Low-orbit satellite ground communication anti-interference test method and device

Abstract

The application belongs to the technical field of satellite communication, and discloses a low-orbit satellite ground communication anti-interference test method and device, the method comprising: acquiring an original orbit parameter set and performing calculation to obtain an orbit dynamic parameter set and an interference parameter set; performing calculation according to the orbit dynamic parameter set and the interference parameter set to obtain a real-time radio frequency signal; performing calculation according to the real-time radio frequency signal to obtain a performance index set; performing analysis according to the performance index set, the orbit dynamic parameter set and the interference parameter set to obtain an optimization suggestion set; and generating a test report based on a formatting template and the optimization suggestion set. The application can accurately test the ground communication anti-interference scene of a low-orbit satellite.

Description

Technical Field

[0001] This application relates to the field of satellite communication technology, and in particular to a method and apparatus for testing anti-interference capabilities of low-orbit satellite ground communication. Background Technology

[0002] Low Earth orbit (LEO) satellites operate at altitudes of 200-2000 kilometers above the Earth, offering advantages such as low cost, high transmission speed, and low latency, making them suitable for developing satellite internet services. As of early 2026, over 1 million LEO satellites had been declared globally, with approximately 14,000 in orbit; domestically, over 200,000 had been declared, with about 260 in orbit. Currently, LEO satellite internet is routinely deployed, and terrestrial applications have entered commercial operation, with communication modules widely integrated into various terminals. LEO satellite communication systems differ significantly from GEO satellite communication and terrestrial mobile communication. Their high-speed motion (approximately 7.8 km / s) results in a significant Doppler effect and faces dynamic interference issues. Currently, testing of LEO satellite terrestrial communication modules primarily utilizes existing technologies such as standard signal generators with spectrum analyzers and static channel simulators.

[0003] However, most existing testing techniques have significant limitations. Standard signal generators and spectrum analyzers cannot simulate dynamic Doppler and rapidly changing interference; static channel simulators cannot reflect the dynamic characteristics of a satellite's actual orbit; single-source interference testing cannot reproduce multiple types of dynamic interference environments; discrete testing lacks bidirectional interactive simulation of links, and single-unit testing cannot verify system-level performance. Furthermore, low-Earth orbit satellite communication itself faces challenges such as dynamic Doppler frequency shift, complex interference, rapidly changing channels, and handover interference, making it difficult for existing technologies to comprehensively verify its anti-interference performance.

[0004] Therefore, how to accurately test the anti-interference scenarios of ground communication for low-orbit satellites has become an urgent problem to be solved. Summary of the Invention

[0005] This application provides a method and apparatus for testing anti-interference capabilities of low-Earth orbit satellite ground communication. It enables real-time calculation based on a realistic set of original orbital parameters, replacing static or linear variation models. This makes the calculation process more closely reflect the current orbital parameters, providing a comprehensive and reliable data foundation for subsequent signal generation and performance analysis. Furthermore, it unifies multiple types of interference parameter sets with dynamic channels and time-varying Doppler, reproducing the coupling effect of these three. The real-time radio frequency (RF) signals calculated based on the orbital dynamic parameter set and interference parameter set accurately reflect the signal characteristics in the actual scenario, providing an accurate basis for obtaining performance index sets. The performance index set calculated through real-time RF signals comprehensively presents the system's operating status. The optimization suggestion set obtained after analyzing the orbital dynamic parameter set and interference parameter set can accurately locate problems in the system's operation and provide feasible improvement directions. The test report generated based on the formatted template and optimization suggestion set enables standardized presentation of test results, facilitating quick review by relevant personnel, improving the efficiency and quality of testing work, providing support for system optimization and improvement, and reducing testing and optimization costs.

[0006] In a first aspect, embodiments of this application provide a method for testing anti-interference capabilities of low-Earth orbit satellite ground communication, the method comprising: Obtain the original orbital parameter set and perform calculations to obtain the orbital dynamic parameter set and disturbance parameter set; Real-time radio frequency signals are obtained by calculating based on the dynamic parameters set of the orbit and the interference parameters set. A set of performance indicators is obtained by calculating based on real-time radio frequency signals; An optimization suggestion set is obtained based on the analysis of the performance index set, the track dynamic parameter set, and the disturbance parameter set; Test reports are generated based on formatted templates and optimization suggestion sets.

[0007] Furthermore, the original orbital parameter set is obtained and calculated to obtain the orbital dynamic parameter set and disturbance parameter set, including: The original orbital parameter set is obtained and parsed, formatted, and double-buffered to obtain a formatted orbital parameter set. Based on the formatted orbit parameter set, time difference calculation, iterative calculation, and data packaging are performed to obtain the satellite state vector set; Based on the satellite state vector set, relative position vector calculation, relative velocity vector calculation, satellite-to-ground distance calculation, radial velocity calculation, and radial acceleration calculation are performed to obtain the relative motion parameter set; Doppler parameters are obtained by calculating the Doppler frequency shift, Doppler rate of change, and amplitude limiting based on the set of relative motion parameters. Based on satellite orbit parameters, terminal position parameters, terminal velocity parameters, carrier frequency, and Doppler parameters, terminal position coordinate transformation, terminal velocity target transformation, satellite position and velocity calculation, satellite-to-ground geometric relationship calculation, Doppler parameter calculation, and time delay loss calculation are performed to obtain the orbit dynamic parameter set; Based on the preset test scenario, preset interference fingerprint library and track dynamic parameter set, the interference type is selected, interference waveform is generated, interference dynamic correlation is calculated and interference parameters are packaged to obtain the interference parameter set.

[0008] Furthermore, based on the orbital dynamic parameter set and the interference parameter set, real-time radio frequency signals are obtained, including: Based on the dynamic parameters set of the track and the interference parameters set, the baseband signal is generated, Doppler modulation is performed, channel effect superposition is performed, interference superposition is performed, and up-conversion and RF output are performed to obtain the downlink test signal. The uplink received signal is obtained by transmitting based on the downlink test signal. Based on the uplink received signal, track dynamic parameter set and interference parameter set, downconversion and sampling, uplink Doppler superposition, uplink interference superposition, demodulation and decoding and synchronization status detection are performed to obtain demodulated data; Based on the set of relative motion parameters, free space propagation loss, atmospheric absorption loss, rain attenuation loss, multipath fading loss, total path loss, and propagation delay are calculated to obtain the channel parameters. Based on the channel parameters and Doppler parameters, the DDS frequency control word is calculated, the digitally controlled attenuator control value is calculated, the time delay control value is calculated, and the real-time signal is modulated to obtain the real-time radio frequency signal.

[0009] Furthermore, based on real-time radio frequency signals, a set of performance indicators is obtained, including: Based on real-time RF signals and demodulated data, bit error rate, throughput, synchronization status statistics, and handover success rate are calculated to obtain a set of performance indicators. The performance metrics set includes bit error rate, throughput, probability of lockout, average lockout time, and handover success rate.

[0010] Furthermore, based on the performance index set, track dynamic parameter set, and disturbance parameter set, an optimization suggestion set is obtained, including: Based on the performance index set, track dynamic parameter set, and disturbance parameter set, time alignment, statistical analysis, feature importance analysis, and critical threshold identification are performed to obtain the correlation analysis result set; Based on the association analysis result set, bottleneck location rules are matched, optimization parameters are calculated, and optimization suggestions are generated to obtain an optimization suggestion set.

[0011] Furthermore, the original orbital parameter set is obtained and subjected to data parsing, formatting, and double-buffering loading to obtain a formatted orbital parameter set, including: Obtain the original orbital parameter set, and parse the TLE format string to obtain the orbital element parameters; The orbital element parameters are formatted using fixed-point number formatting to obtain a formatted orbital parameter set.

[0012] Furthermore, based on the formatted orbit parameter set, time difference calculations, iterative calculations, and data packaging are performed to obtain a satellite state vector set, including: The time difference between the current time and the orbital element epoch time is calculated based on the formatted orbital parameter set. The pipeline architecture is used to process the iterative calculation of one satellite per clock cycle. For each satellite, the SGP4 / SDP4 model is iterated based on the orbital elements and time difference to obtain the position vector and velocity vector in the ECEF coordinate system. The position and velocity vectors are packaged into a 64-bit floating-point format to obtain the satellite state vector set.

[0013] Secondly, embodiments of this application provide a low-orbit satellite ground communication anti-interference testing device, the device comprising: The dynamic signal synthesis module is used to acquire the original orbital parameter set and perform calculations to obtain the orbital dynamic parameter set and the interference parameter set. The real-time signal calculation module is used to calculate and obtain real-time radio frequency signals based on the track dynamic parameter set and interference parameter set; The performance index calculation module is used to calculate and obtain a set of performance indicators based on real-time radio frequency signals; The optimization suggestion generation module is used to analyze the performance index set, track dynamic parameter set, and disturbance parameter set to obtain an optimization suggestion set; The test report generation module is used to generate test reports based on formatted templates and optimization suggestion sets.

[0014] Thirdly, embodiments of this application provide a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it performs the steps of a low-orbit satellite ground communication anti-interference test method as described in any of the above embodiments.

[0015] Fourthly, embodiments of this application provide a computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the steps of a low-orbit satellite ground communication anti-interference test method as described in any of the above embodiments.

[0016] In summary, compared with the prior art, the beneficial effects of the technical solution provided in this application include at least the following: This application provides a method for testing anti-interference capabilities of low-Earth orbit satellite ground communication. It enables real-time calculation based on a realistic set of original orbital parameters, replacing static or linear variation models. This makes the calculation process more closely reflect the current orbital parameters, providing a comprehensive and reliable data foundation for subsequent signal generation and performance analysis. Furthermore, it unifies multiple types of interference parameter sets with dynamic channels and time-varying Doppler, reproducing the coupling effect of these three. The real-time radio frequency (RF) signals calculated based on the orbital dynamic parameter set and interference parameter set accurately reflect the signal characteristics in the actual scenario, providing an accurate basis for obtaining performance index sets. The performance index set calculated through real-time RF signals comprehensively presents the system's operating status. The optimization suggestion set obtained after analyzing the orbital dynamic parameter set and interference parameter set can accurately locate problems in the system's operation and provide feasible improvement directions. The test report generated based on the formatted template and optimization suggestion set enables standardized presentation of test results, facilitating quick review by relevant personnel, improving the efficiency and quality of testing work, providing support for system optimization and improvement, and reducing testing and optimization costs. Attached Figure Description

[0017] Figure 1 A flowchart illustrating an exemplary embodiment of this application is provided for a method of testing anti-interference capabilities for low-Earth orbit satellite ground communication.

[0018] Figure 2 This is a structural diagram of a low-orbit satellite ground communication anti-interference test device provided as an exemplary embodiment of this application. Detailed Implementation

[0019] The technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments.

[0020] Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0021] Please see Figure 1 This application provides a method for testing anti-interference capabilities of low-Earth orbit satellite ground communication, which specifically includes the following steps: Step S1: Obtain the original orbital parameter set and perform calculations to obtain the orbital dynamic parameter set and disturbance parameter set.

[0022] The raw orbit parameter set may include TLE data or precise orbit parameters received from external interfaces (such as networks or configuration files).

[0023] In some embodiments, the original orbital parameter set is obtained and calculated to obtain the orbital dynamic parameter set and the disturbance parameter set, including: Step S11: Obtain the original orbital parameter set and perform data parsing, formatting, and double-buffering loading to obtain the formatted orbital parameter set.

[0024] In some embodiments, the original orbital parameter set is obtained and subjected to data parsing, formatting, and double-buffering loading to obtain a formatted orbital parameter set, including: Step S111: Obtain the original orbital parameter set and parse the TLE format string to obtain the orbital element parameters.

[0025] Step S112: Format the orbital element parameters using fixed-point number formatting to obtain a formatted orbital parameter set.

[0026] In one feasible implementation, data parsing is first performed, converting the TLE format string into orbital element parameters (semi-major axis). eccentricity Track inclination Right ascension of ascending node Perigeal argument , and the near point angle epochal time Next, data formatting is performed, converting the parsed orbital parameters into a fixed-point number format that the FPGA can process (using Q16.16 format, 16 bits for the integer part and 16 bits for the fractional part). Finally, double-buffered loading is performed, using a double-buffered mechanism to write the orbital parameters into buffer A of the FPGA's on-chip BRAM, while buffer B is used for the current calculation cycle, ensuring seamless parameter updates. The final output is a formatted set of orbital parameters, i.e., orbital element parameters in fixed-point number format.

[0027] Step S12: Perform time difference calculation, iterative calculation, and data packaging based on the formatted orbit parameter set to obtain the satellite state vector set.

[0028] In some embodiments, time difference calculation, iterative calculation, and data packaging are performed based on a formatted orbit parameter set to obtain a satellite state vector set, including: Step S121: Calculate the time difference between the current time and the orbital element epoch time based on the formatted orbital parameter set.

[0029] Step S122: Using a pipelined architecture, iterative calculations are performed on one satellite per clock cycle. For each satellite, based on the orbital elements and time difference, the SGP4 / SDP4 model is iterated to obtain the position vector and velocity vector in the ECEF coordinate system.

[0030] Step S123: Pack the position vector and velocity vector into a 64-bit floating-point format to obtain the satellite state vector set.

[0031] In one feasible implementation, the formatted orbit parameter set and the current timestamp are used. (From system clock, expressed in GPS seconds or UTC seconds, with an accuracy of 1ms), the first step is to calculate the time difference, calculating the time difference between the current moment and the orbital element epoch time. The second step involves iterative calculations. A pipelined architecture processes one satellite per clock cycle. For each satellite, based on orbital elements and time differences, the SGP4 / SDP4 model is iterated, outputting the position vector in the ECEF coordinate system. and velocity vector The third step involves data packaging, where the calculation results are packaged into a 64-bit floating-point format and transferred to the processor's shared memory via the bus. This ultimately yields the satellite state vector set, containing the satellite ID, and the Earth-centered Earth-fixed coordinate (ECEF) position vector. Velocity vector Timestamp data, etc. Among them, refer to Position vector components on the coordinate axes; Velocity vector components on the coordinate axes.

[0032] Step S13: Calculate the relative position vector, relative velocity vector, satellite-to-ground distance, radial velocity, and radial acceleration based on the satellite state vector set to obtain the relative motion parameter set.

[0033] In one feasible implementation, the calculation is performed based on a satellite state vector set and a terminal state vector; wherein the terminal state vector is a preset or real-time injected terminal position vector. and velocity vector .in refer to Position vector components on the coordinate axes; Velocity vector components on the coordinate axes. First step: Calculate the relative position vector. The second step is to calculate the relative velocity vector: The third step is to calculate the distance between the satellite and the Earth (Euclidean norm): Fourth step, calculate the radial velocity (vector dot product divided by distance): Fifth step: Calculate radial acceleration (using numerical differentiation method): ,in (Calculate the update cycle); Step 6: Calculate the satellite elevation angle Azimuth The final output set of relative motion parameters includes the relative position vector. Relative velocity vector Distance between stars and Earth radial velocity Radial acceleration Satellite elevation angle Azimuth .

[0034] Step S14: Calculate the Doppler frequency shift, Doppler rate of change, and amplitude limiting based on the set of relative motion parameters to obtain the Doppler parameters.

[0035] In one feasible implementation, based on the relative motion parameter set and carrier frequency... (Preset configuration parameters, such as 12.5GHz, 14.0GHz, etc.) and the speed of light (Constant) Calculations are performed. The first step is to calculate the Doppler frequency shift. ,like The unit is m / s. The unit is m / s. The unit is Hz. The unit is Hz; the second step is to calculate the Doppler rate of change: Doppler rate of change The third step is to perform numerical stability processing, which limits the amplitude of the calculation results. , To pre-set based on orbital altitude and frequency band (e.g.) ); Fourth step, for Low-pass filtering is performed to eliminate high-frequency noise introduced by numerical differentiation. The final output is the Doppler parameter (Doppler frequency shift). Doppler rate of change ).

[0036] Step S15: Based on the satellite orbit parameters, terminal position parameters, terminal velocity parameters, carrier frequency, and Doppler parameters, perform terminal position coordinate transformation, terminal velocity target transformation, satellite position and velocity calculation, satellite-to-ground geometric relationship calculation, Doppler parameter calculation, and time delay loss calculation to obtain the orbit dynamic parameter set.

[0037] The satellite orbital parameters, terminal position parameters, terminal velocity parameters, carrier frequency, and Doppler parameters can be included in the original orbital parameter set.

[0038] In one feasible implementation, calculations are performed based on satellite orbital parameters and terminal position parameters. Satellite orbital parameters include satellite ID, two-line orbital elements (TLE), or precise orbital parameters; terminal position parameters (terminal latitude, longitude, and altitude coordinates); and terminal velocity parameters (terminal velocity vector). (Zero vector in static terminal case); carrier frequency (Test frequency, such as 12.5 GHz).

[0039] Furthermore, firstly, the terminal position coordinates are transformed, converting the terminal's latitude, longitude, and altitude into a position vector in the ECEF coordinate system. : ; Among them, R N Here are the parameters for the rotation matrix: h is the altitude, lat is the latitude, and lon is the longitude.

[0040] in, , , .

[0041] Second, terminal velocity coordinate transformation: convert the velocity vector into an ECEF velocity vector.

[0042] : ; in, It is a rotation matrix, determined by the latitude and longitude of the terminal.

[0043] In one feasible implementation, assume the geographic coordinates of the terminal to be measured (WGS-84 ellipsoid): latitude (North latitude), longitude (East longitude), altitude The terminal uses speed Heading east, Traveling north, vertical speed (Horizontal motion), then: ; Third, satellite position and velocity calculation is based on the TLE parameter and the current time. The SGP4 / SDP4 model was used to calculate the satellite's position vector in the ECEF coordinate system. and velocity vector .

[0044] Fourth, calculation of the geometric relationship between space and Earth, relative position vector. Relative velocity vector Distance between stars and Earth Radial velocity Radial acceleration (through the analysis of) Numerical differentiation).

[0045] Fifth, Doppler parameter calculation, Doppler frequency shift. ,in The speed of light is constant; the Doppler rate of change: .

[0046] Sixth, delay and loss calculation, propagation delay. Free space loss Satellite elevation angle , where (E,N,U) are the coordinates of the station center coordinate system.

[0047] The final output orbital dynamic parameter set includes , , , , .

[0048] Step S16: Based on the preset test scenario, preset interference fingerprint library and track dynamic parameter set, select interference type, generate interference waveform, calculate interference dynamic correlation and package interference parameters to obtain interference parameter set.

[0049] In one feasible implementation, processing is performed based on a preset test scenario (such as anti-interference capability test, switching test, etc.), a set of track dynamic parameters, and a preset interference fingerprint database (pre-stored interference waveform features and parameterized models).

[0050] In one feasible implementation, the original orbital parameter set can be obtained and calculated according to the implementation method of step S15 to obtain the orbital dynamic parameter set; the orbital dynamic parameter set and the preset interference fingerprint library are processed in step S16 to obtain the interference parameter set.

[0051] The first step is interference type selection. Based on the configuration of the preset test scenario, select the interference type code from the interference fingerprint database. These correspond to 1) co-frequency continuous wave interference; 2) broadband noise interference; 3) pulse interference; 4) frequency sweep interference; 5) multi-tone interference; and 6) modulation deception interference.

[0052] Step 2: Interference Waveform Generation: Continuous Wave Interference Broadband noise interference is generated via a Gaussian white noise generator with configurable bandwidth; impulse interference. ,in Given the initial pulse interference amplitude, T pulse The pulse time period is given by rect(), which is the pulse rectangle function. The reference frequency is t, where t is the time parameter; the frequency sweep interference is the instantaneous frequency. ,in To initialize the frequency, The frequency at the current moment. This represents the current frequency and the initial time interval.

[0053] Step 3: Interference dynamic correlation calculation, frequency tracking mode (targeted jamming): ,in Preset offset; power varies with elevation angle mode Simulates the spatial attenuation of ground-based interference sources; in timing control mode, the interference type is switched according to the satellite orbital position, such as... Interference is enabled at any time. Turn off interference when necessary.

[0054] The fourth step is to package the interference parameters and encode the interference type. Instantaneous frequency Instantaneous power Timing control flags Packed into a set of interference parameters.

[0055] The final output interference parameter set includes , , , Waveform sampling sequence.

[0056] Step S2: Calculate the real-time radio frequency signal based on the track dynamic parameter set and the interference parameter set.

[0057] In some embodiments, a real-time radio frequency signal is obtained by calculation based on a set of dynamic orbital parameters and a set of interference parameters, including: Step S21: Based on the track dynamic parameter set and interference parameter set, perform baseband signal generation, Doppler modulation, channel effect superposition, interference superposition, up-conversion and RF output to obtain the downlink test signal.

[0058] In one feasible implementation, processing is performed based on a set of orbital dynamic parameters, a set of interference parameters, a set of channel parameters, and baseband test data (preset test sequences, such as PN codes, voice / video streams).

[0059] The first step is to generate the baseband signal and generate the test sequence. (such as a symbol stream modulated by QPSK).

[0060] The second step is Doppler modulation. In practice, the carrier frequency is adjusted in real time using an NCO (numerically controlled oscillator).

[0061] The third step involves the superposition of channel effects and time delay. This is achieved through digital delay lines; loss superposition. This is achieved through a digitally controlled attenuator. Here is the loss fitting function, and t is the time parameter; multipath superposition. This is achieved through an FIR filter. This refers to the channel effect resulting from multipath superposition. This is due to the superposition effect of channel loss. is the multipath superposition fitting function, and t is the time parameter.

[0062] The fourth step is interference superposition, which generates an interference signal based on the interference parameter set. For continuous wave / frequency sweep interference, frequency is generated via DDS. For pulse interference, control is applied using a duty cycle switch; the interference signal is superimposed on the communication signal. .

[0063] The fifth step is up-conversion and RF output, which up-converts the baseband signal to an RF carrier. The signal is injected into the communication module under test via the radio frequency interface.

[0064] The final output downlink test signal is an RF signal superimposed with Doppler, channel effects and interference.

[0065] Step S22: Perform a transmission operation based on the downlink test signal to obtain the uplink received signal.

[0066] Step S23: Based on the uplink received signal, track dynamic parameter set, and interference parameter set, perform downconversion and sampling, uplink Doppler superposition, uplink interference superposition, demodulation and decoding, and synchronization status detection to obtain demodulated data.

[0067] In one feasible implementation, processing is performed based on the uplink received signal (the radio frequency signal transmitted by the module under test), the track dynamic parameter set, and the interference parameter set.

[0068] The first step is down-conversion and sampling, which down-converts the received radio frequency signal to baseband at a sampling rate of [missing information]. Perform AD sampling.

[0069] The second step involves uplink Doppler superposition. Due to satellite motion, the uplink signal also exhibits a Doppler frequency shift. This is simulated at the receiver. ,in This is the uplink carrier frequency.

[0070] The third step is uplink interference superposition. Based on the uplink interference configuration, an uplink interference signal is generated and superimposed on the received signal.

[0071] The fourth step is demodulation and decoding. Carrier synchronization is achieved by tracking the carrier frequency through a phase-locked loop; symbol synchronization is achieved by extracting the optimal sampling point using the Gardner algorithm; channel equalization is achieved by compensating for channel distortion using an LMS adaptive equalizer; and the demodulated bit stream is output.

[0072] Step 5: Synchronization status detection, carrier lock detection: phase-locked loop phase detector output variance Time is locked; Frame synchronization detection: detects the frame header matching degree and outputs the synchronization flag.

[0073] The final output is demodulated data, including the demodulated bitstream. Synchronization status flag Carrier lock flag .

[0074] Step S24: Calculate free space propagation loss, atmospheric absorption loss, rain attenuation loss, multipath fading loss, total path loss, and propagation delay based on the relative motion parameter set to obtain the channel parameters.

[0075] Please refer to Table 1, which is a table of atmospheric absorption losses. Under standard atmospheric conditions (temperature 15°C, water vapor density 7.5 g / m³, sea level pressure 1013.25 hPa), the estimated values ​​of specific atmospheric absorption attenuation in the zenith direction for different frequencies are as follows.

[0076] Table 1 Please refer to Table 2, which is a table of rain attenuation losses. The reference values ​​for k and α coefficients for commonly used satellite communication frequency bands under different polarizations are as follows.

[0077] Table 2 In one feasible implementation, based on the relative motion parameter set and carrier frequency... (Preset configuration parameters); Rainfall intensity Calculations are performed using preset parameters and polarization methods (preset parameters, such as horizontal / vertical / circular polarization, etc.).

[0078] Step 1, Calculation of free space propagation loss: ,in The unit is meters. The unit is Hz.

[0079] Step 2: Calculation of atmospheric absorption loss: ,in This refers to atmospheric absorption loss in the zenith direction (look up the table according to the frequency), such as at 12.5 GHz. ).

[0080] Step 3: Rain attenuation loss calculation ,in For path reduction factor, rainfall attenuation coefficient (dB / km) and (Look up the table based on frequency and polarization) Inclined path length (km), The height of the rain roof. This refers to the terminal altitude.

[0081] Step 4: Calculation of multipath fading loss: ; in, At the elevation angle, multipath enhancement occurs at low elevation angles, resulting in negative losses (gains).

[0082] Step 5, Calculate total path loss: .

[0083] Step 6, Propagation delay calculation: , where d is the distance between the star and the Earth, and c is the speed of light.

[0084] Final output channel parameters (free space loss) Atmospheric absorption loss Rain attenuation loss Multipath fading Total path loss Propagation delay wait).

[0085] Step S25: Calculate the DDS frequency control word, digitally controlled attenuator control value, time delay control value, and perform real-time signal modulation based on channel parameters and Doppler parameters to obtain the real-time radio frequency signal.

[0086] In one feasible implementation, based on channel parameters, Doppler parameters, and reference signal parameters (carrier frequency)... Reference power Reference delay ) to perform calculations.

[0087] The first step is to calculate the DDS frequency control word and the target signal frequency. DDS control word calculation ,in For the number of bits in the phase accumulator, The DDS clock frequency (e.g., 1 GHz).

[0088] The second step involves calculating the control value of the digitally controlled attenuator and determining the target output power. Attenuator control value ,in For attenuator steps (e.g., 0.5 dB / bit).

[0089] The third step is to calculate the delay control value and the total delay. ; Convert to number of sampling points ,in This represents the signal sampling rate.

[0090] The fourth step is real-time signal modulation. The FPGA reads the DDS control word and generates a carrier signal with the target frequency. The baseband data amplitude is adjusted by a digitally controlled attenuator. The signal delay is adjusted by a digital delay line.

[0091] Final Output Control Instruction Set (DDS Frequency Control Word) CNC attenuator control value Delay control value etc.); the modulated test signal (i.e., the real-time radio frequency signal, which is output to the module under test through the radio frequency interface).

[0092] In some embodiments, the real-time performance of signal data is a critical factor, and measures should be taken to ensure it. Key measures include segmented lookup table + interpolation: For very large constellations (>100 satellites), the time series of orbital positions can be pre-calculated offline, stored in DDR4 memory, and then read and interpolated by the FPGA at 1ms intervals, reducing the amount of real-time computation. Predictive correction method: Utilizing the first-order analytical solution of orbital mechanics, linear prediction is used between two complete SGP4 calculations, and a complete SGP4 correction is performed every 10ms, ensuring accuracy while reducing computational load.

[0093] Step S3: Calculate the performance index set based on the real-time radio frequency signal.

[0094] In some embodiments, a set of performance metrics is calculated based on real-time radio frequency signals, including: Step S31: Calculate the bit error rate, throughput, synchronization status, and handover success rate based on the real-time radio frequency signal and demodulated data to obtain a set of performance indicators.

[0095] Step S32, the performance metric set includes bit error rate, throughput, probability of lock loss, average lock time and handover success rate.

[0096] In one feasible implementation, based on the demodulated data (such as a bitstream) The calculations are performed on data such as synchronization status flags, raw transmitted data, and handover event records (event logs during satellite / beam handover).

[0097] Step 1, Bit Error Rate Calculation: Updated after each frame of data, the sliding window size is [size missing]. Bits. Let the original bitstream of the transmitted data be... , and the bitstream obtained after demodulation The comparison is performed for bit error rate calculation.

[0098] Step 2, throughput calculation: ,in To correctly decode the number of bits, For the measurement period, Symbol rate, For modulation efficiency.

[0099] The third step is to perform synchronization status statistics and calculate the probability of lock loss. ,in For the unlock count, Total number of synchronization states; Average lock time: , Let be the locking time of the i-th unlocked event. To lock the count, This represents the average lockout time.

[0100] Step 4: Calculate the handover success rate. The handover success flag is extracted from the signaling interaction. Handover success rate. ,in This is a count of successful signaling handovers. This represents the total count of signaling handover attempts. This refers to the signaling handover success rate.

[0101] The final output performance metric set includes , , , , Timestamp.

[0102] Step S4 involves analyzing the performance index set, track dynamic parameter set, and disturbance parameter set to obtain an optimization suggestion set.

[0103] In some embodiments, an optimization suggestion set is obtained by analyzing a performance index set, a track dynamic parameter set, and a disturbance parameter set, including: Step S41: Based on the performance index set, track dynamic parameter set, and disturbance parameter set, perform time alignment, statistical analysis, feature importance analysis, and critical threshold identification to obtain the correlation analysis result set.

[0104] In one feasible implementation, step S41 may include: The first step is time alignment, which involves aligning the three sets of data—performance index set, interference parameter set, and orbital dynamic parameter set—according to timestamps to construct an analysis sample. Furthermore, nearest neighbor matching and linear interpolation algorithms can be used to align the performance index set (sampling period 10ms), the orbital dynamic parameter set (sampling period 1ms), and the disturbance parameter set (sampling period variable) to a unified time grid (step size 10ms), ensuring the temporal consistency of subsequent analysis samples. Specifically, let the performance index set data points be... The set of dynamic orbital parameters is The interference parameter set is Generate a unified time grid. ( For each Performance metrics are taken from the forward nearest neighbor values, and orbital parameters are obtained using linear interpolation (e.g., ...). The interference parameters are taken from the nearest neighbor (due to the discrete nature of the interference type). The output is the aligned sample set. .

[0105] The second step is statistical analysis to calculate the interference intensity. With bit error rate correlation coefficient The average probability of lock loss under each type of interference is statistically analyzed to quantify the impact of each type of interference on system performance.

[0106] The third step is feature importance analysis and constructing the training set: input features. The system outputs labels, extracts feature importance scores, and ranks and identifies key features. Specifically, a random forest model can be constructed, with input features including interference type encoding. Interference power Doppler frequency shift Doppler rate of change Satellite elevation angle The output label is the bit error rate. Or a sign of loss of lock. The importance score for each feature is calculated using the decrease in the Gini coefficient. After sorting, key features (such as Doppler rate of change) are identified. ).

[0107] The fourth step is to identify critical thresholds for key interference types. Scanning interference intensity From low to high; using binary search combined with piecewise linear interpolation, find the point where the bit error rate first exceeds the threshold. (like The interference intensity at which the threshold is reached is used as the critical threshold. .

[0108] Output the association analysis result set, including feature importance ranking and key interference types. Critical threshold Correlation coefficient matrix.

[0109] Step S42: Based on the association analysis result set, perform bottleneck location rule matching, optimization parameter calculation, and optimization suggestion generation to obtain an optimization suggestion set.

[0110] In one feasible implementation, step S42 may include: The first step is bottleneck location rule matching. Based on a predefined rule base, a forward chain inference engine is used to match the current analysis results and output the bottleneck type. For example: Rule 1: If the critical interference type is impulse interference and the probability of loss of lock is... If so, the bottleneck type is automatic gain control response lag.

[0111] Rule 2: If the feature importance is... Highest score and and If the correlation is greater than 0.8, the bottleneck type is insufficient frequency tracking loop bandwidth.

[0112] Rule 3: If the key interference type is frequency sweeping interference and The bottleneck type is the lack of anti-frequency sweeping interference algorithm.

[0113] Rule 4: If the elevation angle is <15° and the probability of loss of lock is >20% and the interference type is not strong interference, then the bottleneck type is low elevation angle multipath / insufficient suppression.

[0114] Rule 5: If the interference type is polyphonic interference and BER > 1e -3 If so, the bottleneck type is digital predistortion or insufficient equalizer order.

[0115] Rule 6: If the switching success rate is <95% and the Doppler change rate is >300Hz / s, then the bottleneck type is beam switching algorithm lag.

[0116] Furthermore, the correlation analysis results obtained from the above processing (such as key interference types, lock loss probability, feature importance ranking, correlation coefficient, etc.) are then analyzed. The system takes the minimum elevation angle, etc., as a set of facts, checks the condition expression of each rule in turn, and outputs the corresponding bottleneck type when the first rule that meets the condition is found.

[0117] The second step is to optimize parameter calculations based on the bottleneck type: For example, loop bandwidth optimization: ,in This represents the maximum Doppler change rate that the current loop can track.

[0118] In some feasible implementations, if the bottleneck type is automatic gain control response hysteresis, then based on the pulse width... Calculate the new time constant And suggest an initial attenuation value; if the bottleneck type is a lack of anti-sweep interference algorithm, then based on the sweep rate... Calculate the bandwidth required for the adaptive notch filter .

[0119] The third step is to generate optimization suggestions. The template engine is used to populate the optimization parameters into natural language suggestions, including bottleneck location descriptions, parameter adjustment suggestions, algorithm optimization suggestions, and expected performance improvement indicators.

[0120] The final output is a set of optimization suggestions, including bottleneck location descriptions, parameter adjustment suggestions, algorithm optimization suggestions, and expected performance improvement indicators.

[0121] Step S5: Generate a test report based on the format template and optimization suggestion set.

[0122] In one feasible implementation, a test report is generated according to a formatted template based on the test dataset, optimization suggestion set, parameter configuration set, and other data generated in the aforementioned steps. It is particularly important to note that the construction of the test dataset is fundamental to the effectiveness of this invention. This application performs automated testing under various interference conditions, collecting data to form a sample set. It is recommended that the test dataset sample size be no less than 10,000 sets, covering different intensities, elevation angles, and Doppler dynamics for each type of interference.

[0123] The low-Earth orbit satellite ground communication anti-interference testing method provided in the above embodiments can perform real-time calculations based on the real original orbit parameter set, replacing static or linear variation models. This makes the calculation process closer to the current orbit parameter situation, providing a comprehensive and reliable data foundation for subsequent signal generation and performance analysis. Furthermore, it unifies multiple types of interference parameter sets with dynamic channels and time-varying Doppler, reproducing the coupling effect of the three. The real-time radio frequency signals calculated based on the orbit dynamic parameter set and interference parameter set can realistically reflect the signal characteristics in the actual scenario, providing an accurate basis for obtaining the performance index set. The performance index set calculated through real-time radio frequency signals can comprehensively present the system's operating status. The optimization suggestion set obtained after analyzing the orbit dynamic parameter set and interference parameter set can accurately locate problems in the system operation and provide feasible improvement directions. The test report generated based on the formatted template and optimization suggestion set can achieve standardized presentation of test results, facilitating quick review by relevant personnel, improving the efficiency and quality of testing work, providing support for system optimization and improvement, and reducing testing and optimization costs.

[0124] In one feasible implementation, during testing, real-time collected interference parameters and Doppler dynamics can be input into a trained random forest model. The model then predicts the BER and lockout probability of the current communication link in real time. If the predicted value exceeds a preset threshold, the system can issue an early warning and indicate the most likely cause (based on feature importance backtracking).

[0125] In one feasible implementation, after completing a round of testing, all test data is collected, and feature importance analysis and partial dependency graphs using machine learning models are used to identify the key interference types and critical intensities that lead to performance degradation. For example, analysis may reveal that "when the Doppler change rate is >200Hz / s and the interference is pulse interference, the probability of loss of lock-up surges," thus pinpointing the synchronization tracking loop as the performance bottleneck.

[0126] In one feasible implementation, the association rules mined by the machine learning model are transformed into actionable optimization suggestions. For example, if "interference type = impulse interference & interference intensity > -50dBm" causes a loss of lock, the suggestion is to "enhance the impulse interference suppression algorithm or increase the dynamic range of automatic gain control." If "Doppler change rate > 300Hz / s" leads to an increased bit error rate, the suggestion is to "optimize the carrier tracking loop bandwidth or adopt an open-loop compensation mechanism." After generating the suggestions, communication module parameters can be automatically configured, and regression verification can be performed using the same test scenario.

[0127] In some embodiments, the anti-interference test analysis results and monitoring fusion results are input. Scenario: Satellite elevation angle drops from 30° to 10°, interference type is frequency sweeping interference, interference intensity is -40dBm, terminal loses lock. Bottleneck identification: Automatic gain control cannot keep up with the combined changes of rapid signal attenuation and interference.

[0128] Further, proceed to step A (rule triggering): The rule engine detects "bottleneck = automatic gain control" and activates the automatic gain control optimization submodule.

[0129] Step B (Model Invocation): Input "Elevation Angle Change Rate, Interference Type, Interference Intensity" into a pre-trained "Optimal Automatic Gain Control Parameter Prediction Model" (neural network). Model Output: Suggested initial attenuation value for automatic gain control = -20dB, suggested automatic gain control adjustment step = 2dB / ms.

[0130] Step C (Constraint Check): Another set of rules checks whether the output value is within the hardware safety range (e.g., the step cannot exceed 3dB / ms, otherwise it may cause oscillation), and if it exceeds the range, it is truncated to the safety boundary.

[0131] Final output recommendation: In scenarios with low elevation angle, rapid fading, and strong frequency sweep interference, a lag in the automatic gain control response was detected. It is recommended to set the automatic gain control starting point to -20dB and increase the adjustment step to 2dB / ms to enhance the tracking capability of dynamic signals.

[0132] Please see Figure 2 Another embodiment of this application provides a low-orbit satellite ground communication anti-interference test device, the device comprising: The dynamic signal synthesis module 101 is used to acquire the original track parameter set and perform calculations to obtain the track dynamic parameter set and the interference parameter set.

[0133] The real-time signal calculation module 102 is used to calculate the real-time radio frequency signal based on the track dynamic parameter set and the interference parameter set.

[0134] The performance index calculation module 103 is used to calculate the performance index set based on the real-time radio frequency signal.

[0135] The optimization suggestion generation module 104 is used to analyze the performance index set, the track dynamic parameter set, and the disturbance parameter set to obtain an optimization suggestion set.

[0136] Test report generation module 105 is used to generate test reports based on format templates and optimization suggestion sets.

[0137] The specific limitations of the low-Earth orbit satellite ground communication anti-interference testing device provided in this embodiment can be found in the embodiment of the low-Earth orbit satellite ground communication anti-interference testing method described above, and will not be repeated here. Each module in the above-described low-Earth orbit satellite ground communication anti-interference testing device can be implemented entirely or partially through software, hardware, or a combination thereof. Each module can be embedded in or independent of the processor in a computer device in hardware form, or it can be stored in the memory of a computer device in software form, so that the processor can call and execute the operations corresponding to each module.

[0138] This application provides a computer device that may include a processor, memory, network interface, and database connected via a system bus. The processor provides computing and control capabilities. The memory includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores an operating system, computer programs, and a database. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage medium. The network interface communicates with external terminals via a network connection. When the computer program is executed by the processor, it causes the processor to perform the steps of a low-Earth orbit satellite ground communication anti-interference test method as described in any of the above embodiments.

[0139] The working process, working details, and technical effects of the computer equipment provided in this embodiment can be found in the embodiment of a low-orbit satellite ground communication anti-interference test method described above, and will not be repeated here.

[0140] This application provides a computer-readable storage medium storing a computer program thereon. When executed by a processor, the computer program implements the steps of a low-Earth orbit satellite ground communication anti-interference test method as described in any of the above embodiments. The computer-readable storage medium refers to a data storage medium, which may include, but is not limited to, floppy disks, optical disks, hard disks, flash memory, USB flash drives, and / or memory sticks. The computer may be a general-purpose computer, a special-purpose computer, a computer network, or other programmable devices.

[0141] The working process, working details, and technical effects of the computer-readable storage medium provided in this embodiment can be found in the embodiment of a low-orbit satellite ground communication anti-interference test method described above, and will not be repeated here.

[0142] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0143] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0144] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A method for testing anti-interference capabilities of low-Earth orbit satellite ground communication, characterized in that, The method includes: The process involves acquiring and calculating the original orbital parameter set to obtain a dynamic orbital parameter set and an interference parameter set. This includes: acquiring the original orbital parameter set and performing data parsing, formatting, and double-buffering loading to obtain a formatted orbital parameter set; performing time difference calculation, iterative calculation, and data packaging based on the formatted orbital parameter set to obtain a satellite state vector set; performing relative position vector calculation, relative velocity vector calculation, satellite-to-ground distance calculation, radial velocity calculation, and radial acceleration calculation based on the satellite state vector set to obtain a relative motion parameter set; performing Doppler frequency shift calculation, Doppler rate of change calculation, and amplitude limiting processing based on the relative motion parameter set to obtain Doppler parameters; performing terminal position coordinate transformation, terminal velocity target transformation, satellite position velocity calculation, satellite-to-ground geometric relationship calculation, Doppler parameter calculation, and time delay loss calculation based on the satellite orbital parameters, terminal position parameters, terminal velocity parameters, carrier frequency, and the Doppler parameters to obtain a dynamic orbital parameter set; and performing interference type selection, interference waveform generation, interference dynamic correlation calculation, and interference parameter packaging based on a preset test scenario, a preset interference fingerprint database, and the dynamic orbital parameter set to obtain an interference parameter set. Real-time radio frequency signals are obtained by calculating based on the aforementioned dynamic orbit parameter set and interference parameter set. A set of performance indicators is obtained by calculating based on the real-time radio frequency signal; An optimization suggestion set is obtained by analyzing the performance index set, the track dynamic parameter set, and the interference parameter set. Specifically, this includes: performing time alignment, statistical analysis, feature importance analysis, and critical threshold identification based on the performance index set, track dynamic parameter set, and interference parameter set to obtain a correlation analysis result set; and performing bottleneck location rule matching, optimization parameter calculation, and optimization suggestion generation based on the correlation analysis result set to obtain an optimization suggestion set. A test report is generated based on the formatted template and the set of optimization suggestions.

2. The low-orbit satellite ground communication anti-interference test method according to claim 1, characterized in that, The step of calculating the real-time radio frequency signal based on the orbital dynamic parameter set and interference parameter set includes: Based on the aforementioned dynamic orbit parameter set and interference parameter set, baseband signal generation, Doppler modulation, channel effect superposition, interference superposition, up-conversion and RF output are performed to obtain the downlink test signal; Based on the downlink test signal, a transmission operation is performed to obtain the uplink received signal; Based on the uplink received signal, the track dynamic parameter set, and the interference parameter set, downconversion and sampling, uplink Doppler superposition, uplink interference superposition, demodulation and decoding, and synchronization status detection are performed to obtain demodulated data; Based on the set of relative motion parameters, free space propagation loss, atmospheric absorption loss, rain attenuation loss, multipath fading loss, total path loss, and propagation delay are calculated to obtain the channel parameters. Based on the channel parameters and the Doppler parameters, the DDS frequency control word is calculated, the digitally controlled attenuator control value is calculated, the time delay control value is calculated, and the real-time signal is modulated to obtain the real-time radio frequency signal.

3. The low-orbit satellite ground communication anti-interference test method according to claim 2, characterized in that, The calculation based on the real-time radio frequency signal yields a set of performance indicators, including: Based on the real-time radio frequency signal and the demodulated data, the bit error rate is calculated, the throughput is calculated, the synchronization status is statistically analyzed, and the handover success rate is calculated to obtain a set of performance indicators. The performance metrics set includes bit error rate, throughput, probability of lockout, average lockout time, and handover success rate.

4. The low-orbit satellite ground communication anti-interference test method according to claim 1, characterized in that, The process of obtaining the original orbital parameter set and performing data parsing, formatting, and double-buffering loading to obtain a formatted orbital parameter set includes: Obtain the original orbital parameter set, and parse the TLE format string to obtain the orbital element parameters; The orbital element parameters are formatted using fixed-point number formatting to obtain a formatted orbital parameter set.

5. The low-orbit satellite ground communication anti-interference test method according to claim 4, characterized in that, The process of calculating the time difference, iteratively calculating, and packaging data based on the formatted orbit parameter set to obtain a satellite state vector set includes: The time difference between the current time and the orbital element epoch time is calculated based on the formatted orbital parameter set. The pipeline architecture is used to process the iterative calculation of one satellite per clock cycle. For each satellite, the SGP4 / SDP4 model is iterated based on the orbital elements and time difference to obtain the position vector and velocity vector in the ECEF coordinate system. The position vector and the velocity vector are packaged into a 64-bit floating-point format to obtain the satellite state vector set.

6. A low-orbit satellite ground communication anti-interference testing device, characterized in that, The device includes: The dynamic signal synthesis module is used to acquire and calculate the original orbital parameter set to obtain the orbital dynamic parameter set and the interference parameter set. This includes: acquiring the original orbital parameter set and performing data parsing, formatting, and double-buffering loading to obtain a formatted orbital parameter set; performing time difference calculation, iterative calculation, and data packaging based on the formatted orbital parameter set to obtain a satellite state vector set; performing relative position vector calculation, relative velocity vector calculation, satellite-to-ground distance calculation, radial velocity calculation, and radial acceleration calculation based on the satellite state vector set to obtain a relative motion parameter set; performing Doppler frequency shift calculation, Doppler rate of change calculation, and amplitude limiting processing based on the relative motion parameter set to obtain Doppler parameters; performing terminal position coordinate transformation, terminal velocity target transformation, satellite position velocity calculation, satellite-to-ground geometric relationship calculation, Doppler parameter calculation, and time delay loss calculation based on the satellite orbital parameters, terminal position parameters, terminal velocity parameters, carrier frequency, and the Doppler parameters to obtain the orbital dynamic parameter set; and performing interference type selection, interference waveform generation, interference dynamic correlation calculation, and interference parameter packaging based on a preset test scenario, a preset interference fingerprint database, and the orbital dynamic parameter set to obtain an interference parameter set. The real-time signal calculation module is used to calculate the real-time radio frequency signal based on the track dynamic parameter set and the interference parameter set. The performance index calculation module is used to calculate a set of performance indicators based on the real-time radio frequency signal; The optimization suggestion generation module is used to analyze the performance index set, the track dynamic parameter set, and the interference parameter set to obtain an optimization suggestion set. This includes: performing time alignment, statistical analysis, feature importance analysis, and critical threshold identification based on the performance index set, track dynamic parameter set, and interference parameter set to obtain a correlation analysis result set; and performing bottleneck location rule matching, optimization parameter calculation, and optimization suggestion generation based on the correlation analysis result set to obtain the optimization suggestion set. The test report generation module is used to generate a test report based on the formatted template and the set of optimization suggestions.

7. A computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the steps of the low-orbit satellite ground communication anti-interference test method as described in any one of claims 1 to 5.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the steps of the low-orbit satellite ground communication anti-interference test method as described in any one of claims 1 to 5.

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