mhurhangee/patent-ind-claim-en huggingface dataset:
A method implemented by a network node, for transmitting synchronization sequences, comprised ina synchronization signal, in a beam sweap to one or more wireless devices, the method comprising: determining multiple synchronization sequences, such that each synchronization sequence comprises a respective timing indication from which a timing of a forthcoming transmission event is derivable, wherein the forthcoming transmission event is a reserved time slot where a wireless device is allowed to transmit, wherein the reserved time slot is a random access window; and transmitting each beam, comprising the synchronization sequences, to the one or more wireless devices, at a different point in time, wherein the synchronization sequences is repeated in each of the transmitted beams. determining multiple synchronization sequences, such that each synchronization sequence comprises a respective timing indication from which a timing of a forthcoming transmission event is derivable, wherein the forthcoming transmission event is a reserved time slot where a wireless device is allowed to transmit, wherein the reserved time slot is a random access window; and transmitting each beam, comprising the synchronization sequences, to the one or more wireless devices, at a different point in time, wherein the synchronization sequences is repeated in each of the transmitted beams.
A robot arm configured to passively conform to a plurality of irregular articles comprising a manipulator movable with the robot arm with a plurality of dual acting cylinders attached to the manipulator , each of the dual acting cylinders having a front chamber and a rear chamber and each having a vacuum cup movable as the dual acting cylinder extends and retracts, each of the vacuum cups connected to a passageway extending through the dual acting cylinder with each passageway changing length as the dual acting cylinder extend and retract, a vacuum source is switchably connected to the vacuum cups through the passageway and a compressed air source is switchably connected to each of the front and rear chambers to respectively retract and extend the vacuum cups , comprising means for: extending dual acting cylinders from the manipulator by pressurizing the rear chamber; ; preparing dual acting cylinders to be proximally, passively moved by opening front and rear cylinders to atmosphere; actuating each vacuum source of each dual acting cylinder to provide suction to a respective vacuum cup ; moving the manipulator distally with the robot arm to conform to the plurality of irregular articles , the movement causing each dual acting cylinder to passively and proximally retract from contact of the vacuum cup with a respective irregular article to passively conform the vacuum cups and dual acting cylinders into contact with the plurality of irregular articles. extending dual acting cylinders from the manipulator by pressurizing the rear chamber; ; preparing dual acting cylinders to be proximally, passively moved by opening front and rear cylinders to atmosphere; actuating each vacuum source of each dual acting cylinder to provide suction to a respective vacuum cup ; moving the manipulator distally with the robot arm to conform to the plurality of irregular articles , the movement causing each dual acting cylinder to passively and proximally retract from contact of the vacuum cup with a respective irregular article to passively conform the vacuum cups and dual acting cylinders into contact with the plurality of irregular articles.
A salient pole rotor for an electrical machine, the rotor comprising: a longitudinal axis; a plurality of salient poles, each pole having a pole body and an integral pole tip ; and a rotor winding with a plurality of coils , each coil having a plurality of turns and being positioned on the pole body of a respective salient pole ; wherein each pole body includes a coil winding part having an outer profile around which the turns of the respective coil are wound in-situ and a coil mounting part on which the respective coil is at least partially mounted at a final mounting position by being moved along the pole body from the coil winding part to the coil mounting part ; wherein the coil mounting part has an outer profile that differs from the outer profile of the coil winding part in that the coil winding part includes an undercut and in that the coil mounting part does not include an undercut; and wherein each turn of each coil includes two substantially straight axially-extending sides orientated substantially parallel to the longitudinal axis of the rotor and an inner profile that differs from the outer profile of the coil winding part . a longitudinal axis; a plurality of salient poles, each pole having a pole body and an integral pole tip ; and a rotor winding with a plurality of coils , each coil having a plurality of turns and being positioned on the pole body of a respective salient pole ; wherein each pole body includes a coil winding part having an outer profile around which the turns of the respective coil are wound in-situ and a coil mounting part on which the respective coil is at least partially mounted at a final mounting position by being moved along the pole body from the coil winding part to the coil mounting part ; wherein the coil mounting part has an outer profile that differs from the outer profile of the coil winding part in that the coil winding part includes an undercut and in that the coil mounting part does not include an undercut; and wherein each turn of each coil includes two substantially straight axially-extending sides orientated substantially parallel to the longitudinal axis of the rotor and an inner profile that differs from the outer profile of the coil winding part . wherein each pole body includes a coil winding part having an outer profile around which the turns of the respective coil are wound in-situ and a coil mounting part on which the respective coil is at least partially mounted at a final mounting position by being moved along the pole body from the coil winding part to the coil mounting part ; wherein the coil mounting part has an outer profile that differs from the outer profile of the coil winding part in that the coil winding part includes an undercut and in that the coil mounting part does not include an undercut; and wherein each turn of each coil includes two substantially straight axially-extending sides orientated substantially parallel to the longitudinal axis of the rotor and an inner profile that differs from the outer profile of the coil winding part .
A system comprising: a central processing unit, CPU; a secure code store comprising a set of self-contained secure code which does not reference any other modifiable code; an operational code store comprising a set of operational code; a controller including functionality to initially execute, upon system start-up, one of: (a) the set of secure code when the system is configured with a first hardware configuration, wherein execution of the set of secure code comprises overwriting a current version of the operational code stored in the operational code store with a replacement version of the operational code referenced by the secure code; and (b) the set of operational code when the system is configured with a second hardware configuration, wherein the secure code store is electrically isolated from one or more other components of the system when the system is configured with the second hardware configuration, wherein the set of secure code cannot be accessed when the system is configured with the second hardware configuration; and an integrated circuit configured to control a state of the CPU; wherein in the first hardware configuration the integrated circuit is disabled to disable the CPU. a central processing unit, CPU; a secure code store comprising a set of self-contained secure code which does not reference any other modifiable code; an operational code store comprising a set of operational code; a controller including functionality to initially execute, upon system start-up, one of: (a) the set of secure code when the system is configured with a first hardware configuration, wherein execution of the set of secure code comprises overwriting a current version of the operational code stored in the operational code store with a replacement version of the operational code referenced by the secure code; and (b) the set of operational code when the system is configured with a second hardware configuration, wherein the secure code store is electrically isolated from one or more other components of the system when the system is configured with the second hardware configuration, wherein the set of secure code cannot be accessed when the system is configured with the second hardware configuration; and (a) the set of secure code when the system is configured with a first hardware configuration, wherein execution of the set of secure code comprises overwriting a current version of the operational code stored in the operational code store with a replacement version of the operational code referenced by the secure code; and (b) the set of operational code when the system is configured with a second hardware configuration, wherein the secure code store is electrically isolated from one or more other components of the system when the system is configured with the second hardware configuration, wherein the set of secure code cannot be accessed when the system is configured with the second hardware configuration; and an integrated circuit configured to control a state of the CPU; wherein in the first hardware configuration the integrated circuit is disabled to disable the CPU.
System for providing electrical power to an aerial vehicle comprising: an aerial vehicle ; a plurality of light-emitting diodes, LEDs, carried by the aerial vehicle ; a propulsion and control system of the aerial vehicle; at least one electrical circuit carried by the aerial vehicle , wherein the at least one electrical circuit has a DC buck converter electrically in series with at least a portion of the plurality of LEDs ; a tether connected between the aerial vehicle and a power source positioned remote from the aerial vehicle , wherein electrical power is transmitted to the aerial vehicle and at least a portion of the plurality of LEDs through the tether ; and at least one amperage boost regulator electrically in parallel to the DC buck converter , wherein the amperage boost regulator comprises an additional LED , and wherein when a voltage received through the tether across the DC buck converter approaches a maximum input voltage level of the DC buck converter , the amperage boost regulator is configured to draw greater amperage thereby causing a voltage drop, wherein an input voltage remains below the maximum voltage level of the DC buck converter to allow the DC buck converter to effectively maintain power priority over the amperage boost regulator , thereby ensuring the propulsion and control system of the aerial vehicle are not unduly limited. an aerial vehicle ; a plurality of light-emitting diodes, LEDs, carried by the aerial vehicle ; a propulsion and control system of the aerial vehicle; at least one electrical circuit carried by the aerial vehicle , wherein the at least one electrical circuit has a DC buck converter electrically in series with at least a portion of the plurality of LEDs ; a tether connected between the aerial vehicle and a power source positioned remote from the aerial vehicle , wherein electrical power is transmitted to the aerial vehicle and at least a portion of the plurality of LEDs through the tether ; and at least one amperage boost regulator electrically in parallel to the DC buck converter , wherein the amperage boost regulator comprises an additional LED , and wherein when a voltage received through the tether across the DC buck converter approaches a maximum input voltage level of the DC buck converter , the amperage boost regulator is configured to draw greater amperage thereby causing a voltage drop, wherein an input voltage remains below the maximum voltage level of the DC buck converter to allow the DC buck converter to effectively maintain power priority over the amperage boost regulator , thereby ensuring the propulsion and control system of the aerial vehicle are not unduly limited.
An optical sensor (100, 200, 311, 501-510) comprising: a photodetector ; and a light source disposed on the photodetector , wherein the optical sensor (100, 200, 311, 501-510) is configured to operate the light source in a light source mode, and operate the photodetector in a photodetector mode, based on a control signal, and wherein the control signal comprises mode selection information indicating one among the light source mode and the photodetector mode that is selected, and mode duration information of the selected one among the light source mode and the photodetector mode, characterized in that in the light source mode, only the light source operates and the photodetector does not operate, and in the photodetector mode, only the photodetector operates and the light source does not operate. a photodetector ; and a light source disposed on the photodetector , wherein the optical sensor (100, 200, 311, 501-510) is configured to operate the light source in a light source mode, and operate the photodetector in a photodetector mode, based on a control signal, and wherein the control signal comprises mode selection information indicating one among the light source mode and the photodetector mode that is selected, and mode duration information of the selected one among the light source mode and the photodetector mode, characterized in that in the light source mode, only the light source operates and the photodetector does not operate, and in the photodetector mode, only the photodetector operates and the light source does not operate.
A measuring station system for calibrating a reference system for vehicle measurement, comprising: a calibration device having multiple calibration device reference features ; a calibration frame having at least three support points configured for accommodating a reference system carrier for the reference system to be calibrated; and a reference system having at least one camera , which is arranged on the support points of the calibration frame with the aid of the reference system carrier ; characterised in that the calibration frame has at least three calibration frame reference features and the positions of the support points and of the calibration frame reference features in a shared coordinate system (K) are known; and the calibration frame is configured such that the calibration frame reference features and at least a selection of the calibration device reference features are detectable by the camera of the reference system . a calibration device having multiple calibration device reference features ; a calibration frame having at least three support points configured for accommodating a reference system carrier for the reference system to be calibrated; and a reference system having at least one camera , which is arranged on the support points of the calibration frame with the aid of the reference system carrier ; characterised in that the calibration frame has at least three calibration frame reference features and the positions of the support points and of the calibration frame reference features in a shared coordinate system (K) are known; and the calibration frame is configured such that the calibration frame reference features and at least a selection of the calibration device reference features are detectable by the camera of the reference system .
An epoxy-oxetane compound represented by the chemical formula (I): (in the formula (I), A's may be the same as or different from each other, and each independently represents a group represented by the chemical formula (II); R's may be the same as or different from each other, and each independently represents a hydrogen atom or a hydrocarbon group having a carbon number of 1 to 20; m represents an integer of 0 to 2; and n's may be the same as or different from each other, and each independently represents an integer of 0 to 20); and (in the formula (II), R's may be the same as or different from each other, and each independently represents a hydrogen atom or a hydrocarbon group having a carbon number of 1 to 20; and n represents an integer of 0 to 20).
A cleansing composition comprising: a) an anionic surfactant; b) an amphoteric and/or zwitterionic surfactant; c) a C 6 -C 14 acid, C 6 -C 14 alcohol and/or C 6 -C 14 amide; d) from 30 to 85% by weight water, forming a lamellar precursor composition, and e) structuring agent, wherein less than 0.0075% by weight of the anionic surfactant is isethionate, wherein the anionic surfactant is from 35 to 100% by weight taurate, preferably 100% by weight taurate, and further wherein the cleansing composition comprises less than 1% by weight sulfate, preferably no sulfate, wherein the cleansing composition comprises inorganic salt, and wherein the pH is from 4.9 to 6.0. a) an anionic surfactant; b) an amphoteric and/or zwitterionic surfactant; c) a C 6 -C 14 acid, C 6 -C 14 alcohol and/or C 6 -C 14 amide; d) from 30 to 85% by weight water, forming a lamellar precursor composition, and e) structuring agent, wherein less than 0.0075% by weight of the anionic surfactant is isethionate, wherein the anionic surfactant is from 35 to 100% by weight taurate, preferably 100% by weight taurate, and further wherein the cleansing composition comprises less than 1% by weight sulfate, preferably no sulfate, wherein the cleansing composition comprises inorganic salt, and wherein the pH is from 4.9 to 6.0.
A support device for an automatic concrete pump, comprising a frame with a set according to claim 9, wherein the swivel legs are hinged to the frame so as to be able to swivel relative to each other, wherein the swivelling section of the front swivel leg is swivel-mounted on the frame.
An illumination device for an endoscope , the device comprising illumination means for coupling light into a light guide connectable to the device, the illumination means comprising an LED matrix array comprising a plurality of LED pixels (4a, ..., 4n) forming an emission area , and a light guide port associated with the illumination means for positioning a light-guiding transmission area , which is disposed at an end of the light guide, essentially orthogonally to a main emission direction (L) of the emission area of the LED matrix array , characterized in that the device comprises detection means which are configured to detect LED pixels of the emission area that are directed at non-light-guiding portions (7a, ..., 7n) of the light guide in the main emission direction (L), and that the device has a control unit configured to selectively operate the LED pixels (4a, ..., 4n) of the LED matrix array for coupling light into the light guide in such a manner that at least some of the LED pixels directed at the non-guiding portions (7a, ..., 7n) of the light guide in the main emission direction (L) are operated at lower power or deactivated. a light guide port associated with the illumination means for positioning a light-guiding transmission area , which is disposed at an end of the light guide, essentially orthogonally to a main emission direction (L) of the emission area of the LED matrix array , characterized in that the device comprises detection means which are configured to detect LED pixels of the emission area that are directed at non-light-guiding portions (7a, ..., 7n) of the light guide in the main emission direction (L), and that the device has a control unit configured to selectively operate the LED pixels (4a, ..., 4n) of the LED matrix array for coupling light into the light guide in such a manner that at least some of the LED pixels directed at the non-guiding portions (7a, ..., 7n) of the light guide in the main emission direction (L) are operated at lower power or deactivated.
A rotorcraft with a fuselage comprising a lower shell , an inner floor , and at least one lower fuselage compartment arranged between the inner floor and the lower shell , wherein the at least one lower fuselage compartment is equipped with a floor fitting provided at the inner floor and at least two lateral fittings , and wherein the at least one lower fuselage compartment is at least accessible via an opening formed in the lower shell , the rotorcraft comprising: at least one non-retractable wheel-type landing gear rigidly attached in the at least one lower fuselage compartment and extending at least partly through the opening formed in the lower shell , comprising: at least one wheel ; a shock absorber connected to the at least one wheel , comprising: a shock absorber tube with an associated shock absorber tube length axis , and a shock absorber rod telescopically mounted to the shock absorber tube ; at least two mounting arms extending laterally from the shock absorber tube toward the at least two lateral fittings in the at least one lower fuselage compartment , wherein the at least two mounting arms are mounted to the at least two lateral fittings ; and a mounting pin device extending laterally from the shock absorber tube and comprising a mounting pin connected to the floor fitting provided at the inner floor . at least one wheel ; a shock absorber connected to the at least one wheel , comprising: a shock absorber tube with an associated shock absorber tube length axis , and a shock absorber rod telescopically mounted to the shock absorber tube ; a shock absorber tube with an associated shock absorber tube length axis , and a shock absorber rod telescopically mounted to the shock absorber tube ; at least two mounting arms extending laterally from the shock absorber tube toward the at least two lateral fittings in the at least one lower fuselage compartment , wherein the at least two mounting arms are mounted to the at least two lateral fittings ; and a mounting pin device extending laterally from the shock absorber tube and comprising a mounting pin connected to the floor fitting provided at the inner floor .