LOCKING DEVICE FOR LOCKING A PIVOTABLY MOUNTED DOOR OF A CONTAINER, IN PARTICULAR A LUGGAGE COMPARTMENT DOOR OF AN OVERHEAD LUGGAGE COMPARTMENT, AND OVERHEAD LUGGAGE COMPARTMENT WITH A LOCKING DEVICE OF THIS TYPE
A locking device (1) for locking a pivotably mounted door (21) of a container (20) in the closed position, with a housing (2), at least one hook (3) for hooking into a holder shaft (26), and an actuating handle (4) for unlocking the hook (3), wherein the at least one hook (3) can be actuated by the actuating handle (4) via at least one driver (6) in such a way that, upon movement of the actuating handle (4), the at least one hook (3) is movable out of the closed position, wherein the actuating handle (4) is freely movable about a predefined angular range (Δα), before the at least one hook (3) can be unlocked, and with at least one display (5) for identifying an incompletely locked state of the door (21), and an overhead luggage compartment (22) with a locking device (1) of this type. The at least one display (5) is arranged on at least one lateral outer surface (15) of the actuating handle (4) and substantially perpendicularly with respect to the second rotational axis (D2) for the actuating handle (4).
E05B 41/00 - Locks with visible indication as to whether the lock is locked or unlocked
E05C 3/16 - Fastening devices with bolts moving pivotally or rotatively with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch
2.
LOCKING DEVICE FOR A DOOR, IN PARTICULAR AIRCRAFT INTERIOR DOOR
Locking device (1) for locking a door (2, 2a), having: an adjustable actuating element (3) and a locking element (4) which is connected thereto and, by adjustment of the actuating element (3), is movable between a closed position (SS) closing the door (2, 2a) and an open position (SO) releasing the door (2, 2a), wherein a delay means (8) is provided which, in a starting state (ZA), blocks an adjustment of the locking element (4) from the closed position (SS) into the open position (SO) and, in an end state (ZE), releases same, wherein the actuating element (3), depending on position (P1, P2), keeps the delay means (8) in the starting state (ZA) or releases the transfer thereof into the end state (ZE), wherein, during a delay time, the delay means (8) is designed for transfer from the starting state (ZA) into the end state (ZE), by means of a change in the position of the actuating element (3), such that, after expiry of the delay time, the locking element (4) is movable from the closed position (SS) into the open position (SO).
A luggage compartment for an aircraft, comprising: a luggage compartment housing enclosing a storage space for a piece of hand luggage, a door part, a pivoting device, by means of which the door part can be pivoted between a closed position closing a loading opening of the luggage compartment housing and an open position releasing the loading opening of the luggage compartment housing, wherein the door part comprises a recess at an upper corner region, so that an adjoining section of the door part at the side of the recess is guided into the interior of the storage space during transfer from the closed position to the open position.
Disclosed is a luggage compartment (2) for an aircraft, having: a luggage compartment housing (3) that encloses a storage space (8) for a piece of hand luggage, a door part (9), a pivoting device (10), with which the door part (9) can pivot between a closed position, which closes off a loading opening (12) of the luggage compartment housing (3), and an open position which releases the loading opening (12) of the luggage compartment housing (3), wherein the door part (9) has a recess (17) in an upper comer region, so that a section (9A) of the door part (9) laterally adjoining the recess (17) is guided into the interior of the storage space (8) when transferring the door part from the closed into the open position.
The invention relates to an induction welding method for joining fiber-reinforced plastic (FRP) components, having the following steps: - arranging a first FRP component (27) and a second FRP component (28), with a first FRP component section (33) of the first FRP component (27) overlapping with a second FRP component section (34) of the second FRP component (28) so as to define an overlap region (32), and the first FRP component section (33) being an edge section (25) of the first FRP component (27); - inductively heating the first FRP component (27) and/or the second FRP component (28) in the overlap region (32) using an electromagnetic field, in particular the electromagnetic field of an inductor (2); and - welding the first FRP component (27) to the second FRP component (28) in the overlap region (32). A specific electrical resistance of the first FRP component section (33) and/or the second FRP component section (34) is adjusted in-plane so that when the welding process is carried out in the first FRP component section (33) and/or in the second FRP component section (34) an edge effect is reduced or prevented, and a specified temperature distribution (5) is created.
B29C 65/36 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
B29C 65/00 - Joining of preformed partsApparatus therefor
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
6.
INDUCTION WELDING METHOD AND DEVICE FOR INDUCTION WELDING
AVSVSAVSSS); inductively heating the joint (17) to the welding temperature using the process parameter by means of the first inductor (3) or by means of a second inductor (4) which differs from the first inductor; and welding the first join part (3) to the second join part (4) at the joint (17).
B29C 65/36 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
B29C 65/00 - Joining of preformed partsApparatus therefor
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
The invention relates to a luggage compartment (1) for an aircraft (2), having: - a luggage housing (4), - a chute (8) with a base (10) and two lateral walls (9) for receiving a piece of luggage, - a joint (14) between the luggage compartment housing (4) and the chute (8), said chute (8) being lowerable from a raised stowed position into a lowered loading position by being pivoted about the joint (14), and - a cover element (19) which closes a loading opening (16) of the chute (8) in the stowed position of the chute (8) and which releases the loading opening (16) of the chute (8) in the loading position, wherein - the cover element (19) can be moved, in particular raised, from a closing position, which closes the loading opening (16), into an open position, which releases the loading opening (16) when the chute (8) is lowered from the stowed position into the loading position.
The invention relates to an aircraft sliding door comprising: a door leaf, which is slidable between a closed position and an open position in the opening and closing direction, respectively, and has a door top part and a door bottom part, which are arranged in a pulled-out state in the closed position and in a pushed-together state in the open position; a guide rail; and a drive device having an electric motor for assisting the movement of the door leaf from the open position to the closed position, wherein the drive device has a spindle that is connected to the electric motor and is inclined with respect to the opening and closing direction such that the door leaf is automatically transferred into the open position along the spindle when the electric motor is in a de-energised state.
The invention relates to a method for joining fiber-plastic composite (FPC) components, in particular aircraft FPC components, comprising the following steps: i) providing a first and a second FPC component, the first FPC component having a recess; ii) introducing a stabilizing device into the recess of the first FPC component, the stabilizing device having a basic body with a cavity, an opening and a pressing element, which pressing element has at least partially a higher flexibility than the base body; iii) filling the cavity with a fluid, so that the pressing element is pressed against a delimiting surface of the first FPC component, which delimits the recess; iv) connecting the first FPC component to the second FPC component by joining at a connecting point, wherein a pressure force, is exerted onto the connecting point by means of the pressing element for stabilizing the form of the recess.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 33/50 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling elastic
B29C 65/70 - Joining of preformed partsApparatus therefor by moulding
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
10.
HINGE ARRANGEMENT FOR A DOOR OF AN OVERHEAD LUGGAGE COMPARTMENT
The invention relates to a hinge arrangement (1) for a door (32) of an overhead luggage compartment (26), having - a side cover panel (2), - a lever arm (3) for supporting the door (32), which lever arm is connected to the side cover panel (2) so as to pivot about a pivot axis (4) and can be pivoted between a first pivot position, which corresponds to an open position of the door (32), and a second pivot position, which corresponds to a closed position of the door (32), - a spring element (5) which is connected to the lever arm (3) is order to support a movement of the lever arm (3) between the second pivot position and the first pivot position, and - a setting element (6) by means of which pretensioning of the spring element (5) can be set.
The method relates to a cabin fitting (1) for a passenger cabin, comprising: - a first pivoting part (3), - a second pivoting part (4) which can be pivoted with respect to the first pivoting part (3) about a pivot axis (5) between an open position and a closed position, and – an electrical element (13) which is arranged on the second pivoting part (4) and can be connected to the first pivoting part (3) via an electrical connection line (15), wherein the first pivoting part (3) comprises a first contact connection element (17) and the electrical connection line (15) comprises a second contact connection element (18) which corresponds to the first contact connection element (17), wherein the first (17) and/or the second contact connection element (18) has at least one magnet (19) and the contact connection elements (17, 18) can be transferred from a disconnected position into a contact position, wherein the second contact connection element (18) can be arranged on the second pivoting part (4) such that, by transferring the second pivoting part (4) into the closed position, the contact connection elements (17, 18) are brought into the contact position and held in the contact position.
The invention relates to an overhead luggage compartment for an aircraft, comprising: a luggage compartment housing (4) having two side parts (4A), an upper part (5) and a lower part (6) which enclose a receiving space (7) for luggage; a door (8); and a hinge device (9) which is connected to each of the upper part (5) and the door (8) and by means of which the door (8) can be pivoted between an open and a closed position relative to the luggage compartment housing (4); wherein the hinge device (9) has a mounting bracket (12) having an upper mounting leg (13) and a lower mounting leg (14), wherein the upper mounting leg (13) is attached to the upper side of the upper part (5) and the lower mounting leg (14) is attached to the lower side of the upper part (5).
The invention relates to an overhead cabin fitting (1) for an aircraft, comprising: an overhead luggage compartment (3) for luggage; a ventilation device (4) having a housing (5), an air inlet (6), an air channel (7) and an air outlet (8); and a lighting device (9) having lighting elements (10); wherein the ventilation device (4) and the lighting device (9) are each arranged above the overhead luggage compartment (3), and a support (11) on which the lighting elements (10) are arranged is provided at the air outlet (8) of the ventilation device (4).
The invention relates to a luggage compartment (1) for an aircraft, comprising: a luggage-compartment housing (2); a chute (6) for receiving an item of luggage (13); a joint (10) between the luggage-compartment housing (2) and the chute (6), wherein the chute (6) can be lowered from a closed position into an open position by pivoting about the joint (10); a device (15) for automatic opening of the chute (6) both when not loaded and when loaded with the item of luggage (13), wherein the device (15) for automatic opening of the chute (6) comprises a spring device (16) having a spring element (17) which pushes the chute (6) in the direction of the open position.
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
15.
LOCKING DEVICE FOR LOCKING A PIVOTABLY MOUNTED DOOR OF A CONTAINER, IN PARTICULAR A LUGGAGE COMPARTMENT DOOR OF AN OVERHEAD LUGGAGE COMPARTMENT, AND OVERHEAD LUGGAGE COMPARTMENT WITH A LOCKING DEVICE OF THIS TYPE
A locking device (1) for locking a pivotably mounted door (21) of a container (20) in the closed position, with a housing (2), at least one hook (3) for hooking into a holder shaft (26), and an actuating handle (4) for unlocking the hook (3), wherein the at least one hook (3) can be actuated by the actuating handle (4) via at least one driver (6) in such a way that, upon movement of the actuating handle (4), the at least one hook (3) is movable out of the closed position, wherein the actuating handle (4) is freely movable about a predefined angular range (Δα), before the at least one hook (3) can be unlocked, and with at least one display (5) for identifying an incompletely locked state of the door (21), and an overhead luggage compartment (22) with a locking device (1) of this type. The at least one display (5) is arranged on at least one lateral outer surface (15) of the actuating handle (4) and substantially perpendicularly with respect to the second rotational axis (D2) for the actuating handle (4).
E05B 41/00 - Locks with visible indication as to whether the lock is locked or unlocked
E05C 3/16 - Fastening devices with bolts moving pivotally or rotatively with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch
41 - Education, entertainment, sporting and cultural services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Conducting instructional courses; Personnel training; Arranging, conducting and organisation of seminars; Arranging and conducting of workshops [training]; Education information; Organisation of entertainment and cultural events; Information about entertainment and entertainment events provided via online networks and the Internet; Personal development training; Coaching; Business mentoring services; Organisation of sporting events. Hosting online facilities for conducting interactive discussions; Hosting platforms on the Internet.
The invention relates to an ultrasonic testing device and to a method for nondestructively testing a component, in particular a fiber-plastic composite component, having: an ultrasonic testing head; and a liquid nozzle with a liquid inlet, a liquid outlet, and an inner surface which tapers towards the liquid outlet, wherein the liquid nozzle has at least one liquid guiding rib which protrudes inwards into the sound chamber from the tapering inner surface of the liquid nozzle upstream of the ultrasonic testing head.
B05B 13/04 - Means for supporting workArrangement or mounting of spray headsAdaptation or arrangement of means for feeding work the spray heads being moved during operation
B05B 1/34 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl
G01N 29/32 - Arrangements for suppressing undesired influences, e.g. temperature or pressure variations
18.
Cascade element for a thrust reverser system of an engine
A cascade element for a thrust reverser system of an engine, more particularly a jet engine, comprises a number of mutually adjacent deflecting vanes for deflecting an air flow, at least one of the deflecting vanes being twisted about its longitudinal axis at least along a twist longitudinal portion, and an engine having a cascade element of this type and to a method for producing a cascade element of this type, wherein additive manufacturing is carried out.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 1/76 - Control or regulation of thrust reversers
Disclosed is a luggage compartment (2) for an aircraft, having: a luggage compartment housing (3) that encloses a storage space (8) for a piece of hand luggage, a door part (9), a pivoting device (10), with which the door part (9) can pivot between a closed position, which closes off a loading opening (12) of the luggage compartment housing (3), and an open position which releases the loading opening (12) of the luggage compartment housing (3), wherein the door part (9) has a recess (17) in an upper corner region, so that a section (9A) of the door part (9) laterally adjoining the recess (17) is guided into the interior of the storage space (8) when transferring the door part from the closed into the open position.
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
20.
LOCKING ELEMENT FOR RELEASABLY LOCKING A ROTATIONAL MOVEMENT OF AN ADAPTER RELATIVE TO A BODY OF A PUSH-PULL ROD, AND PUSH-PULL ROD COMPRISING SUCH A LOCKING ELEMENT
The disclosure relates to: a locking binding element for releasably locking an adapter relative to a body of a pushpull rod, said element comprising a lever arm and a pin connected to the lever arm, a snap-action element, and a latching device; and a push-pull rod comprising such a locking device. According to the disclosure, the snap-action element is rotatably connected to the lever arm. This allows a more flexible use of the locking element on the push-pull rod.
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
19 - Non-metallic building materials
20 - Furniture and decorative products
27 - Floor and wall coverings
Goods & Services
Screens for aircraft interior cabins; screens for use in the
aerospace industry. Sanitary areas and apparatus, toilet rooms and toilet
modules for sanitary use, washrooms for sanitary purpose,
shower rooms for sanitary purpose, shower cubicles, toilets
[water-closets], toilet bowls, toilet seats, automatic
toilet seats, sink units, all the aforesaid goods, for use
in the following fields: airplanes, aerospace. Airplane seats; functional rooms for aircraft interior
cabins and spacecraft interior cabins, in particular
changing rooms and changing modules, stowage compartments,
storage cabinets and storage cabinet modules; civilian
drones; aircraft interior cabins and spacecraft interior
cabins. Changing rooms and changing modules (structures), not of
metal; cockpit partitions (structures), not of metal. Stowage compartments for storage use, storage cabinets,
storage cabinet modules, for use in the following fields:
aeroplanes, aerospace. Floor mats and floor coverings for aircraft interior cabins
and spacecraft interior cabins.
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
19 - Non-metallic building materials
20 - Furniture and decorative products
27 - Floor and wall coverings
Goods & Services
Screens for aircraft interior cabins; screens for use in the
aerospace industry. Sanitary areas and apparatus, toilet rooms and toilet
modules for sanitary use, washrooms for sanitary purpose,
shower rooms for sanitary purpose, shower cubicles, toilets
[water-closets], toilet bowls, toilet seats, automatic
toilet seats, sink units, all the aforesaid goods, for use
in the following fields: airplanes, aerospace. Airplane seats; functional rooms for aircraft interior
cabins and spacecraft interior cabins, in particular
changing rooms and changing modules, stowage compartments,
storage cabinets and storage cabinet modules; civilian
drones; aircraft interior cabins and spacecraft interior
cabins. Changing rooms and changing modules (structures), not of
metal; cockpit partitions (structures), not of metal. Stowage compartments for storage use, storage cabinets,
storage cabinet modules, for use in the following fields:
aeroplanes, aerospace. Floor mats and floor coverings for aircraft interior cabins
and spacecraft interior cabins.
An on-board toilet cubicle for an aircraft, including a front long side and a rear long side; a front short side and a rear short side, which are each connected at one end to the front long side and at their other end to the rear long side, the long sides and the short sides enclosing an interior of the toilet cubicle, and the front and the rear long sides each being wider than the front and the rear short sides; a toilet unit with a toilet opening; and an L-shaped door for accessing the on-board toilet cubicle, the L-shaped door having one door leg in the front long side and one door leg in the front short side, the toilet unit arranged adjacent to the rear long side, and the door leg in the front long side being wider than the door leg in the front short side.
The invention relates to an aircraft sliding door (1) comprising: a door leaf (5), which is slidable between a closed position and an open position in the opening and closing direction, respectively, and has a door top part (5A) and a door bottom part (5B), which are arranged in a pulled-out state in the closed position and in a pushed-together state in the open position; a guide rail (9), inclined with respect to the opening and closing direction, for guiding the door leaf (5) between the closed position and the open position; and a drive device (11) having an electric motor (12) for assisting the movement of the door leaf (5) from the open position to the closed position, wherein the drive device (11) has a spindle (13), in particular a ball screw, that is connected to the electric motor (12) and is inclined with respect to the opening and closing direction such that the door leaf (5) is automatically transferred into the open position along the spindle (13) when the electric motor (12) is in a de-energised state.
The invention relates to an aircraft sliding door (1) comprising: a door leaf (5), which is slidable between a closed position and an open position in the opening and closing direction, respectively, and has a door top part (5A) and a door bottom part (5B), which are arranged in a pulled-out state in the closed position and in a pushed-together state in the open position; a guide rail (9), inclined with respect to the opening and closing direction, for guiding the door leaf (5) between the closed position and the open position; and a drive device (11) having an electric motor (12) for assisting the movement of the door leaf (5) from the open position to the closed position, wherein the drive device (11) has a spindle (13), in particular a ball screw, that is connected to the electric motor (12) and is inclined with respect to the opening and closing direction such that the door leaf (5) is automatically transferred into the open position along the spindle (13) when the electric motor (12) is in a de-energised state.
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
19 - Non-metallic building materials
20 - Furniture and decorative products
Goods & Services
Floor mats and floor coverings, namely floor runners for aircraft interior cabins and spacecraft interior cabins Video screens for aircraft interior cabins; video screens for use in the aerospace industry bath cubicles, toilet rooms and toilet modules being parts of sanitary installations; washrooms being parts of sanitary installations; shower rooms in the nature of cubicles for sanitary purpose; shower cubicles, toilets for water-closets, toilet bowls, toilet seats, automatic toilet seats; sinks, all the aforesaid goods, for use in the fields of airplanes and aerospace Airplane seats; aircraft structural parts, namely stowage compartments for storage use, storage cabinets and storage cabinet modules; civilian drones Non-metal structures, namely, changing rooms and changing modules as structures; Non-metal structures, namely, cockpit partitions Metal storage cabinets, namely, stowage compartments for storage use, storage cabinets, and storage cabinet modules, for use in the fields of airplanes and aerospace
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
19 - Non-metallic building materials
20 - Furniture and decorative products
Goods & Services
Floor mats and floor coverings, namely floor runners for aircraft interior cabins and spacecraft interior cabins Video screens for aircraft interior cabins; video screens for use in the aerospace industry bath cubicles, toilet rooms and toilet modules being parts of sanitary installations; washrooms being parts of sanitary installations; shower rooms in the nature of cubicles for sanitary purpose; shower cubicles, toilets for water-closets, toilet bowls, toilet seats, automatic toilet seats; sinks, all the aforesaid goods, for use in the fields of airplanes and aerospace Airplane seats; aircraft structural parts, namely stowage compartments for storage use, storage cabinets, and storage cabinet modules; civilian drones Non-metal structures, namely, changing rooms and changing modules as structures; Non-metal structures, namely, cockpit partitions Metal storage cabinets, namely, stowage compartments for storage use, storage cabinets, and storage cabinet modules, for use in the fields of airplanes and aerospace
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
19 - Non-metallic building materials
20 - Furniture and decorative products
27 - Floor and wall coverings
Goods & Services
(1) Video screens for aircraft interior cabins; video screens for use in the aerospace industry.
(2) Bath cubicles, water closets, and toilets being parts of sanitary installations; washrooms comprised of toilets and sinks being parts of sanitary installations; shower rooms in the nature of cubicles for sanitary purpose; shower cubicles, toilets for water-closets, toilet bowls, toilet seats, automatic toilet seats; sinks, all the aforesaid goods, for use in the fields of airplanes and aerospace.
(3) Airplane seats; aircraft structural parts, namely stowage compartments for storage use, storage cabinets, and storage cabinet modules; civilian drones.
(4) Non-metal structures, namely, changing rooms and portable changing rooms as structures; non-metal structures, namely, plastic and fibre reinforced plastic cockpit partitions.
(5) Metal storage cabinets, namely, stowage compartments for storage use, storage cabinets, and storage cabinet modules, for use in the fields of airplanes and aerospace.
(6) Floor mats and floor coverings, namely protective vinyl floor runners and rugs in the nature of floor runners for aircraft interior cabins and spacecraft interior cabins.
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
19 - Non-metallic building materials
20 - Furniture and decorative products
27 - Floor and wall coverings
Goods & Services
(1) Video screens for aircraft interior cabins; video screens for use in the aerospace industry.
(2) Bath cubicles, water closets, and toilets being parts of sanitary installations; washrooms comprised of toilets and sinks being parts of sanitary installations; shower rooms in the nature of cubicles for sanitary purpose; shower cubicles, toilets for water-closets, toilet bowls, toilet seats, automatic toilet seats; sinks, all the aforesaid goods, for use in the fields of airplanes and aerospace.
(3) Airplane seats; aircraft structural parts, namely stowage compartments for storage use, storage cabinets, and storage cabinet modules; civilian drones.
(4) Non-metal structures, namely, changing rooms and portable changing rooms as structures; non-metal structures, namely, plastic and fibre reinforced plastic cockpit partitions.
(5) Metal storage cabinets, namely, stowage compartments for storage use, storage cabinets, and storage cabinet modules, for use in the fields of airplanes and aerospace.
(6) Floor mats and floor coverings, namely protective vinyl floor runners and rugs in the nature of floor runners for aircraft interior cabins and spacecraft interior cabins.
30.
METHOD FOR JOINING FIBRE-REINFORCED PLASTIC COMPONENTS AND STABILISING DEVICE
The invention relates to a method for joining fiber-plastic composite (FPC) components (3, 4), in particular aircraft FPC components, comprising the following steps: i) providing a first (3) and a second FPC component (4), the first FPC component (3) having a recess (2); ii) introducing a stabilizing device (1) into the recess (2) of the first FPC component (3), the stabilizing device (1) having a preferably elongate basic body (10) with a cavity (11), an opening (12) and a pressing element (13), which pressing element (13) has at least partially a higher flexibility than the base body (10); iii) filling the cavity (11) with a fluid, so that the pressing element (13) is pressed against a delimiting surface (17) of the first FPC component (3), which delimits the recess (2); iv) connecting the first FPC component (3) to the second FPC component (4) by joining at a connecting point (8), wherein a pressure force (F), which is directed towards the outside, is exerted onto the connecting point (8) by means of the pressing element (13) for stabilizing the form of the recess (2). The invention also relates to a method for producing an aircraft part, to a stabilizing device (1) and to a tool having a stabilizing device (1).
The invention relates to a method for joining fiber-plastic composite (FPC) components (3, 4), in particular aircraft FPC components, comprising the following steps: i) providing a first (3) and a second FPC component (4), the first FPC component (3) having a recess (2); ii) introducing a stabilizing device (1) into the recess (2) of the first FPC component (3), the stabilizing device (1) having a preferably elongate basic body (10) with a cavity (11), an opening (12) and a pressing element (13), which pressing element (13) has at least partially a higher flexibility than the base body (10); iii) filling the cavity (11) with a fluid, so that the pressing element (13) is pressed against a delimiting surface (17) of the first FPC component (3), which delimits the recess (2); iv) connecting the first FPC component (3) to the second FPC component (4) by joining at a connecting point (8), wherein a pressure force (F), which is directed towards the outside, is exerted onto the connecting point (8) by means of the pressing element (13) for stabilizing the form of the recess (2). The invention also relates to a method for producing an aircraft part, to a stabilizing device (1) and to a tool having a stabilizing device (1).
01 - Chemical and biological materials for industrial, scientific and agricultural use
05 - Pharmaceutical, veterinary and sanitary products
Goods & Services
Liquid coatings being chemicals, namely, antimicrobial surface coatings for inhibiting and preventing the growth of microbes on various surfaces; Liquid coatings being active chemical ingredients for use as an ingredient in the manufacture of antimicrobial sprays and coatings, antibacterial sprays and coatings, and antiseptic sprays and coatings; Liquid coatings being chemical preparations for use in the manufacture of antimicrobial sprays and coatings, antibacterial sprays and coatings, and antiseptic sprays and coatings used in aircraft cabins, land vehicles, water vehicles; Liquid coatings being chemicals having the ability to prevent or inhibit the growth of microbes, bacteria, fungi, molds, algae and viruses, for use in the manufacture of plastics, coatings, resins, blends and dispersions and in the manufacture of goods made of the foregoing Disinfectants
01 - Chemical and biological materials for industrial, scientific and agricultural use
05 - Pharmaceutical, veterinary and sanitary products
Goods & Services
(1) Liquid coatings being chemicals, namely, antimicrobial surface coatings for inhibiting and preventing the growth of microbes on various surfaces; Liquid coatings being active chemical ingredients for use as an ingredient in the manufacture of antimicrobial sprays and coatings, antibacterial sprays and coatings, and antiseptic sprays and coatings; Liquid coatings being chemical preparations for use in the manufacture of antimicrobial sprays and coatings, antibacterial sprays and coatings, and antiseptic sprays and coatings used in aircraft cabins, land vehicles, water vehicles; Liquid coatings being chemicals having the ability to prevent and inhibit the growth of microbes, bacteria, fungi, molds, algae and viruses, for use in the manufacture of plastics, coatings, resins, blends and dispersions and in the manufacture of goods made of the foregoing.
(2) All-purpose disinfectants and antiseptics; all-purpose chemical coatings used as vermin destroying disinfectants; all-purpose chemical coatings used as vermin repelling disinfectants; disinfectants for sterilization; disinfecting wipes used to destroy or control micro-organisms on hard surfaces; floor liquid disinfectants.
The invention relates to a change-over coupling, change-over device and checking or processing system, comprising: a clamping element for bracing with a corresponding clamping element on the change-over adapter, at least one electrical and/or optical plug connection element for connecting to at least one corresponding electrical and/or optical plug connection element on the change-over adapter, and a fluid coupling element for connecting to a corresponding fluid coupling element on the change-over adapter. In at least one example, the fluid coupling element protrudes further in the direction of the connection with the change-over adapter than the electrical and/or optical plug connection element.
A locking device for locking a first component to a second component having a catch element for fastening to the first or second component, the catch element comprising a first latching recess; having a latching unit for fastening to the second or first component; the latching unit comprising a first latching body for engagement with the at least one latching recess of the catch element; the latching unit comprising a release element, which comprises a first receiving opening for receiving the first latching body; and the release element can be moved between a rest position, which arranges the first latching body in the first latching recess of the catch element and in the receiving opening of the release element, and a release position, which releases the engagement between the first latching body and the first latching recess of the catch element.
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
19 - Non-metallic building materials
20 - Furniture and decorative products
27 - Floor and wall coverings
Goods & Services
Screens for aircraft interior cabins; Screens for use in the aerospace industry. Sanitary areas, Toilet rooms and toilet modules, Washrooms, Shower rooms, Shower cubicles, Toilets [water-closets], Toilet bowls, Toilet seats, Automatic toilet seats, Sink units, all the aforesaid goods, for use in the following fields: Airplanes, Aerospace. Airplane seats; Functional rooms for aircraft interior cabins and spacecraft interior cabins, in particular Changing rooms and changing modules, Stowage compartments, Storage cabinets and storage cabinet modules; Civilian drones; Aircraft interior cabins and spacecraft interior cabins. Changing rooms and changing modules, not of metal; Cockpit partitions, not of metal. Stowage compartments, Storage cabinets, storage cabinet modules, for use in the following fields: Aeroplanes, Aerospace. Flooring and floor coverings for aircraft interior cabins and spacecraft interior cabins.
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
19 - Non-metallic building materials
20 - Furniture and decorative products
27 - Floor and wall coverings
Goods & Services
Screens for aircraft interior cabins; Screens for use in the aerospace industry. Sanitary areas, Toilet rooms and toilet modules, Washrooms, Shower rooms, Shower cubicles, Toilets [water-closets], Toilet bowls, Toilet seats, Automatic toilet seats, Sink units, all the aforesaid goods, for use in the following fields: Airplanes, Aerospace. Airplane seats; Functional rooms for aircraft interior cabins and spacecraft interior cabins, in particular Changing rooms and changing modules, Stowage compartments, Storage cabinets and storage cabinet modules; Civilian drones; Aircraft interior cabins and spacecraft interior cabins. Changing rooms and changing modules, not of metal; Cockpit partitions, not of metal. Stowage compartments, Storage cabinets, storage cabinet modules, for use in the following fields: Aeroplanes, Aerospace. Flooring and floor coverings for aircraft interior cabins and spacecraft interior cabins.
The invention relates to an ultrasonic testing device and to a method for nondestructively testing a component, in particular a fiber-plastic composite component, having: an ultrasonic testing head (37); and a liquid nozzle (38) with a liquid inlet (42), a liquid outlet (43), and an inner surface (45) which tapers towards the liquid outlet (43), wherein the liquid nozzle (38) has at least one liquid guiding rib (47) which protrudes inwards into the sound chamber from the tapering inner surface (45) of the liquid nozzle (38) upstream of the ultrasonic testing head (37).
B05B 1/34 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl
G01N 29/28 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details providing acoustic coupling
G01N 29/32 - Arrangements for suppressing undesired influences, e.g. temperature or pressure variations
The invention relates to an ultrasonic testing device and to a method for nondestructively testing a component, in particular a fiber-plastic composite component, having: an ultrasonic testing head (37); and a liquid nozzle (38) with a liquid inlet (42), a liquid outlet (43), and an inner surface (45) which tapers towards the liquid outlet (43), wherein the liquid nozzle (38) has at least one liquid guiding rib (47) which protrudes inwards into the sound chamber from the tapering inner surface (45) of the liquid nozzle (38) upstream of the ultrasonic testing head (37).
B05B 1/34 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl
G01N 29/28 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details providing acoustic coupling
G01N 29/32 - Arrangements for suppressing undesired influences, e.g. temperature or pressure variations
42.
AIRCRAFT AND METHOD FOR TREATING STALE AIR IN AN AIRCRAFT CABIN
The invention relates to a method for treating stale air in an aircraft cabin (4) of an aircraft (1), in particular for rendering pathogens, such as viruses, harmless, said method having the steps of: removing stale air from the aircraft cabin (4); mixing the stale air from the aircraft cabin (4) with fresh air in a mixing chamber (13), the bleed air from an engine (10) of the aircraft (1) being used as fresh air; introducing an airflow from the mixing chamber (13) into the aircraft cabin (4); heating the stale air from the aircraft cabin (4) with the heat of the bleed air of the engine to at least 56°C, preferably at least 65°C, in particular at least 75°C, before introducing the airflow from the mixing chamber (13) into the aircraft cabin (4).
The invention relates to a cascade element (1) for a thrust reverser system (22) of an engine (20), more particularly a jet engine, comprising a number of mutually adjacent deflecting vanes (2) for deflecting an air flow, at least one of the deflecting vanes (2) being twisted about its longitudinal axis (4) at least along a twist longitudinal portion (3). The invention also relates to an engine (20) having a cascade element (1) of this type and to a method for producing a cascade element (1) of this type, wherein additive manufacturing is carried out.
B29C 64/00 - Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
F02K 1/60 - Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
44.
CASCADE ELEMENT FOR A THRUST REVERSER SYSTEM OF AN ENGINE
The invention relates to a cascade element (1) for a thrust reverser system (22) of an engine (20), more particularly a jet engine, comprising a number of mutually adjacent deflecting vanes (2) for deflecting an air flow, at least one of the deflecting vanes (2) being twisted about its longitudinal axis (4) at least along a twist longitudinal portion (3). The invention also relates to an engine (20) having a cascade element (1) of this type and to a method for producing a cascade element (1) of this type, wherein additive manufacturing is carried out.
F02K 1/60 - Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
B29C 64/00 - Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
45.
Method for producing a fiber-reinforced plastic comparison body and testing method
The invention relates to a method for producing a fiber-reinforced plastic (FRP) comparison body for modeling a layer porosity for the non-destructive testing of FRP components, comprising the following steps: i. producing a first part by a. arranging a first FRP layer having a cut-out; b. arranging at least one second FRP layer on the first FRP layer; c. prehardening the assembly of the first FRP layer and the second FRP layer in order to obtain the first part; ii. producing a second part by a. arranging further FRP layers; b. pre-hardening the assembly of further FRP layers in order to obtain the second part; iii. joining the first part to the second part, the cut-out on the first part facing the second part; and iv. hardening the assembly of the first part and the second part, a layer porosity being formed at the cut-out in the first FRP layer.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
The invention relates to a method for producing a fiber-plastic composite reference body for simulating delamination for the nondestructive testing of FPC components, in particular aircraft components, comprising the following steps: i. producing a first insert by a. arranging a first FPC layer; b. forming a recess in the first FPC layer; c. procuring the first FPC layer, in order to obtain the first insert; ii. producing a second insert by a. arranging a second FPC layer; b. pre-curing the second FPC layer, in order to obtain the second insert; iii. providing at least one first FPC layer and at least one second FPC layer with a first clearance and a second clearance; iv. inserting the first insert and the second insert into the respective clearance of the corresponding FPC layer; v. curing the arrangement, a delamination being simulated at the recess of the first insert.
B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
B32B 3/30 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer formed with recesses or projections, e.g. grooved, ribbed
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B64F 5/60 - Testing or inspecting aircraft components or systems
The invention relates to an on-board toilet cubicle (1), in particular an on-board toilet cubicle for an aircraft, comprising: a front long side (2) and a rear long side (3); a front short side (4) and a rear short side (5), which are each connected at one end to the front long side (2) and at their other end to the rear long side (3), the long sides (2, 3) and the short sides (4, 5) enclosing an interior (8) of the on-board toilet cubicle (1), and the front and the rear long sides (2, 3) each being wider than the front and the rear short sides (4, 5); a toilet unit (7) with a toilet opening (10); and an L-shaped door (11) for accessing the on-board toilet cubicle (1), the L-shaped door (11) having one door leg (12) in the front long side (2) and one door leg (13) in the front short side (4), the toilet unit (1) being arranged adjacently to the rear long side (3), and the door leg (12) in the front long side (2) being wider than the door leg (13) in the front short side (4).
E06B 3/36 - Arrangements of wings characterised by the manner of movementArrangements of movable wings in openingsFeatures of wings or frames relating solely to the manner of movement of the wing with only one kind of movement with a single vertical axis of rotation at one side of the opening, or swinging through the opening
E04H 1/12 - Small buildings or other erections for limited occupation, erected in the open air or arranged in buildings, e.g. kiosks, waiting shelters for bus stops or for filling stations, roofs for railway platforms, watchmen's huts or dressing cubicles
The invention relates to an on-board toilet cubicle (1), in particular an on-board toilet cubicle for an aircraft, comprising: a front long side (2) and a rear long side (3); a front short side (4) and a rear short side (5), which are each connected at one end to the front long side (2) and at their other end to the rear long side (3), the long sides (2, 3) and the short sides (4, 5) enclosing an interior (8) of the on-board toilet cubicle (1), and the front and the rear long sides (2, 3) each being wider than the front and the rear short sides (4, 5); a toilet unit (7) with a toilet opening (10); and an L-shaped door (11) for accessing the on-board toilet cubicle (1), the L-shaped door (11) having one door leg (12) in the front long side (2) and one door leg (13) in the front short side (4), the toilet unit (1) being arranged adjacently to the rear long side (3), and the door leg (12) in the front long side (2) being wider than the door leg (13) in the front short side (4).
E04H 1/12 - Small buildings or other erections for limited occupation, erected in the open air or arranged in buildings, e.g. kiosks, waiting shelters for bus stops or for filling stations, roofs for railway platforms, watchmen's huts or dressing cubicles
E06B 3/36 - Arrangements of wings characterised by the manner of movementArrangements of movable wings in openingsFeatures of wings or frames relating solely to the manner of movement of the wing with only one kind of movement with a single vertical axis of rotation at one side of the opening, or swinging through the opening
49.
LOCKING ELEMENT FOR RELEASABLY LOCKING A ROTATIONAL MOVEMENT OF AN ADAPTER RELATIVE TO A BODY OF A PUSH-PULL ROD, AND PUSH-PULL ROD COMPRISING SUCH A LOCKING ELEMENT
The invention relates to: a locking binding element (1) for releasably locking an adapter (3) relative to a body (4) of a push-pull rod (1), said element comprising a lever arm (5) and a pin (6) connected to the lever arm (5), a snap-action element (7), and a latching device (8); and a push-pull rod (2) comprising such a locking device (1). According to the invention, the snap-action element (7) is rotatably connected to the lever arm (5). This allows a more flexible use of the locking element (1) on the push-pull rod (2).
F16G 11/12 - Connections or attachments, e.g. turnbuckles, adapted for straining of cables, ropes or wire
50.
LOCKING ELEMENT FOR RELEASABLY LOCKING A ROTATIONAL MOVEMENT OF AN ADAPTER RELATIVE TO A BODY OF A PUSH-PULL ROD, AND PUSH-PULL ROD COMPRISING SUCH A LOCKING ELEMENT
The invention relates to: a locking binding element (1) for releasably locking an adapter (3) relative to a body (4) of a push-pull rod (1), said element comprising a lever arm (5) and a pin (6) connected to the lever arm (5), a snap-action element (7), and a latching device (8); and a push-pull rod (2) comprising such a locking device (1). According to the invention, the snap-action element (7) is rotatably connected to the lever arm (5). This allows a more flexible use of the locking element (1) on the push-pull rod (2).
The invention relates to a change-over coupling (1), change-over device (26) and checking or processing system (27), in particular for the non-destructive checking of a component, comprising: a clamping element (3) for bracing with a corresponding clamping element (4) on the change-over adapter (5); at least one electrical (6a, 6b, 6c, 6d) and/or optical plug connection element (7) for connecting to at least one corresponding electrical (14a, 14b, 14c, 14d) and/or optical plug connection element (15) on the change-over adapter (5); and a fluid coupling element (8a, 8b), in particular a water coupling element, for connecting to a corresponding fluid coupling element (29a, 29b) on the change-over adapter (5); wherein the fluid coupling element (8a, 8b) protrudes further in the direction of the connection with the change-over adapter (5) than the electrical (6a, 6b, 6c, 6d) and/or optical (7) plug connection element, such that, before coming together by connecting the fluid coupling element (8a, 8b) and the corresponding fluid coupling element (29a, 29b) on the change-over adapter (5), the electrical (6a, 6b, 6c, 6d) and/or optical plug connection element (7) and the corresponding electrical (14a, 14b, 14c, 14d) and/or optical plug connection element (15) on the change-over adapter (5) are aligned with one another.
B25J 15/04 - Gripping heads with provision for the remote detachment or exchange of the head or parts thereof
B25J 19/00 - Accessories fitted to manipulators, e.g. for monitoring, for viewingSafety devices combined with or specially adapted for use in connection with manipulators
The invention relates to a change-over coupling (1), change-over device (26) and checking or processing system (27), in particular for the non-destructive checking of a component, comprising: a clamping element (3) for bracing with a corresponding clamping element (4) on the change-over adapter (5); at least one electrical (6a, 6b, 6c, 6d) and/or optical plug connection element (7) for connecting to at least one corresponding electrical (14a, 14b, 14c, 14d) and/or optical plug connection element (15) on the change-over adapter (5); and a fluid coupling element (8a, 8b), in particular a water coupling element, for connecting to a corresponding fluid coupling element (29a, 29b) on the change-over adapter (5); wherein the fluid coupling element (8a, 8b) protrudes further in the direction of the connection with the change-over adapter (5) than the electrical (6a, 6b, 6c, 6d) and/or optical (7) plug connection element, such that, before coming together by connecting the fluid coupling element (8a, 8b) and the corresponding fluid coupling element (29a, 29b) on the change-over adapter (5), the electrical (6a, 6b, 6c, 6d) and/or optical plug connection element (7) and the corresponding electrical (14a, 14b, 14c, 14d) and/or optical plug connection element (15) on the change-over adapter (5) are aligned with one another.
B25J 15/04 - Gripping heads with provision for the remote detachment or exchange of the head or parts thereof
B25J 19/00 - Accessories fitted to manipulators, e.g. for monitoring, for viewingSafety devices combined with or specially adapted for use in connection with manipulators
53.
METHOD FOR PRODUCING A FIBER-PLASTIC COMPOSITE REFERENCE BODY AND TEST METHOD
The invention relates to a method for producing a fibre-plastic-composite (FPC) reference body (26) for simulating delamination (24) for the nondestructive testing of FPC components, in particular aircraft components, comprising the following steps: i. producing a first insert (3) by a. arranging a first FPC layer (1); b. forming a recess (4) in the first FPC layer (1); c. pre-curing the first FPC layer (1), in order to obtain the first insert (3); ii. producing a second insert (9) by a. arranging a second FPC layer (25); b. pre-curing the second FPC layer (25), in order to obtain the second insert (9); iii. providing at least one first FPC layer (10) and at least one second FPC layer (12) with a first clearance (11) and a second clearance (13); iv. inserting the first insert (3) and the second insert (9) into the respective clearance (11, 13) of the corresponding FPC layer (10, 12); v. curing the arrangement, a delamination being simulated at the recess (4) of the first insert (10).
B29C 70/10 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements
B32B 3/08 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
B32B 37/00 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
B32B 41/00 - Arrangements for controlling or monitoring lamination processesSafety arrangements
The invention relates to a method for producing a fiber-reinforced plastic (FRP) comparison body (30) for modeling a layer porosity (14) for the non-destructive testing of FRP components, comprising the following steps: i. producing a first part (6) by a. arranging a first FRP layer (1) having a cut-out (2); b. arranging at least one second FRP layer (7) on the first FRP layer (1); c. pre-hardening the assembly of the first FRP layer (1) and the second FRP layer (7) in order to obtain the first part (6); ii. producing a second part (8) by a. arranging further FRP layers (9); b. pre-hardening the assembly of further FRP layers (9) in order to obtain the second part (8); iii. joining the first part (6) to the second part (8), the cut-out (2) on the first part (6) facing the second part (8); and iv. hardening the assembly of the first part (6) and the second part (8), a layer porosity (14) being formed at the cut-out (2) in the first FRP layer (1).
The invention relates to a method for producing a fibre-plastic-composite (FPC) reference body (26) for simulating delamination (24) for the nondestructive testing of FPC components, in particular aircraft components, comprising the following steps: i. producing a first insert (3) by a. arranging a first FPC layer (1); b. forming a recess (4) in the first FPC layer (1); c. pre-curing the first FPC layer (1), in order to obtain the first insert (3); ii. producing a second insert (9) by a. arranging a second FPC layer (25); b. pre-curing the second FPC layer (25), in order to obtain the second insert (9); iii. providing at least one first FPC layer (10) and at least one second FPC layer (12) with a first clearance (11) and a second clearance (13); iv. inserting the first insert (3) and the second insert (9) into the respective clearance (11, 13) of the corresponding FPC layer (10, 12); v. curing the arrangement, a delamination being simulated at the recess (4) of the first insert (10).
The invention relates to a method for producing a fiber-reinforced plastic (FRP) comparison body (30) for modeling a layer porosity (14) for the non-destructive testing of FRP components, comprising the following steps: i. producing a first part (6) by a. arranging a first FRP layer (1) having a cut-out (2); b. arranging at least one second FRP layer (7) on the first FRP layer (1); c. pre-hardening the assembly of the first FRP layer (1) and the second FRP layer (7) in order to obtain the first part (6); ii. producing a second part (8) by a. arranging further FRP layers (9); b. pre-hardening the assembly of further FRP layers (9) in order to obtain the second part (8); iii. joining the first part (6) to the second part (8), the cut-out (2) on the first part (6) facing the second part (8); and iv. hardening the assembly of the first part (6) and the second part (8), a layer porosity (14) being formed at the cut-out (2) in the first FRP layer (1).
12 - Land, air and water vehicles; parts of land vehicles
17 - Rubber and plastic; packing and insulating materials
42 - Scientific, technological and industrial services, research and design
Goods & Services
Lightweight structural parts for aircraft; land vehicles
(except bicycles); boats; rail vehicles and cable car
cabins; vehicle chassis. Lightweight insulating materials; composite materials;
fabrics of glass fibres, plastic fibres and carbon fibres;
artificial resins; pre-impregnated insulating fabrics. Technical consultancy in the field of manufacturing
construction parts from lightweight building materials of
plastic; design and construction drafting of construction
parts of lightweight building materials for aircraft, land
vehicles (except bicycles), boats, rail vehicles and cable
car cabins; material testing; raw material testing;
technical project studies.
58.
Locking device and sliding door with locking device
A locking device for locking a first component to a second component, the device having: a catch element for fastening to the first or second component; a latching unit for fastening to the second or first component; the latching unit comprising a release element; and the release element can be moved between a rest position, which arranges the first latching body in the first latching recess of the catch element and in the receiving opening of the release element, and a release position, which releases the engagement between the first latching body and the first latching recess of the catch element.
12 - Land, air and water vehicles; parts of land vehicles
17 - Rubber and plastic; packing and insulating materials
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Lightweight structural parts for aircraft; land vehicles (except bicycles), namely, automobiles; boats; rail vehicles and cable car cabins; vehicle chassis
(2) Lightweight insulating materials, namely, insulating fabrics, insulating materials made of polyethylene foam, insulating materials made of polyurethane foam, insulation materials for aircraft; finished and semifinished composite materials made of lightweight building material mainly consisting of plastic for aeroplanes, motor vehicles, boats, rail vehicles, and cable-supported cabins; sandwich-structured composite materials mainly consisting of plastic sheeting for manufacturing cabin interior components and aerostructures of aeroplanes as well as space vehicles; pre-impregnated textiles, namely glass and carbon fibres for manufacturing cabin interior components and aerostructures of aeroplanes as well as space vehicles; artificial resins in the form of sheets for manufacturing cabin interior components and aerostructures of aeroplanes as well as space vehicles; thermoplastic elastomer resins in pellet form for use in manufacture; semi-processed thermoplastic polymer resins used in manufacturing; semi-processed synthetic, conductive and thermosetting resins being coatings, sealants and insulators; semi-processed thermosetting polymer resins used in manufacturing; pre-impregnated insulating fabrics (1) Technical consultancy in the field of manufacturing construction parts from lightweight building materials of plastic; design and construction drafting of construction parts of lightweight building materials for aircraft, land vehicles (except bicycles), boats, rail vehicles and cable car cabins; material testing; raw material testing; technical feasibility and development studies in the field of manufacturing lightweight components for aeroplanes, motor vehicles, boats, rail vehicles and cable-supported cabins
12 - Land, air and water vehicles; parts of land vehicles
17 - Rubber and plastic; packing and insulating materials
42 - Scientific, technological and industrial services, research and design
Goods & Services
Lightweight structural parts for aircraft; land vehicles (except bicycles); boats; rail vehicles, namely, passenger carriages; cable car cabins; vehicle chassis Lightweight insulating materials; composite materials, namely, plastic composite material in the form of profiles, boards, sheets, blocks, rods, powder, and pellets for use in manufacturing; insulating fabrics of glass fibres, plastic fibres and carbon fibres, not for textile use; artificial resins, semi-processed; pre-impregnated insulating fabrics Technical consultancy in the field of manufacturing construction parts from lightweight building materials of plastic; design and construction drafting of construction parts of lightweight building materials for aircraft, land vehicles (except bicycles), boats, rail vehicles and cable car cabins; material testing; raw material testing; technical project studies, namely, conducting scientific feasibility studies
The invention relates to an aerodynamic profiled body for an aircraft, in particular a winglet, comprising a front profiled element having a profile front edge, a rear profiled element having a profile rear edge, and an adjusting unit, which connects the front profiled element to the rear profiled element and by means of which the rear profiled element can be moved in relation to the front profiled element, wherein the adjusting unit has a front mounting device connected to the front profiled element, a rear mounting device connected to the rear profiled element, and a force-transmitting device, which connects the front mounting device and the rear mounting device to each other.
The invention relates to an overhead luggage compartment for an aircraft, comprising an upper luggage compartment element, a lower luggage compartment element movable between a locked and an open position, a holding device for holding the lower luggage compartment element in the closed position, a lifting spring for supporting the movement of the lower luggage compartment element from the open position to the closed position, and a retaining device for fixing the lifting spring in the tensioned state in the open position of the lower luggage compartment element. An operating handle for releasing the retaining device in the open position of the lower luggage compartment element is provided, wherein the lower luggage compartment element is movable, optionally with support by the lifting spring or with the lifting spring fixed in a tensioned state, from the open position to the closed position.
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
E05F 3/10 - Closers or openers with braking devices, e.g. checksConstruction of pneumatic or liquid braking devices with liquid piston brakes with a spring, other than a torsion spring, and a piston, the axes of which are the same or lie in the same direction
E05F 3/22 - Additional arrangements for closers, e.g. for holding the wing in opened or other position
E05F 1/10 - Closers or openers for wings, not otherwise provided for in this subclass spring-actuated for swinging wings
Overhead luggage compartment for an aircraft, having an upper luggage compartment element, having a lower luggage compartment element which is movable between an open and a closed position, having a first holding device for holding the lower luggage compartment element in its closed position, and having a second holding device for holding the lower luggage compartment element in its open position, wherein an operating element is provided which is connected via a force transmission device to the second holding device to hold the lower luggage compartment element in its open position, wherein the second holding device can be switched by arrangement of the operating element from a holding position into a release position.
G01N 33/536 - ImmunoassayBiospecific binding assayMaterials therefor with immune complex formed in liquid phase
E05C 17/50 - Devices for holding wings openDevices for limiting opening of wings or for holding wings open by a movable member extending between frame and wingBraking devices, stops or buffers, combined therewith by mechanical means in which the wing or a member fixed thereon is engaged by a movable fastening member in a fixed positionDevices for holding wings openDevices for limiting opening of wings or for holding wings open by a movable member extending between frame and wingBraking devices, stops or buffers, combined therewith by mechanical means in which a movable fastening member mounted on the wing engages a stationary member comprising a single pivoted securing member
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
E05B 7/00 - Handles pivoted about an axis parallel to the wing
A hinge for articulatedly connecting first and second components, with first and second hinge parts for fastening to the first and second components, respectively, with a first pivot arm which comprises a first articulation axis on the first hinge part and a second articulation axis on the second hinge part, wherein the first hinge part comprises a longitudinal guide for the first articulation axis of the first pivot arm, and with a second pivot arm which comprises a first articulation axis on the first hinge part and a second articulation axis on the second hinge part, wherein the first hinge part comprises a damping element, wherein the first pivot arm is connected to a braking element, wherein a setting element is provided which comprises a pressing part, which acts on the damping element, and an actuating part, wherein the actuating part is in an access hole of the first hinge part.
The invention relates to a locking device (11) for locking a first component, in particular a door leaf (6), to a second component, in particular to a door frame (3), having a catch element (13) for fastening to the first or second component, the catch element (13) comprising a first latching recess (20); having a latching unit (16) for fastening to the second or first component; the latching unit (16) comprising a first latching body (21) for engagement with the at least one latching recess (20) of the catch element (13); the latching unit (16) comprising a release element (22) which comprises a first receiving opening (23) for receiving the first latching body (21); and the release element (22) can be moved between a rest position, which arranges the first latching body (21) in the first latching recess (20) of the catch element (13) and in the receiving opening (23) of the release element (22), and a release position, which releases the engagement between the first latching body (21) and the first latching recess (20) of the catch element (13). The invention also relates to a sliding door (1) having such a locking device (11).
The invention relates to a locking device (11) for locking a first component, in particular a door leaf (6), to a second component, in particular to a door frame (3), having a catch element (13) for fastening to the first or second component, the catch element (13) comprising a first latching recess (20); having a latching unit (16) for fastening to the second or first component; the latching unit (16) comprising a first latching body (21) for engagement with the at least one latching recess (20) of the catch element (13); the latching unit (16) comprising a release element (22) which comprises a first receiving opening (23) for receiving the first latching body (21); and the release element (22) can be moved between a rest position, which arranges the first latching body (21) in the first latching recess (20) of the catch element (13) and in the receiving opening (23) of the release element (22), and a release position, which releases the engagement between the first latching body (21) and the first latching recess (20) of the catch element (13). The invention also relates to a sliding door (1) having such a locking device (11).
A control surface element for an aircraft, more particularly a spoiler, comprising an upper outer skin element that has an outer air flow face; comprising a lower outer skin element; comprising at least one reinforcement rib; and comprising a core element made of a foam material; wherein the reinforcement rib is positioned between two core segments of the core element.
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
B32B 5/18 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
B32B 27/06 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
B29K 79/00 - Use of other polymers having nitrogen, with or without oxygen or carbon only, in the main chain, as moulding material
B29K 105/04 - Condition, form or state of moulded material cellular or porous
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
Overhead luggage compartment (1) for an aircraft, with an upper luggage compartment element (2), with a lower luggage compartment element (3) which is movable between an open and a closed position, and with a spring and damping device (9) which has a spring element (10) and a damping element (11) and is connected to a side panel (6) of the upper luggage compartment element (2) and to a side wall (5) of the lower luggage compartment element (3), wherein the spring element (10) is arranged outside the damping element (11) in a manner offset with respect to the damping element (11) in a direction (13) parallel to the main plane of the side panel (6) of the upper luggage compartment element (2) and the side wall (5) of the lower luggage compartment element (3).
Folding table, in particular for an aircraft, with a frame preferably to be installed in an armrest or in a side-panelling in the aircraft, with a support device for a table top, with a displacement device for displacing the support device along the frame from a stowed position to a deployed position, with a folding device for folding a support element of the support device from the deployed position to a use position, and with a drive device for assisting the displacement device in displacing the support device from the stowed position to the deployed position, wherein the drive device comprises a linear drive element which is connected to the displacement device via a cable pull device.
The invention relates to an aerodynamic profiled body (1) for an aircraft, in particular a winglet, comprising a front profiled element (2) having a profile front edge (4a), a rear profiled element (3) having a profile rear edge (3a), and an adjusting unit (7), which connects the front profiled element (2) to the rear profiled element (3) and by means of which the rear profiled element (3) can be moved in relation to the front profiled element (2), wherein the adjusting unit (7) has a front mounting device (8) connected to the front profiled element (2), a rear mounting device (9) connected to the rear profiled element (3), and a force-transmitting device (10), which connects the front mounting device (8) and the rear mounting device (9) to each other.
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
The invention relates to an aerodynamic profiled body (1) for an aircraft, which comprises a front profiled element (2) with a profile leading edge (4a) and a rear profiled element (3) with a profile trailing edge (3a). The invention aims to enable the aerodynamic profiled body (1) to adapt the profile geometry inflight with constructively simple means and without significantly affecting the airflow around the profile. This is solved by the aerodynamic profiled body (1) comprising an adjusting unit (7) that connects the front profiled element (2) to the rear profiled element (3) and by means of which the rear profiled element (3) is adjustable relative to the front profiled element (2), wherein the adjusting unit (7) comprises a front mounting device (8) that is connected to the front profiled element (2), a rear mounting device (9) that is connected to the rear profiled element (3) and a force-transmitting device (10) that connects the front mounting device (8) and the rear mounting device (9) to one another, the force-transmitting device (10) comprises an elastically deformable leaf spring element (11), wherein the adjusting unit (7) comprises a drive for transmitting a torque to the elastically deformable leaf spring element (11), wherein the leaf spring element (11) is essentially arranged centrally between a profile upper side (2a; 3a) and a profile underside (2b; 3b). The aerodynamic profiled body (1) can be used as a winglet.
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
B64C 23/06 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
The invention relates to a fan case for an aircraft engine in the region of the fan thereof, comprising a plurality of substantially cylindrically arranged fiber-reinforced plastic layers that are joined together, wherein a reinforcement ply made of a glass fiber-reinforced plastic is disposed between an inner layer and an outer layer. According to the invention, the reinforcement ply consists of at least 20 plies of a glass fiber-reinforced plastic, and that deformation layers are disposed on both sides of the reinforcement ply, which deformation layers have a lower strength than the reinforcement ply.
B32B 17/04 - Layered products essentially comprising sheet glass, or fibres of glass, slag or the like in the form of fibres or filaments bonded with or embedded in a plastic substance
B32B 17/06 - Layered products essentially comprising sheet glass, or fibres of glass, slag or the like comprising glass as the main or only constituent of a layer, next to another layer of a specific substance
B32B 17/10 - Layered products essentially comprising sheet glass, or fibres of glass, slag or the like comprising glass as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 5/24 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F04D 29/52 - CasingsConnections for working fluid for axial pumps
The invention relates to a control surface element for an airplane, in particular a spoiler, comprising a composite fiber element that has a surface around which air flows, a mounting device for movably mounting the composite fiber element on a structural component, and a reinforcing structure for reinforcing the composite fiber element. The reinforcing structure comprises at least one reinforcing element which is integrally formed with the composite fiber element. The reinforcing structure comprises a primary reinforcing element which is designed to receive main loads and which is connected to at least one secondary reinforcing element that is designed to receive secondary loads. The composite fiber element comprises a recess for integrally forming the primary reinforcing element.
The invention relates to a casing for an aircraft engine, in particular a bypass pipe or fan casing, consisting of a plurality of hardened prepreg plies in which the fibers are oriented differently, and to a method for producing a casing of said type. In order to improve the resistance properties of the casing, especially in fire resistance tests, and reduce the amount of wasted prepreg material, at least one reinforcement ply is provided that consists of a prepreg strip having several windings, and the prepreg strip of each reinforcement ply includes a lateral overlapping portion.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
The invention relates to a folding table (1), in particular for an aircraft (1"), having a frame (2), preferably for installation in an armrest or in side cladding (1') in the aircraft (1"), having a supporting device (5) for a tabletop (5'), having a displacement device (7) for displacing the supporting device (6) along the frame (2) from a stowed position into a withdrawal position, having a folding device (8) for folding a supporting element (6) of the supporting device (5) out of the withdrawal position into a position of use, wherein the displacement device (7) has a guide device (16) each on opposite sides of the frame (2), wherein the guide devices (16) each have a guide rail (18) connected to the frame (2) and a guide carriage (17) that can be moved along the guide rail (18). Arranged between a track (21) of the guide rail (18) and a track (22) of the guide carriage (17) are rolling elements (23), which are accommodated in recesses (24) in a rolling-element cage (25).
The invention relates to an overhead luggage compartment (1) for an aircraft, comprising an upper luggage compartment element (2), a lower luggage compartment element that is movable between a locked and an open position, a holding device (11) for holding the lower luggage compartment element in the closed position thereof, a lifting spring (9) for supporting the movement of the lower luggage compartment element (3) from the open position to the closed position, and a retaining device (16) for fixing the lifting spring (9) in the tensioned state in the open position of the lower luggage compartment element (3). An operating handle (15) for releasing the retaining device (16) in the open position of the lower luggage compartment element (3) is provided, wherein the lower luggage compartment element (3) is movable, optionally with support by the lifting spring (9) or with the lifting spring (9) fixed in a tensioned state, from the open position in the direction of the closed position.
The invention relates to an overhead luggage compartment (1) for an aircraft, comprising an upper luggage compartment element (2), a lower luggage compartment element that is movable between a locked and an open position, a holding device (11) for holding the lower luggage compartment element in the closed position thereof, a lifting spring (9) for supporting the movement of the lower luggage compartment element (3) from the open position to the closed position, and a retaining device (16) for fixing the lifting spring (9) in the tensioned state in the open position of the lower luggage compartment element (3). An operating handle (15) for releasing the retaining device (16) in the open position of the lower luggage compartment element (3) is provided, wherein the lower luggage compartment element (3) is movable, optionally with support by the lifting spring (9) or with the lifting spring (9) fixed in a tensioned state, from the open position in the direction of the closed position.
An overhead luggage compartment wherein an operating element (8) is provided which is connected to a second holding device (10) by means of a force transmission device (11) in order to hold the lower luggage compartment element (3) in its open position, it being possible for the second holding device (10) to be transferred from a holding position into a release position by means of the operating element (8) and it being possible for the second holding device (10) to be transferred into the release position independently of the movement of the lower luggage compartment element (3) thus enabling a greater support of the closing process, without making it more difficult to initiate the closing process.
Overhead luggage compartment (1) for an aircraft, having an upper luggage compartment element (2), having a lower luggage compartment element (3) which is movable between an open and a closed position, having a first holding device (9) for holding the lower luggage compartment element (3) in its closed position, and having a second holding device (10) for holding the lower luggage compartment element (3) in its open position, wherein an operating element (8) is provided which is connected via a force transmission device (11) to the second holding device (10) to hold the lower luggage compartment element (3) in its open position, wherein the second holding device (10) can be switched by means of the operating element (8) from a holding position into a release position.
Hinge (1) for articulatedly connecting a first component (2) to a second component (3), with a first hinge part (4) for fastening to the first component (2) and with a second hinge part (5) for fastening to the second component (3), with a first pivot arm (6) which has a first articulation pin (8) on the first hinge part (4) and a second articulation pin (9) on the second hinge part (5), wherein the first hinge part (4) has a longitudinal guide (12) for the first articulation pin (8) of the first pivot arm (6), and with a second pivot arm (7) which has a first articulation pin (10) on the first hinge part (4) and a second articulation pin (11) on the second hinge part (5), wherein the second hinge part (5) has a further longitudinal guide (13) for the second articulation pin (11) of the second pivot arm (7), wherein the first hinge part (4) has a damping element (17), wherein the first pivot arm (6) is connected to a braking element (19), wherein a setting element (22) for setting a contact pressure between the damping element (17) and the braking element (19) is provided which has a pressing part (23), which acts on the damping element (17), and an actuating part (24) which is accessible on an outer face of the first hinge part (4), wherein the actuating part (24) of the setting element (22) is arranged in an access hole (30) in the first hinge part (4), wherein the access hole (30) terminates at an end side (4a) of the first hinge part (4) that faces the second hinge part (5).
Hinge (1) for articulatedly connecting a first component (2) to a second component (3), with a first hinge part (4) for fastening to the first component (2) and with a second hinge part (5) for fastening to the second component (3), with a first pivot arm (6) which has a first articulation pin (8) on the first hinge part (4) and a second articulation pin (9) on the second hinge part (5), wherein the first hinge part (4) has a longitudinal guide (12) for the first articulation pin (8) of the first pivot arm (6), and with a second pivot arm (7) which has a first articulation pin (10) on the first hinge part (4) and a second articulation pin (11) on the second hinge part (5), wherein the second hinge part (5) has a further longitudinal guide (13) for the second articulation pin (11) of the second pivot arm (7), wherein the first hinge part (4) has a damping element (17), wherein the first pivot arm (6) is connected to a braking element (19), wherein a setting element (22) for setting a contact pressure between the damping element (17) and the braking element (19) is provided which has a pressing part (23), which acts on the damping element (17), and an actuating part (24) which is accessible on an outer face of the first hinge part (4), wherein the actuating part (24) of the setting element (22) is arranged in an access hole (30) in the first hinge part (4), wherein the access hole (30) terminates at an end side (4a) of the first hinge part (4) that faces the second hinge part (5).
A device for a spaced apart connection of a structural element, in particular made from a fiber-reinforced plastic composite material, with a holding element by means of a connection screw, with a distance compensation element comprising a longitudinal bore for the passage of the connection screw, and with an entraining element arranged in the longitudinal bore, which entraining element can be connected to the connection screw by means of a friction fit, so that the distance compensation element can be transferred into an abutment position bridging the distance between the structural element and the holding element by screwing in of the connection screw, wherein the distance compensation element is connected to an insertion part via a screw connection, which insertion part comprises a fastening section that can be arranged within the structural element for bonding with the structural element.
F16B 43/02 - Washers or equivalent devicesOther devices for supporting bolt-heads or nuts with special provisions for engaging surfaces which are not perpendicular to a bolt axis or do not surround the bolt
F16B 5/01 - Joining sheets or plates to one another or to strips or bars parallel to them by means of fastening elements specially adapted for honeycomb panels
F16B 5/02 - Joining sheets or plates to one another or to strips or bars parallel to them by means of fastening members using screw-thread
B64C 1/12 - Construction or attachment of skin panels
A control surface element (1) for an aircraft, more particularly a spoiler, comprising an upper outer skin element (2) that has an outer air flow face (4); comprising a lower outer skin element (3); comprising at least one reinforcement rib (8); and comprising a core element (9) made of a foam material; wherein the reinforcement rib (8) is positioned between two core segments (10) of the core element (9).
A control surface element (1) for an aircraft, more particularly a spoiler, comprising an upper outer skin element (2) that has an outer air flow face (4); comprising a lower outer skin element (3); comprising at least one reinforcement rib (8); and comprising a core element (9) made of a foam material; wherein the reinforcement rib (8) is positioned between two core segments (10) of the core element (9).
The invention relates to a folding table (1), in particular for an aircraft (3), comprising a supporting device (9) for a tabletop (6), a pull-out device (11) for moving the supporting device (9) for the tabletop (6) from a substantially vertical stowing position to a substantially horizontal usage position via a pull-out position, in particular a substantially vertical pull-out position, wherein the pull-out device (11) has a guiding device (12) for guiding the supporting device (9) between the stowing position and the pull-out position, characterized in that the guiding device (12) has a substantially linear first guide track (13) for a first guide element (14) on the supporting device (9) and a second guide track (15) for a second guide element (18) on the supporting device (9), which second guide track has a linear segment (16) and an arcuate segment (17), wherein the supporting device (9) can be slid along the linear segment (16) of the second guide track (15) of the guiding device (12) from the stowing position into the pull-out position and can be pivoted along the arcuate segment (17) of the second guide track (15) of the guiding device (12) from the pull-out position into the usage position.
The invention relates to a folding table (1), in particular for an aircraft (3), comprising a supporting device (9) for a tabletop (6), a pull-out device (11) for moving the supporting device (9) for the tabletop (6) from a substantially vertical stowing position to a substantially horizontal usage position via a pull-out position, in particular a substantially vertical pull-out position, wherein the pull-out device (11) has a guiding device (12) for guiding the supporting device (9) between the stowing position and the pull-out position, characterized in that the guiding device (12) has a substantially linear first guide track (13) for a first guide element (14) on the supporting device (9) and a second guide track (15) for a second guide element (18) on the supporting device (9), which second guide track has a linear segment (16) and an arcuate segment (17), wherein the supporting device (9) can be slid along the linear segment (16) of the second guide track (15) of the guiding device (12) from the stowing position into the pull-out position and can be pivoted along the arcuate segment (17) of the second guide track (15) of the guiding device (12) from the pull-out position into the usage position.
Overhead luggage compartment for aircraft, comprising a tray, which is pivotable about an axis of rotation between a closed and an open position, and comprising a housing, which encloses the tray in the closed position and which has devices arranged thereon for fastening to a supporting structure of the aircraft, and a suspension device for a passenger service unit, and comprising a closure element. According to the invention the housing is formed by two frame parts arranged lateral to the tray, which frame parts are connected to each other by means of cross-braces, and the fastening devices and the suspension device for the passenger service unit and at least one stop element for limiting the open position of the tray are arranged on the frame parts; thus reducing the weight and height of the luggage compartment, with the volume staying the same or increasing.
B60R 7/00 - Stowing or holding appliances inside of vehicle primarily intended for personal property smaller than suit-cases, e.g. travelling articles, or maps
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
The invention relates to an overhead luggage compartment (1) for aircraft (F), comprising: a trough (3) for accommodating pieces of luggage (L), which trough can be pivoted about an axis of rotation (A) between a closed position and an open position; an enclosure (4), which encloses the trough (3) in the closed position and which has devices (5) arranged thereon for fastening to a supporting structure (S) of the aircraft (F) and has a suspension device (6) for a passenger service unit (7); and a closure element (8) for holding the trough (3) in the closed position. In order to create an easily mountable overhead luggage compartment (1) having the lowest possible weight and the greatest possible volume for accommodating the pieces of luggage (L), the enclosure (4) is formed by two frame parts (9) arranged lateral to the trough (3), which frame parts (9) are connected to each other by means of cross-braces (10), and the fastening apparatuses (5) and the suspension device (6) for the passenger service unit (7) and at least one stop element (25) for limiting the open position of the trough (3) are arranged on the frame parts (9).
Folding table (1), in particular for an aircraft, with a frame (2) preferably to be installed in an armrest or in a side-panelling (1') in the aircraft, with a support device (5) for a table top (5'), with a displacement device (7) for moving the support device (5) along the frame (2) from a stowed position to a deployed position, with a folding device (8) for folding a support element (6) of the support device (5) from the deployed position to a use position, and with a drive device (9) for assisting the displacement device (7) in moving the support device (5) from the stowed position to the deployed position, wherein the drive device (9) has a linear drive element (10) which is connected to the displacement device (7) via a cable pull device (11).
Folding table (1), in particular for an aircraft, with a frame (2) preferably to be installed in an armrest or in a side-panelling (1') in the aircraft, with a support device (5) for a table top (5'), with a displacement device (7) for moving the support device (5) along the frame (2) from a stowed position to a deployed position, with a folding device (8) for folding a support element (6) of the support device (5) from the deployed position to a use position, and with a drive device (9) for assisting the displacement device (7) in moving the support device (5) from the stowed position to the deployed position, wherein the drive device (9) has a linear drive element (10) which is connected to the displacement device (7) via a cable pull device (11).
The invention relates to a fan case (1) for an aircraft engine (2) in the region of the fan (3) thereof, comprising a plurality of substantially cylindrically arranged fiber-reinforced plastic layers that are joined together; a reinforcement ply (6) made of glass fiber-reinforced plastic is disposed between an inner layer (4) and an outer layer (5). According to the invention, the reinforcement ply (6) consists of at least 20 plies of glass fiber-reinforced plastic, and deformation layers (7) are disposed on both sides of the reinforcement ply (6), said deformation layers (7) being less strong than the reinforcement ply (6).
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
The invention relates to a fan case (1) for an aircraft engine (2) in the region of the fan (3) thereof, comprising a plurality of substantially cylindrically arranged fiber-reinforced plastic layers that are joined together; a reinforcement ply (6) made of glass fiber-reinforced plastic is disposed between an inner layer (4) and an outer layer (5). According to the invention, the reinforcement ply (6) consists of at least 20 plies of glass fiber-reinforced plastic, and deformation layers (7) are disposed on both sides of the reinforcement ply (6), said deformation layers (7) being less strong than the reinforcement ply (6).
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
94.
CASING FOR AN AIRCRAFT ENGINE, AND METHOD FOR PRODUCING A CASING OF SAID TYPE
The invention relates to a casing (1) for an aircraft engine (2), in particular a bypass pipe or fan casing, consisting of a plurality of hardened prepreg plies (3) in which the fibers (9) are oriented differently, and to a method for producing a casing (1) of said type. In order to improve the resistance properties of the casing (1), especially in fire resistance tests, and reduce the amount of wasted prepreg material, at least one reinforcement ply (5) is provided that consists of a prepreg strip (6) having several windings, and the prepreg strip (6) of each reinforcement ply (5) includes a lateral overlapping portion (7).
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
95.
CASING FOR AN AIRCRAFT ENGINE, AND METHOD FOR PRODUCING A CASING OF SAID TYPE
The invention relates to a casing (1) for an aircraft engine (2), in particular a bypass pipe or fan casing, consisting of a plurality of hardened prepreg plies (3) in which the fibers (9) are oriented differently, and to a method for producing a casing (1) of said type. In order to improve the resistance properties of the casing (1), especially in fire resistance tests, and reduce the amount of wasted prepreg material, at least one reinforcement ply (5) is provided that consists of a prepreg strip (6) having several windings, and the prepreg strip (6) of each reinforcement ply (5) includes a lateral overlapping portion (7).
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
The invention relates to a control surface element (4) for an airplane, in particular a spoiler, comprising a composite fiber element (3) that has a surface (8) around which air flows, a mounting device (5) for movably mounting the composite fiber element (3) on a structural component, and a reinforcing structure (9) for reinforcing the composite fiber element (3). The reinforcing structure (9) has at least one reinforcing element which is integrally formed with the composite fiber element (3). The reinforcing structure (9) has a primary reinforcing element (10) which is designed to receive main loads and which is connected to at least one secondary reinforcing element (11; 11', 11") that is designed to receive secondary loads. The composite fiber element (3) has a recess (15) for integrally forming the primary reinforcing element (10).
There is provided a control surface element for an airplane, such as a spoiler. The control surface element includes a composite fiber element that has a surface around which air flows. The control surface element includes a mounting device for movably mounting the composite fiber element on a structural component. The control surface element includes a reinforcing structure for reinforcing the composite fiber element. The reinforcing structure includes at least one reinforcing element that is integrally formed with the composite fiber element. The reinforcing structure includes a primary reinforcing element which is designed to receive main loads and which is connected to at least one secondary reinforcing element that is designed to receive secondary loads. The composite fiber element has a recess for integrally forming the primary reinforcing element. The at least one secondary reinforcing element is embodied as a junction of the primary reinforcing element.
An overhead luggage compartment for aircraft can be constructed as a fixed luggage compartment with a stationary housing and a pivotable flap, or as a lowerable luggage compartment with a lowerable tray, a stationary part having side walls and a movable part which is pivotable between a closed and an open position and has a closure element for retaining the movable part in the closed position. Those parts define a luggage-receiving space. Two fastening devices for fastening to a supporting structure of the aircraft on the side walls of the stationary part are disposed on the stationary part. At least one further fastening device is disposed in the region of the lower side of the rear side of the stationary part. The fastening devices are the same for the fixed luggage compartment and for the lowerable luggage compartment.
The invention relates to an overhead luggage compartment (1) for airplanes, comprising a stationary luggage compartment element (2) which can be secured to a structural element and comprising a movable luggage compartment element (3) which can be loaded with a piece of luggage, said compartments being connected together by a joint (4) such that the movable luggage compartment element (3) can be pivoted between an open position and a closed position. The overhead luggage compartment also comprises a device (10) for holding the movable luggage compartment element (3) in the open position, said device having a force transmission element (11) which is connected to the joint (4) between the stationary luggage compartment element (2) and the movable luggage compartment element (3). In the open position of the movable luggage compartment element (3), the joint (4) can be moved depending on the load state of the movable luggage compartment element (3), wherein when the movable luggage compartment element (3) is in the open position, the force transmission element (11) is arranged in an active position in the unloaded state and in an inactive position in the loaded state by means of a movement of the joint (4). In the active position of the force transmission element (11), a holding torque is exerted which counteracts the pivot of the movable luggage compartment element (3) from the open position in the direction of the closed position.
