Constellation network reliability simulation method and system based on streaming computation

Abstract

The invention provides a constellation network reliability simulation method and system based on streaming computation, which can set simulation parameters and automatically construct a data table based on the simulation parameters. And generating a first data element including a satellite health state matrix, a same-orbit link state matrix and a cross-orbit link state matrix corresponding to the plurality of target satellites once at an interval of a preset simulation step length. And in response to generation of any first data element, calculating a second data element corresponding to any first data element based on any first data element. The second data element comprises a connected state matrix and an off-network rate of each target satellite. And in response to generation of any second data element, calculating a third data element corresponding to any second data element. The third data element comprises any second data element converted into the preset format. And in response to generation of any third data element, storing any third data element into the data table. The simulation efficiency can be improved, and the high-efficiency and multi-round simulation requirements can be met.

Description

Technical Field

[0001] The present invention relates to the technical field of industrial big data and system reliability simulation, and in particular to a constellation network reliability simulation method and system based on streaming computing. Background Art

[0002] Satellite constellations usually contain hundreds, thousands, or even tens of thousands of satellite nodes. Complex network topologies can be formed through inter-satellite links. Reliability simulation can be used to achieve reliability design of satellite constellations.

[0003] The conventional reliability simulation process is a serial process. The simulation proceeds according to a certain step size. In the constellation network reliability simulation, the step size is generally set to 1 hour by default. Each step performs the following simulation calculations: First, the status of all nodes and intersatellite links in the constellation is simulated and sampled, and the satellite health (normal / failure) state matrix and link (on / off) state matrix are obtained at each simulation step based on the network replenishment strategy and link repair strategy. Then, based on the satellite health state matrix and link state matrix, the connectivity status of each satellite with other satellites is calculated to find out the satellites that are out of the network, and the satellite disconnection rate is calculated accordingly. Finally, the reliability of the entire network topology is evaluated based on the satellite disconnection rate time series.

[0004] However, when the process data and result data involved in each step of the simulation need to be written into the database synchronously, the conventional serial simulation program will run slower and it will be difficult to meet the requirements of high-efficiency, multi-round simulation. Summary of the invention

[0005] The present invention provides a constellation network reliability simulation method and system based on streaming computing, which can improve simulation efficiency.

[0006] The technical solution of the present invention to solve the above technical problems is as follows:

[0007] On the one hand, the present invention provides a constellation network reliability simulation method based on streaming computing, in which simulation parameters are set. The simulation parameters include parameters associated with the simulation target constellation and parameters associated with the execution of the simulation. The target constellation includes multiple target satellites and multiple orbits, and the multiple target satellites include key satellites and ordinary satellites. The key satellite is a satellite used for communicating with the earth, and the ordinary satellite communicates with the earth indirectly through the key satellite. Based on the simulation parameters, a data table is automatically constructed. The simulation step size is preset at each interval, and a first data element is generated once based on the simulation parameters and preset rules. The first data element includes a satellite health state matrix, a co-orbit link state matrix, and a cross-orbit link state matrix corresponding to multiple target satellites. The satellite health state matrix is ​​used to characterize the state of each target satellite, and the state of the target satellite includes a normal state and an abnormal state. The satellite in the normal state has a communication function, and the satellite in the abnormal state loses the communication function. The co-orbit link state matrix is ​​used to characterize the state of the co-orbit link corresponding to each target satellite, and the cross-orbit link state matrix is ​​used to characterize the state of the cross-orbit link corresponding to each key satellite; the state of the co-orbit link and the state of the cross-orbit link both include a connected state and an interrupted state. In response to generating a target first data element, based on the target first data element, a second data element corresponding to the target first data element is calculated. The target first data element is the first data element generated at any time, and the second data element corresponding to the target first data element includes a connectivity state matrix and an off-network rate of each target satellite. In response to generating a target second data element, a third data element corresponding to the target second data element is calculated, and the target second data element is the second data element generated at any time. The third data element corresponding to the target second data element includes the target second data element converted into a preset format. In response to generating a target third data element, the target third data element is stored in the data table.

[0008] Based on the above technical solution, the present invention can also be improved as follows.

[0009] Furthermore, the simulation parameters include the number of multiple orbits, the number of target satellites operating on any orbit, the number of cross-orbit links, the average failure interval between each inter-satellite link interruption, the repair time of each inter-satellite link interruption, the average failure interval between each target satellite, the satellite network repair interval of each target satellite, the simulation step size, the simulation round, the identification of the target constellation and the position of each key satellite. Among them, the inter-satellite link is a communication link between two adjacent target satellites in the constellation network topology diagram.

[0010] Further, a preset number of data table fields are set, a preset number of data table fields are updated based on the simulation parameters, and a data table is generated based on the updated preset number of data table fields.

[0011] Further, the first satellite health status matrix, the first satellite failure duration matrix, the first co-orbit link interruption duration matrix, the first cross-orbit link interruption duration matrix, the first co-orbit link state matrix and the first cross-orbit link state matrix corresponding to the multiple target satellites are obtained. Wherein, if the first data element is generated for the first time, the first satellite health status matrix is ​​a preset initial satellite health status matrix, the first satellite failure duration matrix is ​​a preset initial satellite failure duration matrix, the first co-orbit link interruption duration matrix is ​​a preset initial co-orbit link interruption duration matrix, the first cross-orbit link interruption duration matrix is ​​a preset initial cross-orbit link interruption duration matrix, the first co-orbit link state matrix is ​​a preset initial co-orbit link state matrix, and the first cross-orbit link state matrix is ​​a preset initial cross-orbit link state matrix. If the first data element is generated for the Nth time, the first satellite health status matrix is ​​the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link status matrix is ​​the on-orbit link status matrix included in the first data element determined for the N-1th time, the first cross-orbit link status matrix is ​​the cross-orbit link status matrix included in the first data element determined for the N-1th time, the first satellite failure duration matrix is ​​determined based on the satellite health status matrix included in the first data element determined for the N-2th time and the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link interruption duration matrix is ​​determined based on the on-orbit link status matrix included in the first data element determined for the N-2th time and the on-orbit link status matrix included in the first data element determined for the N-1th time, and the first cross-orbit link interruption duration matrix is ​​determined based on the cross-orbit link status matrix included in the first data element determined for the N-2th time and the cross-orbit link status matrix included in the first data element determined for the N-1th time, and N is greater than or equal to 2.

[0012] Based on the failure probability of each target satellite, the first satellite failure duration matrix and the satellite network repair interval, the first satellite health state matrix is ​​updated to obtain the satellite health state matrix. Based on the first satellite health state matrix and the satellite health state matrix, the first satellite failure duration matrix is ​​updated.

[0013] For any orbit, determine the first target satellite and the second target satellite on any orbit. The first target satellite is a target satellite in an abnormal state after this step of simulation. The second target satellite is a target satellite in an abnormal state before this step of simulation and in a normal state after this step of simulation. Determine the co-orbital link coupled with the state of the first target satellite and the co-orbital link coupled with the state of the second target satellite. Based on the state of the co-orbital link coupled with the state of the first target satellite and the state of the co-orbital link coupled with the state of the second target satellite, update the data corresponding to the co-orbital link coupled with the state of the first target satellite in the first co-orbital link state matrix, and update the data corresponding to the co-orbital link coupled with the state of the second target satellite in the first co-orbital link state matrix to obtain the second co-orbital link state matrix. Determine the third co-orbital link in the target constellation, and the co-orbital link coupled with the state of the first target satellite and the co-orbital link coupled with the state of the second target satellite are different from the third co-orbital link. Based on the link interruption probability, the first co-orbital link interruption duration matrix, and the repair time of the inter-satellite link interruption, update the data corresponding to the third co-orbital link in the second co-orbital link state matrix to obtain the co-orbital link state matrix. Based on the first co-track link state matrix and the co-track link status matrix, the first co-track link interruption duration matrix is ​​updated.

[0014] Determine the cross-track link coupled with the state of the first target satellite and the cross-track link coupled with the state of the second target satellite. Based on the state of the cross-track link coupled with the state of the first target satellite and the state of the cross-track link coupled with the state of the second target satellite, update the data corresponding to the cross-track link coupled with the state of the first target satellite in the first cross-track link state matrix, and update the data corresponding to the cross-track link coupled with the state of the second target satellite in the first cross-track link state matrix to obtain the second cross-track link state matrix. Determine the third cross-track link in the target constellation, and the cross-track link coupled with the state of the first target satellite and the cross-track link coupled with the state of the second target satellite are different from the third cross-track link. Based on the link interruption probability, the first cross-track link interruption duration matrix, and the repair time of the inter-satellite link interruption, update the data corresponding to the third cross-track link in the second cross-track link state matrix to obtain the cross-track link state matrix. Based on the first cross-track link state matrix and the cross-track link state matrix, update the first cross-track link interruption duration matrix.

[0015] A first data element is generated based on a satellite health status matrix, a co-orbit link status matrix, and a cross-orbit link status matrix.

[0016] Further, in response to generating the target first data element, based on the co-orbit link state matrix, the cross-orbit link state matrix, and the position of each key satellite included in the target first data element, the adjacency matrix corresponding to each key satellite is determined. The adjacency matrix is ​​converted into a reachable matrix. Based on the reachable matrix, the backbone network is determined. The backbone network is a network including the largest number of key satellites, and any two key satellites in the backbone network are reachable. Based on the backbone network, the offline state of each key satellite is determined. For any orbit, based on the offline state of the key satellite included in any orbit, the connectivity state between the ordinary satellite included in any orbit and the backbone network is determined. Based on the connectivity state between the ordinary satellites on each orbit and the backbone network, the connectivity state matrix and the offline rate of each target satellite are determined. Based on the connectivity state matrix and the offline rate of each target satellite, the second data element corresponding to the target first data element is determined.

[0017] On the other hand, the present invention provides a constellation network reliability simulation system based on streaming computing, including: a simulation configuration module, which is used to set simulation parameters. The simulation parameters include parameters associated with the simulation target constellation and parameters associated with executing the simulation. The target constellation includes multiple target satellites and multiple orbits; the multiple target satellites include key satellites and ordinary satellites, the key satellites are satellites used to communicate with the earth, and the ordinary satellites communicate with the earth indirectly through key satellites. An automatic table building module is used to automatically build a data table based on the simulation parameters. A custom data source module is used to generate a first data element once based on the simulation parameters and preset rules at each preset simulation step. The first data element includes a satellite health status matrix, a co-orbit link status matrix, and a cross-orbit link status matrix corresponding to multiple target satellites. The satellite health status matrix is ​​used to characterize the status of each target satellite, and the status of the target satellite includes a normal state and an abnormal state. The satellite in the normal state has a communication function, and the satellite in the abnormal state loses the communication function. The co-orbit link status matrix is ​​used to characterize the status of the co-orbit link corresponding to each target satellite, and the cross-orbit link status matrix is ​​used to characterize the status of the cross-orbit link corresponding to each key satellite; the status of the co-orbit link and the status of the cross-orbit link both include a connected state and an interrupted state;

[0018] A first conversion operator module is used for calculating, in response to generating a target first data element, a second data element corresponding to the target first data element based on the target first data element. The target first data element is the first data element generated at any time, and the second data element corresponding to the target first data element includes a connectivity state matrix and an off-network rate of each target satellite;

[0019] A second conversion operator module is used to calculate a third data element corresponding to the target second data element in response to generating a target second data element, where the target second data element is any second data element generated at any time. The third data element corresponding to the target second data element includes the target second data element converted into a preset format;

[0020] The data sink module is used for storing the target third data element into the data table in response to generating the target third data element.

[0021] Based on the above technical solution, the present invention can also be improved as follows.

[0022] Furthermore, the simulation parameters include the number of multiple orbits, the number of target satellites operating on any orbit, the number of cross-orbit links, the average failure interval between each inter-satellite link interruption, the repair time of each inter-satellite link interruption, the average failure interval between each target satellite, the satellite network repair interval of each target satellite, the simulation step size, the simulation round, the identification of the target constellation and the position of each key satellite. Among them, the inter-satellite link is a communication link between two adjacent target satellites in the constellation network topology diagram.

[0023] Further, the automatic table creation module is specifically used to set a preset number of data table fields, update a preset number of data table fields based on the simulation parameters, and generate a data table based on the updated preset number of data table fields.

[0024] Further, the custom data source module is specifically used to obtain the first satellite health status matrix, the first satellite failure duration matrix, the first co-orbit link interruption duration matrix, the first cross-orbit link interruption duration matrix, the first co-orbit link state matrix and the first cross-orbit link state matrix corresponding to multiple target satellites. Wherein, if the first data element is generated for the first time, the first satellite health status matrix is ​​a preset initial satellite health status matrix, the first satellite failure duration matrix is ​​a preset initial satellite failure duration matrix, the first co-orbit link interruption duration matrix is ​​a preset initial co-orbit link interruption duration matrix, the first cross-orbit link interruption duration matrix is ​​a preset initial cross-orbit link interruption duration matrix, the first co-orbit link state matrix is ​​a preset initial co-orbit link state matrix, and the first cross-orbit link state matrix is ​​a preset initial cross-orbit link state matrix. If the first data element is generated for the Nth time, the first satellite health status matrix is ​​the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link status matrix is ​​the on-orbit link status matrix included in the first data element determined for the N-1th time, the first cross-orbit link status matrix is ​​the cross-orbit link status matrix included in the first data element determined for the N-1th time, the first satellite failure duration matrix is ​​determined based on the satellite health status matrix included in the first data element determined for the N-2th time and the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link interruption duration matrix is ​​determined based on the on-orbit link status matrix included in the first data element determined for the N-2th time and the on-orbit link status matrix included in the first data element determined for the N-1th time, and the first cross-orbit link interruption duration matrix is ​​determined based on the cross-orbit link status matrix included in the first data element determined for the N-2th time and the cross-orbit link status matrix included in the first data element determined for the N-1th time, and N is greater than or equal to 2.

[0025] Based on the failure probability of each target satellite, the first satellite failure duration matrix and the satellite network repair interval, the first satellite health state matrix is ​​updated to obtain the satellite health state matrix. Based on the first satellite health state matrix and the satellite health state matrix, the first satellite failure duration matrix is ​​updated.

[0026] For any orbit, determine the first target satellite and the second target satellite on any orbit. The first target satellite is a target satellite in an abnormal state after this step of simulation. The second target satellite is a target satellite in an abnormal state before this step of simulation and in a normal state after this step of simulation. Determine the co-orbital link coupled with the state of the first target satellite and the co-orbital link coupled with the state of the second target satellite. Based on the state of the co-orbital link coupled with the state of the first target satellite and the state of the co-orbital link coupled with the state of the second target satellite, update the data corresponding to the co-orbital link coupled with the state of the first target satellite in the first co-orbital link state matrix, and update the data corresponding to the co-orbital link coupled with the state of the second target satellite in the first co-orbital link state matrix to obtain the second co-orbital link state matrix. Determine the third co-orbital link in the target constellation, and the co-orbital link coupled with the state of the first target satellite and the co-orbital link coupled with the state of the second target satellite are different from the third co-orbital link. Based on the link interruption probability, the first co-orbital link interruption duration matrix, and the repair time of the inter-satellite link interruption, update the data corresponding to the third co-orbital link in the second co-orbital link state matrix to obtain the co-orbital link state matrix. Based on the first co-track link state matrix and the co-track link status matrix, the first co-track link interruption duration matrix is ​​updated.

[0027] Determine the cross-track link coupled with the state of the first target satellite and the cross-track link coupled with the state of the second target satellite. Based on the state of the cross-track link coupled with the state of the first target satellite and the state of the cross-track link coupled with the state of the second target satellite, update the data corresponding to the cross-track link coupled with the state of the first target satellite in the first cross-track link state matrix, and update the data corresponding to the cross-track link coupled with the state of the second target satellite in the first cross-track link state matrix to obtain the second cross-track link state matrix. Determine the third cross-track link in the target constellation, and the cross-track link coupled with the state of the first target satellite and the cross-track link coupled with the state of the second target satellite are different from the third cross-track link. Based on the link interruption probability, the first cross-track link interruption duration matrix, and the repair time of the inter-satellite link interruption, update the data corresponding to the third cross-track link in the second cross-track link state matrix to obtain the cross-track link state matrix. Based on the first cross-track link state matrix and the cross-track link state matrix, update the first cross-track link interruption duration matrix.

[0028] A first data element is generated based on a satellite health status matrix, a co-orbit link status matrix, and a cross-orbit link status matrix.

[0029] Further, the first conversion operator module is specifically used to determine the adjacency matrix corresponding to each key satellite based on the co-orbit link state matrix, the cross-orbit link state matrix, and the position of each key satellite included in the target first data element in response to generating the target first data element. The adjacency matrix is ​​converted into a reachable matrix. Based on the reachable matrix, the backbone network is determined. The backbone network is a network including the largest number of key satellites, and any two key satellites in the backbone network are reachable. Based on the backbone network, the offline state of each key satellite is determined. For any orbit, based on the offline state of the key satellite included in any orbit, the connectivity state between the ordinary satellite included in any orbit and the backbone network is determined. Based on the connectivity state between the ordinary satellites on each orbit and the backbone network, the connectivity state matrix and the offline rate of each target satellite are determined. Based on the connectivity state matrix and the offline rate of each target satellite, the second data element corresponding to the target first data element is determined.

[0030] The beneficial effects of the present invention are as follows: the present invention includes S1, setting simulation parameters; S2, automatically constructing a data table based on the simulation parameters. S3, generating a first data element once at each preset simulation step length based on the simulation parameters and preset rules. S4, in response to generating a target first data element, calculating a second data element corresponding to the target first data element based on the target first data element. S5, in response to generating a target second data element, calculating a third data element corresponding to the target second data element. S6, in response to generating a target third data element, storing the target third data element in the data table.

[0031] Among them, S1-S2 is the preparation link before the constellation network reliability simulation program is executed, and the execution of each step of the simulation includes all the links of S3-S6. Conventional serial simulation programs must execute the corresponding processing links of S3-S6 in order in each step before entering the next step of simulation. In the present invention, after each link of S3-S6 completes its own current step simulation task, it can automatically enter the next step of simulation after sending the data elements to the downstream, without waiting for all links of S3-S6 to be processed before entering the next step of simulation. It can improve the simulation efficiency and meet the requirements of high-efficiency and multi-round simulation. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 A schematic diagram of a constellation network topology;

[0033] Figure 2 A schematic diagram of a flow chart of a constellation network reliability simulation method based on streaming computing provided by the present invention;

[0034] Figure 3 A schematic diagram of a process for generating a first data element provided by the present invention;

[0035] Figure 4A schematic diagram of the structure of a custom data source module provided by the present invention;

[0036] Figure 5 A schematic diagram of a process for generating a second data element provided by the present invention;

[0037] Figure 6 A schematic diagram of the structure of a constellation network reliability simulation system based on streaming computing provided by the present invention;

[0038] Figure 7 A schematic diagram of the result of printing the first data element to the console provided by the present invention;

[0039] Figure 8 The figure is a schematic diagram of the curve of the network disconnection rate in 5 tests provided by the present invention. DETAILED DESCRIPTION

[0040] The technical solutions in the embodiments of the present application will be described below in conjunction with the drawings in the embodiments of the present application. Among them, in the description of the present application, unless otherwise specified, " / " indicates that the objects associated before and after are in an "or" relationship, for example, A / B can represent A or B; "and / or" in the present application is only a description of the association relationship of the associated objects, indicating that there can be three relationships, for example, A and / or B, which can represent: A exists alone, A and B exist at the same time, and B exists alone, where A and B can be singular or plural. And, in the description of the present application, unless otherwise specified, "multiple" refers to two or more than two. "At least one of the following" or similar expressions refers to any combination of these items, including any combination of single items or plural items. For example, at least one of a, b, or c can represent: a, b, c, ab, ac, bc, or abc, where a, b, c can be single or multiple. In addition, in order to facilitate the clear description of the technical solutions of the embodiments of the present application, in the embodiments of the present application, the words "first", "second" and the like are used to distinguish between the same items or similar items with substantially the same functions and effects. Those skilled in the art will understand that the words "first", "second" and the like do not limit the quantity and execution order, and the words "first", "second" and the like do not necessarily limit the differences. At the same time, in the embodiments of the present application, the words "exemplary" or "for example" are used to indicate examples, illustrations or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or design.

[0041] Currently, the world's aerospace powers are proposing and gradually implementing various large / giant satellite constellation construction projects and plans, and the technological innovation and transformation of the next generation of global Internet is quietly taking place. Satellite constellations usually contain hundreds, thousands, or even tens of thousands of satellite nodes, and form a complex network topology through intersatellite links. In actual engineering, the satellite constellation network topology is generally a non-complete grid type, with StarLink and Iridium as typical representatives. In the case of non-complete grid topology, see Figure 1 , the satellites in the constellation are divided into key satellites (e.g., satellite 101) and ordinary satellites (e.g., satellite 102). Among them, the satellites connected across orbits are key satellites, and other satellites in the same orbit are ordinary satellites. With the increase in the number of satellite nodes and inter-satellite links in the constellation, the reliability assessment of the constellation network faces major challenges. Traditional reliability analysis methods, such as reliability block diagrams and fault tree analysis, are not sufficient to support the reliability assessment of large-scale satellite constellation networks.

[0042] As the satellite constellation continues to operate in orbit, intersatellite link interruptions and satellite node failures will occur from time to time, causing changes in the constellation network topology. The spatiotemporal distribution characteristics of link interruptions and node failures have a very important and complex impact on the reliability of network operation. Therefore, when designing constellation network solutions, it is necessary to rely on reliability simulation methods and related software to evaluate the reliability level of the network and efficiently collect a large amount of process data and result data generated by reliability simulation.

[0043] The conventional reliability simulation process is a serial process. The simulation proceeds according to a certain step size. In the constellation network reliability simulation, the step size is generally set to 1 hour by default. Each step performs the following simulation calculations: First, the status of all nodes and intersatellite links in the constellation is simulated and sampled, and the satellite health (normal / failure) state matrix and link (on / off) state matrix are obtained at each simulation step based on the network replenishment strategy and link repair strategy. Then, based on the satellite health state matrix and link state matrix, the connectivity status of each satellite with other satellites is calculated to find out the satellites that are out of the network, and the satellite disconnection rate is calculated accordingly. Finally, the reliability of the entire network topology is evaluated based on the satellite disconnection rate time series.

[0044] However, when the process data and result data involved in each step of the simulation need to be written into the database synchronously, the conventional serial simulation program will run slower and it will be difficult to meet the requirements of high-efficiency, multi-round simulation.

[0045] In view of the above problems, the present invention provides a constellation network reliability simulation method and system based on streaming computing, which can improve the simulation efficiency and meet the requirements of high-efficiency and multi-round simulation.

[0046] See also Figure 2The constellation network reliability simulation method based on streaming computing provided by the present invention includes the following steps S201-S206:

[0047] S201: Setting simulation parameters.

[0048] The simulation parameters include parameters associated with the simulation target constellation and parameters associated with executing the simulation. The target constellation includes multiple target satellites and multiple orbits. The multiple target satellites include key satellites and ordinary satellites. The key satellites are satellites used for communicating with the earth. Ordinary satellites communicate with the earth indirectly through key satellites. Multiple key satellites and multiple ordinary satellites can operate on each orbit.

[0049] In some embodiments, when conducting constellation network reliability simulation analysis, there are many parameter setting issues, including network topology parameters, basic reliability parameters, simulation execution parameters, etc. Specifically, the simulation parameters that can be set include the number of multiple orbits M, the number of target satellites N running on any orbit, the number of cross-orbit links K, the average failure interval time linkMtbf of each inter-satellite link interruption, the repair time of each inter-satellite link interruption, the average failure interval time satMtbf of each target satellite, the satellite network repair interval time of each target satellite, the simulation step size, the simulation round, the identification of the target constellation, and the position of each key satellite, etc. Among them, the inter-satellite link is the communication link between two adjacent target satellites in the constellation network topology diagram.

[0050] In some embodiments, after setting the simulation parameters, a parameter configuration file corresponding to each simulation parameter may be generated, wherein the parameter configuration file includes the simulation parameters converted into a preset parameter format.

[0051] S202: Automatically construct a data table based on the simulation parameters.

[0052] Under the streaming computing paradigm, each data element needs to be written into the database in real time. Each simulation step of the constellation network reliability simulation generates corresponding process data and result data, which need to be written into the database after each step of the simulation is completed. Since the configuration parameters of the constellation network reliability simulation are different, a matching table needs to be established in the database before each simulation is executed. In order to save the tedious process of manual table creation by the user, in some embodiments, a preset number of data table fields can be set. Based on the simulation parameters, a preset number of data table fields are updated. Based on the updated preset number of data table fields, a data table is generated. That is, the embodiment of the present application can save the tedious process of manual creation of data tables by users, and can realize automatic creation of data tables.

[0053] Exemplarily, the process of automatically creating a data table in an embodiment of the present application is described in detail below.

[0054] First, you can get the timestamp of the start of the simulation program execution, accurate to milliseconds, and define the table name with the prefix string "consimul_", such as "consimul_1724039488785". Then, you can design the corresponding fields, for example, set the following 8 fields:

[0055] ts timestamp(3), this field is the timestamp corresponding to each simulation step;

[0056] cons_id int, this field is the key of the constellation;

[0057] simul_step, this field is the simulation process;

[0058] sathealth char(n1), this field is the satellite health status string, converted from the matrix, n1 = M*N, bound to the configuration parameters;

[0059] ordlink char(n2), this field is the same track link status string, converted from the matrix, n2 = M*N, bound to the configuration parameters;

[0060] keylink char(n3), this field is the cross-track link status string, converted from the matrix, n3 = M*K, bound to the configuration parameters;

[0061] satlink char(n4), this field is the satellite connectivity status string, converted from the matrix, n4 = M*N, bound to the configuration parameters;

[0062] satdiscrate double, this field is the satellite disconnection rate.

[0063] From the above content, it can be seen that when the satellite health status, co-orbit link status, and cross-orbit link status in the satellite constellation simulation configuration parameters change, the data types of the corresponding table fields sathealth, ordlink, and keylink must be adjusted (updated). These are configuration parameter binding fields, and the benefits of automatically creating tables through the program are obvious.

[0064] S203: Generate a first data element once at each preset simulation step based on simulation parameters and preset rules.

[0065] Among them, the first data element includes a satellite health status matrix, a co-orbit link status matrix and a cross-orbit link status matrix corresponding to multiple target satellites. The satellite health status matrix is ​​used to characterize the status of each target satellite. The status of the target satellite includes a normal state and an abnormal state. The satellite in the normal state has the communication function, and the satellite in the abnormal state loses the communication function. The co-orbit link status matrix is ​​used to characterize the status of the co-orbit link corresponding to each target satellite, and the cross-orbit link status matrix is ​​used to characterize the status of the cross-orbit link corresponding to each key satellite; the status of the co-orbit link and the status of the cross-orbit link both include a connected state and an interrupted state.

[0066] In some embodiments, a first satellite health status matrix, a first satellite failure duration matrix, a first co-orbit link interruption duration matrix, a first cross-orbit link interruption duration matrix, a first co-orbit link state matrix, and a first cross-orbit link state matrix corresponding to multiple target satellites may be obtained.

[0067] Among them, if the first data element is generated for the first time, the first satellite health status matrix is ​​the preset initial satellite health status matrix, the first satellite failure duration matrix is ​​the preset initial satellite failure duration matrix, the first on-orbit link interruption duration matrix is ​​the preset initial on-orbit link interruption duration matrix, the first cross-orbit link interruption duration matrix is ​​the preset initial cross-orbit link interruption duration matrix, the first on-orbit link state matrix is ​​the preset initial on-orbit link state matrix, and the first cross-orbit link state matrix is ​​the preset initial cross-orbit link state matrix.

[0068] If the first data element is generated for the Nth time, the first satellite health status matrix is ​​the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link status matrix is ​​the on-orbit link status matrix included in the first data element determined for the N-1th time, the first cross-orbit link status matrix is ​​the cross-orbit link status matrix included in the first data element determined for the N-1th time, the first satellite failure duration matrix is ​​determined based on the satellite health status matrix included in the first data element determined for the N-2th time and the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link interruption duration matrix is ​​determined based on the on-orbit link status matrix included in the first data element determined for the N-2th time and the on-orbit link status matrix included in the first data element determined for the N-1th time, and the first cross-orbit link interruption duration matrix is ​​determined based on the cross-orbit link status matrix included in the first data element determined for the N-2th time and the cross-orbit link status matrix included in the first data element determined for the N-1th time, and N is greater than or equal to 2.

[0069] The first satellite health state matrix can be updated based on the failure probability of each target satellite, the first satellite failure duration matrix and the satellite network repair interval to obtain a satellite health state matrix. Based on the first satellite health state matrix and the satellite health state matrix, the first satellite failure duration matrix is ​​updated.

[0070] For any orbit, the first target satellite and the second target satellite on any orbit can be determined. The first target satellite is a target satellite in an abnormal state after this step of simulation. The second target satellite is a target satellite in an abnormal state before this step of simulation and in a normal state after this step of simulation. Determine the co-orbital link coupled with the state of the first target satellite and the co-orbital link coupled with the state of the second target satellite. Based on the state of the co-orbital link coupled with the state of the first target satellite and the state of the co-orbital link coupled with the state of the second target satellite, update the data corresponding to the co-orbital link coupled with the state of the first target satellite in the first co-orbital link state matrix, and update the data corresponding to the co-orbital link coupled with the state of the second target satellite in the first co-orbital link state matrix to obtain the second co-orbital link state matrix. Determine the third co-orbital link in the target constellation, and the co-orbital link coupled with the state of the first target satellite and the co-orbital link coupled with the state of the second target satellite are different from the third co-orbital link. Based on the link interruption probability, the first co-orbital link interruption duration matrix, and the repair time of the inter-satellite link interruption, update the data corresponding to the third co-orbital link in the second co-orbital link state matrix to obtain the co-orbital link state matrix. Based on the first co-track link state matrix and the co-track link status matrix, the first co-track link interruption duration matrix is ​​updated.

[0071] It is also possible to determine a cross-track link coupled with the state of the first target satellite and a cross-track link coupled with the state of the second target satellite. Based on the state of the cross-track link coupled with the state of the first target satellite and the state of the cross-track link coupled with the state of the second target satellite, update the data corresponding to the cross-track link coupled with the state of the first target satellite in the first cross-track link state matrix, and update the data corresponding to the cross-track link coupled with the state of the second target satellite in the first cross-track link state matrix to obtain the second cross-track link state matrix. Determine a third cross-track link in the target constellation, and the cross-track link coupled with the state of the first target satellite and the cross-track link coupled with the state of the second target satellite are different from the third cross-track link. Based on the link interruption probability, the first cross-track link interruption duration matrix, and the repair time of the intersatellite link interruption, update the data corresponding to the third cross-track link in the second cross-track link state matrix to obtain the cross-track link state matrix. Based on the first cross-track link state matrix and the cross-track link state matrix, update the first cross-track link interruption duration matrix.

[0072] The first data element may be generated based on a satellite health status matrix, a co-orbit link status matrix, and a cross-orbit link status matrix.

[0073] For example, the following is combined Figure 3 , describes in detail the process of generating the first data element in the embodiment of the present application. Among them, the embodiment of the present application can generate the first data element through a custom data source module. Figure 4 As shown, the custom data source module may include a constructor submodule, a run() function submodule, and a cancel() function submodule.

[0074] Among them, the constructor submodule can be used to:

[0075] Extract simulation parameters from the class input parameters, which are configuration parameters packaged into the sample class "ConsSimulParams";

[0076] Define the variable running as a marker to control the run() function loop;

[0077] Based on satMtbf, linkMtbf and the simulation step size (the default is 1 hour), the satellite failure probability and link interruption probability for sampling are calculated respectively.

[0078] The run() function submodule is the core part of the custom data source module. The main body is a double-layer nested loop. The outer loop controls the simulation execution rounds, and the inner loop controls the simulation step. The running variable controls the loop termination. The run() function submodule can be used for:

[0079] At the beginning of each simulation cycle, the matrices involved in the simulation are initialized. The satellite health status matrix satHealth (matrix dimension M×N) is initialized to a matrix of all 1s (1 indicates normal, 0 indicates abnormal), and the satellite failure time matrix satFailureTime (matrix dimension M×N) is initialized to a matrix of all 0s.

[0080] The link status matrix linkOrd (matrix dimension M×N) of the same track is initialized to a matrix of all 1s (1 indicates connectivity, 0 indicates interruption), and the link interruption duration matrix delinkOrdTime (matrix dimension M×N) of the same track is initialized to a matrix of all 0s.

[0081] The cross-track link state matrix linkKey (matrix dimension M×K) is initialized to an all-1 matrix (1 indicates connectivity, 0 indicates interruption), and the cross-track link interruption duration matrix delinkKeyTime (matrix dimension M×K) is initialized to an all-0 matrix.

[0082] In each simulation step, the matrix satHealth and the matrix satFailureTime must first be operated. SatHealth is updated according to the satellite failure probability and the satellite failure duration matrix, and satFailureTime is updated according to the changes in satHealth before and after the current step.

[0083] Then, the matrix linkOrd and the matrix delinkOrdTime need to be operated in the same way as the satellite node related matrix update operation. The difference is that it is necessary to identify the links coupled with the satellite nodes from the M×N co-orbit links. Two aspects need to be considered: on the one hand, find out the satellite nodes that fail at the end of this simulation step. The links directly related to them are all disconnected, and this simulation step has no effect on their state changes; on the other hand, find out the normal satellite nodes that fail at the beginning of this simulation step. The links directly related to them are all normal, and this simulation step has no effect on their states.

[0084] Similarly, finally, the above method should be used to perform relevant operations on the matrix linkKey and the matrix delinkKeyTime.

[0085] The current timestamp, constellation ID, simulation step, satHealth, linkOrd, and linkKey are packaged into "ConstellationSourceData" and output. The loop sleeps for 1ms to arrange the event time of each simulation source data in ascending order to facilitate subsequent data element processing.

[0086] The cancel() function submodule performs only one process, which is to set the variable running to false.

[0087] S204: In response to generating a target first data element, based on the target first data element, determine a second data element corresponding to the target first data element.

[0088] The target first data element is the first data element generated at any time, and the second data element corresponding to the target first data element includes the connectivity state matrix and the offline rate of each target satellite.

[0089] The embodiment of the present application is different from the serial simulation program, and the data source simulation and subsequent processing steps can be processed in a distributed manner, which can greatly improve the simulation efficiency. In the embodiment of the present application, after reading any first data element, the first data element can be calculated, and the connectivity state matrix and the disconnection rate of the target satellite can be obtained based on the multiple state matrices in the first data element.

[0090] For details, see Figure 5In response to generating the target first data element, based on the co-orbit link state matrix, the cross-orbit link state matrix, and the position of each key satellite included in the target first data element, the adjacency matrix corresponding to each key satellite is determined. The adjacency matrix is ​​converted into a reachable matrix. Based on the reachable matrix, a backbone network is determined. The backbone network is a network including the largest number of key satellites, and any two key satellites in the backbone network are reachable. Based on the backbone network, the offline state of each key satellite is determined.

[0091] For any orbit, the connectivity status between the common satellites included in any orbit and the backbone network is determined based on the offline status of the key satellites included in any orbit.

[0092] Based on the connectivity status between the common satellites on each orbit and the backbone network, the connectivity status matrix and the network disconnection rate of each target satellite are determined. Based on the connectivity status matrix and the network disconnection rate of each target satellite, the second data element corresponding to the target first data element is determined.

[0093] S205: In response to generating the target second data element, determining a third data element corresponding to the target second data element.

[0094] The target second data element is a second data element generated at any time. The third data element corresponding to the target second data element includes the target second data element converted into a preset format.

[0095] Since the second data element contains a large number of matrix elements, these matrices cannot be directly stored in the database. In order to compress the data storage space as much as possible, the second data element needs to be converted into a data format that is easy to store, that is, converted into a corresponding third data element. The third data element includes a string formed by concatenating row by row, and the length of the string matches the format of the data table.

[0096] S206: In response to generating the target third data element, storing the target third data element into the data table.

[0097] Among them, the addSink function of Flink itself can be called to write the obtained third data element into the data table one by one in real time according to the stream computing method.

[0098] It can be seen that in the constellation network reliability simulation method based on streaming computing provided in the embodiment of the present application, S201-S202 is the preparation link before the constellation network reliability simulation program is executed, and the execution of each step of the simulation includes all the links of S203-S206. In the conventional serial simulation program, each step must execute the corresponding processing links of S203-S206 in sequence before entering the next step of simulation. In the present invention, after each link of S203-S206 processes its own current step simulation task and sends the data element to the downstream, it can enter the next step of simulation by itself, without waiting for all the links of S203-S206 to be processed before entering the next step of simulation. It can improve the simulation efficiency and meet the requirements of high efficiency and multi-round simulation.

[0099] On the other hand, the present invention provides a constellation network reliability simulation system based on streaming computing, see Figure 6 , including a simulation configuration module, an automatic table creation module, a custom data source module, a first conversion operator module, a second conversion operator module and a data sink module.

[0100] The simulation configuration module is used to set simulation parameters.

[0101] The simulation parameters include parameters associated with the simulation target constellation and parameters associated with executing the simulation. The target constellation includes multiple target satellites and multiple orbits; the multiple target satellites include key satellites and ordinary satellites. The key satellites are satellites used for communicating with the earth, and the ordinary satellites communicate with the earth indirectly through the key satellites.

[0102] The automatic table building module is used to automatically build data tables based on simulation parameters.

[0103] The custom data source module is used to preset the simulation step size at each interval and generate a first data element once based on simulation parameters and preset rules.

[0104] Among them, the first data element includes a satellite health status matrix, a co-orbit link status matrix and a cross-orbit link status matrix corresponding to multiple target satellites. The satellite health status matrix is ​​used to characterize the status of each target satellite. The status of the target satellite includes a normal state and an abnormal state. The satellite in the normal state has the communication function, and the satellite in the abnormal state loses the communication function. The co-orbit link status matrix is ​​used to characterize the status of the co-orbit link corresponding to each target satellite, and the cross-orbit link status matrix is ​​used to characterize the status of the cross-orbit link corresponding to each key satellite; the status of the co-orbit link and the status of the cross-orbit link both include a connected state and an interrupted state.

[0105] The first conversion operator module is used for, in response to generating a target first data element, calculating a second data element corresponding to the target first data element based on the target first data element.

[0106] The target first data element is the first data element generated at any time, and the second data element corresponding to the target first data element includes the connectivity state matrix and the offline rate of each target satellite.

[0107] The second conversion operator module is used for calculating a third data element corresponding to the target second data element in response to generating the target second data element.

[0108] The target second data element is a second data element generated at any time. The third data element corresponding to the target second data element includes the target second data element converted into a preset format.

[0109] The data sink module is used for storing the target third data element into the data table in response to generating the target third data element.

[0110] In some embodiments, the simulation parameters include the number of multiple orbits, the number of target satellites operating on any orbit, the number of cross-orbit links, the average failure interval between each intersatellite link interruption, the repair time of each intersatellite link interruption, the average failure interval between each target satellite, the satellite network repair interval of each target satellite, the simulation step size, the simulation round, the identification of the target constellation, and the position of each key satellite, etc. Among them, the intersatellite link is a communication link between two adjacent target satellites in the constellation network topology diagram.

[0111] In some embodiments, the automatic table creation module is specifically used to set a preset number of data table fields, update the preset number of data table fields based on the simulation parameters, and generate a data table based on the updated preset number of data table fields.

[0112] In some embodiments, the custom data source module is specifically used to obtain the first satellite health status matrix, the first satellite failure duration matrix, the first co-orbit link interruption duration matrix, the first cross-orbit link interruption duration matrix, the first co-orbit link state matrix, and the first cross-orbit link state matrix corresponding to multiple target satellites. Wherein, if the first data element is generated for the first time, the first satellite health status matrix is ​​a preset initial satellite health status matrix, the first satellite failure duration matrix is ​​a preset initial satellite failure duration matrix, the first co-orbit link interruption duration matrix is ​​a preset initial co-orbit link interruption duration matrix, the first cross-orbit link interruption duration matrix is ​​a preset initial cross-orbit link interruption duration matrix, the first co-orbit link state matrix is ​​a preset initial co-orbit link state matrix, and the first cross-orbit link state matrix is ​​a preset initial cross-orbit link state matrix. If the first data element is generated for the Nth time, the first satellite health status matrix is ​​the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link status matrix is ​​the on-orbit link status matrix included in the first data element determined for the N-1th time, the first cross-orbit link status matrix is ​​the cross-orbit link status matrix included in the first data element determined for the N-1th time, the first satellite failure duration matrix is ​​determined based on the satellite health status matrix included in the first data element determined for the N-2th time and the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link interruption duration matrix is ​​determined based on the on-orbit link status matrix included in the first data element determined for the N-2th time and the on-orbit link status matrix included in the first data element determined for the N-1th time, and the first cross-orbit link interruption duration matrix is ​​determined based on the cross-orbit link status matrix included in the first data element determined for the N-2th time and the cross-orbit link status matrix included in the first data element determined for the N-1th time, and N is greater than or equal to 2.

[0113] Based on the failure probability of each target satellite, the first satellite failure duration matrix and the satellite network repair interval, the first satellite health state matrix is ​​updated to obtain the satellite health state matrix. Based on the first satellite health state matrix and the satellite health state matrix, the first satellite failure duration matrix is ​​updated.

[0114] For any orbit, determine the first target satellite and the second target satellite on any orbit. The first target satellite is a target satellite in an abnormal state after this step of simulation. The second target satellite is a target satellite in an abnormal state before this step of simulation and in a normal state after this step of simulation. Determine the co-orbital link coupled with the state of the first target satellite and the co-orbital link coupled with the state of the second target satellite. Based on the state of the co-orbital link coupled with the state of the first target satellite and the state of the co-orbital link coupled with the state of the second target satellite, update the data corresponding to the co-orbital link coupled with the state of the first target satellite in the first co-orbital link state matrix, and update the data corresponding to the co-orbital link coupled with the state of the second target satellite in the first co-orbital link state matrix to obtain the second co-orbital link state matrix. Determine the third co-orbital link in the target constellation, and the co-orbital link coupled with the state of the first target satellite and the co-orbital link coupled with the state of the second target satellite are different from the third co-orbital link. Based on the link interruption probability, the first co-orbital link interruption duration matrix, and the repair time of the inter-satellite link interruption, update the data corresponding to the third co-orbital link in the second co-orbital link state matrix to obtain the co-orbital link state matrix. Based on the first co-track link state matrix and the co-track link status matrix, the first co-track link interruption duration matrix is ​​updated.

[0115] Determine the cross-track link coupled with the state of the first target satellite and the cross-track link coupled with the state of the second target satellite. Based on the state of the cross-track link coupled with the state of the first target satellite and the state of the cross-track link coupled with the state of the second target satellite, update the data corresponding to the cross-track link coupled with the state of the first target satellite in the first cross-track link state matrix, and update the data corresponding to the cross-track link coupled with the state of the second target satellite in the first cross-track link state matrix to obtain the second cross-track link state matrix. Determine the third cross-track link in the target constellation, and the cross-track link coupled with the state of the first target satellite and the cross-track link coupled with the state of the second target satellite are different from the third cross-track link. Based on the link interruption probability, the first cross-track link interruption duration matrix, and the repair time of the inter-satellite link interruption, update the data corresponding to the third cross-track link in the second cross-track link state matrix to obtain the cross-track link state matrix. Based on the first cross-track link state matrix and the cross-track link state matrix, update the first cross-track link interruption duration matrix.

[0116] A first data element is generated based on a satellite health status matrix, a co-orbit link status matrix, and a cross-orbit link status matrix.

[0117] For the description of the custom data source module, please refer to the description of the custom data source module in the aforementioned method embodiment, which will not be repeated here.

[0118] In some embodiments, the first conversion operator module is specifically used to determine the adjacency matrix corresponding to each key satellite based on the co-orbit link state matrix, the cross-orbit link state matrix, and the position of each key satellite included in the target first data element in response to generating the target first data element. The adjacency matrix is ​​converted into a reachable matrix. Based on the reachable matrix, the backbone network is determined. The backbone network is a network including the largest number of key satellites, and any two key satellites in the backbone network are reachable. Based on the backbone network, the offline state of each key satellite is determined. For any orbit, based on the offline state of the key satellite included in any orbit, the connectivity state between the ordinary satellite included in any orbit and the backbone network is determined. Based on the connectivity state between the ordinary satellites on each orbit and the backbone network, the connectivity state matrix and the offline rate of each target satellite are determined. Based on the connectivity state matrix and the offline rate of each target satellite, the second data element corresponding to the target first data element is determined.

[0119] In some schemes, multiple embodiments of the present application can be combined, and the combined scheme can be implemented. Optionally, some operations in the process of each method embodiment are optionally combined, and / or the order of some operations is optionally changed. In addition, the execution order between the steps of each process is only exemplary and does not constitute a restriction on the execution order between the steps. There can also be other execution orders between the steps. It is not intended to indicate that the execution order is the only order in which these operations can be performed. A person of ordinary skill in the art will think of a variety of ways to reorder the operations described herein. In addition, it should be noted that the process details involved in a certain embodiment of this article are also applicable to other embodiments in a similar manner, or different embodiments can be used in combination.

[0120] In addition, some steps in the method embodiment may be equivalently replaced by other possible steps. Alternatively, some steps in the method embodiment may be optional and may be deleted in certain usage scenarios. Alternatively, other possible steps may be added to the method embodiment. Furthermore, the method embodiments may be implemented separately or in combination.

[0121] The following is a detailed description of the example verification of the constellation network reliability simulation method and system based on streaming computing provided by the present invention.

[0122] 1. Constellation network reliability simulation test configuration

[0123] The stream computing program is tested based on the simulation configuration in the previous example. The topology diagram of the constellation under this configuration can be found in Figure 1The constellation consists of 10 orbits, with 21 ordinary satellites and 3 key node satellites on each orbital plane. In addition, the constellation has 3 cross-orbit links. The MTBF of link interruption is set to 1000 hours, and the link repair time is 24 hours; the MTBF of satellite failure is set to 43800 hours, and the satellite network repair time is 720 hours; the simulation is executed for 10000 steps, that is, the constellation is simulated to operate on orbit for 10000 hours.

[0124] 2. Test items and test methods

[0125] The main test items and their test methods are shown in Table 1:

[0126] Table 1

[0127]

[0128] 3. Test process and results

[0129] 1. Custom data source test

[0130] in accordance with Figure 2 , run the steps S201-S203 of the Flink program, read the first data element generated, and print the result to the console as follows Figure 7 shown.

[0131] The test results show:

[0132] The first data element contains the timestamp, constellation ID, simulation step, satellite health status matrix, co-orbit link status matrix, and cross-orbit link status matrix;

[0133] The timestamps are increasing, the simulation step size increases correctly, and the data is not out of order;

[0134] The program takes about 22 seconds to run;

[0135] The time difference between the last data and the first data is 18320ms.

[0136] 2. Test of the first conversion operator module

[0137] in accordance with Figure 2 The process runs steps S201-S204 of the Flink program to generate the second data element, which can be printed to the console normally.

[0138] The test results show:

[0139] The source data elements include timestamp, constellation ID, simulation step, satellite health status matrix, co-orbit link status matrix, cross-orbit link status matrix, satellite connectivity status matrix and satellite disconnection rate;

[0140] The timestamps are increasing, the simulation step size increases correctly, and the data is not out of order;

[0141] The program takes about 25 seconds to run;

[0142] The time difference between the last data and the first data is 18375ms.

[0143] 3. Simulation overall test

[0144] in accordance with Figure 2 The whole process of running the Flink program (steps S201-S206) was carried out to test the program running time including writing to the database. A total of 5 tests were performed. The test results are shown in Table 2 below.

[0145] Table 2

[0146]

[0147] It can be seen that the average time taken to run the whole process is about 74 seconds. Checking the database, the data corresponding to the five simulations can be written into the data table normally.

[0148] 4. Offline rate test

[0149] In the data table, the off-line rate data of the five tests can be exported and the off-line rate curves can be drawn respectively (for example, see Figure 8 ). Among them, the off-grid rate ≤ 5% can be used as the constellation reliability evaluation standard, and the average constellation reliability value obtained after 5 simulations is 80.6%.

[0150] Through the description of the above implementation methods, technical personnel in the relevant field can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional modules is used as an example. In actual applications, the above-mentioned functions can be assigned to different functional modules as needed, that is, the internal structure of the system can be divided into different functional modules to complete all or part of the functions described above.

[0151] In the several embodiments provided in the present application, it should be understood that the disclosed systems and methods can be implemented in other ways. For example, the system embodiments described above are only schematic. For example, the division of the modules or units is only a logical function division. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of systems or units, which can be electrical, mechanical or other forms.

[0152] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0153] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a readable storage medium. Based on this understanding, the technical solution of the embodiment of the present application is essentially or the part that contributes or all or part of the technical solution can be embodied in the form of a software product, which is stored in a storage medium, including several instructions to enable a device (which can be a single-chip microcomputer, chip, etc.) or a processor (processor) to perform all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read only memory (ROM), random access memory (RAM), disk or optical disk and other media that can store program code.

[0154] The above contents are only specific implementation methods of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present application shall be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A constellation network reliability simulation method based on streaming computing, characterized in that: include: Setting simulation parameters; the simulation parameters include parameters associated with a simulation target constellation and parameters associated with executing the simulation; The target constellation includes a plurality of target satellites and a plurality of orbits; the plurality of target satellites include key satellites and common satellites, the key satellites are satellites used for communicating with the earth, and the common satellites communicate with the earth indirectly through the key satellites; Automatically construct a data table based on the simulation parameters; At each interval, a preset simulation step length is set, and a first data element is generated once based on the simulation parameters and preset rules; The first data element includes a satellite health status matrix, a co-orbit link status matrix, and a cross-orbit link status matrix corresponding to the multiple target satellites; the satellite health status matrix is ​​used to characterize the status of each of the target satellites, and the status of the target satellite includes a normal state and an abnormal state; The satellite in the normal state has a communication function, and the satellite in the abnormal state loses the communication function; the on-orbit link state matrix is ​​used to characterize the state of the on-orbit link corresponding to each of the target satellites, and the cross-orbit link state matrix is ​​used to characterize the state of the cross-orbit link corresponding to each of the key satellites; the state of the on-orbit link and the state of the cross-orbit link both include a connected state and an interrupted state; In response to generating a target first data element, calculating a second data element corresponding to the target first data element based on the target first data element; The target first data element is the first data element generated at any time; The second data element corresponding to the target first data element includes a connectivity state matrix and a disconnection rate of each target satellite; In response to generating a target second data element, calculating a third data element corresponding to the target second data element; The target second data element is the second data element generated at any time; The third data element corresponding to the target second data element includes the target second data element converted into a preset format; In response to generating a target third data element, the target third data element is stored in the data table.

2. The method according to claim 1, characterized in that The simulation parameters include the number of the multiple orbits, the number of target satellites operating on any orbit, the number of cross-orbit links, the average failure interval between interruptions of each inter-satellite link, the repair time of each inter-satellite link interruption, the average failure interval between each of the target satellites, the satellite network reconnection interval between each of the target satellites, the preset simulation step size, the simulation round, the identification of the target constellation and the position of each of the key satellites; the inter-satellite link is a communication link between two adjacent target satellites in the constellation network topology diagram.

3. The method according to claim 2, characterized in that The method of automatically constructing a data table based on the simulation parameters comprises: Set a preset number of data table fields; Based on the simulation parameters, updating the preset number of data table fields; The data table is generated based on the updated preset number of data table fields.

4. The method according to claim 3, characterized in that The preset simulation step length per interval, generating a first data element once based on the simulation parameters and preset rules, comprises: Obtain a first satellite health status matrix, a first satellite failure duration matrix, a first on-orbit link interruption duration matrix, a first cross-orbit link interruption duration matrix, a first on-orbit link state matrix, and a first cross-orbit link state matrix corresponding to the multiple target satellites; wherein, if the first data element is generated for the first time, the first satellite health status matrix is ​​a preset initial satellite health status matrix, the first satellite failure duration matrix is ​​a preset initial satellite failure duration matrix, the first on-orbit link interruption duration matrix is ​​a preset initial on-orbit link interruption duration matrix, the first cross-orbit link interruption duration matrix is ​​a preset initial cross-orbit link interruption duration matrix, the first on-orbit link state matrix is ​​a preset initial on-orbit link state matrix, and the first cross-orbit link state matrix is ​​a preset initial cross-orbit link state matrix; if the first data element is generated for the Nth time, the first satellite health status matrix is ​​the first data element determined for the N-1th time. The satellite health status matrix included, the first on-orbit link status matrix is ​​the on-orbit link status matrix included in the first data element determined for the N-1th time, the first cross-orbit link status matrix is ​​the cross-orbit link status matrix included in the first data element determined for the N-1th time, the first satellite failure duration matrix is ​​determined based on the satellite health status matrix included in the first data element determined for the N-2th time and the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link interruption duration matrix is ​​determined based on the on-orbit link status matrix included in the first data element determined for the N-2th time and the on-orbit link status matrix included in the first data element determined for the N-1th time, the first cross-orbit link interruption duration matrix is ​​determined based on the cross-orbit link status matrix included in the first data element determined for the N-2th time and the cross-orbit link status matrix included in the first data element determined for the N-1th time, and N is greater than or equal to 2; Based on the failure probability of each of the target satellites, the first satellite failure duration matrix and the satellite network repair interval, the first satellite health status matrix is ​​updated to obtain the satellite health status matrix; Based on the first satellite health status matrix and the satellite health status matrix, updating the first satellite failure duration matrix; For any of the orbits, determine a first target satellite and a second target satellite on the orbit; the first target satellite is the target satellite that is in an abnormal state after the simulation in this step; the second target satellite is the target satellite that is in an abnormal state before the simulation in this step and is in a normal state after the simulation in this step; determining a co-orbital link coupled to a state of the first target satellite and a co-orbital link coupled to a state of the second target satellite; Based on the state of the co-orbital link coupled with the state of the first target satellite and the state of the co-orbital link coupled with the state of the second target satellite, updating the data corresponding to the co-orbital link coupled with the state of the first target satellite in the first co-orbital link state matrix, and updating the data corresponding to the co-orbital link coupled with the state of the second target satellite in the first co-orbital link state matrix to obtain a second co-orbital link state matrix; Determining a third co-orbital link in the target constellation, wherein the co-orbital link coupled to the state of the first target satellite and the co-orbital link coupled to the state of the second target satellite are both different from the third co-orbital link; Based on the link interruption probability, the first co-orbit link interruption duration matrix, and the repair time of the inter-satellite link interruption, updating the data corresponding to the third co-orbit link in the second co-orbit link state matrix to obtain the co-orbit link state matrix; Based on the first co-track link state matrix and the first co-track link state matrix, updating the first co-track link interruption duration matrix; Determining a cross-orbit link coupled to a state of the first target satellite and a cross-orbit link coupled to a state of the second target satellite; Based on the state of the cross-orbit link coupled with the state of the first target satellite and the state of the cross-orbit link coupled with the state of the second target satellite, updating the data corresponding to the cross-orbit link coupled with the state of the first target satellite in the first cross-orbit link state matrix, and updating the data corresponding to the cross-orbit link coupled with the state of the second target satellite in the first cross-orbit link state matrix to obtain a second cross-orbit link state matrix; Determining a third cross-orbit link in the target constellation, wherein the cross-orbit link coupled to the state of the first target satellite and the cross-orbit link coupled to the state of the second target satellite are both different from the third cross-orbit link; Based on the link interruption probability, the first cross-track link interruption duration matrix, and the repair time of the inter-satellite link interruption, updating the data corresponding to the third cross-track link in the second cross-track link state matrix to obtain the cross-track link state matrix; Based on the first cross-track link state matrix and the cross-track link state matrix, updating the first cross-track link interruption duration matrix; The first data element is generated based on the satellite health status matrix, the co-orbit link status matrix, and the cross-orbit link status matrix.

5. The method according to claim 4, characterized in that In response to generating a target first data element, calculating a second data element corresponding to the target first data element based on the target first data element includes: In response to generating the target first data element, determining an adjacency matrix corresponding to each of the key satellites based on the on-orbit link state matrix, the cross-orbit link state matrix, and the position of each of the key satellites included in the target first data element; Converting the adjacency matrix into a reachability matrix; Based on the reachable matrix, a backbone network is determined; the backbone network is a network including the largest number of the key satellites; any two of the key satellites in the backbone network are reachable; Based on the backbone network, determining the offline status of each of the key satellites; For any one of the orbits, based on the offline state of the key satellite included in the any one of the orbits, determining the connectivity state between the common satellite included in the any one of the orbits and the backbone network; Determining a connectivity matrix and a disconnection rate of each target satellite based on connectivity between the common satellites on each orbit and the backbone network; Based on the connectivity state matrix and the network disconnection rate of each of the target satellites, a second data element corresponding to the target first data element is determined.

6. A constellation network reliability simulation system based on streaming computing, characterized in that: include: A simulation configuration module, used to set simulation parameters; the simulation parameters include parameters associated with the simulation target constellation and parameters associated with executing the simulation; The target constellation includes a plurality of target satellites and a plurality of orbits; the plurality of target satellites include key satellites and common satellites, the key satellites are satellites used for communicating with the earth, and the common satellites communicate with the earth indirectly through the key satellites; An automatic table building module, used for automatically building a data table based on the simulation parameters; A custom data source module, used for generating a first data element once at each preset simulation step based on the simulation parameters and preset rules; The first data element includes a satellite health status matrix, a co-orbit link status matrix, and a cross-orbit link status matrix corresponding to the multiple target satellites; the satellite health status matrix is ​​used to characterize the status of each of the target satellites, and the status of the target satellite includes a normal state and an abnormal state; The satellite in the normal state has a communication function, and the satellite in the abnormal state loses the communication function; the on-orbit link state matrix is ​​used to characterize the state of the on-orbit link corresponding to each of the target satellites, and the cross-orbit link state matrix is ​​used to characterize the state of the cross-orbit link corresponding to each of the key satellites; the state of the on-orbit link and the state of the cross-orbit link both include a connected state and an interrupted state; a first conversion operator module, configured to, in response to generating a target first data element, calculate a second data element corresponding to the target first data element based on the target first data element; The target first data element is the first data element generated at any time; The second data element corresponding to the target first data element includes a connectivity state matrix and a disconnection rate of each target satellite; a second conversion operator module, configured to calculate, in response to generating a target second data element, a third data element corresponding to the target second data element; The target second data element is the second data element generated at any time; The third data element corresponding to the target second data element includes the target second data element converted into a preset format; The data sink module is used for storing the target third data element into the data table in response to generating the target third data element.

7. The system according to claim 6, characterized in that The simulation parameters include the number of the multiple orbits, the number of target satellites operating on any orbit, the number of cross-orbit links, the average failure interval between interruptions of each intersatellite link, the repair time of each intersatellite link interruption, the average failure interval between each of the target satellites, the satellite network reconnection interval of each of the target satellites, the simulation step size, the simulation rounds, the identification of the target constellation and the position of each of the key satellites; the intersatellite link is a communication link between two adjacent target satellites in the constellation network topology diagram.

8. The system according to claim 7, characterized in that The automatic table building module is used to automatically build a data table based on the simulation parameters, specifically for: Set a preset number of data table fields; Based on the simulation parameters, updating the preset number of data table fields; The data table is generated based on the updated preset number of data table fields.

9. The system according to claim 8, characterized in that The custom data source module is used to preset a simulation step size at each interval, and to generate a first data element based on the simulation parameters and preset rules, specifically for: Obtain a first satellite health status matrix, a first satellite failure duration matrix, a first on-orbit link interruption duration matrix, a first cross-orbit link interruption duration matrix, a first on-orbit link state matrix, and a first cross-orbit link state matrix corresponding to the multiple target satellites; wherein, if the first data element is generated for the first time, the first satellite health status matrix is ​​a preset initial satellite health status matrix, the first satellite failure duration matrix is ​​a preset initial satellite failure duration matrix, the first on-orbit link interruption duration matrix is ​​a preset initial on-orbit link interruption duration matrix, the first cross-orbit link interruption duration matrix is ​​a preset initial cross-orbit link interruption duration matrix, the first on-orbit link state matrix is ​​a preset initial on-orbit link state matrix, and the first cross-orbit link state matrix is ​​a preset initial cross-orbit link state matrix; if the first data element is generated for the Nth time, the first satellite health status matrix is ​​the first data element determined for the N-1th time. The satellite health status matrix included, the first on-orbit link status matrix is ​​the on-orbit link status matrix included in the first data element determined for the N-1th time, the first cross-orbit link status matrix is ​​the cross-orbit link status matrix included in the first data element determined for the N-1th time, the first satellite failure duration matrix is ​​determined based on the satellite health status matrix included in the first data element determined for the N-2th time and the satellite health status matrix included in the first data element determined for the N-1th time, the first on-orbit link interruption duration matrix is ​​determined based on the on-orbit link status matrix included in the first data element determined for the N-2th time and the on-orbit link status matrix included in the first data element determined for the N-1th time, the first cross-orbit link interruption duration matrix is ​​determined based on the cross-orbit link status matrix included in the first data element determined for the N-2th time and the cross-orbit link status matrix included in the first data element determined for the N-1th time, and N is greater than or equal to 2; Based on the failure probability of each of the target satellites, the first satellite failure duration matrix and the satellite network repair interval, the first satellite health status matrix is ​​updated to obtain the satellite health status matrix; Based on the first satellite health status matrix and the satellite health status matrix, updating the first satellite failure duration matrix; For any of the orbits, determine a first target satellite and a second target satellite on the orbit; the first target satellite is the target satellite that is in an abnormal state after the simulation in this step; the second target satellite is the target satellite that is in an abnormal state before the simulation in this step and is in a normal state after the simulation in this step; determining a co-orbital link coupled to a state of the first target satellite and a co-orbital link coupled to a state of the second target satellite; Based on the state of the co-orbital link coupled with the state of the first target satellite and the state of the co-orbital link coupled with the state of the second target satellite, updating the data corresponding to the co-orbital link coupled with the state of the first target satellite in the first co-orbital link state matrix, and updating the data corresponding to the co-orbital link coupled with the state of the second target satellite in the first co-orbital link state matrix to obtain a second co-orbital link state matrix; Determining a third co-orbital link in the target constellation, wherein the co-orbital link coupled to the state of the first target satellite and the co-orbital link coupled to the state of the second target satellite are both different from the third co-orbital link; Based on the link interruption probability, the first co-orbit link interruption duration matrix, and the repair time of the inter-satellite link interruption, updating the data corresponding to the third co-orbit link in the second co-orbit link state matrix to obtain the co-orbit link state matrix; Based on the first co-track link state matrix and the first co-track link state matrix, updating the first co-track link interruption duration matrix; Determining a cross-orbit link coupled to a state of the first target satellite and a cross-orbit link coupled to a state of the second target satellite; Based on the state of the cross-orbit link coupled with the state of the first target satellite and the state of the cross-orbit link coupled with the state of the second target satellite, updating the data corresponding to the cross-orbit link coupled with the state of the first target satellite in the first cross-orbit link state matrix, and updating the data corresponding to the cross-orbit link coupled with the state of the second target satellite in the first cross-orbit link state matrix to obtain a second cross-orbit link state matrix; Determining a third cross-orbit link in the target constellation, wherein the cross-orbit link coupled to the state of the first target satellite and the cross-orbit link coupled to the state of the second target satellite are both different from the third cross-orbit link; Based on the link interruption probability, the first cross-track link interruption duration matrix, and the repair time of the inter-satellite link interruption, updating the data corresponding to the third cross-track link in the second cross-track link state matrix to obtain the cross-track link state matrix; Based on the first cross-track link state matrix and the cross-track link state matrix, updating the first cross-track link interruption duration matrix; The first data element is generated based on the satellite health status matrix, the co-orbit link status matrix, and the cross-orbit link status matrix.

10. The system according to claim 9, characterized in that The first conversion operator module is used to calculate, in response to generating a target first data element, a second data element corresponding to the target first data element based on the target first data element, specifically for: In response to generating the target first data element, determining an adjacency matrix corresponding to each of the key satellites based on the on-orbit link state matrix, the cross-orbit link state matrix, and the position of each of the key satellites included in the target first data element; Converting the adjacency matrix into a reachability matrix; Based on the reachable matrix, a backbone network is determined; the backbone network is a network including the largest number of the key satellites; any two of the key satellites in the backbone network are reachable; Based on the backbone network, determining the offline status of each of the key satellites; For any one of the orbits, based on the offline state of the key satellite included in the any one of the orbits, determining the connectivity state between the common satellite included in the any one of the orbits and the backbone network; Determining a connectivity matrix and a disconnection rate of each target satellite based on connectivity between the common satellites on each orbit and the backbone network; Based on the connectivity state matrix and the network disconnection rate of each of the target satellites, a second data element corresponding to the target first data element is determined.

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