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: 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.

Abstract: 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.

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: 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.