Inter-satellite communication method and device

Abstract

The invention provides an inter-satellite communication method and device. The method comprises the following steps: acquiring first communication state information of a first satellite; generating a first physical frame signal according to the first communication state information; a first physical frame signal is sent to a second satellite, and the second satellite and the first satellite are located in the same communication link and are adjacent to each other; a second physical frame signal sent by a second satellite is received, the second physical frame signal is sent according to the first communication state information in the first physical frame signal, and the second physical frame signal is used for transmitting the first service data, so that the second satellite can acquire the first communication state information of the first satellite in time; and the second satellite sends the second physical frame signal to the first satellite under the condition of acquiring the communication state information of the first satellite, so that the timeliness and the high efficiency of communication between the first satellite and the second satellite are improved.

Description

Technical Field

[0001] The present disclosure relates to the field of satellite communication technology, and in particular to an inter-satellite communication method and device. Background Art

[0002] At present, satellite Internet has become the focus of development in the global information and communication field. Many international constellations have been deployed on a large scale, especially the rapid development of low-orbit satellite constellations. Space laser links are an important part of satellite Internet transmission links, with the advantages of large communication capacity, strong anti-electromagnetic interference ability, good confidentiality, and no need for radio frequency licenses.

[0003] During the communication between two adjacent satellites in a space laser link, one of the satellites can only determine the communication status information of the other satellite through ground-based notification. This method has a high latency problem and may result in the inability to determine the communication status information of the other satellite in a timely manner, thereby resulting in the inability of the two adjacent satellites to conduct intersatellite communication in a timely and efficient manner. Summary of the invention

[0004] The present disclosure aims to solve one of the technical problems in the related art at least to some extent.

[0005] To this end, the first purpose of the present disclosure is to propose an inter-satellite communication method, so as to generate a first physical frame signal according to the first communication status information of the first satellite, and send the first physical frame signal to the second satellite, so that the second satellite can obtain the first communication status information of the first satellite in time, and the second satellite sends the second physical frame signal to the first satellite when knowing the first communication status information of the first satellite (for example, orbital position, statistical bit error rate, etc.), so that when the second satellite knows that the communication performance of the first satellite has declined according to the bit error rate in the first communication status information of the first satellite, it can re-plan the space networking whole network link, thereby improving the timeliness of the space networking whole network link planning, and at the same time, the second satellite can obtain the orbital position of the first satellite in time according to the communication status information of the first satellite, and when the inter-satellite link is disconnected during the communication with the first satellite, the inter-satellite link can be reconnected in time according to the orbital position of the first satellite, thereby reducing the time for reconnecting the inter-satellite link during the communication process, thereby improving the timeliness and efficiency of the communication between the first satellite and the second satellite.

[0006] The second objective of the present disclosure is to provide an inter-satellite communication device.

[0007] A third objective of the present disclosure is to provide an electronic device.

[0008] A fourth objective of the present disclosure is to provide a computer-readable storage medium.

[0009] A fifth object of the present disclosure is to provide a computer program product.

[0010] To achieve the above-mentioned purpose, the first aspect embodiment of the present disclosure proposes an inter-satellite communication method, including: obtaining first communication status information of a first satellite; generating a first physical frame signal based on the first communication status information; sending the first physical frame signal to a second satellite, wherein the second satellite is in the same communication link as the first satellite and is adjacent to the first satellite; receiving a second physical frame signal sent by the second satellite, wherein the second physical frame signal is sent based on the first communication status information in the first physical frame signal, and the second physical frame signal is used to transmit first business data.

[0011] The inter-satellite communication method of the disclosed embodiment obtains first communication status information of a first satellite; generates a first physical frame signal according to the first communication status information; sends the first physical frame signal to a second satellite, wherein the second satellite is in the same communication link as the first satellite and is adjacent to the first satellite; receives a second physical frame signal sent by the second satellite, wherein the second physical frame signal is sent according to the first communication status information in the first physical frame signal, and the second physical frame signal is used to transmit first business data. Thus, the first physical frame signal is generated according to the first communication status information of the first satellite, and the first physical frame signal is sent to the second satellite, so that the second satellite can obtain the first communication status information of the first satellite in a timely manner, and the second satellite obtains the first communication status information of the first satellite in a timely manner. When the first communication status information of the first satellite (for example, orbital position, statistical bit error rate, etc.) is known, a second physical frame signal is sent to the first satellite. When the second satellite learns that the communication performance of the first satellite has declined according to the bit error rate in the first communication status information of the first satellite, it can re-plan the link of the entire space network, thereby improving the timeliness of the planning of the entire space network link. At the same time, the second satellite can obtain the orbital position of the first satellite in time according to the communication status information of the first satellite. When an inter-satellite link is disconnected during communication with the first satellite, the inter-satellite link can be reconnected in time according to the orbital position of the first satellite, thereby reducing the time for reconnecting the inter-satellite link during communication, thereby improving the timeliness and efficiency of communication between the first satellite and the second satellite.

[0012] To achieve the above-mentioned purpose, the second aspect embodiment of the present disclosure proposes an inter-satellite communication device, including: an acquisition module, used to acquire first communication status information of a first satellite; a generation module, used to generate a first physical frame signal according to the first communication status information; a sending module, used to send the first physical frame signal to a second satellite, wherein the second satellite is in the same communication link as the first satellite and is adjacent to the first satellite; a receiving module, used to receive a second physical frame signal sent by the second satellite, wherein the second physical frame signal is sent according to the first communication status information in the first physical frame signal, and the second physical frame signal is used to transmit first business data.

[0013] To achieve the above-mentioned purpose, the third aspect embodiment of the present disclosure proposes an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the inter-satellite communication method as described in the first aspect embodiment of the present disclosure is implemented.

[0014] In order to achieve the above-mentioned objectives, the fourth aspect embodiment of the present disclosure proposes a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the inter-satellite communication method as described in the first aspect embodiment of the present disclosure is implemented.

[0015] In order to achieve the above-mentioned purpose, the fifth aspect embodiment of the present disclosure proposes a computer program product. When the instruction processor in the computer program product executes, the inter-satellite communication method as described in the first aspect embodiment of the present disclosure is implemented.

[0016] Additional aspects and advantages of the present disclosure will be given in part in the following description and in part will be obvious from the following description or learned through practice of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and / or additional aspects and advantages of the present disclosure will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0018] Figure 1 A schematic diagram of a flow chart of an inter-satellite communication method provided by an embodiment of the present disclosure;

[0019] Figure 2 A flowchart of another inter-satellite communication method provided by an embodiment of the present disclosure;

[0020] Figure 3 A schematic diagram of the virtual channel transmission overhead provided by an embodiment of the present disclosure;

[0021] Figure 4 A flowchart of another inter-satellite communication method provided by an embodiment of the present disclosure;

[0022] Figure 5 A flowchart of another inter-satellite communication method provided by an embodiment of the present disclosure;

[0023] Figure 6 A schematic diagram of a structure overhead for transmitting first communication state information provided in an embodiment of the present disclosure;

[0024] Figure 7 An exemplary schematic diagram of an intersatellite communication network architecture provided by an embodiment of the present disclosure;

[0025] Figure 8 A schematic diagram of a first physical frame structure provided in an embodiment of the present disclosure;

[0026] Fig. 9 A schematic diagram of the structure of an inter-satellite communication device provided by an embodiment of the present disclosure;

[0027] Fig.10 The invention is a block diagram of an electronic device for inter-satellite communication according to an exemplary embodiment. DETAILED DESCRIPTION

[0028] Embodiments of the present disclosure are described in detail below, examples of which 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 disclosure, and should not be construed as limiting the present disclosure.

[0029] At present, the physical frame signal transmission of the space laser communication networking system is generally a custom frame format and only includes frame synchronization header, frame header overhead, service data, FEC (Forward Error Correction) channel coding and other information, but does not have the physical frame overhead for inter-satellite information transmission. Therefore, the position, attitude, performance status and other information of the satellite laser communication payload are not shared between the two ends of the communication through the inter-satellite transmission physical frame. If the communication status of the laser communication payload of the communication peer is to be obtained, the data needs to be updated through the ground measurement and control link or on-line measurement and control.

[0030] During the laser communication between two adjacent satellites in a space laser link, the communication status information of one satellite (e.g., orbital position) is an important parameter for calculating and controlling the pointing and signal processing system of the coarse and fine tracking mechanism of the satellite laser communication terminal. In the absence of orbital information transmission between the two satellites, the target satellite can only be positioned by ground-based positioning, but this ground-based positioning method has the problem of high latency and lacks the timeliness of obtaining relevant communication status information at both ends of the link establishment, resulting in the inability of the intersatellite laser communication terminals of the two adjacent satellites to clearly understand the communication status (e.g., orbital position, attitude, etc.) of the other end in real time.

[0031] In view of the above problems, the present disclosure proposes an inter-satellite communication method and device. It should be noted that the inter-satellite communication method of the embodiment of the present disclosure can be applied to the inter-satellite communication device of the embodiment of the present disclosure, and the inter-satellite communication device can be a satellite laser communication terminal in a satellite laser communication system. The first satellite and the second satellite can correspond to a satellite laser communication terminal respectively.

[0032] The inter-satellite communication method and apparatus according to the embodiments of the present disclosure will be described below with reference to the accompanying drawings.

[0033] Figure 1 A schematic diagram of a flow chart of an inter-satellite communication method provided in an embodiment of the present disclosure.

[0034] like Figure 1 As shown, the intersatellite communication method may include the following steps:

[0035] Step 101: Acquire first communication status information of a first satellite.

[0036] In an embodiment of the present disclosure, a satellite laser communication terminal on a first satellite may obtain first communication status information of the first satellite, wherein the first communication status information may include orbital information of the first satellite (such as position information, time information, and operating rate information, etc.), statistical bit error rate (bit error rate statistics before correction and bit error rate statistics after correction), optical amplifier output power, version information (protocol version number and optical machine version number), input power received by a low noise amplifier, and a solar avoidance angle, etc.

[0037] Step 102: Generate a first physical frame signal according to the first communication state information.

[0038] In order to improve the timeliness and efficiency of intersatellite communication, a satellite in intersatellite communication can be made aware of the communication status of the other satellite in a timely manner, that is, the second satellite can be informed of the communication status of the first satellite in a timely manner. As an example, a first physical frame signal can be generated according to the first communication status information, that is, the first communication status information of the first satellite can be transmitted through the first physical frame signal.

[0039] Step 103: Send a first physical frame signal to the second satellite.

[0040] The second satellite is in the same communication link with the first satellite and is adjacent to the first satellite.

[0041] Furthermore, the first physical frame signal may be sent to the second satellite, so that the second satellite can learn the communication status information of the first satellite through the first physical frame signal.

[0042] For example, the second satellite can promptly obtain the orbital position information of the first satellite based on the first communication status information. When the intersatellite link is disconnected during the communication with the first satellite, the intersatellite link can be reconnected in time according to the orbital position of the first satellite, thereby reducing the time for reconnecting the intersatellite link during the communication process. For another example, when the second satellite learns that the communication performance of the first satellite has declined based on the bit error rate in the first communication status information, the space networking whole network link planning is re-planned, thereby improving the timeliness of the space networking whole network link planning. For another example, the second satellite can promptly learn the signal transmission power of the first satellite based on the optical amplifier output power in the first communication status information, thereby improving the timeliness of the space networking whole network link planning. In the case where the link communication performance is degraded during communication with the first satellite, it can be checked whether the link communication performance is degraded due to a decrease in the signal transmission power of the first satellite, thereby locating the link problem. For another example, the second satellite can promptly obtain the signal reception power of the first satellite based on the input power of the low noise amplifier received in the first communication status information. In the case where the link communication performance is degraded during communication with the first satellite, it can be checked whether the link communication performance is degraded due to a decrease in the signal structure power of the first satellite, thereby locating the link problem. For another example, the second satellite performs communication adaptation with the first satellite based on the version information (such as the protocol version number or the optical machine version number) in the first communication status information.

[0043] It should be noted that the second satellite is in the same communication link as the first satellite and is adjacent to the first satellite, that is, the first satellite and the second satellite are two adjacent satellites on the same laser communication link.

[0044] Step 104: Receive a second physical frame signal sent by a second satellite.

[0045] The second physical frame signal is sent according to the first communication state information in the first physical frame signal, and the second physical frame signal is used to transmit the first service data.

[0046] Further, after the second satellite learns the communication status information of the first satellite according to the first physical frame signal sent by the first satellite, it sends a second physical frame signal to the first satellite, that is, the second satellite sends service data to the first satellite after learning the communication status of the first satellite. The second physical frame signal is generated according to the first service data, and the second physical frame signal can be used to transmit the first service data.

[0047] In summary, by acquiring the first communication status information of the first satellite; generating a first physical frame signal according to the first communication status information; sending the first physical frame signal to the second satellite; and receiving the second physical frame signal sent by the second satellite, the first physical frame signal is generated according to the first communication status information of the first satellite, and the first physical frame signal is sent to the second satellite. The second satellite can obtain the first communication status information of the first satellite in a timely manner. When the second satellite learns the first communication status information of the first satellite (for example, orbital position, statistical bit error rate, etc.), the second satellite sends the second physical frame signal to the first satellite. When the second satellite learns that the communication performance of the first satellite has decreased according to the bit error rate in the first communication status information of the first satellite, the space networking whole network link planning can be re-performed, thereby improving the timeliness of the space networking whole network link planning. At the same time, the second satellite can obtain the orbital position of the first satellite in a timely manner according to the communication status information of the first satellite. When an intersatellite link is disconnected during communication with the first satellite, the intersatellite link can be reconnected in a timely manner according to the orbital position of the first satellite, thereby reducing the time for reconnecting the intersatellite link during communication, thereby improving the timeliness and efficiency of communication between the first satellite and the second satellite.

[0048] In order to clearly illustrate how the above embodiment generates a first physical frame signal according to the first communication state information, the present disclosure proposes another inter-satellite communication method.

[0049] Figure 2 A flowchart of another inter-satellite communication method provided by an embodiment of the present disclosure.

[0050] like Figure 2 As shown, the intersatellite communication method may include the following steps:

[0051] Step 201: Acquire first communication status information of a first satellite.

[0052] Step 202: Set the field value of the logical channel identification field in the frame header overhead to a first identification value.

[0053] The field value of the logical channel identification field is used to indicate the type of data being transmitted.

[0054] As an example, the first physical frame signal includes a frame header overhead and a data field, wherein the frame header overhead includes a logical channel identification field. When the field value of the logical channel identification field in the frame header overhead is set to a first identification value, the field value of the logical channel identification field can be used to indicate that the quantity type transmitted in the corresponding virtual channel is inter-satellite information. It should be noted that the first physical frame signal may also include fields such as a frame synchronization header and FEC coding.

[0055] In addition, when the field value of the logical channel identification field in the frame header overhead is set to the second identification value, the field value of the logical channel identification field can be used to indicate that the quantity type transmitted in the corresponding logical channel is service data.

[0056] Step 203: Add first communication status information to the data field corresponding to the first identification value to generate a first physical frame signal.

[0057] Furthermore, first communication status information may be added to the data field corresponding to the first identification value, thereby generating a first physical frame signal.

[0058] For example, Figure 3 As shown, the first communication state information is added to the data field corresponding to the first identification value, that is, the inter-satellite information transmission overhead is set in the virtual channel corresponding to the first identification value.

[0059] In addition, when the field value of the logical channel identification field is the second identification value, the second service data may be added to the data field corresponding to the second identification value to generate a third physical frame signal, and the third physical frame signal is sent to the second satellite.

[0060] It should be noted that, in order to improve the efficiency of intersatellite communication and reduce the occupancy of business data transmission, the transmission frequency of the first physical frame signal may be lower than the transmission frequency of the third physical frame signal. For example, the transmission frequency of the third physical frame signal may be 10 Gbps, and the transmission frequency of the first physical frame signal may be 100 Hz, that is, when the intersatellite communication rate is 10 Gbps, the transmission frequency of the first physical frame signal may be 100 Hz.

[0061] In an embodiment of the present disclosure, before sending the third physical frame signal to the second satellite, a fourth physical frame signal sent by the second satellite may be received, wherein the fourth physical frame signal is generated according to the second communication state information of the second satellite; and according to the second communication state information in the fourth physical frame signal, the third physical frame signal is sent to the second satellite. The sending frequency of the fourth physical frame signal is less than the sending frequency of the second physical frame signal.

[0062] That is to say, the first satellite sends the third physical frame signal to the second satellite based on the second communication status information of the second satellite, thereby realizing the status intercommunication between the first satellite and the second satellite, and further improving the timeliness and efficiency of inter-satellite communication. The second communication status information may include the orbit information of the second satellite (such as position information, time information, and operating rate information, etc.), statistical bit error rate (bit error rate statistics before correction and bit error rate statistics after correction), optical amplifier output power, version information (protocol version number and optical machine version number), input power received by the low noise amplifier and the solar avoidance angle, etc.

[0063] Step 204: Send a first physical frame signal to the second satellite.

[0064] The second satellite is in the same communication link with the first satellite and is adjacent to the first satellite.

[0065] Step 205: Receive a second physical frame signal sent by a second satellite.

[0066] The second physical frame signal is sent according to the first communication state information in the first physical frame signal, and the second physical frame signal is used to transmit the first service data.

[0067] In summary, by setting the field value of the logical channel identification field in the frame header overhead to the first identification value, wherein the field value of the logical channel identification field is used to indicate the type of data being transmitted; in the data domain corresponding to the first identification value, the first communication status information is added to generate a first physical frame signal, thereby generating the first physical frame signal according to the first communication status information, thereby realizing that the communication status information of the first satellite is sent to the second satellite, the second satellite can obtain the first communication status information of the first satellite in a timely manner, and when the second satellite learns the communication status information of the first satellite, the first physical frame signal is sent to the first satellite, When the second satellite learns that the communication performance of the first satellite has declined based on the bit error rate in the first communication status information of the first satellite, it can re-plan the entire space network link, thereby improving the timeliness of the entire space network link planning. At the same time, the second satellite can obtain the orbital position of the first satellite in time according to the communication status information of the first satellite. When an inter-satellite link is disconnected during communication with the first satellite, the inter-satellite link can be reconnected in time according to the orbital position of the first satellite, thereby reducing the time for reconnecting the inter-satellite link during communication, thereby improving the timeliness and efficiency of communication between the first satellite and the second satellite.

[0068] In order to clearly illustrate how the above embodiment generates a first physical frame signal according to the first communication state information, the present disclosure proposes another inter-satellite communication method.

[0069] Figure 4 A flowchart of another inter-satellite communication method provided by an embodiment of the present disclosure.

[0070] like Figure 4 As shown, the intersatellite communication method may include the following steps:

[0071] Step 401: Acquire first communication status information of a first satellite.

[0072] Step 402: Acquire multiple consecutive reserved bytes in the frame header overhead.

[0073] As an example, a plurality of consecutive reserved byte bits may be set in the frame header overhead of the first physical frame. For example, 10 consecutive reserved byte bits may be set, so that a plurality of consecutive reserved byte bits in the frame header overhead may be obtained.

[0074] Step 403: Add the first communication state information to a plurality of consecutive reserved bytes to generate a first physical frame signal.

[0075] As an example, the first communication status information can be divided into first communication status sub-information and second communication status sub-information according to the transmission frequency of each information in the first communication status information, wherein the transmission frequency of the first communication status sub-information is lower than the set frequency threshold, and the transmission frequency of the second communication status sub-information is greater than the set frequency threshold. Then, the first communication status sub-information and the second communication status sub-information are added to a plurality of consecutive reserved bytes to generate a first physical frame signal.

[0076] Step 404: Send a first physical frame signal to a second satellite.

[0077] The second satellite is in the same communication link with the first satellite and is adjacent to the first satellite.

[0078] Step 405: Receive a second physical frame signal sent by a second satellite.

[0079] The second physical frame signal is sent according to the first communication state information in the first physical frame signal, and the second physical frame signal is used to transmit the first service data.

[0080] In summary, by obtaining multiple consecutive reserved byte positions in the frame header overhead; adding the first communication status information to the multiple consecutive reserved byte positions to generate a first physical frame signal, thereby adding the first communication status information to the multiple consecutive reserved byte positions to generate a first physical frame signal, without occupying the transmission of business data, and sending the first physical frame signal to the second satellite, the first communication status information of the first satellite is sent to the second satellite, and the second satellite can obtain the first communication status information of the first satellite in time. When the second satellite knows the first communication status information of the first satellite, it sends the second physical frame signal to the first satellite, thereby improving the timeliness and efficiency of communication between the first satellite and the second satellite.

[0081] In order to clearly explain how the first communication state information is added to a plurality of consecutive reserved bytes in the above embodiment to generate a first physical frame signal, the present disclosure proposes another inter-satellite communication method.

[0082] Figure 5 A flowchart of another inter-satellite communication method provided by an embodiment of the present disclosure.

[0083] like Figure 5 As shown, the intersatellite communication method may include the following steps:

[0084] Step 501: Acquire first communication status information of a first satellite.

[0085] Step 502: Acquire multiple consecutive reserved bytes in the frame header overhead.

[0086] In the embodiment of the present disclosure, a plurality of consecutive byte bits may be reserved in the frame header overhead, for example, 10 consecutive bytes may be reserved, thereby obtaining a plurality of consecutive reserved byte bits in the frame header overhead.

[0087] Step 503: Acquire, from the first communication status information, first communication status sub-information in which the sending frequency is lower than the set frequency threshold.

[0088] In the embodiment of the present disclosure, the first communication status information may include but is not limited to orbital information of the first satellite (such as position information, time information, and operating rate information, etc.) and version information (protocol version number and optical machine version number), wherein the sending frequency requirement of the version information is relatively low, and the sending frequency of the version information may be less than the set threshold, and the sending frequency requirement of the orbital information is relatively high, and the sending frequency of the orbital information may be greater than the set threshold. Therefore, the first communication status sub-information with a sending frequency lower than the set frequency threshold can be obtained from the first communication status information.

[0089] Step 504: Acquire second communication status sub-information except the first communication status sub-information from the first communication status information.

[0090] Furthermore, from the first communication status information, second communication status sub-information other than the first communication status sub-information can be acquired.

[0091] Step 505: Add the target information in the first communication status sub-information to a plurality of consecutive first reserved byte positions arranged in front of a plurality of reserved byte positions in the first physical frame signal.

[0092] As an example, the first communication status sub-information is segmented to obtain multiple segmentation information, and a target segmentation sequence is generated based on the multiple segmentation information; the number of first physical frame signals sent to the second satellite is determined, wherein the sent first physical frame signal includes the segmentation information in the target segmentation sequence; based on the number, the target segmentation information is determined from the target segmentation sequence; and the target segmentation information is added as target information to multiple consecutive first reserved byte positions arranged in front of the multiple reserved byte positions.

[0093] That is to say, in order to reduce the occupancy of business data, the first communication status sub-information with a lower transmission frequency requirement is sent to the second satellite through multiple first physical frames. Therefore, the first communication status sub-information can be divided into multiple segmented information, and each segmented information is added to the first multiple consecutive reserved byte bits arranged in front of a first physical frame signal.

[0094] Step 506: Add the second communication status sub-information to a plurality of consecutive second reserved byte bits in the plurality of reserved byte bits in the first physical frame signal except the first reserved byte bits.

[0095] The sending frequency of the second communication status sub-information is greater than a set frequency threshold.

[0096] In the embodiment of the present disclosure, the second communication status sub-information with a higher transmission frequency requirement may be added to a plurality of consecutive second reserved byte bits in the plurality of reserved byte bits in the first physical frame signal except the first reserved byte bit.

[0097] For example, Figure 6 As shown, the first communication status sub-information can be transmitted via 256 first physical frame signals (ie, transmitted in a multi-frame form), and the second communication status sub-information is directly deployed as overhead information in the first physical frame signal.

[0098] Step 507: Send a first physical frame signal to the second satellite.

[0099] The second satellite is in the same communication link with the first satellite and is adjacent to the first satellite.

[0100] Step 508: Receive a second physical frame signal sent by a second satellite.

[0101] The second physical frame signal is sent according to the first communication state information in the first physical frame signal, and the second physical frame signal is used to transmit the first service data.

[0102] In summary, by obtaining multiple consecutive reserved byte positions in the frame header overhead; obtaining the first communication status sub-information whose sending frequency is lower than the set frequency threshold from the first communication status information; obtaining the second communication status sub-information except the first communication status sub-information from the first communication status information; adding the target information in the first communication status sub-information to the multiple consecutive first reserved byte positions arranged in front of the multiple reserved byte positions in the first physical frame signal; adding the second communication status sub-information to the multiple consecutive second reserved byte positions except the first reserved byte position in the multiple reserved byte positions in the first physical frame signal, thereby dividing the first communication status information into the first communication status sub-information and the second communication status sub-information, it is possible to transmit the first communication status information to the second satellite in a targeted manner without occupying a large amount of transmission of business data, so that the second satellite can obtain the first communication status information of the first satellite in a timely manner, and the second satellite sends the second physical frame signal to the first satellite according to the first communication status information of the first satellite obtained in a timely manner, thereby improving the timeliness and efficiency of communication between the first satellite and the second satellite.

[0103] In order to explain the above embodiment clearly, an example is given for illustration.

[0104] For example, Figure 7 As shown, Figure 7 This is an exemplary schematic diagram of an inter-satellite communication network architecture. The inter-satellite communication network may include multiple satellites, and the satellites communicate with each other via inter-satellite laser links. Figure 7 In the example, three satellites are shown. In actual implementation, the number of satellites included in the inter-satellite communication network is not limited to this. Each satellite includes a satellite access payload, a satellite router, and a satellite laser communication terminal.

[0105] Among them, the satellite access payload is used to support the access of ground terminals; the satellite router is used to support signal forwarding and routing between satellite communication payloads; the laser communication terminal is used to transmit signals between satellites through inter-satellite links; in addition, the satellite terminal is a ground user access terminal, and the ground gateway is connected to the ground network, which can receive user data transmitted through the satellite network and access the user data to other ground networks.

[0106] After the intersatellite laser link of the system is stably established, Figure 8As shown in the figure, the satellite laser communication terminal on the satellite can encapsulate the physical layer transmission frame (physical frame), and add the satellite orbit and motion information, the local receiving and transmitting light power, the statistical bit error rate, the sun avoidance angle and other communication status information to the virtual channel transmission overhead. The logical channel identifier in the physical frame can occupy 6 bits. The logical channel identifier can be used to distinguish different types of data in the inter-satellite link. For example, the logical channel identifier is 0b111111, which can be used to identify the logical channel with business data; for example, the logical channel identifier is 0b000000, which can be used to identify the inter-satellite information transmission overhead. When the logical channel identifier is 0b000000, the inter-satellite information transmission frame (the first physical frame signal) is mainly responsible for transmitting the inter-satellite link establishment, ranging and link status information, etc. The specific transmission content is shown in Table 1.

[0107] Table 1 Definition of inter-satellite information overhead in physical frame

[0108]

[0109] The transmission frequency of the inter-satellite information transmission frame may be 100 Hz; in addition, byte positions may be reserved in the inter-satellite information transmission frame, and inter-satellite information may be transmitted through the reserved byte positions. It should be noted that the inter-satellite information transmission method through the virtual channel and the inter-satellite information transmission method through the reserved byte positions may be performed selectively.

[0110] In the disclosed embodiment, intersatellite information transmission is completed through the intersatellite link. Both ends of the communication link can use the communication status information transmitted between satellites to correct the ephemeris information of the opposite communication terminal in real time to ensure a stable and reliable intersatellite laser communication link and fast reconnection of the intersatellite link after disconnection. In addition, both parties in intersatellite communication can also predict the solar eclipse situation of the other end in advance based on the solar avoidance angle provided by the other satellite.

[0111] At the same time, in terms of the intersatellite link communication status, both ends of the communication can always grasp the current communication status of the other end's intersatellite laser communication terminal through real-time monitoring of the statistical bit error rate before and after correction.

[0112] In order to implement the above embodiments, the present disclosure also proposes an inter-satellite communication device.

[0113] Fig. 9 A schematic diagram of the structure of an inter-satellite communication device provided in an embodiment of the present disclosure.

[0114] like Fig. 9 As shown, the inter-satellite communication device 900 includes: an acquisition module 910 , a generation module 920 , a sending module 930 and a receiving module 940 .

[0115] The acquisition module 910 is used to acquire the first communication state information of the first satellite; the generation module 920 is used to generate the first physical frame signal according to the first communication state information; the sending module 930 is used to send the first physical frame signal to the second satellite, wherein the second satellite is in the same communication link as the first satellite and is adjacent to the first satellite; the receiving module 940 is used to receive the second physical frame signal sent by the second satellite, wherein the second physical frame signal is sent according to the first communication state information in the first physical frame signal, and the second physical frame signal is used to transmit the first service data.

[0116] As a possible implementation method of an embodiment of the present disclosure, the first physical frame signal includes: a frame header overhead and a data field, the frame header overhead includes a logical channel identification field, and a generation module 920 is used to set the field value of the logical channel identification field in the frame header overhead to a first identification value, wherein the field value of the logical channel identification field is used to indicate the type of data transmitted; in the data field corresponding to the first identification value, the first communication status information is added to generate the first physical frame signal.

[0117] As a possible implementation of the embodiment of the present disclosure, the inter-satellite communication device 900 further includes: a setting module and a first adding module.

[0118] Among them, the setting module is used to set the field value of the logical channel identification field in the frame header overhead to the second identification value; the first adding module is used to add the second service data in the data domain corresponding to the second identification value, generate a third physical frame signal, and send the third physical frame signal to the second satellite.

[0119] As a possible implementation method of an embodiment of the present disclosure, the receiving module 940 is further used to receive a fourth physical frame signal sent by a second satellite, wherein the fourth physical frame signal is generated based on second communication status information of the second satellite; the acquisition module 910 is further used to acquire the second communication status information in the fourth physical frame signal, so as to send a third physical frame signal to the second satellite based on the second communication status information.

[0120] As a possible implementation method of an embodiment of the present disclosure, the first physical frame signal includes: a frame header overhead, the frame header overhead includes multiple consecutive reserved byte bits, and a generation module 920 is used to obtain multiple consecutive reserved byte bits in the frame header overhead; the first communication status information is added to the multiple consecutive reserved byte bits to generate the first physical frame signal.

[0121] As a possible implementation method of an embodiment of the present disclosure, the generation module 920 is also used to obtain first communication status sub-information whose sending frequency is lower than a set frequency threshold from the first communication status information; obtain second communication status sub-information other than the first communication status sub-information from the first communication status information; add the target information in the first communication status sub-information to a plurality of consecutive first reserved byte positions arranged in front of a plurality of reserved byte positions in the first physical frame signal; add the second communication status sub-information to a plurality of consecutive second reserved byte positions other than the first reserved byte position in a plurality of reserved byte positions in the first physical frame signal, wherein the sending frequency of the second communication status sub-information is greater than the set frequency threshold.

[0122] As a possible implementation method of the embodiment of the present disclosure, the generation module 920 is further used to divide the first communication status sub-information into multiple pieces of segmentation information, and generate a target segmentation sequence according to the multiple pieces of segmentation information; determine the number of first physical frame signals sent to the second satellite, wherein the sent first physical frame signal includes the segmentation information in the target segmentation sequence; determine the target segmentation information from the target segmentation sequence according to the number; and add the target segmentation information as the target information to multiple consecutive first reserved byte positions arranged in front of the multiple reserved byte positions.

[0123] As a possible implementation manner of an embodiment of the present disclosure, the first communication status information includes at least one of the following information: version information, statistical bit error rate, orbit information, optical amplifier output power, input power received by the low noise amplifier, and a sun avoidance angle.

[0124] The intersatellite communication device of the disclosed embodiment obtains first communication status information of a first satellite; generates a first physical frame signal according to the first communication status information; sends the first physical frame signal to a second satellite; and receives a second physical frame signal sent by the second satellite. Thus, the first physical frame signal is generated according to the first communication status information of the first satellite, and the first physical frame signal is sent to the second satellite. The second satellite can obtain the first communication status information of the first satellite in a timely manner. When the second satellite learns the first communication status information of the first satellite (for example, orbital position, statistical bit error rate, etc.), the second satellite sends the second physical frame signal to the first satellite. , when the second satellite learns that the communication performance of the first satellite has declined according to the bit error rate in the first communication status information of the first satellite, it can re-plan the entire space network link, thereby improving the timeliness of the entire space network link planning. At the same time, the second satellite can obtain the orbital position of the first satellite in time according to the communication status information of the first satellite. When the inter-satellite link is disconnected during the communication with the first satellite, the inter-satellite link can be reconnected in time according to the orbital position of the first satellite, thereby reducing the time for reconnecting the inter-satellite link during the communication process, thereby improving the timeliness and efficiency of the communication between the first satellite and the second satellite.

[0125] It should be noted that the above explanation of the embodiment of the inter-satellite communication method is also applicable to the inter-satellite communication device of this embodiment, and will not be repeated here.

[0126] In order to implement the above embodiments, the present application also proposes an electronic device, such as Fig.10 As shown, Fig.10 The invention is a block diagram of an electronic device for inter-satellite communication according to an exemplary embodiment.

[0127] like Fig.10 As shown, the electronic device 1000 includes:

[0128] The memory 1010 and the processor 1020, the bus 1030 connecting different components (including the memory 1010 and the processor 1020), the memory 1010 stores a computer program, and when the processor 1020 executes the program, the inter-satellite communication method described in the embodiment of the present disclosure is implemented.

[0129] Bus 1030 represents one or more of several types of bus structures, including a memory bus or memory controller, a peripheral bus, an accelerated graphics port, a processor or a local bus using any of a variety of bus architectures. For example, these architectures include but are not limited to Industry Standard Architecture (ISA) bus, Micro Channel Architecture (MAC) bus, Enhanced ISA bus, Video Electronics Standards Association (VESA) local bus and Peripheral Component Interconnect (PCI) bus.

[0130] The electronic device 1000 typically includes a variety of electronic device readable media. These media can be any available media that can be accessed by the electronic device 1000, including volatile and non-volatile media, removable and non-removable media.

[0131] The memory 1010 may also include computer system readable media in the form of volatile memory, such as random access memory (RAM) 1040 and / or cache memory 1050. The electronic device 1000 may further include other removable / non-removable, volatile / non-volatile computer system storage media. By way of example only, the storage system 1060 may be used to read and write non-removable, non-volatile magnetic media ( Fig.10 not shown, usually called a "hard drive"). Although Fig.10 Not shown, a disk drive for reading and writing to a removable non-volatile disk (e.g., a "floppy disk"), and an optical disk drive for reading and writing to a removable non-volatile optical disk (e.g., a CD-ROM, a DVD-ROM, or other optical media) may be provided. In these cases, each drive may be connected to the bus 1030 via one or more data medium interfaces. The memory 1010 may include at least one program product having a set (e.g., at least one) of program modules that are configured to perform the functions of the various embodiments of the present disclosure.

[0132] A program / utility 1080 having a set (at least one) of program modules 1070 may be stored, for example, in the memory 1010, such program modules 1070 including but not limited to an operating system, one or more application programs, other program modules, and program data, each of which or some combination may include an implementation of a network environment. The program modules 1070 generally perform the functions and / or methods of the embodiments described in the present disclosure.

[0133] The electronic device 1000 may also communicate with one or more external devices 1090 (e.g., keyboards, pointing devices, displays, etc.), one or more devices that enable a user to interact with the electronic device 1000, and / or any device that enables the electronic device 1000 to communicate with one or more other computing devices (e.g., network cards, modems, etc.). Such communication may be performed through an input / output (I / O) interface 1092. Furthermore, the electronic device 1000 may also communicate with one or more networks (e.g., a local area network (LAN), a wide area network (WAN), and / or a public network, such as the Internet) through a network adapter 1093. Fig.10 As shown, the network adapter 1093 communicates with other modules of the electronic device 1000 via the bus 1030. It should be understood that although Fig.10Not shown, other hardware and / or software modules may be used in conjunction with electronic device 1000, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems.

[0134] The processor 1020 executes various functional applications and data processing by running the programs stored in the memory 1010 .

[0135] It should be noted that the implementation process and technical principles of the electronic device of this embodiment refer to the above explanation of the inter-satellite communication of the embodiment of the present disclosure, and will not be repeated here.

[0136] In order to implement the above embodiments, the present application also proposes a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the inter-satellite communication method described in the above embodiments is implemented.

[0137] In order to implement the above embodiments, the present disclosure further provides a computer program product. When an instruction processor in the computer program product is executed, the inter-satellite communication method described in the above embodiments is executed.

[0138] In the description of this specification, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0139] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means 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 representations 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, without contradiction.

[0140] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. An intersatellite communication method, characterized in that: include: Acquiring first communication status information of a first satellite; Generate a first physical frame signal according to the first communication state information; Sending the first physical frame signal to a second satellite, wherein the second satellite is in the same communication link as the first satellite and is adjacent to the first satellite; A second physical frame signal sent by the second satellite is received, wherein the second physical frame signal is sent according to first communication state information in the first physical frame signal, and the second physical frame signal is used to transmit first service data.

2. The method according to claim 1, characterized in that The first physical frame signal includes: a frame header overhead and a data field, the frame header overhead includes a logical channel field, and the generating the first physical frame signal according to the first communication state information includes: Setting a field value of a logical channel identification field in the frame header overhead to a first identification value, wherein the field value of the logical channel identification field is used to indicate a data type of the transmitted data; The first communication status information is added to the data field corresponding to the first identification value to generate the first physical frame signal.

3. The method according to claim 2, characterized in that The method further comprises: Setting the field value of the logical channel identification field in the frame header overhead to a second identification value; In the data field corresponding to the second identification value, second service data is added to generate a third physical frame signal, and the third physical frame signal is sent to the second satellite.

4. The method according to claim 3, characterized in that Before sending the third physical frame signal to the second satellite, the method further includes: receiving a fourth physical frame signal sent by the second satellite, wherein the fourth physical frame signal is generated according to second communication state information of the second satellite; The second communication state information in the fourth physical frame signal is obtained to send the third physical frame signal to the second satellite according to the second communication state information.

5. The method according to claim 1, characterized in that The first physical frame signal includes: a frame header overhead, wherein the frame header overhead includes a plurality of consecutive reserved byte bits; The step of generating a first physical frame according to the first communication state information includes: Acquire a plurality of consecutive reserved byte bits in the frame header overhead; The first communication status information is added to the multiple consecutive reserved byte bits to generate the first physical frame signal.

6. The method according to claim 5, characterized in that The adding the communication status information to the plurality of consecutive reserved byte bits to generate the first physical frame signal includes: Acquire, from the first communication status information, first communication status sub-information in which the sending frequency is lower than a set frequency threshold; Acquire second communication status sub-information other than the first communication status sub-information from the first communication status information; Adding the target information in the first communication status sub-information to a plurality of consecutive first reserved byte bits arranged in front of the plurality of reserved byte bits in the first physical frame signal; The second communication status sub-information is added to a plurality of consecutive second reserved byte bits in the plurality of reserved byte bits in the first physical frame signal except the first reserved byte bit, wherein the sending frequency of the second communication status sub-information is greater than the set frequency threshold.

7. The method according to claim 6, characterized in that The step of determining, according to the first communication status sub-information, target information to be added to a plurality of consecutive first reserved byte positions arranged in front of a plurality of the reserved byte positions in the first physical frame signal comprises: Segmenting the first communication status sub-information to obtain a plurality of segmentation information, and generating a target segmentation sequence according to the plurality of segmentation information; Determine the number of first physical frame signals sent to the second satellite, wherein the sent first physical frame signals include segmentation information in the target segmentation sequence; Determining target segmentation information from the target segmentation sequence according to the number; The target segmentation information is added as target information to a plurality of first consecutive reserved byte positions arranged in front of the plurality of reserved byte positions.

8. The method according to claim 1, characterized in that The first communication status information includes at least one of the following information: Version information; Statistical bit error rate; Track information; OA output power; The input power received by the LNA; Sun avoidance angle.

9. An intersatellite communication device, characterized in that: include: An acquisition module, used to acquire first communication status information of a first satellite; A generating module, configured to generate a first physical frame signal according to the first communication state information; A sending module, configured to send the first physical frame signal to a second satellite, wherein the second satellite is in the same communication link as the first satellite and is adjacent to the first satellite; A receiving module is used to receive a second physical frame signal sent by the second satellite, wherein the second physical frame signal is sent according to the first communication state information in the first physical frame signal, and the second physical frame signal is used to transmit the first service data.

10. An electronic device, characterized in that: The invention comprises a memory, a processor and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the inter-satellite communication method according to any one of claims 1 to 8 is implemented.

11. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the inter-satellite communication method according to any one of claims 1 to 8 is implemented.

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