Abstract: Folding table, in particular for an aircraft, with a frame preferably to be installed in an armrest or in a side-panelling in the aircraft, with a support device for a table top, with a displacement device for displacing the support device along the frame from a stowed position to a deployed position, with a folding device for folding a support element of the support device from the deployed position to a use position, and with a drive device for assisting the displacement device in displacing the support device from the stowed position to the deployed position, wherein the drive device comprises a linear drive element which is connected to the displacement device via a cable pull device.

Abstract: An annulus filler, mounted to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, is disclosed. The annulus filler, formed from a polymer matrix composite material, includes an outer lid, defining an airflow surface for air drawn through the engine in an axial airflow direction, and a support structure, connectable to the rotor disc, to support the rear of the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. Under centrifugal loads, the opposing support walls resiliently deform. Each support wall has a concave rear edge. Each rear edge has a first curved section, a second curved section and a substantially straight section therebetween.

Abstract: A device for opening an aircraft door, comprising: a support arm arranged between the aircraft fuselage and the aircraft door; an opening system for opening the aircraft door; a support arm cover covering the support arm in the closed position of the aircraft door, the support arm cover having a cover element, and a flap element which swivels between being flush with the cover element, and a state in which the flap element overlaps the cover element; and a guide system for guiding the flap element, wherein the guide system has at least one guide arm, one end of which is joined in an articulated manner to the support arm, and the other end of which is joined to at least one guide element, which guide element can be guided along a guide track on the inner side of the flap element, when the aircraft door is opened.

Abstract: A frame for reinforcing a hull of a craft, particularly an aircraft, contains at least one frame element that is shaped in accordance with the curvature of the hull and has recesses at a side facing the hull for the passage of longitudinal beams of the craft. Each frame element is integrally formed from a fiber-reinforced plastic composite material and the recesses are configured as integral cut-outs of each frame element.

Abstract: A decompression unit is suitable for use in a decompression opening of a wall element of an aircraft. The unit includes a panel which can be mounted via a frame in or over the decompression opening. The panel can be moved out of the frame at a predetermined differential pressure ?p in order to open the decompression opening. In order to form a decompression unit of as simple a design as possible and with an optimum response behavior, the panel is formed by at least one hardened prepreg layer with at least one separating joint that is filled with cured resin as a predetermined breaking point. The separating joint breaks when the predetermined differential pressure is exceeded.

Abstract: A method using a tool for producing a fiber composite component includes a planar fiber lay-up placed on a carrier mold, provided with a stiffening section protruding from the lay-up and pressed between parts of a molding tool. A chamber sealed from the mold is formed by an air-tight film enclosing the tool, the lay-up and the stiffening section. The chamber is connected to a resin supply line and a vacuum line. Resin is aspirated by negative pressure applied to the vacuum line, and the lay-up and the stiffening section are saturated by resin to form the fiber composite component. Air and resin are drawn between the parts of the tool, through the stiffening section and into a suction channel extending in the tool and connected to the vacuum line through a suction opening of the tool, for conducting air and/or resin.

Abstract: A device fixes fittings, in particular wall or floor elements in airplanes, to a structure such that no vibrations are generated. The device has a fixing element which is configured on one end for fixing to the structure and on the opposite end for receiving the fittings. The opposite end of the fixing element is movably mounted in a spacer sleeve which can be connected to the fittings to be received and which contains an elongated hole-shaped cross-section, and the opposite end is configured for fixing to the fittings. At least one damping element is provided and disposed between the structure and the fittings. The spacer sleeve has an elongated hole-shaped cross-section, and the one end of the fixing element is formed by a stand or can be connected to a stand. The stand is configured for movably mounting in a rail section that lies on the structure.

Abstract: A concealed 180° hinge for the movable connection of two parts between a collapsed state and a fully opened-out state of the parts has at least two U-shaped pivoting brackets. The hinge, which has the highest possible strength and also allows the two parts to be moved in relation to one another without any risk of collision, includes rotary pins of the two pivoting brackets on the one hinge part that are arranged in a plane substantially parallel to the plane of the part, which can be connected to this one hinge part. The rotary pins of the two pivoting brackets on the second hinge part are disposed in a plane located substantially perpendicularly to the plane of the part, which can be connected to this second hinge part.

Abstract: A ceiling panel for lining the interior of a vehicle, particularly an airplane, includes a plastic composite element having elements disposed at lateral edges extending substantially in a movement direction of the vehicle for fastening to a supporting structure of the vehicle or parts connected thereto. At least one fixation device is provided on a transverse edge disposed substantially transversely to the movement direction and at least one counter piece is provided on an opposite transverse edge, as viewed in the movement direction, to avoid an offset in a perpendicular direction between consecutive ceiling panels. The at least one fixation device is configured to complement the at least one counter piece and a form-locking connection can be produced and detached again without tools in the substantially perpendicular direction, by the interaction of each fixation device with a respective counter piece.

Abstract: A method using a tool for producing a fiber composite component includes a planar fiber lay-up placed on a carrier mold, provided with a stiffening section protruding from the lay-up and pressed between parts of a molding tool. A chamber sealed from the mold is formed by an air-tight film enclosing the tool, the lay-up and the stiffening section. The chamber is connected to a resin supply line and a vacuum line. Resin is aspirated by negative pressure applied to the vacuum line, and the lay-up and the stiffening section are saturated by resin to form the fiber composite component. Air and resin are drawn between the parts of the tool, through the stiffening section and into a suction channel extending in the tool and connected to the vacuum line through a suction opening of the tool, for conducting air and/or resin.

Abstract: A decompression unit is suitable for use in a decompression opening of a wall element of an aircraft. The unit includes a panel which can be mounted via a frame in or over the decompression opening. The panel can be moved out of the frame at a predetermined differential pressure ?p in order to open the decompression opening. In order to form a decompression unit of as simple a design as possible and with an optimum response behavior, the panel is formed by at least one hardened prepreg layer with at least one separating joint that is filled with cured resin as a predetermined breaking point. The separating joint breaks when the predetermined differential pressure is exceeded.

Abstract: A device fixes fittings, in particular wall or floor elements in airplanes, to a structure such that no vibrations are generated. The device has a fixing element which is configured on one end for fixing to the structure and on the opposite end for receiving the fittings. The opposite end of the fixing element is movably mounted in a spacer sleeve which can be connected to the fittings to be received and which contains an elongated hole-shaped cross-section, and the opposite end is configured for fixing to the fittings. At least one damping element is provided and disposed between the structure and the fittings. The spacer sleeve has an elongated hole-shaped cross-section, and the one end of the fixing element is formed by a stand or can be connected to a stand. The stand is configured for movably mounting in a rail section that lies on the structure.

Abstract: A concealed 180° hinge for the movable connection of two parts between a collapsed state and a fully opened-out state of the parts has at least two U-shaped pivoting brackets. The hinge, which has the highest possible strength and also allows the two parts to be moved in relation to one another without any risk of collision, includes rotary pins of the two pivoting brackets on the one hinge part that are arranged in a plane substantially parallel to the plane of the part, which can be connected to this one hinge part. The rotary pins of the two pivoting brackets on the second hinge part are disposed in a plane located substantially perpendicularly to the plane of the part, which can be connected to this second hinge part.

Abstract: The invention relates to a guide-vane arrangement (1) for deviating the flow present in the by-pass flow channel (2) of an engine (3), said arrangement comprising an outer ring (4) and an inner ring (5) and guide vanes (6) arranged therebetween in a substantially radial manner, wherein the outer ring (4) has elements (7) for connecting to an outer engine structure (8), and the inner ring (5) has elements (9) for connecting to an inner engine structure (10), with a plurality of segments (11) being provided.

Abstract: Track beams for the cowling of a jet engine for aircraft are formed of a base body with at least one slide for displaceably mounting a thrust reverser of the jet engine. A connection is provided for an inner engine cowling and fittings for detachably and pivotally attaching to a supporting structure or for connecting to another track beam. To provide such a track beam which has a particularly low weight yet, nevertheless, is sufficiently stiff, the base body is formed by a hollow profile section with a substantially closed cross-section. The hollow section is produced of a carbon-fiber-reinforced synthetic material by way of a resin-infusion process. Two flanges are provided on the hollow section of the base body of the track beam for providing a connection to the inner engine cowling.

Abstract: A frame for reinforcing a hull of a craft, particularly an aircraft, contains at least one frame element that is shaped in accordance with the curvature of the hull and has recesses at a side facing the hull for the passage of longitudinal beams of the craft. Each frame element is integrally formed from a fiber-reinforced plastic composite material and the recesses are configured as integral cut-outs of each frame element.

Abstract: A modular aircraft window includes an outer pane and an inner pane each inserted in a substantially rectangular frame. A foldable shade is disposed on one of the frames and has a freely movable end that is coupled with an operating unit for opening and closing the shade. The assembly further includes at least one shade raising and lowering mechanism in one or both of the longitudinal parts of the frame and a drive mechanism mounted in the lower transverse part of the frame. The drive mechanism includes a threaded spindle which, in order to provide for a particularly stable and long-lasting construction of the drive mechanism, is movable solely translationally and is coupled with a transmission mechanism operating the at least one raising and lowering mechanism.