Abstract: A luggage system includes a luggage compartment having a base body and a flap which is movable between a closed position and an open position and is configured to make accessible or close an interior space of the base body. The flap includes a first flap element facing the interior space of the base body and a second flap element facing away from the interior space of the base body, wherein an installation space for components which are to be installed in the region of the luggage compartment is provided between the first and the second flap element.

Abstract: A cabin attendant seat comprises a seat element and a backrest. The backrest is movable relative to the seat element between an upright position, wherein a backrest surface of the backrest extends at an angle of approximately 80 to 100° relative to a seat surface of the seat element, and a folded-back position, wherein the backrest surface of the backrest extends substantially co-planar with the seat surface of the seat element.

Abstract: A door assembly, particularly for doors of passenger aircraft, includes a door frame, a door having a door body hingedly installed in the door frame, at least one hooking pintle attached to the door frame or an edge of the door body extending along a pintle axis, and at least one door latch connected to an edge of the door body or the door frame, respectively, the door latch having a substantially C-shaped latch body configured to rotate around an axis parallel to the pintle axis of the hooking pintle. The door assembly further includes a bistable latch and hook mechanism configured to catch the door latch in hooking engagement with the hooking pintle and to retain the door latch in a direction perpendicular to the door body in an overcenter position.

Abstract: A seating arrangement in a cabin of an aircraft includes a floor with a first surface area, a furnishing item with a respective boundary surface, which extends in a vertical direction from the cabin floor, and toward which is directed a first surface area, at least two folding seats, and optionally a partitioning system. The folding seats are arranged on the boundary surface of the furnishing item, and set up to be swiveled into a neutral position and use position, wherein an individual located in the first surface area can sit on the at least two folding seats in the use position. At least one of the at least two folding seats is not designed as a flight attendant seat.

Abstract: A system for mounting aircraft system components in the crown area of an aircraft comprising a first longitudinal carrier element, a second longitudinal carrier element and a bridging element which connects the first longitudinal carrier element to the second longitudinal carrier element. The system is mountable in the crown area of an aircraft in such a way that the first and the second longitudinal carrier elements extend substantially parallel to the longitudinal axis of the aircraft. A plurality of cable ducts for accommodating electrical lines is provided on the first and/or the second longitudinal carrier elements.

Abstract: An accumulator arrangement suitable for use in a cooling system designed for operation with a two-phase refrigerating medium, includes an accumulator vessel with a receptacle for receiving a refrigerating medium. A liquefier of the accumulator arrangement is adapted to liquefy refrigerating medium to be received into the receptacle of the accumulator vessel before fed in the receptacle of the accumulator vessel and includes a refrigerating medium outlet for discharging refrigerating medium which liquefied in the liquefier from the liquefier.

Abstract: A pressure bulkhead made of fiber composite material for an aircraft fuselage for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure. The bulkhead comprises a first area element, at least one second area element and a plurality of core elements. The first area element has a plurality of receptacles. Each receptacle is configured to receive a core element. The core elements are received in the receptacles between surfaces facing one another of the first area element and of the at least one second area element. The surfaces facing one another of the first area element and of the at least one second area element are connected to one another in regions without core elements.

Abstract: A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said core having at least one recess into which a stopper is introduced, into which at least one attachment element can be introduced to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fiber running direction being wound around the core. In addition, the invention relates to a method for the production of a sandwich panel according to the invention.

Abstract: A segment and a method for producing such a segment, in particular for an aircraft, having a skin field and a skin field stiffening structure. The skin field and stiffening structure are made from fiber-reinforced plastic materials. The stiffening structure is bonded to an inner surface of the skin field and comprises a multiplicity of first stiffeners and mounts which are formed integrally with the first stiffeners and extend in a transverse direction of the first stiffeners for the connection of second stiffeners to form an integral lattice structure. Reinforcement elements are provided for mechanically fixing the mounts to the skin field. Each reinforcement element has a connection section and a blocking section having an extension in a direction inclined to the connection section. The connection section penetrates the skin field and the mounts, and the blocking section is in contact with an outer surface of the skin field.

Abstract: A fairing transition is provided for covering a gap between a movable body and a fixed body on a vehicle that includes, but is not limited to a base plate that is attachable to a vehicle, a cover plate that is attachable to the base plate. The base plate and the cover plate include, but are not limited to a correspondingly formed connecting profile having positive fit on surfaces that face each other, with the connecting profile configured to slide the cover plate onto the base plate. Furthermore, the cover plate is lockable to the base plate in an end position.

Abstract: A surveillance device and method provide access to a surveillance system for keeping a cabin of an aircraft under surveillance. A computer program may be used to execute the method for accessing the surveillance system. The surveillance device includes an authentication unit for examining an access-authorization request for access to the surveillance system, and a control unit for selecting, on the basis of the access-authorization request, a display unit from a plurality of display units provided in the aircraft, and for relaying a video-image signal corresponding to a captured video image of a subarea of the cabin of the aircraft to the selected display unit for the purpose of displaying the video image.

Abstract: An additive layer manufacturing method is disclosed for producing a three-dimensional object and to a corresponding object. Layers of a powder material are applied to a carrier and irradiated, before the following layer is applied, with a laser beam or particle beam selectively only in the areas of the layer which correspond to the three-dimensional object to be produced. Irradiation occurs such that the powder material in the corresponding areas is locally melted or sintered. A first portion is constructed before a second portion or the first portion is provided as a separate component, on which a support structure and second portion are constructed. The support structure is constructed in the form of a plurality of support legs, which extend from the first portion to the second portion and are connected thereto at their opposite ends and are spaced apart from one another at least along part of their length.

Abstract: A method for testing a component in a high lift system of an aircraft comprises the steps of activating a brake coupled with at least one hydraulic motor, commanding a rotation of the at least one hydraulic motor for a predetermined period of time, wherein the brake remains activated, acquiring a sensor output of a motion sensor coupled with a central power control unit for moving a high lift surface during the commanded rotation of the at least one hydraulic motor, determining a motion of the power control unit from the acquired sensor output, comparing the determined motion with a predetermined threshold value, and generating a brake indication signal if the determined motion exceeds the predetermined motion threshold value.

Abstract: Method for detecting a defective node which is connected to a bus, the node incrementing an internal error counter in a normal operating state when an error is detected, and the node switching to an isolated operating state, in which the node does not exchange any messages via the bus if the internal error counter of the node exceeds a predetermined error threshold value, and the node switching from the isolated operating state to the normal operating state when a condition is fulfilled and that change in state being detected, and the node being detected as being defective if a rate of the detected state changes exceeds an adjustable change rate or a number of detected state changes exceeds an adjustable state change threshold value.

Abstract: A system for supplying passengers with air comprises an air supply line and an individual air panel with at least one air nozzle. The air supply line can be fitted with a plurality of laterally situated air outlets, which are spaced apart at uniform distances from each other. The individual air panel comprises an air tap opening with a width and length, wherein the length is several times greater than the width. The individual air panel can be variably positioned in the longitudinal direction on the air supply line in such a way that the air tap opening in the longitudinal direction is arranged parallel to the air supply line, and that the air tap opening covers at least one air outlet. In this way, air can flow out of the air supply line through the air outlet and air tap opening to the air nozzle.

Abstract: A covering system for an interior space of a vehicle comprises at least one surface element and at least one sealing element. The surface element comprises an upper surface and at least one bounding edge extending at an angle to the upper surface. The surface element furthermore comprises at least one recess, which runs at least adjacent to the bounding edge. The sealing element has an extent corresponding at least partly with the at least one bounding edge, and a shape corresponding at least partly with the recess of the surface element.

Abstract: A composite reinforcement component for an aircraft or spacecraft, including a first element assembly aligned in a first extension plane, and a second element assembly aligned in a second, perpendicular, extension plane, the second element assembly intersecting the first element assembly at an intersection of the first and second extension planes. The first and second element assembly each have a pair of staggered comb components. Each comb component includes a base and a plurality of rectangular protrusions extending coplanar from the extension planes of the respective element assembly. The rectangular protrusions form comb teeth of one comb component which are overlapping with comb teeth of the other comb component of the pairs of comb components. The comb teeth of the first element assembly are offset along the intersection by a single comb tooth width with respect to the comb teeth of the second element assembly.

Abstract: An evacuation slide comprises a sliding face having a top end portion adapted to be positioned adjacent to an exit of a region to be evacuated, and a bottom end portion adapted to be positioned adjacent to an escape route leading away from the region to be evacuated and being arranged at a lower height than the region to be evacuated. A light signal generating device is adapted to irradiate at least one light beam onto the escape route which extends further in a direction parallel to a center line of the escape route than in a direction perpendicular to the center line of the escape route so as to indicate a predefined evacuation direction along the escape route.

Abstract: A system is provided for cooling a heat-dissipating device in a vehicle with a fuselage, a passenger cabin, and a region pneumatically communicating with the previously mentioned, which region is situated outside the passenger cabin. At least one heat exchanger is provided for transferring heat of the heat-dissipating device to air, and at least one air conveying device for conveying air through the heat exchanger. The air conveying device is designed to convey air from the passenger cabin to the heat exchanger. The heat exchanger is designed to subject the inflowing air to heat of the heat-dissipating device and to dissipate it to the region situated outside the passenger cabin, thus inducing mixing of the air that has been subjected to heat with the air present in the outside region, and inducing a return flow from the outside region to the passenger cabin by way of their pneumatic connection.

Abstract: An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices.