Injection data automatic comparison method and device

Abstract

The present application provides an automatic comparison method and device for injection data, the method comprising: constructing a first telemetry parameter according to the format definition of the injection data; performing inverse analysis on the injection data sent to the spacecraft to obtain an inverse analysis result and retrieve the corresponding first telemetry parameter; generating a dynamic criterion according to the inverse analysis result and the first telemetry parameter, and obtaining a comparison result according to the dynamic criterion and a second telemetry parameter fed back by the spacecraft according to the injection data. The comparison efficiency of whether the injection data is correctly executed is greatly improved, and the workload of manual comparison and the risk of misoperation can be effectively reduced.

Description

Technical Field

[0001] The present application relates to the field of communication technology, and more particularly to a method and device for automatically comparing injected data. Background Art

[0002] With the continuous development of space exploration missions, the number and types of spacecraft are gradually increasing. The control data structures and processing requirements of different spacecraft are also quite different. Among them, injection data, as an important instruction format for spacecraft uplink control, is directly used in key processes such as spacecraft flight program injection, platform maintenance, orbit control and attitude control.

[0003] In order to accurately control the spacecraft, it is necessary to timely understand the execution status of the injected data. However, the type format of spacecraft injection data is complex, and the parameter types are diverse. At present, the ground remote control software mainly judges whether the injected data is correctly received by the spacecraft through the availability of the injected data and the correctness of the CRC check. However, whether it is correctly executed still needs to be monitored by real-time downlink telemetry and manually judged. This manual execution judgment method of injection data requires a lot of manpower and is very prone to errors. Summary of the invention

[0004] The purpose of this application is to provide a method and device for automatic comparison of injected data, so as to realize that the ground remote control software automatically receives the telemetry parameter status on the device and then performs intelligent comparison with the injected data, thereby reducing the workload of manual comparison and reducing the risk of misoperation.

[0005] To achieve the above-mentioned purpose, the present application provides an automatic comparison method for injected data, which comprises: constructing a first telemetry parameter according to a format definition of the injected data; inversely solving the injected data sent to the spacecraft to obtain an inverse solution result and retrieving the corresponding first telemetry parameter; generating a dynamic criterion according to the inverse solution result and the first telemetry parameter, and obtaining a comparison result according to the dynamic criterion and a second telemetry parameter fed back by the spacecraft according to the injected data.

[0006] In the above-mentioned automatic comparison method of injected data, optionally, constructing the first telemetry parameter according to the format definition of the injected data also includes: generating a unique identification number according to the format definition of the injected data, and constructing the corresponding first telemetry parameter according to the injected data; and generating a telemetry parameter configuration library according to the correspondence between the first telemetry parameter and the identification number.

[0007] In the above-mentioned automatic comparison method of injected data, optionally, inversely solving the injected data sent to the spacecraft to obtain an inverse solution result and retrieving the corresponding first telemetry parameter includes: inversely solving the injected data sent to the spacecraft to obtain an inverse solution result and a corresponding identification number; and retrieving the corresponding first telemetry parameter in the telemetry parameter configuration library through the identification number.

[0008] In the above-mentioned automatic comparison method of injected data, optionally, obtaining a comparison result based on the dynamic criterion and the analysis of the second telemetry parameters fed back by the spacecraft according to the injected data includes: acquiring multiple groups of the second telemetry parameters continuously collected within a preset period; comparing the multiple groups of the second telemetry parameters with the dynamic criterion respectively to obtain multiple comparison results; and obtaining a comparison result based on the multiple comparison results.

[0009] The present application also provides an automatic comparison device for injected data, the device comprising a construction module, an inverse solution module and a comparison module; the construction module is used to construct a first telemetry parameter according to the format definition of the injected data; the inverse solution module is used to inversely solve the injected data sent to the spacecraft to obtain an inverse solution result and retrieve the corresponding first telemetry parameter; the comparison module is used to generate a dynamic criterion according to the inverse solution result and the first telemetry parameter, and obtain a comparison result according to the dynamic criterion and the second telemetry parameter feedback from the spacecraft according to the injected data.

[0010] In the above-mentioned automatic comparison device for injected data, optionally, the construction module further includes an identification generation unit and an association unit; the identification generation unit is used to generate a unique identification number according to the format definition of the injected data, and to construct a corresponding first telemetry parameter according to the injected data; the association unit is used to generate a telemetry parameter configuration library according to the correspondence between the first telemetry parameter and the identification number.

[0011] In the above-mentioned automatic comparison device for injected data, optionally, the inverse solution module includes an analysis unit and a query unit; the analysis unit is used to inversely solve the injected data sent to the spacecraft to obtain an inverse solution result and a corresponding identification number; the query unit is used to retrieve the corresponding first telemetry parameter in the telemetry parameter configuration library through the identification number.

[0012] In the above-mentioned automatic comparison device for injection data, optionally, the comparison module includes an acquisition unit, a comparison unit and an analysis unit; the acquisition unit is used to obtain multiple groups of the second telemetry parameters continuously collected within a preset period; the comparison unit is used to compare the multiple groups of the second telemetry parameters with the dynamic criterion respectively to obtain multiple comparison results; the analysis unit is used to obtain a comparison result based on the multiple comparison results.

[0013] The present application also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the above method when executing the computer program.

[0014] The present application also provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program for executing the above method.

[0015] The present application also provides a computer program product, comprising a computer program / instruction, which implements the steps of the above method when executed by a processor.

[0016] The beneficial technical effect of the present application is that it greatly improves the efficiency of comparing and judging whether the injected data is executed correctly, and can effectively reduce the workload of manual comparison and reduce the risk of misoperation. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings described herein are used to provide a further understanding of the present application, constitute a part of the present application, and do not constitute a limitation of the present application. In the drawings:

[0018] Figure 1 A schematic diagram of a flow chart of an automatic comparison method of injected data provided in an embodiment of the present application;

[0019] Figure 2 A schematic diagram of a construction process of a first telemetry parameter provided in an embodiment of the present application;

[0020] Figure 3 A schematic diagram of the injection data reverse analysis process provided by an embodiment of the present application;

[0021] Figure 4 A schematic diagram of a comparison result acquisition process provided in an embodiment of the present application;

[0022] Figure 5 A logical diagram of an automatic comparison method for injection data provided by an embodiment of the present application;

[0023] Figure 6 A schematic diagram of the structure of an automatic injection data comparison device provided in one embodiment of the present application;

[0024] Figure 7 A schematic diagram of the structure of an electronic device provided in one embodiment of the present application. DETAILED DESCRIPTION

[0025] The following will describe the implementation methods of the present application in detail in conjunction with the accompanying drawings and embodiments, so that the implementation process of how the present application applies technical means to solve technical problems and achieve technical effects can be fully understood and implemented accordingly. It should be noted that as long as there is no conflict, the various embodiments in the present application and the various features in the embodiments can be combined with each other, and the technical solutions formed are all within the protection scope of the present application.

[0026] In addition, the steps shown in the flowcharts of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowcharts, in some cases, the steps shown or described can be performed in an order different from that shown here.

[0027] Please refer to Figure 1 As shown, the injection data automatic comparison method provided in the present application comprises:

[0028] S101 constructs a first telemetry parameter according to the format definition of the injected data;

[0029] S102 performs inverse analysis on the injected data sent to the spacecraft to obtain an inverse analysis result and retrieve the corresponding first telemetry parameter;

[0030] S103 generates a dynamic criterion according to the inverse solution result and the first telemetry parameter, and obtains a comparison result according to the dynamic criterion and a second telemetry parameter fed back by the spacecraft according to the injection data.

[0031] In this way, the present application can confirm whether the injected data is correctly executed by comparing whether the telemetry parameters at both ends are consistent, which can reduce the time waste caused by manual comparison work and reduce unnecessary risks caused by misoperation. Among them, the specific implementation method of reverse decoding the injected data to determine the reverse decoding result will be detailed in the subsequent embodiments, and will not be described one by one here.

[0032] In an embodiment of the present application, please refer to Figure 2 As shown, constructing the first telemetry parameter according to the format definition of the injected data may also include:

[0033] S201 generates a unique identification number according to the format definition of the injected data, and constructs a corresponding first telemetry parameter according to the injected data;

[0034] S202 generates a telemetry parameter configuration library according to the correspondence between the first telemetry parameter and the identification number.

[0035] Specifically, in this embodiment, corresponding identification numbers can be generated based on the format definition of the injected data, and then the corresponding first telemetry parameters can be determined based on the identification numbers, and the corresponding relationship between the two can be stored to build a telemetry parameter configuration library. Among them, the link of determining the first telemetry parameter according to the identification number can be manually specified by the staff, or generated by other existing rules and algorithms, and this application does not make further limitations on this.

[0036] Please refer to Figure 3 As shown, based on the telemetry parameter configuration library constructed in the above-mentioned embodiment, in one embodiment of the present application, the injection data sent to the spacecraft is inversely solved to obtain the inverse solution result and the corresponding first telemetry parameter is retrieved, which includes:

[0037] S301 reversely decodes the injected data sent to the spacecraft to obtain a reversed decoding result and a corresponding identification number;

[0038] S302 retrieves the corresponding first telemetry parameter from the telemetry parameter configuration library through the identification number.

[0039] In actual work, a corresponding unique identification number can be defined for each format of the injected data, and a telemetry parameter configuration library can be established. For each identification number, the corresponding telemetry parameters can be bound. For example, the injection data format of the start and stop control function of the spacecraft fan is defined as the identification number SR01, which contains two injection parameters, the fan start control temperature SR01-1 and the fan stop control temperature SR01-2. The telemetry parameters corresponding to the identification number SR01, the fan start control temperature value CR001 and the fan stop control temperature CR002, are bound in the telemetry parameter configuration library.

[0040] In the above step S102, the specific process of inversely solving the injected data sent to the spacecraft to obtain the inverse solution result is as follows: after the injected data is sent to the spacecraft, the injected data is inversely solved to obtain the corresponding identification number and the injected data inverse solution result. For example, after the spacecraft fan start control and stop control temperature injection data is annotated, the data is inversely solved to obtain the identification number of the injected data annotated as SR01, and the values ​​of the injected parameters fan start control temperature SR01-1 and fan stop control temperature SR01-2 of the injected data inverse solution result.

[0041] Thereafter, generating a dynamic criterion according to the inverse solution result and the first telemetry parameter in step S103 may include: searching for the corresponding telemetry parameter in the telemetry parameter configuration library according to the unique identification number obtained by inverse solution of the injected data, and generating a dynamic criterion for the injected data in combination with the inverse solution result of the injected data. For example, the identification number SR01 obtained after inverse solution of the injected data of the fan start-up and stop-control function of the spacecraft, the corresponding telemetry parameters fan start-up control temperature value CR001 and fan stop-control temperature CR002 are found in the telemetry parameter configuration library, and the dynamic criterion is generated by combining the values ​​of the injected parameters fan start-up control temperature SR01-1 and fan stop-control temperature SR01-2 in combination with the inverse solution result of the injected data, and the transmitted telemetry parameter fan start-up control temperature value CR001 is equal to the value of the inverse solution result SR01-1 and the fan stop-control temperature CR002 is equal to the value of the inverse solution result SR01-2.

[0042] Please refer to Figure 4 As shown, in one embodiment of the present application, obtaining a comparison result according to the dynamic criterion and the second telemetry parameter analysis of the spacecraft according to the feedback of the injection data may include:

[0043] S401 obtains multiple groups of the second telemetry parameters continuously collected within a preset period;

[0044] S402: compare the plurality of groups of the second telemetry parameters with the dynamic criterion respectively to obtain a plurality of comparison results; and obtain a comparison result according to the plurality of comparison results.

[0045] Specifically, in actual work, according to the dynamic criterion of the injected data, the corresponding telemetry parameters transmitted in real time after the injected data is sent are received, and the comparison result is obtained by using the three-judgment-two method within a fixed comparison time. For example, after injecting the temperature injection data of the start-stop control of the spacecraft fan, according to the generated dynamic criterion, the comparison result is obtained by using the three-judgment-two method within a fixed comparison time according to the transmitted telemetry parameter value. Among them, the three-judgment-two method is explained as follows: three frames of telemetry data are continuously taken within a fixed comparison time. If two frames of telemetry data meet the design binding criterion, the comparison result is obtained.

[0046] To more clearly understand the overall method logic of the above embodiments provided by this application, please refer to Figure 5 As shown, the above process is generally described.

[0047] First, the corresponding identification number and telemetry parameters need to be generated and saved according to the injected data (not shown);

[0048] Afterwards, after confirming the injected data, an identification number can be obtained according to the injected data analysis, and an injected data back-calculation result can be obtained through inverse identification; the identification number is used to retrieve the first telemetry parameter in the telemetry parameter configuration library;

[0049] Based on the injection data back-calculation result and the first telemetry parameter, the injection data dynamic criterion can be determined. The injection data comparison result can be obtained by comparing the injection data dynamic criterion with the telemetry result transmitted by the spacecraft after the injection data is executed.

[0050] Please refer to Figure 6 As shown, the present application also provides an automatic comparison device for injected data, the device comprising a construction module, an inverse solution module and a comparison module; the construction module is used to construct a first telemetry parameter according to the format definition of the injected data; the inverse solution module is used to inversely solve the injected data sent to the spacecraft to obtain an inverse solution result and retrieve the corresponding first telemetry parameter; the comparison module is used to generate a dynamic criterion according to the inverse solution result and the first telemetry parameter, and obtain a comparison result according to the dynamic criterion and the second telemetry parameter feedback from the spacecraft according to the injected data.

[0051] In the above-mentioned automatic comparison device for injection data, the construction module further includes an identification generation unit and an association unit; the identification generation unit is used to generate a unique identification number according to the format definition of the injection data, and to construct the corresponding first telemetry parameter according to the injection data; the association unit is used to generate a telemetry parameter configuration library according to the correspondence between the first telemetry parameter and the identification number. The inverse solution module includes a parsing unit and a query unit; the parsing unit is used to perform inverse solution on the injection data sent to the spacecraft to obtain an inverse solution result and a corresponding identification number; the query unit is used to retrieve the corresponding first telemetry parameter from the telemetry parameter configuration library through the identification number. The comparison module includes a collection unit, a comparison unit and an analysis unit; the collection unit is used to obtain multiple groups of the second telemetry parameters continuously collected within a preset period; the comparison unit is used to compare multiple groups of the second telemetry parameters with the dynamic criterion respectively to obtain multiple comparison results; the analysis unit is used to obtain a comparison result based on multiple comparison results.

[0052] The beneficial technical effect of the present application is that it greatly improves the efficiency of comparing and judging whether the injected data is executed correctly, and can effectively reduce the workload of manual comparison and reduce the risk of misoperation.

[0053] The present application also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the above method when executing the computer program.

[0054] The present application also provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program for executing the above method.

[0055] The present application also provides a computer program product, comprising a computer program / instruction, which implements the steps of the above method when executed by a processor.

[0056] like Figure 7 As shown, the electronic device 600 may further include: a communication module 110, an input unit 120, an audio processing unit 130, a display 160, and a power supply 170. It is worth noting that the electronic device 600 does not necessarily have to include Figure 7 In addition, the electronic device 600 may also include Figure 7 For components not shown, reference may be made to the prior art.

[0057] like Figure 7 As shown, the central processor 100 is sometimes also referred to as a controller or an operation control, and may include a microprocessor or other processor devices and / or logic devices. The central processor 100 receives inputs and controls the operations of various components of the electronic device 600.

[0058] The memory 140 may be, for example, one or more of a cache, a flash memory, a hard drive, a removable medium, a volatile memory, a non-volatile memory or other suitable devices. The above-mentioned information related to the failure may be stored, and a program for executing the relevant information may also be stored. The CPU 100 may execute the program stored in the memory 140 to implement information storage or processing.

[0059] The input unit 120 provides input to the CPU 100. The input unit 120 is, for example, a key or a touch input device. The power supply 170 is used to provide power to the electronic device 600. The display 160 is used to display display objects such as images and text. The display may be, for example, an LCD display, but is not limited thereto.

[0060] The memory 140 may be a solid-state memory, such as a read-only memory (ROM), a random access memory (RAM), a SIM card, etc. It may also be a memory that saves information even when the power is off, can be selectively erased, and is provided with more data, examples of which are sometimes referred to as EPROMs, etc. The memory 140 may also be some other type of device. The memory 140 includes a buffer memory 141 (sometimes referred to as a buffer). The memory 140 may include an application / function storage unit 142, which is used to store application programs and function programs or processes for executing the operation of the electronic device 600 through the central processor 100.

[0061] The memory 140 may also include a data storage unit 143 for storing data, such as contacts, digital data, pictures, sounds, and / or any other data used by the electronic device. The driver storage unit 144 of the memory 140 may include various drivers for communication functions of the electronic device and / or for executing other functions of the electronic device (such as messaging applications, address book applications, etc.).

[0062] The communication module 110 is a transmitter / receiver 110 that transmits and receives signals via an antenna 111. The communication module (transmitter / receiver) 110 is coupled to the central processor 100 to provide input signals and receive output signals, which may be the same as the case of a conventional mobile communication terminal.

[0063] Based on different communication technologies, multiple communication modules 110 may be provided in the same electronic device, such as a cellular network module, a Bluetooth module and / or a wireless LAN module. The communication module (transmitter / receiver) 110 is also coupled to a speaker 131 and a microphone 132 via an audio processor 130 to provide an audio output via the speaker 131 and receive an audio input from the microphone 132, thereby realizing a common telecommunication function. The audio processor 130 may include any suitable buffer, decoder, amplifier, etc. In addition, the audio processor 130 is also coupled to the central processor 100, so that the sound can be recorded on the local machine through the microphone 132, and the sound stored on the local machine can be played through the speaker 131.

[0064] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment in combination with software and hardware. Moreover, the present application may adopt the form of a computer program product implemented in one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that include computer-usable program code.

[0065] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0066] These computer program instructions may also be stored in a computer-readable memory capable of directing a computer or other programmable data processing device to operate in a specific manner, so that the instructions stored in the computer-readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0067] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0068] The specific embodiments described above further illustrate the purpose, technical solutions and beneficial effects of the present application. It should be understood that the above description is only a specific embodiment of the present application and is not intended to limit the scope of protection of the present application. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application should be included in the scope of protection of the present application.

Claims

1. A method for automatically comparing injected data, characterized in that: The method comprises: Constructing a first telemetry parameter according to the format definition of the injected data; Inversely solve the injected data sent to the spacecraft to obtain an inverse solution result and retrieve the corresponding first telemetry parameter; Generate a dynamic criterion according to the inverse solution result and the first telemetry parameter, and obtain a comparison result according to the dynamic criterion and a second telemetry parameter fed back by the spacecraft according to the injection data; Obtaining a comparison result based on the dynamic criterion and the analysis of the second telemetry parameters fed back by the spacecraft according to the injected data includes: acquiring multiple groups of the second telemetry parameters continuously collected within a preset period; comparing the multiple groups of the second telemetry parameters with the dynamic criterion respectively to obtain multiple comparison results; and obtaining a comparison result based on the multiple comparison results.

2. The method for automatically comparing injected data according to claim 1, characterized in that: Constructing the first telemetry parameter according to the format definition of the injected data also includes: generating a unique identification number according to a format definition of the injected data, and constructing a corresponding first telemetry parameter according to the injected data; A telemetry parameter configuration library is generated according to the correspondence between the first telemetry parameter and the identification number.

3. The automatic comparison method of injection data according to claim 2, characterized in that: Inversely solving the injected data sent to the spacecraft to obtain the inverse solution result and retrieve the corresponding first telemetry parameter includes: Inversely solve the injected data sent to the spacecraft to obtain an inverse solution result and a corresponding identification number; The corresponding first telemetry parameter is retrieved from the telemetry parameter configuration library through the identification number.

4. An automatic comparison device for injection data, characterized in that: The device comprises a construction module, an inverse solution module and a comparison module; The construction module is used to construct a first telemetry parameter according to the format definition of the injected data; The inverse solution module is used to inversely solve the injection data sent to the spacecraft to obtain an inverse solution result and retrieve the corresponding first telemetry parameter; The comparison and judgment module is used to generate a dynamic criterion according to the inverse solution result and the first telemetry parameter, and obtain a comparison and judgment result according to the dynamic criterion and the second telemetry parameter fed back by the spacecraft according to the injection data; obtaining a comparison and judgment result according to the dynamic criterion and the second telemetry parameter fed back by the spacecraft according to the injection data includes: obtaining multiple groups of the second telemetry parameters continuously collected within a preset period; Compare multiple groups of the second telemetry parameters with the dynamic criterion respectively to obtain multiple comparison results; and obtain a comparison result based on the multiple comparison results.

5. The automatic injection data comparison device according to claim 4, characterized in that: The construction module also includes an identification generation unit and an association unit; The identification generating unit is used to generate a unique identification number according to the format definition of the injected data, and to construct a corresponding first telemetry parameter according to the injected data; The association unit is used to generate a telemetry parameter configuration library according to the correspondence between the first telemetry parameter and the identification number.

6. The automatic injection data comparison device according to claim 5, characterized in that: The inverse solution module includes a parsing unit and a query unit; The analysis unit is used to inversely analyze the injection data sent to the spacecraft to obtain an inversely analyzed result and a corresponding identification number; The query unit is used to retrieve the corresponding first telemetry parameter from the telemetry parameter configuration library through the identification number.

7. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the method according to any one of claims 1 to 3 is implemented.

8. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program for causing a computer to execute the method according to any one of claims 1 to 3.

9. A computer program product comprising a computer program / instructions, characterized in that When the computer program / instructions are executed by a processor, the steps of the method according to any one of claims 1 to 3 are implemented.

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