A general service method and system applied to a satellite platform

Abstract

The application discloses a general service method and system applied to a satellite platform and belongs to the field of remote sensing / communication satellite platforms, and solves the technical problems that in the prior art, due to the need of new load access for new adaptability development and test work, a long development cycle is caused, and under the condition that test is not comprehensive, there is a risk of load service failure, and maintenance is difficult. Step 1, a general service template table is constructed; step 2, after the general service template table is filled in, the general service template table is converted into satellite on-service instructions; and step 3, a general service program is designed and is used for executing the satellite on-service instructions. The application is used for realizing the general service method without special customization development for different loads.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of remote sensing / communication satellite platform, in particular to a generalization service method and system applied to a satellite platform. BACKGROUND

[0002] For the existing satellite platform, most of the load services are realized through customized program design. For the generalization satellite platform, the development and debugging work is large, and new adaptive development and testing work is needed for each new load access. Not only is there a problem of large workload, but each new function also brings certain technical risks, and there is a risk of load service failure under incomplete testing. The specific performance is as follows:

[0003] 1) Long development cycle: new code needs to be rewritten each time a new load is accessed (average time consumption 3-6 months);

[0004] 2) Reliability risk: custom code test coverage is insufficient (usually <85%), which can easily cause on-orbit failure;

[0005] 3) Maintenance difficulty: platform software needs to be frequently iterated with load updates, increasing technical verification costs.

[0006] In summary, the existing technology has the technical problems of long development cycle, incomplete testing, risk of load service failure, and maintenance difficulty due to the need for new adaptive development and testing work for new load access. SUMMARY

[0007] The present application solves the technical problems of long development cycle, incomplete testing, risk of load service failure, and maintenance difficulty due to the need for new adaptive development and testing work for new load access in the prior art.

[0008] The generalization service method applied to a satellite platform according to the present application comprises the following steps:

[0009] Step 1, constructing a generalization service template table;

[0010] Step 2, after filling out the generalization service template table, converting it into satellite on-load service instructions;

[0011] Step 3, designing a generalization service program for executing satellite on-load service instructions.

[0012] Further, in the embodiment of the present application, the satellite on-load service instructions in step 2 include a basic information area, an attitude control information area, a service information area, and a supplementary information area.

[0013] Further, in the embodiment of the present application, the general service program in step 3 comprises the following steps:

[0014] Step 31, judging whether to call the attitude control, if yes, calling the attitude control program to execute the corresponding attitude maneuver action, if no, not calling the attitude control program and entering step 32;

[0015] Step 32, sequentially accessing the service information area from the service information starting byte to obtain the instruction parameters, and the cycle times are wherein, is the service information area length, is the single service information length;

[0016] Step 33, the center machine executes the instructions according to the instruction parameters in sequence.

[0017] Further, in the embodiment of the present application, the step 32 of sequentially accessing the service information area from the service information starting byte comprises the following steps:

[0018] According to the subscript to access the service information of the service information area, the subscript comprises and , and specifically comprises:

[0019] ;

[0020] wherein, is the starting subscript of the instruction component code, is the starting subscript of the instruction serial number, is the starting subscript of the instruction time offset, is the starting subscript of the instruction parameter length, is the starting subscript of the instruction parameter array, is the service information starting byte, is the current accessed service information serial number.

[0021] Further, in the embodiment of the present application, the step 32 of obtaining the instruction parameters comprises the following steps:

[0022] Step 321, judging whether the current service information is valid, if yes, executing step 322, if no, re-executing step 321 to access the next service information;

[0023] Step 322, obtaining the instruction information of the current service information, judging whether it is marked as a long instruction, if no, synchronizing the instruction information of the current service information to the center machine instruction cache array, executing step 323, if yes, judging whether the long instruction cache area information is reasonable, if yes, executing step 323, if no, reporting an error and then restoring the cache array to access the next service information and execute step 321;

[0024] Step 323, judge whether the combination of the instruction parameter length of the current service information and the instruction component code of the current service information is reasonable, if yes, execute step 324, if not, report an error and restore the cache array, access the next service information, and execute step 321;

[0025] Step 324, copy the instruction according to the size relationship of the instruction parameter length of the current service information, the pointer position and the maximum instruction parameter length, obtain the instruction parameter, mount the copied instruction parameter to the center machine, access the next service information, execute step 321, and the process ends after the loop is completed.

[0026] Further, in the embodiment of the application, the step 322 judges whether it is marked as a long instruction, specifically:

[0027] When the center machine instruction parameter length required by the satellite single machine is greater than the maximum instruction parameter length in a single service information , it is marked as a long instruction processing.

[0028] Further, in the embodiment of the application, the step 324 copies the instruction according to the size relationship of the instruction parameter length of the current service information, the pointer position and the maximum instruction parameter length, specifically:

[0029] If , copy all instruction parameters from the current pointer position, and update the pointer position;

[0030] If , copy the instruction parameters from the current pointer position, and the copied instruction parameter byte length is ;

[0031] If , copy the instruction parameters from the current pointer position, and the copied instruction parameter byte length is ;

[0032] Wherein, is the instruction parameter length of the current service information, is the pointer, is the maximum instruction parameter length.

[0033] Further, in the embodiment of the application, the step 322 judges whether the long instruction cache area information is reasonable, specifically:

[0034] Judge whether the instruction component code of the current service information is consistent with the component code in the center machine instruction cache array, if yes, it is reasonable, if not, it is not reasonable.

[0035] Further, in the embodiment of the application, the step of restoring the cache array is specifically:

[0036] Reset the central machine instruction cache array, the pointer is set to 0, and the long instruction flag is set to unmarked.

[0037] The universal service system applied to the satellite platform is constructed based on the method, and comprises the following modules:

[0038] The universal service template module constructs a universal service template table.

[0039] The template conversion module converts the satellite onboarding service instruction after the universal service template table is filled in.

[0040] The service analysis storage and execution module designs a universal service program for executing the satellite onboarding service instruction.

[0041] The present application solves the technical problems in the prior art that new load access needs new adaptability development and testing work, resulting in a long development cycle, incomplete testing, risk of load service failure, and difficult maintenance.

[0042] The present application provides a universal service method applied to a satellite platform, which unifies and standardizes the service instruction format of the load by establishing a universal service template table, automatically generates the conversion of the universal service template table to the satellite onboarding service instruction, and standardizes the program of the service module of the satellite platform without the need for customized development for different loads. BRIEF DESCRIPTION OF DRAWINGS

[0043] The above and / or additional aspects and advantages of the present application will become apparent and more readily appreciated from the following description, taken in conjunction with the following drawings, in which:

[0044] Figure 1 is a satellite onboarding service instruction schematic diagram according to the first embodiment;

[0045] Figure 2 is a universal service method flowchart applied to a satellite platform according to the second embodiment;

[0046] Figure 3 is a universal service template schematic diagram according to the fourth embodiment;

[0047] Figure 4is a general service template service instruction area schematic diagram according to the fourth embodiment;

[0048] Figure 5 is a plan details schematic diagram according to the fourth embodiment;

[0049] Figure 6 is an uplink instruction schematic diagram according to the fourth embodiment. DETAILED DESCRIPTION

[0050] Various embodiments of the present application will be described below with reference to the accompanying drawings. The embodiments described by reference to the drawings are exemplary and are intended to explain the present application, and should not be understood as limiting the present application.

[0051] Embodiment One. A general service method applied to a satellite platform, comprising the following steps:

[0052] Step 1, constructing a general service template table;

[0053] Step 2, after filling out the general service template table, converting it into a satellite uplink service instruction;

[0054] Step 3, designing a general service program for executing the satellite uplink service instruction.

[0055] The prior art has the technical problems of a large amount of work, technical risks of new functions, and frequent iteration of platform software to update the load, which increases the cost of technical verification.

[0056] To solve the above technical problems, the present embodiment provides a general service method applied to a satellite platform, which replaces the original customized service implementation method, and specifically comprises the following steps:

[0057] Step 1, constructing a general service template table;

[0058] The general service template table design process is as follows:

[0059] The general service template table used in the present embodiment is generated by manually filling in an excel file. The excel file contains a plurality of information, including but not limited to task basic information, task start time, basic information, attitude control information, service information, and other supplementary information. The format of the generated satellite uplink service instruction is as shown in Figure 1 , wherein the service information area is defined in Table 1.

[0060] Table 1

[0061]

[0062] Step 2, after filling in the general business template table, convert it into satellite injection business instructions;

[0063] The satellite injection business instructions include a basic information area, an attitude control information area, a business information area, and a supplementary information area. The conversion program converts the general business template table into satellite injection business instructions as follows:

[0064] The conversion program used in the embodiment is generated using the python (computer program) language. By reading the instruction-related information in the general business template table excel file, the information in the excel file is sequentially pieced together into a 512-byte hexadecimal string according to the specified satellite injection business instruction format.

[0065] Step 3, design a general business program for executing satellite injection business instructions.

[0066] The process of the satellite executing general business through general instructions is as follows:

[0067] Suppose that in the satellite injection business instructions, the satellite attitude control starting byte is , the business information starting byte is , and the satellite injection business instructions contain several basic information, including attitude control enable information , task execution start time , injection instruction total length , business information area length , and single business information length .

[0068] Therefore, by constructing a general business template table, designing a general business program, and executing satellite injection business instructions converted from the general business template table, the embodiment solves the technical problem of the prior art that the development cycle is long, the test is not comprehensive, and the risk of payload business failure exists, and the maintenance is difficult due to the need for new adaptive development and test work when new payloads are accessed.

[0069] Embodiment Two. The embodiment is a further limitation of the general business method applied to the satellite platform of Embodiment One. The general business program in Step 3 includes the following steps as shown in Figure 2 .

[0070] Step 31, determine whether to call attitude control. If yes, call the attitude control program to execute the corresponding attitude maneuver action. If no, do not call the attitude control program and go directly to Step 32.

[0071] Check the attitude control enable information in the satellite injection business instructions flag is enabled, the starting byte of satellite attitude control is obtained according to the content of satellite on-orbit service instruction The satellite on-orbit service instruction is accessed, the corresponding attitude control program is called, the attitude control information area is accessed by the program, and the corresponding attitude maneuvering action is executed.

[0072] In step 32, the service information area is accessed in sequence from the service information starting byte to obtain instruction parameters, and the number of cycles is , wherein is the length of the service information area, is the length of a single service information;

[0073] The business center machine instruction buffer array is , the current buffer array pointer is , and the long instruction flag is . Assuming that the current cycle is the th cycle, the th service information in the service information area of the satellite on-orbit service instruction is accessed, and the service information contains the center machine instruction component code , the instruction serial number , the instruction time offset , the instruction parameter length , and the instruction parameter array , wherein the instruction parameter array is the data structure of the instruction parameter content in the computer. The service information in the service information area is accessed according to the subscript, and the subscript includes , , , and , and specifically includes:

[0074] ;

[0075] , wherein is the starting subscript of the instruction component code, is the starting subscript of the instruction serial number, is the starting subscript of the instruction time offset, is the starting subscript of the instruction parameter length, is the starting subscript of the instruction parameter array, is the service information starting byte, is the serial number of the currently accessed service information.

[0076] In the embodiment, the instruction parameter includes the following steps:

[0077] Step 321, judge whether the current service information is valid, if yes, execute step 322, if not, re-execute step 321, access the next service information;

[0078] If the instruction component code in the first service information is not 0x00 and not 0xAA (reserved), it is judged that the first service information is valid, and the subsequent process is continued. If the instruction component code in the first service information is not 0x00 and not 0xAA (reserved), it is judged that the first service information is valid, and the subsequent process is continued.

[0079] Step 322, get the instruction information of the current service information, judge whether it is marked as a long instruction, if not, synchronize the instruction information of the current service information to the central machine instruction cache array, execute step 323, if yes, judge whether the long instruction cache area information is reasonable, if yes, execute step 323, if not, report an error and restore the cache array, access the next service information, execute step 321;

[0080] When the length of the central machine instruction parameters required by the satellite single machine is greater than the maximum instruction parameter length in a single service information , it is marked as a long instruction processing, and it is judged whether the long instruction flag bit in the instruction information of the first service information is marked:

[0081] If it is in the unmarked state, the component code, instruction number, instruction time offset, instruction parameter length and instruction parameter array in the central machine instruction cache array are synchronized and assigned with the instruction information in the first service information.

[0082] If it is in the marked state, it is judged whether the instruction component code of the first service information is consistent with the component code in the central machine instruction cache array , if not, output error information, reset the central machine instruction cache array , the pointer is set to 0, the flag bit is set to unmarked, and the current loop is jumped out to step 321. In the embodiment, the judgment of whether the long instruction cache area information is reasonable is specifically:

[0083] Judge whether the instruction component code of the current service information is consistent with the component code in the central machine instruction cache array, if yes, it is reasonable, if not, it is not reasonable.

[0084] Judge whether the instruction component code of the current service information is consistent with the component code in the central machine instruction cache array, if yes, it is reasonable, if not, it is not reasonable.

[0085] ​​​​​​Step 323: Determine whether the combination of the instruction parameter length of the current business information and the instruction component code of the current business information is reasonable. If yes, proceed to step 324. If no, after reporting an error, restore the cache array, access the next business information, and proceed to step 321.

[0086] In this embodiment, determining whether the combination of the instruction parameter length of the current business information and the instruction component code of the current business information is reasonable is specifically as follows:

[0087] Determine if the instruction component code of the current business information is erroneous, and whether the instruction parameter length of the current business information and the instruction component code of the current business information meet the requirements for satellite remote control instruction decomposition. If yes, it is reasonable; otherwise, it is unreasonable.

[0088] Step 324: Copy the instruction based on the relationship between the instruction parameter length, pointer position, and maximum instruction parameter length of the current business information to obtain the instruction parameters. Then, mount the copied instruction parameters to the central machine, access the next business information, execute step 321, and the process ends after the loop is completed.

[0089] According to the The instruction copying process is based on the relationship between the instruction parameter length, pointer position, and maximum instruction parameter length for each business information item. Specifically:

[0090] If the first Length of instruction parameters for each business information Greater than the maximum instruction parameter length in a single business message This indicates that the central machine instruction to be sent is a long instruction, and the long instruction flag is set to 0. Mark as marked.

[0091] like Then, all instruction parameters are copied from the current pointer position, and the pointer is updated after the copying is complete. The location has been updated to Exit the current loop and proceed to step 321;

[0092] like Then, the instruction parameters are copied from the current pointer position, and the length of the copied instruction parameters in bytes is... After completion, the command parameters are mounted to the central machine, and the central machine's command cache array is reset. Long instruction flag Mark as marked, then exit the current loop and proceed to step 321;

[0093] like This indicates that the instruction is a short instruction, copying the instruction parameters from the current pointer position. The length of the copied instruction parameters in bytes is [length missing]. The command parameters are then loaded onto the central machine, and the current loop is exited to step 321.

[0094] Step 33: The central unit executes the instructions in the order of the instruction parameters, performs the corresponding general business, and the process ends after the business is completed.

[0095] Implementation Method 3. This implementation method describes a generalized service system applied to a satellite platform. The system is constructed based on the method described in Implementation Method 1 and includes the following modules:

[0096] The generalized business template module builds a generalized business template table;

[0097] The template conversion module converts the completed generalized business template form into satellite uploading business instructions.

[0098] The business parsing, storage, and execution module is designed to execute generalized business programs for satellite uploading business instructions.

[0099] The generalized service system applied to a satellite platform described in this embodiment includes two parts: a ground system and a satellite system. The ground system includes a generalized service template module and a template conversion module, while the satellite system includes a service parsing, storage, and execution module.

[0100] Implementation Method 4. This implementation method is based on the generalized service method and system applied to a satellite platform described in Implementation Methods 1 to 3. It uses one of the multiple space-based general service tests conducted on a certain in-orbit Jilin-1 satellite as an example to provide an instance:

[0101] Determine the business execution time and specific implementation details, and prepare an Excel file. The Excel file used should be as follows: Figure 3 and Figure 4 As shown in the table, the specific instruction component names, instruction names, and instruction component codes are identified by codes.

[0102] After the table is completed, a Python program is called to generate the corresponding annotation command code. This command code is then provided to the satellite ground station, and the command is annotated within the appropriate tracking and control cycles. After annotation, the satellite decomposes the command into service operations according to the method described above and executes specific general services. The annotated commands and execution cycles are as follows: Figure 5 , Figure 6 As shown, this embodiment underwent multiple tests during the ground testing phase. The ground test results showed that the method was effective and met expectations. Specific general services can be executed according to this method. This invention is used for the rapid implementation of payload services without the need for payload access.

[0103] The above has carried on the detailed introduction to the general service method and system applied to the satellite platform provided by the application, the principle and implementation mode of the application are described by applying specific examples in this paper, the above example description is only used for helping understanding the method of the application and its core idea; meanwhile, for the general technical personnel in the art, according to the idea of the application, the specific implementation mode and application range will have the change, and the above is described, the content of the specification should not be understood as the limitation of the application.

Claims

1. A method for generalizing services applied to a satellite platform, characterized by, It comprises the following steps: Step 1, constructing a general business template table; Step 2, converting the completed general business template table into satellite injection business instructions; Step 3, designing a general business program for executing the satellite injection business instructions; The general business program in step 3 comprises the following steps: Step 31, judging whether to call the attitude control, if yes, calling the attitude control program to execute the corresponding attitude maneuver action, if no, not calling the attitude control program and entering step 32; Step 32, sequentially access the service information area from the service information start byte to obtain the instruction parameters, the number of loops is wherein, is the service information area length, is the single service information length; Step 33, the central machine executing the instruction parameters in sequence; The instruction parameter acquisition in step 32 comprises the following steps: Step 321, judging whether the current business information is valid, if yes, executing step 322, if no, re-executing step 321 and accessing the next business information; Step 322, acquiring the instruction information of the current business information, judging whether it is marked as a long instruction, if no, synchronizing the instruction information of the current business information to the central machine instruction cache array and executing step 323, if yes, judging whether the long instruction cache area information is reasonable, if yes, executing step 323, if no, reporting an error and restoring the cache array, accessing the next business information and executing step 321; Step 323, judging whether the combination of the instruction parameter length of the current business information and the instruction component code of the current business information is reasonable, if yes, executing step 324, if no, reporting an error, restoring the cache array, accessing the next business information and executing step 321; Step 324, copying the instruction according to the size relationship among the instruction parameter length of the current business information, the pointer position and the maximum instruction parameter length, obtaining the instruction parameter, mounting the copied instruction parameter to the central machine, accessing the next business information and executing step 321, and the process ends after the loop is completed.

2. The method of claim 1, wherein the method is applied to a satellite platform. The satellite injection business instructions in step 2 comprise a basic information area, an attitude control information area, a business information area and a supplementary information area.

3. The method of claim 1, wherein the method is applied to a satellite platform. In step 32, the business information area is accessed from the business information starting byte, specifically: According to the subscript to access the service information area of the service information, the subscript includes and , specifically: ； wherein is the starting index of the instruction component code, is the starting index of the instruction number, is the starting index of the instruction time offset, is the starting index of the instruction parameter length, is the starting index of the instruction parameter array, is the starting byte of the service information, is the current accessed service information number.

4. The method of claim 1, wherein the method is applied to a satellite platform. In step 322, whether it is marked as a long instruction is judged, specifically: When the length of the center machine instruction parameters required by the satellite single machine is greater than the maximum instruction parameter length in a single service information , mark it as long instruction processing.

5. The method of claim 1, wherein the method is applied to a satellite platform. In step 324, the instruction is copied according to the size relationship among the instruction parameter length of the current business information, the pointer position and the maximum instruction parameter length, specifically: If then copy all instruction parameters from the current pointer position and update the pointer position; If then copy the instruction parameters from the current pointer position, the copied instruction parameter byte length is restore the cache array; If , then copy the instruction parameters from the current pointer position, the copied instruction parameter byte length is ; wherein, is a length of an instruction parameter of the current service information, is a pointer, is a maximum instruction parameter length.

6. The method of claim 1, wherein the method is applied to a satellite platform. In step 322, whether the long instruction cache area information is reasonable is judged, specifically: Whether the instruction component code of the current business information is consistent with the component code in the central machine instruction cache array is judged, if yes, it is reasonable, if no, it is not reasonable.

7. A method for generalizing services applied to a satellite platform according to claim 1 or 5, characterized in that, The cache array is restored, specifically: The central machine instruction cache array is reset, the pointer is set to 0, and the long instruction flag is set to unmarked.

8. A generalised service system for a satellite platform, said system being constructed on the basis of the method according to claim 1, characterised in that, It comprises the following modules: A general business template module for constructing a general business template table; A template conversion module for converting the completed general business template table into satellite injection business instructions; A business analysis storage and execution module for designing a general business program for executing the satellite injection business instructions.

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