Method and system for implementing long and short frame memory unloading of deep space exploration spacecraft memory data

Abstract

The present invention provides a method and system for realizing long and short frame memory unloading of memory data of deep space exploration spacecraft, including: receiving the operating parameters of each subsystem stand-alone and software on the satellite by integrated electronic software, integrating the parameter groups of each subsystem stand-alone and software on the satellite into conventional real-time telemetry frames and conventional delayed telemetry frames; when the ground user needs to analyze some special data in the computer memory, or when a subsystem stand-alone software on the detector is abnormal, the ground sends a memory unloading instruction to the detector; the integrated electronic software receives the ground memory unloading instruction, organizes the integrated electronic software or remote terminal software memory data to be unloaded to the ground; the integrated electronic software transmits the memory data of the satellite integrated electronic software or remote terminal control software to the ground in the form of telemetry frames. The present invention can flexibly select the memory unloading data of each stand-alone control software of the spacecraft to be transmitted to the ground, and improve the flexibility of memory data acquisition when the detector is in orbit.

Description

Technical Field

[0001] The present invention relates to the technical field of deep space exploration vehicle electronic equipment, and in particular to a method and system for implementing long and short frame memory unloading of memory data of a deep space exploration spacecraft. Background Art

[0002] With the continuous development of space exploration projects, deep space exploration has many flight phases and many interference factors in satellite-to-ground communication. How to ensure that various spacecraft operating parameters can be transmitted back to the ground in a timely manner is an indispensable function in spacecraft design. At present, data communications of on-orbit spacecraft mostly use fixed bit rate transmission. Spacecraft telemetry parameters only use telemetry parameter information on the transmitter using a fixed-length telemetry frame. Deep space exploration spacecraft, such as the Mars rover, face the problem of long communication delay between the rover and the ground. The round-trip communication data between the earth and Mars can take up to 45 minutes. Therefore, it is necessary to more reliably ensure that the operating data of each single machine and software of the rover can be quickly transmitted back to the earth.

[0003] In particular, after a detector fails, it is necessary to quickly obtain abnormal information. At this time, quickly obtaining the memory data of each stand-alone software is the key to ensuring that the ground can quickly find the abnormal problem of the spacecraft. Existing spacecraft-ground communications mostly use only real-time telemetry and delayed telemetry data. However, telemetry data is immutable. Once the telemetry parameters are determined, the ground's understanding of the spacecraft status is limited to telemetry data, and other computer operating parameters are invisible. When an abnormality occurs, it is difficult to find the abnormal location if the telemetry parameters are not designed reasonably. If the positioning is not timely after the spacecraft abnormality occurs, the abnormal problem cannot be solved in time, which may affect the normal operation of the spacecraft and cause the spacecraft to be directly scrapped. Therefore, a flexible data transmission channel is needed that allows the ground to observe all the memory data of each stand-alone control software of the spacecraft.

[0004] At present, there is no related patent for the technology of unloading spacecraft memory data in the aerospace field. Comparative study with the patent of satellite telemetry data processing method, the invention patent with publication number CN101354829B discloses a satellite telemetry data transmission method, which includes the following steps: (1) the satellite service center computer sends the collected telemetry data of each lower computer of the whole satellite to the satellite service data storage module; (2) the satellite service data storage module receives, formats and stores the telemetry data; (3) through ground command control, the satellite service data storage module sends the stored telemetry data to the data downlink transmission module; (4) the data downlink transmission module sends the telemetry data downlink.

[0005] The invention patent with the publication number CN103279585B discloses a method for realizing the full recording of real-time telemetry data of a spacecraft, and the steps are as follows: (1) setting the telemetry transmission cycle of the CTU to the transmission time of 4 frames of telemetry information, and setting the CTU to store data through two time slices, each time slice storing 2 frames of telemetry information; (2) setting a solid-state memory for storing the transferred data of the CTU, and the CTU and the solid-state memory communicate through the 1553B bus; (3) the CTU collects telemetry information in real time and stores it in the SRAM; (4) in each telemetry transmission cycle, the CTU judges the transmitted telemetry information, uses the data transmission opportunity of segment numbers 63 to 103 to store special data segments, uses the data transmission opportunity of segment numbers 1 to 62 to store real-time telemetry data, and uses the data transmission period of segment numbers 0 and 63 to 127 to store data segments of segment numbers 104 to 127, and all data to be stored are stored in the solid-state memory through the CTU via the 1553B bus.

[0006] The invention patent with the publication number CN103347025B discloses a method for processing telemetry data of a spacecraft, wherein the spacecraft sends one or more groups of telemetry data with a small amount of data to the ground through a data frame according to the data protocol; the spacecraft sends a group of telemetry data with a large amount of data to the ground through multiple data frames according to the data protocol; the ground processes the received data according to the data protocol to obtain a valid data frame; and searches for a parsing rule table corresponding to the valid data frame according to the data packet identifier of the valid data frame, wherein the parsing rule table stores the operations performed on the telemetry data in the valid data frame and the data file written to the telemetry data in the valid data frame; the valid data frame is processed according to the operations in the parsing rule table and the written data file, and finally the telemetry data is written to the corresponding data file. These patents for telemetry data processing can only solve the function of transmitting telemetry data of spacecraft, and the length of the data frame transmitted to the ground is single and cannot be adjusted. On the other hand, none of them considers the transmission requirements of the memory data of each stand-alone control software of the spacecraft. Summary of the invention

[0007] In view of the defects in the prior art, the present invention provides a method and system for realizing long and short frame memory unloading of memory data of a deep space exploration spacecraft.

[0008] According to a method and system for implementing long and short frame memory unloading of deep space exploration spacecraft memory data provided by the present invention, the scheme is as follows:

[0009] In a first aspect, a method for implementing long and short frame memory unloading of memory data of a deep space exploration spacecraft is provided, the method comprising:

[0010] Step S1: The integrated electronic software receives the operating parameters of each subsystem stand-alone and software on the satellite, and integrates the conventional real-time telemetry frame and conventional delayed telemetry frame of the operating parameter group of each subsystem stand-alone and software on the satellite according to the design requirements;

[0011] Step S2: When the ground user needs to analyze some special data in the computer memory, or when a subsystem stand-alone software on the detector is abnormal, the ground sends a memory unloading instruction to the detector;

[0012] Step S3: After the integrated electronic software receives the ground memory download instruction, it organizes the integrated electronic software or remote terminal software memory data to be downloaded to the ground according to the instruction requirements;

[0013] Step S4: The integrated electronic software transmits the memory data of the satellite integrated electronic software or the remote terminal control software to the ground in the form of telemetry frames.

[0014] Preferably, the memory download target is integrated electronic software or remote terminal control software which can be specified by a ground user.

[0015] Preferably, the data frame types designed for the telemetry frames unloaded from the memory of the detector include long frames and short frames, the total length of the data frames unloaded from the long frame memory is designed to be 1024 bytes, and the total length of the data frames unloaded from the short frame memory is designed to be 256 bytes.

[0016] Preferably, the ground user can choose to use long frame memory offloading or short frame memory offloading according to different ground-to-space communication rates;

[0017] When the ground communication code rate is lower than 256000bps, a short frame memory with a length of 256 bytes is selected to unload the frame;

[0018] When the ground communication code rate is higher than 256000bps, the long frame memory with a length of 1024 bytes is selected to unload the frame.

[0019] Preferably, when the remote terminal control software mounted on the 1553B bus performs memory unloading, a data cache queue is designed. When the memory unloading operation is performed, the memory unloading data of the remote terminal control software is first stored in the memory unloading queue, and the integrated electronic software reads the memory unloading data of the remote terminal control software from the memory unloading data queue and transmits it to the ground.

[0020] Preferably, when the spacecraft is performing memory data memory unloading, the default short frame memory unloading is transmitted to the ground at a ratio of 1:3 between real-time telemetry frames and memory unloading frames, and the long frame memory unloading is transmitted to the ground at a ratio of 1:1 between real-time telemetry frames and memory unloading frames. If the integrated electronic software does not receive the memory unloading data from the remote terminal control software during the period when the memory unloading frames need to be transmitted, the real-time telemetry frames are directly obtained for transmission during this period to ensure continuous and uninterrupted transmission of data between the satellite and the ground.

[0021] Preferably, the memory offload mode of the integrated electronic software design has conventional real-time telemetry frames and memory offload frames being proportionally transmitted;

[0022] In the short frame memory unloading mode, since the data volume of a short frame is only 256 bytes, the short frame memory unloading is designed to be transmitted to the ground in a ratio of 1:3 between the conventional real-time telemetry frame and the memory unloading frame;

[0023] Long frame memory unloading mode is designed to transmit the long frame memory unloading to the ground in a 1:1 ratio of conventional real-time telemetry frames and memory unloading frames because the long frame data volume is 1024 bytes per frame.

[0024] The memory download mode designed by the integrated electronic software can not only download the memory data in real time, but also ensure the uninterrupted download of the detector's real-time telemetry.

[0025] Preferably, after the integrated electronic software enters the memory unloading mode, the integrated electronic software periodically organizes the remote terminal control software memory unloading at a rate of 500ms. When no memory unloading data of the remote terminal control software is received within a certain period, the memory unloading is not stopped during the period, and the remote terminal control software memory unloading data acquisition failure count is set to +1, and at the same time, the regular real-time telemetry frame is transmitted during the current period.

[0026] Only when the remote terminal control software memory unloading data acquisition failure count during the entire memory unloading process is greater than 3 times, the remote terminal control software memory unloading is stopped and the memory unloading mode is exited.

[0027] Preferably, a fault tolerance number is set for unloading data from the memory of the remote terminal control software.

[0028] In a second aspect, a system for realizing long and short frame memory unloading of memory data of a deep space exploration spacecraft is provided, the system comprising:

[0029] Module M1: The integrated electronic software receives the operating parameters of each subsystem and software on the satellite, and integrates the parameter groups of each subsystem and software on the satellite into conventional real-time telemetry frames and conventional delayed telemetry frames according to the design requirements;

[0030] Module M2: When the ground user needs to analyze some special data in the computer memory, or when a subsystem stand-alone software on the detector is abnormal, the ground sends a memory unloading instruction to the detector;

[0031] Module M3: After the integrated electronic software receives the ground memory unloading instruction, it organizes the integrated electronic software or remote terminal software memory data to unload the ground according to the instruction requirements;

[0032] Module M4: The integrated electronic software transmits the memory data of the satellite integrated electronic software or the remote terminal control software to the ground in the form of telemetry frames.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] The present invention can flexibly select the memory unloaded data of each stand-alone control software of the spacecraft to be transmitted to the ground according to different ground code rates and different memory unloaded data size requirements, thereby improving the flexibility of memory data acquisition when the detector is in orbit; specifically:

[0035] 1. The data cache queue designed in the present invention improves the reliability of data interaction;

[0036] 2. The scheme designed by the present invention for the memory unloading data and the real-time telemetry data to complement each other ensures the continuity of satellite-to-ground communication data when the remote terminal control software memory is unloaded;

[0037] 3. In the present invention, the fault tolerance times for the memory data downloading of the remote terminal control software are set, which can improve the fault tolerance rate of data interaction between the integrated electronic software end and the remote terminal control software end, and prevent the memory downloading from the remote terminal control software from being mistakenly stopped due to timing jitter when transmitting the memory data downloading to the integrated electronic software, resulting in incomplete memory data downloading. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0039] Figure 1 Unload each terminal system block diagram for spacecraft memory;

[0040] Figure 2 Unload the control logic diagram for memory. DETAILED DESCRIPTION

[0041] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0042] An embodiment of the present invention provides a method for implementing long and short frame memory unloading of memory data of a deep space exploration spacecraft, the method comprising: designing the satellite's memory unloading telemetry frames into two types of data frames, long frames and short frames; designing the total length of the long frame memory unloading data frames to be 1024 bytes, and the total length of the short frame memory unloading data frames to be 256 bytes; the user can choose to use long frame memory unloading or choose short frame memory unloading according to different ground-to-space communication rates; the user can specify the memory unloading target as integrated electronic (BC) software or remote terminal (RT) control software; the user can set the memory unloading data length according to the actual application scenario.

[0043] In order to improve the reliability of data interaction, a data cache queue is designed for the memory unloading of the remote terminal (RT) software mounted on the 1553B bus. When performing the memory unloading operation, the memory unloading data of the remote terminal (RT) control software is first stored in the memory unloading queue, and the integrated electronic software reads the memory unloading data of the remote terminal (RT) control software from the memory unloading data queue and transmits it to the ground.

[0044] In order to ensure the continuity of satellite-to-ground communication data when the remote terminal (RT) control software memory is being unloaded, the present invention designs a scheme that complements the memory unloaded data with the real-time telemetry data. When the spacecraft is performing memory data unloading, the default short frame memory unloading mode is to transmit to the ground at a ratio of 1:3 between the real-time telemetry frame and the memory unloading frame, and the default long frame memory unloading mode is to transmit to the ground at a ratio of 1:1 between the real-time telemetry frame and the memory unloading frame. If the onboard memory unloading data is not obtained in time when the memory unloading frame needs to be transmitted, the real-time telemetry frame is directly obtained within this cycle for transmission, thereby ensuring continuous and uninterrupted transmission of data between the satellite and the ground.

[0045] In order to improve the fault tolerance rate of data interaction between the comprehensive electronic (BC) software and the remote terminal (RT) control software, a fault tolerance number is set for the memory unloading data of the remote terminal control software to prevent the memory unloading from being mistakenly stopped due to timing jitter when the memory unloading data of the remote terminal control software is transmitted to the comprehensive electronic software, resulting in incomplete memory data unloading.

[0046] Reference Figure 1 and Figure 2 As shown, the specific steps of the method include:

[0047] Step S1: The integrated electronic software receives the operating parameters of each subsystem stand-alone and software on the satellite, and integrates the conventional real-time telemetry frame and conventional delayed telemetry frame of the operating parameter group of each subsystem stand-alone and software on the satellite according to the design requirements;

[0048] Step S2: When the ground user needs to analyze some special data in the computer memory, or when a subsystem stand-alone software on the detector is abnormal, the ground sends a memory unloading instruction to the detector;

[0049] Step S3: After the integrated electronic software receives the ground memory unloading instruction, it organizes the integrated electronic (BC) software or remote terminal (RT) software memory data to be unloaded to the ground according to the instruction requirements;

[0050] Step S4: The integrated electronic software transmits the memory data of the satellite integrated electronic software or the remote terminal control software to the ground in the form of telemetry frames. The memory download target is the integrated electronic software or the remote terminal control software, which can be specified by the ground user.

[0051] Specifically, the data frame types designed for the detector's memory unloaded telemetry frame include long frames and short frames. The total length of the long frame memory unloaded data frame is designed to be 1024 bytes, and the total length of the short frame memory unloaded data frame is designed to be 256 bytes.

[0052] Ground users can choose to use long frame memory offloading or short frame memory offloading according to different ground-to-space communication rates; when the ground communication code rate is low, choose short frame memory offloading frames with small data volume; when the ground communication code rate is high, choose long frame memory offloading frames with large data volume. Users can choose which memory to use for offloading frames according to the actual application scenario.

[0053] In order to improve the reliability of data interaction, a data cache queue is designed when the remote terminal control software mounted on the 1553B bus performs memory unloading. When performing the memory unloading operation, the memory unloading data of the remote terminal control software is first stored in the memory unloading queue, and the integrated electronic software reads the memory unloading data of the remote terminal control software from the memory unloading data queue and transmits it to the ground.

[0054] In order to ensure the continuity of satellite-to-ground communication data when the remote terminal control software memory is being downloaded, the present invention has designed a scheme for complementing the memory downloaded data with the real-time telemetry data. When the spacecraft is performing memory data memory downloading, the default short frame memory download is transmitted to the ground at a ratio of 1:3 between the real-time telemetry frame and the memory downloaded frame, and the default long frame memory download is transmitted to the ground at a ratio of 1:1 between the real-time telemetry frame and the memory downloaded frame. If the integrated electronic software does not receive the remote terminal control software memory downloaded data during the period when the memory downloaded frame needs to be downloaded, the real-time telemetry frame is directly obtained for download during this period to ensure continuous and uninterrupted data download between the satellite and the ground.

[0055] The memory download mode designed by the integrated electronic software can not only download the memory data in real time, but also ensure the uninterrupted download of the detector's real-time telemetry.

[0056] In the memory unloading mode designed by the integrated electronic software, conventional real-time telemetry frames and memory unloading frames are transmitted in proportion. In the short frame memory unloading mode, since the short frame data volume is only 256 bytes per frame, it is designed that short frame memory unloading is transmitted to the ground in a ratio of 1:3 between conventional real-time telemetry frames and memory unloading frames. In the long frame memory unloading mode, since the long frame data volume is 1024 bytes per frame, it is designed that long frame memory unloading is transmitted to the ground in a ratio of 1:1 between conventional real-time telemetry frames and memory unloading frames.

[0057] In order to improve the fault tolerance rate of data interaction between the comprehensive electronic (BC) software or the remote terminal (RT) control software, a fault tolerance number is set for the memory unloading data of the remote terminal control software to prevent the memory unloading from being mistakenly stopped due to timing jitter when the memory unloading data of the remote terminal control software is transmitted to the comprehensive electronic software, resulting in incomplete memory data unloading.

[0058] After the integrated electronic software enters the memory unloading mode, the integrated electronic software organizes the remote terminal control software memory unloading periodically at 500ms. When no memory unloading data is received from the remote terminal control software within a period, the memory unloading is not stopped during the period, and the remote terminal control software memory unloading data acquisition failure count is set to +1. At the same time, the current period transmits regular real-time telemetry frames. The remote terminal control software memory unloading is stopped only when the remote terminal control software memory unloading data acquisition failure count is > 3 times during the entire memory unloading process, and the memory unloading mode is exited.

[0059] Next, the present invention will be described in more detail.

[0060] A method for implementing long and short frame memory unloading of memory data of a deep space exploration spacecraft is used for memory data communication between the spacecraft and the ground.

[0061] During the spacecraft's in-orbit flight, the integrated electronic software receives the operating parameters of each subsystem and software on the spacecraft, and integrates the parameter groups of each subsystem on the spacecraft into regular real-time telemetry frames and regular delayed telemetry frames according to the design requirements. Under normal working conditions, the communication between the spacecraft and the ground only requires remote control, injection or telemetry parameters. When the ground user needs to analyze some special data in the computer memory, or when a subsystem stand-alone software on the probe is abnormal, the ground needs to send a memory unloading instruction to the probe.

[0062] The existing spacecraft designs all use integrated electronic software as the data processing core, which is responsible for the data interaction of all subsystem stand-alone control software. The physical connection between the subsystems of most spacecraft uses RS422 serial port and 1553B bus. RS422 serial port communication is mostly used for communication between each stand-alone control software and the sub-FPGA module it contains. Communication between each stand-alone control software mostly uses 1553B bus. The existing spacecraft design integrated electronic software is used as a bus controller (BC), and other stand-alone control software is used as a remote terminal (RT). Figure 1 The figure shows a block diagram of the terminal systems for unloading spacecraft memory.

[0063] After receiving the ground memory download instruction, the spacecraft integrated electronic software organizes the integrated electronic (BC) computer or remote terminal (RT) computer memory data to download to the ground according to the demand. The integrated electronic software transmits the memory data of the satellite integrated electronic software or remote terminal (RT) control software to the ground in the form of telemetry frames. Figure 2 Unload the control logic diagram for the memory. Figure 2 As shown, the method comprises the following steps:

[0064] After the integrated electronic software receives the ground memory unloading instruction, the spacecraft integrated electronic software memory unloading management module runs periodically every 500ms. First, the current memory unloading working state is judged. The memory unloading working state is divided into three states: starting state, ongoing memory unloading state, and other / stopped memory unloading state. If the current spacecraft memory unloading state is the starting state, it is further determined whether the specific unloading target is the integrated electronic (BC) computer or the remote terminal (RT) computer. After identifying the memory unloading target, the memory unloading start address and the total number of unloading packages are set according to the instructions on the ground. If the memory is unloaded to the remote terminal (RT) computer, the memory unloading start instruction must be forwarded to the remote terminal (RT) computer, and the memory unloading state on the current device is set to the ongoing memory unloading state. The operation in this cycle is completed and waits to enter the next 500ms working cycle.

[0065] When the integrated electronic software runs to the next 500ms operation cycle, it is determined that the current memory unloading state is in progress. Then the memory data of the unloading target is organized to be unloaded to the ground. The present invention designs two types of data frames, long frame and short frame, for the memory unloading telemetry frame of the detector. The total frame length of the long frame memory unloading data is designed to be 1024 bytes, and the total frame length of the short frame memory unloading data is designed to be 256 bytes. Ground users can choose to use long frame memory unloading or short frame memory unloading according to different ground-to-earth communication rates. When the ground communication code rate is lower than 256000bps, a short frame memory unloading frame with a length of 256 bytes is selected; when the ground communication code rate is higher than 256000bps, a long frame memory unloading frame with a length of 1024 bytes is selected. Users can choose which memory unloading frame to use according to the actual application scenario. After the integrated electronic software determines that the current memory unloading state is in progress, it determines whether the unloading mode selected by the ground is long frame memory unloading or short frame memory unloading.

[0066] If the ground chooses to use long frame memory unloading, the integrated electronic software calls the long frame memory unloading logic. The long frame memory unloading is transmitted to the ground in a 1:1 ratio of real-time telemetry frames and memory unloading frames.

[0067] Determine whether the operation cycle of the integrated electronic software memory unloading module is Tm_cycle%2==0 (Tm_cycle is the operation count of the integrated electronic software memory unloading module, which is +1 per cycle and accumulates cyclically).

[0068] If Tm_cycle%2 is equal to 0:

[0069] Then determine the unloading target:

[0070] If the unloading target is a comprehensive electronic (BC) computer, determine whether the total number of unloading packages has reached the maximum package data. If it has reached the maximum number of packages, exit the memory unloading mode. If it has not reached the maximum number of packages, directly obtain the memory data of the comprehensive electronic computer and unload it on the ground.

[0071] If the unloading target is a remote terminal (RT) computer, it is determined whether the total number of unloading packets has reached the maximum number of packets or whether the failure count of the remote terminal (RT) computer memory unloading data acquisition is greater than 3 times. If the conditions are met, the memory unloading mode is exited. If the conditions are not met, the memory unloading data is read from the remote terminal (RT) computer memory unloading data queue. In order to improve the reliability of data interaction, a data cache queue is designed for memory unloading of the remote terminal (RT) computer mounted on the 1553B bus. When performing a memory unloading operation, the memory unloading data of the remote terminal (RT) computer control software is first stored in the memory unloading queue, and the integrated electronic software reads the remote terminal (RT) computer memory unloading data from the memory unloading data queue and transmits it to the ground. If the data is successfully retrieved from the remote terminal (RT) computer memory data unloading queue, the acquired remote terminal (RT) computer memory data will be transmitted to the ground. If the data is failed to be retrieved from the remote terminal (RT) computer memory data unloading queue, in order to improve the fault tolerance rate of data interaction between the integrated electronic (BC) computer and the remote terminal (RT) computer, a fault tolerance number is set for the memory unloading data of the remote terminal control software to prevent the memory unloading from being mistakenly stopped due to timing jitter when the remote terminal control software memory unloading data is transmitted to the integrated electronic software, resulting in incomplete memory data unloading. In the case of failure to read the remote terminal (RT) computer memory unloading, only the remote terminal (RT) computer memory unloading data acquisition failure count is set +1, and the real-time telemetry frame is transmitted in the current cycle (the design idea of ​​this method is that when the memory unloading frame needs to be transmitted, if the on-board memory unloading data is not obtained in time, the real-time telemetry frame is directly obtained in this cycle for transmission, to ensure continuous and uninterrupted transmission of data between the satellite and the ground). The remote terminal (RT) computer memory unloading will be stopped and the memory unloading mode will be exited only when the remote terminal (RT) computer memory unloading data acquisition failure count during the entire memory unloading process is greater than 3 times.

[0072] If Tm_cycle%2 is not equal to 0, the real-time telemetry frame is transmitted. This design method can not only transmit the memory data in real time, but also be compatible with the uninterrupted transmission of the detector's real-time telemetry, and the data is transmitted alternately.

[0073] When the integrated electronic software detects that the memory unloading working state is other / stop memory unloading state, it exits memory unloading.

[0074] If the ground chooses to use short frame memory unloading, the integrated electronic software calls the short frame memory unloading logic. The short frame memory unloading function logic is the same as the long frame memory unloading function logic, only the memory unloading frame data length is adjusted from 1024 bytes to 256 bytes, and the real-time telemetry frame and memory unloading frame are designed to be transmitted to the ground in a ratio of 1:3.

[0075] The embodiments of the present invention provide a method and system for implementing long and short frame memory unloading of memory data of a deep space exploration spacecraft. The method can flexibly select the memory unloading data of each stand-alone control software of the spacecraft to be transmitted to the ground according to different ground code rates and different memory unloading data volume requirements, thereby improving the flexibility of memory data acquisition when the detector is in orbit.

[0076] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0077] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A method for implementing long and short frame memory unloading of deep space exploration spacecraft memory data, characterized in that: include: Step S1: The integrated electronic software receives the operating parameters of each subsystem stand-alone and software on the satellite, and integrates the conventional real-time telemetry frame and conventional delayed telemetry frame of the operating parameter group of each subsystem stand-alone and software on the satellite according to the design requirements; Step S2: When the ground user needs to analyze some special data in the computer memory, or when a subsystem stand-alone software on the detector is abnormal, the ground sends a memory unloading instruction to the detector; Step S3: After the integrated electronic software receives the ground memory download instruction, it organizes the integrated electronic software or remote terminal software memory data to be downloaded to the ground according to the instruction requirements; Step S4: the integrated electronic software transmits the memory data of the satellite integrated electronic software or the remote terminal control software to the ground in the form of telemetry frames; When the spacecraft is performing memory data memory unloading, by default, the short frame memory unloading is transmitted to the ground at a ratio of 1:3 between the real-time telemetry frame and the memory unloading frame, and the long frame memory unloading is transmitted to the ground at a ratio of 1:1 between the real-time telemetry frame and the memory unloading frame. If the integrated electronic software does not receive the memory unloading data from the remote terminal control software during the period when the memory unloading frame needs to be transmitted, the real-time telemetry frame is directly obtained for transmission during this period to ensure continuous and uninterrupted transmission of data between the spacecraft and the ground. The memory offload mode designed by the integrated electronic software is used to transmit regular real-time telemetry frames and memory offload frames in proportion; In the short frame memory unloading mode, since the data volume of a short frame is only 256 bytes, the short frame memory unloading is designed to be transmitted to the ground in a ratio of 1:3 between the conventional real-time telemetry frame and the memory unloading frame; Long frame memory unloading mode is designed to transmit the long frame memory unloading to the ground in a 1:1 ratio of conventional real-time telemetry frames and memory unloading frames because the long frame data volume is 1024 bytes per frame. The memory download mode designed by the integrated electronic software can not only download the memory data in real time, but also ensure the uninterrupted download of the detector's real-time telemetry.

2. The method for implementing long and short frame memory unloading of deep space exploration spacecraft memory data according to claim 1 is characterized in that: The memory unloading target can be designated by the ground user as integrated electronic software or remote terminal control software.

3. The method for implementing long and short frame memory unloading of deep space exploration spacecraft memory data according to claim 1, characterized in that: The data frame types designed for the telemetry frames unloaded from the memory of the detector include long frames and short frames. The total length of the data frames unloaded from the memory of the long frame is designed to be 1024 bytes, and the total length of the data frames unloaded from the memory of the short frame is designed to be 256 bytes.

4. The method for implementing long and short frame memory unloading of deep space exploration spacecraft memory data according to claim 3 is characterized in that: Ground users can choose to use long frame memory offload or short frame memory offload according to different ground-to-space communication rates; When the ground communication code rate is lower than 256000bps, a short frame memory with a length of 256 bytes is selected to unload the frame; When the ground communication code rate is higher than 256000bps, the long frame memory with a length of 1024 bytes is selected to unload the frame.

5. The method for implementing long and short frame memory unloading of deep space exploration spacecraft memory data according to claim 1, characterized in that: When the remote terminal control software mounted on the 1553B bus performs memory unloading, a data cache queue is designed. When performing the memory unloading operation, the memory unloading data of the remote terminal control software is first stored in the memory unloading queue, and the integrated electronic software reads the memory unloading data of the remote terminal control software from the memory unloading data queue and transmits it to the ground.

6. The method for implementing long and short frame memory unloading of deep space exploration spacecraft memory data according to claim 1, characterized in that: After the integrated electronic software enters the memory unloading mode, the integrated electronic software organizes the remote terminal control software memory unloading periodically at 500ms. When the remote terminal control software memory unloading data is not received within a certain period, the memory unloading is not stopped during the period, and the remote terminal control software memory unloading data acquisition failure count is set to +1, and the regular real-time telemetry frame is transmitted in the current period. Only when the remote terminal control software memory unloading data acquisition failure count during the entire memory unloading process is greater than 3 times, the remote terminal control software memory unloading is stopped and the memory unloading mode is exited.

7. The method for implementing long and short frame memory unloading of deep space exploration spacecraft memory data according to claim 1, characterized in that: Set the fault tolerance times for unloading data from the memory of the remote terminal control software.

8. A system for realizing long and short frame memory unloading of deep space exploration spacecraft memory data, characterized in that: include: Module M1: The integrated electronic software receives the operating parameters of each subsystem and software on the satellite, and integrates the parameter groups of each subsystem and software on the satellite into conventional real-time telemetry frames and conventional delayed telemetry frames according to the design requirements; Module M2: When the ground user needs to analyze some special data in the computer memory, or when a subsystem stand-alone software on the detector is abnormal, the ground sends a memory unloading instruction to the detector; Module M3: After the integrated electronic software receives the ground memory unloading instruction, it organizes the integrated electronic software or remote terminal software memory data to unload the ground according to the instruction requirements; Module M4: The integrated electronic software transmits the memory data of the satellite integrated electronic software or the remote terminal control software to the ground in the form of telemetry frames; When the spacecraft is performing memory data memory unloading, by default, the short frame memory unloading is transmitted to the ground at a ratio of 1:3 between the real-time telemetry frame and the memory unloading frame, and the long frame memory unloading is transmitted to the ground at a ratio of 1:1 between the real-time telemetry frame and the memory unloading frame. If the integrated electronic software does not receive the memory unloading data from the remote terminal control software during the period when the memory unloading frame needs to be transmitted, the real-time telemetry frame is directly obtained for transmission during this period to ensure continuous and uninterrupted transmission of data between the spacecraft and the ground. The memory offload mode designed by the integrated electronic software is used to transmit regular real-time telemetry frames and memory offload frames in proportion; In the short frame memory unloading mode, since the data volume of a short frame is only 256 bytes, the short frame memory unloading is designed to be transmitted to the ground in a ratio of 1:3 between the conventional real-time telemetry frame and the memory unloading frame; Long frame memory unloading mode is designed to transmit the long frame memory unloading to the ground in a 1:1 ratio of conventional real-time telemetry frames and memory unloading frames because the long frame data volume is 1024 bytes per frame. The memory download mode designed by the integrated electronic software can not only download the memory data in real time, but also ensure the uninterrupted download of the detector's real-time telemetry.

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