71 results about "Radio navigation" patented technology

The invention relates to the technical field of underwater navigation and positioning, and particularly discloses a wide-area very-low-frequency radio navigation and underwater sound combined underwater navigation and positioning method, which comprises the following steps that: a very-low-frequency navigation transmitting station transmits a very-low-frequency radio navigation time service signal; the semi-submersible acoustic beacon receives a very-low-frequency radio navigation time service signal; performing position calibration and time synchronization; the semi-submersible acoustic beacon emits an underwater acoustic navigation signal, and the underwater carrier calculates the three-dimensional coordinates of the underwater carrier according to the received underwater acoustic navigation signal. According to the invention, a shore-based very-low-frequency radio navigation and underwater sound combined navigation mode is adopted, and a very-low-frequency radio navigation time service signal has a certain underwater entry depth, so that the problem of time synchronization between semi-submersible acoustic beacons is solved, and auxiliary calibration of the positions of the semi-submersible acoustic beacons is provided; the semi-submersible acoustic beacon emits an underwater navigation signal to realize navigation and positioning of a deepwater underwater carrier, and reliable navigation service with wide area coverage, high precision and low power consumption is provided for the underwater carrier.

The invention belongs to the technical field of radio wave propagation, and particularly discloses a three-dimensional FDTD complex path ASF prediction method based on multiple GPUs. According to the method, the three-dimensional FDTD algorithm is realized through multiple GPUs, and the method is used for predicting the ASF on a complex path. The method comprises the following steps: firstly, preprocessing parameters, and copying the parameters to a device end, namely a GPU end; secondly, updating an electric field component in the whole calculation area; then updating the field source, and exchanging the electric field components # imgabs0 # and # imgabs1 # on the adjacent GPUs; updating the magnetic field component in the whole calculation area; and finally, circulating and judging an end condition, and outputting the ASF when the calculation is finished. The method solves the problem of poor ASF prediction precision caused by the fact that a two-dimensional time delay prediction method cannot consider the transverse effect, overcomes the defect that a traditional three-dimensional FDTD method is difficult to simulate large-area low-frequency ground wave propagation, and provides a theoretical basis and technical support for improving the service precision of a low-frequency radio navigation time service system.

The invention provides a satellite signal processing method and device, equipment, a storage medium and a product. The method is applied to terminal equipment, the terminal equipment comprises a satellite radio navigation service (RNSS) receiving unit and a satellite radio determination service (RDSS) receiving unit, and the method comprises the following steps: obtaining local Beidou time based on a satellite signal received by the RNSS receiving unit; according to the corresponding satellite transmission time delay, calculating to obtain total transmission time delay; on the basis of the local Beidou, according to the total transmission time delay, the transmitting time of the target RDSS signal is predicted; performing error analysis on the emission time of the target RDSS signal, and determining corresponding time uncertainty; measurement is carried out through the RNSS receiving unit, Doppler frequency shift between the satellite and the terminal equipment is determined, and corresponding frequency uncertainty is obtained; and receiving the RDSS signal through an RDSS receiving unit according to the transmitting time, the corresponding time uncertainty and the corresponding frequency uncertainty.

The invention relates to the technical field of radio navigation and countering, and particularly discloses an unmanned aerial vehicle interference system and device based on phased array radar direction finding. The system comprises a phased array radar direction finding module, an environment electromagnetic propagation characteristic modeling module, an interference beam dynamic planning module and a digital beam forming interference module. Through constructing a three-dimensional electromagnetic propagation model and based on propagation loss and a multipath effect predicted by the model, a beamforming weight used for pre-compensating environmental influence is optimized and calculated, and finally an interference antenna array is driven to radiate an intelligent beam subjected to environmental pre-compensation, so that high-intensity interference is formed at an actual physical position of a target unmanned aerial vehicle, and the target unmanned aerial vehicle is subjected to environmental pre-compensation. Direction finding errors are overcome, and interference efficiency and electromagnetic compatibility are improved.

The invention introduces a Doppler radio direction finding system, which relates to the technical field of radio navigation and comprises an antenna array unit, a radio frequency switch matrix, a logic controller, a single-channel receiver and a signal processing unit. The logic controller drives the radio frequency switch matrix to alternately execute clockwise and anticlockwise antenna scanning actions in a single measurement period, and the signal processing unit respectively extracts phase slopes corresponding to forward and reverse scanning, generates an environment error component according to the sum of the two phase slopes and identifies a specific antenna oscillator at a standing wave node. The logic controller responds to the feedback instruction and physically skips the conduction operation on the specific antenna oscillator in the subsequent time sequence, the physical symmetry of positive and negative scanning and an environment feedback mechanism are utilized, environment standing wave interference is actively avoided on the premise that radio frequency channels are not increased, and qualitative change improvement of anti-multipath direction finding precision under a single-channel system is achieved.

According to the bionic butterfly and the flight control system thereof disclosed by the invention, intelligent flight of the bionic butterfly is realized in a breakthrough manner by fusing a high-precision radio navigation module and a multi-stage environment perception control system; based on polar coordinate positioning of VOR / DME signals and a course deviation dynamic correction algorithm, the navigation precision is improved to a navigation level standard; an original five-mode switching architecture (including a sudden strong wind emergency mechanism) realizes millisecond-level mode arbitration and wing-tail cooperative control through three-dimensional perception of real-time wind speed, wind direction and duration. The deep combination of bionic and engineering mechanics not only reproduces the wave type energy-saving flight path of the butterfly in the nature, but also greatly improves the wind resistance and reduces the energy consumption through the innovative designs of free falling obstacle avoidance, asymmetric flapping and the like.

The invention discloses a robust adaptive fusion filtering astronomical attitude determination method and system, and belongs to the technical field of radio navigation. The method comprises the following steps: constructing an integrated navigation model of a starlight and inertial integrated navigation system based on Lie group description; obtaining an observation residual error and an observation residual error covariance of a corresponding mode; robust and adaptive mode parallel sub-filtering is carried out, and posterior states and covariances in the two modes are updated; updating the mode probability; and fusing the updated posterior state with the covariance to obtain fusion output of parallel sub-filtering, taking the fusion output of the parallel sub-filtering as final estimation of the starlight and inertial integrated navigation system based on Lie group description, and outputting an astronomical attitude determination result containing an azimuth angle, a pitch angle and a roll angle. The high-precision astronomical attitude determination method has strong adaptability, strong robustness and accuracy when coping with complex noise and measuring outliers, and can realize high-precision astronomical attitude determination of starlight and inertial integrated navigation in a complex dynamic environment.

The invention relates to the field of radio navigation, and discloses a multi-parameter early warning method and system based on ground disaster monitoring equipment, and the method comprises the steps: obtaining rainfall, soil moisture content and environment temperature and humidity parameters, and gradually displaying the generated carrier fluctuation and environment disturbance through a collection process; performing time period-by-period arrangement on the multi-parameter sampling data, and extracting corresponding satellite positioning residual errors and environment variable amplitudes when instantaneous fading, rainfall pulsation and soil moisture change superposition occur in a satellite link; performing section-by-section deconstruction on the base line of the bottom layer, and combining displacement change, rainfall sudden increase and soil humidity fluctuation of adjacent monitoring points to construct an abnormal identification surface for evaluating the reliability of satellite positioning; re-regularizing the interference degree of the hidden signal gap on the satellite resolving link according to a time sequence; and carrying out delayed abduction on the pushing trend of slight deformation of the slope body. The method has the advantage of improving the reliability of ground disaster monitoring based on satellite positioning.

The present invention relates to the field of radio navigation system state evaluation. Provided is a radio navigation system state evaluation method based on multi-dimensional data-augmented learning. The method comprises: acquiring function operation monitoring data of a radio navigation system, and selecting data associated with system health; performing sliding window processing on the selected data, so as to obtain sample data including time information; dividing the sample data into a training set, a first test set and a second test set, and constructing positive and negative samples; establishing and training a contrastive learning model; establishing and training a deep one-class support vector machine; and using output results of the contrastive learning model and deep one-class support vector machine for the test sets to complete evaluation. In the present invention, deep features of measured data are learned by means of contrastive learning, and the deep one-class support vector machine is used to construct a state evaluation model. The present invention has the advantages of high detection precision and interpretability, has important theoretical and engineering practice significance, and realizes precise quantitative evaluation of the health state of an airborne radio navigation system.

The invention belongs to the technical field of radio wave propagation, and particularly discloses a rugged topography path low-frequency ground wave propagation characteristic prediction method based on an FD algorithm, and the method comprises the steps: firstly building a 3DPE model under an irregular topography, then building a discretization matrix equation, combining boundary impedance conditions based on a unilateral approximation method, and then carrying out the iteration solving of a field matrix, thereby achieving the prediction of the rugged topography path low-frequency ground wave propagation characteristic. And finally, the magnetic field intensity and the secondary time delay of radio wave propagation are solved by utilizing a field result in the whole calculation area. According to the method, the problem that low-frequency ground wave propagation characteristics are not accurately represented in transverse irregular terrain modeling through a 2DPE method is effectively solved, and meanwhile, the limitation that low-frequency ground wave propagation prediction precision is insufficient in a complex rugged terrain environment through a traditional 3DPE model is overcome; theoretical guidance can be provided for performance optimization of a low-frequency radio navigation time service system, and the navigation positioning and time service precision in a complex terrain area is further improved.

The invention discloses a GNSS (Global Navigation Satellite System) navigation anti-interference antenna for an intelligent boat and an anti-interference method thereof, which belong to the technical field of GNSS radio navigation and comprise an antenna array, an anti-interference signal processing unit, an AIS (Automatic Identification System) receiving module and a data fusion processing module. The anti-interference signal processing unit forms space null in an interference coming direction through a self-adaptive digital beam forming algorithm so as to suppress and suppress interference; and the data fusion processing module performs kinematics cross validation on the external reference ship information acquired by the AIS receiving module and the GNSS positioning result of the ship so as to accurately identify deception interference and output an alarm. According to the invention, through dual mechanisms of suppression suppression and cheating verification, the reliability and safety of radio navigation positioning of the intelligent boat in a complex electromagnetic environment can be significantly improved.

1. Name of the product in this design: Network Positioning Device. 2. Application of this design: Net position indicator for radio navigation and positioning of fishing nets or fishing boats. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

Anti-interference device for satellite radionavigation signal receiver The invention relates to an anti-interference device (10, 30, 40, 50) comprising: - an analog-to-digital converter (12) configured to transform a received analog radionavigation signal into a digital signal comprising a plurality of samples;- at least one pre-cumulative filter (22) adapted to a modulation of the transmitted signal, each filter corresponding to an impulse response filter, substantially equal to a waveform of the transmitted signal, allowing for the accumulation of samples and operating at the sampling frequency of the received signal, and delivering at the output a filtered complex signal, said device further comprising at least one first amplitude processing module (24) configured to process the amplitude of said filtered complex signal, said first amplitude processing module being both downstream of said pre-cumulative filter and upstream of at least one signal demodulation channel. Figure for the abbreviation: Figure 1;

The present application relates to a kind of rotation accelerometer gravity gradiometer attitude error post-processing compensation method, comprising the following steps: step 1, original motion data is acquired using the inertial measurement unit fixed with gravity gradient sensor, and the positioning and speed information provided by radio navigation are combined to complete original data acquisition;Step 2, the attitude error of gravity gradient sensor in the measurement process is optimally estimated;Step 3, based on the coordinate transformation matrix of gravity gradient tensor under different coordinate systems, the error compensation of gravity gradient measurement value is carried out, and finally the gravity gradient measurement data after attitude error compensation is obtained.The present application can be used in dynamic measurement environment, and the measurement information of carrier motion is measured using gyroscope and accelerometer, the attitude error of gravity gradient measurement component is estimated and compensated offline with high precision, and then the dynamic measurement precision of rotation accelerometer gravity gradiometer is improved.

The embodiment of the invention provides an interactive multi-model factor graph integrated navigation method based on tight coupling attitude constraint. In a specific embodiment, the method comprises the following steps: constructing an integrated navigation system; constructing an inertial measurement unit factor pre-integrated by the inertial navigation system; constructing a direct celestial navigation factor and a refraction celestial navigation factor which are respectively and tightly coupled with an inertial measurement unit factor based on the star sensor observation condition of the celestial navigation system; constructing a horizontal radio navigation factor and a vertical radio navigation factor based on the position information of the land-based radio navigation system; acquiring height measurement data of the barometric altimeter to construct barometric altimeter factors; dynamically adjusting the weight ratio of the height measurement data of the vertical radio navigation factor to the height measurement data of the barometric altimeter factor through an interactive multi-model algorithm; and carrying out global state estimation of the integrated navigation system on a factor graph framework formed by the factors.

The utility model relates to the technical field of radio navigation, in particular to a height-adjustable automatic guide vehicle navigation radar shield mechanism, which comprises a radar guide vehicle and a radar mounting base, a quick-release bolt is inserted in one side of the radar mounting base in a penetrating manner and is rotatably connected with the radar mounting base, the quick-release bolt comprises a bolt rod assembly, and one end of the bolt rod assembly is rotatably connected with a rotating ring. A clamping hoop is installed on the outer side of the tightening latch assembly, a rubber strip adheres to one side of the clamping hoop, a plug block is arranged on the inner side of the tightening latch assembly in an inserted mode, an annular groove is formed in the circumferential direction of the plug block, an inserting groove is formed in the inner side of the plug block, a protruding block is embedded in the inner side of the plug block, a pointing groove is formed in the outer side of the plug block, and the tightening latch assembly comprises a rotating rod. The protective cover can complete vertical displacement on the radar mounting base by means of the sliding groove, and the height of the protective cover can be flexibly adjusted, so that the protective cover can adapt to navigation radars with different mounting heights and boundary dimensions, and the limitation of an immobilized structure on equipment type selection is broken through.

The present application provides an outdoor positioning method and device, which is applied to a ground positioning server in a positioning system, and the method includes: obtaining signal reception information collected by each drone and corresponding receiving station location information; determining multiple distance differences based on the signal reception information, wherein there is a measurement error between the distance difference and the true value due to noise; estimating the position of the target object based on the multiple receiving station location information and the multiple distance differences to determine the target position. In this way, the ground positioning server in the present application obtains the signal reception information about the target object collected by each drone to obtain multiple distance differences, and then obtains the target position through the distance differences and the receiving station location information, thereby improving the accuracy and efficiency of the ground positioning server in measuring the position of the target object, effectively reducing the measurement error of the drone, and thus improving the accuracy of radio navigation.

The invention relates generally to the radio navigation field and may be applied to design of Global Navigation Satellite System (GNSS) Receivers, and particularly of GNSS GPS (USA), Galileo (EU), Glonass (Russia), Beidou (China), QZSS (Japan), IRNSS (India), and augmentation systems SBAS (different states). In the invention, the function of generating various PRN codes is repositioned from numerous tracking channels of multi-frequency, multi-constellation GNSS receiver to a shared PRN code generator unit, which serves in series all tracking channels. Such centralization of the PRN codes generation function enables a significant complexity reduction when the GNSS receiver includes a great number of tracking channels. A sufficient speed performance of the shared PRN code generator is achieved due to transfer of the PRN code lines from the shared PRN code generator to the receiver tracking channels via a dedicated parallel bus. Speed performance requirements to the dedicated parallel bus of the shared PRN code generator is kept moderate by a special number of symbols choice of PRN code lines thus providing uniformity of tracking channels requests to get new code lines. Use of several alternate means of PRN code lines forming: PRN Code ROM, PRN Code RAM, LFSR-based and one-shot PRN code generators - permits choosing optimal generation means for each type of GNSS signals.

The invention discloses a method for realizing digital signal processing of a VOR receiver based on an FPGA (Field Programmable Gate Array) technology, which relates to the technical field of radio navigation and digital signal processing and comprises the following steps of: constructing a VOR full-digital simulation signal source, and simulating signal input in a VOR system; performing digital down-conversion and filtering processing on the received radio frequency signal, and separating a variable phase signal and a reference phase signal through a digital filter; calculating a phase difference by adopting a zero-cross detection method; all the modules are integrated into an FPGA system, and performance testing is carried out. According to the invention, not only can the angle measurement precision, real-time performance and anti-interference capability of the VOR receiver be improved, but also the defects of large temperature drift and large size of the traditional analog receiver can be overcome, the characteristics of reconfigurability and parallel processing of the FPGA are utilized, the requirements of miniaturization and high reliability of modern aviation navigation equipment are met, the upgrading and updating of the full-digital VOR technology in the aviation field are promoted, and the application prospect is wide. And powerful technical support is provided for safe aviation flight.

The invention relates to a land-based area radio navigation system and method based on a Beidou ground-based augmentation system, and belongs to the field of radio navigation. The method comprises the following steps: selecting at least four appropriate foundation enhancement base stations according to service area characteristics; transforming the selected ground-based augmentation base station into a regional radio navigation base station, and constructing a regional radio navigation system by using the existing power supply and network infrastructure of the ground-based augmentation base station; the regional radio navigation base station broadcasts a radio navigation signal; and the terminal receives the regional radio navigation signal, and demodulates and resolves the regional radio navigation signal so as to obtain position information. According to the invention, cost reduction and benefit increase of the land-based area radio navigation system can be promoted.

The present invention relates to the field of radio navigation, and discloses an NDB antenna tuning system with a preemptive logic of "whoever uses it controls it", comprising a remote end, a local end, a preemptive logic control circuit, and a tuning circuit. The remote end and the local end are respectively connected to the input port of the preemptive logic control circuit through different interfaces, the display synchronization output interface of the preemptive logic control circuit is respectively connected to the interface of the display circuit of the remote end and the local end, and the tuning selection output interface is connected to the tuning circuit, so as to realize the preemptive logic control function of "whoever uses it controls it". The system realizes the convenience and controllability of the staff in debugging and maintaining the NDB antenna tuning unit, greatly improves the efficiency of collaborative work, and saves labor costs.

The application introduces a kind of Doppler radio direction finding system, and relates to radio navigation technical field, including antenna array unit, radio frequency switch matrix, logic controller, single channel receiver and signal processing unit.The logic controller drives radio frequency switch matrix to alternately execute clockwise and counterclockwise direction antenna scanning action in single measurement cycle, signal processing unit extracts corresponding phase slope of positive and negative direction scanning respectively, generates environment error component according to the sum of two and identifies specific antenna oscillator at standing wave node, and logic controller responds to feedback instruction to physically skip on-off operation of the specific antenna oscillator in subsequent timing.The application uses physical symmetry of positive and negative scanning and environment feedback mechanism to actively avoid environment standing wave interference without increasing radio frequency channel, and realizes qualitative change promotion of multipath direction finding precision under single channel system.

The present invention provides an automatic tuning method for aircraft radio navigation, which includes obtaining the estimated position A of the aircraft and K navigation stations within a preset range; calculating the distances between the aircraft and each navigation station; forming navigation station pairs in pairs, and calculating the angles between each pair of navigation station pairs and the estimated position A of the aircraft; calculating the distances between the navigation station pairs and the estimated position A of the aircraft, and selecting the navigation station pair with the shortest distance from the estimated position A of the aircraft; calculating the navigation performance ANP value β of each group of navigation station pairs; obtaining a new navigation station pair for automatic tuning; comparing the new navigation station pair with the current navigation station pair to determine whether to switch to the new navigation station pair. The method designed by the present invention has rigorous logic and strong practicability, avoids the parameters for calculating the effective navigation distance in the traditional method, reduces the calculation amount, and can avoid the frequent switching problem of the navigation station pair during tuning.

The present invention discloses a method, device and medium for checking land-based aviation radio navigation signals. The method comprises the following steps: receiving navigation measurement data and navigation station information data, performing validity check on the land-based navigation measurement data; if the data is invalid, issuing an alarm and tuning to other navigation stations to reacquire the data; if the data is valid, performing rationality check on the land-based navigation measurement data; if the data is unreasonable, issuing an alarm and tuning to other navigation stations to reacquire the data; if the data is reasonable, maintaining the current navigation station and reacquiring the data; after completing the validity check, the present invention infers the navigation measurement data based on the positions of the aircraft and the navigation station, and then performs rationality check on the actual measurement data; if there is invalid or unreasonable data, issuing an alarm and notifying the radio tuning module to tune to other navigation stations, thereby realizing a secondary check on the validity and rationality of the land-based navigation radio signal.

A system and method to opportunistically receive and use measurements on a priori unknown radio signals, not intended for radio navigation or geolocation, in conjunction with aiding data to improve navigation / geolocation position and time estimation yield and accuracy.

The invention relates generally to the radio navigation field and may be applied to design of Global Navigation Satellite System (GNSS) Receivers, and particularly of GNSS GPS (USA), Galileo (EU), Glonass (Russia), Beidou (China), QZSS (Japan), IRNSS (India), and augmentation systems SBAS (different states). In the invention, the function of generating various PRN codes is repositioned from numerous tracking channels of multi-frequency, multi-constellation GNSS receiver to a shared PRN code generator unit, which serves in series all tracking channels. Such centralization of the PRN codes generation function enables a significant complexity reduction when the GNSS receiver includes a great number of tracking channels. A sufficient speed performance of the shared PRN code generator is achieved due to transfer of the PRN code lines from the shared PRN code generator to the receiver tracking channels via a dedicated parallel bus. Speed performance requirements to the dedicated parallel bus of the shared PRN code generator is kept moderate by a special number of symbols choice of PRN code lines thus providing uniformity of tracking channels requests to get new code lines. Use of several alternate means of PRN code lines forming: PRN Code ROM, PRN Code RAM, LFSR-based and one-shot PRN code generators—permits choosing optimal generation means for each type of GNSS signals.

A system for controlling an impedance matching circuitry can include an antenna, a receiving or transmitting circuitry, an impedance matching circuitry, a circuitry, and a controller. The impedance matching circuitry can be coupled between the antenna and the receiving or transmitting circuitry. The circuitry can be configured to set a value of an impedance of the impedance matching circuitry. The controller can be configured to determine, based on a state of an electronic device, that the electronic device is configured to perform one or more functions with one or more of a satellite radio navigation signal at a first or a second frequency, a wireless local area network signal at a third or a fourth frequency, or a personal area network signal at a fifth or a sixth frequency. The controller can be configured to control, in response to a determination of the state of the electronic device, the circuitry.

The present application relates to the field of radio navigation, and discloses a multi-parameter early warning method and system based on ground disaster monitoring equipment, wherein the multi-parameter early warning method based on ground disaster monitoring equipment comprises acquiring rainfall, soil moisture content and environmental temperature and humidity parameters, and gradually showing the generated carrier wave fluctuation and environmental disturbance through the collection process; the multi-parameter sampling data is implemented hour-by-hour segment arrangement, and when satellite link appears transient fading, rainfall pulsation and soil moisture change superposition, the corresponding satellite positioning residual error and environmental variable amplitude are extracted; the segment-by-segment deconstruction is carried out on the bottom baseline, combined with the displacement change of the adjacent monitoring point, the sudden increase of rainfall and the soil humidity fluctuation, the abnormal identification surface for evaluating the satellite positioning reliability is constructed; the interference degree of the hidden signal gap to the satellite solution link is re-regularized according to the time sequence; the delay extension of the promotion trend of the slight deformation of the slope body is carried out. The present application has the advantage of improving the reliability of satellite positioning-based ground disaster monitoring.

The application relates to the field of satellite navigation and timing technology, in particular to a Beidou and INS (inertial navigation system) fused real-time high-precision timing method, which comprises the following steps: generating pseudo-range residuals and code-minus-carrier based on Beidou satellite signals, and generating satellite channel fuzzy vectors by applying fuzzy reasoning; performing spatial clustering based on the multi-dimensional features of satellite signals, and configuring parallel sub-filters for satellite clusters; the sub-filters utilize satellite channel fuzzy vectors and carrier dynamic information to output error correction amounts and uncertainty variances; the satellite observations are corrected by using the error correction amounts, and a composite noise covariance matrix is constructed based on the uncertainty variances; the corrected observations and the composite noise covariance matrix are input into a navigation solver to extract high-precision time information. The application significantly improves the positioning and timing precision of a radio navigation system in a complex dynamic environment by hierarchically and cooperatively estimating and compensating the propagation errors of satellite signals.

The invention discloses a medium wave navigation simulation method based on Hilbert change analog signals, and relates to the field of radio navigation, the method comprises the following steps: S1, setting working signal parameters, and initializing the orientation of a radio compass; s2, the electromagnetic propagation model calculates signal amplitude and phase information received by the omnidirectional antenna and the loop antenna under the current aircraft attitude; s3, carrying out carrier wave reconstruction, and generating an annular modulation signal; s4, superposing the signals; s5, calculating envelope modulation depth, and judging whether the direction of the current loop antenna is the real azimuth angle of the navigation station according to whether the modulation depth approaches zero; s6, if yes, outputting an azimuth angle; and if not, adjusting the pointing angle of the loop antenna, and repeating the steps S2 to S5. According to the method, the fundamental process of direction finding logic is reconstructed from the phase level, so that the simulation system can still keep stable direction finding performance in a complex multi-path environment, and the engineering practicability and environmental adaptability of the method are enhanced.