Heat resistance using titanium dioxide nanofibers

• US 8,916,082 B2
• Filed: 11/17/2008
• Issued: 12/23/2014
• Est. Priority Date: 11/17/2008
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Harris, John N., Slaton, Daniel B.
• Primary Examiner(s): Choi, Peter Y
• Application Number:
  US12/272,638
• Publication Number:
  US 20100285264A1
• Time in Patent Office: 2,227 Days
• Field of Search: 264/234, 264/319, 442/59
• US Class Current: 264/319
• 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 method of fabricating a structure having enhanced heat resistance, comprising:

fabricating a plurality of randomly oriented titanium dioxide nanofibers into a paper mat using a binder, the titanium dioxide nanofibers having an average diameter of about 10 nanometers, the paper mat having a thickness no greater than 0.080 inches;

after fabricating the paper mat, impregnating the paper mat with a resin to form an impregnated paper mat;

forming a composite structure by heating the impregnated paper mat; and

fabricating a structure using the composite structure, the structure having a thickness corresponding to said paper mat.

2. The method of claim 1 wherein fabricating the structure using the composite structure comprises fabricating a light block under a window reveal in an aircraft sidewall panel.

3. A method of fabricating an aircraft structure with enhanced heat resistance, comprising:

doping a plurality of titanium dioxide nanofibers with anions to form a plurality of doped titanium dioxide nanofibers, the titanium dioxide nanofibers having an average diameter of about 10 nanometers;

forming a paper mat comprising the plurality of doped titanium dioxide nanofibers and a binder, the paper mat having a thickness no greater than 0.080 inches, the plurality of doped titanium dioxide nanofibers randomly oriented in the paper mat;

impregnating the paper mat with a resin selected from the group consisting of phenolic, benzoxazine and bis-phenol cyanate ester;

forming a composite structure by thermoforming the impregnated paper mat; and

fabricating the aircraft structure using the composite structure.

4. The method of claim 3 wherein the thickness of the aircraft structure is greater than the thickness of the composite structure.