A method, system, storage medium, and electronic device for satellite power-on time statistics

Abstract

The present invention relates to the technical field of satellite test data statistics, and in particular to a method, system, storage medium and electronic device for satellite power-on time statistics. The method includes: when performing a power-on test on a satellite each time, storing characteristic telemetry parameters for characterizing the working states of each individual component of the satellite in a database; determining at least one target component from all the individual components according to user requirements, and obtaining the characteristic telemetry parameters of each target component from the database, and obtaining the power-on duration of each target component through a quantity statistics method. It can realize the automatic query and saving of the power-on duration of each individual component of the satellite, with high statistical efficiency. After obtaining the statistical results, it is convenient to control the ground test progress, and it is also convenient for users to calculate the average failure time of each target component, thereby determining the reliability status of the satellite.

Description

Background Art

[0002] As a product, a satellite has a bathtub curve characteristic in terms of the failure rate change during its life cycle. Before leaving the factory, the tests and experiments carried out during the formal model stage of the satellite are equivalent to the early life stage. Since on-orbit maintenance is not possible, satellite products generally require high reliability, that is, a long mean time between failures. The mean time between failures is a reliability index to measure a product (especially electrical products), and the unit is "hour".

[0003] In order to test the mean time between failures of a satellite, each satellite has to undergo a certain period of testing and experiments before leaving the factory. Currently, there are some qualitative standards in the industry, that is, by making the satellite reach a certain power-on time to further evaluate whether the satellite meets the factory requirements. For example, the cumulative power-on time of the entire satellite exceeds 1000 hours, etc. Thus, obtaining accurate cumulative power-on time of the entire satellite plays a key role in further evaluating the reliability status of the entire satellite subsequently.

[0004] Satellite comprehensive testing refers to testing the electrical functions and performances at each stage of satellite development, and verifying whether its performance indicators and functional parameters meet the design requirements. It is an important part in the process of satellite development. Satellite testing will accumulate a large amount of test data. In order to facilitate the analysis of test data, testers generally use database query software to obtain the required test data information. Currently, the database query software used in testing has realized the query function of database characteristic telemetry parameters, that is, by setting the characteristic telemetry parameters and time to be queried, the specific status of the corresponding telemetry within this time period can be obtained, and then the subsequent interpretation and analysis can be completed. However, most of such software rarely integrates the function of counting the power-on time of the entire satellite. The counting work of power-on time sometimes needs to be manually counted by testers. Manual counting is very difficult to be accurate and error-free. Moreover, the counting for each single-unit component takes a lot of time to complete, bringing a great burden to the testing work. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a satellite power-on time counting method, system, storage medium and electronic device in view of the deficiencies of the prior art.

[0006] The technical solution of a satellite power-on time counting method of the present invention is as follows:

[0007] When performing a power-on test on the satellite each time, store the characteristic telemetry parameters used to characterize the working states of the individual unit components of the satellite in the database;

[0008] Determine at least one target component from all single-component parts according to user requirements, obtain the characteristic telemetry parameters of each target component from the database, and obtain the power-on duration of each target component through a quantity statistics method.

[0009] The beneficial effects of a satellite power-on time statistics method of the present invention are as follows:

[0010] It can realize the automatic query and saving of the power-on duration of each single-component part of the satellite, with high statistical efficiency. After obtaining the statistical results, it is convenient to control the ground test progress and for the user to calculate the average failure time of each target component, thereby determining the reliability status of the satellite.

[0011] On the basis of the above solution, a satellite power-on time statistics method of the present invention can also be improved as follows.

[0012] Further, the obtaining of the power-on duration of each target component through the quantity statistics method includes:

[0013] When the characteristic telemetry parameter of any target component is an analog quantity, in combination with the sampling frequency and the normal threshold range corresponding to the characteristic telemetry parameter of this target component, obtain the power-on duration of this target component, where the sampling frequency refers to: the telemetry downlink frequency of the characteristic telemetry parameter of this target component.

[0014] Further, the obtaining of the power-on duration of each target component through the quantity statistics method further includes:

[0015] When the characteristic telemetry parameter of any target component is a status digital quantity, in combination with the sampling frequency, obtain the power-on duration of this target component.

[0016] Further, it further includes:

[0017] Send the power-on duration of each target component to the terminal of the user.

[0018] The technical solution of a satellite power-on time statistics system of the present invention is as follows:

[0019] It includes a storage module and a query module;

[0020] The storage module is used for: when performing a power-on test on the satellite each time, storing the characteristic telemetry parameters for characterizing the working states of the various single-component parts of the satellite in the database;

[0021] The query module is used for: determining at least one target component from all single-component parts according to user requirements, obtaining the characteristic telemetry parameters of each target component from the database, and obtaining the power-on duration of each target component through a quantity statistics method.

[0022] The beneficial effects of a satellite power-on time statistical system of the present invention are as follows:

[0023] It can automatically query and save the power-on duration of each single-component of the satellite, with high statistical efficiency. After obtaining the statistical results, it is convenient to control the ground test progress, and it is also convenient for users to calculate the average failure time of each target component, thereby determining the reliability status of the satellite.

[0024] Based on the above solution, a satellite power-on time statistical system of the present invention can also be improved as follows.

[0025] Further, the query module is specifically used for:

[0026] When the characteristic telemetry parameter of any target component is an analog quantity, combining the sampling frequency and the normal threshold range corresponding to the characteristic telemetry parameter of the target component to obtain the power-on duration of the target component, where the sampling frequency refers to: the telemetry downlink frequency of the characteristic telemetry parameter of the target component.

[0027] Further, the query module is also specifically used for:

[0028] When the characteristic telemetry parameter of any target component is a status digital quantity, combining the sampling frequency to obtain the power-on duration of the target component.

[0029] Further, it further includes a sending module, and the sending module is used to send the power-on duration of each target component to the intelligent terminal of the user.

[0030] A storage medium of the present invention stores instructions, and when a computer reads the instructions, the computer executes a satellite power-on time statistical method described in any one of the above.

[0031] An electronic device of the present invention includes a processor and the above storage medium, and the processor executes the instructions in the storage medium. Description of the Drawings

[0032] Figure 1 It is a flowchart of a satellite power-on time statistical method according to an embodiment of the present invention;

[0033] Figure 2 It is a schematic diagram of a database configuration interface;

[0034] Figure 3 It is a schematic diagram of a parameter configuration interface;

[0035] Figure 4 It is a schematic diagram of an output interface;

[0036] Figure 5Schematic diagram of the structure of a satellite power-on time statistics system according to an embodiment of the present invention. Detailed implementation manners

[0037] As Figure 1 shown, a satellite power-on time statistics method according to an embodiment of the present invention includes the following steps:

[0038] S1. When performing a power-on test on the satellite each time, store the characteristic telemetry parameters representing the working states of each single-unit component of the satellite in a database;

[0039] Among them, it is necessary to pre-establish a satellite test database, create a data table for storing satellite telemetry frames and telemetry parameters. During the power-on process of the whole satellite, the satellite TT&C system downloads the telemetry data to the ground test system through the TT&C link, and the ground test system completes the parsing, display, storage, and query of the telemetry.

[0040] S2. Determine at least one target component from all single-unit components according to user requirements, and obtain the characteristic telemetry parameters of each target component from the database, and obtain the power-on duration of each target component through a quantity statistics method.

[0041] For example, the single-unit components can be flywheels, three-axis fiber optic gyroscopes, and magnetometers. Determine at least one target component from all single-unit components according to user requirements. For example, determine the flywheel as the target component, and obtain the characteristic telemetry parameters of the flywheel from the database. The characteristic telemetry parameter is a digital quantity, and the state after power-on is "1" and the state after power-off is "0". By counting the number of telemetry data with the state of the characteristic telemetry parameter of the flywheel power-on state being "1" and combining the sampling frequency of the telemetry, the power-on duration of the flywheel is finally obtained.

[0042] For example, when the power-on duration of the flywheel exceeds the predetermined test power-on duration and no faults occur to the flywheel during the test, it is considered that the performance of the flywheel is reliable. By analogy, the power-on durations of other single-unit components of the satellite can be calculated. When they all exceed the corresponding standard test power-on durations and no faults occur, it can be considered that the performances of other single-unit components of the satellite are reliable, and further it shows that the performance of the satellite is reliable.

[0043] A satellite power-on time statistics method of the present application can realize the automatic query and saving of the power-on duration of each single-unit component of the satellite, with high statistical efficiency. After obtaining the statistical results, it is convenient for users to calculate the mean time between failures of each target component, and further determine the reliability of the satellite.

[0044] Optionally, in the above technical solution, in S2, obtaining the power-on duration of each target component through a quantity statistics method includes:

[0045] S20. When the characteristic telemetry parameter of any target component is an analog quantity, combine the sampling frequency and the normal threshold range corresponding to the characteristic telemetry parameter of the target component to obtain the power-on duration of the target component, where the sampling frequency refers to the telemetry download frequency of the characteristic telemetry parameter of the target component. Specifically:

[0046] For example, when the target component is a power controller, the characteristic telemetry parameter characterizing the working state of the power controller is the voltage of the NS001 bus. The voltage of the NS001 bus is an analog quantity, the sampling frequency is once per second, and the normal threshold range of the voltage of the NS001 bus corresponding to the powered-on power controller is 21V - 29V. From the database, count the number of valid data of the voltage of the NS001 bus within 21V - 29V. For example, if the number of valid data meeting the conditions is 100, then P = A * SUM(valid data quantity), where P is the power-on duration, A is the sampling frequency, and SUM(valid data quantity) is the total number of valid data meeting the threshold obtained through data query, that is, P = 1 * 100 = 100 seconds, which means the power-on duration of the power controller is 100 seconds.

[0047] Optionally, in the above technical solution, in S2, when obtaining the power-on duration of each target component through the quantity statistics method, it further includes:

[0048] S21. When the characteristic telemetry parameter of any target component is a status digital quantity, combine the sampling frequency to obtain the power-on duration of the target component. Specifically:

[0049] For example, when the target component is Flywheel X, the telemetry name that can be used as a characteristic telemetry parameter for counting the power-on time of Flywheel X is the flywheel power-on status. The code of this characteristic telemetry parameter is ZB062, and ZB062 is a status digital quantity, specifically including the power-on state and the non-power-on state. The sampling frequency is once per second. Count the number of times the power-on status of ZB062 for Flywheel X is "1" from the database. For example, it is 100 times, and the power-on duration of Flywheel X of ZB062 is obtained as 100 seconds.

[0050] The quantity statistics method in the present invention can also be explained by the following formula:

[0051]

[0052] Where A is the sampling frequency, A ∈ (1, 2, 4, 8, 16, 32), i is the data storage time, each piece of valid data corresponds to a data storage time, X i is the valid data stored in the database. If it is a digital quantity, Xi ∈ (0, 1); if it is an analog quantity, Xi ∈ (lower limit of the valid range, upper limit of the valid range), that is, the upper and lower limits of the normal threshold range;

[0053] Use the database query statement to obtain all valid data where the characteristic telemetry parameters meet the conditions, and sum up all the valid data on this basis.

[0054] Among them, it should be noted that the telemetry parameters used to characterize the working status of each single-component of the satellite have been determined during the satellite design. After the satellite is powered on, the satellite on-board subsystem completes telemetry acquisition and framing, and the TT&C subsystem transmits it to the ground via the TT&C link. The ground test system obtains each frame of telemetry data transmitted by the satellite TT&C link in real time, and after completing data parsing, sends it to the test database to complete the storage of test data. The telemetry parameter code can be understood as an alias of the telemetry parameter, and this alias serves as the unique identifier of a certain telemetry data on this satellite. The query software can obtain the actual telemetry data information reflecting the component health status through the telemetry parameter code.

[0055] Optionally, in the above technical solution, the single-component is a flywheel, a three-axis fiber optic gyroscope or a magnetometer, and there are other components of the satellite, which are not listed one by one here.

[0056] Optionally, in the above technical solution, it further includes:

[0057] S3. Send the power-on duration of each target component to the user's terminal and store it in the local in the form of a file at the same time for the user to view.

[0058] Since different satellites have their own test databases, when testing different satellites, the parameters can be modified in the database configuration interface, and the name of the accessed database can be modified, so as to realize the access to test databases with different names. It can also be switched between different test databases in the form of a drop-down menu, as Figure 2 shown.

[0059] A characteristic telemetry parameter configuration interface can also be set, as Figure 3 shown. Through the characteristic telemetry parameter configuration interface, the characteristic telemetry parameter configuration of any single-component can be realized. In the configuration page, the Chinese description of the corresponding characteristic telemetry parameter is on the left, and the telemetry parameter configuration area is on the right. This area can complete the configuration of the telemetry parameter code, and the telemetry parameter code corresponding to each single-component can be filled in.

[0060] An output interface can also be written to display the power-on duration of each single-component during each test to identify the name of the single-component whose power-on time to be checked is obtained, as Figure 4 shown. In addition, different functions can be set according to the actual situation, which will not be elaborated here.

[0061] A method for counting the satellite power-on time in this application, as well as the above-mentioned database configuration interface, parameter configuration interface, and output interface, can be specifically implemented through programming in Visual Basic for Applications (abbreviated as VBA). Specifically:

[0062] Visual Basic for Applications (abbreviated as VBA) is a new generation of standard macro language, which is developed based on Visual Basic for Windows. It is different from traditional macro languages. Traditional macro languages do not have the characteristics of high-level languages and do not have the concepts and methods of object-oriented programming. However, VBA provides an object-oriented programming method and a relatively complete programming language. VBA is easy to learn and master. The macro recorder can be used to record various operations of users and convert them into VBA program code. In this way, users can easily convert their daily work into VBA program code to automate the work.

[0063] At present, some test software has implemented the function of counting the power-on time. However, in terms of use, there are still problems such as cumbersome configuration steps and easy errors, resulting in the software being unable to execute or the query results being inaccurate.

[0064] In addition, due to the frequent change of characteristic telemetry parameters, the number of databases will increase. This results in the need to connect multiple databases to query data from different periods. If you want to query the telemetry data of multiple databases, you need to restart the database query software and select the corresponding database for query, or you need to open multiple database query software in parallel. The usage process is relatively cumbersome. And a method for counting the satellite power-on time in this application has the following advantages:

[0065] 1) Greatly reduce the time cost of obtaining the power-on time of the entire satellite and each component. Click the button, and it only takes a few seconds to obtain the power-on time of the entire satellite and each component, which is convenient and fast.

[0066] 2) Simple operation, reducing the difficulty of software use for testers. Only by completing the configuration of the database name and the corresponding characteristic telemetry parameters can the application of the software be realized.

[0067] 3) Strong versatility and simple configuration. To obtain the power-on time of a single component, only the characteristic telemetry parameter code corresponding to the single component needs to be configured, without other configurations.

[0068] 4) It can meet the power-on time statistics under different telemetry downlink rates. Due to different satellite telemetry scheduling mechanisms, the telemetry of each data packet is downlinked at different cycle frequencies. Some data packets are transmitted once per second, while some are transmitted once every 16 seconds or 32 seconds. This method can complete the power-on time statistics of telemetry with different cycle frequencies.

[0069] 5) By configuring the list of database names, it is convenient to switch between different databases to complete the subsequent statistics of the power-on time of different databases, without restarting the software or starting multiple software applications.

[0070] 6) The software development is based on the well-known EXCEL. Compared with other software tools, on the basis of achieving the same functions, it is more in line with everyone's usage habits, and at the same time can complete subsequent data analysis with the help of the data analysis function of EXCEL.

[0071] In the above embodiments, although the steps are numbered S1, S2, etc., they are only specific embodiments given in this application. Those skilled in the art can adjust the execution order of S1, S2, etc. according to the actual situation, and this is also within the protection scope of the present invention. It can be understood that in some embodiments, it may include some or all of the above embodiments.

[0072] Such as Figure 5 As shown, a satellite power-on time statistics system 200 according to an embodiment of the present invention includes a storage module 210 and a query module 220;

[0073] The storage module 210 is used for: when performing a power-on test on the satellite each time, storing the characteristic telemetry parameters representing the working states of each single machine component of the satellite in the database;

[0074] The query module 220 is used for: determining at least one target component from all single machine components according to the user's needs, obtaining the characteristic telemetry parameters of each target component from the database, and obtaining the power-on duration of each target component through a quantity statistics method.

[0075] It can realize the automatic query and saving of the power-on duration of each single machine component of the satellite, with high statistical efficiency. After obtaining the statistical results, it is convenient for users to calculate the average failure time of each target component, and then determine the reliability of the satellite.

[0076] Optionally, in the above technical solution, the query module 220 is specifically used for:

[0077] When the characteristic telemetry parameter of any target component is an analog quantity, combining the sampling frequency and the normal threshold range corresponding to the characteristic telemetry parameter of the target component to obtain the power-on duration of the target component, where the sampling frequency refers to: the telemetry downlink frequency of the characteristic telemetry parameter of the target component.

[0078] Optionally, in the above technical solution, the query module 220 is further specifically used for:

[0079] When the characteristic telemetry parameter of any target component is a status digital quantity, combining the sampling frequency to obtain the power-on duration of the target component.

[0080] Optionally, in the above technical solution, a sending module is further included, and the sending module is configured to send the power-on duration of each target component to the user's intelligent terminal.

[0081] For the parameters and the steps for each unit module in the satellite power-on time statistics system 200 of the present invention to implement corresponding functions, reference may be made to the parameters and steps in the embodiments of the satellite power-on time statistics method in the foregoing text, which will not be elaborated herein.

[0082] A storage medium according to an embodiment of the present invention stores instructions, and when a computer reads the instructions, the computer is caused to execute the satellite power-on time statistics method according to any one of the above.

[0083] An electronic device according to an embodiment of the present invention includes a processor and the above storage medium, and the processor executes the instructions in the storage medium. The electronic device may be a computer, a mobile phone, or the like.

[0084] Those skilled in the art of the present technology know that the present invention can be implemented as a system, a method, or a computer program product.

[0085] Therefore, the present disclosure can be specifically implemented in the following forms, that is: it can be all hardware, can also be all software (including firmware, resident software, microcode, etc.), and can also be a combination of hardware and software. Generally referred to as "circuit", "module" or "system" in this article. In addition, in some embodiments, the present invention can also be implemented in the form of a computer program product in one or more computer-readable media, and the computer-readable media contains computer-readable program code.

[0086] Any combination of one or more computer-readable media can be adopted. The computer-readable media can be a computer-readable signal medium or a computer-readable storage medium. The computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or component, or any combination of the above. More specific examples (non-exhaustive list) of the computer-readable storage medium include: an electrical connection having one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In this document, the computer-readable storage medium can be any tangible medium that contains or stores a program, and the program can be used by or in combination with an instruction execution system, device, or component.

[0087] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A method for satellite power-on time statistics, characterized in that, Including: When performing a power-on test on the satellite each time, storing the characteristic telemetry parameters used to characterize the working states of the individual components of the satellite in a database; Determining at least one target component from all the individual components according to user requirements, obtaining the characteristic telemetry parameters of each target component from the database, and obtaining the power-on duration of each target component through a quantity statistics method; The obtaining the power-on duration of each target component through the quantity statistics method includes: When the characteristic telemetry parameter of any target component is an analog quantity, combining the sampling frequency and the normal threshold range corresponding to the characteristic telemetry parameter of this target component to obtain the power-on duration of this target component, where the sampling frequency refers to the telemetry downlink frequency of the characteristic telemetry parameter of this target component; Wherein, when the target component is a power controller, the characteristic telemetry parameter characterizing the working state of the power controller is the voltage of the NS001 bus. The voltage of the NS001 bus is an analog quantity, the sampling frequency is once per second, and the normal threshold range of the voltage of the NS001 bus corresponding to the powered-on power controller is 21V - 29V. From the database, count the effective data volume of the voltage of the NS001 bus within 21V - 29V. Then there is P = A * SUM, where P is the power-on duration, A is the sampling frequency, and SUM is all the effective data volume that meets the threshold obtained through data query; The obtaining the power-on duration of each target component through the quantity statistics method further includes: When the characteristic telemetry parameter of any target component is a status digital quantity, combining the sampling frequency to obtain the power-on duration of this target component.

2. The method for satellite power-on time statistics according to claim 1, characterized in that, Also including: Sending the power-on duration of each target component to the user's terminal.

3. A satellite power-on time statistics system, characterized in that, Including a storage module and a query module; The storage module is used for: when performing a power-on test on the satellite each time, storing the characteristic telemetry parameters used to characterize the working states of the individual components of the satellite in a database; The query module is used for: determining at least one target component from all the individual components according to user requirements, obtaining the characteristic telemetry parameters of each target component from the database, and obtaining the power-on duration of each target component through a quantity statistics method; The query module is specifically used for: When the characteristic telemetry parameter of any target component is an analog quantity, combining the sampling frequency and the normal threshold range corresponding to this characteristic telemetry parameter of this target component to obtain the power-on duration of this target component, where the sampling frequency refers to the telemetry downlink frequency of the characteristic telemetry parameter of this target component; Wherein, when the target component is a power controller, the characteristic telemetry parameter characterizing the working state of the power controller is the voltage of the NS001 bus. The voltage of the NS001 bus is an analog quantity, the sampling frequency is once per second, and the normal threshold range of the voltage of the NS001 bus corresponding to the powered-on power controller is 21V - 29V. From the database, count the effective data volume of the voltage of the NS001 bus within 21V - 29V. Then there is P = A * SUM, where P is the power-on duration, A is the sampling frequency, and SUM is all the effective data volume that meets the threshold obtained through data query; The query module is further specifically configured to: When the characteristic telemetry parameter of any target component is a status digital quantity, the power-on duration of the target component is obtained in combination with the sampling frequency.

4. The satellite power-on time statistics system according to claim 3, characterized in that, It further includes a sending module, and the sending module is configured to send the power-on duration of each target component to the terminal of the user.

5. A storage medium, characterized in that, Instructions are stored in the storage medium, and when the computer reads the instructions, the computer executes a satellite power-on time statistics method according to any one of claims 1 to 2.

6. An electronic device, characterized in that, It includes a processor and the storage medium according to claim 5, and the processor executes the instructions in the storage medium.

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