Abstract: A control system for an aircraft includes a hydraulic pump, first hydraulic line, second hydraulic line, a first actuator coupled with a first control surface, a second actuator coupled with a second control surface, and a third actuator coupled with a third control surface. The first control surface and the second control surface are at a distance to each other and symmetrically relative to a symmetry axis. The third control surface is substantially on the symmetry axis, and the first hydraulic line and the second hydraulic line are connected to the hydraulic pump. The first actuator is connected to the first hydraulic line, and the second actuator is connected to the second hydraulic line. The third actuator is connected to the first hydraulic line downstream of the first actuator at a junction point, and the first hydraulic line at least partially includes a larger diameter than the second hydraulic line.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.

Abstract: A method for producing an aircraft fuselage for simplifying and accelerating the production of the aircraft fuselage. The method includes providing a fuselage structure which surrounds an interior space and has an inner side facing the interior space, providing an insulating panel for insulating the fuselage structure, wherein the insulating panel has an inner surface and an outer surface, providing a film which is provided with electric strip conductors, fastening the film to the inner surface of the insulating panel, and attaching the insulating panel to the inner side of the fuselage structure.

Abstract: An aircraft includes a fuselage, a wing attached thereto, a wing tip device attached to a wing end of the wing (2), a wing-like element having a wing root, a wing leading edge and a wing trailing edge, and a torque control device having a rotatable interface means. The torque control device is adapted for rotatably supporting the wing root of the wing-like element on the interface means about a rotational axis extending from the interface means into the wing-like element and to limit the degree of rotation depending on a torque introduced into the interface means by the wing-like element. The wing-like element is adapted to induce a rotation around the rotational axis in an air flow. The wing root is coupled with the wing tip device, the wing or the fuselage through the torque control device such that the leading edge extends into an airflow surrounding the aircraft.

Abstract: A method for joining two components of a meltable material comprises the steps of providing a first component having a first border region and a second component having a second border region, placing the second component relative to the first component so as to form an overlap between the first border region and the second border region under a gap between the first border region and the second border region, continuously heating opposed sections of the first border region and the second border region at the same time through at least one energy source arranged in the gap at least partially, continuously providing a relative motion of the at least one energy source along the first border region and the second border region in the gap, and continuously pressing already heated sections of the first border region and the second border region onto each other.

Abstract: An assembly-ready joint for an aircraft assembly is disclosed. The joint includes a first joint part having a spigot. The joint also has a second joint part with a housing. A floating socket is in an interior of the housing. The second joint part receives the spigot in the floating socket. The joint is arranged to receive a curable medium, such as curable resin, in the interior to contract between the housing and the floating socket.

Abstract: A vehicle seat having at least one seat shell, the seat shell having a frame with two spaced-apart frame units and a shell surface arrangement extending from one of the frame units to the other frame unit. The shell surface arrangement has a net-like structure having a first fiber-reinforced plastic, and the seat shell has at least one holding element connected to a corresponding receiving element for fastening the seat shell.

Abstract: A device is disclosed including a frame, a transfer roller with a circumferential lateral wall, a drive unit, a slit nozzle with a muzzle end for dispensing lacquer, and a deformation unit. The slit nozzle and the deformation unit are each connected to the frame, and an outside contact surface of the lateral wall includes several depressions, the transfer roller is mounted rotatably about an axis of rotation at the frame. The drive unit is configured to drive the transfer roller in a rotation direction of the transfer roller, such that the lateral wall continuously passes through a first angular range and the second angular range, each fixed to the frame. The deformation unit is arranged to elastically deform the lateral wall resulting in a respective first deformation section of the lateral wall passing through the first angular range and a respective second deformation section of the lateral wall passing through the second angular range.

Abstract: A wastewater tank arrangement for an aircraft, including a wastewater tank and a drain pipe having a first end and an opposite second end, the drain pipe fastened with its first end to the wastewater tank and having a second end for connection to a service panel in the aircraft structure. Providing a wastewater tank arrangement can effectively compensate tolerances between the wastewater tank and the service panel, and can effectively compensate installation and manufacturing tolerances during the course of the initial installation, in that the wastewater tank arrangement has a tolerance compensation device configured to connect the second end of the drain pipe to the service panel and compensate tolerances between the second end of the drain pipe and the service panel.

Abstract: A shell arrangement for a fuselage of an aircraft includes a first shell portion extending in a curved manner in a shell peripheral direction and a second shell portion extending in a curved manner in the shell peripheral direction, wherein, in an overlapping portion of the shell arrangement, a first end region of the first shell portion and a second end region of the second shell portion overlap each other in the shell peripheral direction and a first outer face of the first shell portion and a second inner face of the second shell portion are adhesively bonded to each other by an adhesive layer, and wherein an edge of the first shell portion which terminates the first end region with respect to the shell peripheral direction extends in the overlapping portion in an undulating manner in a shell longitudinal direction which extends transversely relative to the shell peripheral direction.

Abstract: A flap support for supporting a flap of a wing for an aircraft is disclosed and includes a load bearing fairing shell and a reinforcement structure at least partially received in the interior space of the fairing structure and mounted to the first and second side wall portions of the fairing shell. The fairing shell includes a front attachment device configured for attachment to a main wing, and the reinforcement structure includes an aft attachment device configured for attachment to the main wing. The flap support further includes a hinge device configured for forming an articulated connection to the flap.

Abstract: A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.

Abstract: An aircraft air conditioning system comprising an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer. A first compressor is arranged in the ambient air supply line and is configured to compress the ambient air flowing through the ambient air supply line. A bleed air supply line allows a flow of bleed air bled off from an engine or an auxiliary power unit therethrough. A bleed air turbine is driven by the bleed air flowing through the bleed air supply line and is coupled to the first compressor so as to drive the first compressor.

Abstract: A flap system driving a leading-edge flap between retracted and extended positions comprises a leading-edge flap having first and second flap joints, first and second scissor links, a first connecting link, and an actuator. The actuator couples with either the first scissor link or first connecting link. The first scissor link is rotatable supported on a first fixed point by a first support joint. An end of the first scissor link opposite the first support joint couples with the first flap joint. The first connecting link is rotatably supported on a second fixed point by a second support joint. An end of the first connecting link opposite the second support joint rotatably couples with an end of the second scissor link. An opposite end of the second scissor link couples with the second flap joint. The first and second scissor links are rotatably coupled to form a scissor arrangement.

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 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: 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: 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: 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 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.