A structural arrangement comprising a fiber reinforced polymer component, a cold gas spraying electrically conductive layer, and a polyether sulfone foil arranged on the fiber reinforced polymer component, at least in a region between the fiber reinforced polymer component and the cold gas sprayed electrically conductive layer.

An aircraft fuselage for transporting passengers in a lower deck, the fuselage having a longitudinal axis and interior compartment, having an intermediate floor fastened to the fuselage structure, extending through the interior compartment and dividing the interior compartment into an upper deck and a lower deck, having a support device for supporting the intermediate floor on the fuselage structure. The support device is fastened to the intermediate floor and by an opposite end in the lower deck to the fuselage structure. The support device has a concave form and has an energy absorption element such that in a crash of an underside of the fuselage undergoes a defined plastic deformation and absorbs a defined amount of kinetic energy. In a crash, the fuselage structure is, at the underside of the aircraft fuselage, deformed at most to such an extent that a minimum height between a seat surface of passenger seats in the lower deck and the intermediate floor is not undershot.

An aircraft having a fuselage having a pressurized upper space above the floor and a lower space beneath the floor, a wing, a hollow support stay fixed between the lower space level of the fuselage and the wing, an electric motor propeller propulsion system fixed beneath each wing, the output shaft of the motor driving a propeller in rotation, a production system having a fuel cell producing electrical energy supplying the electric motor with electricity via electrical conductors, a hydrogen reservoir fixed in the lower space, and a hydrogen inlet pipe feeding hydrogen from a hydrogen reservoir to the production system, wherein the hydrogen inlet pipe extends through the interior of the support stay. The electrical conductors or the hydrogen pipes pass through the stays on the outside of the fuselage and therefore at a distance from the passengers and the electronic systems of the aircraft.

An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.

An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.

A composite material structure includes: a first composite material member including a first reinforcing fiber that is electrically conductive and impregnated with a first resin; a second composite material member including a second reinforcing fiber that is electrically conductive and impregnated with a second resin; an adhesive layer disposed between the first composite material member and the second composite material member to bond the first composite material member to the second composite material member; and an electromagnetic shielding member covering at least part of an area, exposed to an exterior, of the adhesive layer. At least one of the first and second composite material members has a predefined lightning current direction in which a lightning current generated by a lightning strike passes. The shielding member is disposed over an entire plane of a side face in a direction orthogonal to the lightning current direction.

A method of additively manufacturing a fire and overheat detection system (FODS) clamp onto a rail tube is provided. The method includes building a base of a clamp body on the rail tube, sequentially building portions of a locking feature and holders of the clamp body on the base and sequentially building remaining portions of the holders and flanges forming grooves at each of the holders of the clamp body on the base.

Systems and methods are provided for curing a composite part. The method includes the steps of: disposing a heat blanket at a composite material; applying, with a controller, power to heaters distributed across multiple cells of a heat blanket to heat the composite material at the heat blanket; monitoring, with the controller, a temperature of the composite material at each of the multiple cells via thermocouples distributed across the multiple cells; and individually adjusting, with the controller, an amount of power applied to the heaters, for each of the multiple cells, in response to the monitored temperature and a target temperature.

A method for producing a structural section of a vehicle comprises the steps of providing multiple separate skin panels of a fiber-reinforced plastic having an inner side, an outer side and a border running peripherally around the respective skin panel; arranging at least one stiffening component of a fiber-reinforced plastic on each skin panel, on the respective inner side; integrally connecting the respective at least one stiffening component to the skin panels concerned to form a structural component; arranging at least two structural components on a carrier, so that at least regions of the borders of the structural components concerned are in surface-area contact; and integrally connecting the regions of the borders that are in surface-area contact to one another.

The present embodiment relates to a composite fibre structure (100) and a method (200) of manufacturing the composite fibre structure (200). The composite fibre structure (100) includes a core (102) and an outer layer (108) enclosing the core (102). The core (102) further includes at least one of a permanent core (104) and a temporary core (106). The permanent core (104) is 3-D printed along with the temporary core (106) to form the core structure (102). The permanent core (104) and the temporary core (106) are placed alternatively along the section, extending throughout the length of the composite fibre structure (100), or the permanent core (104) and temporary core (102) can be alternate along the length of the composite fibre structure (100). The layer (108), made of a reinforcement material, wraps the core (102) to form the composite fibre structure (100).