Low-orbit satellite routing processing method, device and satellite for intersatellite solar transit interruption

Abstract

The present application provides a low-orbit satellite routing processing method, device and satellite for inter-satellite solar transit interruption, which is used to efficiently and accurately generate a route table by combining static solar transit link status information and dynamic abnormal link status information. The method includes: the first satellite obtains the solar transit link status information sent by the ground processing center, the solar transit link status information is used to indicate the link status between the first satellite and the second satellite under the solar transit phenomenon, the second satellite includes the adjacent satellites of the first satellite, and the number of the second satellites is multiple; the first satellite updates the abnormal link status information, the abnormal link status information is used to indicate the real-time link status between the first satellite and the second satellite; the first satellite integrates the solar transit link status information and the abnormal link status information to obtain the inter-satellite link status information; the first satellite generates a routing table based on the inter-satellite link status information, and the routing table is used to indicate the shortest network path from the first satellite to the second satellite.

Description

Technical Field

[0001] The present application relates to the field of communications, and in particular to a low-orbit satellite routing processing method, device and satellite for inter-satellite solar transit interruption. Background Art

[0002] With the development of space technologies such as polymer cameras, synthetic aperture radars, and large-capacity satellite communications, the amount of information transmitted by various spacecraft has increased exponentially. The microwave-based communication methods currently used by satellites can no longer meet the corresponding needs. In addition, the frequency resources of the space microwave band are very valuable. In recent years, the number of communication satellites has continued to increase, and the frequency resources of satellite communications, especially those used for intersatellite links, have been in short supply. Based on these two reasons, the industry has been prompted to develop in the direction of laser communications.

[0003] Space laser communication is a communication method that uses laser beams as carrier waves to transmit information such as images, voices, and signals in space. It has the advantages of fast transmission rate, large communication capacity, strong anti-interference ability, high security and confidentiality, small system terminal size, light weight, and low power consumption. It has become one of the development trends of future satellite communication links and has triggered a research boom among aerospace powers. Although intersatellite laser transmission has many advantages, the current laser communication payload technology still cannot avoid the solar eclipse problem. When the solar eclipse occurs, the interruption of the intersatellite link will cause the topology of the network to change. This requires the intersatellite routing algorithm to adapt to this change and synchronously update its own routing table to avoid transmission path failure.

[0004] In the process of researching existing related technologies, the inventors found that since intersatellite laser communication payloads are still in the development stage and the technology maturity is relatively low, there are very few satellites that are actually used in orbit, and most of them are still in the technical verification stage and do not involve network routing issues. Therefore, there is very little engineering research on routing changes caused by solar eclipse problems in low-orbit satellite networks, making it difficult to efficiently and stably solve the impact of solar eclipse problems on routing. Summary of the invention

[0005] The present application provides a low-orbit satellite routing processing method, device and satellite for inter-satellite solar transit interruption, which is used to efficiently and accurately generate a routing table by combining static solar transit link status information and dynamic abnormal link status information, thereby solving the impact of the solar transit problem on routing that is difficult to solve in the prior art.

[0006] In a first aspect, the present application provides a low-orbit satellite routing processing method for intersatellite solar transit interruption, the method comprising:

[0007] The first satellite acquires solar transit link status information sent by the ground processing center. The solar transit link status information is processed by the ground processing center. The solar transit link status information is used to indicate the link status between the first satellite and the second satellite under the solar transit phenomenon. The second satellite includes an adjacent satellite of the first satellite, and the number of the second satellites is multiple;

[0008] The first satellite updates abnormal link status information, where the abnormal link status information is used to indicate a real-time link status between the first satellite and the second satellite;

[0009] The first satellite integrates the solar transit link status information and the abnormal link status information to obtain the inter-satellite link status information;

[0010] The first satellite generates a routing table based on the inter-satellite link status information, where the routing table is used to indicate the shortest network path from the first satellite to the second satellite.

[0011] In combination with the first aspect of the present application, in a first possible implementation method of the first aspect of the present application, both the daily link status information and the abnormal link status information are represented by an adjacency matrix. In the adjacency matrix, 1 represents the link connectivity status and 0 represents the link interruption status.

[0012] In combination with the first possible implementation of the first aspect of the present application, in a second possible implementation of the first aspect of the present application, the first satellite fuses the solar transit link status information and the abnormal link status information to obtain the inter-satellite link status information, including:

[0013] The first satellite performs AND operation on the solar transit link status information and the abnormal link status information to obtain the inter-satellite link status information which is also in the form of an adjacency matrix.

[0014] In combination with the first aspect of the present application, in a third possible implementation manner of the first aspect of the present application, the first satellite generates a routing table based on the inter-satellite link state information, including:

[0015] The first satellite searches for the shortest network path from the first satellite to the second satellite based on the inter-satellite link status information;

[0016] The first satellite converts the search results into a routing table.

[0017] In combination with the third possible implementation manner of the first aspect of the present application, in a fourth possible implementation manner of the first aspect of the present application, the first satellite searches for the shortest network path from the first satellite to the second satellite based on the inter-satellite link state information, including:

[0018] The first satellite searches for the shortest network path from the first satellite to the second satellite based on the inter-satellite link status information under the search principle of the Dijkstra algorithm.

[0019] In combination with the first aspect of the present application, in a fifth possible implementation manner of the first aspect of the present application, the first satellite updates the abnormal link state information, including:

[0020] The first satellite periodically sends a link detection signal to an adjacent satellite. If no response signal is received, the first satellite determines that the link is disconnected. If a response signal is received, the first satellite determines that the link is connected.

[0021] The first satellite updates the abnormal link status information based on the link detection signal response result obtained by itself and other abnormal link status information broadcasted by the second satellite. The other abnormal link status information broadcasted by the second satellite is obtained by the second satellite itself.

[0022] In combination with the fifth possible implementation of the first aspect of the present application, in a sixth possible implementation of the first aspect of the present application, the method further includes:

[0023] The first satellite broadcasts abnormal link status information in the satellite topology structure, so that the second satellite generates corresponding abnormal link status information according to the received abnormal link status information combined with the link detection signal response result processed by itself.

[0024] In a second aspect, the present application provides a low-orbit satellite routing processing device for intersatellite solar transit interruption, the device comprising:

[0025] an acquisition unit, used to acquire solar transit link status information sent by a ground processing center, the solar transit link status information being processed by the ground processing center, the solar transit link status information being used to indicate a link status between a first satellite and a second satellite under a solar transit phenomenon, the second satellite including an adjacent satellite of the first satellite, and the number of the second satellites being multiple;

[0026] an updating unit, used for updating abnormal link status information, where the abnormal link status information is used for indicating a real-time link status between the first satellite and the second satellite;

[0027] A fusion unit, used for fusing the transit link status information and the abnormal link status information to obtain the inter-satellite link status information;

[0028] The generating unit is used to generate a routing table based on the inter-satellite link status information, where the routing table is used to indicate the shortest network path from the first satellite to the second satellite.

[0029] In combination with the second aspect of the present application, in a first possible implementation method of the second aspect of the present application, both the daily link status information and the abnormal link status information are represented by an adjacency matrix. In the adjacency matrix, 1 represents the link connectivity status and 0 represents the link interruption status.

[0030] In conjunction with the first possible implementation of the second aspect of the present application, in a second possible implementation of the second aspect of the present application, the fusion unit is specifically used to:

[0031] The solar transit link status information and the abnormal link status information are processed by AND operation to obtain the inter-satellite link status information which is also in the form of an adjacency matrix.

[0032] In combination with the second aspect of the present application, in a third possible implementation manner of the second aspect of the present application, the generating unit is specifically configured to:

[0033] Based on the inter-satellite link status information, searching for the shortest network path from the first satellite to the second satellite;

[0034] Convert the search results into a routing table.

[0035] In combination with the third possible implementation of the second aspect of the present application, in a fourth possible implementation of the second aspect of the present application, the generating unit is specifically configured to:

[0036] Under the search principle of Dijkstra algorithm, based on the inter-satellite link status information, the shortest network path from the first satellite to the second satellite is searched and processed.

[0037] In combination with the second aspect of the present application, in a fifth possible implementation manner of the second aspect of the present application, the updating unit is specifically configured to:

[0038] A link detection signal is periodically sent to an adjacent satellite. If no response signal is received, the first satellite determines that the link is disconnected. If a response signal is received, the first satellite determines that the link is connected.

[0039] The abnormal link status information is updated based on the link detection signal response result obtained by itself and other abnormal link status information broadcasted by the second satellite. The other abnormal link status information broadcasted by the second satellite is obtained by the second satellite itself.

[0040] In combination with the fifth possible implementation manner of the second aspect of the present application, in a sixth possible implementation manner of the second aspect of the present application, the apparatus further includes a broadcasting unit, which is configured to:

[0041] The abnormal link status information is broadcasted in the satellite topology structure, so that the second satellite generates corresponding abnormal link status information according to the received abnormal link status information combined with the link detection signal response result processed by itself.

[0042] In a third aspect, the present application provides a satellite, including a processor and a memory, wherein a computer program is stored in the memory, and when the processor calls the computer program in the memory, the method provided in the first aspect of the present application or any possible implementation method of the first aspect of the present application is executed.

[0043] In a fourth aspect, the present application provides a computer-readable storage medium, which stores multiple instructions, and the instructions are suitable for a processor to load to execute the method provided by the first aspect of the present application or any possible implementation of the first aspect of the present application.

[0044] From the above content, it can be concluded that the present application has the following beneficial effects:

[0045] In response to the solar eclipse problem of the low-orbit satellite network, the present application obtains the solar eclipse link status information sent by the ground processing center on the one hand, and updates the abnormal link status information on the other hand. At this time, the inter-satellite link status information is obtained by fusing the static solar eclipse link status information and the dynamic abnormal link status information, and then a routing table is generated from the inter-satellite link status information. In this way, the routing table is generated efficiently and accurately. In the processing of the routing table, the effective link status inferred by the ground processing center based on the solar eclipse phenomenon and the satellite's own real-time link status inferred are taken into account, thereby solving the impact of the solar eclipse problem on routing that is difficult to solve in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0047] Figure 1 A flowchart of a low-orbit satellite routing processing method for intersatellite solar transit interruption in this application;

[0048] Figure 2 A data structure diagram of the connection matrix of this application;

[0049] Figure 3 A schematic diagram of a scenario for generating and processing a routing table for this application;

[0050] Figure 4 A schematic diagram of a scenario for triggering an update of the routing table for this application;

[0051] Figure 5 A schematic diagram of a scenario of the broadcast mechanism of this application;

[0052] Figure 6 This is another scenario diagram of the broadcast mechanism of this application;

[0053] Figure 7 This is another scenario diagram of the broadcast mechanism of this application;

[0054] Figure 8 This is another scenario diagram of the broadcast mechanism of this application;

[0055] Fig. 9 A schematic diagram of the structure of a low-orbit satellite routing processing device for intersatellite solar transit interruption in this application;

[0056] Fig.10 This is a schematic diagram of the structure of the satellite of this application. DETAILED DESCRIPTION

[0057] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of this application.

[0058] The terms "first", "second", etc. in the specification and claims of this application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments described here can be implemented in an order other than that illustrated or described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or modules is not necessarily limited to those steps or modules clearly listed, but may include other steps or modules that are not clearly listed or inherent to these processes, methods, products or devices. The naming or numbering of steps in this application does not mean that the steps in the method flow must be executed in the time / logical sequence indicated by the naming or numbering. The process steps that have been named or numbered can change the execution order according to the technical purpose to be achieved, as long as the same or similar technical effects can be achieved.

[0059] The division of modules in this application is a logical division. There may be other division methods when it is implemented in actual applications. For example, multiple modules can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, and the indirect coupling or communication connection between modules can be electrical or other similar forms, which are not limited in this application. In addition, the modules or submodules described as separate components may or may not be physically separated, may or may not be physical modules, or may be distributed in multiple circuit modules, and some or all of the modules may be selected according to actual needs to achieve the purpose of the present application.

[0060] Before introducing the low-orbit satellite routing processing method for intersatellite solar transit interruption provided by the present application, the background content involved in the present application is first introduced.

[0061] The low-orbit satellite routing processing method, device and computer-readable storage medium for inter-satellite solar transit interruptions provided in the present application can be applied to satellites to efficiently and accurately generate a routing table by combining static solar transit link status information and dynamic abnormal link status information, thereby solving the impact of the solar transit problem on routing that is difficult to solve in the prior art.

[0062] The low-orbit satellite routing processing method for intersatellite solar transit interruption mentioned in the present application can be executed by a low-orbit satellite routing processing device for intersatellite solar transit interruption, or a satellite integrated with the low-orbit satellite routing processing device for intersatellite solar transit interruption. The low-orbit satellite routing processing device for intersatellite solar transit interruption can be implemented in hardware or software.

[0063] Next, the low-orbit satellite routing processing method for inter-satellite solar transit interruption provided by the present application is introduced.

[0064] First, see Figure 1 , Figure 1 A flow chart of a low-orbit satellite routing processing method for inter-satellite solar transit interruption provided by the present application is shown. The low-orbit satellite routing processing method for inter-satellite solar transit interruption provided by the present application may specifically include the following steps S101 to S104:

[0065] Step S101, a first satellite acquires solar transit link status information sent by a ground processing center, the solar transit link status information is processed by the ground processing center, and the solar transit link status information is used to indicate a link status between the first satellite and a second satellite under a solar transit phenomenon, the second satellite includes an adjacent satellite of the first satellite, and the number of the second satellites is multiple;

[0066] It can be understood that in the present application, the calculation and speculation of the impact of the solar eclipse phenomenon on the inter-satellite link status can be specifically handled by a ground processing center on the ground. The ground processing center can be understood as a cluster of equipment that performs centralized control in the low-orbit satellite communication network. The ground processing center can send the processed solar eclipse link status information to the satellite in the sky through the communication link between the ground station and the satellite. This process can be called information uplink processing.

[0067] It can be understood that the solar transit link status information is processed from an overall perspective. In this way, the solar transit link status information obtained by various satellites in the sky from the ground is universal, or corresponding.

[0068] Among them, the solar transit link status information can be understood as being processed under the condition that the impact of the solar transit phenomenon on the intersatellite link status remains relatively unchanged within a specific time range (time slice). Therefore, the solar transit link status information received by the satellite each time may be the specific solar transit link status information of only one time slice, or it may be the specific solar transit link status information of multiple time slices. For example, each received solar transit link status information can also be configured with a start time and an end time, and the satellite selects the corresponding specific solar transit link status information according to the current time.

[0069] To put it more simply, the solar transit link status information is the feature of the solar transit interruption change block, which is addressed by the present application. The idea of ​​snapshot is adopted to periodically inject static solar transit link status information to the satellite to reflect the topological relationship changes (intersatellite link changes) caused by the solar transit.

[0070] After receiving the solar transit link status information sent by the ground control center, the satellite can determine the corresponding inter-satellite link status in the low-orbit satellite communication network based on the description content, providing part of the data basis for subsequent routing calculations.

[0071] Step S102, the first satellite updates abnormal link status information, where the abnormal link status information is used to indicate a real-time link status between the first satellite and the second satellite;

[0072] On the other hand, for the satellite itself, it also calculates and speculates the inter-satellite link status between itself and other satellites in the sky. The processing results are recorded as abnormal link status information, which reflects the inter-satellite link status determined by the satellite itself from a real-time perspective, and determines whether there is a sudden link interruption. In this way, real-time inter-satellite link status processing centered on the satellite itself is realized, providing part of the data basis for subsequent routing calculations.

[0073] Step S103, the first satellite integrates the transit link status information and the abnormal link status information to obtain inter-satellite link status information;

[0074] At this time, after obtaining the static solar eclipse link status information and the abnormal link status information, the satellite in the sky can fuse the two to generate a new link status information, recorded as the inter-satellite link status information. In this inter-satellite link status information, the effective link status speculated by the ground processing center on the solar eclipse phenomenon and the satellite's own real-time link status are taken into account, and the inter-satellite link that is not affected by the solar eclipse phenomenon or other environmental conditions is determined from the overall level.

[0075] Step S104: The first satellite generates a routing table based on the inter-satellite link status information, where the routing table is used to indicate the shortest network path from the first satellite to the second satellite.

[0076] It can be understood that after obtaining the intersatellite link status information, the satellite can continue to process it and process it into a usable routing table for the network path required for subsequent intersatellite communication, especially the shortest network path, thereby completing the processing of routing information.

[0077] Among them, it is necessary to understand that for the generation of the routing table, if there is a routing table generated at a historical time point, the newly generated routing table can overwrite the original routing table, thus completing a routing table update operation. As for the information such as the daily link status information required to generate the new routing table, it can be understood as the information obtained by the link status maintenance operation.

[0078] For example, the routing table involved in this application may be a structure as shown in Table 1 below:

[0079] Table 1 - Routing Table

[0080] Destination Address Next hop address Hop Count 01 Star X1 Star M1 02 Star X2 Star M2 … … … N Star XN Star MN

[0081] It can be seen from the embodiments shown above that, in response to the solar eclipse problem of the low-orbit satellite network, the present application obtains the solar eclipse link status information sent by the ground processing center on the one hand, and updates the abnormal link status information on the other hand. At this time, the inter-satellite link status information is obtained by fusing the static solar eclipse link status information and the dynamic abnormal link status information, and then a routing table is generated from the inter-satellite link status information. In this way, the routing table is generated efficiently and accurately. In the processing of the routing table, the effective link status inferred by the ground processing center based on the solar eclipse phenomenon and the satellite's own real-time link status inferred are taken into account, thereby solving the impact of the solar eclipse problem on routing that is difficult to solve in the prior art.

[0082] Continue to the above Figure 1 Each step of the illustrated embodiment and possible implementation methods thereof in practical applications are described in detail.

[0083] In actual applications, as a practical implementation method, for the above-mentioned solar eclipse link status information and abnormal link status information, in order to facilitate data generation, retrieval and processing, they can be represented by an adjacency matrix. In the adjacency matrix, 1 represents the link connectivity status and 0 represents the link interruption status.

[0084] For details, please refer to Figure 2 A data structure diagram of the connection matrix of the present application is shown for understanding.

[0085] In addition, as another practical implementation, when both the transit link state information and the abnormal link state information are adjacency matrices, the present application is also configured with a more convenient generation and processing mechanism of the inter-satellite link state information, namely:

[0086] The first satellite performs AND operation on the solar transit link status information and the abnormal link status information to obtain the inter-satellite link status information which is also in the form of an adjacency matrix.

[0087] The transit link status information is recorded as the transit adjacency matrix, and the abnormal link status information is recorded as the abnormal adjacency matrix. Since both use "1" or "0" to indicate whether each intersatellite link in the matrix is ​​connected, the connectivity status identifiers of the intersatellite links at the same position of the two can be ANDed. Only when the connectivity status of the two adjacency matrices is 1 can a connectivity status of 1 be generated. Otherwise, if there is a 0 or both are 0, an interruption status of 0 is generated. Under this processing method, high processing efficiency can be achieved.

[0088] The data processing work of the intersatellite link status information to the routing table can be understood as the conversion of data form, and in the conversion process, it can also involve the search process of the shortest network path, that is, Figure 1 Step S103 of the illustrated embodiment may include the following contents:

[0089] The first satellite searches for the shortest network path from the first satellite to the second satellite based on the inter-satellite link status information;

[0090] The first satellite converts the search results into a routing table.

[0091] Among them, the network path referred to in this application, including the shortest network path, is a network path formed on a satellite basis. For example, the network path from satellite A to satellite F and then to satellite O is formed based on the state of the intersatellite link. Among different network paths, based on the low-cost operation requirements of communication, the shortest network path is used as much as possible to complete the data transmission between satellites (intersatellite communication).

[0092] It is understandable that in the specific process of the search processing, different search algorithms can be used to achieve the purpose of searching for the shortest network path.

[0093] As another practical implementation, the present application adopts the Dijkstra algorithm, that is, the first satellite searches for the shortest network path from the first satellite to the second satellite based on the inter-satellite link status information under the search principle of the Dijkstra algorithm.

[0094] Dijkstra's algorithm can be understood as the shortest path algorithm from one vertex to the remaining vertices, which solves the shortest path problem in a weighted graph. The main feature of Dijkstra's algorithm is that it starts from the starting point and adopts a greedy algorithm strategy, traversing the adjacent nodes of the vertex that is closest to the starting point and has not been visited each time until it expands to the end point. It is highly adaptable to the search for the shortest inter-satellite network path involved in this application, and can therefore bring efficient and accurate search results.

[0095] For the above content, you can also refer to Figure 3 A scenario diagram of the routing table generation process of the present application is shown for understanding.

[0096] Back to the satellite's own abnormal detection and processing of the real-time communication link, that is, the processing of abnormal link status information, which can be specifically implemented by the response mechanism of the link detection signal. For example, you can refer to the following content:

[0097] The first satellite periodically sends a link detection signal to an adjacent satellite. If no response signal is received, the first satellite determines that the link is disconnected. If a response signal is received, the first satellite determines that the link is connected.

[0098] The first satellite updates the abnormal link status information based on the link detection signal response result obtained by itself and other abnormal link status information broadcasted by the second satellite. The other abnormal link status information broadcasted by the second satellite is obtained by the second satellite itself.

[0099] It can be found that the processing of abnormal link status information by the satellite of this application is not simply to determine the inter-satellite link status by whether the satellite can get an effective response when sending link detection signals to other satellites in the low-orbit satellite communication network. In actual operation, this application believes that this method has a certain degree of inaccuracy and time-consuming and labor-intensive problems. In the low-orbit satellite communication network, there are often many satellites, and the distance between satellites may be very far. If the link detection signal is sent and feedback is processed at a high frequency and long distance, there may be significant problems in the signal transmission accuracy, transmission time and transmission cost.

[0100] In contrast, the present application introduces link detection processing for adjacent intersatellite links. From the perspective of a single satellite, the local satellite only sends a link detection signal (such as a HELLO packet) to the adjacent satellite, and determines whether the intersatellite link with the adjacent satellite is normal by whether a response signal (such as also a HELLO packet) can be received from the adjacent satellite; from an overall level, each satellite only detects the intersatellite link status between itself and its adjacent satellite, so that the detection results can also cover the intersatellite link status of the entire network, and it is only necessary to synchronize the small-scale link detection results between the satellites.

[0101] In this way, the transmission accuracy, transmission time and transmission cost can be taken into account, so as to realize the accurate, efficient and low-cost realization of abnormal link status information.

[0102] In addition, under this mechanism, it can also be adapted to the autonomous update processing of abnormal link status information in actual applications. That is, if a satellite finds that the intersatellite link between itself and an adjacent satellite is abnormal, it can quickly update the abnormal link status information and synchronize the entire network, prompting other satellites to also update their abnormal link status information, thereby promoting all satellites in the entire network to autonomously update their corresponding routing tables and ensure the intersatellite communication quality of the entire network.

[0103] At the same time, the above is the processing of abnormal link status information from the perspective of the first satellite. It should be understood that other satellites are also processing abnormal link status information. Accordingly, the first satellite can also broadcast the abnormal link status information in the satellite topology structure, so that the second satellite generates corresponding abnormal link status information based on the received abnormal link status information and the link detection signal response result processed by itself.

[0104] Furthermore, for easier understanding, a group of examples are provided for illustrative purposes.

[0105] See also Figure 4 A schematic diagram of a scenario in which the present application triggers an update of a routing table is shown. In a normal working cycle, each solar transit adjacency matrix has an invalidity property. After the previous matrix times out, the satellite switches to the next matrix and synchronously updates the inter-satellite adjacency matrix to recalculate the routing table.

[0106] When the dynamic link status detection determines that there is a real-time link abnormality, that is, when the satellite does not receive the HELLO packet (response signal) for three consecutive cycles at a non-solar transit time, an abnormal interrupt update is triggered.

[0107] In a low-orbit satellite communication network, a satellite node that detects a link change generates and floods abnormal link status information. The abnormal link status information describes the link status from the source node to its neighbor nodes, which may include the following three elements:

[0108] 1. The number of the satellite node that initiated this link state information (hereinafter referred to as the source node);

[0109] 2. The numbers of all adjacent nodes of the source node;

[0110] 3. The link status between the source node and its adjacent nodes.

[0111] As an example, the content of abnormal link status information may be as shown in Table 2 below:

[0112] Table 2 - Abnormal link status information example

[0113]

[0114] After other satellite nodes receive the abnormal link status information, they update the local abnormal link status information based on the received abnormal link status information, and recalculate their own routing tables based on the shortest path principle. At the same time, the update message of the local abnormal link status information can be spread to all nodes in the entire network through the broadcast mechanism. In this way, all nodes update their respective local abnormal link status information, and then achieve their respective local routing convergence.

[0115] For easier understanding, you can also combine Figures 5 to 8 The scenario diagrams of the broadcast mechanism of the present application are shown in sequence to understand the effect of the solution of triggering the whole network to update the routing table according to the local abnormal interruption in the above content.

[0116] The above is an introduction to the low-orbit satellite routing processing method for inter-satellite solar transit interruptions provided by the present application. In order to facilitate better implementation of the low-orbit satellite routing processing method for inter-satellite solar transit interruptions provided by the present application, the present application also provides a low-orbit satellite routing processing device for inter-satellite solar transit interruptions from the perspective of functional modules.

[0117] See also Fig. 9 , Fig. 9 This is a structural diagram of a low-orbit satellite routing processing device for inter-satellite solar transit interruption in the present application. In the present application, the low-orbit satellite routing processing device 900 for inter-satellite solar transit interruption may specifically include the following structure:

[0118] An acquisition unit 901 is used to acquire solar transit link status information sent by a ground processing center, where the solar transit link status information is processed by the ground processing center, and the solar transit link status information is used to indicate a link status between a first satellite and a second satellite under a solar transit phenomenon, where the second satellite includes an adjacent satellite of the first satellite, and the number of the second satellites is multiple;

[0119] An updating unit 902, configured to update abnormal link status information, where the abnormal link status information is used to indicate a real-time link status between the first satellite and the second satellite;

[0120] A fusion unit 903 is used to fuse the transit link status information and the abnormal link status information to obtain the inter-satellite link status information;

[0121] The generating unit 904 is configured to generate a routing table based on the inter-satellite link status information, where the routing table is used to indicate the shortest network path from the first satellite to the second satellite.

[0122] In combination with the second aspect of the present application, in a first possible implementation method of the second aspect of the present application, both the daily link status information and the abnormal link status information are represented by an adjacency matrix. In the adjacency matrix, 1 represents the link connectivity status and 0 represents the link interruption status.

[0123] In conjunction with the first possible implementation of the second aspect of the present application, in a second possible implementation of the second aspect of the present application, the fusion unit 903 is specifically configured to:

[0124] The solar transit link status information and the abnormal link status information are processed by AND operation to obtain the inter-satellite link status information which is also in the form of an adjacency matrix.

[0125] In combination with the second aspect of the present application, in a third possible implementation manner of the second aspect of the present application, the generating unit 904 is specifically configured to:

[0126] Based on the inter-satellite link status information, searching for the shortest network path from the first satellite to the second satellite;

[0127] Convert the search results into a routing table.

[0128] In combination with the third possible implementation of the second aspect of the present application, in a fourth possible implementation of the second aspect of the present application, the generating unit 904 is specifically configured to:

[0129] Under the search principle of Dijkstra algorithm, based on the inter-satellite link status information, the shortest network path from the first satellite to the second satellite is searched and processed.

[0130] In combination with the second aspect of the present application, in a fifth possible implementation manner of the second aspect of the present application, the updating unit is specifically configured to:

[0131] A link detection signal is periodically sent to an adjacent satellite. If no response signal is received, the first satellite determines that the link is disconnected. If a response signal is received, the first satellite determines that the link is connected.

[0132] The abnormal link status information is updated based on the link detection signal response result obtained by itself and other abnormal link status information broadcasted by the second satellite. The other abnormal link status information broadcasted by the second satellite is obtained by the second satellite itself.

[0133] In combination with the fifth possible implementation manner of the second aspect of the present application, in a sixth possible implementation manner of the second aspect of the present application, the apparatus further includes a broadcasting unit 905, which is configured to:

[0134] The abnormal link status information is broadcasted in the satellite topology structure, so that the second satellite generates corresponding abnormal link status information according to the received abnormal link status information combined with the link detection signal response result processed by itself.

[0135] This application also provides a satellite from the perspective of hardware structure, see Fig.10 , Fig.10 A schematic diagram of the structure of the satellite of the present application is shown. Specifically, the satellite of the present application may include a processor 1001, a memory 1002, and an input / output device 1003. The processor 1001 is used to execute the computer program stored in the memory 1002 to implement the following Figure 1 The steps of the low-orbit satellite routing processing method for intersatellite solar transit interruption in the corresponding embodiment; or, the processor 1001 is used to execute the computer program stored in the memory 1002 to implement the following Fig. 9 Corresponding to the functions of each unit in the embodiment, the memory 1002 is used to store the processor 1001 executing the above Figure 1 The computer program required for the low-orbit satellite routing processing method for inter-satellite solar transit interruption in the corresponding embodiment.

[0136] Exemplarily, the computer program may be divided into one or more modules / units, one or more modules / units are stored in the memory 1002, and executed by the processor 1001 to complete the present application. One or more modules / units may be a series of computer program instruction segments capable of completing specific functions, and the instruction segments are used to describe the execution process of the computer program in the computer device.

[0137] The satellite may include, but is not limited to, a processor 1001, a memory 1002, and an input-output device 1003. Those skilled in the art will appreciate that the illustration is merely an example of a satellite and does not constitute a limitation on the satellite, and may include more or fewer components than shown in the illustration, or a combination of certain components, or different components. For example, the satellite may also include a network access device, a bus, etc., and the processor 1001, the memory 1002, the input-output device 1003, etc. are connected via a bus.

[0138] The processor 1001 may be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or any conventional processor, etc. The processor is the control center of the satellite, and uses various interfaces and lines to connect various parts of the entire device.

[0139] The memory 1002 can be used to store computer programs and / or modules. The processor 1001 implements various functions of the computer device by running or executing the computer programs and / or modules stored in the memory 1002 and calling the data stored in the memory 1002. The memory 1002 can mainly include a program storage area and a data storage area, wherein the program storage area can store an operating system, an application required for at least one function, etc.; the data storage area can store data created according to the use of the satellite, etc. In addition, the memory can include a high-speed random access memory, and can also include a non-volatile memory, such as a hard disk, a memory, a plug-in hard disk, a smart memory card (Smart Media Card, SMC), a secure digital (SecureDigital, SD) card, a flash card (Flash Card), at least one disk storage device, a flash memory device, or other volatile solid-state storage devices.

[0140] When the processor 1001 is used to execute the computer program stored in the memory 1002, the following functions can be implemented:

[0141] Those skilled in the art can clearly understand that for the convenience and simplicity of description, the specific working process of the low-orbit satellite routing processing device, satellite and its corresponding units described above for intersatellite solar transit interruption can refer to the following. Figure 1 The description of the low-orbit satellite routing processing method for inter-satellite solar transit interruption in the corresponding embodiment will not be repeated here in detail.

[0142] A person of ordinary skill in the art will appreciate that all or part of the steps in the various methods of the above embodiments may be completed by instructions, or by controlling related hardware through instructions. The instructions may be stored in a computer-readable storage medium and loaded and executed by a processor.

[0143] To this end, the present application provides a computer-readable storage medium, in which a plurality of instructions are stored, and the instructions can be loaded by a processor to execute the present application as follows: Figure 1 The steps of the low-orbit satellite routing processing method for intersatellite solar transit interruption in the corresponding embodiment, the specific operation can refer to the following Figure 1 The description of the low-orbit satellite routing processing method for inter-satellite solar transit interruption in the corresponding embodiment will not be repeated here.

[0144] The computer-readable storage medium may include: a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, etc.

[0145] Due to the instructions stored in the computer-readable storage medium, the present application can be executed. Figure 1 The steps of the low-orbit satellite routing processing method for intersatellite solar transit interruption in the corresponding embodiment, therefore, the present application can be implemented as follows Figure 1 The beneficial effects that can be achieved by the low-orbit satellite routing processing method for inter-satellite solar transit interruption in the corresponding embodiment are detailed in the previous description and will not be repeated here.

[0146] The above is a detailed introduction to the low-orbit satellite routing processing method, device, satellite and computer-readable storage medium for intersatellite solar transit interruptions provided by the present application. Specific examples are used in this article to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method of the present application and its core idea; at the same time, for technical personnel in this field, according to the idea of ​​the present application, there will be changes in the specific implementation method and application scope. In summary, the content of this specification should not be understood as a limitation on the present application.

Claims

1. A low-orbit satellite routing processing method for intersatellite solar transit interruption, characterized in that: The method comprises: The first satellite acquires solar transit link status information sent by a ground processing center, the solar transit link status information is processed by the ground processing center, and the solar transit link status information is used to indicate a link status between the first satellite and a second satellite under a solar transit phenomenon, the second satellite includes an adjacent satellite of the first satellite, and the number of the second satellite is multiple; The first satellite updates abnormal link status information, where the abnormal link status information is used to indicate a real-time link status between the first satellite and the second satellite; The first satellite fuses the solar transit link status information and the abnormal link status information to obtain inter-satellite link status information; The first satellite generates a routing table based on the inter-satellite link status information, wherein the routing table is used to indicate the shortest network path from the first satellite to the second satellite; The link status information of the sun eclipse and the abnormal link status information are both represented by an adjacency matrix, in which 1 represents a link connected state and 0 represents a link disconnected state; The first satellite fuses the transit link status information and the abnormal link status information to obtain inter-satellite link status information, including: The first satellite performs an AND operation on the solar transit link status information and the abnormal link status information to obtain the inter-satellite link status information which is also in the form of an adjacency matrix.

2. The method according to claim 1, characterized in that: The first satellite generates a routing table based on the inter-satellite link status information, including: The first satellite searches for the shortest network path from the first satellite to the second satellite based on the intersatellite link status information; The first satellite converts the search results into the routing table.

3. The method according to claim 2, characterized in that The first satellite searches for the shortest network path from the first satellite to the second satellite based on the intersatellite link status information, including: The first satellite searches for the shortest network path from the first satellite to the second satellite based on the inter-satellite link status information under the search principle of the Dijkstra algorithm.

4. The method according to claim 1, characterized in that The first satellite updates abnormal link status information, including: The first satellite periodically sends a link detection signal to the adjacent satellite. If no response signal is received, the first satellite determines that the link is disconnected. If a response signal is received, the first satellite determines that the link is connected. The first satellite updates the abnormal link status information based on the link detection signal response result obtained by itself and other abnormal link status information broadcasted by the second satellite, where the other abnormal link status information broadcasted by the second satellite is obtained by the second satellite itself.

5. The method according to claim 4, characterized in that The method further comprises: The first satellite broadcasts the abnormal link status information in the satellite topology structure, so that the second satellite generates corresponding abnormal link status information according to the received abnormal link status information and the link detection signal response result processed by itself.

6. A low-orbit satellite routing processing device for intersatellite solar transit interruption, characterized in that: The device comprises: an acquisition unit, configured to acquire solar transit link status information sent by a ground processing center, wherein the solar transit link status information is processed by the ground processing center, and the solar transit link status information is used to indicate a link status between a first satellite and a second satellite under a solar transit phenomenon, wherein the second satellite includes an adjacent satellite of the first satellite, and the number of the second satellites is multiple; an updating unit, configured to update abnormal link status information, wherein the abnormal link status information is used to indicate a real-time link status between the first satellite and the second satellite; A fusion unit, configured to fuse the transit link status information and the abnormal link status information to obtain inter-satellite link status information; a generating unit, configured to generate a routing table based on the inter-satellite link status information, wherein the routing table is used to indicate the shortest network path from the first satellite to the second satellite; The link status information of the sun eclipse and the abnormal link status information are both represented by an adjacency matrix, in which 1 represents a link connected state and 0 represents a link disconnected state; The fusion unit is specifically used for: The transit link status information and the abnormal link status information are processed by AND operation to obtain the inter-satellite link status information which is also in the form of an adjacency matrix.

7. A satellite, characterized in that: The method comprises a processor and a memory, wherein the memory stores a computer program, and the processor executes the method according to any one of claims 1 to 5 when calling the computer program in the memory.

8. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a plurality of instructions, and the instructions are suitable for being loaded by a processor to execute the method according to any one of claims 1 to 5.

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