2428 results about "System error" patented technology

An implantable infusion pump possesses operational functionality that is, at least in part, controlled by software operating in two processor ICs which are configured to perform some different and some duplicate functions. The pump exchanges messages with an external device via telemetry. Each processor controls a different part of the drug infusion mechanism such that both processors must agree on the appropriateness of drug delivery for infusion to occur. Delivery accumulators are incremented and decremented with delivery requests and with deliveries made. When accumulated amounts reach or exceed, quantized deliverable amounts, infusion is made to occur. The accumulators are capable of being incremented by two or more independent types of delivery requests. Operational modes of the infusion device are changed automatically in view of various system errors that are trapped, various system alarm conditions that are detected, and when excess periods of time lapse between pump and external device interactions.

Methods of determining a corrected analyte concentration in view of some error source are provided herein. The methods can be utilized for the determination of various analytes and / or various sources of error. In one example, the method can be configured to determine a corrected glucose concentration in view of an extreme level of hematocrit found within the sample. In other embodiments, methods are provided for identifying various system errors and / or defects. For example, such errors can include partial-fill or double-fill situations, high track resistance, and / or sample leakage. Systems are also provided for determining a corrected analyte concentration and / or detecting some system error.

The present invention provides a method and apparatus for capturing system error messages. The method includes accessing information associated with an error. The method further includes identifying a category associated with the error based upon the accessed information and accessing at least one pre-determined attribute in the accessed information based upon the identified category.

Methods and systems disclosed herein relate generally to data processing by applying machine learning techniques to iteration data to identify anomaly subsets of iteration data. More specifically, iteration data for individual iterations of a workflow involving a set of tasks may contain a client data set, client-associated sparse indicators and their classifications, and a set of processing times for the set of tasks performed in that iteration of the workflow. These individual iterations of the workflow may also be associated with particular data sources. Using the iteration data, anomaly subsets within the iteration data can be identified, such as data items resulting from systematic error associated with particular data sources, sets of sparse indicators to be validated or double-checked, or tasks that are associated with long processing times. The anomaly subsets can be provided in a generated communication or report in order to optimize future iterations of the workflow.

A system and method for verifying a memory consistency model for a shared memory multiprocessor computer systems generates random instructions to run on the processors, saves the results of the running of the instructions, and analyzes the results to detect a memory subsystem error if the results fall outside of the space of possible outcomes consistent with the memory consistency model. A precedence relationship of the results is determined by uniquely identifying results of a store location with each result distinct to allow association of a read result value to the instruction that created the read result value. A precedence graph with static, direct and derived edges identifies errors when a cycle is detected that indicates results that are inconsistent with memory consistency model rules.

An inertial (“INS”) / GPS receiver includes an INS sub-system which incorporates, into a modified Kalman filter, GPS observables and / or other observables that span previous and current times. The INS filter utilizes the observables to update position information relating to both the current and the previous times, and to propagate the current position, velocity and attitude related information. The GPS observable may be delta phase measurements, and the other observables may be, for example, wheel pick-offs (or counts of wheel revolutions) that are used to calculate along track differences, and so forth. The inclusion of the measurements in the filter together with the current and the previous position related information essentially eliminates the effect of system dynamics from the system model. A position difference can thus be formed that is directly observable by the phase difference or along track difference measured between the previous and current time epochs. Further, the delta phase measurements can be incorporated in the INS filter without having to maintain GPS carrier ambiguity states. The INS sub-system and the GPS sub-system share GPS and INS position and covariance information. The receiver time tags the INS and any other non-GPS measurement data with GPS time, and then uses the INS and GPS filters to produce INS and GPS position information that is synchronized in time. The GPS / INS receiver utilizes GPS position and associated covariance information and the GPS and / or other observables in the updating of the INS filter. The INS filter, in turn, provides updated system error information that is used to propagate inertial current position, velocity and attitude information. Further, the receiver utilizes the inertial position, velocity and covariance information in the GPS filters to speed up GPS satellite signal re-acquisition and associated ambiguity resolution operations

An electronically controlled roll towel dispenser with a data communication system. The dispenser automatically dispenses a predetermined length of paper toweling from a supply roll after a length of toweling has been detached by a user pulling and tearing the protruding toweling against a stationary cutting blade. The dispenser is battery powered with an electric motor, an electromechanical dispensing mechanism, and an embedded microcontroller for controlling and monitoring operation of the dispenser. In addition to primary control functions, the microcontroller monitors parameters such as battery condition, towel usage, system status, system errors, and unsafe operating conditions. Pushbutton switches are also provided for programming towel length and the dispense delay. The dispenser further includes an optical transmitter for transmitting visual and infrared data to a receiving device. Useful information about the status of the dispenser can be visibly discerned by an operator through the use of primitive low-speed flash patterns, while high-speed infrared digital data can be simultaneously embedded in or multiplexed with the visible data.

A system and a method for rapidly diagnosing bugs of system software are apply for rapidly localizing a system program fault that causes a system error and then feeding back to a subscriber. First, according to the subscriber's requirement, a program of system fault analysis standard is preset and written into the system. Next, a plurality of fault insertion points is added into a program module of the system according to the subscriber's requirement for the precision of the fault analysis result. Then, fault management information is generated at the fault insertion points during the running process of the system program, and the management information is monitored for collecting relevant system fault data. After that, the collected system fault data is analyzed in real time through the program of system fault analysis standard, so as to obtain the minimum fault set for causing the system error.

A defect identification tool is disclosed that predicts locations at which defects in a microdevice are most likely to occur. The tool may identify both a type of defect and the particular netlists in which that defect is likely to occur. A test circuit generation tool can then subsequently use this defect information to generate a test circuit that tests for the defect in the identified portions of the microcircuit. Similarly, an automatic test pattern generation tool may use the defect location information to generate test data custom-tailored to check for faults corresponding to the identified defect in the specified portions of the microcircuit. Various implementations of the tool may be used both to identify the locations at which defects caused by systematic errors, such as manufacturing process deficiencies or flaws, are most likely to occur and the locations at which randomly-created defects are most likely to occur.

The invention relates to an operation positioning device and method and a robot operation system. The operation positioning device comprises a positioning ruler, an upper computer and a series-connection mechanical arm with at least six degrees of freedom. The upper computer is connected with the series-connection mechanical arm, the positioning ruler comprises two opposite surfaces allowing X-rays to transmit, the two opposite surfaces are fixedly connected through a connecting surface allowing X-rays to transmit, the two opposite surfaces are respectively provided with a group of marks, each group of marks comprise at least four mark points which are not located on the same straight line, and the mark points are X-ray-proof components. Any opposite surface or the connecting surface is fixedly connected with a ruler handle, and the ruler handle is connected with the tail end of the series-connection mechanical arm through a port. The upper computer adjusts the position of the positioning ruler by controlling movement of the series-connection mechanical arm, space positioning calculation is conducted according to the mark points in collected images, and a planning path is obtained. The device can achieve perspective positioning at any angle, and can eliminate system errors caused when an operation path is calculated, increase working space and improve the operation positioning accuracy.

The invention discloses a method for estimating a discontinuous orthogonal frequency division multiplying channel based on compressed sensing. The method comprises the steps of: designing a channel estimating pilot pattern, selecting a pilot pattern and estimating a channel frequency domain response. The pilot pattern is selected by using two schemes. The first scheme is to maintain a traditional uniform pilot pattern and automatically disable a pilot at a disabled sub-carrier in order that an available pilot presents a natural non-homogeneity. The second scheme is to fix the quantity of the pilots and utilize the following optimized problems to search P sub-carrier transporting pilot marks in the available sub-carrier based on a criterion of recovering matrixes correlation minimization, wherein L is the channel length, P is the number of pilots, and N is the total number of OFDM system sub-carriers. The method of the invention can be applied to various scenes of the disabled sub-carrier. Through the method of the invention with fewer pilots, the acquired channel estimating property and system error ratio property are better than those acquired by using the other methods in prior art.

A system and technique for detecting data errors in a memory device. More specifically, data errors in a memory device are detected by initiating an internal READ command or cleansing operation from a set of logic which is internal to the memory system in which the memory devices reside. Rather than relying on a READ command to be issued from an external device, via a host controller, the cleansing logic initiates a cleansing routine in response to an event such as an operator instruction or a periodic schedule. By implementing the cleansing operation, the system does not rely on external READ commands to verify data integrity. Further, a monitoring device is coupled between the cleansing logic and a memory scheduler. The monitoring device provides a feed back mechanism from which to vary the frequency of certain memory requests such as the cleansing and scrubbing operations. The cleansing routine may rely on typical ECC error logging mechanisms and may be used in a RAID memory architecture. Further, the cleansing routine may be used in conjunction with other error logging and correction logic, as well as scrubbing logic.

A power fault diagnostic mechanism for a computer system having a power system that includes a controller. A variable is recorded in a non-volatile memory associated with the power system. The variable assumes a first state when the computer system is powered on and operating. The variable remains in the first state until it enters a second state when the computer system is powered off in response to a power-off request. The controller operates in a standby mode when the computer system is powered off. Upon being powered up, e.g., after a utility power disturbance, the controller reads the variable in the non-volatile memory. This allows determination of whether a disturbance has occurred, even when the computer system was powered off. The controller maintains a local error log based on the variable accessed from the non-volatile memory. A system error log is updated by the operating system using the local error log.

System and method of estimating radio channel bit error rate (BER) in a digital radio telecommunications system wherein the soft output of the turbo decoder is used as pointer or index to look-up-tables containing the bit-wise BER of a certain bit in the data field of the received frame. A quantizer quantizes the received data frame and the quantized bit operates on a switch which selects the appropriate look-up-table. By means of accumulation and scaling the average BER of a certain amount of bits are calculated. Decoding bit-errors may occur but as they are submitted to posterior probability estimation, systematic errors which normally happen at low SNR are avoided.

The present disclosure relates to various methods for measuring the amount of an analyte present in a biological fluid using an electrochemical testing process. Various embodiments are disclosed, including the use of AC test signals and the performance of tests having a Total Test Time within about 2.0 seconds or less, and / or having a clinically low Total System Error.

The invention discloses a non-cooperative spacecraft attitude estimation method based on virtual sliding mode control, and belongs to the technical field of non-cooperative spacecraft navigation. The non-cooperative spacecraft attitude estimation method comprises the following steps: utilizing a virtual control sliding mode controller based on the Lyapunov principle; using target satellite absolute attitude obtained by a stereoscopic vision system as a control objective; according to motion characteristics of the target satellite, establishing a virtual satellite motion model of the target satellite; using a kinetic model of the virtual satellite as a controlled member to obtain attitude parameters of the virtual satellite; using attitude parameters estimated by the virtual satellite and the target satellite absolute attitude obtained by the stereoscopic vision system as controlled input, and calculating the virtual revolving moment on the motion model of the virtual satellite through the virtual sliding mode controller, so as to realize the estimation of the target satellite attitude parameters by the virtual control sliding mode controller. The non-cooperative spacecraft attitude estimation method disclosed by the invention is low in calculated amount, and can still achieve higher convergence rate and higher precision when the initial error of the state variables is high or the system error emerges, so as to meet the requirements of the high performance navigation system.

The invention discloses a structure and a design method of an improved active-disturbance-rejection position controller for a direct current (DC) motor; the DC motor is taken as a controlled object, and an output position signal is taken as a controlled variable; the controller mainly consists of four parts, i.e., a tracking differentiator, a nonlinear state error feedback part, an extended state observer and a disturbance compensation part. The improved active-disturbance-rejection position controller is mainly used to improve a fal function in a nonlinear function in the extended state observer, and the fal function is used to determine the tracking performance of the extended state observer and the controller; the concrete improvement measure is adding a linear feedback area into non-linear feedback; therefore, the problem that in the traditional method, timely control cannot be realized when the system error is too large and the gain is too low can be solved on the basis of guaranteeing system stability. By comparing simulation lines obtained before and after the improvement for the controller, the structure and the design method which are provided by the invention are proved to accelerate the output signal response speed under the condition that the position error of the DC motor is larger, thus improving the integral control performance of a system.

The present invention provides a Satellite-bone camera space image distortion correction method based on the stellar map matching, the stellar point on the image is used as referecen point, achieving the distortion correction, including following steps: (1)image segmentation, extracting the stellar facula in the image; (2) calculating areal coordinates of each facula by the centroid method, as a real coordinate; (3) processing pre-correction according to the deformation parameter obtained by the ground standardization of the camera; (4) processing stellar map matching by single frame or multiple frames Hausdorff distance stellar map matching method, calculating academic coordinate corresponding to the practical coordinate; (5) calculating deformation parameter of the image by the corresponding relation between the practical coordinate and the academic coordinate; (6) obtaining corrected image by the three steps fitting of a polynomial and interpolation method. In addition, the invention aiming at correctoon impact of the camera plain shaft point system error, provides a adaptive compensation method. The invention has small operation, evident image correcting effect, and effectively preventing the impact of the correction caused by the image noise and the input system error.

The invention discloses a reentry aircraft finite time control method based on a disturbance observer and relates to the reentry aircraft finite time control method. The reentry aircraft finite time control method belongs to the field of aircraft control technology. The reentry aircraft finite time control method comprises the following steps: a first step, establishing a reentry aircraft dynamic model, presenting a finite time gesture tracking task; a second step, performing feedback linear processing on a model which is established in the first step; a third step, providing a finite time control law; a fourth step, providing a finite time disturbance observer for estimating system uncertainty and outer disturbance; and a fifth step, providing a finite time global sliding mode control method based on the disturbance observer, and effectively improving tracking precision of a gesture control system through substituting an estimated disturbance value into the control law. The reentry aircraft finite time control method has functions of improving system error convergence speed, preventing a singular problem and improving uncertainty of the controlled system to the parameter, global robustness of outer disturbance and tracking precision.

The invention discloses a sequential approximation analog to digital converter with digital correction and a processing method thereof aiming at the defect of difficult composition manufacture of a coupling capacitor in the traditional sequential approximation analog to digital converter. The sequential approximation analog to digital converter comprises a main DAC (Digital Analogue Converter), acalibration DAC, a comparer, a control circuit and a storage. The sequential approximation analog to digital converter is characterized in that the main DAC comprises a high-K-bit CDAC (Capacitance Digital Analogue Converter) and a low-N-bit CDAC. Introduced system errors and capacitance matching errors are digitally corrected and eliminated, error voltages corresponding to capacitors in the high-K-bit CDAC are quantized and stored in the storage, and two-digit 0 are added behind the tail of the quantized residual error voltage digital code and participate in the calculation of the error voltages. When normal conversion is carried out, the error voltage digital codes are accumulated and then last two digits are discarded, the remain digital codes are used as the input of the calibration DAC, thus the accuracy of the analog to digital converter is improved.

The invention discloses a temperature compensation method for a pressure sensor. In the method, the coupling error of a measurement system of the pressure sensor can be compensated inside the sensor, and external equipment directly reads a pressure numeric value. The method is simple to operate, and benefits the avoidance of measurement error caused by secondary sampling, and the reduction of the influence of system error and lag error on a gauge point by adopting a multi-calibration averaging method. A pressure compensation curve is fitted by using gauge point reliability analysis and taking variance as weight, and the fitted compensation curve is closer to a reliable gauge point, thereby improving measurement accuracy.

The invention discloses a quad-rotor UAV fault tolerance control method based on an adaptive fault estimation observer, and belongs to the field of aviation aircraft control. The method comprises thata fault model of a quad-rotor attitude system is established according to a dynamic model of a quad-rotor UAV by considering a performer fault of a UAV system; a performer of the UAV includes four rotor motors in practicality, faults correspond to the four rotor motors, the fault model is processed, the faults are divided into two groups decoupled mutually, and a final attitude fault model is obtained; according to the provided fault model, the adaptive fault estimation observer is designed, corresponding adaptive laws are provided, the performance fault is estimated, and an H(infinite) method and an interval matrix method are used on external disturbance and parameter nondeterminacy respectively in the design process; and an attitude system error fault model is obtained on the basis of the fault model, a dynamic output feedback fault tolerance controller is designed on the basis of a fault estimated value, and fault tolerance control of the quad-rotor UAV is realized. Influence of the performer fault on performance of the quad-rotor UAV can overcome, and the safety and reliability of the UAV in the flight process are ensured fully.

The invention discloses a life prediction method of accelerated life test based on grey RBF neural network. An original curve of reliability and failure time is constructed by collecting test data; class ratio test is conducted on failure time data; a curve of reliability and accumulated failure time is constructed; three layers of RBF artificial neural network are established; RBF artificial neural network is trained; the well-trained neural network is used for prediction; and finally the prediction value of the dummy accumulated failure time obtained by prediction is reduced so as to obtain the life information of the products under normal stress. The method has no need of establishing physical accelerator model and resolving complex multivariate likelihood equation set, thereby avoiding the introduction of system error in the life prediction, solving the problem of needing a large number of training samples for artificial neural network modeling in accelerated life test, also being applied to small sample test data, and facilitating the application in actual engineering. Compared with the existing BP neural network prediction method, the life prediction precision is obviously improved.

The invention relates to a time-domain ground-air electromagnetic detection system and a calibration method, in particular to a system consisting of an induction signal recording device connected with a ground recording device global position system (GPS) synchronization unit, a closed abnormal ring and a data quality evaluation system, and a calibration method for the time-domain ground-air electromagnetic detection system. The closed abnormal ring and the induction signal recording device are adopted, the induction current and induction voltage are simultaneously recorded, and the 24-bit 200Hz sampling rate, a bandwidth of 0-13KHz and a dynamic range of an amplifier of 160dB are achieved. Moreover, the system is synchronous with a ground transmitter and an air receiver GPS, and during measurement, by removing earth background field data, a pure closed abnormal ring electromagnetic signal containing a geometric error is extracted, is input into the data quality evaluation system, andis compared and fitted with the computed closed abnormal ring theoretical value, the system error, the geometric parameter error and the detection resolution of the time-domain ground-air electromagnetic detection system are determined, and the performance of the electromagnetic detection system is tested and calibrated.

The invention discloses a position fixing navigation system (PFNS) based on a GNSS satellite and a method thereof, wherein, the method comprises the following steps: a sparse continuous service satellite positioning datum station network is established at a positioning area or the periphery of the area, the datum station carries out continuous high sampling rate observation and transmits observed data to a system center by a communication link; then, the system center processes the data provided by the datum station network to obtain high-precision real-time relevant system error correcting information; finally, the relevant system error of the user is interpolated / extrapolated according to the relevant error of the datum station network, and relevant correction and processing are carried out, thus obtaining the accurate three-dimension coordinate of the user. The invention has the advantages of high positioning precision, wide coverage area and convenient use, etc., thus being suitable for high-precision and real-time / rapid positioning application under special circumferences.

An information gathering system and method that utilizes a computer to authenticate, poll and store user responses to a customized questionnaire. The questionnaire can be a ballot. The computer utilizes various databases to authenticate and generate the customized questionnaire. The computer records user responses securely and anonymously. User and / or system errors are eliminated before finalizing the response database. An identification number is assigned to each user which allows the user to verify the integrity of the user's response by accessing a response database. The user is provided access to a tabulation database to allow the user to verify the user's voting choices and the voting choices of other voters.

An online system monitoring technique quickly and efficiently identifies failures or other system errors arising during operation of an intermediate network node, such as a network switch. The technique comprises Keep Alive Buffer packets / cells (“KABs”) that exercise data and control paths extending from every ingress port to every egress port in the switch. By exercising the data and control paths, the KABs enable testing of, and ensuring against, component failures, missing modules or other types of failure that can be detected as soon as possible, to thereby prevent data flow backup or other performance degradation in the switch.

The invention belongs to navigation methods and particularly relates to a method for combined navigation of an inertia / visual odometer / laser radar. The method comprises (1) state model establishment, (2) visual odometer speed measurement based on characteristic information, (3) establishment of a measurement equation and obtaining of a measurement value, (4) Kalman filtering and (5) system error correction. The method has the advantages that a machine vision autonomous navigation technology is used, a monocular camera can measure a vector speed under the conditions of a known distance through the difference of a front frame image and a rear frame image, the laser radar can accurately measure the distance of an observation point and then measure a vector speed, navigation is performed by utilizing combination of the speed obtained through measurement and an inertial reference speed, and high-accuracy navigation is performed finally under the conditions of no outside reference information.

This invention relates to a test method for error model verification of an inertial measurement system, which sets up a multifunction software platform to simulate and argue the airliner load test plan directly including: designing specific flying trails based on the error model of an inertial sensor, in which, an aircraft flies along the designed flying trail and collects inertial sensor data of specific flight path points and transmits them to a master navigation computer, then the collected data are compared with the data output by a measurement primary standard device to get the measurement error of the sensor to compute and get the error parameters in the inertial navigation error model with an airborne inertial navigation space multi-position online demarcating method to understand the inertial navigation performance and is convenient for the compensation in navigation computation.