A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.

An aircraft has an internal combustion engine and a wing including a hollow structural member. The aircraft has an electrical network including: at least one alternating current electrical generator configured to be driven by the internal combustion engine; an electrical motor configured to drive an aircraft propulsor; at least one conductor configured to electrically couple the electrical motor and the electrical generator; wherein the electrical conductor is formed of the hollow structural member of the aircraft wing.

A method and apparatus for applying a seal to a structure, for example sealing an aircraft fuel tank. The method comprises: providing a mould part; positioning the mould part against a surface of the structure thereby to create a mould cavity between the mould part and the surface; introducing a sealant into the mould cavity; curing the sealant within the mould cavity thereby to apply the seal to the surface; and removing the mould part from the surface with the seal applied thereto. The sealant may be a UV curing sealant and curing the sealant may comprise passing UV light through the mould part.

A method and apparatus for applying a seal to a structure, for example sealing an aircraft fuel tank. The method comprises: providing a mould part; positioning the mould part against a surface of the structure thereby to create a mould cavity between the mould part and the surface; introducing a sealant into the mould cavity; curing the sealant within the mould cavity thereby to apply the seal to the surface; and removing the mould part from the surface with the seal applied thereto. The sealant may be a UV curing sealant and curing the sealant may comprise passing UV light through the mould part.

The purpose of the present invention is to provide: a structural material for structures which is capable of attaining reductions in working time and cost in production steps and of preventing an increase in weight; a fuel tank; a main wing; and an aircraft. A rib (11) as the structural material for structures is characterized by comprising a carbon-fiber-reinforced plastic wherein the reinforcement comprises carbon fibers and the matrix comprises a plastic, and the surface of the carbon-fiber-reinforced plastic was coated with a low-viscosity surface-protective material (18) having conductivity imparted thereto.

The purpose of the present invention is to provide: a structural material for structures which is capable of attaining reductions in working time and cost in production steps and of preventing an increase in weight; a fuel tank; a main wing; and an aircraft. A rib (11) as the structural material for structures is characterized by comprising a carbon-fiber-reinforced plastic wherein the reinforcement comprises carbon fibers and the matrix comprises a plastic, and the surface of the carbon-fiber-reinforced plastic was coated with a low-viscosity surface-protective material (18) having conductivity imparted thereto.

A system and method for improving fuel storage within the wing of an aircraft. In one exemplary embodiment, the system and method eliminate the traditional spars and ribs, and any spanwise and cordwise connecting vertical webs, within a wing. Instead, the system comprises a plurality of modified flared spars, each having a length defined by an angled hat section, to form a wing structure. The modified flared spars may also comprise one or more lengths defined by a specialized section configured to accommodate a portion of a box section, or any other internal component of the wing. The system and method may also involve a contiguous fuel bladder of any size/type. The fuel bladder for the wing may comprise a fabric coated or impregnated with an elastomeric material that may include a polyurethane dispersion layer combined with a sealant.

A system and method for improving fuel storage within the wing of an aircraft. In one exemplary embodiment, the system and method eliminate the traditional spars and ribs, and any spanwise and cordwise connecting vertical webs, within a wing. Instead, the system comprises a plurality of modified flared spars, each having a length defined by an angled hat section, to form a wing structure. The modified flared spars may also comprise one or more lengths defined by a specialized section configured to accommodate a portion of a box section, or any other internal component of the wing. The system and method may also involve a contiguous fuel bladder of any size/type. The fuel bladder for the wing may comprise a fabric coated or impregnated with an elastomeric material that may include a polyurethane dispersion layer combined with a sealant.

A method can include generating reference image data representing a field of view of an interior of a fuel tank, and generating active image data representing the field of view of the interior of the fuel tank when the fuel tank contains fuel. The method can further include producing, by a processing device, a fuel measurement value representing an amount of fuel contained in the fuel tank based on the reference image data and the active image data, and outputting, by the processing device, an indication of the fuel measurement value.

A wing assembly include at least one fuel tank having a tank outboard end. In addition, the wing assembly includes a stout wing rib located proximate the tank outboard end and extending between a front spar and a rear spar. The wing assembly also includes at least one outboard wing rib located outboard of the stout wing rib and defining an outboard wing bay. The wing assembly also includes an upper skin panel and a lower skin panel each coupled to the front spar, the rear spar, the stout wing rib, and the outboard wing rib. A plurality of bead stiffeners are coupled to the upper skin panel and/or the lower skin panel and are spaced apart from each other within the outboard wing bay.