Abstract: A pressure bulkhead for a pressurized fuselage of a vehicle has an axial inner surface and an axial outer surface. The pressure bulkhead includes a tank that is seated on at least one of the inner surface and the outer surface, and extends in the axial direction. The tank includes at least one connection for introducing and/or discharging a fluid.

Abstract: For increasing the speed in 3D printing, for avoiding the conveying elements slipping from the conveyed semi-finished product, and for improving the transmission of force from the conveying elements to the semi-finished products to be conveyed, a conveying installation is provided for an additive manufacturing machine. The conveying installation for conveying a semi-finished product comprises a longitudinal conveying mechanism which by means of a periodic movement of at least one conveying element conveys the semi-finished product along a conveying direction which is parallel to the semi-finished product longitudinal axis. The conveying element when moving in the conveying direction acquires the semi-finished product, and when moving counter to the conveying direction is released from the semi-finished product. This results in a movement of the semi-finished product in the conveying direction.

Abstract: A method of providing ice protection on a surface of an aircraft using exhaust air from a laminar flow control compressor. An aircraft structure, for example a wing, includes a skin. The skin has an external surface, on an outer face of the skin. The skin has an internal surface, located opposite the external surface on an inner face of the skin. The aircraft structure includes a laminar flow control system including a compressor. The aircraft structure is so arranged that the exhaust air from the compressor is directed onto the internal surface of the skin of the aircraft structure, for example thus providing hot exhaust air which function as an ice protection system (whether by de-icing or anti-icing).

Abstract: A rail for the fastening of equipment elements, such as, in particular, seats, in aircraft, includes a holding region for connection to an equipment element of an aircraft, and a support region to fasten the rail to a carrier element of the aircraft. The rail has a metallic shell which is, for example, made of titanium and which is filled with a fiber-reinforced thermoplastic filler material which is reinforced by short fibers. To produce the rail, a metallic molded part is used as a casting mold and is filled, for example by injection, with the filler material and, after the rail has been produced, forms the metallic shell for the filler material.

Abstract: An internal cladding part for cladding a fuselage structure of an aircraft is disclosed having a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner. The insulation structure is disposed in the receptacle cavity between the first and the second cover layer.

Abstract: 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.

Abstract: An aircraft pylon comprising a primary structure and a pipe segment having an internal duct positioned inside at least one structural tube primary structure. This solution makes it possible to reduce the crowding outside the structural tubes of the primary structure, makes it easier to integrate other equipment inside the pylon, and may help to improve the aerodynamic performance of the pylon by reducing its cross section.

Abstract: A floor structure for an aircraft includes a rail that defines a recess having an opening and a bottom and designed to receive one or more attachment elements, a covering element arranged above a segment of the recess so as to provide a complementary bearing surface above the opening, and a cellular supporting structure having a first end that rests on the bottom of the recess, and a second end supporting the covering element. Thus, the covering element can be sufficiently thin to avoid or limit the formation of steps at the surface of the floor structure.

Abstract: A tyre monitoring device configured to be mounted on a wheel is described. The device includes a pressure sensor for sensing an inflation pressure of a tyre on the wheel; a wireless communication interface configured to receive data indicative of a command to indicate tyre pressure; a storage storing a predetermined pressure value; an indicator configured to provide a first indication and a second indication, wherein the first indication is different from the second indication; and a processing system configured to operate the indicator to provide the first indication or the second indication responsive to receipt of the command to indicate tyre pressure, and based at least in part on the inflation pressure and the predetermined pressure value.

Abstract: An anterior part of an aircraft propulsion assembly nacelle, having an air intake lip disposed at a front end and an outer panel, of which an outer face extends an outer part of the air intake lip. A front edge of the outer panel and a rear edge of the air intake lip are shaped so as to overlap radially and to nest so as to ensure a continuous surface between the outer surface of the outer part of the air intake lip and the outer face of the outer panel. Moreover, the front edge of the outer panel is connected to the rear edge of the air intake lip with no added rigid element. This permits a rigid connection while avoiding creating local irregularities on the outer surface of the nacelle, which irregularities might disrupt the flow of air around the nacelle, giving rise to additional drag.

Abstract: A method and a system for estimating state of wear of a cutting tool mounted on a machine tool. The system includes an acquisition module configured to acquire at least one operating signal specific to the cutting tool during at least one interaction of introduction or of extraction between the cutting tool and the material to be machined, and a microprocessor configured to generate from the at least one operating signal a wear signature of the cutting tool and to determine the state of wear of the cutting tool as a function of the signature.

Abstract: A method for optimizing the load factor of luggage compartments in an aircraft cabin for a flight includes creation of at least one digital image of a piece of luggage, which is intended to be transported in the luggage compartments during the flight, by a passenger of the flight using a camera, determination of dimensions of the piece of luggage using the at least one digital image, comparison of the previously determined dimensions with free volume in the luggage compartments in the aircraft cabin on the flight, and consideration of the result of the comparison when loading the luggage compartments before the beginning of the flight.

Abstract: A forward part of an aircraft propulsion unit nacelle, comprising an air intake lip, an acoustic panel, and a rigid connection between the acoustic panel and the air intake lip. The acoustic panel has a resistive surface and a back skin, and the rigid connection is formed between the air intake lip and the back skin of the acoustic panel to form a propagation path for forces between the air intake lip and the back skin. This configuration gives freedom from design constraints, which enables an increase in the acoustic treatment region toward the front of the nacelle. An aircraft propulsion unit comprising a nacelle having such a forward part is also provided.

Abstract: A movement device for a luggage compartment flap having a mounting arm for the mounting of a luggage compartment flap. The movement device furthermore includes an actuator which is coupled to the second section the mounting arm and which is configured to, when activated, move the mounting arm such that the luggage compartment flap is moved at least part of the way from an open position to a closed position. As a result of this movement of the luggage compartment flap, the latter can be more easily reached and, for example, moved manually into its closed position. Also provided are a luggage compartment having a movement device, a vehicle region having a multiplicity of luggage compartments, and a vehicle having at least one movement device.

Abstract: An acoustic panel for an aircraft nacelle air intake comprising a resistive skin perforated by noise absorption holes and a core against which the resistive skin extends, wherein the resistive skin has a smooth visible face and a castellated rear face with alternating ribs and grooves. The noise absorption holes are formed exclusively in the grooves, i.e., in a zone where the skin is less thick, which enables the holes to have a diameter that is both greater than the thickness of the skin and small enough not to have any impact on drag. The mechanical strength of the resistive skin provided by the ribs ensures that the lesser thickness of the resistive skin in the grooves does not render the resistive skin overly flexible.

Abstract: A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.

Abstract: Processes and systems for determining that a piece of luggage has been left behind in an overhead bin of a vehicle. When a passenger places a piece of luggage into the overhead bin, it is associated with that passenger by detecting that the passenger has sat down in a particular seat after the luggage has been placed into the overhead bin. When it has been determined that the passenger has deboarded the vehicle, and the luggage has not been removed, reminder signals are sent.

Abstract: A main electrical cabling is subject to variations in ambient temperature over its length. A detection system for detecting fault in the main electrical cabling able to cause a serial arc, or heating within a connection, includes a monitor electrical cabling placed as a return loop alongside the main electrical cabling, a monitoring device, and a return cable bringing back electrical potential at the output of the main electrical cabling to the monitoring device. The monitoring device includes a controllable current generator injecting, into the monitor electrical cable, a current dependent on current flowing through the main electrical cabling. Electronic circuitry determines a difference in voltages at inputs and outputs of the main electrical cabling and of the monitor electrical cabling, to detect a potential fault in the main electrical cabling leading to a serial arc or increase in temperature. A fault in the main electrical cabling is detected despite variations in temperature.

Abstract: A connector system for an aircraft, for connecting a hose line, includes a skin panel which has a clearance which extends between an external face and an internal face, a primary part which on the clearance is disposed on an internal side of the skin panel that is defined by the internal face, a cover mounted on the primary part and movable between a closing position in which the cover covers the clearance of the skin panel, and an opening position in which the cover releases the clearance of the skin panel, and a tubular connector port mounted on the primary part and movable between a storage position in which the connector port is disposed on the internal side of the skin panel, and a use position in which the connector port projects beyond the external face of the skin panel.

Abstract: A molding device for producing a shell element reinforced with supporting elements and composed of fiber composite material, including a mold part with a mold surface including a cavity for receiving a supporting element of the shell element, and a mold core to be arranged in the cavity and to support the supporting element on the shell element when the supporting element of the shell element is arranged in the cavity. The molding device enables prevention of the mold cores from falling out in an uncontrolled manner when the shell element is removed from the mold as the mold core includes a holding device to engage with the supporting element of the shell element to be produced located in the cavity and to hold the mold core on the supporting element when the shell element to be produced is released from the mold part.