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: 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: 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: A spiral wound gasket comprises an annulus constituted by a plurality of superposed turns of a profiled metal strip wound upon itself to form a spiral and, interposed between at least some of said superposed turns, a number of turns of a relatively soft sealant material in strip form, the width of said metal strip being selected so that prior to use the wound metal spiral is essentially flush with the surface of an associated guide ring and the width of the strip of relatively soft sealant material being selected so that prior to use, it projects a significant distance on both sides of the gasket from said superposed metal turns axially of said annulus. The preferred relatively soft sealant material is exfoliated graphite foil or a fluorocarbon resin, unsintered PTFE being particularly preferred. The sealant material preferably projects from the metal spiral to define an overall gasket thickness on the order of 25 to 40 percent greater than that of the guide ring.

Abstract: A spiral wound gasket comprises an annulus constituted by a plurality of superposed turns of a profiled metal strip wound upon itself to form a spiral and, interposed between at least some of said superposed turns, a number of turns of a relatively soft sealant material in strip form, the thickness of said metal strip being selected so that prior to use the wound metal spiral is essentially flush with the surface of an associated guide ring and the thickness of the strip of relatively soft sealant material being selected so that prior to use, it projects a significant distance on both sides of the gasket from said superposed metal turns axially of said annulus. The preferred relatively soft sealant material is exfoliated graphite foil, which projects from the metal spiral to define an overall gasket thickness on the order of 25 to 40% greater than that of the guide ring.

Abstract: A system for supplying air to the interior of a shoe, particularly of a skiing boot for Alpine skiing is disclosed. The shoe or skiing boot comprises a shell and a gaiter, which is pivoted to the shell and pivotally movable in the longitudinal direction of the shoe. An air-handling device is mounted on the shell of the shoe and is connected to actuating means. The latter is also connected to the gaiter and during a forward and rearward pivotal movement of the gaiter move up and down to impart a pumping motion to the air-handling device so that air is pumped into the interior of the shoe. The air inlet is preferably disposed near the sole of the shoe.

Abstract: At least one plastic sheeting element which is oriented at least monoaxially and at least in part in a direction which differs appreciably from the longitudinal direction of the sheeting element is twisted to form a string for a ball-striking implement.