Topological design method and system for guaranteeing robustness of satellite network capacity, electronic equipment and storage medium

Abstract

This invention discloses a topology design method, system, electronic device, and storage medium to ensure the capacity robustness of satellite networks. It primarily addresses the shortcomings of existing technologies that do not fully consider the impact of network topology on capacity robustness and the difficulty in efficiently selecting suitable topologies as the network scales up. The implementation scheme involves: obtaining the parameters of the satellite network to be designed and the failure probability of inter-satellite links; setting a connection factor based on the inter-satellite link failure probability and determining the offset of each orbital plane that satisfies the connection factor constraint; establishing connection rules for intra-orbit links within the orbital plane based on the inter-satellite link distance; and establishing connection rules for inter-orbit links between orbital planes based on the inter-satellite link distance and offset, thereby obtaining a satellite network topology that meets the capacity robustness requirements. By introducing link failure probability constraints during the topology design stage, this invention effectively enhances the capacity of bottleneck links and ensures the network capacity robustness of the satellite network in the event of link failure, and can be used for satellite network topology design.

Description

Technical Field

[0001] This invention belongs to the field of satellite communication technology, and in particular relates to a topology design method and system for ensuring the robustness of satellite network capacity. It can be used to ensure the capacity of satellite networks under fault scenarios, improve the robustness of satellite network capacity, and provide guidance for the design of low-Earth orbit satellite network topologies. Background Technology

[0002] With large-scale LEO constellations becoming mainstream, multi-hop relay between satellites has become a key factor affecting satellite network capacity. However, space environment effects, including space debris, light radiation, and node and link failures caused by high-energy particles, can significantly reduce satellite network capacity. This is especially true when failures occur on links that constitute network bottlenecks, where end-to-end latency increases due to changes in transmission paths, severely impacting satellite network capacity. As the scale of satellite networks increases, the number of satellites that can establish inter-orbit links with each satellite also increases, leading to an exponential increase in the number of satellite network topologies. Therefore, how to quickly design topologies that ensure robustness in guaranteeing satellite network capacity is a pressing issue that needs to be addressed.

[0003] Patent application number 202311301320.6 discloses a method for designing low-Earth orbit (LEO) satellite networks. Based on preset connection rules for establishing inter-satellite links in the Walker constellation, it calculates the capacity of a single satellite and the total capacity of the satellite network according to the link budget equation. The ratio of the total network capacity to the total cost of building the network is used as the first optimization objective to optimize the satellite network, resulting in the LEO communication satellite network. However, because this method is based on preset connection rules, it cannot calculate the network capacity under different connection rules. Furthermore, since this method does not consider the impact of node and link failures on the satellite network, it cannot assess the robustness of the network capacity.

[0004] Patent application number 202510457349.6 discloses a fault analysis method for low-Earth orbit (LEO) satellites. This method collects data on the impact of space debris on LEO satellite signal transmission, analyzes this data, compares it with data related to inter-satellite link network load balancing, and issues commands to repair the LEO satellite links based on the comparison results. However, this method only reduces interference by adjusting the satellite's attitude, neglecting the changes in inter-satellite link distances caused by node and link failures. This could lead to increased end-to-end latency and affect network capacity. Summary of the Invention

[0005] The purpose of this invention is to propose a topology design method, system, electronic device, and storage medium to ensure the robustness of satellite network capacity, thereby addressing the shortcomings of the prior art that does not consider the impact of different topologies on network capacity robustness and makes it difficult to select a suitable topology as the network scale increases, thus improving the robustness of satellite network capacity.

[0006] The technical approach to achieving the objective of this invention is as follows: In the satellite network topology design stage, the robustness of the satellite network capacity is improved by increasing the capacity of bottleneck links in the satellite network; by introducing inter-satellite link distance constraints, the search space of candidate topologies is compressed, the problem of exponential growth in the number of topologies caused by the increase in network size is suppressed, and the efficiency of topology selection is improved.

[0007] Based on the above ideas, the technical solution of the present invention includes:

[0008] 1. A topology design method for ensuring the robustness of satellite network capacity, characterized by establishing connection relationships between satellite nodes, comprising:

[0009] (1) Obtain the parameters of the satellite network to be designed and the failure probability of the inter-satellite links, including: satellite network scale Number of satellite network orbital planes Number of satellites on each plane , No. The first orbital plane satellite Phase factor Satellite network orbital altitude Satellite network orbital inclination Probability of inter-satellite link failure Probability of failure of the same track link ,in , ;

[0010] (2) Set the connection rules for co-orbit links and inter-orbit links in the satellite network:

[0011] The aforementioned co-track link connection rules are based on satellites. Adjacent satellites in the same orbital plane Establish a co-track link between them, where express right Perform the remainder operation;

[0012] The rules for connecting the different tracks are set as follows:

[0013] Set the connection factor based on the acquired parameters. ,in, This represents the probability of failure of the off-track link. This represents the probability of failure of a link on the same track. For when When the minimum value is obtained value, For satellite The number of satellites reachable only via inter-orbit links using the minimum hop count routing method;

[0014] In satellite Satellites in the adjacent orbit to the right Establish heterogeneous links between them, among which For the first The offsets corresponding to each orbital plane satisfy the connectivity factor. constraints .

[0015] Furthermore, in step (2), the connection factor is set according to the acquired parameters. Its implementation includes:

[0016] (2e) Based on the number of network orbital planes Number of satellites on each plane Set the initial number of satellites ,satellite The source node;

[0017] (2f) Use the minimum hop count routing method for satellites in the network The process is repeated sequentially, when the satellites and When the shortest path between them is reached only through a different track link, then let Repeat the above traversal process until all satellites in the network have been traversed, and obtain the number of satellites. ,in , ;

[0018] (2g) Based on the number of satellites Probability of failure of off-track links and the probability of failure of the same track link Calculate the connection factor .

[0019] Furthermore, in the satellite mentioned in (2) Satellites in the adjacent orbit to the right Establishing inter-track links between them, the implementation of which includes:

[0020] (2h) Based on the number of satellite network orbital planes Satellite network orbital inclination Calculate the included angle between adjacent track planes. The angle between the line of intersection with the adjacent orbital plane and the Earth's axis of rotation ;

[0021] (2i) Based on the scale of the satellite network Phase factor Satellite network orbital altitude Earth's radius Angle between adjacent track planes The angle between the line of intersection with the adjacent orbital plane and the Earth's axis of rotation Calculate the distance between two satellites ;

[0022] (2j) Based on distance To determine whether it is less than [a certain value] within a complete operational cycle of the two satellites. Permanent line-of-sight visibility conditions:

[0023] if Then proceed to step (4c);

[0024] Otherwise, it will be impossible to establish a co-track link and reacquire the required satellite network parameters;

[0025] (2k) Based on distance Calculate the signal-to-noise ratio at the receiver. ;

[0026] (2l) If Then the satellite and There are inter-satellite links, which establish heterogeneous links between two satellites, i.e., bidirectional data transmission paths between orbital planes.

[0027] 2. A topology design system for ensuring the robustness of satellite network capacity, characterized in that it comprises:

[0028] The network parameter acquisition module is used to acquire the parameters of the satellite network to be designed and the failure probability of the inter-satellite links;

[0029] The connection rule setting module is used to set the connection rules of the satellite network based on the parameters obtained by the network parameter acquisition module.

[0030] The topology design module is used to establish inter-satellite links between satellite nodes based on the connection rules determined by the connection rule setting module, thereby completing the design of the satellite network topology.

[0031] 3. An electronic 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 program, it implements the topology design method for a satellite network as described in any one of claims 1 to 5.

[0032] 4. A non-transitory computer-readable storage medium, characterized in that the non-transitory computer-readable storage medium stores computer instructions, the computer instructions being used to cause the computer to execute the topology design method of the satellite network according to any one of claims 1 to 5.

[0033] Compared with the prior art, the present invention has the following advantages:

[0034] In the topology design phase, this invention, based on the failure probability of inter-satellite links, adjusts the connection factor... The configuration and compression of the search space for candidate network topologies can suppress the exponential growth in the number of candidate topologies caused by the increase in network size, while enhancing the capacity of bottleneck links in the network topology. This solves the shortcomings of existing technologies that do not fully consider the impact of network topology on capacity robustness and are difficult to efficiently select suitable topologies as the network size expands. It improves the robustness of satellite network capacity and can ensure network capacity requirements even when the satellite network fails. Attached Figure Description

[0035] Figure 1 This is a flowchart illustrating the implementation of the topology design method for ensuring the robustness of satellite network capacity according to the present invention.

[0036] Figure 2 This is a schematic diagram of the satellite network in the method of the present invention;

[0037] Figure 3 This is the method of the present invention that determines the relationship with the satellite. A diagram illustrating a satellite capable of establishing inter-satellite links;

[0038] Figure 4 This is the method of the present invention for determining each satellite Candidate set of off-track link offsets Schematic diagram;

[0039] Figure 5 This is a block diagram of the topology design system for ensuring the robustness of satellite network capacity in this invention;

[0040] Figure 6 This is a schematic diagram of the electronic device in this invention;

[0041] Figure 7 This is a schematic diagram of the satellite network capacity simulation results in this invention. Detailed Implementation

[0042] The specific embodiments and effects of the present invention will be further described in detail below with reference to the accompanying drawings.

[0043] Example 1: Topology design method for ensuring the robustness of satellite network capacity.

[0044] Reference Figure 1 The implementation steps of this example include the following:

[0045] Step 1. Obtain the parameters of the satellite network to be designed and the failure probability of the inter-satellite links.

[0046] like Figure 2 As shown, the satellite network is a Walker constellation generated by STK, with Seed as the seed satellite, an orbital altitude of 550km, an orbital inclination of 60°, a network size of 72, 6 orbital planes, and a phase difference of 1 between adjacent orbital planes.

[0047] Obtain the parameters of the satellite network to be designed and the failure probability of inter-satellite links, including: satellite network scale. Number of satellite network orbital planes Number of satellites on each plane , No. The first orbital plane satellite Phase factor Satellite network orbital altitude Satellite network orbital inclination Probability of inter-satellite link failure Probability of failure of the same track link ,in , .

[0048] In this embodiment, the satellite network scale is set. Number of satellite network orbital planes Number of satellites on each plane , No. The first orbital plane satellite Phase factor Satellite network orbital altitude Satellite network orbital inclination Probability of inter-satellite link failure in different orbits Probability of failure of the same track link ,in , .

[0049] Step 2. Configure the co-orbit link connection rules for the satellite network.

[0050] The aforementioned co-track link is on the satellite satellites in the same orbital plane and adjacent satellites Establish a bidirectional data transmission path between the orbital planes, wherein express right The connection rules for this co-track link are set to include the remainder, as determined by the remainder operation:

[0051] (2.1) Based on the number of satellites on each plane Satellite network orbital altitude and Earth's radius Calculate the distance between adjacent satellites in the same orbital plane: ;

[0052] (2.2) Based on the distance between adjacent satellites in the same orbital plane Determine the connection rules for the same-track link:

[0053] (2.2.1) Based on orbital altitude and Earth's radius Set permanent line-of-sight visibility conditions: , the distance Compare with this permanent line-of-sight condition:

[0054] if If so, proceed to step (2.2.2).

[0055] Otherwise, it will be impossible to establish a co-track link and reacquire the required satellite network parameters;

[0056] (2.2.2) Based on distance Calculate the signal-to-noise ratio at the receiver:

[0057] ,

[0058] in, For the power of the satellite transmitter, For transmit gain, For receiving gain, For noise power spectral density, At the speed of light, The frequency of the satellite transmitter;

[0059] (2.2.3) Based on the signal-to-noise ratio at the receiving end Determine whether it is greater than the decision threshold. :

[0060] if Then the satellite and There are inter-satellite links, which establish co-orbit links between two satellites, i.e., bidirectional data transmission paths within the orbital plane;

[0061] Otherwise, it will be impossible to establish a co-track link and reacquire the required satellite network parameters.

[0062] In this embodiment, the number of satellites on each plane Satellite network orbital altitude Earth's radius Satellite transmitter power transmit gain Receiver gain Noise power spectral density speed of light The frequency of satellite transmitters ,like Figure 3 As shown, the distance between adjacent satellites in the same orbital plane Meeting the permanent line-of-sight visibility condition, the signal-to-noise ratio at the receiver is [value missing]. This allows for the establishment of bidirectional data transmission paths between orbital planes.

[0063] Step 3: Configure the connection rules for inter-orbit links in the satellite network.

[0064] The aforementioned inter-orbit link is located on a satellite. Satellites in the adjacent orbit to the right Establish a bidirectional data transmission path between the orbital planes, wherein For the first The offsets corresponding to each orbital plane satisfy the connectivity factor. constraints The connection rules for this inter-track link include:

[0065] (3.1) Set the connection factor based on the acquired parameters. :

[0066] (3.1.1) Based on the number of network orbital planes Number of satellites on each plane Set the initial number of satellites Set up satellite As the source node,

[0067] (3.1.2) The minimum hop count routing method is used to route satellites in the network. The process is repeated sequentially, when the satellites and When the shortest path between them is reached only through a different track link, then let ,in , ;

[0068] (3.1.3) Repeat step (3.1.2) above until all satellites in the network have been traversed and the number of satellites is obtained. ;

[0069] (3.1.4) Based on the number of satellites Probability of failure of off-track links and the probability of failure of the same track link Calculate the connection factor :

[0070] ,

[0071] in, For when When the minimum value is obtained value.

[0072] (3.2) Based on the connection factor Determine the connection rules for the inter-track links:

[0073] (3.2.1) Initialize the satellite Candidate set of off-track link offsets: ;

[0074] (3.2.2) For the adjacent track plane on the right satellites on When the satellite and When there are different track links, the offset will be... Store in the candidate set: ,in, ;

[0075] (3.2.3) Repeat step (3.2.2) until on the track plane All satellite nodes have been traversed, and the satellites have been obtained. Candidate set of off-track link offsets ;

[0076] (3.2.4) From the candidate set In the middle, select the connection factor that satisfies Constraints: The offset is used as the first Final connection offset of each orbital plane .

[0077] (3.2.5) Based on the number of satellite network orbital planes Satellite network orbital inclination Calculate the included angle between adjacent track planes. The angle between the line of intersection with the adjacent orbital plane and the Earth's axis of rotation :

[0078] ,

[0079] ;

[0080] (3.2.6) Based on the scale of the satellite network Phase factor Satellite network orbital altitude Earth's radius Angle between adjacent track planes The angle between the line of intersection with the adjacent orbital plane and the Earth's axis of rotation Calculate the distance between two satellites :

[0081] ;

[0082] (3.2.7) Based on the distance between the two satellites Determine the connection rules for the inter-track links:

[0083] (3.2.7a) Based on orbital altitude and Earth's radius Set permanent line-of-sight visibility conditions: , the distance Compare with this permanent line-of-sight condition:

[0084] if If so, proceed to step (3.2.7b).

[0085] Otherwise, it will be impossible to establish a co-track link and reacquire the required satellite network parameters;

[0086] (3.2.7b) Based on distance Calculate the signal-to-noise ratio at the receiver:

[0087] ,

[0088] in, For the power of the satellite transmitter, For transmit gain, For receiving gain, For noise power spectral density, At the speed of light, The frequency of the satellite transmitter;

[0089] (3.2.7c) Based on the signal-to-noise ratio at the receiving end Determine whether it is greater than the decision threshold. :

[0090] if Then the satellite and There are inter-satellite links, i.e., bidirectional data transmission paths between orbital planes;

[0091] Otherwise, it will be impossible to establish a cross-orbit link and reacquire the required satellite network parameters.

[0092] In this embodiment, the probability of cross-track link failure is... Probability of failure of the same track link ,satellite For the source node; when , Get the minimum value, set This example determines each satellite. Candidate set of off-track link offsets As by Figure 4 As shown.

[0093] from Figure 4 It can be seen that the satellite Adjacent track surface on the right satellites on , , There are heterogeneous links between them. Based on the candidate offset set, Satisfying the connection factor The constraints are selected in this example. , , , , , This serves as the final offset for each orbital plane.

[0094] Satellite network scale Number of track planes Number of satellites on each plane Satellite network orbital altitude Satellite network orbital inclination 60°, Earth's radius Satellite transmitter power transmit gain Receiver gain Noise power spectral density speed of light The frequency of satellite transmitters Distance between adjacent orbital plane satellites Meeting the permanent line-of-sight visibility condition, the signal-to-noise ratio at the receiver is [value missing]. In satellite Satellites in the adjacent orbit to the right A bidirectional data transmission path is established between the orbital planes, thus completing the topology design of the satellite network.

[0095] It should be noted that the step numbers in the above examples are only for the purpose of clearly describing the present invention and facilitating understanding, and their order is not limited.

[0096] Example 2: Topology design system for ensuring the robustness of satellite network capacity.

[0097] Reference Figure 5 This example includes: a network parameter acquisition module 1, a connection rule setting module 2, and a topology design module 3. The connection rule setting module 2 includes a same-track link connection rule submodule 21, a connection factor calculation submodule 22, and a different-track link connection rule submodule 23. The topology design module 3 includes a same-track link establishment submodule 31 and a different-track link establishment submodule 32.

[0098] The working principle of the entire system is as follows:

[0099] The network parameter acquisition module 1 is used to acquire the satellite network parameters to be designed and the failure probability of inter-satellite links, including: satellite network size, number of satellite network orbital planes, number of satellites in each plane, phase factor, satellite network orbital altitude, satellite network orbital inclination, failure probability of cross-orbit links and failure probability of same-orbit links, and transmit the above parameters to the connection rule setting module 2 respectively.

[0100] The connection rule setting module 2 is used to determine the connection rules of the satellite network based on the parameters transmitted by the network parameter acquisition module 1. Specifically, the same-orbit link connection rule submodule 21 determines the same-orbit link connection rules between adjacent satellites in the same orbital plane based on the number of satellites on each plane and the satellite network orbital altitude, and transmits these rules to the topology design module 3. The connection factor calculation submodule 22 determines the connection factor based on the number of orbital planes, the number of satellites on each plane, the probability of failure of different orbital links, and the probability of failure of the same-orbit link, and transmits this factor to the different-orbit link connection rule submodule 23. The different-orbit link connection rule submodule 23 generates a candidate set of different-orbit link offsets for each satellite based on the transmitted satellite network size, phase factor, satellite network orbital altitude, satellite network orbital inclination, and connection factor. It then determines the orbital plane offsets that satisfy the connection factor constraints, obtains the different-orbit link connection rules between each satellite and its corresponding satellite in the adjacent orbit to its right, and transmits these rules to the topology design module 3.

[0101] The topology design module 3 is used to establish connection rules according to the connection rule setting module 2. Specifically, the same-track link establishment submodule 31 establishes same-track links between adjacent satellite nodes in the orbital plane according to the same-track link connection rules transmitted by the connection rule submodule 21, forming the topology structure in the satellite network plane. The different-track link establishment submodule 32 establishes different-track links between corresponding satellite nodes in the orbital plane according to the different-track link connection rules transmitted by the different-track link connection rule submodule 23 and the offset of each orbital plane, forming the topology structure between satellite network planes, and finally completes the topology design to ensure the robustness of satellite network capacity.

[0102] 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 a program instruction product. 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.

[0103] 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.

[0104] Example 3: Electronic equipment for topology design to ensure robustness of satellite network capacity.

[0105] Reference Figure 6 This embodiment provides a specific hardware architecture for an electronic device, which consists of a processor 601, a memory 602, an input / output interface 603, and a communication interface 604. The processor 601, memory 602, input / output interface 603, and communication interface 604 communicate via an internal bus to achieve data interaction between the components.

[0106] The processor 601 can be implemented in various forms such as general-purpose central processing unit (CPU), digital signal processor (DSP), application-specific integrated circuit (ASIC), or single-chip and multi-chip integrated circuits. It is responsible for scheduling and running corresponding program instructions to complete the entire operation process of the robust topology design method for ensuring satellite network capacity.

[0107] The memory 602 can be implemented in one of the following forms: read-only memory (ROM), random access memory (RAM), solid-state storage device, or dynamic storage device, and is used to carry the operating system and various functional programs. When the topology design method of the present invention is deployed in the form of software or firmware, the corresponding program code resides in the memory 602 and is read and called by the processor 601 during runtime.

[0108] The input / output interface 603 is integrated into the device as a built-in component, and can also be connected to the device through an external expansion interface to provide corresponding functions. It supports the input of required data such as satellite network configuration parameters and inter-satellite link failure probability through peripherals such as keyboard and touch panel.

[0109] The communication interface 604 constitutes a unified data transmission channel between various functional components inside the device, and undertakes the task of information transmission between the processor 601, the memory 602 and the input / output interface 603.

[0110] It should be noted that the above device description only uses processor 601, memory 602, input / output interface 603, and communication interface 604 as examples. However, in specific implementations, the device may also include other components necessary for normal operation. Furthermore, those skilled in the art will understand that the above device may only include the components necessary for implementing the embodiments of this specification, and does not necessarily include all the components shown in the figures.

[0111] The non-transitory computer-readable storage medium provided in this embodiment of the invention stores a plurality of instructions that can be loaded by a processor to execute steps in any of the topology design methods for ensuring the capacity robustness of satellite networks provided in this embodiment of the invention.

[0112] The non-transitory computer-readable medium of this embodiment includes both permanent and non-permanent media for storing information. The information may be computer-readable instructions, data structures, program modules, or other data. This computer storage medium includes, but is not limited to: phase-change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other non-transfer medium for storing information accessible by a computing device.

[0113] The effects of this invention can be further illustrated by the following simulation results:

[0114] I. Simulation Conditions

[0115] In the Opnet simulation software, satellite networks corresponding to the network topology of this invention and the mainstream 2D-Torus topology were established respectively. The simulation duration was set to 5 minutes, the failure probability of the same orbit link was 10%, the failure probability of the different orbit link was 10%, and the number of simulations was 100.

[0116] The simulation uses network capacity as the core evaluation index, which is the total amount of data that all receiving nodes in the entire satellite network can receive within the statistical period, divided by the simulation duration.

[0117] II. Simulation Content and Results

[0118] Under the above simulation conditions, the network capacity corresponding to the robust satellite network topology guaranteed by this invention and the existing 2D-Torus topology was statistically analyzed 100 times. Probability density curves of network capacity for different topologies were plotted, and the results are as follows: Figure 7 As shown.

[0119] Depend on Figure 7 As can be seen, the probability density curve of the network capacity of the proposed robust topology for satellite network capacity is shifted to the right, with the peak occurring around a network capacity of 45 and a distribution range of approximately 35 to 60. In contrast, the peak of the probability density curve of the existing 2D-Torus topology occurs around a network capacity of 32, with a distribution range of approximately 20 to 40, indicating that its overall network capacity level is significantly lower. Comparing the two, under the same link failure probability, the average network capacity of the proposed robust topology is approximately 40% higher than that of the 2D-Torus topology. This demonstrates that the proposed topology can maintain a high network capacity level even when a link fails, effectively verifying the significant advantages of this invention in ensuring the robustness of satellite network capacity.

[0120] The above descriptions are merely a few specific examples of the present invention and do not constitute a limitation thereof. Obviously, those skilled in the art, after understanding the content and principles of the present invention, can make various modifications and changes in form and detail without departing from the principles and structure of the present invention. For example, the total number of constellations set in this example... Number of orbital planes track inclination 60°, track height Phase factor Probability of failure of the same track link probability of failure of off-track link In addition to satellite network parameters and link failure probabilities, satellite network and link failure probabilities of other constellation parameters under this configuration can also be used, for example... , , 53° , , , For example, besides the rule of establishing links on the same track first and then establishing links on different tracks as in this example, the rule of establishing links on different tracks first and then establishing links on the same track can also be used. However, these modifications and changes based on the ideas of this invention are still within the scope of protection of the claims of this invention.

Claims

1. A robust topology design method for ensuring satellite network capacity, characterized by establishing connection relationships between satellite nodes, wherein... include: (1) Obtain the parameters of the satellite network to be designed and the failure probability of the inter-satellite links, including: satellite network scale Number of satellite network orbital planes Number of satellites on each plane , No. The first orbital plane satellite Phase factor Satellite network orbital altitude Satellite network orbital inclination Probability of inter-satellite link failure Probability of failure of the same track link ,in , ; (2) Set the connection rules for co-orbit links and inter-orbit links in the satellite network: The aforementioned co-track link connection rules are based on satellites. Adjacent satellites in the same orbital plane Establish a co-track link between them, where express right Perform the remainder operation; The rules for connecting the different tracks are set as follows: Set the connection factor based on the acquired parameters. ,in, This represents the probability of failure of the off-track link. This represents the probability of failure of a link on the same track. For when When the minimum value is obtained value, For satellite The number of satellites reachable only via inter-orbit links using the minimum hop count routing method; In satellite Satellites in the adjacent orbit to the right Establish heterogeneous links between them, among which For the first The offsets corresponding to each orbital plane satisfy the connectivity factor. constraints .

2. The method according to claim 1, characterized in that, In the satellite mentioned in (2) Adjacent satellites in the same orbital plane Establishing a co-track link between them, the implementation of which includes: (2a) Based on the number of satellites on each plane Satellite network orbital altitude and Earth's radius Calculate the distance between adjacent satellites in the same orbital plane: ; (2b) Based on distance To determine whether it is less than [a certain value] within one complete operational cycle of the two satellites. Permanent line-of-sight visibility conditions: if If so, proceed to step (2c); Otherwise, it will be impossible to establish a co-track link and reacquire the required satellite network parameters; (2c) Based on distance Calculate the signal-to-noise ratio at the receiver: ， in, For the power of the satellite transmitter, For transmit gain, For receiving gain, For noise power spectral density, At the speed of light, For the frequency of the satellite transmitter; (2d) Based on the signal-to-noise ratio at the receiving end Determine whether it is greater than the decision threshold. : if Then the satellite and There are inter-satellite links, which establish co-orbit links between two satellites, i.e., bidirectional data transmission paths within the orbital plane; Otherwise, it will be impossible to establish a co-track link and reacquire the required satellite network parameters.

3. The method according to claim 1, characterized in that, In step (2), the connection factor is set according to the acquired parameters. Its implementation includes: (2e) Based on the number of network orbital planes Number of satellites on each plane Set the initial number of satellites ,satellite The source node; (2f) Use the minimum hop count routing method for satellites in the network The process is repeated sequentially, when the satellites and When the shortest path between them is reached only through a different track link, then let Repeat the above traversal process until all satellites in the network have been traversed, and obtain the number of satellites. ,in , ; (2g) Based on the number of satellites Probability of failure of off-track links and the probability of failure of the same track link Set the connection factor : ， in, For when When the minimum value is obtained value.

4. The method according to claim 1, characterized in that, In the satellite mentioned in (2) Satellites in the adjacent orbit to the right Establishing inter-track links between them, the implementation of which includes: (2h) Based on the number of satellite network orbital planes Satellite network orbital inclination Calculate the included angle between adjacent track planes. The angle between the line of intersection with the adjacent orbital plane and the Earth's axis of rotation : ； ； (2i) Based on the scale of the satellite network Phase factor Satellite network orbital altitude Earth's radius Angle between adjacent track planes The angle between the line of intersection with the adjacent orbital plane and the Earth's axis of rotation Calculate the distance between two satellites : ； (2j) Based on distance To determine whether it is less than [a certain value] within one complete operational cycle of the two satellites. Permanent line-of-sight visibility conditions: if Then proceed to step (4c); Otherwise, it will be impossible to establish a co-track link and reacquire the required satellite network parameters; (2k) Based on distance Calculate the signal-to-noise ratio at the receiver: ， in, For the power of the satellite transmitter, For transmit gain, For receiving gain, For noise power spectral density, At the speed of light, For the frequency of the satellite transmitter; (2l) Based on the signal-to-noise ratio at the receiving end Determine whether it is greater than the decision threshold. : if Then the satellite and There are inter-satellite links, which establish a cross-orbit link between two satellites, i.e., a two-way data transmission path between orbital planes; Otherwise, it will be impossible to establish a cross-orbit link and reacquire the required satellite network parameters.

5. The method according to claim 1, characterized in that, The offset mentioned in (2) is implemented as follows: (2m) Initialize the satellite Candidate set of off-track link offsets ; (2n) For the adjacent orbital plane on the right Satellites on When the satellite and When there are different track links, the offset will be... Store in the candidate set: ,in, ; (2o) Repeat step (2b) until on the orbital plane All satellite nodes have been traversed, and the satellites have been obtained. Candidate set of off-track link offsets ; (2p) From the candidate set In the middle, select the connection factor that satisfies Constraints: The offset is used as the first Final connection offset of each orbital plane .

6. A robust topology design system for ensuring satellite network capacity, characterized in that, include: The network parameter acquisition module is used to acquire the parameters of the satellite network to be designed and the failure probability of the inter-satellite links; The connection rule setting module is used to set the connection rules of the satellite network based on the parameters obtained by the network parameter acquisition module. The topology design module is used to establish inter-satellite links between satellite nodes based on the connection rules determined by the connection rule setting module, thereby completing the design of the satellite network topology.

7. The system according to claim 6, characterized in that, The connection rule setting module includes: The co-track link connection rules submodule is used for satellite Adjacent satellites in the same orbital plane Establish connection rules for bidirectional transmission paths between them; The connectivity factor calculation submodule is used to determine the satellite network connectivity factor. ; The inter-orbit link connection rules submodule is used to generate a candidate set of inter-orbit link offsets for each satellite. And determine the final connection offset of each orbital plane from it. In satellite Satellites in the adjacent orbit to the right Establish bidirectional transmission path connection rules between them.

8. The system according to claim 6, characterized in that, The topology design module includes: The co-orbit link establishment submodule is used to establish co-orbit links between satellite nodes in the orbital plane according to the co-orbit link connection rules determined by the connection rule setting module, forming a topology in the satellite network plane; The heterogeneous link establishment submodule is used to establish heterogeneous links between satellite nodes in the orbital plane according to the heterogeneous link connection rules determined by the connection rule setting module, thereby forming a topology between satellite network planes.

9. An electronic 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 program, it implements the topology design method for the satellite network as described in any one of claims 1 to 5.

10. A non-transitory computer-readable storage medium, characterized in that, The non-transitory computer-readable storage medium stores computer instructions for causing the computer to execute the topology design method of the satellite network according to any one of claims 1 to 5.

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