| AIRBUS OPERATIONS GMBH Patent applications |
| Patent application number | Title | Published |
|---|
| 20160129987 | INJECTION MOLDING METHOD FOR THE MANUFACTURE OF A PRIMARY-STRUCTURE CONNECTION ELEMENT - An aircraft including a primary-structure connection element for attaching the aircraft skin to the primary structure of the aircraft is provided. The primary-structure connection element is designed as a shearweb, a clip and/or as a frame stabilization element or as a rib stabilization element and is manufactured from a fiber-reinforced thermoplastic material with the use of injection molding. Likewise, an injection molding method for the manufacture of such a primary-structure connection element is provided, in which method the fiber-reinforced thermoplastic material is injected in its melted state into an injection molding device. The manufactured shearweb etc. is removed from the injection molding device. In this method, in particular, chopped carbon fibers and/or glass fibers in combination with polyphenylene sulfide (PPS) and/or polyetherether ketone (PEEK) are used, for example also in pellet form. | 05-12-2016 |
| 20160114881 | METHOD FOR DETERMINING A STATE OF A COMPONENT IN A HIGH LIFT SYSTEM OF AN AIRCRAFT, HIGH LIFT SYSTEM OF AN AIRCRAFT AND AIRCRAFT HAVING SUCH A HIGH LIFT SYSTEM - A method for determining a state of a component in a high lift system of an aircraft, the high lift system including a central power control unit for providing rotational power by a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces, includes acquiring in an extended position in flight a first position of a first position pick-off unit coupled with the component, mechanically coupled with a high lift surface, and coupled with a drive station; acquiring in flight a second position of a second position pick-off unit arranged in or at the central power control unit in the extended position; determining a deviation between a first measure based on the first position and a second measure based on the second position; determining, whether the deviation exceeds a predetermined threshold; and if so, generating a signal indicating an abnormal state of the component. | 04-28-2016 |
| 20160095593 | STAPLING DEVICE WITH LOCKING MECHANISM - A stapling device includes a stapling needle system that is guided through the base body of the stapling device. The stapling needle system can be passed through a hole in one or more components. By exerting a tensile force on the stapling needle system, the component or components can be sandwiched between the stapling needle head and base body of the stapling device. The stapling needle system can be positively locked with the base body by means of a locking device, so as to lock the stapling device in place. | 04-07-2016 |
| 20160075102 | FIBER COMPOSITE COMPONENT WITH AN ELECTRICALLY CONDUCTIVE FIBER MATERIAL FOR REINFORCEMENT AS WELL AS A DEVICE FOR ITS MANUFACTURE - A fiber composite component as a structural component of an aircraft, encompasses a mat-shaped, electrically conductive fiber material embedded in several layers into a synthetic resin matrix, wherein individual fibers protrude as free fiber ends from the flat plane of the mat-shaped fiber material, so as to establish an electrical bridge connection between adjacent layers of the fiber material through an interspersed synthetic resin layer. A device for manufacturing such a fiber material is also described. | 03-17-2016 |
| 20160068278 | PREVENTING CRACKS AT BOLTED OR RIVETED JOINTS OF AIRCRAFT STRUCTURAL PARTS - A method for joining two aircraft structural parts by a bolted or riveted joint and for preventing cracks at said joint includes a step of providing a first metallic aircraft structural part and a second aircraft structural part, wherein the first aircraft structural part includes a first joint region and a second aircraft structural part includes a second joint region. Furthermore, the method includes a step of inducing compressive residual stresses in a first area of the first joint region for preventing cracks. Finally, the method includes a step of fastening together the first and second aircraft structural parts at the first and second joint regions by a bolted or riveted joint. An aircraft including first and second aircraft structural parts is also described. | 03-10-2016 |
| 20160064751 | FUEL CELL SYSTEM, A FIRE FIGHTING SYSTEM, AND AN AIRCRAFT - A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid. | 03-03-2016 |
| 20160050013 | Wireless Aircraft Network and Method for Wirelessly Connecting Aircraft in a Network - A wireless aircraft network includes a plurality of aircrafts having transceiver devices for transceiving wireless communication, a plurality of ground-based network stations having transceiver devices for transceiving wireless communication, and a network operator station configured to store location data regarding the current geographical location of the plurality of aircrafts in a location data table of the network operator station and to determine a most efficient network path for each of the plurality of aircrafts to one of a plurality of ground-based network stations depending on the current geographical location of the plurality of aircrafts and the geographical location of the plurality of ground-based network stations. | 02-18-2016 |
| 20160047246 | MORPHING TRAILING EDGE DEVICE FOR AN AIRFOIL - A morphing trailing edge device for an airfoil includes a skin member, an actuator, and a torsion element. The skin member is configured to extend on a surface of a trailing edge region of an airfoil and includes a load introduction point within a reinforced area. The skin member further includes a stiffening member arranged essentially perpendicular to the load introduction point, wherein the load introduction point, the reinforced area and the stiffening member are integrated into the skin member. The actuator is configured to drive the torsion element with an actuation load. The torsion element is configured to translate the actuation load to the load introduction point, so that the actuation load morphs the trailing edge region up- or downwardly relative to a horizontal plane. A morphing airfoil for an aircraft, an aircraft with a morphing airfoil and a method for manufacturing a morphing airfoil are also described. | 02-18-2016 |
| 20160046393 | PROCESSING DEVICE FOR THE ASSEMBLY OF AIRCRAFT - A processing device for the assembly of an aircraft encompasses a positioning frame, a guide device and a movable tool arm. The positioning frame can be attached to a segment of a hall floor. The guide device is movably guided on the positioning frame. The movable tool arm is attached to the guide device, and its free end exhibits a tool holder. The processing method for the assembly of aircraft encompasses the steps of providing a positioning frame on a segment of the hall floor, and guiding a guide device on the positioning arm. The guide device here exhibits a movable tool arm, and a free end of the tool arm exhibits a tool holder. | 02-18-2016 |
| 20160046392 | Method For Assembling An Aircraft Fuselage - A method for assembling an aircraft fuselage includes different steps. In a first step the secondary structural components and interior components are assembled to form a core structure. The core structure comprises a cabin floor, side wall panels and ceiling panels. In another step of the method a primary structure is arranged around the core structure to form a part of a fuselage. | 02-18-2016 |
| 20160039516 | JOINT ARRANGEMENT, DRIVE SYSTEM FOR DRIVING CONTROL SURFACES OF AN AIRCRAFT AND AIRCRAFT WITH SUCH A DRIVE SYSTEM - A joint arrangement includes an outer joint component, an inner joint component, a cage and at least two balls located between the outer and inner joint component and in openings of the cage. The balls run in ball recesses, while at least two are in a mechanical contact with pressing devices, which are adapted for holding the respective balls in a radially flexible position relative to one of the inner joint component, the outer joint component and the cage and for pressing the respective balls into the corresponding recesses. Such a joint arrangement is based on a homokinetic joint and allows a homogenous transfer of torque without alternating acceleration and deceleration due to the action of the joint itself. Furthermore, a reliable and effective torque limitation may be accomplished. | 02-11-2016 |
| 20160039387 | RE-CONFIGURABLE PASSENGER BENCH SEAT - A passenger bench seat comprises a backrest, a seat element, a fastening rail which extends substantially parallel to a longitudinal axis of the seat element in the region of an edge of the seat element that faces towards the backrest, and a seatbelt system. In a first configuration of the passenger bench seat, the seatbelt system includes a first number of seatbelts which are detachably fastened to the fastening rail in first positions which are adapted to the first configuration of the passenger bench seat. In a second configuration of the passenger bench seat, on the other hand, the seatbelt system includes a second number of seatbelts which are detachably fastened to the fastening rail in second positions which are adapted to the second configuration of the passenger bench seat. | 02-11-2016 |
| 20160030781 | Supply System And Method For Providing Electric Energy, Oxygen Depleted Air And Water As Well And Aircraft Having Such A Supply System - A supply system for providing at least oxygen depleted air and water in a vehicle includes a catalytic converter, at least one hydrogen supply means, at least one air supply means, at least one outlet for oxygen depleted air, and a control unit coupled with the catalytic converter. The catalytic converter is couplable with the hydrogen supply means and is adapted for producing water under consumption of hydrogen from the at least one hydrogen supply means and oxygen. The catalytic converter is further couplable with the at least one air supply means for additionally producing oxygen depleted air. Further, the control unit is adapted for selectively operating the catalytic converter based on a demand of water and oxygen depleted air. | 02-04-2016 |
| 20160019770 | Apparatus For Operating A Door Of An Aircraft, An Aircraft Having Such An Apparatus And Method For Operating A Door Of An Aircraft - A system for operating an aircraft door includes an operating handle having a lever and a grip, a slide arming means movable between a first position representing an armed state and a second position representing a disarmed state, a control unit coupled with the slide arming means, warning means arranged in the vicinity of the slide arming means and a sensor. The sensor is adapted for detecting the proximity of a hand of a user in a field around the grip, which field covers a distance of at least 10 cm and not exceeding 50 cm to the grip, and for producing a proximity signal representing the proximity of a hand of a person. The control unit is adapted for operating the warning means on receiving the proximity signal of the sensor to attention to the slide arming means when the slide arming means is in the first position. | 01-21-2016 |
| 20150367424 | Drilling Template, Drilling Template Arrangement And Method For Introducing Bores - A drilling template for use in the field of producing aircraft or spacecraft or parts thereof has a first template part and a second template part. The first template part and the second template part are in each case provided here with means for fixing positions of bores to be produced. The drilling template has coupling means, by which the first template part and the second template part can be coupled to one another in such a way that the coupled template parts are movable relative to one another. | 12-24-2015 |
| 20150362343 | DEVICE AND METHOD FOR DETERMINING THE POSITION OF A MOVABLE TRANSPORTATION UNIT - A device and a method for determining the position of a movable transportation unit are described. The device and the method are suitable for accurately detecting the position, automatically fixing loads in position and/or loading and unloading transportation units in aircraft in a relatively quick manner. The device includes a movable transportation unit and a detection means. The transportation unit has a recess for receiving a locking unit in order to lock the transportation unit. The detection means detects when the recess in the movable transportation unit is in a position for engagement with the locking unit. The method for determining the position of a movable transportation unit includes moving the transportation unit from an initial position into a target position, providing the locking unit at the target position of the transportation unit, and locking the locking unit by the engagement thereof in the recess in the transportation unit. | 12-17-2015 |
| 20150356236 | Method And Apparatus For Aligning Segments - An apparatus for aligning segments with one another include a positioning device and a projection device, installed on the construction site, projecting projection lines onto the segments from different directions so that distances between the projection lines and reference points applied to the segments can be determined. The position of the individual reference points on the segments can be determined with reference to a coordinate system by an evaluation device. Based on the spatial arrangement of the reference points, theoretical best-fit planes and best-fit lines are then generated for each segment. The segments are levelled by moving the positioning device or adjusting the shortest possible distance between the theoretical best-fit planes and best-fit lines to the projection lines and are aligned by again moving the positioning device so that the distances between the theoretical best-fit planes and best-fit lines of the first segment and of the second segment are minimised. | 12-10-2015 |
| 20150344122 | AIRCRAFT DOOR AND AIRCRAFT COMPRISING SUCH AN AIRCRAFT DOOR - An aircraft door includes an outer shell with an exterior and an interior, a stiffening structure arranged on the interior of the outer shell, and at least one door seal arranged on the interior of the outer shell. The door seal is circumferential in an edge region. In the edge region between the outer shell and the door seal at least one circumferential stiffening component is arranged that is connected to the stiffening structure. Thus, in a particularly simple manner and without modifications to a stiffening structure, an aircraft door may be provided with very substantial stiffness in an edge region. | 12-03-2015 |
| 20150343732 | Waste Compaction System For A Vehicle, Cabin Monument For A Vehicle Having Such A Waste Compaction System And Vehicle Having At Least One Waste Compaction System - A waste compaction system for a vehicle includes a moveable trolley for storing waste, and a docking station integratable into a cabin monument for inserting the trolley. The trolley includes a housing having an opening for inserting waste, a vacuum waste compacting mechanism inside the housing and a first suction port accessible from outside the housing, the first suction port being couplable with the vacuum waste compacting mechanism. The docking station and the trolley are adapted to each other such that the trolley is engageable with the docking station, and wherein the docking station includes a second suction port couplable with a suction line in the vehicle and the first suction port. Resultantly, a lightweight and efficient waste compaction system is provided, which allows moving the trolley for collecting waste inside a cabin of the vehicle. | 12-03-2015 |
| 20150336680 | Tank System For The Cryogenic Storage Of Hydrogen, And Aircraft With A Tank System For The Cryogenic Storage Of Hydrogen - A tank system for the cryogenic storage of hydrogen includes a tank structure with at least one hollow body for accommodating liquid hydrogen and at least one insulating means, which encloses the tank structure, for insulating the at least one hollow body. The tank structure has an exterior shape that is integrateable in a load-bearing primary structure of an aircraft. The tank structure is load bearing and is designed to at least partially absorb a load introduced into the primary structure. This makes it possible to achieve a particularly efficient design of an aircraft in which the fuselage of the aircraft is not divided into two parts by the hydrogen tank integrated therein, can be arranged near the center of gravity, and essentially does not increase the additional weight of the aircraft. | 11-26-2015 |
| 20150333418 | Contact Sealing Ring, Electrical Contact Point And Method For Contacting Electrically Conductive Components - A contact sealing ring includes an electrically conductive annular disc which has a central through-opening, a first electrically conductive contact formation which protrudes from a first side of the annular disc, and a second electrically conductive contact formation which protrudes from a second side, opposite the first side, of the annular disc. | 11-19-2015 |
| 20150329197 | Flow Body With A Load Introduction Element Integrated Therein, Method For Manufacturing A Flow Body, And Aircraft With Such A Flow Body - A flow body for an aircraft with a leading edge and a trailing edge includes a first spar, a second spar, and an external skin that spans from the leading edge to the trailing edge and on both sides rests on the spars. At least one of the first spar and the second spar includes a web and two spaced-apart flanges that enclose the web, on which flanges the skin that spans the respective spar is arranged. At least one of the first spar and the second spar includes at least one load introduction fin that forms an integral component with the web and extends outwards by way of one of the flanges and the skin that rests on the spars. | 11-19-2015 |
| 20150321743 | METHOD FOR MANUFACTURING A LOAD BEARING STRUCTURE AND SUCH A LOAD BEARING STRUCTURE - A method for manufacturing a load bearing structure involves providing a panel; providing a first set of split stiffening elements on a surface of the panel, wherein the split stiffening elements of the first set have bottom surfaces and central portions with open top clearances, respectively, spaced apart from each other; providing a second set of stiffening elements having bottom surfaces and top surfaces and central portions, respectively; inserting the stiffening elements of the second set into respective open top clearances of the split stiffening elements of the first set and providing the second set of stiffening elements on the surface of the panel for forming a grate structure; and attaching top surfaces to the split stiffening elements of the first set for forming complete profiles. | 11-12-2015 |
| 20150314872 | Galley Segment For A Cabin Of A Vehicle, Cabin Of A Vehicle And Aircraft Having A Cabin With Such A Galley Segment - A compact galley segment, which allows to safely and temporarily fix trolleys outside of a closed storage space includes a first trolley storage space, a second trolley storage space, a retractable trolley restraint device and a plurality of vertically arranged walls. The first trolley storage space includes a plurality of delimiting walls defining an inner space for receiving at least one trolley and an opening for inserting or removing the at least one trolley into or from the inner space. The second trolley storage space includes at least one placement space for temporarily placing a trolley. The trolley restraint device is integrated into or onto at least one of the plurality of vertically arranged walls and is configured for releasably restraining a trolley temporarily positioned in the second trolley storage space and for being fully retractable into the outer contour of the galley segment. | 11-05-2015 |
| 20150308383 | ENGINE FOR PROPELLING AN AIRCRAFT AND AIRCRAFT HAVING AT LEAST ONE ENGINE AND AT LEAST ONE HYDROGEN TANK - An engine for propelling an aircraft includes an annular fuel cell arrangement having at least one fuel cell, at least one electric motor couplable to the fuel cell arrangement, at least one fan couplable to the electric motor and a cowling having an inlet and an outlet nozzle. The fuel cell arrangement is arranged inside the cowling, the at least one fan is arranged between the inlet and the fuel cell arrangement inside the cowling, the electric motor is operable under consumption of electric power delivered by the fuel cell arrangement and the at least one fan is designed to produce a thrust force by creating an accelerated airflow at the outlet nozzle. The engine is extremely efficient and comprises a distinct low noise. | 10-29-2015 |
| 20150298797 | Aircraft Having A System For Influencing The Yaw Moment And A Method For Influencing The Yaw Moment Of An Aircraft - An aircraft includes a system for influencing the yaw moment. The system includes a thrust generation means, an energy store which can be coupled to the thrust generation means for transmitting energy to the thrust generation means, and a trigger device. The thrust generation means is set up so as to provide a thrust force, including a thrust direction vector at a distance from a yaw axis of the aircraft. The trigger device is set up to couple the energy store to the thrust generation means at least for a predetermined period T on demand. The ability to compensate part of the thrust asymmetry independently of a rudder unit if an engine fails means that the rudder unit can be configured with smaller dimensions. This leads to a considerable reduction in the aerodynamic resistance of the aircraft, and thus to a weight-equivalent advantage, without leading to safety compromises. | 10-22-2015 |
| 20150298401 | CURING TOOL FOR SHELL COMPONENTS AND METHOD FOR CURING SHELL COMPONENTS - A curing tool for a shell component, includes a first tool component, which is cuboid and has a wedge-shaped bevel forming a first sheared edge on a first side edge, and a second tool component, which is cuboid, has a wedge-shaped bevel forming a second sheared edge on a first side edge and has a first corner bevel on a second side edge diagonally opposite the first side edge. The wedge angles of the first and the second sheared edge are equal. | 10-22-2015 |
| 20150284097 | Apparatus For Holding A Cabin Attendant Seat, Cabin Arrangement In A Vehicle And Vehicle Having A Cabin And Such A Cabin Arrangement - An apparatus for holding a cabin attendant seat in a cabin of a vehicle includes a base body attachable to a wall surface in the cabin, at least one holding mechanism for holding a cabin attendant seat, at least one linear movement mechanism, and at least one arresting mechanism. The at least one linear movement mechanism is attached to the base body and supports the at least one holding mechanism. The at least one linear movement mechanism is configured for laterally moving the at least one holding mechanism between at least two laterally distanced discrete positions. The at least one arresting mechanism is coupled with the at least one linear movement mechanism and is configured for arresting the at least one linear movement mechanism in the at least two discrete positions. By this apparatus a very space effective provision of a cabin attendant seat especially on a monument is given. | 10-08-2015 |
| 20150259070 | LAYOUT OF A SANITARY UNIT - A sanitary unit for a cabin region on board a vehicle is provided with a first lavatory facility and a second lavatory facility. The first and the second lavatory facilities in each case form a longitudinally-directed interior space comprising two longitudinal sides and two narrow sides. In each case a narrow side comprises an access door. The first and the second lavatory facilities adjoin each other by their longitudinal sides and are separated from each other by a shared middle wall. The shared middle wall extends between lateral connection regions on the narrow sides and comprises at least one offset at least in a middle region between the two lateral connection regions in the horizontal direction. | 09-17-2015 |
| 20150259067 | MODULE FOR AN AIRCRAFT - A module for an aircraft has a fuselage structure and a floor element defining a floor plane. The module includes a frame device adapted for mounting a functional element and the frame device is adapted for attachment to the floor element of the aircraft at a first location in the floor plane. | 09-17-2015 |
| 20150252824 | HOLDER FOR CONNECTING A MODULE TO A COMPONENT OF AN AIRCRAFT OR SPACECRAFT, ARRANGEMENT, AIRCRAFT OR SPACECRAFT, AND METHOD - A holder for connecting a module to a component of an aircraft or spacecraft includes a first holder portion having a first adhesive face and a second holder portion having a second adhesive face. The first and second holder portions are movable relative to one another in an initial state of the holder such that a portion of the component can be received between the holder portions so as to glue the holder portions to the component by means of an adhesive layer in each case. The holder has two or more guided parts which are movable relative to one another by means of mutually cooperating guide faces in the initial state of the holder. The guide faces are suitably formed for being glued together using an adhesive. The holder can be used to counter peeling stress of an adhesive connection of the holder in the region of the first and/or second adhesive face. | 09-10-2015 |
| 20150239550 | CONTROL SYSTEM FOR AIRCRAFT HIGH LIFT DEVICES AND METHOD FOR CONTROLLING THE CONFIGURATION OF AIRCRAFT HIGH LIFT DEVICES - A control system for an aircraft high lift device includes a threshold setting unit configured to output one of a plurality of configuration change thresholds as an active output threshold, a threshold deactivation unit coupled to the threshold setting unit and configured to temporarily increase the active output threshold to a deactivation value, a configuration setting unit coupled to the threshold deactivation unit and configured to set the aircraft high lift device from a first configuration to a second configuration, if a measured value of an angle-of-attack of the aircraft exceeds the active output threshold, and a threshold control unit configured to control the threshold deactivation unit to temporarily increase the active output threshold to the deactivation value while the aircraft high lift device is mechanically moving from a first configuration to a second configuration. | 08-27-2015 |
| 20150232198 | VISUAL SIGNALLING OF AN AIRCRAFT - This relates to an aircraft providing visual signalling of an aircraft. An aircraft for providing visual signalling is provided with at least one multifunctional light unit comprising at least one light source for outboard light emission, which unit is provided on sideway facing areas of the aircraft. The sideway facing areas comprise lateral facing sideway surface areas and/or forward and backwards facing surface areas of the aircraft. The at least one multifunctional light unit is configured to provide i) directional signalling of the aircraft, or ii) status signalling of the aircraft, wherein the status signalling relates to at least one of the group of status of the aircraft, status of the current flight mission, and status of the traffic situation; and/or iii) identification signalling of the aircraft. | 08-20-2015 |
| 20150231767 | FASTENING DEVICE AND METHOD - A fastening device includes a fastening needle system, which is guided in a base body of the fastening device. The fastening needle system is configured to be led through a drilling hole of one or more components. By exercising a pulling force onto the fastening needle system, the components can be fastened between the front portion of the fastening needle and the base body. A fastening system may include the fastening device and a fastening pliers. | 08-20-2015 |
| 20150226243 | ATTACHMENT STRUCTURE OF AN AIRCRAFT - An attachment structure for an equipment unit of an aircraft includes a first attachment device extending in a longitudinal direction of the aircraft, wherein the first attachment device is attached to a stringer and to a frame and wherein the first attachment device has a first engagement element and a second attachment device attachable to the equipment unit, wherein the second attachment device has a second engagement element adapted for engaging into the first engagement element, such that a force from the equipment unit in the longitudinal direction on the second attachment device is transferred via the second engagement element to the first engagement element and via the first attachment device to the stringer and the frame. | 08-13-2015 |
| 20150225065 | Stiffening Element, Method For Coupling The Same, And Shell Component For An Aircraft Or Spacecraft - A method for coupling a first and a second stiffening element for a skin of an aircraft or spacecraft, wherein the first stiffening element has a cross-sectional profile with first and second web portions extending from a flange portion of a predefined width toward the skin includes forming a coupling zone of the first stiffening element wherein the second web portion is at least partially removed to expose an inner surface of the first web portion, and a step of fastening a coupling element, for coupling the stiffening elements, to the coupling zone of the first stiffening element. | 08-13-2015 |
| 20150224688 | METHOD AND A ROBOTIC SYSTEM FOR THE ATTACHMENT OF AN ARRANGEMENT - A method for the attachment of an arrangement for the attachment of a system to a structure at least partially, wherein a first element of the arrangement is bonded to the structure, wherein the first element is created by injecting at least one material into a mould carried by a robotic system to a target position of the arrangement on the structure which is closed at one side by pressing it against the structure, and after the first element is cured, a second element of the arrangement is coupled directly or indirectly to the first element, and a robotic system for executing such a method. | 08-13-2015 |
| 20150217868 | PASSENGER SEAT FOR AN AIRCRAFT - A passenger seat for an aircraft includes a seat pan for providing a seat surface for a passenger, a backrest with a lean-against surface for leaning against, and a rear surface situated opposite the lean-against surface. In this design the rear surface comprises two indentations, with each of them designed to at least partially accommodate a knee of a further passenger seated behind the passenger. | 08-06-2015 |
| 20150217503 | Pultrusion Methods And Arrangements For Manufacturing A Fibre-Reinforced Composite Product - In a pultrusion method for manufacturing a fibre-reinforced composite product comprising reinforcing fibres embedded in a thermoplastic matrix material, the following is performed along a path of pultrusion: providing a preform; further downstream, inductively heating the preform to a processing temperature of the thermoplastic matrix material; and, further downstream, introducing the preform into a die and consolidating the preform by means of the die while the preform passes through the die. | 08-06-2015 |
| 20150215664 | DISPLAY DEVICE FOR A VEHICLE - A display device for a vehicle includes a housing, a display screen, and at least one functional unit, including an operating element, each being a switch unit or a communication unit, adapted to be releasably coupled to the housing and includes an insertion portion and an operating element support portion supporting the respective operating element, and a first contact arrangement provided on the insertion portion and electrically coupled to the operating element. The housing includes at least one functional unit coupling arrangement, each adapted to be selectively and releasably coupled to at least one of the at least one functional unit and including a cavity inside the housing for receiving the insertion portion of the at least one functional unit, a second contact arrangement in the cavity, a retaining means, and an opening in an exterior wall of the housing communicating the cavity with the exterior of the housing. | 07-30-2015 |
| 20150148995 | Aircraft Power Management System And Method For Managing Power Supply In An Aircraft - An aircraft power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load coupled in parallel to the first power supply bus bar, a bus bar switch configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold, and at least one tertiary electrical equipment including a tertiary load coupled to the first power supply bus bar downstream of the at least one primary electrical equipment. | 05-28-2015 |
| 20150145702 | WARNING CIRCUITRY AND WARNING DEVICE FOR AN AIRCRACT - A warning light circuitry includes a first logic gate adapted for receiving a first, a second, a third, and a fourth input signal; a second logic gate adapted for receiving a fifth, a sixth, and a seventh input signal; a third logic gate electrically connected to the first and second logic gate; and a warning light electrically connected to the third logic gate. The first logic gate is adapted for providing a first output signal to the third logic gate upon receiving the first, the second, the third, and the fourth input signals. The second logic gate is adapted for providing a second output signal to the third logic gate upon receiving the fifth, the sixth, and the seventh input signals. Therein the third logic gate is adapted for triggering the warning light upon receiving the first or the second output signal. | 05-28-2015 |
| 20150145326 | Aircraft Power Management System And Method For Managing Power Supply In An Aircraft - A power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, a power management device coupled to the first power supply bus bar, at least one primary electrical equipment including a primary load being coupled in parallel to the power management device, and at least one secondary electrical equipment including a secondary load being coupled in parallel to the power management device. The power manager device is configured to supply electrical power to the at least one secondary electrical equipment, to supply electrical power to the at least one primary electrical equipment, and to deactivate the power supply to the at least one secondary electrical equipment, as long as the at least one primary electrical equipment is supplied with electrical power. | 05-28-2015 |
| 20150145298 | TELESCOPIC SEAT RAIL COVER - A seat rail cover for a seat rail includes a first longitudinal section and a second longitudinal section. The first longitudinal section includes a first cover element and a first support element. The first support element extends in a longitudinal direction of the seat rail cover and protrudes from the first cover element transversely to the longitudinal direction. The second longitudinal section includes a second cover element and a second support element. The second support element extends in longitudinal direction and protrudes from the second cover element transversely to the longitudinal direction. The first longitudinal section is movable in longitudinal direction of the seat rail cover with respect to the second longitudinal direction from a non extended state to an extended state. Such a seat rail cover provides a variable length and may improve the dispersion of loads applied to the cover elements of the seat rail cover. | 05-28-2015 |
| 20150144640 | Cargo Container For An Aircraft - A cargo container for accommodating transport goods and for being arranged in a cargo compartment of a means of transport is provided. The cargo container includes a housing that can be closed so that it is airtight, and an internal coating. The internal coating is incombustible and is arranged on an inner surface of the housing. Thus, the cargo container makes it possible to limit propagation of a fire to the internal space of the housing. | 05-28-2015 |
| 20150141234 | MANUFACTURING METHOD AND MANUFACTURING TOOL FOR REINFORCED STRUCTURAL ELEMENTS - A manufacturing method for reinforced structural elements includes providing a reinforcement structure including a first material, and embedding the reinforcement structure in an encasing matrix comprising a second material using additive layer manufacturing, ALM. A manufacturing tool for reinforced structural elements includes a positioning component including a jig for clamping a reinforcement structure including a first material and an ALM robot configured to embed a reinforcement structure clamped in the jig in an encasing matrix including a second material. | 05-21-2015 |
| 20150140914 | Air Transmission System for Flexible Passenger Supply Units - An air supply system for passengers includes an air supply line with a plurality of laterally situated air outlets, an individual air panel with at least one air nozzle and an air inlet opening. The individual air panel can be variably positioned along the air supply line in such a way that the air inlet opening faces one of the air outlets. A plurality of magnetic valves is arranged at the air outlets of the air supply line. One of the magnetic valves may be magnetically actuated by the individual air panel, when the air inlet opening of the individual air panel faces said one magnetic valve, so that air can flow out of the air supply line through the air outlet and the air inlet opening to the air nozzle. | 05-21-2015 |
| 20150136908 | PASSENGER DOOR CORNER COMPONENT AND MANUFACTURING METHOD FOR PASSENGER DOOR CORNER COMPONENT OF AIRCRAFT OR SPACECRAFT - A manufacturing method for passenger door corner components of aircraft or spacecraft includes using additive layer manufacturing, ALM, to form an integral passenger door corner component. The integral passenger door corner component includes a substantially cruciform shape having a frame coupling member with two frame couplings as end pieces. The frame coupling member intersect with a beam coupling member with two beam couplings as end pieces. | 05-21-2015 |
| 20150136751 | HEATED FLOOR PANEL FOR AN AIRCRAFT AND AIRCRAFT HAVING A HEATED FLOOR PANEL - A heated floor panel for an airborne vehicle and an airborne vehicle having at least one heated floor panel are described. The floor panel includes a controller housing, a first heated panel configured to heat the floor panel, a panel connector arranged in a wall of the controller housing, at least one power line coupled between the panel connector and the first heated panel and configured to supply electric power, which is input to the panel connector, to the first heated panel, a switch connected in one of the power lines, and a microcontroller connected to the switch and configured to actuate the switch for interrupting the electric power supply to the first heated panel in case of an electric fault in the floor panel. | 05-21-2015 |
| 20150118001 | SYSTEM AND METHOD OF MANUFACTURING COMPOSITE MODULES - A system for producing a fibre-reinforced composite module, such as a panel module, having an integrated stiffening structure for an aircraft or spacecraft includes a form core assembly station for assembling a plurality of form cores covered with reinforcing fibre layers to constitute at least one stiffening element of the integrated stiffening structure, a form core placement station which receives assembled form cores from the assembly station for placing or depositing the assembled form cores in or on a moulding tool, and a turning station for rotating or inverting the assembled form cores. The turning station is configured to convey or transport the assembled form cores from the assembly station to the placement station. The turning station defines a path which is configured to rotate or invert the assembled form cores as they are conveyed or moved to the placement station. | 04-30-2015 |
| 20150104632 | SYSTEM FOR MOUNTING OF COMPONENTS - A mounting system includes a first and second mounting part having a first and second base part with a first and second plurality of first and second locking means respectively, for mounting two components to each other. Each of the locking means is attached to the respective base part and is provided with an attachment part extending from the base part, and a distal part provided as a head portion with at least one engaging section protruding sidewards over the attachment part. The locking means are laterally displaceable in relation to the base part to allow sidewards displacement of the engaging sections for engagement and disengagement of the locking means and thus the first and the second base. In the engaged state, latching means are provided blocking the sidewards displacement of the engaging sections to an extent that a disengagement of the locking means is prevented. | 04-16-2015 |
| 20150090840 | CARGO DOOR ARRANGEMENT - A cargo door arrangement for an aircraft includes a fuselage portion, a cargo door and a locking mechanism. The fuselage portion includes a skin portion, at least one fuselage former and an opening. The cargo door includes at least one door former. The locking mechanism includes a first engagement element, a second engagement element and a connecting means. The first engagement element has a tapered portion and is rigidly connected to the door former. The second engagement element includes a tapered cavity having a shape matching the shape of the tapered portion and is rigidly connected the fuselage former. In the closed position the tapered portion is engageable with the cavity. The connecting means is adapted to rigidly connect in the closed position the door former to the first or second engagement element. | 04-02-2015 |
| 20150083862 | PRESSURIZED FUSELAGE OF AN AIRCRAFT, WITH A FUSELAGE STRUCTURE AND A PRESSURE BULKHEAD SPECIALLY MOUNTED THEREIN - A pressurized fuselage of an aircraft includes a fuselage structure and a pressure bulkhead mounted therein for forming a fuselage-internal pressure region. The pressure bulkhead is attached on the edge region, by way of mounting means, to the inside of the fuselage structure. The mounting means comprise at least one pivoting socket arrangement, arranged on the edge side of the pressure bulkhead, which edge side faces away from the pressure region, and interacts with the fuselage structure, as well as a supporting frame element, arranged on the opposite edge side and supporting itself on the fuselage structure. | 03-26-2015 |
| 20150083860 | Method For The Assembly Of An Aircraft Fuselage And Fuselage Manufacturing Station - A method for the assembly of an aircraft fuselage, to a fuselage manufacturing station and to a construction kit includes providing a pre-assembled cockpit unit, a pre-assembled wing box, a pre-assembled tail unit and a plurality of pre-fabricated fuselage shell segments. Furthermore, the method involves positioning the cockpit unit, the wing box and the tail unit. Moreover, a first front fuselage shell segment is positioned on a front connecting region of the wing box, and a first rear fuselage shell segment is positioned on a rear connecting region of the wing box. The first front fuselage shell segment is joined to a second front fuselage shell segment, and the first rear fuselage shell segment is joined to a second rear fuselage shell segment. As a result of the above, following the assembly of the aircraft fuselage an aircraft fuselage can be provided that already comprises equipment elements or functional elements. | 03-26-2015 |
| 20150082708 | COVER PLATE AND DOOR ARRANGEMENT FOR A MEANS OF TRANSPORTATION - A cover plate for covering a door clearance between a skin of a means of transportation and a door as well as a door arrangement with such a cover plate is proposed. The cover plate includes a mounting region for permanently fastening the cover plate on the door; a covering region for covering the door clearance; and a fastening device that is designed for fixing the covering region on the skin when the door is closed. | 03-26-2015 |
| 20150069183 | Arrangement For Guiding A Cable Between A Wing And An Aerodynamic Body Movably Supported Relative Thereto; Wing Of An Aircraft Having Such An Arrangement And Aircraft Having Such A Wing - An assembly for guiding a cable between a structural part of an aircraft and a movable aerodynamic body includes a chain of pivotally connected links, a first coil device arranged between each pair of the links for guiding the cable between two angular positions, and a second coil device arranged at the first end of the chain for passing the cable from the chain to the aerodynamic body. The support of the assembly is statically determinate through the use of a bracket pivotally connected to one of the links at the structural part, which bracket does not permit a translative motion relative to the structural part. This is further supported by a bearing located at one of the links which is connected to the second coil device, which bearing permits angular rotation at least in two orthogonal directions, but no translative motion relative to the aerodynamic body. | 03-12-2015 |
| 20150061587 | Method And Device For Communication With A Personal Electronic Device In An Aircraft - A communication module includes a communication module, having an inductive energy transfer unit, a transfer driver coupled to the inductive energy transfer unit and configured to generate driver signals for operating the inductive energy transfer unit, a charging processor coupled to the transfer driver and configured to control the inductive energy transfer unit to operate in an inductive power charging operation mode, and a communication processor coupled to the transfer driver and configured to control the inductive energy transfer unit to operate in a near field communication (NFC), operation mode. | 03-05-2015 |
| 20150058777 | AIRCRAFT WITH CENTRALIZED GENERATED AND UNIFIED CABIN CONTROL PANEL DISPLAYS - A method for operating a control panel of an aircraft includes: sending display data from a control panel to a central controller of the aircraft, the display data including values to be displayed on a display screen of the control panel; loading, in the central controller, a display template from a central data storage, the display template including information for layouting the display data; generating a display page for the control panel in the central controller by merging the display data and the display template; sending the display page to the control panel; and displaying the display page on a display screen of the control panel. | 02-26-2015 |
| 20150053838 | Mounting System for Mounting an Object in a Space of a Transportation Means and Transportation Means with a Space and at least one such Mounting System - A mounting system for objects in a transportation means includes a profile rail, at least one locking device with a base body that is bringable in surface contact with a supporting surface of the profile rail and at least one locking body which is interlockable with the profile rail, as well as an actuating device with an actuating element that extends parallel to the profile rail and a clamping body that is connected to the actuating element. The clamping body is realized in such a way that it exerts a compressive force, which results in the locking body being interlocked, upon a component of the locking device during a motion of the actuating element in a first direction parallel to the profile rail and releases the interlock during a motion of the actuating element in a second, opposite direction. | 02-26-2015 |
| 20150053291 | METHOD FOR MANUFACTURING A FLUID ROUTING COMPONENT BY LAYER-WISE BUILDUP - A method for manufacturing a fluid-leading component includes positioning a base element machined by a material-removing method with a planar upper face in a mounting support. The method at least includes the initial application of a layer section with predetermined dimensions of a particulate material in a predetermined region on the planar upper face of the base element; the heating of the layer section by a heat source in such a manner that the particles of the material within predetermined dimensions bond; and the application thereto and heating of at least one further layer section with predetermined dimensions of a particulate material in a predetermined region. In this way it is possible, in the generative manufacturing method, to obviate the need to provide support structures that subsequently have to be removed, and the base element is a functional part of the component to be manufactured. | 02-26-2015 |
| 20150052970 | DROP TEST DEVICE AND METHOD FOR CARRYING OUT A DROP TEST - A drop test device includes a suspension frame, a delay roller which is placed and mounted on the suspension frame, and at least one suspension cable, a first end of which is connected in a stationary manner to an attachment point on the outer surface of the delay roller and a second end of which includes a mounting which can be releasably or fixedly connected to a drop object. | 02-26-2015 |
| 20150041597 | WINGTIP DEVICE OF A WING, AND ALSO A WING WITH SUCH A WINGTIP DEVICE - A wingtip device for a wing is provided. The wingtip device has an inner end and an outer end, and in which the local dihedral of the wingtip device increases or reduces from the inner end to the outer end, with a pressure-side flow surface and a suction-side flow surface. At least two ancillary wing sections are arranged on the wingtip device, projecting in each case from the flow surface of the wingtip device. The ancillary wing sections in each case form an interface with the surface of the wingtip device; which interfaces are located spaced apart from one another. A wing with such a wingtip device is also provided. | 02-12-2015 |
| 20150037549 | PANEL AND METHOD OF PRODUCING SAME - A method of producing a panel for lining or cladding an aircraft interior, such as an aircraft cargo hold includes arranging at least one resin layer of a thermo-plastic polymer and at least one reinforcement layer of reinforcement fibres upon one another in a stack, wherein each resin layer extends adjacent and/or substantially parallel to each reinforcement layer; and consolidating the stack to form a panel by applying heat and pressure to the stack. The pressure is applied to the stack in a direction substantially perpendicular to a primary plane of the layers. The pressure is applied to the stack in a non-constant distribution over the primary plane. A corresponding panel for lining or cladding an aircraft interior, such as a cargo hold is also described. | 02-05-2015 |
| 20150036697 | Method Of Transmitting Speech And Digital Data Via An Analog Speech Channel - A method of transmitting speech and digital data via an analog speech channel within a single frequency band, wherein an analog speech signal is transmitted via the speech channel and a stream of digital data is encoded by an encoding device to a sequence of blocks of symbols taken from a predetermined set of symbols. The transmission of the analog speech signal is periodically blanked during predetermined spaced time intervals, and the blocks of symbols are transmitted during the time intervals. In each time interval a plurality of signals are transmitted via a corresponding plurality of spaced predetermined carrier frequencies. A receiver receives the analog speech signal and the signals transmitted during the time intervals. The signals are demodulated to recover the individual symbols and the respective block of symbols transmitted during the time interval groups, and the digital data is recovered by decoding recovered blocks of symbols. | 02-05-2015 |
| 20150029737 | DAYLIGHT INPUT IN AIRCRAFT - An aircraft with a daylight input system may provide improved illumination with a reduced energy demand. The aircraft has a fuselage construction and at least one interior area arranged within the fuselage construction and includes the daylight input system. The daylight input system includes at least one light receiving device arranged in an outer wall, at least one light guiding device and at least one light emitting device arranged on the inner side. In this case, the light receiving device serves for receiving daylight present in the surrounding outside the outer wall and transmitting the same into the light guiding device. The light guiding device optically couples the light receiving device to the light emitting device. This light emitting device in turn emits the received daylight into an interior space on the inner side of a wall construction, wherein at least a partial deflection of the daylight is provided. | 01-29-2015 |
| 20150008285 | PRESSURE FUSELAGE OF AN AIRCRAFT WITH A FUSELAGE SHELL AND A PRESSURE BULKHEAD DISPOSED THEREIN - A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells. | 01-08-2015 |
| 20140349214 | Device For Cooling And Dehumidifying Gases, Method For Cooling And Dehumidifying Gases, And Vehicle With A Fuel Cell System And A Device For Cooling And Dehumidifying Fuel Cell Exhaust Air - A device for cooling and dehumidifying gases includes a first hollow body with a gas inlet, a gas outlet and a condensate drain; a second hollow body with a coolant inlet and a coolant outlet; and a drive unit. The first hollow body encloses the second hollow body at least in part. One of the first hollow body and the second hollow body is pivotally held relative to the other hollow body and includes at least one turbulence-generating body that extends in the direction of the other hollow body. For rotating the pivotally held hollow body the drive unit is couplable to the hollow body. In this manner a single-stage device for cooling and dehumidifying gases that include water vapor is implemented, which device requires little installation space and is of a particularly lightweight construction. Thus the device is particularly well suited for use in vehicles, in particular in aircraft. | 11-27-2014 |
| 20140349042 | Variable-Length Rail Cover For A Seat Rail - A rail cover for a seat rail includes a plurality of longitudinal section parts, wherein each longitudinal section part includes a first partial longitudinal section and a second partial longitudinal section, which abut one another in the longitudinal direction of the longitudinal section part. A first longitudinal section part is movable in the longitudinal direction of the rail cover with respect to a second longitudinal section part abutting the first longitudinal section part in the longitudinal direction of the rail cover, wherein in a non-expanded state of the rail cover, the first partial longitudinal section of the second longitudinal section part overlaps the second partial longitudinal section of the first longitudinal section part in the longitudinal direction of the rail cover. | 11-27-2014 |
| 20140346282 | FLAP ARRANGEMENT FOR A WING OF AN AIRCRAFT AND AN AIRCRAFT WITH A WING COMPRISING SUCH A FLAP ARRANGEMENT - A flap arrangement for a wing of an aircraft includes a base member, at least one first flap, at least one second flap and at least one connecting assembly. The first flap is movably supported on the base member and the second flap is movably supported on the first flap. The connecting assembly is mechanically coupled with the base member and the second flap and is designed to move the second flap relative to the first flap when the first flap is moved relative to the base member. Due to the resulting forced guiding of a second flap relative to a first flap a separate actuator for moving the second flap and linkages extending outside of the shape defining contour of the flap arrangement may substantially be eliminated. | 11-27-2014 |
| 20140346277 | DEVICE FOR LIMITING THE DEFLECTION ON A DOOR ARRANGED IN A FUSELAGE CELL OF AN AIRCRAFT - The invention relates to a device for limiting the deflection of a door ( | 11-27-2014 |
| 20140343784 | ACTUATION SYSTEM FOR FLIGHT CONTROL SURFACE - The present disclosure provides an actuation system for a flight control surface of an aircraft, having: a support frame for supporting a flight control surface, the support frame being configured to be mounted to an airframe structure of the aircraft for movement between a first position and a second position to operate and move the control surface; an actuation mechanism configured to effect movement of the support frame between the second position and the first position; and a detection device for detecting a fault in the actuation mechanism, the detection device comprising a deflector configured to deflect or skew the support frame away from or out of the first position in the event of a fault in the actuation mechanism. | 11-20-2014 |
| 20140339360 | Modifiable aircraft monument - An aircraft monument for installation in an aircraft cabin comprising a first functional module, a second functional module and a side wall for delimiting the first module from at least one of a region of the aircraft cabin adjacent to the first module and a region of the aircraft monument adjacent to the first module. The side wall is movable between a first and a second operational position and comprises a first side-wall region separating the first and second functional modules and in the second operational position, the side wall is displaced in the direction of the second module relative to its position in the first operational position, so that a movement of the side wall from its first operational position into its second operational position results in an enlargement of a base area of the first module and a corresponding diminution of a base area of the second module. | 11-20-2014 |
| 20140329452 | PASSENGER SUPPLY SYSTEM FOR INSTALLATION IN A PASSENGER SUPPLY CHANNEL - A passenger supply system installed in a passenger supply channel (PSC) on board a vehicle, such as an aircraft. The supply system comprises a rail track configured to be mounted along the PSC. The supply system further comprises an indiv panel mounted on the rail track and connectable to the PSC for supplying a passenger with conditioned air, medical outlet and/or oxygen. The indiv panel comprises a crossover area. The supply system further comprises a passenger supply unit mounted on the rail track and connectable to the PSC for supplying the passenger with light, visual information and/or sound information. The supply unit comprises an overlapping area. The supply unit and the indiv panel are configured such that in a mounted state of the supply unit and of the indiv panel the overlapping area of the supply unit at least partially overlaps with the crossover area of the indiv panel. | 11-06-2014 |
| 20140326829 | Cabin attendant seat with additional support - A cabin attendant seat for an aircraft, a seat system comprising such a cabin attendant seat, an aircraft monument comprising such a cabin attendant seat and an aircraft comprising such an aircraft monument. The cabin attendant seat comprises a backrest element and a seat element. The cabin attendant seat is movable from a starting position into at least one end position. The cabin attendant seat further comprises an adapter element, the adapter element being arranged in the cabin attendant seat and configured to connect the cabin attendant seat, in the at least one end position, to an aircraft seat provided in the aircraft. | 11-06-2014 |
| 20140323170 | METHOD FOR CONSIDERABLY ENHANCING THE AVAILABILITY OF WIRELESS CONNECTIONS - A control unit and a method for controlling a wireless data transmission between a wireless terminal and access points of a communications network in a transportation device, as well as a computer program for executing the method. The wireless terminal is assigned to two or more of the access points in such a way that one communications channel is available between the wireless terminal and the access points for wireless data transmission between the wireless terminal and the access points. A control unit is used, in the case of transmission from the access points towards the wireless terminal, to select at least one of the access points for wireless transmission to the terminal and/or in the case of transmission from the terminal towards the access points, to determine a message for further use in the communications network based on the messages received from the terminal by the access points. | 10-30-2014 |
| 20140318701 | SANDWICH PANEL WITH INTEGRATED REINFORCING STRUCTURE AND METHOD FOR THE PRODUCTION THEREOF - A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said core having at least one recess into which a stopper is introduced, into which at least one attachment element can be introduced to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fibre running direction being wound around the core. In addition, the invention relates to a method for the production of a sandwich panel according to the invention. | 10-30-2014 |
| 20140318235 | METHOD AND SYSTEM FOR MONITORING THE OPERATIONAL STATE OF A PUMP - A method and a system for monitoring the operational state of a pump including acquiring a set characteristic diagram of the pump, the characteristic diagram of the pump being defined by a functional relationship between a first pump operating parameter characteristic of the operational state of the pump and a second pump operating parameter characteristic of the operational state of the pump. Subsequently, an actual characteristic diagram of the pump is acquired when the pump is installed in a higher-level system, in particular an aircraft system, and is running. Finally, the actual characteristic diagram of the pump is compared with the set characteristic diagram of the pump. | 10-30-2014 |
| 20140312174 | WING TIP SHAPE FOR A WING, IN PARTICULAR OF AIRCRAFT - A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction. | 10-23-2014 |
| 20140312173 | DOUBLE CABIN ATTENDANT SEAT - A cabin attendant seat for an aircraft, an aircraft monument comprising such a cabin attendant seat and an aircraft comprising such an aircraft monument. The cabin attendant seat is movable from a starting position into at least one end position. The cabin attendant seat includes at least one backrest element and two seat elements. Each of the two seat elements is movable relative to the at least one backrest element between a folded position and an unfolded position. | 10-23-2014 |
| 20140309811 | WIRELESS NETWORK FOR CONTROLLING THE OXYGEN SYSTEM OF AN AIRCRAFT - A control device for activating an oxygen system of a means of transport, in particular an aircraft, a control system having such a control device, an associated method for activating an oxygen system of a means of transport, in particular an aircraft, and a computer program for carrying out the method. Furthermore, a network is provided for a means of transport, in particular for an aircraft. The control device for activating the oxygen system comprises a first activation unit which is configured to activate at least a part of the oxygen system by wireless transmission of a first activation signal. | 10-16-2014 |
| 20140306372 | Method And Apparatus For Producing A Fiber-Reinforced Plastics Casting - An apparatus and method for producing a fiber-reinforced plastics casting (FRP), includes a moulding box filled with free flowing moulding material, in what a prototype of casting or a textile preform is inserted, forming a mould cavity for infiltration the inserted preform of textile with synthetic resin material in order to form a fiber-reinforced plastics casting (FRP). | 10-16-2014 |
| 20140306061 | PASSENGER SEAT AND PASSENGER SEATING SYSTEM HAVING A FLEXIBLE SEATING ARRANGEMENT FOR MEANS OF PASSENGER TRANSPORT - A folding passenger seat and a corresponding passenger seating system for means of passenger transport are provided. The folding passenger seat comprises a seat frame, on which a front seat leg having a first fastening element and a rear seat leg having a second fastening element are arranged. The first fastening element and the second fastening element are configured to be connected to rails on a cabin floor of the means of passenger transport and to be displaced in the rails. A first joint element is arranged between the first fastening element and the second fastening element such that a spacing between the first fastening element and the second fastening element is variable. In particular, the first joint element may be arranged between the front seat leg and the seat frame or between the rear seat leg and the seat frame. | 10-16-2014 |
| 20140301095 | Exterior Structure Component For An Aircraft, Aircraft With An Exterior Structure Component, And Method For Manufacturing An Exterior Structure Component For An Aircraft - An exterior structure component for an aircraft with an illuminating device includes a structure with an interior side and an exterior surface with at least one illuminated region and a multitude of optical fibers that extend from the interior side to the at least one illuminated region of the exterior surface. The optical fibers end on the interior side of the exterior structure component in a common interface area that is couplable to an illuminating device. The structure is made from a fiber composite material in which the optical fibers are integrated. In this manner a particularly weight-saving illuminating device that is capable of withstanding external influences may be provided. | 10-09-2014 |
| 20140299309 | Aircraft Cooling System - An aircraft cooling system including a cooler which is adapted to supply cooling energy to an aircraft device to be cooled, and a heat transfer arrangement which is adapted to transfer waste heat generated by the cooler to a cabin air extraction system. The heat transfer arrangement comprises a heat transfer circuit, in which a liquid heat transfer medium heated by the waste heat of the cooler circulates. | 10-09-2014 |
| 20140299290 | Aircraft air-conditioning system - An aircraft air-conditioning system including an air-conditioning unit which is designed to provide cooled process air. A process air line conducts cooled process air provided by the air-conditioning unit into a working area of an aircraft cabin. A cooler supplies cooling energy to a device to be cooled which is provided in the working area of the aircraft cabin. Finally, the aircraft air-conditioning system includes a heat transfer arrangement which transfers waste heat generated by the cooler to process air flowing through the process air line. | 10-09-2014 |
| 20140298824 | Aircraft cooling system and method for operating an aircraft cooling system - An aircraft cooling system including a cooler having a cold transfer circuit, in which a cold transfer medium circulates. The cooler supplies cooling energy to an aircraft device to be cooled. The aircraft cooling system further includes a heat transfer arrangement having a heat transfer circuit, in which a heat transfer medium circulates and which is thermally coupled to the cold transfer circuit of the cooler via a heat exchanger, in order to absorb waste heat generated by the cooler and transfer it to a cabin air extraction system. The heat transfer arrangement further includes at least one heat pump which brings about an increase of the heat energy transfer from the cold transfer medium circulating in the cold transfer circuit of the cooler to the heat transfer medium circulating in the heat transfer circuit, at least in certain operating phases of the aircraft cooling system. | 10-09-2014 |
| 20140298582 | Crew Rest Compartment And Means Of Transport - A crew rest compartment for a means of transport includes a first bunk and a second bunk, wherein the first bunk is located above the second bunk. Each bunk includes a sleeping area for accommodating a sleeping crew member, wherein each sleeping area has a longitudinal direction. The first bunk is aligned such that the longitudinal direction of the first bunk and a longitudinal direction of the crew rest compartment enclose an angle which differs from 0° and 90°. | 10-09-2014 |
| 20140295773 | TRANSMITTER FOR WAKING UP ELECTRONIC SYSTEMS, RECEIVER, AIRCRAFT AND SPACECRAFT AND METHOD - The present disclosure pertains to a transmitter for waking up electronic systems with a first signal generator which is designed to generate a carrier signal with a first frequency, a second signal generator which is designed to generate an informational signal with a second frequency, a single-sideband modulator which is designed to modulate the information signal by the carrier signal, and a transmission device which is designed to emit the generated carrier signal and the modulated information signal. The present disclosure also pertains to a receiver, an aircraft and spacecraft and a method. | 10-02-2014 |
| 20140286691 | Fuselage Structure For A Means Of Transport, Means Of Transport And Method For Producing A Fuselage Structure For A Means Of Transport - A fuselage structure for a means of transport includes at least two fuselage segments, in each case including an outer skin with an end edge. In a connecting region of two fuselage segments the end edges of the fuselage segments are spaced apart from each other. Connecting elements establish a mechanical connection between two fuselage segments. Conducting structure-borne sound is reduced by multiple deflection of the sound path, and thus results in a reduction in structure-borne sound-induced noise in the cabin of the means of transport. | 09-25-2014 |
| 20140284973 | SEAT WITH UNIVERSAL DEVICE FOR RECEIVING AN ELECTRONIC GADGET FOR AN AIRCRAFT OR SPACECRAFT - The present disclosure pertains to a seat for an aircraft or spacecraft, including a receiving device which is integrated inside the seat and is configured to receive, in an exchangeable manner, an electronic gadget fitted with a screen, and including a safety screen which is arranged in the seat such that the screen is inaccessible from outside but is visible through the safety screen, wherein the receiving device is configured to receive an electronic gadget in the form of a tablet PC or a PDA. The present disclosure furthermore pertains to a corresponding aircraft or spacecraft. | 09-25-2014 |
| 20140265481 | SEAT DEVICE FOR AN AIRCRAFT OR SPACECRAFT - The present disclosure pertains to a seat device for an aircraft or spacecraft with at least one photoelectric device, which is designed to provide electrical energy such that this energy can be used to charge or supply an electrical device, and/or amplify audio signals, and/or transmit data. | 09-18-2014 |
| 20140242910 | METHOD AND SYSTEM FOR ALLOCATING PERSONAL ELECTRONIC DEVICES TO SEATS IN AN AIRCRAFT - The present disclosure relates to a method for allocating a personal electronic device (PED) to a seat in an aircraft, including of connecting a PED to a wireless network of the aircraft, identifying the PED to a near-field communications device of a seat of the aircraft, matching and assigning the seat to which the PED has been identified to the connection data of the PED to the wireless network of the aircraft, and unlocking seat-based control functions for the PED via the wireless network of the aircraft. | 08-28-2014 |
| 20140241282 | MONITORING THE HIGH-FREQUENCY AMBIENT PARAMETERS BY MEANS OF A WIRELESS NETWORK IN AN AIRCRAFT - A network node of a wireless communications network is provided in a means of transportation, for an aircraft, for ascertaining sources of interference, to a system with such a network node, to an associated method for ascertaining sources of interference of a wireless communications network provided in a means of transportation, for the aircraft, and to a computer program for executing the method. The network node includes an interference-power-ascertaining component, for ascertaining an interference power of an interfering radiation emitted from a source of interference, and a transmitting component for wireless or wirebound transmission of the ascertained interference power to a control device for determining at least one of a direction of the interfering radiation and a distance of the source of interference, including the position of the source of interference, on the basis of the ascertained interference power. | 08-28-2014 |
| 20140238501 | AIRCRAFT INERTING SYSTEM - A method of controlling a flow rate of inerting gas introduced into a vented aircraft fuel tank, the method comprising: monitoring changes in a quantity of a fuel in the aircraft fuel tank; monitoring changes in the ambient air pressure external to the aircraft fuel tank; and actively controlling a flow rate of inerting gas, {dot over (m)}(I), introduced into the aircraft fuel tank based upon changes in the quantity of fuel in the fuel tank and changes in the ambient air pressure, p. Also, an aircraft including a vented fuel tank, a supply of inerting gas for rendering inert the fuel tank ullage, and a controller for performing the method. | 08-28-2014 |
| 20140216635 | METHOD FOR ASSEMBLING ELEMENTS OF COMPOSITE MATERIAL FOR AIRCRAFTS, WITH STRESS RELAXATION IN THE ELEMENTS - The invention relates to a method of assembling composite material parts ( | 08-07-2014 |
| 20140209648 | Holding Arrangement For A Mobile Device, Passenger Seat With A Holding Arrangement For A Mobile Device And Vehicle - A holding arrangement for a mobile device in a cabin of a vehicle has a cabin equipment component, a support device arranged on the cabin equipment component, a holding device for holding a mobile device and a covering pane. The support device is designed to receive the holding device and further has an access opening arranged on a side opposite the cabin equipment component. Furthermore, the support device is designed to slidably hold the covering pane for opening and closing the access opening arranged on the side opposite the cabin equipment component in such a manner that the covering pane is movable to a closed position and to an open position, wherein in its open position the covering pane extends beyond the support device. Hereby, an improved holding function and temporary theft prevention may be accomplished. | 07-31-2014 |
| 20140202824 | FASTENING DEVICE FOR RELEASABLY FASTENING A MECHANISM IN THE REGION OF A FLOOR OF AN AIRCRAFT OR SPACE CRAFT AND ARRANGEMENT FOR A CARGO LOADING SYSTEM - A fastening device is disclosed for releasably fastening a mechanism in the region of a floor of an aircraft or spacecraft and includes a base component and a latch component. The latch component includes at least one holding portion including a latch-component-side holding face and is movably coupled to the base component between an unlocked and a locked position. When positioned in a predefined mounting position on the floor component and/or on the base component, the holding portion of the latch component engages a fastening portion, and the latch-component-side holding face faces the mechanism-side holding face. During passage of the latch component from locked position into unlocked position a gap between the latch-component-side holding face and the mechanism-side holding face continuously widens. The invention further relates to an arrangement for a cargo loading system. | 07-24-2014 |
| 20140196390 | FIREPROOF BULKHEAD OF A HIGHLY POROUS STRUCTURE WITH INTUMESCENT COATING AND METHOD FOR ITS PRODUCTION - The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure. | 07-17-2014 |
| 20140188429 | MEASUREMENT METHOD AND DEVICE FOR DETERMINING THE POSITION OF A PROFILE COMPONENT APPLIED TO A SHELL COMPONENT - A measurement method for determining the position of an omega profile component placed on a shell component of an aircraft, in which the ACTUAL position of the omega profile component relative to the shell component is optically acquired in a contactless manner, so as to subsequently compare the latter with a defined DESIRED position, wherein several adjacently spaced apart measuring points are established at two mutually opposing flank sides of the profile cross section of the omega profile component, through which a regression line is run according to the path measurement principle based on coordinates, whose point of intersection is drawn upon to determine the orthogonal position of the omega profile component relative to the shell component. | 07-03-2014 |
| 20140176935 | Measuring Method And System For Measuring Positions Of Elements Of A Structure - A method for measuring a position of an element of a structure includes the steps of: attaching a receiving device to the element at a measurement position; attaching a first reference device to the receiving device; determining a first measurement point with a first measurement device adapted to measure a position of the first reference device; removing the first reference device; attaching a second reference device to the receiving device; and determining a second measurement point with a second measurement device adapted to measure a position of the second reference device. | 06-26-2014 |
| 20140166819 | Flap System For An Aircraft, Method For Adjusting The Lift Of An Aircraft And Aircraft Comprising A Main Wing And At Least One Flap System - A flap system for an aircraft includes a flow body, a trailing flap and a movement means. The flow body includes an upper surface and a lower surface, the lower surface having a recess. The movement means is attachable to the flow body and the trailing flap. The trailing flap includes a shape that corresponds to the recess in the lower surface. The movement means is adapted for conducting at least a chordwise movement of the trailing flap such that it is movable out of and into the recess of the flow body in absence of a gap between the leading edge of the trailing flap and the flow body. Thereby, a clear increase in a lift coefficient may be achieved, while at the same time maintaining a low complexity and a high reliability of the flap system. | 06-19-2014 |
| 20140166810 | Profiled Strip As A Fire Indication Device In An Aircraft - A door for a storage compartment of an aircraft includes a door leaf and a profiled strip connected to an edge of the door leaf. The profiled strip includes openings that provide a path for gas exchange such that smoke from the storage compartment is detectable outside of the storage compartment by passing the profiled strip. | 06-19-2014 |
| 20140166566 | WATER SUPPLY WITH A BIDIRECTIONAL UV DISINFECTION DEVICE - A water disinfection system includes a water disinfection device, having a UV light generator for the UV treatment of water, and a water pipe, having a first pipe portion and a second pipe portion and a third pipe portion which branches off between the first and the second pipe portion. The water disinfection device includes a first water connection and a second water connection. The first water connection is connected to the first pipe portion. The second water connection is connectable to a water reservoir which is to be provided. The second pipe portion is connectable to a water source which is to be attached. The third pipe portion is connectable to a tap for water, so as to be able in this way to provide an improvement in the water quality. | 06-19-2014 |
| 20140166195 | METHOD AND APPARATUS FOR PRODUCTION OF COMPOSITE PREFORM - A method of producing a composite preform having a profile with variable profile height or width is provided. The method includes: providing a plurality of first fibre layers overlapping or upon one another in or substantially parallel to a primary plane; inserting a second fibre layer via a guide member between two of the first fibre layers at an edge region of the preform profile, such that the second fibre layer extends substantially parallel to the first fibre layers; and positioning the edge region of the preform profile, and thus respective edge regions of the first fibre layers, out of the primary plane to set or determine a dimension of the preform profile in the primary plane. | 06-19-2014 |
| 20140165370 | Screwing Device And Use Of A Screwing Device - A screwing device includes a threaded hole that extends from an insertion opening to an end of the screwing device, which end is opposite the insertion opening. In the region of the insertion opening a first radial sealing element is arranged that by way of the insertion opening extends outwards in an axial direction of the hole. Spaced apart from the first sealing element in an axial direction of the hole a second radial sealing element is arranged in the screwing device with the internal diameter of the second radial sealing element being smaller than the external diameter of the threaded hole. In this manner a screwing device may be provided that is self-locking, exchangeable, and fluid-proof and that is suitable especially for vehicles and in particular for aircraft. | 06-19-2014 |
| 20140158208 | DRAINING APPARATUS FOR DRAINING LIQUIDS FROM A VEHICLE, AIRCRAFT HAVING A DRAINING APPARATUS AND METHOD FOR DRAINING LIQUIDS FROM A VEHICLE - A draining apparatus for draining liquids from a vehicle includes a containment; a drain mast having an outlet opening and an inlet; and an actuator. The containment is adapted for being coupled with a structure of the vehicle, wherein the actuator is coupled with the drain mast and adapted for moving the drain mast into a retracted position and at least one extracted position relative to the containment, and wherein the containment is further adapted for accommodating the drain mast in the retracted position at least partially. The drainage apparatus has clear advantages regarding the parasitic drag compared to known drainage masts as it is only deployed into the flow when it is absolutely necessary. | 06-12-2014 |
| 20140154447 | Peelable adapter element - A peelable adapter element for balancing out assembly and/or component tolerances, with a core body to define a minimum dimension and at least one stack of films bound to the core body to define a maximum dimension, which includes a plurality of peelable metal films detachably joined with each other by a respective binder film. The core body is formed of a plastic matrix with integrated fiber reinforcement. | 06-05-2014 |
| 20140152088 | System And A Method For Determining A Cabin Layout In A Cabin Of A Vehicle And To An Aircraft - A system for determining a cabin layout in a cabin of a vehicle, includes a system for contactless transfer of power with primary magnetic elements and secondary magnetic elements that each overlap with at least one primary magnetic element. Based on sequentially providing power to primary magnetic elements and measuring at least one electric value in the powered primary magnetic element overlapping states of secondary magnetic elements and primary magnetic elements can be determined. By determining overlapping states for all primary magnetic elements in the cabin the number and positions of all secondary magnetic elements and all vehicle components attached thereto can be collected. The system avoids powering two contiguous primary magnetic elements to prevent a wrong determination of an overlapping state. | 06-05-2014 |
| 20140151511 | AIRCRAFT WITH AT LEAST TWO AIRCRAFT FUSELAGES AND TWO MAIN WINGS - An aircraft includes at least two aircraft fuselages and two elongate main wings, wherein the main wings each have an extension direction which are at an angle to one another that differs from zero. Each of the two main wings is connected to the at least two aircraft fuselages. The main wings can thus be equipped mechanically simply and so as to have a low weight, and at the same time the transmission of forces between the wings and the fuselages is performed via a plurality of connections, and this leads to a relatively low material stress. | 06-05-2014 |
| 20140151510 | Formvariable Aerodynamic Fairing Body For A Flap Actuator Mechanism Of An Aircraft - An aerodynamic fairing body for an aircraft, a corresponding aircraft and a corresponding method of manufacture for an aerodynamic fairing body are described. The fairing body is configured so as to accommodate a flap adjustment mechanism. Further, the fairing body is configured so as to be arranged at a predetermined distance from an engine of the aircraft, which produces a blast which varies depending on the flight phase. Furthermore, the fairing body is configured so as to be varied in shape in such a way that the fairing body is located outside the blast of the engine permanently. In other words, the fairing body can be varied in shape in such a way that it is located outside the engine blast in any flight phase of the aircraft. | 06-05-2014 |
| 20140151309 | WATER SUPPLY SYSTEM COMPRISING A VENTURI PIPE - A water supply system includes a first pipe, a water reservoir, and a Venturi pipe having a first Venturi nozzle terminal, a second Venturi nozzle terminal and a Venturi nozzle branch arranged between the first and second Venturi nozzle terminal. The first Venturi nozzle terminal is connected via the first pipe to the water reservoir. The first Venturi nozzle terminal is connectable to a second pipe to fill the water reservoir. The branch of the Venturi pipe is connectable to a third pipe to supply taps. Water flows through the Venturi pipe from the first Venturi nozzle terminal to the second Venturi nozzle terminal when the water reservoir is filled, and water flows through the Venturi pipe from the second Venturi nozzle terminal to the Venturi nozzle branch during the supply procedure, to provide a water supply system which requires less maintenance and is less temperamental. | 06-05-2014 |
| 20140141193 | METHOD AND APPARATUS FOR FORMING A CURVED PREPREG STRIP - The present invention relates to a method of forming a curved prepreg strip or sheet, especially for use in fabricating a composite component. The method includes providing a strip or sheet of prepreg material having reinforcing fibres and drawing or conveying the prepreg material in a travel direction, wherein the material is drawn or conveyed in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction. Similarly, the invention relates to an apparatus for forming a curved prepreg strip or sheet, having: a mechanism for drawing or conveying a strip or sheet of prepreg material in a travel direction, wherein the mechanism is configured to draw or convey the strip or sheet of prepreg material in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction. | 05-22-2014 |
| 20140140864 | HYDRAULIC MOTOR-PUMP-ARRANGEMENT AND HYDRAULIC SYSTEM FOR A VEHICLE - An arrangement for selectively making available hydraulic power in separate hydraulic circuits comprises two displacement machines, two free-wheels and a drive unit that is preferably arranged between the displacement machines. The free-wheels block in opposite directions and are coupled to the displacement machines. Consequently, the first displacement machine is driven in a first rotating direction of the drive unit while the second displacement machine is only driven in a second, opposite rotating direction of the drive unit. This makes it possible to realize an intermittent operation for selectively making available additional hydraulic power in separate hydraulic subsystems by choosing the rotating direction accordingly. This arrangement can reduce the weight and the complexity of a hydraulic system. | 05-22-2014 |
| 20140138483 | TOILET ARRANGEMENT FOR A VEHICLE - A toilet arrangement for a vehicle includes a first toilet compartment, an adjacent second toilet compartment and a partition wall situated between the first toilet compartment and the second toilet compartment, wherein the partition wall is movably supported and designed for being transferred into an open position, in which the partition between the first toilet compartment and the second toilet compartment is removed. This makes it possible to convert two relatively small toilet compartments into a larger toilet compartment that is suitable for use by persons with limited mobility. | 05-22-2014 |
| 20140138480 | HIGH LIFT SYSTEM FOR AN AIRCRAFT WITH TWO SEPARATE DRIVE UNITS - A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves. | 05-22-2014 |
| 20140134043 | REINFORCED VEHICLE STRUCTURAL PART, VEHICLE AND METHOD - A vehicle structure component reinforced by means of an area, a vehicle including such a vehicle structure component, and a corresponding method to reinforce a vehicle structure component are proposed. The area includes a compressive residual stress in a first direction and a compressive or tensile residual stress in a second direction being vertically aligned to the first direction, wherein the ratio of the compressive stress in the first direction and the compressive or tensile residual stress lies between −0.2 and +1.0. Hence, the propagation direction of cracks in such areas is diverted, faster pressure equalization takes place, and further crack propagation is inhibited. | 05-15-2014 |
| 20140131917 | METHOD AND APPARATUS FOR PRODUCING AN AIRCRAFT STRUCTURAL COMPONENT - A method for producing an aircraft structural component includes the steps of introducing a plurality of semi-finished product layers for producing a component from a fibre-reinforced, thermoplastic plastic material into a compression mould, applying pressure to the stacked semi-finished product layers, the stacked semi-finished product layers being fixed, before pressure is applied, at particular points in their position in the compression mould and/or relative to one another in such a way that, while pressure is being applied to the semi-finished product layers stacked in the compression mould, a sliding movement of the semi-finished product layers relative to one another and/or relative to the compression mould, preventing wrinkling in the semi-finished product layers, takes place, and removing the aircraft structural component from the compression mould. | 05-15-2014 |
| 20140126096 | Apparatus And Method For An Under-Voltage Protection Of An Electrical Network, Especially In An Aircraft Comprising A Fuel Cell - An apparatus for protecting an electrical network of an aircraft includes a power switch, an activation means coupled with the power switch, and a detection circuit connectable to the electrical network for detecting a voltage. The detection circuit is coupled with the activation means. The activation means is adapted for opening the power switch once the detected voltage is lower than a predetermined voltage. This is particularly advantageous for high voltage direct current networks temporarily, primarily or permanently powered by a fuel cell system. | 05-08-2014 |
| 20140120357 | Composition for the Local Application of Chemical Conversion Layers - An aqueous composition for forming a chemical conversion layer on a metal surface, wherein the composition contains at least one active component for the formation of the chemical conversion layer, as well as at least one thickener, and has a viscosity in the range between 10 mPa*s and 10000 mPa*s. | 05-01-2014 |
| 20140113207 | FUEL CELL SYSTEM FOR GENERATING ENERGY AND WATER - Fuel cell systems aboard means of transport can be used for generating energy and for producing water. In order to reduce the overall weight of the system, the fuel cell is controlled or regulated in dependence on a current fill level or a limit level of the water tank, as well as a predicted future water consumption. In this way, it may be possible to minimize the water quantity to be stored in the water tank. | 04-24-2014 |
| 20140104732 | SUPPLY SYSTEM FOR AN AIRCRAFT, USE OF A SHIELDED SUPPLY LINE IN AN AIRCRAFT AND AN AIRCRAFT WITH A SUPPLY SYSTEM - A supply system for supplying energy in an aircraft includes at least one electrical line including at least one core connectable to a pole of a current source, an electrically conductive shield, and a detection unit having at least two electrical inputs. The shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield. At least one port of the detection unit is connected to the at least one core. At least another port of the detection unit is connected to at least one of the shield and the at least one core. The detection unit is adapted for detecting a differential current over the at least one core or an absolute current between the shield and a ground potential for generating a warning signal if a predetermined threshold value for the detected current value is exceeded. | 04-17-2014 |
| 20140097662 | VARIABLE-LENGTH RAIL COVER - A rail cover for a seat rail includes a cover element for completely covering a longitudinal portion of the seat rail. The cover element extends at least in part in a plane of extension that is formed by a longitudinal direction and a transverse direction of the rail cover and includes a first, rigid, longitudinal portion and a second longitudinal portion that follows on from the first longitudinal portion. The first longitudinal portion and the second longitudinal portion are mechanically coupled together by means of a flexible portion, wherein the second longitudinal portion is designed to carry out a pivoting movement in a direction across the plane of extension. | 04-10-2014 |
| 20140090802 | AIRCRAFT THERMAL CONTROL SYSTEM AND METHOD OF OPERATING AN AIRCRAFT THERMAL CONTROL SYSTEM - An aircraft thermal control system includes a thermal control unit including an internal circuit, an evaporator and a condenser, the evaporator and the condenser being disposed in the internal circuit. The aircraft thermal control system further includes a cooling circuit which is thermally coupled to the evaporator of the thermal control unit, and a heating circuit which is thermally coupled to the condenser of the thermal control unit. | 04-03-2014 |
| 20140087283 | FUEL CELL SYSTEM FOR AN AIRCRAFT, METHOD FOR OPERATING A FUEL CELL SYSTEM IN AN AIRCRAFT AND AIRCRAFT WITH SUCH A FUEL CELL SYSTEM - A fuel cell system includes a first fuel cell unit having a first fuel cell and a second fuel cell, a second fuel cell unit having a third fuel cell and a fourth fuel cell, a hydrogen tank coupled to all fuel cells, an oxygen supply unit and an air inlet. Oxidant inlets of the first fuel cell and the fourth fuel cell are couplable with the air inlet. Oxidant inlets of the second fuel cell and the third fuel cell are couplable with the oxidant supply unit couplable with at least one of the oxygen supply unit and the air inlet. Exhaust outlets of the first and fourth fuel cells are couplable with an inert gas outlet. Exhaust outlets of the second and third fuel cells are coupled with an exhaust switching unit couplable with the inert gas outlet and a water outlet. | 03-27-2014 |
| 20140087143 | Method for producing a structural component, and structural component - A method for manufacturing a structural assembly comprising at least two assembly components interconnected by means of a thermoplastic plastics material, and useful in the field of aviation or space travel. First, a first assembly component and a second assembly component are provided and arranged so as to form an arrangement. Second, the arrangement is subjected to creep forming at a temperature which is selected in such a way that the thermoplastic plastics material melts at least in part during the creep forming so as to connect the first assembly component and the second assembly component. The invention further relates to structural assemblies, in particular for an aircraft or spacecraft, and to an aircraft or spacecraft comprising a structural assembly of this type. | 03-27-2014 |
| 20140084951 | METHOD FOR DETECTING A DEVICE THAT GENERATES SPURIOUS SIGNALS IN AN ELECTRICAL NETWORK, AN ELECTRICAL SYSTEM AND AN AIRCRAFT - A method for detecting a device that generates spurious signals in an electrical network, to which several devices and at least one fault detection device are connected, includes the steps of monitoring the electrical network for electrical spurious signals, sequentially deactivating each device for a predetermined time T when an electrical spurious signal has been detected, and checking the electrical network for the disappearance of the respective spurious signal, and signaling as soon as the respective spurious signal has disappeared upon deactivating a respective device. This makes it possible to especially reliably detect a device in an electrical network that couples an undesired spurious signal into the network. | 03-27-2014 |
| 20140084508 | METHOD AND DEVICE FOR PRODUCING A FIBRE COMPOSITE COMPONENT - The present invention provides a method for producing a fibre composite component, comprising: arranging a first and a second mould in relation to one another in such a way that these together form a first cavity; laying a fibre material on the first and/or second mould; filling the formed first cavity with a casting material and solidifying said casting material in order to seal the first and the second mould to one another and/or interconnect them; and infiltrating the fibre material with a matrix and curing said matrix to form the fibre composite component. | 03-27-2014 |
| 20140079956 | METHOD, SYSTEM AND MOLDING TOOL FOR MANUFACTURING COMPONENTS FROM COMPOSITE FIBER MATERIALS - In a method for manufacturing components from composite fiber materials, at least one placeholder is inserted into a recess in a molding tool, wherein the unfinished component is subsequently produced, the placeholder is removed, at least one lifting pad is inserted into the recess and the unfinished component is removed from the molding tool by inflating the lifting pad. In a system for manufacturing components from composite fiber materials, the component removal process is monitored and controlled by a computer unit in order to prevent predetermined maximum component loads from being exceeded. The gentle component removal process makes it possible to avoid consequential costs for repairing or reworking the components. | 03-20-2014 |
| 20140077577 | Device for the attachment of seats in passenger cabins, a seat track, a holding device, and a method - A device for the attachment of seats in passenger cabins of aeroplanes, road coaches, ships, railways, and similar, with at least one seat track, which has at least one exterior latching section, and with at least one holding device for purposes of attaching the seat to the at least one seat track. The at least one holding device has two integrated arms to engage around the latching sections and a multiplicity of teeth to fix it in position. The teeth can be moved in the vertical direction of the seat track. A seat track thermally is coated on at least some sections with exterior latching sections. A method is disclosed for the attachment of seats in passenger cabins. | 03-20-2014 |
| 20140072472 | DYNAMIC DISINFECTION METHOD FOR A VEHICLE DRINKING WATER TANK - A method for disinfecting a vehicle drinking water tank is disclosed, wherein the method is designed for dynamic disinfection. By providing a vehicle drinking water tank with a spray diffuser, which is arranged inside the vehicle drinking water tank, the disinfecting liquid can be sprayed over substantially the entire inner surface of the tank. Partial filling of the drinking water tank with a disinfecting liquid starts the disinfection method. The dynamics of the disinfection method are achieved by spraying the disinfecting liquid in such a way that a moved film of disinfecting liquid is formed and wets an inner surface of the drinking water tank. Material transport at the inner wall of the tank is improved and mechanical shear forces act on the biofilm, which is to be removed and/or disinfected, in combination with the biochemical disinfection forces. | 03-13-2014 |
| 20140061387 | SURFACE ELEMENT FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR IMPROVING HIGH-LIFT GENERATION ON A SURFACE ELEMENT - A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an additional flap for harmonizing the flow above a pylon or other add-on body can be eliminated. | 03-06-2014 |
| 20140060090 | Method of servicing an aircraft cooling system and aircraft cooling system - A method of servicing an aircraft cooling system comprises connecting a refilling container containing a two-phase refrigerant to a refrigerant connection provided in a cooling circuit of the cooling system, supplying refrigerant from the refilling container into the cooling circuit of the cooling system, and operating a condenser disposed in the cooling circuit so as to liquefy gaseous refrigerant flowing through the cooling circuit. | 03-06-2014 |
| 20140059826 | SYSTEMS AND METHODS FOR LOAD INTRODUCTION ELEMENT FOR A MOVABLE SURFACE OF AN AIRCRAFT - A load introduction element for a movable surface of an aircraft comprises a load introduction body that is connectable with the surface. A fitting connected with the load introduction body with a first section and a second section. The first section comprises a first bearing means, the second section comprises a second bearing means, and the first or second section comprises a third bearing means. The fitting is pivotally connected with the load introduction body by way of the first bearing means. An adjustment unit connects the second bearing means with the load introduction body in a variable position and is positioned on a side of the load introduction body that is opposite the fitting. In this manner adjustment of a reference position of a surface takes place without the need for an access flap. By loosening the adjustment unit the movable surface is pivotable without moving a flap drive. | 03-06-2014 |
| 20140054420 | PASSIVE LOAD ALLEVIATION FOR A FIBER REINFORCED WING BOX OF AN AIRCRAFT WITH A STIFFENED SHELL STRUCTURE - Awing box of an aircraft with a stiffened shell structure, consisting of fiber reinforced material includes a skin for absorbing shear loads, and several stringers arranged on the inner side of the wing box for absorbing axial loads, in which at least 60% of the mass of the stiffened shell structure is concentrated in the stringers, wherein the stringers provide at least 80% of the axial stiffness of the stiffened shell structure. In the specific case of wing structure, this embodiment allows the use of unbalanced laminates for the skin to induce higher nose-down twist of the wing box without any loss in bending stiffness and so envisaging higher weight saving capability. | 02-27-2014 |
| 20140054419 | PRESSURIZED AIRPLANE FUSELAGE, COMPRISING A PRESSURE BULKHEAD - A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area, wherein the edge of the pressure bulkhead is circumferentially attached to the fuselage structure by fastening means, wherein the fastening means include a pair of ring-shaped attachment frames made of an open or hollow profile, which are disposed at each side of the pressure bulkhead respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure. | 02-27-2014 |
| 20140054418 | DOOR FRAME CONSTRUCTION, FUSELAGE PORTION AND AIRCRAFT OR SPACECRAFT - The present invention provides a door frame construction in particular for an aircraft or spacecraft, including a former; a fibre metal laminate which is connected to the former; and an outer skin which is connected to the fibre metal laminate. | 02-27-2014 |
| 20140051014 | METHOD FOR MANUFACTURING A SOLID OXIDE FUEL CELL ELEMENT BY LAYER-WISE BUILDUP AND SOLID OXIDE FUEL CELL ELEMENT - A method for manufacturing a solid oxide fuel cell element by layer-wise buildup wherein at least one section of the element is built up by carrying out a step that at least includes the following at least once: applying a layer section of a particulate ceramic material with predefined dimensions onto a base layer in a predefined area and heating the layer section by means of a heat source such that the particles of the ceramic material connect to one another within the predefined dimensions. The solid oxide fuel cell element manufactured with the method is realized in one piece, as well as highly compact, and has a low weight. | 02-20-2014 |
| 20140050884 | STRUCTURAL COMPONENT COMPRISING AT LEAST ONE MAIN-LOAD-BEARING COVERING SHELL AND A CARRIER STRUCTURE FOR FIXING THE MAIN-LOAD-BEARING COVERING SHELL, AND FLOW BODY COMPRISING SUCH A STRUCTURAL COMPONENT - Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part. | 02-20-2014 |
| 20140048656 | HIGH LIFT COMPONENT FOR AN AIRCRAFT, HIGH LIFT SYSTEM, METHOD FOR ADJUSTING THE HIGH LIFT CHARACTERISTICS OF AN AIRCRAFT AND AIRCRAFT - A high lift component includes at least one intermediate seal on at least one lateral surface, wherein the intermediate seal includes at least one hollow body made of an elastic material, which hollow body includes a fluid inlet that is connectable to a fluid source. A gap between two high lift components, which gap is subjected to dynamic changes in geometry, can be flexibly sealed in this manner. | 02-20-2014 |
| 20140048655 | HIGH LIFT SYSTEM FOR AN AIRCRAFT AND METHOD FOR INFLUENCING THE HIGH LIFT CHARACTERISTICS OF AN AIRCRAFT - A high lift system for an aircraft includes a basic body, a flap which is movably mounted on the basic body and has a flap edge, and a retaining element. The high lift system is set up to form a gap between the flap edge and the basic body. The retaining element is mounted on a region of the flap close to the flap edge and extends towards the basic body to restrict the distance between the flap edge and the basic body. The retaining element is preferably configured as a linear attachment means. Consequently, a gap dimension between a flap and a basic body can be influenced to restrict flexing effects during loading of the flap and of the basic body. | 02-20-2014 |
| 20140048650 | CABIN SEGMENT, CABIN AND VEHICLE WITH A CABIN - A cabin segment for a vehicle includes two or more parking spaces, arranged side by side and separated from each other by at least one intermediate wall, for accommodating serving trolleys, and furthermore a vehicle attendant seat which on one side is held on one of the at least one intermediate walls so as to be pivotable on an axis. The vehicle attendant seat is pivotable to an in-use position and to an out-of-the-way position. The in-use position and the out-of-the-way position are situated apart by 90° or more relative to the pivoting of the vehicle attendant seat. This makes possible particularly efficient use of space without having to forego parking spaces or a vehicle attendant seat. | 02-20-2014 |
| 20140047814 | DRIVE UNIT, METHOD FOR PROVIDING POWER, AND USE OF A DRIVE UNIT - A drive unit includes a combustion chamber for combusting a fuel/air mixture, and a fuel cell device, wherein the fuel cell device includes at least one fuel cell, which in each case includes an anode that is couplable to a fuel line, a cathode that is couplable to an air source, and a fluid outlet and is arranged upstream of the combustion chamber. The combustion chamber further includes a combustion chamber inlet for supplying the fuel/air mixture, and a combustion chamber outlet for discharging exhaust gas, and the combustion chamber inlet is connected to the fluid outlet of the fuel cell device. In this way a hybrid drive unit can be provided which apart from mechanical power also generates electrical power at high efficiency. | 02-20-2014 |
| 20140042269 | DRIVE SYSTEM FOR CONTROL SURFACES OF AN AIRCRAFT - A drive system for driving control surfaces of an aircraft includes at least one drive unit, at least one main shaft connectable to the at least one drive unit and at least two adjusting units for each control surface to be driven. Each adjusting unit includes a differential, two rotary actuators and an adjustment lever. The differential has at least one input means and two output means and is adapted to transfer torque from the at least one input means to the two output means. The input means is connectable to the main shaft, the two rotary actuators each have a rotation input means and a motion output means. The rotation input means is connectable to one of the output means of the differential each and the adjustment lever is connected to the motion output means of both rotary actuators. | 02-13-2014 |
| 20140042184 | SMART MULTI-SOAP DISPENSER - A water amount controlling device includes a control unit for controlling an amount of water to be supplied, and a washing agent receptacle including a detection unit , wherein the detecting unit is adapted for detecting and identifying e.g. a type, a consistency or an amount of washing agent dispensed from a washing agent reservoir to be received in the washing agent receptacle, and wherein the control unit is adapted for controlling an amount of water based on the detected and identified property of the quantity of washing agent. | 02-13-2014 |
| 20140034711 | PRESSING A WELD USING THE FRICTION AGITATION WELDING PROCESS FOR BETTER SURFACE ADJUSTMENT - A friction agitation welding process for the joining of abutting plate-shaped workpieces consisting of an aluminium alloy, wherein a rotating Bobbin tool is moved along a weld between the two plate-shaped workpieces during feed, exerting a first and a second contact pressing force on first and second sides, respectively, and wherein said Bobbin tool is subjected to an additional axial force during its movement along the weld to plastically deform the area of the created welding seam such that the welding seam is pressed towards one side of the plate-shaped workpieces while forming a welding seam elevation protruding opposite from the workpiece surface. | 02-06-2014 |
| 20140027088 | HEAT EXCHANGER, HEATER AND GALLEY - A heat exchanger for cooling air, with a coolant onward-flow connection for feeding liquid coolant for cooling air and a coolant return-flow connection for discharging liquid coolant. For removing ice by melting accumulated ice in the heat exchanger, a heater is provided that is associated with an electrical heating element. An operational safety device prevents overheating of the heater. The operational safety device comprises a fault-current detection device. Such a heater, with a heating element for heating air for subjecting accumulated ice to heated air, and with such an operational safety device is provided. Also, a galley for a commercial aircraft is provided with a receiving space for trolleys, and a cooling device for cooling the receiving space. The cooling device comprises such a heat exchanger for cooling air. | 01-30-2014 |
| 20140021304 | PROFILE PLATE PORTION FOR USE AS AN OUTER WALL OF A FLOW BODY, METHOD FOR MANUFACTURING A PROFILE PLATE PORTION AND FLOW BODY COMPONENT COMPRISING A SUCTION-EXTRACTION DEVICE FOR FLUID - A profile plate portion is disclosed for use as an outer wall of a flow body including a first profile plate panel that is fluid permeable, a second profile plate panel extending along the first profile plate panel, and a reinforcing device for supporting the first profile plate panel and the second profile plate panel on one another. Fluid can flow through the reinforcing device, and/or fluid of the flow present at the first profile plate panel, which flows through the first profile plate panel, can flow through the reinforcing device in the local profile plate thickness direction from the first profile plate panel to the second profile plate panel and in some regions can flow through to an inside that is situated opposite the flow side. A method is disclosed for manufacturing a profile plate portion and a flow body component with a suction-extraction device for fluid. | 01-23-2014 |
| 20140017037 | METHOD FOR PRODUCING A CONNECTOR, CONNECTOR AND AIRCRAFT OR SPACECRAFT - A method for producing a connector, in particular for repair, in particular in the field of aviation and aerospace, including the steps of: providing a base layer; attaching a first layer of fibre composite material having a first rigidity to the base layer; attaching a second layer of fibre composite material having a second rigidity to the first layer, offset therefrom, the second rigidity being greater than the first rigidity; and riveting the first layer to the base layer and riveting the second layer to the first layer and to the base layer. | 01-16-2014 |
| 20130343805 | STRUCTURAL ELEMENT FOR AN AIRCRAFT AND/OR SPACECRAFT AND METHOD FOR PRODUCING SUCH A STRUCTURAL ELEMENT - The present invention provides a structural element for an aircraft and spacecraft, having a core which includes core regions which are uncoupled from one another by means of an expansion joint arranged between the core regions. The present invention further provides a method for producing a structural element for an aircraft or spacecraft, including the following method steps: providing a core of the structural element, which core includes core regions; and arranging an expansion joint between the core regions. The present invention relates still further to an aircraft and/or spacecraft having such a structural element. | 12-26-2013 |
| 20130341847 | DEVICE FOR THE TEMPORARY POSITION FIXING OF AIRCRAFT STRUCTURES TO BE INTERCONNECTED - A device for the temporary position fixing of adjacently arranged aircraft structures to be interconnected includes a support frame with at least one vacuum suction cup for temporary surface attachment and with clamping means for the position fixing of the aircraft structures to be interconnected. The support frame with the at least one vacuum suction cup in the region of a transverse gap is attached on the side of one aircraft structure. The support frame includes mechanical contact pressure means for the gap-bridging position fixing of the adjacent other aircraft structure. On the support frame there is a counter support to pressure elements of the contact pressure means. | 12-26-2013 |
| 20130334369 | MODULAR CABIN SEGMENT, CABIN FOR A VEHICLE AND VEHICLE WITH A CABIN - A modular cabin segment for a vehicle includes a first lateral segment module that accommodates a first toilet arrangement with at least one toilet compartment and a second lateral segment module, wherein in each case an outer lateral face of the first segment module and of the second lateral segment module is designed to adapt in each case to an inner wall of a cabin of the vehicle so as to correspond to the aforesaid. At least one of the modules includes at least one cabin attendant seat that on one side is held on the at least one module so that it can be pivoted on an axis. In this manner very good integration of many different functions in the manner of a construction kit is achieved in order to be able to accommodate a greater number of passenger seats elsewhere within the limited space provided in a cabin. | 12-19-2013 |
| 20130334289 | MOVABLE JOINING DEVICE FOR CONNECTING STRUCTURAL COMPONENTS OF AN AIRCRAFT - A movable joining device for connecting structural components of an aircraft, with joining means moveably arranged on a guiding device situated on the outside of the structural components so as to fixedly connect joining edges of the structural components positioned adjacent to each other, wherein the joining means includes a welding unit that can move on the rail-like guiding device, and is equipped with a special so-called bobbin tool as a tool for friction stir welding. | 12-19-2013 |
| 20130331019 | AIRCRAFT OUTER SKIN HEAT EXCHANGER, AIRCRAFT COOLING SYSTEM AND METHOD FOR OPERATING AN AIRCRAFT OUTER SKIN HEAT EXCHANGER - An aircraft outer skin heat exchanger includes a first cooling air inlet and a first cooling air duct section, in which a first heat carrier fluid duct section is arranged. A cooling air conveying device is configured to convey a cooling air stream in such a way through the first cooling air inlet and the first cooling air duct section that the cooling air stream is subdivided by a first heat carrier fluid duct section, arranged in the first cooling air duct section, into two partial air streams which flow through the first cooling air duct section substantially parallel to one another and in the same direction. | 12-12-2013 |
| 20130327887 | DEVICE FOR AN ADJUSTABLE FLAP OF A WING - The invention concerns a device for a adjustable flap adjustably mounted on a main wing surface of an aeroplane wing, in particular, a landing flap, with at least one adjustment unit for purposes of adjustment of the adjustable flap, which has an actuator arranged, or that can be arranged, on the main wing surface, and has a kinematic adjustment mechanism running between the actuator and the adjustable flap, wherein the adjustable flap is mechanically coupled with the actuator via the kinematic adjustment mechanism. At least one damping unit for purposes of damping a dynamic loading effected by the adjustable flap on the adjustment unit, which can occur as a result of a critical malfunction event occurring in the region of the adjustable flap, is arranged, or can be arranged, between the main wing surface and the adjustable flap. | 12-12-2013 |
| 20130327127 | LEAKAGE DETECTION DEVICE AND AIRCRAFT WITH A BLEED AIR SYSTEM AND AT LEAST ONE LEAKAGE DETECTION DEVICE - A leakage detection device comprises a cuff of an elastic material for being circumferentially wrapped around a region of a fluid-carrying conduit, wherein the cuff has an inner surface and an outer surface, through which at least one opening extends. At least one holder that comprises at least one guide element for guiding a measuring element over the opening is arranged at the edge of the opening. In this way, the measuring element can be positioned at a predetermined radial distance from the opening. | 12-12-2013 |
| 20130320150 | WING FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR REDUCING AERODYNAMIC DRAG AND IMPROVING MAXIMUM LIFT - A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased. | 12-05-2013 |
| 20130320137 | RUDDER SYSTEM FOR AN AIRCRAFT - A rudder system for an aircraft includes a centre box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the centre box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a centre box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses. | 12-05-2013 |
| 20130319650 | METHOD FOR OPERATING AN AIRCRAFT COOLING SYSTEM AND AIRCRAFT COOLING SYSTEM - In a method for operating an aircraft cooling system a cooling medium is guided through a cooling circuit, which is connected to a refrigerating machine and to at least one cooling station associated with a cooling energy consumer, to supply cooling medium cooled by the refrigerating to the cooling station. A temperature of the cooling medium upstream of the cooling station and a temperature of the cooling medium downstream of the cooling station are detected. The mass flow of cooling medium supplied to the cooling station is controlled in dependence on a thermal output of the cooling energy consumer and in dependence on a difference between the temperature of the cooling medium upstream of the cooling station and the temperature of the cooling medium downstream of the cooling station. | 12-05-2013 |
| 20130313367 | AIRCRAFT INTERIOR COMPONENT SYSTEM AND METHOD FOR MOUNTING AN INTERIOR COMPONENT SYSTEM IN AN AIRCRAFT - An aircraft interior component system includes an aircraft interior component, a first structure holder fastened to an element of the aircraft structure, and a first component holder fastened to the aircraft interior component. The first component holder is fastened to the aircraft interior component in a first region thereof which faces an aircraft cabin ceiling when the aircraft interior component is mounted in an aircraft. The first structure holder and the first component holder attach the aircraft interior component in a suspended manner to the element, such that a mounting gap is present, at least in a second region of the aircraft interior component facing an aircraft cabin floor when the aircraft interior component is mounted in an aircraft, between a rear side of the aircraft interior component and an aircraft component opposite the rear side of the aircraft interior component. | 11-28-2013 |
| 20130311112 | METHOD AND APPARATUS FOR DETERMINING THE THRUST ON A VEHICLE - A method for determining the thrust of at least one engine, which is held on a supporting structure of a vehicle, includes the steps of acquiring the elongation of at least one structural element onto which the thrust of the at least one engine acts, by means of at least one strain gage; calculating the force causing the elongation in the at least one structural element, taking into account the materials characteristics of the structural element; and determining the thrust of the at least one engine as an effective force component in the direction of thrust of the vehicle. It is thus not necessary to carry out an estimate of the thrust on the basis of other physical variables such as shaft speeds, pressure or exhaust gas temperature of engines. | 11-21-2013 |
| 20130307324 | Energy supply network; method and aircraft or spacecraft - An energy supply network, especially for an aircraft or spacecraft, including a first coupling device, the first coupling device being configured to couple the energy supply network to an external energy source, a first high voltage direct current, HVDC, segment, the first HVDC segment being coupled to the first coupling device and a second HVDC segment, the second HVDC segment being coupled to the first coupling device. Also provided is a corresponding method and an aircraft or spacecraft incorporating such an energy supply network. | 11-21-2013 |
| 20130306797 | HYDROGEN TANK FOR H2-INJECTION - To save weight and to enhance safety, a hydrogen tank for supplying an engine with hydrogen is attached externally to an aircraft. | 11-21-2013 |
| 20130306794 | AIRCRAFT STRUCTURAL ASSEMBLY - An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft. | 11-21-2013 |
| 20130306793 | Fuselage Segment For A Fuselage Of An Aircraft, Aircraft Fuselage and Aircraft - A fuselage segment for an aircraft fuselage includes a wall with a closed cross section, a first cabin floor, a second cabin floor, and a cargo hold floor. The first cabin floor, the second cabin floor, and the cargo hold floor are vertically spaced apart from each other and connected to the wall. A first passenger region is arranged above the first cabin floor, a second passenger region is arranged above the second cabin floor, and a cargo region is arranged above the cargo hold floor. The cargo region is dimensioned in such a manner that for at least four passenger seats a maximum of 1 m | 11-21-2013 |
| 20130305810 | SENSORS FOR LAYOUT VALIDATION OF AN OXYGEN MODULE - A sensor device for an oxygen module mountable on board an aircraft includes an electrical conducting element, a defining device for defining at least one measurement section, assigned to the oxygen module, on the electrical conducting element, and an evaluating unit for determining an electrical resistance present along the at least one measurement section, the evaluating unit further being configured to ascertain, based on the determined electrical resistance, whether the oxygen module is present. An aircraft has at least one oxygen module mounted on board the aircraft and at least one sensor device of the above type. | 11-21-2013 |
| 20130301997 | Method for connecting an optical waveguide, embedded in a fibre composite component, to an external optical waveguide - A method for connecting an optical waveguide embedded in a fibre composite component, in particular of an aircraft and spacecraft, to an external optical waveguide, comprising the following steps: ascertaining a path of the embedded optical waveguide in the fibre composite component; determining a nodal position at which the embedded optical waveguide is to be coupled with the external optical waveguide; exposing, at least in portions, the embedded optical waveguide at the nodal position by removing at least part of the fibre composite component around the embedded optical waveguide; severing the exposed embedded optical waveguide; aligning relative to each other an end portion of the severed, embedded optical waveguide and an end portion of the external optical waveguide; and splicing the mutually aligned end portions of the optical waveguides. | 11-14-2013 |
| 20130300862 | OPTICAL MEASURING DEVICE WITH A SLIDER AND OPTICAL MEASUREMENT METHOD - An optical measuring device for measuring a surface contour of an object, includes a tripod on which a camera platform is mounted, wherein on the camera platform at least two photo cameras are arranged for imaging the object comprising marking elements, and the at least two photo cameras are arranged on the camera platform in such a manner that imaging the object can be carried out from two different perspectives, wherein between the camera platform and the tripod a displacement device for the linear displacement of the camera platform in three directions that are independent of each other is arranged. | 11-14-2013 |
| 20130287505 | NOISE REDUCTION UNIT FOR VACUUM SUCTION DRAINS - A noise reduction unit for inserting in a vacuum suction drain is adapted to be flown through by a material to be conveyed through the vacuum suction drain and comprises an inlet section with a first diameter, a middle section with a second diameter and an outlet section with a third diameter. The middle section is adapted to affect a flow velocity reduction of the material to be conveyed such that the noise level arising during the conveying process is being reduced. | 10-31-2013 |
| 20130286673 | PASSENGER SERVICE SYSTEM WITH IMPROVED AIR GUIDANCE - A passenger service system includes an individual ventilation arrangement and/or a lighting arrangement, wherein at least one air nozzle of the individual ventilation arrangement and/or at least one reading lamp of the lighting arrangement is/are disposed in the region of a service surface of the passenger service system, The service surface of the passenger service system includes a substantially flat portion as well as a buckled portion, which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis (L | 10-31-2013 |
| 20130285442 | SYSTEM FOR CONTACTLESS TRANSFER OF ENERGY AND DATA AND VEHICLE WITH SUCH A SYSTEM - A system for the contactless transfer of energy and data includes a transfer path with a primary coil and with a secondary coil. The primary control unit is designed to lead data-modulated first alternating-voltage signals of a first frequency range into the primary coil. The secondary control unit is designed to receive the first alternating-voltage signals of the first frequency range from the secondary coil, and to demodulate the modulated-on data. The system further includes a feed-in line for feeding a second alternating-voltage signal of a second frequency range to a primary line leading to a primary coil and an activation line that is connected to a secondary line that is connected to the secondary coil. A first filter filters the second alternating-voltage signal from the secondary line and provides the signal to an activation connection. | 10-31-2013 |
| 20130284855 | GUIDING MECHANISM FOR OPENING AND CLOSING A CARGO DOOR OF AN AIRCRAFT, AIRCRAFT WITH SUCH A GUIDING MECHANISM AND METHOD FOR OPENING AND CLOSING A CARGO DOOR OF AN AIRCRAFT - A guiding mechanism is disclosed for moving a cargo door into extended cargo door positions to open and into a retracted cargo door position to close at least one section of an opening of a loading hatch on a fuselage of an aircraft. A first structural component in the form of the cargo door is pivotably supported on a second structural component on a front lateral edge by a pivot joint arranged in a pivoting axis in order to assume the extended cargo door positions on the loading hatch. The guiding mechanism features at least one actuator for moving the cargo door, a supporting device arranged on an actuating element, and a spring mechanism on the actuator for exerting a compressive force. | 10-31-2013 |
| 20130277502 | FLOW BODY HAVING A LEADING EDGE, A SURFACE AND AN ACTIVE FLOW CONTROL SYSTEM AND VEHICLE COMPRISING AT LEAST ONE SUCH FLOW BODY AND AN AIR SOURCE - A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings. | 10-24-2013 |
| 20130277498 | HIGH-LIFT SYSTEM FOR A WING OF AN AIRCRAFT - A high-lift system for a wing of an aircraft is provided. The high-lift system includes movably held high-lift flaps, at least one drive unit, at least one transmission shaft connected to the drive unit, and several actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-lift flaps. The actuator devices each comprise a driven element and a torque limiting means. In one example, the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means. If one actuator device is blocked, for example as a result of a defective tooth arrangement or some other defect, the torque to be produced by the intact actuator device increases and triggers its torque limiting means. This ensures synchronous operation and in the case of malfunction prevents damage to or detachment of a flap. | 10-24-2013 |
| 20130277495 | DEVICE AND METHOD FOR INCREASING THE AERODYNAMIC LIFT OF AN AIRCRAFT - A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics. | 10-24-2013 |
| 20130271915 | HEAT DISSIPATION OF POWER ELECTRONICS OF A COOLING UNIT - A cooling unit in a transport unit includes power electronics; a heat exchanger for thermally coupling a cooling agent of a central cooling system of the transport unit with air of the cooling unit to cool one or more generating devices; and a heat pipe for heat dissipation of the power electronics. At a first portion of the heat pipe, at least some of a working agent is in the liquid phase and, at a second portion of the heat pipe, at least some of the working agent is in the gas phase. In the first portion of the heat pipe, heat from the power electronics is absorbed by evaporating the working agent in the liquid phase. In the second portion of the heat pipe, heat is released to the cooling agent by condensing the working agent in the gas phase. | 10-17-2013 |
| 20130270390 | AIRCRAFT HAVING AN AIRCRAFT FUSELAGE AND AN AIR SUCKING FUSELAGE COMPONENT - An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices. | 10-17-2013 |
| 20130266770 | Method and apparatus for joining parts to be joined which are subject to tolerance - A method for joining parts to be joined which are subject to tolerance in the aerospace sector. The method involves determining the geometric data of a first and second part to be joined, determining the joining gap dimensions of the first and second parts from the determined geometric data and arranging a plurality of shape elements which can be connected together in planar manner in a first region of a surface of the first part. The method moreover comprises application of a first adhesive layer onto the plurality of shape elements and in a second region of the surface of the first part. The method finally involves joining the first and second parts, the first adhesive layer being brought into contact with the surface of the second part. A corresponding apparatus is provided for joining parts which are subject to tolerance in the aerospace sector. | 10-10-2013 |
| 20130266765 | STRUCTURAL COMPONENT, AIRCRAFT OR SPACECRAFT, AND METHOD - A structural component for an aircraft or spacecraft, comprising: a planar member; a reinforcing member which projects from the planar member and is rigidly connected thereto; the reinforcing member comprising at least a foam layer and a cover layer, a plurality of pins extending at least through the foam layer and the cover layer, and at least the pins and the cover layer comprising a curable matrix. | 10-10-2013 |
| 20130266756 | MAIN-LOAD-BEARING PLANKING SHELL AND STRUCTURAL COMPONENT AND FLOW BODY COMPRISING SUCH A MAIN-LOAD-BEARING PLANKING SHELL - According to the invention a main-load bearing skin shell for a structural component is provided, wherein the skin shell for being affixed to a support component comprises an outer edge section with an outer edge and comprises: a connection region that does not comprise a core layer, which connection region extends along the edge with the inner skin section and the outer skin section, wherein in an end region of the core layer along the outer edge section of the skin shell reinforcement devices are integrated that project through the shear-force-absorbing core layer. | 10-10-2013 |
| 20130261852 | MONITORING DEVICE FOR AN ACTUATION SYSTEM OF AN AIRCRAFT, ACTUATION SYSTEM AND METHOD FOR RECONFIGURING THE ACTUATION SYSTEM - A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap. | 10-03-2013 |
| 20130256461 | FLAP ARRANGEMENT AND AIRCRAFT WITH AT LEAST ONE FLAP ARRANGEMENT - A flap arrangement includes a basic body, a hinge arrangement, and a flap that by the hinge arrangement is movably held on the basic body. The hinge arrangement includes at least three bearing points spaced apart from each other and arranged on a shared hinge line, wherein two bearing points are rigidly connected to the basic body and to the flap, and wherein the remaining bearing points in each case allow local movement between the basic body and the flap in at least one first spatial direction perpendicularly to the hinge line. Thus, load-induced constraint forces between the basic body and the control surface can be prevented. | 10-03-2013 |
| 20130256457 | FUSELAGE SEGMENT AND METHOD FOR MANUFACTURING A FUSELAGE SEGMENT - The invention pertains to a fuselage segment ( | 10-03-2013 |
| 20130256451 | AIRCRAFT HAVING AT LEAST TWO AIRCRAFT FUSELAGES AND A FIRST WING ARRANGEMENT WITH AT LEAST TWO WING SECTIONS THAT ARE NOT CONNECTED TO EACH OTHER - An aircraft having at least two separate aircraft fuselages is provided. The aircraft includes a first wing arrangement with at least two non-connected wing sections, and a second wing. In each case the wing sections of the first wing arrangement extend from the outside of an aircraft fuselage towards the outside. The second wing is arranged between insides of the at least two aircraft fuselages. Connecting regions of the first wing arrangement and of the second wing are arranged so as to be offset relative to each other at least on an X-Z-plane of an aircraft-fixed coordinate system. Consequently, the first wing arrangement and the second wing do not influence each other as a result of downwash, and in addition it is possible to do without horizontal stabilizer units that generate downthrust. | 10-03-2013 |
| 20130252118 | FUEL CELL SYSTEM FOR GENERATING ENERGY AND WATER - Fuel cell systems aboard means of transport can be used for generating energy and for producing water. In order to reduce the overall weight of the system, the fuel cell is controlled or regulated in dependence on a current fill level or a limit level of the water tank, as well as a predicted future water consumption. In this way, it may be possible to minimize the water quantity to be stored in the water tank. | 09-26-2013 |
| 20130249178 | SEAT BENCH TRANSPORT DEVICE - Disclosed is a seat bench transport device according to the invention for transporting a bench of seats for a vehicle, comprising a chassis, a retaining rail pair that is arranged on the chassis and includes two retaining rails extending parallel to one another for accommodating seat bench feet, the lengthwise sides of these rails that face one another being open at least in sections and the lengthwise sides thereof that face away from one another each having at least one locking section, and a displacement mechanism for moving the retaining rails transversely relative to one another. | 09-26-2013 |
| 20130248164 | METHOD FOR CONTROLLING AN AIRCRAFT AIR CONDITIONING SYSTEM AND AIRCRAFT AIR CONDITIONING SYSTEM - In a method for controlling an aircraft air conditioning system, a heating or cooling demand of an aircraft region to be air conditioned is determined. A volume flow of recirculation air discharged from the aircraft region to be air conditioned and a volume flow of compressed air into a mixing chamber of the aircraft air conditioning system is controlled such that the heating or cooling demand of the aircraft region to be air conditioned is met, while the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system is minimized. | 09-26-2013 |
| 20130240668 | CONDENSATION WATER-FREE INSULATION SYSTEM FOR PASSENGER AIRCRAFT - An insulation arrangement for thermally and acoustically insulating an aircraft fuselage, which comprises at least one insulation packet arranged on an exterior skin of the aircraft. The insulation packet includes dimensionally rigid foam, and comprises a shape corresponding at least with a structural component on the exterior skin, as the result of which the insulation packet is retained on the structural component even without any additional attachment elements. As a result, ventilation openings need not be provided, thereby reducing condensation water accumulating in aircraft insulation. | 09-19-2013 |
| 20130240126 | METHOD FOR REINFORCING A FIBER COMPOSITE COMPONENT AND ARRANGEMENT FOR PRODUCING A REINFORCED FIBER COMPOSITE COMPONENT - A method and an arrangement for reinforcing a fibre composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, with the pressure element, is then applied in a reproducible manner to the fibre composite component to be reinforced, to form a moulding portion. The formed moulding portion is cured to connect the reinforcing element to the fibre composite component. The fastening device and the pressure element are then removed from the fibre composite component. | 09-19-2013 |
| 20130239598 | AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM WITH CONDITIONED HEAT SINK - An air conditioning system for an aircraft includes at least one air conditioning pack which for the purpose of heat dissipation can be connected to at least one cooling air inlet of the aircraft and is designed to cool air and to introduce it at a cabin pressure into a passenger cabin of the aircraft. A separately operable cooling device is designed to cool the ambient air flowing into the cooling air inlet. | 09-19-2013 |
| 20130239398 | Method and a connecting system for the joining of moulded parts - A method for the connection of moulded parts, wherein a locking collar pin with locking grooves or with an external thread, is driven through the moulded parts and subsequently a locking collar is locked together with at least some of the locking grooves, or with threaded sections of the locking collar pin, by the application of radial pressure, or by means of a screwing operation. A connecting system with a locking ring pin, which has a punching section for purposes of punching through the moulded parts, and also locking grooves for purposes of active engagement with a locking ring; the latter extends over at least two adjacent locking grooves in the axial direction, or over at least two adjacent threads in the axial direction. | 09-19-2013 |
| 20130234486 | PASSENGER SEAT SYSTEM - A passenger seat system includes a backrest and a seat, which has a first sub-portion having a first surface and a second, opposite surface to the first surface as well as a second sub-portion having a first surface and a second, opposite surface to the first surface. The sub-portions are relatively movable in order to provide first and second operating positions. In the first operating position the sub-portions are positioned in relation to the backrest one behind the other such that the first surface of the first sub-portion and the first surface of the second sub-portion form a usable total seat surface. In the second operating position the sub-portions are positioned in relation to the backrest one above the other such that one of the surfaces of the first sub-portion or the first surface of the second sub-portion forms a usable partial seat surface. | 09-12-2013 |
| 20130234373 | METHOD AND MANUFACTURING DEVICE FOR MANUFACTURING A FIBER COMPOUND SANDWICH COMPONENT - The invention relates to methods and to a manufacturing device for manufacturing a sandwich component. A semifinished product arrangement is soaked with a flowable matrix material, for example a resin, in particular by an infusion method. By using the method of the invention, inherent tensile stresses introduced by the respective method and remaining in the sandwich component to be manufactured are reduced, and moreover the risk of crack formation in the course of the process, afterwards and during operation of the sandwich component is minimized. | 09-12-2013 |
| 20130233004 | COOLING SYSTEM FOR OPERATION WITH A TWO-PHASE REFRIGERANT - A cooling system particularly suitable for use on board an aircraft includes a cooling circuit allowing circulation of a two-phase refrigerant therethrough. An evaporator in the cooling circuit has a refrigerant inlet and a refrigerant outlet. A condenser in the cooling circuit has a refrigerant inlet and a refrigerant outlet. A detection device is configured to output a signal indicative of the state of aggregation of the refrigerant in a connecting portion of the cooling circuit which connects the refrigerant outlet of the evaporator to the refrigerant inlet of the condenser. A control device is configured to control at least one of the temperature and the pressure of the refrigerant in the connecting portion of the cooling circuit in dependence on the signal output by the detection device such that the refrigerant in the connecting portion of the cooling circuit is maintained in its gaseous state of aggregation. | 09-12-2013 |
| 20130233003 | RELIABLE COOLING SYSTEM FOR OPERATION WITH A TWO-PHASE REFRIGERANT - A cooling system, in particular for use on board an aircraft, includes a first cooling circuit allowing circulation of a two-phase refrigerant therethrough, a first evaporator disposed in the first cooling circuit, a first condenser disposed in the first cooling circuit, and a first heat sink adapted to provide cooling energy to the first condenser. The cooling system further includes a second cooling circuit allowing circulation of a two-phase refrigerant therethrough, a second evaporator disposed in the second cooling circuit, a second condenser disposed in the second cooling circuit, a second heat sink adapted to provide cooling energy to the second condenser, and a cooling energy transfer arrangement which is adapted to transfer cooling energy provided by the first heat sink and/or the first condenser to the second cooling circuit or to transfer cooling energy provided by the second heat sink and/or the second condenser to the first cooling circuit. | 09-12-2013 |
| 20130228667 | HOLDING DEVICE FOR INTERIOR LINING PARTS OF A FUSELAGE AND SUPPORTING SYSTEM EMPLOYING SUCH HOLDING DEVICES - A holding device for in particular panel-shaped interior lining parts of a fuselage, has a configuration that is easy and simple to mount, each holding device includes a supporting device, which is used to anchor the holding device on a primary structure of the fuselage and comprises a joint; a connecting tube, which extends out of the supporting device and one end of which is attached to the joint; a mounting for an interior lining part, to which mounting the other, opposite end of the connecting tube to the one end is attached; and a lanyard, which is fastened to the supporting device is and the mounting and extends through the connecting tube and the length of which is greater than the length of the connecting tube. | 09-05-2013 |
| 20130227975 | COOLING SYSTEM WITH A PLURALITY OF SUBCOOLERS - A cooling system, in particular for use on board an aircraft, includes a cooling circuit allowing circulation of a two-phase refrigerant therethrough, an evaporator disposed in the cooling circuit, and a condenser disposed in the cooling circuit. A plurality of subcoolers is arranged in series in the cooling circuit downstream of the condenser. | 09-05-2013 |
| 20130227969 | ACCUMULATOR ARRANGEMENT WITH AN INTEGRATED SUBCOOLER - An accumulator arrangement for use in a cooling system suitable for operation with two-phase refrigerant includes a condenser having a refrigerant inlet and a refrigerant outlet. The accumulator arrangement further includes an accumulator for receiving the two-phase refrigerant therein, the accumulator having a refrigerant inlet connected to the refrigerant outlet of the condenser and a refrigerant outlet. Finally, the accumulator arrangement includes a subcooler having a refrigerant inlet and a refrigerant outlet, the refrigerant inlet of the subcooler being connected to the refrigerant outlet of the accumulators, and the subcooler being arranged at least partially within the interior of the accumulator. | 09-05-2013 |
| 20130224443 | REINFORCEMENT DEVICE FOR THE PURPOSE OF REINFORCING A MAIN LOAD-BEARING COVERING PANEL AND MAIN LOAD-BEARING COVERING PANEL - The invention concerns a reinforcement device for the purpose of reinforcing a main load-bearing covering panel, also a corresponding main load-bearing covering panel, a structural component of a flow body, and also a corresponding flow body. Here the reinforcement device serves the purpose of accommodating and transferring forces and/or stresses in the interior of the covering panel. In accordance with the present invention, in addition to forces and/or stress in the normal direction, forces and/or stresses in a crosswise direction, that is to say, for example, transverse stresses and/or shear stresses, can also be accommodated and transferred. | 08-29-2013 |
| 20130222347 | DEVICE AND METHOD FOR EXCHANGING INFORMATION BETWEEN AT LEAST ONE OPERATOR AND A MACHINE - A device and a method for exchanging information between at least one operator and a machine which comprises the following components: a display means, which is set up so as to display information from the machine to the at least one operator visually and three-dimensionally; an input means, which is set up so as to detect the position of objects, preferably the position of the fingers of at least one operator, in three-dimensional space in relation to the display means, in a time-resolved manner by optical and/or acoustic and/or electromagnetic measurement methods, and to detect at least one operator input from the detected progression over time in accordance with at least one predetermined criterion and to pass said operator input on to the machine. | 08-29-2013 |
| 20130216850 | STRUCTURAL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT - A structural component for an aircraft or spacecraft having an outer skin, comprising at least one former element for reinforcing the outer skin. The former element is arcuately curved in accordance with an inner contour of the outer skin | 08-22-2013 |
