A low earth orbit satellite working mode autonomous configuration method and device

Abstract

The application discloses a kind of low-orbit satellite working mode autonomous configuration method and device, through instruction group analysis, sequential execution, telemetry verification and the full automation execution of abnormal rollback, get rid of the dependence of traditional star-ground big closed loop on artificial, significantly reduce the workload of ground artificial intervention, efficiently adapt to the batch operation and maintenance scene of large-scale constellation consisting of hundreds to thousands of satellites;By designing abnormal rollback mechanism, combined with the device state stability buffer of the first waiting time, ensure that telemetry data truly reflects the execution effect, when an exception occurs, automatically and accurately rollback to the specified instruction group to re-execute, improve the success rate of working mode configuration, avoid the whole satellite function interruption caused by single instruction error;In addition, the method can adapt to the scene constraint of low-orbit satellite single visible arc segment, without waiting for artificial intervention across arc segment, significantly shorten the complex working mode configuration cycle, improve satellite task response efficiency.

Description

Technical Field

[0001] This invention belongs to the field of low-Earth orbit satellite communication technology, specifically relating to a method and apparatus for autonomous configuration of low-Earth orbit satellite working modes. Background Technology

[0002] In traditional satellite equipment control mechanisms, a common practice is to manually compile command sequences on the ground and upload them one by one to the onboard system. During execution, telemetry data must be transmitted back to the ground for manual interpretation to confirm the current step's status and determine whether to initiate subsequent operations. This control process forms a large closed-loop control link between the satellite and the ground, entirely reliant on manual execution, resulting in a massive workload for ground control.

[0003] Especially in low-Earth orbit satellite applications, due to the limited duration of the visible arc of the ground station (usually only 8-15 minutes per visible window), the configuration of complex working modes often requires sending hundreds of command sequences, which need to be completed step by step across multiple visible arcs. This not only significantly extends the mission preparation cycle, but also causes problems such as insufficient continuity of command sequence execution and delays in manual intervention, which seriously restricts the mission response efficiency and working mode switching flexibility of the satellite system.

[0004] Faced with the scenario of a large constellation in orbit consisting of hundreds or even thousands of satellites, the working modes of onboard payload equipment are numerous, and the corresponding number of command and control state combinations is enormous. Under these circumstances, the traditional mode of relying on manual sending of commands one by one and interpreting telemetry data can no longer meet the requirements of efficiency and accuracy for complex on-orbit testing and large-scale operational maintenance of satellites.

[0005] It is evident that existing technologies still need improvement and enhancement. Summary of the Invention

[0006] To overcome the shortcomings of existing technologies, this invention provides a method and apparatus for autonomous configuration of low-Earth orbit (LEO) satellite operating modes. Through fully automated execution of command group parsing, sequential execution, telemetry verification, and anomaly rollback, it eliminates the reliance on manual intervention in traditional large-scale satellite-ground closed-loop systems, significantly reducing the workload of ground-based manual intervention and efficiently adapting to large-scale constellation batch operation and maintenance scenarios consisting of hundreds to thousands of satellites. By designing an anomaly rollback mechanism, combined with a device status stabilization buffer during the first waiting period, it ensures that telemetry data accurately reflects the execution effect. When an anomaly occurs, it automatically and accurately rolls back to the designated command group for re-execution, improving the success rate of operating mode configuration and avoiding the interruption of the entire satellite's function due to a single command error. Furthermore, this method can adapt to the scenario constraints of a single visible arc segment of a LEO satellite, eliminating the need for manual intervention across arc segments, significantly shortening the complex operating mode configuration cycle, and improving satellite mission response efficiency.

[0007] The technical solution adopted by this invention to solve its technical problem is as follows:

[0008] Step 1: Receive and parse the instruction group data to determine the number of instruction groups;

[0009] The instruction group data includes one or more instruction groups, and each instruction group includes sub-instruction information and telemetry interpretation information;

[0010] The telemetry interpretation information includes telemetry location, telemetry interpretation conditions, and rollback location;

[0011] Step 2: Determine if the current instruction group index is less than the number of instruction groups. If so, execute the sub-instruction information in sequence.

[0012] Step 3: When the first waiting time preset in the executed sub-instruction information is reached, the actual telemetry data is obtained according to the telemetry position in the telemetry interpretation information of the same instruction group;

[0013] Step 4: Compare and verify the actual telemetry data with the telemetry interpretation conditions. If the verification fails, return to execute the sub-instruction information corresponding to the rollback position.

[0014] Preferably, step 1 specifically comprises:

[0015] When instruction group data is received, the current instruction group index is initialized; the instruction group data is parsed to obtain the instruction group frame header, data type, and number of instruction groups.

[0016] Preferably, the sub-instruction information includes a sub-instruction frame header, instruction data type, first wait time, and sub-instruction content.

[0017] Preferably, step 2 specifically comprises:

[0018] Determine if the current instruction group index is less than the number of instruction groups; if so, execute the sub-instruction content in the sub-instruction information in sequence according to the sub-instruction frame header.

[0019] Preferably, step 3 specifically comprises:

[0020] When the first waiting time preset in the executed sub-instruction information is reached, the number of telemetry interpretation information included in the same instruction group is determined; when the same instruction group includes only one telemetry interpretation information, the actual telemetry data is obtained based on the telemetry position of that telemetry interpretation information; when the same instruction group includes multiple telemetry interpretation information, the actual telemetry data is obtained in sequence based on the telemetry position of each telemetry interpretation information.

[0021] Preferably, the telemetry interpretation information further includes a telemetry interpretation frame header, interpretation data type, second waiting time, and telemetry type.

[0022] Preferably, step 4 specifically comprises:

[0023] During the second waiting period, the actual telemetry data is compared with the telemetry interpretation conditions multiple times to obtain multiple comparison results; if any comparison result shows that the verification fails, the sub-instruction information corresponding to the rollback position is returned for execution.

[0024] Preferably, the comparison of the actual telemetry data with the telemetry interpretation conditions includes: when the actual telemetry data is a numerical parameter, determining whether the actual telemetry data is within the allowable error range set by the telemetry interpretation conditions; when the actual telemetry data is a state parameter, comparing the actual telemetry data with the telemetry interpretation conditions bit by bit.

[0025] Preferably, in step 4, if multiple comparison results indicate that the verification is successful, then return to determine whether the current instruction group index is less than the number of instruction groups.

[0026] A device for autonomously configuring the working mode of a low-Earth orbit satellite, comprising:

[0027] The parsing module is used to receive and parse instruction group data to determine the number of instruction groups; the instruction group data includes one or more instruction groups, each instruction group includes sub-instruction information and telemetry interpretation information; the telemetry interpretation information includes telemetry position, telemetry interpretation conditions, and rollback position.

[0028] The execution module is used to determine whether the current instruction group index is less than the number of instruction groups. If so, the sub-instruction information is executed in sequence.

[0029] The acquisition module is used to acquire actual telemetry data based on the telemetry position in the telemetry interpretation information of the same instruction group when the first waiting time preset in the executed sub-instruction information is reached.

[0030] The verification module is used to compare and verify the actual telemetry data with the telemetry interpretation conditions. If the verification fails, it returns the sub-instruction information corresponding to the rollback position.

[0031] The beneficial effects of this invention are as follows:

[0032] This invention constructs an on-board autonomous closed-loop control process through a fully automated link of instruction group parsing, sequential execution, telemetry verification, and anomaly rollback. This eliminates the reliance on manual intervention in traditional large-scale satellite-to-ground closed-loop systems, significantly reducing the workload of ground-based manual intervention and efficiently adapting to large-scale constellation batch operation and maintenance scenarios consisting of hundreds to thousands of satellites. By designing an anomaly rollback mechanism, combined with a device status stabilization buffer during the first waiting time, it ensures that telemetry data accurately reflects the execution effect. Accurate rollback to a designated instruction group for re-execution improves the success rate of working mode configuration and avoids complete satellite function interruption caused by a single instruction error. Furthermore, this method can adapt to scenarios where the single visible arc of a low-Earth orbit satellite is only 8 to 15 minutes, eliminating the need for cross-arc waiting for manual intervention, significantly shortening the configuration cycle of complex working modes, and improving satellite mission response efficiency. Attached Figure Description

[0033] Figure 1 A flowchart illustrating the method for autonomous configuration of low-Earth orbit satellite operating modes provided in this embodiment of the invention;

[0034] Figure 2 This is a schematic diagram of the structure of the low-orbit satellite autonomous configuration device provided in an embodiment of the present invention;

[0035] Figure 3 This is a schematic diagram of the structure of the autonomous configuration device for low-Earth orbit satellite working mode provided in an embodiment of the present invention;

[0036] Figure 4 This is a schematic diagram of the structure of instruction group data provided in an embodiment of the present invention. Detailed Implementation

[0037] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0038] This application discloses a method for autonomous configuration of low-Earth orbit satellite operating modes. For ease of understanding, the specific process of the embodiments of this invention is described below. Please refer to [link / reference]. Figure 1 and Figure 4 One embodiment of the autonomous configuration method for low-Earth orbit satellite operating modes in this invention includes:

[0039] 101. Receive and parse instruction group data to determine the number of instruction groups. The instruction group data includes one or more instruction groups. Each instruction group includes sub-instruction information and telemetry interpretation information. The telemetry interpretation information includes telemetry position, telemetry interpretation conditions, and rollback position.

[0040] In this embodiment, the complete instruction set and verification rules required for the satellite to configure the target working mode are obtained, i.e., instruction group data, to provide data support for subsequent autonomous execution. The parsing process of the instruction group data requires first locating the starting position of the instruction group through the instruction group frame header, and then parsening it in a structured manner according to the instruction group frame header, data type, number of instruction groups, and the order of each instruction group to ensure that the data extraction is complete and error-free.

[0041] In this embodiment, the instruction group data is designed for scenarios where low-orbit satellites have short visible arcs, complex operating modes, and large-scale constellation batch operation and maintenance. It can cover the configuration requirements of any operating mode, such as payload power-on, data transmission, attitude adjustment, etc., providing technical support for the large-scale application of satellite internet constellations.

[0042] 102. Determine if the current instruction group index is less than the number of instruction groups. If so, execute the sub-instruction information in sequence.

[0043] In this embodiment, an indexing mechanism is used to ensure that instructions are executed in a preset order, avoiding instruction execution chaos and ensuring the logical consistency of the working mode configuration.

[0044] 103. When the first waiting time preset in the executed sub-instruction information is reached, the actual telemetry data is obtained according to the telemetry position in the telemetry interpretation information of the same instruction group;

[0045] In this embodiment, the first waiting time is a necessary buffer for the on-board equipment to stabilize its state after executing the instruction content of the sub-instruction information, ensuring that the actual telemetry data obtained can truly reflect the execution effect of the sub-instruction information.

[0046] 104. Compare and verify the actual telemetry data with the telemetry interpretation conditions. If the verification fails, return to execute the sub-instruction information corresponding to the rollback position.

[0047] In this embodiment, the execution status is autonomously verified by comparing the actual telemetry data with the telemetry interpretation conditions. When an anomaly occurs, the execution is re-executed based on the rollback position to the specified sub-instruction information, thus solving the problem of manual intervention and restart after instruction execution failure in the traditional mode. The rollback position is a preset instruction group number, which is set by the ground according to the logical association configured by the working mode. For example, if an instruction group depends on the execution result of the preceding 3rd instruction group, the rollback position can be set to 3. If no rollback is required, this field is fixed as hexadecimal "0000".

[0048] The autonomous configuration method for low-Earth orbit (LEO) satellite operating modes disclosed in this invention constructs an on-board autonomous closed-loop control process through a fully automated link of command group parsing, sequential execution, telemetry verification, and anomaly rollback. This eliminates the reliance on manual intervention in traditional large-scale satellite-ground closed-loop systems, significantly reducing the workload of ground-based manual intervention and efficiently adapting to large-scale constellation batch operation and maintenance scenarios consisting of hundreds to thousands of satellites. By designing an anomaly rollback mechanism, combined with the equipment status stabilization buffer during the first waiting time, it ensures that telemetry data accurately reflects the execution effect. Accurate rollback to the designated command group for re-execution further improves the success rate of operating mode configuration and avoids the interruption of the entire satellite's function due to a single command error. Furthermore, this method can adapt to scenarios where the single visible arc of a LEO satellite is only 8 to 15 minutes, eliminating the need for manual intervention across arcs, significantly shortening the complex operating mode configuration cycle, and improving satellite mission response efficiency.

[0049] Furthermore, in this embodiment of the invention, receiving and parsing instruction group data to determine the number of instruction groups includes:

[0050] 201. When instruction group data is received, initialize the current instruction group index.

[0051] In this embodiment, the initial value of the instruction group index is usually set to 0 to mark the position of the instruction group to be executed, which is the basis for realizing the sequential execution of instructions. By initializing the instruction group index, it can be ensured that each time the instruction group data is parsed, it is executed sequentially starting from the first instruction group, avoiding the problem of instruction skipping or repeated execution caused by index residue, ensuring the sequentiality and consistency of instruction execution, and avoiding instruction execution chaos caused by parsing logic loopholes. For example, when the satellite restarts and reloads the instruction group, initializing it through the current instruction group index can ensure that the configuration process starts from the beginning.

[0052] 202. Parse the instruction group data to obtain the instruction group frame header, data type, and number of instruction groups.

[0053] In this embodiment, the overall location and attribute identification of the instruction group data are completed by parsing three core fields: the instruction group frame header, data type, and instruction group quantity. This lays the foundation for the subsequent extraction of sub-instruction information and telemetry interpretation information. Please refer to [link to relevant documentation]. Figure 4The instruction group frame header is a four-byte hexadecimal "1ACFFC1D", used as a delimiter for the instruction group data, distinguishing it from other data frames on the satellite and ensuring accurate identification of the start position of the instruction group data during parsing. The data type is a two-byte hexadecimal "CCCC", used to distinguish the type of instruction group data, such as working mode configuration instruction group, equipment test instruction group, etc., ensuring that the satellite only parses instruction group data related to the current mission and avoids confusion with other on-board data. The instruction group quantity is used to determine the total number of instruction groups n (n≥1) contained in the current instruction group data, providing a basis for subsequent steps to determine whether the current instruction group index is less than the instruction group quantity. For example, when n=5, the index needs to traverse the 5 instruction groups corresponding to 0 to 4 in sequence.

[0054] Further, in this embodiment of the invention, the sub-instruction information includes a sub-instruction frame header, instruction data type, first wait time, and sub-instruction content. It is determined whether the current instruction group index is less than the number of instruction groups; if so, the sub-instruction information is executed sequentially, including:

[0055] 301. Determine if the current instruction group index is less than the instruction group number.

[0056] In this embodiment, the existence of unexecuted sub-instruction information is determined by comparing the current instruction group index with the number of instruction groups. The current instruction group index is initialized to 0. After each instruction group is executed, the current instruction group index is automatically incremented by 1 and compared with the number of instruction groups n again. If the current instruction group index is less than the number of instruction groups n, the next instruction group is executed. If the current instruction group index is greater than or equal to the number of instruction groups n, the entire configuration process ends. For example, when n=3, the indices are 0, 1, and 2 in sequence. After the instruction group corresponding to index 2 is executed, the process terminates, thereby realizing the fully automated execution of instruction group data.

[0057] 302. If so, then execute the sub-instruction content in the sub-instruction information in sequence according to the sub-instruction frame header.

[0058] In this embodiment, please refer to Figure 4 The sub-instruction frame header is a unique identifier for the sub-instruction, ensuring that the low-orbit satellite can accurately identify the starting position of each sub-instruction information, avoiding confusion and mis-execution between sub-instruction information; the sub-instruction content is valid instruction data that can be directly recognized by the onboard equipment, such as payload power-on instructions, frequency configuration instructions, etc., and its execution effect is completely consistent with the instruction being individually uploaded from the ground, ensuring the accuracy of the configuration result.

[0059] Furthermore, in this embodiment of the invention, when the preset first waiting time in the executed sub-instruction information is reached, actual telemetry data is obtained based on the telemetry position in the telemetry interpretation information of the same instruction group, including:

[0060] 401. When the first waiting time preset in the executed sub-instruction information is reached, determine the number of telemetry interpretation information included in the same instruction group.

[0061] In this embodiment, by clearly defining the verification dimension corresponding to the current command group, a basis is provided for subsequent data acquisition. When the satellite parses the telemetry interpretation data structure of the current command group, the total number of telemetry interpretation information is determined by counting the number of telemetry interpretation frame headers (hexadecimal "EB90"). For example, if the telemetry interpretation data of a certain command group contains 3 "EB90" frame headers, it is determined that there are 3 telemetry interpretation information. Acquisition and verification logic are designed separately for scenarios with single and multiple telemetry interpretation information to ensure that the required data can be accurately acquired regardless of the number of verification dimensions, and to ensure that each verification step is performed in sequence.

[0062] 402. When the same instruction group includes only one telemetry interpretation information, the actual telemetry data is obtained based on the telemetry location of that telemetry interpretation information.

[0063] In this embodiment, when only a single telemetry dimension verification is required, the corresponding telemetry data is accurately extracted from the specified satellite real-time telemetry data stream based on the "telemetry location" field (which specifies the specific byte position of the telemetry data in the telemetry frame, such as bytes 10 to 13), the "telemetry type" field (such as rapid change telemetry, engineering telemetry), and the "telemetry length" field (the number of bytes of telemetry data to be extracted) in the telemetry interpretation information, thereby ensuring the accuracy of data extraction.

[0064] 403. When the same instruction group includes multiple telemetry interpretation information, the actual telemetry data shall be obtained in sequence based on the telemetry position of each telemetry interpretation information.

[0065] In this embodiment, when multiple dimensions need to be verified, such as when an instruction execution requires simultaneous verification of three telemetry parameters—voltage, current, and temperature—the telemetry interpretation information is extracted sequentially according to its order in the instruction group. The extraction logic for each telemetry interpretation information is consistent with that of a single scenario, ensuring the comprehensiveness of the verification. After acquiring actual telemetry data, a telemetry interpretation is performed, that is, the real-time telemetry data is compared with the telemetry interpretation conditions. Only when all telemetry interpretations pass is the instruction considered to have been successfully executed. Each telemetry interpretation information can be set with different rollback positions to achieve refined anomaly handling.

[0066] In this embodiment, the actual telemetry data is acquired after the first waiting time (t1). The first waiting time is preset by the ground according to the characteristics of the equipment. For example, if a load needs 5 seconds to stabilize after being powered on, the first waiting time is 5 seconds. This ensures that the actual telemetry data can truly reflect the stable state after the command is executed, avoids verification deviations caused by unstable equipment, and improves the configuration success rate.

[0067] Please see Figure 4 Furthermore, in this embodiment of the invention, the telemetry interpretation information further includes a telemetry interpretation frame header, interpretation data type, second waiting time, and telemetry type; the actual telemetry data is compared and verified with the telemetry interpretation conditions; if the verification fails, the sub-instruction information corresponding to the rollback position is returned, including:

[0068] 501. During the second waiting period, the actual telemetry data was compared with the telemetry interpretation conditions multiple times to obtain multiple comparison results.

[0069] In this embodiment, by performing multiple comparisons within the second waiting time, misjudgments caused by fluctuations in single telemetry data are avoided, thereby ensuring the reliability of the verification results. The second waiting time (t2) is a preset cyclic judgment time (e.g., 3 seconds) on the ground, used to perform multiple sampling comparisons after the telemetry data stabilizes, providing a time window for multiple comparisons and avoiding telemetry data anomalies caused by accidental factors such as instantaneous electromagnetic interference, thereby balancing verification efficiency and reliability and adapting to scenarios where the visible arc of low-orbit satellites is short. Within the second waiting time t2, the satellite extracts actual telemetry data at a fixed cycle and compares it with the telemetry interpretation conditions, with a cumulative comparison count greater than or equal to 3 times to ensure the statistical significance of the verification results.

[0070] In this embodiment, the telemetry interpretation frame header (“EB90”) is used to locate the starting position of the telemetry interpretation information, the interpretation data type (“5555”) is used to identify the data as telemetry interpretation information, which is different from the sub-instruction information, and the telemetry type is used to clarify the category of telemetry data, such as slow change telemetry, state telemetry, etc., to provide adaptation logic for data comparison.

[0071] 502. If any comparison result indicates that the verification fails, return the sub-instruction information corresponding to the rollback position.

[0072] In this embodiment, if a verification fails even once, the system immediately rolls back to the specified position to quickly fix the execution error, prevent error accumulation, and eliminate the need for manual intervention to restart, thereby increasing the probability of successful configuration of the working mode. Specifically, when verification fails, the satellite updates the current instruction group index to the sequence number corresponding to the rollback position, and then returns to the step of determining whether the current instruction group index is less than the number of instruction groups. All instruction groups starting from the rollback position are then re-executed. For example, if the verification of the instruction group with index 5 fails and the rollback position is 3, then the current instruction group index is updated to 3, and instruction groups 3, 4, and 5 are re-executed.

[0073] Furthermore, in this embodiment of the invention, comparing the actual telemetry data with the telemetry interpretation conditions includes:

[0074] 601. When the actual telemetry data is a numerical parameter, determine whether the actual telemetry data is within the allowable error range set by the telemetry interpretation conditions.

[0075] In this embodiment, for continuously changing physical quantities (such as voltage, current, power, etc.), an error range judgment method is adopted to adapt to the natural fluctuations of parameters, avoid unnecessary rollbacks caused by small parameter fluctuations, and improve configuration efficiency. When the actual telemetry data is a numerical parameter, the telemetry interpretation condition is the ground-preset "target value ± allowable error" range. For example, when the voltage target value is 12V and the allowable error is ±0.5V, the interpretation condition is 11.5V to 12.5V. If the actual telemetry data extracted by the satellite falls within the target value ± allowable error range, the comparison is deemed successful. The allowable error is set according to the equipment accuracy and mission requirements. For example, the voltage allowable error of a high-precision payload can be set to ±0.1V.

[0076] 602. When the actual telemetry data is a state-type parameter, compare the actual telemetry data with the telemetry interpretation conditions bit by bit.

[0077] In this embodiment, for discrete state identifiers (such as device operating status, switch status, etc.), a bit-by-bit comparison method is adopted to ensure that the states are completely consistent, avoid configuration risks caused by missing state bits, and improve the reliability of device operation. The state parameters are usually represented by binary or hexadecimal bytes (e.g., 1 byte represents 8 switch states, and each bit corresponds to one state). During comparison, the bits are compared byte by byte. If the state of all bits is consistent with the telemetry judgment condition (e.g., the judgment condition is 0x03, and the actual data is also 0x03), the comparison is considered to be successful; if any bit is inconsistent, the verification is considered to be unsuccessful.

[0078] The telemetry type field in the telemetry interpretation information implicitly identifies the parameter type. For example, voltage telemetry, circuit telemetry, and temperature telemetry are mostly numerical parameters, while status telemetry is a status parameter. The satellite can automatically match the corresponding comparison logic based on this field without additional configuration.

[0079] Furthermore, in this embodiment of the invention, after comparing and verifying the actual telemetry data with the telemetry interpretation conditions, the method further includes:

[0080] 701. If multiple comparison results indicate that the verification passed, return to the step of determining whether the current instruction group index is less than the instruction group number.

[0081] In this embodiment, if all comparisons pass within the second waiting time t2, the current command group is deemed to have passed verification, thus ensuring the certainty of the verification result. After successful verification, the satellite increments the current command group index by 1 and then returns to the step of determining whether the current command group index is less than the number of command groups, proceeding to the execution flow of the next command group. For example, after the current command group with index 2 passes verification, the index is updated to 3, and the satellite continues to determine whether 3 is less than the number of command groups n. When the command group index is updated, if the index is greater than or equal to n, meaning all command groups have passed verification, the entire working mode configuration process terminates, the satellite saves the current configuration state, and enters the target working mode. After each command group passes verification, the satellite automatically records the execution time, verification result, telemetry data, and other information of that command group, forming a configuration log, which facilitates subsequent ground querying and auditing, improving the maintainability of the system.

[0082] The above describes the method for autonomous configuration of low-Earth orbit satellite operating modes in embodiments of the present invention. The following describes the device for autonomous configuration of low-Earth orbit satellite operating modes in embodiments of the present invention. Please refer to [link to relevant documentation]. Figure 2 One embodiment of the low-Earth orbit satellite autonomous configuration device for operating modes in this invention includes:

[0083] The parsing module 801 is used to receive and parse instruction group data to determine the number of instruction groups. The instruction group data includes one or more instruction groups, and each instruction group includes sub-instruction information and telemetry interpretation information. The telemetry interpretation information includes telemetry position, telemetry interpretation conditions, and rollback position.

[0084] The execution module 802 is used to determine whether the current instruction group index is less than the number of instruction groups. If so, the sub-instruction information is executed in sequence.

[0085] The acquisition module 803 is used to acquire actual telemetry data based on the telemetry position in the telemetry interpretation information of the same instruction group when the first waiting time preset in the executed sub-instruction information is reached.

[0086] The verification module 804 is used to compare and verify the actual telemetry data with the telemetry interpretation conditions. If the verification fails, it returns the sub-instruction information corresponding to the rollback position.

[0087] Based on the same ideas as the methods in the above embodiments, the apparatus provided in this application can implement the methods in the above embodiments.

[0088] above Figure 2 The autonomous configuration device for low-Earth orbit satellite operating modes in this embodiment of the invention will be described in detail from the perspective of modular functional entities. The autonomous configuration device for low-Earth orbit satellite operating modes in this embodiment of the invention will be described in detail from the perspective of hardware processing.

[0089] Figure 3 This is a schematic diagram of a low-Earth orbit (LEO) satellite autonomous configuration device 900 provided in an embodiment of the present invention. The LEO satellite autonomous configuration device 900 can vary significantly due to different configurations or performance characteristics. It may include one or more central processing units (CPUs) 910 and a memory 920, and one or more storage media 930 (e.g., one or more flash storage devices) for storing application programs 933 or data 932. The memory 920 and storage media 930 can be temporary or persistent storage. The program stored in the storage media 930 may include one or more modules (not shown in the diagram), each module including a series of instruction operations on the LEO satellite autonomous configuration device 900. Furthermore, the processor 910 may be configured to communicate with the storage media 930 and execute the series of instruction operations in the storage media 930 on the LEO satellite autonomous configuration device 900 to implement the steps of the LEO satellite autonomous configuration method provided in the above-described method embodiments.

[0090] The autonomous configuration device 900 for low-Earth orbit satellite operation mode may also include one or more power supplies 940, one or more wired or wireless network interfaces 950, one or more input / output interfaces 960, and / or one or more operating systems 931, such as SpaceOS, SylixOS, and other embedded real-time operating systems. Those skilled in the art will understand that... Figure 3 The illustrated structure of the autonomous configuration equipment for low-Earth orbit satellite operating modes does not constitute a limitation on the autonomous configuration equipment for low-Earth orbit satellite operating modes. It may include more or fewer components than illustrated, or combine certain components, or have different component arrangements.

[0091] The present invention also provides a computer-readable storage medium, which can be a non-volatile computer-readable storage medium or a volatile computer-readable storage medium, wherein the computer-readable storage medium stores instructions that, when executed on a computer, cause the computer to perform the steps of the method for autonomous configuration of low-Earth orbit satellite working mode.

[0092] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working process of the system, device, or unit described above can be referred to the corresponding process in the foregoing method embodiments, and will not be repeated here.

[0093] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods of the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

Claims

1. A method for autonomous configuration of low earth orbit satellite operational modes, characterized in that, The method comprises the following steps: Step 1: receiving and parsing instruction group data to determine the number of instruction groups; The instruction group data comprises one or more instruction groups, each instruction group comprising sub-instruction information and telemetry interpretation information; When the instruction group data is received, initializing a current instruction group index; parsing the instruction group data to obtain an instruction group frame header, a data type and the number of instruction groups; The sub-instruction information comprises a sub-instruction frame header, an instruction data type, a first waiting time and sub-instruction content; The telemetry interpretation information comprises a telemetry position, a telemetry interpretation condition and a rollback position; Step 2: determining whether the current instruction group index is less than the number of instruction groups, and if so, executing the sub-instruction information in sequence; Step 3: when the preset first waiting time in the executed sub-instruction information is reached, obtaining actual telemetry data according to the telemetry position in the telemetry interpretation information of the same instruction group; Step 4: comparing and verifying the actual telemetry data with the telemetry interpretation condition, and if the verification fails, returning to execute the sub-instruction information corresponding to the rollback position. 2.The method of claim 1, wherein, The step 2 specifically comprises: Determining whether the current instruction group index is less than the number of instruction groups; if so, executing the sub-instruction content in the sub-instruction information in sequence according to the sub-instruction frame header.

3. The method of claim 2, wherein, The step 3 specifically comprises: When the preset first waiting time in the executed sub-instruction information is reached, determining the number of telemetry interpretation information included in the same instruction group; when the same instruction group includes only one telemetry interpretation information, obtaining actual telemetry data based on the telemetry position of the telemetry interpretation information; when the same instruction group includes multiple telemetry interpretation information, obtaining actual telemetry data based on the telemetry positions of the respective telemetry interpretation information in sequence.

4. The method of claim 3, wherein, The telemetry interpretation information further comprises a telemetry interpretation frame header, an interpretation data type, a second waiting time and a telemetry type.

5. The method of claim 4, wherein, The step 4 specifically comprises: Within the second waiting time, comparing the actual telemetry data with the telemetry interpretation condition multiple times to obtain multiple comparison results; if any comparison result indicates that the verification fails, returning to execute the sub-instruction information corresponding to the rollback position.

6. The method of claim 5, wherein, The comparison of the actual telemetry data with the telemetry interpretation condition comprises: when the actual telemetry data is a numerical parameter, determining whether the actual telemetry data is within an allowable error range set by the telemetry interpretation condition; when the actual telemetry data is a state parameter, comparing the actual telemetry data with the telemetry interpretation condition bit by bit.

7. The method of claim 6, wherein, In the step 4, if the multiple comparison results all indicate that the verification passes, returning to execute the determination of whether the current instruction group index is less than the number of instruction groups.

8. An autonomous configuration apparatus employing the autonomous configuration method of the low earth orbit satellite operation mode according to claim 1, characterized by, The method comprises: A parsing module, configured to receive and parse instruction group data to determine the number of instruction groups; the instruction group data comprises one or more instruction groups, each instruction group comprising sub-instruction information and telemetry interpretation information; the telemetry interpretation information comprises a telemetry position, a telemetry interpretation condition and a rollback position; An execution module, configured to determine whether a current instruction group index is less than the number of instruction groups, and if so, execute the sub-instruction information in sequence; An obtaining module, configured to, when a preset first waiting time in the executed sub-instruction information is reached, obtain actual telemetry data according to a telemetry position in the telemetry interpretation information of the same instruction group; A verification module is configured to compare the actual telemetry data with the telemetry interpretation condition, and if the verification fails, return to execute the sub-instruction information corresponding to the rollback position.

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