Electric charge dissipation system for aircraft

Patent metadata

Field	Value
Publication number	US-9802714-B2
Application number	US-95944910-A
Country	US
Kind code	B2
Filing date	Dec 3, 2010
Priority date	Dec 3, 2010
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

Abstract

A method, apparatus, and composite fuel tank for manufacturing a structure is provided. A first composite layer and a second composite layer are placed on a mold. The second composite layer and the first composite layer are cured. The first composite layer and the second composite layer form the structure. The second composite layer is configured to dissipate an electric charge on a surface of the structure.

First claim

What is claimed is:

1. An apparatus comprising:
a first composite layer;
a second composite layer co-cured to an interior side of the first composite layer, wherein the first composite layer and the second composite layer form a fuel tank, and wherein the second composite layer comprises a conductivity configured to:
comprise a resistivity of 1×10 6 ohms-meters to about 1×10 9 ohms-meters configured to dissipate a static electric charge generated on an inside surface of the fuel tank; and
reduce a galvanic corrosion;

a primer layer layered on the interior side of the second composite layer, opposite the first composite layer; and
a sealant layer layered on the interior side of the primer layer, opposite the second composite layer.

2. The apparatus of claim 1 , further comprising the second composite layer configured to reduce an undesired electrical discharge, caused by a source outside of the fuel tank, in an interior of the fuel tank.

3. The apparatus of claim 1 , wherein the second composite layer is configured to reduce a number of inconsistencies, associated with drilling holes in the second composite layer, in the fuel tank.

4. The apparatus of claim 1 , wherein the first composite layer and the second composite layer are co-cured.

5. The apparatus of claim 1 further comprising:
a number of composite layers located between the first composite layer and the second composite layer.

6. The apparatus of claim 1 , wherein the second composite layer further comprises reinforcement fibers composed of a material selected from at least one of the group consisting of: glass, carbon, ceramic, silica, organic materials, plastic, a polymer, nylon, and metal.

7. The apparatus of claim 1 , wherein the second composite layer comprises fibers and wherein the fibers comprise a coating of a conductive material.

8. The apparatus of claim 1 , wherein the second composite layer comprises fibers that form a reinforcement and a resin that forms a matrix in the reinforcement.

9. The apparatus of claim 8 , wherein the resin is configured to provide the conductivity configured to dissipate the static electric charge on the interior side of the fuel tank.

10. The apparatus of claim 8 ,
wherein the fibers of the second composite layer are coated with a first conductive material;
wherein the resin of the matrix of the second composite layer includes a second conductive material;
wherein the first conductive material is a metal; and
wherein the second conductive material is a metal alloy.

11. The apparatus of claim 8 , wherein the fibers are doped to provide the conductivity and the resin is doped to provide the conductivity.

12. The apparatus of claim 1 , wherein the second composite layer comprises fiberglass.

13. The apparatus of claim 1 , wherein the fuel tank connects to an aircraft.

14. The apparatus of claim 13 , wherein the fuel tank is located in an object selected from one of a mobile platform, a stationary platform, a land-based structure, an aquatic-based structure, a space-based structure, an aircraft, a surface ship, a tank, a personnel carrier, a train, a spacecraft, a space station, a satellite, a submarine, an automobile, a power plant, a bridge, a dam, a manufacturing facility, and a building.

15. The apparatus of claim 13 , wherein the galvanic corrosion is reduced between the fuel tank and other structures that contact the fuel tank.

16. The apparatus of claim 13 , wherein the second composite layer reduces electrical discharge in an interior of the fuel tank, the electrical discharge is a discharge that travels through the first composite layer.

17. The apparatus of claim 1 , wherein a thickness of the primer layer is configured to increase dissipation of the static electric charge.

18. The apparatus of claim 1 , the sealant layer comprises the interior side of the fuel tank.

19. The apparatus of claim 1 , further comprising a number of additional layers between the first composite layer and the second composite layer; wherein the number of additional layers comprises a number of conductive layers; and wherein the number of additional layers provide for isolation of the fuel tank that reduces galvanic corrosion.

20. An aircraft that comprises:
a fuel tank that comprises a rigid form that comprises a cross section that comprises a first composite layer, a second composite layer, a primer, and a sealant,
wherein the second composite layer and the first composite layer form a co-cured structure;
wherein the first composite layer comprises carbon;
wherein the second composite layer comprises a reinforcement that comprises a resin infused into a fabric;
wherein the reinforcement comprises fibers;
wherein the fibers are configured to form the fabric;
wherein the reinforcement takes a form of the fabric containing the fibers;
wherein the fabric is manufactured through weaving, knitting, spreading, and bonding;
wherein the second composite layer comprises a matrix;
wherein the matrix takes a form of resin;
wherein the fibers comprise a conductivity such that an electric charge is dissipated from a surface that faces an interior of the fuel tank;
wherein the conductivity is configured such that an undesired electrical discharge within the fuel tank is at least one of: reduced, and prevented;
wherein the fibers comprise:
a material that comprises at least one of: glass, carbon, ceramic, silica, organic materials, plastic, a polymer, nylon, and metal; and
a coating that comprises a first conductive material;

wherein the resin is configured to provide conductivity, in addition to the conductivity of the fibers, through a second conductive material in the resin;
wherein the first conductive material coating the fibers and the second conductive material in the resin are both configured to provide the conductivity for the second composite layer;
wherein the coating and the second conductive material each comprise at least one of: a metal, a metal alloy, nickel, and carbon;
wherein the sealant is formed on the primer;
wherein the second composite layer comprises a resistivity of 1×10 6 ohms-meters to about 1×10 9 ohms-meters configured to dissipate a static electric charge generated on an inside surface of the fuel tank;
wherein the second composite layer is configured to reduce and prevent undesired electrical discharge, caused by a source external to the fuel tank, in an interior of the fuel tank, from a current that travels through the first composite layer; and
wherein the second composite layer is configured to reduce galvanic corrosion from occurring from other structures that may contact fuel tank.

Assignees

• Gerken Noel Timothy
• Ackerman Patrice K
• Price William O'Neil
• Kwon Eddie
• Rimbey Peter Raymond
• Boeing Co

Inventors

• Gerken Noel Timothy
• Ackerman Patrice K
• Price William O'Neil
• Kwon Eddie
• Rimbey Peter Raymond

Classifications

• B64D37/32 Primary

  Safety measures not otherwise provided for, e.g. preventing explosive conditions · CPC title

• B64D45/02 Primary

  Lightning protectors; Static dischargers · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• Y02T50/40

  Weight reduction · CPC title