Abstract: An aircraft seat assembly for aircraft passengers having restricted mobility comprises a seat base assembly that comprises a first carrier device and a first fastening means. The aircraft seat assembly further comprises a wheelchair sub-frame, a second carrier device and a second fastening means. The dimensions of the wheelchair sub-frame are adapted to the dimensions of aisles provided in the aircraft cabin. Finally, the aircraft seat assembly comprises a seat which comprises a fastening means that is complementary to the first fastening means of the seat base assembly and to the second fastening means of the wheelchair sub-frame.

Abstract: The disclosure provides methods for the detection of a possible joint defect, in particular a root fusion defect, in a friction stir weld seam, wherein two members are joined together and the methods include generating of a tensile stress in the region of the friction stir weld seam in the elastic range, and testing in at least some regions of a lower face of the friction stir weld seam, in order to detect any joint defect.

Abstract: A method for producing a tubular structural component and device for production thereof are disclosed. A tubular molding tool has an inner mold surface shaped corresponding to an outer surface of the structural component. A support surface of an expandable support, formed corresponding to the molding tool shape such that in an unexpanded state the support fills the molding tool while the support surface and the mold surface run parallel leaving an expansion spacing of the support surface to the mold surface, is covered with a tubular non-crimp fiber fabric, such that fibers of a fiber layer of the non-crimp fiber fabric run diagonally around the support. After the support has been arranged in the molding tool, the non-crimp fiber fabric is pressed against the mold surface by expanding the support with radial expansion of the non-crimp fiber fabric. The non-crimp fiber fabric is infiltrated by a curable matrix.

Abstract: A standardized/modularized partition wall with a basic sandwich structure for purposes of separating a cabin area of an aeroplane. The partition wall has a multiplicity of defined zones for the flexible positioning of holding fixtures for the connection of accessories such as flat screens, baby carriers, newspaper racks, and similar, and which is dimensioned for a maximum population with accessories.

Abstract: The invention relates to a housing part containing a lubricant reservoir and at least one respective inlet and outlet opening for filling and draining a lubricating fluid into and from the lubricant reservoir. The inlet and outlet openings are sealed by releasable closure devices each comprising a sensor means for determining the operation parameters in a lubricant contained in the lubricant reservoir and for generating and/or storing sensor signals, as well as a transceiver for the transmission of the sensor signals to an external processing unit.

Abstract: A supplementary power supply apparatus for electric onboard consumers of a vehicle, in particular flying machines. The apparatus includes openly disposed visible solar surfaces of several solar cells that are arranged in areas on the surface of an outer skin of the vehicle or integrated in the latter in the manner of a layer. Each of the solar cells includes at least two electric terminals by means of which the solar cells may be interconnected to form a solar generator, and several ones of the electric terminals are configured as generator terminals of the solar generator for one or several predetermined voltages between two respective ones of these generator terminals.

Abstract: The method according to the invention allows the production of a complex, integral (onepiece) fiber composite part having a plurality of internal and undercut stiffening elements employing removable cores. Because connection elements are no longer necessary, a high weight savings potential results, because, for example, rivets and rivet flanges required for this purpose, as in the case of conventional assembly from individual parts (differential construction), become superfluous.

Abstract: A method and an apparatus for carrying out the method for installing an especially dome-shaped pressure bulkhead on a one-piece, substantially conical rear section for an aircraft, wherein said rear section includes a connection area and an end area. The method involves the steps of horizontally accommodating a prefabricated rear section in a horizontal support; inserting the rear section into a pivoting frame; pivoting the rear section into a vertical position using the pivoting frame, wherein the connection area of the rear section points upward; horizontally placing and centering the pressure bulkhead on the connection area, and joining the pressure bulkhead with the rear section in the area of the connection area.

Abstract: A cabin attendant seat for an aircraft, an aircraft monument comprising such a cabin attendant seat and an aircraft comprising such an aircraft monument. The cabin attendant seat is movable from a starting position into at least one end position. The cabin attendant seat includes at least one backrest element and two seat elements. Each of the two seat elements is movable relative to the at least one backrest element between a folded position and an unfolded position.

Abstract: A compact galley segment, which allows to safely and temporarily fix trolleys outside of a closed storage space includes a first trolley storage space, a second trolley storage space, a retractable trolley restraint device and a plurality of vertically arranged walls. The first trolley storage space includes a plurality of delimiting walls defining an inner space for receiving at least one trolley and an opening for inserting or removing the at least one trolley into or from the inner space. The second trolley storage space includes at least one placement space for temporarily placing a trolley. The trolley restraint device is integrated into or onto at least one of the plurality of vertically arranged walls and is configured for releasably restraining a trolley temporarily positioned in the second trolley storage space and for being fully retractable into the outer contour of the galley segment.

Abstract: A rail system for use when assembling a component in an aircraft comprises a first rail element having a securing device which is designed to be complementary to a first securing device provided in the region of a floor of an aircraft fuselage element and is adapted to cooperate with the first securing device in order to releasably secure the first rail element in the region of the floor of the aircraft fuselage element, wherein a section of the first rail element projects beyond an edge of the floor of the aircraft fuselage element in the connected state of the first rail element and the aircraft fuselage element.

Abstract: A fluid cooling device for the propulsion unit of a propfan type aircraft including a compressed air intake at the air compressor of the turbomachine, an air vein capable of conveying the collected compressed air to a cooler, and a system for conveying the heat of the lubricant to the cooler is provided. The cooler includes a matrix body provided with a plurality of ducts for a cooling agent, the ducts extending along a first inner surface up to a second outer surface of the matrix body such that the collected pressurized air serving as a cooling agent can pass through the matrix body, the matrix body of the cooler forming a portion of the outer skin of the propulsion unit; and a set of fins extending from the outer surface towards the outside of the propulsion unit, and oriented mainly parallel to the air flow direction when the aircraft is in flight.

Abstract: A sealing device for mounting a monument on a structural element of an aircraft and for providing a seal between the sealing device and the floor of the aircraft is provided. The sealing device comprises a cylindrical element with a pin for attaching the sealing device to the structural element and a recess for receiving another pin of a mounting device to which the monument is attached. The sealing device may have a smaller diameter than a mounting block of the mounting device such that the seal cannot be damaged by trolley wheels.

Abstract: A system for supplying an aircraft with inert gas is provided. The system includes at least one fuel cell with an air inlet and an exhaust air outlet as well as a membrane device with an inlet, an outlet and a vapor-permeable membrane. The exhaust air outlet is in fluid communication with the inlet of the membrane device. The membrane device guides a gas from the inlet to the outlet and to give off to the outside through the membrane any water vapor contained therein. This leads to a cost efficient, passive and reliable dehumidifaction of inert exhaust gas for inerting purposes, and a dehumidification device that does not or only marginally increases the weight of the aircraft.

Abstract: An engine for propelling an aircraft includes an annular fuel cell arrangement having at least one fuel cell, at least one electric motor couplable to the fuel cell arrangement, at least one fan couplable to the electric motor and a cowling having an inlet and an outlet nozzle. The fuel cell arrangement is arranged inside the cowling, the at least one fan is arranged between the inlet and the fuel cell arrangement inside the cowling, the electric motor is operable under consumption of electric power delivered by the fuel cell arrangement and the at least one fan is designed to produce a thrust force by creating an accelerated airflow at the outlet nozzle. The engine is extremely efficient and comprises a distinct low noise.

Abstract: Disclosed is a method for the installation of systems in an aeroplane fuselage, a device with a rails system for the execution of the method, and a freight loading system, which uses the rails system as a guidance system for cargo.

Abstract: An aircraft wing has a main wing element with a spar and a leading edge rib supported by the spar, a high lift device movably mounted to the main wing element, and an actuation mechanism with a drive shaft and a gear train. The gear train has a drive cog carried by the drive shaft, an actuator cog coupled to the high lift device, and one or more intermediate cogs mounted to the rib and coupled in series with the drive cog and the actuator cog so as to transmit torque from the drive cog to the actuator cog which moves the high lift device between a retracted position and an extended position in which the high lift device increases the camber of the wing. Sizes of the cogs in the gear train are selected so that the drive shaft rotates at a higher rate than the high lift device.

Abstract: A method for delivering announcements via a cabin communication facility comprising at least one cabin loudspeaker and via an on-board entertainment system comprising at least one headset output comprises the steps of delivering an announcement via the at least one cabin loudspeaker, beginning at a first instant, and delivering the announcement via the at least one headset output, beginning at a second instant, which differs from the first instant, the delivering of the announcement via the at least one cabin loudspeaker and the delivering of the announcement via the at least one headset output being initiated at differing instants.

Abstract: An aircraft includes a system for influencing the yaw moment. The system includes a thrust generation means, an energy store which can be coupled to the thrust generation means for transmitting energy to the thrust generation means, and a trigger device. The thrust generation means is set up so as to provide a thrust force, including a thrust direction vector at a distance from a yaw axis of the aircraft. The trigger device is set up to couple the energy store to the thrust generation means at least for a predetermined period T on demand. The ability to compensate part of the thrust asymmetry independently of a rudder unit if an engine fails means that the rudder unit can be configured with smaller dimensions. This leads to a considerable reduction in the aerodynamic resistance of the aircraft, and thus to a weight-equivalent advantage, without leading to safety compromises.

Abstract: A curing tool for a shell component, includes a first tool component, which is cuboid and has a wedge-shaped bevel forming a first sheared edge on a first side edge, and a second tool component, which is cuboid, has a wedge-shaped bevel forming a second sheared edge on a first side edge and has a first corner bevel on a second side edge diagonally opposite the first side edge. The wedge angles of the first and the second sheared edge are equal.