Abstract: A joint arrangement includes an outer joint component, an inner joint component, a cage and at least two balls located between the outer and inner joint component and in openings of the cage. The balls run in ball recesses, while at least two are in a mechanical contact with pressing devices, which are adapted for holding the respective balls in a radially flexible position relative to one of the inner joint component, the outer joint component and the cage and for pressing the respective balls into the corresponding recesses.

Abstract: An aircraft cabin arrangement for a passenger aircraft, extending along a cabin axis which runs centrally through the aircraft cabin arrangement, having a ceiling trim arrangement provided in the upwardly pointing part of the outer wall of the aircraft cabin arrangement and is arranged above the cabin axis, wherein the ceiling trim arrangement comprises a central ceiling panel element and lateral ceiling panel elements which have a panel element, wherein the central ceiling panel element is arranged vertically above the cabin axis, wherein the lateral ceiling panel elements adjoin the central ceiling panel element on both sides in the lateral direction perpendicularly with respect to the cabin axis, wherein one or more of the central ceiling panel element and the lateral ceiling panel elements has a flat lighting device which is embodied in a flat fashion such that it extends over a surface section of the ceiling panel element.

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, and at a lower height, than the region. The sliding face, at the top end portion, comprises a flat porch section connected to an inclined section of the sliding face via a transition section. The sliding face has at least one of a first guidance marking placed in the flat porch section and having a shape and orientation adapted indicate a predefined evacuation direction in the inclined section of the sliding face and a second guidance marking placed in the transition section and having a shape and orientation adapted to indicate a separation between the flat porch section and the inclined section.

Abstract: A method for determining the position of a component in a high lift system of an aircraft, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft; and actuator drive stations coupled with the power control unit and movable high lift surfaces. The method comprises the steps of acquiring a first rotational position of a first position pick-off unit mechanically coupled with the power control unit by means of a first gear having a first gear ratio, acquiring at least one second rotational position of at least one second position pick-off unit mechanically coupled with a driven element in at least one drive station, and determining the number of full rotations the first position pick-off unit has already accomplished between a neutral position and an intended maximum number of rotations.

Abstract: A method for determining a state of a component in a high lift system of an aircraft comprises the steps of extending at least one high lift surface, which is coupled with two drive struts, wherein at least one of the two drive struts is a load sensing drive strut, to a first extended position, acquiring a first load sensed by a load sensing drive strut associated with the at least one high lift surface at a first flight state having a first speed, comparing the first load with a known nominal load for the first extended position and the first flight state under consideration of a predetermined threshold, and producing an alarm signal in case the acquired load differs from the nominal load including the predetermined threshold.

Abstract: A method for coating a surface of an aircraft is provided. The method comprises the steps of cutting to size at least one film section from a shrinkable film material in such a manner that the film section relative to a surface section of the aircraft, which surface section is to be coated with the film section, comprises an overmeasure that is determined by the degree of shrinkage of the film material; applying the film section and a functional coating to the surface section so that the functional coating is arranged between the surface section and the film section; and shrinking the film section by heating it to a temperature that corresponds at least to the shrinkage temperature of the film section and at least to the flow temperature of the functional coating until the contours of the film section largely conform to the contours of the surface section.

Abstract: An aircraft wing has a spoiler movable from a reference position with a deflection angle ?ref to a given target deflection angle ?target by an actuator powered mechanism. An upstream edge of the spoiler is interconnected with the aircraft wing exclusively via a strip element made of a resiliently flexible material and via the actuator powered mechanism. A downstream edge of the strip element extends along the whole or at least along a major part of the upstream edge of the spoiler. The actuator powered mechanism is constructed and arranged such that, while moving the spoiler, the strip element is bent with a constant strain along the strip element. A cross-section of the strip element for all deflection angles ? assumes the form of a ring segment with a radius R(?) at least within a given margin of failure, with ?, ?target, ?ref?[??1; ?2].

Abstract: An aircraft wing has an upper surface element and a first actuator powered mechanism for varying the shape of the surface element which includes: an upstream segment SEG1, a downstream segment SEG2, an interconnecting segment SEG3 interconnecting a downstream edge of SEG1 with an upstream edge of SEG2, wherein the interconnecting segment SEG3 extends along the whole or at least a major part of the downstream edge of SEG1 and the whole or at least a major part of the upstream edge of SEG2, and a link element LNK interconnecting an upstream edge of SEG1 with an upper surface of the aircraft wing, and the first mechanism interconnecting a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the airfoil. The first mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2.

Abstract: The invention relates to a planar structure for joining, in particular for the material-uniting joining, of at least two components. According to the invention, the planar structure is flexible and formed by at least one reaction strand. The reaction strand comprises a preferably cylindrical core, which is provided, at least in some areas, with a coating, which is constructed with a plurality of coaxially applied layers with a small thickness. To produce the layers, two different materials are used, the layers being constructed alternately with one of the two materials. Because of the high degree of flexibility of the reactive planar structure and its arbitrary area extent, components with a complex geometry in the region of the joint faces as well as large-format components can be joined in a material-uniting manner without problems.

Abstract: A system for cooling an aircraft fuel cell system comprising a first cooling circuit thermally coupled to a first fuel cell, to remove thermal energy generated by the first fuel cell during operation from the first fuel cell, and a first heat exchanger arranged in the first cooling circuit and adapted to transfer thermal energy, removed from the first fuel cell via the first cooling circuit, to the aircraft surroundings. The system comprises a second cooling circuit thermally coupled to a second fuel cell, to remove thermal energy generated by the second fuel cell during operation from the second fuel cell, and a second heat exchanger arranged in the second cooling circuit and adapted to transfer thermal energy, removed from the second fuel cell via the second cooling circuit, to the aircraft surroundings. The first cooling circuit is thermally couplable to the second cooling circuit.

Abstract: An aircraft landing flap includes a flap member having an abrasion-resistant coating coated on an abrasion region exposed to mechanical rubbing contacts with an aircraft spoiler. The coating comprises a polyurethane matrix based on aliphatic components and fillers embedded in the polyurethane matrix so as to increase resistance to abrasion.

Abstract: A water supply system includes a first pipe, a water reservoir, and a Venturi pipe having a first Venturi nozzle terminal, a second Venturi nozzle terminal and a Venturi nozzle branch arranged between the first and second Venturi nozzle terminal. The first Venturi nozzle terminal is connected via the first pipe to the water reservoir. The first Venturi nozzle terminal is connectable to a second pipe to fill the water reservoir. The branch of the Venturi pipe is connectable to a third pipe to supply taps. Water flows through the Venturi pipe from the first Venturi nozzle terminal to the second Venturi nozzle terminal when the water reservoir is filled, and water flows through the Venturi pipe from the second Venturi nozzle terminal to the Venturi nozzle branch during the supply procedure, to provide a water supply system which requires less maintenance and is less temperamental.

Abstract: The invention relates to a fixing thread 1, 5, 10, 16 for sewing together reinforcing fibers, in particular to form a fiber preform, for the production of a fiber-reinforced composite component by means of impregnation with a curable polymer material. According to the invention, the fixing thread 1, 5, 10, 16 has an interface 4, 9, 15, 19 for locally increasing the ductility of a matrix formed by the curable polymer material and has at least one core thread 2, 6, 11, 12, 17, so as in particular to reduce the tendency for microcracks to form in the matrix of the finished composite component in the regions where the fixing threads 1, 5, 10, 16 penetrate. The interface 4 may be formed, for example, by an enclosure of the core thread 1 by a thermoplastic polymer material, for example by polyethylene, polypropylene or the like.

Abstract: An interior component for an interior room of an aircraft is provided. The interior component includes a body having a first surface and a second surface and a multitude of functional modules which form a passenger service unit. The second surface is arranged opposite to the first surface and comprises a recess. The multitude of functional modules are arranged one after another in the recess in the longitudinal direction of the interior component, such that a first front surface of the functional module arranged frontally in the longitudinal direction closes flush with a first front surface of the body.

Abstract: An actuation device for opening an emergency exit flap of a cockpit door is provided. The actuation device comprises a support structure, at least two securing elements, an actuation element and a deflection mechanism. The support structure is configured so as to be fastened to the emergency exit flap. The securing elements are integrated into the support structure and are configured so as to fasten the actuation device, and thus the emergency exit flap, to the cockpit door. The actuation element is connected to the support structure. Therein, the deflection mechanism connects the securing elements to the actuation element in such a way that a force which is exerted on the actuation element is diverted in such a way that the securing elements are released from the cockpit door.

Abstract: The present disclosure pertains to a window module for an aircraft or spacecraft, including a window frame which comprises, at least in portions, a current-generating element for generating an electric current.

Abstract: A method for determining a state of a component in a high lift system of an aircraft is proposed, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces.

Abstract: A trailing-edge flap system for a wing of an aircraft comprises a trailing-edge flap, a guide rail attached to the trailing-edge flap, a carriage slidably engaging the guide rail and rotatably attachable to a fixed position on the wing structure, and a drive means coupled the wing structure to a first joint on the guide rail. The drive means is configured to move the trailing-edge flap relative to the wing structure by moving the guide rail along the carriage by moving the first joint relative to the wing structure, such that the trailing-edge flap translates and rotates. The trailing-edge flap is at least movable into a cruise position, a high-lift position and an air brake position.

Abstract: A passenger seat for a means of transportation is provided, which comprises a seat frame with a top side, which top side is configured for supporting a seat pan with a seat cushion for providing a seating area for a passenger, and a bottom side opposing the top side. The passenger seat further comprises a stowage cavity arranged between the top side and the bottom side of the seat frame. The seat frame further comprises a first beam and a second beam, both beams being arranged parallel to each other and parallel to a transversal axis of the passenger seat. The top side of the seat frame provides an access to the stowage cavity such that a stowage compartment, which is configured to accommodate an item of luggage, is insertable into the stowage cavity through the access.

Abstract: An aircraft air conditioning system comprises a plurality of temperature zones and at least one door. Comprises an air-conditioning unit configured to condition and provide air to at least one of the plurality of temperature zones, temperature zone sensors each associated with a temperature zone for measuring the temperature therein, and a control unit. The control unit receives information representing the closing state of a cabin door, and is coupled to the temperature zone sensors and configured to control the temperature of the conditioned air provided to at least one of the plurality of temperature zones in two operation modes. In a first mode, when doors are closed, the temperature control depends on the measured temperatures in the temperature zones. In the second mode, it depends on a set-temperature, independent of the measured temperature in a temperature zone affected by an open door.