Satellite batch reconfiguration method, device and ground control platform

Abstract

This application provides a method for batch reconfiguration of satellites, comprising: a command chain generation step, determining reconfiguration commands and corresponding reconfiguration data, and generating a command chain; a satellite to be reconfigured step, determining one of multiple satellites as the current satellite to be reconfigured; a telemetry acquisition step, acquiring telemetry data of the current satellite to be reconfigured; a command transmission condition judgment step, determining whether a first non-volatile memory is idle and whether a second non-volatile memory is reconfigurable; a reconfiguration command and reconfiguration data transmission step, sending the reconfiguration command and reconfiguration data to the first non-volatile memory; a reconfiguration data verification step, verifying the reconfiguration data; an on-orbit reconfiguration step, performing code reconfiguration on the second non-volatile memory; and a command chain advancement step, determining the next satellite as the current satellite to be reconfigured and performing the telemetry acquisition step. This application solves the problem of low efficiency caused by manual operation in the existing satellite batch reconfiguration process.

Description

Technical Field

[0001] This application belongs to the technical field of satellite on-orbit reconfiguration, specifically relating to a method, apparatus, ground control platform, computer-readable storage medium, and computer program product for batch reconfiguration of satellites. Background Technology

[0002] Satellite reconfiguration refers to the dynamic adjustment or reorganization of a satellite's functional architecture, mission mode, or resource allocation during its on-orbit operation, through software or hardware, to adapt to changing space environments, mission requirements, or to cope with malfunctions. Software reconfiguration typically involves uploading new software algorithms or code to alter the satellite's signal processing flow, data transmission protocols, or mission priorities, without requiring changes to the hardware structure.

[0003] With the development of mega-constellations, software reconfiguration technology for these constellations has become indispensable. Current satellite software reconfiguration technology requires manual operation for the batch reconfiguration of each satellite, failing to achieve fully automated batch processing and resulting in low efficiency. However, as the number of satellites in mega-constellations continues to increase, potentially exceeding ten thousand in the future, manual operation for the batch reconfiguration of each satellite is clearly insufficient to meet the demands of such a large-scale deployment.

[0004] Therefore, a new method for satellite on-orbit reconfiguration is urgently needed to address the shortcomings of the existing technologies. Summary of the Invention

[0005] The main objective of this application is to provide a method, apparatus, ground control platform, computer-readable storage medium, and computer program product for batch reconfiguration of satellites, in order to solve the problem of low efficiency caused by manual operation in the existing satellite batch reconfiguration process.

[0006] To address the aforementioned technical problems, in a first aspect, this application proposes a batch reconfiguration method for multiple satellites, comprising: a command chain generation step, wherein a ground control platform determines reconfiguration commands and corresponding reconfiguration data, the number of reconfiguration commands corresponding to the number of satellites, and the ground control platform sorts the reconfiguration commands according to the arrangement order of the satellites to generate a command chain corresponding one-to-one with each of the satellites; a satellite to be reconfigured step, wherein the ground control platform determines one of the satellites as the current satellite to be reconfigured; a telemetry acquisition step, wherein the ground control platform acquires telemetry data of the current satellite to be reconfigured, each of the satellites including a first non-volatile memory and a second non-volatile memory, the capacity of the first non-volatile memory being greater than the capacity of the second non-volatile memory, and the telemetry data including the current state of the first non-volatile memory and the checksum of the second non-volatile memory; and a command transmission condition judgment step, wherein based on the telemetry data of the current satellite to be reconfigured, the ground control platform determines the first non-volatile memory... The process involves several steps: First, determining if the satellite is in an idle state and if the second non-volatile memory is reconfigurable. If neither the idle nor reconfigurable state is simultaneously satisfied, the ground control platform performs another telemetry acquisition step on the satellite to be reconfigured. Second, the reconfiguration command and data transmission step: If both the idle and reconfigurable states are satisfied, the ground control platform determines the reconfiguration command corresponding to the satellite in the command chain and sends the reconfiguration command and its corresponding reconfiguration data to the first non-volatile memory of the satellite to be reconfigured. Third, the reconfiguration data verification step: The first non-volatile memory of the satellite to be reconfigured verifies the reconfiguration data. Fourth, the on-orbit reconfiguration step: If the reconfiguration data passes the verification of the satellite to be reconfigured, the reconfiguration command performs code reconfiguration on the second non-volatile memory. Fifth, the command chain advancement step: The satellite to be reconfigured sends the execution result of the code reconfiguration to the ground control platform. Based on the execution result, the ground control platform performs the satellite determination step, determining the next satellite in the sequence of multiple satellites as the current satellite to be reconfigured, until the batch reconfiguration of multiple satellites is completed.

[0007] Furthermore, in the instruction sending condition judgment step, if the current state of the first non-volatile memory satisfies the condition of sending two or more instructions within 15 seconds, the ground control platform determines that the first non-volatile memory is in an idle state; if the check value is a four-byte hexadecimal number, the ground control platform determines that the second non-volatile memory is in a reconfigurable state.

[0008] Furthermore, in the on-orbit reconfiguration step, the verification of the satellite to be reconfigured includes: the data header, data address, data length, and checksum of the reconfigured data, which are verified by the satellite to be reconfigured.

[0009] Furthermore, after the data reconstruction verification step, the system also includes: a data reconstruction correction step, in which the reconstructed data fails the verification of the current satellite to be reconstructed, and the current satellite to be reconstructed sends the verification result to the ground control platform. Based on the verification result, the ground control platform corrects the reconstructed data of the current satellite to be reconstructed; and a command chain correction step, in which the ground control platform determines the corrected reconstructed data as the reconstructed data of the corresponding reconstructed command for the current satellite to be reconstructed, so as to update the command chain. The ground control platform then performs the telemetry acquisition step again for the current satellite to be reconstructed.

[0010] Secondly, this application provides a method for batch reconfiguration of satellites for a ground control platform, comprising: a command chain generation step, determining reconfiguration commands and corresponding reconfiguration data, wherein the number of reconfiguration commands corresponds to the number of satellites, and sorting the reconfiguration commands according to the arrangement order of the multiple satellites to generate a command chain corresponding one-to-one with each of the multiple satellites; a satellite to be reconfigured step, determining one of the multiple satellites as the current satellite to be reconfigured; a telemetry acquisition step, acquiring telemetry data of the current satellite to be reconfigured, wherein each of the multiple satellites includes a first non-volatile memory and a second non-volatile memory, the capacity of the first non-volatile memory is greater than the capacity of the second non-volatile memory, and the telemetry data includes the current state of the first non-volatile memory and the check value of the second non-volatile memory; and a command transmission condition judgment step, based on the telemetry data of the current satellite to be reconfigured. The process involves several steps: First, determining whether the first non-volatile memory is idle and whether the second non-volatile memory is reconfigurable. If neither idle nor reconfigurable conditions are met simultaneously, the telemetry acquisition step is repeated for the satellite to be reconfigured. Next, a reconstruction instruction and data transmission step is performed. If both idle and reconfigurable conditions are met, the corresponding reconstruction instruction in the instruction chain is determined, and the reconstruction instruction and its corresponding reconstruction data are sent to the first non-volatile memory of the satellite to be reconfigured. Then, a reconstruction result reception step is performed. If the reconstruction data passes the verification of the satellite to be reconfigured and code reconstruction is completed, the execution result of code reconstruction is received from the satellite to be reconfigured. Finally, an instruction chain advancement step is performed. In response to the execution result, the satellite to be reconfigured step is executed, determining the next satellite in the sequence of satellites to be reconfigured as the current satellite to be reconfigured, until the batch reconstruction of multiple satellites is completed.

[0011] Furthermore, after the reconstruction command and reconstruction data transmission steps, the system also includes: a reconstruction data correction step, in which if the reconstruction data fails the verification of the current satellite to be reconstructed, the verification result of the reconstruction data of the current satellite to be reconstructed is received, and the reconstruction data of the current satellite to be reconstructed is corrected; and a command chain correction step, in which the corrected reconstruction data is determined as the reconstruction data of the reconstruction command corresponding to the current satellite to be reconstructed, so as to update the command chain and execute the telemetry acquisition step again for the current satellite to be reconstructed.

[0012] Thirdly, this application provides a batch reconfiguration device for satellites, used on a ground control platform, comprising: a command chain generation module configured to determine reconfiguration commands and corresponding reconfiguration data, wherein the number of reconfiguration commands corresponds to the number of satellites, and the reconfiguration commands are sorted according to the arrangement order of the multiple satellites to generate a command chain corresponding one-to-one with each of the multiple satellites; a satellite to be reconfigured determination module configured to determine one of the multiple satellites as the current satellite to be reconfigured; a telemetry acquisition module configured to acquire telemetry data of the current satellite to be reconfigured, wherein each of the multiple satellites includes a first non-volatile memory and a second non-volatile memory, the capacity of the first non-volatile memory is greater than the capacity of the second non-volatile memory, and the telemetry data includes the current state of the first non-volatile memory and the check value of the second non-volatile memory; and a command transmission condition judgment module configured to determine the command transmission condition based on the current satellite to be reconfigured. The system measures whether the first non-volatile memory is idle and whether the second non-volatile memory is reconfigurable. If the idle and reconfigurable states are not simultaneously satisfied, the telemetry acquisition step is performed again on the satellite to be reconfigured. The reconstruction instruction and reconstruction data transmission module is configured to determine the reconstruction instruction corresponding to the satellite to be reconfigured in the instruction chain if the idle and reconfigurable states are simultaneously satisfied, and send the reconstruction instruction and its corresponding reconstruction data to the first non-volatile memory of the satellite to be reconfigured. The reconstruction result receiving module is configured to receive the execution result of the code reconstruction from the satellite to be reconfigured if the reconstruction data passes the verification of the satellite to be reconfigured and the code reconstruction is completed. The instruction chain advancement module is configured to execute the satellite to be reconfigured step in response to the execution result, and determine the next satellite in the multiple satellites as the current satellite to be reconfigured according to the arrangement order of the multiple satellites, until the batch reconstruction of multiple satellites is completed.

[0013] Fourthly, this application provides a ground control platform including a memory and a processor, the processor being configured to implement the steps of the method as described in the third aspect.

[0014] Fifthly, this application provides a computer storage medium having computer instructions stored thereon, which, when executed by a processor, implement the steps of the method as described in the third aspect.

[0015] Sixthly, this application also provides a computer program product, including a computer program or instructions, which, when executed by a processor, implement the steps of the method as described in the third aspect.

[0016] Compared with the prior art, this application has the following advantages: This invention automates the entire reconfiguration process based on existing reconfiguration procedures, eliminating the need for manual intervention, thereby improving the efficiency of on-orbit reconfiguration of satellite software and significantly reducing labor costs. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the composition of the giant constellation described in this application; Figure 2 This is a flowchart illustrating the batch reconfiguration method for satellites according to the first aspect of this application. Figure 3 This is a flowchart illustrating a method for batch reconfiguration of satellites for a ground control platform, representing a second aspect of an embodiment of this application. Figure 4 This is a schematic diagram of the composition structure of a batch reconfiguration device for satellites for a ground control platform, which is a third aspect of the embodiments of this application. Detailed Implementation

[0018] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. However, the embodiments described below are only some embodiments of this application, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the protection scope of this application. Unless obvious from the context or otherwise, the same reference numerals in the figures represent the same structures or operations.

[0019] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0020] Flowcharts are used in this application to illustrate the operations performed by the system according to embodiments of this application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, various steps can be processed in reverse order or simultaneously. Furthermore, other operations may be added to these processes, or one or more steps may be removed from these processes.

[0021] Please see Figure 1 The giant constellation consists of multiple satellites 100. The onboard computer of each satellite 100 communicates with the ground control platform 200 via a satellite-to-ground link, which includes an uplink and a downlink.

[0022] Please see Figure 2 The first aspect of this application proposes a method for batch reconfiguration of satellites, comprising: A1, Command Chain Generation Step: The ground control platform determines the reconstruction command and the corresponding reconstruction data. The number of reconstruction commands corresponds to the number of satellites. The ground control platform sorts the reconstruction commands according to the arrangement order of the satellites to generate a command chain that corresponds one-to-one with each of the satellites. A2, Step 1: Determine the satellite to be reconstructed. The ground control platform will identify one of the multiple satellites as the current satellite to be reconstructed. A3, Telemetry Acquisition Steps: The ground control platform acquires the telemetry data of the satellite to be reconstructed. Each of the multiple satellites includes a first non-volatile memory and a second non-volatile memory. The capacity of the first non-volatile memory is greater than the capacity of the second non-volatile memory. The telemetry data includes the current state of the first non-volatile memory and the verification value of the second non-volatile memory. A4, Command transmission condition judgment step: Based on the telemetry data of the satellite to be reconstructed, the ground control platform determines whether the first non-volatile memory is in an idle state and whether the second non-volatile memory is in a reconstructable state. If the idle state and the reconstructable state are not satisfied at the same time, the ground control platform performs the telemetry acquisition step A3 again for the satellite to be reconstructed. A5, Reconstruction Instruction and Reconstruction Data Transmission Steps: If both the idle state and the reconstructable state are satisfied, the ground control platform determines the reconstruction instruction corresponding to the satellite to be reconstructed in the instruction chain, and sends the reconstruction instruction and its corresponding reconstruction data to the first non-volatile memory of the satellite to be reconstructed. A6, Reconstruction data verification step: The first non-volatile memory of the satellite to be reconstructed verifies the reconstruction data; A7, In-orbit reconfiguration step: If the reconfiguration data passes the verification of the satellite to be reconfigured, the reconfiguration command performs code reconfiguration on the second non-volatile memory; A8, Command Chain Advancement Step: The satellite to be reconstructed sends the execution result of the code reconstruction to the ground control platform. Based on the execution result, the ground control platform executes the satellite to be reconstructed determination step, determining the next satellite among the multiple satellites as the current satellite to be reconstructed according to the arrangement order of the multiple satellites, until the batch reconstruction of multiple satellites is completed. A9, Reconstruction data correction step: If the reconstruction data fails the verification of the current satellite to be reconstructed, the current satellite to be reconstructed will send the verification result to the ground control platform. Based on the verification result, the ground control platform will correct the reconstruction data of the current satellite to be reconstructed. A10, Command Chain Correction Step: The ground control platform determines the corrected reconstruction data as the reconstruction data of the reconstruction command corresponding to the satellite to be reconstructed, so as to update the command chain. The ground control platform then performs telemetry acquisition step A3 again for the satellite to be reconstructed.

[0023] The batch reconfiguration method for satellites disclosed in this application constructs reconfiguration instructions and reconfiguration data corresponding sequentially to each satellite, forming an instruction chain corresponding to multiple satellites to be reconfigured. Telemetry is used to determine whether the current satellite to be reconfigured meets the conditions for instruction uploading. Once the conditions are met, the reconfiguration instructions and reconfiguration data are uploaded to the first non-volatile memory of the corresponding satellite. After the reconfiguration data passes verification, the reconfiguration instructions perform code reconfiguration operations on the satellite's second non-volatile memory. After the current reconfiguration instruction is sent and the code reconfiguration operation is successfully executed, the next instruction will be sent to the next satellite. This method achieves automated transmission of reconfiguration instructions, enabling continuous reconfiguration operations on multiple in-orbit satellites, improving the efficiency of batch reconfiguration of mega-constellations, and significantly reducing the cost of manual operation.

[0024] The batch reconfiguration method for satellites according to this application will be described below through a specific embodiment.

[0025] First, the ground control platform writes source code in C language, compiles it in modules, and generates an executable file format (e.g., out or bin format) for the onboard computer of the satellite to be reconstructed. Then, through automated tools, it adds data headers, data addresses, data lengths, and checksums to the reconstructed data, and converts the bin or out file into a txt file. This txt file is the final file that the onboard computer can import, which is the reconstructed data.

[0026] The reconfiguration process is expected to involve one or more satellites. The ground control platform will assign satellite numbers (e.g., "SS GEN1-54", "SS GEN1-55") based on the number of satellites and the execution order, and automatically generate corresponding reconfiguration instructions. This forms a chain of reconfiguration instructions, with each satellite to be reconfigured having its own set of reconfiguration instructions and corresponding reconfiguration data. Generally, the ground control platform will begin the reconfiguration operation with the first satellite; therefore, the first satellite is identified as the current satellite to be reconfigured.

[0027] Understandably, each reconfiguration command in the command chain needs to be checked to ensure it meets the command transmission conditions before being uploaded from the ground control platform to the satellite's onboard computer. Each satellite sends telemetry data to the ground control platform in real time via the satellite-to-ground link. This telemetry data includes the current state of the first non-volatile memory and the checksum of the second non-volatile memory. After acquiring this telemetry data, the ground control platform needs to determine whether it meets the command transmission conditions.

[0028] In the embodiments of this application, both the first non-volatile memory and the second non-volatile memory are Flash memories. By setting the capacity of the first non-volatile memory to be greater than that of the second non-volatile memory, it is ensured that the satellite to be reconstructed has sufficient memory to simultaneously receive reconstruction instructions and reconstruction data, thereby improving the stability of the satellite's on-orbit code reconstruction process.

[0029] Specifically, if the current state of the first non-volatile memory satisfies the condition of being transmitted twice or more within 15 seconds, it indicates that the first non-volatile memory of the satellite to be reconstructed is in an idle state and can perform operations such as erasing and writing. If the check value of the second non-volatile memory is a four-byte hexadecimal number (e.g., 34685CB5, 8680BEA4, 2459ADF4, etc.), this check value is the sum of the checks on the existing executable code blocks on the satellite to be reconstructed, indicating that the code in the second non-volatile memory meets the preset requirements and is in a reconstructable state, and subsequent code reconstruction operations can be performed.

[0030] If both the idle state and the reconfiguration state are met simultaneously, the ground control platform sends the first reconfiguration command and corresponding reconfiguration data of the command chain to the satellite to be reconfigured. The reconfiguration command and data are temporarily stored in the first non-volatile memory. After the reconfiguration data passes the verification of the satellite to be reconfigured, it is then written to the second non-volatile memory. If the idle state and the reconfiguration state are not met simultaneously, the ground control platform will reacquire the telemetry data of the satellite to be reconfigured until both states are met simultaneously. This configuration ensures the effectiveness of the reconfiguration command transmission.

[0031] After the satellite to be reconstructed receives the reconstruction command and corresponding reconstruction data, the first non-volatile memory will perform a verification on the data header, data address, data length, and checksum of the reconstruction data. If the reconstruction data passes the verification, the reconstruction command will be activated. The reconstruction command will perform code reconstruction on the second non-volatile memory, that is, erase the old code in the second non-volatile memory and write the new code in the reconstruction data into the second non-volatile memory. After that, the satellite to be reconstructed will send the execution result of the code reconstruction to the ground control platform. According to the execution result, the ground control platform will determine the next satellite to be reconstructed according to the arrangement order of multiple satellites, until the batch reconstruction of all satellites is completed.

[0032] If the reconstructed data fails verification, it indicates that the reconstructed data corresponding to the satellite to be reconstructed is incorrect. The satellite will then generate a verification result for the reconstructed data and send it to the ground control platform in the form of a telemetry packet. The ground control platform corrects the reconstructed data based on this result, re-determines the corrected reconstructed data as the reconstructed data corresponding to the reconstructed command for the satellite to be reconstructed, and updates the command chain accordingly. After this, it reacquires telemetry data for the satellite to be reconstructed. This setup effectively avoids interruptions in the subsequent reconstructing process due to errors in a small portion of the reconstructed data, ensuring the continuity of the on-orbit reconstructing process. Furthermore, by updating the reconstructed data corresponding to all reconstructed commands in the command chain until it is completely error-free, it ensures that subsequent reconstructing processes can directly utilize the updated command chain for complete reconstructing operations, further improving the efficiency of batch satellite reconstructing.

[0033] Please see Figure 3 The second aspect of this application proposes a batch reconfiguration method for satellites for a ground control platform, comprising: B1, Instruction chain generation step: determine the reconstruction instructions and the reconstruction data corresponding to the reconstruction instructions, the number of reconstruction instructions corresponds to the number of satellites, sort the reconstruction instructions according to the arrangement order of the multiple satellites, so as to generate an instruction chain that corresponds one-to-one with each of the multiple satellites; B2, the satellite to be reconstructed step, which determines one of the multiple satellites as the current satellite to be reconstructed; B3, Telemetry Acquisition Step: Acquire the telemetry data of the satellite to be reconstructed. Each of the multiple satellites includes a first non-volatile memory and a second non-volatile memory. The capacity of the first non-volatile memory is greater than the capacity of the second non-volatile memory. The telemetry data includes the current state of the first non-volatile memory and the check value of the second non-volatile memory. B4, instruction sending condition judgment step, based on the telemetry data of the current satellite to be reconstructed, determine whether the first non-volatile memory is in an idle state and whether the second non-volatile memory is in a reconfigurable state. If the idle state and the reconfigurable state are not satisfied at the same time, execute the telemetry acquisition step B3 again for the current satellite to be reconstructed. B5, Reconstruction Instruction and Reconstruction Data Transmission Step: If the idle state and the reconstructable state are simultaneously satisfied, determine the reconstruction instruction corresponding to the current satellite to be reconstructed in the instruction chain, and send the reconstruction instruction and its corresponding reconstruction data to the first non-volatile memory of the current satellite to be reconstructed. B6, Reconstruction Result Receiving Step: If the reconstruction data passes the verification of the current satellite to be reconstructed and the code reconstruction is completed, the execution result of the code reconstruction is received from the current satellite to be reconstructed. B7, Command Chain Advancement Step: In response to the execution result, the satellite to be reconstructed determination step is executed, and the next satellite among the multiple satellites is determined as the current satellite to be reconstructed according to the arrangement order of the multiple satellites, until the batch reconstruction of the multiple satellites is completed.

[0034] Preferably, after step B5, the method further includes: B8, Reconstruction data correction step: If the reconstruction data fails the verification of the current satellite to be reconstructed, receive the verification result of the reconstruction data of the current satellite to be reconstructed, and correct the reconstruction data of the current satellite to be reconstructed; B9, Command Chain Correction Step: The corrected reconstructed data is determined as the reconstructed data of the reconstructed command corresponding to the current satellite to be reconstructed, so as to update the command chain, and the telemetry acquisition step is executed again for the current satellite to be reconstructed.

[0035] The details of each step in this embodiment can be found in the aforementioned embodiments, and will not be repeated here.

[0036] Please see Figure 4The third aspect of this application proposes a batch reconfiguration device for satellites, used on a ground control platform, comprising: a command chain generation module configured to determine reconfiguration commands and corresponding reconfiguration data, wherein the number of reconfiguration commands corresponds to the number of satellites, and the reconfiguration commands are sorted according to the arrangement order of the multiple satellites to generate a command chain corresponding one-to-one with each of the multiple satellites; a satellite to be reconfigured determination module configured to determine one of the multiple satellites as the current satellite to be reconfigured; a telemetry acquisition module configured to acquire telemetry data of the current satellite to be reconfigured, wherein each of the multiple satellites includes a first non-volatile memory and a second non-volatile memory, the capacity of the first non-volatile memory being greater than the capacity of the second non-volatile memory, and the telemetry data including the current state of the first non-volatile memory and the check value of the second non-volatile memory; and a command transmission condition judgment module configured to determine the command transmission condition based on the current satellite to be reconfigured. The system measures whether the first non-volatile memory is idle and whether the second non-volatile memory is reconfigurable. If the idle and reconfigurable states are not simultaneously satisfied, the telemetry acquisition step is performed again on the satellite to be reconfigured. The reconstruction instruction and reconstruction data transmission module is configured to determine the reconstruction instruction corresponding to the satellite to be reconfigured in the instruction chain if the idle and reconfigurable states are simultaneously satisfied, and send the reconstruction instruction and its corresponding reconstruction data to the first non-volatile memory of the satellite to be reconfigured. The reconstruction result receiving module is configured to receive the execution result of the code reconstruction from the satellite to be reconfigured if the reconstruction data passes the verification of the satellite to be reconfigured and the code reconstruction is completed. The instruction chain advancement module is configured to execute the satellite to be reconfigured step in response to the execution result, and determine the next satellite in the multiple satellites as the current satellite to be reconfigured according to the arrangement order of the multiple satellites, until the batch reconstruction of multiple satellites is completed.

[0037] The fourth aspect of this application proposes a ground control platform, including a memory and a processor, wherein the processor is configured to implement various processes of the embodiments of the above-described satellite batch reconfiguration method and can achieve the same technical effect. To avoid repetition, it will not be described in detail here.

[0038] The processor can be a central processing unit (CPU). The processor can also be other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, or combinations of the above types of chips.

[0039] This application also provides a computer-readable storage medium storing computer program instructions that, when executed by a processor, implement the steps of the aforementioned satellite batch reconfiguration method.

[0040] This application also provides a computer program product comprising a computer program or instructions that, when executed by a processor, implement the steps of the aforementioned satellite batch reconfiguration method.

[0041] The above-mentioned batch satellite reconstruction method can be implemented as a computer program, stored on a hard disk, and loaded into a processor for execution to implement the batch satellite reconstruction method of this application.

[0042] This application also includes a computer-readable medium storing computer program code that, when executed by a processor, implements the aforementioned method for batch reconfiguration of satellites.

[0043] When the satellite batch reconfiguration method is implemented as a computer program, it can also be stored as an article of art in a computer-readable storage medium. For example, computer-readable storage media can include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, magnetic stripes), optical discs (e.g., compact discs (CDs), digital multifunction discs (DVDs)), smart cards, and flash memory devices (e.g., electrically erasable programmable read-only memory (EPROM), cards, sticks, key drives). Furthermore, the various storage media described herein can represent one or more devices and / or other machine-readable media used for storing information. The term "machine-readable medium" can include, but is not limited to, wireless channels and various other media (and / or storage media) capable of storing, containing, and / or carrying code and / or instructions and / or data.

[0044] It should be understood that the embodiments described above are merely illustrative. The embodiments described herein may be implemented in hardware, software, firmware, middleware, microcode, or any combination thereof. For hardware implementation, the processor may be implemented within one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, and / or other electronic units designed to perform the functions described herein, or combinations thereof.

[0045] Some aspects of this application can be executed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The aforementioned hardware or software may be referred to as a "data block," "module," "engine," "unit," "component," or "system." The processor may be one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. Furthermore, aspects of this application may manifest as computer products residing in one or more computer-readable media, including computer-readable program code. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, magnetic tapes, etc.), optical discs (e.g., compressed CDs, digital multifunction DVDs, etc.), smart cards, and flash memory devices (e.g., cards, sticks, key drives, etc.).

[0046] A computer-readable medium may contain a propagated data signal containing computer program code, for example, on baseband or as part of a carrier wave. This propagated signal may take various forms, including electromagnetic, optical, and so on, or suitable combinations thereof. A computer-readable medium can be any computer-readable medium other than a computer-readable storage medium, which can be connected to an instruction execution system, apparatus, or device to enable communication, propagation, or transmission of a program for use. The program code located on the computer-readable medium can be propagated through any suitable medium, including radio, cable, fiber optic cable, radio frequency signals, or similar media, or any combination of the above media.

[0047] For those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application and therefore remain within the spirit and scope of the exemplary embodiments of this application.

[0048] In some embodiments, numbers describing the quantity of components and attributes are used. It should be understood that such numbers used in the description of embodiments are modified in some examples with the terms "approximately," "approximately," or "generally." Unless otherwise stated, "approximately," "approximately," or "generally" indicates that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, which may be changed depending on the characteristics required by individual embodiments. In some embodiments, numerical parameters should take into account specified significant digits and employ a general method of digit reservation. Although the numerical ranges and parameters used to confirm their breadth of scope in some embodiments of this application are approximate values, in specific embodiments, such values ​​are set as precisely as feasible.

[0049] Although this application has been described with reference to specific embodiments, those skilled in the art should recognize that the above embodiments are only used to illustrate this application, and various equivalent changes or substitutions can be made without departing from the spirit of this application. Therefore, any changes or modifications to the above embodiments within the scope of the essential spirit of this application will fall within the scope of this application.

Claims

1. A method for batch reconfiguration of satellites, used for batch reconfiguration of multiple satellites, characterized in that, include: In the instruction chain generation step, the ground control platform determines the reconstruction instructions and the reconstruction data corresponding to the reconstruction instructions. The number of reconstruction instructions corresponds to the number of satellites. The ground control platform sorts the reconstruction instructions according to the arrangement order of the satellites to generate an instruction chain that corresponds one-to-one with each of the satellites. In the step of determining the satellite to be reconstructed, the ground control platform determines one of the multiple satellites as the current satellite to be reconstructed. In the telemetry acquisition step, the ground control platform acquires the telemetry data of the satellite currently to be reconstructed. Each of the multiple satellites includes a first non-volatile memory and a second non-volatile memory. The capacity of the first non-volatile memory is greater than the capacity of the second non-volatile memory. The telemetry data includes the current state of the first non-volatile memory and the check value of the second non-volatile memory. In the instruction sending condition judgment step, based on the telemetry data of the current satellite to be reconstructed, the ground control platform determines whether the first non-volatile memory is in an idle state and whether the second non-volatile memory is in a reconfigurable state. If the idle state and the reconfigurable state are not simultaneously satisfied, the ground control platform performs the telemetry acquisition step again for the current satellite to be reconstructed. The steps for sending reconstruction instructions and reconstruction data are as follows: If the idle state and the reconfigurable state are simultaneously satisfied, the ground control platform determines the reconstruction instruction corresponding to the current satellite to be reconfigured in the instruction chain, and sends the reconstruction instruction and its corresponding reconstruction data to the first non-volatile memory of the current satellite to be reconfigured. The data verification step involves the first non-volatile memory of the satellite to be reconstructed verifying the reconstructed data. In the on-orbit reconfiguration step, if the reconfiguration data passes the verification of the satellite to be reconfigured, the reconfiguration instruction performs code reconfiguration on the second non-volatile memory; In the instruction chain advancement step, the satellite to be reconstructed sends the execution result of the code reconstruction to the ground control platform. Based on the execution result, the ground control platform executes the satellite to be reconstructed determination step, determining the next satellite among the multiple satellites as the current satellite to be reconstructed according to the arrangement order of the multiple satellites, until the batch reconstruction of the multiple satellites is completed.

2. The batch reconfiguration method for satellites according to claim 1, characterized in that, In the instruction sending condition judgment step, if the current state of the first non-volatile memory satisfies the condition of sending two or more instructions within 15 seconds, the ground control platform determines that the first non-volatile memory is in an idle state; if the check value is a four-byte hexadecimal number, the ground control platform determines that the second non-volatile memory is in a reconfigurable state.

3. The batch reconfiguration method for satellites according to claim 1, characterized in that, In the on-orbit reconfiguration step, the verification of the satellite to be reconfigured includes: the data header, data address, data length, and checksum of the reconfigured data being verified by the satellite to be reconfigured.

4. The method for batch reconfiguration of satellites according to any one of claims 1-3, characterized in that, Following the data reconstruction and verification step, the method further includes: The data reconstruction correction step involves the following steps: If the reconstructed data fails the verification of the current satellite to be reconstructed, the current satellite to be reconstructed will send the verification result to the ground control platform. Based on the verification result, the ground control platform will correct the reconstructed data of the current satellite to be reconstructed. In the instruction chain correction step, the ground control platform determines the corrected reconstructed data as the reconstructed data of the reconstructed instruction corresponding to the current satellite to be reconstructed, so as to update the instruction chain, and the ground control platform performs the telemetry acquisition step again for the current satellite to be reconstructed.

5. A method for batch reconfiguration of satellites, used on a ground control platform, characterized in that, include: The instruction chain generation step involves determining the reconstruction instructions and the corresponding reconstruction data, wherein the number of reconstruction instructions corresponds to the number of satellites, and sorting the reconstruction instructions according to the arrangement order of the multiple satellites to generate an instruction chain that corresponds one-to-one with each of the multiple satellites. The step of determining the satellite to be reconstructed involves identifying one of the multiple satellites as the current satellite to be reconstructed. The telemetry acquisition step involves acquiring the telemetry data of the satellite currently to be reconstructed. Each of the multiple satellites includes a first non-volatile memory and a second non-volatile memory. The capacity of the first non-volatile memory is greater than the capacity of the second non-volatile memory. The telemetry data includes the current state of the first non-volatile memory and the check value of the second non-volatile memory. The instruction sending condition judgment step, based on the telemetry data of the current satellite to be reconstructed, determines whether the first non-volatile memory is in an idle state and whether the second non-volatile memory is in a reconfigurable state. If the idle state and the reconfigurable state are not simultaneously satisfied, the telemetry acquisition step is executed again for the current satellite to be reconstructed. The steps for sending reconstruction instructions and reconstruction data include: if the idle state and the reconfigurable state are simultaneously satisfied, determining the reconstruction instruction corresponding to the current satellite to be reconfigured in the instruction chain, and sending the reconstruction instruction and its corresponding reconstruction data to the first non-volatile memory of the current satellite to be reconfigured; The reconstruction result receiving step involves receiving the execution result of the code reconstruction from the current satellite to be reconstructed if the reconstruction data passes the verification of the current satellite to be reconstructed and the code reconstruction is completed. In response to the execution result, the instruction chain advancement step executes the satellite to be reconstructed determination step, which determines the next satellite among the multiple satellites as the current satellite to be reconstructed according to the arrangement order of the multiple satellites, until the batch reconstruction of the multiple satellites is completed.

6. The batch reconfiguration method for satellites according to claim 5, characterized in that, Following the reconstruction instruction and reconstruction data sending steps, the method further includes: The data reconstruction correction step involves receiving the verification result of the reconstruction data of the current satellite to be reconstructed if the reconstruction data fails the verification of the current satellite to be reconstructed, and correcting the reconstruction data of the current satellite to be reconstructed. The instruction chain correction step involves determining the corrected reconstructed data as the reconstructed data of the reconstructed instruction corresponding to the current satellite to be reconstructed, thereby updating the instruction chain, and then performing the telemetry acquisition step again on the current satellite to be reconstructed.

7. A batch reconfiguration device for satellites, used on a ground control platform, characterized in that, include: The instruction chain generation module is configured to determine the reconstruction instructions and the reconstruction data corresponding to the reconstruction instructions. The number of reconstruction instructions corresponds to the number of satellites. The reconstruction instructions are sorted according to the arrangement order of the multiple satellites to generate an instruction chain that corresponds one-to-one with each of the multiple satellites. The satellite to be reconstructed determination module is configured to determine one of the plurality of satellites as the current satellite to be reconstructed; The telemetry acquisition module is configured to acquire telemetry data of the satellite currently to be reconstructed. Each of the multiple satellites includes a first non-volatile memory and a second non-volatile memory. The capacity of the first non-volatile memory is greater than the capacity of the second non-volatile memory. The telemetry data includes the current state of the first non-volatile memory and the check value of the second non-volatile memory. The instruction sending condition judgment module is configured to determine whether the first non-volatile memory is in an idle state and whether the second non-volatile memory is in a reconfigurable state based on the telemetry data of the current satellite to be reconfigured. If the idle state and the reconfigurable state are not satisfied at the same time, the telemetry acquisition step is executed again for the current satellite to be reconfigured. The reconfiguration instruction and reconfiguration data transmission module is configured to, if the idle state and the reconfigurable state are simultaneously satisfied, determine the reconfiguration instruction in the instruction chain corresponding to the current satellite to be reconfigured, and send the reconfiguration instruction and its corresponding reconfiguration data to the first non-volatile memory of the current satellite to be reconfigured; The reconstruction result receiving module is configured to receive the execution result of the code reconstruction from the current satellite to be reconstructed if the reconstruction data passes the verification of the current satellite to be reconstructed and the code reconstruction is completed. The instruction chain advancement module is configured to, in response to the execution result, execute the satellite to be reconstructed determination step, and determine the next satellite among the multiple satellites as the current satellite to be reconstructed according to the arrangement order of the multiple satellites, until the batch reconstruction of the multiple satellites is completed.

8. A ground control platform, characterized in that, include: A memory and a processor, the processor being configured to implement the steps of the method according to any one of claims 5 or 6.

9. A computer-readable storage medium, characterized in that, It stores computer instructions that, when executed by a processor, implement the steps of the method according to any one of claims 5 or 6.

10. A computer program product, comprising a computer program or instructions, characterized in that, When the computer program or instructions are executed by a processor, they implement the steps of the method according to any one of claims 5 or 6.

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