Abstract: A holder system for fastening an aircraft interior component to a transporting apparatus and to an aircraft structure includes an interior component holder configured to be connected to the interior component and which has a fastening device for fastening the interior component holder to the transporting apparatus. A structure holder is configured to be connected to the aircraft structure. A connecting element is fastened to the interior component holder and is configured to be connected to the structure holder in order to fasten the interior component to the aircraft structure.

Abstract: An aircraft cooling system for cooling heat loads on board an aircraft includes a cold producing device, a first cold carrier fluid circuit thermally coupled to the cold producing device and connected to a first heat load in order to carry off heat from the first heat load, a second cold carrier fluid circuit connected to a second heat load in order to carry off heat from the second heat load, a heat exchanger disposed in the second cold carrier fluid circuit and configured to thermally couple the second cold carrier fluid circuit to an ambient temperature surrounding the aircraft, and a coupling system configured to selectively thermally couple the first cold carrier fluid circuit to the second cold carrier fluid circuit or thermally uncouple it from the second cold carrier fluid circuit.

Abstract: A holder for fastening an interior component, intended for mounting in an aircraft, to a transporting apparatus, includes an interface element configured to be connected to the transporting apparatus for the purpose of fastening the holder to the transporting apparatus. A bearing element is connected to the interface element and has a fixed bearing for bearing a first interior component holder connected to the interior component and a movable bearing for bearing a second interior component holder connected to the interior component.

Abstract: Producing a local reinforcement in a core structure of a composite sandwich structure involves forming a hole in a cover layer and the core of the sandwich structure, forming a hollow space in the core with a diameter the same as or preferably larger than that of the hole, introducing a spatial bounding device through the hole into the hollow space, seating the spatial bounding device in the hollow space to contact outwardly against parts of the core preferably by outwardly expanding the device, and introducing a filler material into the spatial bounding device. A sandwich structure includes a core between cover layers, and a local reinforcement including a hole in at least one of the cover layers, a space in the core with a larger diameter than the hole, a spiral sleeve in the space, and a filler material inside the spiral sleeve.

Abstract: A wall element for the sound-insulating interior lining of a transport device, comprising at least one sandwich element, at least one insulation package and at least one absorber plane element. The sandwich element comprises at least one core layer, a first cover layer and a second cover layer, wherein the first cover layer and the second cover layer are each arranged on one side of the core layer. At least the first or the second cover layer is a microperforated layer; the sandwich element possesses a shear rigidity that is adjusted in such a way that the sandwich element comprises one or several coincidence boundary frequencies that are determined by the shear rigidity, which coincidence boundary frequencies are outside the frequency range that dominates the noise in the interior of the cabin; and the shear rigidity of the sandwich element at the same time is sufficient for said sandwich element to be used as an interior lining.

Abstract: The present invention relates to a rear-illuminable aircraft interior component consisting of a transparent or translucent thermoplastic, a translucent varnish layer disposed on the latter and a decorative varnish layer disposed on the translucent varnish layer, as well as the use of a rear-illuminable aircraft interior component of this kind as a rear-illuminable aircraft window ring.

Abstract: The invention relates to an aircraft side fairing, with a component (9) in the form of individual hollow chambers (12, 13, 14) which are arranged essentially in a preferably curved plane and are arranged between two cover layers (1, 2), wherein a gastight film which completely encases the component (9) with the hollow chambers (12, 13, 14) is provided and, after application of a vacuum to evacuate the hollow chambers (12, 13, 14), surrounds the component (9) with the hollow chambers in a gastight manner.

Abstract: The present invention relates to a production method for producing a sensor film for measuring cracks of a material surface using the comparative vacuum measurement method. A gallery having a predetermined gallery course is milled along a surface of the sensor film using a milling apparatus. The sensor film comprises a plastic material.

Abstract: An arrangement is provided for de-icing pipeline connections of an aircraft, which are connected to all fresh air outlets of an air conditioner, whose construction includes, but is not limited to the functions of multiple turbines and heat exchangers, having a first pipeline, which is connected to a first turbine, and a second pipeline, which is connected to a second turbine, the two pipelines, which are each connected downstream from the two turbines and to which process air is fed at the turbine outlets, being connected at the pipe ends and being continued using a third pipeline. The arrangement is characterized in that a first hot air source is fed hot fresh air from a bleed air system of the aircraft and is connected at its outlet to a fourth pipeline, into which temperature-reduced fresh air is fed from the hot air source.

Abstract: An interconnecting strut includes two coaxially arranged strut elements which may be displaced relative to one another in the longitudinal direction of the interconnecting strut, two end stops defining the mutual displaceability of the two strut elements, as well as damping elements, which when a specific permissible displacement is exceeded, damp the displacement movement of the strut elements before reaching the end stops, in which the damping elements consist of a material which is plastically deformable in the occurring force range, the damping elements being compressed for damping the displacement movement in the longitudinal direction and, at the same time, being subjected to a cross-sectional enlargement transversely to the longitudinal direction, due to the compression.

Abstract: The present invention relates to an emergency ram air inlet valve, also designated as an ERAI valve, of an aircraft. The valve includes an actuating element for opening and/or closing the valve and a controller operatively coupled to the valve, by which the valve can be set at different open angles. The open angle is set as a function of a temperature prevailing or preset in the aircraft cabin.

Abstract: An air conditioning arrangement for an aircraft with a plurality of climate zones that may be individually temperature-controlled includes a main branching system having an air supply feed path system with a mixing chamber and a plurality of sub-branching systems branching from the mixing chamber and leading to one of the climate zones in each case. Basic temperature control means are used for controlling the temperature of the air supply in the mixing chamber. Individual temperature-control means are used on the other hand for individually controlling the temperature of the air supply in each of the sub-branching systems as a function of a desired temperature value of the respective climate zone. Basic temperature control of the air supply in the mixing chamber preferably takes place independently of a temperature requirement of the climate zone with associated combined heat and power engine.

Abstract: A system and method for manufacturing welded structures comprises components to be welded, a welding additive material which, before the welding, has a shaped profile and the shaped profile is disposed between components to be welded and conforms with at least one of the components to be welded. At least one heat source is used in the method to weld the components, producing a weld seam on at least one side of one of the components.

Abstract: A floor panel, in particular for covering floors of cargo holds of aircraft, is formed by a plurality of milled profiles, which are friction stir welded along their longitudinal edges, with preference continuously to form longitudinal (butt) seams. The milled profiles each form a beam “of equal stress”, with an upper flange and a lower flange spaced apart from one another along their extent. The milled profiles have a double-T-shaped cross-sectional profile, the upper flanges and the lower flanges being respectively connected by webs. With preference, the milled profiles are milled out in one piece from solid material of a sufficiently tough aluminum alloy. The joining together of the floor panel including a plurality of milled profiles that are arranged in parallel and friction stir welded allows a high mechanical load-bearing capacity of the floor panel in comparison with conventional sandwich floor panels along with a comparatively low weight.

Abstract: An adjustment device aligns supporting parts that receive the guide rails of a freight loading system for structures having inherent dimensional tolerances, in particular for receiving structures in an aircraft fuselage. Each supporting part is designed as a bearing insert held with an adjustable movement in a bearing eye of a bearing block, and in that the bearing block has at least two tensioning elements that bear on the bearing insert.

Abstract: A holding system for fixing a line assembly includes a fixing band, and a fixing band retaining element, which is arranged on the line assembly and comprises at least one guiding element for receiving the fixing band, the fixing band retaining element comprising two ends, one end being provided with at least one or more cavities or recesses, into which the other end can be plugged or hooked.

Abstract: A cooling system for cooling a fuel-cell system on board an aircraft, in one example, includes a hydrogen accumulator, a connecting device coupling the hydrogen accumulator, with an external cooling system for dissipating heat arising upon charging of the hydrogen accumulator. The hydrogen accumulator cools down upon removal of hydrogen, because of which cooling of a condenser occurs. The cooling system need not utilize a secondary cooling loop for condenser cooling.

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 intercostals for an aircraft or space craft for diverting a load from a first rib to a second rib and/or a skin of the aircraft and/or space craft, with at least one opening region for guiding through system lines or the like, wherein the intercostal has a traverse that is movable at least between a first and a second position, wherein the traverse in the first position is provided for forming a force flow for diverting a load between the first rib and the second rib, and in the second position reveals the opening region from a predetermined side.

Abstract: An energy buffer device supplies energy to a consumer in an aircraft, and an electrical system for an aircraft. In one example, the device includes an energy feed device, an energy storage device and an energy supply device. The energy supply device may have line with a larger cross-sectional area than a corresponding line of the energy feed device. With the use of an energy buffer device, power may be switched on only for a short period of time. In addition, in case of a voltage breakdown in an on-board network, energy may be stored in an energy storage device. Supply of energy may thus occur over a short time at correspondingly high power, without placing a load on an on-board network or a generator.