168results about How to "Improve the determination accuracy" patented technology

A process and a device are provided for determining the pose as the entirety of the position and the orientation of an image reception device. The process is characterized in that the pose of the image reception device is determined with the use of at least one measuring device that is part of a robot. The device is characterized by a robot with an integrated measuring device that is part of the robot for determining the pose of the image reception device.

The invention discloses a combined scheduling method of satellite-ground measurement and control resources of a low-mid-orbit satellite constellation based on orbit determination constraint satisfaction, and belongs to the field of combined scheduling of the satellite-ground measurement and control resources. The method comprises the steps of (1) building a visible geometry model, (2) building a visible link model, (3) building the constraint condition of orbit determination, (4) carrying out preprocessing, (5) determining a resource distribution principle, (6) building a combined scheduling model of the satellite-ground measurement and control resources, and (7) carrying out algorithm solution. Compared with the prior art, the method has the advantages that the scheduling result is reasonable, the scheduling process is efficient, and the scheduling method is high in universality. The air-and-ground-based integrated scheduling of the measurement and control resources is achieved. The transition from ground-based measurement and control to air-and-ground-based combined measurement and control in China is achieved.

The invention discloses a method for simultaneously determining a pile position and a critical depth of an anti-slide pile by using displacement monitoring, which is applicable to determining and designing the pile position and the critical depth of the anti-slide pile on an accumulated layer landslide. The method comprises the following steps of: (1) performing investigation, analysis and evaluation aiming at the geology of a side slope to be managed to determine a landslide body region; (2) dividing grids on the landslide body and selecting a displacement monitoring point position; (3) monitoring equipment mounting and displacement monitoring; (4) determining a synthetic total displacement value S (i, j) and vertical displacement direction rate of each monitoring point of landslide displacement; (5) determining landslide instability property and an anti-slide pile space reinforcement position; (6) determining the critical depth of a shearing slip band of the landslide body; (7) determining the pile length of the anti-slide pile of the landslide; and (8) performing information construction of the anti-slide pile. The method has the advantages of less investment cost, reliable design principle, high position determination accuracy, easiness, convenience, fastness, easiness in implementation and strong engineering applicability.

A rotation detecting device and a rotation detecting method determines normal rotation / reverse rotation of a rotating shaft based on a rotation signal different between the normal rotation and the reverse rotation of the rotating shaft. The rotation signal is set to have a pulse width different between the normal rotation and the reverse rotation of a crankshaft that is an output shaft of an internal combustion engine. By determining whether or not the pulse width is greater than a threshold value, the normal rotation or the reverse rotation of the crankshaft is detected. Whether or not the crankshaft is rotating normally is determined based on engine rotating speed, a cylinder in which a piston is in a predetermined position, an engine load, a starter switch, intake pressure, battery voltage, and the like. When the condition for the normal rotation is satisfied, the threshold of the pulse width is set based on a pulse width of a rotation signal measured at this time.

The invention belongs to the technical field of aircraft flying load design, and relates to the improvement on a method for determining a wing structure load when a transportation aircraft drops goods. The method for determining the wing structure load is characterized by comprising the step of initializing aircraft air-dropping goods parameters, the step of analyzing aircraft limited element modals, the step of calculating an aircraft non-steady aerodynamic coefficient matrix, the step of calculating an aircraft air-dropping goods dynamic response, the step of calculating a wing structure load dynamic response, and the step of determining the design load of the wing structure in the process of air-dropping. By means of the improved method for determining the wing structure load when the transportation aircraft drops the goods, the determining precision of the wing structure load is improved, and the safety of the wing structure and the flying safety of the aircraft are guaranteed.

The invention discloses a system and a method for determining the environment traffic capacity of an expressway based on vehicle emission. The system comprises a data acquisition system, a processor, a display and a server, wherein the processor is used for analyzing and processing data which are acquired by the data acquisition system; the display and the server are connected with the processor; the processor is in wireless connection and communication with the data acquisition system through a wireless communication system; and the data acquisition system consists of meteorological parameter detection equipment, traffic flow detection equipment and pollutant concentration detection equipment. The method comprises the following steps of: 1, acquisition and real-time uploading of the data; 2, determination of the environment traffic capacity of the expressway: determination of the cumulated amount of various vehicle emission pollutants, determination of a dilution factor f, and determination of the environment traffic capacity of a road section j of the expressway; and 3, synchronous output and storage of a processing result. The invention has the advantages of novel and reasonable design, convenience for implementation, high real-time performance, high determination accuracy of the environment traffic capacity of the expressway, high reliability, high practicability and high popularization and application value.

The terminal device includes object lens, universal joints, motor drive and angular displacement sensor, part for switching channels, star capture channel and part, satellite laser communication channel and module, interfaces between each module and CPU, CPU, and interface between CPU and satellite platform. CPU controls switching part in adjustment channel so that light signal received by system can be transferred to star capture channel to capture stars, or to satellite laser communication channel, where relevant modules are cooperated to carry out satellite laser communication. Syncretizing function of star sensor, the system can accomplish capture procedure between communication terminal devices without need of scanning.

The invention relates to a determination method of pulse TOA of X-ray pulsar-based navigation. The method comprises the steps of firstly, performing pulse contour folding in a selected folding cycle according to a photon sequence obtained within the observation time, performing normalization so as to obtain a normalized intensity vector, then performing feature subspace decomposition on a covariance matrix of the normalized intensity vector, so as to obtain a noise subspace matrix, constructing a searching vector according to a standard pulse contour, then obtaining a spectrum of the pulse TOA from the noise subspace matrix and the searching vector, and searching a spectrum peak value of the spectrum of the pulse TOA, so as to obtain a value of the pulse TOA. According to the method, the pulse TOA is determined on the basis of the feature subspace decomposition, so that the calculation accuracy of the pulse TOA can be effectively increased, and the pulse contour folding is adopted, so that the approximation degree of a pulse contour estimated value and the standard pulse contour is increased, thereby increasing the calculation accuracy of the pulse TOA within the observation time.

The invention discloses a method for testing chip junction temperature in LED illumination lamps. The invention determines LED chip junction temperature in an LED illumination lamp according to the law that LED material forbidden band width changes along with temperature, comprising three steps: (1) switching on pulse voltage with very low duty ratio, thud directly obtaining the illuminating peak position of the LED chip at the temperature; (2) measuring the illuminating peak position of the LED lamp under normal operating condition, contrasting the illuminating peak positions to obtain the drifting volume of the illuminating peak positions, namely the difference of the two, and using the drifting volume of wave length to measure the temperature difference of the two; and (3) measuring under very low pulse voltage in step 1 with temperature being room temperature, and judging the temperature of the LED chip in the LED lamp under the condition according to the room temperature and the temperature difference of the two. The invention can represent the actual temperature of the LED chip in the LED lamp under different conditions within the error range of plus or minus 0.6 degree, thus being beneficial for the performance representation and optimized research of the LED lamp.

A state of an energization of a normal open type drain valve interposed between a fresh air introducing port of a canister and a drain filter is checked. And if the valve is not the energized state (open state), the tank internal pressure is checked. If the tank internal pressure is lower than a predetermined value and the state is maintained for a predetermined time, it is determined that the drain valve is close-stuck. If the drain valve is close-stuck, the pressure in the canister becomes negative, and the negative pressure is introduced in a fuel tank via a passage to an atmosphere and a pressure control valve. Closed sticking of the drain valve can be detected by checking the tank internal pressure.

In a method of enhanced position determination of a user terminal associated with at least one cell in a cellular communications network, providing a predetermined cell identity definition SO1 providing Sl a representation of a barometric pressure measure for the user terminal, said barometric pressure measure corresponding to an altitude of the user terminal, and determining S2 at least one geographical region definition based on the provided predetermined cell identity definition and the provided representation of barometric pressure measure, said at least one geographical region definitioncorresponding to a horizontal region associated with said predetermined cell identity definition and said representation of said barometric pressure measure.

The invention discloses a double-LaBr3 crystal detector element energy spectrum logger based on a controllable neutron source. The double-LaBr3 crystal detector element energy spectrum logger comprises a cylindrical shell, wherein the cylindrical shell is internally provided with a LaBr3 detector I and a LaBr3 detector II from top to bottom, the controllable neutron source is connected with a photomultiplier at the top part of the LaBr3 detector I, a chromium foil is arranged between the LaBr3 detector I and the LaBr3 detector II, and the photomultiplier, the LaBr3 detector I, the chromium foil and the LaBr3 detector II are arranged in a boron sleeve body which is positioned in the cylindrical shell; a tungsten shielding body is arranged between the controllable neutron source and the boron sleeve body, and the controllable neutron source is connected with a neutron detector through a neutron acceleration part. According to the double-LaBr3 crystal detector element energy spectrum logger based on the controllable neutron source, disclosed by the invention, by utilizing the controllable neutron source and the double LaBr3 detectors with high resolution, the content measuring accuracy of elements such as C and Mg and the longitudinal resolution can be increased, the measurement information can be increased, and the purpose of simultaneously determining parameters of stratum element content, mineral content, porosity degree and the like can be realized; the double-LaBr3 crystal detector element energy spectrum logger has the characteristics that the environmental hazard is reduced, effective stratum information is enriched, and the like.

An inspecting apparatus includes an image pickup unit configured to pick up a plurality of images of an inspection target object with different exposure times and generate, image data of an inspection target object image including an inspection region, a weighted-image-data generating unit configured to weight, for each of the image data generated with the exposure times different from one another, data of pixels indicating a region where a difference in gradation of pixel values is relatively large among regions of pixels included in the image data and generate weighted image data, an image-data combining unit configured to generate combined image data obtained by combining the generated respective weighted image data, and a determining unit configured to determine a state of the inspection region on the basis of image data of a reference image set and the generated combined image data.

The invention provides a high precision propellant filling method for a high orbit satellite with parallel-connection flat-laid storage tanks. The high precision propellant filling method comprises the steps that before test, a standard weight is used for calibrating a barycenter test board; the satellite is directly mounted on the barycenter test board, and before a propellant is filled, influence, of tools on the periphery of the satellite, on the test is eliminated; in the filling process, the mass and the barycenter of the satellite are directly measured; and after filling, the creeping effect of the barycenter test board is calibrated, and test is conducted again. By adoption of the filling method provided by the invention, the precision of mass test is smaller than 0.6 kg, the precision of barycenter test is smaller than 0.5 mm, the error of satellite filling is decreased, the determination precision, of the transverse barycenter of the satellite, on the ground is increased, a direct basis is provided for determination of the transverse barycenter position of the satellite at the ignition time of an orbit transfer section apogee engine, control over disturbance torque is facilitated, and safe orbit transfer can be ensured.

The invention discloses a method for measuring the low background carrier concentration in a semiconductor material device, and the method comprises the following steps: measuring the flat belt voltage on the surface of a region to be measured and the differential capacitance response under the optical excitation condition; establishing a numerical value model of the region to be measured and theadjacent region; and comparing the surface differential capacitance under the optical excitation condition of the region to be measured of the numerical value model and the practical measurement so as to determine the balanced carrier concentration. The method disclosed by the invention is suitable for the accurate measurement of the specific function region in the semiconductor material or device provided with a complicated structure, and the background carrier concentration of the specific function region is lower than 1015cm<-3>; and method can be used for detecting a single microcosmic block in an integrated or array device.

The invention relates to a multi-sensor data and track information time synchronization method. The method comprises the following steps: S1) obtaining a sensitive time of gyro combined data; S2) determining a track calculating time; S3) collecting attitude data and exposure time data of a star sensor; S4) according to computer data and the exposure time data of the star sensor, calculating the exposure time of the star sensor; S5) according to the exposure time of the star sensor and the track calculating time, performing calculation to obtain deviation quaternion caused by time difference; and S6) performing calculation to obtain attitude quaternion of the star sensor after synchronization with the track calculating time. The multi-sensor data and track information time synchronization method can effectively guarantee time synchronization of various sensitive data and track data required by satellite attitude determination, so that the authentic satellite attitude having high precision is obtained.

The invention provides a total tardiness transport plan scheduling algorithm based on improved particle swarm optimization. The algorithm comprises the steps of firstly, establishing a total tardiness value mathematic model based on input variables and defining the number n of to-be-processed works and the number m of machines, and the time pj required for processing of each to-be-processed work and the delivery term dj; secondly, solving a construction drawing according to the total tardiness value mathematic model; thirdly, based on the construction drawing and according to state transition rules and pheromone update rules, completing search and acquiring a solution making the total tardiness T minimum. Based on the ant colony algorithm and according to the characteristics of the total tardiness transport plan scheduling problem (P / / T) of parallel machines, the improved Heuristic Ant Colony Optimization (hACO) is proposed and performance optimization research is performed on the algorithm to improve the determination accuracy of optimal solutions of events and guarantee the internal data processing and screening efficiency.

The invention discloses a method and device for determining lift-off information of an unmanned aerial vehicle base station, equipment and a medium. The method comprises the following steps: obtainingthe latitude and longitude of a target area and the radius of the target area, rasterizing the target area; establishing a grid model by taking the latitude and longitude of the target area as an original point according to the radius of the target area and the grid precision, and calculating the telephone traffic coverage center-of-gravity position of each grid and the telephone traffic coveragecenter-of-gravity weight value of each grid in the grid model; obtaining working parameters of a plurality of current network cells, adjusting the telephone traffic coverage gravity center weight value of each grid according to the working parameters of each current network cell; and determining a target lift-off longitude and latitude position of the unmanned aerial vehicle base station according to the telephone traffic coverage gravity center position of each grid and the adjusted telephone traffic coverage gravity center weight value. According to the technical scheme, the determination precision and the determination speed of the base station position can be improved, and the cost of manually acquiring the base station position is reduced.

The invention relates to a method for determining a relative adjoint orbit of a space target and belongs to the technical field of aerospace deep space exploitation. The method for determining the orbit state at the current moment comprises the following steps: (1) carrying out the recursion for a predicted value of the orbit state at an arbitrary moment according to an orbit dynamics equation, btaining a predicted observed quantity and further obtaining a difference value between a real observation value and the predicted value; (2) working out solutions of a system of linear equations by utilizing an observation equation and the difference value obtained in the step (1), thus obtaining an orbit state estimated deviation solution set; (3) carrying out increasing arrangement on the solutions obtained in the step (2) according to numerical values, and eliminating the solutions with the difference of two adjacent items greater than a measurement error limit; (4) determining the orbit state estimation deviation to be a middle item in the set obtained in the step (3) if the solution number of the set is an odd number, and determining the orbit state estimation deviation to be an average value of two continuous middle items in the set if the solution number of the set is an even number; (5) determining the orbit parameter estimation value at the current moment to be the sum of the orbit state predicted value and the orbit state estimation deviation. By adopting the method, the interference of a complicated dynamics model and noise can be alleviated.

The invention discloses a space-based optical angle measurement segmental arc initial orbit determination and association method for a GEO target, and the method comprises the steps: screening a space-based platform measurement segmental arc, and carrying out the coordinate system conversion of the height and latitude and longitude data of a space-based platform, and obtaining a position vector and a velocity vector under a J2000 coordinate system; selecting two space-based platform measurement arc segments aiming at the GEO target from the screened measurement arc segments, and respectively sampling right ascension and declination data in the two arc segments; for each arc section, according to right ascension and declination data of a sampling point, determining a distance range from the space-based platform to the GEO target to generate a slope distance search grid point, in the search grid point, determining an initial orbit corresponding to each sampling point by adopting a bacterial foraging algorithm and a genetic algorithm, and obtaining a corresponding sub-satellite point trajectory; further obtaining a longitude average value of each arc section; and calculating a difference value of the longitude average values of the two arc segments, and when the difference value is smaller than a preset threshold value, determining that the two arc segments are associated.

The invention relates to an altered volcano rock effective reservoir determination method and device in oil-gas exploration. The method includes the steps of determining the volcanic rock development layer type and the volcanic rock type of a processed well section, selecting lithologic parameter values of different unaltered volcanic rocks of the processes well section according to the volcanic rock development layer type and the volcanic rock type, obtaining a rock alteration factor of the processed well section by the utilization of the lithologic parameter values of the different unaltered volcanic rocks according to the change relation of the volcanic rock alteration degree and logging response on the basis of conventional logging data, obtaining a reservoir quality factor of the processed well section according to porosity, deep lateral resistivity, shallow lateral resistivity on the basis of the conventional logging data, and determining an altered volcano rock effective reservoir according to the fact that the difference between the reservoir quality factor and the rock alteration factor and full-diameter core storage-percolation capability are in a linear positive correlation relationship.

The invention provides a transverse centroid high-precision guarantee method for a parallel tiled tank satellite in AIT stages. The transverse centroid high-precision guarantee method comprises the following steps: in the structural assembly stage, tank mounting plate form and position errors as well as apogee engine bracket mounting errors are controlled; in the propulsion system welding assembly stage, tank mounting position errors as well as apogee engine mounting position and pointing errors are controlled; in the whole satellite general assembly stage, the quality and the centroid are controlled when a solar array in the unfolded state; and before delivery, the whole satellite transverse centroid measurement is performed through high-precision centroid measurement equipment. According to the transverse centroid high-precision guarantee method provided by the invention, a plurality of transverse centroid guarantee measures are implemented in all the AIT stages of the whole satellite, the transverse centroid of the satellite is controlled to be near the origin when the solar array is in the initial unfolded state, the transverse centroid determination accuracy of the satellite is improved (lower than or equal to 1 mm), and the transverse centroid change of a satellite orbit maneuver section is reduced, thereby reducing the disturbance torque generated by an apogee engine and ensuring safe orbit maneuver; and meanwhile, the consumption of a propellant is lowered.

The embodiment of the invention discloses an image processing method and device, an electronic device and a storage medium. The method comprises the following steps: carrying out scene recognition onan image to be processed to obtain at least one scene label of the image to be processed; When no priority scene label exists in the at least one scene label, obtaining scene parameters of the to-be-processed image, and determining a target scene of the to-be-processed image according to the scene parameters; And based on a brightness processing mode corresponding to the target scene, carrying outbrightness processing on the to-be-processed image to obtain a processed image. According to the technical scheme, the determination precision of the target scene of the to-be-processed image is improved, the optimal brightness processing mode of the to-be-processed image is further determined according to the target scene, and the image brightness of the to-be-processed image is improved.

The invention relates to a method for improving the attitude measurement accuracy of a star sensor, belonging to the field of satellite analysis. The method comprises the following steps: establishinga satellite attitude determination system model so as to acquire the estimated state value of satellite attitude; subtracting an estimated gyroscopic drift value from the estimated state value so asto obtain a sample sequence; subjecting the sample sequence to discrete Fourier transform so as to obtain the frequency spectrum of the sample sequence and reading the frequency of the errors of the estimated gyroscopic drift value form the frequency spectrum of the sample sequence; estimating the amplitude of the periodic errors of gyroscopic drift so as to calculate the estimated amplitude valueof the low-frequency errors of the star sensor; establishing a reference model for the low-frequency error of the star sensor based on the frequency of the periodic errors of gyroscopic drift and theestimated amplitude value of the low-frequency errors of the star sensor; and updating the estimated state value of the satellite attitude according to the reference model for the low-frequency errors of the star sensor. The method provided by the invention fully takes the influence of the low-frequency errors of the star sensor on the attitude of the star sensor into consideration, so the attitude measurement accuracy of the star sensor is improved.

The embodiment of the invention discloses a driving direction determination method and device, equipment and a storage medium. The method comprises the following steps: obtaining track data reported by a target vehicle, the method comprises the following steps: acquiring trajectory data, forming at least one corresponding driving trajectory based on the trajectory data, determining a fan-shaped area corresponding to each driving trajectory, determining a target trajectory point on the corresponding driving trajectory based on each fan-shaped area, and determining the driving direction of eachdriving trajectory according to the target trajectory point and the fan-shaped area corresponding to each driving trajectory. Compared with the prior art, the direction of the driving track is determined only according to the coordinates of the starting point and the terminal point of the driving track. According to the embodiment of the invention, the driving track of the target vehicle is subjected to region division to obtain the corresponding fan-shaped region, and the driving direction of the driving track is determined by utilizing the fan-shaped region and the target track point corresponding to each driving track, so that the determination precision of the driving direction is improved.

Method for determining the refractive index (n) of a material of a contact lens, in particular of a soft contact lens, the contact lens (1) having a first surface and a second surface defining a lens geometry there between, by measuring the wavefront issued by the contact lens (1) with a wavefront sensor (4), obtaining data of the geometry of at least one section of the contact lens (1) with an optical coherence tomography system (3) and communicating the geometry of the at least one section of the contact lens (1) from the optical coherence tomography system (3) to an analyzer, particularly a computer, and determining the refractive index (n) of the material of the contact lens from the geometry of the at least one section of the contact lens and from the wavefront issued by the contact lens (1).

The invention belongs to the technical field of aircraft simulation, and particularly relates to a method for determining the dynamic response of an aircraft in a mobile wind field environment. The method comprises the following steps: initializing aerodynamic load calculation parameters; updating the local equivalent moment of each grid on the surface of the aircraft; carrying out interpolation to obtain the wave gust speed of each grid; calculating the incidence angle, the sideslip angle and the dynamic pressure of each grid; interpolating to obtain a pressure coefficient at the centroid of each grid; and integrating all grids to obtain the external aerodynamic load of the aircraft. According to the improved method for determining the external aerodynamic load of the aircraft in the mobile wind field environment, the influence of the process that the aircraft is surrounded by the mobile wind field on the aerodynamic load is considered, the determination process of the aerodynamic load is simplified, and the determination precision of the aerodynamic load is improved.

The invention discloses an image similarity determination method. The method comprises the following steps: obtaining a pair of target images to be determined in similarity; the pair of target imagescomprises a first image and a second image; the pair of target images comprises a first image and a second image. Extracting at least two image features of a target image pair; Each image feature of the target image pair is input into a depth convolution network model trained in advance based on the corresponding image feature, and the similarity determination results of each depth convolution network model are obtained. The similarity between the first image and the second image in the target image pair is determined based on the weighting operation of the similarity determination result of each depth convolution network model. The technical proposal provided by the embodiment of the invention effectively improves the determination accuracy of the image similarity, and improves the performance of the image recognition and the target tracking task based on the image similarity. The invention also discloses an image similarity determination device, equipment and a storage medium, whichhave corresponding technical effects.