Abstract: A pole-shaped aircraft framework assembly including a first plug-and-turn connector forming a first end, a second plug-and-turn connector forming a second end, the second end opposite the first end, a first rod extending from the first plug-and-turn connector towards the second plug-and-turn connector, and a coupling component coupled to the second plug-and-turn connector for detachable coupling with the first rod. The first rod has a circumferential outer surface including alternately on a circumferential path in a cross-sectional plane of the first rod a ridged section and a plain section. The coupling component includes a tubular part having a circumferential inner surface including alternately on a circumferential path in a cross-sectional plane of the tubular part at least one ridged section and at least one plain section. One of the first rod and the coupling component is rotatable relative to the other one, engaging respective ridges of the first rod and the coupling component.

Abstract: A mobile satellite communication gateway includes an aircraft communication interface and a satellite communication interface. The aircraft communication interface is designed to make a bidirectional data connection between the satellite communication gateway and a data network of an aircraft, while the satellite communication interface is designed to make a bidirectional data connection between the satellite communication gateway and a satellite communication network. The satellite communication gateway includes a signal processing device, which is coupled to the aircraft communication interface and the satellite communication interface and which is designed to interchange data between the data network of the aircraft and the satellite communication network.

Abstract: A method for operating a wing (5) including a fixed wing (9), a foldable wing tip portion (11) mounted to the fixed wing (9) pivotally between an extended position and a folded position, an actuation unit (13) for actuating movement of the foldable wing tip portion (11), and an arresting unit (15) for locking the foldable wing tip portion (11) in the extended position and/or in the folded position. The method includes controlling the actuation unit (13) to move the foldable wing tip portion (11) either to the extended position or to the folded position until the foldable wing tip portion (11) or the actuation unit (13) contacts a stop element (28), continuing actuation until the actuation unit (13) reaches a stall condition, detecting the stall condition of the actuation unit (13), and locking the arresting unit (15) upon detection of the stall condition.

Abstract: An applicator for application onto and embossing microprofiling of a fluidic medium on a substrate, in particular in the aerospace sector, and a corresponding application device having such an applicator. The applicator has a circumferentially moving die that has an embossing profile, a press for the die and a stabilizing device, in particular a hardening device, for the applied medium. In addition, the applicator has a hollow support body, surrounded by the die at a distance forming a gap, the press being arranged in the gap. The application device has, in addition to the applicator, a handling device for a relative movement between the applicator and a workpiece.

Abstract: A functional unit in a passenger cabin includes a support unit and a passenger seat system. The passenger seat system is formed in two parts and has an upper constructional unit and a lower constructional unit that are each separate components, the upper constructional unit arranged on the support unit and containing at least one backrest, and the lower constructional unit containing a seat frame, at least one seat element and restraint for the passenger on the seat. The seat frame is fastenable to seat rails on the floor of a passenger cabin. For the use position, the upper and lower constructional units are positioned such that a passenger seat is formed. In the use position, personal comfort for the individuals on the seats is not impaired as far as possible, and the division of the seat system into two parts cannot be seen by the user.

Abstract: An assembly for arrangement to the surface of an aerodynamic profile comprises an array of actuators, which are designed as piezo actuators and plasma actuators.

Abstract: For a seat group arrangement for a passenger cabin of an aircraft it is proposed to realize a temporary enlargement of the circulation area by widening the longitudinal aisle of the aircraft for the entry and exit period. For this purpose, a passenger seat group has a supporting frame which is provided with seat legs for fastening to the aircraft floor. At least one first fixedly secured seat having in each case a seat part and in each case a backrest and a further seat which is movable in the transverse direction and has a seat part and a backrest is provided on the supporting frame. The further seat is connected to the supporting frame via a folding device, and the folding device is configured to realize a change in width of the further seat in relation to the seat legs of the supporting frame.

Abstract: A flight control surface assembly for mounting to a main wing of an aircraft includes flight control surfaces side by side with a gap between each two of them, a connection assembly for movably connecting the flight control surfaces to the main wing to be selectively movable in a predetermined synchronous movement between retracted and extended positions, a drive arrangement operable to effect predetermined synchronous movement, and a control unit connected to the drive arrangement to control the drive arrangement. The flight control surface assembly includes for each gap a separate pair of electrical components with a first electrical component and a second electrical component fixedly mounted to a another one of the two flight control surfaces separated by the gap. The first and second electrical components of each pair are configured to wirelessly transfer electrical energy over the gap.

Abstract: An aircraft with a fuselage and with wings connected thereto, wherein a support strut extends between the fuselage and each of the wings, which support strut is connected both to the fuselage and to the wing. The support strut has a hydraulic working cylinder, which can be pressurized with hydraulic fluid in a controlled manner for the purpose of pivoting the wing.

Abstract: A method for producing a vehicle component from a fiber-reinforced plastic including providing a skin panel having an inner side, outer side and mounting portion. The skin panel is a fiber-reinforced thermoplastic material. At least one stiffening component has a connection surface. The stiffening component is a fiber-reinforced thermoplastic material. The stiffening component and skin panel are contacted wherein the connection surface lies on the mounting portion. The method includes areally warming a joining zone so the stiffening component and skin panel are welded together. The joining zone is cooled. A determined geometry of the combination of stiffening component and skin panel is compared with a predefinable geometry. The joining zone is re-warmed, deforming the stiffening component and the skin panel, and the method includes cooling in order to attain the predefinable geometry if the determined geometry deviates from the predefinable geometry.

Abstract: A vertical tail unit (7) for flow control including: an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25), and surrounds an interior space (29), and wherein the outer skin (13) includes a porous section (31) in the area of the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13), wherein the air inlet (17) is fluidly connected to the pressure chamber (15), wherein the air outlet (19) is fluidly connected to the pressure chamber (15). The vertical tail unit (7) has reduced drag and an increased efficiency because the air inlet (17) is formed as an opening (35) in the outer skin (13) at the leading edge (23).

Abstract: A production system for automated assembly of vehicle components, in particular for automated assembly of structural components of an aircraft or spacecraft.

Abstract: A vertical tail unit (7) including an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25) with opposite lateral sides (27a, 27b), and surrounds an interior space (29), and wherein the outer skin (13) has a porous section at the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13) and fluidly connected to the pressure chamber (15), and an air outlet (19) provided in the outer skin (13) and fluidly connected to the pressure chamber (15).

Abstract: A shrouded valve assembly includes a valve with a valve pipe and a valve channel. A valve member in the valve channel can regulate flow of fluid through the valve channel. A valve shroud provides a valve shroud chamber. First and second shrouded pipe assemblies are on opposite sides of the valve, each including a pipe in fluid communication with a respective end of the valve channel, and a pipe shroud providing a pipe shroud chamber. Each pipe shroud chamber is in fluid communication with a respective end of the valve shroud chamber. The pipe assemblies are connected to the valve shroud by first and second connections and to the valve by third and fourth connections, the fourth connection more flexible than both the first connection and the second connection. Load passes between the pipe assemblies via the valve shroud rather than via the valve, protecting the valve from damage.

Abstract: A door assembly for a vehicle. The door assembly includes a door frame, a door panel, a rotating strut, and a linear door guide. The door opens and closes through a combination of rotating and sliding motion, which minimizes the required operational footprint. The strut is mounted on the door panel such that the strut is hidden from view when the door is in an open position.

Abstract: A system for wireless distribution of aircraft data, avionics parameters or control commands between a standardized aircraft interface point and other systems, including a portable in-flight entertainment (IFE) server. The system comprises an aircraft data system with avionics buses for carrying at least one of aircraft data, avionics parameters or control commands. A first module is configured to directly interface with the avionics buses, in order to read/write data. A second module is configured to combine/adapt the data and generate signals of the combined/adapted data. A third module is configured to transmit the signals from the second module via wireless standard protocols towards the portable IFE server. The IFE server is configured to receive the signals from the third module.

Abstract: A floor arrangement for a cabin of a vehicle, in particular of an aircraft or spacecraft, comprises a carrier plate formed with a multiplicity of first fastening perforations and a multiplicity of reinforcing notches. The first fastening perforations are arranged one behind another in fastening rows at a uniform longitudinal distance. The fastening rows are oriented parallel at a uniform transverse distance from one another at an angle of orientation of 45° with respect to a longitudinal direction of the floor arrangement. The reinforcing notches run along the angle of orientation in a manner offset with respect to the fastening rows. A floor panel is formed with a multiplicity of second fastening perforations and is arranged above the carrier plate such that the second fastening perforations are arranged above the first fastening perforations to fasten cabin elements through the floor panel to the carrier plate.

Abstract: The invention relates to a fastening unit (100) for movably fastening an aircraft component (300) to a support structure (400) of an aircraft (500). The fastening unit (100) has a connection element (5) having a hole (5a). The fastening unit (100) also has a first support arm (1) having a first end (1a) for connecting to the support structure (400) of the aircraft (500) and having a second end (1b) for connecting to the connection element (5). The fastening unit (100) also has a second support arm (2) having a first end in (2a) for connecting to the support structure (400) of the aircraft (500) and having a second end (2b) for connecting to the connection element (5).

Abstract: A color based heating system is disclosed. A film for repair of aircraft components of fiber reinforced plastic has color changing properties that can include being temperature-dependent. The color changing properties can be reversible. A system for heating a repair site of a component of fiber reinforced plastic includes the film, a camera and a heating plate. The heating plate can have individually controllable heating zones. A controller can use local color signals of the camera for locally controlling local heating zones of the heating plate. The controller can assign local color signals of the camera to temperatures.

Abstract: In a manufacturing method for a component, a clamping force is applied perpendicular to a surface of a first portion of a semifinished product containing reinforcing fibers via opposing first clamping surfaces of a first clamping tool. A clamping force is applied perpendicular to a surface of a second portion of the semifinished product via mutually opposing first clamping surfaces of a second clamping tool, spaced a first distance from the first clamping tool. A shaping device deforms a third portion of the semifinished product lying between the first and the second portions to form a first subportion and an opposite second subportion. The first distance is reduced to a second distance. A clamping force is applied perpendicular to the surfaces of the first and second subportions via a second clamping surface of the first clamping tool and an opposite second clamping surface of the second clamping tool.