an aircraft.

43-52. -52. (canceled)

53. An aircraft compartment heater system comprising two or more independently activated electrical resistance heaters connected in parallel in an electrical circuit having a voltage source, each heater of which comprises an electrical resistance heating element encapsulated in a substantially non-compressible polymer that is substantially in the form of a sheet, wherein the electrical circuit comprises two or more thermostats disposed in different regions within the aircraft compartment each of which independently modulates the voltage application to the two or more electrical resistance in response to the temperature sensed by each of the two or more thermostats.

54. The aircraft compartment heater system of claim 53, wherein at least two of the independently activatable heating elements are disposed near different seats in the passenger compartment and are controlled by thermostats operable by individuals sitting in the corresponding seats.

55. The aircraft compartment heater system of claim 54, wherein each of the independently activatable heaters is disposed in a location selected from the group consisting of i) within the corresponding seat, ii) beneath the leg space of the corresponding seat, iii) in a wall or ceiling of the compartment adjacent the corresponding seat, and iv) on a surface in front of the corresponding seat.

56. The aircraft compartment heater system of claim 55, wherein the thermometer is selected from the group consisting of a temperature responsive switch, and a thermistor.