| AIRBUS OPERATIONS GMBH Patent applications |
| Patent application number | Title | Published |
|---|
| 20120130528 | DEVICE FOR SPATIALLY ORIENTING AT LEAST TWO SUBGROUP COMPONENTS AND METHOD - The invention relates to a device for spatially aligning at least two large-format subassembly components, in particular at least one side shell | 05-24-2012 |
| 20120124808 | METHOD FOR REDUCING THE INSTALLATION TIME FOR A SUPPLY CHANNEL - A method is introduced for reducing the installation time for a supply channel on a first retaining structure in an aircraft. The method includes, but is not limited to pre-wiring a stowage compartment outside of the aircraft, installing a supply channel unit in the aircraft at a standardized installation position predefined by the first retaining structure. Standardizing the installation steps in this way makes numerous advantages possible, including a reduction in the installation time of the passenger supply channel within the framework of a final assembly of cabin components. | 05-24-2012 |
| 20120123738 | CLOSING DEVICE, HOUSING PART OF A LUBRICANT CONTAINER, DIAGNOSTIC SYSTEM AND DIAGNOSTIC METHOD FOR MONITORING THE OPERATING STATE OF A LUBRICANT IN THE HOUSING PART - The invention relates to a housing part containing a lubricant reservoir and at least one respective inlet and outlet opening for filling and draining a lubricating fluid into and from the lubricant reservoir. The inlet and outlet openings are sealed by releasable closure devices each comprising a sensor means for determining the operation parameters in a lubricant contained in the lubricant reservoir and for generating and/or storing sensor signals, as well as a transceiver for the transmission of the sensor signals to an external processing unit. | 05-17-2012 |
| 20120119405 | DEVICE AND METHOD FOR PRODUCING A COMPOSITE COMPONENT - The present invention provides a device for producing a composite fiber component. The device comprises a shaping tool having a shaping surface for shaping a resin-soaked fiber material, a filter panel that is arranged at the shaping surface and comprises a porous material, and a means for generating a negative pressure at the shaping surface at a side of the filter panel that faces away from the fiber material. In another aspect, the invention provides a method for producing a composite fiber component. First, a filter panel comprising a porous material is provided. In subsequent steps, a resin-soaked fiber material is arranged on the filter panel, the fiber material on the filter panel is covered and a negative pressure is generated at a side of the filter panel that faces away from the fiber material. | 05-17-2012 |
| 20120119036 | WING OF AN AIRCRAFT OR SPACECRAFT, COMPRISING A MOBILE FLOW BODY - A wing of an aircraft or spacecraft, the wing including at least a movable flow body, the wing including a movable support member, which is connected to the flow body, for rotating the flow body on the wing, the wing including a flow body control element, the flow body control element being fixed to the wing in a first point and the support member in a second point, the two points of the flow body control element and of the support member forming an axis, the flow body control element being formed at a predetermined angle to the axis and the flow body control element guiding the flow body in a predetermined plane about this axis. | 05-17-2012 |
| 20120119029 | MONUMENT FOR A CABIN OF A VEHICLE - An area-expandable monument is provided for a cabin of a vehicle that includes, but is not limited to two housing parts that are displaceable relative to each other and can be fastened. A gap between the housing parts in an expanded state can be covered by a covering element. In the monument, a first sanitary fixture could be arranged whose position adapts to the spatial state of the monument. Optionally, there is also a pivotable second sanitary fixture that can be activated with the monument in its pushed-out state. | 05-17-2012 |
| 20120119024 | INSULATION ARRANGEMENT IN AN AIRCRAFT - An insulation arrangement with a holding device that comprises a collar forms an overlapping region between a second insulating package and the collar such that incidental condensation water on a first insulation package drains to the second insulating package along the collar under the influence of the gravitational force and from there into a bilge of the aircraft equipped with the insulation arrangement on a waterproof cover film of the second insulating package. This prevents condensation water from dripping into a passenger cabin. | 05-17-2012 |
| 20120118528 | COOLING CONCEPT FOR FUEL CELL EMERGENCY POWER SUPPLY - A system is provided for cooling a heat-dissipating device in a vehicle with a fuselage, a passenger cabin, and a region pneumatically communicating with the previously mentioned, which region is situated outside the passenger cabin. At least one heat exchanger is provided for transferring heat of the heat-dissipating device to air, and at least one air conveying device for conveying air through the heat exchanger. The air conveying device is designed to convey air from the passenger cabin to the heat exchanger. The heat exchanger is designed to subject the inflowing air to heat of the heat-dissipating device and to dissipate it to the region situated outside the passenger cabin, thus inducing mixing of the air that has been subjected to heat with the air present in the outside region, and inducing a return flow from the outside region to the passenger cabin by way of their pneumatic connection. | 05-17-2012 |
| 20120118408 | FLOW LIMITER AND USE OF A FLOW LIMITER IN AN AIR DISTRIBUTION SYSTEM OF AN AIR CONDITIONING SYSTEM OF AN AIRCRAFT - A flow limiter comprises a line segment with an air inlet and an air outlet and at least one resistance element. The resistance element is positioned within the line segment and impresses a predetermined flow resistance on an air flow that extends from the air inlet to the air outlet. Preferably, the resistance element extends at least in part in an axial direction of the line segment. Such a flow limiter is used to adjust an air volume flow and comprises particularly low generation of intrinsic noise. | 05-17-2012 |
| 20120116736 | METHOD FOR THE ACOUSTIC ANALYSIS OF A BODY AND A SYSTEM FOR THE EXECUTION OF SUCH A METHOD - A system and method for the acoustic analysis of a body, in particular a fuselage structure of an aircraft, is provided including: inputting data for geometry, material, boundary conditions and acoustic parameters of the body, generating a body idealised in terms of its structural mechanics, and a cavity simulating the interior of the body, on the basis of the data inputted as a numerical body model, inputting the geometry of the body with a pattern of nodes and the generation of finite elements, stimulating an acoustic loading case by subjecting the body model to at least one sound pressure wave at a defined frequency, analyzing the effect of the sound pressure wave on the body model, and outputting a sound reduction index (R) for the body with reference to that frequency. | 05-10-2012 |
| 20120112505 | SCREEN FOR A PASSENGER CABIN - The invention relates to a device for creating an individually delimited zone of a passenger cabin in a means of transport for at least one passenger seat. The device comprises a modular cabin element that has been attached in a positionally variable manner to stationary guide rails of the passenger seat by way of quick-release fasteners. Associated with this cabin element is an extendable and affixable privacy screen roller blind that forms a flexible dividing element, which privacy screen roller blind extends from the underside of the hatrack or the PSU panel or the ceiling arrangement, and in the lateral region in addition the sidewall lining of the passenger cabin, to the modular cabin element, and by means of which privacy screen roller blind an individually delimited zone can be implemented. | 05-10-2012 |
| 20120112011 | CASING FOR A LIFTING AID - A casing for a lifting aid for an aircraft, comprising at least one strake which extends essentially in a protruding manner in the direction of flight in relation to an outer surface of the casing. An aircraft comprising a lifting aid and said type of casing. | 05-10-2012 |
| 20120111486 | METHOD FOR PRODUCING A HOLLOW COMPONENT AND DEVICE - A method and apparatus for producing a hollow component, in particular in the field of aviation or aerospace, including the following steps: provision of an inner contour closed along its circumference; laying of a fibre material over the inner contour; and curing of a matrix of the fibre material to form the component. | 05-10-2012 |
| 20120104184 | AIRCRAFT COMPRISING A DEVICE FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT, AND A METHOD FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT - An aircraft including a device for influencing the directional stability of the aircraft is provided. The device includes a control-input device; a flight control device; a sensor device for acquiring the rotation rates, including the yaw rates, of the aircraft; and at least one actuator, which is coupled with ailerons, spoilers, an elevator and a rudder. The flight control device includes a control function generating adjusting commands for the actuators for controlling the aircraft according to control commands. The aircraft includes two tail-mounted flaps, each including an actuator connected with the flight control device, situated symmetrically to each other and on opposite sides of the fuselage, and movable between retracted and extended positions. The control function is designed such that the adjusting commands that are generated on the basis of the control commands depending on the acquired rotation rates include adjusting commands to the actuators of the tail-mounted flaps. | 05-03-2012 |
| 20120102869 | LIGHTWEIGHT STRUCTURAL PANEL - What is described is a lightweight structural panel which comprises a planarly extended outer skin of given thickness and stiffening elements which are connected to this outer skin and are arranged at a given distance from one another. According to the invention, the outer skin is formed by component layers which are each extended in the planar direction of the lightweight structural panel and complement one another in the direction of thickness to form the thickness of the outer skin and are interconnected, the stiffening elements being formed in one piece with one of the component layers. | 05-03-2012 |
| 20120101794 | DEVICE AND METHOD FOR THE RESIDUAL ANALYSIS OF A RESIDUUM TO DETECT SYSTEM ERRORS IN THE SYSTEM BEHAVIOUR OF A SYSTEM OF AN AIRCRAFT - The present invention provides a device and a method for the residual analysis of a residuum to detect system errors in the system behaviour of an aircraft. The device for the residual analysis of a residuum comprises an apparatus to generate the residuum at least dependent on the reference variable and the system output variable, a comparator unit to provide an analytical result by comparing the residuum to a given threshold, a first unit to provide a constant threshold portion, a second unit to provide an adaptive threshold portion at least dependent on the reference value, which can change over time, and a third unit to provide the threshold by linking the constant threshold portion to the adaptive threshold portion. | 04-26-2012 |
| 20120101682 | METHOD AND SYSTEM FOR COLLECTION STATE INFORMATION OF PARTS IN A PASSENGER CABIN OF A VEHICLE - A method for collecting defect data of parts in a passenger cabin of a vehicle includes, but is not limited to connecting an electronics device allocated to a user to a central communication device, retrieving a user interface provided by the communication device by the electronics device, dialog-based inquiring of defect data of parts by the communication device by way of the user interface on the electronics device, and storing the requested defect data by the communication device in a central data storage unit. The electronics device can be mobile or permanently installed. Mobile electronics devices can be implemented by personal electronics devices of the passengers, which devices were brought into the passenger cabin. | 04-26-2012 |
| 20120098455 | Lighting Device Having A Plurality Of Light Sources - A lighting device ( | 04-26-2012 |
| 20120098212 | DEVICE FOR PREVENTING THE PASSAGE OF GASES AND/OR FLUIDS FROM A WINGBOX INTO A FUSELAGE OF AN AIRCRAFT - The invention relates to a device for preventing gases and/or fluids emanating from a wing box | 04-26-2012 |
| 20120097323 | METHOD FOR PRODUCING A FIBRE COMPOSITE COMPONENT FOR AIR AND SPACE TECHNOLOGY - A method for producing a fibre composite component, in particular for aerospace, the method comprising the following steps: forming a mould core from a material comprising cork by a moulding tool to establish an outer geometry of said mould core; arranging the so formed mould core adjacent to an at least partly hardened stiffening element on a base element of said composite component to be produced for the shaping of at least one moulded portion of said fibre composite component to be produced; and multistage exposure of at least said moulded portion to heat and/or pressure to produce said fibre composite component; a corresponding mould core and a corresponding fibre composite component. | 04-26-2012 |
| 20120091282 | HIGH LIFT SYSTEM FOR AN AIRCRAFT AND METHOD FOR DETECTING FAULTS IN A HIGH LIFT SYSTEM FOR AN AIRCRAFT - The present invention relates to a high lift system for an aircraft, comprising a flap, which is arranged on a wing box and which can be moved between a retracted position and at least one extended position relative to the wing box by means of a drive device, a support construction, which is arranged on the wing box in the area of the drive device and to which the flap is coupled and which comprises a movable support element, which can be moved to move the flap relative to the wing box, and an acceleration sensor arranged in the area of the flap or the movable support element for detecting accelerations of the flap. | 04-19-2012 |
| 20120090768 | APPARATUS AND METHOD FOR DRAPING KNITTED FIBER FABRICS FOR CURVED PROFILED STRUCTURAL PARTS OF FIBER COMPOSITE MATERIAL - An apparatus for draping knitted fiber fabrics for curved profiled structural parts of fiber composite material includes a mold having a mold surface that corresponds to a portion of the desired profile geometry and curvature of the profiled structural part, a clamping device for tensioning a layer of a knitted fiber fabric along a tensioning line in a prestressed state, and a movement device for producing a relative movement between the mold and the clamped-in fabric layer such that the mold surface moves close to the fabric layer in a direction perpendicular to the tensioning line and, in the further course of the relative movement, pushes through the tensioning line such that the fabric layer completely covers the mold surface. The clamping device is equipped to load the fabric layer during the entire draping operation with a tensile force acting along the tensioning line. | 04-19-2012 |
| 20120085862 | AIRCRAFT GALLEY HAVING A PARTITION PANEL SYSTEM - An aircraft galley partition panel system has first and second partition panels. An assembly slot extends from an edge of the first panel and receives an assembly section of the second panel such that main surfaces of the first and second panels are substantially perpendicular. A first guide device carried by the assembly slot interacts with a complementary second guide device arranged in a region of the assembly section of the second panel. An assembly section of the first partition panel carries a third guide device which interacts with a complementary fourth guide device arranged in a region of a lateral surface of the second panel facing the assembly section of the first panel. Projections of the first and second connecting devices are received in complementary recesses in a base body of the aircraft galley to connect the first and second panels respectively to the base body. | 04-12-2012 |
| 20120084962 | CLAMPING DEVICE AND METHOD FOR ASSEMBLY OF STRINGER COUPLINGS - A clamping device is provided for an assembly of a stringer coupling in a region of a lateral butt joint between a first and a second fuselage section of an aircraft for coaxially connecting a respective first and second stringer of the first and the second fuselage sections, the stringer coupling intersecting a frame element profile in the region of the lateral butt joint. A supporting yoke is configured to bridge the frame element profile in an arc-shaped manner and includes a first end foot supported by the stringer coupling on the first side of the frame element profile and a second end foot supported by the stringer coupling on the second side of the frame element profile. The supporting yoke includes a middle tensioning hook configured to interact with the frame element profile. The first and the second end feet are tensionable against the stringer coupling. | 04-12-2012 |
| 20120073750 | PRESSING APPARATUS AND PRESSING AND DEPOSITING SYSTEM FOR DEPOSITING A SLIVER ON A DOUBLE-CURVED SURFACE, AND USE AND METHOD - A pressing apparatus is provided for depositing a sliver on a surface with a first segment and at least one second segment that can respectively roll along the surface. The pressing apparatus furthermore features an assembly frame for holding the segments. The first segment features a first rolling element and a suspension apparatus and the second segment features a second rolling element. The suspension apparatus is designed for attaching the first segment to the assembly frame and for rotatably mounting the first rolling element on the assembly frame. The suspension apparatus is designed for allowing a relative movement between the first rolling element and the second rolling element in a radial direction of the first rolling element. | 03-29-2012 |
| 20120073749 | PRESSING-ON DEVICE FOR PRESSING ON FIBER-REINFORCED THERMOPLASTIC MATERIALS, FIBER ARRANGING DEVICE, AND METHOD FOR ARRANGING A FIBER-REINFORCED THERMOPLASTIC MATERIAL - A pressing-on device for pressing fiber-reinforced thermoplastic materials onto a mold is described. The pressing-on device has a main body and a pressing-on layer provided on a surface of the main body. The pressing-on layer is implemented in this case using an inorganic material, preferably a ceramic material, and has a flexibility because of its structure which allows it to adapt itself to the contour of a mold. Increased heat resistance of the pressing-on device and improved properties of the processed fiber-reinforced thermoplastic material can be achieved. | 03-29-2012 |
| 20120072079 | RECONFIGURATION OF CABIN LAYOUTS - A control and monitoring system is provided in the aircraft cabin and controls a reconfiguration process with corresponding software in combination with reconfiguration data received from the ground personnel. The control is realized, for example, with a suitable light signals and the unlocking of the seats at certain times. All work sequences are acoustically and/or optically displayed such that the reconfiguration can also be carried out by untrained personnel. | 03-22-2012 |
| 20120068016 | AERODYNAMIC FAIRING DEVICE, AIRCRAFT COMPONENT ARRANGEMENT WITH AN AERODYNAMIC FAIRING DEVICE AND METHOD FOR INSTALLING SUCH A FAIRING PART - A fairing device for creating an aerodynamic cover for an area of an aircraft structure, including a first fairing part with an outer side forming a first exterior flow contour, and having a fairing section for contacting a first section of the aircraft structure and a connecting section. The first fairing part includes a mounting device for receiving a connecting element. The fairing device includes a second fairing part including a fairing section having an outer side forming a second exterior flow contour and is designed for contacting a second section of the aircraft structure and a connecting section. The shape of the outer side of the second fairing part is adapted to the inner side of the connecting section of the first fairing part in an overlapping area, so the connecting section of the first fairing part forms a joint piece protruding over the second fairing part in the overlapping area. | 03-22-2012 |
| 20120068014 | SEGMENT OF A FUSELAGE OF AN AIRCRAFT - According to an exemplary embodiment of the invention a fuselage segment of an aircraft fuselage is provided, which aircraft fuselage comprises four different radii of curvature, wherein two radii of curvature comprise centre points that are not situated on a vertical symmetry axis of the fuselage segment. | 03-22-2012 |
| 20120067498 | METHOD FOR THE THERMAL JOINING OF TWO COMPONENTS, AND A THERMAL JOINING STRIP - A method for a thermal joining of two thermoplastic components includes arranging at least one reactive sheet entity in a mating zone between the two thermoplastic components. A multiply perforated metallic sheet entity configured as a bonding agent is disposed on each side of the at least one reactive sheet entity, at least in some regions of the mating zone. The at least one reactive sheet entity is activated so as thermally join the two thermoplastic components in the regions of the mating zone. | 03-22-2012 |
| 20120064816 | System and process for cooling an aircraft zone using an aircraft-external air assembly - A system for cooling an aircraft zone includes a mixing chamber ( | 03-15-2012 |
| 20120063522 | METHOD FOR DIRECTIONAL DIGITAL DATA TRANSMISSION BETWEEN AN AIRCRAFT AND A GROUND STATION - The invention relates to a method for digital and directional data transmission between aircraft and ground stations. In this arrangement data is exchanged digitally and directly, in other words directly by means of directional antennae, between the aircraft and the ground stations. Furthermore, transmission lobes are adapted during flight, and the directional antennae on the aircraft only illuminate regions on the ground that are located at a minimum distance across the flight path of the aircraft. | 03-15-2012 |
| 20120062184 | WIRELESS SELF-SUFFICIENT MONITORING SYSTEM FOR A DOOR LOCK MECHANISM - The invention relates to a monitoring system for monitoring a state of a door lock mechanism of a door or of a closure of a storage space of a means of transportation, comprising a generator and a sensor/actuator. The generator produces electrical energy from vibration energy, and the sensor detects the state of the door lock mechanism. The sensor uses the kinetic energy that is produced by the actuation of the door lock to generate an electrical signal, which is then transmitted to a microcontroller. | 03-15-2012 |
| 20120061524 | AEROFOIL COMPRISING A HIGH LIFT FLAP - A wing is provided, including a high-lift flap arranged on the wing such that it is movable by means of at least two adjustment mechanisms arranged side-by-side in the spanwise direction of the wing and adjustable by means of a drive device. Each adjustment mechanism includes a first adjustment lever, articulated on a main wing surface via a first pivotal articulation, with the formation of a first rotation axis; a second adjustment lever, articulated on the high-lift flap via a second pivotal articulation, with the formation of a second rotation axis; and a central articulation, linking together the first and the second adjustment levers, with the formation of a third rotation axis. An intermediate articulated part is arranged on at least one of the adjustment mechanisms for coupling the first adjustment lever and the main wing surface, or for coupling the second adjustment lever and the high-lift flap. | 03-15-2012 |
| 20120061523 | SLATS WITH A FLEXIBLE TRAILING EDGE - Embodiments of the invention relate to an aerodynamic body with an extension in the spanwise direction, wing chord direction and wing thickness direction for coupling to a wing of an aircraft. This aerodynamic body can here be used for a leading edge flap or slat of an aircraft wing. To improve the flow characteristics, the rear side of the aerodynamic body is provided with a skin section that can be molded between a convex curvature and concave curvature. | 03-15-2012 |
| 20120060524 | AIR CONDITIONER HAVING AN AIR DEHUMIDIFYING DEVICE AND METHOD FOR OPERATING SUCH AN AIR CONDITIONER - An aircraft air conditioning system has a fresh air line connected to a fresh air inlet for supplying fresh air to the air conditioning system and a sorption device disposed in the fresh air line which contains a sorbent for taking up moisture from the fresh air flowing through the fresh air line. The sorption device is adapted to expose the sorbent contained in the sorption device to ambient pressure surrounding an aircraft carrying the aircraft air conditioning system when the aircraft is flying for the purpose of regeneration of the sorbent. The sorption device is thermally connectable to a heat source that is adapted, when the aircraft is flying and while the sorbent contained in the sorption device is exposed to the ambient pressure, to supply thermal energy from the heat source to the sorbent contained in the sorption device for the purpose of assisting the regeneration. | 03-15-2012 |
| 20120060271 | TOILET MONUMENT WITH RECEPTACLE FOR A MOBILE SANITARY UNIT - A toilet monument is provided, in particular for a passenger transport vehicle, which includes, but is not limited to a receptacle that is configured to receive a mobile sanitary unit. The mobile sanitary unit includes, but is not limited to components for operating the sanitary unit. The mobile sanitary unit may be removed completely from the toilet monument in order to make it possible to affect decentralized cleaning and servicing of the mobile sanitary unit. The term mobile sanitary unit refers, for example, to a toilet unit, a hand wash facility, a urinal or a shower unit. | 03-15-2012 |
| 20120056037 | FUSELAGE CELL STRUCTURE FOR AN AIRCRAFT IN HYBRID DESIGN - A fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one brace which is at least one of a longitudinal and a transverse brace is disposed so as to form at least one of a longitudinal seam and a transverse seam between the at least one double shell skin panel and the at least one monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flange that are disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the at least one monolithic skin panel to the at least one double shell skin panel. | 03-08-2012 |
| 20120056036 | MONUMENT WITH AN AUTONOMOUS WATER MODULE - An autonomous water module is provided for aircraft, preferably a water module embodied as a water trolley, and to a monument for aircraft, which includes, but is not limited to a device for receiving said type of water module, and finally, an aircraft equipped with said type of autonomous water module and/or said type of monument. The autonomous water module includes, but is not limited to a container having the standard dimensions of a trolley, and the container includes, but is not limited to a fresh-water tank, a device for dispensing fresh water, and a device for discharging gray water. | 03-08-2012 |
| 20120055617 | Method for Producing Fuselage Cell Sections for Aircraft with Composite Fibre Materials, and a Device - The invention relates to a production method for producing seamless, integral aircraft fuselage sections. The method comprises the following steps:
| 03-08-2012 |
| 20120055183 | SYSTEM AND METHOD FOR COOLING A SPACE IN A VEHICLE - A system for cooling a space in a vehicle comprises a sorption wheel, at least one heat exchanger, at least a first humidifier unit and at least one fuel cell, wherein the sorption wheel is adapted for drying ambient air and for conveying dried process air to the downstream heat exchanger and the heat exchanger is adapted for cooling process air, with the heat exchanger being connected to the first humidifier unit for humidifying cooled process air, and wherein the fuel cell is connected to the sorption wheel and adapted for making available fuel cell exhaust air for regenerating the sorption wheel and water to be introduced into the first humidifier unit. Since the utilization of fuel cells is increasingly considered in modern vehicles and, in particular, commercial aircraft, the system according to the invention makes it possible to realize a symbiotic relationship between already installed fuel cells and cooling systems in vehicles, in which the further use of the waste products heat and humidity leads to fuel savings. In addition, an evaporative cooling method is presented, in which a fuel cell serves for supplying heat and water. | 03-08-2012 |
| 20120043428 | HIGH-LIFT FLAP, ARRANGEMENT OF A HIGH-LIFT FLAP TOGETHER WITH A DEVICE FOR INFLUENCING THE FLOW ON THE SAME AND AIRCRAFT COMPRISING SAID ARRANGEMENT - An aerodynamic body of an aircraft with an air outlet opening and an air intake opening that communicates with the air outlet opening via an air conduit is described. A flow delivery driver device for influencing the flow within the air conduit is integrated into the air conduit. The surfaces of the aerodynamic body in the body chord direction include at least one air outlet opening in the front region of the aerodynamic body, and at least one air intake opening on the upper surface of the aerodynamic body and in the rear region of the aerodynamic body and/or on the upper surface of the aerodynamic body in the trailing edge region and/or on the lower surface of the aerodynamic body in the trailing edge region. Arrangements of a main wing and an adjustable flap, and an aircraft with such an aerodynamic body are also described. | 02-23-2012 |
| 20120037619 | DEVICE FOR REDUCING LOADS ON LATCHES AND LOADS ON CARGO CONTAINERS - The invention relates to a device for reducing latch loads during the process of loading and flying air cargo containers inside cargo holds of aircraft. The device exhibits a floor plate of a cargo unit of a transport means, an edge profile, a rail bumper as well as a first damping unit. The first damping unit is situated between the edge profile and the floor plate, or between the edge profile and the rail bumper of the cargo unit. The first damping unit is designed for damping a movement by the cargo unit in a direction of movement of the cargo unit so as to reduce the loads placed on the cargo unit. | 02-16-2012 |
| 20120034028 | FASTENING DEVICE FOR A MODULE ELEMENT IN AN AIRPLANE - A fastening device for attaching a module element to a support structure in an aircraft includes a stud having a first end defining a broadened head configured to engage the support structure, a section which adjoins the head and defines a first lateral dimension and a second lateral dimension that is larger than, and is disposed at least substantially perpendicularly to, the first lateral dimension, and a second opposite end connected to a lever which is movable between open and closed positions relative to the stud. A bushing, which may be electrically conductive, is provided on and longitudinally movable along the stud, which is configured to contact the support structure and to support an outer wall of the module element. An eccentric may be actuated by the lever and is responsive to movement of the lever into the closed position to move the bushing along the stud towards the head. | 02-09-2012 |
| 20120032030 | HIGH LIFT SYSTEM FOR AN AIRPLANE, AIRPLANE SYSTEM AND PROPELLER AIRPLANE HAVING A HIGH LIFT SYSTEM - A high-lift system of an aeroplane is described, including one or more high-lift flaps, an activation device with an activation function for generating adjustment commands for adjusting the adjustment state of the high-lift flaps, and a drive device coupled with the high-lift flaps, which is configured such that on the basis of activation commands the high-lift flaps are adjusted between a refracted adjustment state and an extended adjustment state. The activation function, on the basis of input values, generates adjustment commands and transmits these to the drive device for adjusting the high-lift flaps. The activation function has a function for the automatic retraction of the high-lift flap in flight, which in a flight condition in which the high-lift flap has assumed an extended adjustment state, whilst taking into account an engine thrust and a minimum flight altitude, generates an activation command, in accordance with which the high-lift flap retracts. | 02-09-2012 |
| 20120032027 | PASSENGER SERVICES CONDUIT - A multifunctional module is provided for a passenger services conduit in an aircraft. The multifunctional module includes, but is not limited to a first interface and at least one utility unit for providing a passenger with services. The first interface is for connecting the utility unit to the passenger utility conduit, the interface, for example, being designed as a mechanical interface. | 02-09-2012 |
| 20120032026 | WORK AREA IN AN AIRCRAFT - A work area is provided for members of a flight crew that includes, but is not limited to a central module, which borders an area adapted for being closed intended for use by crewmembers to change clothes. The central module is arranged in the tail area of the aircraft cabin, and can be used for stowing trolleys. The area is closed by lateral doors, and can be used as a passageway when the doors are open. | 02-09-2012 |
| 20120025024 | DEVICE FOR THE MOUNTING OF CONNECTORS - A device for mounting at least one connector in an aircraft fuselage includes a first and a second traverse configured to connect the device to a structural section of the aircraft fuselage at end sections of the first and second traverses. A frame element extends transversely between the first and the second traverses and is configured to accommodate the at least one connector. A first and a second connecting profile respectively connect the frame element to the first and second traverse. | 02-02-2012 |
| 20120021635 | DEVICE FOR CONNECTING A FIRST ELECTRIC CABLE TO A SECOND ELECTRIC CABLE, DISTRIBUTOR ARRANGEMENT AND AIR- OR SPACECRAFT - The present invention provides a device for connecting a first electric cable to a second electric cable, said device comprising: a first cable lug which comprises a first connection portion for electrically contacting the first electric cable and a socket portion having a conical socket; a second cable lug which comprises a second connection portion for electrically contacting the second electric cable and a plug portion having a conical plug; wherein the plug can be inserted into the socket and conductively contacted therewith in order to connect the first cable to the second cable in an electrically conductive manner. | 01-26-2012 |
| 20120020801 | STRUCTURAL ELEMENT FOR AN AIRCRAFT OR SPACECRAFT AND METHOD FOR PRODUCING SUCH A STRUCTURAL ELEMENT - The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimise the natural vibration behaviour of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behaviour of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behaviour of the structural element is optimised. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element. | 01-26-2012 |
| 20120012707 | INTEGRATION OF SUPPLY FUNCTIONS IN A STORAGE COMPARTMENT - Integration of supply functions is provided in a storage compartment. In particular, an integrated module is provided, which can be mounted in the overhead area of a passenger cabin, and exhibits different system components, which are automatically hooked up to the supply system of the transport (e.g., an aircraft) during the mechanical installation of the module on the load-bearing structure of the cabin. | 01-19-2012 |
| 20120012706 | INTEGRATED MONUMENT - A monument is provided for an aircraft. The monument includes, but is not limited to several system components with identical, substantially identical or similar functions that can be connected by way of a single system connection arrangement to the supply in the aircraft. Distribution of the supply media, received by the aircraft, to the individual system components takes place within the monument. The system connections can thus be identical to the system connections of a single monument. | 01-19-2012 |
| 20120012705 | TRANSFORMABLE LUGGAGE STORAGE COMPARTMENT FOR AN AIRCRAFT CABIN - A storage compartment is provided for a transportation means, for mounting in an overhead region. The storage compartment includes, but is not limited to a universal housing module and a transformable container module. Various container modules, in particular fixed bins and pivot bins, can be installed in the universal housing module without this requiring any alteration of the housing module. The transformable container module can be converted within the housing module from a state as a fixed container to a state as a movable chute. | 01-19-2012 |
| 20120012704 | ACCOMMODATION MODULE WITH SEPARATE PRIVATE AREA - Indicated herein is a lounge module for crewmembers of an aircraft, which exhibits a screen device, such as a privacy roller blind. This privacy roller blind can be used to visually demarcate a first aisle area from a second aisle area, thereby creating a private area for the aircraft crew. | 01-19-2012 |
| 20120012698 | AIRCRAFT COMPRISING AN INSULATION SYSTEM FOR THERMAL AND ACOUSTIC INSULATION - The invention relates to an aircraft comprising an insulation system for thermal and acoustic insulation. Said insulation system includes a cabin, an outer skin, a sound insulating unit, and a heat insulating unit. The sound insulating unit is designed to acoustically insulate the aircraft. The heat insulating unit is designed to thermally insulate the aircraft. The sound insulating unit and the heat insulating unit are arranged between the cabin and the outer skin. | 01-19-2012 |
| 20120006938 | POWER GENERATING SYSTEM FOR INTEGRATION INTO AN AIRCRAFT SYSTEM - A power generation system for integration into an aircraft system, including a secondary power supply device having a generator turbine arranged in a duct running between a forward opening and a rearward opening on the fuselage of the aircraft. An electromagnetic unlocking device locks and unlocks a covering device on the forward opening, depending on a signal strength supplied to the unlocking device. The system also includes an actuation device that generates an opening or closing signal for an opening and closing device, and an opening function switching device that activates the unlocking device electrically with a signal strength that locks the covering device in an initial state, and on receipt of a power requirement signal from a power generation monitoring device, activates the unlocking device with a second signal strength that unlocks the covering device. | 01-12-2012 |
| 20120006236 | ADHESIVE HOLDER FOR HOLDING OBJECTS AND KIT, AS WELL AS METHOD FOR MAKING AN ADHESIVE HOLDER - An adhesive holder for holding objects comprises an adhesive layer, an object holder, an adapter with a contact surface and a counter element with a counter surface. The counter surface of the counter element is positionable at a distance from the contact surface of the adapter in order to enclose a section of a structural element. The adhesive layer can be applied onto the contact surface of the adapter or onto the counter surface of the counter element. The adhesive holder according to the invention makes it possible to introduce a force into a structural element by exerting compressive stress and shearing stress only such that the adhesive connection is much more durable and the adhesive holder can be subjected to higher loads than in the state of the art. | 01-12-2012 |
| 20120003908 | Method And System For Emergency Ventilation Of An Aircraft Cabin In The Case Of A Leak In The Area Of An Air Mixer - In a method for emergency ventilation of an aircraft cabin ( | 01-05-2012 |
| 20120003480 | 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. | 01-05-2012 |
| 20120001481 | POWER DISTRIBUTION DEVICE FOR DISTRIBUTING POWER AND A METHOD FOR THE DISTRIBUTION OF POWER - A power distribution device has a number N | 01-05-2012 |
| 20120001028 | WING OF AN AIRCRAFT AND ASSEMBLY OF A WING COMPRISING A DEVICE FOR INFLUENCING A FLOW - A wing of an aircraft is described, having: a main wing, at least one high lift flap which can be moved between a retracted and an extended position, and a spoiler. The main wing has ejection openings, arranged side-by-side along the main wing spanwise direction, and in the main wing chordwise direction, and which are connected via an air conduit with the outlet device of a flow delivery driver device on the main wing or on the spoiler. The spoiler has inlet openings for the intake of air, which are connected via an air conduit with the inlet device of the flow delivery driver device. The flow delivery driver device has a receiver device for the reception of command signals for purposes of adjustment of the flow delivery driver device. An arrangement of a wing with a device for purposes of flow control with such a wing is also described. | 01-05-2012 |
| 20120000630 | Cooling Of An Electronic Device In An Aircraft By Case-By-Case Single-Phase Or Two-Phase Cooling - Cooling of an electronic device in an aircraft by case-by-case single-phase or two-phase cooling | 01-05-2012 |
| 20120000220 | Adsorption Cooling System And Adsorption Cooling Method For An Aircraft - An adsorption cooling system ( | 01-05-2012 |
| 20110315408 | Fire Extinguishing System for an Airplane and Method for Fire Fighting in an Airplane - An airplane fire extinguishing system comprises an extinguishing agent storage unit with an activatable closing device, which makes possible, when active, an outflow of extinguishing agent from the extinguishing agent storage unit, and a supply line, connected with the closing device and an outlet opening, via which the extinguishing agent can be conducted from the extinguishing agent storage unit to the outlet opening, in order to eject it there for firefighting, wherein one or more sensor systems are present, by means of which a current airplane state can be determined, and a control unit, connected with the closing device and an actuatable input element, is present, via which the closing device can be activated, the control unit constructed and configured in such a way that the closing device is activated, as a function of the current airplane state, which exists at the time of an actuation of the input element. | 12-29-2011 |
| 20110313564 | MODULAR ADAPTIVE ELECTRICAL FREIGHT LOADING SYSTEM - A cargo loading system for a means of transport with a power drive unit | 12-22-2011 |
| 20110309784 | COUNTER ELECTRO-MOTORIC FORCE BASED FUNCTIONAL STATUS DETECTION OF AN ELECTRO-MOTOR - The present invention relates to a circuit for detecting a functional status of an electro-motor. Typical electro-motors need additional components to identify the functional status of the motor. This means additional weight for such motors determining the functional status. According to the present invention a circuit is provided using a part of a motor as a sensor for detecting the functional status of the electro-motor. | 12-22-2011 |
| 20110309214 | APPARATUS FOR AFFIXING AN OBJECT TO A RAIL - An apparatus for affixing an object to a rail includes, but is not limited to at least one base body, at least one locking body and at least one operating element. The locking body is held so as to be movable relative to the base body and is connected to the operating element by way of at least one bearing. The operating element is arranged so as to be rotatable in the base body, includes, but is not limited to a cam that acts on the base body, and when rotated moves the locking body towards the base body. In this way apparatus is created which makes possible the manual affixing and undoing, without the need for tools, of an object on and from a rail, for example, if needed, in order to reposition displaceable monuments in a cabin of an aircraft. | 12-22-2011 |
| 20110308714 | METHOD AND SHAPING DEVICE FOR PRODUCING A COMPOSITE FIBRE COMPONENT FOR AIR AND SPACE TRAVEL - A forming tool with a predefined mould portion is provided in a method for producing a reinforced fibre composite component for aviation and aerospace. A forming/support element is moulded by means of the mould portion of the forming tool. A semi-finished fibre product is then deposited at least in portions on the shaped forming/support element. The deposited semi-finished fibre product is deformed by means of the forming/support element to form at least one reinforcing portion. The forming/support element is then removed from the forming tool together with the reinforcing section formed on this element, followed by defined positioning of the reinforcing section thus formed with respect to an associated fibre composite component portion by supporting with the forming/support element. The reinforcing portion is cured to form the reinforced fibre composite component. A forming device is provided with a predefined mould portion which holds a forming/support element such that it can be removed. | 12-22-2011 |
| 20110306285 | Method And System For Emergency Ventilation Of An Aircraft Cabin - The invention relates to a method for emergency ventilation of an aircraft cabin ( | 12-15-2011 |
| 20110305031 | ILLUMINATION DEVICE FOR SEVERAL PEOPLE IN AIRPLANES - The invention relates to a lighting device and a method for illuminating a projection area based on a plurality of different lighting patterns. The lighting unit is controlled based on lighting data, which are received from an external central system via an interface, or stored in a memory unit. In this way, a plurality of different lighting patterns can be realized, so that at least up to four reading lamps can be replaced by a single lighting unit. | 12-15-2011 |
| 20110303791 | Fuselage Section of an Aircraft and Method for the Production of the Fuselage Section - In accordance with the method, an inside layer of a fuselage section skin made from first fibers is placed on a manufacturing surface, the first fibers being placed in one or more first fiber directions. On the inside layer, a stiffening structure is formed from stiffening fibers, the stiffening fibers being placed in one or more stiffening fiber directions. An outside layer of the fuselage section skin, comprising fourth fibers, is placed on the stiffening structure formed from stiffening fibers, the fourth fibers being placed in one or more fourth fiber directions. The stiffening structure is designed and developed in such a way that the fuselage section does not require an additional stiffening structure, is connected with the fuselage section skin, and comprises the inside layer, the stiffening structure, and the outside layer; in particular, an additional stiffening structure in the form of stringers and frames is not required. | 12-15-2011 |
| 20110303786 | SILENCER FOR AN AUXILIARY POWER UNIT OF AN AIRCRAFT - A silencer for an auxiliary power unit of an aircraft comprises an inlet, an outlet, a housing and a flow channel with a porous wall material that is arranged in the housing. An intermediate space is formed between the housing and the flow channel and divided into outer cells that are arranged around the flow channel by means of one or more partitions. This makes it possible to realize a very compact silencer with very good sound insulation properties. The sound dampening can be additionally improved by dividing the outer cells into outer regions and inner regions, by adapting the shape of the silencer to a tail section of an aircraft and by arranging an annular channel on the outlet. | 12-15-2011 |
| 20110300880 | SENSORS FOR AN AIRCRAFT FOR LOCATING DEVICES - The invention relates to a sensor network for determining the position of devices and gear in an aircraft. The sensor network exhibits several sensor nodes, which have an autonomous power supply. The sensor nodes can communicate wirelessly with each other and with a central processing unit. The position of each individual sensor node can be determined by evaluating high-frequency signal parameters. | 12-08-2011 |
| 20110300786 | System And Method For Ventilating Explosive Regions Of An Aircraft | 12-08-2011 |
| 20110299470 | SENSOR AND SENSOR NETWORK FOR AN AIRCRAFT - The invention relates to a sensor network in an aircraft, which comprises several sensor nodes that communicate with a central data collection and evaluation unit via a radio transmission path. Data transmission can take place in various ways. For example, different frequency ranges are provided, from which the respective frequency range enabling the best data transmission quality is selected. | 12-08-2011 |
| 20110297805 | WALL MOUNTING FOR ON-BOARD ENTERTAINMENT CONTROL UNITS - A standardized wall is provided for mounting control units of system components in an aircraft cabin with a fastening unit and at least one plug unit. The fastening unit is designed for guiding the control unit during an installation movement of the control unit on the wall mounting. The plug unit is designed for producing a plug connection between the control unit and the wall mounting during the installation movement of the control unit on the wall mounting. | 12-08-2011 |
| 20110297796 | VANE HAVING A REGULATING FLAP AND A GAP COVERING DEVICE AND AN ADJUSTING MECHANISM FOR A GAP COVERING DEVICE - A wing, having an adjustable flap that can be moved between a retracted and an extended setting is provided, as well as a gap-covering device, with an adjustment lever and a gap-covering flap arranged on the latter with a flow surface. The adjustment lever with the gap-covering flap is pre-loaded by means of a pre-loading device into a first setting, in which the gap-covering flap is located in the interior of the wing. The adjustable flap and the adjustment lever with the gap-covering flap are mechanically coupled such that as the adjustable flap moves into its retracted setting, a movement of the adjustment lever takes place against the pre-load effected by the pre-loading device, into a second setting. The flow surface of the gap-covering flap in the second setting of the adjustment lever runs between the upper side of the retracted adjustable flap and the wing flow surface. | 12-08-2011 |
| 20110297788 | SHELL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT - The present invention provides a shell component for an aircraft or spacecraft. The shell component comprises a skin panel, a plurality of stringers which are arranged on the skin panel, a former which comprises a fibre composite material and is arranged over the stringers so as to cross said stringers, and a former connection structure which comprises a ductile material and a plurality of foot portions fixed to the skin panel. The foot portions each transition integrally into a shoulder portion fixed to the former over an associated fixing span, the fixing spans associated with the foot portions extending along the former substantially continuously over the stringers. | 12-08-2011 |
| 20110294409 | Side Feeder Air Guiding Element For An Aircraft Air-Conditioning System - An air guiding element ( | 12-01-2011 |
| 20110294319 | Line System - The invention relates to a line system, in particular in an aircraft cabin. The line system has a line channel ( | 12-01-2011 |
| 20110290951 | CABLE MANAGEMENT DEVICE FOR BUNDLES OF CABLES IN AN AIRCRAFT - A cable management device accommodates bundles of cables in an aircraft. The cable management device includes a star shaped cable management element and a retaining clamp. The star-shaped cable management element includes a plurality of outer-radial recesses disposed in an outer radius of the star-shaped cable management element that are spaced apart from each other. Each outer-radial recess is configured to accommodate a cable inserted therein. The retaining clamp is disposed around an outer circumference of the star-shaped cable management element so as to encompass the star-shaped cable management element and close the outer radial recesses. The retaining clamp includes an attachment portion configured to affix the cable management element to a stationary supporting structure. | 12-01-2011 |
| 20110290940 | PRESSURE BULKHEAD FOR PURPOSES OF ARRANGEMENT IN AN AIRCRAFT FUSELAGE - A pressure bulkhead for a fuselage of an aircraft is configured for bounding a fuselage interior relative to an external environment. The pressure bulkhead includes a flat skin configured to span a cross-section of the fuselage and having a cavity disposed at a core region of the skin. The core region is radially bounded by a ring element. A plurality of radial stiffeners extend on the skin and provide stabilization of the skin. Each radial stiffener is fixed at an end to the ring element. A reinforcement element extends over the ring element. | 12-01-2011 |
| 20110290939 | CIRCUMFERENTIAL STIFFENER FOR AN AIRCRAFT FUSELAGE - A circumferential stiffener configured for a fuselage of an aircraft includes a web disposed at an angle to a normal axis of the circumferential stiffener, at least one inner flange, at least one outer flange and an integral angle profile configured for connection to a skin section of the fuselage. | 12-01-2011 |
| 20110290784 | HEATING SYSTEM HAVING AT LEAST ONE ELECTROTHERMAL HEATING LAYER, A STRUCTURAL COMPONENT HAVING SUCH A HEATING LAYER, A HEATING METHOD AND A METHOD FOR PRODUCING A SEMI-FINISHED COMPONENT OR A COMPONENT HAVING A HEATING DEVICE - A heating system including an energy supply device, wherein the heating system includes a base heating device having an insulation layer, with an electrothermal base heating layer arranged thereon and with an electrical connecting device by way of which the energy supply device is connected to the base heating layer. The heating system includes an additional heating device having an insulation layer, with an electrothermal additional heating layer arranged thereon and with an electrical connecting device by way of which the energy supply device is connected to the additional heating layer. The energy supply device is connected to the heating layers by way of the connecting devices and in the activation phase, current is supplied during at least a partial period of time to the additional heating layer so that the base heating layer generates heat permanently, while the additional heating layer generates heat in the partial period of time. | 12-01-2011 |
| 20110287249 | ANTI-EROSION LAYER FOR AERODYNAMIC COMPONENTS AND STRUCTURES AND METHOD FOR THE PRODUCTION THEREOF - An anti-erosion layer is provided for aerodynamic components or structures and to a method for producing such a layer. Microscale or nanoscale hard material particles are embedded in a binding layer that includes a material that adheres to the aerodynamic component or structure. The anti-erosion layer can be applied by spraying or by evaporation coating. | 11-24-2011 |
| 20110284691 | Method for connecting a first material to a second material in aircraft construction - The invention concerns a method of connecting a first material to a second material by means of a heat-activatable adhesive material ( | 11-24-2011 |
| 20110284689 | AIRCRAFT CABIN PANEL FOR SOUND REDUCTION - The present invention relates to an aircraft cabin panel for sound reduction in an interior space. The invention in particular also relates to an aircraft comprising an interior lining with sound-absorbing and sound-reducing panels. In order to provide a panel that is optimized in terms of the design space required by it and in terms of its weight, for use in aircraft, which panel provides improved sound reduction and sound absorption characteristics, an aircraft cabin panel for sound reduction in an interior space is provided, which aircraft cabin panel in at least one region comprises a sandwich construction with a core layer, a first covering layer and a second covering layer. The core layer comprises sound absorbing open-pore core material. The first and the second covering layer are connected to the core layer in a planar fashion. The first covering layer is arranged towards the sound waves to be absorbed and the second covering layer is arranged opposite the first covering layer. The first covering layer is designed so as to be acoustically transparent. | 11-24-2011 |
| 20110284201 | Auxiliary Cooling Device For Connection To An Aircraft Liquid Cooling System - An auxiliary cooling device ( | 11-24-2011 |
| 20110283713 | System For Cooling A Heat Exchanger On Board An Aircraft | 11-24-2011 |
| 20110278395 | STRUCTURAL COMPONENT WITH IMPROVED CONDUCTIVITY AND MECHANICAL STRENGTH, AND A METHOD FOR ITS MANUFACTURE - A structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection. | 11-17-2011 |
| 20110277924 | METHOD AND DEVICE FOR FITTING A FUSELAGE SHELL WITH A WINDOW FRAME - A method of fitting a fuselage shell of an aircraft with at least one window frame of a cabin window includes positioning an uncured laminate including a fiber-reinforced plastic-based composite material configured to form a fuselage shell on a mold surface. A window aperture is introduced into the laminate. A window frame including a fiber-reinforced plastic-based composite material is positioned on the laminate in a region of the window aperture. The laminate is cured under the action of pressure and temperature so as to connect the window frame with the laminate by a material bond. | 11-17-2011 |
| 20110274863 | THERMAL INSULATING TAPE WITH FIRE PROTECTING SYSTEM AND ITS USE IN AIRCRAFT CONSTRUCTION - A thermal insulating tape is configured for fire protection for use in aircraft construction. The insulating tape has a multilayer construction including a flexible carrier tape providing protection against burn-through, the carrier tape being formed as a thermally conductive metal tape. An adhesive film is disposed on a first side of the carrier tape and is configured for partial fixation or complete wrapping of the insulating tape on a protected component. A flexible intumescent coating is disposed on a second side of the carrier tape. | 11-10-2011 |
| 20110274418 | FLUID CONDUIT WITH PTC FABRIC HEATING - Fluid conduit segments are provided that include, but are not limited to integrated heating systems for protection against freezing. To this effect PTC-fabric heating elements are provided that are integrated in the fluid conduit segments and that in the negative temperature range include, but are not limited to a PTC-temperature-dependent resistance. The heating system thus provides a higher output in the negative temperature range and a lower output in the positive temperature range, i.e., the heating limits itself until temperature equalization has been reached. | 11-10-2011 |
| 20110270482 | ADAPTIVE CENTRAL MAINTENANCE SYSTEM AND METHOD FOR PLANNING MAINTENANCE OPERATIONS FOR SYSTEMS - A maintenance system for generating maintenance instructions for at least one system, the maintenance system having a plurality of system components set up to receive operating data for a system from a central control unit of the system, to use said data to identify a fault of a system component, to compare the fault with predefined known faults and to retrieve maintenance operations which have already been carried out or are predefined and are correlated with the known faults from a main memory and to select a maintenance operation which correlates with the identified fault in order to rectify the fault and to output the operation as a maintenance instruction. A method for planning maintenance operations has steps of monitoring the systems for faults and generating a maintenance instruction. | 11-03-2011 |
| 20110266986 | FAULT DETECTION METHOD FOR ELECTRIC MOTORS WITH ONE OR SEVERAL STAR POINTS - A detection and control device is provided for detecting a motor fault of an electric motor with star point topology, with an evaluation unit, a control unit, and a return unit. The return unit is configured for returning a star point potential of the electric motor to the evaluation unit, the evaluation unit is configured for evaluating the star point potential and the control unit is designed for passivating a motor fault on the basis of the evaluation. The function of the return unit and of the evaluation unit may also be assumed by control lines and by the control unit. | 11-03-2011 |
| 20110266398 | WING/FUSELAGE CONNECTION OF AN AIRCRAFT - A wing-fuselage connection of an aircraft, in which a wing ( | 11-03-2011 |
| 20110266392 | PASSENGER SUPPLY ARRANGEMENT FOR AN AEROPLANE - A passenger supply arrangement provides a communications system and comfort system for a passenger of an aeroplane. The passenger supply arrangement includes a presentation surface configured to be integrated into a backrest of a passenger seat of an aeroplane and a passenger supply module configured to be disposed above the passengers seats of the aeroplane. The passenger supply module includes at least one projector configured to project an image onto the presentation surface. The image includes a monitoring area for playback of video and an operating area for displaying and for actuation of operating elements of the passenger supply module. | 11-03-2011 |
| 20110255968 | ADJUSTER DEVICE FOR AN AIRCRAFT, COMBINATION OF AN ADJUSTER DEVICE AND AN ADJUSTER DEVICE FAULT RECOGNITION FUNCTION, FAULT-TOLERANT ADJUSTER SYSTEM AND METHOD FOR RECONFIGURING THE ADJUSTER SYSTEM - An adjustment device to be coupled to an adjustment flap of an aircraft, with an actuator, adjustment kinematics, and a gearing, wherein the adjustment device can be coupled to a controller/monitor for purposes of its actuation. The adjustment device includes a first load sensor, on the input side of the actuator for determining the load arising on the input side due to actuation of the adjustment flap, and a second load sensor, on the output side of the actuator for determining the load arising on the output side due to actuation. The first load sensor and second load sensor are functionally linked with a fault-recognition function for receiving sensor values ascertained by the load sensors, to assign a fault state to the adjustment device. A combination of an adjustment device and a fault recognition function, a fault-tolerant adjustment system, and a method for reconfiguring the adjustment system are also provided. | 10-20-2011 |
| 20110253878 | SUPPORTING PILLAR FOR AN AIRCRAFT'S STRUCTURAL COMPONENT MANUFACTURED BY A SELECTIVE LASER MELTING PROCESS - The invention relates to an elongated supporting pillar for a high-strength structural component, wherein the supporting pillar is designed to absorb bending forces that act transversely to a longitudinal direction of extension of the supporting pillar. The supporting pillar comprises a wall which at least partially encloses an elongated cavity of the supporting pillar. A reinforcement structure is arranged within the cavity and transversely to the direction of longitudinal extension in such a manner that the reinforcement structure can absorb at least some of the bending forces. The reinforcement structure is designed integrally with the wall, wherein both the wall and the reinforcement structure comprise a meltable material. | 10-20-2011 |
| 20110248514 | LOCKING MECHANISM FOR AN AIRCRAFT DOOR AND METHOD FOR THE LOCKING OF AN AIRCRAFT DOOR - A locking mechanism for an aircraft door includes a plurality of frame-side fittings and a plurality of door-side fittings. Each frame-side fitting includes a pin with an eccentric rotary cylinder mounted on each pin. Each door-side fitting includes an eccentric rotary latch configured to encompass at least a section of a corresponding rotary cylinder. Also a method of locking a door using the locking mechanism. | 10-13-2011 |
| 20110248122 | FORE FLAP DISPOSED ON THE WING OF AN AIRCRAFT - A leading edge slat arranged on the aerofoil of an aircraft. The leading edge slat is provided on the front of the main wing. The leading edge slat has a partially extended setting, with its trailing edge flat against the wing, and a further extended setting, with its trailing edge spaced apart from the nose of the wing to open a gap feeding high-energy air from the lower surface of the slat to the upper surface of the wing. The leading edge slat includes a body and a trailing edge facing the main wing, which can be bent around the spanwise direction of the slat relative to the body, and on which the trailing edge of the slat is provided, and which by means of a device generating a contact force is loaded for making contact between the trailing edge of the slat and the profile nose of the wing. | 10-13-2011 |
| 20110248117 | MULTILAYER BOARD FOR ACOUSTIC INSULATION - A multilayer board is provided for acoustic insulation and to a method for producing said board. In order to reduce sound emission and at the same time improve stability, a multilayer board for acoustic insulation is proposed that includes, but is not limited to a core sheet, a first covering layer and a second covering layer. At least one of the two covering layers is of a closed design. The core sheet is arranged between the first covering layer and the second covering layer and is firmly connected in a planar fashion to the covering layers. Furthermore, the core sheet comprises slits that extend within the core sheet in the direction of the core sheet thickness, which slits reduce the shear stiffness of the board and thus ensure an improved acoustic insulation effect. On both sides the core sheet comprises continuous edge zones, which extend parallel to the covering layers, in order to, together with the covering layers, ensure the best possible stability of the board. The invention in particular also relates to an aircraft with an interior lining formed by panels that comprise the multilayer boards according to the invention in order to provide acoustic insulation. | 10-13-2011 |
| 20110247432 | Aircraft Conduit Monitoring System And Method - The invention relates to an aircraft conduit monitoring system comprising a conduit that conducts gas from a source to a point of application. A flow sensing device and a pressure sensing device are provided within the conduit. At least one set value of a gas mass flow rate and at least one set value of a pressure are sensed in a learning mode of operation. Said set values are compared with sensed actual values in the normal mode of operation. A gas volume flow rate can also be sensed and processed instead of a gas mass flow rate. | 10-13-2011 |
| 20110240796 | SUPPLY UNIT FOR FLEXIBLE SUPPLY CHANNELS - According to one exemplary embodiment of the invention, a service unit for being installed on a service channel of an aircraft is disclosed, wherein said service unit features a mounting device and a connecting device. These two devices cooperate in such a way that the mounting and the automatic connecting are realized in one step when the service unit is moved into the installation position. | 10-06-2011 |
| 20110237173 | System And Method For Air Conditioning An Aircraft Cabin With Improved Cooling Capacity | 09-29-2011 |
| 20110235350 | Overhead Reading Lamp for A Passenger Seat - An overhead reading lamp for a passenger seat, in particular in an aircraft cabin, comprises a first plurality of light sources ( | 09-29-2011 |
| 20110233334 | STRUCTURE, ESPECIALLY A FUSELAGE STRUCTURE OF AN AIRCRAFT OR A SPACECRAFT - The present invention provides a fuselage structure ( | 09-29-2011 |
| 20110226901 | METHOD FOR LAYING A FLOOR COVERING IN A CABIN OF A VEHICLE - A method for laying a floor covering onto a floor in a cabin of a vehicle comprises the steps of applying a connection means to an element of a group comprising the floor covering and a floor, compacting the floor covering into a compact unit having an open end, bringing the floor covering into the cabin, pulling the open end of the floor covering along a length of the cabin beneath seats disposed in the cabin on the cabin floor and connecting the floor covering to the cabin floor using the connection means. The connection is made by way of one or more adhesive layers, for example. In this way, a carpet floor can be laid or replaced in a cabin of a vehicle without having to remove the seats located in the cabin. | 09-22-2011 |
| 20110226377 | Aircraft System Carrier Element - An aircraft system carrier element ( | 09-22-2011 |
| 20110220759 | POWER DISTRIBUTION SYSTEM - The invention relates to a power distribution system for an aircraft that comprises at least one engine, comprising at least one torque transmission means that is movably held and is connected to at least one shaft of the engine and extends from the shaft of the engine to an interior region of the aircraft fuselage, and at an end pointing away from the engine comprises at least one interface for introducing a torque. At the interface of the torque transmission means it is possible both to operate mechanical and to start the engine. Consequently in the aircraft it is possible to essentially do without converting mechanical energy to electrical energy and the subsequent use of electrical energy for generating mechanical power. This is particularly favourable in the case of twin-engine commercial aircraft that are used on short hauls. | 09-15-2011 |
| 20110220527 | SEALABLE APPARATUS WITH DATA- AND ENERGY TRANSMISSION THROUGH ELECTROMAGNETIC INDUCTION - The invention relates to the transmission of data and energy to sealed elements of sealable apparatus. To do so, the invention proposes the use of two antennas for electromagnetic induction. The non-cabled transmission of data and energy makes possible a random allocation of sealed elements into a plurality of receiving apparatus. | 09-15-2011 |
| 20110216505 | Aircraft Electronics Cooling Apparatus For An Aircraft Having A Liquid Cooling System - The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system ( | 09-08-2011 |
| 20110215203 | ATTACHMENT STRUCTURE, ATTACHMENT DEVICE AND ATTACHMENT SYSTEM FOR ATTACHMENT OF A FINISHING COMPONENT IN AN AIRCRAFT - An attachment device for attaching an equipment component in an aircraft, comprising a second attachment element for attaching an equipment component in an aircraft, the second attachment element comprising a guiding element, a contact element and a locking element, wherein the guiding element is introducible into a first section of a first attachment element, wherein the guiding element is movable from the first section of a first attachment element according to the present invention into a second section of the first attachment element, wherein the first attachment element and the second attachment element are mechanically couplable by engaging from behind the first attachment element in the second section of the first attachment element, wherein, in the coupled state, the contact element provides a mechanical contact between first and second attachment element and wherein by operating the locking element the first attachment element and the second attachment element are releasably fixable relative to one another. | 09-08-2011 |
| 20110215201 | STRUT SYSTEM FOR THE STABILIZATION OF THE SHELL OF AN AERODYNAMIC AIRCRAFT COMPONENT FOR A COMMERCIAL AIRCRAFT - The invention relates to a strut system for the stabilisation of the shell ( | 09-08-2011 |
| 20110215198 | MULTIFUNCTIONAL CARGO HOLD SYSTEM - An embodiment of the invention, relates to a multifunctional cargo hold system for an aircraft with a cargo hold floor; a retainer rail fitted to the cargo hold floor, suitable for the assembly of means for rolling and/or fixing of loaded elements, wherein the means has a variable assembly with regard to the longitudinal direction of the retainer rail, wherein the cargo hold system has a number of cargo positions, suitable for accommodating elements of the group, including a net for partitioning the cargo hold, a standard container, a palette, a telescopic system, an underfloor catering container, an underfloor rest space, a conveyor of fixed length and a conveyor of variable length, wherein each load position can accommodate at least four of the elements. | 09-08-2011 |
| 20110212678 | System And Method For Air-Conditioning An Aircraft Cabin | 09-01-2011 |
| 20110210607 | ADAPTIVE POWER SUPPLY - A voltage supply unit for providing an adaptive voltage supply to a consumer in a means of transport, wherein the voltage supply unit comprises a voltage output device and an output control device. The output control device and the voltage output device are designed to set an output voltage of the voltage supply unit adaptively in a consumer-dependent manner. | 09-01-2011 |
| 20110210606 | METHOD AND DEVICE FOR PROVIDING AN ELECTRICAL SYSTEM ALTERNATING VOLTAGE IN AN AIRCRAFT - The present invention provides a method and a device for providing a three-phase electrical system alternating voltage for an electrical system of an aircraft, a plurality of voltage sources being provided which comprise at least one engine generator and a further voltage source, in particular a fuel cell, comprising one or more frequency converters for converting an alternating voltage of variable frequency provided by the respective engine generator into a first output alternating voltage and comprising at least one cyclo-inverter for cyclo-inverting a voltage provided by the respective further voltage source into a second output alternating voltage which is synchronous with the first output alternating voltage and constitutes the electrical system alternating voltage. | 09-01-2011 |
| 20110210206 | CONNECTION OF A WING TO A FUSELAGE OF AN AIRPLANE - An aerofoil connection on a fuselage airframe comprising a plurality of double-jointed coupling members. In each case at least two z-coupling members extending substantially parallel to a vertical axis of the aircraft and in each case at least two xz-coupling members are arranged in the region of two longitudinal edges of a fuselage airframe recess wherein the xz-coupling members are configured in each case for a first maximum of a load in the event of a crash and of a load in normal flight operation parallel to a longitudinal axis of the aircraft, and for a second maximum of a load in the event of a crash and of a load in normal flight operation parallel to the vertical axis. The xz-coupling members are capable of absorbing force components parallel to the x-axis as well as force components which arise parallel to the z-axis. | 09-01-2011 |
| 20110208466 | TEST EQUIPMENT AND METHOD FOR TESTING AN AIRCRAFT OXYGEN SYSTEM CONTROL DEVICE - The present invention provides test equipment ( | 08-25-2011 |
| 20110208442 | METHOD AND APPARATUS FOR TESTING VALVE CONTROL SYSTEM - The present invention provides a method and apparatus for testing a valve control system in an aircraft fuel supply system having a plurality of control valves, wherein the control system includes a processor adapted to receive feedback signals from each of the plurality of control valves, the method comprising the steps of: connecting a test device to the control system such that the test device is connected for signal transmission to the processor; outputting a signal to the processor simulating a feedback signal from at least one of the control valves; detecting a control signal which is output by the processor to the at least one of the control valves; and identifying the detected control signal which is output by the processor to the control valve. | 08-25-2011 |
| 20110205089 | AIRCRAFT POWER FAILURE SIMULATION APPARATUS AND METHOD - Disclosed is a flight management means verification apparatus ( | 08-25-2011 |
| 20110203391 | APPARATUS AND METHOD FOR TESTING AN AIRCRAFT PEDAL SYSTEM - An apparatus ( | 08-25-2011 |
| 20110198439 | WHEEL DRIVE SYSTEM FOR AN AIRCRAFT COMPRISING A FUEL CELL AS AN ENERGY SOURCE - The invention pertains to a wheel drive system for an aircraft that features at least one electric motor and at least one fuel cell as energy source for the electric motor, wherein the electric motor is coupleable to at least one wheel of at least one landing gear of the aircraft. The inventive wheel drive system reduces the fuel consumption and lowers the emission of CO | 08-18-2011 |
| 20110192937 | NON-PLANAR WING TIP DEVICE FOR WINGS OF AIRCRAFT, AND WING COMPRISING SUCH A WING TIP DEVICE - A wing tip device for a wing includes a root and a tip, and the following determinant characteristics: the local dihedral of the wing tip device continuously increases or decreases from the root to the tip; the local sweep of the trailing edge continuously increases along its progression from the root to the tip of the wing tip device; where the local sweep of the leading edge continuously increases in the progression of the leading edge from the root to a first intermediate point; continuously decreases from the first intermediate point to a second intermediate point; and continuously increases from the second intermediate point at least to a region before of the tip of the wing tip device; as well as a wing comprising a wing tip device. | 08-11-2011 |
| 20110192935 | DEVICE FOR HOLDING LUGGAGE IN A PASSENGER CABIN OF AN AIRCRAFT - The invention relates to a device for holding luggage in a passenger cabin of an aircraft, said device being arranged above a seat row in a passenger cabin of an aircraft or a vehicle and being fastened to a structure which is fixed to the aircraft. The luggage rack comprises an outer housing which is fixed in position and into which a separate inner housing is fit in a positive-locking manner. The inner housing is arranged relative to the outer housing so that said inner housing can move between two end positions about a moving pivot point close to the center of gravity in a force-operated manner. In the closed end position, the luggage rack is visibly integrated into a cabin lining of the passenger cabin. | 08-11-2011 |
| 20110188862 | LAYOUT APPARATUS, RADIO APPARATUS, AND METHOD FOR COMMUNICATING IN AN AIRPLANE - A layout apparatus for communicating includes, but is not limited to, a structural device, a first signal adjustment device and a radio device. The structural device is designed for configuring the layout of a room, and the first signal adjustment device is adapted for the electrical-optical conversion of an antenna signal. Furthermore, the first signal adjustment device and the radio device are arranged in the structural device, and the radio device is connected to the first signal adjustment device in such a manner that the antenna signal can be transmitted and/or received as a radio signal. | 08-04-2011 |
| 20110188198 | Aircraft Signal Computer System Having A Plurality Of Modular Signal Computer Units - An aircraft signal computer system ( | 08-04-2011 |
| 20110186683 | METHOD AND A DEVICE FOR THE MANUFACTURE OF A STIFFENING STRUCTURE FOR AN AIRCRAFT FUSELAGE SEGMENT, AND ALSO A STIFFENING STRUCTURE - A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners. | 08-04-2011 |
| 20110186681 | LOAD PATH-OPTIMIZED PIVOTABLE HATRACK - The invention relates to a device for receiving baggage in a passenger cabin for aircraft, which device comprises a stowage compartment, also referred to as a “hatrack”, which stowage compartment is arranged above a seat row so as to be swivellable in longitudinal direction of the aircraft. The hatrack includes a single-part housing that forms a baggage receptacle. Starting from an open loading position, the housing is swivellable to a transport position or stowage position on a pivot axis that is arranged near the centre of gravity and that is associated with a bottom of the housing. For affixation of the hatrack the housing is connected to a structure of the aircraft fuselage, which structure is fixed to the aircraft, by means of an exterior frame. | 08-04-2011 |
| 20110186263 | HEAT EXCHANGER FOR THE OUTER SKIN OF AN AIRCRAFT - A heat exchanger for an outer skin of an aircraft comprises at least one feed line for a coolant, at least one discharge line for the coolant and at least one bundle of coolant channels through which coolant flows, wherein in the case of the heat exchanger being attached to the outer skin, the coolant channels are positioned directly on the outer skin of the aircraft, at least in areas, for dissipating heat to the surrounding environment of the aircraft. The heat exchanger may comprise cooling fins around which air flows for increasing the heat dissipation. | 08-04-2011 |
| 20110186150 | AIR DISTRIBUTION SYSTEM, FLOW RESTRICTOR AND CONTROL SYSTEM - An air distribution system comprises at least one air conduit, at least one air outlet, at least one flow restrictor, at least one sensor for acquiring an air state and at least one control unit. The air outlet is connected to the air conduit, the flow restrictor is positioned on the air conduit, and the control unit is connected to the sensor. The control unit is designed, in the case of any deviation of a measured air state at the air outlet from a predetermined desired air-state, to cause the flow restrictor to vary its aperture cross section. In particular in the case of air distribution systems comprising a multitude of air outlets efficient and quick trimming can take place in this manner. | 08-04-2011 |
| 20110183595 | AIRCRAFT WITH AT LEAST ONE PRESSURIZED FUSELAGE AREA AND AT LEAST ONE UNPRESSURIZED AREA AND METHOD FOR VENTILATING OF AN UNPRESSURIZED AREA OF AN AIRCRAFT - An aircraft includes, but is not limited to at least one fuselage with at least one pressurised fuselage region and at least one non-pressurized region and at least one air conditioning system for air conditioning the at least one pressurised fuselage region. The non-pressurized region includes, but is not limited to an air inlet and an air outlet connected to an air source from the pressurised fuselage region. Consequently it is possible to avoid the use of blowers, outlet valves and ram air flaps for ventilating non-pressurized regions of an aircraft. | 07-28-2011 |
| 20110180664 | Overhead Luggage Compartment with a Mounting for a Control Unit - An overhead luggage compartment is provided with a mounting for a control unit, having a first, top guide, which is fastened in the overhead luggage compartment. A second, bottom guide extends below and at least substantially parallel to the first guide. The first guide comprises a horizontal, first portion adjoined in an inward direction of the luggage compartment by a second portion, which extends obliquely upwards from the level of the first portion. The first portion of the first guide and the second guide are telescopically extensible in horizontal direction. The second guide is open in the direction of the first guide. A first suspension point is coupled rotatably to the outer end of the extensible portion of the first guide. A second suspension point is disposed inwards of the first suspension point and configured for displaceable engagement with the first portion and the second portion of the first guide. A third suspension point is disposed below the first suspension point and the second suspension point and configured for displaceable engagement with the second guide. | 07-28-2011 |
| 20110180618 | System For Targeted Local Air Humidification - In order to increase the air humidity in a cabin region ( | 07-28-2011 |
| 20110177771 | System For Cooling An Aircraft Zone, To Be Connected To An Aircraft-External Air Unit | 07-21-2011 |
| 20110174006 | ZONE TEMPERATURE CONTROL ON BOARD AN AIRPLANE BY MEANS OF FUEL CELL WASTE HEAT - The invention relates to an air conditioning system for a transportation means, having multiple zones to be air-conditioned, which may be variably air-conditioned by means of processed supply air in combination with individual trim air conduits, wherein the air conditioning system further has at least one heat exchanger for heating supply air by means of the exhaust heat of a fuel cell, and for discharging the supply air into a trim air distributor supplying the trim air conduits. | 07-21-2011 |
| 20110171896 | System And Method For Pumping Recirculation Air From An Aircraft Cabin | 07-14-2011 |
| 20110170263 | Aircraft Electronics Cooling Apparatus For An Aircraft Having A Liquid Cooling System - The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system ( | 07-14-2011 |
| 20110168701 | Storage System for Emergency Equipment - A storage system for an emergency apparatus provided in a conveyance includes at least one structure-holder connectable to a structural component of the conveyance. A frame is attached to the at least one structure-holder, and a carrier is configured to receive the emergency apparatus. A locking apparatus has a locking position in which the carrier is fastened to the frame, and an unlocking position in which the carrier is detached from the frame. A belt element is fixedly connected to the carrier. A first end of a retaining belt is connectable to a structural component of the conveyance via a belt-winder, and a second end of the retaining belt is fastenable in a detachable manner via a belt lock to the belt element. | 07-14-2011 |
| 20110168324 | METHOD FOR PRODUCING AN INTEGRAL FIBER COMPOSITE PART - The method according to the invention allows the production of a complex, integral (onepiece) fibre composite part having a plurality of internal and undercut stiffening elements employing removable cores. Because connection elements are no longer necessary, a high weight savings potential results, because, for example, rivets and rivet flanges required for this purpose, as in the case of conventional assembly from individual parts (differential construction), become superfluous. | 07-14-2011 |
| 20110166751 | METHOD FOR POSITIONING AT LEAST ONE COMPONENT, IN PARTICULAR A SEAT, IN OR ON AN AIRCRAFT OR SPACECRAFT, AND AIRCRAFT OR SPACECRAFT - The present invention provides methods for positioning at least one component, in particular a seat, in or on an aircraft or spacecraft comprising the following steps: controlling at least one light source of the aircraft or spacecraft to display at least one desired position of at least one component; and positioning the at least one component in the at least one desired position displayed. | 07-07-2011 |
| 20110164429 | READING LAMP OR SPOTLIGHT - A reading device, such as a reading lamp or reading spotlight, is provided for use in a vehicle, such as a motor vehicle with immovable properties or ships. The reading device for example can be used in passenger cabins and/or cockpits of aircraft. The reading device includes, but is not limited to an LED light source with a color temperature that can be adjusted with the color “warm-white” to “cold-white”, a primary optics or lens advantageously designed as a converging lens, and a secondary optics or lens to focus the light emitted by the light source onto a surface, such as a reading plane to be illuminated. | 07-07-2011 |
| 20110163204 | HIGH LIFT SYSTEM FOR AN AIRCRAFT WITH A HIGH LIFT FLAP AND METHOD FOR ADJUSTING THE HIGH LIFT FLAP - A high lift system for an aircraft with at least one high lift flap arranged on each of the main wings of the aircraft. The high lift system includes an input device for the generation of flight phase-related requirements for the high lift flap. The high lift system further includes a control device, with a conversion function with which the flight phase-related requirements are converted into setting commands for the actuation of a lift device for the adjustment of the high lift flap. The conversion function is configured such that from a take-off requirement, a setting command to the drive device is generated with which the leading edge flap of the high lift flap is arranged in a set state in which a gap exists between the leading edge flap and the main wing with a gap width of between 0.1% and 0.4% relative to the local wing chord. | 07-07-2011 |
| 20110162717 | APPARATUS AND METHOD FOR TESTING AN AIRCRAFT TANK SYSTEM - An apparatus for testing an aircraft tank system includes a fuel supply device including a fuel reservoir, a fuel supply line for supplying fuel from the fuel reservoir to a fuel outlet of the fuel supply device, and a first isolation valve disposed in the fuel supply line. A fuel transfer line transfers fuel from the fuel outlet of the fuel supply device to the aircraft tank system and a second isolation valve is disposed in the fuel transfer line. An electronic control unit (ECU) of the apparatus is adapted to control the first isolation valve and the second isolation valve so as to interrupt the supply of fuel through the fuel supply line and the transfer of fuel through the fuel transfer line, respectively, in response to a test parameter signal provided to the electronic control unit (ECU). | 07-07-2011 |
| 20110159798 | CONTROL DEVICE FOR SHIELDING A ROOM - A control device that shields a room from incoming signals includes an interference device which is adapted for querying an interference signal for rendering a signal that enters a room unrecognisable by superposition with the interference signal. | 06-30-2011 |
| 20110159229 | METHOD FOR EDGE SEALING A COMPONENT, DEVICE FOR IMPLEMENTING THE METHOD, AS WELL AS EDGE-SEALED COMPONENT - A method for edge sealing a fiber-reinforced component formed from a carbon fiber-reinforced thermoplastic or duroplastic plastic material includes electrostatic coating of at least one section of an edge of the component with a thermoplastic powder so as to form a powder coating; and fusing and cross-linking the powder coating in a furnace so as to create a smooth edge seal. | 06-30-2011 |
| 20110157557 | AREA PROJECTION SYSTEM FOR REPRODUCING A VISUAL SIGNAL ON A SURFACE - An area projection system for reproducing a visual signal on a surface, comprising a light source, a fibre element comprising a plurality of light guide elements, a carrier element and imaging optics, wherein the fibre element comprises a first end and a second end, wherein the first end of the fibre element is arranged on the light source and the second end of the fibre element is arranged on the carrier element, wherein the imaging optics are arranged on the second end of the fibre element, wherein the area projection system is adapted to transmit a visual signal from the light source to the fibre element and subsequently to the imaging optics, and wherein the imaging optics are adapted to reproduce the visual signal on a surface. | 06-30-2011 |
| 20110156309 | METHOD AND DEVICE FOR THE MANUFACTURE OF A COMPONENT - A method of manufacturing a component from a composite-fiber-material semifinished product includes providing a forming support having a contour including at least one section corresponding to a surface of the manufactured component. The semifinished product is placed onto the forming support and the semifinished product is formed such that the semifinished product contacts the forming support. Further, a device form manufacturing component includes the forming support having the contour including at least one section corresponding to the surface of the manufacture component. | 06-30-2011 |
| 20110156305 | METHOD AND DEVICE FOR MANUFACTURING A FIBER COMPOSITE COMPONENT WITH AN INTEGRAL STRUCTURAL DESIGN - A method for manufacturing a fiber composite component having an integral structural design includes positioning a sheet-like fibrous semi-finished product in a mold that defines an outer contour of the fiber composite component. Dimensionally stable fibrous semi-finished products, each having dimensions corresponding to a respective portion of the manufactured fiber composite component, are arranged on the sheet-like fibrous semi-finished product. The dimensionally stable fibrous semi-finished products are stabilized and fixed in place using mold cores. The semi-finished products are resin infiltrated using one of a first or a second gating process so as to form a construct. The first gating process includes gating via the mold cores at a head of each dimensionally stable fibrous semi-finished product and performing extraction in an area of the mold. The second gating process including gating in an area of the mold and performing extraction via the mold cores at the head of each dimensionally stable fibrous semi-finished product. The construct is hardened and demolded by removing the mold cores. | 06-30-2011 |
| 20110155854 | METHOD FOR THE MANUFACTURE OF A FIBER-REINFORCED COMPONENT, DEVICE FOR IMPLEMENTING THE METHOD, AND FIBER-REINFORCED COMPONENT - A method for the manufacture of a fiber-reinforced component includes heating a blank of a carbon-fiber-reinforced thermoplastic plastic material to at least a melting temperature of the thermoplastic plastic material; introducing the blank into an at least two-part moulding tool; forming the fiber-reinforced component by applying pressure on the blank using the moulding tool; and injecting a further thermoplastic plastic material into at least one edge region of the moulding tool so as to form an edge seal. | 06-30-2011 |
| 20110155853 | Interface Element, Aircraft Interior Equipment Component And Method For Installing An Aircraft Interior Equipment Component - An interface element ( | 06-30-2011 |
| 20110155852 | STIFFENING ELEMENT FOR AN AIRCRAFT AND A SURFACE STRUCTURE WITH A STIFFENING ELEMENT OF THIS TYPE - A stiffening element for stiffening a surface structure of an aircraft includes a web and a foot configured to connect to the surface structure. The foot includes an inner section near the web and an outer section further from the web than the inner section. The outer section has a greater elasticity than the inner section. | 06-30-2011 |
| 20110155850 | CROSS-BEAM AND AN AIRCRAFT WITH CROSS-BEAMS OF THIS TYPE - A cross-beam for a floor structure of an aircraft includes a web having opposing end sections configured to connect to opposing structural sections of an aircraft fuselage and at least one stepped section. The stepped section is formed by a displacement of the web in a direction corresponding to a normal axis of the web. | 06-30-2011 |
| 20110154567 | RECLINING ARRANGEMENT - According to an exemplary embodiment of the present invention, a rest arrangement is provided, comprising a first support element and a lying-down facility. The lying-down facility comprises a first fastening region which in turn comprises a first fastening element and a second fastening element. The lying-down facility is affixed to the support element with the use of the first and the second fastening elements. The lying-down facility is slidable or pivotable between a first state in which the lying-down facility is arranged so as to be essentially horizontal, and a second state, wherein the transition between the first state and the second state takes place as a combined rotational movement and translational movement. | 06-30-2011 |
| 20110151764 | Air Duct for Supplying Ambient Air in an Aircraft - The invention relates to an air duct ( | 06-23-2011 |
| 20110149517 | Aircraft Electronics Cooling Apparatus For An Aircraft Having A Liquid Cooling System - The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system ( | 06-23-2011 |
| 20110147524 | FIRE DETECTION SYSTEM AND METHOD FOR CONFIGURING A FIRE DETECTION SYSTEM - The invention relates to a fire detection system comprising one or several fire sensors, in which fire detection system a monitoring unit communicates with the fire sensors and by way of a configuration unit may be configured by means of configuration data, wherein the configuration data comprises information relating to the fire sensors within the means of transport, which fire sensors are to be used in the means of transport. The invention further comprises a method for configuring a fire detection system and an aircraft comprising such a fire detection system. | 06-23-2011 |
| 20110147520 | MULTI FUNCTIONAL SUPPLY PROFILE - A supply system is provided that includes, but is not limited to a profile element. The profile element includes, but is not limited to a front wall, a rear wall, and webs between the front wall and the rear wall so that there are ducts within the profile element. The supply system also includes, but is not limited to at least one functional component integrated in at least one of the plurality of ducts. | 06-23-2011 |
| 20110147117 | VACUUM WASTE-WATER SYSTEM SOUND-ABSORBER - A vacuum waste-water system sound-absorber includes a connection stub for a vacuum waste-water system and an aspiration air duct, wherein the aspiration air duct is radially delimited by a pipe, wherein the pipe is delimited at an interior of the aspiration air duct by an internal wall and is delimited at an exterior of the aspiration air duct by an external wall, wherein the internal wall comprises openings in a radial direction, wherein the external wall comprises openings in radial direction, wherein a sound-absorbent material is arranged between the internal wall and the external wall. | 06-23-2011 |
| 20110146957 | System And Method For Cooling A Device Subjected To Heat In A Vehicle, Particularly An Aircraft - A cooling system ( | 06-23-2011 |
| 20110146686 | AUTONOMOUS O2 CHANNEL EXTENDING IN THE LONGITUDINAL DIRECTION - The present invention is concerned with a system for the oxygen supply of persons in an aircraft. In order to provide the simplest possible system, which is suitable in particular for a reconfiguration of the seat devices ( | 06-23-2011 |
| 20110139934 | SYSTEM AND METHOD FOR PREVENTION OF INADVERTENT ESCAPE SLIDE DEPLOYMENT FOR AN AIRCRAFT - The invention relates to a system and a method for preventing inadvertent slide deployment for an aircraft, comprising at least one sensor for sensing the proximity of a person in front of an aircraft door, and at least one optical warning means operable to provide an optical indication in the vicinity of a slide arming lever when the sensor detects the proximity of a person in front of the aircraft door. The system according to the invention provides an effective prevention for inadvertent slide deployment that is capable to guide trained and untrained persons to the information they need in order to disarm the slide in sufficient time before the door handle is gripped and pulled to open the aircraft door in normal operation conditions. | 06-16-2011 |
| 20110139930 | ERGONOMIC AND SPACE-SAVING ARRANGEMENT OF STRUCTURES UNDER A REST AREA IN AN AIRCRAFT - The invention relates to a rest compartment arrangement in an aircraft, comprising a rest compartment and at least one monument, wherein the rest compartment is arranged above a cabin floor and comprises a passage that extends from a rest compartment floor in the direction of the cabin floor. When compared to the state of the art, the invention is characterised in that the at least one monument comprises at least one wall which above a seat region situated therein forms a recess to accommodate the passage. As a result of this, monuments can be positioned in a space-saving manner underneath the passage in the cabin without this resulting in reduced comfort, because the recess above the seat region is not perceived to be distracting by the passenger. | 06-16-2011 |
| 20110138603 | PREASSEMBLY AND INTEGRATION OF AIRCRAFT CABINS - According to an exemplary embodiment of the invention, pre-assembly and integration of part of an aircraft cabin takes place outside the aircraft structure by means of an assembly device. After pre-assembly, the part of the aircraft cabin is slid into the open section of the aircraft structure where it is installed. | 06-16-2011 |
| 20110136425 | FRESH AIR INLET FOR AN AIRCRAFT - The invention relates to a fresh air inlet for an aircraft that features at least one ram air inlet with at least one ram air inlet opening, at least one secondary air inlet opening that is spaced apart from the ram air inlet and at least one movably mounted flap, wherein the flap can be moved into a first position and into a second position, and wherein the flap essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and at least in certain areas extends into the air flow directed toward the ram air inlet opening in order to shield the ram air inlet opening from foreign matter in the second position. The air inlet according to the invention makes it possible to reduce the pressure loss of the air inlet on the ground or during flight phases with relatively slow speed due to the enlarged cross-sectional surface. This results in that the actual ram air inlet can be optimized for cruising phases, and that the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced. | 06-09-2011 |
| 20110135868 | SECTION REINFORCEMENT FOR SANDWICH STRUCTURES - To form a cutout reinforcement according to the invention for a sandwich construction, according to the invention two methods are combined to improve the strength characteristics of a braid core which preferably consists of foamed material. For this purpose, a braiding is combined with fibre bundles which are pulled through holes in the braid core. As a result, the cutout reinforcement according to the invention for a sandwich construction has particularly outstanding strength characteristics, while the component has only a low weight. | 06-09-2011 |
| 20110133028 | MOUNTING DEVICE FOR A RETRACTABLE DISPLAY - A display mount is provided for a vehicle, such an aircraft. The display mount includes, but is not limited to a support frame and a display accommodation device. The support frame is designed for incorporation in a supply channel, and the display accommodation device is designed to receive a display. The display accommodation device is connected to the support frame such that the display accommodation device is movable with a combined rotational movement and translational movement relative to the support frame between a first operating position and a second operating position. | 06-09-2011 |
| 20110133027 | AIRCRAFT HAVING A FORCE TRANSMISSION ELEMENT BETWEEN A CABIN STRUCTURAL ELEMENT AND A PRIMARY STRUCTURE - The invention relates to an aircraft comprising a force transmission element which detachably connects a cabin structural segment to an aircraft primary structure and which comprises a cabin bearing element and a structure bearing element, the cabin bearing element being connected to the cabin structural segment and the structure bearing element being connected to the aircraft primary structure. The force transmission element is designed in such a manner that a force transmission can take place between the cabin structural segment and the aircraft primary structure with at least one degree of freedom of movement. | 06-09-2011 |
| 20110127379 | Modular Device Holder - The invention relates to a device holder for mounting devices in a vehicle. Said device holder comprises at least one external rack and at least one internal rack. The at least one external rack can be mounted on the vehicle structure and has a storage space that is designed to introduce and releasably attach the at least one internal rack. The internal rack has means for forming at least one compartment that has a variable size in order to introduce and mount at least one device. The device holder according to the invention can be particularly well adjusted to the devices that are to be integrated into the vehicle, can optimally utilize the available space, and can be equipped with user-specific devices in standard racks. | 06-02-2011 |
| 20110126562 | INDIVIDUAL TEMPERATURE-CONTROL OF AIRCRAFT CABIN REGIONS BY HEATING AND EVAPORATIVE COOLING - An air conditioning system for an aircraft for the individual air conditioning of regions of a cabin of an aircraft includes a central air conditioning device, which provides a pressurized and temperature-controlled central air flow. A part of the central air flow is supplied to a first cabin region. Another part of the central air flow is heated in a heating device or cooled in a cooling device and supplied to another cabin region. Water evaporates in the cooling device, in order to cool the air flow to be supplied to the cabin region. | 06-02-2011 |
| 20110121479 | Forming Device for Manufacturing Profiled Semifinished Products, System with such a Forming Device and Method for Manufacturing Profiled Semifinished Products - Disclosed is a method for producing a profiled semifinished fiber composite (FC) product from a semifinished product ( | 05-26-2011 |
| 20110121134 | ARRANGEMENT OF A FIRST AND A SECOND FURNISHING - An arrangement, includes a first furnishing and a second furnishing, at least one part of the first furnishing being movable in the direction of the second furnishing, and at least one part of the second furnishing being movable to free a space for receiving the at least one part of the first furnishing. | 05-26-2011 |
| 20110121133 | BURN THROUGH RESISTANT AIRCRAFT FUSELAGE - The invention relates to an aircraft fuselage ( | 05-26-2011 |
| 20110120873 | MULTIFUNCTIONAL COATING OF ALUMINIUM PIECES - The invention relates to a method for application of a multifunctional coating to the surface of a workpiece made from aluminium or an aluminium alloy. The invention further relates to a workpiece, which may be produced by such a method. | 05-26-2011 |
| 20110115124 | Method For Manufacturing A FRC/FRP- Component From Rovings With A Moulding Tool And Moulding Tool For Implementing The Method - The invention pertains to a method for manufacturing a FRC/FRP-component component from rovings by means of a moulding tool with a mould surface, featuring the steps of: applying rovings formed of dry fibers onto the mould surface by depositing the rovings under tension with predetermined orientations between deflection devices by means of an application device, applying binder material onto the tensioned rovings; consolidating the arrangement of fiber strands and binder material by applying heat and pressure in order to produce a preform for the component to be manufactured; separating the preform from the deflection devices and removing the preform from the moulding tool; and carrying out an injection process or infusion process in order to manufacture the component after separating the preform from the deflection devices; as well as to a moulding tool and a device for implementing the method. | 05-19-2011 |
| 20110114895 | Fiber Composite Part for an Aircraft or Spacecraft - In a fibre composite component for an aircraft or spacecraft which has electrically conductive fibres at least in portions, the fibres are coupled with an electrical energy source for charging with current to heat up the fibres and/or for measuring the electrical resistance of the fibres. | 05-19-2011 |
| 20110114795 | Aerodynamic Flap and Wing - An aerodynamic flap with an articulation device to form an axis of rotation for purposes of a rotatable mounting of the aerodynamic flap on a wing section or structural section, with the flap coupled to the wing section in accordance with its intended purpose, with a front flap section situated upstream of the axis of rotation, as viewed in the flow direction, with a front edge line, and a rear flap section situated behind the axis of rotation, wherein a multiplicity of extension pieces are arranged on the front flap section, distributed over the span width of the flap, whose ends project beyond the front edge line of the flap as exposed parts, as viewed from the axis of rotation, wherein the extension pieces are rigid and arranged on the flap, such that one surface of the extension pieces forms an aerodynamically uniform surface with the upper or lower side of the flap, and such that when the flap is deflected the exposed ends of the extension pieces on one surface of the flap are directed at an angle against the flow to generate vortices, and in a neutral position of the flap are situated underneath the boundary layer of the wing, as well as a wing with such an aerodynamic flap. | 05-19-2011 |
| 20110114789 | UNIT FOR ACCOMMODATION OF MEMBERS OF AN AIRCRAFT CREW - The application relates to a unit for accommodating at least one member of an aircraft crew, wherein the unit is designed in such a manner that it can be arranged in a crew rest compartment of an aircraft, wherein the unit comprises first means, second means and third means for changing the volume of the unit, wherein the unit comprises: a lying-down facility for crew members, wherein the lying-down facility comprises first means for displacing the lying-down facility, a front panel, wherein the front panel comprises second means for displacing the front panel, and a sidewall, wherein the sidewall comprises third means for displacing the sidewall. Furthermore, the application comprises a crew rest compartment for accommodating at least one crew member, wherein the crew rest compartment is designed to be arranged in an aircraft, wherein the crew rest compartment comprises a unit according to the invention. | 05-19-2011 |
| 20110114788 | DISPOSITION ZONE IN AN AIRCRAFT PASSENGER CABIN - The invention pertains to an aircraft with at least one passenger cabin that comprises at least one door entry area for the passengers and for the flight attendants that is visually separated from the passenger cabin and referred to as a space unit. Variable or mobile elements assigned to at least one partition wall/one monument of the space element can be arranged in the space unit that can be used as a disposition zone during the flight phase in order to realize working areas or service and/or comfort facilities for passengers or for the flight attendants. | 05-19-2011 |
| 20110111683 | System For Ventilation Of An Aircraft Area | 05-12-2011 |
| 20110108188 | TAPE INSTALLATION DEVICE AND METHOD FOR THE CONSTRUCTION OF A LAMINATE - The present invention creates a tape laying device as well as a method for the construction of a laminate by means of a tape laying device, in particular in the field of aviation and aerospace. The tape laying device comprises a laying arrangement for laying tape for the construction of a laminate and a stimulation arrangement by means of which the tape which has to be laid can be stimulated directly and evenly over the thickness thereof so as to be heated. The idea the present invention is based on consists in that instead of the stimulation at the surface of the tape which has to be laid which is known to the Applicant a direct and evenly stimulation of the tape which has to be laid takes place, that means, a stimulation which acts substantially direct and evenly over the thickness of the tape which has to be laid on the tapes components. The heating achieved by this is much faster than by means of convection according to the known approach. Therefore, the desired tackiness of the tape which has to be laid can be achieved at the desired high laying velocity. | 05-12-2011 |
| 20110101174 | High Lift System For An Aircraft - A high lift system for an aircraft includes: a main wing, a flap disposed on the main wing of the aircraft that can be adjusted between a retracted position and several extended positions relative to the main wing by means of flap actuating means and a drive device, said system further comprising a carrier part disposed on the main wing to which the flap actuating means are coupled and relative to which the flap actuating means for adjusting the flap can be moved, wherein the carrier part is disposed on the main wing by means of a bearing device comprising an adjusting device with which the orientation of the carrier part relative to the orientation of the main wing can be adjusted. | 05-05-2011 |
| 20110101172 | Wing For An Aircraft - The invention pertains to an aerodynamic body that can be adjusted relative to a main wing of an aircraft by means of an adjusting device, wherein a gap between the aerodynamic body and another aerodynamic body or a component of the fuselage or the main wing is formed on one lateral end and the gap is variable due to the adjustability of the aerodynamic body, featuring a gap bridge-over device with a shell part that extends along the gap and overlaps the outer shell of the aerodynamic body in the wingspread direction on the front side thereof in such a way that the shell part can be telescopically moved relative to this aerodynamic body in the wingspread direction; to an airfoil for an aircraft with a main wing and a plurality of aerodynamic bodies that are arranged adjacent to one another transverse to the chord direction; to an airfoil for an aircraft with a main wing and an aerodynamic body that can be adjusted relative to the main wing by means of an adjusting device and is arranged adjacent to a component of the fuselage or the main wing transverse to the chord direction, as well as to an aircraft with such an airfoil. | 05-05-2011 |
| 20110101169 | DEVICE FOR THE GENERATION OF AERODYNAMIC VORTICES AND ALSO A REGULATING FLAP AND WING WITH A DEVICE FOR THE GENERATION OF AERODYNAMIC VORTICES - A device for the generation of aerodynamic vortices to be arranged on the spanwise side edge of a wing, or a regulating flap adjustably arranged on the latter, which in each case have a chordwise direction and a spanwise direction, wherein the device is formed from one aerofoil component or from a plurality of aerofoil components, wherein the at least one aerofoil component is designed as a part that can be moved relative to the wing or regulating flap in its spanwise direction, wherein the device for vortex generation has an actuation device for the retraction and extension of the aerofoil components into a recess, and also a drive device to operate the actuation device. A regulating flap of a wing, and also a wing, with such a device for the generation of aerodynamic vortices, and a wing, which has at least two aerofoil segments at its side edge situated at the spanwise end. | 05-05-2011 |
| 20110101168 | Method of Controlling an Aircraft in Flight, Especially to Reduce Wake Vortices - The flight of an aircraft is controlled by controlling the aircraft propulsion thrust and adjusting aerodynamic control elements so that the aircraft flies along a specified flight path. In order to reduce wake vortices generated by and trailing behind the aircraft, a wake vortex parameter is determined as a function of a spoiler deflection, and a spoiler element is adjusted to a spoiler deflection value in an optimum range in which the spoiler influence on the wake vortex parameter is maximized and the spoiler influence on the aircraft performance is at its lowest level for achieving that maximum spoiler influence on the wake vortex parameter. | 05-05-2011 |
| 20110101166 | CONTROL UNIT AND METHOD FOR CONTROLLING THE SUPPLY OF A VEHICLE WITH MULTIPLE FUELS - A control unit for controlling the supply of a vehicle having at least one internal combustion engine with multiple fuels has at least one input means for supplying optimization parameters, fuel parameters, and operational data, at least one storage unit for storing the optimization parameters, the fuel parameters, and the operational data, and at least one computing unit. The control unit is adapted for being connected to at least one first supply apparatus for supplying a first fuel to the internal combustion engine and to at least one second supply apparatus for supplying a second fuel to the internal combustion engine, and of controlling a first mass flow of supplied first fuel and a second mass flow of supplied second fuel. The computing unit optimizes the ratio of first mass flow and second mass flow for all operational phases of the vehicle to fulfill the specified optimization parameters. | 05-05-2011 |
| 20110100747 | SANDWICH ELEMENT FOR THE SOUND-ABSORBING INNER CLADDING OF MEANS OF TRANSPORT, ESPECIALLY FOR THE SOUND-ABSORBING INNER CLADDING OF AIRCRAFT - A sandwich element for sound-absorbing inner cladding of means of transport, especially aircraft, comprising a three-dimensionally constructed core disposed between two substantially parallel cover layers is provided. | 05-05-2011 |
| 20110099700 | MONITORING DEVICE FOR A VACUUM TOILET - A monitoring device and method are provided for monitoring a vacuum toilet, as well as a personal transport vehicle, in particular an aircraft, which uses a monitoring device for vacuum toilets. The monitoring device has a position detector for detecting the position of a toilet lid, a mechanical latching device and a flushing control unit. The latching device is designed to latch the toilet lid in an open position based on the weight of a person acting on a toilet seat. The flushing control unit is further designed to control the flushing operation based on the toilet lid position, and to block the flushing operation upon detection of the toilet lid in the open position. This makes it possible to improve both the comfort and hygienic conditions for the toilet user while using the vacuum toilet. | 05-05-2011 |
| 20110095136 | AIRCRAFT WITH VERTICAL STABILIZERS ARRANGED ON A CENTRAL FUSELAGE BODY AND METHOD, AS WELL AS CONTROL UNIT, FOR COMPENSATING A NEGATIVE PITCHING MOMENT - An aircraft includes, but is not limited to a central fuselage body without horizontal stabilizer, at least one high-lift control surface, at least one vertical stabilizer that is arranged on the central fuselage body and at least one extendable compensation control surface. The compensation control surface may be moved independently of the high-lift control surface of the aircraft and generates a positive tail-heavy pitching moment when it is moved into the flow against the aircraft. Due to this measure, a negative pitching moment during the actuation of high-lift control surfaces may be at least partially eliminated without influencing the high lift. Rudder segments that may be moved opposite to one another on two vertical stabilizers that are arranged mirror-symmetrical referred to the longitudinal axis of the aircraft preferably are used for this purpose. | 04-28-2011 |
| 20110095128 | AIRCRAFT WITH AT LEAST TWO RUDDER UNITS IN A NON CENTRAL ARRANGEMENT - An aircraft has at least two rudder units in a non-central arrangement. The rudder units have a profile and are rigidly secured to the aircraft. The profile is adjusted in such a way as to yield an inflow at a positive geometric angle of incidence, so that the profile generates a lift force having a component pointing in the flight direction. This makes it possible to offset a portion of the aircraft drag. | 04-28-2011 |
| 20110094205 | SYSTEM FOR INERTING A VOLUME IN A VEHICLE - A system is provided for inerting a volume in a vehicle has at least one exhaust gas extraction point on at least one internal combustion engine of the vehicle, and exhaust gas line for routing exhaust gas from the exhaust gas extraction point to the volume, and at least one exhaust gas inlet on the volume for introducing exhaust gas to generate a low-activity environment in the volume. Precisely in vehicles with internal combustion engines, using exhaust gas for inerting a volume makes it possible to suggest an especially simple, cost-effective and robust solution to guard against the formation of an ignitable mixture in the volume or the like. | 04-28-2011 |
| 20110090064 | System and method for stockkeeping in an aircraft galley | 04-21-2011 |
| 20110089291 | COUPLING DEVICE FOR COUPLING FUSELAGE SECTIONS; COMBINATION OF A COUPLING DEVICE AND AT LEAST ONE FUSELAGE SECTION; AND METHOD FOR PRODUCING THE COUPLING DEVICE - A coupling device for connecting fuselage sections, in each case forming a transverse abutting region for creating an aircraft fuselage comprising fuselage sections with a fuselage skin, a multitude of annular frame elements and stringers, wherein the coupling device has a rib-like design and includes: a strip-shaped transverse splicing plate for coupling the fuselage skins, a rib, which extends in the middle on the transverse splicing plate, for coupling an annular frame element, and a multitude of rib-like stringer coupling parts that extend on both sides of the transverse splicing plate, for coupling the stringers, as well as a method for producing the coupling device from a solid, rectangular, material trip of suitable thickness and length. | 04-21-2011 |
| 20110088538 | METHOD AND DEVICE FOR PRODUCING FIBER-REINFORCED PLASTIC PROFILE PARTS - The present invention provides a method for producing a fiber-reinforced plastic profile part ( | 04-21-2011 |
| 20110088243 | FASTENING SYSTEM AND METHOD FOR FASTENING AN ELEMENT OF AIRPLANE INTERIOR EQUIPMENT - The invention relates to a method for fastening an element of airplane interior equipment to a supporting structure in an airplane, comprising the steps of connecting the element of the airplane interior equipment to a first fixing device by using a first locking device, pivoting the element of the airplane interior equipment relative to the supporting structure, and connecting the element of the airplane interior equipment to a second fixing device by using a second locking device. Thus the element of the airplane interior equipment is fastened relative to the supporting structure. | 04-21-2011 |
| 20110084166 | ARRANGEMENT FOR DIVIDING A SPACE INTO A PLURALITY OF AREAS - The invention relates to an arrangement for dividing a space into a plurality of areas, said arrangement comprising at least one frame with at least one fixing means for holding the frame in corresponding frame receiving elements, and at least one foldable defining means. The frame is formed in such a way that the arrangement essentially fits onto at least one wall of the space when it is fixed, the foldable defining means being able to be held on the frame and preventing an air flow between adjacent areas of the space separated by the arrangement. The arrangement according to the invention enables a thermal separation of two adjacent areas of a space, that can each be air-conditioned differently, without forming an area containing air which is a mixture from two regions at different temperatures. | 04-14-2011 |
| 20110084165 | DECOUPLING TECHNOLOGY OF THE STAIR HOUSE TO THE OVERHEAD COMPARTMENT - Aircraft that are used for intercontinental flights require individual compartments or rest areas (crew rest compartments) for pilots and flight attendants that are also referred to as room elements. It is known to arrange these room elements a certain distance above a seating area for the passengers, wherein these room elements can be reached from a floor structure via a room element in the form of a stair assembly (stairhouse). The room element is connected to the room element by means of locking elements in order to achieve an acoustic decoupling. | 04-14-2011 |
| 20110079683 | SAFETY SYSTEM FOR REDUCING THE EXPLOSION RISK OF A FUEL TANK - A safety system for reducing the explosion risk of a fuel tank comprises at least one fluid source and at least one fluid container with an inlet and an outlet for a fluid, wherein the fluid container has a structure that is flexible at least in some regions and is designed in such a manner that it can be positioned in a hollow space of the fuel tank, which hollow space is situated above the fuel, with said fluid container when fluid flows into the hollow space essentially occupying the space up to the top of the fuel tank. In this way it is possible to avoid the presence of a free air volume in the fuel tank, which counteracts any formation of a potentially explosive mixture and in this way reduces the explosion risk. | 04-07-2011 |
| 20110073716 | Ram Air Duct Flap Arrangement And Ram Air Duct - A ram air duct flap arrangement ( | 03-31-2011 |
