CURIE TEMPERATURE CONTROLLED INDUCTION HEATING

• US 20080128078A1
• Filed: 12/01/2006
• Published: 06/05/2008
• Est. Priority Date: 12/01/2006
• Status: Abandoned Application

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: May, Tom, Wilenski, Mark S.
• Application Number:
  US11/565,900
• Publication Number:
  US 20080128078A1
• Time in Patent Office: Days
• US Class Current: 156/272.4
• CPC Class Codes: B29C 2035/0811 using induction
• CPC Class Codes: B29C 2035/0816 using eddy currents
• CPC Class Codes: B29C 73/10 using patches sealing on the surface of the article B29C73/14 takes precedence
• CPC Class Codes: H05B 2206/023 using the curie point of the material in which heating current is being generated to control the heating temperature
• CPC Class Codes: H05B 6/106 in the form of fillings

Abstract

A heating apparatus and a method for using a heating apparatus for repairing composite structures. The heating apparatus includes a high temperature matrix having magnetic particles therein. The magnetic particles have a predetermined Curie temperature. The apparatus also includes a coil in communication with a power source. The coil is disposed adjacent the matrix and magnetic particles. The coil provides an alternating current sufficient to heat the magnetic particles up to about the predetermined Curie temperature. The method utilizes the uniform heat provided by the heating apparatus to bond a repair patch to a composite material.

Claims

1. A heating apparatus comprising:

a matrix having a surface and magnetic particles, the magnetic particles having a Curie temperature; and

a coil operatively coupled to an alternating current power source, the coil being disposed near the magnetic particles, the coil configured to heat the magnetic particles to a temperature up to about their Curie temperature.

2. The apparatus of claim 1, wherein the heat provided by the matrix is substantially uniform along the surface.

3. The heating apparatus of claim 1, wherein the matrix comprises a high temperature matrix.

4. The apparatus of claim 1, further comprising a controller to regulate current from the power source.

5. The apparatus of claim 1, wherein the predetermined Curie temperature is a temperature from about room temperature to about 650°

F.

6. The apparatus of claim 5, wherein the predetermined Curie temperature is a temperature from about 160°

F. temperature to about 650°

F.

7. The apparatus of claim 6, wherein the predetermined Curie temperature is a temperature from about 250°

F. temperature to about 350°

F.

8. The apparatus of claim 1, wherein the matrix is selected from the group consisting of polyetheretherketone, polyetherketoneketone and combinations thereof.

9. The apparatus of claim 1, wherein the magnetic particles contain a material selected from the group consisting of magnetite, Cu—

Ni—

Fe alloys, samarium containing materials, neodymium containing materials and combinations thereof.

10. The apparatus of claim 1, wherein the surface is sealable to a substrate to form a vacuum bag.

11. A method of repairing composite structures comprising:

applying a repair patch to a damaged substrate surface, the repair patch comprising an uncured matrix material and adhesive;

placing a heating apparatus substantially near at least a portion of the repair patch, the heating apparatus comprising;

a matrix having magnetic particles therein, the magnetic particles having a predetermined Curie temperature; and

a coil operatively coupled to a power source, the coil being disposed near the magnetic particles; and

providing an alternating current to the coil sufficient to heat the magnetic particles up to about the predetermined Curie temperature.

12. The method of claim 11, wherein the matrix comprises a high temperature matrix.

13. The method of claim 11, further comprising curing the composite patch with heat generated by the heating apparatus.

14. The method of claim 11, wherein the repair patch comprises a thermoset or thermoplastic material.

15. The method of claim 14, wherein the resin material is selected from the group consisting of epoxy, bismalemide, polyimide, cyanate ester and combinations thereof

16. The method of claim 11, wherein the repair patch further comprises reinforcing fibers.

17. The method of claim 16, wherein the reinforcing fibers are selected from the group consisting of carbon fibers, graphite fibers, boron fibers, silicon carbide fibers, glass fibers, organic fibers and combinations thereof.

18. The method of claim 16, wherein the reinforcing fibers are preimpregnated fibers.

19. The apparatus of claim 11, further comprising a controller to regulate current from the power source.

20. The method of claim 11, wherein the predetermined Curie temperature is a temperatures from about room temperature to about 650°

F.

21. The method of claim 20, wherein the predetermined Curie temperature is a temperatures from about 160°

F. temperature to about 650°

F.

22. The method of claim 21, wherein the predetermined Curie temperature is a of temperatures from about 250°

F. temperature to about 350°

F.

23. The method of claim 11, wherein the matrix is selected from the group consisting of polyetheretherketone, polyetherketoneketone and combinations thereof.

24. The method of claim 11, wherein the magnetic particles contain a material selected from the group consisting of magnetite, Cu—

Ni—

Fe alloys, samarium containing materials, neodymium containing materials and combinations thereof.

25. The method of claim 11, wherein the damaged substrate surface is part of a mobile platform.

26. The method of claim 11, further comprising placing a vacuum bag overlying the heating apparatus and the repair patch.

27. The method of claim 11, further comprising placing a vacuum bag intermediate to the heating apparatus and the repair patch.