A constellation inter-frequency spectrum compatibility analysis method

Abstract

The application provides a constellation inter-frequency spectrum compatibility analysis method and system, the method comprising: making each interference system and disturbed system reference satellite traverse all ground grid points, solving the lumped interference and corresponding probability of all grids; summing the probability of the lumped interference of each given lumped interference interval on all grids to obtain the lumped interference probability distribution. The application has the advantages that: the method provided by the application is basically consistent with the simulation results of the traditional compatibility analysis method, has the same accuracy, is higher in calculation efficiency, and gradually increases in calculation efficiency with the increase of the constellation satellite scale, and can greatly reduce the calculation cost.

Description

Technical Field

[0001] This application belongs to the field of spectrum compatibility technology, specifically relating to a method for analyzing spectrum compatibility between constellations. Background Technology

[0002] Frequency and orbital resources are fundamental elements for the development of the space information network application industry, and are also valuable strategic resources that countries around the world are vying for. The rapid development and deployment of mega-internet constellations have led to the depletion of frequency and orbital resources and increasingly serious interference. The contradiction between the large demand for frequencies and the limited frequency resources is a key problem constraining the development of many low-Earth orbit satellite constellations. Achieving coexistence on the same frequency under the constraint of limited frequency resources is an urgent task at present, and effective and reliable compatibility simulation analysis results are the key basis for the quantitative analysis of coexistence on the same frequency.

[0003] Current research on satellite frequency compatibility analysis methods largely relies on time Monte Carlo simulation analysis. However, for compatibility analysis between large-scale constellations, the computational efficiency and overhead are insufficient for practical needs. Furthermore, current space Monte Carlo simulation analysis often employs stochastic geometry and other techniques, which improve computational efficiency and reduce overhead to some extent. However, stochastic geometry struggles to accurately depict the distribution of satellites within a real constellation, making it difficult to guarantee the accuracy and reliability of the analysis results. Therefore, researching an efficient spectral compatibility analysis method for large-scale constellations is of significant importance. Summary of the Invention

[0004] The purpose of this application is to overcome the shortcomings of large-scale constellation compatibility analysis methods, such as low simulation efficiency and low result accuracy.

[0005] To achieve the above objectives, this application proposes a method for inter-constellation spectral compatibility analysis, comprising:

[0006] The reference satellites of each interfering and disturbed system traverse all ground grid points to solve for the lumped interference and corresponding probability of all grids;

[0007] The probability distribution of lumped interference is obtained by summing the probabilities of lumped interference for each given lumped interference interval on all grids.

[0008] As an improvement to the above method, the method for solving the lumped interference is as follows:

[0009] ;

[0010] in, Indicates the disturbed reference satellite in the 1st century. q The grid, the interference reference satellite in the 1st grid p Lumped disturbance when there are individual grids; This indicates the transmission power that interferes with the NGSO satellite; Indicates the gain of the interfering NGSO satellite antenna; Indicates the off-axis angle of the NGSO satellite transmitter; Indicates the antenna gain of the disturbed earth station; Indicates the off-axis angle of the received data from the disturbed earth station; This indicates link loss.

[0011] As an improvement to the above method, the probability is calculated as follows:

[0012] ;

[0013] in, Indicates the disturbed reference satellite in the 1st century. q The grid, the interference reference satellite in the 1st grid p The probability of each grid cell; Indicates the interference reference satellite in the p The probability density function of each grid cell; Indicates the disturbed reference satellite in the 1st century. q The probability density function of each grid cell.

[0014] As an improvement to the above method, the expression for the probability density function is:

[0015] ;

[0016] in, Indicates the satellite's latitude and longitude coordinates on the ground. The probability density function of the projection location, superscript T Indicates matrix transpose; Indicates longitude , Indicate latitude , Indicates orbital inclination angle; intermediate variable , Indicates the argument of perigee; ; e This represents the orbital eccentricity.

[0017] This application also provides an inter-constellation spectrum compatibility analysis system, implemented based on the above method, the system comprising:

[0018] The module for obtaining satellite lumped interference and corresponding probabilities is used to enable the reference satellites of the interfering system and the disturbed system to traverse all ground grid points and solve for the lumped interference and corresponding probabilities of all grids.

[0019] The module for obtaining the lumped interference probability distribution is used to sum the probabilities of lumped interference for each given lumped interference interval on all grids to obtain the lumped interference probability distribution.

[0020] Compared with existing technologies, the advantages of this application are:

[0021] The method proposed in this application yields simulation results that are basically consistent with those of traditional compatibility analysis methods. While maintaining the same accuracy, it is more computationally efficient. Furthermore, the computational efficiency gradually increases with the size of the constellation satellites, which can significantly reduce computational overhead. Attached Figure Description

[0022] Figure 1 The diagram shows the flowchart of the inter-constellation spectral compatibility analysis method.

[0023] Figure 2 The figure shows the cumulative probability distribution curve of I / N for a jamming system with 900 jamming targets.

[0024] Figure 3 The figure shows the cumulative probability distribution curve of I / N for a jamming system with 3600 jamming targets.

[0025] Figure 4 The figure shows the cumulative probability distribution curve of I / N for a jamming system with 6000 jamming targets.

[0026] Figure 5 The figure shows the cumulative probability distribution curve of I / N for a jamming system with 12,000 jamming devices. Detailed Implementation

[0027] The technical solution of this application will be described in detail below with reference to the accompanying drawings.

[0028] The inter-constellation spectrum compatibility analysis method provided in this application is based on the spatial enumeration interference calculation method, that is, by traversing the possible locations of the constellation reference satellite, and performing simulation analysis on the lumped interference generated by the constellation configuration corresponding to the reference satellite at each possible location.

[0029] In large-scale inter-constellation interference scenarios, the downlink lumped interference noise ratio of the disturbed ground station Represented as:

[0030] (1)

[0031] in, Indicates interference power; Indicates noise power; This indicates the transmission power that interferes with non-geostationary orbit (NGSO) satellites; Indicates the interference with the NGSO satellite antenna gain. This indicates the antenna gain of the disturbed earth station. Indicates the off-axis angle of the NGSO satellite transmitter. Indicates the off-axis angle of the received signal from the disturbed earth station. This indicates link loss.

[0032] As shown below, This indicates that the total number of satellites is m The constellation, the reference satellite is Spherical coordinates (LLA coordinates) of all satellites within the constellation:

[0033] (2)

[0034] in, The first step in the process of traversing the spatial position of the reference satellite One location; Indicates the reference satellite in the The longitude of each location; Indicates the reference satellite in the The dimension of each position; Indicates the reference satellite in the The height of each position.

[0035] Reference satellite space ergonomics The connection between the disturbed NGSO satellite and the disturbed ground station at the first location and the second The angle between the line connecting the interfering NGSO satellite and the disturbed ground station is shown below.

[0036] (3)

[0037] in, The Earth-fixed coordinates of the disturbed satellite. For the first Earth-fixed coordinates of an interfering NGSO satellite. The coordinates of the disturbed ground station are in the Earth-fixed system. This represents the dot product. This indicates scalar multiplication.

[0038] Indicates the space traversal of the first p At each location, the connection between the disturbed NGSO satellite and the disturbed ground station is respectively... m The set of angles between the lines connecting the interfering NGSO satellites and the disturbed ground stations.

[0039] (4)

[0040] Calculate the lumped interference noise ratio generated by all satellites in the constellation. At this point, the lumped interference obtained according to Equation 1 is the location of the reference satellite of the constellation. The resulting lumped interference:

[0041] (5)

[0042] in, Indicates interference power; Indicates noise power; This indicates the transmission power that interferes with the NGSO satellite; Indicates the interference with the NGSO satellite antenna gain. This indicates the maximum gain of the NGSO satellite antenna that interferes. This indicates the antenna gain of the disturbed earth station. This indicates link loss.

[0043] This indicates that the reference satellites for a large-scale constellation traverse all of space. A set of LLA coordinates for each location:

[0044] (6)

[0045] Baseline satellite traversal After determining all spatial locations, the sum of lumped interference noise ratios generated under all spatial configurations of the constellation can be obtained. .

[0046] (7)

[0047] Because the spatial enumeration process differs from the temporal Monte Carlo method, it cannot be achieved through... To directly obtain the cumulative statistical distribution function corresponding to the interference-to-noise ratio, it is necessary to obtain the probability of the reference satellite appearing at different spatial locations. Therefore, it is necessary to construct a probability distribution model based on the satellite's spatial location to obtain the cumulative statistical distribution function corresponding to the interference-to-noise ratio.

[0048] After selecting any satellite in the constellation as the reference satellite, the positions of all satellites in a single Walker constellation can be determined using the reference satellite's position and the constellation parameters:

[0049] (8)

[0050] in, This indicates that the reference satellite is in orbit ( l =1) or descending orbit ( l The position determined by =2) i The first orbital plane j The location of the satellite; This indicates that the reference satellite is in orbit (l =1) or descending orbit ( l =2) The actual position is determined by the first i The first orbital plane j The distance from each satellite to the Earth's center is determined by the orbital eccentricity, the semi-major axis of the orbit, and the mean anomaly angle of each satellite. The reference satellite is being raised to orbit ( l =1) or descending orbit ( l =2) The actual position is determined by the first i The first orbital plane j The orientation vector of a satellite is determined by the mean anomaly, true anomaly, deviated anomaly, and orbital phase angle of the satellites in the constellation.

[0051] After establishing the positional relationship between the reference satellite and the constellation satellites, the positional distribution of the reference satellite will determine the constellation distribution. First, this is done by projecting latitude and longitude coordinates onto the ground... (wherein, longitude) ,latitude , Let (where is the orbital inclination) be the probability density function representing the ground projection position of the reference satellite.

[0052] (9)

[0053] in, , , It is the track inclination angle. e It is the orbital eccentricity. It is the perigee argument.

[0054] When the orbit is circular, the probability density function of the reference satellite's ground position projection degenerates into:

[0055] (10)

[0056] The spatial positions of the interfering and affected NGSO reference satellites are determined by their ground projection grid points. The coordinates of the ground grid points are determined by the grid spacing. The position of the reference satellite can be set as follows: This converts latitude, longitude, and altitude coordinates into Earth-fixed coordinates.

[0057] In the Earth-fixed system, the three-dimensional coordinate matrix of each ground point can be represented as:

[0058] (11)

[0059] in, Indicates the orbital altitude of the NGSO satellite. Indicates the first The latitude of a ground grid, Indicates the first The longitude of each ground grid.

[0060] If the power, antenna, and other parameters of the interfered system are known, the lumped interference received by the interfered system can be calculated based on the position of the reference satellite. The probability distribution of the ground grid describes the probability of interference occurring when the reference satellite's nadir point is located within that ground grid. This process can be expressed as a probability-based mathematical model for interference calculation:

[0061] (12)

[0062] in, It refers to the probability of a satellite being at a certain location in space; It is the spatial position coordinate vector of all satellites in the constellation determined based on the reference star; These are parameters related to the interference and disturbance of the system link, including parameters such as transmit power, antenna gain, and off-axis angle; The reference satellite is in position p Lumped interference generated by the system; It is a reference satellite in p The probability of lumped disturbance generated by the entire system at a given location.

[0063] like Figure 1 As shown, the inter-constellation spectrum compatibility analysis method provided in this application includes: traversing all ground grid points on the reference satellites of both the interfering and affected systems, solving for the lumped interference and corresponding probabilities of all grids, and statistically obtaining the probability distribution of the lumped interference. The probabilities of lumped interference in a given lumped interference interval on all grids are summed, and this process is repeated for all lumped interference intervals to obtain the lumped interference probability distribution. The pseudocode for obtaining the lumped interference probability distribution is shown in Table 1.

[0064] Table 1. Pseudocode for obtaining the probability distribution of lumped interference

[0065]

[0066] The following example demonstrates the inter-constellation spectrum compatibility analysis method provided in this application. For ease of analysis, the interfering NGSO satellite system is modeled after the orbital configuration of the Starlink constellation, i.e., a satellite with an orbital altitude of 630 km. Its transmit power, carrier bandwidth, and center frequency are based on its beam information registered with the ITU, and the antenna model is the ITU-R S.1528 antenna model. The affected NGSO satellite system is modeled after the orbital configuration of the Oneweb constellation, i.e., a satellite with an orbital altitude of 1200 km. Its transmit power, carrier bandwidth, and center frequency are based on its beam information registered with the ITU, and the antenna model is the ITU-R S.1528 antenna model. The ground station antenna model is the ITU-R S.580-6 antenna model, and the visibility elevation angle threshold between the NGSO satellite and the ground station is set to 30°. Table 2 shows the downlink simulation parameters of the disturbed constellation system. The total number of satellites in the disturbed constellation is 720, and the constellation adopts a delta constellation configuration, distributed across 40 orbital planes. Table 3 shows the downlink simulation parameters of the interfering constellation system. The total number of satellites in the interfering constellation is selected for simulation analysis at scales of 900, 3600, 6000, and 12000, respectively, with 9, 30, 60, and 60 orbital planes, respectively.

[0067] Table 2 Downlink Simulation Parameters of the Disturbed System

[0068]

[0069] Table 3 Downlink Simulation Parameters of the Interference System

[0070]

[0071] The cumulative I / N distribution curves obtained by using this method and time-domain extrapolation methods with different simulation step sizes under interference scenarios of different scales are shown below. Figures 2-5As shown. When the number of satellites in the jamming system is 900, compared with the simulation results of the 10-second step-size scenario, the maximum INR values ​​of the 30-second and 60-second simulation step-size scenarios differ by 0.47 dB and 1.5 dB, respectively, indicating a certain degree of error between the simulation results under different simulation step-size scenarios; the INR values ​​do not exceed the threshold of -12.2 dB. When the number of satellites in the jamming system is 3600, compared with the simulation results of the 10-second step-size scenario, the maximum INR values ​​of the 30-second and 60-second simulation step-size scenarios differ by 0.49 dB and 1.6 dB, respectively, indicating a slightly larger error between the simulation results under different simulation step-size scenarios; the probability of the INR exceeding the threshold differs by approximately 0.7% and 1.9%, respectively. When the number of satellites in the jamming system is 6000, compared with the simulation results of the 10-second step size scenario, the maximum INR values ​​for the 30-second and 60-second step size scenarios differ by 0.76 dB and 1.8 dB, respectively, indicating a further increase in the error between the simulation results under different step size scenarios; the probability of INR exceeding the threshold differs by approximately 0.8% and 2.1%, respectively. When the number of satellites in the jamming system is 12000, compared with the simulation results of the 10-second step size scenario, the maximum INR values ​​for the 30-second and 60-second step size scenarios differ by 1 dB and 2.2 dB, respectively, indicating a larger error between the simulation results under different step size scenarios; compared with the simulation results of the 60-second step size scenario, the probability of INR exceeding the threshold differs by approximately 2.5%, while the probability of INR exceeding the threshold is basically the same compared to the simulation results of the 30-second step size scenario. The simulation results obtained by this method under different simulation scale scenarios are basically consistent with those obtained with a simulation step size of 10 seconds. Figures 2-5 In the table, time-extrapolated analysis method (10s), time-extrapolated analysis method (30s), and time-extrapolated analysis method (60s) represent time-extrapolated analysis methods (step sizes of 10s, 30s, and 60s), respectively. Fine Mesh Partitioning Method represents a fine mesh partitioning method, and INR Threshold Values ​​(-12.2 dB) represents an interference-to-noise ratio threshold of -12.2 dB.

[0072] This application also provides an inter-constellation spectrum compatibility analysis system, implemented based on the above method, the system comprising:

[0073] The module for obtaining satellite lumped interference and corresponding probabilities is used to enable the reference satellites of the interfering system and the disturbed system to traverse all ground grid points and solve for the lumped interference and corresponding probabilities of all grids.

[0074] The module for obtaining the lumped interference probability distribution is used to sum the probabilities of lumped interference for each given lumped interference interval on all grids to obtain the lumped interference probability distribution.

[0075] This application may also provide a computer device, including: at least one processor, memory, at least one network interface, and a user interface. The various components in this device are coupled together via a bus system. It is understood that the bus system is used to implement communication between these components. In addition to a data bus, the bus system also includes a power bus, a control bus, and a status signal bus.

[0076] The user interface can include a display, keyboard, or clicking device. Examples include a mouse, trackball, touchpad, or touchscreen.

[0077] It is understood that the memory in the embodiments disclosed in this application may be volatile memory or non-volatile memory, or may include both volatile and non-volatile memory. The non-volatile memory may be read-only memory (ROM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), electrically erasable programmable read-only memory (EEPROM), or flash memory. The volatile memory may be random access memory (RAM), which is used as an external cache. By way of example, but not limitation, many forms of RAM are available, such as Static Random Access Memory (SRAM), Dynamic Random Access Memory (DRAM), Synchronous DRAM (SDRAM), Double Data Rate SDRAM (DDRSDRAM), Enhanced Synchronous DRAM (ESDRAM), Synchlink DRAM (SLDRAM), and Direct Rambus RAM (DRRAM). The memories described herein are intended to include, but are not limited to, these and any other suitable types of memory.

[0078] In some implementations, the memory stores elements such as executable modules or data structures, or subsets thereof, or extended sets thereof: operating systems and applications.

[0079] The operating system includes various system programs, such as the framework layer, core library layer, and driver layer, used to implement various basic business functions and handle hardware-based tasks. The application programs include various applications, such as media players and browsers, used to implement various application functions. Programs implementing the methods of the embodiments of this disclosure can be included in the application programs.

[0080] In the above embodiments, the processor can also invoke programs or instructions stored in memory, specifically programs or instructions stored in an application program, for the following purposes:

[0081] Follow the steps described above.

[0082] The above methods can be applied to or implemented by a processor. The processor may be an integrated circuit chip with signal processing capabilities. During implementation, each step of the above methods can be completed by integrated logic circuits in the processor's hardware or by software instructions. The processor can be a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. It can implement or execute the methods, steps, and logic diagrams disclosed above. The general-purpose processor can be a microprocessor or any conventional processor. The steps of the disclosed methods can be directly implemented by a hardware decoding processor, or by a combination of hardware and software modules in the decoding processor. The software modules can reside in random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, or other mature storage media in the art. This storage medium is located in memory; the processor reads information from the memory and, in conjunction with its hardware, completes the steps of the above methods.

[0083] It is understood that the embodiments described in this application can be implemented using hardware, software, firmware, middleware, microcode, or a combination thereof. For hardware implementation, the processing unit can be implemented in one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), general-purpose processors, controllers, microcontrollers, microprocessors, other electronic units for performing the functions described in this application, or combinations thereof.

[0084] For software implementation, the technology of this application can be implemented by executing the functional modules (e.g., procedures, functions, etc.) of this application. The software code can be stored in memory and executed by a processor. The memory can be implemented in the processor or outside the processor.

[0085] This application may also provide a non-volatile storage medium for storing a computer program. When the computer program is executed by a processor, it can implement the steps in the above method embodiments.

[0086] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application and are not intended to limit it. Although this application has been described in detail with reference to the embodiments, those skilled in the art should understand that modifications or equivalent substitutions to the technical solutions of this application do not depart from the spirit and scope of the technical solutions of this application, and should all be covered within the scope of the claims of this application.

Claims

1. A method for analyzing inter-constellation spectral compatibility, comprising: The reference satellites of each interfering and disturbed system traverse all ground grid points to solve for the lumped interference and corresponding probability of all grids; The solution method for the lumped interference is as follows: ； in, Indicates the disturbed reference satellite in the 1st century. q The grid, the interference reference satellite in the 1st grid p Lumped disturbance when there are individual grids; This indicates the transmission power that interferes with the NGSO satellite; Indicates the gain of the interfering NGSO satellite antenna; Indicates the off-axis angle of the NGSO satellite transmitter; Indicates the antenna gain of the disturbed earth station; Indicates the off-axis angle of the received data from the disturbed earth station; Indicates link loss; Summing the probabilities of lumped interference for each given lumped interference interval across all grids yields the lumped interference probability distribution. The method for solving the probability is as follows: ； in, Indicates the disturbed reference satellite in the 1st century. q The grid, the interference reference satellite in the 1st grid p The probability of each grid cell; Indicates the interference reference satellite in the p The probability density function of each grid cell; Indicates the disturbed reference satellite in the 1st century. q The probability density function of each grid cell; The expression for the probability density function is: ； in, Indicates the satellite's latitude and longitude coordinates on the ground. The probability density function of the projection location, superscript T Indicates matrix transpose; Indicates longitude , Indicate latitude , Indicates orbital inclination angle; intermediate variable , Indicates the argument of perigee; ; e This represents the orbital eccentricity.

2. A constellation spectral compatibility analysis system, implemented based on the method of claim 1, characterized in that, The system includes: A module for obtaining lumped interference and corresponding probabilities from satellites is used to enable the reference satellites of both the interfering and affected systems to traverse all ground grid points, solving for the lumped interference and corresponding probabilities across all grids; and The module for obtaining the lumped interference probability distribution is used to sum the probabilities of lumped interference for each given lumped interference interval on all grids to obtain the lumped interference probability distribution.

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