Abstract: The invention relates to a method for joining at least two aircraft fuselage segments (2, 3) by friction stir welding with a tool (8) generating friction heat for the partial plasticisation of an edge region (6, 7) of at least one of the two aircraft fuselage segments and a counter bearing (10) for absorbing the force exerted by the tool (8) on at least one of the two aircraft fuselage segments, wherein at least one of the two aircraft fuselage segments comprises at least one rib (17) and/or one stringer (16). In order to minimise the necessary expense incurred in association with the production aids for the FSW process, it is proposed that the at least one rib (17) and/or the at least one stringer (16) of the at least one aircraft fuselage segment (2, 3) should be used as a counter bearing (10).

Abstract: The invention relates to a hydro sound damper, in particular for integration in an aircraft hydraulic system, with a throughout inner tube, wherein the inner tube comprises a perforation section which is coaxially encompassed by a housing under formation of a gas-filled cavity. The perforation section is coaxially encompassed by a metal felt cylinder at least in sections and an elastomeric membrane bears on the metal felt cylinder for generating a gas cushion, which is closed in itself. Due to the metal felt cylinder a pushing through of the elastomeric membrane into the bores of the perforation section is avoided when the hydraulic system is depressurized. Furthermore, the metal felt cylinder, which is infiltrated respectively flowed through, produces an improved damping characteristic which might moreover be adjusted by a variation of the flow resistance of the used metal felt.

Abstract: A service apparatus for a transportation means comprises a first component in the form of an air shower with an air inlet and at least one air outlet, and a second component in the form of an illumination device. The first component and the second component are arranged essentially centrically in relation to each other, wherein one of the two components encloses the other component essentially in a ring-shaped manner. In this way an integral reading light with a forced-air nozzle, or an integral forced-air nozzle with a reading light, is implemented that uses little design space.

Abstract: A fiber metal laminate panel with a number of layers, arranged in the form of a laminate, of a planar metal material and a fiber material, the planar metal material being joined at splices by a metal-metal connection to overlapping metal layers, and, in reinforced regions which are used to attach the panel to a support structure with longitudinally extending support elements, additional layers of at least the planar metal material being provided. The additional metal layers reinforcing the panel are formed by overlapping metal-metal connections of the splices.

Abstract: A high-lift flap of an aircraft is provided having a device for influencing the flap vortex as well as a device for influencing the flap vortex at the lateral edge of the aerodynamic high-lift flap, which can be achieved effectively and at low cost.

Abstract: What is described is a lightweight structural panel which comprises a planarly extended outer skin of given thickness and stiffening elements which are connected to this outer skin and are arranged at a given distance from one another. According to the invention, the outer skin is formed by component layers which are each extended in the planar direction of the lightweight structural panel and complement one another in the direction of thickness to form the thickness of the outer skin and are interconnected, the stiffening elements being formed in one piece with one of the component layers.

Abstract: The present invention creates a tape laying device as well as a method for the construction of a laminate by means of a tape laying device, in particular in the field of aviation and aerospace. The tape laying device comprises a laying arrangement for laying tape for the construction of a laminate and a stimulation arrangement by means of which the tape which has to be laid can be stimulated directly and evenly over the thickness thereof so as to be heated. The idea the present invention is based on consists in that instead of the stimulation at the surface of the tape which has to be laid which is known to the Applicant a direct and evenly stimulation of the tape which has to be laid takes place, that means, a stimulation which acts substantially direct and evenly over the thickness of the tape which has to be laid on the tapes components. The heating achieved by this is much faster than by means of convection according to the known approach.

Abstract: The invention relates to improved methods and apparatus for performing ground vibration tests (so-called “ground vibration tests”) on an airplane. In the method according to the invention, the airplane is jacked up essentially undamped (“rigidly”) in conventional holding points with lifting devices. For purposes of the ground vibration test, the airplane is then excited to vibrate in a known manner using a plurality of vibration exciters, and the vibrations are acquired with a plurality of measuring transducers, in particular accelerometers. A dynamic vibration model of the airplane theoretically calculated beforehand can here be adjusted. The boundary conditions are removed during or after the ground vibration test, meaning the influence of the lifting device is “mathematically canceled out”, so that the determined measured values reflect the so-called “free-free” state of the airplane, as if the airplane had actually been in free flight during the ground vibration tests.

Abstract: The invention relates to a retaining device for retaining objects on a vehicle wall, comprising: a supporting element (4) for placing on a front side (2) of the wall (1) with devices (5) for retaining one or a plurality of objects (6) and a fastening element (8, 9) for locking the supporting element (4) on a rear side (3) of the wall (1), as well as a method for mounting objects with this retaining device. In order to reduce the installation cost, and in order not to be dependent on the supporting wall thickness, the fastening element (8) is pin-shaped and has a head (9) at one end so that it can be inserted through an opening (7) in the wall (1) and can be prevented against sliding out in one direction, and the supporting element (4) comprises a connecting device (13) with which the supporting element (4) can be solidly connected to the fastening element (8) projecting from the front side (2) of the wall.

Abstract: A device (10) for connecting two duct elements (12, 14) and a baffle (34) in an aircraft air conditioning system may include first (30) and second (32) connecting flanges each connected to one of the two duct elements (12, 14), and at least one connecting element (38) formed on the first connecting flange (30) which interacts with at least one corresponding connecting element (40) formed on the second connecting flange (32) to establish the connection of the two duct elements (12, 14) and the baffle (34). The first (30) and/or second connecting flange (32) has/have an opening (44) for receiving the baffle (34), which is substantially disc-shaped and formed with at least one air passage (46, 48). The baffle (34) serves to control the flow of at least one air stream flowing through the connected duct elements (12, 14).

Abstract: A method for manufacturing a sandwich panel includes, but is not limited to the steps of providing at least one air-permeable core layer and at least one porous cover layer, applying an adhesive onto a first area of the core layer, pressing the cover layer onto the first area of the core layer to connect the cover layer to the core layer, and applying an airstream that from the outside is directed onto the cover layer and that moves through the cover layer and the core layer. By means of such an airstream it is possible to prevent excessive accumulation of adhesive on the cover layer, which otherwise would result in partial blocking of the cover layer. By varying the intensity of the airstream the flow resistance of the arrangement including, but not limited to, the cover layer and the core layer may be determined and set during the bonding process. In this way a sandwich panel with precise sound-absorption behavior can be manufactured.

Abstract: The present invention provides a device, in particular within the aeronautical and aerospace fields, comprising a first and second tool and guide means, which guide the first and second tools in such a way that they press a preliminary fabric arranged in a pressing zone of the device along a second axis as said fabric moves along a first axis through the pressing zone, said second axis being substantially transverse to the first axis, so as to form a consolidated preliminary fabric, the guide means guiding the first and second tools parallel to one another, in part, along the first axis in the pressing zone.

Abstract: The present invention relates to a turbofan propulsion simulator means, in particular for a turbofan of an aircraft or spacecraft, wherein the turbofan propulsion simulator means comprises a modular configuration, wherein the turbofan propulsion simulator means comprises a module, wherein the module is a turbine means to drive the turbofan of the turbofan propulsion simulator means, wherein the turbine means can be coupled with at least two fan means, characterized in that, the at least two fan means to be connected with the turbofan propulsion simulator means comprises almost or essentially the same mass and/or almost or essentially the same barycentre.

Abstract: A floor system for a fuselage section of an aircraft is provided. The floor system has an essentially self-supporting design and is substantially mechanically separate from the fuselage section as primary structure. Consequent to the free or self-supporting design of the floor system in the fuselage cell, the layout of the floor system along an aircraft axis can be matched to customer specifications in a simple manner without reference to structural boundary conditions of the fuselage structure. A floor surface for the floor system is formed from a number of floor elements which can be fitted with functional elements, wherein filling of empty spaces or cavities can be achieved with a number of floor equalization elements. As the floor elements have a relatively large support or fixing surface the loads induced by the functional elements are introduced into the floor system distributed over a large area such that the structural components thereof can be of a structurally lighter and thus weight-saving size.

Abstract: The present invention relates to a method and a device for placing at least one material layer onto a relief mold for producing a composite material. Thereby, an elastically-reversibly deformable body with a surface relief that is designed to correspond to the relief mold is pressed against the material layer, as a result of which the surface of said body is deformed, and the material layer can be picked up. As a result of its elastically-reversible characteristics the body subsequently deforms back to its initial state so that the material layer can easily be placed onto the relief mold.

Abstract: The present invention relates to an aircraft cabin panel for sound reduction in an interior space. The invention in particular also relates to an aircraft comprising an interior lining with sound-absorbing and sound-reducing panels. In order to provide a panel that is optimized in terms of the design space required by it and in terms of its weight, for use in aircraft, which panel provides improved sound reduction and sound absorption characteristics, an aircraft cabin panel for sound reduction in an interior space is provided, which aircraft cabin panel in at least one region comprises a sandwich construction with a core layer, a first covering layer and a second covering layer. The core layer comprises sound absorbing open-pore core material. The first and the second covering layer are connected to the core layer in a planar fashion. The first covering layer is arranged towards the sound waves to be absorbed and the second covering layer is arranged opposite the first covering layer.

Abstract: Latching devices are disclosed for an escape chute in an aircraft, wherein the escape chute has a girt bar for connection to the latching device and the escape chute is accommodated on an aircraft door in a storage container arranged on the inner side thereof. A latching device can include two floor fittings connected to the aircraft, in each of which an end pin of the girt bar can be arranged, a rotating shaft with at least two brackets for movement of the girt bar, two rockers for latching the girt bar, two door fittings, in which the rotating shaft is received so as to be pivotable, and two press-down elements.

Abstract: A passenger seat with an integrated child seat that comprises a folded-in position and a folded-out position. In its folded-in position the passenger seat can be used as a seat for an adult passenger. In its folded-out position the child seat can be used as a seat for a child seated with his/her back in forward direction.

Abstract: A multilayer structural element, such as a skin panel for an aircraft fuselage, comprises a plurality of metal webs and a plurality of fiber webs arranged as layers in a sandwich structure, where the metal webs of neighbouring layers form stepped connecting regions. A material strip is provided on an outer surface of the sandwich structure for at least partially covering an outlying connecting region, and the material strip enables the placement of rivets at uniform spacing for fastening a structure to the structural element.

Abstract: The present invention provides a fuselage structure (1; 1?) of an aircraft comprising an annular skin segment (2; 2?) which has a cross-sectional opening (3; 3?), a pressure cap (4; 4?) for a pressure-tight closure of the cross-sectional opening (3; 3?), and a plurality of tension struts (7, 8, 9; 7?, 8?, 9?) which in each case connect the pressure cap (4; 4?) to the annular skin segment (2; 2?) and absorb loads acting on the pressure cap (4; 4?), as tensile loads. This advantageously means that the tension struts (7, 8, 9; 7?, 8?, 9?) do not have to absorb substantially any bending moments. Consequently, the tension struts can be produced with a relatively small cross section, which entails a reduction in weight. Furthermore, it is possible to produce and mount tension struts (7, 8, 9; 7?, 8?, 9?) of this type in a simple manner.