Panel structure

• US 8,070,994 B2
• Filed: 06/14/2005
• Issued: 12/06/2011
• Est. Priority Date: 06/18/2004
• Status: Active Grant

• Current Assignee: Zephyros, Inc.
• Original Assignee: Zephyros, Inc.
• Inventors: Carlson, David, Madaus, Brandon, Harthcock, Matthew, Barton, Kearney, Walker, Jason, Taylor, Charles L Jr.
• Primary Examiner(s): Michener, Jennifer K.
• Assistant Examiner(s): Slawski, Magali P
• Application Number:
  US11/151,957
• Publication Number:
  US 20060000186A1
• Time in Patent Office: 2,366 Days
• Field of Search: 264 464- 469, 527/931, 428/117, 428/116, 521/50
• US Class Current: 264/46.5
• CPC Class Codes: B29C 44/1228 Joining preformed parts by the expanding material
• CPC Class Codes: B29C 44/186 Filling multiple cavities B29C44/181, B29C44/182 and B29C44/188 takes precedence
• CPC Class Codes: B29K 2995/0002 insulating
• CPC Class Codes: B29L 2031/776 Walls, e.g. building panels
• CPC Class Codes: B32B 2250/40 Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
• CPC Class Codes: B32B 2262/0261 Polyamide fibres
• CPC Class Codes: B32B 2262/101 Glass fibres
• CPC Class Codes: B32B 2262/106 Carbon fibres, e.g. graphite fibres
• CPC Class Codes: B32B 2307/102 Insulating
• CPC Class Codes: B32B 2307/304 Insulating
• CPC Class Codes: B32B 2307/732 Dimensional properties
• CPC Class Codes: B32B 2419/00 Buildings or parts thereof
• CPC Class Codes: B32B 2439/00 Containers; Receptacles
• CPC Class Codes: B32B 2479/00 Furniture
• CPC Class Codes: B32B 2509/00 Household appliances
• CPC Class Codes: B32B 2605/00 Vehicles
• CPC Class Codes: B32B 3/12 characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
• CPC Class Codes: B32B 5/18 characterised by features of a layer of foamed material
• CPC Class Codes: B32B 5/20 foamed in situ
• CPC Class Codes: E04C 2/365 by honeycomb structures
• CPC Class Codes: Y02T 50/40 : Weight reduction
• CPC Class Codes: Y10T 428/24157 : Filled honeycomb cells [e.g., solid substance in cavities, etc.]

Abstract

A panel structure and a method of forming the panel structure are disclosed. The panel structure typically includes at least one panel associated with a material. The panel structure has been found particularly advantageous for use as an interior panel of an airplane.

Claims

1. A method of forming an interior panel structure for providing sound absorption, damping, or attenuation comprising:

providing a first panel formed at least partially of an epoxy/glass composite material, the first panel being an inner panel of an aircraft;

providing a second panel formed at least partially of a porous material that includes a metal, the second panel being an outer panel of an aircraft;

locating a honeycomb support intermediate the first panel and the second panel, such that the support includes a plurality of openings, a first surface and a second surface;

locating a layer of heat activated foamable material including an elastomer on the first surface of the honeycomb support so that the heat activated material enters each of the plurality of openings;

placing the first panel in contact with the layer of foamable heat activated material and the first surface of the honeycomb support;

placing the second panel in contact with the second surface of the honeycomb support;

exposing the heat activated material to a temperature in the range of about 150°

F. to about 550°

F. for at least about 10 minutes to cause the epoxy glass composite to cure and the heat activated foamable material to expand to create a foam material and to occupy a volume that is at least 400% of the volume occupied by the first layer of heat activated material prior to expansion and bond to at least the first panel, the side surface of the panels, the honeycomb support, and the sides of the honeycomb support whereby after expansion and cure the foam material remains in a softened state post-cure and fills from about 5% to about 90% of each of the plurality of openings within the honeycomb support so that space remains between the foam material and the second panel so that sound is absorbed by the space and foam material.

2. The method of claim 1, wherein no further adhesive is used to bond the foamable material to the first panel and the honeycomb structure.

3. The method of claim 1, wherein a plurality of spaces are formed between the expanded foamable material in each of the plurality of openings and the second panel so that sound becomes absorbed into the plurality of spaces.

4. The method of claim 1, wherein the panel structure is placed in a panel press thereby causing the first layer of heat activated material to expand and materials of the first panel and second panel to bond with the first surface and second surface of the honeycomb support.

5. The method of claim 1, wherein the first and second panels are individually formed of metal or polymeric material.

6. The method of claim 5, wherein the polymeric material is reinforced with fibrous materials.

7. The method of claim 1, wherein after expansion of the first layer of heat activated material, the material fills at least 5% and less than 75% of each of the plurality of openings within the honeycomb support.

8. The method of claim 1, wherein after expansion of the first layer of heat activated material, the material fills at least 30% and less than 60% of each of the plurality of openings within the honeycomb support.

9. The method of claim 1, wherein expansion, of the heat activated materials provides adhesion between at least one of the panels and the honeycomb support.