Abstract: An apparatus for affixing an object to a rail includes, but is not limited to at least one base body, at least one locking body and at least one operating element. The locking body is held so as to be movable relative to the base body and is connected to the operating element by way of at least one bearing. The operating element is arranged so as to be rotatable in the base body, includes, but is not limited to a cam that acts on the base body, and when rotated moves the locking body towards the base body. In this way apparatus is created which makes possible the manual affixing and undoing, without the need for tools, of an object on and from a rail, for example, if needed, in order to reposition displaceable monuments in a cabin of an aircraft.

Abstract: The present invention discloses a method for controlling a high-lift device or a flight control surface of an aircraft or spacecraft, especially with a system according to the present invention, comprising the steps of receiving, at least one first control unit, a command signal from a commander unit via a data network, providing a primary control signal to at least one secondary control unit via the data network, wherein the primary control signal depends on the received command signal, receiving, at the at least one second control unit, a sensor signal of one or more sensors of the high-lift device or flight control surface, and providing a secondary control signal to one or more actuators of the high-lift device or flight control surface, wherein the secondary control signal depends on the received sensor signal. Furthermore, the present invention discloses a system and an aircraft or spacecraft.

Abstract: Systems and methods for sound damping in air conditioning systems in an aircraft is provided. In one embodiment, an air conditioning conduit can comprise a sound-damping wall that at least partially encloses a continuous hollow space for guiding the air. The wall comprises a multilayer design with a core layer and at least one first cover layer. The core layer comprises a sound-absorbing open-pore core material so that the wall shows an acoustic effect. The first cover layer is airtight, is arranged on the external surface of the core layer, and is two-dimensionally connected to the core layer. The two-dimensional connection between the core layer and the first cover layer causes a composite effect in such a manner that the wall is self-supporting and has a structural function in order to be able to transfer mechanically-occurring loads to structural parts of the aircraft.

Abstract: This invention provides a fuselage of an aircraft or space vehicle with a fuselage section having an outer skin, wherein at least the outer skin of the fuselage section consists of a glass-fiber reinforced aluminum laminate to form a safety zone for passengers in the event of a fire.

Abstract: A method for presenting information by means of an autostereoscopic 3D-display in a passenger cabin of an aircraft or spacecraft, comprising the following steps: provision of the autostereoscopic 3D-display in a predetermined portion of the passenger cabin; provision of a first item of information by means of the autostereoscopic 3D-display such that this information can be detected from a first seat in the passenger cabin; simultaneous provision of a second item of information, which is different from the first item of information, by the autostereoscopic 3D-display such that this second item of information can be detected from a second seat in the passenger cabin. A display device for implementing a method of this type. A passenger cabin for an aircraft or spacecraft comprises a display device of this type. An aircraft or spacecraft having a display device of this type or having a passenger cabin of this type.

Abstract: A fuselage section of an aircraft includes a skin, a plurality of frames positioned transversely to a longitudinal axis of a fuselage of the aircraft, and a plurality of longitudinal stringers at least one of which is configured with a closed transversal section including a stringer hat, two stringer webs, and two stringer feet joined to the skin. At least one of the frames is configured in at least one sector with a frame foot joined to the skin, a frame web having holes at crossing zones with the stringers, a frame cap, and a frame cap extension which does not interfere with the stringers. The frames are joined to, at least, the stringer hats at crossing zones of the frames and the stringer hats.

Abstract: A blade seal comprises a flexible member having a relatively thick edge opposite a relatively thin edge, and an actuator at least partially embedded in the flexible member for actively deflecting the thin edge with respect to the thick edge upon activation of the actuator. The blade seal may be fixed to an aerodynamic trailing edge of either a fixed aerofoil portion or a flight control surface of an aerofoil for sealing between the fixed aerofoil portion and the flight control surface. Also, a method of sealing an aerofoil using the blade seal.

Abstract: The invention relates to a device for limiting the deflection of a door (1), particularly a hatch or a freight door, arranged in a fuselage cell (3) of an aircraft, having at least one holding element (5) arranged preferably in the region of a door jamb (4) or in the region of a door leaf edge (7). In order to ensure deflection limitation for doors, hatches and freight doors in aircraft which can be triggered manually independently of an actuation of the normal locking system, it is proposed according to the invention that the at least one holding element (5) can, if there is a sufficient pressure difference ?p between the internal pressure pi prevailing in the fuselage cell (3) and the outside air pressure pa prevailing outside of the fuselage cell (3), be brought into engagement with at least one abutment (6) arranged in the region of the door leaf edge (7) or the door jamb (4).

Abstract: A rail cover for a seat rail includes a plurality of longitudinal section parts, wherein each longitudinal section part includes a first partial longitudinal section and a second partial longitudinal section, which abut one another in the longitudinal direction of the longitudinal section part. A first longitudinal section part is movable in the longitudinal direction of the rail cover with respect to a second longitudinal section part abutting the first longitudinal section part in the longitudinal direction of the rail cover, wherein in a non-expanded state of the rail cover, the first partial longitudinal section of the second longitudinal section part overlaps the second partial longitudinal section of the first longitudinal section part in the longitudinal direction of the rail cover.

Abstract: A flap arrangement for a wing of an aircraft includes a base member, at least one first flap, at least one second flap and at least one connecting assembly. The first flap is movably supported on the base member and the second flap is movably supported on the first flap. The connecting assembly is mechanically coupled with the base member and the second flap and is designed to move the second flap relative to the first flap when the first flap is moved relative to the base member. Due to the resulting forced guiding of a second flap relative to a first flap a separate actuator for moving the second flap and linkages extending outside of the shape defining contour of the flap arrangement may substantially be eliminated.

Abstract: A system for controlling an aircraft control parameter including a control interface including a mobile element configured to move on a travel, of which at least two portions are separated by a neutral position; a return element bringing the mobile element back to the neutral position when it is not actuated; and an interaction element, and a control unit configured to memorize an item of information corresponding to a first position of the mobile element at an instant of activation of the interaction element; and generate a setpoint of the aircraft control parameter, as a function of a control associated with the first position of the mobile element for which said information has been memorized; or a current position of the mobile element, when this current position is situated on the same portion of travel as the first position and is more remote than the latter from the neutral position.

Abstract: A device for cooling and dehumidifying gases includes a first hollow body with a gas inlet, a gas outlet and a condensate drain; a second hollow body with a coolant inlet and a coolant outlet; and a drive unit. The first hollow body encloses the second hollow body at least in part. One of the first hollow body and the second hollow body is pivotally held relative to the other hollow body and includes at least one turbulence-generating body that extends in the direction of the other hollow body. For rotating the pivotally held hollow body the drive unit is couplable to the hollow body. In this manner a single-stage device for cooling and dehumidifying gases that include water vapor is implemented, which device requires little installation space and is of a particularly lightweight construction. Thus the device is particularly well suited for use in vehicles, in particular in aircraft.

Abstract: A method for edge sealing a fiber-reinforced component formed from a carbon fiber-reinforced thermoplastic or duroplastic plastic material includes electrostatic coating of at least one section of an edge of the component with a thermoplastic powder so as to form a powder coating; and fusing and cross-linking the powder coating in a furnace so as to create a smooth edge seal.

Abstract: A method for the manufacture of a fiber-reinforced component includes heating a blank of a carbon-fiber-reinforced thermoplastic plastic material to at least a melting temperature of the thermoplastic plastic material; introducing the blank into an at least two-part molding tool; forming the fiber-reinforced component by applying pressure on the blank using the molding tool; and injecting a further thermoplastic plastic material into at least one edge region of the molding tool so as to form an edge seal.

Abstract: A passenger seat system includes a backrest and a seat, which has a first sub-portion having a first surface and a second, opposite surface to the first surface as well as a second sub-portion having a first surface and a second, opposite surface to the first surface. The sub-portions are relatively movable in order to provide first and second operating positions. In the first operating position the sub-portions are positioned in relation to the backrest one behind the other such that the first surface of the first sub-portion and the first surface of the second sub-portion form a usable total seat surface. In the second operating position the sub-portions are positioned in relation to the backrest one above the other such that one of the surfaces of the first sub-portion or the first surface of the second sub-portion forms a usable partial seat surface.

Abstract: A double-skin nozzle system including an internal tube for transporting a liquid, formed by a plurality of tube portions connected to one another by removable junction systems, an external tube positioned around the internal tube and formed by a plurality of tube portions connected to one another by junction systems, wherein at least two junction systems each include a blocking device for blocking, along the external tube, the flow of a liquid coming from a leak from the internal tube, and at least one drain for removing the liquid coming from the leak from the internal tube.

Abstract: The invention concerns a pressure application roller unit 2 for the laying down of fiber strips 80 on a surface 82, with a pressure application roller 7 mounted in a mounting unit 35 such that it can rotate about a shaft 10. In accordance with the invention the pressure application roller 7 is subdivided into a multiplicity of roller segments 4, 6 arranged next to one another, which in each case are mounted in the mounting unit 35 such that they can be displaced. As a consequence of this configuration an optimal adaptability of the pressure application roller unit 2 to a surface 82 of a molding tool 84 that is curved in one or two dimensions is provided. By this means the pressure application roller unit 2 can be guided by means of a robot arm 102, even over molding tool surfaces that are more highly spherically curved in some sections.

Abstract: In one aspect of the method for displaying an image on a screen of a cockpit of an aircraft, control means: control a first display on the screen of an image comprising a background; and then control a second display so that, in at least one zone of the image that is determined independently of the background, the background presents a non-zero second mean luminance that is less than a first mean luminance that it presented during the first display. In another aspect, the control means control the display on the screen of an image comprising a background in such a manner, that at least in a zone of the image that is determined independently of the background, the background presents non-zero mean luminance that is less than mean luminance of the remainder of the background.

Abstract: The invention in particular has as an object the control of execution of software commands of a data-processing system in an aircraft cockpit comprising means for allowing a user to call up these commands. For these purposes, the means making it possible to call up these commands initially are locked in order to block calls to software commands. At the time of reception of an information item for unlocking these means, they are unlocked and the software commands may be called up. The software commands may be called up via the call-up means only if these means are in an unlocked state.

Abstract: An aircraft nacelle includes, on its outside surface, at least one opening that is blocked by at least one movable part (16) that is kept in closed position by at least one locking mechanism that connects the movable part (16) to another part of the nacelle (16?), characterized in that it includes an anchoring point (32) on one of the two parts (16?) that are to be connected, and a detachable link (34) that is connected to a traction element (36) that is integral with the other part (16) that is to be connected.