AIRBUS DEUTSCHLAND GMBH Patent applications |
Patent application number | Title | Published |
20140324783 | Process For Electronic Archiving Of Data Objects and Computer Program Product - The application relates to a method for the electronic archiving of data objects by means of a data processing device, wherein the method comprises the following steps: receipt of a hash value tuple comprising one or a plurality of hash values, wherein each hash value is assigned to a data object, receipt of time information on the hash value tuple indicating a time period within which the hash values of the hash value tuple should be electronically archived and comparison of the time information with a predetermined time specification, wherein archiving steps are carried out if the time information specifies a time period for electronic archiving that is shorter than the predetermined time specification. The application furthermore relates to a computer program product. | 10-30-2014 |
20140186180 | Switchable Vortex Generator and Array Formed Therewith, and Uses of the Same - A vortex generator is useable in a model in a fluid-dynamic channel. In order to save time during the development of vehicles, in particular, aircraft, to save wind tunnel time, it is suggested to configure the vortex generator to be switchable. A switchable vortex generator can be used, in particular, on models in fluid-dynamic channels and in fluid-dynamic channel tests. | 07-03-2014 |
20140146469 | MULTISTAGE COOLING OF ELECTRONIC COMPONENTS OF AN AIRCRAFT - The invention discloses the multistage cooling of an aircraft electronic system ( | 05-29-2014 |
20120273051 | OPTIMIZED DEFROSTING REGULATION OF PARALLEL ARRANGED FRESH AIR OUTLETS OF AIR CONDITIONERS - An arrangement is provided for de-icing pipeline connections of an aircraft, which are connected to all fresh air outlets of an air conditioner, whose construction includes, but is not limited to the functions of multiple turbines and heat exchangers, having a first pipeline, which is connected to a first turbine, and a second pipeline, which is connected to a second turbine, the two pipelines, which are each connected downstream from the two turbines and to which process air is fed at the turbine outlets, being connected at the pipe ends and being continued using a third pipeline. The arrangement is characterized in that a first hot air source is fed hot fresh air from a bleed air system of the aircraft and is connected at its outlet to a fourth pipeline, into which temperature-reduced fresh air is fed from the hot air source. The fourth pipeline is connected at its pipe end to two further valve-regulated pipelines, of which a fifth or a sixth pipeline is connected to the first or the second pipeline, and through which temperature-reduced fresh air is transported and fed valve-regulated to the first and/or second pipeline. | 11-01-2012 |
20120119030 | REINFORCEMENT BEAM AS WELL AS METHOD AND FIBER LAMINATE FOR MANUFACTURING THE REINFORCEMENT BEAM - Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight. | 05-17-2012 |
20120018918 | TOOL, ARRANGEMENT, AND METHOD FOR MANUFACTURING A COMPONENT, COMPONENT - This application describes a tool, an arrangement, and a method of manufacturing a component. The manufacturing of the component is achieved by a resin transfer from a storage chamber via a transfer line into a working chamber. Before the resin transfer, taking place, for example by a compressed air charging of the storage chamber, the storage chamber is filled with an amount of resin adjusted to the size of the component. Furthermore, a semi-finished product, consisting of cut-to-size reinforcement fibers, is inserted into the working chamber that is adjusted to the form of the component to be produced. Storage chamber, transfer line, and working chamber are configured in a one-piece mould casing of the tool. The application further describes a component manufactured by the above-mentioned tool or by the above-mentioned method respectively. | 01-26-2012 |
20120014757 | Arrangement For Noise Reduction In Vacuum Systems - The present invention relates to an arrangement for adapting the transportation behaviour of material to be conveyed, which arrangement comprises a first container, which is coupleable to a first pressure level; a second container, which is coupleable to a second pressure level; a connecting line for transporting material to be conveyed from the first container to the second container; and a pressure reduction device by means of which a pressure difference between the first container and the second container is controllably variable. | 01-19-2012 |
20110318445 | METHOD AND DEVICE FOR PLACING THIN MATERIAL LAYERS ONTO A RELIEF MOULD - The present invention relates to a method and a device for placing at least one material layer onto a relief mould for producing a composite material. Thereby, an elastically-reversibly deformable body with a surface relief that is designed to correspond to the relief mould is pressed against the material layer, as a result of which the surface of said body is deformed, and the material layer can be picked up. As a result of its elastically-reversible characteristics the body subsequently deforms back to its initial state so that the material layer can easily be placed onto the relief mould. | 12-29-2011 |
20110192523 | METHOD FOR JOINING A FIRST COMPONENT FORMED OF A PLASTIC MATERIAL TO A SECOND COMPONENT, AND JOINING ELEMENT AND DEVICE - A method for joining a first component made of a plastic material, in particular a thermoplastic and/or thermosetting plastic material, to a second component by applying a joining element on the first component, wherein the joining element has a supporting plate formed of a thermoplastic and/or thermosetting plastic material and comprising a connecting means and a supporting plate bore. A joining element for creating a junction in accordance with the method, is also disclosed. Furthermore, a device, in particular for performing the method, is disclosed. | 08-11-2011 |
20110163203 | FLEXIBLE POWER RACEWAY - A connection system for cables comprises a raceway adapted to cover the cable and a raceway outlet element connectable to the raceway. The raceway outlet element includes a first connection element for connecting the cable to second connection element. | 07-07-2011 |
20110108663 | PROPULSION DEVICE WITH A PLURALITY OF ENERGY CONVERTERS FOR AN AIRCRAFT - The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a first energy converter ( | 05-12-2011 |
20110101163 | TAIL STRUCTURE FOR AN AIRCRAFT OR SPACECRAFT - A tail structure for an aircraft or spacecraft, which adjoins a fuselage section of the aircraft or spacecraft, includes a support construction for supporting at least one craft component, and a bulkhead unit intended for the pressure-tight sealing of the fuselage section and able to be coupled both to the support construction and to the fuselage section so as to form a force flow path between the at least one craft component and the fuselage section. | 05-05-2011 |
20110084173 | METHOD AND DEVICE FOR PROVIDING AUTOMATIC LOAD ALLEVIATION TO A HIGH LIFT SURFACE SYSTEM, IN PARTICULAR TO A LANDING FLAP SYSTEM, OF AN AIRCRAFT - A method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device at least one high lift surface, which is actuated by means of a local mechanical final control element, is brought to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement. If a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit to the rotary shaft arrangement is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed. | 04-14-2011 |
20110071778 | Apparatus For Performing Ground Vibration Tests On Airplanes - The invention relates to improved methods and apparatus for performing ground vibration tests (so-called “ground vibration tests”) on an airplane. In the method according to the invention, the airplane is jacked up essentially undamped (“rigidly”) in conventional holding points with lifting devices. For purposes of the ground vibration test, the airplane is then excited to vibrate in a known manner using a plurality of vibration exciters, and the vibrations are acquired with a plurality of measuring transducers, in particular accelerometers. A dynamic vibration model of the airplane theoretically calculated beforehand can here be adjusted. The boundary conditions are removed during or after the ground vibration test, meaning the influence of the lifting device is “mathematically canceled out”, so that the determined measured values reflect the so-called “free-free” state of the airplane, as if the airplane had actually been in free flight during the ground vibration tests. | 03-24-2011 |
20110068226 | MODULAR SEAT SYSTEM FOR A VEHICLE - A modular seat system for a passenger compartment of a vehicle includes at least one seat, which has a seat unit with a seating element and a seat back and a seat frame with at least one pair of essentially vertical support elements, at whose upper end a bearing structure is arranged on which the seat unit rests, a fixing structure in the floor of the passenger compartment with at least two longitudinal rails, which have a predetermined spacing from one another, for accommodating the lower ends of the support elements, and an adapter plate for the fixing of the support elements, which adapter plate is fitted to the lower end of the support elements, and is fitted in a mobile fashion to at least one support element, so that the spacing of the support elements from one another is variable independently of the width of the seat unit. | 03-24-2011 |
20110041307 | REPLACEABLE CARTRIDGE FOR LIQUID HYDROGEN - A replaceable cartridge for coupling to a consumer or to a filling station, wherein the replaceable cartridge comprises at least one disconnectable connection coupling for connection to the consumer or the filling station. Furthermore, the replaceable cartridge comprises a tank for holding liquid hydrogen. | 02-24-2011 |
20110024561 | FRAME ELEMENT, AIRCRAFT AIR-CONDITIONING SYSTEM AND METHOD FOR THE INSTALLATION OF A FRAME ELEMENT IN AN AIRCRAFT - A frame element ( | 02-03-2011 |
20110009042 | FUSELAGE OF AN AIRCRAFT OR SPACECRAFT AND METHOD OF ACTIVELY INSULATING SUCH A FUSELAGE - The present invention relates to a fuselage of an aircraft or spacecraft, with at least one shell element and a structural element. An interspace to which air can be admitted by an air stream is provided between the at least one shell element and the structural element. The fuselage is distinguished by the fact that, to form the air-admitting air stream as an outgoing/incoming air stream of a pressurized interior space of the fuselage, the interspace is connected to a corresponding outgoing/incoming air connection of the interior space. The invention also relates to a corresponding aircraft or spacecraft and to a method of actively insulating such a fuselage. | 01-13-2011 |
20110006778 | TESTER FOR TESTING OPERATIONAL RELIABILITY OF A COCKPIT OXYGEN DISTRIBUTION CIRCUIT - The present invention relates to a tester ( | 01-13-2011 |
20110006159 | FUSELAGE OF AN AIRCRAFT OR SPACECRAFT AND CORRESPONDING AIRCRAFT OR SPACECRAFT - The invention relates to a fuselage of an air- or spacecraft. The fuselage comprises at least one shell element and one insulation element. The insulation element is configured as a passive, watertight insulation element and can be mounted on an inner side of the at least one shell element in a completely air- and watertight manner. The invention furthermore relates to a respective aircraft or spacecraft. | 01-13-2011 |
20110003218 | Device, Method and System for Producing Thermal and/or Kinetic and Electrical Energy - The present concerns an apparatus ( | 01-06-2011 |
20100316853 | AIRCRAFT WITH PAINTED EXTERIOR SURFACE AND DECORATIVE FILM - An aircraft includes a fuselage having a painted exterior surface having a first color; a decorative film including plastic and having a second color different from the first color and adhesively bonded to the fuselage, wherein the decorative film includes at least one of a polyvinyl fluoride film, a polyester film, a polyvinyl chloride film, a polyethylene film, and a polypropylene film, wherein the decorative film is formable via one of polymerization, polyaddition and polycondensation; and a layer of clear paint containing a UV filter for erosion protection and covering the decorative film. | 12-16-2010 |
20100304039 | PROCESSING DEVICE AND METHOD FOR COATING A RUDDER UNIT OF AN AIRCRAFT - A processing device for coating a surface of a rudder unit of an aircraft includes a plurality of spatially delimited work stations, wherein each of the plurality of work stations are disposed in succession and are configured to produce an assembly line-like coating process, wherein the plurality of work stations. The work stations include a pretreating station configured to activate the surface so as to form an activated surface; a painting station disposed downstream of the pretreating station and configured to paint the activated surface with at least one layer of paint having a first color so as to form a painted surface and configured to dry the painted surface immediately after the painting; and a decorating station. | 12-02-2010 |
20100304009 | DEVICE AND METHOD FOR PAINTING CURVED OUTER SURFACES OF AN AIRCRAFT - A device for painting a curved outer surface of an aircraft includes a paint applicator having a plurality of spray painting heads each assigned to one of a plurality of different base color supply units containing one of polyurethane aircraft paint and ink. The device further includes a spatially adjustable positioning device configured to move the paint applicator relative to the curved outer surface and at least one sensor device configured to determine a three-dimensional geometry of the curved outer surface. The device also includes a control unit configured to coordinate a movement of the positioning device with a paint output of the paint applicator, wherein the control unit is configured to alternately activate each of the plurality of spray painting heads so as to produce a picture motif so as to derive a two-dimensional driving geometry based on the three-dimensional geometry. | 12-02-2010 |
20100301177 | DEVICE FOR LAYING A CABLE HARNESS IN AN AIRCRAFT - A device for bridging a cable harness between two aircraft structure elements of an aircraft includes an elongated connecting rod having a plurality of radial snap-in holes and configured to bridge a space between the two aircraft structure elements and affix to at least one of the two aircraft structure elements. The device also includes a cable guiding element having at least one receiving section for receiving the cable harness and at least one attachment section circumferentially surrounding the connecting rod, the attachment section having a resiliently held radially directed locking pin, wherein the locking pin corresponds to one of the plurality of the radial snap-in holes so as to form a clip connection and a positive locking engagement between the at least one attachment section and the connecting rod. | 12-02-2010 |
20100294896 | HOLDING DEVICE FOR MOUNTING PARTS INSTALLED INSIDE AN AIRCRAFT FUSELAGE - A holding device for a mounting part installed inside an aircraft fuselage having a lining including an insulating mat, the holding device includes a fastening part attached to the aircraft fuselage and protruding through an opening in the insulating mat; a sealing disk; and a holding part configured to attach the mounting part and being disposed on an inner side of the aircraft fuselage and cooperating with the fastening part configured to attach the mounting part so as to simultaneously fix the insulating mat between the fastening part and the holding part, wherein the holding part extends through the opening in a sealed manner, and wherein a lower surface of the sealing disk contacts and seals an edge region of the opening when the holding part is installed on the fastening part. | 11-25-2010 |
20100294564 | CABLE GUIDING ARRANGEMENT FOR A CABLEFORM INSIDE AN AIRCRAFT CABIN - A cable guiding arrangement for at least one electrical cable harness installed in an aircraft cabin includes a guide rail having at least one receiving pocket and an attachment surface configured to receive the at least one cable harness; a plurality of retaining heads spaced apart from each other in a longitudinal direction along the guide rail and configured to affix the at least one electrical cable harness; and at least one insertion element disposed on an edge of the guide rail configured to attach at least one laterally branching-off cable of the at least one cable harness, the at least one insertion element including at least one retaining head section and an insertion section, wherein the insertion section is disposed in the at least one receiving pocket. | 11-25-2010 |
20100288244 | METHOD FOR CONTROLLING THERMAL EFFLUENTS GENERATED BY AN AIRCRAFT AND COOLING DEVICE FOR AN AIRCRAFT IMPLEMENTING SAID METHOD - A process for management of thermal effluents of an aircraft that includes an airframe ( | 11-18-2010 |
20100282937 | MODULAR HOLDING DEVICE FOR MOUNTING PARTS LOCATED INSIDE AN AIRCAFT FUSELAGE - A holding device for a mounting part installed inside an aircraft fuselage includes an anchor plate configured to attach the holding device to a support rail of the aircraft fuselage and including at least one engagement section. The holding device further includes a holder module separably connected to the anchor plate and configured to fix the mounting part to the aircraft fuselage and having a hook section configured to postively engage the at least one engagement section so as to fasten the holder module to the anchor plate, and at least two clamping blocks disposed on the holder module. | 11-11-2010 |
20100282900 | System for Reducing Aerodynamic Noise at a Supplementary Wing of an Aircraft - A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which through an actuator device can be moved between at least one of the stable states and at least one additional state. | 11-11-2010 |
20100279013 | Painting device, painting arrangement, method for painting a curved surface of an object, and use of an inkjet device for painting an aircraft - A painting device for painting a curved surface ( | 11-04-2010 |
20100273410 | Device And Method For Distributing Air In A Cargo Aircraft - The invention relates to a device and a method for distributing air in a cargo aircraft. The cargo aircraft has an air distribution system ( | 10-28-2010 |
20100267323 | Method For Controlling The Temperature Of Feed Air Injected Into The Cabin Zone Of A Passenger Aircraft - With a method for controlling the temperature of feed air which is injected into the cabin zone of a passenger aircraft, the cabin of which is sub-divided into several cabin zones supplied respectively with specially temperature-controlled feed air, the temperature of the injected feed air is controlled for each cabin zone, dependent upon the deviation of an injection temperature actual value for the feed air injected into the cabin zone in question, measured by sensors, in relation to an injection temperature optimum value. If there is no, or at least no usable reading of the ambient temperature of this cabin zone for a cabin zone, an optimum value for the injection temperature of this cabin zone can be established in accordance with a variation, whereby it is determined upon the basis of the injection temperature optimum values and/or the injection temperature actual values of other cabin zones, whereby the measurement by sensors of the cabin temperature works reliably. In accordance with another variation, the injection temperature optimum value of a cabin zone can be established without measuring ambient temperature by sensors or without reliably measuring ambient temperature from the temperature measured for the external surrounds of the aircraft. | 10-21-2010 |
20100266138 | Device and method for active sound damping in a closed interior space - The invention relates to a method and device for active sound damping in a closed interior space ( | 10-21-2010 |
20100247848 | Sandwich element for sound-absorbing inner cladding of transport means, especially for sound-absorbing inner cladding of aircraft fuselage cells - A sandwich element for a sound-absorbing inner cladding of transport means, such as aircraft fuselage cells, comprising a honeycomb-shaped core structure and cover layers applied to both sides of the core structure. At least one cover layer is constructed as permeable to air at least in sections and a covering is disposed at least in sections on at least one cover layer, wherein a sound absorption layer is disposed at least in sections in the area of at least one cover layer. | 09-30-2010 |
20100244313 | Method for Handling a Liquid - A method for handling a liquid, in particular for the metered transfer of a liquid that is viscous at room temperature from a reservoir to a receiving container for the purpose of further processing the viscous liquid. In the method the receiving container is filled with the liquid. In this arrangement the liquid is present in a plurality of individual portions. Furthermore, the liquid is cooled such that the individual portions are present in a predominantly solid state of aggregation. Preferably, the individual portions are sufficiently small so that the transferred liquid is a frozen granulate. | 09-30-2010 |
20100243814 | Emergency Evacuation System, in Particular for a Tailless Aeroplane - A device for selective emergency evacuation of persons from a first level to a second level situated above the first level, or to a third level situated below the first level. For evacuation to the second level a stair arrangement is provided. One end of the device is connected to the first level while the other end is displaceable between the second level and the third level or vice versa. For evacuation to the third level, the device is changeable to a slide. The device may provide for emergency evacuation of persons from a first level deck, or passenger deck of a blended wing-body aircraft, selectively to the top, second level of the aircraft, or to the bottom third level of the aircraft. | 09-30-2010 |
20100236704 | APPARATUS AND METHOD FOR AUTOMATICALLY FABRICATING TAPE WITH THREADS FOR VISUALIZATION OF AIR STREAMS ON AERODYNAMIC SURFACES - Apparatus and method for visualizing air stream by little threads on aerodynamic surfaces such that strips of adhesive tape populated with threads are automatically fabricated. | 09-23-2010 |
20100200696 | QUICK-CHANGE FASTENING SYSTEM FOR MOUNTING AN ELEMENT TO A FASTENING STRUCTURE - The present application describes a quick-change fastening system for demountably mounting an element to a fastening structure. The element comprises an engagement element that is designed to engage a bearing element of the fastening structure, wherein the element is hingeably held around the bearing element between a hooked-in position and a fastened position. The element further comprises a fastening element that can be affixed to a locking element of the fastening structure when the element is in its fastened position. The engagement element and the bearing element are designed such that along a hingeing movement of the element a form-fit connection is established when the element is in its hooked-in position, and that a force-fit connection is established when the element is in its fastened position. | 08-12-2010 |
20100170995 | SUPPORT STRUCTURE FOR A WING - A support structure for an aircraft, includes one or several bar elements and one or several junction elements. At least one bar element includes a transition region which can be made to engage at least one junction element. When the transition region of the bar element engages at least one junction element, centric force transmission takes place between the bar element and the junction element. | 07-08-2010 |
20100170238 | SYSTEM AND METHOD FOR THE TEMPERATURE REGULATION OF A HYDRAULIC FLUID - The present invention provides a device and a method for regulating a temperature (T) of hydraulic fluid in at least one hydraulic circuit ( | 07-08-2010 |
20100158037 | DETERMINISTIC COMMUNICATION SYSTEM - The invention relates to a communication system and a method for controlling a communication system for communicating audio data between each of a plurality of terminal units (T | 06-24-2010 |
20100155530 | FLEXIBLE POWER RACEWAY - A connection system for cables comprises a raceway adapted to cover the cable and a raceway outlet element connectable to the raceway. The raceway outlet element includes a first connection element for connecting the cable to second connection element. | 06-24-2010 |
20100153684 | Modular Avionics System of an Aircraft - A modular avionics system includes several cabinets arranged at various locations in an aircraft and interconnected in a network. The cabinets are used for controlling or processing signals from and to sensors, actuators and other systems of the aircraft. The system includes parallel processors, for example transputers. The cabinets comprise at least two core processor modules (CPM | 06-17-2010 |
20100148003 | STRUCTURING CONSTRUCTION FOR AN AIRCRAFT FUSELAGE - A structuring construction ( | 06-17-2010 |
20100147399 | Wiring Arrangement For Protecting A Bleed Air Supply System Of An Aircraft Against Overheating And Bleed Air Supply System Incorporating Such A Wiring Arrangement - The present invention relates to a wiring arrangement ( | 06-17-2010 |
20100143617 | CORE STRUCTURE AND METHOD FOR PRODUCING A CORE STRUCTURE - The present invention relates to a method for producing a core structure. Firstly, a first core structure and a second core structure are fastened. The first core structure and the second core structure are positioned at a defined distance. A reinforcement element is introduced into a cavity between the first core structure layer and the second core structure layer. The reinforcement element, the first core structure layer, and the second core structure layer form a self-supporting core structure. | 06-10-2010 |
20100140393 | RUDDER OF A COMMERICAL AIRCRAFT - A rudder of a commercial aircraft is provided that is divided along its longitudinal direction in at least one region and the parts of the rudder can be spread against the air flow surrounding the aircraft by means of an actuator in order to decelerate the aircraft. | 06-10-2010 |
20100132920 | Redundant Aircraft Cooling System For Redundant Aircraft Components - An aircraft cooling system ( | 06-03-2010 |
20100127123 | Double-Walled Floor Segment for a Means of Locomotion for Accommodating System Components - This application describes a floor segment ( | 05-27-2010 |
20100126189 | Service Method And Service Device For A Liquid Cooling System Of An Aircraft - The present invention discloses a service method and a service device ( | 05-27-2010 |
20100116943 | AIRCRAFT COMPONENT EXPOSED TO STREAMING SURROUNDING AIR - An aircraft component, such as a wing, has perforations through an outer wall for boundary layer suction. In the space between the outer wall and inner wall partition walls form pressure channels and suction channels that are adjacent to each other and alternate, which channels communicate with the perforations. For example, alternating channels may be formed by a corrugated structure having trapezoidal corrugations providing a larger area for the suction channels than for the pressure channels. The pressure channels may be coupled to a hot-air reservoir by a control device, lines and valves, and the suction channels may be coupled to a vacuum reservoir, unless a short-circuit valve is used to cross connect the lines. | 05-13-2010 |
20100112933 | CONTROL DEVICE FOR SHIELDING A ROOM - A control device that shields a room from incoming signals includes a receiving device, an interference device and a transmitting device. By the receiving device transmission signals are received, from which an interference signal is determined in order to interfere with the transmission signal. This interference signal is emitted by way of the transmitting device. | 05-06-2010 |
20100096230 | Energy Absorber for Aircraft - An energy absorber for aircraft includes one or more energy absorber elements and a housing, whereby the energy absorber elements can absorb crash impulses by plastic deformation within the housing. | 04-22-2010 |
20100090429 | FASTENING DEVICE FOR FASTENING A MOVABLE ELEMENT - A fastening device for fastening a movable element to a structure includes a support member and at least one belt retractor having a retractable belt and a fitting. The belt retractor may be fastened to a support member. The belt retractor is arranged in such a way that, if the fitting couples the structure and the movable element, the retractor prevents unrolling of the belt by more than a predefinable range if an external force, such as sudden mid-air turbulence acts on the movable element. Thus, the movable element is secured. | 04-15-2010 |
20100090061 | FUSELAGE OF AN AIRCRAFT OR SPACECRAFT OF CRP/METAL HYBRID CONSTRUCTION WITH A METAL FRAMEWORK - The present invention provides an inherently rigid fuselage of an aircraft or spacecraft comprising shell elements or fuselage barrels of CRP construction, wherein the shell elements or fuselage barrels each have an outer skin and an inner skin, which each at least partially or completely consist of a CRP material, wherein a composite core element is provided between the outer skin and the inner skin, and wherein the fuselage in the interior has a metal framework which is connected to the shell elements or fuselage barrels. | 04-15-2010 |
20100084819 | SURFACE SEAL AS WELL AS METHOD FOR PRODUCING SEALED JOINTS WITH THIS SURFACE SEAL - A surface seal for sealing a riveted and/or screwed joint between a first and a second component of an aircraft. The surface seal is arranged in the region of joining surfaces of the first and the second component. The surface seal is formed with a pressure-resistant plastic film that is provided with a pressure-sensitive adhesive layer on both sides. The surface seal | 04-08-2010 |
20100072318 | PROPULSION DEVICE FOR OPERATION WITH A PLURALITY OF FUELS FOR AN AIRCRAFT - The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a propulsion unit and an energy converter. The energy converter is adapted for providing propulsion energy to the propulsion unit by a first fuel. Furthermore, the energy converter is adapted for providing propulsion energy to the propulsion unit by a second fuel. The propulsion unit adapted for generating forward thrust by the propulsion energy. | 03-25-2010 |
20100071447 | Production Method Of A Sensor Film - The present invention relates to a production method for producing a sensor film for measuring cracks of a material surface using the comparative vacuum measurement method. A gallery having a predetermined gallery course is milled along a surface of the sensor film using a milling apparatus. The sensor film comprises a plastic material. | 03-25-2010 |
20100071386 | Cooling Device for Installation in an Aircraft - The present invention relates to a cooling device ( | 03-25-2010 |
20100065760 | METHOD FOR DETERMINING A CHARACTERISTIC PARAMETER OF A CRP SPECIMEN - The invention relates to a method for determining at least one characteristic parameter of a CRP specimen ( | 03-18-2010 |
20100065685 | PRESSURE BULKHEAD FOR AN AEROSPACE FUSELAGE - A pressure bulkhead for an aerospace fuselage includes a bulkhead main portion having an approximately flat shape in unloaded state; and a frame supporting and connecting said bulkhead main portion to the fuselage; wherein said bulkhead main portion includes an airtight structure having a reticular component. | 03-18-2010 |
20100065681 | Floor Structure in an Aircraft With Continuous Panels - A floor structure in an aircraft includes a plurality of seat rails that extend parallel in relation to each other, and at least one floor panel. The floor panel extends over the seat rails and rests on the individual seat rails. In order to be able to fasten interior equipment components to the seat rails situated underneath the floor panels, the at least one floor panel includes a plurality of through-holes through which the interior equipment components of the aircraft can be locked into place on the seat rails. | 03-18-2010 |
20100065612 | Filler Material, In Particular For Improving The Quality Of A Joint Seam Formed During Thermal Joining Of Two Metallic Structural Components - A filler material improves the quality of a joint seam formed during thermal joining of two metallic structural components and includes a core and a coating that surrounds the core at least in sections Because the filler material comprises a coating on the core, the alloying material for the coating may be selected largely independently of any possibly limiting metallurgical requirements in relation to the base material for the core so that with the use of the heterogeneous filler material optimal joint seam characteristics of the joined structural components always result, largely irrespective of the materials composition of the core If an essentially H-shaped cross-sectional geometry of the filler material used, moreover, preliminary fixing or alignment of the structural components that are to be joined in a thermal joining process becomes possible. | 03-18-2010 |
20100059625 | FRONT PORTION FOR AN AIRCRAFT INCLUDING A REST COMPARTMENT FOR AT LEAST ONE PILOT - A front portion of a fuselage of an aircraft including a cockpit, a washroom, an access corridor to the cockpit alongside the washroom, and a rest compartment with at least one berth for at least one pilot. The corridor alongside the washroom includes a mechanism separating the corridor from the cockpit and a door for blocking access to the passenger cabin. The rest compartment can be accessed from the access corridor to the cockpit, between the separation mechanism between the corridor and the cockpit and the corridor door. The washroom includes two access doors, a first access door for accessing the washroom from the access corridor to the cockpit in the area located between the separation mechanism between the corridor and the cockpit and the corridor door, and a second access door for accessing the washroom from the passenger cabin. | 03-11-2010 |
20100051401 | FORCE LEVEL CONTROL FOR AN ENERGY ABSORBER FOR AIRCRAFT - A force level control for an energy absorber is provided for aircraft, and includes an adjustment element and a housing, whereby via the adjustment element, a bending radius of the energy absorber element is continuously adjustable in the housing. | 03-04-2010 |
20100047013 | Device for Connecting Two Duct Elements and a Baffle in an Aircraft Air Conditioning System - The invention relates to a device ( | 02-25-2010 |
20100044522 | AIR INLET FOR A VEHICLE - The invention relates to an air inlet for a vehicle comprising an opening with an opening contour in an outer skin of the vehicle; at least one bottom element; one or several walls between the opening contour and the bottom element; and an air guide channel with a longitudinal axis, wherein the bottom element extends from the outer skin of the vehicle to an interior region of the vehicle underneath a border edge of the opening, and the air guide channel adjoins from between the bottom element and the border edge, wherein at least one transition region between the opening contour and the walls at least in some regions comprises an essentially convex-shaped profile that essentially extends parallel to the air guide channel. The air inlet according to the invention is in a position to remove air from a flow boundary layer and to provide said air to air-consuming systems. | 02-25-2010 |
20100044518 | METHOD AND DEVICE FOR PROVIDING AUTOMATIC LOAD ALLEVIATION TO A HIGH LIFT SURFACE SYSTEM, IN PARTICULAR TO A LANDING FLAP SYSTEM, OF AN AIRCRAFT - A method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device at least one high lift surface, which is actuated by means of a local mechanical final control element, is brought to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement. If a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit to the rotary shaft arrangement is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed. | 02-25-2010 |
20100044512 | Drainage Device, Aircraft, and Method for Letting Out a Fluid that is Present Between the Exterior Skin and the Interior Lining of an Aircraft - A drainage device for letting out a fluid that is present between the exterior skin and the interior lining of an aircraft, wherein the drainage device comprises a collecting vessel and an outlet line. The collecting vessel is designed to collect the fluid that is present between the exterior skin and the interior lining and the outlet line is connected to the collecting vessel and is designed to let out the collected fluid. | 02-25-2010 |
20100044510 | Floor Structure for a Fuselage - The present invention provides a floor structure for a fuselage comprising a plurality of cross beams to which respectively at least one first strut and at least one second strut are associated for connecting the respective cross beam to the fuselage. The at least one first strut is aligned in a corresponding first direction vector and the at least second strut is aligned corresponding to a second direction vector. The projections of the first direction vector and of the second direction vector onto the longitudinal direction of the fuselage are different for absorbing a force acting in the longitudinal direction of the fuselage on the floor structure, through the first and second struts. | 02-25-2010 |
20100043300 | WINDOW ELEMENT FOR INSERTING IN A STRUCTURAL PART AND METHOD OF INTEGRATION OF A WINDOW ELEMENT IN A STRUCTURAL PART - Window element ( | 02-25-2010 |
20100040427 | Locking Device for Fastening a Container - A locking device for fastening containers for an aircraft. The locking device comprises at least one locking arrangement that can be affixed to an aircraft floor and that comprises a retaining element. The locking arrangement can be fastened to the aircraft floor such that a gap for adjusting the container is provided between the container and the locking arrangement. The retaining element of the locking arrangement can subsequently be moved in the direction of the payload such that a gap between the locking arrangement and the payload can be adjusted. | 02-18-2010 |
20100038487 | FUSELAGE STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT, WITH A FOAM LAYER AS THERMAL INSULATION - The present invention creates a fuselage structural component of an aircraft or spacecraft, with a non-load-bearing outer skin and a load-bearing inner framework structure, wherein a foam layer which effects heat insulation and/or impact protection is arranged between the outer skin and the inner framework structure. | 02-18-2010 |
20100038409 | Joining Method For Joining Components - A method is provided for connecting components particularly in the field of aerospace wherein a first component is connected to a second component, comprising the following steps: arranging at least one nano- or microstructured material between the first and the second component, initiating an exothermic reaction of the nano- or microstructured material for connecting both components with each other. | 02-18-2010 |
20100037107 | Method for testing a communication connection - The invention relates to a method for testing a communication connection ( | 02-11-2010 |
20100028741 | HYDRIDE FUEL-CELL COOLER AND CONDENSATE COOLER FOR AIRCRAFT - A cooling system for cooling a fuel-cell system on board an aircraft, in one example, includes a hydrogen accumulator, a connecting device coupling the hydrogen accumulator, with an external cooling system for dissipating heat arising upon charging of the hydrogen accumulator. The hydrogen accumulator cools down upon removal of hydrogen, because of which cooling of a condenser occurs. The cooling system need not utilize a secondary cooling loop for condenser cooling. | 02-04-2010 |
20100025532 | SHELL ELEMENT AS PART OF AN AIRCRFAFT FUSELAGE - The present invention provides a shell element as part of an aircraft fuselage, wherein the shell element is formed as a curved sheet-like element and is at least partially or completely of CRP construction. | 02-04-2010 |
20100025531 | Aircraft-fuselage assembly concept - An aircraft fuselage section includes a first interior tube as well as a second interior tube that are produced in an upstream production step, which interior tubes are subsequently enclosed by an exterior tube. For spacing and in order to provide more stability to the tubes the interior tubes are enclosed by straps that are arranged between the interior tubes and the exterior tube. | 02-04-2010 |
20100024438 | Cooling assembly for cooling a thermal body for an aircraft - A cooling assembly for cooling a thermal body for an aircraft. The cooling assembly has a Peltier element with a hot side and a cold side. Furthermore, the cooling assembly has a thermal body. The thermal body is arranged in heat-conductive contact with the cold side of the Peltier element. The hot side of the Peltier element is adapted to dissipate thermal energy to an aircraft structure, such that the thermal body may be cooled. | 02-04-2010 |
20100019568 | ENERGY SUPPLY SYSTEM FOR SUPPLYING ENERGY TO AIRCRAFT SYSTEMS - An energy supply system for an aircraft comprises at least one fuel cell and at least one energy storage device, wherein the fuel cell, of which there is at least one, is coupled to the energy storage device, of which there is at least one, such that the energy storage device can be charged by means of the fuel cell. | 01-28-2010 |
20100019405 | Tool for a Resin Transfer Moulding Method - A tool for a resin transfer moulding method comprises a cavity, a resin trap and a transition region, wherein the cavity is designed such that a component can be accommodated in it. Furthermore, the resin trap is integrated in the tool, and the transition region is designed such that with it a connection between the cavity and the resin trap can be established. | 01-28-2010 |
20100019095 | WING OF AN AIRCRAFT - Wing of an aircraft having a mainplane ( | 01-28-2010 |
20100019094 | WING TIP SHAPE FOR A WING, IN PARTICULAR OF AIRCRAFT - A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction. | 01-28-2010 |
20100018723 | Fire Protection With Fuel Cell Exhaust Air - A fire protection system for reducing the danger of fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the room to be protected. | 01-28-2010 |
20100018322 | Switchable Vortex Generator and Array Formed Therewith, and Uses of the Same - The invention relates to a vortex generator ( | 01-28-2010 |
20100018199 | Device for Reducing Hydraulic-Fluid Oscillation in a Hydraulic System - A device for reducing hydraulic-fluid oscillation in a hydraulic system, in particular in a hydraulic system of an aircraft, wherein the hydraulic system comprises a pump that is driven by a drive, which pump conveys a fluid to a hydraulic line by pressure pulsation. The device comprises an actuator, arranged in the hydraulic line for generating pressure pulsation that compensates for the pressure pulsation of the pump. | 01-28-2010 |
20100014009 | Visualisation System in an Aircraft - A visualization system in the passenger cabin of an aircraft, by which visualization system data relating to informing, instructing and entertaining passengers can be visually presented, along with graphic effects. The visualization system includes a lining panel to line the passenger cabin, and a control unit. The lining panel is coated with a flexible display that is coupled to the control unit, which, for the purpose of presenting information, is equipped to supply electricity in a targeted manner to the display. | 01-21-2010 |
20100012782 | Aircraft With Modular Structure - An aircraft includes a module carrier for accommodating a plurality of module elements in which in each case at least one system element is integrated. The module elements and system elements are networked among each other such that a desired aircraft model is implemented. | 01-21-2010 |
20100009617 | Aircraft Air Conditioning System With Cyclone Dischargers - The invention relates to an aircraft air conditioning system with at least one fresh air supply line ( | 01-14-2010 |
20100008053 | AVIONICS EQUIPMENT CARRIER SYSTEM WITH QUICK-MOUNT HOUSING AND QUICK-MOUNT MODULES - An avionics equipment carrier system for slide-in modules with data processing, data transmitting, data storage or data displaying devices, such as for example electronics printed circuit boards, network components, storage devices, display devices and the like, or power supply devices, includes a housing, at least one module rack for accommodating the slide-in modules and at least one backplane board with Ethernet connection architecture. When the dimensions of the housing comply with ARINC standards, and the housing is arranged for installation in an avionics module rack as a quick-mount housing, and any desired circuit boards of a specific standard format can be used in the slide-in modules which are designed as quick-mount modules. | 01-14-2010 |
20100006707 | Advanced Trailing Edge Control Surface on the Wing of an Aircraft - An aircraft wing trailing edge control surface including a trailing edge flap adjustable to different positions, a sealing flap on the upper side between the wing and the flap, and a ventilation flap on the underside between the wing and the flap. The flap is adjustable downward through positive positions and upward through negative positions. The wing profile is closed on the upper side by the sealing flap and the underside by the ventilation flap when the flap is used as a control flap and adjusted between negative and low positive positions. The ventilation flap releases air flow from the wing underside to the upper side of the flap and the sealing flap is retracted to release an outflow of air from the upper side of the flap when the flap is used for increasing lift and the flap is adjusted between low and high positive positions. | 01-14-2010 |
20100006202 | Apparatus and Method for Producing a Large-Area Fibre-Composite Structural Component - The present invention provides an apparatus and a method for producing a large-area fibre-composite structural component, in particular for the aircraft sector, comprising a predetermined shaping element, a controllable laying device for the defined laying of at least one fibrous sheet over or into the predetermined shaping element, a controllable turning device for a defined turning of the predetermined shaping element and of the laying device in relation to each other by a predetermined turning angle, and a central control device, which is connected to the laying device and the turning device for controlling of the same. | 01-14-2010 |
20100005495 | Information and Entertainment System in an Aircraft - An information system in an aircraft, whereby information system data relating to informing, instructing and entertaining passengers can be visually presented. The information system includes an aircraft window with at least one pane and a control unit. The at least one pane, is coated with a translucent display that is coupled to the control unit, which, for the purpose of presenting information, is equipped to supply electrical current in a targeted manner to the display. | 01-07-2010 |
20100001135 | Retaining Device - A retaining device includes a fireproof core enclosed by a non-fireproof case, wherein a pre-tensioned fireproof device is integrated in the case and attached to the core. The fireproof device relaxes in such a way, when the case melts, that a construction element is reliably held between the carrier and the device. | 01-07-2010 |
20100001131 | Method of and Apparatus for Producing Aerodynamic Resistance on an Aircraft - The invention concerns an apparatus for and a method of producing aerodynamic resistance on an aircraft, comprising at least one braking flap, wherein the at least one braking flap can be extended into the airflow around the aircraft. In accordance with the invention at least one braking flap is arranged on the fuselage of the aircraft in a region over the wings of the aircraft. | 01-07-2010 |
20090321571 | Window for aircraft with microstructure as a sunscreen - An aircraft window includes a microstructure so that light rays with a correspondingly large angle of incidence are reflected back to the exterior region. By contrast, light rays with another, i.e. smaller, angle of incidence are allowed to pass almost without hindrance. The microstructures are designed as optical prisms, wherein the order of magnitude of the prisms is in the region of light wave lengths. | 12-31-2009 |
20090321568 | Aircraft Fuselage with Circular-Arc-Shaped Exterior Contour - A fuselage section comprises an interior that forms a passenger cabin. In horizontal projection the fuselage section is geometrically defined by a first exterior skin region and a second exterior skin region, wherein the second exterior skin region faces the first exterior skin region. Both the first exterior skin region and the second exterior skin region in longitudinal direction of the passenger cabin comprise in horizontal projection a circular-arc-shaped contour of uniform radius of curvature. | 12-31-2009 |
20090321564 | Vertically Movable Passageway for Rest Rooms in Ceiling Region - A vertically movable passageway for a space in the ceiling region in an aircraft cabin. The passageway comprises a passageway floor and a displacement device, wherein the displacement device is designed to variably set the height (h | 12-31-2009 |
20090321090 | Fuel Cell System for Extinguishing Fires - A fire fighting system for extinguishing a fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the fire source. | 12-31-2009 |
20090320582 | Wind tunnel with a model arranged therein, particularly a model of an aircraft, for acquiring and evaluating a plurality of measuring data, as well as method - A wind tunnel with a model arranged therein, particularly a model of an aircraft, for acquiring and evaluating a plurality of measuring data, wherein the wind tunnel comprises at least one computer unit and at least one visual display terminal particularly at least one monitor, as well as at least one sensor for acquiring the measuring data. A plurality of measuring data of the wind tunnel, particularly measuring data on flow and/or pressure conditions on the model and/or in the region of the model, which data are determinable by the at least one sensor, can be processed in real time and with consideration of geometrical data of the model by the at least one computer unit and visualized on the at least one visual display terminal during a wind tunnel measurement. | 12-31-2009 |
20090314889 | GALLEY AND METHOD OF CATERING FOR PASSENGERS ON AN AIRCRAFT - A galley including a galley body on a cabin floor for accommodating storage boxes, appliances and at least one service cart; storage boxes for storing goods, and a service cart. The galley body has a plurality of vertical levels that are substantially equidistant from each other, each of the vertical levels divided into a plurality of laterally adjacent compartments whose horizontal and vertical dimensions are equal to an integer multiple of the respective dimensions of a single one of the storage boxes. A transfer table is provided in front of the galley body for access to the compartments. A method includes catering for passengers on an aircraft. | 12-24-2009 |
20090311469 | Composite Plate and Method of Draining a Composite Plate - The present invention concerns a composite plate ( | 12-17-2009 |
20090310118 | Method And Lidar System For Measuring Air Turbulences On Board Aircraft And For Airports And Wind Farms - The invention relates to a method for measuring air turbulences with a lidar system, particularly on board aircraft during which a pulsed expanded laser beam ( | 12-17-2009 |
20090309762 | Method of and Apparatus for Monitoring the Condition of Structural Components - The present invention relates to a method of monitoring the condition of structural components, in which an optical sensor in conjunction with a computing unit ascertains image deviations from successive images of the structural components to be monitored, and therefrom ascertains changes in shape of the structure. Robust three-dimensional scanning of the structural components is possible when using two or more sensors. The invention further relates to an apparatus for monitoring the condition of structural components having an optical sensor and an apparatus having two or more sensors. Finally the invention relates to an aircraft in which the methods or apparatuses according to the invention are used. | 12-17-2009 |
20090308976 | Cover panel for an aircraft, more particularly a landing gear cover panel for a cargo plane - The invention relates to a cover panel for a landing gear for an aircraft with at least one pivotal closable flap | 12-17-2009 |
20090308577 | Device For Providing A Cooled Or Heated Liquid Onboard An Aircraft - A device for providing a cooled or heated liquid, in particular cooled drinking water comprises a reservoir for receiving the liquid to be cooled or to be heated. The reservoir is thermally coupled with a conduit through which a cooling medium or a heat transfer medium may flow and comprises a first as well as a second circulation connection, with the first circulation connection being connected with the second circulation connection via a circulation conduit. | 12-17-2009 |
20090305622 | PROCESS AND SYSTEM FOR CONTROLLING THE PRESSURE IN AN AIRCRAFT CABIN - In a process and a system for controlling the pressure in an aircraft cabin the status of at least one aircraft door is detected by at least one detection device by transmitting a signal indicative of the status of the aircraft door to a unit for controlling an avionics ventilation system which is controlled in dependence upon the signal indicative of the status of the aircraft door in such a way that a build-up of pressure in the aircraft cabin is prevented when the signal indicative of the status of the aircraft door indicates that the aircraft door is not fully closed and secured. | 12-10-2009 |
20090304438 | CONNECTING ELEMENT AND USE OF SUCH A CONNECTING ELEMENT FOR FASTENING AIRCRAFT COMPONENTS IN THE CASE OF A CFK-METAL HYBRID CONSTRUCTION - The present invention relates to the use of connecting elements for fastening CFK components and metal components in an aircraft or spacecraft, wherein a CFK component and a metal component can be connected to each other via at least one connecting element. The connecting element in this case is produced from an electrically non-conducting material, or has a shank and is produced from an electrically conducting or non-conducting material, wherein the shank is provided with a sleeve consisting of an electrically non-conducting material. | 12-10-2009 |
20090303567 | Transmission-controlled window glazing - The invention relates to a window glazing comprising at least two window panes with an intermediate ventilated space arranged therebetween, wherein at least one window pane is provided with a layer which is arranged on the interior side thereof and whose transmission is controllable. More specifically, said invention relates to a multilayer glazing comprising corresponding intermediate spaces in which a sweeping gas circulates, wherein said sweeping gas consists of a mixture of air and other gaseous components in which the sweeping gas content is adjustable. | 12-10-2009 |
20090301832 | Energy Absorber for Aircraft - An energy absorber for aircraft, which includes one or more energy absorber elements and a housing, whereby the energy absorber elements can absorb crash impulses by plastic deformation within the housing. Thus, the load on the primary structure and the respective inboard devices is limited, which can lead to an increased, passive safety of the passengers and a weight reduction. | 12-10-2009 |
20090301110 | Air-Conditioning System For Aircraft - Air-conditioning system ( | 12-10-2009 |
20090300991 | Water Deflector and System Having Multiple Water Deflectors of this Type - A water deflector includes a water-diverting area and an attachment area for attachment to a seal profile. The water-diverting area and the attachment area are connected to one another via a connection area, which is elastically deformable in such a way that when force acts on the water-diverting area, it is movable in relation to the attachment area. The water deflector can be used in the area of a door, wherein the water deflector deforms when the door is closed and comes to rest in a cavity between the seal profile and the door outer skin, and assumes its starting shape again when the door is opened. | 12-10-2009 |
20090300834 | System for Flushing a Vacuum Toilet and Toilet Cover for a System of This Type - A system for flushing a vacuum toilet contains a flushing water reservoir container, which may be filled with flushing water, a toilet bowl, which is connectable using a vacuum wastewater line and via a flushing valve to a vacuum system, and a spray device, situated in the toilet bowl, which is connected via a Venturi nozzle to the flushing water reservoir container. A partial vacuum is generated in the vacuum wastewater line when the flushing valve is open, which generates an airflow, by which flushing water contained in the flushing water reservoir container is suctioned, sprayed via the spray device into the toilet bowl, and suctioned into the vacuum wastewater line. | 12-10-2009 |
20090298408 | Enhanced Piccolo Ducting With Sidewall Air Outlets | 12-03-2009 |
20090295223 | SYSTEM FOR CONTACT LESS DATA AND POWER TRANSMISSION - A system for contactless data and power transmission between a first vehicle component and a second vehicle component includes a first control unit, a second control unit, and a transducer with a primary winding and a secondary winding. The first control unit is adapted to generate an alternating voltage at a signal output port from a voltage present at a voltage input port, where the frequency of the alternating voltage is modulated depending on the data that is input at a data input port, and wherein the second control unit is adapted to demodulate the data and provide it at the data output port. | 12-03-2009 |
20090294592 | Fastening Device for an Aircraft Interior Equipment Component - The invention relates to a fastening device for an aircraft interior equipment component, with at least one suspension point ( | 12-03-2009 |
20090294590 | Framework wing box for a wing - A wing box for an aircraft wing with a framework and a first shell. The framework is connected to the first shell such that a load acting on the first shell can be transferred by the framework. | 12-03-2009 |
20090294585 | ASSEMBLY FOR STORING OBJECTS IN THE CABIN OF A VEHICLE - The invention relates to an assembly for storing objects in the cabin of a vehicle, comprising at least one frame with attachment means, and at least one holding device for mounting the objects, wherein the frame has a contour that, at least in some regions, essentially corresponds to the interior contour of a storage container so that the frame can be arranged in the storage container and can be attached in the storage container with the use of the attachment means, and wherein the holding device can be removably stored in the frame. The assembly according to the invention can be placed in a pre-assembled state in the vehicle, thus reducing the time required for installation and maintenance, while at the same time making better use of the available space. | 12-03-2009 |
20090294394 | CONVEYING DEVICE FOR A TROLLEY IN AN AIRCRAFT CABIN - The invention relates to a conveying device for a trolley, in particular to a refreshments trolley, in an aircraft passenger cabin and consists in the fact that the conveying device comprises an electric drive with two drive wheels | 12-03-2009 |
20090294018 | Method for joining aircraft fuselage elements by friction stir welding (FSW) - The invention relates to a method for joining at least two aircraft fuselage segments ( | 12-03-2009 |
20090293494 | Hybrid drive for an aircraft - A drive device for an aircraft comprises a gas turbine apparatus for generating a first drive energy and electric motor for generating a second drive energy. The gas turbine apparatus and the electric motor are set up in such a way that the drive unit may be provided with at least one of the first drive energy and the second drive energy. The drive unit is set up to generate propulsion using at least one of the first drive energy and the second drive energy. | 12-03-2009 |
20090291625 | Air System - An air system for pressurizing and air conditioning a cockpit and cabin space of a plane comprises a compressor ( | 11-26-2009 |
20090289146 | INTEGRATED ACOUSTIC DECOUPLING IN A HABITATION MODULE - According to an exemplary embodiment of the invention, a combined habitation module for the crew of an aircraft is provided, which habitation module comprises two monument units that are separated from each other by a gap such that acoustic decoupling of the two monument units from each other is provided. In this way noise propagation within the habitation module may be prevented to a large extent. | 11-26-2009 |
20090289144 | TRIMMABLE HORIZONTAL STABILIZER - A trimmable horizontal stabilizer is provided adjacent to the fuselage of an aircraft and has a predetermined aerodynamic profile. A movable elevator is arranged adjacent to the horizontal stabilizer. The horizontal stabilizer has a load-bearing structure which extends in the span direction and is firmly connected to the fuselage of the aircraft, and movable areas which are connected to the load-bearing structure such that they can move and can be moved independently of the elevator in order to trim the horizontal stabilizer by varying the aerodynamic profile. | 11-26-2009 |
20090283641 | AIRCRAFT WITH CONNECTION ELEMENT FOR CONNECTING A CONDUIT SYSTEM TO COOLING AGGREGATES IN AIRCRAFT CABINS - The invention relates to an aircraft with a connection element for connecting at least one first conduit element or the like positioned in a supply chamber of an aircraft with at least one second conduit element positioned in a cabin chamber of the aircraft, wherein supply chamber and cabin chamber are separated from each other by means of a separation element, substantially comprising a connection part comprising fastening elements for fastening the first and second conduit element. | 11-19-2009 |
20090283636 | Module for an Aircraft - A module for an aircraft having a fuselage structure and a floor element defining a floor plane. The module includes a frame device adapted for mounting a functional element and the frame device is adapted for attachment to the floor element of the aircraft at a first location in the floor plane. The frame device is adapted for attachment to the fuselage structure of the aircraft at a second location, wherein the second location is not in the floor plane. | 11-19-2009 |
20090283633 | INFILL PANEL OF A SUPPLY ARRANGEMENT IN A PASSENGER CABIN - A supply device in a passenger cabin, such as an aircraft passenger cabin, includes a first panel or “function panel” having one or more comfort elements, operating elements, visual display elements, and communication elements; and a second panel or an “infill panel”, which includes flexible supply channels. The panels are guided and lined up in a rail system of a PSC channel that is arranged in the direction of flight above a passenger seat row. The function panels are individually positionable in the PSC channel relative to the passenger seat row, wherein the infill panel synchronously follows a linear actuating movement of the function panel, and in this process automatically compensates for the distance dimension S | 11-19-2009 |
20090277888 | SYSTEM AND METHOD FOR MANUFACTURING WELDED STRUCTURES, AND A WELDING ADDITIVE MATERIAL FOR THIS PURPOSE - A system and method for manufacturing welded structures comprises components to be welded, a welding additive material which, before the welding, has a shaped profile and the shaped profile is disposed between components to be welded and conforms with at least one of the components to be welded. At least one heat source is used in the method to weld the components, producing a weld seam on at least one side of one of the components. | 11-12-2009 |
20090277445 | System For Improving Air Quality In An Aircraft Pressure Cabin - A system for improving the air quality in a pressure cabin of an aircraft comprises a recirculation air circuit by means of which a portion of the cabin air, referred to as recirculation air, is withdrawn from the pressure cabin, filtered and then recirculated into the pressure cabin. To increase the oxygen partial pressure of the air fed back into the pressure cabin, the quantity of recirculation air is passed wholly or partially through a nitrogen generator ( | 11-12-2009 |
20090277204 | Adjustable Orifice For Use In An Air Conditioning System, In Particular An Aircraft Air Conditioning System - An adjustable orifice ( | 11-12-2009 |
20090276201 | Method For Configuring A Test Arrangement, Test Method And Test Arrangement - The invention relates to a method for configuring a test arrangement ( | 11-05-2009 |
20090274615 | Device for the Generation of Hydrogen Gas by Dehydrogenation of Hydrocarbon Fuels - A device for generation of hydrogen gas by dehydrogenation of hydrocarbon fuels. The device includes a fuel reservoir connected to a reactor by a fuel line to supply said reactor with fuel. The reactor has a first discharge for recycling of residual hydrocarbons generated during dehydrogenation to the fuel reservoir and optionally cooperates with a catalyst. The fuel reservoir may contact a heat exchanger by the fuel line and the first discharge. The fuel may be preheated by the heat exchanger which may be introduced to the reactor by the fuel line and the reactor may have a heating device for heating the introduced fuel to reaction temperature. The residual fuel generated by dehydrogenation in the reactor may be cooled by the heat exchanger and may be returned to the fuel reservoir. The reactor may have a second discharge for the extraction of the hydrogen gas generated on dehydrogenation. | 11-05-2009 |
20090274097 | INFORMATION TRANSMISSION TO AN AIRCRAFT - A system and a method for information transmission to an aircraft and for the subsequent provision of the information, which includes an information system for an aircraft including a receiver for receiving a message in a mobile communication standard from a ground system. The message contains a message header and a message body including information prepared with a further header. An interpreter analyses the further header of the message and separates the information, and at least one display device is provided for presenting the information. The receiver is connected to the display device by way of the interpreter so as to be able to communicate. The messages transmitted are, for example, SMS messages or MMS messages. | 11-05-2009 |
20090272853 | Lift-Augmenting Flap, in Particular for Leading Edge Flap, for an Aerodynamically Effective Wing - A lift-augmenting leading edge flap for a carrying wing of an aircraft, wherein the flap comprises an essentially rigid main body which makes a transition from the first side to the second side of the wing the flap being adjustable by a retention- and actuation mechanism coupled between the flap and wing box, between a first, retracted, position and a second, extended, position, wherein the first transition region of the flap is slidable to rest in each position essentially free of any gap, against the first skin of the wing box or against the wing end cover, in relation to the wing end cover. | 11-05-2009 |
20090272844 | Method and Device for Supporting the Take-Off Rotation of an Aircraft - A method and a device for supporting the take-off rotation of an aircraft, which aircraft comprises on each side of the aircraft at least two main landing gear units, arranged one behind the other, which main landing gear units comprising wheels. For supporting the take-off rotation, in at least one rear pair of the main landing gear units the distance between the wheels of these rear main landing gear units, which wheels roll on the ground, and the fuselage, may actively be reduced. | 11-05-2009 |
20090272843 | ADJUSTING DEVICE FOR ADJUSTING A HIGH-LIFT FLAP AND AIRFOIL WING COMPRISING SUCH AN ADJUSTING DEVICE - Adjusting device for adjusting a high-lift flap ( | 11-05-2009 |
20090266937 | REDUCTION OF FRICTIONAL LOSSES IN THE REGION OF BOUNDARY LAYERS ON SURFACES, AROUND WHICH A FLUID FLOWS - An aerodynamic body with a plurality of nozzles for throttling a fluid flow to be removed by suction through the nozzles in a self-regulated fashion is disclosed. The aerodynamic body according to one example, includes a plurality of throttling nozzles with a throttle section that is defined by an inlet and an outlet. In one example, the interior wall of the throttle section may be designed such that an effective flow cross section is reduced in a self-regulated fashion due to the creation of turbulences on the interior wall of the throttle section as the pressure differential between the inlet and the outlet of the throttle section increases. | 10-29-2009 |
20090263676 | Method for Connection At Least Two Pieces of Sheet Material, Particularly At Least Two Metal Sheets for a Lightweight Structure As Well a Joining and Lightweight Structure - A method for connecting at least two sheet-like formations, in particular at least two metal sheets with a thin material thickness for aircraft, comprises establishing butt-joint connections between the sheet-like formations by forming a joining region; mechanical processing of the sheet-like formations and/or of the joining region; mechanical and/or chemical adhesive pre-treatment of the sheet-like formations and/or of the joining region; and pasting-on at least one reinforcement element in the region of the top and/or the bottom of the joining region, wherein for the purpose of forming a second load path the width of the at least one reinforcement element is wider than the width | 10-22-2009 |
20090261202 | Universal Retaining Device, Particularly For Fastening Panel Elements And/Or Accessory Parts In Aircraft - A universal bracket for fastening different panel elements and/or additional devices in aircraft, comprises a base plate for fastening to a substructure, a support plate connected to the base plate and a plurality of spring clips received in the support plate to provide a releasable and vibration-damping connection to the panel elements. The base plate has at least one bore screen for fastening at least one device carrier for fastening at least one additional device, in particular emergency lighting, an emergency exit sign. or the like, in different positions, wherein the fastening of the device carriers is provided with a fastening device such as fastening rivets, screws or the like. | 10-22-2009 |
20090260706 | Pipeline For Conducting Air For Air Conditioning In Aircrafts - The invention relates to a pipeline | 10-22-2009 |
20090260449 | DEVICE FOR TEST LOADING - The present invention provides a device for test loading a fuselage barrel, in particular in the aviation and aerospace industry. The device comprises a first and a second pressure bulkhead for sealing the fuselage barrel at the end faces thereof in a pressure-tight manner. The device further comprises a support device which may be coupled to the first pressure bulkhead, on the one hand, and to the second pressure bulkhead, on the other hand, extending through the fuselage barrel. Moreover, the device comprises a loading device which may be coupled to the support device, on the one hand, and to a portion of the fuselage barrel, on the other hand, for introducing loads into the fuselage barrel. The resulting advantage is that gravitational force and/or acceleration forces acting on the masses arranged in the fuselage barrel, for example cargo, in particular during the flight phase may be simulated by means of components which are exclusively arranged within the fuselage barrel, which is pressurised during the test. Thus a provision of through-holes in the fuselage skin for passing through hydraulic cylinders and the sealing of said holes relative to the fuselage skin, as in the device known to the applicant, are avoided. | 10-22-2009 |
20090255354 | Linear actuating organ, in particular for the remote actuation of displaceable components in wind tunnel models - A linear actuating element for the remote control of adjustable components on wind tunnel models includes a housing and a gear motor for driving a threaded spindle. On the threaded spindle a threaded nut for moving a pusher rod is arranged. The threaded spindle is connected to the gear motor by a chain drive, wherein the threaded spindle and a gear motor axle are arranged so as to be substantially anti-parallel. Due to the anti-parallel arrangement of the gear motor axle and of the threaded spindle, the linear actuating element on the one hand comprises a compact design. Consequently the linear actuating element is in particular suited to the remote control of adjustable components on wind tunnel models with small spatial dimensions. On the other hand the linear actuating element makes it possible to generate very considerable mechanical actuating forces while at the same time providing very good positioning and repetition accuracy. | 10-15-2009 |
20090255277 | OPTIMIZED DEFROSTING REGULATION OF PARALLEL ARRANGED FRESH AIR OUTLETS OF AIR CONDITIONERS - An arrangement is provided for de-icing pipeline connections of an aircraft, which are connected to all fresh air outlets of an air conditioner, whose construction includes, but is not limited to the functions of multiple turbines and heat exchangers, having a first pipeline, which is connected to a first turbine, and a second pipeline, which is connected to a second turbine, the two pipelines, which are each connected downstream from the two turbines and to which process air is fed at the turbine outlets, being connected at the pipe ends and being continued using a third pipeline. The arrangement is characterized in that a first hot air source is fed hot fresh air from a bleed air system of the aircraft and is connected at its outlet to a fourth pipeline, into which temperature-reduced fresh air is fed from the hot air source. The fourth pipeline is connected at its pipe end to two further valve-regulated pipelines, of which a fifth or a sixth pipeline is connected to the first or the second pipeline, and through which temperature-reduced fresh air is transported and fed valve-regulated to the first and/or second pipeline. | 10-15-2009 |
20090252917 | Reinforcement of cellular materials - The invention pertains to a method for reinforcing cellular materials ( | 10-08-2009 |
20090250921 | Docking and Undocking of Liquid Carrying Lines to and From a Docking Body - A docking system for docking a liquid stream carrying line to a docking body, a line end for docking a liquid stream carrying line to a docking interface of a docking body, as well as to a method for preventing liquid from continuing to flow when undocking a line end of a liquid stream carrying line from a docking interface of a docking body. The docking system includes a line end having a first form that is conically tapered in the direction of flow and a docking interface which is situated on the docking body and has a second form that is conically tapered in the direction of flow. The first conically tapered form and the second conically tapered form are adapted to one another in such a way that, in the docked state, they are mutually set apart in one coupling region by an interspace defined by a sealing ring, concentrically opposing one another. Thereby, the first conically tapered form is equipped on its periphery with at least one cleaning element, which extends from the first conically tapered form toward the second conically tapered form in order to capture liquid that may accumulate in the interspace. | 10-08-2009 |
20090250554 | SELF-SUPPORTING CABIN STRUCTURE - A cabin structural unit for attaching cabin installation elements is provided for an aircraft. The cabin structural unit is set up in such a way that a cabin installation element is attachable. The cabin structural unit is implemented as self-supporting and fastenable to an aircraft structure. | 10-08-2009 |
20090250293 | ACOUSTICALLY OPTIMIZED CABIN WALL ELEMENT - A wall element for the sound-insulating interior lining of a transport device, comprising at least one sandwich element, at least one insulation package and at least one absorber plane element. The sandwich element comprises at least one core layer, a first cover layer and a second cover layer, wherein the first cover layer and the second cover layer are each arranged on one side of the core layer. At least the first or the second cover layer is a microperforated layer; the sandwich element possesses a shear rigidity that is adjusted in such a way that the sandwich element comprises one or several coincidence boundary frequencies that are determined by the shear rigidity, which coincidence boundary frequencies are outside the frequency range that dominates the noise in the interior of the cabin; and the shear rigidity of the sandwich element at the same time is sufficient for said sandwich element to be used as an interior lining. Sound-insulating interior lining according to the aspects according to the invention provides adequate sound insulation also in the lower frequency range of below 500 Hz, without increasing the weight of the interior lining when compared to the weight of conventional interior linings. | 10-08-2009 |
20090246502 | COMPOSITE PANEL - The invention pertains to a composite panel with a first cover layer, a second cover layer and a first core layer that is arranged between the first cover layer and the second cover layer and features a plurality of cells that are separated from one another by walls at least in certain areas, wherein the first cover layer features a draining layer. The inventive composite panel may be distinguished from a composite panel according to the state of the art in that a second core layer with a plurality of cells that are separated from one another by walls at least in certain areas is arranged between the first cover layer and the first core layer. | 10-01-2009 |
20090242150 | CURTAIN SUPPORT ASSEMBLY, IN A FRAMEWORK DESIGN, IN A CABIN OF A VEHICLE - The invention relates to a curtain support assembly to receive a curtain rail for a curtain for separating at least two regions in a cabin of a vehicle, comprising one or several header components for covering a space formed between the curtain rail and a ceiling in the cabin. The assembly according to the invention comprises one or several load-bearing frame structures, each comprising at least one profile component, on which in each case on at least one side the header components are arranged. The frame structure may be made from standard components and may comprise header components that are hardly subjected to any mechanical loads and that are therefore less demanding to produce. | 10-01-2009 |
20090242149 | Partition wall with integrated curtain rail flap - The invention relates to a partition wall for partitioning at least two regions in a cabin of a vehicle. The invention includes a partition comprising a body that may be moved into a first open position and into a second closed position and comprising a curtain rail, wherein the body is designed in the first position to cover an aisle that is adjacent to the partition, at least in some regions, by means of a curtain that has been affixed to the curtain rail. | 10-01-2009 |
20090242147 | CURTAIN SUPPORT ASSEMBLY WITH INTEGRATED STORAGE FACILITY IN A CABIN OF A VEHICLE - The invention relates to a curtain support assembly to receive a curtain rail for a curtain for separating at least two regions in a cabin of a vehicle, comprising two or more header components for covering a space formed between the curtain rail and a ceiling in the cabin. The assembly according to the invention distinguishes itself from the state of the art in that between the header elements, for the purpose of holding objects, a hollow space is formed that is accessible by way of one or several closable openings to the cabin. In a further improvement, a roller is integrated in the hollow space, by way of which roller the curtain may be rolled up or down and may easily be stowed away. | 10-01-2009 |
20090230676 | Articulate connection piece for tubes - The invention relates to a connection piece ( | 09-17-2009 |
20090230245 | SEPARATION ELEMENT FOR ATTENUATING THE PROPAGATION OF LIGHT IN AN AIRCRAFT - The invention relates to a separation element for separating a first space from a second space in an aircraft. The separation element can be affixed between a ceiling region of the cabin, a hatrack in the ceiling region of the cabin, and between a movable space separation device. Furthermore, as a result of attachment between the ceiling region, the hatrack and the movable space separation device, the separation element is connectable in a lightproof manner to the ceiling region, and in a lightproof manner to the hatrack. Furthermore, the separation element is designed in such a manner that it is connectable in a lightproof manner to the movable space separation device. | 09-17-2009 |
20090221224 | Air Conditioning Arrangement For An Aircraft With A Plurality Of Climate Zones That May Be Individually Temperature-Controlled - An air conditioning arrangement ( | 09-03-2009 |
20090221154 | FASTENING SYSTEM FOR FASTENING A CABIN FITTING ELEMENT TO A SUPPORT STRUCTURE OF AN AIRCRAFT - A fastening system for fastening a cabin fitting element with at least one electrical installation on a support structure of an aircraft. During installation into the support structure, the cabin fitting element is fixed in succession by at least one loose bearing in at least one degree of translational freedom and then by at least one fixed bearing in the at least one further degree of translational freedom. In order to ensure an improved installation and dismantling of cabin covering panels with electrical installation and to reduce the weight due to the components and also the installation space which is required, according to the disclosed embodiments a contact device with a bush arrangement and a plug arrangement is integrated in the at least one loose bearing and/or the at least one fixed bearing, by which an electrical connection is produced between the support structure and the electrical installation of the cabin fitting element on fixing at least of one degree of translational freedom. | 09-03-2009 |
20090220320 | Insert For A Sandwich Component Having A Honeycomb Core - An insert ( | 09-03-2009 |
20090218734 | Tool, Arrangement, and Method for Manufacturing a Component, Component - This application describes a tool, an arrangement, and a method of manufacturing a component. The manufacturing of the component is achieved by a resin transfer from a storage chamber via a transfer line into a working chamber. Before the resin transfer, taking place, for example by a compressed air charging of the storage chamber, the storage chamber is filled with an amount of resin adjusted to the size of the component. furthermore, a semi-finished product, consisting of cut-to-size reinforcement fibers, is inserted into the working chamber that is adjusted to the form of the component to be produced. Storage chamber, transfer line, and working chamber are configured in a one-piece mould casing of the tool. The application further describes a component manufactured by the above-mentioned tool or by the above-mentioned method respectively. | 09-03-2009 |
20090218724 | Method for producing a sandwich construction, in particular a sandwich construction for the aeronautical and aerospace fields - The present invention provides a method of producing a construction, in particular a sandwich construction for the aeronautical and aerospace fields, comprising the following steps. A heating material is initially applied on one side of a core construction material. In a further step a reinforcing element is introduced into the core construction material and the heating material in such a way that the reinforcing element extends through the core construction material and the heating material and has a portion which projects beyond the heating material. The heating material is then heated to soften the projecting portion at least in regions and said projecting portion is subsequently deformed using the softened region as a pivot point to engage the core construction material from behind and to form the construction. This method is distinguished in particular by the fact that it allows the portions to be heated substantially simultaneously, and not sequentially as in the state of the art. The time saved as a result in turn has a positive effect on production costs. | 09-03-2009 |
20090218452 | Clamping Part and Retention Device Having a Clamping Part of this Type - A retaining device for attachment to a screw contains a hollow base element for receiving a clamping part. The hollow base element has a floor having a hole, and an inner surface of the base element on the floor area of the retaining device is implemented as conical to contact the outer surface of the conical body of the clamping part. The clamping part can be moved downward in the direction of the floor by rotating the retaining device around its own axis and biting into a screw which is inserted through the hole and runs through the opening of the clamping part. | 09-03-2009 |
20090218440 | INTEGRATED MULTIFUNCTIONAL POWERED WHEEL SYSTEM FOR AIRCRAFT - The invention relates to a powered wheel system for an aircraft, comprising at least one undercarriage with several rotatably held wheels, with the powered wheel system comprising two or more motors of which in each case at least one motor is coupled to at least one of the wheels, and comprising at least one control device that is coupled to the motors. A control device is equipped to control operation of the motors independently of each other as far as their respective rotary speeds and direction of rotation are concerned, so that the system is able, among other things, to effect taxiing; by means of rotary speed differentials on different motors to be able to steer the aircraft; prior to landing to bring the wheel circumference speeds to landing speed; and to boost the undercarriage brakes of the aircraft. Furthermore, by means of an improvement of the system according to the invention, the rotary speeds of the wheels may be determined with precision. The invention furthermore relates to a method for driving wheels of an aircraft. | 09-03-2009 |
20090217593 | Internal swivel door for compartment of a vehicle - Internal swivel door for compartment of a vehicle | 09-03-2009 |
20090217494 | Retaining Clip for Releasable Fixing of Modules Strung Together on a Distributor Bar - A retaining clip for releasable fixing of a plurality of modules strung together on a distributor bar for forming a module series, wherein the distributor bar has a substantially U-shaped cross-sectional geometry with two legs as well as a back wall and the two legs, have a plurality of recesses. The retaining clip has a substantially U-shaped cross-sectional geometry with two retaining clip legs as well as a connecting bar between the two retaining clip legs, whereby the two retaining clip legs each have at least one detent, which may be brought into locking engagement from the outside into respectively two opposite recesses of the distributor bar, such that the retaining clip may be snapped onto the distributor bar for securing the modules of the module series from lateral displacement in the longitudinal direction of the distributor bar with this. | 09-03-2009 |
20090214900 | Fuel Cell System for Supplying Aircraft - A fuel cell system for aircraft with a passenger cabin comprises a fuel cell. The fuel cell comprises a first inlet connection, a first outlet connection, a cathode side and an anode side, wherein the first inlet connection is formed as the inlet connection of the cathode side and wherein the first outlet connection is formed as the outlet connection of the cathode side. In addition, the fuel cell system is designed in such a way that at the first inlet connection, a gas with a pressure is applied, which corresponds to an air pressure in the passenger machine. | 08-27-2009 |
20090212977 | DEVICE FOR ERROR DETECTION OF ADJUSTABLE FLAPS - With a device for error detection of adjustable flaps on aircraft wings, it is proposed that each flap is provided with a tube as a transmission element arranged in the wing span. The tube is connected fixedly at one end with the flap and is rotatably held. On the free end of the tube, a measuring arm is fixedly arranged on the tube and a sensor fixed to the flap structure is arranged. When an error occurs, the flap twists, whereby a distance change between the sensor and measuring arm occurs. The signals of the sensor are transmitted for error localization of each flap to an evaluation device, which switches off the drive via a control device with occurring errors. | 08-27-2009 |
20090212976 | Method and system for monitoring of the temperature of the surface of an aircraft - The invention relates to a method and a system for monitoring the temperature of an aircraft, in which at least one camera connected to a first processing unit, for imaging detection of at least one region of the substantially upwardly-pointing outer surface of the aircraft, detects an images once, several times, or at regular intervals and transmits this to the first processing unit, wherein the light spectrum which may be detected by the camera lies substantially in the infrared range and the first processing unit determines the temperatures of substantially all the pictorially detected locations or has these determined by a downstream signal-processing device, in each case compares the temperature for individual locations with a predetermined maximum design temperature for the relevant location, and if the maximum design temperature is exceeded, generates a warning signal. The warning signal may be used to prevent takeoff of the aircraft, wherein the determined exceeding of the temperature may be checked by checking the measurements by means of a thermographic image of the surface of the aircraft in the cockpit of the aircraft and the prevention of takeoff may be deactivated if necessary. | 08-27-2009 |
20090206200 | ASSEMBLY AND METHOD FOR STOWING AWAY AND REMOVING A SURVIVAL KIT IN A PASSENGER CABIN OF AN AIRCRAFT - An assembly and a method for stowing away and removing a survival kit in a passenger cabin of an aircraft, comprising a first stowage compartment that may be put in place in a floor of the passenger cabin, wherein the first stowage compartment is equipped for completely accommodating the survival kit and for leading out a hook that is connected to the survival kit by way of a strap, which hook is used for hooking the survival kit to an attachment means of a rescue device with the first stowage compartment remaining closed. | 08-20-2009 |
20090200818 | Retention System and Cover for This With an Integrated Retention Function - A retention system with a cover ( | 08-13-2009 |
20090200424 | Lateral Force Joint - A lateral force joint, with which a plate-like spar can be fastened to a fuselage strap mounted on an airplane fuselage. The plate-like spar has a through bore, into which a fastening cylinder mounted on the flange can be inserted for connecting both components. In order to allow for the location of the spar to be adjusted with respect to the fuselage strap, a bearing bush of the spar is eccentrically fitted into the through bore. Correspondingly, the fastening cylinder of the fuselage strap is mounted eccentrically on a bearing bush so that a rotation of the bearing bushes allows the lateral force joint to be adjusted. | 08-13-2009 |
20090200103 | SONIC ABSORPTION DEVICE FOR AN AIR PIPELINE OF AN AIRCRAFT, IN PARTICULAR OF AN AIR CONDITIONING SYSTEM OF AN AIRCRAFT - A sonic absorption device for an air pipeline of an aircraft, which sonic absorption device comprises at least one curved pipe section whose respective interior wall is clad with a sound absorption material, wherein within the curved pipe section at least one air guidance means is arranged for a flow optimisation, wherein for further weight-neutral sound absorption the air guidance means arranged within the curved pipe section comprises a microperforation on at least one side surface. | 08-13-2009 |
20090199920 | Arrangement for storing and conveying liquid, especially in an aircraft - At least one liquid tank has an outlet opening and a drain stub extending therefrom. A circular flange has plural connection openings with connection stubs respectively extending therefrom. A drain line is connected to the circular flange and communicates with all of the connection stubs. The drain stub of each tank is flange-connected to a respective connection stub extending from the circular flange. Unneeded connection stubs can be closed with blind flanges. This provides a modular reconfigurable system allowing a selected plurality of liquid tanks to be connected to a single drain line through the flange arrangement. | 08-13-2009 |
20090194635 | OVERHEAD BIN FOR USE ON BOTH SIDES IN AN AIRCRAFT - An overhead bin for use on both sides in a passenger cabin of an aircraft, includes a first baggage compartment and a second baggage compartment, a first opening and a second opening for loading items into the first baggage compartment and into the second baggage compartment, and a partition for dividing the first baggage compartment from the second baggage compartment. The first baggage compartment and the second baggage compartment differ from each other in their shape and/or alignment. With several overhead bins, the alignment of a larger and a smaller baggage bin can alternate so that adequate bin space for stowing hand baggage is available to passengers in the center seats. | 08-06-2009 |
20090193835 | Cooling System and Freight Container | 08-06-2009 |
20090191018 | Carrier system for receiving components - A carrier system for receiving a component comprises a bottom plate integrated in the design of a conventional ball mat in order to introduce forces, e.g., acting on the ball mat, into the structure, for example an aircraft structure. | 07-30-2009 |
20090189733 | Luggage Compartment Actuation - A detection unit for integration in a luggage compartment of an airplane, having a capacitive sensor with an active layer, wherein the capacitive sensor is adapted to detect a first event triggered by a user, wherein the detection unit is adapted to transmit a first control signal to a control mechanism, wherein the first control signal corresponds to the first event and wherein the active layer comprises carbon fibre electrically isolated from a surrounding compartment structure. | 07-30-2009 |
20090189018 | Method for isolating a cabin wall of an aircraft or for cooling or heating of cabin air and a cabin wall suitable therefore - The present invention relates to a method for insulating an aircraft cabin | 07-30-2009 |
20090189017 | RELEASABLE FASTENING OF A COMPONENT IN AN AIRCRAFT - A device for the releasable fastening of a component in an aircraft includes a component carrier with a base plane, wherein the component carrier comprises an installation state in which the base plane of the component carrier comprises an angle relative to the horizontal base plane of the aircraft, and wherein the component carrier is equipped to accommodate a component in a releasably affixed manner. | 07-30-2009 |
20090184126 | AIRFREIGHT CONTAINER AND AIRCRAFT - The idea of the present invention is that an airfreight container according to the invention, which is designed especially for an unpressurized cargo hold of an aircraft, comprises an airtight and pressure-tight container housing with a container interior space for accommodating airfreight goods. This airfreight container furthermore comprises an internal compressed air generating device which is designed. for independently generating compressed air for supplying the container interior space with compressed air. The concept according to the invention of an at least partly autonomous airfreight container, which is created as a result, provides that the airfreight container according to the invention, in addition to the pure bundling of goods, now provides, moreover, different supply systems, such as the device for compressed air generation and compressed air provision, corresponding to the specific requirements. The particular advantage of this solution according to the invention is that cargo aircraft now do not have to provide supply systems, or have to provide at least a significantly reduced number of supply systems, in their cargo hold, and all further functions are now fulfilled by the airfreight container itself when required. | 07-23-2009 |
20090180627 | Active sound blocker - A noise reduction system for actively blocking a noise source for a means of transport. The noise reduction system comprises at least one counter sound source and at least one intensity sensor. The at least one counter sound source and the at least one intensity sensor are arranged in a measuring region. In the measuring region, measuring of the noise intensity of the noise source and measuring of the counter sound intensity of the counter sound source are by the intensity sensor. Based on the measured noise intensity and the counter sound intensity, the counter sound source is controllable such that the sound energy input of the noise source can be globally reduced by the counter sound source. | 07-16-2009 |
20090180250 | PEAK-LOAD COOLING OF ELECTRONIC COMPONENTS BY PHASE-CHANGE MATERIALS - Cooling device for electronic components, in particular for power electronics in an aircraft, comprising an energy storage device which is in heat-conducting communication with at least one electronic component which is to be cooled, and which storage device is in the form of a material which performs a change in phase on absorbing the waste heat from the at least one electronic component. | 07-16-2009 |
20090179110 | Extended Decompression Flap Arrangement - The invention concerns an apparatus for producing a rapid air pressure equalisation between regions of an aircraft fuselage which are separated from each other by an aircraft fuselage structure and which have an air pressure difference relative to each other, in an aircraft, in particular a passenger aircraft, comprising at least one through-flow opening in the aircraft fuselage structure, a decompression flap ( | 07-16-2009 |
20090179109 | System and method for adjusting control surfaces for wind tunnel models - A system and a method for adjusting and locking a control surface that is movably arranged on a wind-tunnel aircraft model and comprises a drive arrangement for driving the control surface, and a locking arrangement. The drive arrangement comprises a first drive motor, arranged in a fixed manner relative to the control surface, at least one first connecting rod eccentrically connectable to the first drive motor, and at least one lever, whose one end can be held on the first connecting rod and whose other end can be held on a fixed point of the aircraft model. The locking arrangement can be attached in a fixed manner relative to the control surface and is further designed to block a relative movement between the control surface and the aircraft model. | 07-16-2009 |
20090173825 | AIRCRAFT DOOR WITH OVERSIZING - An aircraft fuselage section is provided in which an outer skin construction provides at least one door opening having a width, such that it is divided by at least one rib of the fuselage skeleton of the aircraft fuselage section into multiple opening areas. | 07-09-2009 |
20090173572 | Sandwich panel for sound absorption - An aircraft cabin panel for sound absorption, with a core layer that comprises a plurality of cells that extend in an open manner across the thickness of the core layer and that are separated from each other by cell walls, and with a first cover layer that faces away from the sound field, as well as a second cover layer that faces towards the sound field and that comprises a plurality of perforation holes. The second cover layer is multi-layered and apart from a layer with the perforation also comprises a second layer that acts as a flow resistance device. The second layer is arranged on the outside, and visually closes off the perforation, and the outer layer comprises an air-permeable woven fabric. | 07-09-2009 |
20090171634 | Method for Reconstructing Gusts and Structural Loads at Aircraft, in Particular Passenger Aircraft - A method for reconstructing gusts and/or structural loads at aircraft, in particular passenger aircraft. The method includes generating an observer on the basis of a nonlinear model of the aircraft which describes the movement of the aircraft in all six degrees of freedom (DoF) and the elastic motion of the aircraft structure; continuously supplying all the data and measurements substantial for the description of the state of the aircraft to the observer; and calculating the gust velocities and structural loads (manoeuvre and gust loads) by the observer from the supplied data and measurements. | 07-02-2009 |
20090167331 | Testing apparatus and method for detecting a contact deficiency of an electrically conductive connection - A testing apparatus and a method for detecting a contact deficiency of an electrically conductive connection. The testing apparatus comprises a measuring chamber, in which several system elements of the connection that are connected in an electrically conductive fashion are positioned, a heat radiator that is supplied with energy and the transferred thermal radiation of which is emitted into the measuring chamber and directed toward the region of the system elements that, after having been heated, generate a thermal field of the insulated and the metallic system components of these connected system elements, a thermal (image) acquisition unit for optically capturing the generated thermal field and for realizing a signal conversion into a thermal image of the connected system elements, and a thermal (image) reproduction unit for the visual reproduction of the converted thermal image. | 07-02-2009 |
20090167321 | Method and Apparatus for Determining an Interfering Field Strength in an Aircraft - The disclosed embodiments relates to a method and an apparatus for determining the interfering field strength in an aircraft and the impairment of an electric system in the aircraft including cables between the outer shell and the interior paneling of the fuselage for transmitting signals within the aircraft. | 07-02-2009 |
20090166475 | APPARATUS FOR THE PIVOTAL FASTENING OF AN ACTIVE SURFACE, IN PARTICULAR A SPOILER ON A WIND TUNNEL MODEL OF AN AIRCRAFT - An apparatus ( | 07-02-2009 |
20090166471 | Fuselage Structure and Method for the Production of a Fuselage Structure - The present invention provides a method for the production of a fuselage structure, and a fuselage structure, in particular of an aircraft or spacecraft, with an inner shell arrangement which has an upper inner shell and a lower inner shell, the upper inner shell being spaced apart at least in some sections from the lower inner shell by a first gap in order to form a window region; and a window band which is arranged at least in the window region and has a pane device which comprises a grid structure which absorbs fuselage forces. | 07-02-2009 |
20090166127 | Sandwiich panel for sound absorption - An aircraft cabin panel for sound absorption, with a sandwich construction, comprising a core layer that comprises a plurality of tube-like or honeycomb-like cells that extend in an open manner across the thickness of the core layer and that are separated from each other by cell walls and that are uniform in design. A first cover layer faces away from the sound field, as well as a second cover layer that faces towards the sound field and that comprises a plurality of perforation holes and adjacent cells are interconnected by way of apertures in the cell walls. The perforation of the second cover layer comprises a distance (b) between holes, which distance exceeds the opening width (c) of the cells of the core layer, wherein the first cover layer is closed and wherein the cell walls comprise a perforation so that they are acoustically transparent in the direction parallel to the cover layers. | 07-02-2009 |
20090165900 | Method fo the Heat Treatment of a Profile, Device for the Heat Treatment of a Profile and Profile - A method and device for the heat treatment of a profile, in particular an extruded profile for aircraft. The profile may be formed by one or more different, in particular curable, aluminium alloys. The method provides that at least two regions of a profile are subjected to a different heat treatment. The device includes a first chamber that encloses a first region of a profile and a second chamber that encloses a second region of the profile, wherein different temperatures can be set in the first and second chambers. The profile has at least two regions that each have different material properties and are formed by differential heat treatment. | 07-02-2009 |
20090165878 | Device for Mixing Fresh Air and Heating Air and Use of the Device in a Ventilation System of an Aircraft - The invention relates to a device ( | 07-02-2009 |
20090165197 | System for flushing a vaccum toilet - A system for flushing a vacuum toilet in an aircraft, with a bowl drain for removing toilet waste water from a bowl, a drain line, a bypass flow line for feeding-in air, a drainage valve and a waste water line. The bowl drain and the bypass flow line are connectable to the drain line, and the drainage valve on the input side is connectable to the drain line, and on the output side is connectable to a waste water line. In an implementation of the vacuum toilet as a vacuum urinal, the system may provide either water flushing or waterless flushing. | 07-02-2009 |
20090159748 | Decompression Device With Adjustable Release Pressure - The invention relates to a decompression element for pressure equalisation in a cabin of an aircraft, with a decompression element frame ( | 06-25-2009 |
20090159747 | Aircraft Fuselage Element - An aircraft fuselage element ( | 06-25-2009 |
20090159744 | System box for accommodating aircraft systems - A system box for accommodating aircraft systems, and for load transmission between an aircraft structure and a crew rest compartment. The system box comprises a first, a second and a third region, wherein the three regions differ from each other. The first region is adapted for attachment of the system box to the primary structure of the aircraft, wherein the second region is adapted for mechanical contact with a crew rest compartment for the aircrew. The mechanical contact in turn is adapted for load transmission between the aircraft structure and the crew rest compartment. Necessary aircraft systems are accommodated in the third region of the system box. | 06-25-2009 |
20090155403 | Press Device for the Energy-Efficient Curing of a Sandwich Component for Aircraft - A press device for the energy-efficient curing of a sandwich component for an aircraft, comprising an open and mechanically adequately loadable core structure with cover layers applied to one side or to both sides, characterised in that the sandwich component is restrained between a pressure piston, an abutment and sidewalls of the press device, thus forming an essentially closed interior space, and at least one cover layer and/or the core structure comprise/comprises a curable duroplastic plastic material. | 06-18-2009 |
20090152405 | Wing and method for reducing effects of propeller airflow on lift distribution - A wing for an aircraft includes a non-balanced lift gradient because as a result of at least one propeller slipstream flowing onto the wing the induced drag of the wing is increased. To reduce the increased induced drag, the wing comprises a first region with a reduced local wing camber and/or reduced local twist, and a second region with an increased local wing camber and/or increased local twist. The first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards. The second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards. | 06-18-2009 |
20090152399 | LINE SYSTEM ARRANGEMENT IN AN AIRCRAFT OR SPACECRAFT HAVING A FUSELAGE - A line system arrangement in an aircraft or spacecraft having a fuselage includes at least one receiving region for receiving at least one component of a line system, wherein the at least one receiving region is accessible, at least in some sections, from outside the fuselage of the aircraft and spacecraft for installation and/or maintenance of the line system; and an aircraft or spacecraft with a corresponding arrangement. | 06-18-2009 |
20090152398 | Device for limiting the deflection of a door arranged in a fuselage cell of an aircraft - The invention relates to a device for limiting the deflection of a door ( | 06-18-2009 |