Patent application number | Description | Published |
20130020030 | DEVICE AND METHOD FOR THE PRODUCTION OF MULTI-ARCHED STRUCTURAL COMPONENTS FROM A FIBER COMPOSITE - A device for the production of structural components from a fiber composite material, the components being three-dimensionally arched over a large surface, including a jig having a convex mounting surface having receiving channels for the insertion of structural components, wherein the loaded jig interacts with a laminating bonding device having a corresponding shape for forming the structural component under pressure, wherein the mounting surface includes a plurality of individually elastically deformable mounting shell parts arranged adjacent to each other along at least one longitudinally extending pitch line and attached to a plurality of elastically deformable supporting frame elements extending on the interior of the shell at a right angle to the pitch line, and a plurality of actuators for deforming the mounting surface between an extended position (A) and at least one retracted position (B) to move the jig from the bonding device relative to the receiving channels without undercuts. | 01-24-2013 |
20130035027 | MIXER ASSEMBLY FOR AN AIRCRAFT AIR CONDITIONING SYSTEM - A mixer for an aircraft air conditioning system has first and second fresh air lines and first and second recirculation air lines. A first premixer is connected to the first fresh air line and the first recirculation air line, to mix the fresh air with the recirculation air thereof. A second premixer is connected to the second fresh air line and the second recirculation air line, to mix the fresh air with the recirculation air thereof. A main mixer is connected by a first premixed air line to the first premixer and by a second premixed air line to the second premixer. The main mixer is adapted to be supplied through the first premixed air line and the second premixed air line exclusively with premixed air from the first and/or the second premixer. | 02-07-2013 |
20130037346 | Plate Absorber - An aircraft cabin plate absorber includes a supporting panel, a cover panel and an intermediate layer which is arranged between the supporting panel and the cover panel. The cover panel includes a cover layer which is visible from the cabin space, and is arranged on the supporting panel on the side facing the sound inside the cabin space. The cover panel is fastened to the supporting panel by the intermediate layer, and comprises at least one connecting region, in which it is connected to the supporting panel, and at least one absorption region, in which it is arranged so as to oscillate with respect to the supporting panel. The panel is optimized in term of space requirement and weight for use in aircraft and has improved sound absorption properties. | 02-14-2013 |
20130045060 | Machining Apparatus and Method for Machining a Laminate - A machining method for machining a superficial portion of a laminate using machine tool having a depth limiter which restricts a maximum depth of the machine tool. A guide frame having an inner guide contour restricts a maximum dimension of the superficial portion, and is secured over the superficial portion. The superficial portion is machined while the machine tool is guided by the guide contour. From another point of view, a machining apparatus for machining a superficial portion of a material is provided. The machining apparatus comprises a guide frame, an inner guide contour for guiding a machine tool, an attachment member for securing the guide frame to an attachment member, adjacent to the superficial portion, of the material. | 02-21-2013 |
20130056579 | WING WITH RETRACTABLE WING END PIECE - The invention relates to a wing with an extension in the wingspan direction, in the wing chord direction and in the wing thickness direction for use in an aircraft, with a retractable wing end piece. A mechanical lever system is here used, which can execute a pivoting motion of a wing end piece comprising both a rotational component and a translational component. The lever kinematics here comprises two lever arrangements, for which a respective two hinged devices are provided. | 03-07-2013 |
20130056583 | HANDLING SYSTEM FOR HANDLING OBJECTS IN A VEHICLE, STORAGE DEVICE AND METHOD FOR HANDLING OBJECTS IN A VEHICLE - A handling system for handling objects in a vehicle comprises a storage apparatus that is positionable outside a vehicle cabin, an access device that is positionable in a vehicle cabin, and a transport device for transporting objects between the storage apparatus and the access device. The storage apparatus comprises a storage space and a connection station that is connectable to the transport device, wherein the storage apparatus comprises at least one drive device for moving carriers on which objects to be stored are held. The handling system comprises at least one guiding device that with the drive device guides the carriers on at least one circular path within the storage space. The storage space thus comprises a vertical flat shape that results in a significantly smaller reduction in the available cargo volume in a vehicle, while at the same time maximizing the design space available for passenger seats. | 03-07-2013 |
20130061611 | AIR CONDITIONING SYSTEM WITH HYBRID OPERATION FOR AN AIRCRAFT - A system for air conditioning an aircraft cabin is provided. The system includes at least one cooling circuit, at least one compressed-air line and at least one compressor for compressing air. The cooling circuit is connected to the compressor by way of the compressed-air line, and the compressor is drivable independently of bleed air. This makes it possible to tap engine bleed air at a lower pressure than usual, because an arising difference from a required operating pressure can be compensated for by the compressor. The air conditioning system can thus be operated by means of a hybrid energy supply. | 03-14-2013 |
20130074952 | PROTECTIVE DEVICE FOR A PRESSURE LINE, PRESSURE LINE SECTION AND HYDRAULIC SYSTEM - The invention pertains to a protective device for a pressure line for conveying pressurized fluids, as well as to a pressure line section with a pressure line for conveying pressurized fluids and a corresponding protective device. | 03-28-2013 |
20130075528 | AIRCRAFT FUSELAGE WITH DOOR STOPPERS ATTACHED TO A DOOR FRAME BULKHEAD - An aircraft fuselage includes at least one opening that can be closed by a flap or door, which comes to abut against at least one door stopper that is arranged on a fuselage-side door frame bulkhead and transfers the impact forces into an intermediate costal for diversion into an aircraft structure that encompasses bulkheads, wherein the door frame bulkhead exhibits an opening, through which an impact section of the door stopper extends, wherein a fastening plate section adjoining the latter comes to abut the rear side of the door frame bulkhead, which interacts with means for directly introducing the impact forces from the door stopper into the intermediate costal. | 03-28-2013 |
20130075536 | High Lift System For An Aircraft - A high lift system for an aircraft includes at least one lift flap arranged on a wing forming a gap between a leading edge of the wing and a trailing edge of the lift flap in an extended position of the lift flap, and at least one flap adjustment mechanism for moving the lift flap between a retracted and at least one extended position relative to the wing. The wing includes a depression with a leading depression edge for accommodating the lift flap in a retracted position, and arranged in such an area of the wing that a correspondingly formed trailing edge region of the lift flap includes a curvature, by which the gap between the leading edge of the wing and trailing edge of the lift flap is convergent. A convergent and improved gap increases the efficiency of a high lift system without any active or movable means. | 03-28-2013 |
20130081900 | SILENCER FOR AN AUXILIARY POWER UNIT OF AN AIRCRAFT - A silencer for an auxiliary power unit of an aircraft includes an inlet, an outlet, a housing, and a flow channel of a porous material, arranged in the housing. Between the housing and the flow channel an intermediate space is created, which space is divided by at least one outer partition into outer cells arranged around the flow channel. A central body includes a casing that is permeable to gas at least in some regions and that is arranged in the interior of the silencer. The central body includes inner partitions dividing the central body into inner cells. The resonance frequency of the inner cells corresponds to the natural frequency of the first radial mode in a channel formed between the central body and the inner surface of the inlet. In this manner particularly good sound attenuation is achieved with a compact installation space of a silencer. | 04-04-2013 |
20130082141 | ACTUATION DEVICE FOR OPENING AN EMERGENCY EXIT FLAP OF A COCKPIT DOOR - An actuation device for opening an emergency exit flap of a cockpit door is provided. The actuation device comprises a support structure, at least two securing elements, an actuation element and a deflection mechanism. The support structure is configured so as to be fastened to the emergency exit flap. The securing elements are integrated into the support structure and are configured so as to fasten the actuation device, and thus the emergency exit flap, to the cockpit door. The actuation element is connected to the support structure. Therein, the deflection mechanism connects the securing elements to the actuation element in such a way that a force which is exerted on the actuation element is diverted in such a way that the securing elements are released from the cockpit door. | 04-04-2013 |
20130086783 | JOINING APPARATUS FOR JOINING STRUCTURAL COMPONENTS OF AN AIRCRAFT - A joining apparatus for joining together structural components of an aircraft, includes positioning means for holding the structural components to be joined in a defined desired position, in which the structural components can be fixedly joined together by means of a joining device that can be moved relative to the structural components by way of guiding means, wherein the positioning means encompass a formative frame structure that is detachably secured to the structural components to be connected along the joining edges outside in the edge area, and serves as a guiding means for the joining device movably secured hereupon. | 04-11-2013 |
20130094012 | METHOD AND APPARATUS FOR MEASURING THE FLOW VELOCITY BY MEANS OF A PLASMA - A method and device for measuring the flow speed of a fluid, in one example, of air, is provided. The method and device include the use of laser radiation, in which, by means of at least one laser beam pulse focused in the fluid flow in the radiation focus a plasma is formed, and the acoustic and/or optical effects occurring during plasma formation are acquired, and from them the flow speed of the fluid is determined | 04-18-2013 |
20130094168 | WALL MOUNTING FOR ON-BOARD ENTERTAINMENT CONTROL UNITS - A standardized wall mounting is provided for mounting control units of system components in an aircraft cabin with a fastening unit and at least one plug unit. The fastening unit is designed for guiding the control unit during an installation movement of the control unit on the wall mounting. The plug unit is designed for producing a plug connection between the control unit and the wall mounting during the installation movement of the control unit on the wall mounting. | 04-18-2013 |
20130094994 | WATER SYSTEM FOR A VEHICLE AND METHOD FOR REDUCING GERMS IN A WATER SYSTEM - A water system for a vehicle is provided. The water system comprises at least one water supply source, at least one water-conducting device, at least one closing valve and at least one germ reduction connection. The germ reduction connection and the water supply source are connected to the water-conducting device. The germ reduction connection is designed to introduce a germ-reducing fluid into the water-conducting device. The closing valve is arranged between the water supply source and the germ reduction connection and is designed to be fully closed thus preventing the ingress of germ-reducing fluid into the water supply source. By means of such a water system it is possible to carry out sterilization or disinfection very easily and quickly without this requiring any major maintenance work. | 04-18-2013 |
20130099056 | FUSELAGE CELL FOR AN AIRCRAFT, PARTICULARLY AN AIRPLANE - A fuselage cell for an aircraft includes at least two shell segments forming a fuselage cell. The shell segments are provided with a plurality of longitudinal and/or circumferential reinforcements that are integral with a skin panel of the respective shell segment. The reinforcements at least sectionally form a closed cross-sectional geometry together with at least the skin panel of the corresponding shell segment in order to create at least one hollow space, wherein at least one system component at least sectionally extends and/or at least one system medium is at least sectionally routed in the at least one hollow space. The reinforcements also fulfill the function of accommodating at least part of the system components and system mediums of the technical equipment of the aircraft. This results in weight savings and a simplified installation because the number of required mountings and connectors for the system components is reduced. | 04-25-2013 |
20130111656 | DISPOSABLE SEATING-SURFACE COVER FOR A TOILET-SEAT FLAP, AND TOILET MODULE - A disposable seating-surface cover ( | 05-09-2013 |
20130111938 | Heat exchanger, cooling system and method for operating a heat exchanger and a cooling system - A heat exchanger with at least one cooling segment having a first, a second, and a third portion. A first heat carrier flow path, through which a first heat carrier medium flows, extends through the first portion. A second heat carrier flow path, through which a second heat carrier medium flows, extends through the second portion. A first coolant flow path, through which a first coolant medium flows, extends through the third portion. The heat exchanger comprises at least one cooling body, a second coolant medium flowing through a second coolant flow path extending through the cooling body. The first and the second heat carrier flow paths are thermally coupled, respectively, to the first and the second coolant flow path, to discharge heat energy of at least one of the first and the second heat carrier medium to at least one of the first and the second coolant medium. | 05-09-2013 |
20130115404 | LIGHTWEIGHT STRUCTURE, PARTICULARLY PRIMARY AIRCRAFT STRUCTURE OR SUBASSEMBLY, AS WELL AS METHOD FOR THE MANUFACTURE THEREOF - A lightweight structure at least sectionally composed of a plurality of connected mosaic elements and/or skin mosaic elements. The lightweight structure allows an essentially load-appropriate arrangement of the mosaic elements and/or the skin mosaic elements including the optional skin. The lightweight structure requires a significantly reduced number of connecting elements, such that the assembly effort can be reduced and an additional weight reduction can be achieved. Also, two variations of a method for manufacturing a lightweight structure are provided. Large-format lightweight structures such as, for example, an aircraft fuselage cell or partial shells thereof can also be manufactured in a reliable and dimensionally accurate fashion because only mosaic elements and skin mosaic elements, with relatively small dimensions, need to be handled. Other applications of the lightweight structure include launch vehicles, rocket stages, space stations, space station modules, satellites and masts or towers of wind power plants. | 05-09-2013 |
20130118180 | Exhaust Gas Treatment Of Gas Turbine Engines - A gas turbine engine, especially a turbojet or turbofan for an aircraft, includes a combustion section and an exhaust section produces an exhaust gas. The emission products can be reduced by using a gas treatment device with a reactor and an injection device. The reactor produces a nitrogeneous substance such as ammonia. This reducing agent is injected in the gas phase in the exhaust section of the gas turbine engine. By selective non catalytic reaction the Nitrogen oxides of the exhaust gas can be reduced. Furthermore the injection device is arranged such that the temperature window of this reduction process is ranging from 850° C. to 1100° C. The reactor for producing gaseous ammonia can either be a thermal reactor or a high pressure plasma device. | 05-16-2013 |
20130118493 | PASSENGER SERVICE MODULE AND PASSENGER SERVICE SYSTEM - A passenger service module ( | 05-16-2013 |
20130118770 | Method for the automated manufacture of a fibre composite component with integrated lightning protection, and also a fibre composite component - A method for manufacturing a fiber composite plastic component with integrated lightning protection. The steps include, for a positive mold, automatically laying down a ribbon-form pre-preg material or dry ribbon-form reinforcing fiber strands onto the mold. Then, automatically laying down a ribbon-form lightning protection material onto the pre-preg material or the reinforcing fiber strands. For a negative mold, the steps include automatically laying down the lightning protection material on the negative mold, then automatically laying down the pre-preg material or the dry reinforcing fiber strands onto the positioned lightning protection material. The method also includes curing the laminate construction formed with the pre-preg material and the lightning protection material to form the fiber composite component, or infiltrating the dry reinforcing fiber strands with a plastic, and subsequently curing the laminate construction formed with the infiltrated reinforcing fiber strands and the lightning protection material to form the fiber composite component. | 05-16-2013 |
20130119209 | MOUNTING DEVICE FOR MOUNTING A CABLE OR A LINE ON A STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT, AND AIRCRAFT OR SPACECRAFT - A mounting device for mounting a cable or a line on a structural component of an aircraft or spacecraft. The mounting device comprises at least two parts, one of these parts being configured as an attachment part and being provided to be attached to the structural component. The other part is configured as a receiving part and is provided to receive a portion of the cable or of the line. Both parts can be coupled together by means of at least a first ball-and-socket joint. This coupling is configured such that the two parts can be brought into a plurality of spatial positions relative to one another. Also provided is an aircraft or spacecraft, in particular an aircraft, which has a structural component and a cable or a line which is mounted on the structural component by a mounting device of this type. | 05-16-2013 |
20130120163 | METHOD AND SYSTEM FOR DISPLAYING INFORMATION ON A DISPLAY UNIT IN AN AIRCRAFT CABIN - A method and system for displaying information on an electrical display unit in an aircraft cabin including a generating unit for generating at least one signal which clearly identifies the information, a first acquiring unit for wirelessly acquiring the at least one signal and a control unit for controlling the display unit on the basis of the at least one signal. The system may also have a second acquiring unit for acquiring departure and/or arrival location information relating to a flight and a third acquiring unit for acquiring passenger information. | 05-16-2013 |
20130125566 | VEHICLE WITH A COOLING SYSTEM FOR COOLING AND METHOD FOR COOLING IN A VEHICLE - A cooling system of a vehicle with a fuel cell includes an absorbent circuit with an absorber tank, a regenerator tank, an absorbent pump and a first pressure reduction means and a coolant circuit with a condenser connected to a steam outlet of the regenerator tank, a second pressure reduction means and an evaporator arranged between a steam inlet of the absorber tank and the second pressure reduction means. The regenerator tank is designed to desorb the coolant in solution in the absorbent by absorbing a first quantity of heat and to introduce it in a vaporous state into the condenser. The evaporator is designed to evaporate the coolant while absorbing a second quantity of heat and to introduce it in the vaporous state into the absorber tank. At least one of the first and of the second quantity of heat could be provided by the fuel cell. | 05-23-2013 |
20130126672 | ROTATABLE CABIN ATTENDANT SEAT AND AIRCRAFT MONUMENT ARRANGEMENT WITH A ROTATABLE CABIN ATTENDANT SEAT - A cabin attendant seat ( | 05-23-2013 |
20130129445 | TIE BAR FOR PURPOSES OF CONNECTING EQUIPMENT FITTING OF AN EQUIPMENT MODULE, IN PARTICULAR AN OVERHEAD COMPARTMENT, TO A STRUCTURE FITTING OF A FUSELAGE CELL STRUCTURE OF AN AERONAUTICAL VEHICLE - A tie bar for connecting an equipment fitting of an equipment module to a structure fitting of a fuselage cell structure. At each end the tie bar has a fork head each with a fork head hole for a bolt. The spacing between the fork heads can be continuously adjusted. A captive bushing is utilized for sound and vibration decoupling. The bushings which are a press fit in the fork head holes can no longer fall out during the handling of the tie bars | 05-23-2013 |
20130130607 | MIXING DEVICE FOR AN AIRCRAFT AIR CONDITIONING SYSTEM - A mixing device for an aircraft air conditioning system includes a plurality of cold-air supply lines, which are devised to supply cold air to the mixing device. A plurality of warm-air supply lines is further provided, which are devised to supply warm air to the mixing device. A first premixing chamber is connected to the cold-air supply lines and devised to mix the cold air that is fed through the cold-air supply lines into the first premixing chamber. A second premixing chamber is connected to the warm-air supply lines and devised to mix the warm air that is fed through the warm-air supply lines into the second premixing chamber. Finally, a main mixing chamber is connected to the first and the second premixing chambers and devised to mix the cold air premixed in the first premixing chamber with the warm air premixed in the second premixing chamber. | 05-23-2013 |
20130134776 | Energy supply system, aircraft or spacecraft and method - An energy supply system, an aircraft and spacecraft using such an energy supply system and a method for providing electrical energy with the energy supply system. The energy supply system comprises an energy source which generates a direct current or a direct voltage. A converter is coupled to the energy source and is designed to convert the generated direct current or the generated direct voltage into an output current specified for the energy supply system or an output voltage specified for the energy supply system. A switching device is designed to couple an output of the energy supply system to the converter or directly to the energy source as a function of the electrical power required by the energy supply system. | 05-30-2013 |
20130134916 | CONTROLLING AN ELECTRICAL CONSUMER OF AN AIRCRAFT - An electrical consumer of an aircraft comprises an electric motor and an inverter for producing an alternating voltage for the electric motor. A method for controlling the electrical consumer comprises determining a rotational frequency for the electric motor. The method also includes establishing whether the rotational frequency leads to oscillations in the input current of the inverter which are below a predefined threshold, the oscillations being produced by the inverter when producing a supply voltage for the electric motor, and changing the rotational frequency if it has been established that the rotational frequency leads to oscillations below the predefined threshold. | 05-30-2013 |
20130139374 | Attachment arrangement, a connecting device, and also a method - An attachment arrangement for attaching a component to a base item, with at least one fixing device for fixing one section of the component on a section of the base item. At least one connecting device with a connecting element and at least one receiving element are provided. One of the elements is arranged on a component section and the other of the elements is arranged on a base item section. The two elements detachably engage with one another in a form fit. Loads can be transferred at least in the direction of a first axis, and a relative movement is possible between the elements in the direction of a second axis, different from the first axis. A connecting device is disclosed for such an attachment arrangement. A method is disclosed for purposes of attaching a component to a base item by means of such an attachment arrangement. | 06-06-2013 |
20130139891 | METHOD AND SYSTEM FOR CONTROLLING AN AUXILIARY POWER UNIT - A method for controlling the operation of an auxiliary power unit supplying an aircraft air conditioning system with compressed process air includes determining a heating or cooling requirement of an aircraft region to be air-conditioned, determining a desired value of at least one process air flow parameter in dependence on the determined heating or cooling requirement of the aircraft region to be air-conditioned, controlling the operation of the auxiliary power unit in dependence on the determined process air flow parameter desired value, acquiring an actual value of the at least one process air flow parameter, comparing the process air flow parameter actual value with the process air flow parameter desired value and controlling the operation of the auxiliary power unit in dependence on the result of the comparison of the process air flow parameter actual value with the process air flow parameter desired value. | 06-06-2013 |
20130143070 | Aluminium Material Which Can Be Exposed To High Temperatures, Is Alloyed With Scandium And Has Improved Extrudability - The present invention relates to the use of a process for producing an aluminium material which can be exposed to high temperatures and is alloyed with scandium. In this process, a precursor material made of an alloy comprising the metals aluminium and scandium is introduced into a vacuum chamber, the precursor material is subjected to vacuum degassing and the precursor material is treated with nitrogen gas. This is followed by final vacuum degassing of the precursor material. | 06-06-2013 |
20130149483 | FIBER COMPOSITE COMPONENT ASSEMBLY HAVING AT LEAST TWO PLATE-SHAPED COMPOSITE STRUCTURES AND PROCESSES FOR PREPARING SAME - A fiber composite component assembly includes at least two plate-shaped composite structures which in each case are made from synthetic-resin embedded fibers and are integrally interconnected by way of an adhesive layer arranged in between, and additional mechanical reinforcement means, wherein the fiber composite components include several partial regions that do not contain synthetic resin, which partial regions can be brought to flush conformity with each other and which are arranged so as to be spaced apart from each other, through which partial regions the mechanical reinforcement means that can subsequently be bonded-in with synthetic resin have been passed. | 06-13-2013 |
20130149894 | Interface device for cabin monuments - An interface device for a cabin monument, in particular for assembly in an aircraft or spacecraft, including a routing device, a first plurality of interface connection sockets, which are connected to the routing device via a first plurality of connection lines and to which a vehicle interface of the aircraft or spacecraft can be connected. A second plurality of interface connection sockets are provided which are connected to the routing device via a second plurality of connection lines and to which a cabin monument can be connected. The routing device is constructed so as to selectively electrically connect interface connection sockets of the first plurality of interface connection sockets to interface connection sockets of the second plurality of interface connection sockets. | 06-13-2013 |
20130149950 | Support structure for use in an air supply arrangement and service supply system comprising said type of support structure and method for configuration - A support structure for an air supply arrangement for air conditioning aircraft passenger cabins. The air supply arrangement comprises at least one centrally controlled cabin ventilation system and an individually adjustable cabin ventilation system. The support structure includes: a first section for receiving and/or integrating cabin ventilation system components, a second section for receiving and/or integrating passenger emergency oxygen supply components and a third section comprising a plurality of receiving devices. Each receiving device receives and releasably secures an active module for individually adjustable cabin ventilation. The third section has at least the number of receiving devices required for at least one receiving device to be associated with each seating row for a maximum number of seating rows arrangeable in the cabin A supply system includes at least one such support structure and at least one of the active modules. A method is provided for configuring a corresponding supply system. | 06-13-2013 |
20130152704 | APPARATUS AND METHOD FOR ACQUIRING MECHANICAL LOADS ON THRUST ELEMENTS - A device for acquiring mechanical loads on mechanically loaded bodies is provided. The device exhibits a resonance-capable micro-bridge structure, an alternating voltage source with a variable frequency, an impedance measuring device for acquiring the impedance of the micro-bridge structure and an electronic unit for receiving determined impedance values and changing the frequency of the alternating voltage source. By exciting the micro-bridge structure and measuring its impedance, a conclusion can be drawn as to the expansion-dependent resonance frequency, which in return makes it possible to determine the expansion, and hence the mechanical load. Such a device is sufficiently accurate, and largely independent of outside influences. | 06-20-2013 |
20130154357 | ELECTRICAL SYSTEM FOR AN AIRCRAFT - An electrical system for an aircraft is provided. The system comprises an inverter for transforming a first alternating current from an on-board network having a variable frequency into a second alternating current, and at least a first electrical load and at least a second electrical load, which are configured to be operated simultaneously by the second alternating current. | 06-20-2013 |
20130156595 | RIBLET STRUCTURE ON A FLOW SURFACE AND METHOD - A riblet structure for a flow surface is provided. The riblet structure has a multitude of riblets that comprise a matrix material which includes reinforcement elements. The reinforcement elements can be designed as reinforcement fibers that extend in the longitudinal direction or as particles. In this manner the abrasion resistance can be improved and erosion can be retarded. | 06-20-2013 |
20130157536 | AIRCRAFT INTERIOR LINING COMPONENT AND METHOD FOR PRODUCING AN AIRCRAFT INTERIOR LINING COMPONENT - An aircraft interior lining component includes a composite material, wherein the composite material includes a matrix, first reinforcing fibres embedded in the matrix and second reinforcing fibres embedded in the matrix. The strength of an interface between a surface of the first reinforcing fibres and the matrix surrounding the surface of the first reinforcing fibres is greater than the strength of an interface between a surface of the second reinforcing fibres and the matrix surrounding the surface of the second reinforcing fibres. | 06-20-2013 |
20130158700 | INTEGRATED CARGO LOADING SYSTEM ARCHITECTURE - A cargo loading system for a cargo compartment of a means of transport, for example a cargo aircraft or a passenger aircraft, is provided. The system includes at least one power drive unit for transporting cargo of the means of transport. The power drive unit and a control module are coupled to a BUS system. The control module generates control signals for the power drive unit and maintenance data of the power drive unit for the control and maintenance of the power drive unit. The BUS system transmits the control signals and maintenance data of the power drive unit between the control module and the power drive unit. In this manner an existing hardware platform of the means of transport can be used, and weight and cabling as well as the number of control boxes of the means of transport can be reduced. | 06-20-2013 |
20130159205 | FREIGHT EVALUATION FOR AN AIRCRAFT - A freight evaluation system for providing freight information with respect to an item of freight of an aircraft includes a freight evaluation unit for collecting and analyzing data of a freight loading system and a recognition system and for determining the current position of the item of freight therefrom. | 06-20-2013 |
20130160061 | SKY MARSHAL VIDEO ACCESS - A surveillance device and method provide access to a surveillance system for keeping a cabin of an aircraft under surveillance. A computer program may be used to execute the method for accessing the surveillance system. The surveillance device includes an authentication unit for examining an access-authorisation request for access to the surveillance system, and a control unit for selecting, on the basis of the access-authorisation request, a display unit from a plurality of display units provided in the aircraft, and for relaying a video-image signal corresponding to a captured video image of a subarea of the cabin of the aircraft to the selected display unit for the purpose of displaying the video image. | 06-20-2013 |
20130160472 | AIRCRAFT AIR CONDITIONING SYSTEM COMPRISING A SEPARATE REFRIGERATION CYCLE - An air-conditioning system for an aircraft includes a compressed air branch for conveying externally supplied and pressurized air, preferably bleed air. Furthermore, a cooling circuit for conveying preferably liquid refrigerant is provided and extends through a ram air duct. The system also includes a first heat exchanger for the heat transfer between the compressed air branch and the cooling circuit, a compressed air turbine arranged in the compressed air branch and a cooling circuit compressor arranged in the cooling circuit and mechanically coupled to the compressed air turbine. The system can have a modular design and be positioned at optimal locations in the aircraft due to the separation of the compressed air branch and the cooling circuit. In this way, the length of hot compressed air ducts can be shortened. | 06-27-2013 |
20130160923 | SYSTEM AND METHOD FOR REPAIRING A STRUCTURAL COMPONENT - A system for repairing a structural component, in particular an aircraft structural component, includes a repair patch which is connected to the structural component in such a manner that it covers an opening in the structural component resulting from removing a damaged region of the structural component. A sensor is fastened to the repair patch in a region of the repair patch covering the opening in the structural component and is designed to detect strains and/or stresses occurring in the repair patch. An evaluating device is adapted to evaluate the strain values and/or stress values detected by the sensor and, in dependence on the result of this evaluation, output a signal which is characteristic of the quality state of the connection between the structural component and the repair patch. | 06-27-2013 |
20130160979 | ACCUMULATOR ARRANGEMENT FOR STORING A REFRIGERATING MEDIUM, AND METHOD OF OPERATING SUCH AN ACCUMULATOR ARRANGEMENT - An accumulator arrangement suitable for use in a cooling system designed for operation with a two-phase refrigerating medium, includes an accumulator vessel with a receptacle for receiving a refrigerating medium. A liquefier of the accumulator arrangement is adapted to liquefy refrigerating medium to be received into the receptacle of the accumulator vessel before fed in the receptacle of the accumulator vessel and includes a refrigerating medium outlet for discharging refrigerating medium which liquefied in the liquefier from the liquefier. The accumulator arrangement includes a heat exchanger arranged in the receptacle of the accumulator vessel and a refrigerating medium inlet connected to the refrigerating medium outlet of the liquefier for feeding refrigerating medium liquefied in the liquefier into the heat exchanger, and a refrigerating medium outlet which opens into the receptacle of the accumulator vessel for discharging refrigerating medium from the heat exchanger into the receptacle of the accumulator vessel. | 06-27-2013 |
20130161450 | BOARDING AID - A computing unit allocates boarding paths, available for boarding a transport unit, in particular an aircraft, to passengers of the transport unit. An associated method allocates boarding paths, available for boarding the transport unit to passengers of the transport unit. A computer program carries out the method, and a directing system directs passengers of the transport unit along boarding paths available for boarding the transport unit. The computing unit is configured to form two or more changeable seat groups from a plurality of seats provided in the transport unit and to allocate the boarding paths, available for boarding the transport unit, to the two or more seat groups formed. | 06-27-2013 |
20130162831 | PASSENGER MONITORING AND DIRECTING SYSTEM FOR USE IN AN AIRCRAFT CABIN - A passenger monitoring and directing system for use in an aircraft cabin is provided. This system includes at least one information unit to be arranged in the aircraft cabin and at least one passenger monitoring device. The information unit includes at least one monitoring portion and the passenger monitoring device is assigned to the information unit and arranged relative to its monitoring portion in order to monitor the passengers through the monitoring portion of the information unit. | 06-27-2013 |
20130166063 | FULLY AUTOMATED CARGO LOADING SYSTEM - Systems and methods are provided for the loading and unloading of cargo in transport means. In one example, a cargo loading system having a fully automated conveyor system and a fully automated bolt system for locking the cargo unit is provided. Manual interventions of the loading personnel in the cargo space may not be necessary. | 06-27-2013 |
20130167817 | System For Contactless Power Transfer - A system for inductive contactless power transfer between a first vehicle part and at least one collector that can be variably positioned relative to the first vehicle part in a passenger cabin of a vehicle includes primary windings (P | 07-04-2013 |
20130168495 | NON-FOGGING VEHICLE WINDOW - A vehicle window with a primary window pane arrangement, a secondary window pane that is spaced apart from the primary window pane arrangement and a window funnel that extends between the secondary window pane and the primary window pane arrangement is provided. The vehicle window includes an intermediate space that is formed by the window funnel, the secondary window pane and the primary window pane arrangement, and the intermediate space is sealed and equipped with an air inlet for introducing dehumidified air into the intermediate space. Due to the seal, humid air leading to condensation and frost in the intermediate space is prevented from flowing into the intermediate space during a pressure compensation flow. The passenger comfort is enhanced due to the improved view through the window. | 07-04-2013 |
20130168496 | COVERING DEVICE AND AIRCRAFT AREA COMPRISING A COVERING DEVICE - A covering device includes a sealing element and a rib structure which is disposed on a surface of the sealing element. The rib structure includes a plurality of ribs which extend parallel to the surface of the sealing element, wherein the bendability of the ribs parallel to the surface of the sealing element is high, and perpendicular to the surface of the sealing element is low. | 07-04-2013 |
20130169130 | SEALING SYSTEM WITH A POSITIONING DEVICE - A sealing system for an aircraft device to be sealed off from the environment includes a door, which, when connected to the housing, is movable between an open position, in which the door clears a door aperture in the housing, and a closed position, in which the door closes the door aperture. The sealing system includes a sealing element, on which a sealing surface is formed, wherein the sealing surface is adapted to interact sealingly with a contact surface when the door is situated in its closed position. A positioning device is provided, which is adapted to move the door substantially at right angles to the sealing surface or to the contact surface between a first position, in which the sealing surface is not movable into sealing contact with the contact surface, and a second position, in which the sealing surface is movable into sealing contact with the contact surface. | 07-04-2013 |
20130170894 | Retaining device for a component of an aircraft or spacecraft - A retaining device for a component of an aircraft or spacecraft. The retaining device comprises a fuselage cell portion and a component portion, which portions are interconnected via at least one fastener. A gap is formed between the fastener and the component portion, of such a type that the fuselage cell portion and the component portion are movable relative to one another. | 07-04-2013 |
20130174917 | PRIORITY VALVE ASSEMBLY AND METHOD FOR OPERATING A PRIORITY VALVE ASSEMBLY - A priority valve assembly includes a fluid supply line, a first fluid discharge line, and a second fluid discharge line, both of which are to be supplied with fluid via the fluid supply line. A priority valve throttles a fluid flow from the fluid supply line into the second fluid discharge line to prioritise the supply of fluid to the first fluid discharge line over the supply of fluid to the second fluid discharge line if a control parameter which is characteristic for an inlet fluid pressure (p | 07-11-2013 |
20130175402 | AIR SUCKING VEHICLE FUSELAGE COMPONENT, METHOD FOR PRODUCING AN AIR SUCKING VEHICLE FUSELAGE COMPONENT AND A VEHICLE, ESPECIALLY AN AIRCRAFT, WITH AN AIR SUCKING VEHICLE FUSELAGE COMPONENT - An air-sucking vehicle fuselage component includes an outer delimitation part, and inner delimitation part, and connecting elements. The inner delimitation part is connected via the connecting elements to the outer delimitation part. The outer delimitation part includes a continuously curved shape. The inner delimitation part includes two or more flat delimitation part components, which are each connected to one another at one edge to form a connection edge, and the connection edge is configured to be attached to the outer delimitation part. A type of framework structure is thus provided, which causes increased stability and can split impacting objects in particular if two inner delimitation part components are used on the vehicle fuselage component. | 07-11-2013 |
20130175831 | PASSENGER SEAT WITH A LUGGAGE RECEIVING DEVICE - A passenger seat has a backrest and a seat which has first and second sections each having a first surface for a seat area and a second opposite surface. The second section pivots relative to the first section between a first position, in which the first surfaces of the first and second sections form a usable total seat area, and a second operational position, in which the second section is folded relative to the first section in the direction towards the backrest. Attached to the second seat section is a holder movable relative to the second surface of the second seat section between a first position, in which the holder extends substantially parallel to the second surface of the second seat section, and a second position, in which the holder extends at from 60° to 120° relative to the second surface of the second seat section. | 07-11-2013 |
20130181089 | ADJUSTMENT SYSTEM OF AN AEROPLANE WITH AN ADJUSTABLE FLAP - An adjustment system of an aeroplane, having: at least one adjustable flap on each of the wing of an aeroplane, adjustable with an adjustment device, a drive device for purposes of driving the adjustment devices, and a load sensor for purposes of recording the load occurring in the load path between the actuator and the adjustable flap of the respective adjustment device. The load sensor is embodied as a sensor for purposes of measuring the longitudinal force occurring in a drive rod along its longitudinal direction. | 07-18-2013 |
20130181374 | MOLDING TOOL AND METHOD FOR MANUFACTURING A FIBER REINFORCED PLASTIC AERODYNAMIC AIRCRAFT COMPONENT - A molding tool for manufacturing a fiber-reinforced plastic aerodynamic aircraft component, which aircraft component, in order to form several bays arranged on the inside and delimited by an outer skin and spars arranged spaced apart from each other, in each case includes a multi-part mold core that matches the shape of the respective bay, wherein to conform to local skin reinforcements and/or spar reinforcements that extend into at least one of the bays, the multi-part mold core includes four or five core parts, of which two core parts comprising a triangular cross section are arranged along opposing edges of the bay, which edges interact with two or three core parts that fill the space between the two triangular core parts, which space extends diagonally relative to the bay. | 07-18-2013 |
20130187009 | AIRCRAFT WITH WINGS AND A SYSTEM FOR MINIMIZING THE INFLUENCE OF UNSTEADY FLOW STATES - An aircraft (F) with wings ( | 07-25-2013 |
20130187661 | Test System for Plug-in Connectors, Aircraft or Spacecraft and Method - A test system for plug-in connectors, especially for plug-in connectors in an airplane. A transmitting device which is designed for sending out a test signal to the plug-in connectors to be tested, and comprising at least one receiving device for each plug-in connector to be tested which is electrically coupled with the respective plug-in connector and which is designed for receiving the transmitted test signal and outputting an acknowledgement signal in response to receiving the transmitted test signal. Furthermore, the present invention creates an aircraft or a spacecraft and a method. | 07-25-2013 |
20130198263 | SERVER SYSTEM, AIRCRAFT OR SPACECRAFT AND METHOD - The present invention provides a server system, in particular for an aircraft or spacecraft, comprising an integration device which has at least two server modules which have in each case at least one program-controlled arithmetic-logic means, at least one memory which is coupled with the program-controlled arithmetic-logic means, and at least one communication interface which is coupled with the program-controlled arithmetic-logic means, comprising at least one data line which interconnects the two server modules for data communication by the communication interfaces thereof, and comprising a server interface which is configured to connect the integration device to a data network for data communication by the communication interfaces of the server modules, the integration device being configured to exchange data with the data network. The present invention also provides an aircraft or spacecraft and a method. | 08-01-2013 |
20130199201 | MAIN ENGINE START BY MEANS OF AN AIRCRAFT AIR CONDITIONING SYSTEM - An air conditioning system in an aircraft is provided. The system comprises at least one air cycle air-conditioning pack with a compressor comprising a bleed air outlet and with a compressed-air line connected to the bleed air connection, which compressed-air line is connectable to a starter turbine for a main engine. With the use of air from a compressor of an air conditioning pack it is not necessary to switch off the air conditioning pack; bleed air removal from the auxiliary power units becomes obsolete; and, since there is no unnecessary discharge of compressed air from a bleed air system, noise pollution on the ground is reduced. | 08-08-2013 |
20130199218 | ICING PROTECTION SYSTEM FOR AN AIRCRAFT AND METHOD FOR OPERATING AN ICING PROTECTION SYSTEM - An icing protection system comprises a fuel cell, an evaporative cooling system, a thermal deicing device, a control unit and a device for measuring the pressure in the evaporative cooling system. The evaporative cooling system is in thermal contact with the fuel cell and with the thermal deicing device in order to conduct heat from the fuel cell to the thermal deicing device. The control unit controls the electrical power demanded from the evaporatively cooled fuel cell in dependence on a deviation of the pressure measured by the pressure measuring device from a predetermined NOMINAL pressure. In this way, an energetically very efficient and very well controllable icing protection system is made available that can be operated without bleed air supplied by engines or electrical energy provided by engine generators. | 08-08-2013 |
20130200213 | INTERIOR COMPONENT CARRIER SYSTEM, AIRCRAFT INTERIOR COMPONENT MODULE AND ASSEMBLY METHOD - An interior component carrier system for use in assembly of aircraft interior components in an aircraft includes a retaining system with at least one retaining element. A first connection device for connecting the retaining element to a first aircraft interior component and a second connection device are provided on the retaining element. On the retaining element a structural retainer is provided for fastening the retaining element to an aircraft structure. The interior component carrier system includes a hinge connectable to a second and a third aircraft interior component such that the third aircraft interior component is pivotable about a longitudinal axis of the hinge relative to the second aircraft interior component. The second connection device mounted on the retaining element is configured to be connected to the hinge and/or to a region of the second or third aircraft interior component, that is adjacent to the hinge. | 08-08-2013 |
20130200216 | SUPPLY SYSTEM FOR A MEANS OF A TRANSPORT, METHOD FOR PROVIDING AN INERT GAS AND ELECTRIC POWER, AIRCRAFT WITH SUCH A SUPPLY SYSTEM AND USE OF A FUEL CELL - The invention relates to a device for producing an inert gas that comprises a fuel tank for a fuel, at least one fuel cell with a cathode, an anode, a reactor for reforming fuel from the fuel tank into a hydrogenous fuel gas and an inert gas outlet. The reactor comprises a fuel gas outlet that is connected to a fuel gas inlet arranged on the anode of the fuel cell. The inert gas outlet is arranged downstream of the reactor and forms a fluid sink for non-hydrogenous reaction products of the reactor. | 08-08-2013 |
20130200652 | METHOD FOR INFILTRATING SILICONE INTO A FIBER COMPOSITE STRUCTURE AND DEVICE FOR EXECUTING A METHOD FOR PRODUCING A FIBER COMPOSITE WORKPIECE - The invention relates to a method for producing a fiber composite workpiece. In the method according to the invention, cross-linking silicone is used with the aid of a volatile diluent for infiltrating individual mats of a mat composite. A further object of the present invention is a device for performing the method according to the invention. | 08-08-2013 |
20130204470 | METHOD FOR PLANNING A LANDING APPROACH OF AN AIRCRAFT, COMPUTER PROGRAM PRODUCT, MEDIUM WITH A LANDING APPROACH PLAN STORED THEREON, AS WELL AS DEVICE FOR PLANNING A LANDING APPROACH - A method and computer program product for planning a landing approach of an aircraft based on an actual position or first nominal position of the aircraft during its approach for landing on a runway, including providing a stabilization flight path section and stabilization region and/or stabilization point defined by an altitude profile by at least one configuration change point in the stabilization flight path section with a change of the overall profile configuration of the airfoils and with a predetermined final approach flight status of the aircraft, and checking or changing position of the at least one configuration change measure in a change and/or the addition of an additional configuration change measure to the stabilization flight path section and by changing a speed profile along the stabilization flight path section so that the aircraft reaches the predetermined final approach flight status in the stabilization region or at the stabilization point. | 08-08-2013 |
20130206819 | PROCESS FOR CONNECTING TWO AIRCRAFT FUSELAGE SEGMENTS BY MEANS OF FRICTION TWIST WELDING - A process for connecting two aircraft fuselage segments and a reinforcing profile arranged in the joint region of the two aircraft fuselage segments by friction twist welding using a rotating tool, wherein a cover plate is brought onto the aircraft fuselage segments to be connected above the joint regions and after the friction twist welding the remainder of the cover plate is milled off. This makes it possible to overcome significantly greater gap tolerances in the edges to be connected so that the dimension tolerance requirements for the aircraft fuselage segments can be reduced. Furthermore, a smooth surface can be achieved in the welding region. | 08-15-2013 |