Abstract: A three-dimensional printing device includes a movable unit with a superconductor and a printing head arrangement for printing a printing material, a magnetic field generator adapted to generate a magnetic field, and a control device. The magnetic field generator and the movable unit are adapted for coupling in a force-locking manner by means of frozen magnetic flux, and the controlling device is adapted to control a magnetic field strength of the magnetic field generator.

Abstract: An aircraft interior lining component is formed at least partially of a thermoplastic foam material and includes a first surface which faces an interior of an aircraft cabin when the aircraft interior lining component is mounted in an aircraft, and a second surface which faces away from the interior of the aircraft cabin when the aircraft interior lining component is mounted in an aircraft. The second surface of the aircraft interior lining component includes at least one supporting section and at least one surface section adjacent to the supporting section and recessed relative to the supporting section. The supporting section is dimensioned and arranged so that it is supported, when the aircraft interior lining component is mounted in an aircraft, on an element of a primary structure of the aircraft at least when a predetermined load acts on the first surface of the aircraft interior lining component.

Abstract: A device for controlling an opening forming an air inlet or air outlet in an outer skin of a vehicle. The device comprises a multiple-member inlet ramp, which is configured to vary at least one of a degree of opening of the opening and a cross section of an air duct connected to the opening; an actuator, which is coupled to the multiple-member inlet ramp and is configured to move the multiple-member inlet ramp into a shape related to at least one of a certain degree of opening and a certain cross section; and a movement control device, which is configured to control a movement of the multiple-member inlet ramp.

Abstract: A wearable manufacturing assistance device (1) for supporting a manufacturing tool (3), the manufacturing assistance device (1) includes a body unit (7) including a fastener (11) for fastening the body unit (7) to the back (13) of a technician (5) in a wearing position (15), and an arm member (9) which has an attachment end (19) attached to the body unit (7) and a tool end (21) opposite to the attachment end (19), wherein at the tool end (21) a mounting device (23) for mounting the manufacturing tool (3) to the arm member (9) is provided. While the wearable manufacturing assistance device (1) is fastened to the back (13) of the technician (5) and is in a wearing position (15), the arm member (9) extends from the attachment end (19) at the body unit (7) over a shoulder (17) and laterally past a head (27) of the technician (5).

Abstract: In controlling pressure in an aircraft cabin, during flight operation, an effective flow cross-sectional area of at least one outflow valve is controlled to adjust air flow exiting the cabin through the outflow valve so pressure within the cabin is controlled according to a predetermined cabin pressure control strategy. During flight operation of the aircraft, an effective flow cross-sectional area of at least one negative relief valve is controlled to adjust air flow entering the cabin through the negative relief valve so a negative differential pressure between the pressure within the aircraft cabin and an ambient pressure prevailing outside of the aircraft cabin is prevented from exceeding a predetermined threshold value. During ground operation of the aircraft, the effective flow cross-sectional area of the at least one negative relief valve is controlled to allow an equalization between pressure within the cabin and ambient pressure prevailing outside of the aircraft.

Abstract: A shaping tool for forming a semi-finished product which contains reinforcing fibers and is fed to the shaping tool in a continuous process comprises a first shaping-tool element and a second shaping-tool element which is located opposite the first shaping-tool element. The shaping-tool elements have shaping faces which face towards the semi-finished product, at least in certain operating phases of the shaping tool, and which are curved and/or inclined, at least in certain sections, in a direction of conveyance of the semi-finished product through the shaping tool, and/or curved and/or inclined, at least in certain sections, in a direction perpendicular to the direction of conveyance of the semi-finished product.

Abstract: A fiber composite component includes an integrated structural health sensor arrangement, wherein the component includes a plurality of layers of fibers embedded in a matrix material, wherein the layers include at least two strain sensing fibers arranged parallel and at a distance to each other, wherein the strain sensing fibers are lithiated carbon fibers having piezoelectric characteristics.

Abstract: A fiber composite component having an integrated structural health sensor arrangement includes a plurality of layers of fibers embedded in a matrix material, at least two rupture sensing fibers arranged on or in at least one of the layers, wherein the rupture sensing fibers are carbon fibers having an electrically insulating coating, and two electrical connection devices, each being accessible from an outer delimiting surface or an outer edge of the component, wherein the electrical connection devices are connected to different ends of the rupture sensing fibers.

Abstract: A fuselage includes a fuselage section with an inner surface having a non-circular contour and a spherical pressure bulkhead with an outer edge. The outer edge of the spherical pressure bulkhead is attached to the inner surface of the fuselage section and extends along a line, which is non-circular. The line extends in a three-dimensional space extending parallel to the inner surface of the fuselage section. An aircraft and a method for manufacturing a fuselage are also described.

Abstract: A method for assembling at least two parts, connected by main and secondary definitive connections arranged in predetermined positions, includes: secondary definitive connections each housed in secondary definitive holes passing through the parts to be assembled, made independently of one another before the parts are assembled, main definitive connections each housed in main definitive holes passing through the parts to be assembled, made during the same operation while the parts are held in place by the secondary definitive connections.

Abstract: A network includes a power over data link, a data switch coupled to a data bus and configured to transmit and/or receive data from and/or to the data bus via the power over data link, and a service device coupled to the data switch via the power over data link and configured to transmit and/or receive data from and/or to the data switch via the power over data link. The service device has a power splitter to split the data signal of the power over data link from the power supply, service functions coupled to the power splitter and configured to receive power from the power splitter, and a voltage comparator coupled to the power splitter. The voltage comparator is configured to detect voltage level of the power supply, and based on the detected voltage level, to selectively activate and/or deactivate one or more of the service functions.

Abstract: To make available monitoring of the lock in a way which permits a variable configuration of the galley design and ensures reliable checking without limiting the sequencing and operation, an aircraft galley module lock-monitoring device includes a multiplicity of locking elements, a multiplicity of sensors and a signal-processing unit. The locking elements are designed to be moved from a release position into a locking position. The locking elements are designed to secure, in the locking position, a galley insert in a receptacle region, and to release the galley insert in the release position. The galley insert may include aircraft trolleys and standard units. The sensors are designed to sense at least the locking positions of the locking elements and to transmit a locking signal to the signal-processing unit. The signal-processing unit is designed to generate a lock status display on the basis of the locking signals.

Abstract: An emergency power supply system for providing hydraulic power and electric power in an aircraft includes a fuel cell having an electric outlet for providing electric power, a conversion unit couplable with at least one of an AC bus and a DC bus and the electric outlet, and at least one hydraulic pump having a reconfigurable electric motor and a motor control unit and being couplable with a hydraulic system for providing hydraulic power. The conversion unit is adapted for converting a supply voltage of the electrical outlet to at least one of an AC voltage matching a predetermined voltage at the AC bus and a DC voltage matching a predetermined voltage at the DC bus. The reconfigurable electric motor is couplable with the fuel cell and the AC bus and is adapted for being operated by the supply of electric power either from the fuel cell or the AC bus.

Abstract: A method for controlling takeoffs of mechanical energy and/or air on a turbine engine for the propulsion of an aircraft. It is based on a protocol for the exchange of a request/authorization between and by the energy manager and a system for controlling the turbine engine. This protocol is implemented as a result of a modification of the takeoff requirement. It is intended to check whether the surge margin is compatible with the modification of the takeoff requirement and, if the need arises, to apply temporary measures in order to prevent surge in the turbine engine, for example by providing at least a part of the energy requirements by a buffer. This permits the optimization of the operation of a turbine engine for the propulsion of an aircraft, while avoiding the risk of surge of the turbine engine.

Abstract: A 3D printing method includes mixing a sintered component which is selected from the group comprising ceramic materials, ceramic material combinations, metal materials, metal material combinations and metal alloys, with at least one surface coating component which is selected from the group comprising boron nitride, graphene, carbon nanotubes, tungsten sulfide, tungsten carbide, molybdenum sulfide, molybdenum carbide, calcium fluoride, caesium molybdenum oxide sulfide, titanium silicon carbide and cerium fluoride, in a powder mixture; and laser sintering or laser melting the powder mixture in a selective laser sintering method or a selective laser melting method.

Abstract: A lightning diverter element having integrated ESD protection, including a support and metallic segments disposed on the support is disclosed, wherein the support has a resistance per unit length in a range from 100 k?/m to 100 M?/m. Furthermore, a high-frequency device is disclosed, wherein such a lightning diverter element is disposed on a surface of a component of the high-frequency device. Finally, a vehicle including such a lightning diverter element and/or such a high-frequency device is disclosed.

Abstract: A fiber composite component with integrated active electromagnetic shielding includes a fiber composite layer having reinforcing fibers, and an electric conductor, which extends on the fiber composite layer along the fiber composite layer and produces an electromagnetic field during operation, wherein a proportion of the reinforcing fibers is designed as conduction fibers, which are arranged to follow the electric conductor within the fiber composite layer and are designed to produce an opposing electromagnetic field during operation which attenuates the electromagnetic field of the electric conductor.

Abstract: The present invention provides a cabin management system for an aircraft or spacecraft, comprising: at least one first terminal, which acts as an interface for one or more passengers; at least one second terminal, which performs safety-related functions; and at least one means set up to provide and/or receive video data to/from the first terminal and safety-related data to/from the second terminal.

Abstract: An apparatus for draping knitted fiber fabrics for curved profiled structural parts of fiber composite material includes a mold having a mold surface that corresponds to a portion of the desired profile geometry and curvature of the profiled structural part, a clamping device for tensioning a layer of a knitted fiber fabric along a tensioning line in a prestressed state, and a movement device for producing a relative movement between the mold and the clamped-in fabric layer such that the mold surface moves close to the fabric layer in a direction perpendicular to the tensioning line and, in the further course of the relative movement, pushes through the tensioning line such that the fabric layer completely covers the mold surface. The clamping device is equipped to load the fabric layer during the entire draping operation with a tensile force acting along the tensioning line.

Abstract: A leading-edge slat for an aircraft is proposed, which includes a front skin), a back skin, a spar and an air inlet for receiving air at an elevated temperature for de-icing or anti-icing. In the slat, at least one air chamber is created, which is supplied with said air. A first portion of the back skin is attached to the spar at a distance to the bottom section, wherein a second portion of the back skin is attached to the top section. Thereby, a region in front of the fixed leading edge is created, into which air from air outlets integrated into the back skin can be exhausted outside of the slat.