Spacecraft dynamic test execution method based on telemetry data

Abstract

The invention discloses a spacecraft dynamic test execution method based on telemetry data, and relates to the technical field of data adjustment. The method comprises the following steps: firstly, collecting telemetering data of each data source, testing and analyzing the telemetering data, and carrying out real-time reference alignment and data interpretation on the telemetering data of the plurality of data sources of the spacecraft so as to identify the validity and accuracy of the data; and finally, according to the interpretation result and the average time length of the telemetering control instruction, the acquisition strategy of telemetering data is optimized, the high efficiency and accuracy of the data acquisition process are ensured, and the accuracy and reliability of the dynamic test of the spacecraft are ensured. And the time sequence of the telemetering data is ensured by means of low-complexity time performance. Furthermore, telemetering data transmission of the tested software is used as a time sequence control point, and a time sequence control engine is used for performing time sequence synchronous control on the automatic test tool and the test target machine, so that a test result error caused by mismatching of a test time sequence is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of data adjustment, and in particular to a method for executing dynamic tests of a spacecraft based on telemetry data. Background Art

[0002] The background of spacecraft dynamic testing based on telemetry data stems from the complexity and high risk of spacecraft during launch, on-orbit operation and mission execution. In order to ensure the reliability and stability of spacecraft systems in extreme environments, telemetry technology came into being. By obtaining various operating data of spacecraft in real time, including temperature, vibration, attitude, power system status, etc., the ground control center can monitor the health of the spacecraft in a timely manner and predict and handle possible faults.

[0003] Prior art, such as the invention patent with announcement number: CN115617023B, discloses a method and device for locating abnormalities in a spacecraft attitude control system, wherein the method comprises: determining a set of information on sample telemetry data to be detected, the sample telemetry data to be detected comprising: a name of a telemetry parameter to be detected, parameter characteristics and data values ​​corresponding to each name of the telemetry parameter to be detected; preprocessing the sample telemetry data to be detected to obtain processed telemetry data; performing attitude determination mode telemetry and attitude control mode telemetry parameter change sequence detection on the processed telemetry data according to preset spacecraft characteristics; marking the attitude determination mode telemetry and attitude control mode telemetry parameter change sequence according to a preset data marking method to generate an attitude fault feature sequence; and automatically locating abnormal device components in the attitude control system according to the attitude fault feature sequence.

[0004] Prior art, such as the invention patent announcement with announcement number: CN104834305B, discloses a distribution network automation terminal telemetry anomaly analysis system and method based on a DMS system, including a current anomaly monitoring module and a voltage anomaly monitoring module, wherein the current anomaly monitoring module and the voltage anomaly monitoring module are respectively connected to the DMS system and the distribution network production system, and the current anomaly monitoring module compares the real-time telemetry data of the three-phase current of the DMS system with its historical telemetry data and the feeder switch current in the DMS system to determine whether the telemetry current of the distribution network automation terminal is abnormal so as to issue a telemetry anomaly work order to the distribution network production system; the voltage anomaly monitoring module compares the real-time telemetry data of the phase-to-phase voltage on the power supply side and the phase-to-phase voltage on the load side of the DMS system with the historical telemetry data and the limit voltage to determine whether the telemetry voltage of the distribution network automation terminal is abnormal so as to issue a telemetry anomaly work order to the distribution network production system.

[0005] At present, there are several problems in the process of dynamic testing of spacecraft with telemetry data. On the one hand, during the testing process of spacecraft software, telemetry data is limited by factors such as bandwidth capacity, measurement and control means, and mission requirements. This may cause the state data of a certain control cycle of the spacecraft software to arrive at different times when transmitted to the ground through the telemetry channel. When performing automatic testing, the latest received telemetry parameters of each frame may not accurately reflect the state of the same control cycle of the spacecraft software, thereby causing test failure. On the other hand, traditional automatic testing tools are all time-driven. Their mechanism is to query the system time or the telemetry data of the software under test at a fixed frequency, and drive the test execution after the execution conditions are met. Since the automatic test driver software and the test environment are executed asynchronously, and there are query interval delays, test execution response delays, instruction and data transmission delays, etc., the timing of automatic test instruction sending and data interpretation cannot be accurately controlled, and there are risks such as instruction sending delays and interpretation delays, which leads to the test conclusion not being able to truly reflect the software status. Summary of the invention

[0006] In view of the deficiencies in the prior art, the present invention provides a method for executing spacecraft dynamic testing based on telemetry data, which can effectively solve the problems involved in the above-mentioned background technology.

[0007] To achieve the above objectives, the present invention is implemented through the following technical solutions: a spacecraft dynamic test execution method based on telemetry data, including collecting telemetry data from various data sources of the spacecraft, testing and analyzing the telemetry data from various data sources of the spacecraft, obtaining alignment results of the telemetry data from various data sources of the spacecraft, and aligning the telemetry data from various data sources of the spacecraft to obtain telemetry alignment data of various data sources of the spacecraft.

[0008] The telemetry alignment data of each data source of the spacecraft are analyzed to obtain the quality index of the telemetry alignment data of each data source of the spacecraft, and the telemetry alignment data of each data source of the spacecraft are interpreted and processed according to the quality index of the telemetry alignment data of each data source of the spacecraft to obtain the interpretation result of the telemetry alignment data of each data source of the spacecraft.

[0009] According to the interpretation results of the telemetry alignment data of each data source of the spacecraft, the collection of telemetry data is adjusted in combination with the average duration of the telemetry control instructions of the spacecraft, and the dynamic adjustment quality result of the telemetry data is obtained.

[0010] Furthermore, the telemetry data of each data source of the spacecraft includes the time point of sending each test command, the time point of starting to execute each test command, the time point of sending each telemetry data, the time point of receiving each telemetry data, the time interval for collecting telemetry data, and the average query interval delay of telemetry data.

[0011] Furthermore, the telemetry data of each data source of the spacecraft is tested and analyzed, and the specific analysis process is: extracting the time point of sending each test command of each data source of the spacecraft and the time point of starting to execute each test command, and performing difference processing to obtain the test execution response delay of each test command.

[0012] The time points of receiving telemetry data and sending telemetry data of each data source of the spacecraft are extracted, and the difference processing is performed to obtain the transmission delay of each telemetry data.

[0013] The test execution response delay of each test command of each data source of the spacecraft, the transmission delay of each telemetry data, the collection time interval of telemetry data and the average query interval delay of telemetry data are extracted, and the alignment requirement index of the telemetry data of each data source of the spacecraft is obtained after processing. The alignment requirement index of the telemetry data of each data source of the spacecraft is used to evaluate the synchronization degree of telemetry data.

[0014] Furthermore, the alignment results of the telemetry data of each data source of the spacecraft are obtained, and the specific analysis conditions are: extracting the alignment requirement index of the telemetry data of each data source of the spacecraft, and comparing it with the alignment requirement index threshold of the telemetry data of each data source of the spacecraft stored in the database to obtain the alignment results of the telemetry data of each data source of the spacecraft, the alignment results of the telemetry data of each data source of the spacecraft include those that need alignment and those that do not need alignment, if the alignment requirement index of the telemetry data of a certain data source of the spacecraft is higher than or equal to the alignment requirement index threshold of the telemetry data of the spacecraft data source, then the alignment result of the telemetry data of the spacecraft data source is defined as requiring alignment, and the telemetry data of the spacecraft data source is aligned, if the alignment requirement index of the telemetry data of a certain data source of the spacecraft is lower than the alignment requirement index threshold of the telemetry data of the spacecraft data source, then the alignment result of the telemetry data of the spacecraft data source is defined as not requiring alignment.

[0015] Furthermore, the telemetry data of each data source of the spacecraft are aligned to obtain the telemetry alignment data of each data source of the spacecraft. The specific process is: according to the alignment result of the telemetry data of each data source of the spacecraft, the telemetry data of each data source of the spacecraft are aligned; if the alignment result of the telemetry data of a certain data source of the spacecraft needs to be aligned, the telemetry data of the data source of the spacecraft is aligned, and the telemetry data of the data source of the spacecraft is marked as the telemetry alignment data of each data source of the spacecraft; if the alignment result of the telemetry data of a certain data source of the spacecraft does not need to be aligned, the telemetry data of the data source of the spacecraft is directly marked as the telemetry alignment data of each data source of the spacecraft, thereby obtaining the telemetry alignment data of each data source of the spacecraft.

[0016] Furthermore, the telemetry alignment data of each spacecraft data source are analyzed to obtain a quality index of the telemetry alignment data of each spacecraft data source. The specific analysis process is: counting the data collection time point in each spacecraft data source, and extracting the data collection time point in each spacecraft data source, extracting the reference time point stored in the database, performing absolute value processing on the difference between the reference time point and the data collection time point in each spacecraft data source, and obtaining the collection time difference of each data in each spacecraft data source.

[0017] The mean error of the collection time of each data in each data source of the spacecraft is counted, and the data missing rate in each data source of the spacecraft is counted. The quality index of the telemetry alignment data of each data source of the spacecraft is obtained after processing. The quality index of the telemetry alignment data of each data source of the spacecraft is used to indicate the reliability of the alignment quality of the telemetry data.

[0018] Furthermore, the telemetry alignment data of each data source of the spacecraft are interpreted and processed to obtain the interpretation results of the telemetry alignment data of each data source of the spacecraft. The specific process is: according to the quality index of the telemetry alignment data of each data source of the spacecraft, and compared with the quality index threshold of the telemetry alignment data of each data source of the spacecraft stored in the database, the interpretation results of the telemetry alignment data of each data source of the spacecraft are obtained.

[0019] Furthermore, the judgment results of the telemetry alignment data of each data source of the spacecraft include normal and abnormal. If the quality index of the telemetry alignment data of a certain data source of the spacecraft is higher than or equal to the quality index threshold of the telemetry alignment data of the data source of the spacecraft, the judgment result of the telemetry alignment data of the data source of the spacecraft is defined as normal. If the quality index of the telemetry alignment data of a certain data source of the spacecraft is lower than the quality index threshold of the telemetry alignment data of the data source of the spacecraft, the judgment result of the telemetry alignment data of the data source of the spacecraft is defined as abnormal.

[0020] Furthermore, according to the judgment result of the telemetry alignment data of each data source of the spacecraft, the collection of telemetry data is adjusted in combination with the average duration of the telemetry control instructions of the spacecraft, and the dynamic adjustment quality result of the telemetry data is obtained. The specific process is: if the judgment result of the telemetry alignment data of a data source of the spacecraft is normal, there is no need to collect and adjust the telemetry data; if the judgment result of the telemetry alignment data of a data source of the spacecraft is abnormal, the average duration of the telemetry control instructions of the spacecraft is obtained, and the reference duration of the telemetry control instructions of the spacecraft stored in the database is extracted, and the average duration of the telemetry control instructions of the spacecraft is compared with the reference duration of the telemetry control instructions of the spacecraft stored in the database; if the average duration of the telemetry control instructions of the spacecraft is higher than or equal to the reference duration of the telemetry control instructions of the spacecraft, the telemetry data of the data source of the spacecraft is re-collected and an alarm is triggered; if the average duration of the telemetry control instructions of the spacecraft is lower than the reference duration of the telemetry control instructions of the spacecraft, the frequency of sending the telemetry control instructions is reduced.

[0021] The sending of telemetry control instructions is monitored to obtain dynamic adjustment data of the telemetry control instructions, including telemetry data transmission delay, data loss rate, and number of timed instructions, and a dynamic adjustment quality index of the telemetry data is obtained. The dynamic adjustment quality index of the telemetry data indicates the accuracy of the telemetry system in completing data transmission and control tasks during the dynamic adjustment process.

[0022] According to the dynamic adjustment quality index of the telemetry data, it is compared with the dynamic adjustment quality index threshold of the telemetry data stored in the database. If the dynamic adjustment quality index of the telemetry data is higher than or equal to the dynamic adjustment quality index threshold of the telemetry data, the dynamic adjustment quality result of the telemetry data is marked as qualified; if the dynamic adjustment quality index of the telemetry data is lower than the dynamic adjustment quality index threshold of the telemetry data, the dynamic adjustment quality result of the telemetry data is marked as unqualified and the number of retransmissions of the data packet is reduced.

[0023] Furthermore, the alignment requirement index of the telemetry data of each data source of the spacecraft has the following specific analysis conditions:

[0024]

[0025] In the formula, A j represents the alignment requirement index of the telemetry data of the jth data source of the spacecraft, t j→k represents the test execution response delay of the kth test command of the jth data source of the spacecraft, t j→g represents the g-th telemetry data transmission delay from the j-th data source of the spacecraft, ω j represents the time interval for collecting telemetry data from the jth data source of the spacecraft, T jrepresents the average query interval delay of the telemetry data of the jth data source of the spacecraft, Δt1 represents the test execution definition response delay of the set test command, Δt2 represents the set telemetry data transmission definition delay, Δω represents the set reference collection time interval of the telemetry data, ΔT represents the set reference query interval delay of the telemetry data, α1 represents the correction factor corresponding to the set test execution response delay, α2 represents the correction factor corresponding to the set telemetry data transmission delay, α3 represents the correction factor corresponding to the set collection time interval of the telemetry data, α4 represents the correction factor corresponding to the set average query interval delay of the telemetry data, j represents the number of each data source, m represents the total number of data sources, k represents the number of each test command, s represents the total number of test commands, g represents the number of each test of the telemetry data transmission delay, and h represents the total number of tests of the telemetry data transmission delay.

[0026] The present invention has the following beneficial effects:

[0027] (1) The present invention provides a method for executing dynamic tests of spacecraft based on telemetry data. First, the telemetry data of each data source is collected and tested and analyzed. The telemetry data of multiple data sources of the spacecraft are real-time benchmark aligned and data interpreted, thereby identifying the validity and accuracy of the data. Finally, according to the interpretation results and the average duration of telemetry control instructions, the collection strategy of telemetry data is optimized to ensure the efficiency and accuracy of the data collection process, which helps to ensure the accuracy and reliability of the dynamic test of the spacecraft. The timing of the telemetry data is guaranteed by means of low-complexity time performance. Furthermore, the method of using the telemetry data sent by the tested software as a timing control point and performing timing synchronization control on the automatic test tool and the test target machine through the timing control engine avoids test result errors caused by test timing mismatch.

[0028] (2) The present invention obtains the alignment requirement index of telemetry data, aligns the telemetry data of each data source, and synchronizes the data when necessary. This can help testers identify the time deviation between different data sources, adjust and correct data synchronization problems in a timely manner, ensure data accuracy and consistency, and provide strong data support for dynamic testing and task execution.

[0029] (3) The present invention helps to ensure the accuracy and reliability of telemetry data by obtaining the quality index of each data source of telemetry data, and helps to avoid analysis deviations or test result distortions caused by data delays or errors. Secondly, it makes the data monitoring of spacecraft during flight more efficient, and can quickly identify abnormal data or potential faults, thereby improving the response speed and safety of the test. In addition, the evaluation of the quality index not only helps to judge the data quality, but also provides strong support for subsequent spacecraft performance analysis and problem diagnosis, reduces potential risks, and provides a more accurate decision-making basis for the smooth execution of space missions, avoiding test result errors caused by test timing mismatch.

[0030] (4) The present invention analyzes the interpretation results of the telemetry alignment data of each data source of the spacecraft and compares the average duration of the telemetry control instructions of the spacecraft with the reference duration, thereby effectively avoiding incomplete or inaccurate telemetry data collection caused by insufficient execution time of the control instructions, thereby improving the quality of the telemetry data and the efficiency of the test.

[0031] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of the method flow of the present invention;

[0033] Figure 2 It is a logic flow chart of telemetry reference alignment and test interpretation of the present invention;

[0034] Figure 3 The present invention is a timing control flow chart of the automatic test execution mechanism based on timing synchronization. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] In the description of the present invention, it should be understood that the terms "opening", "upper", "lower", "thickness", "top", "middle", "length", "inside", "all around" and the like indicating orientation or positional relationship are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the components or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0037] See also Figure 1As shown, an embodiment of the present invention provides a technical solution for a spacecraft dynamic test execution method based on telemetry data: a spacecraft dynamic test execution method based on telemetry data, including collecting telemetry data from various data sources of the spacecraft, testing and analyzing the telemetry data from various data sources of the spacecraft, obtaining alignment results of the telemetry data from various data sources of the spacecraft, and aligning the telemetry data from various data sources of the spacecraft to obtain telemetry alignment data of various data sources of the spacecraft.

[0038] The telemetry alignment data of each data source of the spacecraft are analyzed to obtain the quality index of the telemetry alignment data of each data source of the spacecraft, and the telemetry alignment data of each data source of the spacecraft are interpreted and processed according to the quality index of the telemetry alignment data of each data source of the spacecraft to obtain the interpretation result of the telemetry alignment data of each data source of the spacecraft.

[0039] According to the interpretation results of the telemetry alignment data of each data source of the spacecraft, the collection of telemetry data is adjusted in combination with the average duration of the telemetry control instructions of the spacecraft, and the dynamic adjustment quality result of the telemetry data is obtained.

[0040] It should be noted that this embodiment creatively proposes a real-time benchmark alignment method with O(1) time complexity, and uses each telemetry data transmission as a timing control point. The timing of each operation is controlled by the timing synchronization servo engines respectively deployed on the test tool and the target machine. This will not affect the execution logic of the software under test itself, and realize the timing synchronization between the test script and the software under test.

[0041] Specifically, the telemetry data of each data source of the spacecraft include the time point of sending each test command, the time point of starting to execute each test command, the time point of sending each telemetry data, the time point of receiving each telemetry data, the time interval of collecting telemetry data and the average query interval delay of telemetry data.

[0042] Specifically, the telemetry data of each data source of the spacecraft is tested and analyzed. The specific analysis process is: extract the time point of sending each test command of each data source of the spacecraft and the time point of starting to execute each test command, and perform difference processing to obtain the test execution response delay of each test command.

[0043] The time points of receiving telemetry data and sending telemetry data of each data source of the spacecraft are extracted, and the difference processing is performed to obtain the transmission delay of each telemetry data.

[0044] The test execution response delay of each test command of each data source of the spacecraft, the transmission delay of each telemetry data, the collection time interval of telemetry data and the average query interval delay of telemetry data are extracted, and the alignment requirement index of the telemetry data of each data source of the spacecraft is obtained after processing. The alignment requirement index of the telemetry data of each data source of the spacecraft is used to evaluate the synchronization degree of telemetry data.

[0045] Specifically, the alignment results of the telemetry data of each data source of the spacecraft are obtained, and the specific analysis conditions are: extracting the alignment requirement index of the telemetry data of each data source of the spacecraft, and comparing it with the alignment requirement index threshold of the telemetry data of each data source of the spacecraft stored in the database, to obtain the alignment results of the telemetry data of each data source of the spacecraft, the alignment results of the telemetry data of each data source of the spacecraft include those that need alignment and those that do not need alignment, if the alignment requirement index of the telemetry data of a certain data source of the spacecraft is higher than or equal to the alignment requirement index threshold of the telemetry data of the data source of the spacecraft, then the alignment result of the telemetry data of the data source of the spacecraft is defined as requiring alignment, and the telemetry data of the data source of the spacecraft is aligned, if the alignment requirement index of the telemetry data of a certain data source of the spacecraft is lower than the alignment requirement index threshold of the telemetry data of the data source of the spacecraft, then the alignment result of the telemetry data of the data source of the spacecraft is defined as not requiring alignment.

[0046] Specifically, the telemetry data of each data source of the spacecraft are aligned to obtain the telemetry alignment data of each data source of the spacecraft. The specific process is: according to the alignment result of the telemetry data of each data source of the spacecraft, the telemetry data of each data source of the spacecraft are aligned; if the alignment result of the telemetry data of a certain data source of the spacecraft needs to be aligned, the telemetry data of the data source of the spacecraft is aligned, and the telemetry data of the data source of the spacecraft is marked as the telemetry alignment data of each data source of the spacecraft; if the alignment result of the telemetry data of a certain data source of the spacecraft does not need to be aligned, the telemetry data of the data source of the spacecraft is directly marked as the telemetry alignment data of each data source of the spacecraft, thereby obtaining the telemetry alignment data of each data source of the spacecraft.

[0047] It should be noted that the alignment of telemetry data from various data sources of the spacecraft is a process to ensure that multi-source data is coordinated and consistent and meets the requirements of time synchronization. It refers to aligning data from different sensors, devices or systems according to the same timestamp through time synchronization technology for joint analysis. After alignment, a unified time series is usually obtained, which is convenient for comparing data output by different sensors or systems. In this embodiment, a GPS clock is used to provide a unified time reference for all devices, and data from different sensors, different platforms, different times or different signal sources are processed to ensure that they can match each other for further analysis, decision-making or control operations. This process usually includes steps such as data alignment, time synchronization, calibration, and interpolation.

[0048] Specifically, the telemetry alignment data of each data source of the spacecraft are analyzed to obtain the quality index of the telemetry alignment data of each data source of the spacecraft. The specific analysis process is: count the data collection time points in each data source of the spacecraft, and extract the data collection time points in each data source of the spacecraft, extract the reference time points stored in the database, and perform absolute value processing on the difference between the reference time points and the data collection time points in each data source of the spacecraft to obtain the collection time difference of each data in each data source of the spacecraft.

[0049] The mean error of the collection time of each data in each data source of the spacecraft is counted, and the data missing rate in each data source of the spacecraft is counted. The quality index of the telemetry alignment data of each data source of the spacecraft is obtained after processing. The quality index of the telemetry alignment data of each data source of the spacecraft is used to indicate the reliability of the alignment quality of the telemetry data.

[0050] It should be noted that the quality index of the telemetry alignment data of each data source of the spacecraft is analyzed under the following specific conditions:

[0051]

[0052] In the formula, R j represents the quality index of the telemetry alignment data of the jth data source of the spacecraft, T 1 j→i represents the acquisition time difference of the i-th data in the j-th data source of the spacecraft, T 2 j→i represents the mean error of the acquisition time of the i-th data in the j-th data source of the spacecraft, E j represents the data missing rate of the jth data source of the spacecraft, ΔT 1 Indicates the set data collection limit time difference, ΔT 2 represents the set collection time mean boundary error, ΔE represents the set data source boundary data missing rate, μ1 represents the correction factor corresponding to the set data collection time difference, μ2 represents the correction factor corresponding to the set data collection mean time error, and μ3 represents the correction factor corresponding to the set data missing rate.

[0053] It should be noted that there are complex correlations among the acquisition time difference, the mean error of acquisition time, and the data missing rate of each data in each data source of the spacecraft, and they affect each other. First, the acquisition time difference of each data in each data source of the spacecraft directly affects the synchronization of data and the responsiveness of the system. The acquisition time difference refers to the time deviation of data from different sensors or systems at the same time. If the acquisition time difference is large, it means that the information from different data sources may have time inconsistency problems, which will cause deviations in the monitoring of the spacecraft status. Secondly, the mean error of the acquisition time of each data in each data source of the spacecraft is closely related to the timeliness and accuracy of the data. The mean error of the acquisition time of each data in each data source of the spacecraft refers to the average value of the error between the actual time of all acquisitions of the data and its corresponding expected acquisition time, which directly affects the timeliness of data analysis. The increase in the mean error will make the system's monitoring of changes inaccurate, which in turn affects the command and control decision of the spacecraft. At the same time, the data missing rate is also closely related to the acquisition time difference and the mean error. A high data missing rate usually indicates that there are some faults or network problems in the system, resulting in the failure of data collection. Missing data often exacerbates synchronization problems caused by acquisition time differences. Therefore, under higher mean error conditions, the missing data rate is usually higher, especially in scenarios where the system needs to collect and process data more frequently.

[0054] In a specific embodiment, the value range of the correction factor corresponding to the data collection time difference is usually between 0 and 1. When in use, the correction factor corresponding to the data collection time difference can be directly obtained from the database. The correspondence between the data collection time difference and the correction factor is determined by a pre-set mapping table. For example, a mapping table is constructed by the data collection time difference and the correction factor corresponding to the data collection time difference. By inputting the real-time detected collection time difference into the mapping table, the correction factor corresponding to the data collection time difference can be obtained, thereby optimizing the synchronization of data collection and reducing the impact of time deviation.

[0055] In a specific embodiment, the value range of the correction factor corresponding to the mean time error of data collection is generally between 0 and 1. When in use, the correction factor corresponding to the mean time error of data collection can be directly obtained from the database. The correspondence between the mean time error of data collection and the correction factor is determined by a pre-set mapping table. For example, a mapping table is constructed by the mean time error of data collection and the correction factor corresponding to the mean time error of data collection. By inputting the mean time error of data collection detected in real time into the mapping table, the correction factor corresponding to the mean time error of data collection can be obtained, thereby optimizing the time accuracy of the data and reducing the data inconsistency caused by the time error.

[0056] In a specific embodiment, the correction factor corresponding to the data missing rate generally ranges from 0 to 1. When in use, the correction factor corresponding to the data missing rate can be directly obtained from the database. The correspondence between the data missing rate and the correction factor is determined by a pre-set mapping table. For example, a mapping table is constructed by the data missing rate and the correction factor corresponding to the data missing rate. By inputting the data missing rate detected in real time into the mapping table, the correction factor corresponding to the data missing rate can be obtained, thereby optimizing the integrity of the data and reducing query delays and data processing errors caused by missing data.

[0057] Specifically, the telemetry alignment data of each data source of the spacecraft are interpreted and processed to obtain the interpretation results of the telemetry alignment data of each data source of the spacecraft. The specific process is: according to the quality index of the telemetry alignment data of each data source of the spacecraft, and compared with the quality index threshold of the telemetry alignment data of each data source of the spacecraft stored in the database, the interpretation results of the telemetry alignment data of each data source of the spacecraft are obtained.

[0058] It should be noted that, in the present embodiment, the telemetry alignment data of each data source of the spacecraft are aligned and interpreted, wherein the alignment and interpretation of the telemetry alignment data of each data source of the spacecraft includes telemetry data reference alignment and interpretation logic and an automatic test execution mechanism based on timing synchronization.

[0059] It should be noted that if Figure 2 As shown, Figure 2 This is a logic flow chart of telemetry benchmark alignment and test interpretation. The telemetry data benchmark alignment and interpretation logic are as follows: Before the test starts, the benchmark parameter names x1 and x2 of the two telemetry frames that need to be interpreted are pre-specified, and the relationship between the two is described by a formula, such as x1-(x2+5)=0 (Formula 1). Then all telemetry parameter rules that need to be interpreted after benchmark alignment are provided, such as y1-y2=0 (Formula 2). In addition, telemetry frames with faster update cycles must be specified, and telemetry frames with faster update cycles will be used as benchmark comparison sources in the benchmark interpretation stage. The benchmark interpretation is to benchmark align the two telemetry frames based on Formula 1, and then determine whether Formula 2 is satisfied. The benchmark interpretation dynamically caches a portion (such as 10 frames) of telemetry data during the test.

[0060] It should be noted that if Figure 3 As shown, Figure 3This is a timing control flow chart of the automatic test execution mechanism based on timing synchronization, in which the dynamic test execution mechanism based on timing synchronization includes three parts: script execution engine, test target machine and timing synchronization servo engine. The script execution engine is responsible for parsing the automatic test script and executing the script commands therein; the test target machine simulates the target environment of the software under test, executes the simulation of the software under test, and adds timing control at the same time; the timing synchronization servo engine is the core of realizing timing control. On the one hand, it interacts with the script execution engine to control the execution timing of the script commands that need to be synchronized, and on the other hand, it interacts with the test target machine to control the simulation of the software under test. The core operations of the three parts of timing synchronization control.

[0061] Specifically, the judgment results of the telemetry alignment data of each data source of the spacecraft include normal and abnormal. If the quality index of the telemetry alignment data of a certain data source of the spacecraft is higher than or equal to the quality index threshold of the telemetry alignment data of the data source of the spacecraft, the judgment result of the telemetry alignment data of the data source of the spacecraft is defined as normal. If the quality index of the telemetry alignment data of a certain data source of the spacecraft is lower than the quality index threshold of the telemetry alignment data of the data source of the spacecraft, the judgment result of the telemetry alignment data of the data source of the spacecraft is defined as abnormal.

[0062] Specifically, according to the interpretation results of the telemetry alignment data of each data source of the spacecraft, the collection of telemetry data is adjusted in combination with the average duration of the telemetry control instructions of the spacecraft, and the dynamic adjustment quality result of the telemetry data is obtained. The specific process is as follows:

[0063] If the judgment result of the telemetry alignment data of a certain data source of the spacecraft is normal, there is no need to collect and adjust the telemetry data. If the judgment result of the telemetry alignment data of a certain data source of the spacecraft is abnormal, the average duration of the telemetry control instructions of the spacecraft is obtained, and the reference duration of the telemetry control instructions of the spacecraft stored in the database is extracted, and the average duration of the telemetry control instructions of the spacecraft is compared with the reference duration of the telemetry control instructions of the spacecraft stored in the database. If the average duration of the telemetry control instructions of the spacecraft is higher than or equal to the reference duration of the telemetry control instructions of the spacecraft, the telemetry data of the data source of the spacecraft is re-collected and an alarm is triggered. If the average duration of the telemetry control instructions of the spacecraft is lower than the reference duration of the telemetry control instructions of the spacecraft, the frequency of sending the telemetry control instructions is reduced.

[0064] It should be noted that reducing the frequency of sending telemetry control instructions means, for example, that if the average duration of the telemetry control instructions of a spacecraft is lower than the reference duration of the telemetry control instructions of the spacecraft, it is necessary to reduce the frequency of sending instructions by 10%-30% to improve the efficiency of the system, reduce the system load, and ensure that the required data can be efficiently acquired under limited bandwidth conditions.

[0065] The sending of telemetry control instructions is monitored to obtain dynamic adjustment data of the telemetry control instructions, including telemetry data transmission delay, data loss rate, and number of timed instructions, and a dynamic adjustment quality index of the telemetry data is obtained. The dynamic adjustment quality index of the telemetry data indicates the accuracy of the telemetry system in completing data transmission and control tasks during the dynamic adjustment process.

[0066] According to the dynamic adjustment quality index of the telemetry data, it is compared with the dynamic adjustment quality index threshold of the telemetry data stored in the database. If the dynamic adjustment quality index of the telemetry data is higher than or equal to the dynamic adjustment quality index threshold of the telemetry data, the dynamic adjustment quality result of the telemetry data is marked as qualified; if the dynamic adjustment quality index of the telemetry data is lower than the dynamic adjustment quality index threshold of the telemetry data, the dynamic adjustment quality result of the telemetry data is marked as unqualified and the number of retransmissions of the data packet is reduced.

[0067] It should be noted that reducing the number of retransmissions of a data packet means reducing the number of retransmissions by 1-3 times based on the original number of retransmissions to ensure a minimum number of retransmission attempts and setting a minimum value, such as 1 time, or directly abandoning the current data packet.

[0068] It should be noted that the dynamic adjustment quality index of telemetry data has the following specific analysis conditions:

[0069]

[0070] Wherein, V represents the dynamic adjustment quality index of telemetry data, Y represents the data transmission delay, d represents the data loss rate, c represents the number of timeout instructions, ΔY represents the set defined data transmission delay, Δd represents the set defined data loss rate, Δc represents the set defined number of timeout instructions, τ1 represents the correction factor corresponding to the set data transmission delay, τ2 represents the correction factor corresponding to the set data loss rate, and τ3 represents the correction factor corresponding to the set number of timeout instructions.

[0071] It should be noted that the telemetry data transmission delay, data loss rate and number of timeout instructions are not independent parameters, but are related and affect each other. First, the telemetry data transmission delay directly affects the timeliness of the data. When the transmission delay is large, the system may not be able to complete the reception and processing of the telemetry data on time, resulting in a decrease in data validity. This delay may further cause an increase in the data loss rate, because the delay may cause the data packet to fail to complete the transmission within the effective window, increasing the probability of packet loss. Secondly, a high data loss rate will affect the execution reliability of the system instructions. For example, the loss of key telemetry data may cause the instruction to fail to be judged based on complete information, thereby increasing the probability of the number of timeout instructions. Especially in complex test scenarios, a high loss rate may force the system to frequently retransmit or resend instructions, thereby further prolonging the data transmission time and exacerbating the response lag of the system. In turn, frequent timeout instructions will also exacerbate data transmission delays, because the system needs to handle additional error recovery and re-execution processes, resulting in increased link load.

[0072] In a specific embodiment, the value range of the correction factor corresponding to the data transmission delay is generally between 0 and 1. When in use, the correction factor corresponding to the data transmission delay can be directly obtained from the database. The correspondence between the correction factor corresponding to the data transmission delay and the data transmission delay is determined by a pre-set mapping table. For example, a mapping table of data transmission delay and its corresponding correction factor is constructed. During the test process, by inputting the real-time detected data transmission delay into the mapping table, the corresponding correction factor can be quickly obtained, thereby helping to adjust the tolerance range for the transmission delay in the test and improve the real-time performance and accuracy of the data.

[0073] In a specific embodiment, the correction factor corresponding to the data loss rate also ranges from 0 to 1. The test system obtains the corresponding correction factor by counting the data loss rate of the current link and combining it with a predefined mapping table. In specific applications, the real-time detected data loss rate will be used as an input to query the mapping table to obtain the corresponding correction factor, which is used to dynamically optimize the data transmission strategy and reduce the test deviation caused by link congestion or packet loss.

[0074] In a specific embodiment, the correction factor corresponding to the number of timeout instructions is also between 0 and 1, and the correction factor is determined by a pre-set mapping table. For example, a mapping table of the number of timeout instructions and their correction factors is constructed. During the test process, the system monitors the number of timeouts of instruction execution in real time, and enters the value into the mapping table to quickly obtain the corresponding correction factor. The correction factor can be used to dynamically adjust the timeout time of the test instruction or optimize the allocation of system resources, thereby reducing the impact of the timeout instruction on the accuracy of the test result.

[0075] Specifically, the alignment requirement index of telemetry data from various data sources of spacecraft is analyzed under the following conditions:

[0076]

[0077] In the formula, A j represents the alignment requirement index of the telemetry data of the jth data source of the spacecraft, t j→k represents the test execution response delay of the kth test command of the jth data source of the spacecraft, t j→g represents the g-th telemetry data transmission delay from the j-th data source of the spacecraft, ω j represents the time interval for collecting telemetry data from the jth data source of the spacecraft, T j represents the average query interval delay of the telemetry data of the jth data source of the spacecraft, Δt1 represents the test execution definition response delay of the set test command, Δt2 represents the set telemetry data transmission definition delay, Δω represents the set reference collection time interval of the telemetry data, ΔT represents the set reference query interval delay of the telemetry data, α1 represents the correction factor corresponding to the set test execution response delay, α2 represents the correction factor corresponding to the set telemetry data transmission delay, α3 represents the correction factor corresponding to the set collection time interval of the telemetry data, α4 represents the correction factor corresponding to the set average query interval delay of the telemetry data, j represents the number of each data source, m represents the total number of data sources, k represents the number of each test command, s represents the total number of test commands, g represents the number of each test of the telemetry data transmission delay, and h represents the total number of tests of the telemetry data transmission delay.

[0078] It should be noted that the parameters such as the test execution response delay of each test command, the transmission delay of each telemetry data, the collection time interval of telemetry data, and the average query interval delay of telemetry data do not exist independently, but are interdependent and closely related. First, the response delay of the test command directly affects the timing of telemetry data acquisition. If the response time of the test command execution is long, it means that there will be a delay in the system receiving and processing telemetry data, which will increase the transmission delay of telemetry data. Especially in a complex test environment, test commands with large response delays may cause the timeliness of telemetry data transmission to decrease, affecting the real-time nature of the data. Secondly, there is also a close relationship between the collection time interval of telemetry data and the average query interval delay of telemetry data. The collection time interval of telemetry data determines the frequency of data collection, while the query interval delay of the data determines the timeliness of the data to be acquired and further processed. A long collection time interval may cause the system to be unable to respond to rapidly changing events in a timely manner, especially in the case of high-frequency data collection requirements. In contrast, a large query interval delay may cause the system to be unable to obtain real-time telemetry data in a timely manner, affecting the monitoring of the status of the equipment or spacecraft. Long transmission delays usually mean that telemetry data cannot be quickly fed back to the command and control system, which in turn affects the arrangement of collection intervals and query intervals. When the data transmission delay is large, the system may need to increase the collection interval to ensure that data is not lost during transmission, and may also need to adjust the query interval delay to adapt to the lag effect of data transmission. Conversely, shorter transmission delays can improve the real-time nature of the data stream and reduce the system's need to adjust the time interval.

[0079] It should be noted that the query interval delay refers to the difference between the actual query time and the expected query time during the continuous telemetry data query process. In order to accurately measure the query interval delay, a preset time reference is usually used, such as the clock inside the spacecraft or the universal time (UTC) synchronized with the ground station. The test execution response delay refers to the time delay between when the test command is sent and the spacecraft responds and starts to execute the test command. This delay is usually the time difference between the instruction being sent to the spacecraft to start executing the test command. Data transmission delay refers to the time delay between the ground control center sending data and the spacecraft receiving these instructions or data and starting to process them.

[0080] In a specific embodiment, the value range of the correction factor corresponding to the test execution response delay is generally between 0 and 1. When in use, the correction factor corresponding to the test execution response delay can be directly obtained from the database. The correspondence between the correction factor corresponding to the test execution response delay and the test execution response delay is determined by a pre-set mapping table. For example, a mapping table is constructed of the test execution response delay and the correction factor corresponding to the test execution response delay. By inputting the test execution response delay detected in real time into the mapping table, the corresponding correction factor can be quickly obtained, thereby helping to optimize the delay problem in the test execution process.

[0081] In a specific embodiment, the correction factor corresponding to the telemetry data transmission delay generally ranges from 0 to 1. When in use, the correction factor corresponding to the telemetry data transmission delay can be directly obtained from the database. The correspondence between the correction factor corresponding to the telemetry data transmission delay and the telemetry data transmission delay is determined by a pre-set mapping table. For example, a mapping table is constructed of the telemetry data transmission delay and the correction factor corresponding to the telemetry data transmission delay. By inputting the telemetry data transmission delay detected in real time into the mapping table, the corresponding correction factor can be quickly obtained, thereby helping to improve the delay effect during the data transmission process.

[0082] In a specific embodiment, the value range of the correction factor corresponding to the collection time interval of the telemetry data is generally between 0 and 1. When in use, the correction factor corresponding to the collection time interval of the telemetry data can be directly obtained from the database. The correspondence between the correction factor corresponding to the collection time interval of the telemetry data and the telemetry data collection time interval is determined by a pre-set mapping table. For example, a mapping table is constructed of the telemetry data collection time interval and the correction factor corresponding to the telemetry data collection time interval. By inputting the real-time detected telemetry data collection time interval into the mapping table, the corresponding correction factor can be quickly obtained, thereby helping to adjust the collection cycle and optimize the efficiency of data collection.

[0083] In a specific embodiment, the value range of the correction factor corresponding to the average query interval delay of the telemetry data is generally between 0 and 1. When in use, the correction factor corresponding to the average query interval delay of the telemetry data can be directly obtained from the database. The correspondence between the correction factor corresponding to the average query interval delay of the telemetry data and the average query interval delay of the telemetry data is determined by a pre-set mapping table. For example, a mapping table is constructed of the average query interval delay of the telemetry data and the correction factor corresponding to the average query interval delay of the telemetry data. By inputting the query delay of the telemetry data detected in real time into the mapping table, the corresponding correction factor can be quickly obtained, thereby helping to optimize the data query interval and reduce the query delay.

[0084] It should be noted that a method for executing dynamic tests of spacecraft based on telemetry data also includes a database, which is used to store the alignment requirement index threshold of the telemetry data of each data source of the spacecraft, the reference time point, the quality index threshold of the telemetry alignment data of each data source of the spacecraft, the reference duration of the telemetry control instructions of the spacecraft, the dynamic adjustment quality index threshold of the telemetry data, the definition of data transmission delay, the definition of data loss rate, the definition of the number of timeout instructions, the correction factor corresponding to the data transmission delay, the correction factor corresponding to the data loss rate, the correction factor corresponding to the number of timeout instructions, the data collection definition time difference, the collection time mean definition error, the data loss rate of the data source, the correction factor corresponding to the data collection time difference, the correction factor corresponding to the data collection mean time error, the correction factor corresponding to the data loss rate, the test execution definition response delay of the test command, the telemetry data transmission definition delay, the reference collection time interval of telemetry data, the reference query interval delay of telemetry data, the correction factor corresponding to the test execution response delay, the correction factor corresponding to the telemetry data transmission delay, the correction factor corresponding to the collection time interval of telemetry data and the correction factor corresponding to the average query interval delay of telemetry data.

[0085] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0086] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A method for executing spacecraft dynamic tests based on telemetry data, characterized in that: include: Collect telemetry data from various data sources of the spacecraft, test and analyze the telemetry data from various data sources of the spacecraft, obtain alignment results of the telemetry data from various data sources of the spacecraft, and align the telemetry data from various data sources of the spacecraft to obtain telemetry alignment data from various data sources of the spacecraft; Analyze the telemetry alignment data of each data source of the spacecraft to obtain the quality index of the telemetry alignment data of each data source of the spacecraft, and interpret the telemetry alignment data of each data source of the spacecraft according to the quality index of the telemetry alignment data of each data source of the spacecraft to obtain the interpretation result of the telemetry alignment data of each data source of the spacecraft; According to the interpretation results of the telemetry alignment data of each data source of the spacecraft, the collection of telemetry data is adjusted in combination with the average duration of the telemetry control instructions of the spacecraft, and the dynamic adjustment quality results of the telemetry data are obtained to adjust the number of retransmissions of the data packet.

2. The method for executing spacecraft dynamic test based on telemetry data according to claim 1, characterized in that: The telemetry data of each data source of the spacecraft includes the time point of sending each test command, the time point of starting to execute each test command, the time point of sending each telemetry data, the time point of receiving each telemetry data, the time interval of collecting telemetry data and the average query interval delay of telemetry data.

3. The method for executing spacecraft dynamic test based on telemetry data according to claim 2, characterized in that: The telemetry data from various data sources of the spacecraft are tested and analyzed, and the specific analysis process is as follows: Extract the sending time of each test command of each data source of the spacecraft and the starting time of each test command, perform difference processing to obtain the test execution response delay of each test command; Extract the time points of receiving telemetry data and sending telemetry data of each data source of the spacecraft, and perform difference processing to obtain the delay of each telemetry data transmission; The test execution response delay of each test command of each data source of the spacecraft, the transmission delay of each telemetry data, the collection time interval of telemetry data and the average query interval delay of telemetry data are extracted, and the alignment requirement index of the telemetry data of each data source of the spacecraft is obtained after processing. The alignment requirement index of the telemetry data of each data source of the spacecraft is used to evaluate the synchronization degree of telemetry data.

4. The method for executing spacecraft dynamic test based on telemetry data according to claim 2, characterized in that: The alignment results of the telemetry data from each data source of the spacecraft are obtained, and the specific analysis conditions are: The alignment requirement index of the telemetry data of each data source of the spacecraft is extracted, and compared with the alignment requirement index threshold of the telemetry data of each data source of the spacecraft stored in the database to obtain the alignment result of the telemetry data of each data source of the spacecraft, wherein the alignment result of the telemetry data of each data source of the spacecraft includes alignment required and alignment not required. If the alignment requirement index of the telemetry data of a certain data source of the spacecraft is higher than or equal to the alignment requirement index threshold of the telemetry data of the data source of the spacecraft, the alignment result of the telemetry data of the data source of the spacecraft is defined as alignment required, and the telemetry data of the data source of the spacecraft is aligned. If the alignment requirement index of the telemetry data of a certain data source of the spacecraft is lower than the alignment requirement index threshold of the telemetry data of the data source of the spacecraft, the alignment result of the telemetry data of the data source of the spacecraft is defined as alignment not required.

5. The method for executing spacecraft dynamic test based on telemetry data according to claim 4, characterized in that: The telemetry data of each data source of the spacecraft are aligned to obtain the telemetry alignment data of each data source of the spacecraft. The specific process is as follows: The telemetry data of each data source of the spacecraft are aligned according to the alignment result of the telemetry data of each data source of the spacecraft. If the alignment result of the telemetry data of a certain data source of the spacecraft needs to be aligned, the telemetry data of this data source of the spacecraft is aligned and marked as the telemetry alignment data of each data source of the spacecraft. If the alignment result of the telemetry data of a certain data source of the spacecraft does not need to be aligned, the telemetry data of this data source of the spacecraft is directly marked as the telemetry alignment data of each data source of the spacecraft, thereby obtaining the telemetry alignment data of each data source of the spacecraft.

6. The method for executing spacecraft dynamic test based on telemetry data according to claim 1, characterized in that: The telemetry alignment data of each spacecraft data source is analyzed to obtain the quality index of the telemetry alignment data of each spacecraft data source. The specific analysis process is as follows: Count the data collection time points in each data source of the spacecraft, extract the data collection time points in each data source of the spacecraft, extract the reference time points stored in the database, perform absolute value processing on the difference between the reference time points and the data collection time points in each data source of the spacecraft, and obtain the collection time difference of each data in each data source of the spacecraft; The mean error of the collection time of each data in each data source of the spacecraft is counted, and the data missing rate in each data source of the spacecraft is counted. The quality index of the telemetry alignment data of each data source of the spacecraft is obtained after processing. The quality index of the telemetry alignment data of each data source of the spacecraft is used to indicate the reliability of the alignment quality of the telemetry data.

7. The method for executing spacecraft dynamic test based on telemetry data according to claim 1, characterized in that: The telemetry alignment data of each data source of the spacecraft are interpreted and processed to obtain the interpretation result of the telemetry alignment data of each data source of the spacecraft. The specific process is as follows: According to the quality index of the telemetry alignment data of each spacecraft data source, it is compared with the quality index threshold of the telemetry alignment data of each spacecraft data source stored in the database to obtain the interpretation result of the telemetry alignment data of each spacecraft data source.

8. The method for executing spacecraft dynamic test based on telemetry data according to claim 6, characterized in that: The judgment results of the telemetry alignment data of each data source of the spacecraft include normal and abnormal. If the quality index of the telemetry alignment data of a data source of the spacecraft is higher than or equal to the quality index threshold of the telemetry alignment data of the data source of the spacecraft, the judgment result of the telemetry alignment data of the data source of the spacecraft is defined as normal. If the quality index of the telemetry alignment data of a data source of the spacecraft is lower than the quality index threshold of the telemetry alignment data of the data source of the spacecraft, the judgment result of the telemetry alignment data of the data source of the spacecraft is defined as abnormal.

9. The method for executing spacecraft dynamic test based on telemetry data according to claim 6, characterized in that: The telemetry data collection is adjusted in combination with the average duration of the telemetry control command of the spacecraft, and the dynamic adjustment quality result of the telemetry data is obtained, and the number of retransmissions of the data packet is adjusted. The specific process is as follows: If the judgment result of the telemetry alignment data of a certain data source of the spacecraft is normal, there is no need to collect and adjust the telemetry data. If the judgment result of the telemetry alignment data of a certain data source of the spacecraft is abnormal, the average duration of the telemetry control instructions of the spacecraft is obtained, and the reference duration of the telemetry control instructions of the spacecraft stored in the database is extracted, and the average duration of the telemetry control instructions of the spacecraft is compared with the reference duration of the telemetry control instructions of the spacecraft stored in the database. If the average duration of the telemetry control instructions of the spacecraft is higher than or equal to the reference duration of the telemetry control instructions of the spacecraft, the telemetry data of the data source of the spacecraft is re-collected and an alarm is triggered. If the average duration of the telemetry control instructions of the spacecraft is lower than the reference duration of the telemetry control instructions of the spacecraft, the frequency of sending the telemetry control instructions is reduced. Monitor the sending of telemetry control instructions, obtain dynamic adjustment data of telemetry control instructions, including telemetry data transmission delay, data loss rate, and number of timeout instructions, and obtain a dynamic adjustment quality index of telemetry data, which indicates the accuracy of the telemetry system in completing data transmission and control tasks during the dynamic adjustment process; According to the dynamic adjustment quality index of the telemetry data, it is compared with the dynamic adjustment quality index threshold of the telemetry data stored in the database. If the dynamic adjustment quality index of the telemetry data is higher than or equal to the dynamic adjustment quality index threshold of the telemetry data, the dynamic adjustment quality result of the telemetry data is marked as qualified; if the dynamic adjustment quality index of the telemetry data is lower than the dynamic adjustment quality index threshold of the telemetry data, the dynamic adjustment quality result of the telemetry data is marked as unqualified and the number of retransmissions of the data packet is reduced.

10. The method for executing spacecraft dynamic test based on telemetry data according to claim 3, characterized in that: The alignment requirement index of the telemetry data from each data source of the spacecraft, the specific analysis conditions are: In the formula, A j represents the alignment requirement index of the telemetry data of the jth data source of the spacecraft, t j→k represents the test execution response delay of the kth test command of the jth data source of the spacecraft, t j→g represents the g-th telemetry data transmission delay from the j-th data source of the spacecraft, ω j represents the time interval for collecting telemetry data from the jth data source of the spacecraft, T j represents the average query interval delay of the telemetry data of the jth data source of the spacecraft, Δt1 represents the test execution definition response delay of the set test command, Δt2 represents the set telemetry data transmission definition delay, Δω represents the set reference collection time interval of the telemetry data, ΔT represents the set reference query interval delay of the telemetry data, α1 represents the correction factor corresponding to the set test execution response delay, α2 represents the correction factor corresponding to the set telemetry data transmission delay, α3 represents the correction factor corresponding to the set collection time interval of the telemetry data, α4 represents the correction factor corresponding to the set average query interval delay of the telemetry data, j represents the number of each data source, m represents the total number of data sources, k represents the number of each test command, s represents the total number of test commands, g represents the number of each test of the telemetry data transmission delay, and h represents the total number of tests of the telemetry data transmission delay.

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