A fastening device (1) for fastening mechanical element (2) with support structure (3) to fasten a cabin fitting element to a frame of an aircraft, fastening device (1) includes: enclosure (4) mountable to support structure (3); locator bush (5) in enclosure (4 and slidable along longitudinal axis (X) in an unlocked position of the fastening device (1); retaining element (6) around the longitudinal axis (X) and mechanically coupled to locator bush (5); and locking bolt (7) with a bolt head (8) mounting mechanical element (2) between bolt head (8) and enclosure (4), wherein locking bolt (7) is slidable into locator bush (5), and locking bolt (7) has a recess (9) on at least a section of a shell surface of locking bolt (7) and is positively-locking connectable with retaining element (6).
A wing component for an aircraft, comprising a leading edge part and a trailing edge part pivotably mounted to the leading edge part so as to pivot about a pivot axis, an actuator unit configured for moving the trailing edge part relative to the leading edge part, and a damper device configured for damping uncontrolled movement between the leading edge part and the trailing edge part. The trailing edge part comprises a first part portion and a second part portion arranged next to each other in a span direction and configured to pivot about the pivot axis individually, the damper device comprises a damping element coupled between the first part portion and the second part portion to damp relative movement of the first part portion and the second part portion.
B64C 13/38 - Transmitting means with power amplification
F16F 15/02 - Suppression of vibrations of non-rotating, e.g. reciprocating, systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating system
A network discovery method includes: sending, by a master node in a logical root hierarchy level of a data network, a discovery message including a forwarding counter to a first slave node in the data network first logical hierarchy level via a child port; increasing, by the first neighboring slave node, the forwarding counter; forwarding the discovery message with the increased forwarding counter to a second slave node in the first logical hierarchy level; receiving, by the first and second slave nodes, context information from the master node regarding the identities of the master node and the child port; determining, by the first and second slave nodes, its own functional designation based on the forwarding counter and the received context information by comparison with a mapping table; and updating the mapping table by matching the recorded functional designation in the mapping table with the first and slave node identities.
A line assembly for installation in an aircraft fuselage includes a first line section having a first diameter, a second line section having a second diameter, a set of first line brackets, and a set of second line brackets. The first line brackets include a first receiving space configured to hold the first line section and a first support portion for attaching the first line brackets to a fuselage structural part. The second line brackets include a second receiving space configured to hold the second line section and a second support portion for attaching the second line brackets to the first line section. The second line section includes a higher flexibility than the first line section. The second line section is attached to the first line section through a plurality of second line brackets arranged at a distance to and independent from the first line brackets.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
F16L 3/02 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets partly surrounding the pipes, cables or protective tubing
5.
SYSTEM AND METHOD FOR POSITIONING VEHICLE COMPONENTS FOR ASSEMBLY
A system for positioning vehicle components relative to each other on a floor to prepare an assembly. A plurality of carriers receive a vehicle component. A plurality of positioning tables have a lower portions which can be fixed to the floor and a upper portions which receive a carrier. A location device having at least one base and mobile units moveable relative to the base. At some of the positioning tables moves the respective upper portion along at least two movement axes relative to the respective lower portion to position a carrier located thereon. A transport device guides the carriers from an external position to a positioning table and to place them on the upper portion. The location device determines the positions of the respective mobile units relative to the at least one base. A position control unit controls a movement of the upper portions to a predetermined target position.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
G01S 5/02 - Position-fixing by co-ordinating two or more direction or position-line determinations; Position-fixing by co-ordinating two or more distance determinations using radio waves
G01S 5/14 - Determining absolute distances from a plurality of spaced points of known location
G01S 13/46 - Indirect determination of position data
6.
BLIND RIVET, AND SYSTEM AND METHOD FOR MAKING SEALED BLIND RIVET JOINTS
A blind rivet, for connecting workpieces, comprising a hollow, deformable rivet body with a bearing collar and a sleeve attached thereto, a rivet mandrel in the sleeve and extending through the bearing collar, having a tool holder head, and a sealing ring. The sealing ring is arranged between the bearing collar and the tool holder head and is made of a curable and not fully cured sealing material. During contraction of the blind rivet, the sealing ring is pressed axially towards the bearing collar by a tool that can be connected to the tool holder head or by a section of the rivet mandrel. The sealing ring is designed to flow radially and axially into gaps and spaces on the bearing collar and between the bearing collar and the workpieces while the sealing ring is compressed, and to adhere there.
A system for scanning or inspecting an aircraft or spacecraft surface. A ground vehicle has a first inspection device, a hovering platform has a second inspection device. The first inspection device is on a first arm of the ground vehicle. The ground vehicle comprises a vertical pole and a transverse holding element extends therefrom. The hovering platform is electrically connected to the ground vehicle through a cable for transferring electrical power and/or data to the hovering platform. The vertical pole and/or transverse holding element carry the cable. The hovering platform is flexibly held on the vertical pole and/or the transverse holding element through the cable or an additional component. The inspection devices determine a characteristic of the surface and identify points of shape deviation by comparison with an intended characteristic. The system successively inspects the surface through the inspection devices being arranged in different heights at the same time.
A method for operating an on-board water supply and distribution system of an aircraft for supplying water includes a central tank, consumer assemblies with a supply device and a buffer tank, pump operable in a supply mode and reverse mode, filter device, and high-pressure conduit system. The central tank connects to the pump's upstream side. The conduit system connects the downstream side and consumer assemblies. The pump in supply mode delivers water from the downstream side to the buffer tank. In reverse mode, the pump can convey water from the downstream side to the upstream side. The method includes operating the pump in supply mode so water from the central tank goes to a consumer assembly in a first time interval to fill the buffer tank, and operating the pump in reverse mode in a second time interval so water from the buffer tank passes through the filter device.
A trailing edge system for a wing of an aircraft comprises a flap device arrangement configured for being mounted at a trailing edge of an aircraft wing, wherein at least two movable flap devices of the flap device arrangement are spaced apart from each other. A torque element is connecting the movable flap devices for transmitting a torque to the movable flap devices in order to actuate a rotational movement of the movable flap devices. An actuator for rotationally driving the torque element is provided. Also a method of operating control surfaces of an aircraft wing and an aircraft and aircraft wing with such a system.
A water tank for operation in an aircraft includes a rigid tank shell, and a pressure compensation mechanism to equalize a pressure inside of the rigid tank shell with an environment. The pressure compensation mechanism includes a shutoff member to move between a closed position, a first open position allowing air to enter the rigid tank shell and a second open position allowing air to leave the rigid tank shell.
A system for determining the number of passengers in a vehicle, comprising a plurality of sensors arranged to collect data concerning a cabin of the vehicle, wherein the plurality of sensors comprises at least one mm-wave-radar-sensor, and a computation unit, wherein the computation unit is connected to the plurality of sensors and configured to evaluate the data collected by the plurality of sensors in order to determine the number of passengers within the vehicle. Also provided is the vehicle with the system and a method for determining the number of passengers in the vehicle.
A method for operating an on-board water supply and distribution system of an aircraft for supplying water includes a central water tank, first consumer assemblies with buffer tanks each including a heater to heat up water in the buffer tank to a disinfection temperature, pump having upstream and downstream sides to operate in supply and reverse modes, and high-pressure conduit system. The central water tank connects to the pump's upstream side. The conduit system connects the downstream side with a first consumer assembly. The method includes operating the pump in supply mode where water from the central tank goes to a first consumer assembly to fill a buffer tank, operating a buffer tank heater so water heats to a predetermined disinfection temperature, and operating the pump in reverse mode so heated water passes through a part of the conduit system and the upstream side of the pump.
A cabin monument having a monument body and a transparent film which is connected to the monument body. The transparent film has a large number of light-emitting elements. Further provided is an aircraft having at least one such cabin monument and a control device.
A fluid transport device including a first line connector, second line connector and inner line component that fluidly connects the first line connector to the second line connector via respective first and second coupling ends. In a mounted state, an outer line component of the device is attached to the first line connector and to the second line connector, so the outer line component covers the first and second coupling ends. In a demounted state, the outer line component is detached from the first and second line connector, wherein the outer line component is movable relative to the inner line component to uncover the first coupling end or the second coupling end. A method for assembling and disassembling a fluid transport device is also disclosed.
A rail system for the installation of objects in a cabin of a vehicle having a base rail, an installation rail, and connecting devices for connecting the base rail and the installation rail to one another in a mutually parallel orientation. The base rail has a bottom side, with a securing portion for securing the base rail on a structural component of the vehicle, and a top side. The installation rail has an installation surface on which the objects can be mounted and connected to the installation rail. The rail system is configured to position the installation surface with a predetermined spacing to the top side such that at least one lateral intermediate space is formed between the installation surface and the base rail for the purposes of form-fittingly holding a floor panel.
A wing assembly (5) including: a fixed wing portion (7), a first high-lift device (9), a first connecting assembly (19) which allows the first high-lift device (9) to move between a retracted position and an extended position, a second high-lift device (11), a second connecting assembly (21) which allows the second high-lift device (11) to move between a retracted position and an extended position, a drive unit (23) attached to the fixed wing portion (7), and a drive assembly (25) having a first portion (27) is attached to the drive unit (23) and a second portion (29) attached to the second high-lift device (11), wherein the drive unit (23) moves the second high-lift device (11) via the drive assembly (25) between the retracted position and the extended position.
A system for producing a component or semifinished product with a fibre-reinforced foam core, includes a substrate on which the foam core having a first main surface and an opposite second main surface is to be laid; a sewing device having a needle configured to be moved at least linearly; a fibre supply device for three-dimensional supply of a fibre; and a coating device. The sewing device is configured to position the needle at the first main surface and to pierce the foam core, such that a needle tip penetrates through the first main surface and then through the second main surface. The fibre supply device is configured to position a reinforcing fibre such that the reinforcing fibre is hooked into the needle tip. The coating device is configured to coat a reinforcing fibre hooked into the needle tip with resin immediately before the reinforcing fibre enters the foam core.
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 44/56 - After-treatment of articles, e.g. for altering the shape
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
18.
END PLATE FOR CLAMPING ONE OR MORE FUEL CELLS IN A FUEL CELL ARRANGEMENT
An end plate for clamping one or more fuel cells in a fuel cell arrangement, the end plate including one or more integrated storage devices for storing electrical energy. A fuel cell arrangement includes one or more fuel cells and a clamp device for clamping the one or more fuel cells, the clamp device having an end plate including one or more integrated storage device for storing electrical energy, the end plate clamping the one or more fuel cells in the fuel cell arrangement.
MANUFACTURING METHOD FOR MANUFACTURING A PROFILE RAIL, PROFILE RAIL OBTAINABLE THEREBY, MOUNTING SYSTEM AND VEHICLE EQUIPPED THEREWITH AND USE OF THE PROFILE RAIL
A method for manufacturing a profile rail including a base made of a first material and a top portion to be exposed during use of the profile rail in the floor of a vehicle including a second material that is harder and/or less corrosive as the first material. The method includes the steps of providing the base made of the first material, coating at least the top portion of the base with the second material by a cold spray process, and machining the coating to provide a predefined surface structure of the top portion.
A wing assembly is disclosed having a fixed wing portion, a high-lift device, and a connecting assembly movably connecting the high-lift device to the fixed wing portion, such that the high-lift device is movable between a retracted position and at least one extended position. The connecting assembly includes a first connecting element, which extends from a first end portion, at which the first connecting element is rotatably connected to the fixed wing portion, to a second end portion, and a second connecting element, which extends from a first end portion, at which the second connecting element is rotatably connected to the second end portion of the first connecting element, to a second end portion.
A wing (3) for an aircraft (1) including a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5). The trailing edge high lift assembly (9) includes a flap (11) and a connection assembly (13) movably mounting the flap (11) to the main wing (5). The connection assembly (13) includes an actuator unit (35) moving the flap (11) between a retracted position and at least one extended position. The flap (11) includes a leading edge part (23) and a trailing edge part (27) mounted to the leading edge part (23) pivotable about a pivot axis (31).
A coupling kit-of-parts is provided for mounting an interior substructure to a primary structure of an aircraft. The kit includes a locking member and a mounting member. When the locking member is inserted into the mounting member, a first member part and a second member part are pushed radially outward to engage the primary structure in a form-fitting manner. When the locking member is removed, the first and second member parts are urged radially inward thereby disengaging from the primary structure.
F16B 13/06 - Dowels or other devices fastened in walls or the like by inserting them in holes made therein for that purpose with parts gripping in the hole or behind the reverse side of the wall after inserting from the front combined with expanding sleeve
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
23.
REFERENTIAL POSITIONING DEVICE INTENDED TO POSITION RELATIVE TO EACH OTHER AT LEAST ONE CABIN FLOOR GRID AND ONE SIDE SHELL OF AN AIRCRAFT IN ORDER TO ASSEMBLE A FUSELAGE BARREL OF THE AIRCRAFT
A referential positioning device configured to position relative to each other at least one cabin floor grid and one side shell of an aircraft in order to assemble a fuselage barrel of the aircraft is disclosed having at least one fixing support for fixing the referential positioning device to the top of an alignment post of an assembly platform, and a partially spherical support having a spherical surface (S) intended to receive the V-shaped surface of an end of an arm of a transport system for a cabin floor grid of an aircraft. The referential positioning device makes it possible to arrange the cabin floor grid precisely on the assembly platform with respect to the other elements of the fuselage barrel.
A wing for an aircraft includes a leading edge, a trailing edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create a wing box with the upper skin and the lower skin, and at least one droop nose at the leading edge, wherein the at least one droop nose is coupled with a forward end of a hinge arm that extends in a chordwise direction, and wherein a rearward end of the hinge arm is swivably supported directly at or in the wing box.
B64C 3/48 - Varying camber by relatively-movable parts of wing structures
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
25.
DEVICE FOR LATCHING A DOOR OF AN OXYGEN MASK CONTAINER IN AN AIRCRAFT CABIN
A device for latching a door of an oxygen mask container in an aircraft cabin includes a door for an oxygen mask container having an inner side, outer side and hinge, a first latching device attached to the inner side, and a second latching device movable relative to the first latching device to selectively engage or disengage the second latching device. A retaining element is attachable to a structural part inside the oxygen mask container. A test control device on the inner side of the door includes a movable hook element and can move the hook element to a first or second position. The hook element can engage the retaining element in the first position to restrict an opening degree of the door. The hook element is placed in the second position such that when the door is opened, the hook element is moved past the retaining element.
A mandrel is 3D-printed from a thermoplastic material that exhibits a glass transition. The mandrel has a mandrel wall made from the thermoplastic material and a cavity. The mandrel is coated with an elastomer coat and a fiber material is arranged on the elastomer coat. A composite part is formed from the fiber material by inserting the mandrel into a mold, pressurizing the mandrel, and heating the mold to a mold temperature greater than the glass transition temperature without melting the mandrel wall. The mandrel expands and presses the fiber material against the mold. The composite part is cured by increasing the mold temperature and simultaneously melting the mandrel wall.
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 33/48 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details 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
B29C 33/52 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles soluble or fusible
A wing for an aircraft includes a leading edge as a first chordwise edge, a trailing edge as a second chordwise edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create wing box with the upper skin and the lower skin, and at least one of a fluid line, an electrical line, and a mechanical power transfer device attached inside or reaching into the wing box at least partially.
Methods for fastening two fiber composite parts to each other with a fastener that includes electroactive polymer material. The parts have an opening within an inner circumferential surface. Fibers protrude from the inner circumferential surface into the opening and interlock with chains of micrograins of the electroactive polymer material. The fastener may switch between an activated state and a deactivated state and in the deactivated state, the fastener engages the exposed fibers.
A coupling for a hydrogen pipe for coupling multi-wall pipe sections which is equipped with an inner seal and an outer seal and a pressing device that presses the pipe sections together. The hydrogen pipe coupling arrangement comprises at least one spring element configured to apply a pre-pressing force onto the inner seal in addition to a pressing force of the pressing device.
A method for detecting aircraft surface portion characteristics including applying a marking sticker with grid markings adjacent to the aircraft surface portion, simultaneously optically detecting one region of the marking sticker and one region of the surface portion via an optical detection device, removing the optical detection device, hand guiding a sensing device to a predetermined position relative to the marking sticker within the surface portion and detecting a material characteristic there, correlating the detected material characteristic with the respective position in a data set, and generating and storing a damage map in which an optically detected structure of the surface portion is combined with the additional material characteristic at the one position, wherein guiding the sensing device includes projecting a laser line outwardly from the sensing device and moving the sensing device to align the laser line with at the grid marking.
G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object - Details
A compartment for a cabin in a vehicle includes a compartment enclosure assembly defining an outer boundary of the compartment and having a receiving space, a stop body supported on or in the compartment enclosure assembly, and a locking device. The receiving space is accessible from a front of the compartment enclosure assembly, wherein the stop body is pivotally mounted on or in the compartment enclosure assembly about a pivot axis or slidably along an axis between a retracted position, in which the stop body does not project from the front, and an extended position, in which the stop body projects from the front to provide an end stop for a door of the compartment or for a door of an insert to be inserted into the receiving space, wherein the locking device is configured to selectively lock and unlock the stop body in its retracted position.
A honeycomb structure including a first external side, a second external side, and an anti-friction agent buffer for receiving an anti-friction agent. An opening to an anti-friction agent inlet and an opening to an air outlet are present on the first external side. This honeycomb structure may be useful in an aircraft as part of a belly-landing system for the aircraft.
A pump arrangement for providing a saturated or subcooled liquid includes a tank for saturated liquid, a heat exchanger for cooling the saturated liquid, a pump, an expansion valve, and an output for feeding saturated or subcooled liquid to a consumer. A tank outlet is in fluid communication with a liquid inlet of the heat exchanger, such that saturated liquid stored inside the tank can flow into the heat exchanger designed to sub-cool the saturated liquid. A liquid outlet of the heat exchanger is in fluid communication with a pump inlet. The expansion valve outlet is in fluid communication with a coolant inlet of the heat exchanger. An expansion valve inlet is arranged for receiving and expanding a fraction of liquid flowing through the pump arrangement and routing it into the coolant input to at least partially evaporate and receive evaporation enthalpy of the liquid to be subcooled.
F04B 15/08 - Pumps adapted to handle specific fluids, e.g. by selection of specific materials for pumps or pump parts for liquids near their boiling point, e.g. under subnormal pressure the liquids having low boiling points
F02M 59/38 - Pumps characterised by adaptations to special uses or conditions
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
34.
VARIABLE FAIRING FOR A HYDROGEN DUCT SYSTEM INSTALLATION AND USES OF THE SAME
A variable fairing for covering a hydrogen duct system installation on the outside of an aircraft part, wherein the fairing comprises at least one fairing body to be mounted on the aircraft part, an air inlet and an air outlet and at least one movable closure mechanism configured to open and close a top portion of the fairing.
A semi-active noise control system includes a layer configured to be part of an interior panel of an aircraft The layer includes conductive tracks, a driver arrangement, tuned mass dampers, and sensors. Each tuned mass damper has an eigenfrequency that depends on a control signal applied to the tuned mass damper and is connected to the driver arrangement via a conductive track and configured to receive control signals from the driver arrangement. Each sensor is connected to the driver arrangement via a conductive track and is configured to sense vibrations and/or acoustic sounds and send measurement signals to the driver arrangement. The driver arrangement is configured to analyze the measurement signals and to generate and send control signals to the tuned mass dampers such that the eigenfrequency of the tuned mass dampers is matched with the frequency of the vibrations and/or acoustic sounds sensed by the sensors.
A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube, includes a composite structure, which has a hollow-cylindrical, helically wound mesh of fiber strands which form an inner shell surface configured to receive the structural profile, wherein the fiber strands are respectively embedded in a matrix material, which has an electroactive polymer which can be stretched along a longitudinal extent of the fiber strands by application of an electrical voltage, such that the composite structure can be expanded by application of the electrical voltage to introduce the structural profile into the composite structure and can be shrunk by switching off the electrical voltage to fix the structural profile on the shell surface in the composite structure.
B29C 63/42 - Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor by liberation of internal stresses using tubular layers or sheathings
B29C 63/00 - Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor
F16L 3/12 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing
37.
HYDROGEN ACCUMULATION CONTROL SYSTEM FOR MONITORING AND CONTROLLING LEAKED HYDROGEN WITHIN AN INTERIOR SPACE
A hydrogen accumulation control system for monitoring and controlling leaked hydrogen within an interior space, in particular of an aircraft, includes a hydrogen detection system installed within the interior space to detect the presence of gaseous hydrogen in the interior space and to provide occurrence data on the detected hydrogen within the interior space, a system control configured to assess the occurrence data and to determine and initiate a remedial procedure for reduction of the detected hydrogen within the interior space, and a venting system configured to vent the interior space from the detected hydrogen according to the remedial procedure.
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B01D 53/22 - Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by diffusion
A mounting member configured to support a cabin component to be mounted to a mounting rail. The rail mounting arrangement comprises a disengagement locking mechanism that prevents a removal of the mounting member along a transversal direction of the mounting rail, while still allowing movement along the longitudinal direction. The rail mounting arrangement includes a securing mechanism that is configured to secure the mounting member at the desired location along the mounting rail.
A sealing device for covering an aperture in a wing part of an aircraft. The sealing device has a cover plate covering at least a part of the aperture and having an outer surface delimited by a cover plate edge, and at least one holding device coupled with the cover plate. The at least one holding device having a resilient element, the at least one holding device resiliently holds the cover plate in a distance to an actuation element. The distance is variable in a first direction substantially perpendicular to the outer surface. The at least one holding device holds the cover plate in a substantially fixed spatial alignment in a second direction perpendicular to the first direction. The resilient element urges the cover plate towards the actuation element in a mounted state of the sealing device.
A panel for covering a part of a structure in an interior space of an aircraft is disclosed including a main panel section having an interior side and an exterior side, and at least one attachment device coupled with the exterior side. The main panel section is exclusively made from a single thermoplastic material, and the at least one attachment device is adapted for attaching the panel to the respective interior structure.
A bipolar plate for use in a fuel cell device, the bipolar plate including an integrated ply, the ply including one or more electrically conductive fibers and being configured and electrically connectable to a power supply such that the one or more fibers are heated when power is supplied to the ply.
A method for producing an armored wall for an aircraft by determining an available thickness of the wall, an allowable areal mass of the wall, and an available space for a wall deformation due to ballistic impact. The method includes retrieving a parameterization of a plurality of armoring materials, which includes a parameter for each of a plurality of material characteristics for each of the plurality of armoring materials. The method also includes comparing the available wall thickness, the allowable areal mass, and the available deformation space with a corresponding parameter of the parameterization, selecting one armoring material for the wall from the plurality of armoring materials based on a result of comparing, and manufacturing a wall by supplementing the selected armoring material to a basic wall structure.
An aircraft cabin dismantling and recycling system including: a device (10) for transferring aircraft cabin parts to secondary utilization is provided that includes a data input (12), a data processor (14) and an output interface (16). The data input provides cabin base types from a database and initial equipment installation states of the aircraft cabin from an installation state database. The data processor is configured to identify a cabin base type for a current part of the aircraft cabin; assign an initial equipment installation state of the aircraft cabin; estimate changes of the current part and determine a current parameter; identify implementable transferring options for the current part of the aircraft cabin from a database of transferring options based on the current parameter, and select one of the identified transferring options.
A support arrangement for a leading-edge high lift device comprising a support arm for movably supporting the leading-edge high lift device on a wing structure. In order to accommodate the supply of the leading-edge high lift device with a fluid such as an anti-ice fluid, for example pressurized hot air, the support arm is configured as a fluid conduit for feeding fluid to and/or from the leading-edge high lift device. The leading-edge high lift device may be configured as a droop nose device.
Leakage detection for pressurized fuel tanks. To provide facilitated leakage detection, a leakage detection device for pressurized fuel tanks for storing a pressurized fuel includes a fuel-sensing tracer and a light-wave conducting component. The fuel sensing tracer is configured to alter its optical properties in the presence of a predetermined fuel. The light-wave conducting component is in optical contact with the fuel sensing tracer. Light travelling within the light-wave conducting component is modifiable by altered optical properties of the fuel sensing tracer such that modified light is indicative of the presence of fuel at the location of the fuel sensing tracer.
G01M 3/04 - Investigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point
G01M 3/22 - Investigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using special tracer materials, e.g. dye, fluorescent material, radioactive material for valves
B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions
46.
SEALING DEVICE FOR COVERING AN APERTURE IN A WING PART
A sealing device for covering an aperture in a wing part of an aircraft is disclosed having an interface section for fixedly mounting the sealing device to a surface of the wing part adjacent the aperture, a connecting section, and a cover section for covering at least a part of the aperture. The connecting section is arranged between the interface section and the cover section and connects the interface section and the cover section. The connecting section is adapted to resiliently hold the cover section in a predetermined orientation relative to the interface section to cover at least a part of the aperture. The cover section comprises a contact portion for contacting a surface of an actuation element that protrudes through the aperture.
A load introduction system is disclosed including an aerodynamic structure component having an upper skin section and a lower skin section, an attachment unit and a load introduction unit configured to couple the attachment unit to the aerodynamic structure component. The load introduction unit includes a longitudinal connection element with its first end positioned at the upper skin section. The longitudinal connection element extends through the lower skin section such that its second end is positioned outside of the aerodynamic structure component. The first end is anchored to the upper skin section and the second end is anchored to the attachment unit such that the longitudinal connection element forces the attachment unit against the lower skin section.
A actuator arrangement is disclosed in which the high-lift device support that supports and guides movement of a high-lift device, such as a flap, is in axial alignment with a control actuator assembly that controls one or more control surfaces. This allows a single support fairing to be sufficient for covering both the track member and the control actuator assembly and allowing for reduced drag and weight.
A pipe for heating a cryogenic liquefied gas, the pipe having a peripheral wall including a ply of one or more electrically conductive carbon fibers, the ply being configured and electrically connectable to a power supply such that the one or more carbon fibers are heated when power is supplied to the ply.
F16L 53/37 - Ohmic-resistance heating the heating current flowing directly through the pipe to be heated
F16L 9/10 - Rigid pipes of glass or ceramics, e.g. clay, clay tile, porcelain
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
A method for draining a water supply system onboard an aircraft which supplies water from a central water tank to consumers. Water is supplied by a supply pump from the central water tank through supply lines of a conduit system to consumers. Each consumer is associated with a supply valve for drawing water from the conduit system. The supply lines have a maximum internal diameter of 8 mm or less. The method includes closing the supply valves of all consumers, subjecting the supply lines of the conduit system at the at the supply pump to a draining pressure and sequentially opening the supply valves of all consumers for removing water from the supply lines of the conduit system. A corresponding water supply system and an aircraft are disclosed.
A method for draining a local water distribution system including a buffer, supply lines connecting one or more consumers to the buffer and consumer valves associated with the one or more consumers. The buffer is configured for locally storing water from an aircraft water supply system to be distributed to the one or more consumers. Water from the buffer can be dispensed through a consumer of the one or more consumers by opening the consumer valve associated with the respective consumer. Water is drained from the supply lines by opening the consumer valves. Water is drained from the buffer through one of the supply lines and the consumer valves or through a drain valve connecting the buffer to a wastewater system of an aircraft. A corresponding local water distribution system and an aircraft are disclosed.
A luggage compartment, for use in a vehicle, having a housing with an inner volume defining a storage space of the luggage compartment and a flap which is attached to the housing with at least one fastening device. The fastening device has a first portion attached to the flap and a second portion, wherein the second portion of the fastening device is releasably coupled to the first portion of the fastening device and attached to an outer surface of a top wall of the housing. Also a cabin component assembly with the luggage compartment and a ceiling panel arranged adjacent to the top wall of the housing of the luggage compartment and an aircraft with the cabin component assembly.
A component for an aircraft includes at least one connection interface, wherein the connection interface is configured to simultaneously establish an electrical connection and a mechanical connection. An electrical system for an aircraft and a method for connecting components for an aircraft are disclosed.
An expansion tank system for a liquid cooling system includes a first chamber for receiving a coolant, a second chamber for pressurized gas, a first gas conveying device for conveying gas from the first to the second chamber, a second gas conveying device for conveying gas from the second to the first chamber, a first pressure sensor in fluid communication with the first chamber, and a control unit connected to the first gas conveying device, the second gas conveying device and the first pressure sensor for controlling the second conveying device to selectively convey gas from the second to the first chamber if a pressure measured through the first pressure sensor is below a predefined first threshold value, and for controlling the first conveying device to convey gas from the first to the second chamber if a pressure measured through the first pressure sensor is above a second threshold value.
A fuel cell system comprises a fuel cell unit in a housing and comprising an anode part and a cathode part, a hydrogen source for supplying hydrogen to the fuel cell unit, an air supply unit for supplying air to the fuel cell unit, and a catalytic converter for catalytically converting oxygen and hydrogen to generate an inert gas mixture and supplying it to the interior of the housing. The catalytic converter comprises a cathode exhaust gas intake for receiving a cathode exhaust gas from the cathode part of the fuel cell unit. In a method for generating inert gas for a fuel cell system, a purge gas is supplied from the anode part of the fuel cell unit, and/or fresh hydrogen is supplied from a hydrogen supply unit of the fuel cell unit to the catalytic converter, to generate the inert gas mixture.
H01M 8/0662 - Treatment of gaseous reactants or gaseous residues, e.g. cleaning
H01M 8/04223 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids during start-up or shut-down; Depolarisation or activation, e.g. purging; Means for short-circuiting defective fuel cells
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
A bipolar plate for a fuel cell stack comprises a first main boundary surface and a second main boundary surface, arranged parallel and at a distance to each other and define an interior space. A plurality of lateral delimiting surfaces extend between outer edges of the first and second main boundary surfaces to enclose the interior space. At least one of the lateral delimiting surfaces comprises a plurality of lateral openings and at least one of the main boundary surfaces comprises a plurality of axial openings. Internal distribution channels are arranged inside the interior space in a distance to the first main boundary surface and the second main boundary surface, and lateral openings are in fluid connection with the axial openings through at least a part of the internal distribution channels.
H01M 8/0258 - Collectors; Separators, e.g. bipolar separators; Interconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant
57.
Fluid Transport Device And Method For Manufacturing A Fluid Transport Device
University of Ioannina-Special Account for Research Funds (Greece)
Inventor
Friedberger, Alois
Krakowski, Dariusz
Paipetis, Alkiviadis S.
Karalis, George
Abstract
A fluid transport device includes a conduit unit having a wall for separating an inside from an outside of the conduit unit. The device also includes an energy supply unit coupled to the conduit unit and configured to provide electrical energy based on a temperature gradient between the inside and the outside of the conduit unit. The device also includes a monitoring unit configured to monitor a state of the conduit unit and to generate data representative for the state of the conduit unit. The energy supply unit supplies the electrical energy to the monitoring unit, thereby enabling the monitoring unit to monitor the state of the conduit unit. A method for manufacturing a fluid transport device is also described.
ARRANGEMENT INCLUDING A FIBER-REINFORCED COMPOSITE COMPONENT OR ASSEMBLY, AIRCRAFT OR SPACECRAFT, METHOD OF PRODUCING AN ARRANGEMENT, AS WELL AS METHOD OF MONITORING STRUCTURAL INTEGRITY
An arrangement includes a fiber-reinforced composite component or assembly and a monitoring device. The composite component or assembly includes at least first and second reinforcing fiber formation sections stitched to each other using a yarn to connect the fiber formation sections along a seam, the yarn being electrically conductive along a length thereof. The monitoring device is configured and coupled to the yarn so as to be capable of sending an electrical input signal along at least a section of the yarn that forms the seam or part thereof and receiving a response signal on the yarn. Furthermore, an aircraft or spacecraft is provided including at least one arrangement of this type, as well as a method of producing an arrangement including a fiber-reinforced composite component or composite assembly, and a method of monitoring the structural integrity of a fiber-reinforced composite component or assembly.
A filling level monitoring device for monitoring a filling level of a fluid in a container includes exciter(s), sensor(s), a signal source connected to the exciter(s), a processor, at least one spatial orientation and acceleration sensor, and a filling level indicator. The device uses the signal source and the exciter(s) to couple vibrational loads having multiple frequency components into the container. Sensors measure vibrations in the container after the exciters transmit the vibrational loads into the container. The processor performs spectral analysis of the input signal and of vibration signals from the sensors, comparing these respective spectral functions to extract resonance frequencies of the container, which are based on the spatial orientation of the container. The filling level indicator calculates a current filling level of the container from the extracted resonance frequencies and a spatial orientation signal from a spatial orientation sensor by correlating the collected data with reference data.
A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position, and an actuation mechanism for moving the foldable wing tip portion. The actuation mechanism includes a drive arm mounted to the fixed wing in a manner rotatably driven about a drive axis, and the drive arm is configured to effect movement of the foldable wing tip portion between the extended position and the folded position upon rotation of the drive arm about the drive axis.
A connection system includes at least a first part and at least a second part, both comprising a connection surface and being configured to be connected to each other. A plurality of engagement elements is protruding from the connection surface of the first part and from the connection surface of the second part. For connecting different components, the parts are positioned such that their connection surfaces are facing each other. A ductile material is positioned between the connection surfaces of the parts to be connected to each other. The parts are pressed together, wherein the engagement elements are pressed into the ductile material at required positions, thereby compensating position deviations.
A fairing attachment system for a wing of an aircraft includes a high lift support structure configured to movably support a high-lift airfoil element of a wing of an aircraft relative to the wing. The system includes a fairing device extending in a lengthwise direction, configured to provide an aerodynamic housing of the high lift support structure when attached to a surface of the wing, and an adjustable attachment element configured to attach the fairing device to the high lift support structure. The adjustable attachment element is longitudinally extending and adjustable in length to compensate for tolerances of the high lift support structure relative to the wing during assembly. An aircraft wing includes the fairing attachment system. The fairing attachment system is used in a method for mounting a fairing device to a wing of an aircraft.
A multimedia distribution network, useful on board a passenger aircraft, includes a first network node configured as a head controller, a plurality of second network nodes configured as intermediate controllers connected to the first network node, and a plurality of third network nodes configured as end device controllers, each connected to one of the second network nodes. The head controller is configured to transmit a multicast stream of multimedia control signal packets to control the end device controllers to the intermediate controllers. The intermediate controllers are configured to periodically transmit unicast delay queries to the head controller, to process the received multimedia control signal packets to the end device controllers and to distribute processed multimedia control signal packets with a controllable delay based on the content of unicast delay indicator signals sent by the head controller to the intermediate controllers in response to the unicast delay queries.
H04L 65/611 - Network streaming of media packets for supporting one-way streaming services, e.g. Internet radio for multicast or broadcast
H04L 67/12 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
A wing for an aircraft has a main wing and a trailing edge high lift assembly which has a flap and a connection assembly movably mounting the flap to the main wing. The connection assembly has a first actuator unit for moving the flap between the retracted position and at least one extended position. The flap has a leading edge part and a trailing edge part pivotably mounted to the leading edge. The flap has a second actuator unit for moving the trailing edge part relative to the leading edge part within an operating range between an upper operating position and a lower operating position.
An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.
A fire detection, localization and monitoring system for a vehicle compartment, in particular of an aircraft, includes a thermal imaging camera configured to provide thermal monitoring data on heat sources within a monitored area of the vehicle compartment; an optical camera configured to provide visual monitoring data of the monitored area; and a system control configured to analyze the thermal monitoring data and to determine temperature hot spots indicating a potential fire within the monitored area based on the analyzed thermal monitoring data. The system control is further configured to provide a visual indication of determined temperature hot spots within the visual monitoring data.
A lavatory door system for a vehicle, in particular an aircraft, with a lavatory door; a pneumatic actuator configured to open and close the lavatory door based on a differential pressure, wherein the pneumatic actuator is coupled to a vacuum toilet system of the vehicle to generate the differential pressure; and an operating interface configured to receive a user control operation and to selectively release the differential pressure from the vacuum toilet system for operation of the pneumatic actuator based on the received user control operation.
E05F 15/51 - Power-operated mechanisms for wings using fluid-pressure actuators for folding wings
E05B 81/78 - Detection of handle operation; Detection of a user approaching a handle; Electrical switching actions performed by handles as part of a hands-free locking or unlocking operation
E05B 83/00 - Vehicle locks specially adapted for particular types of wing or vehicle
E05F 15/73 - Power-operated mechanisms for wings with automatic actuation responsive to movement or presence of persons or objects
A method of performing a configuration procedure for first and second tire pressure monitoring devices. The method includes loading the first tire pressure monitoring device with first configuration data, and subsequently transmitting, from the first tire pressure monitoring device, a first configuration data signal which encodes the first configuration data. The method includes subsequently loading the second tire pressure monitoring device with second configuration data, and subsequently ending the configuration procedure without transmitting a second configuration data signal which encodes the second configuration data.
A method of configuring a network of tire monitoring devices using an untrusted device is provided. An untrusted device transmits first configuration data to a first tire monitoring device, and then receives a first input verifying that the first configuration data has been loaded to the first tire monitoring device and matches expected first configuration data. The untrusted device transmits second configuration data to a second tire monitoring device, and receives a second input verifying that the second configuration data has been loaded to the second tire monitoring device and matches expected second configuration data. The untrusted device transmits a command initializing generation of a cryptographic parameter by the first tire monitoring device, and causes the cryptographic parameter to be exchanged with the second tire monitoring device such that secure future communication is established between the first and second tire monitoring devices.
B60C 23/04 - Signalling devices actuated by tyre pressure mounted on the wheel or tyre
H04L 67/12 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
A method for temporarily closing openings in an aircraft part during a manufacturing process by providing a first part that has a first opening and positioning a temporary closure member inside that first opening. The temporary closure member has an RFID tag that has stored on it a unique identification. At a later stage in the aircraft manufacturing process, a scanning device is used to scan for the RFID tag based on the identification. The temporary closure member is removed from the first opening and subsequently replaced by a permanent member.
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control (DNC), flexible manufacturing systems (FMS), integrated manufacturing systems (IMS), computer integrated manufacturing (CIM)
G06K 19/077 - Constructional details, e.g. mounting of circuits in the carrier
71.
FIRE DETECTION SYSTEM AND METHOD FOR MONITORING AN AIRCRAFT COMPARTMENT AND SUPPORTING A COCKPIT CREW WITH TAKING REMEDIAL ACTION IN CASE OF A FIRE ALARM
A fire detection system for monitoring an aircraft compartment and supporting a cockpit crew with taking remedial action in case of a fire alarm with a fire detector within the compartment; a monitoring system within the compartment to provide live monitoring data on cargo; a cargo tracking system configured to provide cargo data of the cargo; an aircraft control system configured to provide aircraft status data; a system control configured to assess a fire warning data, the cargo data and the aircraft status data and to provide a recommended remedial procedure based on the assessment in case the fire detector raises a fire alarm at least in an affected portion of the compartment; and a display device configured to display the live monitoring data and the recommended remedial procedure to the cockpit crew in case of a fire alarm
A method for generating improved machine control data. Event series is generated from input machine control data that is linked with a mesh data that is also generated from the input machine control data. Thus, an activation time (t_act) is determined which indicates the point in time at which the additive manufacturing machine prints a portion of the object that is represented by that mesh element. A full 3D-thermal simulation is run on the mesh elements. Each time the element temperature (T_el) exceeds a predetermined threshold, the activation time (t_act) is increased by a predetermined time increment and the event series is updated. Finally the event series is converted back to output machine control data.
A wing for an aircraft is disclosed including a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing, the trailing edge high lift assembly having a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position. The connection assembly includes an actuator unit for moving the flap between the retracted position and the at least one extended position. The flap includes a leading edge part and a trailing edge part mounted to the leading edge part in a manner pivotable about a pivot axis.
A method for determining flow properties of a fluid flowing along a surface by: modulating the current through a heating element of a thermal flow sensor located on the surface with at least one modulation frequency, thereby emitting a thermal wave into the fluid flowing along the surface having a penetration depth inversely proportional to the modulation frequency; measuring an amplitude of a voltage across the heating element at the third harmonic of the at least one modulation frequency, the voltage depending on the thermal conductivity and the volumetric heat capacity of the fluid flowing along the surface; determining a flow velocity at the penetration depth from the attenuation value of the determined amplitude of the voltage; and estimating whether the flow at the penetration depth is laminar or turbulent on the basis of the determined flow velocity. Also, a system and an aircraft with such a system.
G01P 5/12 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring thermal variables using variation of resistance of a heated conductor
75.
EVACUATION SUPPORT SYSTEM, METHOD FOR SUPPORTING AN EVACUA-TION PROCEDURE, AND AIRCRAFT
An evacuation support system comprising a signaling device configured to produce signals guiding evacuees (E) away from overcrowded exit points and towards less crowded exit points. The signaling device may include at least one visual signal and/or at least one audio signal. Also a method for supporting an evacuation procedure and an aircraft having the evacuation support system.
A method for bonding two fiber composite components with each other to form a fiber composite structure includes integrating conductive fibers underneath a bonding surface of at least one of the two fiber composite components, each conductive fiber comprising a carbon fiber coated with an electrically insulating coating, the conductive fibers running along the bonding surface and protruding at least at their ends from the respective fiber composite component; arranging the two fiber composite components against each other at their respective bonding surfaces; passing an electric current through the conductive fibers by electrically contacting the conductive fibers at their protruding ends so that the respective fiber composite component is heated at the bonding surface to a curing temperature; and joining the two fiber composite components with each other at their bonding surfaces via secondary bonding, co-bonding and/or co-curing at the curing temperature, thereby forming the fiber composite structure.
B29C 65/34 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
B29C 65/00 - Joining of preformed parts; Apparatus therefor
B29C 65/48 - Joining of preformed parts; Apparatus therefor using adhesives
77.
APPARATUS FOR THREADING A TOOL UNIT ONTO AN ELONGATE STRUCTURAL ELEMENT
An apparatus for threading a tool unit onto an elongate structural element. The apparatus has a holding arrangement for holding it on a feed device, a tool unit to be threaded onto the elongate structural element. The tool unit has a tool axis and a vibration unit connected to the tool unit and configured to generate a periodic force in at least one first spatial direction that runs transversely with respect to the tool axis. First and second coupling components, held elastically on one another, are provided. The first coupling component is connected to the holding arrangement, the second coupling component is connected to the tool unit. The vibration unit is operated, during a feed movement of the holding arrangement for threading the tool unit onto the elongate structural element, to add an additional, periodically varying transverse component to a feed force acting on the tool unit.
A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) surrounding a plenum (17) and having a first side portion (21), a second side portion (27), an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), wherein the leading edge panel (13) includes micro pores (45), wherein a first port device (49) is arranged in the first side portion (21) fluidly connected to the plenum (17) via a duct (53) defined by a duct structure (105), and wherein the first port device (49) comprises a first door (55) pivotable by a first hinge (57) about a first hinge axis (59).
A protective lining which includes a self-curing potting sealant compound. The lining can be used for an aircraft part, such as a tank wall liner which can be manufactured in-situ by casting the sealant into a prepared mold that is formed at least at the bottom side by the part to be protected by the tank wall liner. Specifically, for fuel tanks, the bottom portion forms the bottom side of the mold, whereas the ribs and stringers form a circumferential wall of the mold that prevents flowing of the potting sealant compound into neighboring molds.
A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) that surrounds a plenum (17), wherein the leading edge panel (13) has a first side portion (21), a second side portion (27), an inner surface (33) and an outer surface (37), wherein the leading edge panel (13) having micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39), wherein a first air inlet/outlet device (49) is arranged in the first side portion (21) and a second air inlet outlet/device (51) is arranged in the second side portion (27), fluidly connected to the plenum (17), and wherein the first air inlet/outlet device (49) comprises a pivotable first door (55) and the second air inlet outlet/device (51) comprises a pivotable second door (61).
A buffer for storing liquid at a consumer pressure includes a storage volume for holding a liquid and a gas. The storage volume may be separated by a partition element into a liquid compartment for holding the liquid and a gas compartment for holding the gas. A pressurizer is configured for increasing the pressure of gas in the storage volume to an operating pressure when liquid is or has been drained from the storage volume. A ventilator reduces the pressure of gas in the storage volume back to the operating pressure when the storage volume is filled with liquid. A water supply system for an aircraft including the buffer and an aircraft including such a water supply system are disclosed.
A wastewater tank arrangement for an aircraft, including a wastewater tank and a drain pipe having a first end and an opposite second end, the drain pipe fastened with its first end to the wastewater tank and having a second end for connection to a service panel in the aircraft structure. Providing a wastewater tank arrangement can effectively compensate tolerances between the wastewater tank and the service panel, and can effectively compensate installation and manufacturing tolerances during the course of the initial installation, in that the wastewater tank arrangement has a tolerance compensation device configured to connect the second end of the drain pipe to the service panel and compensate tolerances between the second end of the drain pipe and the service panel.
F16L 27/11 - Adjustable joints; Joints allowing movement comprising a flexible connection only the ends of the pipe being interconnected by a flexible sleeve the sleeve having the form of a bellows with multiple corrugations
F16L 27/10 - Adjustable joints; Joints allowing movement comprising a flexible connection only
83.
METHOD AND SYSTEM FOR MONITORING A LAMINAR FLOW ON A SURFACE OF AN AIRCRAFT
A method and a system for monitoring a laminar flow on a surface of an aircraft is disclosed including observing a surface of an aircraft by an optical sensor, and processing an image data of that surface by an image processing system in order to determine an actual extend of a laminar flow on the surface. The actual extend of the laminar flow on the surface is compared with a previous extend of the laminar flow on the surface, and/or with a potential maximum extend of laminar flow on the surface determined from flight parameters of the aircraft. A reduction or a possible optimization of the laminar flow is detected and further processed to improve the laminar flow.
A wing for an aircraft. The wing includes a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing. The trailing edge high lift assembly includes a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly is configured such that the flap is movable relative to the main wing in a linear and/or rotational manner. The connection assembly is configured such that the flap is movable relative to the main wing in a decoupled linear and rotational manner.
A tank wall liner for a fuel tank includes a liner body made of a liner material. The liner material is a sealant or composite of sealant and fiber and/or textile materials. Multiple tank wall liners are installed on a tank wall and form a lining surface that seals the fuel in the tank from the tank skin. Also, a tank with the tank wall liner, an aircraft with a tank forming a portion of the fuselage, and methods of manufacturing the tank wall liner and the tank.
A centrifugal reservoir pump for processing a hydrogen stream in an aircraft. In particular, a centrifugal reservoir pump including a pump casing, a hydrogen stream inlet, a rotor being rotatably arranged in the interior part of the pump and including rotor vanes for accelerating the hydrogen stream, and two hydrogen stream outlets. Further provided is a tank unit including the centrifugal reservoir pump and a reservoir for hydrogen. Further provided is an aircraft including a centrifugal reservoir pump or a tank unit. Further provided is a method of processing hydrogen in an aircraft.
A cabin module for an aircraft comprises a section which has an upward-facing surface in an installed state of the cabin module, wherein the upward-facing surface of the section comprises an integrated drainage channel. An aircraft furthermore comprises at least one such cabin module.
A connection assembly for connecting a first element to a second element is provided. The connection assembly has a male element and a female element. The female element has a barrel nut. The barrel nut has a conical inner portion positioned at a first longitudinal region and a cylindrical inner portion positioned at a second longitudinal region. The barrel nut has a first engaging element portion and a first plain portion arranged alternatingly around a circumferential direction of the barrel nut. The male element has a cylindrical bolt-like shape and has a second engaging element portion and a second plain portion arranged alternatingly around a circumferential direction of the male element. The male element further has flattened sides at the second plain portion. The second engaging element portion of the male element is configured to engage with a respective one of the first engaging element portion of the barrel nut.
A module an aircraft fuselage includes a support device including a lower end for connection to a fuselage structure in a lower deck of the fuselage, an upper end for connection to an intermediate floor in the fuselage, and an energy absorption element between the upper end and the lower end. A wall panel is connected to the support device and extends along a longitudinal axis and a circumferential direction. In case of a defined crash of an underside of the aircraft fuselage, the energy absorption element is configured to undergo a defined plastic deformation and absorb a defined amount of kinetic energy of that a part of the fuselage structure connected to the lower end of the support device. The plastic deformation and amount of absorbed energy are of a magnitude that in case of defined crash, the module is configured where the fuselage structure will, at the underside of the aircraft fuselage, deform no more than a minimum height.
A tire monitoring device configured to be mounted on a wheel and including: a pressure sensor for sensing an inflation pressure of a tire on the wheel; a wireless communication interface configured to receive data indicative of a command to indicate tire pressure, wherein the wireless communication interface is configured to communicate with at least one other tire monitoring device; a storage storing a predetermined pressure value; an indicator configured to provide a first indication and a second indication, wherein the first indication is different from the second indication; and a processing system configured to operate the indicator to provide the first indication or the second indication responsive to receipt of the command to indicate tire pressure, and based at least in part on the inflation pressure and the predetermined pressure value.
A compartment system for a vehicle cabin includes a framework assembly for attachment to a vehicle structure, and a container bin. The framework assembly includes a flat bottom section, a top part and a lateral stiffening element. The bottom section has a rear edge for attachment to the structure and a front edge opposite to the rear edge. The top part is spaced from and parallel to the bottom section front edge. The lateral stiffening element is connected to the top part and the bottom section to create the framework assembly having a front opening between the top part and the bottom section front edge. The container bin has a box-like shape and an open front side. The framework assembly and the container bin are configured to detachably attach the container bin in the framework assembly with the open front side arranged in the framework assembly front opening.
A holding system for a wheelchair in an aircraft is proposed, including a plate-shaped base unit having first fastening elements at an underside configured to be connected to complementarily shaped second fastening elements in the form of seat rails on a floor or surrounding structure in the aircraft for fastening the base unit, a front holding unit and a rear holding unit arranged on an upper side of the base unit at a distance from each other and defining therebetween a placement area for a wheelchair. The front holding unit and the rear holding unit are configured to form a releasable form-fit connection with the wheelchair disposed on the placement area so that the wheelchair is braced between the front holding unit and the rear holding unit. The holding system is configured to fix the wheelchair stationarily to the floor during operation of the aircraft.
An apparatus for fastening a component to an aircraft cabin attachment structure, the attachment structure having a fastening tube with a longitudinal axis. The apparatus has an internally bored sleeve rotatably positionable on the fastening tube and an external thread. A holding body connects to the component and has two spaced-apart limbs and a bearing surface enclosed by the limbs, and on which, an internal thread configured to the sleeve external thread, is arranged. A device fixes the holding body to the threaded sleeve and the fastening tube, the external and internal threads being non-self-locking. When the holding body internal thread presses against the threaded sleeve external thread, the threaded sleeve rotates until the external and internal threads align. The fixing device connects the threaded sleeve to the holding body in a rotationally fixed manner and fixes the holding body transversely with respect to the longitudinal axis.
A rail for the fastening of equipment elements, such as, in particular, seats, in aircraft, includes a holding region for connection to an equipment element of an aircraft, and a support region to fasten the rail to a carrier element of the aircraft. The rail has a metallic shell which is, for example, made of titanium and which is filled with a fiber-reinforced thermoplastic filler material which is reinforced by short fibers. To produce the rail, a metallic molded part is used as a casting mold and is filled, for example by injection, with the filler material and, after the rail has been produced, forms the metallic shell for the filler material.
B32B 3/04 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by a layer folded at the edge, e.g. over another layer
B29C 45/00 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
95.
INTERCONNECTING DEVICE FOR SOLID OXIDE FUEL CELLS AND A FUEL CELL STACK COMPRISING THE SAME
An interconnecting device for compact solid oxide fuel cells includes a body having first and second interface surfaces on distinct body sides. The first interface surface includes spaced apart anode and cathode exhaust inputs. The second interface surface includes spaced apart fuel and air supply ports. The anode exhaust input fluidly communicates with the fuel supply port and/or anode exhaust outlet arranged at a distance to the first and second interface surfaces. The cathode exhaust input fluidly communicates with the air supply port and/or cathode exhaust outlet arranged at a distance to the first and second interface surfaces. The first electrical port is arranged at or in the cathode exhaust input and is connectable from the first interface surface. The second electrical port is arranged at or in the fuel supply port and is connectable from the second interface surface, and is electrically connected to the second electrical port.
A method for producing a component with a surface that is suitable for plastic welding or adhesive bonding of two parts is provided. As a preparation step prior to joining, a filler sheet comprising a thermoplastic material or adhesive is arranged on a first surface of a first component and a structuring tool is arranged on the filler sheet. Mechanical force is applied to the structuring tool and heat is applied to the filler sheet such that the filler sheet is attached to the first surface of the first component and such that the structuring tool is partially embedded in the filler sheet. The structuring tool is subsequently removed from the filler sheet to produce a plurality of protrusions in the outer surface of the filler sheet. After surface structuring the first and second components are joined using any type of welding technique or joined using of adhesive bonding.
A connecting rod coupling device for attaching a component to an aircraft fuselage and/or stiffening the fuselage has a first coupler, and a second coupler couplable to the first coupler. The first coupler has an elongate body with a first channel on a lateral surface along a first longitudinal axis. The second coupler has a hollow-cylindrical portion, which, on an inner face along a second longitudinal axis, has a second channel complementing the first channel. The hollow-cylindrical portion has a radial cutout through which the elongate body is radially insertable into the second channel from outside the hollow-cylindrical portion. The second coupler has a closure body, which closes the radial cutout, and can be positioned removably in the cutout to complete the second channel on a radially internal face. The second coupler also has an element, pushable onto the hollow-cylindrical portion to secure the closure body on the hollow-cylindrical portion.
A freight carrier configured to be received in an aircraft cargo hold, a system of one or more such freight carriers and a receiving platform, and a platform, are each provided. The freight carrier includes a floor element having a resting surface configured to lie on a floor surface of a cargo hold of an aircraft. The freight carrier is configured such that its resting surface can be moved over a floor surface in a floor plane. The floor element has a base element having a base surface. The base surface is situated on the base element such that the base surface faces away from the resting surface. The resting surface is provided with an arrangement to allow the freight carrier to be slid over the floor surface. The floor element has a cavity which extends toward the base surface between the front portion and the rear portion.
B65D 88/14 - Large containers rigid specially adapted for transport by air
B65D 81/05 - Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents specially adapted to protect contents from mechanical damage maintaining contents at spaced relation from package walls, or from other contents
B65D 90/00 - Component parts, details or accessories for large containers
B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
99.
FREIGHT CONTAINER INTENDED TO BE RECEIVED IN THE CARGO HOLD OF AN AIRCRAFT
A freight container configured to fit in an aircraft cargo hold includes a floor element. First and second parallel side walls extend away from first and second opposite edges of the floor element base surface. A top wall, parallel to a floor element resting surface, extends between edges of the first and second side walls, which edges are remote from the first and second edges. A front wall extends between the first and second side walls from a base surface third edge to a top wall front edge. The front wall has a first front wall portion, extending from the base surface third edge at a first angle of at least 90° to the resting surface. The front wall has a second front wall portion, extending from the top wall front edge at a second angle of less than 180° and more than 90° to the top wall.
A method of assembling a structure in aircraft or spacecraft production wherein two components to be joined together at a joint are provided, each component comprising a joining region. Sealant is applied to one of the component joining regions. An arrangement is formed by positioning the components relative to each other, whereby an uncured layer of the sealant is formed between associated joining regions. The associated joining regions are clamped against each other using a clamping device, and a clamped state is maintained until the layer of sealant has cured to a pre-defined degree, the clamping device being installable on and transportable along with the arrangement. After the layer of sealant has cured to the pre-defined degree, drilling at a plurality of fastening positions is performed to obtain a hole of final dimension at each fastening position, and installation of a final fastener at each fastening position is performed.
B23P 19/04 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
B23P 21/00 - Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor