Abstract: The invention relates to an aerodynamic profiled body for an aircraft, in particular a winglet, comprising a front profiled element having a profile front edge, a rear profiled element having a profile rear edge, and an adjusting unit, which connects the front profiled element to the rear profiled element and by means of which the rear profiled element can be moved in relation to the front profiled element, wherein the adjusting unit has a front mounting device connected to the front profiled element, a rear mounting device connected to the rear profiled element, and a force-transmitting device, which connects the front mounting device and the rear mounting device to each other.

Abstract: A control surface element for an aircraft, more particularly a spoiler, comprising an upper outer skin element that has an outer air flow face; comprising a lower outer skin element; comprising at least one reinforcement rib; and comprising a core element made of a foam material; wherein the reinforcement rib is positioned between two core segments of the core element.

Abstract: The invention relates to an aerodynamic profiled body for an aircraft, in particular a winglet, comprising a front profiled element having a profile front edge, a rear profiled element having a profile rear edge, and an adjusting unit, which connects the front profiled element to the rear profiled element and by means of which the rear profiled element can be moved in relation to the front profiled element, wherein the adjusting unit has a front mounting device connected to the front profiled element, a rear mounting device connected to the rear profiled element, and a force-transmitting device, which connects the front mounting device and the rear mounting device to each other.

Abstract: A control surface element for an aircraft, more particularly a spoiler, comprising an upper outer skin element that has an outer air flow face; comprising a lower outer skin element; comprising at least one reinforcement rib; and comprising a core element made of a foam material; wherein the reinforcement rib is positioned between two core segments of the core element.

Abstract: A device for connecting movable parts with structural components of airplanes or other high-speed vehicles, including at least one fitting provided with at least one bearing. In order to provide such a device exhibiting low thermal stresses, a low weight, a high bearing capacity and a producibility as simple as possible, it is provided that the at least one fitting is made of a synthetic material and glued with the movable part. The resin transfer molding (RTM)-method is particularly suitable to produce the fitting.

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: For producing a fire-resistant veneer or material composite having different core materials without adding salts or other commercial fire-retardant materials, liquid is drawn out from the pores of the veneer by heat treatment and is replaced by resin, and the veneer is, if required, subjected to a refining process.

Abstract: A device for introducing forces into a luggage compartment and for transferring and/or distributing the forces and/or stresses in vehicles, particularly in fast traveling vehicles such as aircraft, ground vehicles and watercraft, e.g. express trains, speedboats and the like, has a ceiling-side connecting element arranged between extensions of end-side side walls of the luggage compartment. The device has a simple design and can be economically produced. The invention provides for the introduction of the forces into the luggage compartment via the ceiling-side connecting element, configured, for example, as a strip that distributes forces for stresses.

Abstract: The invention relates to a device for introducing forces into a luggage compartment (1) and for transferring and/or distributing the forces and/or stresses in vehicles, particularly in fast-traveling vehicles such as aircraft, ground vehicles and watercraft, e.g. express trains, speedboats and the like. In order to create a device of this type, which has the most simple possible design and can be economically produced, the invention provides that the introduction of forces into the luggage compartment ensues via a ceiling-side connecting element, for example, provided in the form of a strip (8) that distributes forces or stresses.

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: For producing a fire-resistant veneer or material composite having different core materials (4) without adding salts or other commercial fire-retardant materials, according to the invention liquid is drawn out from the pores of the veneer (1) by heat treatment and is replaced by resin, and the veneer is, if required, subjected to a refining process.

Abstract: The invention relates to a method for testing the impermeability of components (1) that contain cavities (7). On at least one side of the component (1) to be tested, at least the surface to be tested is completely wetted with a foam-producing testing liquid (11). The aim of the invention is to create a method that can be carried out as quickly and easily as possible, during which the component (1) to be tested is influenced as little as possible by the testing liquid (11). To this end, the component (1) is subjected to an increase in temperature, and the surface of the component (1) to be tested is subsequently examined with regard to the formation of bubbles (12) in the testing liquid (11). The testing liquid (11) preferably consists of 10 to 20% dissolved surfactants, 2 to 6% alcohol, and 75 to 78% water and a maximum of 5% auxiliary agents.

Abstract: The invention relates to a carrying or guiding device (1), respectively, for aircraft components, in particular for landing flaps arranged on an aircraft wing, comprising a carrier (2) of a substantially U-shaped section and with substantially parallel side walls (3, 4). To provide such a device which has as low a weight as possible and, moreover, has the required strength properties and is as easy to produce and mount as possible, it is provided that the carrier (2) as well as preferably a cover plate (20) arranged at the open side of the carrier (2) is made of fiber reinforced plastic, in particular of carbon fiber (CF) reinforced plastic. The connection between the carrier (2) and the cover plate (20) and any possible connecting elements (21) is preferably provided by gluing and, possibly, by additional rivet or screw connections.

Abstract: The invention relates to an overhead luggage container (1), particularly for airlines, comprising a reinforcing structure (11) which is connected to the container (1) and which is disposed essentially in the direction of the longitudinal extension of the container (1), and at least one device (5) for suspension on a carrying structure (2) of the plane or like. In order to create a container (1) which can be subjected to relatively high static strain without running the risk that the container (1) will fall on the passengers sitting below, while at the same time reducing technical complexity in production and reducing the weight of said container, at least one respective rigid connecting element (17) is arranged to the side of the container (1) between the reinforcing structure (11) and the suspension device (5) in a substantially vertical manner with respect to the longitudinal extension of the container (1).

Abstract: There is disclosed a device for connecting movable parts with structural components of airplanes or the like, including at least one fitting provided with at least one bearing. In order provide such a device exhibiting low thermal stresses, a low weight, a high bearing capacity and a producibility as simple as possible, it is provided that the at least one fitting is made of a synthetic material and glued with the movable part. The resin transfer molding (RTM)-method is particularly suitable to produce the fitting.

Abstract: A pressure frame, designed in particular for an aircraft, including a dome-shaped cover made of composite materials reinforced with fibers, preferably in one single piece, and cover reinforcing devices connected to the cover or produced integrally therewith. To reduce weight and cost while still fulfilling strain requirements, particularly of large aircraft, and to reduce the risk of destruction due to the cover being turned inside out towards the inside of the aircraft, the cover is of essentially uniform thickness and includes at least one cover reinforcing device which is mounted in the central area on the concave side of the cover. Advantageously, this cover reinforcing device in the central area is formed by a reinforcing structure oriented against the curvature of the cover, such as at truncated cone-shaped, mug-shaped or parabolic structure, with a cavity being arranged between the cover and the reinforcing structure.

Abstract: The invention relates to a window unit W for aircraft cabins, comprising an outer window frame 1, an inner window frame 3, a window pane 2 lying between them, and possibly having a sun-visor 4, a roller blind 34 or the like arranged between the inner window frame 3 and a possible covering frame 5, the window unit W being insertable into the opening 7 in a side-wall panel 6 or the like in the aircraft cabin. In order to make it possible for the window unit W to be rapidly and simply installed and removed, the invention makes provision for the window unit W to have a centering device and at least two snap fastenings 13, advantageously with locking devices, to detachably connect it to the side-wall panel 6, or to components connected thereto, the side-wall panel 6, or components connected thereto, having any necessary mating parts for the centering device for the snap fastenings 13.

Abstract: A device for releasably fastening covering panels, in particular ceiling panels in aircraft, on a load-bearing structure, having at least two fastening elements. In order to make it possible for the covering panels to be removed and fastened quickly and easily without the aid of tools, and for loose constituent parts to be avoided, it is provided that all the constituent parts of the fastening elements are connected either to the covering panel and/or to the load-bearing structure, and that all those constituent parts of the fastening elements which are connected to the covering panel are arranged exclusively on that side of the covering panel which is directed toward the load-bearing structure, and that at least one fastening element is designed as a movable bearing, e.g. as a bolt, for absorbing the forces which act essentially perpendicularly with respect to the covering panel, and at least one fastening element is designed as a fixed bearing, e.g.

Abstract: In order to provide a container 1 having a door 2, in particular a luggage compartment for aircraft, the door 2 being mounted via at least one hinge or the like on the container 1 such that it can pivot, having an apparatus for assisting the movement of the door 2 into the open position and for holding the door 2 in the open position, and having an apparatus for holding the door 2 in the closed position, in the case of which container the structural components have as small a physical size as possible and thus occupy as little volume in the container 1 as possible. It is provided that the apparatus for assisting the movement of the door 2 and, possibly, an apparatus for damping the movement of the door 2 are arranged essentially around the pivoting axis of the door 2. The components relating to this are ideally integrated in the or each hinge. The damping of the movement of the door 2 advantageously reduces as the opening angle .alpha.