Patent application number | Description | Published |
20110127747 | Wheel suspension - The invention relates to a wheel suspension having a shock absorber ( | 06-02-2011 |
20140252730 | LATERALLY TILTABLE, MULTITRACK VEHICLE - A laterally tiltable, multitrack vehicle is disclosed. The vehicle includes a vehicle body and at least three wheels, with two of the wheels being assigned to a common axle to form a first wheel pair. A first wheel control part suspends the first wheel of the wheel pair from the vehicle body and a second wheel control part suspends the second wheel of the wheel pair from the vehicle body. The first wheel control part is configured to be coupled to the second wheel control part via a first gearwheel mechanism, and the second wheel control part is configured to be coupled to the first wheel control part via a second gearwheel mechanism. The first and second gearwheel mechanisms each have a negative transmission ratio between a drive shaft and an output shaft. The laterally tiltable, multitrack vehicle may be a motor vehicle. | 09-11-2014 |
20140252731 | LATERALLY TILTABLE, MULTITRACK VEHICLE - A laterally tiltable, multitrack vehicle is disclosed. The vehicle includes a vehicle body and at least three wheels, first and second wheels of the three wheels being assigned to a common axle to form a first wheel pair. The vehicle includes at least one wheel control part suspending each of the first and second wheels of the wheel pair from the vehicle body. At least one resilient element supports each wheel control part on the vehicle body. The resilient element has a non-linear spring characteristic with a spring rate which increases in a compression direction and decreases in a rebound direction. The vehicle may be a motor vehicle. | 09-11-2014 |
20140252732 | LATERALLY TILTABLE, MULTITRACK VEHICLE - A laterally tiltable, multitrack vehicle is disclosed. The vehicle includes a vehicle body and at least three wheels. The first and the second wheels are assigned to a common axle to form a first wheel pair. Each wheel of the wheel pair is rotatably mounted on a wheel support. The wheel supports of the wheel pair are connected to one another in an articulated manner via a double lever which is mounted rotatably at a first pivot point on the vehicle body. The wheel supports of the wheel pair also are connected to one another in an articulated manner via a parallel trailing arm, which runs parallel to the double lever and is configured to transmit lateral tilting of one wheel support to the other wheel support. Each wheel support of the wheel pair is configured to connect in a force-transmitting manner to the vehicle body via a link at at least one second pivot point which is spaced apart from the first pivot point for transmitting lateral tilting of the wheel support to the vehicle body, wherein the link forms an oblique angle with respect to the double lever. | 09-11-2014 |
20140252733 | LATERALLY TILTABLE, MULTITRACK VEHICLE - A laterally tiltable, multitrack vehicle is disclosed. The vehicle includes a vehicle body and at least three wheels. The first and second wheels are assigned to a common axle to form a first wheel pair. A first wheel control part suspends the first wheel of the wheel pair from the vehicle body and a second wheel control part suspends the second wheel of the wheel pair from the vehicle body. The first wheel control part is coupled to the second wheel control part via a double lever rotatably mounted on the vehicle body. At least two pivot points for the double lever can be defined on the vehicle body, the pivot points being spaced apart in a direction of a longitudinal extent of the double lever. | 09-11-2014 |
20140252734 | LATERALLY TILTABLE, MULTITRACK VEHICLE - A laterally tiltable, multitrack vehicle is disclosed. The vehicle includes a vehicle body and three wheels. The first and second wheels are assigned to a common axle to form a first wheel pair. A first cylinder unit supports the first wheel of the wheel pair on the vehicle body and a second cylinder unit supports the second wheel of the wheel pair on the vehicle body. Each cylinder unit includes a first cylinder and a second cylinder connected in series. Each first cylinder has a first diameter and each second cylinder has a second diameter larger than the first diameter. The first and second cylinder units are fluidly connected to each other. Fluid is transferable between cylinder units between a first cylinder of the one cylinder unit and a second cylinder of the other cylinder unit. | 09-11-2014 |
20140306412 | Articulated connection for transferring a steering movement onto a vehicle wheel - An articulated connection can be used to transfer a steering movement to a vehicle wheel. The articulated connection can include an axle journal and a steering arm. The axle journal can be configured to be coupled to the wheel. The steering arm can be configured to receive and transfer the steering movement to the axle journal. The steering arm can be bendable so as to elastically deflect with respect to the axle journal. The steering arm can be curved along a portion of its length and/or the articulated connection can include a limiting device. The limiting device can be configured to limit an amount of deflection of the steering arm in at least one direction. | 10-16-2014 |
Patent application number | Description | Published |
20100301167 | Holder System for Fastening an Aircraft Interior Component to a Transporting Apparatus and to an Aircraft Structure - A holder system for fastening an aircraft interior component to a transporting apparatus and to an aircraft structure includes an interior component holder configured to be connected to the interior component and which has a fastening device for fastening the interior component holder to the transporting apparatus. A structure holder is configured to be connected to the aircraft structure. A connecting element is fastened to the interior component holder and is configured to be connected to the structure holder in order to fasten the interior component to the aircraft structure. | 12-02-2010 |
20110138603 | PREASSEMBLY AND INTEGRATION OF AIRCRAFT CABINS - According to an exemplary embodiment of the invention, pre-assembly and integration of part of an aircraft cabin takes place outside the aircraft structure by means of an assembly device. After pre-assembly, the part of the aircraft cabin is slid into the open section of the aircraft structure where it is installed. | 06-16-2011 |
20120131779 | TRANSPORT DEVICE FOR USE WHEN MOUNTING INTERIOR COMPONENT MODULES IN AN AIRCRAFT - A transport device for use when mounting interior component modules in an aircraft includes an undercarriage and an interior component module carrier unit. The interior component module carrier unit is supported on the undercarriage and is adapted to be connected to an interior component module, which is preassembled outside of the aircraft, in order to transport the interior component module with the aid of the transport device into a final assembly position in an aircraft fuselage element. At least a part of the interior component module carrier unit is movable relative to the undercarriage such that an interior component module connected to the interior component module carrier unit is movable horizontally and vertically relative to the undercarriage. | 05-31-2012 |
20120137487 | METHOD AND SYSTEM FOR MOUNTING INTERIOR COMPONENTS IN AN AIRCRAFT - A method for mounting interior components in an aircraft includes premounting a first interior component and premounting a second interior component. At least one of the first and the second interior component is secured to a mounting device and the first and second interior components are connected to form an individual module. A plurality of individual modules secured to the mounting device are interconnected to form a large module which is secured to the mounting device. The large module is detached from the mounting device and transported to a final-mounting position in an aircraft fuselage element. The detached large module is then mounted in the aircraft fuselage element. | 06-07-2012 |
20130105638 | SUPPLY SYSTEM FOR SUPPLYING PASSENGERS IN A PASSENGER COMPARTMENT OF A VEHICLE | 05-02-2013 |
20130126673 | RAIL SYSTEM AND METHOD AND SYSTEM FOR MOUNTING A COMPONENT IN AN AIRCRAFT - A rail system for use when assembling a component in an aircraft comprises a first rail element having a securing device which is designed to be complementary to a first securing device provided in the region of a floor of an aircraft fuselage element and is adapted to cooperate with the first securing device in order to releasably secure the first rail element in the region of the floor of the aircraft fuselage element, wherein a section of the first rail element projects beyond an edge of the floor of the aircraft fuselage element in the connected state of the first rail element and the aircraft fuselage element. The first rail element furthermore comprises a guide device, which is designed to be complementary to a first guide device provided on an assembly aid, which is to be introduced into the aircraft fuselage element, and is adapted to cooperate with the first guide device to enable a guided displacement of the assembly aid to be introduced into the aircraft fuselage element relative to the rail system. The rail system furthermore comprises a second rail element having a securing device which is designed to be complementary to a second securing device provided in the region of the floor of the aircraft fuselage element and is adapted to cooperate with the second securing device in order to releasably secure the second rail element in the region of the floor of the aircraft fuselage element, wherein a section of the second rail element projects beyond an edge of the floor of the aircraft fuselage element in the connected state of the second rail element and the aircraft fuselage element. The second rail element furthermore comprises a guide device, which is designed to be complementary to a second guide device provided on an assembly aid, which is to be introduced into the aircraft fuselage element, and is adapted to cooperate with the second guide device to enable a guided displacement of the assembly aid to be introduced into the aircraft fuselage element relative to the rail system. | 05-23-2013 |
20130206710 | JIG FOR THE MODELLING OF AT LEAST ONE SECTION OF AN AIRCRAFT FUSELAGE - Disclosed is a jig for the modelling of at least one section of an aircraft fuselage, with a framework structure and with a multiplicity of adapters for the connection of stiffening elements to the framework structure, which can be moved relative to the framework structure, and/or with a multiplicity of adapters for the modelling of profiles of stiffening elements, which can be moved relative to the framework structure. | 08-15-2013 |
Patent application number | Description | Published |
20090135941 | Method for Digital Wireless Message Transmission Over a Broadband Mobile Radio Channel - In an OFDM multi carrier modulation method, M sub-carriers are used in a frequency band of a broadband mobile radio channel and several symbols are used in a time band. With application of a MIMO multi-antenna method with T transmitting antennae and R receiving antennae, for all sub-carriers and all symbols, a single, pre-determined, channel-matched transmission strategy is used, which is described by a maximum of T*R complex values on the signal side, independent of the species of the MIMO multi-antenna method and independent of the size of the frequency/time bands. | 05-28-2009 |
20090220027 | Method For Coding Data Symbols - Data symbols, transmitted by OFDM radio using at least two transmission antennae, are coded by a DSTBC coding and a DSTFBC coding. Two adjacent data symbols of a selected sub-carrier are provided for initializing a DSTFBC coding in a sub-carrier direction and are used for DSTFBC coding of similarly positioned data symbols in further sub-carriers in the sub-carrier. The DSTFBC coding is carried out from the data symbols of the first sub-carrier direction. In each sub-carrier the two data symbols formed by DSTFBC coding are used for initializing a DSTBC coding in the OFDM symbol direction. In the reverse direction, two sequential DSTBC coded data symbols on a first sub-carrier for initializing a DSTFBC coding in a sub-carrier direction and are used for DSTFBC coding of similarly positioned data symbols in further sub-carriers for DSTFBC coding from the data symbols of the first sub-carrier over the adjacent sub-carriers. | 09-03-2009 |
20090323606 | UNEQUAL ERROR PROTECTION FOR A MULTICARRIER TRANSMISSION - A method and apparatuses relate to data transmission between at least one first radio station and at least one second radio station in a radio communication system. At least one portion of an available spectrum is allocated for said at least one data transmission, the at least one portion including a number of adjacent sub-carriers; error protection is used for data transmission, wherein the error protecting is distributed in an unequal manner throughout the at least one portion allocated for the at least one data transmission. Data is transmitted upon completion of said error protection. | 12-31-2009 |
20100002575 | ADAPTIVE MODULATION AND CODING IN A SC-FDMA SYSTEM - A method and a system for transmitting data by a transmitter over a channel having a predetermined channel quality estimate, comprises the steps of splitting (S | 01-07-2010 |
Patent application number | Description | Published |
20100158700 | TURBINE BLADE ASSEMBLIES AND METHODS OF MANUFACTURING THE SAME - A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove. | 06-24-2010 |
20100254807 | TURBINE ROTOR SEAL PLATE WITH INTEGRAL FLOW DISCOURAGER - A seal plate for a turbine engine is provided. The turbine engine has a central axis. The seal plate comprises a forward face extending radially from the central axis. The forward face comprises a flat portion extending circumferentially around the central axis, and a front flow discourager coupled to the flat portion and extending outward from the flat portion. | 10-07-2010 |
20100284819 | TURBINE BLADES AND METHODS OF FORMING MODIFIED TURBINE BLADES AND TURBINE ROTORS - Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform. | 11-11-2010 |
20120093649 | TURBINE BLADES AND TURBINE ROTOR ASSEMBLIES - A turbine blade includes an airfoil defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root, and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the interior including an airfoil cooling circuit for directing airflow through the blade, and a platform supporting the airfoil and having a leading side edge, a trailing side edge, suction side edge, a pressure side edge, an airfoil-facing wall, and a root-facing wall, the platform including a platform cooling circuit having an inlet on the leading side edge and an outlet. The turbine blade may be included in a turbine rotor assembly. | 04-19-2012 |
20120148406 | TURBINE ROTOR DISKS AND TURBINE ASSEMBLIES - A turbine rotor disk is provided. The turbine rotor disk includes a hub, a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces, a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face, and a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface. | 06-14-2012 |
20130071254 | TURBINE BLADES AND METHODS OF FORMING MODIFIED TURBINE BLADES AND TURBINE ROTORS - Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform. | 03-21-2013 |
20130243606 | TURBINE BLADE TIP COOLING - A turbine blade includes a blade portion, the blade portion comprising a tip outer wall and a trailing edge, an internal cooling circuit, the internal cooling circuit being configured for directing cooling air within the blade portion, and a tip trailing edge slot positioned adjacent to the tip outer wall and the trailing edge, the tip trailing edge slot being fluidly connected to the internal cooling circuit. The tip outer wall is recessed at the tip trailing edge slot such that the tip outer wall is not provided over the trailing edge slot, thereby allowing cooling air to flow from the cooling circuit, into the trailing edge slot, and radially over the tip outer wall. | 09-19-2013 |
20140083116 | GAS TURBINE ENGINE COMPONENTS WITH BLADE TIP COOLING - A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit. | 03-27-2014 |
20150075178 | GAS TURBINE ENGINES WITH TURBINE ROTOR BLADES HAVING IMPROVED PLATFORM EDGES - A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion. | 03-19-2015 |
Patent application number | Description | Published |
20090196078 | Static converter - A static converter includes a current converter on the three-phase side and a current converter on the single-phase side, which are electrically conductively linked to one another on the DC voltage side, and which are respectively electrically conductively connected on the AC voltage side to a feeding three-phase network and a single-phase receiving network. According to an embodiment of the invention, one network-commutated current converter is provided as the current converter on the three-phase side, wherein the current converter on the single-phase side has two phase modules which are connected in parallel on the DC voltage side and whose current converter branches each have at least one two-pole subsystem. This results in a static converter which is simpler and costs less than a known static converter. | 08-06-2009 |
20110005879 | DEVICE FOR CONNECTING A SINGLE-PHASE SUPPLY LINE TO A THREE-PHASE POWER SUPPLY SYSTEM - A device for connecting at least one single-phase power supply line which, in particular, feeds the overhead line of a railroad track, to a three-phase power supply network. A primary side of a transformer is connected to the power supply network and a secondary side is connected to the single-phase power supply line and to a ground connection. A symmetry device is connected to a phase of the transformer, to the ground connection, and to the single-phase power supply line. | 01-13-2011 |
20110013441 | STATIC CONVERTER AND METHOD FOR STARTING UP THE CONVERTER - A static converter is disclosed. In at least one embodiment, the static converter includes a power converter circuit which has a plurality of interconnected module branches, wherein each module branch has one or more electrically series-connected two-pole submodules as switchable voltage sources which each include a capacitor as an energy store and power semiconductors as electronic switching elements. A device for precharging the capacitors is included, including at least one power electronics device for providing an adjustable precharge current. The at least one power electronics device, being supplied with power by an auxiliary supply system and being connected to a converter bridge via a precharge transformer, can be used to achieve a sufficiently high voltage level for the capacitors of the submodules when the converter is started up so as to achieve firstly the minimum voltage for supplying power to the power semiconductors and secondly the minimum voltage for synchronization to the systems. A method for starting up such a converter is also disclosed. | 01-20-2011 |