Abstract: A process for producing fiber preforms for composite material components makes it possible to directly produce complex geometries in a flexible and low-cost manner by applying a plurality of dry fiber rovings independently of one another even in spatially uneven contours. It is no longer necessary to use cut fabric strips since fiber preforms are produced straight from the dry fiber rovings. This obviates the need to carry out production, transport and order picking processes. It is not necessary to cut fiber strips to size, and therefore a saving may be made on material. In addition, it is possible to increase the mechanical characteristic values in the composite material because it is not necessary to sew fiber webs. The described process can also readily be scaled since the number of dry fiber rovings arranged next to one another make it possible to vary the area which can be covered.

Abstract: Disclosed is a method for producing single- or multi-layered fiber preforms by the TFP process with fiber strands which are aligned in particular such that they are oriented with the flux of force, wherein the fiber preforms have virtually any desired material thickness without troublesome backing layers and have virtually any desired surface geometry, comprising the steps of: laying and attaching the fiber strands on a flexible and elastic base, in particular a base formed by an elastomer, with a fixing thread led through a sewing head to form the fiber perform; and lifting the fiber preform off the elastic and flexible base.

Abstract: In the case of a structural component of an aircraft or spacecraft comprising a fuselage portion connection region for connecting to an associated fuselage portion and having a thermal expansion coefficient which is approximately matched to the associated fuselage portion; an inner connection region for connecting to an associated installation element and having a thermal expansion coefficient which is approximately matched to the associated installation element; and a separation region for connecting the fuselage portion connection region and the inner connection region, at least one of the regions has a high heat conduction resistance.

Abstract: In the retracted position, aircraft landing gear of an aircraft is supported by an uplock hook. The deployment of the aircraft landing gear includes the steps of supporting at least part of the weight of the landing gear by a releasable catch in the form of an uplock hook, applying a lifting force to the landing gear to remove at least part of the load sustained by the releasable catch, releasing the catch and effecting the downward movement of the landing gear to the deployed position.

Abstract: The present invention relates to a method for producing a chemical conversion layer on a metal surface, comprising the following method steps: (i) providing at least one cloth having a defined area, which is resistant at least in the pH range from 2 to 7 and is tear-proof in the wet state, (ii) bringing the cloth into contact with a liquid, which contains at least one active component for the formation of the chemical conversion layer, so that the cloth is impregnated with the liquid, (iii), applying the cloth impregnated with the liquid to a metal surface, and (iv) removing the cloth from the metal surface at a moment at which the cloth is still at least damp.

Abstract: A vacuum toilet and a method for operating a vacuum toilet, wherein generating negative pressure to remove solids by suction is also used for generating a desired flushing medium flow. To this effect, if necessary, guiding devices are used which influence a flow upstream of a nozzle outlet and downstream of a nozzle outlet such that flow optimization of the flushing medium can be carried out.

Abstract: A device for mounting at least one connector in an aircraft fuselage includes a first and a second traverse configured to connect the device to a structural section of the aircraft fuselage at end sections of the first and second traverses. A frame element extends transversely between the first and the second traverses and is configured to accommodate the at least one connector. A first and a second connecting profile respectively connect the frame element to the first and second traverse.

Abstract: An aircraft jet engine with a longitudinal axis, including a wall enclosing a gas flow ejected from a downstream end of the wall in the longitudinal axis, plural ducts being distributed around the periphery of the downstream end of the wall each including a terminal section, including an outlet opening. Each duct can eject a fluid jet through the outlet opening thereof. The ducts are configured to eject the fluid jets essentially parallel to each other, each fluid jet ejected through the corresponding outlet opening forming a lateral angle with the longitudinal axis in a projection view in a plane with the longitudinal axis.

Abstract: A method for manufacturing welded lap joints comprising the following steps: Providing of two components each having at least one base; allocating the components in such a way that the bases face each other and the components overlap in an overlapping area, which extends at least partially over both components; joining the components by welding in the overlapping area such that a weld joint is formed, wherein at the edge of the overlapping area non welded areas are formed; removing of the non welded areas whereby outer cutting areas are formed at the components, which are arranged at obtuse angles to the overlapping area.

Abstract: A wing box rib, joining an aircraft wing to the wing box and to the rest of the structure, extends advantageously over an adjacent part of the fuselage, having in particular an upper line situated above a junction line of the wing upper surface panel. The connection is simplified, as is the structure of the aircraft and its manufacture, a lightening is possible, and the transmission of stresses takes place in a more favorable manner.

Abstract: A measurement method for determining the position of an omega profile component placed on a shell component of an aircraft, in which the ACTUAL position of the omega profile component relative to the shell component is optically acquired in a contactless manner, so as to subsequently compare the latter with a defined DESIRED position, wherein several adjacently spaced apart measuring points are established at two mutually opposing flank sides of the profile cross section of the omega profile component, through which a regression line is run according to the path measurement principle based on coordinates, whose point of intersection is drawn upon to determine the orthogonal position of the omega profile component relative to the shell component.

Abstract: The invention provides an aircraft with a ventral fairing able to store equipment and systems in lateral zones. The ventral fairing (20) comprises a first zone of length L1 along the X-axis, where the area of the cross-section perpendicular to the X-axis increases in the direction of the air flow and a second zone of length L2, where the area of the cross-section perpendicular to the X-axis decreases in the direction of the air flow, being L1>L2 and being placed the rear end of said first zone behind the intersection of the trailing edge of the wing (15) with the fuselage (13).

Abstract: A linking device including two hinge pins and having flexibility allowing vibrations between these two shafts to be filtered. The device includes a stack of plates connected to one another by layers of elastomer material. Plates of a first type are coupled to one of the shafts in relation to the movements parallel to the plates, while the plates of a second type are coupled to the other shaft in relation to the movements parallel to the plates, so as to allow relative movement of the shafts parallel to the plates. This linking device may be used in particular as a connecting rod, spreader beam or three-point shackle used in connecting a turbine engine to a pylon in a propulsion system of an aircraft such as an airplane.

Abstract: An engine mounting structure for aircraft including an engine mounting system including a device for transmission of the thrust efforts fitted with two lateral connecting rods and with a spreader beam mounted in connected fashion on a support element, through a principal connecting device defining a principal spreader beam hinge line positioned in a plane. The spreader beam is also mounted in connected fashion with some play on the element, using a secondary connecting device located at some distance, as seen from above, from the device, and defining a secondary spreader beam hinge line, which is also positioned in a plane. The rotation of the spreader beam is stopped by device coming into contact with the spreader beam.

Abstract: The subject matter herein discloses a method for producing a fuselage section of an aircraft via large-sized, in particular long, shell segments. The method includes joining at least two skin segments to form a large-sized skin field, welding a plurality of integral stringers onto the skin field, and welding a plurality of integral and closed ring frames to the skin field.

Abstract: A high-energy density beam welding process for two panels includes a step that include placing a metal band on the upper face of at least one panel, in the axis of the desired welded joint before welding the panels, so that the metal band is inserted between the panels and the high-energy density beam during the welding step, and so that the thickness of this metal band integrates all of the geometric faults present on the surface of the welded joint.

Abstract: A display system in a flight deck includes at least one screen adapted for displaying several different applications and at least one cursor associated with the applications, an interaction device includes means for activation of the cursor configurable automatically according to the application displayed, and the interaction device includes a touch-sensitive screen adapted for displaying a visual representation of a control panel of a real physical system of the flight-deck.

Abstract: A locking fastening device for fastening a first component to a second component, an adjustable fastening device for adjustably fastening a first component to a second component, and a component system including at least one first component that is fastened to a second component are described. Also described are a main wing of a wind tunnel model aircraft having an adjusting and fastening system which includes at least one locking fastening device and at least two adjustable fastening devices for adjusting and fastening an aerodynamic additional body that is adjustable relative to the main wing by means of a plurality of retaining devices, as well as a wind tunnel model aircraft having such a main wing.

Abstract: In accordance with the method, an inside layer of a fuselage section skin made from first fibers is placed on a manufacturing surface, the first fibers being placed in one or more first fiber directions. On the inside layer, a stiffening structure is formed from stiffening fibers, the stiffening fibers being placed in one or more stiffening fiber directions. An outside layer of the fuselage section skin, comprising fourth fibers, is placed on the stiffening structure formed from stiffening fibers, the fourth fibers being placed in one or more fourth fiber directions. The stiffening structure is designed and developed in such a way that the fuselage section does not require an additional stiffening structure, is connected with the fuselage section skin, and comprises the inside layer, the stiffening structure, and the outside layer; in particular, an additional stiffening structure in the form of stringers and frames is not required.

Abstract: A silencer for an auxiliary power unit of an aircraft comprises an inlet, an outlet, a housing and a flow channel with a porous wall material that is arranged in the housing. An intermediate space is formed between the housing and the flow channel and divided into outer cells that are arranged around the flow channel by means of one or more partitions. This makes it possible to realize a very compact silencer with very good sound insulation properties. The sound dampening can be additionally improved by dividing the outer cells into outer regions and inner regions, by adapting the shape of the silencer to a tail section of an aircraft and by arranging an annular channel on the outlet.