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.

An aircraft wingbox assembly is disclosed having a wingbox including an upper cover, a lower cover and a pair of spars; a plurality of ribs in the wingbox, wherein the ribs divide the wingbox into bays; and a fuel tank in the wingbox. All or part of the fuel tank is located in a first one of the bays between a first one of the ribs and a second one of the ribs. The fuel tank includes a tank wall and first and second tank lugs extending from the fuel tank wall. A first fastener attaches the first tank lug to the first one of the ribs; and a second fastener attaches the second tank lug to the second one of the ribs.

A fuel tank dam closes a gap that is formed between a first structural component and a second structural component. The fuel tank dam includes a first portion disposed on a first structural component side, a second portion disposed on a second structural component side, an elastic member that is supported by the first portion at one end while supported by the second portion at the other end and closes a gap that is formed between the first portion and the second portion, and a sealing mechanism that seals between the first member and the elastic member.

A fuel tank dam closes a gap that is formed between a first structural component and a second structural component. The fuel tank dam includes a first portion disposed on a first structural component side, a second portion disposed on a second structural component side, an elastic member that is supported by the first portion at one end while supported by the second portion at the other end and closes a gap that is formed between the first portion and the second portion, and a sealing mechanism that seals between the first member and the elastic member.

An aircraft comprising at least one bay for receiving different types of standardized modules. The bay is configured to receive at least two different types of energy modules as standardized modules, preferably two types of energy modules chosen from a conventional fuel tank, a battery, a fuel tank for a fuel cell, a tank for electrofuel, a tank for nano-electrofuel, a gas tank or a combined energy source.

An aircraft comprising at least one bay for receiving different types of standardized modules. The bay is configured to receive at least two different types of energy modules as standardized modules, preferably two types of energy modules chosen from a conventional fuel tank, a battery, a fuel tank for a fuel cell, a tank for electrofuel, a tank for nano-electrofuel, a gas tank or a combined energy source.

Cargo load platform assemblies are especially adapted to provide support for a variety of cargo, such as auxiliary aircraft fuel tanks. According to certain embodiments herein, a load platform is provided which is adapted to being positioned onto a cargo deck of a cargo aircraft. At least one anti-rattle device is operatively associated with the load platform for positionally fixing the load platform to a tie-down ring of the cargo deck of a cargo aircraft. The cargo load platform may support a rigid fuel tank thereon so that auxiliary fuel tankage systems can be provided as may be needed.

Cargo load platform assemblies are especially adapted to provide support for a variety of cargo, such as auxiliary aircraft fuel tanks. According to certain embodiments herein, a load platform is provided which is adapted to being positioned onto a cargo deck of a cargo aircraft. At least one anti-rattle device is operatively associated with the load platform for positionally fixing the load platform to a tie-down ring of the cargo deck of a cargo aircraft. The cargo load platform may support a rigid fuel tank thereon so that auxiliary fuel tankage systems can be provided as may be needed.

A fuel system for an aircraft including a fuel tank for storing fuel during operation of the aircraft and a diffuser disposed inside the fuel tank. The diffuser is configured such that it forms part of a flow path configured to connect a fuel source to the inside of the fuel tank. The diffuser includes a wall which at least partially defines an internal space of the diffuser; an opening in the wall, which provides access to the internal space; and a blocking component configured to block the opening.