A device secures a mobile inspection robot to an aircraft engine. The mobile inspection robot is designed to insert a borescope into the aircraft engine to be inspected. The device includes: at least one positioning or orientation adjusting unit configured to adjust the position or orientation of the mobile inspection robot in relation to the aircraft engine to be inspected and at least one connector for providing a connection, which is rigid in at least one degree of freedom, between the mobile inspection robot and the aircraft engine to be inspected, in order to fix, in at least one degree of freedom, the relative position or orientation of the mobile inspection robot in relation to the aircraft engine to be inspected.
The invention relates to a method (100) for supporting the processing of damage on a blading of a turbomachine (10) having a plurality of blades (11), comprising the following steps/stages: determining (103) a contour for processing (202) for mechanically processing a damaged area (20) of a first blade (11.1) of the blading and capturing (104) a first image (200) of a blade area (12) of the first blade (11.1) comprising the damaged area (20). The invention also relates to a computer program product and a system (1).
B23P 6/00 - Remise en état ou réparation des objets
F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
G01N 21/95 - Recherche de la présence de criques, de défauts ou de souillures caractérisée par le matériau ou la forme de l'objet à analyser
G06T 7/50 - Récupération de la profondeur ou de la forme
A centering aid is for centering borescopes. The centering aid includes an elongate central body with a passage channel for borescope lines and with a spacer device. The spacer device extends variably in a radial direction over an entire circumference of the central body. The spacer device is configured to support the central body in at least two support planes which are mutually spaced apart along the central body and run perpendicularly to a longitudinal direction of the central body.
The invention relates to a film (1) for application to pressurized bodies (20) and to a method for the production thereof. The film (1) according to the invention is distinguished by a slotted perforation (10) consisting of slots (11) in a planar arrangement and also without release of material. In order to produce such a slotted perforation (10), a perforation roller cutter (40) inserted into a cutting plotter (30) can be guided linearly over and into an unperforated film.
The invention relates to an optical output system (10) for an aircraft (100) for the graphical output of data, the optical output system (10) comprising a planar output device (20) for the graphical output of data and a data interface device (30) for providing data to the planar output device (20), wherein the optical output system (10) is configured to be transparent at least in sections, wherein the optical output system (10) comprises a planar shielding device (50) and a switching device (52), wherein the switching device (52) is configured for switching the planar shielding device (50) between at least one transparency state (T) and at least one opaque state (B) for switchably optically shielding the transparency of the optical output system (10) at least in sections. Furthermore, the invention encompasses an aircraft (100) comprising at least one optical output system (10), and the use of an optical output system (10) in an aircraft (100).
G09G 3/20 - Dispositions ou circuits de commande présentant un intérêt uniquement pour l'affichage utilisant des moyens de visualisation autres que les tubes à rayons cathodiques pour la présentation d'un ensemble de plusieurs caractères, p.ex. d'une page, en composant l'ensemble par combinaison d'éléments individuels disposés en matrice
B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
18 - Cuir et imitations du cuir
19 - Matériaux de construction non métalliques
20 - Meubles et produits décoratifs
24 - Tissus et produits textiles
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Sanitary apparatus and installations for aircraft. Parts and fittings for aircraft cabins, namely, seats,
safety belts, luggage rack and stowage systems, tables,
furniture and other furnishings; upholstery made of leather
and imitations of leather for aircraft interiors. Leather and imitations of leather, namely, leatherware and
covers, straps, strings, containers made of leather and
imitations of leather, for aircraft interiors. Non-metallic modular construction units and pre-fabricated
construction elements for aircraft cabins. Furniture including furniture made of leather, mirrors,
frames for aircraft interiors. Textiles and textile goods for aircraft interiors. Installation of interior furnishings of aircraft; servicing,
repair and modification of aircraft cabins and their
interior furnishings. Planning of interior furnishings of aircraft.
A flame-retardant wood substrate is made of a wood substrate with a glass-clear coating, impregnation, or filing primer, which each contain a flame retardant made of at least one compound selected from a plurality of phosphorus compounds, and a finish layer disposed thereon.
B05D 7/00 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers
B27K 3/15 - Imprégnation incluant une polymérisation
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.
G08B 7/06 - Systèmes de signalisation selon plus d'un des groupes ; Systèmes d'appel de personnes selon plus d'un des groupes utilisant une transmission électrique
B60Q 3/46 - Agencement des dispositifs d’éclairage pour l’intérieur des véhicules; Dispositifs d’éclairage spécialement adaptés à l’intérieur des véhicules spécialement adaptés à des types spécifiques de véhicules pour les véhicules de transport en commun, p.ex. les bus Éclairage d’urgence, p.ex. pour issues de secours
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
F21K 9/64 - Agencements optiques intégrés dans la source lumineuse, p.ex. pour améliorer l’indice de rendu des couleurs ou l’extraction de lumière en utilisant des moyens de conversion de longueur d’onde distincts ou espacés de l’élément générateur de lumière, p.ex. une couche de phosphore éloignée
F21K 9/68 - Agencements optiques intégrés dans la source lumineuse, p.ex. pour améliorer l’indice de rendu des couleurs ou l’extraction de lumière - Détails des réflecteurs faisant partie de la source lumineuse
F21V 9/32 - CARACTÉRISTIQUES FONCTIONNELLES OU DÉTAILS FONCTIONNELS DES DISPOSITIFS OU SYSTÈMES D'ÉCLAIRAGE; COMBINAISONS STRUCTURALES DE DISPOSITIFS D'ÉCLAIRAGE AVEC D'AUTRES OBJETS, NON PRÉVUES AILLEURS Éléments modifiant les caractéristiques spectrales, la polarisation ou l’intensité de la lumière émise, p.ex. filtres Éléments contenant un matériau photoluminescent distinct de la source de lumière ou espacé de cette source caractérisés par la disposition du matériau photoluminescent
F21V 13/08 - Combinaisons de deux sortes d'éléments uniquement les éléments étant des filtres, ou des éléments photoluminescents, et des réflecteurs
F21V 23/00 - Agencement des éléments du circuit électrique dans ou sur les dispositifs d’éclairage
F21V 23/02 - Agencement des éléments du circuit électrique dans ou sur les dispositifs d’éclairage les éléments étant des transformateurs ou des impédances
F21V 31/00 - Dispositions d'étanchéité à l'eau ou aux gaz
F21W 106/00 - Dispositifs d’éclairage à l’intérieur des véhicules
F21W 107/30 - Utilisation ou application de dispositifs d’éclairage sur ou dans des types véhicules spécifiques pour les aéronefs
F21Y 105/16 - Sources lumineuses planes comprenant un réseau bidimensionnel d’éléments générateurs de lumière ponctuelle caractérisées par la forme d’ensemble du réseau bidimensionnel carrée ou rectangulaire, p.ex. pour les panneaux de lumière
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
38 - Services de télécommunications
Produits et services
Smart speakers; speakers [audio equipment]; cabinets for
loudspeakers; computer hardware; holders for electric coils;
diaphragms [acoustics]; horns for loudspeakers; sound
reproduction apparatus; equalizers [audio apparatus];
amplifiers; sound transmitting apparatus; audio- and
video-receivers; loudspeaker systems; loudspeaker units;
loudspeaker stands [adapted for]; racks for loudspeakers;
audio speakers for vehicles; audio speakers for vehicles;
loudspeakers with built in amplifiers; audio apparatus;
audio amplifiers; audio electronic apparatus; vibration
dampeners for electronic audio equipment; electronic units
for transmitting audio signals; audio dynamic characteristic
modifiers; computer hardware for routing audio, video, and
digital signals; audio/visual and photographic devices;
parts and fittings for audio apparatus; sound processors;
preamplifiers; sound amplifying receivers; analogue sound
modifiers; integrated audio amplifiers; electroacoustic
emphasisers; digital sound processors; devices for streaming
media content over local wireless networks; radio tuners;
digital music players; headphone consoles; headphones; all
the aforementioned goods solely for use on board aircraft,
in particular on board aeroplanes. Covers for loudspeaker openings in vehicles; vehicle seats;
vehicle parts for interior fittings; airplane seats;
airplanes and structural parts therefor; all the
aforementioned goods solely for use on board aircraft, in
particular on board aeroplanes. Digital transmission services for audio and video data;
video, audio and television streaming services; transmission
of sound by electronic means; transmission of sound or
visual recordings over networks; cable transmission of
sounds, images, signals and data; streaming of data; music
broadcasting; all the aforementioned services solely for use
on board aircraft, in particular on board aeroplanes.
An antenna cladding is for fastening fuselage fittings protruding from an outer skin of the aircraft. The antenna cladding has a carrier for fastening antenna modules thereto; a radome fuselage cladding fastened to the carrier for contact on the outer skin; and a radome cover, which forms a continuous cover and lining for electromagnetic radiation in a predetermined wavelength range with the radome fuselage cladding. The carrier is a fiber composite adapter plate made of fiber having recesses with inserts, which have connection fittings for connection to the fuselage fittings. The connection fittings are arranged between upper and lower faces of the adapter plate and are designed such that the connection fittings do not protrude beyond the upper side of the adapter plate and the fuselage fittings do not protrude into the adapter plate when connected to the connection fittings, but do not project beyond the upper side thereof.
B64C 1/36 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes
H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
H01Q 1/42 - Enveloppes non intimement mécaniquement associées avec les éléments rayonnants, p.ex. radome
The invention relates to a radome wall (1) for communication in the frequency band from 17 to 31 GHz for use in aircraft, and also to a radome with a corresponding radome wall (1). The radome wall (1) comprises a multilayer structure with an alternating arrangement of force-absorbing fixed covering layers and shear-resistant core layers, wherein the radome wall (1) has an asymmetrical layer structure with the layer sequence: outer core layer (21) – inner covering layer (12) – inner core layer (22) – outer covering layer (11), wherein the layer thickness of the inner covering layer (12) is at least five times greater than the layer thickness of the outer covering layer (11).
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
18 - Cuir et imitations du cuir
19 - Matériaux de construction non métalliques
20 - Meubles et produits décoratifs
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Textiles and textile goods for aircraft interiors. Sanitary apparatus and installations for aircraft. Parts and fittings for aircraft cabins, namely, seats, safety belts, luggage rack and stowage systems, tables, furniture and other furnishings; upholstery made of leather and imitations of leather for aircraft interiors. Leather and imitations of leather, namely, leatherware and covers, straps, strings, containers made of leather and imitations of leather, for aircraft interiors. Non-metallic modular construction units and pre-fabricated construction elements for aircraft cabins. Furniture including furniture made of leather, mirrors, frames for aircraft interiors. Installation of interior furnishings of aircraft; servicing, repair and modification of aircraft cabins and their interior furnishings. Planning of interior furnishings of aircraft.
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
Produits et services
Digital transmission services for audio and video data; video, audio and television streaming services; transmission of sound by electronic means; transmission of sound or visual recordings over networks; cable transmission of sounds, images, signals and data; streaming of data; music broadcasting; all the aforementioned services solely for use on board aircraft, in particular on board aeroplanes. Smart speakers; speakers [audio equipment]; cabinets for loudspeakers; computer hardware; holders for electric coils; diaphragms [acoustics]; horns for loudspeakers; sound reproduction apparatus; equalizers [audio apparatus]; amplifiers; sound transmitting apparatus; audio- and video-receivers; loudspeaker systems; loudspeaker units; loudspeaker stands [adapted for]; racks for loudspeakers; audio speakers for vehicles; audio speakers for vehicles; loudspeakers with built in amplifiers; audio apparatus; audio amplifiers; audio electronic apparatus; vibration dampeners for electronic audio equipment; electronic units for transmitting audio signals; audio dynamic characteristic modifiers; computer hardware for routing audio, video, and digital signals; audio/visual and photographic devices; parts and fittings for audio apparatus; sound processors; preamplifiers; sound amplifying receivers; analogue sound modifiers; integrated audio amplifiers; electroacoustic emphasisers; digital sound processors; devices for streaming media content over local wireless networks; radio tuners; digital music players; headphone consoles; headphones; all the aforementioned goods solely for use on board aircraft, in particular on board aeroplanes. Covers for loudspeaker openings in vehicles; vehicle seats; vehicle parts for interior fittings; airplane seats; airplanes and structural parts therefor; all the aforementioned goods solely for use on board aircraft, in particular on board aeroplanes.
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
38 - Services de télécommunications
Produits et services
(1) Smart speakers; speakers [audio equipment]; cabinets for loudspeakers; computer hardware; holders for electric coils; diaphragms [acoustics]; horns for loudspeakers; sound reproduction apparatus; equalizers [audio apparatus]; amplifiers; sound transmitting apparatus; audio- and video-receivers; loudspeaker systems; loudspeaker units; loudspeaker stands [adapted for]; racks for loudspeakers; audio speakers for vehicles; audio speakers for vehicles; loudspeakers with built in amplifiers; audio apparatus; audio amplifiers; audio electronic apparatus; vibration dampeners for electronic audio equipment; electronic units for transmitting audio signals; audio dynamic characteristic modifiers; computer hardware for routing audio, video, and digital signals; audio/visual and photographic devices; parts and fittings for audio apparatus; sound processors; preamplifiers; sound amplifying receivers; analogue sound modifiers; integrated audio amplifiers; electroacoustic emphasisers; digital sound processors; devices for streaming media content over local wireless networks; radio tuners; digital music players; headphone consoles; headphones; all the aforementioned goods solely for use on board aircraft, in particular on board aeroplanes.
(2) Covers for loudspeaker openings in vehicles; vehicle seats; vehicle parts for interior fittings; airplane seats; airplanes and structural parts therefor; all the aforementioned goods solely for use on board aircraft, in particular on board aeroplanes. (1) Digital transmission services for audio and video data; video, audio and television streaming services; transmission of sound by electronic means; transmission of sound or visual recordings over networks; cable transmission of sounds, images, signals and data; streaming of data; music broadcasting; all the aforementioned services solely for use on board aircraft, in particular on board aeroplanes.
15.
METHOD AND COMPUTER PROGRAM PRODUCT FOR MONITORING A BLEED AIR SUPPLY SYSTEM OF AN AIRCRAFT
A method monitors a bleed air supply system of an aircraft, the bleed air supply system having at least two analog sensors for monitoring a state of the bleed air supply system based on sensor data. The method includes: determining at least one characteristic map point cloud from simultaneously acquired sensor data from two respective analog sensors, of the at least two analog sensors, relating to the state of the bleed air supply system over a predefined minimum period of time; comparing the characteristic map point cloud with a corresponding predefined characteristic curve for a relationship between the simultaneously acquired sensor data that is represented by the characteristic map point cloud; and based upon a deviation of the characteristic map point cloud from the predefined characteristic curve beyond a predefined amount being detected: outputting a warning.
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
The invention relates to a device (1) for cleaning fuel in a tank (92) of an aircraft (90), and use thereof. The device has a predetermined flow direction (2) for the fuel and comprises units arranged in a fluid-connected manner to forward the fuel from one to another, namely: – an extraction unit (10) for extracting fuel from a tank (92) of an aircraft (90); - a filter unit (30) for filtering the extracted fuel; and - a recirculation unit (70) for returning the filtered fuel to the tank (92) of the aircraft (90), comprising a hose (71) for selective fluid connection of the device (1) to the tank (92) of the aircraft (90), wherein a pump (80) is provided for conveying the fuel at least through the hose (71) of the recirculation unit (70).
37 - Services de construction; extraction minière; installation et réparation
Produits et services
Space heaters for installation in a cabin or cockpit of an
aircraft; heating plates for installation in a cabin or in
the cockpit of an aircraft. Installation, maintenance and repair of heating equipment
for installation in a cabin or cockpit of an aircraft;
installation, maintenance and repair of heating plates for
installation in a cabin or in the cockpit of an aircraft.
18.
METHOD FOR APPLYING AN AERODYNAMICALLY FUNCTIONAL FILM
A method applies aerodynamically functional film to a body around which complex flow occurs. The method includes: determining flow lines on a surface of the body for a predetermined surrounding flow state on a basis of a computer model of the body using a numerical flow simulation; developing at least one surface segment of the computer model provided with flow lines to form a two-dimensional surface; locating at least one coherent field in the developed surface segment having local flow directions readable at the flow lines in a predetermined angle range around a main flow direction of the respective field; and applying the aerodynamically functional film to the body within the field boundary of the at least one field located in the developed surface segment in such a way that the aerodynamically functional film is aligned along the main flow direction of the respective field.
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
F15D 1/12 - Action sur l'écoulement des fluides autour de corps formés d'un matériau solide en agissant sur la couche-limite
37 - Services de construction; extraction minière; installation et réparation
Produits et services
Space heaters for installation in a cabin or cockpit of an aircraft; heating plates for installation in a cabin or in the cockpit of an aircraft Installation, maintenance and repair of heating equipment for installation in a cabin or cockpit of an aircraft; installation, maintenance and repair of heating plates for installation in a cabin or in the cockpit of an aircraft
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.
B60Q 3/74 - Agencement des dispositifs d’éclairage pour l’intérieur des véhicules; Dispositifs d’éclairage spécialement adaptés à l’intérieur des véhicules caractérisés par leur objet pour l’éclairage général de l’habitacle en combinaison avec un éclairage spécifique, p.ex. des lampes d’habitacle avec des lampes de lecture
The invention relates to a method (100) for the maintenance of airplanes. The actual maintenance (200) of the airplane is carried out according to a maintenance plan that is optimized by using artificial intelligence.
The invention relates to a device (10) for fastening cabin components in the region of side walls (6) of an aircraft structure (1), in particular the aircraft structure (1) of a commercial aircraft, said side walls extending in the vertical direction relative to a horizontal cabin floor (5), and also relates to an aircraft structure (1) equipped with such a device (10). The device (10) comprises a structure consisting of - at least two supports (20) which can be arranged vertically on one side wall (6) of an aircraft structure (1), which are spaced apart in the horizontal direction and are each designed for fastening to at least two defined attachment points (8) of the aircraft structure (1) that are spaced apart from one another in the vertical direction in the region of the side wall (6), and - at least one panel (30) connecting the supports (20) in the horizontal direction, which is designed to be connected to the supports (20) connected by the panel (30) at two connection points (31) spaced apart from one another in the vertical direction, wherein both the at least two supports (20) as well as the at least one panel (30) are designed for fastening cabin components thereto.
The invention relates to an apparatus (1) for borescope inspection of technical devices, said apparatus comprising a borescope head (10) which can be arranged on a shaft (50) and has at least one borescope lens (12) and a lighting means (20), wherein a longitudinal axis (11) of the borescope head (10) coincides with the axis (51) of the shaft (50) when said borescope head is arranged on the shaft (50), and wherein the lighting means (20) has at least one lighting unit (21, 22, 23) having a plurality of lighting elements (24, 25) distributed around the circumference about the longitudinal axis (11) of the borescope head (10) for lighting the area in the vicinity of the borescope head (10), wherein at least one lighting element (24, 25) can be controlled independently of the other lighting elements (24, 25) so as to provide different lighting scenarios.
The invention relates to an access control device (1) for a door (21) of a vehicle, more particularly of an aircraft (3), comprising: - an actuation element (4), which can be brought from a blocking state (5) into a release state (6) and vice versa; - a power supply interface (7), by means of which the access control device (1) can be supplied with power; - a control unit (8), which is designed to carry out open-loop and/or closed-loop control of the state of the actuation element (4); - a near-field communication interface (9), which is designed to read out a digital access authorization and to transmit the digital access authorization to the control unit (8); wherein the control unit (8) is designed to carry out open-loop and/or closed-loop control of the state of the actuation element (4) in accordance with the validity of the digital access authorization, and wherein the power supply interface (7) is designed for the connecting of a portable energy store (10) without the use of tools.
The invention relates to guide devices (20) for guiding a borescope (11) for the borescope inspection of technical devices (10, in particular aircraft engines, and an arrangement comprising a guide device (20) of this type and a borescope (11) guided using same. A guide device (20) according to the invention comprises a securing region (35) for fixedly securing the guide device (20) relative to the technical device (1) to be inspected and a borescope holder (22) for fixedly securing a borescope (11) thereon, wherein the guide device (20) has a translation actuator (23) for changing the distance between the borescope holder (22) and the securing region (25) along a guide axis (90) and a rotation actuator (26) for rotating the borescope holder (22) about the guide axis (90) relative to the securing region (35). Another guide device (20) according to the invention comprises a securing region (35) for fixedly securing the guide device (20) relative to the technical device (1) to be inspected and a guide head (27) with at least two guide rollers (28) for the force-locking forced guidance of the shaft (12) of a borescope (11) along a guide axis (90), wherein at least one of the guide rollers (28) can be driven by a translation actuator (23), and wherein the guide head (27) can be rotated relative to the securing region (35), about the guide axis (90), using a rotation actuator (26).
F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
F01D 25/28 - Dispositions pour le support ou le montage, p.ex. pour les carters de turbines
G01N 21/954 - Inspection de la surface intérieure de corps creux, p.ex. d'alésages
G02B 23/24 - Instruments pour regarder l'intérieur de corps creux, p.ex. endoscopes à fibres
A method removes coatings from a surface. The method includes: applying a stripping agent to the coating to be detached in order to produce a cohesive bond, such that the bond between the stripping agent and the coating to be detached is stronger than the bond between the coating to be detached and the surface; and stripping off the stripping agent together with the coating to be detached adhering thereto.
An apparatus investigates a technical device using a borescope. The apparatus has: a guide tube which is introducible through a borescope opening on the technical device to be inspected using the borescope; and a repeatedly plastically deformable carrier configured to guide a borescope head arranged at one end of the carrier. The guide tube is designed to deform the carrier during the passage of the carrier through the guide tube.
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.
G01N 21/954 - Inspection de la surface intérieure de corps creux, p.ex. d'alésages
G01N 35/00 - Analyse automatique non limitée à des procédés ou à des matériaux spécifiés dans un seul des groupes ; Manipulation de matériaux à cet effet
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.
H04B 7/08 - Systèmes de diversité; Systèmes à plusieurs antennes, c. à d. émission ou réception utilisant plusieurs antennes utilisant plusieurs antennes indépendantes espacées à la station de réception
H04W 8/26 - Adressage ou numérotation de réseau pour support de mobilité
30.
FILM FOR APPLICATION TO PRESSURIZED BODIES AND METHOD FOR THE PRODUCTION THEREOF
The invention relates to a film (1) for application to pressurized bodies (20) and to a method for the production thereof. The film (1) according to the invention is distinguished by a slotted perforation (10) consisting of slots (11) in a planar arrangement and also without release of material. In order to produce such a slotted perforation (10), a perforation roller cutter (40) inserted into a cutting plotter (30) can be guided linearly over and into an unperforated film.
B26D 1/28 - Coupe d'une pièce caractérisée par la nature ou par le mouvement de l'élément coupant; Appareils ou machines à cet effet; Eléments coupants à cet effet comportant un élément qui ne suit pas le mouvement de la pièce ayant un élément coupant se déplaçant autour d'un axe avec un élément coupant non circulaire se déplaçant autour d'un axe sensiblement perpendiculaire à la ligne de coupe et tournant sans arrêt dans le même sens pendant la coupe
The invention relates to a mobile partition wall (10) for selectively segmenting a volume (2, 3), for example the passenger cabin (2) or cargo hold (3) of a commercial aircraft, by way of a flexible tarpaulin (11). Besides the tarpaulin (11) for covering the cross section of the volume (2, 3), the mobile partition wall (10) for selectively segmenting a volume (2, 3) comprises an encircling inflatable supporting structure (12) at the periphery of the flexible tarpaulin (11), wherein the tarpaulin (11) and supporting structure (12) are configured such that, in the inflated state of the supporting structure (12), the mobile partition wall (10) is able to bear with the latter sealingly against the boundary wall (4, 5) of the volume (2, 3) along the cross section to be covered, and is foldable in the uninflated state of the supporting structure (12).
A bleed air supply system has a sensor monitoring the system, an operating condition monitor detecting an operating condition value of the aircraft (other than the bleed air supply system), and independent monitoring modules evaluating a part of the bleed air supply system. The monitoring modules each have an individual monitoring function and individual activation and deactivation parameters based on sensor data and the operating condition value. The method includes: detecting the condition of the bleed air supply system via sensor data and the operating condition value; activating a monitoring module, which has activation parameters met by the sensor data and the operating condition value; monitoring the condition of the bleed air supply system by the activated monitoring module by a monitoring function of the activated monitoring module; and deactivating the activated monitoring module, deactivation parameters of which are met by the sensor data and the operating condition value.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64D 13/02 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant pressurisé
F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
A contamination protection is for edges of a riblet film, which is adhesively bonded to a surface. The riblet film has riblets formed on an upper side of a film layer, and an adhesive layer at a lower side of the film layer. The contamination protection has: an edge protection. The edge protection is formed directly on the riblet film that is adhesively bonded to the surface in such a manner that the edge protection covers the adhesive layer of the riblet film, but does not protrude over the upper side of the riblet film.
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
The invention relates to a method (100) for supporting treatment of damage to blading of a turbomachine (10) having a plurality of blades (11), comprising the following steps: determining (103) a treatment contour (202) for mechanically treating a damaged area (20) of a first blade (11.1) of the blading and capturing (104) a first image (200) of a blade region (12) of the first blade (11.1), which region has the damaged area (20). The invention also relates to a computer program product and to a system (1).
F01D 5/00 - Aubes; Organes de support des aubes; Dispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support
B23P 6/04 - Réparation de pièces ou de produits métalliques brisés ou fissurés, p.ex. de pièces de fonderie
G01N 21/88 - Recherche de la présence de criques, de défauts ou de souillures
35.
METHOD AND COMPUTER PROGRAM PRODUCT FOR THE MAINTENANCE OF COMMERCIAL AIRCRAFT
A method schedules maintenance on aircraft of a fleet. The method includes: determining the required items of maintenance of an aircraft, including deadlines; if the deadline of the maintenance is within the first period of time: specifying a maintenance station adequately equipped for carrying out the maintenance work in the flight network for carrying out the maintenance work in a specific ground time of the aircraft; if that deadline is in the second period of time: specifying a time span required for carrying out the maintenance within the second period of time, and specifying the routing of all aircraft in the flight network in consideration of the technical data of the aircraft and the technical requirements of the individual flight routes. and carrying the maintenance work at the specified maintenance station in the provided ground time.
The invention relates to a building platform (1) for the additive repair of components (50) and to the use thereof. The building platform (1) comprises a plurality of repair positions that are arranged in the plane (91) of the building platform (1) and each have component receptacles (2) for fastening a component (50) to be repaired thereto in a precise position and orientation. At least one component receptacle (2) is individually displaceable in a direction (90) perpendicular to the plane (91) of the building platform (1) and optionally fixable. When this building platform (1) is used, the displaceable component receptacles (2) are fixed in a position along their displaceability such that those faces of the components (50) fastened thereto that are intended for material deposition lie in a common plane (94).
B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
B23P 6/00 - Remise en état ou réparation des objets
B33Y 40/00 - Opérations ou équipements auxiliaires, p.ex. pour la manipulation de matériau
B22F 5/04 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser d'aubes de turbines
B22F 7/06 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de pièces ou objets composés de parties différentes, p.ex. pour former des outils à embouts rapportés
37.
APPARATUS FOR ATTACHING AERODYNAMICALLY FUNCTIONAL FILMS AND USE THEREOF
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.
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
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.
G01B 11/25 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer des contours ou des courbes en projetant un motif, p.ex. des franges de moiré, sur l'objet
G02B 6/04 - OPTIQUE ÉLÉMENTS, SYSTÈMES OU APPAREILS OPTIQUES - Détails de structure de dispositions comprenant des guides de lumière et d'autres éléments optiques, p.ex. des moyens de couplage formés par des faisceaux de fibres
A borescope includes an electronic image capturing unit having at least one image capturing sensor with a receiving cone at a first end of a shaft, the shaft having a shaft axis and through which data and supply lines for the image capturing unit are led. The image capturing unit is arranged on a rotary head. The rotary head is secured to the first end so as to be rotatable about the shaft axis such that an axis of the receiving cone is not parallel to the shaft axis at the first end and so that the rotating head is arranged to capture a panoramic image.
The invention relates to an emergency lighting element (1), more particularly for use as an escape path marking in passenger aircraft. The emergency lighting element (1) comprises a planar, electrically operable radiation source (2) for the planar emission of electromagnetic radiation on the front side of said radiation source. A long-afterglow layer (10) is provided on the front side (3) of the radiation source (2) over the full surface of said front side. The penetration depth for the penetration, into the long-afterglow layer (10), of the radiation emitted by the radiation source (2) at least corresponds to the thickness of the long-afterglow layer (10), and the long-afterglow layer (10) comprises phosphorescent material, the absorption spectrum of which at least partly overlaps with the emission spectrum of the radiation source (2) and the emission spectrum of which lies substantially in the visible range.
G08B 7/06 - Systèmes de signalisation selon plus d'un des groupes ; Systèmes d'appel de personnes selon plus d'un des groupes utilisant une transmission électrique
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.
B29C 73/02 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant un liquide ou un matériau pâteux
B29C 35/08 - Chauffage ou durcissement, p.ex. réticulation ou vulcanisation utilisant l'énergie ondulatoire ou un rayonnement corpusculaire
B29C 73/26 - Appareils ou accessoires non prévus ailleurs pour le prétraitement mécanique
B29C 73/30 - Appareils ou accessoires non prévus ailleurs pour presser localement ou pour chauffer localement
The invention relates to a wood substrate with a flame-retardant finish, characterized in that the wood substrate is provided with a clear coating, is impregnated and/or is provided with a filling primer including a flame retardant, containing at least one compound selected from phosphorus compounds, and is also provided with a paint layer. The invention also relates to a method for producing a wood substrate with a flame-retardant finish.
B27K 3/15 - Imprégnation incluant une polymérisation
B05D 7/06 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers à du bois
B05D 7/00 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers
The invention relates to a wood substrate with a flame-retardant finish, characterized in that the wood substrate is provided with a clear coating, is impregnated and/or is provided with a filling primer including a flame retardant, containing at least one compound selected from phosphorus compounds, and is also provided with a paint layer. The invention also relates to a method for producing a wood substrate with a flame-retardant finish.
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.
B32B 37/00 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons
B32B 38/18 - Manipulation des couches ou du stratifié
B41M 5/03 - Procédés de reproduction ou méthodes de reproduction ou de marquage; Matériaux en feuilles utilisés à cet effet en transférant l'encre de la feuille mère par pression
The invention relates to an antenna cladding (1) for aircraft, in particular for commercial aircraft, for fastening to fuselage fittings projecting from the outer skin (90) of an aircraft, comprising a carrier element (2) for fastening antenna modules (3) thereto, a radome-fuselage cladding (4) fastened to the carrier element (2) for bearing on the outer skin (90) of the aircraft, and a radome covering (5) which forms a continuous cladding with the radome-fuselage cladding (4) and is permeable to electromagnetic radiation in a predetermined wavelength range. The carrier element (2) is a fibre composite adapter plate (20) which has cutouts (22) provided with inserts (23), wherein connecting fittings (26) designed for connecting to the fuselage fittings are provided in the inserts (23), said connecting fittings being arranged between the upper and lower side of the adapter plate (20) and being designed in such a way that the connecting fittings (26) do not project beyond the upper side of the adapter plate (20), and the fuselage fittings, when connected to the connecting fittings (26), project into the adapter plate (20) but not beyond the upper side thereof.
The invention relates to an antenna cladding (1) for aircraft, in particular for commercial aircraft, for fastening to fuselage fittings projecting from the outer skin (90) of an aircraft, comprising a carrier element (2) for fastening antenna modules (3) thereto, a radome-fuselage cladding (4) fastened to the carrier element (2) for bearing on the outer skin (90) of the aircraft, and a radome covering (5) which forms a continuous cladding with the radome-fuselage cladding (4) and is permeable to electromagnetic radiation in a predetermined wavelength range. The carrier element (2) is a fibre composite adapter plate (20) which has cutouts (22) provided with inserts (23), wherein connecting fittings (26) designed for connecting to the fuselage fittings are provided in the inserts (23), said connecting fittings being arranged between the upper and lower side of the adapter plate (20) and being designed in such a way that the connecting fittings (26) do not project beyond the upper side of the adapter plate (20), and the fuselage fittings, when connected to the connecting fittings (26), project into the adapter plate (20) but not beyond the upper side thereof.
The invention relates to a method and a computer program product for monitoring a bleed air supply system (10) of an aircraft. The method according to the invention for monitoring a bleed air supply system (10) of an aircraft, having at least two analogue sensors (18, 19) for monitoring the condition of the bleed air supply system (10) on the basis of the sensor data, comprises the steps of: determining at least one characteristic map point cloud (30) from the simultaneously acquired sensor data by means of in each case two analogue sensors (18, 19) regarding the condition of the bleed air supply system (10) over a predetermined minimum time period; comparing the characteristic map point cloud (30) with a corresponding predetermined characteristic curve (35) therefor for the correlation of the acquired sensor data represented by the characteristic map point cloud (30); and if a deviation of the characteristic map point cloud (30) from the predetermined characteristic curve (35) beyond a predetermined extent is detected: issuing a warning. The computer program product according to the invention is designed to carry out this method.
F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
The invention relates to an additive repair system (1) and to a method for determining correction parameters of a corresponding system (1). The additive repair system (1) comprises a construction platform (2) having a construction volume (3) above it and a laser scanner (4) controlled by a control device (5) for selective laser melting of powdered materials introduced successively in layers into the construction volume (3) at predetermined coordinates. The construction platform (2) has a plurality of repair positions (6) having receptacles (7) with the correct position and orientation for components (10) to be repaired by application of material. Furthermore, a correction module (8) is provided for transforming predetermined repair geometries (20) for components (10) located at individual repair positions (6) using correction parameters determined for the relevant repair position (6), before the repair geometries (20) are transmitted to the control device (5) for controlling the laser scanner (4). The method according to the invention is used for determining correction parameters such as those used by the additive repair system (1) according to the invention.
B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
F01D 5/00 - Aubes; Organes de support des aubes; Dispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support
B22F 5/04 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser d'aubes de turbines
B22F 7/06 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de pièces ou objets composés de parties différentes, p.ex. pour former des outils à embouts rapportés
B22F 10/31 - Commande ou régulation des opérations Étalonnage des étapes de procédé ou réglages des appareils, p.ex. avant ou en cours de fabrication
The invention relates to a centering aid (1) for borescopes and to an assembly (10) comprising such a centering aid (2) and a borescope (11). The centering aid (1) comprises an elongated central body (2) with a through-channel (3) for borescope lines and with a spacer device (4), which extends over the entire circumference of the central body (2) in the radial direction in a variable manner, for supporting the central body (2) on at least two support planes (5) which are mutually spaced along the central body (2) and each of which runs perpendicularly to the longitudinal direction of the central body (2). The assembly (10) comprises a borescope (11) with a borescope head (12) at one end of a borescope shaft (13), in which borescope lines run, and a centering aid (1) according to the invention, wherein the centering aid (1) is arranged directly adjacently to the borescope head (12), and the borescope lines are guided through the through-channel of the centering aid (1).
The invention relates to a centering aid (1) for borescopes and to an assembly (10) comprising such a centering aid (2) and a borescope (11). The centering aid (1) comprises an elongated central body (2) with a through-channel (3) for borescope lines and with a spacer device (4), which extends over the entire circumference of the central body (2) in the radial direction in a variable manner, for supporting the central body (2) on at least two support planes (5) which are mutually spaced along the central body (2) and each of which runs perpendicularly to the longitudinal direction of the central body (2). The assembly (10) comprises a borescope (11) with a borescope head (12) at one end of a borescope shaft (13), in which borescope lines run, and a centering aid (1) according to the invention, wherein the centering aid (1) is arranged directly adjacently to the borescope head (12), and the borescope lines are guided through the through-channel of the centering aid (1).
A tool holds and axially fixes a high-pressure shaft of an aircraft engine in a state where a high-pressure turbine stage is demounted. The tool includes: a shaft end cap having an inner radius, which is adapted to a predetermined shaft diameter, the shaft end cap plugs onto a turbine-side end of the high-pressure shaft; a shaft end cap receptacle receives the shaft end cap in a radially movable manner and in an axially limited manner in a first direction; a connector is fastenable to the shaft end cap receptacle and has a shank, which is insertable into the high-pressure shaft, the connector being configured to axially secure the shaft end cap receptacle; and a spring element, which is positionally fixed with respect to the shaft end cap receptacle, the spring element being configured to apply a predetermined spring force to the shaft end cap in the radial direction.
F01D 25/28 - Dispositions pour le support ou le montage, p.ex. pour les carters de turbines
B25B 27/14 - Outils à main ou outillage d'établi, spécialement conçus pour assembler ou séparer des pièces ou des objets, que cela entraîne ou non une certaine déformation, non prévus ailleurs pour assembler des objets autrement que par ajustage à la presse, ou pour les détacher
52.
METHOD AND COMPUTER PROGRAM PRODUCT FOR AUTOMATED DEFECT DETECTION DURING BORESCOPING OF AN ENGINE
A method automatically detects defects during borescoping of an engine. A video borescope is inserted into the engine such that, engine blades can be moved successively through the image region of the borescope. A possible defect on an engine blade is identified by image recognition on the basis of a video borescope frame. The movement of the engine blades in the image region is detected by comparing successive frames. The possible defect is tracked by optical image recognition on the basis of the successive frames used for detecting the movement. In a condition where a trace of the possible defect on the video image corresponds to the detected movement in terms of direction and speed over a predefined length, the possible defect is identified as an actual defect.
G01N 21/892 - Recherche de la présence de criques, de défauts ou de souillures dans un matériau mobile, p.ex. du papier, des textiles caractérisée par la crique, le défaut ou la caractéristique de l'objet examiné
53.
HEATING MAT FOR USE IN A FLOOR STRUCTURE, FLOOR STRUCTURE, AND METHOD FOR PRODUCING SAME
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.
F24D 13/02 - Systèmes de chauffage électrique utilisant uniquement le chauffage par résistance, p.ex. chauffage par le sol
H05B 3/14 - Eléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur caractérisés par la composition ou la nature du matériau conducteur le matériau étant non métallique
An attachment housing is for fastening to an exterior side of an aircraft. The attachment housing has a functional compartment. The functional compartment is divided in two, and has a ventilation compartment and a protective compartment. A surrounding wall is configured to separate the ventilation compartment from an environment. The surrounding wall has at least one ventilation opening for air exchange between the ventilation compartment and the environment. A dividing wall is arranged between the ventilation compartment and the protective compartment. The dividing wall has at least one passage opening for air exchange between the ventilation compartment and the protective compartment. The passage opening is configured to counter act a penetration of water, moisture, or particles into the protective compartment.
H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
H01Q 1/42 - Enveloppes non intimement mécaniquement associées avec les éléments rayonnants, p.ex. radome
B64C 1/36 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes
B64C 1/40 - Insonorisation ou isolation calorifique
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
G01S 7/02 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe
G01S 13/933 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour prévenir les collisions d'aéronefs ou d'engins spatiaux
55.
SYSTEM AND METHOD FOR DIAGNOSING A VACUUM SUCTION SYSTEM
The present invention relates, in particular, to a system (1) for diagnosing a vacuum suction system (50), in particular a vacuum suction system (50) on board aircraft, wherein the vacuum suction system has at least one pipe section (52), wherein the pipe section (52) is designed to remove a substance in its interior along an axial direction (54) of the pipe section (52) by vacuum suction, wherein the system (1) has at least two capacitor electrodes (2, 4, 52), which are arranged in such a way that an electric field can be formed in the interior of the pipe section (52) in a region between the at least two capacitor electrodes (2, 4, 52), and wherein the system (1) has an evaluation unit (10) and/or is communicatively connected to an evaluation unit, wherein the evaluation unit (10) is designed to determine a parameter which is indicative of an electrical capacitance between the at least two capacitor electrodes (2, 4, 52) and to detect a deposition (6) of material in the region between the at least two capacitor electrodes (2, 4, 52) on the basis of the determination of the parameter which is indicative of the electrical capacitance.
G01B 7/06 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer la longueur, la largeur ou l'épaisseur pour mesurer l'épaisseur
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
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.
G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
G01N 21/954 - Inspection de la surface intérieure de corps creux, p.ex. d'alésages
G02B 23/24 - Instruments pour regarder l'intérieur de corps creux, p.ex. endoscopes à fibres
57.
Method and device for inspecting hard-to-reach components
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.
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.
The invention relates to a bidet system (1) for installing in aircraft, the bidet system comprising a bidet bowl (2) and a water supply (3), wherein the water supply (3) comprises a warm water supply (4). There is provided an actuating means (5) for controlling a cleaning valve (6) which controls the throughflow of water from the warm water supply (4) to a cleaning nozzle (7), wherein the cleaning nozzle (7) provides warm water for cleaning a user on the bidet bowl (2), wherein a branch (8) to a pre-flushing line (9) is provided between the warm water supply (3) and the cleaning valve (6). An activatable pre-flushing valve (10) is arranged in the pre-flushing line (9), wherein the pre-flushing line (9) ends with a pre-flushing outlet (11) into the bidet bowl (2). The invention also relates to a corresponding method for operating a bidet system.
The invention relates to a method for producing a coating (1) on at least part of the surface of a component (10) of high-temperature-resistant ceramic fibre composite materials for protection from environmental influences, and to a component (10) with a corresponding coating (1). The method comprises the steps of: a) applying an adhesive layer (2) to the part of the surface of the component (10) that is to be provided with a coating (1); b) applying a water vapour barrier (3) to the part of the surface of the component (10) that is to be provided with a coating (1); and c) applying an outer layer (4) for protection from environmental influences to the water vapour barrier (3), wherein the outer layer (4) has a defined microstructure comprising micropores and/or microcracks, and so the ratio of the shear modulus G to the compression modulus K of the outer layer (4) is less than or equal to 1.1, wherein the outer layer (4) and the water vapour barrier (3) have a sufficiently high elastic compliance to avoid the occurrence of segmentation cracks, the propagation of segmentation cracks to adjacent layers and/or the premature flaking of the outer layer (4) during the specified proper use of the coated component (10). The component (10) according to the invention is coated using the method according to the invention.
The invention relates to an illumination element for marking escape routes in vehicles, in particular in commercial aircraft, and to an arrangement comprising at least one such illumination element. The illumination element (1) comprises a planar substrate (2) having a base surface, provided for fastening purposes, on the first side (3), and at least one planar electrical lighting element (6) on the second side (5), wherein the ratio of the surface area of the base surface to the thickness of the illumination element (1) is greater than 500mm and the ratio of the surface area of the base surface to the mass of the illumination element (1) is larger than 100mm2/g. The arrangement (100) for marking escape routes in a vehicle comprises at least one illumination element (1) according to the invention, an energy supply infrastructure (110), extending over the passenger area (101) of a vehicle, for the at least one illumination element (1), such that said illumination element can be arranged at a plurality of different positions in the passenger area and can be supplied with energy via the energy supply infrastructure, and a signal emitter (120) for generating and emitting control signals for the at least one illumination element (1).
H01L 51/00 - Dispositifs à l'état solide qui utilisent des matériaux organiques comme partie active, ou qui utilisent comme partie active une combinaison de matériaux organiques et d'autres matériaux; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de tels dispositifs ou de leurs parties constitutives
H01L 51/52 - Dispositifs à l'état solide qui utilisent des matériaux organiques comme partie active, ou qui utilisent comme partie active une combinaison de matériaux organiques et d'autres matériaux; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de tels dispositifs ou de leurs parties constitutives spécialement adaptés pour l'émission de lumière, p.ex. diodes émettrices de lumière organiques (OLED) ou dispositifs émetteurs de lumière à base de polymères (PLED) - Détails des dispositifs
G08B 7/06 - Systèmes de signalisation selon plus d'un des groupes ; Systèmes d'appel de personnes selon plus d'un des groupes utilisant une transmission électrique
H02J 9/00 - Circuits pour alimentation de puissance de secours ou de réserve, p.ex. pour éclairage de secours
B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
H04B 5/00 - Systèmes de transmission à induction directe, p.ex. du type à boucle inductive
B60Q 3/74 - Agencement des dispositifs d’éclairage pour l’intérieur des véhicules; Dispositifs d’éclairage spécialement adaptés à l’intérieur des véhicules caractérisés par leur objet pour l’éclairage général de l’habitacle en combinaison avec un éclairage spécifique, p.ex. des lampes d’habitacle avec des lampes de lecture
B60Q 3/46 - Agencement des dispositifs d’éclairage pour l’intérieur des véhicules; Dispositifs d’éclairage spécialement adaptés à l’intérieur des véhicules spécialement adaptés à des types spécifiques de véhicules pour les véhicules de transport en commun, p.ex. les bus Éclairage d’urgence, p.ex. pour issues de secours
F21S 4/20 - Dispositifs ou systèmes d'éclairage utilisant une guirlande ou une bande de sources lumineuses avec les sources lumineuses maintenues par ou à l'intérieur de supports allongés
F21S 8/00 - Dispositifs d'éclairage destinés à des installations fixes
H01L 21/56 - Capsulations, p.ex. couches de capsulation, revêtements
H02J 50/10 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique utilisant un couplage inductif
F21W 107/30 - Utilisation ou application de dispositifs d’éclairage sur ou dans des types véhicules spécifiques pour les aéronefs
F21W 105/00 - Combinaisons de dispositifs d’éclairage couverts par les groupes
H05B 45/00 - Circuits pour faire fonctionner des diodes électroluminescentes [LED]
H05B 47/19 - Commande de la source lumineuse par télécommande via une transmission sans fil
H05K 1/16 - Circuits imprimés comprenant des composants électriques imprimés incorporés, p.ex. une résistance, un condensateur, une inductance imprimés
F21S 9/02 - Dispositifs d'éclairage avec une source d'énergie incorporée; Systèmes utilisant des dispositifs d'éclairage avec une source d'énergie incorporée la source de courant étant une pile ou un accumulateur
F21V 23/00 - Agencement des éléments du circuit électrique dans ou sur les dispositifs d’éclairage
F21V 23/04 - Agencement des éléments du circuit électrique dans ou sur les dispositifs d’éclairage les éléments étant des interrupteurs
41 - Éducation, divertissements, activités sportives et culturelles
42 - Services scientifiques, technologiques et industriels, recherche et conception
45 - Services juridiques; services de sécurité; services personnels pour individus
Produits et services
Compilation and systematisation of information in databanks;
provision of commercial information from online databases;
professional business consultancy; development of marketing
strategies and concepts; evaluations relating to commercial
matters; consultancy regarding business organisation and
business economics; advisory services relating to the
corporate structure of businesses; maintaining a registry of
certified aerospace technicians. Development of educational courses and examinations;
publication of instructional literature; organisation of
training; provision of training courses; conducting
workshops [training]; production of course materials to be
distributed at seminars for professionals; providing
computer assisted courses of instruction. Quality checking and testing; design and testing for new
product development; testing, analysis and evaluation of the
goods and services of others for the purpose of
certification; process monitoring for quality assurance. Legal compliance auditing; regulatory compliance auditing;
reviewing standards and practices to assure compliance with
laws and regulations; preparation of regulations.
A method for borescope inspection of a component uses a stereo borescope for recording the component. The method includes: generating two stereoscopic partial images by means of the stereo borescope; calculating 3D triangulation data from the two stereoscopic partial images; registering the 3D triangulation data to a 3D CAD reference model of the component captured by the stereo borescope, while determining a projection point; projecting 2D image data determined from the two stereoscopic partial images onto the 3D CAD reference model from the determined projection point; and determining damage by image analysis of the projected 2D image data and by ascertaining deviations of the registered 3D triangulation data vis-à-vis the 3D CAD reference model.
G06F 3/0481 - Techniques d’interaction fondées sur les interfaces utilisateur graphiques [GUI] fondées sur des propriétés spécifiques de l’objet d’interaction affiché ou sur un environnement basé sur les métaphores, p.ex. interaction avec des éléments du bureau telles les fenêtres ou les icônes, ou avec l’aide d’un curseur changeant de comport
G01N 21/954 - Inspection de la surface intérieure de corps creux, p.ex. d'alésages
G06T 7/33 - Détermination des paramètres de transformation pour l'alignement des images, c. à d. recalage des images utilisant des procédés basés sur les caractéristiques
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
H04N 13/239 - Générateurs de signaux d’images utilisant des caméras à images stéréoscopiques utilisant deux capteurs d’images 2D dont la position relative est égale ou en correspondance à l’intervalle oculaire
64.
Optical position determination and identification system
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.
G06V 20/59 - Contexte ou environnement de l’image à l’intérieur d’un véhicule, p.ex. concernant l’occupation des sièges, l’état du conducteur ou les conditions de l’éclairage intérieur
G06V 20/80 - Reconnaissance des objets d’image caractérisés par des motifs aléatoires uniques
65.
TRANSPORT OF FREIGHT IN THE PASSENGER CABIN OF COMMERCIAL AIRCRAFT
The invention relates to a commercial aircraft designed for the transport of freight in the passenger cabin (1), container (20) designed therefor, an arrangement consisting of a corresponding commercial aircraft and container (20) and a method for converting an existing passenger aircraft into a commercial aircraft according to the invention. The passenger cabin (1) of the commercial aircraft comprises at least six seat rails (3) arranged extending on the floor in the longitudinal direction of the passenger cabin (1) and arranged symmetrically to the centre line (1') of the passenger cabin (1) extending in the longitudinal direction, wherein in at least some longitudinal sections of the passenger cabin (1), roller strips (10) each extending parallel to the centre line (1') are releasably fastened to the six seat rails (3) closest to the centre line (1') in order to displace, in the longitudinal direction of the passenger cabin (1), containers (20) which simultaneously lie on all six roller strips (10). The container (20) correspondingly has an outer length greater than the distance between the two outer roller strips (10) of the commercial aircraft and an outer width and outer height suitable for insertion through a passenger door (4) of the commercial aircraft. Furthermore, the base of the container (20) is designed to be suitable for rolling on the roller strips (10) of the commercial aircraft. In the method, passenger seats are removed and the six roller strips (10) described are fastened to the corresponding seat rails (3).
The invention relates to a method for retrofitting a passenger airplane (1), which is equipped with a passenger cabin (2) for transporting passengers, in order to temporarily transport freight. In the starting state, the passenger cabin (2) of the passenger airplane (1) has multiple rows (3, 3') of passenger seats (4) as well as passenger door (5) thresholds (5') and cabin monuments (6), comprising toilets and/or on-board kitchens, connected to drainage systems (10) of the passenger airplane (1). The invention also relates to a retrofit passenger airplane (1). The method has the steps of: removing at least the rear rows (3) of passenger seats (4), when viewed in the direction of flight; installing a flood protection device (20') in the region of the front-most removed row of passenger seats, said flood protection device extending over the entire width of the passenger cabin (2); introducing drainage openings (30) into the floor (9) of the passenger cabin (2),wherein the distance between a newly introduced drainage opening (30) and a drainage connection (11) which was already provided for the door thresholds (5') and/or cabin monuments (6) is smaller than the hull diameter of the passenger airplane (1); and connecting the introduced drainage openings (30) to the provided drainage system (10) such that a drainage from the drainage opening (30) to the provided drainage system (10) is ensured when the passenger airplane (1) is flying straight ahead solely by virtue of the force of gravity.
The invention relates to a cargo bridge (10) for simplified introduction of cargo into the passenger cabin (1) of a commercial aircraft through the door opening (5) of a passenger door (4) that opens outwards to the side, which door is flush with the external skin (3) of the commercial aircraft in the closed state and is outside in front of the external skin (3) in the open state. The cargo bridge (10) comprises: – at least one guide rail (11) which can be fastened, perpendicularly to the door opening (5), to the floor (2) of the passenger cabin (1); and – a bridge element (12) that can be longitudinally displaced along the at least one guide rail (11) between a first and a second end position, wherein the width of the bridge element (12) is smaller than the width of the free cross section (7) of the door opening of the open passenger door (1), and the distance between the first and the second end position is greater than the distance between the inner face of the passenger door (1) on the floor (2) of the passenger cabin in the closed state and the point of the passenger door (1) that projects the furthest beyond the external skin (3) of the commercial aircraft in the open state, such that, in the first end position, the passenger door (1) can be closed and, in the second state, the free end (14) of the bridge element (12) protrudes beyond the open passenger door (4). The invention also relates to a commercial aircraft having a corresponding cargo bridge (10).
The invention relates to a furniture lock (1) having at least one closure point (2) which comprises a closure element (3) and a corresponding closure receptacle (4). The furniture lock (1) comprises a base part (5) which is in mechanical connection (7) with the closure element (3) of the at least one closure point (2), wherein the base part (5) is activatable and during an activation causes a movement of the closure element (3), via the mechanical connection (7), into an open state. Provided on the base part (5) are a plurality of connectors (6) at which a plurality of mechanical connections (7) to a plurality of closure elements (3) can be established, wherein, upon an activation of the base part (5), all of the connected closure elements (3) are moved by means of the respective mechanical connection (7) into an open state. The closure element (3) falls automatically into a closed position in the closure receptacle (4) when the base part (5) is not activated and the closure element (3) and the closure receptacle (4) are positioned fittingly in relation to one another.
E05C 9/00 - Aménagement de pênes à action simultanée ou d'autres dispositifs de blocage en des emplacements bien distincts sur le même battant
E05B 63/14 - Disposition de plusieurs serrures ou de serrures comportant plusieurs pênes, p.ex. placés l'un derrière l'autre
E05B 53/00 - Fonctionnement ou commande des serrures par transmissions mécaniques, p.ex. à distance
E05B 63/20 - Serrures à caractéristiques structurales particulières avec dispositions indépendantes du mécanisme de verrouillage pour maintenir le pêne en position de retrait mises hors fonction automatiquement quand le battant est fermé
E05B 47/00 - Fonctionnement ou commande des serrures ou autres dispositifs d'immobilisation par des moyens électriques ou magnétiques
E05B 65/44 - Serrures pour emplois particuliers pour meubles
41 - Éducation, divertissements, activités sportives et culturelles
42 - Services scientifiques, technologiques et industriels, recherche et conception
45 - Services juridiques; services de sécurité; services personnels pour individus
Produits et services
Compilation and systematisation of information in databanks; provision of commercial information from online databases; professional business consultancy; development of marketing strategies and concepts; evaluations relating to commercial matters; consultancy regarding business organization; consultancy regarding business economics, namely, management consulting in economics; business organization consulting, namely, advisory services relating to the corporate structure of businesses; maintaining a registry of certified aerospace technicians Development of educational courses and printed and digital educational materials for others, namely, examinations; publication of instructional literature, namely, technical texts and papers being reports; organisation of training; provision of training courses; training, namely, conducting workshops; educational services, namely, providing seminars for professionals and production of course materials distributed in connection therewith; providing computer assisted courses of instruction; all of the foregoing in the field of aircraft modification for aerospace engineering purposes Quality checking and testing being quality control for others; design and testing for new product development; testing, analysis and evaluation of the goods and services of others for the purpose of determining conformity with certification standards; process monitoring for quality assurance in the field of the value chain for aircraft; all of the aforesaid services relating to the aerospace technology sector Legal compliance auditing; regulatory compliance auditing; reviewing standards and practices to assure compliance with laws and regulations applicable to aircraft construction and maintenance; legal document preparation services, namely, preparation of regulations
70.
Device, method and assembly for cleaning the core engine of a jet engine
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.
B08B 3/02 - Nettoyage par la force de jets ou de pulvérisations
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
B08B 13/00 - Accessoires ou parties constitutives, d'utilisation générale, des machines ou appareils de nettoyage
The invention relates to a method for removing coatings (2) from surfaces (1), comprising the following steps: - large-area application of a suitably selected stripping agent onto the coating (2) to be detached in order to produce a cohesive connection, so that the connection between the stripping agent (5) and the coating (2) to be detached is stronger than the connection between the coating (2) to be detached and the surface (1); and - detaching the stripping agent (6) together with the adhering coating (2) to be detached.
B08B 7/00 - Nettoyage par des procédés non prévus dans une seule autre sous-classe ou un seul groupe de la présente sous-classe
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
The invention relates to a method for removing coatings (2) from surfaces (1), comprising the following steps: - large-area application of a suitably selected stripping agent onto the coating (2) to be detached in order to produce a cohesive connection, so that the connection between the stripping agent (5) and the coating (2) to be detached is stronger than the connection between the coating (2) to be detached and the surface (1); and - detaching the stripping agent (6) together with the adhering coating (2) to be detached.
B08B 7/00 - Nettoyage par des procédés non prévus dans une seule autre sous-classe ou un seul groupe de la présente sous-classe
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
73.
APPARATUS FOR BORESCOPE INSPECTION OF TECHNICAL DEVICES
The invention relates to an apparatus (1) for borescope investigation of a technical device (20), in particular of aircraft engines and components thereof such as combustion chambers (21); the invention also relates to an arrangement comprising such an apparatus. The apparatus (1) comprises a guide tube (2), which can be introduced through a borescopy opening (22) in a technical device (20) to be borescoped, and a repeatedly plastically deformable carrier element (3) for guiding a borescope head (7) arranged on one end of the carrier element (3), the guide tube (2) being designed to deform the carrier element (3) as the carrier element (3) is guided through the guide tube (2). The arrangement comprises such an apparatus (1) and a flexible borescope, the carrier element (3) of the apparatus (1) being tubular and the borescope being introduced into the carrier element (3) of the apparatus (1).
G02B 23/24 - Instruments pour regarder l'intérieur de corps creux, p.ex. endoscopes à fibres
A61B 1/00 - Instruments pour procéder à l'examen médical de l'intérieur des cavités ou des conduits du corps par inspection visuelle ou photographique, p.ex. endoscopes; Dispositions pour l'éclairage dans ces instruments
74.
APPARATUS AND METHOD FOR INSPECTING TECHNICAL DEVICES USING A BORESCOPE
The invention relates to an apparatus (1) and a method for inspecting technical devices (20) using a borescope. The apparatus (1) comprises an elongate support element (2) which is guided in a deformation unit (10) and is repeatedly plastically deformable, wherein the deformation unit (10) comprises a guide element (13), which is fixed in its position, for axially guiding the support element (2) at an output end (12) and an actuator element (14) embodied for axially guiding the support element (2), with the actuator element being movable in at least a direction perpendicular to the distance between guide element (13) and actuator element (14) in order to selectively apply a bending moment on the support element (2) which is guided by the guide element (13) and the actuator element (14), and wherein a borescope head (5) is arranged at the end of the support element (2) that protrudes from the output end (13) of the deformation unit (10). In the method, an elongate support element (2) which is repeatedly plastically deformable and which comprises a borescope head (3) is selectively pre-deformed at its end to be inserted into the technical device (20) in the region in front of the entry into the technical device (20) during the insertion into the technical device (20) in order thus to follow a specified path of the borescope head (3) within the technical device (20).
G02B 23/24 - Instruments pour regarder l'intérieur de corps creux, p.ex. endoscopes à fibres
A61B 1/00 - Instruments pour procéder à l'examen médical de l'intérieur des cavités ou des conduits du corps par inspection visuelle ou photographique, p.ex. endoscopes; Dispositions pour l'éclairage dans ces instruments
G01N 21/954 - Inspection de la surface intérieure de corps creux, p.ex. d'alésages
75.
CLEANING METHOD FOR CERAMIC FIBER COMPOSITE MATERIALS
DEUTSCHES ZENTRUM FÜR LUFT- UND RAUMFAHRT E. V. (Allemagne)
Inventeur(s)
Peters, Jan-Oke
Gartner, Thomas
Köster, Aenne
Bechheim, Lukas
Abel, Dominic
Klopsch, Linda
Koch, Dietmar
Süss, Fabia
Abrégé
The invention relates to a method for cleaning the surface of components (1) consisting of ceramic fiber composite materials (2) for applying an environment-stabilized protective layer (4'), and to a method for applying an environment-stabilized protective layer (4') to the surface of a component (1) consisting of ceramic fiber composite materials (2). According to the invention, the oxides (5) on the surface of the ceramic fiber composite material (2) that might impede application of an environment-stabilized protective layer (4') are removed by fluoride-ion cleaning and/or stripping the oxide in a water vapor atmosphere and/or hydrogen atmosphere. Subsequently, an environment-stabilized protective layer (4') can be applied to the cleaned surface of the component (1).
C04B 41/91 - Post-traitement des mortiers, du béton, de la pierre artificielle ou des céramiques; Traitement de la pierre naturelle de céramiques uniquement impliquant l'enlèvement d'une partie des matières des objets traités, p.ex. par attaque chimique
C04B 41/89 - Revêtement ou imprégnation pour obtenir au moins deux revêtements superposés de compositions différentes
F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
76.
ARRANGEMENT AND METHOD FOR ADDRESSING AND LOCATING EQUIPMENT
The invention relates to a system and method for addressing seat-mounted electrical equipment in an aircraft cabin, wherein each piece of equipment is non-varyingly logically linked to a transceiver device having a unique identifier and a plurality of transceiver antennae with non-identically oriented antenna lobes, wherein the transceiver device is configured to transmit a signal comprising its unique identifier via each of the transceiver antennae individually and to receive any signal of a neighboring transceiver device attributing it to the actually receiving transceiver antennae in order to determine pattern information pairs, and a central instance is configured to collect the pattern information pairs from the transceiver devices and to compare the pattern information pairs with a stored pattern of the equipment to identify each transceiver devices position in the stored pattern, wherein the pattern information pair comprises the unique identifier of the neighboring transceiver device having transmitted the signal.
H04W 4/48 - Services spécialement adaptés à des environnements, à des situations ou à des fins spécifiques pour les véhicules, p.ex. communication véhicule-piétons pour la communication dans le véhicule
H04W 4/02 - Services utilisant des informations de localisation
A functional enhancement module is for vehicles and for enhancing a functional module which is supplied with electric power via a power supply bus. The functional enhancement module is configured to be supplied with the electric power via the power supply bus. The functional enhancement module includes: a controller having a power specification for a maximum power flow of the functional module and being configured to detect a current power flow at a reference point; and a power controller configured to control a power take-up of the functional enhancement module. The controller is configured to control the power controller in accordance with the detected power flow, such that a combined power take-up of the functional module and the functional enhancement module does not exceed the power specification.
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.
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
H02J 1/04 - Systèmes d'alimentation en courant constant
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p.ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseau; Circuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p.ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
79.
ARRANGEMENT AND METHOD FOR ADDRESSING AND LOCATING EQUIPMENT
The invention relates to an arrangement and a method for addressing equipment (10, 11), especially seat-mounted electrical equipment (10, 11) in an aircraft cabin (2), wherein each piece of equipment (10, 11) is non-varyingly logically linked to a transceiver device (21) having a unique identifier (90) and a plurality of transceiver antennae (23) with non-identically oriented antenna lobes (24), wherein the transceiver device (21) is configured to transmit a signal comprising its unique identifier (90) via each of the transceiver antennae (23) individually and to receive any signal of a neighboring transceiver device (21) attributing it to the actually receiving transceiver antennae (23) in order to determine pattern information pairs, and a central instance (50) is configured to collect the pattern information pairs from the transceiver devices (21) and to compare the pattern information pairs with a stored pattern of the equipment to identify each transceiver devices' (21) position in the stored pattern. The inventive method relates to the operation of this arrangement.
H04W 4/48 - Services spécialement adaptés à des environnements, à des situations ou à des fins spécifiques pour les véhicules, p.ex. communication véhicule-piétons pour la communication dans le véhicule
H04W 4/02 - Services utilisant des informations de localisation
An electronic housing houses electronics for an aircraft. The electronic housing has an outer wall surrounding an electronic receiving compartment; and fasteners on one side of the outer wall on an outer side. The fasteners are configured to engage in a snap-fit connection to a predefined raceway configured for the attachment of a cover by a snap-fit connection.
The invention relates to a method and a computer program product for monitoring a bleed air supply system of an aircraft. At least one sensor (20-22) for monitoring the state of the bleed air supply system (10) by means of the sensor data, at least one operational state monitor (5) for detecting the operational state of the aircraft (1), except for the bleed air supply system (10), using at least one operational state value, and at least two independent monitoring modules (30) for evaluating the state of at least one part of the bleed air supply system (10) are provided for the method, and an individual monitoring function, as well as individual activation and deactivation parameters based on sensor data of at least one sensor and at least one operational state value are provided for each monitoring module (30).
A plug-in connection box for vehicles has a socket and a return apparatus. The socket, is accessible from an access side and has an insertion direction. The socket is arranged in a pivot body, which is mounted in a movable manner in relation to a receptacle in such a way that the insertion direction of the socket is pivotable at an angle in all directions starting from a stationary state of the pivot body. The return apparatus is configured to return the pivot body to the stationary state.
H01R 35/04 - Connecteurs de ligne pouvant tourner d'un angle de rotation limité
B60R 16/027 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleurs; Agencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques pour la transmission de signaux entre des parties ou des sous-systèmes du véhicule entre des parties du véhicule mobiles l'une par rapport à l'autre, p.ex. entre le volant et la colonne de direction
The invention relates to a contamination protection (10) for the edges of riblet films (2) which are adhered to a surface (1) and have riblets (4) formed on the top side (3') of a film layer (3) and an adhesive layer on the bottom side. The contamination protection (10) comprises an edge protection (11, 12) which is formed directly on a riblet film (2) adhered to a surface (1) such that the edge protection (11, 12) covers the adhesive layer (5) of the riblet film (2) but does not protrude beyond the top side (3') of the riblet film (2).
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
The present invention relates to a method for assessing the quality of varnished wood surfaces. In line with the method according to the invention, the following steps are carried out: a. creating a brightness map of the surface, b. creating a curvature map of the surface, c. determining a cross-correlation of the brightness map and the curvature map, d. evaluating the result of the cross-correlation in order to determine that proportion of the unevenness of the surface which can be attributed to varnish defects. The method according to the invention makes it possible to easily distinguish between disruptive varnish defects and those varnish defects which can be attributed to the grain of the wood.
The invention relates to a method for applying an aerodynamically functional film to a body around which complex flow occurs, for example on a commercial aircraft. The method comprises the following steps: – determining the flow lines (4) on the surface (7) of the body around which flow occurs for a predefined state of surrounding flow on the basis of a computer model (1) of the body, using numerical flow simulation; – developing at least one surface segment (3) of the computer model (1), which surface segment is provided with flow lines (4), to form a two-dimensional area; – locating at least one coherent field (10, 20, 30, 40) in the developed surface segment (3) by means of local flow directions which can be read on the flow lines (4) in a predefined angular range about a main flow direction of the relevant field (10, 20, 30, 40); and – within the field limit (10.1-4, 11.1-4, 12.1-4, 13.1-4) of the at least one field (10, 20, 30, 40) located in the processed surface segment, applying an aerodynamically functional film to the body around which flow occurs and, as required, cutting said film to size such that the aerodynamically functional film is oriented in the main flow direction of the relevant field.
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
The invention relates to a method for applying an aerodynamically functional film to a body around which complex flow occurs, for example on a commercial aircraft. The method comprises the following steps: ? determining the flow lines (4) on the surface (7) of the body around which flow occurs for a predefined state of surrounding flow on the basis of a computer model (1) of the body, using numerical flow simulation; ? developing at least one surface segment (3) of the computer model (1), which surface segment is provided with flow lines (4), to form a two-dimensional area; ? locating at least one coherent field (10, 20, 30, 40) in the developed surface segment (3) by means of local flow directions which can be read on the flow lines (4) in a predefined angular range about a main flow direction of the relevant field (10, 20, 30, 40); and ? within the field limit (10.1-4, 11.1-4, 12.1-4, 13.1-4) of the at least one field (10, 20, 30, 40) located in the processed surface segment, applying an aerodynamically functional film to the body around which flow occurs and, as required, cutting said film to size such that the aerodynamically functional film is oriented in the main flow direction of the relevant field.
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
87.
Device and assembly for cleaning the core engine of a jet engine
A device cleans a core engine of a jet engine. The device has: a nozzle installation configured to introduce 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, the line connection being connected to the nozzle installation by a rotary coupling. The nozzle installation has first contact faces configured to bear axially on fan blades of the fan, the first contact faces being configured for defined positioning of the nozzle installation relative to the jet engine.
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
B08B 3/02 - Nettoyage par la force de jets ou de pulvérisations
B08B 13/00 - Accessoires ou parties constitutives, d'utilisation générale, des machines ou appareils de nettoyage
B05B 15/652 - Aménagements de montage pour la liaison fluide de l’appareil de pulvérisation ou de ses sorties aux conduits d’écoulement le jet pouvant être orienté
88.
METHOD AND COMPUTER PROGRAM PRODUCT FOR THE MAINTENANCE OF COMMERCIAL AIRCRAFT
The invention relates to a method for the maintenance of commercial aircraft and to a corresponding computer program product. The method according to the invention relates to the planning of maintenance work (20, 22) on aircraft (FZ1, FZ2, FZ3, FZ4, FZ5) during ongoing flight operations in a flight network. During planning, differentiation is made between a current period of time (T1), in which the complete routing of the aircraft (FZ1, FZ2, FZ3, FZ4, FZ5) is defined, and a subsequent second period of time (T2), in which only the flight routes (10) that are to be operated, but not the routing of the aircraft (FZ1, FZ2, FZ3, FZ4, FZ5) are defined. The computer program product according to the invention is designed to carry out the method according to the invention.
The invention relates to an apparatus for attaching aerodynamically functional films (14.1-5) to surfaces (4) of bodies (1) around which flow occurs and to the use of such an apparatus. The apparatus comprises a self-adhesive, removable positioning film (11) having positioning aids (12) for precise positioning of the positioning film (11) on the surface (4) of the body (1) around which flow occurs and at least one application area (13.1-5) for the aerodynamically functional film (14.1-5) to be applied. The apparatus is used by means of the following steps: a) applying the positioning aid (11) of the apparatus in the position defined by the positioning aids (12) to the surface (4) of the body (1) around which flow occurs; b) applying the aerodynamically functional film (14.1-5) to the surface (4) of the body (1) around which flow occurs in the application areas (13.1-5) of the positioning film (11); and c) removing the positioning film (11).
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
The invention relates to a borescope (1), in particular for the borescopy of fuel chambers (58) of aircraft engines (50), and to an assembly (31) comprising a borescope (1). The borescope (1) comprises an electronic image capturing unit (20) with at least one image capturing sensor (22, 23) with a receiving cone at a first end (4) of a shaft (3) which has a shaft axis (3') and through which data and supply lines (21) for the image capturing unit (20) are guided. The image capturing unit (20) is arranged on a rotary head (10) which is rotatably secured to the first end (4) about the shaft axis (3') such that the axis (22', 23') of the receiving cone is not parallel to the shaft axis (3') on the first end (4) and a panoramic image can be captured by rotating the rotary head (10). The assembly (30) comprises a borescope (1) according to the invention and a control and analysis unit (31) which is designed to control the rotational movement of the rotary head (10) and the image capturing unit (20) and to combine the image data captured by the at least one image capturing sensor (22, 23) in order to form a panoramic image.
The invention relates to a borescope (1), more particularly for borescopy inspection of aircraft engines. The borescope (1) comprises an electronic image capture unit (10) with two image capture sensors (11) as the borescope objective on the end of a shaft (3) designed for introduction into a borescope opening, wherein the position and orientation of the image capture sensors (11) relative to one another is suitable for the determination of 3-D information by triangulation. Furthermore, a pattern projector (20) is provided for projecting a pattern (50) in the common recording area of the image capture sensors (11), which projector comprises a fundamentally optically imaging optical fibre bundle (21) of statistically distributed optical fibres (22) with differing degrees of transmission, with the input face (23) of which a light source (25) is coupled and the output face (24) of which is directed towards the area covered by the image capture sensors (11).
G01B 11/25 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer des contours ou des courbes en projetant un motif, p.ex. des franges de moiré, sur l'objet
The invention relates to a borescope (1), in particular for the borescopy of fuel chambers (58) of aircraft engines (50), and to an assembly (31) comprising a borescope (1). The borescope (1) comprises an electronic image capturing unit (20) with at least one image capturing sensor (22, 23) with a receiving cone at a first end (4) of a shaft (3) which has a shaft axis (3') and through which data and supply lines (21) for the image capturing unit (20) are guided. The image capturing unit (20) is arranged on a rotary head (10) which is rotatably secured to the first end (4) about the shaft axis (3') such that the axis (22', 23') of the receiving cone is not parallel to the shaft axis (3') on the first end (4) and a panoramic image can be captured by rotating the rotary head (10). The assembly (30) comprises a borescope (1) according to the invention and a control and analysis unit (31) which is designed to control the rotational movement of the rotary head (10) and the image capturing unit (20) and to combine the image data captured by the at least one image capturing sensor (22, 23) in order to form a panoramic image.
G02B 23/24 - Instruments pour regarder l'intérieur de corps creux, p.ex. endoscopes à fibres
F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
G01N 21/954 - Inspection de la surface intérieure de corps creux, p.ex. d'alésages
G06T 1/00 - Traitement de données d'image, d'application générale
A61B 1/00 - Instruments pour procéder à l'examen médical de l'intérieur des cavités ou des conduits du corps par inspection visuelle ou photographique, p.ex. endoscopes; Dispositions pour l'éclairage dans ces instruments
The invention relates to a borescope (1), more particularly for borescopy inspection of aircraft engines. The borescope (1) comprises an electronic image capture unit (10) with two image capture sensors (11) as the borescope objective on the end of a shaft (3) designed for introduction into a borescope opening, wherein the position and orientation of the image capture sensors (11) relative to one another is suitable for the determination of 3-D information by triangulation. Furthermore, a pattern projector (20) is provided for projecting a pattern (50) in the common recording area of the image capture sensors (11), which projector comprises a fundamentally optically imaging optical fibre bundle (21) of statistically distributed optical fibres (22) with differing degrees of transmission, with the input face (23) of which a light source (25) is coupled and the output face (24) of which is directed towards the area covered by the image capture sensors (11).
G01B 11/25 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer des contours ou des courbes en projetant un motif, p.ex. des franges de moiré, sur l'objet
G03B 21/00 - Projecteurs ou visionneuses du type par projection; Leurs accessoires
41 - Éducation, divertissements, activités sportives et culturelles
42 - Services scientifiques, technologiques et industriels, recherche et conception
45 - Services juridiques; services de sécurité; services personnels pour individus
Produits et services
Compilation and systematisation of information in databanks; Provision of commercial information from online databases; Professional business consultancy; Development of concepts for business economy; Evaluations relating to commercial matters; Consultancy regarding business organisation and business economics; Advisory services relating to the corporate structure of businesses; Maintaining a registry of certified aerospace technicians. Development of educational courses and examinations; Publication of instructional literature; Organisation of training; Provision of training courses; Conducting workshops [training]; Production of course material distributed at professional seminars; Providing computer assisted courses of instruction; all the aforesaid services, in relation to the following fields: Aerospace engineering. Quality checking and testing; Testing, analysis and evaluation of the goods and services of others for the purpose of certification; Process monitoring for quality assurance; all the aforesaid services, Relating to the following sectors: Aerospace technology. Legal compliance auditing; Regulatory compliance auditing; Reviewing standards and practices to assure compliance with laws and regulations; Preparation of regulations.
95.
Method for applying a titanium aluminide alloy, titanium aluminide alloy and substrate comprising a titanium aluminide alloy
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.
The invention relates to a method for laminating optical defects (5) in surfaces (1). The essential steps of the method are: - digitally optically detecting at least one optical defect (5) and the surrounding surface (1); - digitally imitating the surface (1) in the region of the at least one optical defect (5) using image processing; - printing the surface imitation (13) true to scale onto a transfer film (14) in a mirror-reversed manner; - soaking and activating the printing ink applied onto the transfer film (14); - aligning the transfer film (14) with the surface (1) such that on the transfer film (14), the surface imitation (13) coincides with the optical defect on the surface (1); - pressing and then removing the transfer film (14); - removing the transfer film (14) from the surface (1); - pressing the printing ink remaining on the surface (1); and - applying a protective layer (4).
B32B 38/18 - Manipulation des couches ou du stratifié
B32B 37/00 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons
B44C 1/16 - Procédés non expressément prévus ailleurs pour la production d'effets décoratifs sur des surfaces pour appliquer des images-transfert ou similaires
97.
METHOD AND COMPUTER PROGRAM PRODUCT FOR AUTOMATED DEFECT DETECTION DURING BORESCOPING OF AN ENGINE
The invention relates to a method, and corresponding computer program product, for defect detection, in which a video borescope (2) is introduced into an engine (80) in such a way that, during rotation of an engine shaft (83, 86), the engine blades (90) of an engine stage (81, 84, 85, 87) which are fastened thereon are moved consecutively through the image area of the video borescope (2), the method comprising the following steps: • - identifying a possible defect on an engine blade (90) by image recognition based on an individual image (10) of the video borescope; • - detecting the movement of the engine blades (90) in the image area of the video borescope by comparing every two successive individual images (10, 10'); • - tracking the possible defect on the video image along the detected movement by optical image recognition based on the individual images (10, 10') used for detecting the movement; • - if the trace (92) of a possible defect on the video image corresponds over a predetermined length in direction and speed to the detected movement: identifying the possible defect as an actual defect.
The invention relates to a method for laminating optical defects (5) in surfaces (1). The essential steps of the method are: - digitally optically detecting at least one optical defect (5) and the surrounding surface (1); - digitally imitating the surface (1) in the region of the at least one optical defect (5) using image processing; - printing the surface imitation (13) true to scale onto a transfer film (14) in a mirror-reversed manner; - soaking and activating the printing ink applied onto the transfer film (14); - aligning the transfer film (14) with the surface (1) such that on the transfer film (14), the surface imitation (13) coincides with the optical defect on the surface (1); - pressing and then removing the transfer film (14); - removing the transfer film (14) from the surface (1); - pressing the printing ink remaining on the surface (1); and - applying a protective layer (4).
B32B 38/18 - Manipulation des couches ou du stratifié
B32B 37/00 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons
B44C 1/16 - Procédés non expressément prévus ailleurs pour la production d'effets décoratifs sur des surfaces pour appliquer des images-transfert ou similaires
A method for repairing structured surfaces of a component with a damaged location, including a removal of material in a sub¬ area of the surface, having the steps of: a) ascertaining a comparison surface; b) applying a curable die material, onto the comparison surface; c) while the die material is being pressed against the comparison surface: curing the die material in order to form a transparent die which has a negative shape of the surface structure of the comparison surface; d) filling the damaged location with a material curable with electromagnetic radiation; e) placing the die on the curable material such that the negative shape of the die is aligned correspondingly to the desired surface structure at the damaged location; f) while the die is being pressed : irradiating the curable material with electromagnetic radiation through the transparent die; and removing the die from the cured material without residue.
B29C 73/10 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des pastilles d'obturation appliquées à la surface de l'objet
B29C 73/02 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant un liquide ou un matériau pâteux
B29C 73/30 - Appareils ou accessoires non prévus ailleurs pour presser localement ou pour chauffer localement
The invention relates to a method for repairing structured surfaces (2) of a component (1) with a damaged location (4), including a removal of material in a sub-area (3) of the surface (2), having the steps of: a) ascertaining a comparison surface (5) for the sub-area (3) with an at least comparable surface structure; b) applying a curable die material (7), which is transparent at least in the cured state, onto the comparison surface (5); c) while the die material (7) is being pressed against the comparison surface (5) with a pressing pressure: curing the die material (7) in order to form a transparent die (7') which can be removed from the comparison surface (5) without residue and has the negative shape of the surface structure of the comparison surface (5); d) filling the damaged location (4) of the sub-area (3) with a material (11) which can be cured with electromagnetic radiation; e) placing the die (7') on the curable material (11) in the damaged location (4) such that the negative shape of the transparent die (7') is aligned correspondingly to the desired surface structure at the damaged location (4); f) while the die (7') is being pressed onto the damaged location (4) with a pressing force: irradiating the curable material (11) with electromagnetic radiation through the transparent die (7') and to the material (11); and removing the die (7') from the cured material (11') at the damaged location (4) without residue.
B29C 73/10 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des pastilles d'obturation appliquées à la surface de l'objet
B29C 73/02 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant un liquide ou un matériau pâteux
B29C 73/30 - Appareils ou accessoires non prévus ailleurs pour presser localement ou pour chauffer localement
