Abstract: The present invention relates to a method and a device for placing at least one material layer onto a relief mould for producing a composite material. Thereby, an elastically-reversibly deformable body with a surface relief that is designed to correspond to the relief mould is pressed against the material layer, as a result of which the surface of said body is deformed, and the material layer can be picked up. As a result of its elastically-reversible characteristics the body subsequently deforms back to its initial state so that the material layer can easily be placed onto the relief mould.

Abstract: A thermal insulating element (10?; 10??) comprises a first plate (24) forming at least a part of an outer face of the insulating element (10?; 10??) and a second plate (26) forming a further part of the outer face of the insulating element (10?; 10??). The first and the second plate (24, 26) are connected to each other via a frame structure (12) which establishes a geometry of the insulating element (10?; 10??). The first and the second plate (24, 26) and the frame structure (12) define a cavity filled with air, wherein at least one vent opening (28) is formed in the first and/or the second plate (24, 26) and/or the frame structure (12). A projecting edge portion (34, 36) is formed along an edge of a portion of the insulating element (10?; 10??) which is provided with the at least one vent opening (28), the projecting edge portion (34, 36) being adapted to at least partially cover a gap between two insulating elements (10?; 10??) disposed side by side.

Abstract: Methods and apparatuses for ensuring the dimensional constancy of multisegment physical structures, in particular aircraft structures, during assembly are disclosed. The method includes setting up a spatially-fixed three-dimensional coordinate system which encloses the subsequent assembled physical structure and introducing a plurality of segments of the physical structure to be assembled into the spatially-fixed three-dimensional coordinate system. The method includes recording the positions of the individual segments and the positions of already assembled groups of segments repeatedly within the spatially-fixed three-dimensional coordinate system during assembly.

Abstract: A window element has a cover pane which is substantially flush with an outer skin of an aircraft or other transport, achieving a fluid-dynamically favorable, substantially unbulged exterior surface. As a result of the presence of an additional back-ventilated cover pane arranged in front of the actual outer pane of the window element, a fluid-dynamically favorable integration of the window element into the outer skin of an aircraft fuselage airframe is achieved. Any deformation, such as any buckling or bulging of the outer pane of the window element, as a result of a difference in pressure between the interior of the aircraft fuselage airframe and the exterior space at cruising altitudes, has no fluid-dynamically disadvantageous effect. The outer pane is covered by the cover pane which remains substantially undeformed with respect to the outer skin of the aircraft fuselage airframe, for example. Any deformation of the cover pane is largely eliminated by back-ventilation.

Abstract: A system for improving the air quality in a pressure cabin of an aircraft includes a recirculation air circuit in which a portion of the cabin air, referred to as recirculation air, is withdrawn from the pressure cabin, filtered and then recirculated into the pressure cabin. To increase the oxygen partial pressure of the air fed back into the pressure cabin, the quantity of recirculation air is passed wholly or partially through a nitrogen generator which generates nitrogen and an oxygen-containing waste gas from the recirculation air supplied. The oxygen-containing waste gas of the nitrogen generator, together with any remaining quantity of recirculation air untreated by the nitrogen generator, is recirculated into the pressure cabin. The nitrogen generator, to which only recirculation air is supplied, utilizes a pressure gradient existing in flight between the pressure cabin and the outside of the aircraft for nitrogen generation.

Abstract: A retaining device for attachment to a screw contains a hollow base element for receiving a clamping part. The hollow base element has a floor having a hole, and an inner surface of the base element on the floor area of the retaining device is implemented as conical to contact the outer surface of the conical body of the clamping part. The clamping part can be moved downward in the direction of the floor by rotating the retaining device around its own axis and biting into a screw which is inserted through the hole and runs through the opening of the clamping part.

Abstract: The invention relates to a device for load limitation in a aircraft high lift system, said system comprising individual segments of landing flap systems and slat flap systems, and a drive unit. The inventive device for load limitation comprises a control unit that is connected to position sensors and is embodied in such a way as to process signals from the position sensors and to generate a signal for limiting the supplied drive power. The invention also relates to a method for load limitation. According to said method, signals from at least two position sensors are measured; at least one reference variable is calculated form the measured signals; each reference variable is compared with a corresponding threshold value pre-determined from a maximum authorized load; and a control signal is generated for limiting the drive power, when at least one of the reference variables reaches or exceeds the threshold value.

Abstract: A rail for fastening installations in an aircraft, the rail including a rail base section, a running-surface section that extends in a longitudinal direction with a running surface, and a connection section that connects the running-surface section to the rail base section at the face pointing away from the running surface. The running-surface section laterally on both sides, in each case spaced apart at a predetermined pitch, includes a multitude of projections projecting away from the connection section, each with a top that has substantially the same alignment as the running surface and a bottom that has an alignment that substantially is opposed to the alignment of the running surface. The bottom of the projections forms holding surfaces for holding a fitting. The rail is attached to a floor of the aircraft.

Abstract: A folding seat for an aircraft has a backrest, a seat area and an armrest. The seat area is pivotable. When the seat area is pivoted, the armrest is pivotable downwards, the seat area and the armrest being coupled by at least one coupling element in the form of a bevel gear.

Abstract: A mobile divider for an aircraft or an aircraft cabin with a first wall section, a second wall section that is essentially arranged parallel to the first wall section and a cable duct that is arranged between the first wall section and the second wall section. The cable duct protrudes over an edge of the first wall section and an edge of the second wall section in at least one location. This makes it possible to route a supply line such as, for example, an electric line in the cable duct within the divider and also in the transition region between the divider and, for example, a cabin supply channel such that the supply line is not visible to a passenger traveling in the cabin, particularly in the transition region from the mobile divider into the supply channel.

Abstract: A device for adjusting the lift characteristics of an aircraft with a high lift device that is movably attachable to a wing element and that includes at least one slot covering device, where the at least one slot covering device, is movably attachable to the wing element. The slot covering device is designed to regulate the size of a slot between the wing element and the high lift device.

Abstract: A system and a method according to the invention reduce wake turbulence of an aircraft in that a component affixed to the extremity of the wing of an aircraft disturbs the rolling action of the air in the region of the outer wing by periodic hingeing movements.

Abstract: A rudder of a commercial aircraft is provided that is divided along its longitudinal direction in at least one region and the parts of the rudder can be spread against the air flow surrounding the aircraft by means of an actuator in order to decelerate the aircraft.

Abstract: A flight attendant panel, in which a plurality of computer units can be coupled to a common input/output device by a circuitry. One of the computer units is designated as the master computer unit and controls the circuitry in order to specify which of the computer units should be coupled to the input/output device. The actuation of a switch makes it possible to once again return the flight attendant panel into an original state, in which the master computer unit is coupled to the input/output device by the circuitry.

Abstract: A cooling system for the cooling of heat producing devices in an aircraft is designed with a central cold producing device, at least one cold consumer and a cold conveyance system which connects the cold producing device and the cold consumer. With this cooling system, the cold conveyance system has at least one cooling circuit which supplies a cooled cold carrier medium from the cold producing device to at least one cold consumer and brings the cold carrier medium back to the cold producing device, so that at least one cold consumer is supplied with the cold produced in the cold producing device.

Abstract: A device for improving the breathing air quality for the crew and/or the passengers in an aircraft cabin includes an oxygen source, a water source and a feed line, wherein the feed line is connectable to the oxygen source and the water source in order to oxygenate and/or humidify air that is introduced into the feed line. The feed line is further connected to an inlet port of a locally delimited area of the aircraft cabin and adapted so as to feed oxygenated and/or humidified air to the locally delimited area of the aircraft cabin.

Abstract: A device for the manufacture of drilled holes, cut-outs, plane surfaces or the like, includes an attachment structure, which is designed for the attachment of the device to at least one component to be machined, a feed device, which is designed to track a drill of a drilling machine, and a control device for controlling the feed device and a drilling machine. In one example, the feed device includes a support for the drilling machine, which is arranged substantially in the center of a crossbeam.

Abstract: A pressure bulkhead for an aerospace fuselage includes a bulkhead main portion having an approximately flat shape in unloaded state; and a frame supporting and connecting said bulkhead main portion to the fuselage; wherein said bulkhead main portion includes an airtight structure having a reticular component.