157 results about "Integer ambiguity" patented technology

A partial ambiguity resolving method suitable for a complex dynamic environment belongs to the field of high-precision dynamic satellite navigation relative positioning, and comprises the following steps: constructing a single-epoch carrier phase double-difference difference observation equation; and calculating a weight factor corresponding to each satellite through a standardized residual error and an IGG3 method, and substituting the weight factors into the double-difference factor matrix to obtain a corrected observation value. And resolving the updated observation equation through a weighted iterative least square method. And carrying out partial ambiguity fixation on the corrected ambiguity floating point solution to obtain a whole cycle ambiguity fixed solution. And carrying out Ratio-based posteriori consistency traversal detection, monitoring the number of satellites participating in calculation in a traversal search process, and if the number of the satellites is smaller than a threshold value, outputting a floating point solution. And if the number of satellites after traversal search is greater than or equal to And substituting the fixed solution of the integer ambiguity into the updated observation equation to obtain a fixed solution of a three-dimensional relative position vector and a covariance matrix of the three-dimensional relative position vector.

The invention discloses a satellite navigation positioning method and device and a storage medium. The positioning method comprises the steps that observation parameters collected by a mobile terminal in a preset epoch are obtained, the observation parameters comprise GNSS parameters and inertial navigation correlation parameters, and the GNSS parameters comprise GNSS prior parameters and GNSS posterior parameters; the observation parameters are input into a preset positioning precision evaluation model, a precision evaluation value is obtained, and the positioning precision evaluation model is obtained based on training of historical observation parameters collected by multiple epochs; determining whether the positioning information represented by the current observation parameter is accurate based on the precision evaluation value; when it is determined that the positioning information is inaccurate, a positioning result is determined based on a floating point solution of integer ambiguity; and when the positioning information is determined to be accurate, determining a positioning result based on the fixed solution of the integer ambiguity. The method has the technical effect of improving the positioning precision and the positioning reliability of the global satellite navigation system.

The invention provides a minimum cost flow phase unwrapping method and device based on phase gradient rate assistance. The method comprises the steps that an SAR data set and DEM data of a to-be-monitored area are acquired; based on this, a differential interferogram and a coherence map are generated; respectively calculating a shortest time baseline phase gradient rate and a full time baseline phase gradient rate based on the differential interferogram; constructing a Delaunay triangulation network based on the differential interferogram and the coherence graph, and determining a rotation-free constraint and a design matrix; on the basis of the coherence graph, the shortest time baseline phase gradient rate and the full time baseline phase gradient rate, performing weight determination on each triangular arc segment in the triangulation network to obtain a weight corresponding to each triangular arc segment; and based on the non-rotation constraint, designing a matrix and weights corresponding to the triangular arc segments to solve the integer ambiguity, and completing a phase unwrapping task based on the integer ambiguity. According to the embodiment, the absolute phase of the large-gradient deformation area is obtained, so that high-precision deformation monitoring of the earth surface is realized.

The invention discloses an ambiguity determination method for satellite positioning, a terminal and a medium in the field of satellite navigation and positioning, and the method comprises the steps: obtaining observation data of a base station and a mobile station, eliminating errors through employing a double-difference technology, and carrying out the cycle slip correction, and obtaining the corrected observation data; preliminarily estimating the speed and position of the mobile station; based on the corrected observation data, extracting an optimal ambiguity subset through satellite-level and ambiguity-level screening; constructing a factor graph model by using the optimal ambiguity subset, taking the preliminarily estimated speed and position of the mobile station as initial values, minimizing an error function in a factor graph, and optimizing to obtain a floating solution of ambiguity; obtaining an integer ambiguity solution based on the floating point solution; and verifying the stability of an ambiguity resolving result through consistency, and finally obtaining an ambiguity fixed solution. According to the method provided by the invention, high precision, high efficiency and high stability of ambiguity calculation are realized, and the method is suitable for a high-precision satellite positioning system in a complex environment.

The invention provides a GNSS (Global Navigation Satellite System) integer ambiguity estimation method and equipment based on improved particle swarm optimization, which are used for realizing rapid and accurate estimation of high-dimensional integer ambiguity and comprises the following steps of: performing integer Gaussian transformation parameterization on floating point ambiguity and a variance-covariance matrix thereof; taking a minimum optimal integer candidate vector residual quadratic form as fitness, and establishing an ambiguity search target function; performing direct rounding estimation on the floating point ambiguity to obtain a search initial value; determining a search space of each ambiguity component by combining the floating point ambiguity and the median error after integer Gaussian transformation; setting an improved particle swarm optimization method, and setting a dynamic inertia weight, a dynamic learning factor, a boundary detection and control model, an adaptive iteration model and a scale factor improvement model; and performing optimal and suboptimal integer ambiguity candidate vector estimation, and obtaining a corresponding residual quadratic form. The method can be used for ambiguity calculation of non-difference ambiguity, dual-frequency and ionosphere-free combination models, and can also be popularized to other GNSS integer ambiguity estimation problems.

An integer ambiguity validation method includes: obtaining, at an apparatus in conjunction with the one or more receivers, a plurality of feature values that are based on satellite signals received by a mobile device; determining, at the apparatus, an integer ambiguity vector indicative of integer numbers of carrier phase cycles of the satellite signals between the apparatus and respective satellites; determining, at the apparatus, a probability of the integer ambiguity vector being correct by using the integer ambiguity vector in a machine learning algorithm; and determining, at the apparatus, whether the integer ambiguity vector is correct based on the probability of the integer ambiguity vector being correct and an integer ambiguity vector probability threshold.

The invention relates to a combined attitude determination technology, in particular to a high-precision combined attitude determination method based on a multi-antenna GNSS (Global Navigation Satellite System) and an INS (Inertial Navigation Satellite System), which comprises the following steps of: S1, fixing a GNSS receiver and the INS on a carrier; s2, calculating carrier position information and carrier speed information, and establishing a double-difference carrier phase observation model; s3, calculating a baseline vector predicted value between the antennas; s4, an LAMBDA algorithm model based on INS attitude information constraint is constructed; resolving the IC-LAMBDA algorithm model by using a least square method to obtain an optimal integer solution of the integer ambiguity; s5, calculating a baseline vector between the antennas; carrier attitude information is solved; and S6, fusing the GNSS navigation information and the INS navigation information by using an extended Kalman filter. The method solves the problems of low attitude measurement precision and poor scene adaptability of the existing integrated navigation technology, and is suitable for the fields of unmanned aerial vehicle control, unmanned vehicle driving, unmanned agricultural machinery seeding, marine navigation surveying and mapping and the like.

The embodiment of the invention discloses a precision positioning acceleration method and device based on a low earth orbit satellite / LSTM neural network. The method comprises the steps that a terminal obtains a wide lane phase decimal deviation product, a narrow lane phase decimal deviation product and a first GNSS combination observation value which are generated by a server based on an LSTM method and are subjected to coding processing; determining a first GNSS wide lane real number ambiguity according to the first GNSS wide lane real number Based on a precise point positioning algorithm, determining initial GNSS ionosphere elimination combination real ambiguity and other parameters; performing inter-satellite single difference on the first GNSS wide-lane real number ambiguity, and obtaining the integer ambiguity by combining wide-lane phase decimal deviation product fixation; performing inter-satellite single difference on the initial GNSS ionosphere-free combination real ambiguity, determining a first GNSS narrow-lane real ambiguity by combining the wide-lane integer ambiguity, and fixing the first GNSS narrow-lane real ambiguity by using a narrow-lane phase decimal deviation product through a partial ambiguity fixing method to obtain the integer ambiguity of the narrow-lane phase decimal deviation product; and calculating a user coordinate fixed solution in combination with related parameters.

The embodiment of the invention provides a satellite-based positioning method and device, electronic equipment, a storage medium and a program product. The method comprises the following steps: obtaining the integer ambiguity of a first satellite, and determining the real ambiguity of a second satellite abandoned in the process of resolving the satellites; determining the integer ambiguity of the second satellite according to the real ambiguity of the second satellite; according to the integer ambiguity of the first satellite and the integer ambiguity of the second satellite, the position information of the electronic equipment used for receiving the signals of the satellites is determined, and the effects of increasing the ambiguity of the available satellites and improving ambiguity fixing performance and positioning performance are achieved.

The invention discloses a real-time GNSS satellite clock error estimation and analysis method based on different references, and relates to the technical field of satellite navigation positioning, and the method comprises the steps: data input, which is used for collecting needed real-time data; the data provides necessary basic information for a subsequent processing flow; the data processing is used for data processing of real-time clock error estimation; in the operation process of a GNSS, the accuracy of time is directly related to the satellite-ground distance, and then the positioning precision of a user is influenced. Therefore, ensuring time accuracy becomes a core element of GNSS design and operation. According to the real-time GNSS satellite clock error estimation and analysis method based on different references, real-time satellite clock error estimation is carried out by adopting epoch difference ionosphere-free combination observation values. The method can effectively eliminate ionosphere delay and integer ambiguity, significantly reduce the number of to-be-estimated parameters, and further improve the precision and efficiency of real-time clock error estimation.

A pseudo-range hardware delay calibration method and device are suitable for a single-station receiver, and the method comprises the following steps: carrying out precise point positioning ambiguity fixation (PPP-AR) positioning estimation on a single station based on a satellite-based enhancement service (SSR) correction number, and determining integer ambiguity information; estimating the receiver ionosphere-free combination pseudo-range hardware delay of each satellite of a single station by using the ionosphere-free pseudo-range observation value combination and the ionosphere-free carrier wave observation value combination in combination with the integer ambiguity information, the pseudo-range in the SSR service and the phase clock error correction; the method comprises the following steps: estimating receiver MW pseudo-range hardware delay of each satellite of a single station by using wide lane combination (MW) observation value combination and integer ambiguity information in combination with uncalibrated phase delay and uncalibrated phase deviation (UPD) correction in SSR (Simple Sequence Repeat) service; based on receiver ionosphere-free pseudo-range hardware delay and receiver MW pseudo-range hardware delay, hardware delay information of each satellite and each frequency point of the single-station receiver is separated. According to the embodiment of the invention, the pseudo-range hardware delay calibration of the single-station receiver is realized.

The present invention discloses a method for calculating the integer ambiguity of a dual-frequency single-epoch single-satellite short-baseline inter-station single-difference carrier phase, which performs inter-frequency difference on the inter-station single-difference carrier phase information, eliminates the influence of satellite clock error, ionosphere and troposphere errors, and inter-station clock error, and solves the ambiguity of the single-epoch single-satellite dual-frequency through integer ambiguity constraints and short-baseline geometric constraints, and uses an error rate calculation formula based on the carrier phase random error variance value. The present invention can complete ambiguity fixation when the single-epoch single-satellite dual-frequency points are complete, does not require inter-satellite multi-channels, and has high calculation efficiency; the present invention solves the problem that the carrier phase ambiguity fixation under the condition of pseudo-range information failure or unreliability cannot be used under the condition of antenna-satellite geometric configuration constraints.

The invention discloses an ionosphere activeness rapid determination method and device based on a double-difference observation model, and belongs to the technical field of navigation positioning and ionosphere monitoring. The method comprises the following steps: acquiring observation station GNSS satellite observation data, and constructing a double-difference carrier phase observation equation; performing data quality screening on the received observation station GNSS satellite observation data; estimating an integer ambiguity parameter and a troposphere parameter according to the screened GNSS satellite observation data and the constructed double-difference carrier observation equation; according to the estimation results of the integer ambiguity parameter and the troposphere parameter, resolving to obtain an ionosphere residual error; and carrying out compression quantization on the ionized layer residual error information obtained by calculation to obtain the active degree of the ionized layer in the region. According to the invention, the feasibility and reliability of high-precision positioning of the user through the CORS service during the active period of the ionosphere are guaranteed.

The invention discloses an unmanned aerial vehicle dog RTK positioning method based on singular value robust Kalman filtering. The method comprises the following steps that 1, a robot dog GNSS receiver obtains satellite and base station data; 2, constructing a double-difference observation equation; the method comprises the following steps of: 1, carrying out a floating point ambiguity vector nK, 2, carrying out singular value robust Kalman filtering, and 4, carrying out integer ambiguity fixing and fixed solution calculation, fixing a floating point ambiguity vector nK as an integer ambiguity vector, and solving an integer non-ambiguity state vector # imgabs0 #, namely, a final robot dog receiver r position fixed solution. According to the method, the ambiguity fixing probability is improved, and the RTK positioning robustness of the unmanned aerial vehicle dog is improved.

The invention relates to the technical field of Beidou reference correction, in particular to a Beidou-based space-time reference dynamic correction method. The method comprises the following steps: firstly, collecting Beidou multi-frequency-point observation data, and preprocessing by adopting a Kalman filtering algorithm; then, based on the preprocessed data, a base station network time synchronization mechanism is established by using Beidou satellite signal propagation time difference, spatial reference data of different base stations are integrated through a multi-sensor fusion algorithm and a least square method, and smoothing processing is performed by using a spatial interpolation algorithm; thirdly, selecting an optimal baseline combination based on a space-time synchronization result, constructing a difference observation equation of a Beidou multi-frequency carrier phase and a pseudo range, fixing integer ambiguity by adopting an LAMBDA algorithm, and establishing a unified space-time reference model; and finally, resolving the clock error of the high-precision receiver by utilizing the double-difference integer ambiguity constraint, generating a correction parameter, and dynamically adjusting and updating the correction parameter by adopting a model algorithm. According to the invention, high-precision dynamic correction of the space-time reference is realized.

The invention relates to the technical field of GNSS high-precision positioning, and provides a BIE-based real-time dynamic positioning integer ambiguity resolving method and system, and the method comprises the steps: obtaining a preliminary ambiguity subset through the screening of a satellite elevation angle and a carrier-to-noise ratio, and carrying out the correlation reduction processing; a multi-level screening mechanism is adopted and comprises three stages of dynamic optimization of coarse screening, fine screening and candidate group generation; a weight distribution model is improved based on Laplacian distribution to calculate candidate solution weights and probability weighted fusion is carried out; in combination with an ILS and BIE mixed fixing strategy, BIE weighted averaging is adopted when ILS fixing fails; a positioning result is optimized through dynamic satellite screening and multi-system data fusion, and a jump detection threshold value is set to realize abnormal recalculation. The method improves the reliability of real-time dynamic positioning, and guarantees the continuous and stable operation of the system in a signal shielding or multi-path interference scene through a jump detection and recalculation mechanism.

The invention discloses a partial ambiguity resolving method and device, a medium and equipment, and relates to the technical field of satellite navigation and positioning. Based on the concept that in the partial ambiguity resolving process, after multiple-dimensional ambiguity corresponding parameters are removed, the more accurate the whole-cycle ambiguity resolving based on the remaining ambiguity related parameters is, the more stable the resolving of partial parameters corresponding to partial-dimensional ambiguity subsets is, the invention proposes that in each round of partial ambiguity resolving process, the more accurate the whole-cycle ambiguity resolving is, and the more accurate the whole-cycle ambiguity resolving is, the more stable the resolving of partial parameters corresponding to partial-dimensional ambiguity subsets is. According to the current ambiguity related parameters and the integer ambiguity, and different parameter parts corresponding to ambiguity subsets of different dimensions in the current ambiguity related parameters and the integer ambiguity, respectively solving baseline fixed solutions for multiple times to obtain multiple groups of baseline fixed solutions; the difference between the maximum value and the minimum value in the multiple groups of baseline fixed solutions is compared with the preset threshold value, the stability of the integer ambiguity solution is judged, and the accuracy and the reliability of the partial ambiguity solution are improved by utilizing the statistical characteristics of the ambiguity integer solution.

The invention relates to the cross technical field of satellite navigation, satellite dynamics and the like, in particular to a dynamic orbit determination method based on integer ambiguity fixation, which can obviously improve orbit determination and extrapolation precision, and comprises the following steps: establishing a dynamic orbit determination model, establishing a GPS observation model, and then performing integer ambiguity fixation IAR, a single-difference IAR method adopting single receiver ambiguity correction specifically comprises the steps that firstly, GPS carrier phase observation is divided into continuous tracking segments for processing, for each tracking segment, an average Hatch-Melbourne-Wubbena (HMW) combination is constructed by means of double-frequency pseudo-range and carrier phase data, then cross-segment inconsistency is corrected, integers of wide lane ambiguity are achieved, and a single-receiver ambiguity correction result is obtained. And the corrected wide lane ambiguity is combined with an IF ambiguity floating point estimation value obtained by a least square method for use, and finally, the IF ambiguity difference is constrained as an integer value to realize the fixation of the single-difference ambiguity, and compared with the prior art, the orbit determination precision can be remarkably improved.

A positioning method, device and system and a storage medium are used for improving positioning precision. In the application, a first device determines a first integer ambiguity according to first measurement information. The first measurement information comprises time measurement information and / or carrier phase measurement information. The first measurement information is obtained by performing measurement based on the at least one first reference signal. The first device may also obtain first information indicating a reliability of the first integer ambiguity. Since the first information indicates the reliability of the first integer ambiguity, the positioning precision can be improved by positioning based on the first information and the first integer ambiguity.

The present invention relates to a global satellite navigation terminal and its navigation and positioning method. The global satellite navigation terminal includes a satellite navigation antenna, first and second satellite navigation receivers; and a processing module. The processing module performs the following operations: calculating zero-baseline double-difference observations based on the satellite navigation data of the two satellite navigation receivers, and calculating an observation random noise matrix based on the zero-baseline double-difference observations; calculating single-difference observations based on the observations in the satellite navigation data of one satellite navigation receiver and the corrections obtained from a navigation server, and performing robust adaptive filtering iterative estimation of a robust adaptive parameter vector based on the calculated single-difference observations and the observation random noise matrix; searching for and fixing the integer ambiguity based on the floating-point ambiguity in the robust adaptive parameter vector, and re-solving the robust adaptive parameter vector based on the fixed ambiguity. In this way, high-precision positioning can be achieved based on a more reliable observation random noise model.

The invention relates to a canyon building area Beidou base station site selection optimization method based on multi-base station difference, and the method is characterized in that the method comprises the following steps: S1, initializing parameter setting and base station selection; s2, comparing and updating double-difference integer ambiguity; s3, calculating the fitness value of each base station, evaluating the quality of a base station signal according to the fitness value, comparing the fitness value with the fitness value of the passed best position pbest, and if the fitness value is better, updating the pbest; and comparing the fitness values of all the base stations with the fitness value of the global best position gbest, and if the fitness values are better, updating the gbest. Compared with the prior art, through the multi-base-station difference technology and the optimization algorithm, in combination with the double-difference integer ambiguity and the fitness value, optimization of site selection of the Beidou base stations in the canyon construction area is achieved. The positioning precision is improved through double-difference processing, the optimal base station position is dynamically updated through the fitness value and the optimization algorithm, the method is suitable for complex terrains, and base station signal coverage and quality are ensured.

The invention discloses a joint correction method and system for GNSS (Global Navigation Satellite System) non-structural deformation and a storage medium. According to the method, GNSS pseudo-range and carrier phase observation data and precise products such as a precise orbit and clock correction are obtained, a three-component displacement time sequence caused by a non-tidal atmospheric load, a non-tidal ocean load and a land hydrological load and a temperature-driven thermoelastic displacement time sequence are constructed, and the three-component displacement time sequence and the temperature-driven thermoelastic displacement time sequence are unified to a reference frame and a time system consistent with GNSS calculation. After interpolating the non-structural displacement vector to an observation epoch according to time, converting the non-structural displacement vector to a geocentric rectangular coordinate system from a site local coordinate system ENU, and projecting the non-structural displacement vector to a sight line direction from a satellite to an observation station reference point to form an equivalent geometric distance correction item; the correction terms are respectively applied to pseudo-range observation and carrier phase equivalent meter domain observation in the form of the same domain as observation, and then GNSS daily arc precise calculation is performed to output a coordinate time sequence, and preferably, the method can be used for a precise single-point positioning integer ambiguity fixing technology.

The application discloses a ground absolute microwave ranging method and system based on double-path echo and RTK differential measurement, which can apply carrier phase ranging to absolute ranging. The system adopts RTK differential measurement to solve the phase integer ambiguity, especially simultaneously differentiates the observation values of two ends of the ranging main terminal, solves the extra error introduced by the traditional RTK double difference in the two-point transfer differential value, and finally compensates the error by using an atmospheric refraction correction structure model, so that the sub-millimeter level precision is achieved under the kilometer level measurement distance.

This invention discloses a GNSS integer ambiguity fixing method integrating intelligent optimization algorithms and VIB strategies, belonging to the field of satellite navigation and positioning technology. This method combines the advantages of VIB strategies and swarm intelligence fusion optimization algorithms. By directionally grouping the ambiguity floating-point solution covariance structure, the ambiguities are guided into groups. The PSOAF and AWDE intelligent optimization algorithms are used to perform parallel searches on the grouped ambiguities, improving search efficiency and positioning accuracy. Simultaneously, the probability assessment and fixing judgment of the integer solutions of each sub-block ambiguity and the overall ambiguity ensure the reliability of the ambiguity solutions, making it suitable for complex and dynamic GNSS positioning scenarios.

The application provides a method and device for determining wide-lane integer ambiguity, electronic equipment and VRS system. After the first single-difference wide-lane float ambiguity of a satellite is calculated, the trend error of the single-difference wide-lane float ambiguity is used to correct the first single-difference wide-lane float ambiguity, so as to reduce the error caused by the multipath effect on the first single-difference wide-lane float ambiguity. The corrected first single-difference wide-lane float ambiguity is used to determine the wide-lane integer ambiguity of the satellite in the first time period, so as to suppress the influence of the multipath effect on the observation accuracy of the reference station, improve the correctness of the calculated wide-lane integer ambiguity, and further improve the accuracy of the subsequent positioning and other related calculations through the wide-lane integer ambiguity.

A method of determining an integer ambiguity search space includes: obtaining, at an apparatus, a code phase measurement of a satellite vehicle signal comprising a pseudorandom noise code and a carrier signal; obtaining, at the apparatus, spatial information corresponding to a wireless terrestrial signal transferred between the apparatus and a terrestrial base station; determining, at the apparatus, a satellite positioning system carrier phase integer ambiguity search space based on the code phase measurement; and constraining a size of the satellite positioning system carrier phase integer ambiguity search space based on the spatial information.

The present invention relates to a method for solving floating-point solution coordinates of a modified RTK mobile station differential equation, characterized in that the method comprises the following steps: (1) obtaining the moving speed of a receiver by using Doppler frequency shift velocity measurement; (2) calculating the average moving speed of the receiver between the last solution time and the current time by using the fixed solution coordinates obtained in the previous solution and the floating-point solution coordinates of the current RTK mobile station differential equation; and (3) correcting the floating-point solution coordinates of the current differential equation by using the difference between the moving speed of the receiver obtained in step (1) and the average moving speed calculated in step (2). The present invention uses Doppler frequency shift velocity measurement to obtain the precise speed of the receiver, and uses the difference between the two speeds to correct the floating-point solution coordinates of the current differential equation, so that the floating-point solution coordinates are closer to the fixed solution coordinates, thereby improving the efficiency of solving integer ambiguity.

This application is applicable to the field of positioning and orientation technology, and provides a satellite orientation device, including: a satellite orientation chip and a satellite positioning chip connected to the satellite orientation chip; the satellite orientation chip is configured to determine the first integer ambiguity and the position information of the target vector based on the first pseudorange observation, the first carrier phase observation, the second pseudorange observation, the second carrier phase observation, the first positioning information, the second positioning information, the determined third pseudorange observation, the third carrier phase observation, and the third positioning information of the satellite orientation chip relative to the first satellite, and a preset observation equation; determine the accuracy of the position information based on the first integer ambiguity and the preset integer ambiguity, and determine the direction information of the target vector based on the position information when the accuracy meets the preset requirements, thereby reducing the cost and power consumption of the satellite orientation device and improving the accuracy of orientation.

The application provides a method for determining integer ambiguity candidate solutions, comprising the following steps: determining integer ambiguities that meet a predetermined condition in an ambiguity search space; calculating a weight corresponding to each integer ambiguity; and determining a weight proportion function value corresponding to each integer ambiguity according to the weight, and screening out a predetermined number of integer ambiguities that meet the condition as ambiguity candidate solutions.

The present invention provides a block unwrapping method for a large-scale interseismic interference pattern and related equipment, which divides the interseismic interference pattern of a study area into several sub-blocks with overlapping areas; inputs each sub-block into a trained neural network for integer ambiguity prediction to obtain the integer ambiguity and confidence of each pixel point in each sub-block, takes the average of the confidence of all pixels in each sub-block to obtain the confidence of each sub-block, and re-unwraps the corresponding sub-block or corrects the integer ambiguity of each pixel point in the corresponding sub-block according to the size of the confidence of each sub-block to obtain the updated integer ambiguity of each pixel point in each sub-block; splices the updated integer ambiguity of each pixel point in each sub-block to obtain the integer ambiguity map of the interseismic interference pattern, and obtains the unwrapping interference pattern based on the integer ambiguity map and the interseismic interference pattern, thereby greatly improving the unwrapping accuracy of the isolated island area.