A method for constructing a mega-constellation network cross-track link topology

Abstract

The application discloses a method for constructing a cross-orbit chain topology of a mega-constellation network, and the method comprises the following steps: S1, acquiring the number of uniformly distributed orbit planes in the mega-constellation network P and the number of uniformly distributed satellites in each orbit plane S ; S2, each satellite on each orbit plane establishes an inter-orbit satellite interlink with the satellites adjacent to the orbit plane, meanwhile, each satellite on each orbit plane establishes an inter-orbit satellite interlink with the corresponding satellite on the corresponding orbit plane by selecting at least two cross numbers to form a cross-orbit chain topology of the mega-constellation network, and the greatest common divisor of all cross numbers is 1. The cross-orbit chain topology of the application makes the inter-orbit satellite interlink span the satellites of several orbit planes, under the premise of ensuring global connectivity, significantly improves the long-distance transmission efficiency, breaks through the scale bottleneck of a single-layer constellation, reduces the dependence on the ground gateway station, and makes the mega-constellation network become a high-performance infrastructure complementary to the ground network.

Description

Technical Field

[0001] This application relates to the field of constellation network communication technology, and in particular, to a method for constructing a cross-track link topology for a giant constellation network. Background Technology

[0002] Mega-constellation systems in low Earth orbit (LEO) (such as SpaceX's Starlink project) have experienced explosive growth in recent years. By deploying multiple inter-satellite link (ISL) terminals on satellites, information can be relayed between satellites, significantly reducing reliance on ground gateway stations. These mega-constellations with ISLs are gradually replacing those without, becoming the mainstream direction for future development. The constellation network topology is the spatial geometry of a mega-constellation in LEO formed by interconnecting satellite nodes via ISLs, and its design directly determines the overall performance of the network.

[0003] The closest existing practical solution is the Grid-Mesh topology, especially the Grid 4-ISL topology. This type of topology requires each satellite to establish inter-satellite links with its adjacent satellites in the same orbital plane and with corresponding satellites in adjacent orbital planes on either side, forming a regular grid structure. The Grid 4-ISL topology has become the mainstream choice for research and application due to its ability to balance networking cost and connectivity. Its connection method is as follows... Figure 1 As shown, satellite nodes are interconnected through fixed rules to ensure global network connectivity.

[0004] The main drawbacks of the Grid4-ISL topology are twofold: First, in long-distance transmission scenarios, data packets need to be forwarded hop-by-hop along the grid, resulting in a high total number of hops and accumulated propagation and forwarding delays, leading to low utilization of inter-satellite link resources. Second, as the scale of a single-layer constellation expands, the increased satellite density exacerbates the hop count increase, forcing the adoption of multi-layer constellations. However, cross-layer links are unstable and require reliance on terrestrial networks for relaying, weakening the advantages of space-based independent networking. These issues limit the potential of mega-constellations as independent space information infrastructures to achieve wide coverage, low latency, and high reliability. Summary of the Invention

[0005] This application provides a method for constructing cross-orbit link topology for mega-constellation networks, which solves the technical problems of low transmission efficiency and instability of the Grid4-ISL topology in existing low-orbit mega-constellation systems when expanding the scale of a single-layer constellation, requiring reliance on ground networks for relay, thus weakening the advantages of space-based independent networking.

[0006] This application is achieved through the following solution: A method for constructing cross-orbit link topology for a mega-constellation network, applied to a mega-constellation network deploying satellites according to the Walker Delta constellation configuration, includes the following steps: S1. Obtain the number of uniformly distributed orbital planes in a giant constellation network. P and the number of satellites evenly distributed in each orbital plane S ; S2. Each satellite in each orbital plane establishes an inter-satellite link with its adjacent satellites in the same orbital plane. At the same time, each satellite in each orbital plane establishes an inter-satellite link with its corresponding satellite in the corresponding orbital plane by selecting at least two different span numbers to form a giant constellation network cross-orbit link topology. Here, the span number represents the number of orbital planes crossed by a single inter-satellite link, and at least two span numbers satisfy the condition that the greatest common divisor of all span numbers is 1.

[0007] Furthermore, the process of establishing inter-satellite links between each satellite on each orbital plane and corresponding satellites on the corresponding orbital plane by selecting at least two different cross-link numbers to form a giant constellation network cross-orbit link topology also includes the following steps: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h =P's track surface is defined as the last track, and the gap formed by the first track and the last track being adjacent in spatial geometry is called the first-last track gap; When the phase factors of the giant constellation network F=0 At that time, inter-satellite links are established between satellites with the same in-plane number on the first and last orbits, so that the entire constellation also presents a ring connection in the direction of the different orbits.

[0008] Furthermore, the process of establishing inter-satellite links between each satellite on each orbital plane and corresponding satellites on the corresponding orbital plane by selecting at least two different cross-link numbers to form a giant constellation network cross-orbit link topology also includes the following steps: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h = P The track surface is defined as the end rail, and the gap formed by the first rail and the end rail being adjacent in spatial geometry is called the first-end rail gap. When the phase factors of the giant constellation network F≠0 At that time, the satellites on both sides of the first and last orbit gap establish inter-satellite links to maintain connectivity by correcting the sequence number difference and establishing links, so that the entire constellation also presents a ring connection in the direction of the different orbits. The corrected sequence number difference is the number of in-plane sequence number misalignment between the linked satellites on the first and last orbits.

[0009] Furthermore, the formula for calculating the corrected sequence number difference is: ; in, D To standardize the difference, D= mod( F , S ), NThe number of types of spans.

[0010] This application also provides a device for constructing a cross-orbit link topology for a mega-constellation network, applicable to mega-constellation networks deploying satellites according to the Walker Delta constellation configuration, including: The module for acquiring parameters of a giant constellation network is used to obtain the number of orbital planes that are uniformly distributed in a giant constellation network. P and the number of satellites evenly distributed in each orbital plane S ; The cross-orbit link topology construction module is used to establish inter-satellite links between each satellite in each orbital plane and its adjacent satellites in the same orbital plane. At the same time, each satellite in each orbital plane alternately establishes inter-satellite links with corresponding satellites in the corresponding orbital plane by selecting at least two types of span numbers to form a cross-orbit link topology structure of a giant constellation network. Here, the span number represents the number of orbital planes crossed by a single inter-satellite link, and at least two types of span numbers satisfy the condition that the greatest common divisor of all span numbers is 1.

[0011] Furthermore, the cross-track link building topology construction module is also used for: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h = P The track surface is defined as the end rail, and the gap formed by the first rail and the end rail being adjacent in spatial geometry is called the first-end rail gap. When the phase factors of the giant constellation network F=0 At that time, inter-satellite links are established between satellites with the same in-plane number on the first and last orbits, so that the entire constellation also presents a ring connection in the direction of the different orbits.

[0012] Furthermore, the process of establishing inter-satellite links between each satellite on each orbital plane and corresponding satellites on the corresponding orbital plane by selecting at least two different cross-link numbers to form a giant constellation network cross-orbit link topology also includes the following steps: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h = P The track surface is defined as the end rail, and the gap formed by the first rail and the end rail being adjacent in spatial geometry is called the first-end rail gap. When the phase factors of the giant constellation network F≠0 At that time, the satellites on both sides of the first and last orbit gap establish inter-satellite links to maintain connectivity by correcting the sequence number difference and establishing links, so that the entire constellation also presents a ring connection in the direction of the different orbits. The corrected sequence number difference is the number of in-plane sequence number misalignment between the linked satellites on the first and last orbits.

[0013] Furthermore, the formula for calculating the corrected sequence number difference is: ; in, D To standardize the difference, D= mod( F , S ), N The number of types of spans.

[0014] This application also provides an electronic device, which includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that the processor executes the computer program to implement the giant constellation network cross-track link topology construction method.

[0015] This application also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the aforementioned method for constructing cross-track link topology for a giant constellation network.

[0016] This application also provides a computer program product, including a computer program or computer-executable instructions, which, when executed by a processor, implement the aforementioned method for constructing cross-track link topology for a giant constellation network.

[0017] Compared with the prior art, this application has the following beneficial effects: Compared to the existing Grid4-ISL topology, the proposed method for constructing a giant constellation network cross-track link topology in this application exhibits multi-dimensional and systematic performance advantages. Firstly, in terms of transmission efficiency, this topology significantly reduces the average number of hops in long-distance communication through innovative multi-hop hybrid links. This directly reduces the burden on satellite node forwarding capabilities and inter-satellite link bandwidth resources, freeing up space for the network to carry more service traffic. Secondly, regarding network throughput, the optimized connection method effectively improves traffic distribution, enabling more satellites performing gateway functions to carry traffic from non-gateway satellites in a more balanced manner, thereby significantly increasing the maximum traffic of gateway stations and the overall network throughput. Furthermore, regarding the key indicator of communication latency, thanks to the highly geometrically efficient link design, the total length of some end-to-end paths is shortened, reducing the spatial propagation latency of signals. Simultaneously, the reduction in hop count directly reduces the queuing and processing latency of data packets at nodes along the route, making the latency performance of this application partially superior to or at least equivalent to the traditional Grid4-ISL topology in long-distance transmission scenarios. Finally, this application enhances the scalability of the system. Its design significantly improves the independent networking performance of a single-layer high-density constellation, thereby avoiding the introduction of complex and unstable multi-layer constellation architectures and their cross-layer links, reducing reliance on ground gateway stations for relay, and laying a solid foundation for building a more autonomous and robust space-based information network.

[0018] In addition to the purposes, features, and advantages described above, this application has other purposes, features, and advantages. A further detailed description of this application will be provided below with reference to the figures. Attached Figure Description

[0019] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0020] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort, wherein: Figure 1 This is a schematic diagram of the existing Grid 4-ISL topology; Figure 2 This is a flowchart illustrating the preferred embodiment of the method for constructing a cross-orbit link topology in a giant constellation network according to this application. Figure 3 This is a schematic diagram of the "2" cross-track link topology when the number of crosses is single (2). Figure 4 This is a schematic diagram of a "2-3" cross-track linking topology with a mix of 2 and 3 cross-tracks; Figure 5 This is a schematic diagram of satellite links at the beginning and end of the orbital gap in the Grid 4-ISL topology of constellation 1296,72,0 when the phase factor F=0. Figure 6 This is a schematic diagram of the satellite link at the first and last orbit gaps in the "2-3" cross-orbit link topology of the 1296,72,0 constellation when the phase factor F=0. Figure 7 This is a schematic diagram of satellite links at the beginning and end of the orbital gap in the Grid 4-ISL topology of constellation 1296, 72, 45 when the phase factor F=45. Figure 8 This is a schematic diagram of the satellite link at the first and last orbit gaps in the "2-3" cross-orbit link topology of constellation 1296, 72, 45 when the phase factor F=45. Figure 9 This is a schematic diagram illustrating the relationship between the average number of hops and the distance between users under different topologies; Figure 10 This is a schematic diagram illustrating the relationship between average latency and distance between users under different topologies; Figure 11 This is a diagram comparing the approximate maximum traffic of gateway stations under different topologies; Figure 12This is a schematic diagram of a module of a giant constellation network cross-track link establishment topology construction device according to a preferred embodiment of this application; Figure 13 This is a schematic block diagram of an electronic device according to a preferred embodiment of this application; Figure 14 This is a schematic diagram of the internal structure of a computer device according to a preferred embodiment of this application. Detailed Implementation

[0021] To better understand the technical solution of this application, a detailed description will be provided below in conjunction with the accompanying drawings and specific implementation methods.

[0022] It should be noted that the executing entity in this embodiment can be a computing service device with data processing, network communication, and program execution functions, such as a tablet computer, personal computer, or mobile phone, or a giant constellation network cross-track link establishment topology construction device capable of realizing the above functions. The following description uses a giant constellation network cross-track link establishment topology construction device as the executing entity to illustrate this embodiment and the subsequent embodiments.

[0023] like Figure 2 As shown, a preferred embodiment of this application provides a method for constructing a cross-orbit link topology for a mega-constellation network, applicable to a mega-constellation network deploying satellites in a Walker Delta constellation configuration, including the following steps: S1. Obtain the number of uniformly distributed orbital planes in a giant constellation network. P and the number of satellites evenly distributed in each orbital plane S ; S2. Each satellite in each orbital plane establishes an inter-satellite link with its adjacent satellites in the same orbital plane. At the same time, each satellite in each orbital plane establishes an inter-satellite link with its corresponding satellite in the corresponding orbital plane by selecting at least two different span numbers to form a giant constellation network cross-orbit link topology. Here, the span number represents the number of orbital planes crossed by a single inter-satellite link, and at least two span numbers satisfy the condition that the greatest common divisor of all span numbers is 1.

[0024] Currently, large low-Earth orbit constellations typically employ the Walker Delta constellation configuration. This configuration is a classic symmetrical satellite constellation configuration that achieves continuous global or regional coverage through a uniformly distributed orbital plane, an equal number of satellites, and a fixed phase difference. Commonly used... T , P , F Let's simply define a specific configuration of the Walker Delta constellation, where T The total number of satellites in the constellation. P This represents the number of orbital planes that are uniformly distributed along the equator. FThis is the phase factor, representing the relative positional relationship between satellites in adjacent orbits. Additionally, the number of satellites uniformly distributed within each orbital plane needs to be defined. S And there is a relationship: T=PS .

[0025] Satellites in a constellation are uniquely identified by a dual index: Sat( v , h ) indicates the first h One orbital plane ( h ∈[1, P The first v satellites ( v ∈[1, S ]),in h For the orbital plane number, v This refers to the in-plane index.

[0026] The network topology of a megacons is an abstract mapping of constellation entities at the logical level, representing a dynamic connection architecture composed of satellites as network nodes and ISLs (Integrated Space Networks). Once the constellation's configuration parameters are determined, the spatial positions and trajectories of the satellites are uniquely constrained; different network topologies, by defining the connection rules between nodes, form heterogeneous spatial graph structures. Here, a graph theory model is introduced to formalize the megacons network as a graph. G =( V , E ),in: V The set of all satellite network nodes (hereinafter referred to as "nodes"), and Sat( v , h The corresponding satellite network node is defined as: ( v , h ), and satisfy , E It is a set of edges for bidirectional ISL connections between nodes, the composition of which is determined by specific topology rules.

[0027] In the classic Grid 4-ISL topology, each satellite establishes fixed inter-satellite links with its adjacent satellites in the same orbital plane, and establishes inter-satellite links with corresponding satellites in the adjacent orbital planes on the left and right.

[0028] The cross-orbit link establishment topology proposed in this embodiment retains the same-orbit inter-satellite link rules as in the Grid 4-ISL topology, but reconstructs the inter-satellite link connection strategy for different orbits: defining the number of cross-orbit links. C k ( k= 1,2,…, N ) represents the number of orbital planes traversed by a single inter-satellite link, when C k When =1, the satellite establishes links with satellites in adjacent orbital planes; when Ck When the value is 2, the target for establishing the link is a satellite that is 2 orbital planes apart, and so on.

[0029] If a topology uses only a single span and C k ≠1, the network topology will be divided into C 1 isolated subnet (e.g.) Figure 3 This would disrupt the overall connectivity of the constellation network, therefore a multi-span mixed encoding strategy needs to be introduced: through N Number of species Alternating deployments, while satisfying constraints: This condition ensures that all satellite nodes are interconnected into a unified network (e.g., ...). Figure 3 Name this topology "". "Cross-track link topology (referred to as "Cross-track link topology")" (topology) Figure 4 The topology shown is the number of spans C 1 = 2 and C The "2-3" cross-track linking topology with 2=3 mixed coding demonstrates that this application proposes multiple cross-number mixed coding strategies to ensure that the topology can achieve global network connectivity and prevent network partitioning.

[0030] Compared to the existing Grid4-ISL topology, the proposed method for constructing a giant constellation network cross-track link topology in this embodiment exhibits multi-dimensional and systematic performance advantages. Firstly, in terms of transmission efficiency, this topology significantly reduces the average number of hops in long-distance communication through an innovative multi-span hybrid link architecture. This directly reduces the burden on satellite node forwarding capabilities and inter-satellite link bandwidth resources, freeing up space for the network to carry more service traffic. Secondly, regarding network throughput, the optimized connection method effectively improves traffic distribution, enabling more satellites performing gateway functions to carry traffic from non-gateway satellites more evenly, thereby significantly increasing the maximum traffic of gateway stations and the overall network throughput. Furthermore, regarding the key indicator of communication latency, thanks to the highly geometrically efficient link design, the total length of some end-to-end paths is shortened, reducing the spatial propagation latency of signals. Simultaneously, this embodiment breaks the single adjacent connection mode of the Grid4-ISL topology by changing the inter-satellite link connection rules, enabling long-distance "hop-through" transmission. The reduction in the number of hops directly reduces the queuing and processing latency of data packets at each node along the way, making the latency performance of this embodiment superior to or at least equivalent to the traditional Grid4-ISL topology in long-distance transmission scenarios. Finally, this application enhances the system's scalability. Its design significantly improves the independent networking performance of a single-layer high-density constellation, thereby avoiding the introduction of complex and unstable multi-layer constellation architectures and their cross-layer links, reducing reliance on ground gateway stations for relay, and laying a solid foundation for building a more autonomous and robust space-based information network.

[0031] In summary, the purpose of the giant constellation network cross-orbit link construction topology construction method in this embodiment is to propose a novel cross-orbit link construction topology, enabling inter-satellite links across adjacent orbital planes to connect satellites spaced several orbital planes apart. While ensuring global connectivity, it significantly improves long-distance transmission efficiency, breaks through the bottleneck of single-layer constellation scale, and fully leverages the advantages of space-based independent networking when expanding the scale of single-layer constellations, reducing dependence on ground gateway stations, and making the giant constellation network a high-performance infrastructure that complements the terrestrial network.

[0032] Preferably, the method of establishing inter-satellite links between each satellite on each orbital plane and corresponding satellites on the corresponding orbital plane by selecting at least two different number of links to form a giant constellation network cross-orbit link establishment topology also includes the following steps: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h =P's track surface is defined as the last track, and the gap formed by the first track and the last track being adjacent in spatial geometry is called the first-last track gap; When the phase factors of the giant constellation network F=0 At that time, inter-satellite links are established between satellites with the same in-plane number on the first and last orbits, so that the entire constellation also presents a ring connection in the direction of the different orbits.

[0033] Given a fixed constellation configuration, the cross-orbit link establishment topology proposed in this application has the same total number of satellite nodes and links as the Grid 4-ISL topology. Constrained by the multi-cross-number hybrid networking strategy, the node set needs to be... Divided into N Mutex subclasses: Cross-node set Such nodes will be adjacent to their left and right sides. Establish inter-satellite links between different orbits at the nodes of the orbit; Cross-node set Such nodes will be adjacent to their left and right sides. Establish inter-satellite links between different orbital nodes; and so on until... ; Cross-node set Such nodes will be adjacent to their left and right sides. The nodes on the orbit establish inter-satellite links between different orbits.

[0034] Within each orbital plane, adjacent satellites are interconnected via inter-satellite links, forming a ring topology within the plane. Between orbital planes, h The orbital plane with a value of 1 is defined as the first orbital. h = P The orbital plane is defined as the end rail, and the gap formed by the two rails being geometrically adjacent in space is called the "head-end rail gap". When the phase factorF=0 At the same time, inter-satellite links will also be established between satellites with the same in-plane number on the first and last orbits, making the entire constellation appear as a ring connection in the direction of the different orbits, such as... Figure 5 As shown, in the Grid 4-ISL topology of the 1296,72,0 constellation, when the phase factor F=0, satellites at the beginning and end orbital gaps establish inter-satellite links with the same in-plane index, making the entire constellation appear as a ring connection in the direction of different orbits. Similarly, as... Figure 6 As shown, the "2-3" inter-orbit link topology of the 1296,72,0 constellation establishes inter-satellite links between satellites with the same in-plane index at the first and last orbital gaps when the phase factor F=0, making the entire constellation appear as a ring connection in the direction of the different orbits. In other words, when the phase factor... F When =0, satellites at the beginning and end of the orbit are symmetrically connected to establish inter-satellite links between different orbits.

[0035] Preferably, the method of establishing inter-satellite links between each satellite on each orbital plane and corresponding satellites on the corresponding orbital plane by selecting at least two different number of links to form a giant constellation network cross-orbit link establishment topology also includes the following steps: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h = P The track surface is defined as the end rail, and the gap formed by the first rail and the end rail being adjacent in spatial geometry is called the first-end rail gap. When the phase factors of the giant constellation network F≠0 At that time, satellites on both sides of the first and last orbital gaps establish inter-satellite links to maintain connectivity by correcting the sequence number difference, making the entire constellation appear as a ring connection in the direction of the different orbits. The corrected sequence number difference is the number of in-plane sequence number misalignments between the linked satellites on the first and last orbits, and the formula for calculating the corrected sequence number difference is: ; in, D To standardize the difference, D= mod( F , S ), N The number of types of spans.

[0036] In the Walker Delta constellation, the phase factor F≠0 This will introduce a phase difference Δ between satellites in adjacent orbital planes. F Its nominal value is .when F≠ At 0:00, the cumulative phase difference of satellites with the same serial number on both sides of the first and last orbital gaps. This makes it difficult for them to directly establish geometrically aligned inter-satellite links between different orbits. In this case, satellites on both sides of the initial and final orbital gaps need to maintain connectivity through staggered link establishment, with a uniform difference in in-plane index between the two sides establishing the link. D The calculation formula is: ; like Figure 7 As shown, in the 1296,72,45 constellation Grid 4-ISL topology, the phase factor... F At 45°, satellites at the beginning and end of the orbital gap maintain connectivity by establishing inter-satellite links in different orbits through out-of-order link establishment. The in-plane sequence numbers of the two satellites establishing the link have a unified difference. D= 9. There is a uniform difference in the in-plane sequence numbers between the two parties establishing the link. D= 9, which makes the entire constellation appear as a ring connection in different orbital directions.

[0037] In cross-track link topology, to ensure that the number of spans on both sides of the first and last track joints is the same. C k For satellites to establish a feasible connection, a correction sequence difference needs to be introduced. This correction of the sequence number difference ensures that satellites with the same number of spans can establish stable inter-orbit links at the beginning and end of the orbit, avoiding network partitioning. Similarly, as... Figure 8 As shown, the 1296,72,0 constellation "2-3" cross-orbit link topology in the phase factor F At 45°, satellites at the beginning and end of the orbital gap maintain connectivity by establishing inter-satellite links in different orbits through out-of-order link establishment. The in-plane sequence numbers of the two satellites establishing the link have a unified difference. = 8. There is a uniform difference in the in-plane sequence numbers between the two parties establishing the link. = 8, which causes the entire constellation to form a circular connection in opposite directions. In other words, when the phase factor... F When =0, the satellite connection at the first and last track gaps needs to be adjusted by misalignment.

[0038] In other words, this embodiment addresses the problem of out-of-order connections caused by phase factors by proposing a method to correct the sequence number difference. Adjust the connections to maintain the geometric alignment of links with the same number of spans, forming a ring structure. Figures 5 to 8 The phase factor is displayed intuitively. F=0 and F≠ The connection difference at the first and last rail joints at time 0: when the phase factor F=0 At that time, the satellites are symmetrically connected; when F≠ At 0:00, the connections between each satellite need to be adjusted by misalignment.

[0039] The feasibility of this invention was verified through large-scale system simulation. The simulation used a typical Walker Delta constellation (parameters 1296 / 72 / 45: 53.2°, 625km), comparing the Grid4-ISL topology with three cross-track link topologies ("1-2" topology, "1-3" topology, and "2-3" topology). The simulation lasted 48 hours, with 10,000 user terminals set up globally, using a space-based standalone networking mode.

[0040] Simulation results show that all topologies maintain global connectivity, and there are no unreachable data packets.

[0041] Figure 9 This indicates that the cross-track link topology has a significant advantage in minimum hop count compared to the Grid4-ISL topology, a clear advantage in gateway station traffic, and latency that is comparable to or better than existing technologies.

[0042] Figure 10 This indicates that over longer distances, the average latency of the cross-track link topology is basically the same as that of the Grid4-ISL topology, with a slight advantage in some intervals.

[0043] Figure 11 This indicates that the cross-track link topology is superior to the Grid4-ISL topology in terms of maximum traffic at gateway stations, and is closer to the theoretical maximum traffic.

[0044] As can be seen, the above simulations confirm the effectiveness of the different topologies provided in the above embodiments of this application in a real constellation environment, providing a basis for engineering applications.

[0045] like Figure 12 As shown, another preferred embodiment of this application also provides a mega-constellation network cross-orbit link establishment topology construction device, applied to a mega-constellation network deploying satellites according to the Walker Delta constellation configuration, comprising: The module for acquiring parameters of a giant constellation network is used to obtain the number of orbital planes that are uniformly distributed in a giant constellation network. P and the number of satellites evenly distributed in each orbital plane S ; The cross-orbit link topology construction module is used to establish inter-satellite links between each satellite in each orbital plane and its adjacent satellites in the same orbital plane. At the same time, each satellite in each orbital plane alternately establishes inter-satellite links with corresponding satellites in the corresponding orbital plane by selecting at least two types of span numbers to form a cross-orbit link topology structure of a giant constellation network. Here, the span number represents the number of orbital planes crossed by a single inter-satellite link, and at least two types of span numbers satisfy the condition that the greatest common divisor of all span numbers is 1.

[0046] The giant constellation network cross-orbit link establishment topology construction device provided in this embodiment adopts the giant constellation network cross-orbit link establishment topology construction method in the above embodiment. It solves the technical problems of low transmission efficiency of the Grid4-ISL topology of existing low-Earth orbit giant constellation systems and instability when expanding the scale of a single-layer constellation, which requires reliance on ground network relay, thus weakening the advantages of space-based independent networking. Compared with the prior art, the beneficial effects of the giant constellation network cross-orbit link establishment topology construction device provided in this embodiment are the same as the beneficial effects of the giant constellation network cross-orbit link establishment topology construction method provided in the above embodiment. Moreover, other technical features in the giant constellation network cross-orbit link establishment topology construction device are the same as the features disclosed in the above embodiment method, and will not be repeated here.

[0047] Preferably, in another embodiment of this application, the cross-track link building topology construction module is further used for: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h = P The track surface is defined as the end rail, and the gap formed by the first rail and the end rail being adjacent in spatial geometry is called the first-end rail gap. When the phase factors of the giant constellation network F=0 At that time, inter-satellite links are established between satellites with the same in-plane number on the first and last orbits, so that the entire constellation also presents a ring connection in the direction of the different orbits.

[0048] Preferably, in another embodiment of this application, the method of establishing inter-satellite links between each satellite on each orbital plane and corresponding satellites on the corresponding orbital plane by selecting at least two different number of links to form a giant constellation network inter-orbit link establishment topology further includes the following steps: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h = P The track surface is defined as the end rail, and the gap formed by the first rail and the end rail being adjacent in spatial geometry is called the first-end rail gap. When the phase factors of the giant constellation network F≠0 At that time, the satellites on both sides of the first and last orbit gap establish inter-satellite links to maintain connectivity by correcting the sequence number difference and establishing links, so that the entire constellation also presents a ring connection in the direction of the different orbits. The corrected sequence number difference is the number of in-plane sequence number misalignment between the linked satellites on the first and last orbits.

[0049] Preferably, in another embodiment of this application, the formula for calculating the corrected sequence number difference is: ; in, D To standardize the difference, D= mod( F , S), N The number of types of spans.

[0050] like Figure 13 As shown, a preferred embodiment of this example also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the steps of the giant constellation network cross-track link topology construction method in the above embodiment.

[0051] This embodiment provides an electronic device that employs the giant constellation network cross-orbit link establishment topology construction method described in the above embodiments. This addresses the technical problems of low transmission efficiency and instability in the Grid4-ISL topology of existing low-Earth orbit giant constellation systems, which require reliance on terrestrial networks for relay during single-layer constellation expansion, thus weakening the advantages of space-based independent networking. Compared with the prior art, the beneficial effects of the electronic device provided in this embodiment are the same as those of the giant constellation network cross-orbit link establishment topology construction method described in the above embodiments. Furthermore, other technical features of the electronic device are the same as those disclosed in the methods of the above embodiments, and will not be elaborated upon here.

[0052] like Figure 14 As shown in the preferred embodiment, this embodiment also provides a computer device, which may be a terminal or a liveness detection server, and its internal structure diagram may be as follows. Figure 14 As shown, the computer device includes a processor, memory, and a network interface connected via a system bus. The processor provides computing and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage media. The network interface is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, it implements the steps of the aforementioned method for constructing a cross-track link topology for a mega-constellation network.

[0053] Those skilled in the art will understand that Figure 14 The structure shown is merely a block diagram of a portion of the structure related to the solution of this embodiment, and does not constitute a limitation on the computer device to which the solution of this embodiment is applied. The specific computer device may include more or fewer components than shown in the figure, or combine certain components, or have different component arrangements.

[0054] The computer equipment provided in this application adopts the giant constellation network cross-orbit link establishment topology construction method in the above embodiments, which solves the technical problems of low transmission efficiency of the Grid4-ISL topology of existing low-orbit giant constellation systems, instability when expanding the scale of a single-layer constellation, and the need to rely on ground network relay, thus weakening the advantages of space-based independent networking. Compared with the prior art, the beneficial effects of the computer equipment provided in this embodiment are the same as the beneficial effects of the giant constellation network cross-orbit link establishment topology construction method provided in the above embodiments, and other technical features in the electronic equipment are the same as the features disclosed in the method of the above embodiments, which will not be repeated here.

[0055] A preferred embodiment of this example also provides a storage medium, which includes a stored program that, when the program is executed, controls the device where the storage medium is located to perform the steps of the giant constellation network cross-track link topology construction method in the above embodiment.

[0056] It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases the steps shown or described may be executed in a different order than that shown here.

[0057] If the functions described in this embodiment are implemented as software functional units and sold or used as independent products, they can be stored in one or more computing device-readable storage media. Based on this understanding, the parts of this embodiment that contribute to the prior art or the technical solution can be embodied in the form of a software product. This software product is stored in a storage medium and includes several instructions to cause a computing device (which may be a personal computer, server, mobile computing device, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this embodiment. The aforementioned storage media include: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0058] Those skilled in the art will understand that embodiments of this example can be provided as methods, systems, or computer program products. Therefore, this example can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this example can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in this example can be implemented using various computer languages, such as the object-oriented programming language C++ and the embedded programming language C.

[0059] This embodiment is described with reference to flowchart illustrations and / or block diagrams of the method, apparatus (system), and computer program product according to this embodiment. It should be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0060] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0061] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0062] This embodiment also provides a computer program product, including a computer program that, when executed by a processor, implements the steps of the above-described method for constructing cross-track link topology for a giant constellation network.

[0063] The computer program product provided in this embodiment solves the technical problems of low transmission efficiency and instability in the Grid4-ISL topology of existing low-Earth orbit mega-constellation systems, which require reliance on terrestrial networks for relay when expanding the scale of a single-layer constellation, thus weakening the advantages of space-based independent networking. Compared with the prior art, the beneficial effects of the computer program product provided in this embodiment are the same as those of the mega-constellation network cross-orbit link establishment topology construction method provided in the above embodiments, and will not be repeated here.

[0064] Obviously, those skilled in the art can make various modifications and variations to this embodiment without departing from the spirit and scope of this embodiment. Therefore, if these modifications and variations of this embodiment fall within the scope of the claims of this embodiment and their equivalents, this embodiment is also intended to include these modifications and variations.

Claims

1. A method for constructing a cross-orbit link topology for a mega-constellation network, applied to a mega-constellation network deploying satellites according to the Walker Delta constellation configuration, characterized in that, Including the following steps: S1. Obtain the number of uniformly distributed orbital planes in a giant constellation network. P and the number of satellites evenly distributed in each orbital plane S ; S2. Each satellite in each orbital plane establishes an inter-satellite link with its adjacent satellites in the same orbital plane. At the same time, each satellite in each orbital plane establishes an inter-satellite link with its corresponding satellite in the corresponding orbital plane by selecting at least two different span numbers to form a giant constellation network cross-orbit link topology. Here, the span number represents the number of orbital planes crossed by a single inter-satellite link, and at least two span numbers satisfy the condition that the greatest common divisor of all span numbers is 1.

2. The method for constructing a cross-track link topology for a giant constellation network according to claim 1, characterized in that, Each satellite in each orbital plane establishes inter-satellite links with corresponding satellites in the corresponding orbital plane by selecting at least two different number of links, forming a giant constellation network. The cross-orbit link establishment topology also includes the following steps: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h =P's track surface is defined as the last track, and the gap formed by the first track and the last track being adjacent in spatial geometry is called the first-last track gap. When the phase factors of the giant constellation network F=0 At that time, inter-satellite links are established between satellites with the same in-plane number on the first and last orbits, so that the entire constellation also presents a ring connection in the direction of the different orbits.

3. The method for constructing a cross-orbit link topology in a giant constellation network according to claim 1, characterized in that, Each satellite in each orbital plane establishes inter-satellite links with corresponding satellites in the corresponding orbital plane by selecting at least two different number of links, forming a giant constellation network. The cross-orbit link establishment topology also includes the following steps: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h = P The track surface is defined as the end rail, and the gap formed by the first rail and the end rail being adjacent in spatial geometry is called the first-end rail gap. When the phase factors of the giant constellation network F≠0 At that time, the satellites on both sides of the first and last orbit gap establish inter-satellite links to maintain connectivity by correcting the sequence number difference and establishing links, so that the entire constellation also presents a ring connection in the direction of the different orbits. The corrected sequence number difference is the number of in-plane sequence number misalignment between the linked satellites on the first and last orbits.

4. The method for constructing a cross-track link topology for a giant constellation network according to claim 3, characterized in that, The formula for calculating the difference in the corrected sequence number is: ； in, D To standardize the difference, D= mod( F , S ), N The number of types of spans.

5. A giant constellation network cross-orbit link establishment topology construction device, applied to a giant constellation network deploying satellites according to the Walker Delta constellation configuration, characterized in that, include: The module for acquiring parameters of a giant constellation network is used to obtain the number of orbital planes that are uniformly distributed in a giant constellation network. P and the number of satellites evenly distributed in each orbital plane S ; The cross-orbit link topology construction module is used to establish inter-satellite links between each satellite in each orbital plane and its adjacent satellites in the same orbital plane. At the same time, each satellite in each orbital plane alternately establishes inter-satellite links with corresponding satellites in the corresponding orbital plane by selecting at least two types of span numbers to form a cross-orbit link topology structure of a giant constellation network. Here, the span number represents the number of orbital planes crossed by a single inter-satellite link, and at least two types of span numbers satisfy the condition that the greatest common divisor of all span numbers is 1.

6. The giant constellation network cross-track link establishment topology construction device according to claim 5, characterized in that, The cross-track link building topology construction module is also used for: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h = P The track surface is defined as the end rail, and the gap formed by the first rail and the end rail being adjacent in spatial geometry is called the first-end rail gap. When the phase factors of the giant constellation network F=0 At that time, inter-satellite links are established between satellites with the same in-plane number on the first and last orbits, so that the entire constellation also presents a ring connection in the direction of the different orbits.

7. The giant constellation network cross-track link establishment topology construction device according to claim 5, characterized in that, Each satellite in each orbital plane establishes inter-satellite links with corresponding satellites in the corresponding orbital plane by selecting at least two different number of links, forming a giant constellation network. The cross-orbit link establishment topology also includes the following steps: Between the track planes, the serial numbers h The orbital plane with a value of 1 is defined as the first orbit, with the sequence number being... h = P The track surface is defined as the end rail, and the gap formed by the first rail and the end rail being adjacent in spatial geometry is called the first-end rail gap. When the phase factors of the giant constellation network F≠0 At that time, the satellites on both sides of the first and last orbit gap establish inter-satellite links to maintain connectivity by correcting the sequence number difference and establishing links, so that the entire constellation also presents a ring connection in the direction of the different orbits. The corrected sequence number difference is the number of in-plane sequence number misalignment between the linked satellites on the first and last orbits.

8. The giant constellation network cross-track link establishment topology construction device according to claim 7, characterized in that, The formula for calculating the difference in the corrected sequence number is: ； in, D To standardize the difference, D= mod( F , S ), N The number of types of spans.

9. An electronic device, the 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 computer program, it implements the method for constructing a cross-track link topology for a mega-constellation network as described in any one of claims 1 to 4.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the method for constructing cross-track chain topology for giant constellation networks as described in any one of claims 1 to 4.

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