Abstract: A pneumatic deicing device (1) for breaking and removing an ice deposit accumulated on the outer surface (2) of an aircraft, in particular on an airplane wing. The device (1) includes an outer layer (10) intended to withstand the outside environment, an inner interface layer (50) intended to be bonded to the outer surface of the aircraft, and at least two outer (30) and inner (40) intermediate layers connected to one another by a network of stitches (36) spaced apart to define deicing chambers (35) that can be inflated using injected pressurized air so as to create an expansion of the device causing a mechanical action to break the ice. The inner interface layer (50) with the outer surface (2) of the aircraft includes at least one textile layer (54) having an inner surface (55) intended to be in direct contact with an outer surface (2) of the aircraft.

Abstract: A pneumatic deicing device (1) is provided for breaking and removing an ice deposit accumulated on the outer surface (2) of an aircraft, in particular on an airplane wing. The device (1) includes an outer layer (15) intended to withstand the outside environment, an inner interface layer (50) intended to be connected to the outer surface (2) of the aircraft, and at least two outer (30) and inner (40) intermediate layers connected to one another by an array of stitches (36) so as to define deicing chambers (35) that can be inflated quickly to cause a mechanical action to break the ice. The outer intermediate layer (30) includes a knit textile layer (34). At least one interlayer (20; 32) made from polar elastomer material is arranged above the knit textile layer (34) and immediately in contact with the outer layer (15) and the knit textile layer (34).

Abstract: A flexible fuel tank (10) has, from the inside to the outside of the tank: a single-layer or multilayer liner (2) having properties of sealing with respect to the liquid, impermeability to the vapor of said fuel, and dissipation of electrostatic charges. The liner (2) includes an inner face (2a) intended to be in contact with the fuel and an outer face (2b). An intermediate layer (3) is in contact with the outer face (2b) of the liner (2), for example a coating layer; and a textile reinforcing layer (4) is in contact with the intermediate layer (3).

Abstract: A pneumatic deicing device (1) for breaking and removing an ice deposit accumulated on the outer surface (2) of an aircraft, in particular on an airplane wing. The device (1) includes an outer layer (10) intended to withstand the outside environment, an inner interface layer (50) intended to be bonded to the outer surface of the aircraft, and at least two outer (30) and inner (40) intermediate layers connected to one another by a network of stitches (36) spaced apart to define deicing chambers (35) that can be inflated using injected pressurized air so as to create an expansion of the device causing a mechanical action to break the ice. The inner interface layer (50) with the outer surface (2) of the aircraft includes at least one textile layer (54) having an inner surface (55) intended to be in direct contact with an outer surface (2) of the aircraft.

Abstract: A pneumatic deicing device (1) is provided for breaking and removing an ice deposit accumulated on the outer surface (2) of an aircraft, in particular on an airplane wing. The device (1) includes an outer layer (15) intended to withstand the outside environment, an inner interface layer (50) intended to be connected to the outer surface (2) of the aircraft, and at least two outer (30) and inner (40) intermediate layers connected to one another by an array of stitches (36) so as to define deicing chambers (35) that can be inflated quickly to cause a mechanical action to break the ice. The outer intermediate layer (30) includes a knit textile layer (34). At least one interlayer (20; 32) made from polar elastomer material is arranged above the knit textile layer (34) and immediately in contact with the outer layer (15) and the knit textile layer (34).

Abstract: A flexible fuel tank (10) has, from the inside to the outside of the tank: a single-layer or multilayer liner (2) having properties of sealing with respect to the liquid, impermeability to the vapor of said fuel, and dissipation of electrostatic charges. The liner (2) includes an inner face (2a) intended to be in contact with the fuel and an outer face (2b). An intermediate layer (3) is in contact with the outer face (2b) of the liner (2), for example a coating layer; and a textile reinforcing layer (4) is in contact with the intermediate layer (3).

Abstract: Embodiments of the present invention relate generally to fuel tanks for aviation, and particularly to construction of rigid tank walls that have been found useful in absorbing energy of a magnitude expected during a crash. In some aspects, the rigid tank wall construction includes particular materials, such as a thermoplastic resin matrix. In some aspects, the rigid tank wall construction includes a particular arrangement of reinforcing fibers, such as a twill weave pattern.

Abstract: Embodiments of the present invention relate generally to fuel tanks for aviation, and particularly to construction of rigid tank walls that have been found useful in absorbing energy of a magnitude expected during a crash. In some aspects, the rigid tank wall construction includes particular materials, such as a thermoplastic resin matrix. In some aspects, the rigid tank wall construction includes a particular arrangement of reinforcing fibers, such as a twill weave pattern.

Abstract: Embodiments of the present invention provide thermoplastic hoses for an airborne vehicles. The hoses have an inner layer comprised of polyamide and an external layer of polyamide, and the hose is configured to allow the hose to both operate safely under pressures below 55 psi and withstand internal pressures of at least 15 pounds per square inch, and in specific embodiments, at least about 165 pounds per square inch. Specific embodiments of the hoses described are particularly useful on-board helicopters and smaller aircraft.

Abstract: Systems and methods for establishing electrical continuity about pipes and other conduits are detailed. The systems may include conductive seals formed, for example, of polymeric and conductive materials. Polymeric materials may include rubber, silicon, and fluorosilicon and conductive materials may include metal charges, carbon, carbon nanotubes, carbon fibers, and intrinsically conducting polymers, although neither type of material is so limited.