Heat Resistance Using Titanium Dioxide Nanofibers

• US 20100285264A1
• Filed: 11/17/2008
• Published: 11/11/2010
• Est. Priority Date: 11/17/2008
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Slaton, Daniel B., Harris, John N.
• Granted Patent: US 8,916,082 B2
• Time in Patent Office: Days
• US Class Current: 428/74
• CPC Class Codes: C08K 7/08 Oxygen-containing compounds
• CPC Class Codes: D21H 13/46 Non-siliceous fibres, e.g. from metal oxides
• CPC Class Codes: D21H 17/20 Macromolecular organic compounds
• CPC Class Codes: E04B 1/7662 comprising fiber blankets or batts
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 428/237 Noninterengaged fibered material encased [e.g., mat, batt, etc.]
• CPC Class Codes: Y10T 428/238 Metal cover or casing
• CPC Class Codes: Y10T 428/24124 Fibers
• CPC Class Codes: Y10T 442/20 Coated or impregnated woven, knit, or nonwoven fabric which is not [a] associated with another preformed layer or fiber layer or, [b] with respect to woven and knit, characterized, respectively, by a particular or differential weave or knit, wherein the coating or impregnation is neither a foamed material nor a free metal or alloy layer
• CPC Class Codes: Y10T 442/2631 Coating or impregnation provides heat or fire protection
• CPC Class Codes: Y10T 442/668 Separate nonwoven fabric layers comprise chemically different strand or fiber material
• CPC Class Codes: Y10T 442/696 Including strand or fiber material which is stated to have specific attributes [e.g., heat or fire resistance, chemical or solvent resistance, high absorption for aqueous compositions, water solubility, heat shrinkability, etc.]

Abstract

A composite structure includes a resin and a plurality of titanium dioxide fibers provided in the resin.

Claims

1. A composite, comprising:

a resin; and

a plurality of titanium dioxide fibers provided in said resin.

2. The composite structure of claim 1 wherein said titanium dioxide fibers define a paper mat.

3. The composite structure of claim 2 wherein said titanium dioxide fibers are randomly incorporated into said paper mat.

4. The composite structure of claim 2 wherein said titanium dioxide fibers are non-randomly incorporated into said paper mat.

5. The composite structure of claim 1 wherein said plurality of titanium dioxide fibers comprises a plurality of dyed titanium dioxide fibers.

6. The composite structure of claim 1 wherein said plurality of titanium dioxide fibers comprises a plurality of titanium dioxide fibers with enhanced electrical conductivity.

7. An insulation blanket batting, comprising:

a blanket body comprising a plurality of titanium dioxide fibers.

8. The insulation blanket batting of claim 7 further comprising a plurality of other fiber types provided in said blanket body.

9. The insulation blanket batting of claim 7 further comprising a plurality of fiberglass fibers provided in said blanket body.

10. The insulation blanket of claim 9 wherein said plurality of titanium dioxide fibers comprises at least one distinct layer of said plurality of titanium dioxide fibers in said blanket body.

11. The insulation blanket of claim 7 wherein said plurality of titanium dioxide fibers comprises a plurality of dyed titanium dioxide fibers.

12. An insulation blanket cover film, comprising:

a cover film outer layer; and

at least one layer of titanium dioxide fibers provided on said cover film outer layer.

13. The insulation blanket cover film of claim 12 wherein said cover film outer layer comprises metal.

14. The insulation blanket cover film of claim 13 wherein said metal comprises aluminum.

15. A method of fabricating a structure with enhanced heat resistance, comprising:

providing a plurality of titanium dioxide fibers;

providing a resin;

impregnating said titanium dioxide fibers with said resin; and

forming a composite structure by thermoforming said resin.

16. The method of claim 15 further comprising fabricating an aircraft structure using said composite structure.

17. The method of claim 16 wherein said fabricating said structure using said composite structure comprises fabricating at least one of an interior sidewall, a ceiling panel and a cargo panel using said composite structure.

18. A method of fabricating an insulation blanket with enhanced heat resistance, comprising:

providing insulation blanket batting;

providing an insulation blanket cover layer on said insulation blanket batting;

providing a plurality of titanium dioxide fibers; and

incorporating said plurality of titanium dioxide fibers in at least one of said insulation blanket batting and said insulation blanket cover layer.

19. A method of fabricating a paper mat having enhanced heat resistance, comprising:

providing a plurality of titanium dioxide fibers; and

fabricating said plurality of titanium dioxide fibers into a paper mat.

20. The method of claim 19 further comprising:

providing a resin;

pre-impregnating said paper mat with said resin;

forming a composite structure by thermoforming said resin; and

fabricating a structure using said composite structure.

21. The method of claim 20 wherein said fabricating a structure using said composite structure comprises fabricating a light block under window reveal in an aircraft sidewall panel.

22. A composite structure, comprising:

a resin selected from the group consisting of phenolic, benzoxazine and bis-phenol cyanate ester and having a thickness of about 0.080 inch;

a plurality of titanium dioxide fibers having an average diameter of about 10 nanometers provided in said resin; and

said plurality of titanium dioxide fibers are doped with anions to enhance electrical conductivity of said plurality of titanium dioxide fibers.

23. A method of fabricating a structure with enhanced heat resistance, comprising:

providing a plurality of titanium dioxide fibers having an average diameter of about 10 nanometers;

enhancing electrical conductivity of said plurality of titanium dioxide fibers by doping said plurality of titanium dioxide fibers with anions;

providing a resin selected from the group consisting of phenolic, benzoxazine and bis-phenol cyanate ester and having a thickness of about 0.080 inch;

impregnating said titanium dioxide fibers with said resin;

forming a composite structure by thermoforming said resin; and

fabricating said aircraft structure using said composite structure.