CN117908400A - Digital twinning-based system comprehensive test platform and test method - Google Patents
Digital twinning-based system comprehensive test platform and test method Download PDFInfo
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- CN117908400A CN117908400A CN202311832611.8A CN202311832611A CN117908400A CN 117908400 A CN117908400 A CN 117908400A CN 202311832611 A CN202311832611 A CN 202311832611A CN 117908400 A CN117908400 A CN 117908400A
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- 238000012360 testing method Methods 0.000 title claims abstract description 82
- 238000010998 test method Methods 0.000 title claims abstract description 11
- 230000005284 excitation Effects 0.000 claims abstract description 13
- 238000012544 monitoring process Methods 0.000 claims abstract description 9
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 21
- 238000002347 injection Methods 0.000 claims description 6
- 239000007924 injection Substances 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 4
- 239000000446 fuel Substances 0.000 claims description 4
- 230000003542 behavioural effect Effects 0.000 claims description 2
- 238000012806 monitoring device Methods 0.000 claims 2
- 230000006399 behavior Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
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Abstract
The application belongs to the field of aviation tests, and particularly relates to a digital twin-based system comprehensive test platform and a digital twin-based system comprehensive test method. The test platform comprises: the system tester (1) is used for providing excitation signals and fault signals for each entity device and each virtual entity device; the entity device is used for receiving the signals of the virtual tester and generating entity test results; the virtual entity device (5) is used for receiving the signals of the virtual tester and generating virtual test results; the virtual-to-actual converter (6) is used for switching states between each entity device and the virtual entity device so as to determine a signal input object of the system tester (1); and the signal monitoring equipment (8) is used for acquiring and comparing the entity test result and the virtual test result to form difference data for updating the virtual entity model of the virtual entity equipment (5). The application can continuously perfect the virtual model through the comprehensive test data of the system.
Description
Technical Field
The application belongs to the field of aviation tests, and particularly relates to a digital twin-based system comprehensive test platform and a digital twin-based system comprehensive test method.
Background
In the field of aviation tests, the development of a comprehensive test of a system usually carries out test environment planning in the early stage, and a host unit and a finished product factory build corresponding test environments according to the test environment planning, so that the period is long, the task amount is large, and the cost is high. Along with the proposal of the digital twin concept, an advanced modeling and simulation tool is used for constructing a full life cycle and a value chain of a coverage product, and the past and present behaviors or processes of a certain physical entity are dynamically presented in a digital form, so that a new idea is opened for future system comprehensive experiments.
When the existing digital twin model is used, the effect and the entity model are greatly different, and therefore, a test platform capable of continuously updating the digital twin model is needed to be provided.
Disclosure of Invention
The application aims to provide a digital twin-based system comprehensive test platform and a digital twin-based system comprehensive test method so as to improve the reliability of a digital twin model.
The first aspect of the application provides a digital twinning-based system comprehensive test platform, which mainly comprises:
The system tester is used for providing excitation signals and fault signals for each entity device and each virtual entity device;
The entity equipment comprises a flight control system equipment, an electromechanical system equipment and an avionic system equipment, is connected with the system tester and is used for receiving signals of the virtual tester and generating entity test results;
The virtual entity equipment comprises a flight control system virtual entity, an electromechanical system virtual entity and an avionic system virtual entity, which are all connected with the system tester and used for receiving signals of the virtual tester and generating virtual test results;
The virtual-real converter is used for switching states between each entity device and the virtual entity device so as to determine a signal input object of the system tester;
and the signal monitoring equipment is used for acquiring and comparing the entity test result and the virtual test result to form difference data for updating the virtual entity model of the virtual entity equipment.
Preferably, the system tester is configured to provide a control interface, where the control interface includes at least a power control component for powering on or off each of the physical device and the virtual physical device, a device ID for performing fault signal selection, an aircraft ID, a fault signal control component for disconnecting and connecting a channel fault logic signal, a debug component for performing debug permission, and an excitation injection component for performing excitation signal injection including wheel-mounted.
Preferably, the flight control system device comprises an automatic flight control assembly, a fly-by-wire flight control assembly and a high lift assembly.
Preferably, the electromechanical systems device comprises an integrated electromechanical assembly, a hydraulic assembly and a fuel assembly.
Preferably, the avionics system device includes a display control component, a task component, and a communication component.
Preferably, the virtual entity device comprises a geometric model, a physical model, a behavior model and a rule model, and is used for describing and depicting the flight control, electromechanical and avionic system entity device from a time scale and a space scale.
Preferably, the test platform further comprises a software debugging loading device, and the software debugging loading device is used for providing an operation component for modifying parameters of the virtual entity device, programming the software, loading and unloading the software.
The second aspect of the application provides a digital twin-based system comprehensive test method, which is used for testing by applying the digital twin-based system comprehensive test platform, and comprises the following steps:
Step S1, carrying out power-on initialization of a test platform through a system tester, and selecting a test object as entity equipment through a virtual-actual converter;
Step S2, setting test parameters comprising excitation signals and fault signals through a system tester;
Step S3, loading the test parameters to the selected entity equipment;
s4, after a time period is set, acquiring an entity test result through signal monitoring equipment;
S5, selecting a test object as virtual entity equipment through a virtual-to-actual converter, loading the test parameters to the selected entity equipment, and acquiring a virtual test result through signal monitoring equipment after a set time period;
and S6, comparing the entity test result with the virtual test result, and if the difference of the results exceeds the error range, updating the virtual entity model based on the difference data.
According to the application, the virtual model can be continuously perfected through the comprehensive test data of the system, the purpose of completing the comprehensive test of the system only through the virtual entity is finally achieved, the test efficiency can be improved, and the test cost is reduced.
Drawings
FIG. 1 is a system architecture diagram of a preferred embodiment of a digital twinning-based system integrated test platform of the present application.
FIG. 2 is a flow chart of a preferred embodiment of the digital twinning-based system integration test method of the present application.
The system comprises a 1-system tester, 2-flight control system equipment, 3-electromechanical system equipment, 4-avionic system equipment, 5-virtual entity equipment, a 6-virtual-to-real converter, 7-software debugging loading equipment and 8-signal monitoring equipment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present application without making any inventive effort, are intended to fall within the scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The first aspect of the present application provides a digital twin-based system comprehensive test platform, as shown in fig. 1, mainly including:
the system tester 1 is used for providing excitation signals and fault signals for each entity device and virtual entity device;
the entity equipment comprises a flight control system equipment 2, an electromechanical system equipment 3 and an avionic system equipment 4, which are all connected with the system tester 1 and are used for receiving signals of the virtual tester and generating entity test results;
the virtual entity device 5 comprises a flight control system virtual entity, an electromechanical system virtual entity and an avionic system virtual entity, which are all connected with the system tester 1 and are used for receiving signals of the virtual tester and generating virtual test results;
A virtual-to-actual converter 6, configured to perform state switching between each of the physical devices and the virtual physical device, so as to determine a signal input object of the system tester 1;
And the signal monitoring equipment 8 is used for acquiring and comparing the entity test result and the virtual test result to form difference data for updating the virtual entity model of the virtual entity equipment 5.
In some alternative embodiments, the system tester 1 is configured to provide a control interface, where the control interface includes at least a power control component for powering on or off each of the physical device and the virtual physical device, a device ID for performing fault signal selection, an aircraft ID, a fault signal control component for disconnecting and connecting channel fault logic signals, a debug component for performing debug permission, and an excitation injection component for performing excitation signal injection including on-board.
In some alternative embodiments, the flight control system apparatus 2 includes an automatic flight control assembly, a fly-by-wire flight control assembly, and a high lift assembly. In this embodiment, an automatic flight control assembly, a fly-by-wire flight control assembly, a high lift assembly, and the like are used to implement flight control system functional logic.
In some alternative embodiments, the electromechanical systems device 3 includes an integrated electromechanical assembly, a hydraulic assembly, and a fuel assembly. In this embodiment, integrated electromechanical, hydraulic, and fuel components, etc., are used to implement electromechanical system functional logic.
In some alternative embodiments, the avionics system device 4 includes a display control component, a task component, and a communication component. And the display control component, the task component, the communication component and the like are used for realizing the avionics system function logic.
In some alternative embodiments, the virtual entity device 5 includes a geometric model, a physical model, a behavioral model, and a rule model for describing and depicting the flight control, electro-mechanical, and avionics system entity devices from a time scale and a space scale.
In some alternative embodiments, the test platform further comprises a software debug loading device 7, which is used for providing an operation component for modifying, programming, loading and unloading the parameters of the virtual entity device 5.
The second aspect of the present application provides a digital twin-based system comprehensive test method, as shown in fig. 2, for performing a test using the digital twin-based system comprehensive test platform as described above, the test method comprising:
Step S1, carrying out power-on initialization of a test platform through a system tester 1, and selecting a test object as physical equipment through a virtual-to-actual converter 6.
The step is shown as 201 in fig. 2, the test starts, the test platform device is powered on according to the task to be completed in the test, the test platform is initialized, the initial state of the test platform is set to select the entity device, and the entity device is used as the test object to load the test parameters.
Step S2, test parameters including an excitation signal and a fault signal are given by the system tester 1. As shown at 202 in fig. 2, the initial parameters of the trial are set, mainly as initial conditions of the trial project.
And step S3, loading the test parameters to the selected entity equipment.
And S4, after a set time period, acquiring an entity test result through the signal monitoring equipment 8.
This step is shown at 204 in fig. 2, where after the parameters are loaded for a period of time, the desired monitor signal values are observed and the test results are recorded.
And S5, selecting a test object as virtual entity equipment through the virtual-to-actual converter 6, loading the test parameters to the selected entity equipment, and acquiring a virtual test result through the signal monitoring equipment 8 after a set time period.
The step is shown in 205-208 of fig. 2, after the test equipment is adjusted to be a virtual entity, the parameter loading of the virtual entity is performed in the same manner as the test on the entity equipment, so as to obtain the virtual test parameter.
And S6, comparing the entity test result with the virtual test result, and if the difference of the results exceeds the error range, updating the virtual entity model based on the difference data.
In this step, as shown in 209-211 in fig. 2, the test results in the physical device state and the virtual device state are compared, the requirement is satisfied, if the difference between the results exceeds the error range, the test is terminated in 211, the test is skipped to 210, and the virtual entity model is updated by applying the physical device result data or the difference data, for example, by modifying, software programming, loading and unloading the parameters of the virtual entity device through the software debug loading device 7 shown in fig. 1.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A digital twinning-based system comprehensive test platform, comprising:
the system tester (1) is used for providing excitation signals and fault signals for each entity device and each virtual entity device;
The entity equipment comprises a flight control system equipment (2), an electromechanical system equipment (3) and an avionic system equipment (4), and is connected with the system tester (1) and used for receiving signals of the virtual tester and generating entity test results;
the virtual entity device (5) comprises a flight control system virtual entity, an electromechanical system virtual entity and an avionic system virtual entity, which are all connected with the system tester (1) and used for receiving signals of the virtual tester and generating virtual test results;
The virtual-to-actual converter (6) is used for switching states between each entity device and the virtual entity device so as to determine a signal input object of the system tester (1);
And the signal monitoring equipment (8) is used for acquiring and comparing the entity test result and the virtual test result to form difference data for updating the virtual entity model of the virtual entity equipment (5).
2. The digital twin based system integrated test platform of claim 1, wherein the system tester (1) is configured to provide a control interface including at least a power control component for powering on or off each of the physical devices and the virtual physical devices, a device ID for performing fault signal selection, an aircraft ID, a fault signal control component for disconnecting and connecting channel fault logic signals, a debug component for performing debug permission, and an excitation injection component for performing excitation signal injection including on-board.
3. The digital twinning-based system integrated test platform of claim 1, wherein the flight control system apparatus (2) includes an automatic flight control assembly, a fly-by-wire flight control assembly, and a high lift assembly.
4. The digital twin based system integrated test platform according to claim 1, wherein the electromechanical systems device (3) comprises an integrated electromechanical assembly, a hydraulic assembly and a fuel assembly.
5. The digital twinning-based system integrated test platform of claim 1, wherein the avionics system equipment (4) includes a display control component, a task component, and a communication component.
6. The digital twin based system integrated test platform according to claim 1, wherein the virtual entity devices (5) comprise geometric models, physical models, behavioral models and rule models for describing and depicting the flight control, electro-mechanical and avionic system entity devices from a time scale and a space scale.
7. The digital twin based system integrated test platform according to claim 1, further comprising a software debug loading device (7) for providing operating components for modifying, software programming and loading/unloading parameters of the virtual entity device (5).
8. A digital twin based system integrated test method for testing using the digital twin based system integrated test platform according to any one of claims 1-7, the test method comprising:
Step S1, carrying out power-on initialization of a test platform through a system tester (1), and selecting a test object as entity equipment through a virtual-to-actual converter (6);
Step S2, setting test parameters comprising excitation signals and fault signals through a system tester (1);
Step S3, loading the test parameters to the selected entity equipment;
S4, after a time period is set, acquiring an entity test result through a signal monitoring device (8);
s5, selecting a test object as virtual entity equipment through a virtual-to-actual converter (6), loading the test parameters for the selected entity equipment, and acquiring a virtual test result through a signal monitoring device (8) after a set time period;
and S6, comparing the entity test result with the virtual test result, and if the difference of the results exceeds the error range, updating the virtual entity model based on the difference data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311832611.8A CN117908400A (en) | 2023-12-28 | 2023-12-28 | Digital twinning-based system comprehensive test platform and test method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311832611.8A CN117908400A (en) | 2023-12-28 | 2023-12-28 | Digital twinning-based system comprehensive test platform and test method |
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| CN117908400A true CN117908400A (en) | 2024-04-19 |
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| CN202311832611.8A Pending CN117908400A (en) | 2023-12-28 | 2023-12-28 | Digital twinning-based system comprehensive test platform and test method |
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| CN (1) | CN117908400A (en) |
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