Facc Ag

Fischer Gesellschaft Mbh

Fischer Advanced Composite Components Gesellschaft M.b.h.

Fischer Advanced Composite Components Ag

Facc Af

Fischer Advanced Composite Components Gesellschaft

Fisher Advanced Composite Components Ag

Walter Alfred Stephan

Hermann Filsegger

Josef Fischer

Erich Pamminger

Wolfgang Billinger

Roland Zeillinger

Andreas Maier

Johann Einböck

Richard Reinhold Lechner

Gerhard Reich

Josef Knauseder

Gerhard Mötenhuber

Helmuth Holler

Johann Einboeck

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.

Morphing control surface

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.

Control surface element

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.

Device for connecting movable parts with structural elements of airplanes or the like

Panel

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.

Track beam for the cowling of jet engines

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.

Method for producing a fire-retardant veneer, and corresponding fire-retardant veneer

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.

Device for introducing and distributing forces into or inside a luggage compartment

A suspension device for a lowerable luggage stowage compartment has at least one spring element for assisting the movement of the compartment into a closed position against the force of gravity, and at least one damping element for damping the movement of the compartment into an opened position. A weight detector detects the weight of the compartment, and at least one additional spring element can be actuated based on the detected weight of the compartment. A retention device is provided for fixing the additional spring element. The suspension device provides a compartment that is easy to handle and easy to close even when fully loaded.

Suspension device for lowerable luggage compartments

The invention relates to an overhead luggage container (), particularly for airlines, comprising a reinforcing structure () which is connected to the container () and which is disposed essentially in the direction of the longitudinal extension of the container (), and at least one device () for suspension on a carrying structure () of the plane. In order to create a container () which can be subjected to relatively high static strain without running the risk that the container () will fall on the passengers sitting below, while at the same time reducing technical complexity in production and reducing the weight of the container, at least one respective rigid connecting element () is arranged to the side of the container () between the reinforcing structure () and the suspension device () in a substantially vertical manner with respect to the longitudinal extension of the container (). The connecting element () is used to transmit forces exerted by the luggage on the container () and to deflect them to the suspension devices () and carrying structure () of the plane, thereby relieving the amount of strain placed on the side walls ().

Overhead luggage container, particularly for airplanes

A carrying or guiding device for aircraft components, in particular for landing flaps arranged on an aircraft wing, including a carrier having a substantially U-shaped section with substantially parallel side walls, and a cover plate arranged at the open side. To minimize weight, facilitate manufacture and mounting, and provide sufficient strength, the carrier and the cover plate are made of fiber reinforced plastic, in particular of carbon fiber (CF) reinforced plastic. The connection between the carrier and the cover plate and any possible connecting elements is preferably provided by gluing and, possibly, by additional rivet or screw connections.

Carrying or guiding device for aircraft components

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.

Pressure frame designed in particular for an aircraft

There is disclosed a spoiler for wings, in particular of planes, which spoiler is unfoldable during the landing and take-off of the plane or the like and retractable during cruising. In order to provide for enhanced aerodynamic conditions during landing and taking off without deteriorating the aerodynamic conditions during cruising, a structural member preferably made of a composite material and, in particular, carbon fiber reinforced plastic is arranged on the trailing edge of the spoiler, viewed in the direction opposite to the flight direction. The structural member, during landing or taking off, in the unfolded state of the spoiler with the landing flaps extended reduces the gap formed between the trailing edge of the spoiler and the surface of the landing flap and, during cruising, with the landing flap pulled in and the spoiler retracted abuts on the surface of the landing flap.

Spoiler for wings

The invention relates to a window unit W for aircraft cabins, comprising an outer window frame,an inner window frame,a window pane,lying between them, and possibly having a sun-visor,a roller blind,or the like arranged between the inner window frame,and a possible covering frame,the window unit W being insertable into the opening,in a side-wall panel,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,advantageously with locking devices, to detachably connect it to the side-wall panel,or to components connected thereto, the side-wall panel,or components connected thereto, having any necessary mating parts for the centering device for the snap fastenings,The centering device is advantageously arranged corresponding to a clock position of 6 o'clock, and two snap fastenings 13 are advantageously arranged on the circumference of the window unit (W) corresponding to a clock position of 10 and 2 o'clock.

Window unit for aircraft cabins

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. as a bolt, for additionally absorbing the forces which act essentially in the direction of the covering panel, and that each fastening element which is designed as a fixed bearing has means for tool-free locking and unlocking.

Device for releasably fastening covering panels

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. of the door 2 increases or as the rate at which the door 2 is opened reduces.

Growing community of inventors

St. Martin, Austria

Walter Alfred Stephan