mhurhangee/ep-ind-claims huggingface dataset:
An article comprising a substrate having at least one main surface coated with a layer A having a refractive index lower than or equal to 1.50, wherein said layer A was obtained by deposition of activated species issued from at least one compound C in gaseous form, containing in its structure at least one Si-R group, where R is a fluoroalkyl group, at least one carbon atom, at least one hydrogen atom and optionally at least one nitrogen atom and/or at least one oxygen atom, the deposition of said layer A being carried out by applying a bombardment with an ion beam to layer A while layer A is being formed, and said layer A being not formed from inorganic precursor compounds. the deposition of said layer A being carried out by applying a bombardment with an ion beam to layer A while layer A is being formed, and said layer A being not formed from inorganic precursor compounds.
A system for radar-scanning a field of view, the system comprising: a signal generator that generates electromagnetic signals; a plurality of antennas (18A-18G) radially distributed about a rotatable turret, each of the plurality of antennas electrically connected to the signal generator so as to receive an electromagnetic signal that causes the antenna to direct an electromagnetic beam (24A-24G) along a principal direction (26A-26G) characterized by a rotational position θ to which the antenna is rotated by the rotatable turret and an azimuthal beam angle φ with respect to a rotational axis of the rotatable turret, the azimuthal beam angles (φA-φG) of the plurality of antennas being different from one another, each of the plurality of antennas sensing a reflected portion of the electromagnetic beam reflected from objects within the field of view upon to which the electromagnetic beam has been directed, wherein as the rotatable turret rotates about the rotational axis the principal directions sweep conical figures about the rotational axis, at least a portion of the conical figures intersecting the field of view; and an image processor that determines, based on the reflected portions of the electromagnetic beams sensed by the plurality of antennas, directions and/or ranges to and/or velocities of the objects within the field of view, wherein the rotatable turret is a nose-cone of a projectile or missile. a signal generator that generates electromagnetic signals; a plurality of antennas (18A-18G) radially distributed about a rotatable turret, each of the plurality of antennas electrically connected to the signal generator so as to receive an electromagnetic signal that causes the antenna to direct an electromagnetic beam (24A-24G) along a principal direction (26A-26G) characterized by a rotational position θ to which the antenna is rotated by the rotatable turret and an azimuthal beam angle φ with respect to a rotational axis of the rotatable turret, the azimuthal beam angles (φA-φG) of the plurality of antennas being different from one another, each of the plurality of antennas sensing a reflected portion of the electromagnetic beam reflected from objects within the field of view upon to which the electromagnetic beam has been directed, wherein as the rotatable turret rotates about the rotational axis the principal directions sweep conical figures about the rotational axis, at least a portion of the conical figures intersecting the field of view; and an image processor that determines, based on the reflected portions of the electromagnetic beams sensed by the plurality of antennas, directions and/or ranges to and/or velocities of the objects within the field of view, wherein the rotatable turret is a nose-cone of a projectile or missile.
Mooring plate for fish farm installations, comprising: a plate equipped with several connecting points for shackles connecting anchoring lines, frame lines, crow feet and the like, and a suspension point for connection to a buoy, wherein the plate comprises a number of load cells for registration of forces that act on the plate, the load cells are connected with a communication equipment (20;30) for sending of registered data to an external receiver, the connecting points for the shackles are placed radially and in a circular pattern on the plate, and the load cells are placed between an outer circumference of the plate and respective connecting points. a plate equipped with several connecting points for shackles connecting anchoring lines, frame lines, crow feet and the like, and a suspension point for connection to a buoy, wherein the plate comprises a number of load cells for registration of forces that act on the plate, the load cells are connected with a communication equipment (20;30) for sending of registered data to an external receiver, the connecting points for the shackles are placed radially and in a circular pattern on the plate, and the load cells are placed between an outer circumference of the plate and respective connecting points.
A method for operating a turboprop engine for an aircraft, the method comprising: controlling a propeller of the turboprop engine based on a selected one of a reference propeller rotational speed and a minimum propeller blade angle while the turboprop engine is running; detecting an inflight restart of the turboprop engine; and characterized in that it further comprises controlling the propeller during the inflight restart in accordance with at least one of a modified reference propeller rotational speed and a modified minimum propeller blade angle to maintain an actual propeller blade angle above an aerodynamic disking angle during the inflight restart. controlling a propeller of the turboprop engine based on a selected one of a reference propeller rotational speed and a minimum propeller blade angle while the turboprop engine is running; detecting an inflight restart of the turboprop engine; and characterized in that it further comprises controlling the propeller during the inflight restart in accordance with at least one of a modified reference propeller rotational speed and a modified minimum propeller blade angle to maintain an actual propeller blade angle above an aerodynamic disking angle during the inflight restart.
A cutting information determination method for determining information about how to cut a polarizer-containing long polarizing sheet material along its longitudinal direction so that a long strip-shaped polarizing sheet (SP1; SP2) with a predetermined cut width can be produced, comprising: a defect-detecting step (S101; S201; S301) of detecting information about the positions of defects in the polarizing sheet material characterized in that it further comprises: a defect-counting step of counting (S102; S202; 302) defects present in the longitudinal direction with respect to each of a plurality of points in a width direction perpendicular to the longitudinal direction, based on the information about the positions of the detected defects; and a cutting-position determining step of determining a cutting position in the width direction, at which the polarizing sheet material is to be cut along the longitudinal direction, based on the counted numbers of defects with respect to the plurality of points, and/or a cut-width determining step of determining a width into which the polarizing sheet material is to be cut along the longitudinal direction, based on the counted numbers of defects with respect to the plurality of points. a defect-detecting step (S101; S201; S301) of detecting information about the positions of defects in the polarizing sheet material characterized in that it further comprises: a defect-counting step of counting (S102; S202; 302) defects present in the longitudinal direction with respect to each of a plurality of points in a width direction perpendicular to the longitudinal direction, based on the information about the positions of the detected defects; and a cutting-position determining step of determining a cutting position in the width direction, at which the polarizing sheet material is to be cut along the longitudinal direction, based on the counted numbers of defects with respect to the plurality of points, and/or a defect-counting step of counting (S102; S202; 302) defects present in the longitudinal direction with respect to each of a plurality of points in a width direction perpendicular to the longitudinal direction, based on the information about the positions of the detected defects; and a cutting-position determining step of determining a cutting position in the width direction, at which the polarizing sheet material is to be cut along the longitudinal direction, based on the counted numbers of defects with respect to the plurality of points, and/or a cut-width determining step of determining a width into which the polarizing sheet material is to be cut along the longitudinal direction, based on the counted numbers of defects with respect to the plurality of points.
A communication system comprising: a third network node; a first means that is configured to operate a first network node on a first virtual machine (VNF 200A) and a second network node on a second virtual machine (VNF 200B), wherein the first network node is configured to communicate with the third network node via a first communication session; and a second means that is configured to: initiate a switchover of a communication session with the third network node from the first network node to the second network node; in response to completion of the switchover, forward a control signal indicating termination of the first communication session to the first virtual machine (VNF 200A) operating the first network node; and forward the control signal indicating the termination of the first communication session, from the first virtual machine (VNF 200A) operating the first network node to the second virtual machine (VNF 200B) operating the second network node. a third network node; a first means that is configured to operate a first network node on a first virtual machine (VNF 200A) and a second network node on a second virtual machine (VNF 200B), wherein the first network node is configured to communicate with the third network node via a first communication session; and a second means that is configured to: initiate a switchover of a communication session with the third network node from the first network node to the second network node; in response to completion of the switchover, forward a control signal indicating termination of the first communication session to the first virtual machine (VNF 200A) operating the first network node; and forward the control signal indicating the termination of the first communication session, from the first virtual machine (VNF 200A) operating the first network node to the second virtual machine (VNF 200B) operating the second network node. initiate a switchover of a communication session with the third network node from the first network node to the second network node; in response to completion of the switchover, forward a control signal indicating termination of the first communication session to the first virtual machine (VNF 200A) operating the first network node; and forward the control signal indicating the termination of the first communication session, from the first virtual machine (VNF 200A) operating the first network node to the second virtual machine (VNF 200B) operating the second network node.
A distance estimation device comprising: a first acquiring unit configured to acquire distances from a movable body at a first time and a second time to at least two ground objects, respectively; a second acquiring unit configured to acquire a distance between the at least two ground objects; a calculation unit configured to calculate a moving distance of the movable body from the first time to the second time based on results acquired by the first acquiring unit and the second acquiring unit; and characterized by a calibration unit configured to calculate a traveling speed of the movable body based on the moving distance, wherein the calculation unit makes a time interval from the first time to the second time shorter as the traveling speed of the movable body becomes higher. a first acquiring unit configured to acquire distances from a movable body at a first time and a second time to at least two ground objects, respectively; a second acquiring unit configured to acquire a distance between the at least two ground objects; a calculation unit configured to calculate a moving distance of the movable body from the first time to the second time based on results acquired by the first acquiring unit and the second acquiring unit; and characterized by a calibration unit configured to calculate a traveling speed of the movable body based on the moving distance, wherein the calculation unit makes a time interval from the first time to the second time shorter as the traveling speed of the movable body becomes higher.
Ascertainment device for non-destructive determination of material characteristics of an aircraft component, comprising - a data transmission means; and - an arithmetic-logic unit; wherein the data transmission means is configured to provide image data of a layer, which can be optically detected from outside, of a workpiece to be examined; the arithmetic-logic unit is configured to detect first areas having a first pixel characteristic and second areas having a second pixel characteristic using the image data; the first pixel characteristic being associated with a fibre inlay of a fibre - composite layer; and the second pixel characteristic being associated with a crystalline portion of an at least part-crystalline thermoplastic polymer of the fibre composite layer; and the arithmetic-logic unit is configured to determine a relationship of the first areas to the second areas. - a data transmission means; and - an arithmetic-logic unit;
A thin film photoelectric conversion device, comprising: a substrate; a transparent electrode layer; a photoelectric conversion unit; and a back electrode layer, wherein, the film thickness Zt of the transparent electrode layer is larger at a peripheral portion of the substrate and, along one line segment X in a parallel direction to a main surface of the substrate, decreases towards a central portion thereof and the film thickness Zs of the photoelectric conversion unit is smaller at the peripheral portion of the substrate and, along the line segment X, increases towards the central portion thereof, or the film thickness Zt of the transparent electrode layer is smaller at the peripheral portion of the substrate and, along the line segment X, increases towards the central portion thereof and the film thickness Zs of the photoelectric conversion unit is larger at the peripheral portion of the substrate and, along the line segment X, decreases towards the central portion thereof. a substrate; a transparent electrode layer; a photoelectric conversion unit; and a back electrode layer, wherein, the film thickness Zt of the transparent electrode layer is larger at a peripheral portion of the substrate and, along one line segment X in a parallel direction to a main surface of the substrate, decreases towards a central portion thereof and the film thickness Zs of the photoelectric conversion unit is smaller at the peripheral portion of the substrate and, along the line segment X, increases towards the central portion thereof, or the film thickness Zt of the transparent electrode layer is smaller at the peripheral portion of the substrate and, along the line segment X, increases towards the central portion thereof and the film thickness Zs of the photoelectric conversion unit is larger at the peripheral portion of the substrate and, along the line segment X, decreases towards the central portion thereof.
Method for hardening the surface layer of components, in particular turbomachine components, the component being heated and subjected to ultrasound, characterized in that - the component is heated in a pulsed manner, - the heating and subjection to ultrasound are carried out in a time-synchronized manner and - the component and a sonotrode, made at least in part of tungsten carbide, for subjecting the component to ultrasound are moved relative to one another during subjection. - the component is heated in a pulsed manner, - the heating and subjection to ultrasound are carried out in a time-synchronized manner and - the component and a sonotrode, made at least in part of tungsten carbide, for subjecting the component to ultrasound are moved relative to one another during subjection.
A compounder system for reconstituting, mixing, and delivering a drug from a vial to a receiving container, comprising: a cartridge having: a plurality of controllable fluid pathways fluidly coupled to at least one diluent port and a receiving container port (180, 4302, 7302); and a syringe pump and syringe valve apparatus having a plurality of syringes operable to control movement of one or more fluids through the plurality of controllable fluid pathways, the plurality of controllable fluid pathways being fluidly coupled to a waste port. a cartridge having: a plurality of controllable fluid pathways fluidly coupled to at least one diluent port and a receiving container port (180, 4302, 7302); and a plurality of controllable fluid pathways fluidly coupled to at least one diluent port and a receiving container port (180, 4302, 7302); and a syringe pump and syringe valve apparatus having a plurality of syringes operable to control movement of one or more fluids through the plurality of controllable fluid pathways, the plurality of controllable fluid pathways being fluidly coupled to a waste port.
An aircraft starting and generating system, comprising: a starter/generator that includes a main machine, an exciter, and a permanent magnet generator; and an inverter/converter/controller that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the starter/generator, the ICC including a contactor, characterised in that the exciter includes a stator and a rotor, and wherein the exciter stator includes a winding that is configured to work conjunctionally with the contactor to function as an AC winding during the start mode, and that is configured to work conjunctionally with the contactor as a DC winding during the generate mode. a starter/generator that includes a main machine, an exciter, and a permanent magnet generator; and an inverter/converter/controller that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the starter/generator, the ICC including a contactor, the exciter includes a stator and a rotor, and wherein the exciter stator includes a winding that is configured to work conjunctionally with the contactor to function as an AC winding during the start mode, and that is configured to work conjunctionally with the contactor as a DC winding during the generate mode.
A ventilation device, comprising a closed ventilation box which comprises an external air connection with an external air flap, an intake air connection with an intake air flap, an exhaust air connection with an exhaust air flap, and an outgoing air connection with an outgoing air flap, wherein an intake air unit is provided within the ventilation device, which intake air unit is arranged along the flow section of the intake air between the external air connection and the intake air connection, and an exhaust air unit is provided which is arranged along the flow section of the extracted air between the exhaust air connection and the outgoing air connection, characterized in that controllable circulation air flaps (14, 15) are provided within the ventilation device, which circulation air flaps connect the intake air unit to the exhaust air unit in the open position, and an ozonation module is provided within the ventilation device in the intake air or exhaust air unit.
A nebulizer comprising: a housing; an inlet disposed in the housing; a compressor disposed in the housing; a reservoir disposed in the housing and adapted to receive a quantity of medication; and a nozzle assembly disposed in the housing adjacent the reservoir and in selective fluid communication with the compression chamber, the nozzle assembly adapted to receive a flow of air from the compression chamber and utilize the flow to nebulize the quantity of medication, characterised in that the compressor comprises: a number of rotor members, each rotor member being rotatable about a respective axis, each respective axis being parallel with every other respective axis and spaced an equal distance (r) from a central axis of the compressor; a compression chamber having a variable volume defined by the relative positioning of the number of rotor members, the compression chamber being in selective fluid communication with the inlet; a motor having an output shaft operatively coupled to the number of rotor members in a manner such that rotation of the output shaft causes rotation of each rotor member of the number of rotor members, the motor being adapted to be coupled to a power source. a housing; an inlet disposed in the housing; a compressor disposed in the housing; a reservoir disposed in the housing and adapted to receive a quantity of medication; and a nozzle assembly disposed in the housing adjacent the reservoir and in selective fluid communication with the compression chamber, the nozzle assembly adapted to receive a flow of air from the compression chamber and utilize the flow to nebulize the quantity of medication, characterised in that the compressor comprises: a number of rotor members, each rotor member being rotatable about a respective axis, each respective axis being parallel with every other respective axis and spaced an equal distance (r) from a central axis of the compressor; a compression chamber having a variable volume defined by the relative positioning of the number of rotor members, the compression chamber being in selective fluid communication with the inlet; a motor having an output shaft operatively coupled to the number of rotor members in a manner such that rotation of the output shaft causes rotation of each rotor member of the number of rotor members, the motor being adapted to be coupled to a power source. a number of rotor members, each rotor member being rotatable about a respective axis, each respective axis being parallel with every other respective axis and spaced an equal distance (r) from a central axis of the compressor; a compression chamber having a variable volume defined by the relative positioning of the number of rotor members, the compression chamber being in selective fluid communication with the inlet; a motor having an output shaft operatively coupled to the number of rotor members in a manner such that rotation of the output shaft causes rotation of each rotor member of the number of rotor members, the motor being adapted to be coupled to a power source.
Sensor with a hybrid nanocomposite material, wherein said sensor comprises a sensor layer formed of a tertiary hybrid nanocomposite material, wherein the hybrid nanocomposite material consists of a polymer with high intrinsic conductivity, carbon nanotubes and graphene oxide, wherein the sensor is in the form of a meander antenna.