Large-scale constellation rapid topology sampling method and device in space unreliable environment

Abstract

The invention discloses a rapid topology sampling method and device for a large-scale constellation in an unreliable space environment, and mainly solves the problem of low sampling efficiency in the prior art. According to the implementation scheme, satellite constellation configuration parameters are obtained; different orbit link establishment modes of all satellite nodes under different distortion factors are determined; determining distribution modes of all satellite nodes on a virtual plane under different constellation configurations; judging whether the satellites have synchronism in the critical latitude region crossing event or not, and judging whether topological dynamics can be caused when the first orbit satellite and the tail orbit satellite cross the critical latitude region or not; automatically calculating the number and length of topology snapshots of constellation distortion topology in an orbit period according to a different orbit link establishment mode, a distribution mode of satellite nodes on a virtual plane and a topology dynamic result, and determining a distribution rule of inter-satellite topology snapshots; and converting a calculation result into an inter-satellite topology sampling time point and a corresponding topology snapshot length according to the distribution rule. The method is high in sampling efficiency and low in use threshold, and can be used for design and optimization of a large-scale distorted topological constellation network protocol.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of satellite communication, and particularly relates to a fast topology sampling method and device for a large-scale distorted topology constellation, which can be used for design and optimization of a large-scale distorted topology constellation network protocol, analysis and evaluation of network performance, and planning and deployment of the network. BACKGROUND

[0002] Low Earth Orbit (LEO) satellite networks have become the core infrastructure for building global space-air-ground integrated communication networks due to their wide coverage, large backhaul capacity, and strong anti-destroying ability. With the rapid deployment of large-scale constellations such as SpaceX Starlink and OneWeb, the scale of satellite nodes can reach tens of thousands, and the topology structure presents unprecedented complexity and dynamics. In the unreliable space environment, inter-satellite links may be at risk of disconnection, and the high-speed movement of LEO satellites in certain latitude regions will cause the periodic on-off of inter-satellite link states, making the network topology structure present periodic time-varying characteristics. This dynamic characteristic directly affects the stability of network routing, resource management efficiency, and other aspects, bringing severe challenges to the management of large-scale satellite networks. Therefore, accurate and fast quantification of topology dynamics is an important prerequisite for optimizing satellite network design. Topology dynamics is usually quantitatively described using the number of different topology snapshots and their duration that remain stable within an orbital period, and then providing a basis for the design of satellite networks through topology sampling devices.

[0003] In the prior art, the quantification and analysis of the dynamic characteristics of the topology of low-orbit satellite networks mainly fall into two categories: one is a method based on analytical model derivation, which establishes an inter-satellite visibility model through orbital mechanics and geometric relationships, and derives the topology change rule. However, the theoretical derivation process is tedious and prone to errors. The second is a method based on general network simulation software, which uses tools such as STK, NS-2, and OPNET to establish detailed satellite orbit and network models for simulation. However, due to the large amount of calculation and long time consumption in the simulation process, the simulation results are usually raw link state or node connectivity data, and users need to write complex post-processing scripts to extract the number and duration sequence of topology snapshots, which is inefficient and complex to operate.

[0004] The patent document with application number CN202411212103.4 discloses a method for calculating the topology stability of a low-orbit satellite network based on constellation configuration parameters. It characterizes the stability of the dynamic topology of the satellite network by calculating the statistical law of the over-the-top time and other indicators. However, this method does not provide a deterministic representation of the dynamic characteristics of the satellite network topology, and cannot complete accurate topology sampling. SUMMARY

[0005] The purpose of this invention is to overcome the shortcomings of the prior art and provide a method and apparatus for fast topology sampling of large-scale constellations in unreliable space environments, thereby avoiding complex theoretical derivations or post-processing of simulation results and improving efficiency. The sampling efficiency of constellation-distorted topology snapshots provides fast and accurate topology sampling for network planning and deployment.

[0006] Sample input.

[0007] The technical approach to achieving the objective of this invention is to calculate the representation in real time and directly based on the input constellation configuration and other parameters. The key quantitative indicators such as the number and length of topological snapshots in the dynamic changes of constellation warped topology, as well as the topology sampling time points and corresponding topology snapshot lengths, are used to avoid users having to perform complex theoretical derivations or post-simulation result processing steps, thereby improving efficiency. Sampling efficiency of constellation distorted topology.

[0008] Based on the above ideas, the technical solution of the present invention includes:

[0009] 1. A fast topology sampling method for large-scale constellations in unreliable space environments, characterized by comprising:

[0010] (1) Obtain satellite constellation configuration parameters, including: distortion factor, phase factor, number of satellites per orbit, number of orbital planes, orbital inclination, orbital altitude, and latitude value of critical region;

[0011] (2) Determine the different orbital linking modes of all satellite nodes under different torsion factors, and use them as part of the input for the quantitative calculation of topological dynamic characteristics;

[0012] (3) Determine the distribution pattern of all satellite nodes on the virtual plane under different constellation configurations, and use it as part of the input for the quantitative calculation of topological dynamic characteristics;

[0013] (4) Determine whether the satellite crossing events in the critical latitude region are synchronous, and determine whether the crossing of the critical latitude region by the first and last orbit satellites will lead to topological dynamics. Use the result as part of the input for the quantitative calculation of topological dynamic characteristics.

[0014] (5) Based on the input results of steps (2), (3), and (4), automatically calculate The quantitative indicators of the topological dynamics of constellation distortion topology within one orbital period include the number and length of topological snapshots, and determine the distribution pattern of inter-satellite topological snapshots;

[0015] (6) Based on the distribution pattern of inter-satellite topology snapshots, the calculation results are converted into inter-satellite topology sampling time points and corresponding topology snapshot lengths.

[0016] 2. A fast topology sampling device for large-scale constellations in unreliable space environments, comprising:

[0017] Constellation configuration parameter input module: Used to receive satellite constellation configuration parameters input by the user, including: distortion factor, phase factor, number of satellites per orbit, number of orbital planes, orbital inclination, orbital altitude, and latitude value of critical region;

[0018] The module for determining the different orbit link establishment mode is used to determine the different orbit link establishment mode of all satellite nodes under different torsion factors, and serves as part of the input to the topology dynamic characteristics quantification calculation module.

[0019] Virtual plane satellite distribution pattern determination module: used to determine the distribution pattern of all satellite nodes on the virtual plane under different constellation configurations, and as part of the input of the topology dynamic characteristics quantification calculation module;

[0020] Critical Latitude Region Judgment Module: Used to determine whether satellite crossing events in the critical latitude region are synchronous, and whether the crossing of the critical latitude region by the first and last orbit satellites will cause topological dynamics. Finally, it serves as part of the input for the topological dynamics characteristic quantification calculation module.

[0021] Topology dynamic characteristics quantification calculation module: Used to automatically calculate based on the input information of the module determining the heterogeneous orbit link establishment method, the virtual plane satellite distribution pattern, and the critical latitude region judgment module. The quantitative indicators of the topological dynamics of constellation warp topology within one orbital period include the number and length of topological snapshots;

[0022] Inter-satellite topology sampling output module: This module converts the calculation results from the topology dynamic characteristics quantization calculation module into inter-satellite topology sampling time points and corresponding topology snapshot lengths, and outputs them in a preset format.

[0023] Compared with the prior art, the present invention has the following advantages:

[0024] Firstly, this invention utilizes a graph-based quantitative analysis framework for low-Earth orbit satellite networks. With constellation configuration and high-performance twisted topology, users only need to input basic constellation configuration parameters, and the device will automatically and efficiently calculate the quantized values ​​of topological dynamic characteristics under arbitrary parameters, and output the sampling time point of inter-satellite topology and the corresponding topology snapshot length. This eliminates the tedious theoretical derivation or simulation configuration and result post-processing, greatly reducing the threshold for use and improving the analysis efficiency.

[0025] Secondly, the judgment formulas and calculation formulas involved in this invention are all given in the form of closed formulas. These formulas have low computational complexity, and the computational complexity is not affected by the constellation configuration, making them suitable for large-scale constellations.

[0026] Thirdly, this invention provides real-time and efficient... The dynamic characteristics quantification of constellation warped topology can provide fast and accurate topology sampling input for constellation network protocol design and optimization, network performance analysis and evaluation, and network planning and deployment. Attached Figure Description

[0027] Figure 1 This is a flowchart illustrating the implementation of the fast inter-satellite topology sampling method for large-scale distorted topology constellations according to the present invention.

[0028] Figure 2 This is a schematic diagram illustrating the satellite distribution patterns under four different constellation configurations determined in the method of this invention;

[0029] Figure 3 This is a schematic diagram illustrating the determination of the critical latitude region in the method of the present invention;

[0030] Figure 4 This is a block diagram of the fast inter-satellite topology sampling device for large-scale distorted topology constellations according to the present invention. Detailed Implementation

[0031] The embodiments and effects of the present invention will be described in further detail below with reference to the accompanying drawings.

[0032] Example 1: A Fast Topology Sampling Method for Large-Scale Constellations in Unreliable Space Environments

[0033] This embodiment uses a 720 / 36 / 1:70° angle. Taking constellation satellite networks as an example, this paper illustrates a fast inter-satellite topology sampling method for constellations with large-scale distorted topology.

[0034] Reference Figure 1 The implementation steps of this example include the following:

[0035] Step 1: Obtain and input satellite constellation configuration parameters.

[0036] Satellite constellation configuration parameters include: distortion factor Phase factor Number of satellites per orbit Number of orbital planes Track inclination Track height Latitude value of critical region .

[0037] This example takes, but is not limited to, the distortion factor. Phase factor Number of satellites per orbit Number of orbital planes Track inclination °, orbital altitude Latitude value of critical region °.

[0038] Among them, the distortion factor This is a parameter used to characterize the degree of distortion in twisted mesh topology. Twisted mesh topology can effectively improve network connectivity. It is based on 2D-Torus topology and modifies the initial orbit satellite... and terminal orbit satellite The twisted loop connection method, and using the twist factor To characterize the degree of distortion, .

[0039] Step 2: Determine the different orbit linking modes of all satellite nodes under different distortion factors.

[0040] 2.1) Definition Indicates the orbital number of the satellite. Indicates the satellite's position number on a certain orbit;

[0041] 2.2) According to the track number The value determines the satellite type:

[0042] like Then it is called This is the first satellite in orbit;

[0043] like Then it is called For terminal orbit satellites;

[0044] like Then it is called It is an inner-orbit satellite.

[0045] 2.3) Based on the distortion factor and phase factor The value relationship is used to determine the cross-track link establishment mode:

[0046] when At that time, all satellites used equal phase difference between the front and rear ends: The link establishment method and the link establishment of satellites in different orbits;

[0047] when At that time, inner-orbit satellites use equal phase difference between the front and rear: Link establishment method and link establishment with adjacent satellites in different orbits; first orbit satellite With the terminal orbit satellite Linkage phase difference for:

[0048] ;

[0049] in, Number the location of the terminal orbit satellite. The location of the first satellite in orbit is numbered.

[0050] In this embodiment, , Inner-orbit satellites use equal phase difference between front and rear orbits. The link establishment method involves establishing links with adjacent satellites in different orbits, with a phase difference between the first and last orbit satellites. .

[0051] Step 3: Determine the distribution pattern of all satellite nodes on the virtual plane under different constellation configurations.

[0052] 3.1) Define the virtual orbital plane It maps all satellite nodes in the constellation to a single orbital plane with the same altitude as the orbits in the constellation and an inclination of 90°. Each satellite node is distributed at equal intervals according to the original phase difference of the constellation, that is, maintaining the original angular distance and maintaining the inter-orbit link connection relationship in the network.

[0053] 3.2) Based on satellite nodes In the virtual orbital plane The direction of motion determines the positions of adjacent satellites in the same orbit and adjacent satellites in different orbits:

[0054] Assuming satellite nodes exist The direction of motion is clockwise, and the satellite is known to be... exist The position of the moment is in Adjacent satellites in the same orbit at the same time Located on satellite angular distance in counterclockwise direction Location; adjacent satellites in different orbits Located on satellite angular distance in counterclockwise direction Place;

[0055] 3.3) Determine All satellite nodes Distribution pattern:

[0056] 3.3.1) Assumptions Up satellite node The number of Ignoring the phase difference between adjacent satellites, ,make Determine the factors for the node distribution pattern;

[0057] 3.3.2) According to Take different types of values ​​and determine. All satellite nodes Four different distribution patterns:

[0058] The first type: when hour, Divided evenly Segment, all satellite nodes Distributed in descending order of their numbers and counterclockwise with equal phase differences, they do not overlap, and their phase differences are: , ;

[0059] The second type: when hour, Divided evenly Segment, every phase difference Then there will be If multiple satellites overlap and are distributed at the same point, the overlapping satellites will arrive at the same latitude point simultaneously. ;

[0060] The third type: when and At that time, among them , and There exists a common factor greater than 1, in which case adjacent satellites in different orbits have a skipped and overlapping distribution, and the phase difference between adjacent satellites in different orbits is... quilt Equal division of the phase difference between adjacent satellites in the same orbit quilt equal parts, Divided evenly Segment, every phase difference Then there will be The satellites overlap and are distributed at the same point. ;

[0061] The fourth type: when and At that time, among them , Divided evenly The segments have no overlap, and adjacent satellites on different orbits are distributed in a skip pattern. The phase difference between adjacent satellites is , .

[0062] The above four satellite distribution patterns are represented in specific constellation configurations as follows: Figure 2 As shown, where:

[0063] Figure 2 (a) represents all satellite nodes under constellation configuration 18 / 6 / 1. exist The distribution pattern on the surface conforms to the first distribution pattern.

[0064] Figure 2 (b) represents all satellite nodes under constellation configuration 18 / 6 / 2. exist The distribution pattern on the surface conforms to the second distribution pattern.

[0065] Figure 2 (c) represents all satellite nodes in constellation configuration 18 / 6 / 4. exist The distribution pattern on the surface conforms to the third distribution pattern.

[0066] Figure 2 (d) represents all satellite nodes in constellation configuration 18 / 6 / 5. exist The distribution pattern on it conforms to the fourth distribution pattern.

[0067] In this embodiment, the distribution pattern of all satellite nodes on the virtual plane under this constellation configuration conforms to the first case, i.e., the phase difference is... .

[0068] Step 4: Determine the synchronization and topological dynamics of satellites in the critical latitude region.

[0069] 4.1) As Figure 3 As shown, the Critical Latitude Region (CLR) is defined as the latitudinal region in the LEO satellite network where inter-satellite links between different orbits need to be broken, and it is divided into the North and South CLRs with geocentric symmetry. The latitude value of CLR. Let the orbital inclination be the angle between the line connecting the CLR latitude point to the Earth's center and the intersection of the equatorial plane and the orbital plane. ;

[0070] 4.2) Define the time difference between two consecutive satellites entering / leaving the CLR as . The corresponding phase difference is , Phase difference between two adjacent satellites The corresponding time difference is Then when When the number of satellites distributed in the upper region is even, ;when When the number of satellites distributed in the upper region is odd, ,in For orbital period, For the Earth's radius, Standard gravity parameters;

[0071] 4.3) Define the time property of one satellite entering the CLR while another satellite leaves the CLR as out-of-phase synchronization; 4.4) Two cases to determine whether satellites have synchronization during CLR crossing events:

[0072] Scenario 1:

[0073] when At any given time, when one satellite enters the CLR, another satellite will simultaneously leave the CLR:

[0074] If at this time If the number of satellites distributed in the upper region is even, then the satellites are synchronous during CLR crossing events, and the simultaneous entry and exit events occur in the same half of the CLR. It is a natural number;

[0075] If at this time The number of satellites distributed upwards is odd, and If the satellite is synchronous during the CLR crossing event, the simultaneous entry and exit events are not in the same half of the CLR.

[0076] If at this time The number of satellites distributed upwards is odd, and If the satellite is synchronous during the CLR crossing event, and the simultaneous entry and exit events occur in the same half of the CLR;

[0077] Scenario 2:

[0078] when At that time, if Then any satellite After entering the CLR, before the next satellite enters the CLR, If the satellite leaves the CLR, the satellite entry and exit events are not synchronized; if any satellite After entering the CLR, before the next satellite enters the CLR, If a satellite is about to leave the CLR, the satellite entry and departure events are not synchronized.

[0079] when At that time, if Then the first orbit satellite Entering a CLR event does not cause topology dynamics, and the terminal orbit satellite The departure event does not cause topological dynamics.

[0080] In this embodiment, condition 2 is met, that is, the satellite entry event and the departure event are not synchronous, and the first and last orbit satellites do not cause topological dynamics when they cross the critical latitude region.

[0081] Step 5: Using the different orbit link establishment mode determined in Step 2, the distribution pattern of all satellite nodes on the virtual plane determined in Step 3, and the synchronization of satellites during the CLR crossing event determined in Step 4 as inputs, calculate... A quantitative indicator of the topological dynamics of constellation distortion topology within one orbital period.

[0082] The quantitative indicators of topology dynamic characteristics include the number and length of topology snapshots, which are calculated as follows:

[0083] 5.1) Calculate the number of topology snapshots:

[0084] Calculate the number of topological snapshots under different torsion factors, CLR ranges, and constellation configurations based on the input information and the closed formulas in the table below. , In order to cooperate with satellites Distribution and distortion factor The discrete-valued functions related to the CLR range are calculated in the following table 1.

[0085] Table 1. Number of topological snapshots under different distortion factors, CLR ranges, and constellation configurations.

[0086]

[0087] 5.2 Calculate the length of the topology snapshot

[0088] The topological snapshot length under different distortion factors, CLR ranges, and constellation configurations is calculated based on the input information. The specific calculations are shown in Table 2.

[0089] Table 2. Topological snapshot lengths under different distortion factors, CLR ranges, and constellation configurations.

[0090]

[0091] Within one orbital period: Indicates the length of the first possible topology snapshot; Indicates the length of the second possible topology snapshot; This indicates the first category that may occur under the third type of topology snapshot length; This indicates the second category that may occur under the third type of topology snapshot length; This indicates the third category that may occur under the third type of topology snapshot length;

[0092] 5.3) Definition The phase difference between adjacent satellites entering the CLR in the same orbit is ,when hour, ,when hour, ;

[0093] 5.4) Define the distribution pattern of inter-satellite topological snapshots:

[0094] Assuming that the topological snapshots within an orbital period form a sequence, since The equal phase difference distribution of satellites makes the satellite crossings of the CLR events temporally regular, thus making this a cyclic sequence. The cyclical nature of this sequence is determined by the CLR range, satellite distribution, and distortion factor. The distribution pattern of its inter-satellite topological snapshots is shown below:

[0095] when , , or , , hour:

[0096] like Then the cycle of the topological snapshot distribution is The minimum cycle period is The number of loops is or ,

[0097] like In the cyclic section of the topological snapshot distribution, The minimum cycle period is The number of loops is or ,

[0098] like Then the cycle of the topological snapshot distribution is The minimum cycle period is The number of loops is or ;

[0099] remove , , or In all other cases:

[0100] like The cyclic section of the topological snapshot distribution is The minimum cycle period is 1, and the number of cycles is 1. or ,

[0101] like Then the cycle of the topological snapshot distribution is The minimum cycle period is 2, and the number of cycles is or .

[0102] In this embodiment, the number of topology snapshots is The topology snapshot lengths are respectively , , And the minimum cycle of the topological snapshot distribution is The minimum cycle period is 70, and the number of cycles is 20.

[0103] Step 6: Convert the calculation results of Step 5 into inter-satellite topology sampling time points and corresponding topology snapshot lengths.

[0104] 6.1) Define the time of the first occurrence of topological dynamics within one orbital period as the start time. Specifically, it refers to the start time of the first topological snapshot of the minimum cycle node under the topological snapshot distribution pattern;

[0105] 6.2) Based on the distribution pattern of topological snapshots, obtain all inter-satellite topological sampling time points within one orbital period. And the corresponding topology snapshot length, time point and The interval between them is the length of the first topological snapshot of the smallest cycle node under the topological snapshot distribution law, and so on, for the orbital period. .

[0106] It should be noted that the processes described in the above embodiments can be understood as representing a module, segment, or portion of code comprising one or more executable instructions configured to implement a specific logical function or process. This invention is not limited to the disclosed preferred embodiments, and its implementation may not follow the order shown or discussed. That is, the step numbers in the specification and claims are merely for clear description and understanding of the embodiments of this invention, and their order is not limited.

[0107] Example 2: A fast inter-satellite topology sampling device for large-scale warped topology constellations

[0108] Reference Figure 4 This example includes a constellation configuration parameter input module 1, an orbital link establishment method determination module 2, a satellite distribution pattern determination module 3, a region judgment module 4, a topology dynamic characteristic quantification module 5, and an inter-satellite topology sampling output module 6. The topology dynamic characteristic quantification module includes: a topology snapshot count sub-calculation module 51 and a topology snapshot length calculation sub-module 52. The working principle of the entire device is as follows:

[0109] The constellation configuration parameter input module 1 is used to receive parameters input by the user, including: distortion factor, phase factor, number of satellites per orbit, number of orbital planes, orbital inclination, orbital altitude, and satellite constellation configuration parameters of critical region latitude value;

[0110] The differential orbit link establishment mode determination module 2 is used to determine the differential orbit link establishment mode of all satellite nodes under different torsion factors, and use it as part of the input of the topology dynamic characteristic quantification calculation module 5.

[0111] The satellite distribution pattern determination module 3 is used to determine the distribution pattern of all satellite nodes on the virtual plane under different constellation configurations, and serves as part of the input to the topology dynamic characteristics quantification calculation module 5.

[0112] The region judgment module 4 is used to determine whether the satellite crossing events in the critical latitude region are synchronous, and whether the crossing of the critical latitude region by the first and last orbit satellites will cause topological dynamics. Finally, it serves as part of the input to the topological dynamics characteristic quantification calculation module 5.

[0113] Topology dynamic characteristics quantification calculation module 5: Used to automatically calculate based on the input information of the module determining the heterogeneous orbit link establishment method, the module determining the virtual plane satellite distribution pattern, and the critical latitude region judgment module. The constellation distortion topology is a quantitative index of topological dynamic characteristics within one orbital period. The topology snapshot count sub-calculation module 51 calculates the number of topology snapshots, the topology snapshot length calculation sub-module 52 calculates the length of the topology snapshot, and transmits the calculation results to the inter-satellite topology sampling output module 6.

[0114] The inter-satellite topology sampling output module 6 is used to convert the calculation results of the topology dynamic characteristic quantification calculation module 5 into inter-satellite topology sampling time points and corresponding topology snapshot lengths, and output them in a preset format.

[0115] It should be noted that the above functional modules can be implemented, in whole or in part, through software, hardware, firmware, or any combination thereof. When implemented in software, they can be implemented, in whole or in part, as program instruction products. A program instruction product includes one or a set of program instructions. When the program instructions are loaded and executed on a computer, the described process or function is generated, in whole or in part. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The program instructions can be stored in a computer-readable and writable storage medium, or transferred from one computer's readable and writable storage medium to another.

[0116] The direct coupling or communication connections between the modules shown or discussed in this embodiment can be achieved through indirect coupling or communication connections via interfaces, devices, or modules. The various functional modules and sub-modules in this embodiment can dynamically reside within a single processing unit, or each module can exist physically independently, or two or more modules can dynamically reside within a single processing unit. When these dynamic components are implemented as software functional modules and sold or used as independent products, they can also be stored in a computer-readable and writable storage medium. This storage medium can be a memory, disk, or optical disc, etc.

[0117] The above description is merely two specific embodiments of the present invention and does not constitute any limitation on the present invention. Obviously, those skilled in the art, after understanding the content and principles of the present invention, may make various modifications and changes in form and details without departing from the principles and structure of the present invention. However, these modifications and changes based on the ideas of the present invention are still within the scope of protection of the claims of the present invention.

Claims

1. A fast topology sampling method for large-scale constellations in unreliable space environments, characterized in that, include: (1) Obtain satellite constellation configuration parameters, including: distortion factor Phase factor Number of satellites per orbit Number of orbital planes Track inclination Track height Latitude value of critical region ; (2) Determine the different orbital linking modes of all satellite nodes under different torsion factors, and use them as part of the input for the quantitative calculation of topological dynamic characteristics; (3) Determine the distribution pattern of all satellite nodes on the virtual plane under different constellation configurations, and use it as part of the input for the quantitative calculation of topological dynamic characteristics; (4) Determine whether the satellite crossing events in the critical latitude region are synchronous, and determine whether the crossing of the critical latitude region by the first and last orbit satellites will lead to topological dynamics. Use the result as part of the input for the quantitative calculation of topological dynamic characteristics. (5) Based on the input results of steps (2), (3), and (4), automatically calculate The number and length of topological snapshots within one orbital period of constellation distortion topology are used as quantitative indicators of topological dynamic characteristics, and the distribution pattern of topological snapshots is determined. (6) Based on the distribution pattern of inter-satellite topology snapshots, the calculation results are converted into inter-satellite topology sampling time points and corresponding topology snapshot lengths.

2. The method according to claim 2, characterized in that, The determination of the different orbital linking modes of all satellite nodes under different distortion factors in (2) includes the following implementation: 2a) Definition Indicates the orbital number of the satellite. This indicates the satellite's position number on a given orbit; 2b) Determine the type of satellite based on its orbital number: like Then it is called This is the first satellite in orbit; like Then it is called For terminal orbit satellites; like Then it is called For inner orbit satellites; 2c) Based on the distortion factor With phase factor The numerical relationships determine the different orbit link establishment modes for various types of satellites: when At that time, all types of satellites, namely the first orbit, the last orbit, and the inner orbit satellites, use equal phase difference between the front and rear orbits: The link establishment method and the link establishment of satellites in different orbits; when At that time, inner-orbit satellites use equal phase difference between the front and rear: Link establishment method and link establishment with adjacent satellites in different orbits; first orbit satellite With the terminal orbit satellite Linkage phase difference for: ， in, Number the location of the terminal orbit satellite. The location of the first satellite in orbit is numbered.

3. The method according to claim 1, characterized in that, The determination of the distribution pattern of all satellite nodes on the virtual plane under different constellation configurations in (3) includes the following implementation: 3a) Define the virtual orbital plane It maps all satellite nodes in the constellation to a single orbital plane with the same altitude as the orbits in the constellation and an inclination of 90°. Each satellite node is distributed at equal intervals according to the original phase difference of the constellation, that is, maintaining the original angular distance and the inter-orbit link connection relationship in the network. 3b) Based on satellite nodes In the virtual orbital plane The direction of motion determines the positions of adjacent satellites in the same orbit and adjacent satellites in different orbits: Set up satellite nodes exist The direction of motion is clockwise, and the satellite is known to be... exist The position of the moment is in Adjacent satellites in the same orbit at the same time Located on satellite angular distance in counterclockwise direction Location; adjacent satellites in different orbits Located on satellite angular distance in counterclockwise direction Among them, Number the orbit where the satellite is located. Number the satellite's position on a given orbit; 3c) Determine All satellite nodes Distribution pattern: 3c1) Let Up satellite node The number of Ignoring the phase difference between adjacent satellites, ,make Determine the factors for the node distribution pattern; 3c2) According to Take different types of values ​​and determine. All satellite nodes Different distribution patterns: when hour, Divided evenly Segment, all types of satellite nodes Distributed in descending order of their numbers and counterclockwise with equal phase differences, they do not overlap, and their phase differences are: , ; when hour, Divided evenly Segment, every phase difference Then there will be If multiple satellites overlap and are distributed at the same point, the overlapping satellites will arrive at the same latitude point simultaneously. ,in It is a natural number; when and At that time, adjacent satellites with different orbits are distributed in a skip-over pattern, and the phase difference between adjacent satellites with different orbits is large. quilt Equal division of the phase difference between adjacent satellites in the same orbit quilt equal parts, Divided evenly Segment, every phase difference Then there will be The satellites overlap and are distributed at the same point. ,in , and There exists a common factor greater than 1; when and hour, Divided evenly The segments have no overlap, and adjacent satellites on different orbits are distributed in a skip pattern. The phase difference between adjacent satellites is , .

4. The method according to claim 1, characterized in that, The determination in (4) of whether the satellite crossing events in the critical latitude region are synchronous, and whether the crossing of the critical latitude region by the first and last orbit satellites will lead to topological dynamics, includes the following implementation: 4.1) Define the Critical Latitude Region (CLR) as the latitudinal region in the LEO satellite network where inter-satellite links between different orbits need to be broken, and divide it into North and South CLRs with geocentric symmetry. Latitude value of CLR , Let the orbital inclination be the angle between the line connecting the CLR latitude point to the Earth's center and the intersection of the equatorial plane and the orbital plane. ; 4.2) Define the time difference between two consecutive satellites entering / leaving the CLR as . The corresponding phase difference is , Phase difference between two adjacent satellites The corresponding time difference is Then when When the number of satellites distributed in the upper region is even, ,when When the number of satellites distributed in the upper region is odd, ,in For orbital period, For the Earth's radius, Standard gravity parameters; 4.3) Define the time property of one satellite entering the CLR while another satellite leaves the CLR as anti-phase synchronization; 4.4) Two scenarios for determining whether satellites are synchronous during a CLR crossing event: Scenario 1: when At any given time, when one satellite enters the CLR, another satellite will simultaneously leave the CLR: If at this time If the number of satellites distributed in the upper region is even, then the satellites are synchronous during CLR crossing events, and the simultaneous entry and exit events occur in the same half of the CLR. It is a natural number; If at this time The number of satellites distributed upwards is odd, and If the satellite is synchronous during the CLR crossing event, the simultaneous entry and exit events are not in the same half of the CLR. If at this time The number of satellites distributed upwards is odd, and If the satellite is synchronous during the CLR crossing event, and the simultaneous entry and exit events occur in the same half of the CLR; Scenario 2: when At that time, if Then any satellite After entering the CLR, before the next satellite enters the CLR, If the satellite leaves the CLR, the satellite entry and exit events are not synchronized; if any satellite After entering the CLR, before the next satellite enters the CLR, If a satellite is about to leave the CLR, then the satellite entry and departure events are not synchronized. Number the orbit where the satellite is located. Number the satellite's position on a given orbit; when At that time, if Then the first orbit satellite Entering a CLR event does not cause topology dynamics, and the terminal orbit satellite The departure event does not cause topological dynamics, where, Number the location of the terminal orbit satellite. The location of the first satellite in orbit is numbered.

5. The method according to claim 1, characterized in that, In step (5), the calculation is performed automatically based on the input results. The number of topological snapshots of a constellation's warped topology within one orbital period, implemented as follows: when , hour: like Then the number of topologies is ; like Then the number of topologies is ; when , hour: like Then the number of topologies is , like Then the number of topologies is ; when , , , hour: like Then the number of topologies is , like In a topology with ; when , , , hour: like Then the number of topologies is , like Then the number of topologies is , like Then the number of topologies is ; when , , , hour: like Then the number of topologies is , like Then the number of topologies is ; when , , , hour: like Then the number of topologies is , like Then the number of topologies is ; when , , hour: like Then the number of topologies is , like Then the number of topologies is ; when , , hour: like Then the number of topologies is , like Then the number of topologies is , in, for Up satellite node The number of It is a natural number.

6. The method according to claim 1, characterized in that, In step (5), the calculation is performed automatically based on the input results. The length of a topological snapshot of a constellation warp topology within one orbital period, implemented as follows: when , hour: like The length of the topology snapshot is , like The length of the topology snapshot is ; when , hour: like The length of the topology snapshot is , , like The length of the topology snapshot is , ; when , hour: like The length of the topology snapshot is , like The length of the topology snapshot is ; when , , hour: like and The length of the topology snapshot is: , , ,or or , like and The length of the topology snapshot is: , , ,or or , like and The length of the topology snapshot is: , , like and The length of the topology snapshot is: , , like and The length of the topology snapshot is: , ; when , , hour: like The length of the topology snapshot is: , , like The length of the topology snapshot is: , , Within one orbital period: Indicates the length of the first possible topology snapshot; Indicates the length of the second possible topology snapshot; This indicates the first category that may occur under the third type of topology snapshot length; This indicates the second category that may occur under the third type of topology snapshot length; This indicates the third category that may occur under the third type of topology snapshot length; for Up satellite node The number of For natural numbers, The angle between the line connecting the CLR latitude point to the Earth's center and the intersection of the equatorial plane and the orbital plane. The phase difference between two consecutive satellites entering / leaving the CLR. for Phase difference between two adjacent satellites The corresponding time difference, For orbital period.

7. The method according to claim 1, characterized in that, The determination of the distribution pattern of inter-satellite topological snapshots in (5) includes the following implementation: definition The phase difference between adjacent satellites entering the CLR in the same orbit is ,when hour, ,when hour, ; Suppose that the topological snapshots within one orbital period form a sequence in sequence, according to The satellites are distributed with equal phase differences. This series is a cyclic series, and its cyclic characteristics are determined by the CLR range, satellite distribution, and distortion factor as follows: when , , or , , hour: like Then the cycle of the topological snapshot distribution is The minimum cycle period is The number of loops is or ; like In the cyclic section of the topological snapshot distribution, The minimum cycle period is The number of loops is or ; like Then the cycle of the topological snapshot distribution is The minimum cycle period is The number of loops is or ; remove , , or In all other cases: like The cyclic section of the topological snapshot distribution is The minimum cycle period is 1, and the number of cycles is 1. or ; like Then the cycle of the topological snapshot distribution is The minimum cycle period is 2, and the number of cycles is or ; Within one orbital period: Indicates the length of the first possible topology snapshot; Indicates the length of the second possible topology snapshot; This indicates the first category that may occur under the third type of topology snapshot length; This indicates the second category that may occur under the third type of topology snapshot length; This indicates the third category that may occur under the third type of topology snapshot length. for Up satellite node The number of For natural numbers, The angle between the line connecting the CLR latitude point to the Earth's center and the intersection of the equatorial plane and the orbital plane. The phase difference between two consecutive satellites entering / leaving the CLR. The time difference between two consecutive satellites entering / leaving the CLR. For orbital period.

8. The method according to claim 1, characterized in that, The process of converting the calculation results into inter-satellite topology sampling time points and corresponding topology snapshot lengths in step (6) includes the following implementation: 8a) Define the time of the first occurrence of topological dynamics within an orbital period as the start time. That is, the start time of the first topological snapshot of the minimum cycle node under the topological snapshot distribution law; 8b) Obtain all inter-satellite topology sampling time points within one orbital period based on the distribution pattern of topology snapshots. And the corresponding topology snapshot length, time point and The interval between them is the length of the first topological snapshot of the smallest cycle node under the topological snapshot distribution law, in the orbital period. And so on.

9. An inter-satellite topology sampling device for distorted topological constellations, characterized in that, include: The parameter input module is used to input constellation configuration parameters to the user's satellites; The heterogeneous link establishment determination module is used to determine the heterogeneous link establishment mode of all satellite nodes under different torsion factors; The satellite distribution determination module is used to determine the distribution pattern of all satellite nodes on the virtual plane under different constellation configurations; Region determination module: used to determine whether satellite crossing events in critical latitude regions are synchronous, and whether the crossing of critical latitude regions by the first and last orbit satellites will cause topological dynamics; Topology dynamic characteristics quantification module: used to automatically calculate based on the results of the heterogeneous link establishment module, satellite distribution determination module, and region judgment module. A quantitative indicator of the topological dynamics of constellation warp topology over an orbital period; Inter-satellite topology sampling output module: This module converts the calculation results from the topology dynamic characteristics quantization module into inter-satellite topology sampling time points and corresponding topology snapshot lengths, and outputs them in a preset format.

10. The method according to claim 7, characterized in that, The topology dynamic characteristic quantization module includes: The Topology Snapshot Count submodule is used to calculate the number of topology snapshots of a satellite network within one orbital period. The Topology Snapshot Length submodule is used to calculate the topology snapshot length of a satellite network over one orbital period.

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