Inter-satellite communication method, system, and apparatus for low-orbit satellite and electronic device

Abstract

The present application provides an inter-satellite communication method, system, and device for a low-orbit satellite, and an electronic device. The method comprises: obtaining a plurality of candidate signal frames in a candidate frame sequence of a low-orbit satellite, and identifying first network slices to which the candidate signal frames belong; obtaining a first physical frame of each first network slice, obtaining a target signal frame of the first physical frame from among the plurality of candidate signal frames, and filling the first physical frame with the target signal frame to obtain a second physical frame after filling; and determining a target inter-satellite laser link and a target receiving end that correspond to the second physical frame, and transmitting the second physical frame to the target receiving end by means of the target inter-satellite laser link. The applicability and practicability of the inter-satellite communication method for the low-orbit satellite are optimized, the compatibility with an Ethernet MAC protocol is realized, the development cost and the maintenance cost of inter-satellite communication of the low-orbit satellite are reduced, and the stability of signal interaction is improved.

Description

Intersatellite communication method, system, device and electronic equipment for low-orbit satellites

[0001] This application claims priority to the Chinese patent application filed with the China Patent Office on January 24, 2024, with application number 202410097130.5 and application name “Intersatellite communication methods, systems, devices and electronic equipment for low-orbit satellites”, the entire contents of which are incorporated by reference into this application. Technical Field

[0002] The present application relates to the field of communication technology, and in particular to an inter-satellite communication method, system, device and electronic equipment for low-orbit satellites. Background Art

[0003] The signal transmission state of the inter-satellite laser link between each low-orbit satellite in the low-orbit satellite network is unstable to a certain extent, which has a certain impact on the stability of the signal transmission between each low-orbit satellite.

[0004] In related technologies, signal interaction between low-orbit satellites can be achieved through the CCSDS link layer protocol. However, the CCSDS link layer protocol is designed based on the corresponding requirements of deep space missions and has poor adaptability to signal interaction between low-orbit satellites.

[0005] Therefore, it is very important to achieve stable signal interaction between low-orbit satellites.

[0006] Summary of the Invention

[0007] The present application aims to solve one of the technical problems in the related art at least to a certain extent.

[0008] To this end, the first purpose of this application is to propose an inter-satellite communication method for low-orbit satellites.

[0009] The second objective of this application is to provide an inter-satellite communication device for low-orbit satellites.

[0010] The third objective of this application is to propose an inter-satellite communication system for low-orbit satellites.

[0011] The fourth objective of this application is to provide an electronic device.

[0012] A fifth objective of this application is to provide a computer-readable storage medium.

[0013] A sixth object of the present application is to provide a computer program product.

[0014] To achieve the above-mentioned purpose, the first aspect embodiment of the present application proposes an inter-satellite communication method for a low-orbit satellite, including: obtaining multiple candidate signal frames in a candidate frame sequence of a low-orbit satellite, and identifying the first slice network to which the candidate signal frame belongs; obtaining a first physical frame of the first slice network, and obtaining a target signal frame of the first physical frame from multiple candidate signal frames and filling it to obtain a filled second physical frame; determining a target inter-satellite laser link and a target receiving end corresponding to the second physical frame, and transmitting the second physical frame to the target receiving end through the target inter-satellite laser link.

[0015] To achieve the above-mentioned purpose, the second aspect embodiment of the present application proposes an inter-satellite communication device for a low-orbit satellite, and the device includes: a first acquisition module, used to acquire multiple candidate signal frames in a candidate frame sequence of the low-orbit satellite, and identify the first slice network to which the candidate signal frame belongs; a second acquisition module, used to acquire a first physical frame of the first slice network, and obtain a target signal frame of the first physical frame from multiple candidate signal frames and fill it to obtain a filled second physical frame; a transmission module, used to determine the target inter-satellite laser link and target receiving end corresponding to the second physical frame, and transmit the second physical frame to the target receiving end through the target inter-satellite laser link.

[0016] To achieve the above-mentioned purpose, the third aspect embodiment of the present application proposes an inter-satellite communication system for a low-orbit satellite, wherein the system includes a link layer, wherein the link layer is used to: obtain multiple candidate signal frames in a candidate frame sequence of the low-orbit satellite, and identify the first slice network to which the candidate signal frame belongs; obtain a first physical frame of the first slice network, and obtain a target signal frame of the first physical frame from multiple candidate signal frames and fill it to obtain a filled second physical frame; determine a target inter-satellite laser link for transmitting the second physical frame and a target receiving end for receiving the second physical frame; and transmit the second physical frame to the target receiving end through the target inter-satellite laser link.

[0017] To achieve the above-mentioned purpose, the fourth embodiment of the present application proposes an electronic device, comprising: a processor, and a memory communicatively connected to the processor; the memory stores computer-executable instructions; the processor executes the computer-executable instructions stored in the memory to implement the inter-satellite communication method of low-orbit satellites proposed in the first aspect above.

[0018] To achieve the above-mentioned purpose, the fifth embodiment of the present application proposes a computer-readable storage medium, in which computer execution instructions are stored. When the computer execution instructions are executed by the processor, they are used to implement the inter-satellite communication method of low-orbit satellites proposed in the first aspect above.

[0019] To achieve the above-mentioned purpose, the sixth embodiment of the present application proposes a computer program product, including a computer program, which, when executed by a processor, implements the inter-satellite communication method of low-orbit satellites proposed in the first aspect above.

[0020] The inter-satellite communication method, system, device and electronic equipment for low-orbit satellites provided in the present application obtain a candidate frame sequence to be processed by the low-orbit satellite, and identify the first slice network to which each of the multiple candidate signal frames in the candidate frame sequence belongs. For any first slice network, the first physical frame to be filled in the first slice network is obtained, and at least one target signal frame to fill the first physical frame is screened out from the multiple candidate signal frames and filled, thereby obtaining a filled second physical frame, obtaining a target inter-satellite laser link for transmitting the second physical frame, and a target receiving end for receiving the second physical frame, and transmitting the second physical frame to the target receiving end through the target inter-satellite laser link. In the present application, a first physical frame corresponding to the first slice network is constructed, and the target signal frame is filled into the corresponding first physical frame to obtain a filled second physical frame. The inter-satellite communication of low-orbit satellites is realized by sending the second physical frame, so that the inter-satellite communication between low-orbit satellites is compatible with multiple types of signal frames, and the applicability and practicality of the inter-satellite communication method of low-orbit satellites are optimized. In the scenario where the signal frame is a MAC frame, compatibility with the Ethernet MAC protocol is achieved, and multiplexing of the ground network is achieved, which reduces the development cost and maintenance cost of the inter-satellite communication of low-orbit satellites. The frames to be sent are transmitted through the inter-satellite laser link, which improves the stability of the signal interaction between low-orbit satellites and optimizes the signal interaction method between low-orbit satellites.

[0021] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0023] FIG1 is a schematic flow chart of a method for inter-satellite communication of a low-orbit satellite according to an embodiment of the present application;

[0024] FIG2 is a schematic flow chart of an inter-satellite communication method for a low-orbit satellite according to another embodiment of the present application;

[0025] FIG3 is a schematic flow chart of an inter-satellite communication method for a low-orbit satellite according to another embodiment of the present application;

[0026] FIG4 is a schematic diagram of an inter-satellite communication system for a low-orbit satellite according to an embodiment of the present application;

[0027] FIG5 is a schematic flow chart of an inter-satellite communication method for a low-orbit satellite according to another embodiment of the present application;

[0028] FIG6 is a schematic flow chart of an inter-satellite communication method for a low-orbit satellite according to another embodiment of the present application;

[0029] FIG7 is a schematic flow chart of an inter-satellite communication method for a low-orbit satellite according to another embodiment of the present application;

[0030] FIG8 is a schematic structural diagram of an inter-satellite communication device for a low-orbit satellite according to an embodiment of the present application. DETAILED DESCRIPTION

[0031] The following describes in detail embodiments of the present application. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.

[0032] The following describes the inter-satellite communication method, system, device and electronic equipment for low-orbit satellites in embodiments of the present application with reference to the accompanying drawings.

[0033] FIG1 is a flow chart of an inter-satellite communication method for a low-orbit satellite according to an embodiment of the present application. As shown in FIG1 , the method includes:

[0034] S101: Acquire multiple candidate signal frames in a candidate frame sequence to be processed by a low-orbit satellite, and identify a first slice network to which each of the multiple candidate signal frames belongs.

[0035] In an embodiment of the present application, information exchange can be achieved between low-orbit satellites by sending signal frames. In this scenario, the signal frames to be sent and processed by the low-orbit satellites can be marked as candidate signal frames, and the sequence composed of the candidate signal frames to be processed can be marked as a candidate frame sequence.

[0036] The candidate signal frame may be a data frame MAC frame or other types of data frames, which are not specifically limited here.

[0037] Optionally, the candidate frame sequence carries multiple candidate signal frames, where, for any candidate signal frame, the frame information carried by it stores relevant information of the slice network to which the candidate signal frame belongs, and the slice network can be marked as the first slice network to which the candidate signal frame belongs.

[0038] In this scenario, the frame information carried by each of the multiple candidate signal frames can be read, thereby identifying the first slice network to which each of the multiple candidate signal frames belongs.

[0039] S102: Obtain a first physical frame of a first slice network, and obtain a target signal frame of the first physical frame from a plurality of candidate signal frames and fill it to obtain a filled second physical frame.

[0040] In an embodiment of the present application, there is a corresponding physical frame in the first slice network, and the physical frame under the first slice network can be marked as the first physical frame of the first slice network. In this scenario, at least one corresponding candidate signal frame can be filled in the first physical frame, and the sending of the candidate signal frame can be realized by sending the first physical frame after the candidate signal frame is filled.

[0041] Optionally, a candidate signal frame selection condition preset for the first physical frame can be obtained, and multiple candidate signal frames can be screened based on the selection condition to obtain at least one signal frame that can be filled into the first physical frame, and the at least one signal frame can be marked as a target signal frame to be filled into the first physical frame.

[0042] Furthermore, the partial target signal frame is filled into the first physical frame, and the first physical frame after filling is marked as the second physical frame.

[0043] It should be noted that the first physical frame has a preset filling format. In this scenario, the target signal frame can be split based on the filling format of the first physical frame, so that the split target signal frame can be filled into the first physical frame based on the filling format of the first physical frame. In this scenario, the data frame type to which the target signal frame belongs can be any data frame type that can be adapted to the filling format of the first physical frame after splitting.

[0044] S103: Determine a target inter-satellite laser link and a target receiving end corresponding to the second physical frame, and transmit the second physical frame to the target receiving end through the target inter-satellite laser link.

[0045] In an embodiment of the present application, after the low-orbit satellite obtains the second physical frame, it is necessary to determine the receiving end that receives the second physical frame, and send the second physical frame to the receiving end through the inter-satellite laser link between the low-orbit satellite and the receiving end.

[0046] Optionally, the receiving end can be marked as the target receiving end of the second physical frame, and the intersatellite laser link used by the low-orbit satellite to send the second physical frame to the target receiving end can be marked as the target intersatellite laser link used to send the second physical frame.

[0047] The target receiving end and the corresponding target receiving link of the second physical frame may be determined based on the preconfigured routing information.

[0048] It should be noted that the target receiving end of the second physical frame can be other low-orbit satellites other than the low-orbit satellite currently performing the second physical frame sending processing, or it can be a ground signal receiving end that can interact with the low-orbit satellite. No specific limitation is made here.

[0049] In an embodiment of the present application, there may be corresponding sending conditions when the low-orbit satellite sends a signal frame. In this scenario, the second physical frame can be further processed based on the preset sending conditions, so that the processed second physical frame can meet the preset sending conditions, thereby achieving normal sending of the second physical frame.

[0050] Furthermore, based on the determined target receiving end of the second physical frame and the corresponding target intersatellite laser link, the second physical frame is transmitted to the target receiving end to achieve intersatellite communication between low-orbit satellites.

[0051] The inter-satellite communication method for low-orbit satellites proposed in the present application obtains a candidate frame sequence to be processed by the low-orbit satellite, identifies the first slice network to which multiple candidate signal frames in the candidate frame sequence belong, obtains the first physical frame of the first slice network, obtains the target signal frame from the multiple candidate signal frames and fills it, thereby obtaining the filled second physical frame, obtains the target inter-satellite laser link for transmitting the second physical frame, and the target receiving end for receiving the second physical frame, and transmits the second physical frame to the target receiving end through the target inter-satellite laser link. In the present application, a first physical frame corresponding to the first slice network is constructed, and the target signal frame is filled into the corresponding first physical frame to obtain a filled second physical frame. The inter-satellite communication of low-orbit satellites is realized by sending the second physical frame, so that the inter-satellite communication between low-orbit satellites is compatible with multiple types of signal frames, and the applicability and practicality of the inter-satellite communication method of low-orbit satellites are optimized. In the scenario where the signal frame is a MAC frame, compatibility with the Ethernet MAC protocol is achieved, and multiplexing of the ground network is achieved, which reduces the development cost and maintenance cost of the inter-satellite communication of low-orbit satellites. The second physical frame to be sent is transmitted through the inter-satellite laser link, which improves the stability of the signal interaction between low-orbit satellites and optimizes the signal interaction method between low-orbit satellites.

[0052] In the above embodiment, regarding inter-satellite communication of low-orbit satellites, it can be further understood in conjunction with FIG2 , which is a flow chart of an inter-satellite communication method of low-orbit satellites according to another embodiment of the present application. As shown in FIG2 , the method includes:

[0053] S201, obtaining a plurality of candidate signal frames in a candidate frame sequence to be processed of a low-orbit satellite.

[0054] Optionally, a third physical frame received by the low-orbit satellite is obtained, and an initial frame sequence in the third physical frame is obtained, wherein the initial frame sequence includes multiple initial signal frames.

[0055] In an embodiment of the present application, the physical frame received by the low-orbit satellite as a signal receiving end can be marked as the third physical frame.

[0056] Among them, the third physical frame carries a frame sequence composed of multiple signal frames. This part of the signal frames can be marked as multiple initial signal frames received by the low-orbit satellite, and the sequence composed of the multiple initial signal frames can be marked as the initial frame sequence in the third physical frame.

[0057] In an embodiment of the present application, an error correction code is provided in the third physical frame received by the low-orbit satellite, and the error correction code in the third physical frame can be marked as a second error correction code. The second error correction code in the third physical frame can be obtained, and an error correction check can be performed on the initial frame sequence in the third physical frame based on the second error correction code.

[0058] In this scenario, a preset error correction code identification strategy may be obtained, and the second error correction code may be identified based on the error correction code identification strategy, thereby performing an error correction check on the initial frame sequence in the third physical frame.

[0059] Optionally, in response to the initial frame sequence failing the error correction check, the third physical frame is discarded.

[0060] In the scenario where the initial frame sequence fails the error correction check, it can be determined that the information in the initial signal frame in the initial frame sequence in the third physical frame received by the current low-orbit satellite is erroneous. In this scenario, the third physical frame can be discarded.

[0061] Optionally, in response to the initial frame sequence passing the error correction check, the initial frame sequence is determined to be a candidate frame sequence, and multiple initial frame signals are determined to be multiple candidate signal frames.

[0062] In the scenario where the initial frame sequence passes the error correction check, it can be determined that the information in the multiple initial signal frames carried in the third physical frame received by the current low-orbit satellite is normal. In this scenario, it can be determined that the multiple initial signal frames in the third physical frame can be used as multiple candidate signal frames to be processed by the low-orbit satellite.

[0063] S202: Identify the first slice network to which each of the multiple candidate signal frames belongs.

[0064] Optionally, the second network slice identifier of the second slice network of the low-orbit satellite and the network field identifier of the candidate signal frame can be obtained.

[0065] In an embodiment of the present application, a set consisting of multiple slice networks covering low-orbit satellites can be marked as a second slice network set, wherein each second slice network in the second slice network set has its corresponding network identifier, and the identifier can be marked as a second network slice identifier.

[0066] Correspondingly, the candidate signal frame carries its corresponding network field information, and the network field identifier of the candidate signal frame can be obtained by reading the information carried by the candidate signal frame.

[0067] Optionally, in response to the second network slice identifier matching the network field identifier, the second slice network is determined to be the first slice network to which the candidate signal frame belongs.

[0068] In an embodiment of the present application, in a scenario where a target signal frame is filtered from multiple candidate signal frames to be filled into a first physical frame, a network slice identifier that matches the network field identifier of the candidate signal frame can be identified from multiple second network slice identifiers, and the network slice identifier can be determined as the network slice identifier that matches the candidate signal frame. Further, the second slice network corresponding to the network slice identifier that matches the candidate signal frame is determined as the first slice network to which the candidate signal frame belongs.

[0069] S203: Acquire a first physical frame of the first slice network, and acquire a target signal frame of the first physical frame from multiple candidate signal frames.

[0070] Optionally, in response to identifying that padding space exists in the first physical frame, a target signal frame is obtained for the first physical frame.

[0071] In an embodiment of the present application, if it is identified that there is filling space in the first physical frame, the first physical frame can be determined as the first physical frame used to fill the candidate signal frame under the current first slice network.

[0072] Accordingly, in response to identifying that no padding space exists in the first physical frame, a new blank physical frame of the first slice network is constructed as a new first physical frame, and a target signal frame is obtained for the new first physical frame.

[0073] In an embodiment of the present application, when it is identified that there is no filling space in the first physical frame, a new blank physical frame can be constructed for the first slice network, and the new blank physical frame can be marked as a new first physical frame to be filled under the first slice network.

[0074] Optionally, the first slice network identifier of the first slice network is obtained, and the target signal frame is filtered out from multiple candidate signal frames according to the network field identifier of the candidate signal frame, wherein the network field identifier of the target signal frame matches the first slice network identifier.

[0075] In an embodiment of the present application, the first slice network identifier of the first slice network corresponding to the first physical frame can be obtained, and the network field identifiers of multiple candidate signal frames can be matched with the first slice network identifier, and then some candidate signal frames matching the first slice network identifier can be marked as target signal frames to fill the first physical frame.

[0076] In an embodiment of the present application, the first physical frame has a preset physical frame format, and filling of at least one target signal frame can be achieved based on the physical frame format.

[0077] As an example, the physical frame format of the first physical frame can be understood in conjunction with Figure 3. As shown in Figure 3, the first physical frame includes a frame start field (Frame Start), a slice network identification field (Slice ID), a reserved bit field (Reserved), a frame fragment length field (Fragment Length), a frame fragment start and end identification field (Fragment Flag), a frame fragment field (Fragment), and an error correction code field (Error Correcting Code), wherein the specific information of each field can be understood in conjunction with the following content:

[0078] As shown in Figure 3, the frame start field (Frame Start) is a 32-bit field. In an embodiment of the present application, the physical frames received by the low-orbit satellite are continuous physical frames. In this scenario, the low-orbit satellite can identify the starting position of the received physical frame through this field. The low-orbit satellite can search the received data stream. When the data stream is found to carry this field, it can be determined that a new physical frame has been received, and the position of the field is the starting position of the new physical frame.

[0079] As shown in Figure 3, the slice network identification field (Slice ID) is an 8-bit field. In the scenario of screening the target signal frame to be filled into the first physical frame shown in Figure 3, this field can be used to screen among multiple candidate signal frames to identify the target signal frame among multiple candidate signal frames that can be filled into the first physical frame shown in Figure 3.

[0080] As shown in FIG3 , the reserved bit field (Reserved) can be used for future expansion.

[0081] As shown in Figure 3, the frame fragment length field (Fragment Length) is a 16-bit field, which can be used to represent the length of subsequent adjacent frame fragments. The length of the frame data fragment filled under the frame fragment field 1 (Fragment 1) can be determined by the frame fragment length field 1 (Fragment Length 1) shown in Figure 3. Correspondingly, the length of the frame data fragment filled under the frame fragment field 2 (Fragment 2) can be determined by the frame fragment length field 2 (Fragment Length 2) shown in Figure 3.

[0082] In this scenario, the low-orbit satellite can determine the end position of the frame data segment of each of the multiple target signal frames filled into the first physical frame shown in Figure 3 based on this field.

[0083] As shown in Figure 3, the Fragment Flag field is an 8-bit field that can be used to identify the start and end of each target signal frame in the multiple target signal frames that fill the first physical frame shown in Figure 3. If only some of the candidate signal frames in the candidate frame sequence are determined to be the target signal frames that fill the first physical frame shown in Figure 3, the low-orbit satellite can use this field to identify the boundaries of the candidate frame sequence.

[0084] The boundaries between the candidate frame sequences corresponding to the frame fragment start and end identification field 1 (Fragment Flag1) and the frame fragment start and end identification field 2 (Fragment Flag2) shown in FIG. 3 can be identified.

[0085] As shown in Figure 3, the frame fragment field (Fragment) is a field containing the frame data of the target signal frame, wherein the frame fragment field 1 (Fragment1) is filled with the frame data fragment in the corresponding target signal frame, and the frame fragment field 2 (Fragment2) is filled with the frame data fragment in the corresponding target signal frame, and the target signal frames filled in the two are different.

[0086] As shown in FIG3 , the error correction code field (Error Correcting Code) is a field used for error correction, wherein the error correction code marked on the field can be obtained by Reed-Solomon encoding, the error correction code marked on the field can also be obtained by Turbo encoding, and the error correction code marked on the field can also be obtained by LDPC encoding, which is not specifically limited here.

[0087] S204: Transmit the second physical frame to a target receiving end through a target intersatellite laser link.

[0088] Optionally, it is identified whether the second physical frame meets an error correction code adding condition.

[0089] In an embodiment of the present application, the second physical frame after filling the target signal frame still needs to add an error correction code. There is a preset error correction code addition condition for adding the error correction code. In response to identifying that there is no remaining filling space in the second physical frame, it is determined that the second physical frame meets the error correction code addition condition.

[0090] When there is no remaining padding space in the second physical frame, it can be understood that the current second physical frame has been filled and the physical frame can be sent, and then it can be determined that the second physical frame in this scenario meets the error correction code adding condition.

[0091] Accordingly, in response to identifying that there is remaining padding space in the second physical frame and there is no new candidate frame sequence on the low-orbit satellite, it is determined that the second physical frame meets the error correction code adding condition.

[0092] When it is identified that there is remaining filling space in the second physical frame and the low-orbit satellite has not received any new candidate frame sequence to be processed, in order to optimize the sending timing of the second physical frame, the second physical frame in this scenario can be determined as the second physical frame that meets the error correction code addition conditions.

[0093] Optionally, in response to identifying that the second physical frame meets the error correction code addition condition, the first error correction code is added to the second physical frame, and the added second physical frame is transmitted to the target receiving end through the target intersatellite laser link.

[0094] In an embodiment of the present application, when it is identified that the second physical frame meets the error correction code addition conditions, a corresponding error correction code can be generated for the second physical frame based on a preset encoding method, and the error correction code can be marked as the first error correction code of the second physical frame.

[0095] Furthermore, the first error correction code is added to the second physical frame, and the added second physical frame is determined as the second physical frame to be sent by the low-orbit satellite. The added second physical frame can be transmitted to the target receiving end based on the pre-acquired target inter-satellite laser link.

[0096] The acquisition of the target intersatellite laser link in any second physical frame can be understood in conjunction with the following:

[0097] Optionally, the candidate link transmission status of the candidate inter-satellite laser link of the low-orbit satellite can be obtained, the sending requirements of the first slice network can be obtained, and it can be identified whether the candidate link transmission status of the candidate inter-satellite laser link meets the sending requirements.

[0098] The intersatellite laser links to which the low-orbit satellite can transmit information can be marked as candidate intersatellite laser links, and the data transmission status of the candidate intersatellite laser links can be marked as candidate link transmission status of the candidate intersatellite laser links.

[0099] In an embodiment of the present application, different first slice networks have different information transmission requirements. In this scenario, it is possible to identify whether the candidate intersatellite laser link can meet the information transmission requirements of the first slice network based on the transmission status of the candidate link, and then identify whether the transmission status of the candidate link meets the sending requirements of the first slice network.

[0100] Optionally, in response to identifying that the transmission state of the candidate link meets the transmission requirement, the candidate inter-satellite laser link is determined to be the target inter-satellite laser link.

[0101] It can be understood that when it is identified that the transmission status of the candidate link meets the transmission requirements of the first slice network, the candidate inter-satellite laser link that meets the transmission requirements can be determined as the target inter-satellite laser link.

[0102] As an example, for the first slice network corresponding to real-time services (such as voice and video calls), there are usually high requirements for latency and packet loss rate, but relatively low requirements for bandwidth. Therefore, this type of service can be placed in a high-priority transmission queue, and a target intersatellite laser link that can meet the real-time information transmission requirements of the first slice network can be determined from the candidate intersatellite laser links. It should be noted that for this type of service, a smaller timeout period and a higher retransmission limit can be set for it to achieve real-time transmission of the second physical frame under the first slice network corresponding to this type of service.

[0103] As another example, for non-real-time services (such as email and file transfer), the first slice network corresponding to the service usually has a high tolerance for delay but may have a high bandwidth requirement. Therefore, this type of service can be placed in a low-priority sending queue, and a target intersatellite laser link that can meet the bandwidth information transmission requirements of the first slice network can be determined from the candidate intersatellite laser links. It should be noted that a larger timeout and a lower retransmission limit can be set for this type of service to ensure the integrity of the second physical frame under the first slice network corresponding to this type of service.

[0104] As another example, the first slice network corresponding to control signaling services typically has very high requirements for latency and packet loss rate, as they usually involve the system's operating status and control information. Therefore, this type of service can be placed in the highest priority transmission queue, and a target intersatellite laser link that can meet the timeliness and accuracy of information transmission requirements of the first slice network can be determined from the candidate intersatellite laser links. It should be noted that a smaller timeout and a higher retransmission limit can be set for this type of service to ensure timely and accurate transmission of the second physical frame under the first slice network corresponding to this type of service.

[0105] It should be noted that the initial signal frame, candidate signal frame and target signal frame proposed in the above embodiments are all MAC frames.

[0106] The inter-satellite communication method for low-orbit satellites proposed in the present application constructs a first physical frame corresponding to a first slice network, and fills the target signal frame into the corresponding first physical frame to obtain a filled second physical frame, and realizes the inter-satellite communication of low-orbit satellites by sending the second physical frame, so that the inter-satellite communication between low-orbit satellites is compatible with multiple types of signal frames, and optimizes the applicability and practicality of the inter-satellite communication method of low-orbit satellites. In the scenario where the signal frame is a MAC frame, compatibility with the Ethernet MAC protocol is achieved, and multiplexing of the ground network is achieved, which reduces the development cost and maintenance cost of the inter-satellite communication of low-orbit satellites. The second physical frame to be sent is transmitted through the inter-satellite laser link, which improves the stability of signal interaction between low-orbit satellites and optimizes the signal interaction method between low-orbit satellites.

[0107] The present application further proposes an inter-satellite communication system for a low-orbit satellite, which can be understood in conjunction with FIG4 , which is a schematic diagram of an inter-satellite communication system for a low-orbit satellite according to an embodiment of the present application. As shown in FIG4 , the inter-satellite communication system 400 for a low-orbit satellite includes a link layer 41 , wherein the link layer 41 is used to:

[0108] Acquire multiple candidate signal frames in a candidate frame sequence of a low-orbit satellite, and identify the first slice network to which the candidate signal frames belong; acquire a first physical frame of the first slice network, and obtain a target signal frame of the first physical frame from the multiple candidate signal frames and fill it to obtain a filled second physical frame; determine a target intersatellite laser link for transmitting the second physical frame and a target receiving end for receiving the second physical frame; and transmit the second physical frame to the target receiving end through the target intersatellite laser link.

[0109] As shown in FIG4 , the inter-satellite communication system 400 of the low-orbit satellite further includes a network layer 42 and a control terminal 43 , wherein the network layer 42 is used to send a link scheduling strategy to the link layer, and the link layer determines the target inter-satellite laser link for the second physical frame through the link scheduling strategy.

[0110] The control terminal 43 is used to generate a link scheduling policy and transmit it to the network layer.

[0111] In an embodiment of the present application, the inter-satellite communication method of the low-orbit satellite can be implemented respectively through the network layer 42 and the link layer 41 shown in Figure 4, wherein the network layer 42 can filter out the corresponding target inter-satellite laser link for the frames to be sent under the target slice network, thereby achieving stable sending of the frames to be sent.

[0112] In this scenario, the transmission status of the target inter-satellite laser link can be monitored through the link layer 41 , wherein the real-time link transmission status of the target inter-satellite laser link can be monitored.

[0113] Optionally, the control end 43 shown in FIG. 4 may generate a link scheduling policy, and the network layer 42 may obtain the link scheduling policy through data transmitted from the control end 43 and transmit the link scheduling policy to the link layer 41 .

[0114] Furthermore, the link layer 41 may determine a target inter-satellite laser link for transmission for the second physical frame based on the received link scheduling policy.

[0115] Among them, the link layer 41 can identify the first slice network of each of the multiple candidate signal frames, and according to the first physical frame of the first slice network, determine the target signal frame of the first physical frame from the multiple candidate signal frames and fill it to obtain the filled second physical frame. Furthermore, according to the received link scheduling strategy, the intersatellite laser link that meets the transmission requirements of the second physical frame is screened out from all the intersatellite laser links, and then the link is marked as the target intersatellite laser link of the second physical frame.

[0116] In this scenario, the link layer 41 can also obtain the target receiving end of the second physical frame, determine the target inter-satellite laser link based on the target receiving end and the link scheduling strategy, and then transmit the second physical frame to the target receiving end through the target inter-satellite laser link.

[0117] Optionally, for any first slice network, in response to the real-time link transmission status of the target intersatellite laser link being unable to meet the transmission requirements of the first slice network, link abnormality information of the target intersatellite laser link is generated and transmitted to the control end, and a link scheduling strategy returned by the control end based on the link abnormality information is received. According to the link scheduling strategy, a new target intersatellite laser link is determined for the second physical frame of the first slice network from the remaining candidate intersatellite laser links except the target intersatellite laser link in each candidate intersatellite laser link.

[0118] In the embodiment of the present application, the transmission status of the target inter-satellite laser link monitored by the link layer 41 can be marked as a real-time link transmission status and sent to the network layer 42.

[0119] In this scenario, the link layer 41 can monitor and collect the usage status parameters of any first slice network on its corresponding target inter-satellite link, thereby obtaining the transmission status of the target inter-satellite laser link for the physical frame under the first slice network, and then realizing the collection of relevant parameters of the real-time link transmission status of the target inter-satellite link.

[0120] Among them, the relevant parameters of the real-time link transmission status may include the available bandwidth, delay, bit error rate of the target inter-satellite laser link, and the number of physical frames sent by the first slice network on the target inter-satellite link and the error rate of the physical frames and other related parameters. It can be understood that based on the relevant parameters of the real-time link transmission status, the network layer can obtain relevant information such as the load condition and link quality of the target inter-satellite laser link.

[0121] In an embodiment of the present application, the network layer 42 can send the corresponding link scheduling strategy to the link layer 41. The link layer 41 implements the sending of the second physical frame under each first slice network based on the target inter-satellite laser link of each first slice network carried in the received link scheduling strategy.

[0122] In this scenario, for any first slice network, when the network layer 42 identifies through the real-time link transmission status that the target inter-satellite laser link used by the first slice network cannot meet the physical frame sending requirements of the first slice network, a new link scheduling strategy can be obtained and sent to the link layer 41. The link layer 41 can achieve stable sending of each second physical frame based on the new target inter-satellite laser link of each first slice network carried by the new link scheduling strategy.

[0123] Among them, the link scheduling strategy can be generated based on the control end 43. After receiving the real-time link transmission status, the network layer 42 can generate corresponding link abnormality information and transmit it to the control end 43. The control end 43 generates a new link scheduling strategy based on the received link abnormality information and sends it to the network layer 42, and then sends it down to the link layer 41 through the network layer 42.

[0124] As an example, as shown in Figure 5, based on a preset reporting time interval, the link layer collects parameters of the real-time link transmission status of the target intersatellite laser link and generates a corresponding link status report. Furthermore, the link layer uploads the generated link status report to the network layer.

[0125] As shown in Figure 6, after receiving the link status report, the network layer analyzes the real-time link transmission status of the target intersatellite laser link. When it is identified that the real-time link transmission status of the current target intersatellite link cannot meet the requirements of the corresponding first slice network, the corresponding link abnormality information is generated and sent to the control end. The control end generates a new link scheduling strategy and sends it down to the link layer.

[0126] In this scenario, the link layer can obtain the new target intersatellite laser link of the first slice network in the candidate intersatellite laser link set based on the received new link scheduling strategy, and determine it as the new target intersatellite laser link of the second physical frame to be sent under the first slice network.

[0127] As an example, as shown in FIG5 , after sending a physical frame through a new target intersatellite laser link, the link layer monitors the transmission status of the link and generates a policy execution result corresponding to the new link scheduling policy based on the monitoring result.

[0128] Among them, when the policy execution result indicates that the new target inter-satellite laser link can meet the transmission requirements of the corresponding first slice network, the link status report is uploaded normally after waiting for the next link status report upload time.

[0129] Accordingly, when the policy execution result indicates that the new target intersatellite laser link cannot meet the transmission requirements of the corresponding first slice network, a new link status report can be generated and uploaded to the network layer in a timely manner.

[0130] As shown in Figure 6, the network layer will evaluate and detect the execution effect of the new link scheduling strategy based on the received policy execution results. If the execution effect of the new link scheduling strategy does not meet the sending requirements of the first slice network, the corresponding information can be transmitted to the control end, and a new link scheduling strategy can be generated by the control end and re-sent to the link layer.

[0131] Correspondingly, if the execution effect of the new link scheduling strategy meets the sending requirements of the first slice network, a new link scheduling strategy will not be generated, and the upload of a new link status report will be waited for.

[0132] It should be noted that the inter-satellite communication method for low-orbit satellites proposed in this application, through the collaborative operation of the network layer, the control end and the link layer, conducts inter-satellite communication between low-orbit satellites by sending physical frames through the target inter-satellite laser link, and realizes support for network slicing technology, software defined network (SDN) technology and the Consultative Committee for Space Data Systems protocol (CCSDS protocol).

[0133] To better understand the reception of physical frames by low-orbit satellites, we can refer to Figure 7. As shown in Figure 7, after the low-orbit satellite receives the physical frame, it can check the frame start field, slice network identification field and error correction code field shown in Figure 7.

[0134] When the physical frame fails the error correction check, the physical frame can be discarded and returned to the physical frame receiving link; and when the physical frame passes the error correction check, the receiving process of the physical frame can be started.

[0135] As shown in FIG7 , it is determined whether there is a start identifier of the frame sequence in the physical frame. If so, it can be determined that the frame sequence in the currently received physical frame is a new frame sequence, and the reception processing of each signal frame in the new frame sequence can be started.

[0136] Accordingly, if it is identified that the frame sequence in the physical frame does not have a starting identifier of the frame sequence, it can be determined that the frame sequence of the currently received physical frame has a corresponding historical frame sequence in the set of historical frame sequences that have been received by the low-orbit satellite. It can be understood that the frame sequence and the historical frame sequence are frame sequence fragments of the same frame sequence. In this scenario, the candidate frame sequence can be added to the corresponding position of the historical frame sequence.

[0137] Furthermore, it is detected whether the frame sequence in the currently received physical frame has been completely received. If it has been completely received, the received frame sequence is uploaded to the corresponding processing layer.

[0138] The inter-satellite communication method for low-orbit satellites proposed in the present application constructs a first physical frame corresponding to a first slice network, and fills the target signal frame into the corresponding first physical frame to obtain a filled second physical frame, and realizes the inter-satellite communication of low-orbit satellites by sending the second physical frame, so that the inter-satellite communication between low-orbit satellites is compatible with multiple types of signal frames, and optimizes the applicability and practicality of the inter-satellite communication method of low-orbit satellites. In the scenario where the signal frame is a MAC frame, compatibility with the Ethernet MAC protocol is achieved, and multiplexing of the ground network is achieved, which reduces the development cost and maintenance cost of the inter-satellite communication of low-orbit satellites. The second physical frame is transmitted through the inter-satellite laser link, which improves the stability of signal interaction between low-orbit satellites and optimizes the signal interaction method between low-orbit satellites.

[0139] Corresponding to the inter-satellite communication methods for low-orbit satellites proposed in the above-mentioned embodiments, an embodiment of the present application further proposes an inter-satellite communication device for low-orbit satellites. Since the inter-satellite communication device for low-orbit satellites proposed in the embodiment of the present application corresponds to the inter-satellite communication methods for low-orbit satellites proposed in the above-mentioned embodiments, the implementation methods of the above-mentioned inter-satellite communication methods for low-orbit satellites are also applicable to the inter-satellite communication device for low-orbit satellites proposed in the embodiments of the present application, and will not be described in detail in the following embodiments.

[0140] To implement the above embodiment, the present application further proposes an inter-satellite communication device for a low-orbit satellite. FIG8 is a schematic structural diagram of an inter-satellite communication device for a low-orbit satellite according to an embodiment of the present application. As shown in FIG8 , the inter-satellite communication device 800 for a low-orbit satellite includes:

[0141] The first acquisition module 81 is used to acquire multiple candidate signal frames in the candidate frame sequence to be processed by the low-orbit satellite, and identify the first slice network to which each of the multiple candidate signal frames belongs.

[0142] The second acquisition module 82 is used to acquire a first physical frame of the first slice network, and obtain a target signal frame of the first physical frame from multiple candidate signal frames and fill it to obtain a filled second physical frame.

[0143] The transmission module 83 is configured to determine a target intersatellite laser link and a target receiving end corresponding to the second physical frame, and transmit the second physical frame to the target receiving end via the target intersatellite laser link.

[0144] It should be noted that the explanation of the aforementioned embodiment of the inter-satellite communication method for low-orbit satellites is also applicable to the inter-satellite communication device for low-orbit satellites in this embodiment, and will not be repeated here.

[0145] In an embodiment of the present application, the first acquisition module 81 is also used to: obtain the second network slice identifier of the second slice network of the low-orbit satellite, and the network field identifier of the candidate signal frame; in response to the second network slice identifier matching the network field identifier, determine that the second slice network is the first slice network to which the candidate signal frame belongs.

[0146] In an embodiment of the present application, the second acquisition module 82 is further used to: obtain a first slice network identifier of the first slice network; and filter out a target signal frame from multiple candidate signal frames based on a network field identifier of the candidate signal frame, wherein the network field identifier of the target signal frame matches the first slice network identifier.

[0147] In an embodiment of the present application, the second acquisition module 82 is further used to: in response to identifying that there is padding space in the first physical frame, obtain a target signal frame for the first physical frame; in response to identifying that there is no padding space in the first physical frame, construct a new blank physical frame of the first slice network as a new first physical frame, and obtain a target signal frame for the new first physical frame.

[0148] In an embodiment of the present application, the transmission module 83 is further used to: identify whether the second physical frame meets the error correction code addition condition; in response to identifying that the second physical frame meets the error correction code addition condition, add the first error correction code to the second physical frame, and transmit the added second physical frame to the target receiving end through the target inter-satellite laser link.

[0149] In an embodiment of the present application, the transmission module 83 is further used to: in response to identifying that there is no remaining padding space in the second physical frame, determine that the second physical frame meets the error correction code addition condition; in response to identifying that there is remaining padding space in the second physical frame and there is no new candidate frame sequence on the low-orbit satellite, determine that the second physical frame meets the error correction code addition condition.

[0150] In an embodiment of the present application, the first acquisition module 81 is also used to: obtain the third physical frame received by the low-orbit satellite, and obtain the initial frame sequence in the third physical frame, wherein the initial frame sequence includes multiple initial signal frames; obtain the second error correction code in the third physical frame, and perform an error correction check on the initial frame sequence according to the second error correction code; in response to the initial frame sequence failing the error correction check, discard the third physical frame; in response to the initial frame sequence passing the error correction check, determine the initial frame sequence as a candidate frame sequence, and determine the multiple initial frame signals as multiple candidate signal frames.

[0151] In an embodiment of the present application, the transmission module 83 is further used to: obtain the candidate link transmission status of the candidate intersatellite laser link of the low-orbit satellite; obtain the sending requirements of the first slice network, and identify whether the candidate link transmission status meets the sending requirements; in response to identifying that the candidate link transmission status meets the sending requirements, determine the candidate intersatellite laser link as the target intersatellite laser link.

[0152] In an embodiment of the present application, the transmission module 83 is further used to: monitor the real-time link transmission status of the target inter-satellite laser link; in response to monitoring that the real-time link transmission status cannot meet the transmission requirements, report link abnormality information of the target inter-satellite laser link and receive a new link scheduling strategy; and determine a new target inter-satellite laser link for the second physical frame according to the new link scheduling strategy.

[0153] In an embodiment of the present application, the first physical frame includes a frame start field, a slice network identification field, a reserved bit field, a frame segment length field, a frame segment start and end identification field, a frame segment field, and an error correction code field.

[0154] In the embodiment of the present application, the initial signal frame, the candidate signal frame and the target signal frame are MAC frames.

[0155] The inter-satellite communication device for a low-orbit satellite proposed in the present application obtains a candidate frame sequence to be processed by the low-orbit satellite, and identifies the first slice network to which each of the multiple candidate signal frames in the candidate frame sequence belongs. For any first slice network, the device obtains the first physical frame to be filled under the first slice network, and selects and fills at least one target signal frame for filling the first physical frame from the multiple candidate signal frames, thereby obtaining a filled second physical frame, obtaining a target inter-satellite laser link for transmitting the second physical frame, and a target receiving end for receiving the second physical frame, and transmitting the frame to be sent obtained based on the second physical frame to the target receiving end through the target inter-satellite laser link. In the present application, a first physical frame corresponding to the first slice network is constructed, and the target signal frame is filled into the corresponding first physical frame to obtain a filled second physical frame. The inter-satellite communication of low-orbit satellites is realized by sending the second physical frame, so that the inter-satellite communication between low-orbit satellites is compatible with multiple types of signal frames, and the applicability and practicality of the inter-satellite communication method of low-orbit satellites are optimized. In the scenario where the signal frame is a MAC frame, compatibility with the Ethernet MAC protocol is achieved, and multiplexing of the ground network is achieved, which reduces the development cost and maintenance cost of the inter-satellite communication of low-orbit satellites. The frames to be sent are transmitted through the inter-satellite laser link, which improves the stability of the signal interaction between low-orbit satellites and optimizes the signal interaction method between low-orbit satellites.

[0156] In order to implement the above embodiments, the present application also proposes an electronic device, comprising: a processor, and a memory communicatively connected to the processor; the memory stores computer-executable instructions; the processor executes the computer-executable instructions stored in the memory to implement the inter-satellite communication method of the low-orbit satellite provided in the above embodiments.

[0157] In order to implement the above embodiments, the present application also proposes a computer-readable storage medium, which stores computer-executable instructions. When the computer-executable instructions are executed by a processor, they are used to implement the inter-satellite communication method of low-orbit satellites provided in the above embodiments.

[0158] In order to implement the above embodiments, the present application also proposes a computer program product, including a computer program, which, when executed by a processor, implements the inter-satellite communication method for low-orbit satellites provided in the above embodiments.

[0159] The collection, storage, use, processing, transmission, provision and disclosure of user personal information involved in this application are in compliance with relevant laws and regulations and do not violate public order and good morals.

[0160] It is important to note that personal information collected from users should be used for legitimate and reasonable purposes and should not be shared or sold beyond these legitimate uses. Furthermore, such collection / sharing should be conducted only after receiving the user's informed consent, including but not limited to notifying the user to read the user agreement / user notice and sign an agreement / authorization that includes the relevant user information before using the feature. Furthermore, any necessary steps must be taken to safeguard and secure access to such personal information and ensure that others with access to personal information comply with its privacy policy and procedures.

[0161] This application contemplates providing implementations that allow users to selectively block the use or access of personal information data. Specifically, this disclosure contemplates providing hardware and / or software to prevent or block access to such personal information data. Risks can be minimized by limiting data collection and deleting data once it is no longer needed. Furthermore, where applicable, such personal information can be de-identified to protect user privacy.

[0162] In the descriptions of the foregoing embodiments, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, unless they are mutually inconsistent.

[0163] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of such features. Throughout the description of this application, "plurality" means at least two, for example, two, three, etc., unless otherwise specifically defined.

[0164] Any process or method description in a flowchart or otherwise described herein may be understood to represent a module, segment or portion of code comprising one or more executable instructions for implementing the steps of a custom logical function or process, and the scope of the preferred embodiments of the present application includes alternative implementations in which functions may be performed out of the order shown or discussed, including performing functions in a substantially simultaneous manner or in the reverse order depending on the functions involved, which should be understood by those skilled in the art to which the embodiments of the present application belong.

[0165] The logic and / or steps represented in the flowcharts or otherwise described herein, for example, can be considered as a sequenced list of executable instructions for implementing the logical functions, and can be embodied in any computer-readable medium for use by, or in conjunction with, an instruction execution system, apparatus, or device (e.g., a computer-based system, a system including a processor, or other system that can fetch and execute instructions from an instruction execution system, apparatus, or device). For purposes of this specification, a "computer-readable medium" can be any device that can contain, store, communicate, propagate, or transport a program for use by, or in conjunction with, an instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of computer-readable media include the following: an electrical connection with one or more wires (electronic devices), a portable computer disk cartridge (magnetic device), random access memory (RAM), read-only memory (ROM), erasable and programmable read-only memory (EPROM or flash memory), fiber optic devices, and a portable compact disc read-only memory (CDROM). Furthermore, the computer-readable medium may even be paper or other suitable medium on which the program is printed, since the program may be obtained electronically, for example, by optically scanning the paper or other medium and then editing, interpreting or processing it in another suitable manner if necessary, and then storing it in a computer memory.

[0166] It should be understood that various parts of the present application can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented using software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented using hardware, as in another embodiment, any one of the following technologies known in the art or a combination thereof can be used to implement: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application-specific integrated circuit having a suitable combination of logic gate circuits, a programmable gate array (PGA), a field programmable gate array (FPGA), etc.

[0167] Those skilled in the art will understand that all or part of the steps in the method of the above embodiment can be completed by instructing related hardware through a program, and the program can be stored in a computer-readable storage medium. When the program is executed, it includes one or a combination of the steps of the method embodiment.

[0168] In addition, the functional units in the various embodiments of the present application may be integrated into a processing module, or each unit may exist physically separately, or two or more units may be integrated into a module. The above-mentioned integrated module may be implemented in the form of hardware or in the form of a software functional module. If the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it may also be stored in a computer-readable storage medium.

[0169] The storage medium mentioned above may be a read-only memory, a magnetic disk, or an optical disk, etc. Although the embodiments of the present application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present application. Persons skilled in the art may make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present application.

Claims

1. An inter-satellite communication method for low Earth orbit satellites, characterized in that, The method includes: Obtaining a plurality of candidate signal frames in a candidate frame sequence of a low-earth orbit satellite, and identifying a first slice network to which the candidate signal frames belong; Obtaining a first physical frame of the first slice network, and obtaining a target signal frame of the first physical frame from the plurality of candidate signal frames and filling it to obtain a filled second physical frame; Determining a target inter-satellite laser link and a target receiving end corresponding to the second physical frame, and transmitting the second physical frame to the target receiving end through the target inter-satellite laser link.

2. The method according to claim 1, wherein The identifying the first slice network to which the candidate signal frames belong includes: Obtaining a second network slice identifier of a second slice network of the low-earth orbit satellite, and a network field identifier of the candidate signal frame; In response to the second network slice identifier matching the network field identifier, determining that the second slice network is the first slice network to which the candidate signal frames belong.

3. The method according to claim 1, characterized in that, The obtaining the first physical frame of the first slice network and obtaining the target signal frame of the first physical frame from the plurality of candidate signal frames includes: Obtaining a first slice network identifier of the first slice network; Filtering out the target signal frame from the plurality of candidate signal frames according to the network field identifier of the candidate signal frame, wherein the network field identifier of the target signal frame matches the first slice network identifier.

4. The method according to claim 3, characterized in that Before filtering out the target signal frame from the plurality of candidate signal frames according to the network field identifier of the candidate signal frame, wherein the network field identifier of the target signal frame matches the first slice network identifier, it includes: In response to identifying that there is a filling space in the first physical frame, obtaining the target signal frame for the first physical frame; In response to identifying that there is no filling space in the first physical frame, constructing a new blank physical frame of the first slice network as the new first physical frame, and obtaining the target signal frame for the new first physical frame.

5. The method according to claim 1, characterized in that, The transmitting the second physical frame to the target receiving end through the target inter-satellite laser link includes: Identifying whether the second physical frame meets the error correction code addition condition; In response to identifying that the second physical frame meets the error correction code addition condition, adding a first error correction code to the second physical frame, and transmitting the added second physical frame to the target receiving end through the target inter-satellite laser link.

6. The method according to claim 5, characterized in that, The identifying whether the second physical frame meets the error correction code addition condition includes: In response to identifying that the second physical frame has no remaining filling space, determining that the second physical frame meets the error correction code addition condition; In response to identifying that the second physical frame has remaining filling space and there is no new candidate frame sequence on the low-earth orbit satellite, determining that the second physical frame meets the error correction code addition condition.

7. The method according to claim 1, characterized in that, The obtaining a plurality of candidate signal frames in a candidate frame sequence of a low-earth orbit satellite includes: Obtaining a third physical frame received by the low-earth orbit satellite, and obtaining an initial frame sequence in the third physical frame, wherein the initial frame sequence includes a plurality of initial signal frames; Obtaining a second error correction code in the third physical frame, and performing error correction check on the initial frame sequence according to the second error correction code; In response to the initial frame sequence failing the error correction check, discard the third physical frame; In response to the initial frame sequence passing the error correction check, determine the initial frame sequence as the candidate frame sequence, and determine multiple initial frame signals as multiple candidate signal frames.

8. The method according to claim 1, wherein The determining the target inter-satellite laser link corresponding to the second physical frame includes: Obtain the candidate link transmission status of the candidate inter-satellite laser links of the low-earth orbit satellite; Obtain the transmission requirements of the first slice network, and identify whether the candidate link transmission status meets the transmission requirements; In response to identifying that the candidate link transmission status meets the transmission requirements, determine the candidate inter-satellite laser link as the target inter-satellite laser link.

9. The method according to claim 8, characterized in that, After determining the target inter-satellite laser link corresponding to the second physical frame, include: Monitor the real-time link transmission status of the target inter-satellite laser link; In response to monitoring that the real-time link transmission status cannot meet the transmission requirements, report the link exception information of the target inter-satellite laser link, and receive a new link scheduling policy; According to the new link scheduling policy, determine a new target inter-satellite laser link for the second physical frame.

10. The method according to any one of claims 1-9, characterized in that, The first physical frame includes a frame start field, a slice network identification field, a reserved bit field, a frame segment length field, a frame segment start and end identification field, a frame segment field, and an error correction code field.

11. The method according to any one of claims 1-9, characterized in that, The initial signal frame, the candidate signal frame, and the target signal frame are MAC frames.

12. An inter-satellite communication system for low-earth orbit satellites, characterized in that, The system includes a link layer, wherein the link layer is used for: Obtain multiple candidate signal frames in the candidate frame sequence of the low-earth orbit satellite, and identify the first slice network to which the candidate signal frames belong; Obtain the first physical frame of the first slice network, and obtain and fill the target signal frame of the first physical frame from multiple candidate signal frames to obtain a filled second physical frame; Determine the target inter-satellite laser link for transmitting the second physical frame and the target receiving end for receiving the second physical frame; Transmit the second physical frame to the target receiving end through the target inter-satellite laser link.

13. The system according to claim 12, wherein The system further includes a network layer and a control end, wherein The network layer is used for sending a link scheduling policy to the link layer, and the link layer determines the target inter-satellite laser link for the second physical frame through the link scheduling policy; The control end is used for generating the link scheduling policy and transmitting it to the network layer.

14. An inter-satellite communication device for a low-earth orbit satellite, characterized in that, The device includes: A first acquisition module, configured to acquire multiple candidate signal frames in the candidate frame sequence of the low-earth orbit satellite, and identify the first slice network to which the candidate signal frames belong; A second acquisition module, configured to acquire the first physical frame of the first slice network, and acquire and fill the target signal frame of the first physical frame from multiple candidate signal frames to obtain a filled second physical frame; A transmission module, configured to determine the target inter-satellite laser link and the target receiving end corresponding to the second physical frame, and transmit the second physical frame to the target receiving end through the target inter-satellite laser link.

15. The device according to claim 14, characterized in that, The first acquisition module is further used for: Obtain the second network slice identifier of the second slice network of the LEO satellite, and the network field identifier of the candidate signal frame; In response to the matching of the second network slice identifier and the network field identifier, determine that the second slice network is the first slice network to which the candidate signal frame belongs.

16. The device according to claim 14, characterized in that, The second acquisition module is further configured to: Obtain the first slice network identifier of the first slice network; According to the network field identifier of the candidate signal frame, screen out the target signal frame from multiple candidate signal frames, wherein the network field identifier of the target signal frame matches the first slice network identifier.

17. The device according to claim 16, characterized in that, The second acquisition module is further configured to: In response to identifying that there is a padding space in the first physical frame, obtain the target signal frame for the first physical frame; In response to identifying that there is no padding space in the first physical frame, construct a new blank physical frame of the first slice network as the new first physical frame, and obtain the target signal frame for the new first physical frame.

18. The device according to claim 14, wherein The transmission module is further configured to: Identify whether the second physical frame meets the error correction code addition condition; In response to identifying that the second physical frame meets the error correction code addition condition, add a first error correction code to the second physical frame, and transmit the added second physical frame to the target receiving end through the target inter-satellite laser link.

19. The device according to claim 18, characterized in that, The transmission module is further configured to: In response to identifying that there is no remaining padding space in the second physical frame, determine that the second physical frame meets the error correction code addition condition; In response to identifying that there is remaining padding space in the second physical frame and there is no new candidate frame sequence on the LEO satellite, determine that the second physical frame meets the error correction code addition condition.

20. The device according to claim 14, characterized in that The first acquisition module is further configured to: Obtain the third physical frame received by the LEO satellite, and obtain the initial frame sequence in the third physical frame, wherein the initial frame sequence includes a plurality of initial signal frames; Obtain the second error correction code in the third physical frame, and perform error correction check on the initial frame sequence according to the second error correction code; In response to the initial frame sequence failing the error correction check, discard the third physical frame; In response to the initial frame sequence passing the error correction check, determine that the initial frame sequence is the candidate frame sequence, and determine a plurality of initial frame signals as a plurality of candidate signal frames.

21. The device according to claim 14, characterized in that, The transmission module is further configured to: Obtain the candidate link transmission status of the candidate inter-satellite laser link of the LEO satellite; Obtain the transmission requirement of the first slice network, and identify whether the candidate link transmission status meets the transmission requirement; In response to identifying that the candidate link transmission status meets the transmission requirement, determine that the candidate inter-satellite laser link is the target inter-satellite laser link.

22. The device according to claim 21, characterized in that, The transmission module is further configured to: Monitor the real-time link transmission status of the target inter-satellite laser link; In response to monitoring that the real-time link transmission status cannot meet the transmission requirement, report the link exception information of the target inter-satellite laser link, and receive a new link scheduling policy; According to the new link scheduling policy, determine a new target inter-satellite laser link for the second physical frame.

23. The device according to any one of claims 14 - 22, characterized in that, The first physical frame includes a frame start field, a slice network identification field, a reserved bit field, a frame fragment length field, a frame fragment start and end identification field, a frame fragment field, and an error correction code field.

24. The device according to any one of claims 14 - 22, characterized in that, The initial signal frame, the candidate signal frame, and the target signal frame are MAC frames.

25. An electronic device, characterized in that, Including: a processor, and a memory communicatively connected to the processor; the memory stores computer-executable instructions; the processor executes the computer-executable instructions stored in the memory to implement any one of claims 1-11 the method described above.

26. A computer-readable storage medium, characterized in that, Computer-executable instructions are stored in the computer-readable storage medium, and when the computer-executable instructions are executed by a processor, they are used to implement the method described in any one of claims 1-11.

27. A computer program product, characterized in that, Including a computer program, which when executed by a processor implements the method described in any one of claims 1-11.

Images