Abstract: A plastics material component for an aircraft includes (i) a substrate, which comprises one or more thermosetting plastics materials, and (ii) one or more layers which are applied to the substrate, at least one layer S1 comprising mica. A method for producing the plastics material component includes providing a substrate including at least one thermosetting plastics material or one polymer which is crosslinked to form a thermosetting plastics material, and applying one or more layers to the substrate, wherein at least one layer includes mica. The mica-containing layer is applied directly to the substrate and the application is carried out before and/or during the curing of the thermosetting plastics material.

Abstract: A plastics material component for an aircraft includes (i) a substrate, which comprises one or more thermosetting plastics materials, and (ii) one or more layers which are applied to the substrate, at least one layer S1 comprising mica. A method for producing the plastics material component includes providing a substrate including at least one thermosetting plastics material or one polymer which is crosslinked to form a thermosetting plastics material, and applying one or more layers to the substrate, wherein at least one layer includes mica. The mica-containing layer is applied directly to the substrate and the application is carried out before and/or during the curing of the thermosetting plastics material.

Abstract: An aircraft fuselage includes at least one space arranged in the aircraft fuselage and at least one wall. The wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage underneath the space does not include burnthrough-resistant insulation. The space may be a cargo compartment of the aircraft or a passenger cabin, while the wall may be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly fairing). The design of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR §25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.

Abstract: A facing arrangement for a hold of an aircraft or spacecraft. The facing arrangement comprises a first and a second panel which form a gap between them; a first mounting part which is to be attached to a primary structure of the hold and which has at least one locking arrangement, and a second mounting part which has at least one counter locking arrangement. The locking arrangement and/or the counter locking arrangement passing, at least in portions, through the gap between the first and the second panel. The locking arrangement and the counter locking arrangement being locked together in order to connect the first mounting part to the second mounting part for holding the first and second panels between the first mounting part and the second mounting part.

Abstract: A press device for the energy-efficient curing of a sandwich component for an aircraft, includes an open and mechanically adequately loadable core structure with cover layers applied to one side or to both sides. The sandwich component is restrained between a pressure piston, an abutment and sidewalls of the press device, thus forming an essentially closed interior space. At least one of at least one cover layer and the core structure includes a curable duroplastic plastic material. A conveying device feeds heated air through the core structure of the sandwich component in a closed heated-air circuit or preferably in an open heated-air circuit in order to ensure energy-efficient curing of the sandwich component from the inside out. The heated air is temperature-controlled by a heater. In the case of an open heated-air circuit, heat recovery by a heat exchanger is provided.

Abstract: The invention relates to a method for the production of sandwich components with an open core structure and a cover layer applied to each side, wherein the cover layers are formed with a curable plastic material, and the sandwich component is cured in a closed device under pressure. A charging gas, which may be nitrogen or air, is introduced to the core structure prior to at least partial solidification of the cover layers, wherein a charging gas pressure p Charging gas is selected that is less than or equal to an operating pressure p operating of the closed device in order to, in particular, at least largely prevent the formation of sink marks in the cover layers. Furthermore, the invention relates to a press for implementing the method.

Abstract: A heating system according to the invention comprises a heating layer that is integrated into a prepreg layer of a high-resistance prepreg material. The heating layer may comprise a bonded heating fabric, a metal oxide coating or electrically conductive threads. According to the invention, the heating system is integrated into a component to be heated. This component may consist, for example, of a floor panel for an aircraft.

Abstract: A facing arrangement for a hold of an aircraft or spacecraft. The facing arrangement comprises a first and a second panel which form a gap between them; a first mounting part which is to be attached to a primary structure of the hold and which has at least one locking arrangement, and a second mounting part which has at least one counter locking arrangement. The locking arrangement and/or the counter locking arrangement passing, at least in portions, through the gap between the first and the second panel. The locking arrangement and the counter locking arrangement being locked together in order to connect the first mounting part to the second mounting part for holding the first and second panels between the first mounting part and the second mounting part.

Abstract: The present invention relates to a plastics material component for an aircraft, comprising (i) a substrate, which comprises one or more thermosetting plastics materials, and (ii) one or more layers which are applied to the substrate, at least one layer S1 comprising mica.

Abstract: A fire protection device for an aircraft or spacecraft is disclosed. The fire protection device can include a fireproof bulkhead and an adjusting device, the fireproof bulkhead can be adjusted from a ventilating position I into a screening position II. This may prevent a stream of smoke and heat from penetrating into the cabin when there is a fire underneath the fuselage.

Abstract: A thermal insulating tape is configured for fire protection for use in aircraft construction. The insulating tape has a multilayer construction including a flexible carrier tape providing protection against burn-through, the carrier tape being formed as a thermally conductive metal tape. An adhesive film is disposed on a first side of the carrier tape and is configured for partial fixation or complete wrapping of the insulating tape on a protected component. A flexible intumescent coating is disposed on a second side of the carrier tape.

Abstract: A pipeline for conducting air for air conditioning in aircrafts includes a body portion formed with foamed plastics material or with a dense plastics material. The body portion defines a longitudinal axis and includes an outer surface carrying a wrapping for reinforcing the pipeline. The wrapping includes a plurality of adjacent contacting layers formed by at least one linear reinforcing element wound into a plurality of windings, with adjacent layers having windings angled in opposite directions to form a net-like structure of the wrapping. At least one of the spacing between the windings along the longitudinal axis or the angle of slope between the windings and the longitudinal axis varies in certain sections to change the winding density as a function of local mechanical load requirements on the pipeline.

Abstract: The invention relates to an aircraft fuselage (12) comprising at least one space arranged in the aircraft fuselage and at least one wall (16). According to the invention, the wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage (12) underneath the space does not comprise burnthrough-resistant insulation. The space can be a cargo compartment of the aircraft or a passenger cabin, while the wall can be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly-fairing). The design, according to the invention, of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR §25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.

Abstract: The invention relates to an arrangement for providing active fire protection in aircraft by means of at least one protective shield. According to the invention, the at least one protective shield is formed with an intumescent material, which in the event of a fire can be activated, in particular made to expand, in a controlled manner well below the initial temperature otherwise usual for intumescent materials of the order of 250° C. by means of an electrical heating device. The current temperature in the hold (preferably at various temperature measuring points) of the aircraft is measured by means of at least one temperature sensor and transmitted to a controlling and regulating device. In the event of a fire, the heating devices are activated and the intumescent reactions of the protective shields for providing fire protection are initiated within a temperature interval between 90° C. and 150° C.

Abstract: Provided is a fire protection device for an aircraft or spacecraft. The fire protection device is provided with a fireproof bulkhead and an adjusting device, by means of which the fireproof bulkhead can be adjusted from a ventilating position I into a screening position II. This may prevent a stream of smoke and heat from penetrating into the cabin when there is a fire underneath the fuselage.

Abstract: The invention relates to a method for the production of sandwich components with an open core structure 2 and a cover layer 1, 3 applied to each side, wherein the cover layers 1, 3 are formed with a curable plastic material, and the sandwich component is cured in a closed device under pressure. According to the invention, a charging gas, in particular nitrogen or air, is introduced to the core structure 2 prior to at least partial solidification of the cover layers 1, 3, wherein a charging gas pressure pCharging gas is selected that is less than or equal to an operating pressure pOperating of the closed device in order to, in particular, at least largely prevent the formation of sink marks in the cover layers (1, 3). Furthermore, the invention relates to a press for implementing the method.

Abstract: The invention relates to a pipeline 1, 34 for conducting air, in particular in a temperature range between ?55° C. and +85° C. and at a differential pressure load of at most ±500 hPa relative to cabin pressure, for air conditioning in aircrafts. According to the invention, the pipeline 1, 34 is formed with a foamed plastics material and/or with a dense plastics material, one outer face 9, 36 of the pipeline and/or one inner face 17 of the pipeline comprising a wrapping 6, 37 with at least one linear reinforcing element, in particular with resin-impregnated carbon fibers or glass fibers for reinforcement, at least in certain sections. Owing to the winding 6, 37 provided for reinforcement, at least in certain sections, on the outer face 9, 36 of the pipeline and/or the inner face 17 of the pipeline, the pipeline 1, 34 can be optimally adapted to different load requirements along the section for laying, resulting in a potentially considerable reduction in weight.

Abstract: A press device for the energy-efficient curing of a sandwich component for an aircraft, comprising an open and mechanically adequately loadable core structure with cover layers applied to one side or to both sides, characterised in that the sandwich component is restrained between a pressure piston, an abutment and sidewalls of the press device, thus forming an essentially closed interior space, and at least one cover layer and/or the core structure comprise/comprises a curable duroplastic plastic material. A conveying device feeds heated air through the core structure of the sandwich component in a closed heated-air circuit or preferably in an open heated-air circuit in order to ensure energy-efficient curing of the sandwich component from the inside out. The heated air is temperature-controlled by a heater. In the case of an open heated-air circuit, heat recovery by a heat exchanger is provided.

Abstract: A heating system according to the invention comprises a heating layer that is integrated into a prepreg layer of a high-resistance prepreg material. The heating layer may comprise a bonded heating fabric, a metal oxide coating or electrically conductive threads. According to the invention, the heating system is integrated into a component to be heated. This component may consist, for example, of a floor panel for an aircraft.

Abstract: The application describes an arrangement for coating interior trim components in passenger aircraft while complying with relevant fire protection standards and at the same time improving thermal comfort, with a layer arrangement which comprises a transparent layer and further functional layers, wherein the layer arrangement can be applied to the interior trim components, in particular to the side of the cabin wall which faces the passenger. At least in some regions, a rear coating that faces away from the interior of the cabin of the passenger aircraft has been applied to the transparent layer. Due to the rear coating of the transparent layer, the thermal comfort of passengers which are seated in the window regions of the cabin is believed to be enhanced.