40 results about "Double star" patented technology

The invention discloses an optimal matching double-star SAR fusion imaging method based on CRLB. A global navigation satellite system (GNSS) has the advantages of all-weather operation, wide space coverage and the like, and although a GNSS-R SAR technology in which reflected signals of the GNSS are used for imaging of a ground synthetic aperture radar (SAR) is low in cost and wide in application, the resolution ratio of the GNSS is poor due to the fact that the bandwidth of the GNSS signals is limited. According to the method, an SAR fusion imaging system model composed of a plurality of satellites and a single ground fixed GNSS receiver is established, the mutual relation between a fuzzy function of a GNSS signal and Fisher information is explored, and a system Cramer-Rao lower bound (CRLB) influenced by a bistatic set geometric configuration is deduced. On the basis, a CRLB expression is adopted to identify satellites in the optimal resolution direction of the ground target, and according to the principle that the included angle between the optimal resolution directions is as close as 90 degrees as possible, the imaging results of the selected satellites are subjected to incoherent fusion. By means of the method, unnecessary redundant imaging processing is avoided, and it is ensured that imaging resources are utilized most reasonably. And the resolution performance of the system is improved in a more efficient manner.

A double-satellite formation satellite lightweight autonomous task planning and scheduling method based on multi-objective optimization realizes double-satellite formation satellite autonomous task planning and scheduling with optimal comprehensive efficiency on the basis of on-satellite constraints, and ensures high-precision inter-satellite pointing and inter-satellite spacing maintenance during long-term operation of double satellites. According to the invention, the space between two satellites, the execution capability of a satellite thruster and the like are taken as constraints, a task planning mathematical model is established, formation reference satellite scheduling and orbit / attitude control strategy generation are carried out based on multiple optimization targets, and on-satellite full-autonomous, lightweight and optimal-comprehensive-efficiency rapid autonomous task scheduling is realized.

The invention discloses a method for carrying out correlation and orbit determination on a space target based on a double-star optical observation result, and the method comprises the steps: obtaining the observation vectors of two observation stars for a certain space target in the respective visual fields, calculating the shortest distance between the observation vectors, and if the distance is always smaller than a threshold value in a time sequence, determining that the space target does not exist. And if not, determining that the two observation stars observe the same space target, calculating a midpoint of two observation vector common vertical lines of the same space target by the two observation stars as an orbit determination point, and performing orbit determination on the space target based on an orbit determination point sequence. According to the method, a low-cost space-based optical orbit determination mode is adopted, space target association is completed through an algorithm with low calculation cost, target consistency is judged based on observation vector distance constraints, a complex model or a large amount of calculation power is not needed, efficient processing can still be performed when the number of targets is large and the data size is large, and the cost and efficiency advantages are remarkable.

The invention provides a large-breadth sea surface detection and non-uniform resolution intelligent imaging system based on a double-star SAR, and the system comprises a large-breadth sea surface detection system which is used for carrying out the large-breadth sea surface detection based on a collected SAR echo signal; the intelligent imaging system performs non-uniform resolution intelligent imaging based on the detection result of the large-width sea surface detection; the SAR emission subsystem adopts a phased-array antenna to carry out high-gain narrow-beam scanning emission in a range-direction large-width area, and covers a large-range sea surface area; the SAR receiving subsystem adopts a multi-channel antenna to carry out wide-range parallel receiving on echo signals; the SAR receiving subsystem is configured with a DBF processing module and a resource management and control processing module; and the SAR emission subsystem carries out signal emission based on the antenna beam parameters and the emission signal parameters fed back by the resource management and control processing module. The invention has the advantage of high echo power density, and can effectively reduce the requirement on the sensitivity of a receiving system.

The application discloses a kind of optimal matching double star SAR fusion imaging methods based on CRLB.Global navigation satellite system (GNSS) has the advantages such as all-weather operation and extensive spatial coverage, although the GNSS-R SAR technology for ground synthetic aperture radar (SAR) imaging using reflected signal of GNSS is low in cost and widely used, but because the bandwidth of GNSS signal is limited, its resolution is poor.The application establishes the SAR fusion imaging system model by multiple satellites and a single ground fixed GNSS receiver, explores the interrelation between the ambiguity function of GNSS signal and Fisher information, and deduces the system Cramer-Rao lower bound (CRLB) affected by the geometry configuration of bistatic setting.On this basis, the satellite in the optimal resolution direction for ground target is identified by using CRLB expression, and the imaging results of selected satellite are incoherently fused according to the principle that the included angle between optimal resolution directions is as close to 90 degrees as possible.Through this method, unnecessary redundant imaging processing is avoided, and imaging resources are most reasonably used.The resolution performance of the system is improved in a more efficient way.

The present invention discloses a low dry-to-noise ratio interference detection method and a positioning method based on a multi-beam double-star system, including: determining the interference frequency according to the main satellite interference, and establishing an interference model of the main satellite interference and the secondary satellite interference based on this; performing matched filtering on the interference forwarded by the two multi-beam satellites to the ground receiving station to improve the dry-to-noise ratio between the interferences; performing wavelet decomposition on the interference after matched filtering to obtain wavelet coefficients of different scales and frequencies; then determining a threshold, performing threshold processing on the wavelet coefficients to remove the noise coefficients and retain the interference coefficients. Using the retained interference coefficients for wavelet reconstruction to obtain the denoised interference. The present invention breaks through the double-star positioning limitation condition that the double stars need to jointly cover the interference source, and can realize the positioning of the interference source in a vast area, providing an effective tool for the positioning and troubleshooting of the interference source in the multi-beam satellite communication system.

An inter-satellite pointing target attitude high-precision real-time online prediction method, first, the ground uses the orbit determination program corrected by on-orbit data observation to generate a double-satellite orbit position and velocity value sequence in a predetermined time period, and samples according to the control period, then for each sampling time, the double-satellite orbit position and velocity is used to establish the local orbit coordinate system, and the component of the target star position vector in the local orbit coordinate system is calculated, the pitch and yaw target attitude angle values are calculated according to the target attitude angle definition, the pitch target angle sequence is linearly averaged and estimated, the average orbit period value and the long-term change rate parameter are calculated, and the modified sequence after deducting the long-term change rate is given, for the pitch target angle correction sequence and the yaw target angle sequence, data of a specified average orbit period number is taken from a specified initial time, the fitting coefficient is calculated, finally the generated fitting coefficient is uploaded to the satellite, and the satellite uses the high-precision fitting determination formula to calculate the inter-satellite pointing target attitude angle online every control period.

A method for detecting relative orbital maneuvers of spacecraft based on cluster analysis includes: reading the TLE historical data of the master star of the spacecraft formation and calculating the instantaneous orbital elements, using the SGP4 model for recursion to obtain the orbital state at the moment when the latitude angle is 0; reading the TLE historical data of the slave star of the spacecraft formation and calculating the instantaneous orbital elements, using the SGP4 model to recursively calculate the orbital state at the same time as the master star data, and realizing the time synchronization of the dual-star data; calculating the relative distance of the spacecraft formation, and performing data denoising and normalization to obtain a data set; using the silhouette coefficient to determine the number of clusters, that is, the number of orbital maneuver types; using the fuzzy C-means algorithm for cluster analysis, obtaining a clustering result based on the relative distance of the spacecraft orbit, and realizing orbital maneuver detection. The method of the present invention can effectively avoid the influence of human subjective cognition and experience on the judgment of orbital maneuvers, meet the timeliness requirements of orbital maneuver detection, and significantly improve the accuracy of orbital control maneuver detection.

The present invention discloses a method and system for optimizing the orbital parameters of a double star, including: Step 1) According to the six orbital elements of the primary star, calculate the time interval to obtain the <time, position, velocity> information matrix of the primary star and the theoretical solution set of the <time, position, velocity> information matrix of the secondary star; Step 2) Set the constraint conditions, establish an optimization model for the orbit of the secondary star, and according to the set solution granularity, use the dynamic mutation genetic algorithm. By setting the mutation operation probability that changes dynamically with the iteration step size, optimize the six orbital elements of the secondary star to obtain the actual solution of the <time, position, velocity> information matrix of the secondary star, and use the number of occurrences of the actual solution in the theoretical solution set as the fitness function; Step 3) Calculate the fitness function to obtain the continuous duration of maintaining communication between the two stars of the double star, and judge whether the continuous duration remains unchanged. If it is judged to be yes, go to Step 4), otherwise, go to Step 2); Step 4) Output the positions of the primary star and the secondary star that meet the conditions.

The invention discloses a navigation mode transition method, an electronic device and a medium, in a working process of a first navigation mode, geometric angles among a mother satellite, a service spacecraft and space debris are monitored, and when the geometric angles meet a mode switching requirement, the position of a target orbit under a J2000 coordinate system is obtained through double-satellite geometric estimation; and taking the position as an initial position calculated in the second navigation mode, and switching to the second navigation mode. Before the navigation mode is switched, the target orbit position is determined through double-satellite geometric estimation, the single-satellite navigation positioning precision can be rapidly improved, a good initial value is provided for double-satellite angle measurement filtering, and the convergence process is accelerated.

The invention discloses an astronomical experimental device for simulating the photometric change of double food stars, and the device comprises a fixing unit which comprises a supporting part located at the lower part, an angle display part disposed at the top end of the supporting part, and a length display part transversely disposed on the angle display part. The limiting component is arranged on the angle display component, and the angle display component and the length display component are connected in series through the limiting component; the limiting unit comprises a fixing part located on the length display part and an adjusting part arranged below the fixing part. The invention provides a device capable of meeting more use requirements, improving the use efficiency of the device, facilitating the smooth proceeding of experimental work, and providing a device capable of recording the luminosity change and simulating the luminosity change conditions of different stages of a food double-star experiment by controlling the movement and the shielding degree of a star, so that the experimental efficiency of the food double-star experiment is improved. And thus, a scientific research scheme in the aspect of eating double stars in astronomy can be better assisted for working personnel.

The invention relates to a double-star electromagnetic formation dynamics modeling and control method for a port Hamiltonian system. The method comprises the following steps: defining two slave spacecraft mass center position coordinates in an ECI coordinate system and an LVLH coordinate system; kinetic energy and potential energy of the slave spacecraft under the ECI coordinate system are obtained according to the position coordinates of the mass center of the slave spacecraft; obtaining a Lagrange function L under an LVLH coordinate system according to the slave spacecraft mass center position coordinate and the coordinate system conversion matrix; establishing an Euler-Lagrange equation, selecting a generalized momentum coordinate pj according to Legendre transformation to obtain a Hamiltonian function H, and establishing a port Hamiltonian kinetic model; designing an electromagnetic formation controller according to a trajectory tracking passive control method based on interconnection-damping distribution; and obtaining an electromagnetic satellite formation trajectory tracking magnetic dipole intensity control law according to the electromagnetic formation controller. According to the method, the nonlinear term of the system is reserved, the inherent dissipation characteristic of the system is reflected, the problem that the precision of the system is reduced due to linearization can be avoided, and the passivity of the system is ensured.

This invention discloses a near-space target localization method based on dual-satellite imaging, comprising: simultaneously acquiring original observation images of the same target using two low-Earth orbit (LEO) satellites; acquiring the centroid coordinates of the target region in the two original observation images respectively, and performing coarse localization based on the centroid coordinates to obtain the coarse localization point coordinates of the near-space target; performing forward path correction to generate a simulated image of the target observed by the two LEO satellites under the current localization; performing residual correction on the estimated spatial position of the target to obtain the residual-corrected spatial position of the target; and repeating the above steps based on the residual-corrected spatial position in the current iteration until the iteration conditions are met to obtain the precise localization of the target. By constructing a closed-loop technical scheme of "dual-satellite synchronous imaging - coarse localization - non-uniform atmospheric and imaging system effect coupling correction - image centroid comparison - iterative optimization", the accurate inversion of the three-dimensional position of near-space targets can be achieved.

The present invention discloses a parallel method and device for accelerating the search pipeline of pulsar Fourier domain, including: allocating received astronomical data to multiple parallel processes; each process includes three serial sub-threads, using the first CPU sub-thread to pre-process the allocated astronomical data, using the GPU sub-thread to read the pre-processed data and perform accelerated calculation on the GPU to obtain candidate signal data, using the second CPU sub-thread to read the candidate signal data and perform post-processing and result aggregation, while using queues and queue blocking locks of multiple parallel process architectures to synchronize the task status between sub-threads; dynamically adjusting the number of processes in the processing flow through monitoring feedback; recording the task status and the calculation results of each process in real time and handling abnormal situations. The present invention can effectively improve the pulsar binary search process, and support the use of multi-GPU parallel acceleration, greatly improving the speed of searching for this type of celestial body from FAST astronomical data.

The application provides a method and device for optimal resource allocation decision of star group cooperative observation of space targets. The method comprises: obtaining input parameters, state parameters, constraint parameters and optimization variable parameters; based on the input parameters, the state parameters and the constraint parameters, calculating a benefit coefficient of observation of each target by each satellite, and updating each benefit coefficient based on the optimization variable parameters; calculating a cost coefficient matrix of double-star cooperative observation of targets according to the updated benefit coefficients, and constructing an optimal resource allocation decision model based on the cost coefficient matrix, so as to allocate satellite resources by using the optimal resource allocation decision model. According to the scheme, real-time and rapid optimal solving on the star can be facilitated, so that optimal resource allocation is realized.

This invention relates to a clustering method for observation targets based on continuous observation constraints of two satellites, comprising the following steps: at each moment, determining whether the observation target is physically potentially visible relative to the satellite using off-axis angle constraints and detection distance constraints; when the observation target is physically potentially visible relative to the satellite, using direction vector similarity analysis to extract the spatial nearest neighbor targets of the observation target, constructing a set of satellite line-of-sight candidate directions pointing towards the geometric center of the observation target group; selecting the optimal satellite line-of-sight candidate direction that covers the most observation targets from the set of satellite line-of-sight candidate directions; and setting the sliding window length to seconds, selecting the optimal set of observation targets at each moment within the sliding window, and taking the intersection of all optimal sets of observation targets to select the intersection target group that is always located in the optimal field of view corresponding to the optimal satellite line-of-sight candidate direction within the sliding window as the continuous observation target set.

The application discloses a kind of double-star formation SAR high-keeping imaging method and device, first to the main star raw echo and auxiliary star raw echo of double-star formation SAR system is carried out spectrum pre-filtering processing, filter out the phase error between main and auxiliary images caused by non-overlapping range beam spectrum and azimuth beam spectrum;Establish the relationship equation set of Doppler characteristics and transmission slant range, solve the accurate value of target point and transmission slant range component, calculate main and auxiliary star imaging parameters;Using hyperbolic equivalent method and ECS imaging algorithm, main and auxiliary stars are simultaneously imaged, and high-keeping main and auxiliary star SAR images are obtained simultaneously, to realize double-star integrated SAR imaging.The above-mentioned method and device can realize high-keeping imaging to double-star formation SAR raw echo, reduce development cost and can realize good focusing effect, ensure timeliness, suitable for engineering application double-star SAR data fast imaging processing.

The invention provides a GNSS deception jamming tracking method and system based on double satellites, and the method comprises the steps: carrying out the related operation of deception jamming received by two satellites when the deception jamming transmitted by the same deception jamming source is transmitted to the two satellites; performing short-time coherent integration operation; carrying out fast Fourier transform; taking a plurality of continuous fast Fourier transform results as a group, and performing incoherent integral operation; finding out a maximum value; judging the maximum value by using a set threshold value; when the tracking channel can be configured, configuring the tracking channel based on the delay time corresponding to the maximum value and the spectral line ordinal number of the fast Fourier transform; and repeatedly executing the steps to obtain a sequence of combination of the delay time and the fast Fourier transform times, wherein the sequence is an interference tracking result. The method has the advantages that the method is suitable for a double-satellite monitoring and positioning system, and a solution is provided for solving the problem of current double-satellite-based GNSS deception interference tracking.

The application discloses a space-based space target trajectory segmentation fitting method based on infrared radiation characteristics, and comprises the following steps: (1) acquiring initial positioning information of a space target in a ground-fixed coordinate system through double-star joint observation; (2) monitoring the infrared radiation intensity of the space target in real time through an infrared sensor, identifying the classification points of the space target in different flight stages according to the infrared radiation intensity and signal-to-noise ratio change, and completing target trajectory segmentation; (3) for different flight stages, the least square method is introduced through an adaptive factor, the trajectory optimization fitting of the space target in the space-based scene is completed, high-precision positioning and tracking are realized, and the motion characteristics of the target are acquired. By using the application, the overfitting or underfitting problems in the traditional method can be reduced, so that the precision and reliability of space-based space target detection and tracking are improved, and the application is suitable for a complex space target observation environment.

The invention provides a satellite-borne monostatic / bistatic synthetic aperture radar (SAR) bunching imaging combined time sequence construction method and system. The method comprises the following steps: acquiring main and auxiliary satellite parameters; constructing the pulse repetition frequency of the monostatic / bistatic SAR system based on double-star observation geometry; constructing a bunching imaging primary satellite single-base transmitting / receiving time sequence; constructing a beaming imaging mode cosatellite bistatic receiving time sequence; and outputting main and auxiliary satellite transmitting and receiving time sequences. According to the method, a unistatic / bistatic SAR combined time sequence construction method is effectively broken through, multi-constraint PRF combined optimization, bistatic time sequence cooperative fault tolerance and space-variant characteristic source inhibition measures are provided, and the problems of bistatic transceiving separation, time-frequency synchronization, space-variant compensation and the like which cannot be dealt with by a traditional unistatic SAR time sequence construction method are solved; and a set of complete bistatic time sequence construction system is formed, and the engineering practical value is higher.

The invention discloses a space-based double-star asteroid positioning detection method and system, and belongs to the technical field of asteroid positioning detection, and the method comprises the steps: S1, comparing and analyzing images shot by a space-based constellation at the same time, numbering stars in the images one by one, comparing the positions of the stars in the two images, and screening out asteroids; s2, measuring the center distance between the asteroid image and the observation image, and measuring the offset angle of the asteroid in combination with the view field of the telescope; and S3, calculating the relative position coordinates of the asteroid relative to the earth according to the deviation angle of the asteroid. According to the invention, a simple, accurate and continuous asteroid observation scheme and a positioning method and system can be provided, and reliable reference is provided for prevention of asteroid threats.

The application discloses a kind of space laser communication transceiving systems and methods with multi-wavelength self-loop test function, solve the problem that after laser communication load is launched into orbit, existing technology cannot carry out fast on-orbit self-checking to optical communication transceiving subsystem device, module, circuit etc..The application forms self-test loop light path to the transmitted multi-waveband high-speed laser signal by switching the polarization state of high-speed laser signal, using the principle that polarization beamsplitter group reflects S light and transmits P light, before implementing double-star chain building, self-checking test of the star can be realized, and the transmitting light path is not affected, only need to switch laser polarization state, through single byte telemetry data, the on-orbit state of optical communication transceiving subsystem can be judged, under the urgent condition that satellite transit time is short and test steps are many, on-orbit self-checking test can be quickly and effectively completed.

The application discloses a kind of navigation star library construction methods of approximate uniform distribution under small field of view condition, comprising: (1) using VMT algorithm, set threshold to SAO star table is segmented, only keep following navigation star, store in star library StarLib;(2) in star library StarLib, eliminate the navigation star of brightness and position not fixed, star distance value is too small, that is, eliminate variable star and binary star, obtain basic star library (StarLib1);(3) using approximate uniform distribution of spherical spiral reference point, according to the angle distance between reference point and star, star, the combination characteristics of three star density to rough navigation star, obtain preliminary navigation star library (StarLib2) and alternative star library (StarLib3);(4) on the basis of StarLib2, using KernelSVM-SMO from nonlinear distribution StarLib3 star library, select navigation star, calculate the average value of angle distance between selected star and existing navigation star in current field of view, judge whether less than set threshold, to effectively avoid redundant star, obtain final navigation star library (StarLib4).

A kind of double star formation satellite lightweight autonomous task planning and scheduling method based on multi-objective optimization, the method based on on-board constraint, realize the comprehensive performance optimal double star formation satellite autonomous task planning and scheduling, ensure the high-precision inter-satellite pointing and inter-satellite distance keeping during long-term operation of double star.This application takes the distance between double stars and the execution ability of satellite thruster as constraints, establishes a mathematical model of task planning, generates formation reference star scheduling and orbit / attitude control strategy based on multi-optimization objectives, realizes the full autonomy, lightweight, comprehensive performance optimal rapid autonomous task scheduling on board.

The application discloses a double-star fly-around orbit design method and system and electronic equipment. The core algorithm of the method is a new double-star global coverage algorithm improved from a grid point method and a Monte Carlo algorithm, a related coefficient k value range in initial orbit parameters of micro-nano satellites is determined according to micro-nano satellite parameters, double-star global observation fly-around coverage is calculated according to the initial orbit parameters meeting the related coefficient k value range, space station coverage is determined, double-star fly-around configuration coverage characteristics of the whole surface of the space station are analyzed, and the double-star fly-around orbit facing the whole surface observation of the space station is obtained. The application can effectively provide a model, a method and a basic design idea for global patrol monitoring of the surface of the space station.

The invention discloses a space-based space target trajectory segmentation fitting method based on infrared radiation characteristics, and the method comprises the following steps: (1), obtaining the initial positioning information of a space target in an earth-fixed coordinate system through double-satellite combined observation; (2) the infrared radiation intensity of the space target is monitored in real time through an infrared sensor, grading points of the space target in different flight stages are recognized according to the infrared radiation intensity and signal-to-noise ratio changes, and target track segmentation is completed; and (3) aiming at different flight stages, by introducing a least square method of an adaptive factor, completing trajectory optimization and fine fitting of a space target in a space-based scene, realizing high-precision positioning and tracking, and obtaining motion characteristics of the target. By utilizing the method, the problem of over-fitting or under-fitting in a traditional method can be reduced, so that the precision and reliability of space-based space target detection and tracking are improved, and the method is suitable for a complex space target observation environment.

The present invention provides a time differential navigation method based on a pulsar binary system, and belongs to the field of aerospace navigation technology. Since isolated millisecond pulsars are scarce and unevenly distributed in space, the present invention adopts a pulsar binary system with a specific time propagation delay, and establishes an observation pulse phase model on a spacecraft according to the inherent spin phase and time propagation delay of the pulsar binary system, and linearizes to obtain a navigation measurement model based on the binary system. In order to suppress system errors such as pulsar direction error and linearization error in the measurement model, a time differential model based on the binary system is used, that is, differentials are performed between adjacent filtering periods. Isolated pulsars can be regarded as a special case of the present invention. The present invention can use isolated pulsars and pulsar binary systems for navigation at the same time, expand the range of navigation stars, solve the problem of the small number of currently available pulsars, effectively suppress the influence of system errors, and improve the accuracy of the navigation system.

The invention discloses a satellite-borne laser terminal rotary table pointing zero offset calibration method using double star sensors. Relates to the technical field of spacecraft attitude measurement and pointing control crossing, in particular to a satellite-borne laser terminal rotary table pointing zero offset calibration method using double star sensors. According to the method, a complete attitude transfer chain model is established, inertial attitude data output by a platform star sensor and inertial attitude data output by a terminal star sensor are fused, so that the measurement relative attitude of the terminal star sensor relative to a satellite platform is constructed, and the measurement attitude and a pre-established theoretical attitude chain model are subjected to high-precision alignment; a nonlinear estimation model about the azimuth coding angle zero offset and the pitching coding angle zero offset of the rotary table is constructed, the azimuth and pitching zero offset values of the rotary table can be autonomously estimated in an on-orbit mode with high precision by solving the problem, and finally on-orbit autonomous calibration of the pointing zero offset of the rotary table is achieved. The whole process does not need ground intervention, and the autonomy and long-term stability of satellite pointing control are effectively improved.

The invention provides a design method and device for a double-satellite-following low-ambiguity mixed polarized SAR system, and belongs to the technical field of radars, and the method comprises the steps: transmitting orthogonal circularly polarized waves through two SAR satellites, carrying out the collaborative observation of the same scene, obtaining the polarization information of a static target, and forming a double-satellite-following distributed mixed polarized SAR system; carrying out registration and phase synchronization on a double-star image in the distributed hybrid polarimetric SAR system followed by double satellites to obtain hybrid polarimetric SAR data; and reconstructing a low-ambiguity complete polarization scattering matrix based on the mixed polarization SAR data. According to the invention, the application potential of the polarimetric SAR system is improved, and the defects of low observation breadth, low resolution and low observation range of a complete polarization mode are overcome.

The application provides a method and device for double-star fault identification, electronic equipment and a storage medium, applied to the technical field of satellite navigation, and singular value space vectors and singular value space matrices are obtained by singular value decomposition of an observation coefficient matrix in pseudorange observation. Then, a singular value fault plane is constructed by using the singular value space matrix under double-star fault. Considering the influence of observation noise, whether there is double-star fault can be determined by the angle between the singular value space vector and the singular value fault plane. Through this geometric determination algorithm, the problem of being affected by the identification threshold in double-star fault identification is effectively solved, thereby avoiding the occurrence of missed detection and false alarm.