Noise reduction system for composite structures

Patent metadata

Field	Value
Publication number	US-9353518-B2
Application number	US-201414312688-A
Country	US
Kind code	B2
Filing date	Jun 24, 2014
Priority date	Nov 23, 2011
Publication date	May 31, 2016
Grant date	May 31, 2016

Abstract

A method and apparatus comprising a composite panel and a number of structures to reduce noise radiation from the composite panel. The composite panel has a first face sheet, a second face sheet, and a core located between the first face sheet and the second face sheet. The number of structures is associated with the first face sheet. The number of structures has a mass with a configuration to reduce a speed of waves propagating in the composite panel such that noise radiating from the composite panel is reduced.

First claim

What is claimed is:

1. An apparatus comprising:
a composite panel having:
a first face sheet,
a second face sheet,
a core located between the first face sheet and the second face sheet; and
a number of elongate members, the number of elongate members having a mass with a configuration to reduce a speed of waves propagating in the composite panel such that noise radiating from the composite panel is reduced, the number of elongate members not integrally formed with the first face sheet, the number of elongate members attached individually to an outer surface of the first face sheet, the outer surface of the first face sheet positioned opposite the core and forming an outer surface of the composite panel.

2. The apparatus of claim 1 , wherein the number of elongate members is a first number of elongate members and further comprising:
a second number elongate members associated with the second face sheet.

3. The apparatus of claim 2 , wherein the second number of elongate members are positioned on an outer surface of the second face sheet.

4. The apparatus of claim 1 , wherein the number of elongate members extends from a first side of the composite panel to a second side of the composite panel.

5. The apparatus of claim 1 , wherein the number of elongate members are substantially evenly spaced from each other and extend substantially parallel to each other.

6. The apparatus of claim 1 , wherein the composite panel is disposed in one of a wall, a ceiling, or a floor, of an aircraft.

7. The apparatus of claim 1 , wherein the number of elongate members are substantially insensitive to temperature.

8. The apparatus of claim 1 , wherein the core comprises a honeycomb.

9. the apparatus of claim 1 , wherein the elongate members comprise a number of patches.

10. The apparatus of claim 1 , wherein the elongate members comprise a cross sectional shape selected from one of square, rectangular, trapezoidal, oval and circular.

11. A method for reducing noise radiation from a composite panel, the method comprising:
causing waves to propagate through the composite panel comprising a first face sheet, a second face sheet, and a core located between the first face sheet and the second face sheet; and
reducing a speed of the waves propagating through the composite panel with a number of elongate members associated with the first face sheet, wherein the number of elongate members has a mass with a configuration to reduce the speed of the waves propagating in the composite panel such that the noise radiating from the composite panel is reduced, the number of elongate members not integrally formed with the first face sheet, the number of elongate members attached individually to an outer surface of the first face sheet, the outer surface of the first face sheet positioned opposite the core and forming and outer surface of the composite panel.

12. The method of claim 11 further comprising installing the composite panel in an aircraft.

13. The method of claim 12 further comprising installing the composite panel in one of a wall, a ceiling, or a floor, of an aircraft.

14. The method of claim 11 , wherein the number of elongate members extends from a first side of the composite panel to a second side of the composite panel.

15. The method of claim 11 further comprising reducing the speed of a shear wave through the composite panel.

16. The method of claim 11 , wherein the core comprises a honeycomb.

17. The method of claim 11 , wherein the elongate members comprise a number of patches.

18. The method of claim 11 wherein the elongate members comprise a cross sectional shape selected from one of square, rectangular, trapezoidal, oval, and circular.

19. The method of claim 11 , wherein the core comprises a material selected from one of paper, plastic, foam, a meta aramid material, and a para aramid material.

Assignees

• Boeing Co

Inventors

• Mathur Gopal Prasad
• Chin Cliff L

Classifications

• Y10T428/24149

  Honeycomb-like · CPC title

• Y02T50/46

  Cross-Sectional Technologies · mapped topic

• E04B1/82 Primary

  specifically with respect to sound only ({of floors or ceilings E04B9/001;} noise damping in ducts or channels E04F17/00; noise damping in general G10K11/16) · CPC title

• B64C1/40

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title

• B32B3/12

  characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure · CPC title