Abstract: A process produces a tubular hybrid molding made of a plastics foam element that exhibits temperature-dependent shrinkage and a fiber-plastics composite. The method includes inserting the plastics foam element, unhardened first and second fiber-plastics composite sections into a mold, where the plastics foam element has open pores at locations in contact with the fiber-plastics composite. The plastics foam element and the fiber-plastics composite sections are shaped by the mold. The mold is exposed to a first temperature to minimize the viscosity of the resin in the fiber-plastics composite. The mold is exposed to a second temperature to harden the fiber-plastics composite and to achieve mechanical fixing of the plastics foam element thereon. The mold is exposed to a third temperature to shrink the plastics foam element and cause its shape to conform to that of the mold and achieve a final shape of the said element.

Abstract: A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.

Abstract: A process produces a tubular hybrid molding made of a plastics foam element that exhibits temperature-dependent shrinkage and a fiber-plastics composite. The method includes inserting the plastics foam element, unhardened first and second fiber-plastics composite sections into a mold, where the plastics foam element has open pores at locations in contact with the fiber-plastics composite. The plastics foam element and the fiber-plastics composite sections are shaped by the mold. The mold is exposed to a first temperature to minimize the viscosity of the resin in the fiber-plastics composite. The mold is exposed to a second temperature to harden the fiber-plastics composite and to achieve mechanical fixing of the plastics foam element thereon. The mold is exposed to a third temperature to shrink the plastics foam element and cause its shape to conform to that of the mold and achieve a final shape of the said element.

Abstract: The description covers cabin components for aircraft, which can be produced with a sandwich structure and may have the components 1003 for signal and/or power transmission. The cabin components in this case have at least two prepreg layers 1001, 1005 and, for example, a honeycomb layer 1002, which can be connected to one another by pressing and heating. Furthermore, electrical and/or optical signal paths are shown on cabin components, which can be produced by positioning them there or printing. In addition, according to the description, signal and/or power transmission can take place beyond the boundary of cabin components, by means of a transmitter/receiver path.

Abstract: A coating method wherein in order to simplify the coating method and increase the flexibility thereof with respect to respective desired coatings, provision is made that a powder lacquer layer (3) is applied to a surface (2) of the component (1), and an imprint (4) is applied to the powder lacquer layer (3), preferably by an inkjet method.

Abstract: An internal device arrangement for a passenger cabin, for example of an aircraft, is provided. The device has an internal device element which is selected from a group including wall paneling, window panel, side panel, ceiling paneling and luggage compartment. The device has an electrical apparatus fitted in or on the internal device element; and at least one line for supplying power to the electrical apparatus. Furthermore, a heat dissipation device in the form of an integral component part of the internal device element, the electrical apparatus and/or the at least one line is provided. Such a heat dissipation device makes it possible to dispense with an additional heat sink for temperature management and thus save installation space and weight.

Abstract: Corresponding to reducing the number of components that need to be separately installed, in addition to a weight reduction and a reduction in the cable loom volume, improved system reliability is obtained if the loads relating to a seating space in a passenger cabin (12), in particular in an aircraft, are combined on an overhead panel (17) which is connected, via line connections which are now only short, to a spatially associated supply module (19), which is operated in cutouts (20) in a stub frame (13), in order to anchor a hat rack (11) in the fuselage structure (16) of the cabin (12).

Abstract: A textile web material impregnated with a mixture that contains at least a prepolymer prepolymerized from a starting material of one or more bifunctional or polyfunctional organic cyanates and from a starting material of one or more bifunctional or polyfunctional aromatic alcohols, wherein the one or more bifunctional or polyfunctional organic cyanates and the one or more bifunctional or polyfunctional aromatic alcohols are present in weight ratios ensuring a molar ratio of the OCN groups to the OH groups between 95:5 and 70:30 prior to prepolymerization. The mixture further contains one or more fillers.

Abstract: To implement replenished-air ventilation of a passenger cabin of, for example, an aircraft, an inner wall cladding (12) with integrated replenished-air inlets (18) is proposed. For this purpose, the inner wall cladding (12) has sandwich boards (30) which are constructed from a first top layer (32) facing the passenger cabin (10), a second top layer (34) facing away from the passenger cabin (10) and a sandwich core (36) arranged between the first top layer (32) and the second top layer (34), the sandwich core (36) being designed to be at least partially air-permeable, and the first top layer (32) having at least one air-permeable portion (38).

Abstract: The description covers cabin components for aircraft, which can be produced with a sandwich structure and may have the components 1003 for signal and/or power transmission. The cabin components in this case have at least two prepreg layers 1001, 1005 and, for example, a honeycomb layer 1002, which can be connected to one another by pressing and heating. Furthermore, electrical and/or optical signal paths are shown on cabin components, which can be produced by positioning them there or printing. In addition, according to the description, signal and/or power transmission can take place beyond the boundary of cabin components, by means of a transmitter/receiver path.

Abstract: An internal device arrangement for a passenger cabin, for example of an aircraft, comprises an internal device element (15) which is selected from a group consisting of wall panelling, window panel, side panel, ceiling panelling and luggage compartment; an electrical apparatus (1) such as a lighting element, for example, which is fitted in or on the internal device element (15); and at least one line (2) for supplying power to the electrical apparatus (1). Furthermore, a heat dissipation device (6a . . . f) in the form of an integral component part of the internal device element (15), the electrical apparatus (1) and/or the at least one line (2) is provided. Such a heat dissipation device (6a . . . f) makes it possible to dispense with an additional heat sink for temperature management and thus for savings to be made in terms of installation space and weight.

Abstract: A coating method wherein in order to simplify the coating method and increase the flexibility thereof with respect to respective desired coatings, provision is made that a powder lacquer layer (3) is applied to a surface (2) of the component (1), and an imprint (4) is applied to the powder lacquer layer (3), preferably by an inkjet method.

Abstract: An interior trim component (10) for an aircraft cabin comprises a supporting structure which is formed by a first chamber system (12) which is sealable against the outside atmosphere. The first chamber system (12) forming the supporting structure is adapted to be loaded with an internal pressure which is necessary for producing the desired structural load-bearing capacity of said supporting structure.