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: 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: A seat system for a cabin of a transportation system includes a first seat unit, a second seat unit, and a rail system attachable to a floor of the cabin, having two rails that run parallel to each other, for receiving the seat units on selective positions. A line-up of a plurality of first seat units and at least one second seat unit on the rail system constitutes a seat arrangement. The first seat unit includes a seat frame having a seat cushion and a back cushion. The second seat unit includes a seat frame having a foldable seat cushion and a back cushion. The second seat frame includes two forward seat legs supported on two auxiliary rail segments that are arranged between the rails in a region. The forward seat legs are guidable underneath the seat cushion of a first seat unit arranged in front of it.

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 panel for cladding a ceiling or wall in a cabin, especially the cabin of a passenger aircraft, in which a board is laminated on both sides with a cover layer which is made of fibrous material or fabric, which is impregnated with resin or a thermoplastic material, and is cured under the effects of pressure and temperature, said board having at least one core with a honeycomb structure formed by a large number of walls, said walls being compressed or bent in a pre-defined region of the board by between 5% and 50%.

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 wing (9) having a base section (11) and a tip section (13) pivotably connected to the base section (11) such that the tip section (13) is pivotable between a deployed position and a stowed position in which the spanwise length of the wing (9) is smaller than in the deployed position. The wing arrangement also has an actuating arrangement (19) including a linear hydraulic actuator (21) coupled between the base section (11) and the tip section (13) such that it is operable to selectively move the tip section (13) between the deployed position and the stowed position, a first and a second hydraulic connection portion (79a, 79b) connected to the linear hydraulic actuator (21) such that they are in fluid communication with different chamber sections (27a, 27b) of a cylinder (25) of the linear hydraulic actuator (21), and a first hydraulic subsystem (81a) and a second hydraulic subsystem (81b).

Abstract: A passenger seat arrangement for a vehicle cabin includes at least one first group of passenger seats with a first passenger seat and a second passenger seat, at least one third passenger seat, and an aisle extending parallel to a longitudinal axis. The first passenger seat or the third passenger seat is arranged directly adjacent to the aisle and with a seating direction extending parallel thereto. A seating direction of the second passenger seat is rotated relative to the seating direction of the first passenger seat by a first angle of at least 2°, and the first group of passenger seats and the third passenger seat are arranged adjacent to one another and have a longitudinal offset along the longitudinal axis.

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: 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 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 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: 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.