Abstract: A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction.

Abstract: A device for separating two zones of a passenger cabin including a frame element and an area element which is fastened to said frame element and includes, at least in certain sections, a flexible stretch material. The separating device is detachably fastenable in such a way to a passenger seat installed in the passenger cabin, that the area element extends substantially in one plane with a backrest of the passenger seat and that the section of the area element which includes of a flexible material is transferrable from a non-tensioned physical state into a flexibly stretched physical state in the event of the backrest of the passenger seat being adjusted from an upright position into a reclined position.

Abstract: A screw for an electrically contacting connection includes a screw head and a thread having a thread profile with a first thread flank facing the screw head and a second thread flank facing away from the screw head. The first thread flank is continuously curved from a radially inner bottom region to a radially outer run-out region in such a way that first angles between the center axis and local tangents, which lie on the first thread flank and intersect the center axis of the screw, increase radially outward along this direction. The second thread flank and the center axis include a second angle, which lies below the maximum first angle, in the opposite direction of the first angle. The run-out region continuously connects the first thread flank and the second thread flank to one another and is completely rounded.

Abstract: The invention relates to a wingtip extension comprising a leading edge and a trailing edge, which wingtip extension is affixable to an outer end of a wing, wherein the leading edge, at least in some sections, is essentially straight, and the straight section of the leading edge comprises a leading-edge sweep angle that exceeds the leading-edge sweep angle of the wing, and the local depth of the wingtip extension gradually decreases between a connecting region for connection to the wing and the outer end of the wingtip extension. By means of a wingtip extension according to the invention, in a delta wing a vortex burst region is positioned just behind the wingtip, as a result of which vortex burst region the cores of wingtip vortices burst and eventually become unstable, so that as a result of this the wake vortices of the aircraft can be reduced. The invention furthermore relates to a wing, comprising wingtip extensions according to the invention, as well as to an aircraft comprising such a wing.

Abstract: A cover sheath includes a main body being adapted to define a channel for accommodating at least one conducting cable extending there through, and a hook and loop arrangement disposed on at least a portion of an outer surface of the main body. The main body is made of an electrically conducting material.

Abstract: A communication module includes a communication module, having an inductive energy transfer unit, a transfer driver coupled to the inductive energy transfer unit and configured to generate driver signals for operating the inductive energy transfer unit, a charging processor coupled to the transfer driver and configured to control the inductive energy transfer unit to operate in an inductive power charging operation mode, and a communication processor coupled to the transfer driver and configured to control the inductive energy transfer unit to operate in a near field communication (NFC), operation mode.

Abstract: A fuselage structure includes a pressure bulkhead and a frame being arranged behind the pressure bulkhead. The fuselage structure includes a first beam element with a first cantilever and a second cantilever, while the first beam element extends in a vertical direction of the fuselage structure. The first cantilever and the second cantilever protrude from the first beam element in a first direction toward the frame. The first direction of both cantilevers is inclined at a first angle with respect to a longitudinal direction of the fuselage structure. An aircraft with a fuselage structure and a method for manufacturing a fuselage structure are also described.

Abstract: An aircraft comprising a space-optimized standing seat for cabin attendants in a passenger cabin is provided. The aircraft comprises a cabin attendant seat and a cabin with an aircraft exit. The cabin attendant seat comprises a seating area and a backrest and is arranged in the region of the aircraft exit. Therein, the cabin attendant seat is designed as a standing seat.

Abstract: An air conditioning system for an aircraft for the individual air conditioning of regions of a cabin of an aircraft includes a central air conditioning device, which provides a pressurized and temperature-controlled central air flow. A part of the central air flow is supplied to a first cabin region. Another part of the central air flow is heated in a heating device or cooled in a cooling device and supplied to another cabin region. Water evaporates in the cooling device, in order to cool the air flow to be supplied to the cabin region.

Abstract: A drop test device includes a suspension frame, a delay roller which is placed and mounted on the suspension frame, and at least one suspension cable, a first end of which is connected in a stationary manner to an attachment point on the outer surface of the delay roller and a second end of which includes a mounting which can be releasably or fixedly connected to a drop object.

Abstract: A drive unit includes a combustion chamber for combusting a fuel/air mixture, and a fuel cell device, wherein the fuel cell device includes at least one fuel cell, which in each case includes an anode that is couplable to a fuel line, a cathode that is couplable to an air source, and a fluid outlet and is arranged upstream of the combustion chamber. The combustion chamber further includes a combustion chamber inlet for supplying the fuel/air mixture, and a combustion chamber outlet for discharging exhaust gas, and the combustion chamber inlet is connected to the fluid outlet of the fuel cell device. In this way a hybrid drive unit can be provided which apart from mechanical power also generates electrical power at high efficiency.

Abstract: The present disclosure pertains to a seat device for an aircraft or spacecraft with at least one photoelectric device, which is designed to provide electrical energy such that this energy can be used to charge or supply an electrical device, and/or amplify audio signals, and/or transmit data.

Abstract: The present invention provides a device and a method for the residual analysis of a residuum to detect system errors in the system behavior of an aircraft. The device for the residual analysis of a residuum comprises an apparatus to generate the residuum at least dependent on the reference variable and the system output variable, a comparator unit to provide an analytical result by comparing the residuum to a given threshold, a first unit to provide a constant threshold portion, a second unit to provide an adaptive threshold portion at least dependent on the reference value, which can change over time, and a third unit to provide the threshold by linking the constant threshold portion to the adaptive threshold portion.

Abstract: A system for monitoring a fiber-reinforced composite component in production or in service. The system includes a composite component having reinforcing fibers which are encompassed by a matrix material; at least one optical fiber arranged to extend in a continuous path over a monitoring area of the composite component for contact with the matrix material; a signal generator configured to transmit an optical signal along the at least one optical fiber; and a detector device configured to detect scattering, and in particular backscattering, of the optical signal transmitted along the at least one optical fiber.

Abstract: A fuselage skin window unit for an aircraft, an aircraft with such a fuselage skin window unit and a method for manufacturing such a fuselage skin window unit are described. The fuselage skin window unit includes a fuselage skin section and a window pane section. The fuselage skin section is part of a fuselage skin of the aircraft and has a pattern of pinhole perforations. The window pane section is transparent and arranged so that it covers the pinhole perforations.

Abstract: An electrolyte (EL) for the electrolytic polishing of a metallic substrate includes at least one acid compound (A), at least one fluoride compound (F), and at least one complexing agent (CA). Furthermore, a process for the electrolytic polishing of a metallic substrate wherein the electrolyte (EL) including at least one acid compound (A), at least one fluoride compound (F), and at least one complexing agent (CA) is applied.

Abstract: A method for welding together a first and a second multiple layered thermoplastic layer composite material component, includes removing material of the first and second components along a first and a second longitudinal edge, respectively, by a laser beam to form a first and a second step structure, respectively, having a plurality of steps. Each step is formed by one other or several others of the layers of the first and the second component, respectively, and has a surface section parallel to the direction of extension of the layers and a front section transverse to the direction of extension of the layers. The first and the second components are disposed in the abutting position, and then the first and second components are welded together by welding together the abutting surface sections of the steps of the first and second step structures.

Abstract: A passenger seat and a passenger service supply system is provided, comprising a seat with a seating and a backrest, and a passenger service module providing a passenger service such as conditioned air, a personal light, data network access or a similar service. A passenger service module supply line is connected to the passenger service module with a first end, and comprises an interface, which is adapted to connect a second end of the passenger service module supply line to a central supply line of a means of transport. The passenger service module supply line is thereby at least partly integrated into the seating.

Abstract: A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area. The edge of the pressure bulkhead is circumferentially attached to the fuselage structure. In particular, at least one clamping element is arranged inside a mounting bracket having an open trapezoidal-shaped channel formed by a base section of the mounting bracket and non-parallel sides of the mounting bracket. An edge of the pressure bulkhead is inserted in the trapezoidal shaped mounting bracket, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.

Abstract: A device for painting a curved outer surface of an aircraft includes a paint applicator having a plurality of spray painting heads each assigned to one of a plurality of different base color supply units containing one of polyurethane aircraft paint and ink. The device further includes a spatially adjustable positioning device configured to move the paint applicator relative to the curved outer surface and at least one sensor device configured to determine a three-dimensional geometry of the curved outer surface. The device also includes a control unit configured to coordinate a movement of the positioning device with a paint output of the paint applicator, wherein the control unit is configured to alternately activate each of the plurality of spray painting heads so as to produce a picture motif so as to derive a two-dimensional driving geometry based on the three-dimensional geometry.