Satellite parametric design system and method

Abstract

The invention relates to a satellite parameterization design system and method. The system comprises a parameter configuration module used for carrying out configurable setting on key parameters of a satellite measurement and control link through an uplink remote control link or a communication bus; the key parameters comprise uplink and downlink frequency points, code blocks, spacecraft identifiers, address synchronization words and encryption and decryption key parameters; the parameter backup module is used for storing the configured key parameters in at least three storage media with a power-down nonvolatile characteristic; the parameter recovery module is used for recovering the key parameters from the storage media passing the verification according to the reliability priorities of the storage media after power-on, and when all the storage media are verified to be abnormal, the key parameters are recovered to default parameters; wherein when the parameter configuration module configures parameters, a protocol with a verification algorithm is adopted, and the configured parameters issue real-time values through a downlink telemetering link so as to observe the effective state. By adopting the method, the efficiency and the safety can be improved.

Description

Technical Field

[0001] The present application relates to the field of satellite communication technology, and in particular to a satellite parametric design system and method. Background Art

[0002] A satellite's tracking and control link is the core communication link for its on-orbit operation. It consists of an uplink and a downlink. The uplink is used by ground tracking and control stations to control and manage the satellite and is the only communication link for ground-based satellite monitoring and control. The downlink is used to transmit information about the satellite's on-orbit status back to the ground station. Therefore, the reliability and security of the tracking and control link are of paramount importance.

[0003] In practice, the measurement and control links of different satellite models exhibit significant parameter differences, such as uplink and downlink frequencies, code groups in spread-spectrum systems, spacecraft identification, and address synchronization words. In traditional non-parametric designs, these parameters must be fixed within a single unit, requiring each unit to be modified to adapt to the parameters provided by the entire satellite developer. This not only increases manpower and testing costs, but also requires repeated modifications and testing for subsequent model changes, resulting in low efficiency. Furthermore, in non-parametric designs, the individual units must obtain the specific parameter values ​​from the satellite operator, posing a confidentiality risk. Summary of the Invention

[0004] Based on this, it is necessary to provide a satellite parametric design system and method to address the above technical issues.

[0005] A satellite parametric design system, comprising:

[0006] A parameter configuration module is used to configure key parameters of the satellite measurement and control link through an uplink remote control link or a communication bus; the key parameters include uplink and downlink frequencies, code groups, spacecraft identification, address synchronization words, and encryption and decryption key parameters;

[0007] A parameter backup module, configured to store the configured key parameters in at least three storage media with power-off non-volatile properties;

[0008] A parameter recovery module is used to recover the key parameters from the storage media that have passed the verification according to the reliability priority of the storage media after power-on, and to recover the default parameters when all storage media verifications are abnormal;

[0009] The parameter configuration module adopts a protocol with a verification algorithm when configuring parameters, and the configured parameters are sent down in real time through a downlink telemetry link to observe the effective status.

[0010] In one embodiment, the uplink remote control link includes a high-speed uplink mode, and the communication bus includes a CAN bus or an 422 bus.

[0011] In one embodiment, the storage medium includes FLASH, a satellite computer, and MRAM, and the reliability priorities are MRAM, satellite computer, and FLASH.

[0012] In one embodiment, if the parameters configured by the parameter configuration module are not backed up, they are automatically restored to the backup values ​​after power failure.

[0013] In one embodiment, the key parameters further include scrambling key parameters.

[0014] A satellite parameterized design method, the method comprising:

[0015] Configurable settings for key parameters of the satellite tracking and control link are made through an uplink remote control link or a communication bus. These key parameters include uplink and downlink frequencies, code groups, spacecraft identification, address synchronization words, and key encryption and decryption parameters. The configuration process uses a protocol with a verification algorithm.

[0016] Storing the configured key parameters in at least three storage media with power-off non-volatile properties;

[0017] After power-on, the key parameters are restored from the storage medium that has passed the verification according to the reliability priority of the storage medium. When all storage media verifications are abnormal, the default parameters are restored. After the parameters are configured, the real-time parameter values ​​are sent down through the downlink telemetry link to observe the effective status.

[0018] In one embodiment, the uplink remote control link includes a high-speed uplink mode, and the communication bus includes a CAN bus or an 422 bus.

[0019] In one embodiment, the storage medium includes FLASH, a satellite computer, and MRAM, and the reliability priorities are MRAM, satellite computer, and FLASH.

[0020] In one embodiment, if the parameters configured by the parameter configuration module are not backed up, they are automatically restored to the backup values ​​after power failure.

[0021] In one embodiment, the key parameters further include scrambling key parameters.

[0022] The above-mentioned satellite parameterized design system and system adopt a parameter configurable design. Key parameters such as uplink and downlink frequencies and code groups are configured through uplink remote control links, communication buses, and other paths. The configuration protocol integrates a verification algorithm and is validated through downlink telemetry observation. This allows single machines to be delivered in batches after normal parameterization testing, avoiding the problem of repeated adaptation, modification, and testing of each single machine in non-parametric designs. At the same time, the entire satellite developer can accept multiple machines at a time and allocate them to different satellites for use. The satellite service computer only needs to maintain a set of software programs, further saving costs. Because the parameterized design eliminates the need for the platform to obtain the actual values ​​of the satellite service parameters, and only the entire satellite developer or customer configures the parameters, confidentiality is significantly improved. The parameter backup and recovery design stores parameters in at least three power-off non-volatile storage media and restores the parameters according to reliability priority and verification algorithms. In the event of power failure or medium abnormality, the validity of the parameters can be guaranteed, and even the default value can be restored or reconfigured through instructions. This not only ensures link reliability but also supports on-orbit parameter modification to complete new missions or experimental verification. In summary, the present invention has significant advantages in reducing costs, improving efficiency, enhancing confidentiality, and ensuring reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 Schematic diagram of the structure of a satellite parameterized design method in one embodiment;

[0024] Figure 2 A schematic diagram of a scenario for configuring parameter design in one embodiment;

[0025] Figure 3 A schematic diagram of a configuration parameter design process in one embodiment;

[0026] Figure 4 A block diagram of parameter backup and recovery in one embodiment;

[0027] Figure 5 A flow chart of parameter backup and recovery design in one embodiment;

[0028] Figure 6 is a structural block diagram of a satellite parameter design device in one embodiment;

[0029] Figure 7 FIG. 1 is a diagram showing the internal structure of a computer device in one embodiment. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical solutions and advantages of this application more clear, the following further describes this application in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain this application and are not intended to limit this application.

[0031] In one embodiment, Figure 1As shown, a satellite parameterized design system is provided, including: a parameter configuration module 100, a parameter backup module 200 and a parameter recovery module 300.

[0032] The parameter configuration module 100 is used to configure the key parameters of the satellite tracking and control link through the uplink remote control link or the communication bus; the key parameters include uplink and downlink frequencies, code groups, spacecraft identification, address synchronization words and encryption and decryption key parameters.

[0033] The parameter backup module 200 is used to store the configured key parameters in at least three storage media with power-off non-volatile properties.

[0034] The parameter recovery module 300 is used to recover the key parameters from verified storage media according to the reliability priority of the storage media after power-on. If all storage media fail to verify, the parameters are restored to the default parameters. The parameter configuration module uses a protocol with a verification algorithm to configure parameters, and the configured parameters are transmitted in real time via the downlink telemetry link to observe the effectiveness of the parameters.

[0035] The above-mentioned satellite parameterized design system adopts a parameter configurable design. Key parameters such as uplink and downlink frequencies and code groups are configured through uplink remote control links, communication buses, and other paths. The configuration protocol integrates a verification algorithm and is validated through downlink telemetry observation. This allows single machines to be delivered in batches after normal parameterization testing, avoiding the problem of repeated adaptation, modification, and testing of each single machine in non-parametric designs. At the same time, the entire satellite developer can accept multiple machines at a time and allocate them to different satellites for use. The satellite service computer only needs to maintain a set of software programs, further saving costs. Because the parameterized design eliminates the need for the platform to obtain the actual values ​​of the parameters from the satellite service party, and only the entire satellite developer or the customer configures the parameters, confidentiality is significantly improved. The parameter backup and recovery design stores parameters on at least three power-off non-volatile storage media and restores the parameters according to reliability priority and verification algorithms. In the event of power failure or medium abnormality, the validity of the parameters can be guaranteed, and even the default value can be restored or reconfigured through instructions. This not only ensures link reliability but also supports on-orbit parameter modification to complete new missions or experimental verification. In summary, the present invention demonstrates significant advantages in reducing costs, improving efficiency, enhancing confidentiality, and ensuring reliability.

[0036] In one embodiment, Figure 2As shown, the uplink remote control link includes a high-speed uplink mode, and the communication bus includes a CAN bus or a 422 bus. Since all measurement and control units have an uplink, the uplink can be modified via remote control commands, and the high-speed uplink mode can be modified via uplink commands. Communication buses such as the CAN bus and 422 bus, which are used by the unit to interact with the satellite computer, can also be configured. For other units or devices that can communicate and interact with the unit, parameter configuration for the unit can also be performed. The parameter configuration protocol requires a verification algorithm to prevent parameter misconfiguration. The telemetry link does not involve a specific configuration process; it is used during on-orbit configuration to observe the specific configuration parameters and whether the configuration parameters are effective.

[0037] In one embodiment, Figure 3 As shown in the figure, starting with power-on / reset, after entering the waiting state for parameter configuration, two configuration paths are simultaneously supported: the service computer via the communication bus and the ground equipment via the measurement and control link. Each path first verifies the configuration parameter protocol format. If it does not meet the requirements, it returns to waiting. After the format meets the requirements, the protocol verification is verified again. If it fails, it still falls back. If both pass, the corresponding configurable parameters are modified, and finally the parameter module is made effective, reflecting the dual-path verification and effectiveness logic of the parameter configuration.

[0038] In a specific embodiment, assume that the communication link between the measurement and control unit and ground equipment utilizes a spread spectrum system, and that the satellite computer communicates with the unit via the CAN bus. Assume that the uplink frequency of satellite A is 7239 MHz, and the frequency of satellite B of the same model is 7240 MHz. Using a fixed parameter design would require the unit to develop two programs, and both programs would need to be maintained and upgraded separately, doubling the cost. Using a configurable parameter design allows the satellite computer to be configured via the CAN bus or a remote control link. Furthermore, the parameters of the A and B units can be swapped, allowing for direct comparison experiments and facilitating problem location and analysis.

[0039] In another specific embodiment, when a single machine requires high confidentiality, the design of configurable parameters can include key encryption, decryption, and scrambling parameters. This ensures the reliability of the single machine design, while the specific configuration parameters are configured by the platform or the client, reducing the number of personnel involved in confidentiality. Because configurable parameters can be combined in multiple ways, confidentiality is further enhanced.

[0040] In one embodiment, Figure 4 As shown, the storage media include FLASH, on-board computer, and MRAM, with the reliability priority being MRAM, on-board computer, and FLASH. It is worth noting that the storage media is not limited to the above three types, as long as it has the non-volatile property of power failure.

[0041] Specifically, such as Figure 5As shown, after power is applied, parameters are restored from these devices according to the reliability priority of the media. Data exchange with these media requires a protocol with a verification algorithm. If verification fails, recovery is performed from other media that pass verification. For example, the reliability of the three media mentioned above is MRAM, satellite computer, and flash memory. After power is applied, if the MRAM parameter verification passes, the parameters in the MRAM are restored. If the MRAM parameter verification fails, but the satellite computer verification is normal, recovery is performed from the satellite computer. If both the MRAM and satellite computer verification fail, and the flash memory verification is normal, recovery is performed from the flash memory. If all three external media fail, the default value is restored. This default value is issued by the system, and it is generally unlikely that multiple media will fail simultaneously. If this happens, the satellite computer can also use a contingency plan to directly issue configuration parameters or restore parameters to default via commands.

[0042] The above modules may be embedded in or independent of the processor in the computer device in the form of hardware, or may be stored in the memory of the computer device in the form of software, so that the processor can call and execute the operations corresponding to the above modules.

[0043] In one embodiment, Figure 6 As shown, a satellite parameterized design method is provided, comprising the following steps:

[0044] Step 602: Configuring key parameters of the satellite tracking and control link via an uplink remote control link or a communication bus; the key parameters include uplink and downlink frequencies, code groups, spacecraft identifiers, address synchronization words, and encryption and decryption key parameters. The configuration process uses a protocol with a verification algorithm.

[0045] Step 604: storing the configured key parameters in at least three storage media with power-off non-volatile properties;

[0046] Step 606: After power-on, the key parameters are restored from the storage medium that has passed the verification according to the reliability priority of the storage medium. When all storage media verifications are abnormal, the default parameters are restored. After the parameters are configured, the real-time parameter values ​​are sent down through the downlink telemetry link to observe the effective status.

[0047] In one embodiment, the uplink remote control link includes a high-speed uplink mode, and the communication bus includes a CAN bus or an 422 bus.

[0048] In one embodiment, the storage medium includes FLASH, a satellite computer, and MRAM, and the reliability priorities are MRAM, satellite computer, and FLASH.

[0049] In one embodiment, if the parameters configured by the parameter configuration module are not backed up, they are automatically restored to the backup values ​​after power failure.

[0050] In one embodiment, the key parameters further include scrambling key parameters.

[0051] In one embodiment, a computer device is provided. The computer device may be a server, and its internal structure diagram may be as follows: Figure 7 As shown. The computer device includes a processor, memory, a network interface, and a database connected via a system bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program, and a database. The internal memory provides an environment for the operation of the operating system and computer program in the non-volatile storage medium. The database of the computer device is used to store key parameter data. The network interface of the computer device is used to communicate with an external terminal via a network connection. When executed by the processor, the computer program implements a satellite parameterized design method.

[0052] Those skilled in the art will understand that Figure 7 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than shown in the figure, or combine certain components, or have a different component arrangement.

[0053] In one embodiment, a computer device is provided, including a memory and a processor. The memory stores a computer program, and the processor implements the steps of the method in the above embodiment when executing the computer program.

[0054] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the steps of the method in the above embodiment are implemented.

[0055] Those skilled in the art will appreciate that all or part of the processes in the above-mentioned embodiments can be implemented by instructing the relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0056] The technical features of the above embodiments can be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0057] The above-described embodiments merely represent several implementation methods of the present application. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that a person of ordinary skill in the art may make various modifications and improvements without departing from the spirit of the present application, and such modifications and improvements are intended to fall within the scope of protection of the present application. Therefore, the scope of protection of the present application shall be determined by the appended claims.

Claims

1. A satellite parametric design system, characterized in that: The system comprises: A parameter configuration module is used to configure key parameters of the satellite measurement and control link through an uplink remote control link or a communication bus; the key parameters include uplink and downlink frequencies, code groups, spacecraft identification, address synchronization words, and encryption and decryption key parameters; A parameter backup module, configured to store the configured key parameters in at least three storage media with power-off non-volatile properties; A parameter recovery module is used to recover the key parameters from the storage media that have passed the verification according to the reliability priority of the storage media after power-on, and to recover the default parameters when all storage media verifications are abnormal; The parameter configuration module adopts a protocol with a verification algorithm when configuring parameters, and the configured parameters are sent down in real time through a downlink telemetry link to observe the effective status.

2. The system according to claim 1, wherein: The uplink remote control link includes a high-speed uplink mode, and the communication bus includes a CAN bus or an 422 bus.

3. The system according to claim 1, wherein: The storage media includes FLASH, a spacecraft computer and MRAM, and the reliability priorities are MRAM, spacecraft computer and FLASH.

4. The system according to claim 1, wherein: If the parameters configured by the parameter configuration module are not backed up, they will automatically restore to the backup values ​​after power failure.

5. The system according to any one of claims 1 to 3, characterized in that: The key parameters also include scrambling key parameters.

6. A satellite parameterized design method, characterized in that: The following steps are involved: Configurable settings for key parameters of the satellite tracking and control link are made through an uplink remote control link or a communication bus. These key parameters include uplink and downlink frequencies, code groups, spacecraft identification, address synchronization words, and key encryption and decryption parameters. The configuration process uses a protocol with a verification algorithm. Storing the configured key parameters in at least three storage media with power-off non-volatile properties; After power-on, the key parameters are restored from the storage medium that has passed the verification according to the reliability priority of the storage medium. When all storage media verifications are abnormal, the default parameters are restored. After the parameters are configured, the real-time parameter values ​​are sent down through the downlink telemetry link to observe the effective status.

7. The method according to claim 6, characterized in that The uplink remote control link includes a high-speed uplink mode, and the communication bus includes a CAN bus or an 422 bus.

8. The method according to claim 6, characterized in that The storage media includes FLASH, a spacecraft computer and MRAM, and the reliability priorities are MRAM, spacecraft computer and FLASH.

9. The method according to claim 6, characterized in that If the parameters configured by the parameter configuration module are not backed up, they will automatically restore to the backup values ​​after power failure.

10. The method according to claim 6, characterized in that The key parameters also include scrambling key parameters.

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