EUROCOPTER DEUTSCHLAND GMBH Patent applications |
Patent application number | Title | Published |
20140292556 | OBSTACLE AND TERRAIN WARNING RADAR SYSTEM FOR A ROTORCRAFT - Obstacle and terrain warning radar system ( | 10-02-2014 |
20140170417 | MULTI-LAYERED TRANSPARENCY AND METHOD OF PRODUCING SUCH A MULTI-LAYERED TRANSPARENCY - A multi-layered transparency ( | 06-19-2014 |
20140170373 | GRID TYPE ELEMENT OF OPEN POLYGONAL CELLS - A grid type element ( | 06-19-2014 |
20140170372 | GRID TYPE FIBER COMPOSITE STRUCTURE AND METHOD OF MANUFACTURING SUCH GRID TYPE STRUCTURE - The invention is related to a grid type fiber composite structure ( | 06-19-2014 |
20140158833 | AIR INLET COMBINING A FILTER AND A BYPASS DEVICE FOR USE WITH A TURBINE ENGINE - An air inlet ( | 06-12-2014 |
20140151494 | VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLE AND METHOD OF OPERATING SUCH A VTOL AERIAL VEHICLE - A Vertical Take-off and Landing (VTOL) aerial vehicle ( | 06-05-2014 |
20140140871 | POWER PLANT, AN APPLICATION OF SUCH A POWER PLANT AND A METHOD OF OPERATING SUCH A POWER PLANT - A mobile power plant having an engine together with a main gear box ( | 05-22-2014 |
20140132113 | ELECTRIC CIRCUIT WITH POWER AMPLIFIER FOR PIEZOELETRIC ACTUATORS - An electric circuit with one power amplifier (V | 05-15-2014 |
20140130985 | HEAT CONTROL SYSTEM FOR CONSOLIDATION ROLLER - A heat control system for an adaptive consolidation roller ( | 05-15-2014 |
20140112785 | SEPARABLE BLADE ATTACHMENT FOR A BEARINGLESS ROTOR OF A HELICOPTER - The invention relates to a separable blade attachment ( | 04-24-2014 |
20140070051 | EMPENNAGE OF A HELICOPTER - An empennage ( | 03-13-2014 |
20140061367 | COMPOUND HELICOPTER - The invention relates to a compound helicopter ( | 03-06-2014 |
20140061366 | COMPOUND HELICOPTER WITH TAIL BOOMS - The present invention is related to a compound helicopter ( | 03-06-2014 |
20130316131 | SKIN-STIFFENER TRANSITION ASSEMBLY, METHOD OF MANUFACTURE AND APPLICATION OF SAID SKIN-STIFFENER TRANSITION ASSEMBLY - A skin-stiffener transition assembly ( | 11-28-2013 |
20130315734 | AERODYNAMIC BLADE ATTACHMENT FOR A BEARINGLESS ROTOR OF A HELICOPTER - An aerodynamic blade attachment ( | 11-28-2013 |
20130280076 | AIRFOIL BLADE OF A BEARINGLESS ROTOR OF A HELICOPTER - An airfoil blade ( | 10-24-2013 |
20130280075 | BLADE ATTACHMENT FOR A BEARINGLESS ROTOR OF A HELICOPTER - A blade attachment ( | 10-24-2013 |
20130268154 | DETECTION SYSTEM FOR DETECTION OF DAMAGES ON ROTATING COMPONENTS OF COMPONENTS OF AIRCRAFT AND METHOD OF OPERATING SUCH A DETECTION SYSTEM - A detection system and method for detection of damages on at least one rotating component ( | 10-10-2013 |
20130265185 | PROXIMITY WARNING SYSTEM FOR HELICOPTERS - A proximity warning system for a helicopter ( | 10-10-2013 |
20130264423 | AIR VEHICLE WITH A SLIP PROTECTING AND GAS SEALING COMPOSITE FLOOR - An air vehicle with a slip protecting and gas sealing composite floor ( | 10-10-2013 |
20130264419 | LANDING GEAR VIBRATION ABSORBER AND METHOD OF OPERATING SAID LANDING GEAR VIBRATION ABSORBER - A landing gear vibration absorber ( | 10-10-2013 |
20130263728 | SHOCK AND IMPACT RESISTANT MULTILAYERED COMPOSITE AND METHOD FOR ITS FABRICATION - A shock and impact resistant multilayered composite comprising an outer shatter protection body, and at least one active body along side the shatter protection. At least one highly elastic and tearproof absorption/dissipation body is provided along side the at least one active body, said outer shatter protection body being cured to said at least one active body and said at least one active body being cured to said at least one absorption/dissipation body. The present invention relates as well to a method for fabrication of such a shock and impact resistant multilayered composite. | 10-10-2013 |
20130256458 | EMERGENCY OPENING SYSTEM OF AN AIRCRAFT CABIN DOOR - An emergency opening system ( | 10-03-2013 |
20130248650 | HELICOPTER SKID TYPE LANDING GEAR - A helicopter with a fuselage and a skid-type landing gear mounted to said fuselage. Said landing gear comprises pivotable cross beams and skids, said skids being each disposed in an essentially longitudinal direction laterally on a respective side of the helicopter's landing gear. At least one discrete damper is provided for at least one pivotable cross beam, said discrete damper being connected with one end to the pivotable cross beam and with another end to the fuselage. The pivotable cross beam are of the cantilever type. Fixed bearings and floating bearings are provided at the fuselage. Torsion bar springs are mounted to said fixed bearings and said floating bearings, said respective inner end of at least one pivotable cantilever cross beam being attached to said torsion bar spring at the floating bearing in such a manner that moments are transferred from the respective inner end of each pivotable cantilever cross beam via said torsion bar spring to the fuselage at said fixed bearing. | 09-26-2013 |
20130211630 | FORCE GENERATOR FOR MOUNTING ON A STRUCTURE - The invention relates to a force generator ( | 08-15-2013 |
20130171895 | COMPOSITE GUSSET FILLER AND METHOD OF MANUFACTURE OF SAID COMPOSITE GUSSET FILLER - A composite gusset filler ( | 07-04-2013 |
20130170985 | ELECTRICAL POWERED TAIL ROTOR OF A HELICOPTER - The invention is related to an electrical powered tail rotor ( | 07-04-2013 |
20130168501 | PRIMARY FLIGHT CONTROLS - Primary flight controls ( | 07-04-2013 |
20130147242 | DEVICE FOR PROTECTING AN INDIVIDUAL SITTING ON A SEAT, A SEAT, AND A VEHICLE - A protection device ( | 06-13-2013 |
20130147204 | Hybrid Drive And Energy System For Aircraft - A hybrid drive system for aircraft, in particular helicopters, with at least one energy generating module having an internal combustion engine and a generator that can be powered by the latter to generate electrical energy, and at least one electric motor for powering a drive means of the aircraft. | 06-13-2013 |
20130133465 | COUNTERBALANCED CONTROL STICK SYSTEM - A counterbalanced control stick system for a vehicle comprising: a shaft ( | 05-30-2013 |
20130119185 | DRIVE SYSTEM FOR HELICOPTERS - The rotors of a helicopter are directly connected with electric high-torque motors, and are powered by the latter. Energy generation and rotor drive are separate from each other. The high-torque motor of the main rotor is pivoted to the cabin canopy, so that it can be tilted together with the main rotor. | 05-16-2013 |
20130102431 | PLANETARY GEAR FOR VARIABLE TRANSMISSION - A planetary gear ( | 04-25-2013 |
20130034443 | PLANAR FLEXBEAM UNIT - A planar flexbeam unit ( | 02-07-2013 |
20130034442 | LEAD LAG DAMPER FOR HELICOPTER ROTOR UNIT - A lead lag damper ( | 02-07-2013 |
20130032661 | LOADS INTERFACE, PARTICULARLY A LOADS INTERFACE FOR A PLUG TYPE AIRCRAFT DOOR - A loads interface ( | 02-07-2013 |
20130032660 | LOADS INTERFACE, PARTICULARLY LOADS INTERFACE OF AN AIRCRAFT STRUCTURE AND APPLICATION OF SAID LOADS INTERFACE - A loads interface ( | 02-07-2013 |
20120323410 | FATIGUE MANAGEMENT SYSTEM - A fatigue management system for determining the individual life of an aircraft, particularly the individual life of components of a helicopter, by means of an on board virtual load sensor and a method of operating a fatigue management system. | 12-20-2012 |
20120316724 | NAVIGATION SYSTEM FOR AN AIRCRAFT AND METHOD OF OPERATING SUCH A NAVIGATION SYSTEM - The invention relates to an onboard navigation system for an aircraft ( | 12-13-2012 |
20120315431 | T-PROFILE JUNCTION OF COMPOSITE MATERIALS - A T-profile junction of composite materials with a T-profile ( | 12-13-2012 |
20120256042 | HELICOPTER WITH CYCLOIDAL ROTOR SYSTEM - The invention is related to a helicopter ( | 10-11-2012 |
20120251326 | NOISE AND PERFORMANCE IMPROVED ROTOR BLADE FOR A HELICOPTER - A noise reduced and performance improved rotor blade ( | 10-04-2012 |
20120241563 | EMERGENCY PILOTING BY MEANS OF A SERIES ACTUATOR FOR A MANUAL FLIGHT CONTROL SYSTEM IN AN AIRCRAFT - For emergency piloting of a manual flight control system ( | 09-27-2012 |
20120193471 | MODULAR ADAPTER PLATE SYSTEM - A modular adapter plate system ( | 08-02-2012 |
20120174699 | DEVICE FOR ADAPTIVE BALANCING OF ROTARY DEVICES - A rotary device associated with drive means. The rotary device comprises a shaft and/or a hub and balancing means for balancing its rotational motion. The balancing means has a hollow chamber surrounding the hub and a solid/fluidic material with thixotropic properties, which fills partly the hollow chamber. | 07-12-2012 |
20120156654 | SMOKE SIMULATOR SYSTEM FOR AIRCRAFT COCKPIT - A smoke simulator system ( | 06-21-2012 |
20120154178 | METHOD FOR PRESENTING SPATIAL ATTITUDE AND HEADING INFORMATION OF A VEHICLE - A method of presenting attitude and heading information of a vehicle on a display to a viewer inside the given vehicle, comprising the steps of: using a 2D display, using data provided by an inertial reference system, using a computer and graphical software for treating the data and defining graphical elements, depicting the graphical elements in 3D on the 2D display, and presenting the attitude and heading information on the 2D display by associating them to at least one graphical element. | 06-21-2012 |
20120153079 | ANCHORING ELEMENT AND MOORING DEVICE FOR AN AIRCRAFT - An anchoring element ( | 06-21-2012 |
20120134835 | CONNECTION MEANS - A connection means ( | 05-31-2012 |
20120116660 | WEIGHING SYSTEM AND METHODS OF OPERATING SUCH WEIGHING SYSTEM - A weighing system for detecting total weight, including optional external loads, and monitoring of center of gravity of a helicopter ( | 05-10-2012 |
20120087797 | ROTOR BLADE WITH CONTROL TUBE - A system comprising a rotor blade ( | 04-12-2012 |
20120085480 | APPARATUS AND PROCESS FOR AUTOMATIC, CONTINUOUS PRODUCTION OF PREFORMS - An apparatus and a process for automatic, continuous production of preforms from dry fabrics containing a thermoplastic binder element by feeding individual layers ( | 04-12-2012 |
20120085033 | EMERGENCY JETTISON WINDOW PANE AND ASSOCIATED EJECTION SYSTEM - The invention concerns an ejection system for a window pane or panel which is affixed to a frame structure with at least one clamping seal. The system has means for ejecting the panel or window pane from the clamping seal and (a) a frame part with a housing which surrounds the inner face of the window pane or panel along a peripheral path, wherein the housing has an open end facing the window pane or panel; (b) an inflatable seal arranged in the housing; (c) a pressure source which is joined to the inflatable seal; and (d) an emergency actuation means to release pressure from the gas pressure source. The released air or gas expands the inflatable seal which pushes the window pane or panel out of the clamping seal. | 04-12-2012 |
20120077013 | COMPOSITE ELEMENT MADE FROM A PREFORM - A composite element made from a preform of fiber-reinforced plastic material arranged around a core with a multi-layer thermoplastic foil between the preform and the core and a method for fabrication of such a composite element. At least one of the layers of said multi-layer thermoplastic foil has a different melting temperature from the melting temperature of at least one of the other layers. | 03-29-2012 |
20120072130 | METHOD OF MEASURING TORQUE AND TORQUE MEASURING SYSTEM FOR SAID METHOD - A method of measuring torque acting on a drive shaft ( | 03-22-2012 |
20120032832 | WIDE-BAND HIRF DETECTOR- AND ANALYSIS SYSTEM FOR AIRCRAFT - A method for detecting electromagnetic threats to an aircraft, wherein electromagnetic fields are measured, and in the case of an arising threat to the aircraft being detected, countermeasures are taken, characterized by the following steps: measuring the frequency and the amplitude of at least one electromagnetic field in the frequency range from 9 KHz to 40 GHz; analysing the measured results and determining the field intensity in relation to each measured frequency; comparing the field intensity in relation to each measured frequency with stored limiting values or qualification values, wherein the aircraft is qualified for field intensities that are lower than the limiting values; and providing the result in the form of a warning signal in the case of approaching or exceeding a limiting value. | 02-09-2012 |
20120032031 | CONTROL SYSTEM - The invention relates to a control system and to a method of operating such a control system, particularly to a control system for pilot command inputs for a helicopter, with a mechanical input signal ( | 02-09-2012 |
20120032028 | ACTUATING MECHANISM FOR A VENT DOOR - An actuating mechanism ( | 02-09-2012 |
20120025022 | FUSELAGE STRUCTURE MADE OF COMPOSITE MATERIAL - A fuselage structure, particularly an aircraft door ( | 02-02-2012 |
20110272524 | INTEGRATED MAINTENANCE STEP ON HELICOPTER FUSELAGE - Maintenance steps on helicopters ( | 11-10-2011 |
20110266104 | DEVICE AND PROCESS FOR OSCILLATION INSULATION IN A TRANSMISSION PATH - Device and process for oscillation insulation in a transmission path. The device includes a first body structured and arranged to undergo an oscillation movement, at least one rigid connection element, a second body connected to the first body via the at least one rigid connection element, and an actuator device attached to the at least one connection element. A sensor unit is arranged in an interface area of the at least one connection element, and a regulator unit, connected to the sensor unit, is arranged to control the actuator device to perform an elastic deformation equivalent to an oscillation movement of the first body. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way. | 11-03-2011 |
20110253299 | MANUFACTURING METHOD FOR HOLLOW COMPONENTS MADE OF FIBER COMPOSITE MATERIALS IN TUBULAR DESIGN, TUBULAR FILM AND MANUFACTURING METHOD FOR A TUBULAR FILM - The invention relates to a manufacturing method for hollow components using a tubular film ( | 10-20-2011 |
20110236861 | FLIGHT SIMULATOR VIBRATION SYSTEM - The invention relates to a flight simulator vibration system, particularly to a crew seat ( | 09-29-2011 |
20110236670 | REINFORCED COMPOSITE PART COMPOSED OF AN ASSEMBLY OF AT LEAST TWO DIFFERENT COMPOSITE MEMBERS - The present invention concerns an intermediate reinforced composite part composed of an assembly of at least two composite members ( | 09-29-2011 |
20110233323 | SKID-TYPE LANDING GEAR FOR A HELICOPTER - The invention relates to a skid-type landing gear ( | 09-29-2011 |
20110208373 | SYSTEM FOR CONTROL OF UNMANNED AERIAL VEHICLES | 08-25-2011 |
20110199661 | COCKPIT FOR AN AIRCRAFT - The invention relates to a cockpit for an aircraft, particularly for a helicopter, with transparent extensions ( | 08-18-2011 |
20110196551 | SYSTEM AND METHOD FOR SITUATION SPECIFIC GENERATION AND ASSESSMENT OF RISK PROFILES AND START OF SUITABLE ACTION FOR PROTECTION OF VEHICLES - The present invention relates to a vehicle system ( | 08-11-2011 |
20110194372 | METHOD FOR PREPARING A COMPOSITE MATERIAL OF MULTI COMPONENTS - The invention relates to a method for preparing a composite material of more than one component with the steps of providing at least two resin components (K | 08-11-2011 |
20110190963 | METHOD AND SYSTEM FOR AN OPTIMIZED UTILIZATION OF ENERGY RESOURCES OF AN ELECTRICAL SYSTEM - A method for optimized utilization of available energy resources/sources ( | 08-04-2011 |
20110174426 | METHOD OF FABRICATING A PART OUT OF REINFORCED COMPOSITE MATERIAL, AND A METHOD OF REPAIRING SUCH A PART - The present invention relates to a method of fabricating a composite part presenting an integral structure of composite material comprising at least one reinforcing layer based on reinforcing fibers, fabrics, or textiles, and at least one impregnation matrix, the method consisting in assembling the integral structure, in placing said integral structure in a mold, in impregnating said integral structure with the impregnation matrix by injection or infusion, and in solidifying said impregnated integral structure by raising it to a determined temperature, the method being characterized in that it consists in: using at least two distinct primary parts for making up the integral structure; placing a thermoplastic sheet on at least one of the primary parts so as to make the interface between said primary parts once they are assembled together. | 07-21-2011 |
20110171337 | CONTROLLED CIRCUMFERENTIAL IMPREGNATION DEVICE - The present invention relates to a device for molding by impregnation of at least one reinforcing layer constituting a piece to be molded or at least one reinforcing layer covering a piece, with a resin in liquid form, said device comprising a mold extending around the reinforcing layer by defining a resin circulation space, an end piece for supplying resin in the circulation space, an end piece for evacuating the surplus resin as well as means for generating a flow of resin in the circulation space. | 07-14-2011 |
20110151179 | SEMI-FINISHED PRODUCT AND PREFORM USED TO MANUFACTURE A PART MADE FROM COMPOSITE MATERIAL - A semi-finished product used to mold a composite part including at least one dry laminar reinforcing layer that is designed to be impregnated with an impregnation matrix by liquid injection/infusion. The semi-finished product includes a thermoplastic layer, at least locally, where the properties of the component materials provide the future molded part, at least locally, with the required properties; since the thermoplastic layer has been stitched to at least one reinforcing layer using at least one yarn crossing through the perforations in said thermoplastic layer and in at least one reinforcing layer. | 06-23-2011 |
20110148254 | APPARATUS FOR PRODUCING A HOLDING FRAME OR A TRANSMISSION FRAME FOR A STACKED PIEZOACTUATOR AND ELECTROSTRICTIVE DRIVE WITH A FRAME OF SAID TYPE - An apparatus for producing a holding or transmission frame ( | 06-23-2011 |
20110147564 | METHOD OF FABRICATING AN IMPROVED MOLD CORE AND A MOLD CORE OBTAINED BY SAID METHOD - The present invention relates to a method of fabricating a mold core ( | 06-23-2011 |
20110147525 | SEALING OF AIRFLOW BETWEEN A WING AND A FUSELAGE - A sealing ( | 06-23-2011 |
20110147328 | LIFTING DEVICE FOR REPLACING DYNAMIC OR STATIC COMPONENTS OF HELICOPTER-TYPE AIRCRAFT - The present invention concerns a lifting device for replacing dynamic or static components of helicopter-type rotary wing aircraft. The device in one embodiment comprises a lifting means to move components between an installation/removal position and a loading/unloading position located near the aircraft, a supporting structure on which the lifting means is mounted, and support means rigidly attached to the supporting structure. The support means can rest on and be directly secured to the airframe of the aircraft. | 06-23-2011 |
20110131986 | DEVICE FOR OPENING A PASSENGER DOOR IN CASE OF EMERGENCY - The invention relates to a device for opening a passenger door ( | 06-09-2011 |
20110078996 | FIBER CABLE MADE OF HIGH-STRENGTH SYNTHETIC FIBERS FOR A HELICOPTER RESCUE WINCH - A fiber cable for helicopter rescue winches includes a plurality of load-bearing synthetic-fiber strands braided with one another, at least one electrically conductive insert, and a wear indicator providing a visual check of a state of the fiber cable, where the load-bearing synthetic-fiber strands are encased in a radial direction by a friction-reducing stable fiber layer, an inner cable jacket, and outer cable jacket. | 04-07-2011 |
20110049293 | RETRACTABLE UNDERCARRIAGE FOR AN AIRCRAFT - An undercarriage for a rotary wing aircraft, includes a tubular structure ( | 03-03-2011 |
20110001003 | FILTERING DEVICE WITH INTEGRATED BYPASS FOR AN AIR INLET - A filtering device for an engine or a for power unit with a radial air intake, includes a ring-shaped filter for covering the radial air intake, characterised in that the ring-shaped filter includes a first fixed part and a second mobile part which is movable with respect to the first fixed part through actuator elements, from a filtering position in which the whole radial air intake is covered by the ring-shaped filter, to a bypass position in which the second mobile part uncovers at least partly the radial air intake. | 01-06-2011 |
20100323150 | METHOD FOR PRODUCING A SANDWICH COMPONENT HAVING A HONEYCOMB CORE - A method of producing composite components having a honeycomb core ( | 12-23-2010 |
20100320642 | APPARATUS AND METHOD FOR TAKING UP, POSITIONING AND DRAPING DRY TEXTILE FIBER SEMI-FINISHED PRODUCTS - The invention relates to an apparatus ( | 12-23-2010 |
20100307661 | METHOD FOR PRODUCING A CONTINUOUS, THREE-DIMENSIONAL, CLOSED SEMI-FINISHED PRODUCT MADE OF FIBER COMPOSITE - A method for producing a continuous, three-dimensional, closed semi-finished product made of fibre composite from at least one planar, flat fibrous preform. The method is characterized in that the flat fibrous preform is initially placed flat and aligned to produce a load-bearing fibre orientation and subsequently formed into a three-dimensional structure. In a final step, the three-dimensional structure is then closed to form a closed semi-finished product. | 12-09-2010 |
20100288430 | METHOD AND MOULD TOOL FOR PRODUCING A COMPONENT MADE OF FIBRE-REINFORCED PLASTIC - A method for producing a component made of fibre-reinforced plastic by impregnating a fibre mould-blank ( | 11-18-2010 |
20100278655 | ROTOR BLADE MADE OF A FIBRE-REINFORCED COMPOSITE MATERIAL AND PRODUCTION METHOD FOR IT - A rotor blade in a fibre-reinforced composite design for a tail rotor of a rotary wing aircraft (helicopter), with a blade section ( | 11-04-2010 |
20100278649 | ROTOR WING WITH INTEGRATED TENSION-TORQUE-TRANSMISSION ELEMENT AND METHOD FOR ITS PRODUCTION - A rotor wing in a fibre-reinforced composite design including fibre layers, in particular for a tail rotor of a rotary wing aircraft, with a rotor blade ( | 11-04-2010 |
20100278648 | TENSION-TORQUE-TRANSMISSION ELEMENT FOR A FENESTRON BLADE AND METHOD FOR PRODUCING IT - A tension-torque-transmission element ( | 11-04-2010 |
20100181415 | ROTOR BLADE FOR A ROTARY WING AIRCRAFT - The invention relates to a rotor blade ( | 07-22-2010 |
20100181010 | METHOD FOR PRODUCING CONSTRUCTION ELEMENTS OF FIBRE-REINFORCED PLASTIC MATERIALS - A method for the production of a textile semifinished product consisting of a fibre nonwoven fabric for use as a preform for the production of components composed of fibre-reinforced plastic, in which the fibres are converted by laying/assembling/draping into a fibre nonwoven fabric in the shape of a band corresponding to the power absorptions of the respective component to be generated, being provided with required UD fibre portions and/or thermoplastic fibres and furthermore the fibre architecture of the band is permanently fixed by pre-defined seams. | 07-22-2010 |
20100178167 | METHOD AND DEVICE FOR CONTROLLING A ROTARY WING AIRCRAFT - The invention relates to a method for controlling a rotary wing aircraft with at least one main rotor, comprising a rotor head and rotor blades ( | 07-15-2010 |
20100123045 | DEVICE FOR SWITCHABLE PILOT CONTROL FORCES - A device for controlling vehicles having a manual control unit configured to influence the direction of movement of a vehicle. The manual control unit provides, in a neutral position of the manual control unit, a trim point to determine a preferred direction of movement. The device further includes a force generating device, generating at least one force acting in the direction of the neutral position of the manual control unit; a trim coupling operable to reduce the at least one force acting on the manual control unit; and a trim control unit configured to store and retain the trim point existing prior to an operation of the trim coupling. | 05-20-2010 |
20100114504 | PROCESS FOR CONTACT-FREE DETERMINATION OF FORCES AND/OR TORQUE ACTING ON A HOLLOW-CYLINDRICAL BODY AS WELL AS A MEASUREMENT ARRANGEMENT FOR IMPLEMENTING THE PROCESS - A method and a device for contactless determination of forces and/or moments acting on a hollow cylindrical body ( | 05-06-2010 |
20100109346 | Stop armature for aircraft doors - The invention relates to a stop armature of an armature system of an aircraft door with a fuselage stop armature ( | 05-06-2010 |
20100092707 | METHOD FOR MANUFACTURING A HOLLOW FIBRE COMPOSITE COMPONENT AND INTERMEDIATE PRODUCTS FOR THE MANUFACTURE - A three-dimensional hollow fiber component includes a first sheet having first; second, third, fourth and fifth consecutive adjacent sheet sections, the first and fifth sections being end sections, the sheet shaped so as to surround a first chamber such that the first and fifth sections overlap to form a top wall of the first chamber and are stitched to each other by at least one seam and a second sheet having first, second, third, fourth and fifth adjacent consecutive sheet section, the first and fifth sections being end sections, the sheet sections shaped so as to surround a second chamber such that the first and fifth sections overlap to form a top wall of the second chamber and are stitched to each other by at least one seam. | 04-15-2010 |
20100090067 | AERODYNAMIC PROFILE WITH A REVERSIBLY DEFORMABLE CONTOUR FOR AIRCRAFT, IN PARTICULAR FOR ROTARY WING AIRCRAFT - An aerodynamic profile ( | 04-15-2010 |
20100090062 | DRILL-ELASTIC AND FLEXURALLY RIGID ROD ELEMENT FOR THE SUPPORT AND GUIDANCE OF A MOVABLE FLAP RELATIVE TO A WING OF AN AIRCRAFT - A drill-elastic and flexurally rigid rod element ( | 04-15-2010 |
20100067735 | DEVICE AND METHOD FOR TESTING SYSTEMS WITH VISUAL OUTPUT - The invention relates to a device and a method for testing systems or devices with visual output and at least one mechanical input element. The device comprises an input unit for the automated mechanical actuation of the at least one input element of the device, an image analysis unit, which acquires and analyzes the visual output of the device, and a control unit, which controls the input unit and image analysis unit, and automatically determines a test result based on predetermined desired outputs and the findings of the image analysis unit. | 03-18-2010 |
20100065139 | DEVICE FOR FEEDING COMBUSTION AIR TO AN ENGINE OF AN AIRCRAFT - A device for feeding combustion air to an engine disposed in an interior of an aircraft is comprised of an air inlet duct extending between an exterior surface of the aircraft and the engine, wherein the air inlet duct extends from air inlets disposed in a first region of the exterior surface; at least one further air inlet duct extending between a second region of the exterior surface and the engine, so as to provide a two-way airstream supply; and a control device configured to switch the air supply to the engine to the at least one further air inlet duct when a blockage occurs in the air inlets. | 03-18-2010 |
20100064741 | LOCKING DEVICE FOR SLIDING DOORS OF AIRCRAFT, ESPECIALLY OF HELICOPTERS - A locking device having a door catch system for helicopter doors, which are embodied as sliding doors, which are to be additionally moved (flush-fitted) into the closed position at right angles to the plane of the door opening in response to their closing movement, consisting of a catch ( | 03-18-2010 |
20100064740 | DOOR LOCK FOR DOORS OF AIRCRAFT, ESPECIALLY OF HELICOPTERS - A door lock includes a door catch system for double door-type helicopter doors that can, when being closed, additionally be displaced perpendicularly to the plane of the door opening into the closed position (flush fitting). The door lock includes a catch element ( | 03-18-2010 |
20100052480 | METHOD FOR PRODUCING A HOLDING FRAME OR A TRANSMISSION FRAME FOR A STACKED PIEZOACTUATOR AND ELECTROSTRICTIVE DRIVE WITH A FRAME OF SAID TYPE - The invention relates to a method for producing a holding or transmission frame ( | 03-04-2010 |
20100040886 | GRANULATION AND STABILIZATION OF RESIN SYSTEMS FOR USE IN THE PRODUCTION OF FIBER COMPOSITE COMPONENTS - This invention relates quite in general to production of fiber composite components by infiltration of a fiber material with a synthetic resin and subsequent curing. In order to improve the required preparation of a liquid or viscous resin system, as claimed in the invention especially a synthetic resin granulate ( | 02-18-2010 |
20100015435 | Fiber-reinforced component fabrication with mold cores - A method of fabricating components ( | 01-21-2010 |
20090281684 | FLIGHT GUIDANCE AND NAVIGATION DISPLAY FOR A HELICOPTER - A flight guidance and navigation display ( | 11-12-2009 |
20090277995 | SUPPORTING STRUT FOR SUPPORTING AN INTERMEDIATE DECK THAT IS ARRANGED IN AN AIRCRAFT FUSELAGE, AND METHOD FOR PRODUCING A ROD BODY FOR SUCH A SUPPORTING STRUT - A supporting strut for supporting an intermediate deck ( | 11-12-2009 |
20090277991 | HELICOPTER HAVING MEANS FOR THE AERODYNAMIC SUPPORT OF THE TORQUE EQUALIZATION - A helicopter has at least one main rotor ( | 11-12-2009 |
20090277568 | METHOD FOR MANUFACTURING A HOLLOW FIBER COMPOSITE COMPONENT AND INTERMEDIATE PRODUCTS FOR THE MANUFACTURE - An intermediate product for the manufacture of a hollow fiber-composite component having a shape and dimensions, includes a three-dimensional, hollow preform of reinforcing fiber material corresponding to the shape and the dimensions with a three-dimensional reinforcing fiber structure which is formed from at least one planar, single- or multi-layer blank of two-dimensional, web-like reinforcing fiber material matching the dimensions, and a closable total cross-sectional profile with at least two hollow chambers located adjacent to each other and separated from each other by a rib-like partition. The partition is formed by an overlap region of the at least one blank which is stitched in two dimensions by a compacting seam which fixes the shape and dimensions of the rib-like partition as well as its position relative to adjacent regions of the blank and prefixes, precompacts and reinforces the reinforcing fiber material in the region of the partition. In addition, a method for the manufacture of a hollow fiber-composite component by means of such an intermediate product. | 11-12-2009 |
20090269198 | ROTOR BLADE FOR A ROTARY WING AIRCRAFT - A rotor blade including a rotor blade profile including a profile tip region, a profile trailing edge region including a trailing edge and a profile body having a profile core. A covering skin including an upper skin and a lower skin encase the profile core. A reversibly bendable flexural actuator including a first actuator end disposed at the trailing edge region of the rotor blade profile and a second actuator end projecting past the profile body toward the trailing edge. The second actuator end forms part of the trailing edge region and forms a movable rotor blade flap, the movable rotor blade flap being deformable into an arc-shaped rotor blade flap deflection upon a bending of the flexural actuator. | 10-29-2009 |
20090189023 | AERODYNAMIC HIGH-PERFORMANCE PROFILE FOR AIRCRAFT - Aerodynamic high-performance profile ( | 07-30-2009 |
20090169381 | ROTOR BLADE FOR A ROTOR AIRPLANE - A rotor blade comprises an inner rotor blade root area, a rotor blade main area disposed adjacent to the inner rotor blade root area along a length of the rotor blade and having an aerodynamically effective rotor blade profile, the profile including a nose area and a rear edge area, and a rotor blade tip disposed adjacent to the rotor blade main area along the length of the rotor blade. The rotor blade tip is configured to be deformable relative to the rotor blade main area and is operatively connected to a first actuator device. The first actuator device is configured to initiate a vertical movement of the rotor blade tip upwards or downwards relative to the lift direction. The vertical movement starts from a neutral position relative to the rotor blade main area. | 07-02-2009 |
20090108551 | TRANSPORT WHEEL FOR A HELICOPTER - A transport wheel device for a helicopter having a runner defining an axial direction. The transport wheel includes a holding frame, a wheel axle, a slide, a wheel and a lifting device. The holding frame is detachably securable to the runner. The wheel axle is attached the holding frame by the slide. The slide is continuously adjustable axially with respect to the holding frame and securable in an axial position. A wheel is disposed on the wheel axle. The lifting device is coupled to the holding frame and the wheel axle. The lifting device is configured to vertically move the transport wheel. | 04-30-2009 |
20090078922 | FIBER CABLE MADE OF HIGH-STRENGTH SYNTHETIC FIBERS FOR A HELICOPTER RESCUE WINCH - A fiber cable for helicopter rescue winches includes a plurality of load-bearing synthetic-fiber strands braided with one another, at least one electrically conductive insert, and a wear indicator providing a visual check of a state of the fiber cable. | 03-26-2009 |
20090078826 | AIRCRAFT PRESSURIZED CABIN DOOR MADE OF FIBER COMPOSITE - An aircraft pressurized cabin door includes an integral door structure unit made of fiber composite, the unit including an outer skin and a door framework arranged on an inner side of the outer skin. The framework includes a plurality of edge supports and a plurality of longitudinal supports extending in a width direction between the edge supports so as to form door framework interstices delimited by the inner side of the outer skin, by the edge supports and by the longitudinal supports. The door framework interstices are configured in a manner open toward the inner side of the door. | 03-26-2009 |
20090072089 | AIRCRAFT DOOR ASSEMBLY, AND AIRCRAFT FUSELAGE COMPRISING SUCH AN AIRCRAFT DOOR ASSEMBLY - An aircraft door assembly of an aircraft, having a fuselage with a door opening and a door frame, encompassing an aircraft door fittable in the door frame. The door includes a door structure having an outer skin and is liftable from a locked closed position into a unlocked closed position, pivotable into an open position located outside the door frame and outside the fuselage, pivotable from the open position back into the unlocked closed position, and lowerable into the locked closed position such that in the locked closed position, a door gap is present between the door frame and a door edge. The gap defines a space for lifting and lowering the door. The door also includes, on its outer side and on a door edge region, a door gap covering element that extends over the door gap onto the outer side of the aircraft fuselage and covers the door gap, when the door is in the locked closed position. The door gap covering element is fastened onto the door structure and is movable relative to the outer side of the outer skin. | 03-19-2009 |
20080315725 | Force Generator - A force generator is configured for attachment to a structure in order to controllably introduce vibrational forces into the structure in order to influence the vibration thereof. The force generator encompasses a flexural arm that is fastenable at least at one end to the structure; and an inertial mass that is coupled to the flexural arm remotely from the fastening end of the flexural arm; the flexural arm being equipped with at least one electromagnetic transducer, and a driving system being provided for the transducer, which system is set up such that by driving the transducer, it warps the flexural arm with the inertial mass and the transducer, and thereby displaces the inertial mass, in such a way that vibrational forces of variable amplitude, phase, and frequency are introducible into the structure. | 12-25-2008 |
20080295755 | Method for Production of a Three-Dimensional Curved Fiber Composite Material Structural Component - A method for producing a three-dimensionally curved fiber composite material structural component having a predefined flexural member profile cross section with at least one web area and at least one adjacent flange area, includes providing a flat base fiber laid scrim and disposing a unidirectional fiber laid scrim tape with 0° fibers on a partial area of the fiber laid scrim and fixed by sewing so as to provide a flat prefabricated fiber laid scrim strip having a flange strip area including the unidirectional fiber laid scrim tape and a web strip area free of the fiber laid scrim tape. The prefabricated fiber laid scrim strip is draped to a desired contour, wherein the flange strip area is disposed at an angle of a working plane with respect to web strip area and is curved monoaxially around at least one axis of curvature extending perpendicular to the 0° fibers and parallel to a tape plane of the fiber tape and the web strip area of the fiber laid scrim strip is draped essentially only in the working plane so that the fiber arrangement of the web strip area is distorted. The scrim strip is sewed onto a support material so as to provide a stabilized three-dimensionally curved first sub-fiber laid scrim preform adapted to the fiber composite material structural component to be produced. | 12-04-2008 |
20080277213 | ROTOR BRAKE FOR A ROTARY-WING AIRCRAFT - A rotor brake for a rotary-wing aircraft includes a rotor shaft, a braking-force actuator configured to be hydraulically actuated, a braking-force pick-up element connected to the rotor shaft and operationally connected to the braking-force actuator, an electromechanical piston control element, and a first hydraulic line connecting the electromechanical piston control element to the braking-force actuator so that the braking-force actuator can be actuated electrohydraulically by the electromechanical piston control element. | 11-13-2008 |