Abstract: To reduce sound emission and at the same time improve stability, a multilayer board for acoustic insulation is proposed that includes, but is not limited to a core sheet arranged between a first and a second covering layer. At least one of the two covering layers is of a closed design. The core sheet is firmly connected in a planar fashion to the covering layers. The core sheet comprises slits that extend within the core sheet in the direction of the core sheet thickness, which slits reduce the shear stiffness of the board and thus ensure an improved acoustic insulation effect. On both sides the core sheet comprises continuous edge zones, which extend parallel to the covering layers. An aircraft can have an interior lining formed by panels that comprise the multilayer boards in order to provide acoustic insulation.

Abstract: A method for process management in a collaborative service-oriented workshop for processing objects associated with data representing real data or processes, each object including a structure for storing links to other objects. After determining at least one function and at least one piece of information enabling the execution of the at least one function, an object including at least one reference to the at least one function and the at least one piece of information is created.

Abstract: Disclosed is a vertical rudder control system for an aircraft. The system is comprised of a rudder trim compensation generator that is configured to generate a rudder trim compensation order to set the position of the rudder bar of the aircraft to a neutral position in which the rudder bar is controlled with nil (i.e., zero) pilot effort. The vertical rudder control system includes a flight control calculator for calculating rudder control orders to maintain the nil effort rudder bar position, with the calculation of the rudder control orders being based on a sum of the rudder bar position, determined by a detection unit, and the rudder trim compensation order. The rudder control orders are received by a rudder operating unit, which is used to deflect the vertical rudder by a deflection value based on the rudder control orders.

Abstract: The invention relates to a sensor network in an aircraft, which comprises several sensor nodes that communicate with a central data collection and evaluation unit via a radio transmission path. Data transmission can take place in various ways. For example, different frequency ranges are provided, from which the respective frequency range enabling the best data transmission quality is selected.

Abstract: A connection switching device for an aircraft network includes a switching network and a second identification device. The switching network connects input/output devices, such that applications may be interconnected or such that an application may be connected to a peripheral device. The second identification device detects an input/output device that is connected to the connection switching device.

Abstract: An airplane fire extinguishing system comprises an extinguishing agent storage unit with an activatable closing device, which makes possible, when active, an outflow of extinguishing agent from the extinguishing agent storage unit, and a supply line, connected with the closing device and an outlet opening, via which the extinguishing agent can be conducted from the extinguishing agent storage unit to the outlet opening, in order to eject it there for firefighting, wherein one or more sensor systems are present, by means of which a current airplane state can be determined, and a control unit, connected with the closing device and an actuatable input element, is present, via which the closing device can be activated, the control unit constructed and configured in such a way that the closing device is activated, as a function of the current airplane state, which exists at the time of an actuation of the input element.

Abstract: A device for the production of a part of an aircraft made of composite material of which one surface is able to be in contact with aerodynamic flows includes a male mold, and at least two smoothing panels (12) that can exert pressure on the piece to be produced during a polymerization phase during which a contraction phenomenon appears. At least one of the two smoothing panels (12.1, 12.2) includes a smooth edge with a beveled shape against which at least one surface of the other smoothing panel can slide to compensate for the contraction phenomenon.

Abstract: A fuel cell system having an apparatus for gas drying that includes, but is not limited to at least one cooling element with at least one first surface and at least one detachment device. The cooling element is designed to be thermally connected to a heat sink and to come into contact with gas flowing past. The detachment device is movably held relative to the first surface and is designed to detach frozen water from the first surface.

Abstract: Method for automatically reloading software characterized in that it comprises: a step of detecting corruption (E101) of at least one part of a software package of an on-board programmable device (10-1, 10-2, 10-n); and, in response to signaling, a step of reloading (E103) a non-corrupt version of the said at least one corrupt part of the software in order to replace the said at least one corrupt part of the software.

Abstract: A structural element for reinforcing a fuselage cell of an aircraft is provided. The structural element comprises a reinforcement profile which is made in one piece from a metallic material. The profile is provided with a strap at least in regions. As a result of the strap which is made of a fiber-reinforced layer material or fiber metal laminate and is adhesively bonded, at least in regions, to a flange of the reinforcement profile the structural element has high damage tolerance and advantageous fatigue properties. The fiber metal laminate or layer material is made of a plurality of metal layers and fiber-reinforced plastics material layers which are stacked in alternating fashion and adhesively bonded to one another over the entire surface. The reinforcement profile and the strap are joined by means of a joining layer. Said joining layer is preferably constructed from two prepreg layers and a non-fiber-reinforced adhesive layer.

Abstract: The present disclosure relates to a wall component for an aircraft for forming an outer wall comprising at least one first wall element, at least one second wall element and at least one connecting device for connecting the first wall element to the second wall element. On wall regions that are to be directed towards each other, the first and the second wall element comprise connecting regions. Furthermore, a joint element is provided, which comprises a joint region with a joint region surface that is to be arranged towards the outside of the aircraft, wherein the joint region is designed to be received with a matching fit into a recess formed by the connecting regions of the wall elements, and wherein the joint region surface, when the joint element is inserted, is flush with the outer surfaces of the wall elements.

Abstract: A climate tube, in particular for aircraft, includes an inner layer and an outer layer of fiber composite plastic material. To achieve a high stiffness combined with a low weight and to achieve good thermal insulation properties, disposed between the inner layer and the outer layer is an at least almost completely circumferential honeycomb core, which is firmly connected to the inner layer the outer layer. The radial extent of the honeycomb core is large compared to the radial extent of the inner layer and the outer layer, and the mutually opposed longitudinal ends of the honeycomb core abut one another and are surrounded by a ply of fiber composite plastic material.

Abstract: A gas turbine engine, especially a turbojet or turbofan for an aircraft, includes a combustion section and an exhaust section produces an exhaust gas. The emission products can be reduced by using a gas treatment device with a reactor and an injection device. The reactor produces a nitrogeneous substance such as ammonia. This reducing agent is injected in the gas phase in the exhaust section of the gas turbine engine. By selective non catalytic reaction the Nitrogen oxides of the exhaust gas can be reduced. Furthermore the injection device is arranged such that the temperature window of this reduction process is ranging from 850° C. to 1100° C. The reactor for producing gaseous ammonia can either be a thermal reactor or a high pressure plasma device.

Abstract: Disclosed is a method for placing fiber-reinforced, pre-impregnated, planar semi-finished products on a placement tool for the manufacture of a non-crimp fabric, wherein a placement film is clamped on the placement tool for purposes of holding the non-crimp fabric, and by means of evacuation and/or the application of pressure is fixed in position on the placement tool and/or can be released from the latter. Also disclosed is a placement tool for the execution of such a method.

Abstract: A fresh air inlet for an aircraft features a ram air inlet with a ram air inlet opening, a secondary air inlet opening separate from the ram air inlet and a movably mounted flap. The flap can be moved into a first or second position, and essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and extends away from the aircraft body in the second position to shield the ram air inlet opening from foreign matter in the air. The secondary air inlet reduces the pressure loss of the air inlet on the ground or during flight phases with relatively slow speed due to the enlarged cross-sectional surface. The ram air inlet can be optimized for cruising phases, and the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced.

Abstract: A method for communicating data in an aircraft between at least a first data processing system and a second data processing system locally networked, each processing system being capable of executing at least one application, wherein the data to be exchanged are organized in messages, the aforementioned messages as well as the processing systems and the applications being defined in files stored in a backup unit connected to the network and accessible by the data processing systems.

Abstract: A structural rod has a primary rod that has an axial cavity and a secondary rod inside the axial cavity so that the secondary rod is able to move inside the axial cavity along the direction of the longitudinal axis of the rod. The primary rod has a bearing for fastening the structural rod at the first end in a rigid manner and is not fastened rigidly to the structure at the second end. Conversely, the secondary rod has a bearing for fastening the structural rod at the second end in a rigid manner and is not fastened rigidly to the structure at the first end. The primary and secondary rods are joined through one or more intermediate linkage elements made of a deformable and elastic material.

Abstract: The present invention provides a method and a system for determining forces which act on a body with a controlled volume which is provided inside the flow tunnel and in which the body is arranged. A first measuring means is used to measure a pressure distribution for each surface defining the controlled volume. A second measuring means measures a velocity field for each defining surface of the controlled volume. Furthermore, a calculation unit is provided for calculating the forces acting on the body as a function of the pressure distributions and velocity fields measured for the defining surfaces of the controlled volume.

Abstract: A frame of an aircraft fuselage structure made from composite material, which includes a skin and several stringers fixed on the skin. The frame includes a profile elongated in a longitudinal direction which is hollow over at least a portion of its length. The profile is mounted on two legs. Each leg, intended to be fixed on the skin, includes a first portion extending continuously over the whole length of the profile and a second portion extending from this continuous portion so as to form several openings spaced apart in the longitudinal direction of the profile, in each of which a stringer passes. The presence of the hollow profile in the frame and the structure of the legs makes it possible to dispense with clips and cleats.