Abstract: A heating mat is for use in a floor structure in an aircraft. The heating mat has a layered structure, with a plurality of layers firmly connected to one another, with a layer sequence. The layer sequence includes: a) a walkable protection layer having an unfinished floor covering material made of fiberglass-reinforced plastic or aramid fiber-reinforced plastic; b) an electrically conductive ground fault detection layer; c) an electrical insulation layer; and d) a flat electrical heating element having an electrically conductive heating varnish layer.

Abstract: An arrangement provides addressing for a plurality of equipment. Each piece of the equipment is non-varyingly logically linked to a corresponding transceiver having a unique identifier and a plurality of transceiver antennae with non-identically oriented antenna lobes. Each corresponding transceiver is configured to transmit a signal having the unique identifier associated with the transceiver via each of the transceiver antennae individually and to receive any signal of a neighboring transceiver attributing it to the actually receiving transceiver antennae in order to determine pattern information pairs. A central instance is configured to collect the pattern information pairs from the transceiver transceivers and to compare the pattern information pairs with a stored pattern of the equipment to identify each transceivers' position in the stored pattern.

Abstract: An apparatus is for attaching an aerodynamically functional film to a surface of a body around which flow passes. The apparatus includes: a self-adhesive, redetachable positioning film having positioning aids for the exact positioning of the positioning film on the surface of the body around which flow passes and having at least one application area for the aerodynamically functional film that is to be applied.

Abstract: Embodiments related to a monument for an aircraft cabin. On the monument, a screen is provided for displaying the images captured by a video surveillance device.

Abstract: An apparatus is used for inspecting a technical device using a borescope. The apparatus has a repeatedly plastically deformable and elongated carrier which is guidable in a deforming unit. The deforming unit has a stationary guide configured to axially guide the carrier at an outlet end and an actuator which is designed to axially guide the carrier and can be moved in at least one direction perpendicular to the gap between the guide and the actuator in order selectively to apply a bending moment to the carrier guided by the guide and the actuator. A borescope head is arranged at that end of the carrier which protrudes from the outlet end of the deforming unit.

Abstract: An emergency lighting element includes a planar, electrically operable radiation source for planar emission of electromagnetic radiation at a front side of the radiation source; and a long-afterglow layer over a whole area on the front side of the radiation source. A penetration depth into the long-afterglow layer for radiation emitted by the radiation source corresponds at least to a thickness of the long-afterglow layer. The long-afterglow layer comprises phosphorescent material, an absorption spectrum of the long-afterglow layer at least partly overlaps an emission spectrum of the radiation source and an emission spectrum of the long-afterglow layer lies substantially in a visible range.

Abstract: An illumination element marks escape routes in vehicles. The illumination element includes a planar substrate, which has: a base surface configured for fastening on a first side; and at least one planar electrical lighting element on a second side. A ratio of a surface area of the base surface to a thickness of the illumination element is greater than 500 mm, and a ratio of the surface area of the base surface to a mass of the illumination element is greater than 100 mm2/g.

Abstract: A method refurbishes structured surfaces of a component having a damaged subregion with material detachment. The method comprising: determining a reference region having a similar surface structure as the subregion; while pressing a die material onto the reference region: curing the die material to form a transparent die which is separable from the reference region without leaving residues and has a negative shape of the surface structure of the reference region; filling the damage location with electromagnetic irradiation curable material; placing the die onto the curable material in the damage location with an alignment of the negative shape of the transparent die corresponding to a desired surface structure at the damage location; while the die is being pressed onto the damage location: irradiating the curable material with electromagnetic irradiation through the transparent die until the material is cured; and removing the die from the cured material without leaving residues.

Abstract: A method conceals optical defects in surfaces. The method includes: obtaining a digital image by a digital optical recording the optical defect and a surrounding surface; obtaining an imitation of the surface in a region of the at least one optical defect by image processing of the digital image; printing a mirror-inverted, true-to-scale representation of the surface imitation onto a transfer film; soaking the transfer film; applying an activator onto a the transfer film or onto the surface; aligning the transfer film onto the surface so that the surface imitation on the transfer film coincides with the optical defect on the surface; pressing the transfer film onto the surface; peeling the transfer film from the surface; pressing on the ink remaining on the surface; and after complete drying of the activator and of the ink: applying a protective layer onto the surface imitation.

Abstract: A securing device for a component that can be secured on rails of a floor structure of an aircraft interior includes at least two adapter plates. The adapter plates are decoupled from one another and configured to be secured on the rails. The adapter plates being configured to secure the component having mutually spaced securing attachments.

Abstract: An optical position determination and identification system is for environments having a multiplicity of identically constructed objects. The system includes: a mobile image acquisition unit; and texture elements that are configured to be applied onto the objects. Each of the texture elements has a pattern that respectively comprises pseudorandom deviations from a predetermined basic pattern, which are not visible with the naked eye at a distance of 1 m. The image acquisition unit is configured to identify the texture elements uniquely with the aid of their pseudorandom deviations.

Abstract: A method uses a flexible endoscope to inspect one or more hard-to-reach components of a gas turbine. The flexible endoscope has at least one image capture unit, which is configured to capture visual image information and associated 3D data, and which is located at a free end of the flexible endoscope. The method includes: introducing the flexible endoscope through an inspection opening; capturing the visual image information and the associated 3D data by the at least one image capture unit; comparing the captured 3D data to a 3D model of a component to be examined, and based on the comparison, ascertaining a relative pose of the at least one image capture unit in relation to the component; and texturing the 3D model with the visual image information captured by the at least one image capture unit, in accordance with the ascertained relative pose of the image capture unit.

Abstract: A supplementary function module is for vehicles for the supplementation of a function module supplied with electrical power via a power supply bus. The supplementary function module is configured to be supplied with electrical power via the power supply bus. The supplementary function module has a controller configured to detect a voltage in the power supply bus, and to deactivate the supplementary function module based upon a first predefined voltage variation being detected.

Abstract: A borescope is for optically inspecting gas turbines of aircraft engines. The borescope having an electronic image capture unit as a borescope objective at an end of a shaft, which is suitable for insertion into a borescope opening and configured for accurate positioning of the borescope objective relative to the borescope opening and through which data lines and supply lines for the image capture unit are guided. The image capture unit has: two spaced apart image capture sensors, recording cones of which overlap in a specified recording plane forming a recording region, in such a way that image data of the two image capture sensors are configured to be processed into 3-D data by way of triangulation.

Abstract: An escape path marking for an aircraft includes a lighting element, which luminesces in a dark environment, and which emits an emitted light which exits at an outer side of the escape path marking. A transparent protective element is arranged between the lighting element and the outer side of the escape path marking. A planar grid element, which comprises regularly alternating pure-color transparent and opaque regions, is arranged between the lighting element and the outer side of the escape path marking. A transparent pigmented element is formed and arranged between lighting element and the outer side of the escape path marking such that in an event of external illumination according to at least one predefined illumination scenario, a predefined first color tone results on the outer side of the escape path marking at the transparent regions of the grid element.

Abstract: A device drives a shaft of a jet engine for inspection purposes. The device has: a drive having a part co-rotating with the shaft. The co-rotating part of the unit is configured to lie against a spinner of the shaft and is secured in a non-rotatable manner to at least one fan blade arranged on the shaft using at least one strap.

Abstract: A method applies a titanium aluminide alloy on a substrate. The titanium aluminide alloy has a gamma phase proportion of at least 50% based on an overall composition of the titanium aluminide. The method includes: pretreating a surface of the substrate; heat treating titanium aluminide powder particles at a temperature range of 600° C. to 1000° C. to increase the proportion of the gamma phase; cold spraying the heat-treated powder particles onto the substrate or a part of the substrate to form a layer of titanium aluminide; and thermally post-treating the layer of titanium aluminide applied to the substrate.

Abstract: A device enables borescope inspection of turbine blades of a high-pressure turbine stage of a jet engine. The device has a bend-free guide pipe for introducing a flexible borescope. The device also has: a guide for the guide pipe, the guide being configured to provide clear and reproducible positioning and orientation of the guide pipe; and a securing device configured to releasably secure the guide to an outer side of the jet engine. The securing device is configured to adjust the guide to a predetermined orientation with respect to the outer side of the jet engine. The guide pipe is rigid and shaped in such a manner that an end of the guide pipe that is introduced into the jet engine when the guide is orientated correctly is orientable so as to be directed between two predetermined guide blades.

Abstract: A borescope includes an electronic image capture unit having two image capture sensors as a borescope lens at an end of a shaft that is designed for being inserted into a borescope opening, a position and alignment of the image capture sensors in relation to one another being suitable for ascertaining three-dimension (3D) information using triangulation; and a pattern projector configured to project a pattern into a common recording region of the image capture sensors. The pattern projector includes: a fundamentally optically imaging light-guide bundle, which is made up of statistically distributed optical fibers having differing transmittances, to whose input surface a light source is coupled and whose output surface is aligned with the region captured by the image capture sensors.

Abstract: A device cleans a core engine of a jet engine. The device has: a nozzle installation which is configured for introducing a cleaning medium into the core engine; a connector configured to connect the device in a rotationally fixed manner to a shaft of a fan of the jet engine; and a line connection configured to supply the cleaning medium, which is connected to the nozzle installation by a rotary coupling. The nozzle installation comprises nozzles, comprising at least one flat jet nozzle, and at least one full cone nozzle or hollow cone nozzle.