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380results about How to "Avoid divergence" patented technology

Charge state evaluation method and system of power lithium ion battery

The invention is a charge state evaluation method and system of a power lithium ion battery. According to the method, step one is to establish a circuit model of an equivalent battery. Charging and discharging and standing experiments are performed on the battery, and timing sampling is performed so that a voltage time curve is obtained. Model parameters are identified via a formula so that a non-linear relation between an open-circuit voltage OCV and an SoC is obtained. Step two is to obtain an optical estimation value of the SoC by matrixes of state prediction, prediction error variance, filtering gain, state estimation, estimation error variance, etc., according to Kalman algorithm. According to the system, an analog / digital converter, a program storage device, a programmable storage device, a timer and a displayer are respectively connected with a microprocessor. A current sensor and a voltage sensor are respectively connected in a circuit formed by connecting the battery to be tested and a load, and outputs of the current sensor and the voltage sensor are accessed into the analog / digital converter. The programmable storage device stores battery model parameters obtained by the experiments. The program storage device stores estimation program of the method. Estimation precision of the SoC can reach 1%, and the charge state evaluation method and system is more stable; besides, the system provides estimation values of the SoC in real time.
Owner:GUILIN UNIV OF ELECTRONIC TECH

Multi-system dynamic PPP resolving method based on robust self-adaption Kalman smoothing

The invention discloses a multi-system dynamic PPP resolving method based on robust self-adaption Kalman smoothing. The method includes the steps that receiving machine outline coordinates and receiving machine clock bias of all systems are solved through selecting-weight-iteration pseudo-range single-point positioning, and accordingly all positioning error correction values are calculated according to an error correction model in combination with the satellite precise ephemeris and satellite precise clock bias; strict data quality control is conducted on observation data. Due to the fact that dynamic PPP accuracy is easily affected by undetected small cycle slips or the gross error and the like, an observation equation weight matrix is adjusted according to the observation value residual vectors, and the undetected small cycle slips or the gross error and other influence factors are removed; self-adaption factors are determined according to the state predictive information, and thus the influence on parameter estimation of the predictive information is controlled. By means of the method, when multi-system dynamic PPP is conducted through a single receiving machine, the feature that the number of multi-system satellites is increased greatly, on the basis that the stability of the satellite structure is guaranteed, the influence of the gross error is weaken effectively, the dynamic noise abnormity in dynamic positioning is improved, and finally the high-precision and high-stability multi-system dynamic PPP result is achieved.
Owner:SOUTHEAST UNIV

GNSS/INS/vehicle integrated navigation method for agricultural machinery operation

The invention provides a GNSS/INS/vehicle integrated navigation method for agricultural machinery operation in the technical field of navigation. The method comprises the following steps: S1, inertial navigation calculation is carried out after correction of zero offset of an inertial measurement unit (IMU), and a state transition matrix and a system covariance matrix are calculated through Kalman filtering; S2, whether GNSS information is updated is judged; if the GNSS information is updated, the GNSS information is extrapolated, filtering estimation is carried out by taking the position and speed differences between INS and GNSS as observations, the dynamic condition of the carrier is judged, correction platform error and IMU zero offset error are fed back, and the method returns to S1 for loop execution; or, the current information is the position, speed and attitude information of the carrier; and S3, whether vehicle information is updated is judged; if the vehicle information is updated, the vehicle information is extrapolated, filtering estimation is carried out by taking the speed difference between INS and the vehicle as an observation, and correction platform error and IMU zero offset error are fed back; or, the current information is the position, speed and attitude information of the carrier. The method has high navigation accuracy, and can achieve high navigation accuracy with a low-cost IMU.
Owner:WUXI KALMAN NAVIGATION TECH CO LTD

Real-time navigation system and real-time navigation method for underwater structure detection robot

The invention discloses a real-time navigation system and a real-time navigation method for an underwater structure detection robot. The navigation system comprises a magnetic compass, a gyroscope, an accelerometer, a depth meter and a navigation microprocessor, wherein the magnetic compass, the gyroscope, the accelerometer and the depth meter are used for respectively collecting magnetic field intensity, an angular speed, a linear speed and submerged depth data and transmitting the magnetic field intensity, the angular speed, the linear speed and the submerged depth data to the navigation microprocessor; the navigation microprocessor is used for calculating attitude and position of the underwater robot according to the collected data. The navigation method comprises an attitude algorithm, a speed algorithm and a depth algorithm; according to the attitude algorithm, a complementary filtering method, a quaternion gradient descent method and a Kalman algorithm are combined for obtaining an attitude matrix and an attitude angle; the speed algorithm is used for calculating the speed and the position of the robot by using a three-order upwind scheme with rotary compensation; the depth algorithm is used for processing the data of the depth meter by using a moving average filter algorithm so as to obtain the submerged depth. By virtue of the real-time navigation system for the underwater structure detection robot and the method thereof, the navigation cost is reduced and a relatively good navigation precision is achieved.
Owner:CETC NINGBO MARINE ELECTRONICS RES INST

Latitude unknown self-aligning method of strapdown inertial navigation system under dynamic interference condition

A latitude unknown self-aligning method of a strapdown inertial navigation system under the dynamic interference condition includes the steps that firstly, a geometrical analytic formula is built by means of the characteristic that the projection of gravity acceleration is unchanged in an inertial coordinate system, the gravity acceleration is subjected to integration to obtain speed information, and the latitude value of the position where a carrier is located is calculated according to the speed information; secondly, on the basis of the double-vector altitude determination principle and by means of the characteristic that the gravity acceleration of an inertial system includes north orientation information, rough solution of an initial attitude matrix under the inertial system is achieved; finally, on the basis that coarse alignment is finished, a precise alignment error model under the latitude unknown dynamic interference condition is built according to a speed error equation, a misalignment angle equation and a latitude error equation, the latitude error angle and the misalignment angle of the carrier are calculated by means of the self-adaptive filtering method based on information, the latitude value is compensated with the latitude error angle, the strapdown altitude matrix is corrected according to the misalignment angle, and high-precision quick self-aligning of the strapdown inertial navigation system is achieved.
Owner:BEIJING UNIV OF TECH

CKF filtering-based vehicle dynamic model auxiliary inertial navigation combined navigation method

The invention discloses a CKF filtering-based vehicle dynamic model auxiliary inertial navigation combined navigation method. The CKF filtering-based vehicle dynamic model auxiliary inertial navigation combined navigation method comprises the following steps: calculating posture, speed and position of a vehicle according to angle increment and specific force output by a micro-inertia device and by an inertial navigation numerical value updating algorithm; establishing a three-degree-of-freedom vehicle dynamic model, and calculating the speed of a carrier by taking a steering wheel angle and a longitudinal force as control input quantity and by a fourth order Ronge-Kutta method in real time; designing a CKF filter by taking an inertial navigation equation as a state equation and speed difference between a dynamical model and inertial navigation calculation to perform state estimation on a combined navigation system; performing output correction on strapdown inertial navigation calculation result by the position the speed and the posture error obtained by CKF estimation, and performing feedback correction on the inertial navigation through peg-top and adding error. The method aims at the problems that the inertial navigation error is accumulated along with time and navigation precision cannot be maintained for a long time, and the accuracy and the reliability of a vehicle navigation system can be improved.
Owner:SOUTHEAST UNIV

Strapdown inertial navigation system/global navigation satellite system combined based navigation filter system and method

The invention discloses a strapdown inertial navigation system(SINS) / global navigation satellite system (GNSS) combined navigation filter system comprising a primary binding module, an earth parameter calculation module, an initial alignment module, a strapdown inertial navigation calculation module, an improved filter algorithm parameter calculation module, a normal-mode combined navigation filtering module, a fault-mode combined navigation filtering module and a feedback correction output module. The improved filter algorithm parameter calculation module calculates a sate transition matrix, a system drive noise covariance matrix, and a measurement noise covariance matrix that are needed by an improved kalman filtering algorithem based on data provided by an SINS and a GNSS and transmits the information to the normal-mode combined navigation filtering module and the fault-mode combined navigation filtering module to carry out filtering calculation according to the result and a status flag. According to the invention, the combined navigation filtering algorithm is modularized, thereby obviously improving precision of the combined navigation and accelerating the convergence speed of the combined navigation filtering algorithm; and the kalman filtering divergence can be effectively inhibited.
Owner:CHENGDU GUOXING COMM

Vector search iterative matching method based on inertia/gravity matching integrated navigation

The invention relates to a vector search iterative matching method based on inertia/gravity matching integrated navigation, the vector search iterative matching method is characterized by comprising the following steps of estimating a matched search scope and a current matching performance by an inertial navigation output location; taking a correlative extremal function as a target search to determine an optimal matching transformation; performing constant weighted iteration on the result of matching position to obtain an optimal matching position finally. The vector search iterative matching method provided by the invention serves as a hub for connecting component parts of a gravity matching system; a calculating process from gravity measurement information in real time to a carrier position can be completed; an inertial navigation error range is taken as a matching scope; a global optimum solution can be obtained, and divergence can be restrained; the requirement of an initial position error is low; the error and divergence problems caused by database linear processing of gravity data can be effectively avoided; the efficiency and the property of an algorithm are improved, and the vector search iterative matching method has a strong robustness on an gravity measurement random error and an inertial navigation system variable error.
Owner:TIANJIN NAVIGATION INSTR RES INST

Robot positioning method and device based on SLAM (Simultaneous Localization And Mapping) of covariance intersection fusion

The invention discloses a robot positioning method and device based on SLAM (Simultaneous Localization And Mapping) of covariance intersection fusion. The method comprises the steps of collecting an image of a surrounding environment through a binocular camera of the robot and correcting the image to obtain the corrected image; processing the image, and further constructing a corresponding map point to obtain a state space model of the robot and an observation model of the robot on a road sign; predicting a predicted value of the robot posture at the current moment according to an optimized estimation value of the robot posture at the previous moment; obtaining an observed quantity at the current moment according to the observation model of the robot on the road sign; performing correctionupdate by use of a CI fusion-based filter method in combination with the observed quantity and the predicted value at the current moment to obtain the optimized estimation value of the robot postureat the current moment. According to the robot positioning method and device based on SLAM of covariance intersection fusion, the covariance intersection fusion algorithm is applied to the SLAM, thereby enhancing the robustness in the linear error, improving the filter precision and improving the accuracy of positioning of the robot in different practical application environments.
Owner:ZHEJIANG UNIV OF TECH

High precision real-time contour error estimation method

The invention relates to a high precision real-time contour error estimation method, belongs to the precise high efficiency numerical control processing technology field and particularly relates to the high precision real-time contour error estimation method on the basis of an initial value regeneration Newton iterative method in a numerical control parameter curve interpolation processing process. The method comprises steps that firstly, before each step of iterative calculation, according to present interpolation point parameters and actual cutter location points, an iteration parameter initial value on a parameter curve for Newton iterative calculation perpendicular foot points is calculated on the basis of a first order Taylor series expansion method; secondly, a Newton iterative method is utilized, a single step iteration parameter final value is calculated according to the iteration initial value; thirdly, for avoiding greatly increasing the algorithm calculation time, iteration is ended through double constraints of an iteration termination condition and a largest iteration frequency condition, a perpendicular foot point parameter estimate is acquired, and a contour error vector estimate is further calculated. Through the method, iteration divergence can be effectively avoided, contour error estimation precision is improved, and the method has great signification for guaranteeing contour control precision during parameter curve interpolation processing.
Owner:DALIAN UNIV OF TECH

Helicopter rotor wing type determination method and system

The invention discloses a helicopter rotor wing type determination method and a system. The method comprises the following steps: randomly generating airfoil profile sample points by adopting a Latinhypercube sampling method; according to the airfoil profile sample points, determining upper and lower airfoil profile representation equations of the airfoil profile by adopting a category shape function transformation method; carrying out dynamic characteristic simulation on the airfoil profile by adopting a computational fluid mechanics method according to the upper and lower airfoil profile representation equations to obtain flow field characteristics of the airfoil profile; establishing a mapping relationship between airfoil profile sample points and flow field characteristics by adoptinga Kriging model, and training the mapping relationship by adopting a maximum likelihood estimation method and an expected value criterion to obtain a trained mapping relationship; determining an optimal airfoil profile sample point by adopting an NSGA-II algorithm according to the trained mapping relationship; and determining the rotor wing type according to the optimal wing type sample point. The aerodynamic characteristics of the airfoil profile in the variable incoming flow-variable attack angle state are optimally designed, and the dynamic stall characteristic in the state can be effectively relieved.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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