Electric charge dissipation system for aircraft

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 1×106 ohms-meters to about 1×109 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.