CN117081648A - Satellite control method and device and electronic equipment - Google Patents

Satellite control method and device and electronic equipment Download PDF

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Publication number
CN117081648A
CN117081648A CN202311021256.6A CN202311021256A CN117081648A CN 117081648 A CN117081648 A CN 117081648A CN 202311021256 A CN202311021256 A CN 202311021256A CN 117081648 A CN117081648 A CN 117081648A
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satellite
domain
satellites
candidate
domains
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文少杰
徐晓帆
杨旭坤
章跃跃
杜平
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Shanghai Satellite Internet Research Institute Co ltd
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Shanghai Satellite Internet Research Institute Co ltd
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Priority to CN202311021256.6A priority Critical patent/CN117081648A/en
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    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/1851—Systems using a satellite or space-based relay
    • H04B7/18519—Operations control, administration or maintenance
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L45/00—Routing or path finding of packets in data switching networks
    • H04L45/02—Topology update or discovery
    • H04L45/04—Interdomain routing, e.g. hierarchical routing

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  • Engineering & Computer Science (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Signal Processing (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Radio Relay Systems (AREA)

Abstract

The embodiment of the application provides a satellite control method, a satellite control device and electronic equipment, relates to the technical field of satellite communication, and aims to solve the problem of poor link reliability of the existing satellite control method. Receiving satellite control information aiming at a target satellite network, and transmitting the satellite control information to each satellite sub-domain in the target satellite network through inter-domain routing among at least one satellite sub-domain included in the target satellite network; the satellite domains are divided according to the communication gain of each satellite for the corresponding satellite domain; the communication gain is used for representing the gain provided by the satellite to the corresponding satellite domain in terms of link connectivity and link reliability; and returning satellite control confirmation information when each satellite domain in the target satellite network receives the satellite control information.

Description

Satellite control method and device and electronic equipment
Technical Field
The present application relates to the field of satellite communications technologies, and in particular, to a satellite control method, a satellite control device, and an electronic device.
Background
The satellite internet is a satellite communication system capable of providing broadband access service, has the characteristics of global coverage, no terrain constraint, flexible networking and the like, and can provide access service for terminal users at any time and any place, thereby becoming an important means for improving the communication service quality of future operators.
However, the existing large-scale low-orbit satellite network has the characteristics of huge scale, high-speed movement of satellites, high node density, limited single-satellite resources, unstable inter-satellite links and the like, so that when the centralized network control scheme is adopted to realize satellite control, the increase of the number of hops required for transmitting end to end occurs, the complexity of routing is improved, centralized control data occupy a large amount of bandwidth resources, the inter-satellite links are easily influenced by external environment to cause interruption and the like, thereby not only reducing the data transmission performance of the whole network, but also increasing the control cost of the network.
Therefore, a satellite control method is needed to solve the problem of poor link reliability in the prior art when a large-scale low-orbit satellite network is controlled.
Disclosure of Invention
The embodiment of the application provides a satellite control method, a satellite control device and electronic equipment, which are used for solving the problem of poor link reliability of the existing satellite control method.
In a first aspect, an embodiment of the present application provides a satellite control method, including:
after receiving satellite control information, M satellite domains in a target satellite network send the satellite control information to the satellite domains which do not receive the satellite control information in the target satellite network through inter-domain routing among the satellite domains; the target satellite network comprises N satellite domains, wherein N is a positive integer not smaller than M, and the satellite domains are divided according to the communication gain of the satellite for the corresponding satellite domains; the communication gain is used for representing the gain provided by the satellite to the corresponding satellite domain in terms of link connectivity and link reliability; and returning satellite control confirmation information when all the N satellite domains receive the satellite control information.
In one implementation, the satellite domains are partitioned according to the following method: determining a maximum number of satellites in the satellite domain based on a total number of satellites in the target satellite network and a total cost function; the total cost function is used for describing the control cost and interaction cost of the target satellite network; for each satellite domain, the following operations are performed: determining at least one candidate satellite which has a direct link with a satellite in a satellite sub-domain according to the link connection relation between satellites in the target satellite network; calculating the communication gain of the candidate satellite for the satellite domain according to the link reliability parameter and the connectivity parameter of the candidate satellite; the link reliability parameter is used for representing the link on-off probability of the candidate satellite; and selecting candidate satellites based on the communication gain, and adding the candidate satellites into the satellite sub-domain until the number of satellites in the satellite sub-domain reaches the maximum number of satellites.
In one implementation, the calculating the communication gain of the candidate satellite for the satellite domain according to the link reliability parameter and the connectivity parameter of the candidate satellite includes: determining a connectivity parameter of the candidate satellite according to the number of adjacent satellites with direct links with the candidate satellite in the target satellite network; the connectivity parameter is positively correlated with the number of adjacent satellites; and calculating the communication gain of the candidate satellite according to the communication parameter, the prestored maximum communication of the target satellite network and the prestored link reliability parameter of the candidate satellite.
In one implementation, the selecting candidate satellites based on the communication gain to join the one satellite domain includes: determining the priority of the candidate satellite according to the principle that the priority is higher corresponding to the larger communication gain; and selecting the candidate satellite with the highest priority to join the satellite sub-domain.
In one implementation, the determining the priority of the candidate satellite according to the principle that the priority corresponding to the larger communication gain is higher includes: when a plurality of candidate satellites with equal communication gains exist, determining the priority of the candidate satellites with equal communication gains according to the principle that the priority is higher corresponding to the smaller satellite identification.
In one implementation, the determining the maximum number of satellites in the satellite domain based on the total number of satellites in the target satellite network and the total cost function includes: determining a total cost function of the target satellite network based on inter-domain interaction cost, inter-domain satellite interaction cost and total number of satellites by taking the number of satellite domains as a variable; based on the total cost function, taking the total cost of the target satellite network as an optimization target, and determining the optimal domain division number; the maximum number of satellites is determined based on the total number of satellites and the optimal number of domains.
In one implementation, the determining the optimal number of domains based on the total cost function with the objective satellite network total cost reduced as an optimization objective includes: taking the value of the satellite domain number from 1 to the whole number of the total number of the satellites according to the total cost function, and obtaining the total cost of the satellite network corresponding to the value of each satellite domain number; and determining the minimum value of the total cost of the satellite network by comparing the obtained total cost of the satellite network, and taking the satellite domain number value corresponding to the minimum value as the optimal domain number.
In a second aspect, an embodiment of the present application provides a satellite control device, including:
a receiving unit, configured to make M satellites in a target satellite network receive satellite control information in a domain division manner;
an inter-domain routing unit, configured to send the satellite control information to a satellite domain in which the satellite control information is not received in the target satellite network through inter-domain routing between satellite domains; the target satellite network comprises N satellite domains, wherein N is a positive integer not smaller than M, and the satellite domains are divided according to the communication gain of the satellite for the corresponding satellite domains; the communication gain is used for representing the gain provided by the satellite to the corresponding satellite domain in terms of link connectivity and link reliability;
And the sending unit is used for returning satellite control confirmation information when the satellite control information is received by all the N satellite domains.
In one implementation, the satellite control device further includes: a domain dividing unit; the satellite domain is divided by the domain dividing unit according to the following method: determining a maximum number of satellites in the satellite domain based on a total number of satellites in the target satellite network and a total cost function; the total cost function is used for describing the control cost and interaction cost of the target satellite network; for each satellite domain, the following operations are performed: determining at least one candidate satellite which has a direct link with a satellite in a satellite sub-domain according to the link connection relation between satellites in the target satellite network; calculating the communication gain of the candidate satellite for the satellite domain according to the link reliability parameter and the connectivity parameter of the candidate satellite; the link reliability parameter is used for representing the link on-off probability of the candidate satellite; and selecting candidate satellites based on the communication gain, and adding the candidate satellites into the satellite sub-domain until the number of satellites in the satellite sub-domain reaches the maximum number of satellites.
In one implementation manner, the domain division unit is specifically configured to, for each candidate satellite, calculate, according to the link reliability parameter and the connectivity parameter, a connectivity gain of the corresponding candidate satellite for the one satellite domain, where the connectivity gain is specifically configured to: for each candidate satellite, the following operations are performed: determining a connectivity parameter of a candidate satellite according to the number of adjacent satellites with direct links with the candidate satellite in the target satellite network; the connectivity parameter is positively correlated with the number of adjacent satellites; and calculating the communication gain of the candidate satellite according to the communication parameter, the prestored maximum communication of the target satellite network and the prestored link reliability parameter of the candidate satellite.
In one implementation manner, the domain division unit is specifically configured to, when calculating the communication gain of the candidate satellite for the one satellite domain according to the link reliability parameter and the connectivity parameter of the candidate satellite: determining a connectivity parameter of the candidate satellite according to the number of adjacent satellites with direct links with the candidate satellite in the target satellite network; the connectivity parameter is positively correlated with the number of adjacent satellites; and calculating the communication gain of the candidate satellite according to the communication parameter, the prestored maximum communication of the target satellite network and the prestored link reliability parameter of the candidate satellite.
In one implementation, the domain separation unit is configured to, when selecting a candidate satellite based on the communication gain and adding the candidate satellite to the one satellite domain: when a plurality of candidate satellites with equal communication gains exist, determining the priority of the candidate satellites with equal communication gains according to the principle that the priority is higher corresponding to the smaller satellite identification.
In one implementation, the domain division unit is specifically configured to, when determining the maximum number of satellites in the satellite domain based on the total number of satellites in the target satellite network and the total cost function: determining a total cost function of the target satellite network based on inter-domain interaction cost, inter-domain satellite interaction cost and total number of satellites by taking the number of satellite domains as a variable; based on the total cost function, taking the total cost of the target satellite network as an optimization target, and determining the optimal domain division number; the maximum number of satellites is determined based on the total number of satellites and the optimal number of domains.
In one implementation, the domain division unit is specifically configured to, based on the total cost function, determine an optimal number of domains with the objective of reducing the total cost of the objective satellite network as an optimization objective: taking the value of the satellite domain number from 1 to the whole number of the total number of the satellites according to the total cost function, and obtaining the total cost of the satellite network corresponding to the value of each satellite domain number; and determining the minimum value of the total cost of the satellite network by comparing the obtained total cost of the satellite network, and taking the satellite domain number value corresponding to the minimum value as the optimal domain number.
In a third aspect, an embodiment of the present application provides an electronic device, including:
a memory for storing computer instructions;
a processor coupled to the memory for executing computer instructions in the memory and for implementing the method of any one of the first aspects when the computer instructions are executed.
In a fourth aspect, embodiments of the present application provide a computer-readable storage medium comprising:
the computer readable storage medium stores computer instructions which, when run on a computer, cause the computer to perform the method according to any of the first aspects.
The application has the following beneficial effects:
the embodiment of the application provides a satellite control method, a satellite control device and electronic equipment. In the method, after M satellite domains in a target satellite network receive satellite control information, the satellite control information is sent to the satellite domains which do not receive the satellite control information in the target satellite network through inter-domain routing among the satellite domains; and returning satellite control confirmation information when the satellite control information is received by all the N satellite domains. The satellite domains are divided according to the communication gains of the satellites for the corresponding satellite domains; the connectivity gain is used to characterize the gain provided by the satellite to the corresponding satellite domain in terms of link connectivity and link reliability.
The method for controlling each domain after the satellite is divided into the domains can avoid the problems of high routing complexity and poor network data transmission performance caused by adopting a centralized network control scheme in the related technology. In addition, in the embodiment of the application, the satellite domains are divided according to the communication gain of the satellite for the corresponding satellite domains, so that the link connectivity and the link reliability of each satellite domain can be improved by the satellite in each satellite domain, the topological structure of the satellite domain has higher robustness, and the problem of poor link reliability in the conventional satellite control method is solved.
Additional features and advantages of the application will be set forth in the description which follows and will not be described in detail herein.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present application.
Fig. 1A is a schematic diagram of an application scenario of a satellite control method according to an embodiment of the present application;
FIG. 1B is a schematic diagram of a system architecture applied in dividing satellite domains according to an embodiment of the present application;
FIG. 2 is one of exemplary flowcharts of a satellite control method according to an embodiment of the present application;
FIG. 3 is a schematic diagram of a satellite network topology according to an embodiment of the present application;
FIG. 4 is an exemplary flowchart of a satellite domain division method according to an embodiment of the present application;
FIG. 5 is a schematic diagram of a satellite network topology according to an embodiment of the present application;
FIG. 6 is one of exemplary flowcharts of a satellite control method according to an embodiment of the present application;
fig. 7 is a schematic diagram of a satellite control device according to an embodiment of the present application;
fig. 8 is a schematic structural diagram of an electronic device according to an embodiment of the present application.
Detailed Description
In order to facilitate understanding of the technical solution provided by the embodiments of the present application, the following describes the technical terms related to the embodiments of the present application.
(1) The satellite constellation, the satellite network formed by the inter-satellite links arranged according to a certain rule is called a satellite constellation, the satellite constellation is classified by adopting different standards, the most common standards comprise orbit characteristics, coverage range, space distribution and the like, the satellite constellation is biased to use circular orbits in design, the satellites in the orbit system have fixed ground coverage areas and sub-satellite orbits, the satellite distribution in the constellation is symmetrical, and the stability of the inter-satellite links is effectively ensured. In the embodiment of the present application, the target satellite network may be a satellite constellation.
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the technical solutions of the present application, but not all embodiments. All other embodiments, based on the embodiments described in the present document, which can be obtained by a person skilled in the art without any creative effort, are within the scope of protection of the technical solutions of the present application.
The terms "first" and "second" in embodiments of the application are used to distinguish between different objects and are not used to describe a particular sequence. Furthermore, the term "include" and any variations thereof is intended to cover non-exclusive protection. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not limited to only those listed steps or elements but may include other steps or elements not listed or inherent to such process, method, article, or apparatus. The term "plurality" in the present application may mean at least two, for example, two, three or more, and embodiments of the present application are not limited.
In addition, the term "and/or" herein is merely an association relationship describing an association object, and means that three relationships may exist, for example, a and/or B may mean: a exists alone, A and B exist together, and B exists alone. The character "/" herein generally indicates that the associated object is an "or" relationship unless otherwise specified.
Because the current large-scale low-orbit satellite network has the characteristics of huge scale, high-speed movement of satellites, high node density, limited single-satellite resources, unstable inter-satellite links and the like, the large-scale low-orbit satellite network usually faces extremely large expandable and controllable risks when adopting a centralized network control scheme adopted by a medium-small-scale constellation, and is mainly expressed as follows: (1) The time of the centralized control decision is prolonged, the data volume required to be issued by the network control is increased, and the networking control efficiency is drastically reduced; (2) For a single node with centralized control, not only is the risk of failure of the centralized control existed, but also the problem of loss of important control data transmission exists; (3) In the topology construction and route updating process, a centralized control mode causes a large number of broadcast messages in the network, reduces the bandwidth utilization rate of the network, and even causes the network to be incapable of normal data transmission; (4) The adoption of distributed control similar to the ground makes it difficult to achieve rapid convergence in a dynamic network environment such as the satellite internet to form stable routes, and on-board distributed route calculation is also a serious challenge for on-board resources.
Therefore, it is necessary to design a satellite control method that can effectively reduce the amount of control data and improve the end-to-end data transmission performance under the condition of meeting the characteristics of a large-scale low-orbit satellite network. However, the current satellite control method generally has the problem of poor link reliability.
In view of this, an embodiment of the present application provides a satellite control method, in which after receiving satellite control information in M satellite domains in a target satellite network, the satellite control information is sent to a satellite domain in the target satellite network, where the satellite control information is not received, through inter-domain routing between the satellite domains; and returning satellite control confirmation information when the satellite control information is received by all the N satellite domains. The satellite domains are divided according to the communication gains of the satellites for the corresponding satellite domains; the connectivity gain is used to characterize the gain provided by the satellite to the corresponding satellite domain in terms of link connectivity and link reliability.
The method for controlling each domain after the satellite is divided into the domains can avoid the problems of high routing complexity and poor network data transmission performance caused by adopting a centralized network control scheme in the related technology. In addition, in the embodiment of the application, the satellite domains are divided according to the communication gain of the satellite for the corresponding satellite domains, so that the link connectivity and the link reliability of each satellite domain can be improved by the satellite in each satellite domain, the topological structure of the satellite domain has higher robustness, and the problem of poor link reliability in the conventional satellite control method is solved.
Referring to fig. 1A, an application scenario of a satellite control method according to an embodiment of the present application includes a gateway station 101 and a target satellite network 102, where the target satellite network includes N satellite domains 1020. In fig. 1A, which illustrates that each satellite domain includes 3 satellites, a ground control center may transmit satellite control information to a target satellite network 102 through a gateway station 101. Specifically, the gateway station 101 may transmit satellite control information to M satellite domains within a communication range, in fig. 1A, m=2 as an example. The M satellite domains may send satellite control information to a satellite domain having a direct link with the satellite domain and not receiving the satellite control information through inter-domain routing, until all of the N satellite domains receive the satellite control information, and then return satellite control acknowledgement information to the gateway station 101. Wherein M is a positive integer, and N is an integer not less than M.
The process of transferring satellite control information between satellite domains and the process of returning satellite control confirmation information can be performed by an on-board control center. The on-board control center may determine that a direct link exists between the on-board control center and the M satellite domains after the M satellite domains receive the satellite control information, and control the M satellite domains to send the satellite control information to the satellite domains that have direct links to the satellite domains through inter-domain routing respectively, and do not receive the satellite control information, until the N satellite domains all receive the satellite control information, and then the on-board control center may return satellite control confirmation information to the gateway 101.
Alternatively, the on-board control center may include control nodes in N satellite domains, each of which may include a control node and a border gateway. In one satellite domain, the control node may send satellite control information to a satellite domain that has a direct link with the satellite domain and has not received the satellite control information through the control border gateway.
In some embodiments, the application scenario shown in fig. 1A may further include an acknowledgement information summarizing center, after receiving the satellite control information in each satellite domain, the satellite control acknowledgement information may be sent to the acknowledgement information summarizing center, and then the acknowledgement information summarizing center may return the satellite control acknowledgement information to the gateway station 101. The confirmation information summarizing center may be a selected node in the target satellite network, or the confirmation information summarizing center may be a selected node on the ground.
Fig. 1B is a schematic diagram of a system architecture applied when dividing satellite domains according to an embodiment of the present application. The satellite domains in the target satellite network may be divided by the system before performing the satellite control procedure, and the system may be the server 100, including: memory 110, processor 120, and communication interface 130. Wherein the communication interface 130 may be used to obtain relevant parameters of a target satellite network, the processor 120 is a control center of the server 100, connects various parts of the entire server 100 using various interfaces and lines, performs various functions of the server 100 and processes data by running or executing software programs or modules stored in the memory 110, and invoking data stored in the memory 110. Optionally, the processor 120 may include one or more processing units. The memory 110 may be a high-speed random access memory, or may be a non-volatile memory, such as at least one magnetic disk storage device, flash memory device, or other volatile solid-state storage device.
It should be noted that the application scenario shown in fig. 1A and the system architecture shown in fig. 1B are only examples, and the embodiment of the present application is not limited thereto.
Referring to fig. 2, one of exemplary flowcharts of a satellite control method according to an embodiment of the present application may include the following procedures:
s201, after receiving satellite control information, M satellite domains in the target satellite network send the satellite control information to the satellite domains which do not receive the satellite control information in the target satellite network through inter-domain routing among the satellite domains.
Wherein M is a positive integer, the target satellite network comprises N satellite domains, and N is a positive integer not smaller than M. The satellite domains are divided according to the communication gains of the satellites for the corresponding satellite domains, and the communication gains are used for representing the gains provided by the satellites for the corresponding satellite domains in the aspects of link connectivity and link reliability.
S202, returning satellite control confirmation information when all the N satellite domains receive the satellite control information.
When it is determined that all of the N satellite domains receive satellite control information, the on-board control center may return satellite control confirmation information to the gateway station.
Fig. 3 is a schematic diagram of a satellite network topology according to an embodiment of the present application. In fig. 3, 16 satellites are included at the same altitude in space, wherein the broken lines represent direct links between satellites. Before the target satellite network is divided into N satellite domains, it may be as shown in fig. 3.
In some embodiments, when S201 is performed, referring to fig. 4, which is an exemplary flowchart of a satellite domain division method provided by an embodiment of the present application, N satellite domains included in a target satellite network may be divided according to a procedure shown in fig. 4, where the procedure may be applied to a server shown in fig. 1B:
s401, determining the maximum satellite number of satellite domains based on the total number of satellites of the target satellite network and the total cost function.
Wherein the total cost function is used to describe the control cost and interaction cost of the target satellite network.
In one implementation, before executing S401, the server may obtain parameter information of the target satellite network, including at least: the method comprises the steps of selecting a total number of satellites in a target satellite network, satellite identification of each satellite, the number of orbits in the target satellite network, link connection relations among the satellites, maximum connectivity of the target satellite network, link reliability parameters of the satellites, connectivity parameters of the satellites, preset intra-domain interaction cost and preset inter-domain interaction cost.
The link reliability parameter of the satellite may refer to a link reliability parameter of each link of the satellite. For example, assuming that a satellite is connected to other satellites in the target satellite network by three links, which may be a, b, and c, respectively, the link reliability parameters of the satellite may include a's link reliability parameter, c's link reliability parameter, and c's link reliability parameter.
In some embodiments, S401 may be specifically performed as: the total cost function of the target satellite network is determined based on the inter-domain interaction cost, the inter-domain satellite interaction cost and the total number of satellites by taking the number of satellite domains as a variable. The optimal number of domains may then be determined based on the total cost function with the objective of reducing the total cost of the target satellite network as an optimization objective. And determining the maximum satellite number based on the total number of satellites and the optimal domain number.
In one implementation, assuming that the target satellite network is denoted S, the total number of satellites in the target satellite network is |s|. In the case where the target satellite network is divided into N satellite domains, the satellite domains N i The number of satellites in a system can be expressed as x i . Under the condition of no domain division, the target satellite network maintains the network topology in a broadcast mode, and the network control cost is O (S|) 2 ) In the case of the split domain, the N-th i The cost of maintaining the topology of the satellites in the individual domains isI.e. the N i The intra-domain control cost of the individual domains is +.>Wherein 1 is<x i <S. Since the value of N remains unchanged after determining the number of domains, the optimal number of satellites in each satellite domain can be obtained by minimizing the domain control cost of all satellite domains, and the objective function is set to +. >According to the Cauchy-Schwarz theorem, when x 1 ＝…＝x N When the objective function gets the minimum, i.e. +.>I.e. the network control costs are minimal when the number of satellites in each satellite sector is equal.
And then will beSubstituting the target function into the above target function, the target function can be converted into +.>It follows that the optimal number of satellites in each satellite fraction is related to the satellite fraction and the total number of satellites, and that the optimal number of satellites in each satellite fraction is related to the satellite fraction since the total number of satellites is a determined value. When the number of satellites in the satellite domain is +.>In the time domain, the control cost is +.>The inter-domain control cost is O (N) 2 ) Then the total cost of control of the target satellite network after the domain division is +.> Combining preset intra-domain interaction cost alpha 1 Inter-domain interaction cost alpha 2 The total cost of the available target satellite network is +.>The optimal number of domains is then determined for optimization with the goal of reducing the overall cost of the target satellite network. The optimal satellite number can be used as the maximum satellite number of the satellite domains because the network control cost of the target satellite network is minimum when the satellite numbers in the satellite domains are equal.
Specifically, based on the total cost function, with the reduction of the total cost of the target satellite network as an optimization target, when determining the optimal number of the domains, the server may take the value of the number of the domains of the satellite through an integer between 1 and the total number of the satellites |s| according to the total cost function, so as to obtain the total cost of the satellite network corresponding to the value of the number of the domains of each satellite. And determining the minimum value of the total cost of the satellite network by comparing the obtained total cost of each satellite network, and taking the value of the satellite domain number corresponding to the minimum value as the optimal domain number.
For example, assuming the number of satellites is 2, n=1 and n=2 are substituted into the total cost functionThe total satellite network cost corresponding to n=1 and the total satellite network cost corresponding to n=2 are calculated. Assuming that the total satellite network cost corresponding to n=1 is greater than the total satellite network cost corresponding to n=2, the optimal number of domains is determined to be 2.
And calculating the maximum satellite number according to the optimal domain number and the total satellite number, and satisfying the formula (1).
Wherein n is max Representing the maximum number of satellites, N being the optimal number of domains,representation pair->The result of (2) is rounded up.
S402, for each satellite domain, S4021-S4023 are executed respectively.
In one implementation, S4021-S4023 may be performed by first establishing one satellite domain, which may include at least one initial satellite, and then establishing another satellite domain when the number of satellites in the satellite domain reaches a maximum number of satellites until the satellites in the target satellite network are included in the satellite domain.
In another implementation, N satellite domains may be established according to the number N of optimal domains determined in S401 before performing S4021-S4023, where each satellite domain may include at least one initial satellite.
In some embodiments, the number of initial satellites added to the satellite domain when the satellite domain is established and the selection condition of the initial satellites may be preset in the server, so that the satellite meeting the selection condition of the initial satellites is selected in the target satellite network to be added to the satellite domain according to the preset number of initial satellites and the selection condition of the initial satellites. For example, the number of preset initial satellites may be 1, and the selection condition of the initial satellites may be that the connectivity parameter and the link reliability parameter of the satellites are both greater than a preset threshold. Or the number of the preset initial satellites can be 2, the selection condition of the initial satellites can be that direct links exist between the selected initial satellites, and the connectivity parameters and the link reliability parameters of the satellites are both larger than a preset threshold.
In one implementation, before S401 is performed, satellite identifiers of respective satellites in the target satellite network may also be acquired. The selection condition of the initial satellite can be set according to the satellite identification, that is, when the satellite domain is established, at least one satellite can be selected from the target satellite network according to the satellite identification to join the satellite domain.
In one example, the selection condition of the initial satellite may be that the selection satellite identifies the least one satellite to be split. For example, the target satellite network includes satellites with satellite identifiers of 001, 002, 005 and 010, and if the preset initial number of satellites is 1, the satellite with satellite identifier of 001 may be selected to join the satellite domain when the satellite domain is established. Assuming that the number of preset initial satellites is 2, when establishing satellite domains, satellites with satellite identifiers of 001 and 002 can be selected to join the satellite domains.
In another example, the selection condition of the initial satellite may also be that the selection satellite identifies at least one satellite that is the largest. For example, the target satellite network includes satellites with satellite identifiers of 001, 002, 005 and 010, and if the preset initial number of satellites is 1, the satellite domain may be established by selecting the satellite with the satellite identifier of 010 to join the satellite domain. Assuming that the number of preset initial satellites is 2, when establishing a satellite domain, satellites with satellite identifiers 010 and 005 can be selected to join the satellite domain.
It should be noted that the number of initial satellites and the selection conditions of the initial satellites may be set according to actual situations or experience, which is not limited by the present application.
S4021, determining at least one candidate satellite with a direct link with a satellite in a satellite sub-domain according to the link connection relation between satellites in the target satellite network.
Specifically, the server may determine at least one candidate satellite in the satellites of the target satellite network that has a direct link with a satellite in a satellite domain, and add the at least one candidate satellite to the candidate set.
Referring to fig. 5, which is one of the schematic diagrams of the satellite network topology provided by the embodiment of the present application, in fig. 5, a satellite in a satellite domain includes a satellite a and a satellite B, and since a satellite having a direct link with the satellite a is a satellite E and a satellite having a direct link with the satellite B is a satellite C and a satellite D, determining that the satellite C, the satellite D and the satellite E are candidate satellites, and adding the satellite C, the satellite D and the satellite E to the candidate set.
S4022, calculating the communication gain of the candidate satellite for one satellite domain according to the link reliability parameter and the connectivity parameter of the candidate satellite.
The link reliability parameter is used for representing the link on-off probability of the candidate satellite. That is, the larger the value of the link reliability parameter is, the higher the link reliability of the candidate satellite is. The link reliability parameters for each link of the satellite may be the same or different.
In order to improve the robustness and connectivity of the topological structure of the satellite domains, the embodiment of the application introduces a communication gain index, wherein the index is used for representing the gain provided by a satellite in the aspect of improving the link connectivity and the link reliability in the satellite domains when the satellite is added into one satellite domain. The communication gain index satisfies the formula (1).
In the method, in the process of the application,representing satellite z versus satellite domain N i Is a communication gain of (2); beta 1 、β 2 Is a preset weight factor, beta 1 +β 2 ＝1；p iz Satellite-to-satellite domain N for satellite z i Reliability parameter of direct link between d z The link connectivity parameter is satellite z; d, d max For maximum connectivity of the target satellite network,
it can be seen from equation (1) that the communication gain needs to meet the following two requirements: 1) When a satellite is added into a satellite domain, the satellite needs to improve the connectivity of the satellite domain. 2) Links introduced when adding a satellite to the satellite domain require that link reliability conditions be met.
The server, when executing S4022, may perform the following operations, respectively, for each candidate satellite in the candidate set:
and determining a connectivity parameter of one candidate satellite according to the number of adjacent satellites with direct links with the candidate satellite in the target satellite network. And calculating the communication gain of one candidate satellite according to the communication parameter, the maximum communication of the pre-stored target satellite network and the link reliability parameter pre-stored by the candidate satellite.
Wherein the connectivity parameter is positively correlated with the number of adjacent satellites. For example, assuming that a certain satellite in the target satellite network has 4 adjacent satellites, the connectivity parameter of the satellite is 4.
Specifically, the connectivity parameter, the maximum connectivity of the pre-stored target satellite network, the link reliability parameter pre-stored by one candidate satellite and the preset weight factor are respectively substituted into the formula (1) to obtain the connectivity gain of the candidate satellite.
Based on the scheme, the contribution of the candidate satellite to the aspect of improving the connectivity of the satellite domains can be reflected through the connectivity parameters, and the contribution of the candidate satellite to the aspect of improving the stability of the topological structure of the satellite domains can be reflected through the link reliability parameters. Therefore, when the selected satellite joins the satellite sub-domain, the robustness and connectivity of the topological structure of the satellite sub-domain can be improved by selecting the candidate satellite with large communication gain.
S4023, selecting candidate satellites based on the communication gain, and adding the candidate satellites into a satellite sub-domain until the number of satellites in the satellite sub-domain reaches the maximum number of satellites.
In one implementation, the server may determine the priority of each candidate satellite according to the principle that the higher the connectivity gain corresponds to the higher priority. And then selecting the candidate satellite with the highest priority to add into the satellite domain.
For example, assume that three candidate satellites are included in the candidate set: satellite C, satellite D, and satellite E. The communication gain of satellite C was 0.6, the communication gain of satellite D was 0.7, and the communication gain of satellite E was 0.75. Then it can be determined that the priority of satellite E is highest, the value of the priority being 1; secondly, the satellite D priority is a value 2; the priority of the satellite C is lowest, and the value of the priority is 3. Satellite E may then be added to the satellite domain.
If a plurality of candidate satellites with equal communication gains exist, determining the priority of the plurality of candidate satellites with equal communication gains according to the principle that the priority corresponding to the smaller satellite identifications is higher.
For example, assume that three candidate satellites are included in the candidate set: satellite C, satellite D, and satellite E. The communication gain of satellite C was 0.7, the communication gain of satellite D was 0.7, and the communication gain of satellite E was 0.65. Satellite C has satellite identification 004, satellite D has satellite identification 008, and satellite E has satellite identification 018. When the communication gains of the satellite C and the satellite D are equal, the satellite identifier of the satellite C is smaller than the satellite identifier of the satellite D, so that it can be determined that the priority of the satellite C is higher than that of the satellite D, the priority of the satellite C can be determined to be highest, the priority value is 1, the priority value of the satellite D is 2, the priority of the satellite E is lowest, and the priority value is 3. Satellite C may then be added to the satellite domain.
It should be understood that, in the embodiment of the present application, the value of the priority is represented by a positive integer, and the lower the value of the priority, the higher the priority, and the above-mentioned method of representing the priority is merely exemplary, which is not limited in this aspect of the present application.
In the following, in order to more clearly understand the solution provided by the embodiments of the present application, a satellite control method provided by the present application will be described with reference to specific embodiments.
Referring to fig. 6, one of exemplary flowcharts of a satellite control method according to an embodiment of the present application specifically includes:
s601, acquiring parameter information of a target satellite network.
The parameter information may include: the method comprises the steps of selecting a total number of satellites in a target satellite network, satellite identification of the satellites, number of orbits in the target satellite network, link connection relation among the satellites, maximum connectivity of the target satellite network, link reliability parameters of each link of the satellites, preset intra-domain interaction cost and preset inter-domain interaction cost.
S602, determining the maximum satellite number according to the parameter information.
The method for determining the maximum number of satellites may be described in relation to the method embodiment shown in fig. 4, and will not be described in detail herein.
S603, establishing satellite split domains.
When the target satellite network does not have any satellite domains or the number of the satellites in the existing satellite domains is the maximum number of satellites, establishing the satellite domains and selecting the satellite with the minimum satellite identification as the initial satellite of the satellite domains.
For example, in the absence of any satellite domains in the target satellite network, the satellite may beAs a satellite domain division method,adding satellite s with minimum satellite identification to set N 1 In (b) can be expressed as s ≡N 1 Simultaneously S is removed from the satellite set S, which may be denoted S/S. Wherein the set of satellites S includes all satellites in the target satellite network.
S604, determining candidate satellites in the candidate set.
The method for determining candidate satellites may be described in relation to the method embodiment shown in fig. 4, and will not be described in detail herein.
And S605, determining the communication gain and the priority of the candidate satellite.
The method for determining the communication gain and priority of each candidate satellite may be described with reference to the related description in the method embodiment shown in fig. 4, which is not described herein.
S606, judging whether the satellite number in the satellite domain is smaller than the maximum satellite number.
If yes, then execute S607; if not, then S608 is performed.
In another implementation manner, S606 may further determine whether the number of satellites in the satellite domain is greater than the maximum number of satellites after adding a candidate satellite, and if so, execute S608; if not, then S607 is performed.
S607, selecting the candidate satellite with the highest priority in the candidate set to add into the satellite domain.
After selecting the candidate satellite with the highest priority in the candidate set to join the satellite domain, deleting the candidate satellite joining the satellite domain from the candidate set, and returning to execute S604.
S608, judging whether satellites which are not added into satellite domains exist in the target satellite network.
If yes, return to S603; if the satellite is not present, determining that all satellites in the target satellite network are added into the corresponding satellite domains, and completing the satellite domain separation flow.
Based on the same concept of the above method, referring to fig. 7, a satellite control device 700 according to an embodiment of the present application is provided, where the device 700 is capable of performing each step in the above method, and in order to avoid repetition, details are not described herein. The apparatus 700 comprises a receiving unit 701, an inter-domain routing unit 702, a transmitting unit 703 and a domain dividing unit 704. In one scenario:
a receiving unit 701, configured to make M satellites in a target satellite network receive satellite control information in a domain division manner;
An inter-domain routing unit 702, configured to send the satellite control information to a satellite domain in the target satellite network, where the satellite control information is not received, through inter-domain routing between satellite domains; the target satellite network comprises N satellite domains, wherein N is a positive integer not smaller than M, and the satellite domains are divided according to the communication gain of the satellite for the corresponding satellite domains; the communication gain is used for representing the gain provided by the satellite to the corresponding satellite domain in terms of link connectivity and link reliability;
and a sending unit 703, configured to return satellite control confirmation information when the satellite control information is received by each of the N satellite domains.
In one implementation, the satellite control device further includes: a domain division unit 704; the satellite domain is divided by the domain dividing unit 704 according to the following method: determining a maximum number of satellites in the satellite domain based on a total number of satellites in the target satellite network and a total cost function; the total cost function is used for describing the control cost and interaction cost of the target satellite network; for each satellite domain, the following operations are performed: determining at least one candidate satellite which has a direct link with a satellite in a satellite sub-domain according to the link connection relation between satellites in the target satellite network; calculating the communication gain of the candidate satellite for the satellite domain according to the link reliability parameter and the connectivity parameter of the candidate satellite; the link reliability parameter is used for representing the link on-off probability of the candidate satellite; and selecting candidate satellites based on the communication gain, and adding the candidate satellites into the satellite sub-domain until the number of satellites in the satellite sub-domain reaches the maximum number of satellites.
In one implementation manner, the domain division unit 704 is specifically configured to, for each candidate satellite, calculate, according to the link reliability parameter and the connectivity parameter, a connectivity gain of the corresponding candidate satellite for the one satellite domain, where the connectivity gain is specifically: for each candidate satellite, the following operations are performed: determining a connectivity parameter of a candidate satellite according to the number of adjacent satellites with direct links with the candidate satellite in the target satellite network; the connectivity parameter is positively correlated with the number of adjacent satellites; and calculating the communication gain of the candidate satellite according to the communication parameter, the prestored maximum communication of the target satellite network and the prestored link reliability parameter of the candidate satellite.
In one implementation manner, the domain division unit 704 is specifically configured to, when calculating the communication gain of the candidate satellite for the one satellite domain according to the link reliability parameter and the connectivity parameter of the candidate satellite: determining a connectivity parameter of the candidate satellite according to the number of adjacent satellites with direct links with the candidate satellite in the target satellite network; the connectivity parameter is positively correlated with the number of adjacent satellites; and calculating the communication gain of the candidate satellite according to the communication parameter, the prestored maximum communication of the target satellite network and the prestored link reliability parameter of the candidate satellite.
In one implementation, the domain separation unit 704 is configured to, when selecting a candidate satellite to join the one satellite domain based on the communication gain: when a plurality of candidate satellites with equal communication gains exist, determining the priority of the candidate satellites with equal communication gains according to the principle that the priority is higher corresponding to the smaller satellite identification.
In one implementation, the domain division unit 704 is specifically configured to, when determining the maximum number of satellites in the satellite domain based on the total number of satellites in the target satellite network and the total cost function: determining a total cost function of the target satellite network based on inter-domain interaction cost, inter-domain satellite interaction cost and total number of satellites by taking the number of satellite domains as a variable; based on the total cost function, taking the total cost of the target satellite network as an optimization target, and determining the optimal domain division number; the maximum number of satellites is determined based on the total number of satellites and the optimal number of domains.
In one implementation, the domain division unit 704 is specifically configured to, based on the total cost function, determine an optimal number of domains with respect to reducing the total cost of the target satellite network as an optimization target: taking the value of the satellite domain number from 1 to the whole number of the total number of the satellites according to the total cost function, and obtaining the total cost of the satellite network corresponding to the value of each satellite domain number; and determining the minimum value of the total cost of the satellite network by comparing the obtained total cost of the satellite network, and taking the satellite domain number value corresponding to the minimum value as the optimal domain number.
Based on the same concept of the above method, referring to fig. 8, a schematic structural diagram of an electronic device according to an embodiment of the present application is provided, where the electronic device includes at least one processor 802, and a memory 801 connected or coupled to the at least one processor 802, and further, the electronic device may further include a communication interface 803. The electronic device may interact with other devices via communication interface 803.
By way of example, the communication interface 803 may be a transceiver, a circuit, a bus, a module, a pin, or other type of communication interface. When the electronic device is a chip-type device or circuit, the communication interface 803 in the electronic device may also be an input/output circuit, and may input information (or called receiving information) and output information (or called transmitting information), and the processor may be an integrated processor or a microprocessor or an integrated circuit or a logic circuit, and the processor may determine the output information according to the input information.
The coupling in the embodiments of the present application is an indirect coupling or communication connection between devices, units, or modules, which may be in electrical, mechanical, or other forms for information interaction between the devices, units, or modules. The processor 802 may cooperate with the memory 801 and the communication interface 803. The specific connection medium between the processor 802, the memory 801, and the communication interface 803 is not limited in the present application.
Optionally, referring to fig. 8, the processor 802, the memory 801 and the communication interface 803 are connected to each other through a bus. The bus may be a peripheral component interconnect standard (peripheral component interconnect, PCI) bus or an extended industry standard architecture (extended industry standard architecture, EISA) bus, or the like. The buses may be classified as address buses, data buses, control buses, etc. For ease of illustration, only one thick line is shown in fig. 8, but not only one bus or one type of bus.
In an embodiment of the present application, the memory 801 is used as a non-volatile computer readable storage medium for storing non-volatile software programs, non-volatile computer executable programs, and modules. The Memory 801 may include at least one type of storage medium, and may include, for example, flash Memory, hard disk, multimedia card, card Memory, random access Memory (Random Access Memory, RAM), static random access Memory (Static Random Access Memory, SRAM), programmable Read-Only Memory (Programmable Read Only Memory, PROM), read-Only Memory (ROM), charged erasable programmable Read-Only Memory (Electrically Erasable Programmable Read-Only Memory, EEPROM), magnetic Memory, magnetic disk, optical disk, and the like. Memory 801 is any other medium that can be used to carry or store desired program code in the form of instructions or data structures and that can be accessed by a computer, but is not limited thereto. The memory 801 in the embodiments of the present application may also be circuitry or any other device capable of implementing a storage function for storing instructions, computer programs, and/or data.
In an embodiment of the present application, the processor 802 may be a general-purpose processor, such as a Central Processing Unit (CPU), digital signal processor, application specific integrated circuit, field programmable gate array or other programmable logic device, discrete gate or transistor logic device, discrete hardware components, and may implement or perform the methods, steps, and logic blocks disclosed in the embodiments of the present application. The general purpose processor may be a microprocessor or any conventional processor or the like. The steps of the satellite control method disclosed in connection with the embodiment of the application can be directly embodied as being executed by a hardware processor or by a combination of hardware and software modules in the processor.
The code corresponding to the satellite control method described in the foregoing embodiment may be cured into the chip by programming the processor 802, so that the chip can execute the steps of the satellite control method when running, and how to program the processor 802 is a technology known to those skilled in the art will not be repeated here.
In one or more embodiments, the memory 801 stores instructions executable by the at least one processor 802, and the at least one processor 802 may implement steps of any of the methods described above by invoking instructions or computer programs stored in the memory 801.
Embodiments of the present application also provide a computer-readable storage medium having stored thereon computer instructions which, when run on a computer, cause the computer to perform the steps of any of the methods described above.
Based on the same inventive concept, embodiments of the present application also provide a computer program product comprising: computer program code which, when run on a computer, causes the computer to perform the satellite control method as any of the preceding discussion. Since the principle of the solution of the problem of the computer program product is similar to that of the satellite control method, the implementation of the computer program product can be referred to as implementation of the method, and the repetition is omitted.
Those of ordinary skill in the art will appreciate that: all or part of the steps for implementing the method embodiments described above may be performed by hardware associated with program instructions. The foregoing program may be stored in a computer readable storage medium. The program, when executed, performs steps including the method embodiments described above; and the aforementioned storage medium includes: various media that can store program code, such as ROM, RAM, magnetic or optical disks.
While specific embodiments of the application have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and the scope of the application is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the application, but such changes and modifications fall within the scope of the application. While preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiments and all such alterations and modifications as fall within the scope of the application.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present application without departing from the scope of the application. Thus, it is intended that the present application also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.

Claims (10)

1. A satellite control method, comprising:
after receiving satellite control information, M satellite domains in a target satellite network send the satellite control information to the satellite domains which do not receive the satellite control information in the target satellite network through inter-domain routing among the satellite domains; the target satellite network comprises N satellite domains, wherein N is a positive integer not smaller than M, and the satellite domains are divided according to the communication gain of the satellite for the corresponding satellite domains; the communication gain is used for representing the gain provided by the satellite to the corresponding satellite domain in terms of link connectivity and link reliability;
And returning satellite control confirmation information when all the N satellite domains receive the satellite control information.
2. The method of claim 1, wherein the satellite domains are partitioned according to the following method:
determining a maximum number of satellites in the satellite domain based on a total number of satellites in the target satellite network and a total cost function; the total cost function is used for describing the control cost and interaction cost of the target satellite network;
for each satellite domain, the following operations are performed:
determining at least one candidate satellite which has a direct link with a satellite in a satellite sub-domain according to the link connection relation between satellites in the target satellite network;
calculating the communication gain of the candidate satellite for the satellite domain according to the link reliability parameter and the connectivity parameter of the candidate satellite; the link reliability parameter is used for representing the link on-off probability of the candidate satellite;
and selecting candidate satellites based on the communication gain, and adding the candidate satellites into the satellite sub-domain until the number of satellites in the satellite sub-domain reaches the maximum number of satellites.
3. The method according to claim 2, wherein for each candidate satellite, calculating the communication gain of the corresponding candidate satellite for the one satellite domain according to the link reliability parameter and the connectivity parameter, respectively, comprises:
For each candidate satellite, the following operations are performed:
determining a connectivity parameter of a candidate satellite according to the number of adjacent satellites with direct links with the candidate satellite in the target satellite network; the connectivity parameter is positively correlated with the number of adjacent satellites;
and calculating the communication gain of the candidate satellite according to the communication parameter, the prestored maximum communication of the target satellite network and the prestored link reliability parameter of the candidate satellite.
4. The method of claim 2, wherein selecting candidate satellites for addition to the one satellite domain based on the connected gain comprises:
determining the priority of the candidate satellite according to the principle that the priority is higher corresponding to the larger communication gain;
and selecting the candidate satellite with the highest priority to join the satellite sub-domain.
5. The method of claim 4, wherein determining the priority of the candidate satellite according to the principle that the higher the communication gain corresponds to the higher priority comprises:
when a plurality of candidate satellites with equal communication gains exist, determining the priority of the candidate satellites with equal communication gains according to the principle that the priority is higher corresponding to the smaller satellite identification.
6. The method of any of claims 2-5, wherein determining a maximum number of satellites in a satellite domain based on a total number of satellites in the target satellite network and a total cost function comprises:
determining a total cost function of the target satellite network based on inter-domain interaction cost, inter-domain satellite interaction cost and total number of satellites by taking the number of satellite domains as a variable;
based on the total cost function, taking the total cost of the target satellite network as an optimization target, and determining the optimal domain division number;
the maximum number of satellites is determined based on the total number of satellites and the optimal number of domains.
7. The method of claim 6, wherein the determining an optimal number of domains based on the total cost function with the objective of reducing the total cost of the objective satellite network as an optimization objective comprises:
taking the value of the satellite domain number from 1 to the whole number of the total number of the satellites according to the total cost function, and obtaining the total cost of the satellite network corresponding to the value of each satellite domain number;
and determining the minimum value of the total cost of the satellite network by comparing the obtained total cost of the satellite network, and taking the satellite domain number value corresponding to the minimum value as the optimal domain number.
8. A satellite control device, comprising:
a receiving unit, configured to make M satellites in a target satellite network receive satellite control information in a domain division manner;
an inter-domain routing unit, configured to send the satellite control information to a satellite domain in which the satellite control information is not received in the target satellite network through inter-domain routing between satellite domains; the target satellite network comprises N satellite domains, wherein N is a positive integer not smaller than M, and the satellite domains are divided according to the communication gain of the satellite for the corresponding satellite domains; the communication gain is used for representing the gain provided by the satellite to the corresponding satellite domain in terms of link connectivity and link reliability;
and the sending unit is used for returning satellite control confirmation information when the satellite control information is received by all the N satellite domains.
9. An electronic device, comprising:
a memory for storing computer instructions;
a processor connected to the memory for executing computer instructions in the memory and for implementing the method of any one of claims 1 to 7 when the computer instructions are executed.
10. A computer-readable storage medium, comprising:
the computer readable storage medium stores computer instructions which, when run on a computer, cause the computer to perform the method of any one of claims 1 to 7.
CN202311021256.6A 2023-08-14 2023-08-14 Satellite control method and device and electronic equipment Pending CN117081648A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117278110A (en) * 2023-11-20 2023-12-22 上海卫星互联网研究院有限公司 Island satellite processing method, device and equipment of satellite network

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117278110A (en) * 2023-11-20 2023-12-22 上海卫星互联网研究院有限公司 Island satellite processing method, device and equipment of satellite network
CN117278110B (en) * 2023-11-20 2024-02-02 上海卫星互联网研究院有限公司 Island satellite processing method, device and equipment of satellite network

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