Function-based spacecraft software on-orbit dynamic reconstruction method

Abstract

The invention relates to a spacecraft software on-orbit dynamic reconstruction method based on a function, which is applied to a data transmission control unit of a lower computer of a data transmission subsystem, and realizes the spacecraft software on-orbit dynamic reconstruction based on the function under a software architecture of'interrupt drive + main loop query '. On-line dynamic loading of a function module is realized through a function pointer and a reconstruction patch, and continuous operation of a system is supported. The method belongs to lightweight non-inductive reconstruction, breaks through a traditional method of static reconstruction based on a configuration item level, saves space in the aspects of data transmission and storage, and improves efficiency. According to the method, the on-orbit fault emergency processing capacity and the function upgrading perfection flexibility are effectively improved, and a certain reference value is achieved.

Description

Technical Field

[0001] The present invention relates to a function-based on-orbit dynamic reconstruction method for spacecraft software, which belongs to the technical field of digital transmission payload control, is suitable for on-orbit functional reconstruction of digital transmission lower computer CPU software under an interrupt drive mechanism, realizes dynamic binding of software components and hardware platforms, and can be widely used in the field of payload control. Background Art

[0002] The future on-orbit missions of remote sensing satellites will tend to be more diverse and complex. On-board reconstruction technology can improve the ability to handle emergency faults and quickly and flexibly upgrade and repair system functions. It can solve the problem of insufficient on-orbit information processing capabilities and inflexible expansion of system functions caused by the premature solidification of traditional satellite programs, thereby adapting to the technological development trend of functional softwareization. Summary of the invention

[0003] The technical problem to be solved by the present invention is: to overcome the shortcomings of the prior art and propose a function-based on-orbit dynamic reconstruction method for spacecraft software. During the program running process, function pointers and reconstruction patches are used to implement local online repair and function upgrades, realize rapid dynamic binding of software components and hardware platforms, accelerate on-board autonomous reconstruction, and further improve the emergency handling capability of faults.

[0004] The technical solution adopted by the present invention is:

[0005] First,

[0006] The present invention proposes a function-based on-orbit dynamic reconstruction method for spacecraft software, comprising:

[0007] Step 1: The remote sensing satellite service communicates with the data transmission lower computer through the bus. After the hardware interrupt is triggered, the data transmission lower computer receives the bus data and determines whether the subtask identifier is valid through the protocol. If the subtask identifier is valid, it goes to step 2.

[0008] Step 2: Determine whether static comprehensive reconstruction is enabled. If yes, enter static comprehensive reconstruction mode and proceed to step 3; otherwise, the program runs normally without reconstruction.

[0009] Step 3, using modular design to write an upper configuration item reconstruction program for on-orbit dynamic reconstruction on the ground, the functions corresponding to the functional modules in the upper configuration item reconstruction program are passed in through formal parameters; in the upper configuration item reconstruction program, the function pointer p_func is defined and the reconstruction test stub is set, and the dynamic library and API function are provided; the API function includes the opendll() function for opening the dynamic link library and the getaddll() function for obtaining the entry address and variable address of the reconstruction function;

[0010] Step 4: The on-orbit spacecraft software receives the comprehensive reconstruction instruction and the upper configuration item reconstruction program sent by the ground through the bus, and the on-orbit spacecraft software loads the upper configuration item reconstruction program according to the comprehensive reconstruction instruction;

[0011] Step 5: Determine whether function-level refactoring is enabled. If yes, enter the local refactoring mode and proceed to step 6; otherwise, run normally without refactoring.

[0012] Step 6, simulating the on-board environment on the ground, setting the compilation options and dynamic link parameters, generating the reconstruction patch and the elf file, wherein the elf file is used for redirecting the reconstruction patch;

[0013] Step 7: The on-orbit spacecraft software receives the local reconstruction instruction and data packet sent from the ground through the bus. The data packet includes the reconstruction patch and elf file.

[0014] Step 8: Use the elf file loader to dynamically load the elf file and obtain the entry address of the reconstruction patch;

[0015] Step 9, execute API functions opendll() and getaddll() to implement the function pointer p_func assignment function, and assign the function pointer p_func to the entry address of the reconstruction patch;

[0016] Step 10, in the above configuration item reconstruction program, the main loop determines whether the function pointer p_func is non-null. If the function pointer p_func is non-null, that is, the reconstruction patch entry address is valid, then the reconstruction patch is executed;

[0017] Step 11, obtain the variable address through the API function getaddll(), and further monitor the operation of the reconstruction patch; determine whether the reconstruction patch runs normally, if so, proceed to the next step, otherwise the version is rolled back;

[0018] Step 12: Unload the variable from memory and complete the dynamic reconstruction data comparison.

[0019] Furthermore, the subtask identifier includes a frame header, a frame tail, multi-frame continuity, and a checksum.

[0020] Further, the static full reconfiguration allows enabling full reconfiguration of spacecraft software.

[0021] Further, the function level refactoring allows to enable local refactoring of spacecraft software.

[0022] Furthermore, the reconstruction patch is used to replace the functional module that needs to be modified.

[0023] Furthermore, the reconstruction patches and elf files are temporarily stored in the memory. After running, they will be directly inserted into the running code or modify and improve the functions, and will not be reflected in the source code.

[0024] Furthermore, the version rollback means that once the stand-alone machine is restarted, the source configuration item program in the FLASH is loaded into the memory through the BOOT boot to perform rollback.

[0025] In a second aspect, the present invention further proposes a processor, which is used to run a program, wherein the program executes the function-based on-orbit dynamic reconstruction method of spacecraft software when running.

[0026] In a third aspect, the present invention further proposes a non-volatile storage medium, comprising: a computer program product, which, when executed, executes the function-based on-orbit dynamic reconstruction method of spacecraft software.

[0027] In a fourth aspect, the present invention further proposes a computer program product, which, when executed by a processor, implements the function-based on-orbit dynamic reconstruction method of spacecraft software.

[0028] The advantages of the present invention compared with the prior art are:

[0029] (1) The present invention proposes a method for on-orbit dynamic reconstruction based on the function level. Compared with the traditional "recompile + system restart + boot switch" reconstruction, the present invention has improved the partial function upgrade. It supports the continuous operation of the system and avoids the accidental change of the single machine status and configuration item parameters caused by the system restart, which affects the payload security. It also has good portability and scalability and can be used as a component.

[0030] (2) This paper proposes a lightweight function-level reconstruction, breaking the previous static reconstruction method based on the configuration item level, saving space and improving efficiency in data transmission and storage, and improving the level of software reconstruction refinement, especially in terms of on-track fault isolation and detection, greatly improving the timeliness of response. It supports version rollback and meets the research and development needs of frequent iterations. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 The present invention is a flow chart of the on-orbit dynamic reconstruction method of spacecraft software based on functions. DETAILED DESCRIPTION

[0032] In order to better understand the above technical solution, the technical solution of this application is described in detail below through the accompanying drawings and specific implementations.

[0033] In order to improve the relative flexibility of on-orbit satellites and the ability to reconfigure internal programs, and to solve the pain point of insufficient on-orbit information processing capabilities caused by premature solidification of previous applications, the present invention proposes a function-based on-orbit dynamic reconstruction method for spacecraft software, which is applied to the data transmission control unit of the lower computer of the data transmission subsystem. Through function pointers and reconstruction patches, online dynamic loading of functional modules is realized to support continuous operation of the system, and to avoid unexpected changes in single-machine status and configuration item parameters caused by system restart, which affects the safety of the payload.

[0034] Under the coordinated planning between the satellite and the ground, the data transmission control unit processes multiple subtasks sent by satellite services (involving remote control commands, data blocks, broadcasts, periodic telemetry, etc.) in the data transmission lower computer. During program operation, function pointers and reconstruction patches are used to achieve local online repairs and function upgrades. This will further improve the fault emergency handling capability based on the static reconstruction mode of "recompilation + system restart + boot switching" adopted by traditional lower computer software.

[0035] like Figure 1 As shown, the present invention proposes a function-based on-orbit dynamic reconstruction method for spacecraft software, comprising the following steps:

[0036] Step 1: The remote sensing satellite service communicates with the data transmission lower computer through the bus. After the hardware interrupt is triggered, the data transmission lower computer receives the bus data and determines whether the subtask identifier is valid through the protocol. If the subtask identifier is valid, it goes to step 2.

[0037] Step 2: Determine whether static comprehensive reconstruction is enabled. If yes, enter static comprehensive reconstruction mode and proceed to step 3; otherwise, the program runs normally without reconstruction.

[0038] Step 3, using modular design to write an upper configuration item reconstruction program for on-orbit dynamic reconstruction on the ground, the functions corresponding to the functional modules in the upper configuration item reconstruction program are passed in through formal parameters; in the upper configuration item reconstruction program, the function pointer p_func is defined and the reconstruction test stub is set, and the dynamic library and API function are provided; the API function includes the opendll() function for opening the dynamic link library and the getaddll() function for obtaining the entry address and variable address of the reconstruction function;

[0039] Step 4: The on-orbit spacecraft software receives the comprehensive reconstruction instruction and the upper configuration item reconstruction program sent by the ground through the bus, and the on-orbit spacecraft software loads the upper configuration item reconstruction program according to the comprehensive reconstruction instruction;

[0040] Step 5: Determine whether function-level refactoring is enabled. If yes, enter the local refactoring mode and proceed to step 6; otherwise, run normally without refactoring.

[0041] Step 6, simulating the on-board environment on the ground, setting the compilation options and dynamic link parameters, generating the reconstruction patch and the elf file, wherein the elf file is used for redirecting the reconstruction patch;

[0042] Step 7: The on-orbit spacecraft software receives the local reconstruction instruction and data packet sent from the ground through the bus. The data packet includes the reconstruction patch and elf file.

[0043] Step 8: Use the elf file loader to dynamically load the elf file and obtain the entry address of the reconstruction patch;

[0044] Step 9, execute API functions opendll() and getaddll() to implement the function pointer p_func assignment function, and assign the function pointer p_func to the entry address of the reconstruction patch;

[0045] Step 10, in the above configuration item reconstruction program, the main loop determines whether the function pointer p_func is non-null. If the function pointer p_func is non-null, that is, the reconstruction patch entry address is valid, then the reconstruction patch is executed;

[0046] Step 11, obtain the variable address through the API function getaddll(), and further monitor the operation of the reconstruction patch; determine whether the reconstruction patch runs normally, if so, proceed to the next step, otherwise the version is rolled back;

[0047] Step 12: Unload the variable from memory and complete the dynamic reconstruction data comparison.

[0048] Furthermore, the subtask identifier includes a frame header, a frame tail, multi-frame continuity, and a checksum.

[0049] Further, the static full reconfiguration allows enabling full reconfiguration of spacecraft software.

[0050] Further, the function level refactoring allows to enable local refactoring of spacecraft software.

[0051] Furthermore, the reconstruction patch is used to replace the functional module that needs to be modified.

[0052] Furthermore, the reconstruction patches and elf files are temporarily stored in the memory. After running, they will be directly inserted into the running code or modify and improve the functions, and will not be reflected in the source code.

[0053] Furthermore, the version rollback means that once the stand-alone machine is restarted, the source configuration item program in the FLASH is loaded into the memory through the BOOT boot to perform rollback.

[0054] The method of the present invention is suitable for on-orbit functional reconstruction of the CPU software of the data transmission lower computer based on the BM3803 interrupt drive mechanism, realizing fast dynamic binding of software components and hardware platforms, and accelerating autonomous reconstruction on board. The method effectively improves the response rate of real-time tasks and the reliability of data transmission, and has good portability.

[0055] The present invention proposes a lightweight function-level reconstruction, breaking the traditional static reconstruction method based on the configuration item level, saving space and improving efficiency in data transmission and storage, and improving the level of software reconstruction refinement. It supports version rollback (patches and files will be temporarily stored in memory, and will be directly inserted into the running code or modify and improve functions after running, and will not be reflected in the source code), meeting the research and development needs of frequent iterations.

[0056] Parts of the present invention that are not described in detail belong to the well-known technologies of those skilled in the art.

Claims

1. A function-based on-orbit dynamic reconstruction method for spacecraft software, characterized in that: include: Step 1: The remote sensing satellite service communicates with the data transmission lower computer through the bus. After the hardware interrupt is triggered, the data transmission lower computer receives the bus data and determines whether the subtask identifier is valid through the protocol. If the subtask identifier is valid, it goes to step 2. Step 2: Determine whether static full reconstruction is enabled. If yes, enter static full reconstruction mode and proceed to step 3. Otherwise the program runs normally without reconstruction; Step 3: A configuration item reconstruction program for on-orbit dynamic reconstruction is written on the ground using a modular design. Functions corresponding to functional modules in the configuration item reconstruction program are passed in through formal parameters. In the configuration item reconstruction program, a function pointer p_func is defined and a reconstruction test stub is set, and a dynamic library and an API function are provided. The API functions include the opendll() function to open the dynamic link library and the getaddll() function to obtain the entry address of the reconstruction function and the variable address; Step 4: The on-orbit spacecraft software receives the comprehensive reconstruction instruction and the upper configuration item reconstruction program sent by the ground through the bus, and the on-orbit spacecraft software loads the upper configuration item reconstruction program according to the comprehensive reconstruction instruction; Step 5: Determine whether function-level refactoring is enabled. If yes, enter the local refactoring mode and proceed to step 6. Otherwise it runs normally without reconstruction; Step 6, simulating the on-board environment on the ground, setting the compilation options and dynamic link parameters, generating the reconstruction patch and the elf file, wherein the elf file is used for redirecting the reconstruction patch; Step 7: The on-orbit spacecraft software receives the local reconstruction instruction and data packet sent from the ground through the bus. The data packet includes the reconstruction patch and elf file. Step 8: Use the elf file loader to dynamically load the elf file and obtain the entry address of the reconstruction patch; Step 9, execute API functions opendll() and getaddll() to implement the function pointer p_func assignment function, and assign the function pointer p_func to the entry address of the reconstruction patch; Step 10, in the above configuration item reconstruction program, the main loop determines whether the function pointer p_func is non-null. If the function pointer p_func is non-null, that is, the reconstruction patch entry address is valid, then the reconstruction patch is executed; Step 11, obtain the variable address through the API function getaddll(), and further monitor the operation of the reconstruction patch; determine whether the reconstruction patch runs normally, if so, proceed to the next step, otherwise the version is rolled back; Step 12: Unload the variable from memory and complete the dynamic reconstruction data comparison.

2. The method for dynamic on-orbit reconstruction of spacecraft software based on function according to claim 1, characterized in that: The subtask identifier includes a frame header, a frame tail, multi-frame continuity, and a checksum.

3. The method for dynamic on-orbit reconstruction of spacecraft software based on function according to claim 1, characterized in that: The static full reconfiguration allows enabling a full reconfiguration of the spacecraft software.

4. The method for dynamic on-orbit reconstruction of spacecraft software based on function according to claim 1, characterized in that: The function level refactoring allows to enable local refactoring of spacecraft software.

5. The function-based on-orbit dynamic reconstruction method of spacecraft software according to claim 1, characterized in that: The reconstruction patch is used to replace the functional module that needs to be modified.

6. The method for dynamic on-orbit reconstruction of spacecraft software based on functions according to claim 1, characterized in that: The reconstruction patches and elf files are temporarily stored in the memory. After running, they will be directly inserted into the running code or modify and improve the functions, and will not be reflected in the source code.

7. The function-based on-orbit dynamic reconstruction method of spacecraft software according to claim 6, characterized in that: The version rollback means that once the stand-alone machine is restarted, the source configuration item program in the FLASH is loaded into the memory through the BOOT boot to roll back.

8. A processor, characterized in that: The processor is used to run a program, wherein the program, when running, executes the function-based on-orbit dynamic reconstruction method of spacecraft software as described in any one of claims 1 to 7.

9. A non-volatile storage medium, characterized in that: include: A computer program product, when executed, performs the function-based on-orbit dynamic reconstruction method of spacecraft software as described in any one of claims 1 to 7.

10. A computer program product, characterized in that When the computer program product is executed by a processor, it implements the function-based on-orbit dynamic reconstruction method of spacecraft software as described in any one of claims 1 to 7.

Images