82 results about "Deviation vector" patented technology

A method of performing diagnostics on a system comprises receiving a plurality of measurement parameters, each corresponding to one of a plurality of parameters at a time k, forming a deviation vector from the plurality of measurement parameters, calculating an initial deviation vector from an initial fault vector, calculating a multiple fault isolation deviation vector using the initial deviation vector and the deviation vector, determining if an event is in progress using the multiple fault isolation deviation vector, performing statistical data validity to set a present inhibit flag and a past inhibit flag, and performing module performance analysis according to the present inhibit flag and the past inhibit flag.

An X-ray imaging device includes an X-ray generator, a filter plate detachably attached to an X-ray outlet of the X-ray generator, and a FPD. The filter plate has a plurality of circular markers of different sizes. The smallest marker is disposed at the center of the filter plate. The other markers are disposed on lines radiating from the smallest marker in increasing order of size and at regular intervals. An X-ray radiation beam passes through the markers and patient's body, and is incident upon an imaging surface of the FPD. The FPD produces a preliminary radiographic image from the incident X-ray radiation beam. A deviation vector detector chooses adjoining two marker images of different sizes from the preliminary radiographic image, and identifies to which markers the marker images correspond based on a size ratio. Then, the deviation vector detector determines the center of an X-ray field.

There are provided a method and an apparatus for data processing and a method and an apparatus which are able to precisely diagnose each parameter of an object, such as a machine, capable of operating in a plurality of operation modes.

Detection means 1a-1d detect a multiplicity of normal data sets, each of which includes values of n parameters, for each of the operation modes; Self-Organizing Map creating means 2 creates a SOM for each operation mode, using the normal data sets; abnormal data creating means 7 creates abnormal data sets representing virtual abnormal states by modifying the values of the n parameters of each of the multiple normal data sets so that the abnormal data sets as many as the number of deviation vectors are created for each of the multiple normal data sets; and working mode proportion calculating means 8 creates abnormal operation mode proportion vectors by selecting a self-organizing map which has the highest similarity degree to each of the abnormal data sets from the self-organizing maps created in said step of creating self-organizing maps.

Review bias identification systems and methods are presented. A bias in one or more review elements can be identified by deriving a measure of how a review outlet's product review deviates from an industry average or composite review of the product. A bias engine generates a bias vector for a review outlet where the vector can include multiple bias metrics associated with one or more product properties. The bias engine can further present one or more recommendations of associating the product with a review outlet based on the bias vector.

A controller for an AC rotary machine which performs a smooth drive from a low-speed region including zero speed to a high-speed region, and which can attain, even if an initial value error is present in an estimated phase, desired characteristics by promptly converging the error. An adaptive observation mechanism outputs an estimated magnetic flux phase, an estimated current vector, an estimated magnetic flux vector, and an estimated speed, based on a voltage instruction vector, a current deviation vector, and an amplified deviation vector; a deviation vector calculator calculates the current deviation vector between the estimated current vector and a detected current vector from a current vector detector, and a magnetic flux deviation vector between the estimated magnetic flux vector and a detected magnetic flux vector from a magnetic flux vector detector; and a deviation amplifier amplifies the current deviation vector and the magnetic flux deviation vector, and outputs the result as the amplified deviation vector.

A method for characterizing engine wear includes the steps of generating operational data representative of engine operation, comparing the operational data with baseline operational data generated by a baseline operational model of the engine and generating a first deviation vector based on this comparison, generating a plurality of data images of an engine component following engine operation, comparing each of the plurality of data images with a baseline image of the engine component and generating a second deviation vector based on this comparison, and quantifying a relationship between the first deviation vector and the second deviation vector. The first deviation vector represents variation between the operational data and the baseline operational data. The second deviation vector represents variation between the plurality of data images and the baseline images.

The invention relates to a high-precision real-time satellite positioning method. The method is technically characterized in that a polygonal satellite positioning receiver array formed by a plurality of satellite positioning receiving mechanisms is built; each satellite positioning receiver sends respective ID and observed value coordinate to a processor module; the processor module calculates to obtain a physical geometric figure and an observed value geometric figure; the physical geometric figure and the observed value geometric figure are compared, a deviation vector caused by an error is extracted and a deviation vector function library is formed; the deviation vector is subtracted from an observed value of a satellite positioning receiver antenna phase center, thereby obtaining a corrected satellite positioning value. The high-precision real-time satellite positioning method provided by the invention is reasonable in design, can maximally eliminate positioning errors existing in the satellite positioning receivers, can remarkable improve positioning precision, has the characteristics of reasonable design, high precision, low cost, convenient use and the like, and can be extensively applied and popularized to the general civil field of high-precision real-time satellite positioning navigation.

The invention provides a method for evaluating an uncertainty of track association. The method comprises the following steps of: (1) generating a plurality of track pairs to be evaluated; (2) checking time and space of target track information; (3) constructing a collection of the tracks of the targets taking part in the evaluation; (4) calculating a standardized track likelihood; (5) calculating correction factors used for describing false conditions, omitted conditions, and an undetected area of a sensor; (6) calculating and accounting a standard deviation of a deviation vector; (7) calculating a correction factor used for describing the distribution of the targets; and (8) calculating the uncertainty of the track association of the track pairs. The method has the advantages of comprehensively considering the influence of the factors such as the detection ability of the sensor and the distribution of the targets on the uncertainty of the track association, and being capable of reasonably reflecting the relationships between the uncertainty of the track association and the distance between the targets, the measuring error of the sensor, the correctness of the track association, the detection probability and the like; and in addition, the evaluation results are not sensitive to the systematic error of the sensor, accuracy parameters of the sensor used in the evaluation and the like. The method can be used for constructing self-adaptive, studying or intelligent track data combination systems.

A method for balancing a color wheel comprising: step (a), measuring the rotational deviation vector of a driving motor, including its deviation amount and direction; step (b), adjusting the deviation of a color wheel to make its deviation amount to be the same of the driving motor; and step (c), connecting the color wheel to the driving motor and let the deviation direction thereof to be opposite to each other to reach an expected balance. According to the present invention, an embodiment of the color wheel structure may includes a set of color filter and a ring, before to start the assembly, adjusting the deviation vector of the ring and motor shaft first, and then to assemble it and make the deviation vectors oppositely.

The invention discloses an accuracy control method capable of rapidly carrying a ship body. The accuracy control method specifically comprises the following steps: fixing a plurality of first reflector plates on carrying segments, and fixing a plurality of second reflector plates on reference segments; measuring the actual three-dimensional coordinate of each first reflector plate and the actual three-dimensional coordinate of each second reflector plate respectively by using a total station; generating the deviation vectors A of the first reflector plates and the deviation vectors B of the second reflector plates by using ECO-BLOCK software; generating a margin trimming list by using ECO-OTS software; marking out margin cutting lines and involution check lines on the carrying segments according to the margin trimming list; trimming the carrying segments according to the margin cutting lines; and assembling the carrying segments and the reference segments which are cut. The accuracy control method is simple and convenient in operation, and accurate cutting can be carried out on the carrying segments by carrying out simulation carrying on the carrying segments, so that the accuracyof ship construction is improved, and the construction efficiency of ships is also improved.

A control method for a hierarchical saturation PID (Proportion Integration Differentiation) controller based on integral separation relates to a control method for a hierarchical saturation PID controller, and solves the problem of larger system overshoot and even system oscillation caused by calculated control quantity far more than limit control quantity which corresponds to the maximal output capacity of an execution mechanism due to the integral accumulation of PID operation, wherein the integral accumulation of the PID operation is caused by the hierarchical saturation PID controller added in an integral item. The method comprises the following steps: a deviation vector e is calculated according to a real-time online quaternion Q and a target quaternion Qc; an angular velocity restraint coefficient Li is calculated according to the maximal star control acceleration ai, the maximal rotating angular velocity |Omega i|max and the deviation vector e obtained in the step 1, and an integral separation coefficient matrix Beta is determined according to the deviation vector e; output moment uc is calculated by combining the angular velocity restraint coefficient Li with the integral separation coefficient matrix Beta; and actual star angular velocity speed omega and a updated feedback real-time posture quaternion Q are solved respectively through a posture kinetic equation and a posture kinematic equation. The method can be widely applied in control systems for spacecrafts.

In an electronic device having a circuit outputting a vector sum of two quadrature vector signals, an offset compensating device compensates the offset contained in the vector sum. The offset compensating device aims to flexibly adapt to deviation in characteristics and performances and various fluctuations, and to compensate offset stably and accurately. The offset compensating device includes a deviation monitor unit creating a vector signal by A/D-converting the aforementioned vector sum and by quadrature-demodulating it and monitoring the deviation of the DC components superposed on the vector signal, and an adaptive control unit updating the compensation vector determined in advance, based on adaptive algorithm minimizing expectation value of the product of the inner product between an increment vector and the compensation vector, and the latest deviation vector, and adding the compensation vector to an offset vector to be inputted, while being superposed on the input signal, to a circuit.

The invention relates to an in-orbit compensation method for the deformation of a spaceborne microwave remote sensing instrument. The method includes the following steps that: step 1, the X pointing angle deviation curve and Y pointing angle deviation curve of view vectors in a satellite body coordinate system are solved; and X pointing angle deviation vectors and Y pointing angle deviation vectors are solved; step 3, an X pointing angle sensitivity curve and a Y pointing angle sensitivity curve corresponding to various deformation error parameters are solved; step 4, X pointing angle sensitivity vectors and Y pointing angle sensitivity vectors corresponding to the deformation parameters are solved; step 5, a sensitivity matrix is constructed; step 6, a compensation matrix is constructed;and step 7, by means of the pseudo-inverse form of the compensation matrix, so that a compensation quantity is solved. An optical path model in the method of the invention is applicable to a spaceborne microwave remote sensing instrument comprising a planar reflecting surface, a rotating parabolic reflecting surface, a rotating hyperbolic reflecting surface and the like. With the method adopted, the in-orbit compensation quantities of the deformation of the optical path assemblies of spaceborne microwave remote sensing instruments of various configurations can be calculated.

The invention discloses a cooperative target and non-cooperative target coexistence alternate Kalman space registering method, aims to provide an alternate Kalman space registering method which is notinfluenced by Earth curvature and has high precision of estimation of sensor system deviation. According to the method, under an earth centered earth fixed coordinate system, filtering initial valuesare assigned to measurement system deviation vectors and filtering estimation covariances of two sensors arranged on two moving platforms; a space registering measurement model is established, including constructing a cooperative target which can be observed by only one sensor and a measurement equation which can be simultaneously observed by the two sensors, constructing a non-cooperation targetand a measurement equation which can be simultaneously observed by the two sensors; according to the measurement equation, alternate Kalman filtering of the information based on the cooperative target and the information based on the non-cooperative target is carried out continuously till deviation estimates of the sensor measurement system are acquired, the deviation estimates are further utilized to compensate sensor measurement data, and the whole space registering process is accomplished.

The invention discloses a bio-inspired top-down visual attention method, which comprises the following steps of: (1) extracting the characteristics of all learning maps; (2) representing all the learning maps of the same type with mean vectors and standard deviation vectors; (3) acquiring a top-down map prominent map and a bottom-up prominent map of a map to which attention is to be paid; (4) acquiring a final prominent map; (5) performing a winner-take-all method; (6) performing inhibition of return, and setting pixel values of areas where most prominent points in the final prominent map to be zero to obtain a new final prominent map; and (7) performing attention selection. In the method, in the presentation of a learning target, only own characteristics of the learning target are utilized and the background of the learning target is not taken into account, so the representation of the target has stronger robustness and relatively better visual effect is achieved.

Systems, apparatus, and methods detect a current sensor error in an FOC electric machine system. A voltage command is monitored to detect the presence of an ac component can indicate that an error has occurred at a current sensor. By way of example, a sensor fault detection module can be configured to determine the deviation between an actual voltage command and an ideal voltage command to provide a complex deviation vector. By transforming the deviation vector to a reference frame rotating at the fundamental frequency of the command voltage, a dc component of the positive and negative sequences can be filtered, and their amplitudes determined. Error detection can be based on the total amplitude of the fundamental component, determined by positive and negative component amplitudes. The invention enables an FOC system to operate with two current sensors, rather than three, and provides a dedicated fault diagnostic for a current sensor.

The embodiment of the invention discloses image correction method and device, and belongs to the technical field of processing of images. The image collection method comprises the steps of arranging a plurality of control points at the preset position of the image to be corrected; obtaining the deviation vector of each control point according to the global inclination angle of the image; deviating each control point through the deviation vector to obtain the corrected image. With the adoption of the method, the image can be corrected without cutting, and therefore, the image information is avoided loss, and the user can feel great.

The invention provides a method for estimating the output deviations of a triaxial magnetometer. The method is applied to spacecrafts. The output deviations of the triaxial magnetometer comprise a deviation vector and a deviation matrix. The method comprises the following steps: determining an attitude matrix from star coordinate system to track coordinate system by using a double-vector method; acquiring the measured value of the magnetometer; establishing a deviation model of the magnetometer which is used for defining the relationship among the measured value of the magnetometer, the deviation vector, the deviation matrix and the attitude matrix; and subjecting the deviation model to iterative operation in virtue of Kalman filtering so as to estimate the deviation vector and the deviation matrix in real time. The method provided by the invention is fast in calculation convergence, high in precision and applicable to spacecrafts with stable attitudes and has reference significance to error analysis, in-orbit correction and subsequent designing of the triaxial magnetometer and other triaxial vector sensors with similar measuring principles.

The invention discloses a video image anti-shake method and system for bullet time shooting, wherein the method comprises the following steps: acquiring a camera sequence pose for shooting a to-be-processed image; according to the camera sequence pose, calculating the offset vector of the ideal positions of all cameras and an ideal position of a reference camera; calculating the position of a reference object which is jointly shot by all the cameras; according to the deviation vector of the ideal position of the camera and the position of the reference object, calculating the rotation matrix of the to-be-processed image and rotating the to-be-processed image, and splicing into a video, so that the problem of image shaking of the shot video in the bullet time is solved. According to the video image anti-shake method and system for bullet time shooting provide a fast and practical solution for bullet time shooting; and the method and the system are easy to operate, easy to master and good in video debouncing effect.