Virtual comprehensive test method for electrical system
By establishing a virtual comprehensive test method for electrical systems in the aerospace control system, and using simulation models and workflow simulation, the integration of electrical system design and simulation verification is achieved, solving the problem of the lack of effective simulation verification in the aerospace control system, and improving design efficiency and accuracy.
Patent Information
- Application Number
- CN202411971334.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-30
- Publication Date
- 2025-05-16
AI Technical Summary
The aerospace control system lacks effective comprehensive test simulation verification methods, which makes it difficult to expose design defects in advance, and the engineering application is not very guiding, which reduces the efficiency and effectiveness of closed-loop verification work for aerospace products.
A virtual comprehensive test method for electrical systems is proposed. By establishing a simulation model of aerospace electrical system and a software workflow simulation model, combined with cross-platform virtual joint simulation, the integration of electrical system design and simulation verification is achieved.
The purpose of design-time simulation, post-simulation optimization, and closed-loop iteration of design and management after optimization, improves the efficiency and accuracy of aerospace electrical system design, and reduces the time cost of later comprehensive test and debugging.
Smart Images
Figure CN120010434A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to a virtual comprehensive test method for an electrical system, belonging to the technical field of electrical system tests. Background Art
[0002] The integrated design of aerospace control systems has long lacked comprehensive test simulation verification methods and has relied heavily on physical verification. During the design of electrical system circuits, possible design defects in the system need to be verified through a large number of physical tests and analysis reviews. Traditional analysis methods focus on expert review and qualitative analysis. There is no effective design verification or simulation method to expose problems in advance. The engineering application guidance is not strong, and the manual calculation and test workload is large, which reduces the efficiency and effectiveness of closed-loop verification of aerospace products. At the same time, before the software product enters the system-level test, the system-level process design and simulation verification methods are insufficient. The rationality of the system's information flow and timing flow in the design scheme cannot be completely closed at the beginning of the design. It can only be implemented in the text editing method and the relevant software task book and stand-alone task book. After the development of each link is completed, it is necessary to rely on a large number of comprehensive test debugging in the later stage to confirm the system test process and functional process. At this stage, there is no virtual comprehensive test method for electrical systems in the domestic aerospace field to realize the virtual digital control system comprehensive test function.
[0003] The serial development mode of system design, single machine design, physical product, and test verification widely used in aerospace electrical system design has been unable to adapt to the rapid development needs of aerospace missions. At the same time, the design of information flow and timing flow mainly relies on the designer's engineering development experience, and is modified and iterated through test verification. Faced with the blockade of foreign advanced design software in my country, there is no reference for digital processes. Summary of the invention
[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to propose a virtual comprehensive test method for an electrical system, to innovatively realize an integrated development mode of electrical system design and simulation verification by establishing an aerospace electrical system simulation model and an aerospace electrical system software workflow simulation model and a joint simulation design, and to break the traditional inefficient mode of only being able to verify after the physical delivery of the system.
[0005] The technical solution of the present invention is:
[0006] A virtual comprehensive test method for an electrical system, comprising:
[0007] S1: Establish a simulation model of the aerospace electrical system, carry out electrical function simulation verification and potential path analysis, and obtain a simulation model of the aerospace electrical system that meets the design requirements and does not have potential paths;
[0008] S2: Establish a simulation model of the software workflow of the aerospace electrical system, arrange the system workflow and perform simulation verification to obtain a simulation model of the software workflow of the aerospace electrical system in which the process can run correctly;
[0009] S3: Based on the aerospace electrical system simulation model finally obtained in step S1 and the aerospace electrical system software workflow simulation model finally obtained in step S2, cross-platform virtual joint simulation is carried out, and data of the above two simulation models are exchanged through Ethernet to verify the matching of the process and hardware functions and the coordination of the work between multiple electrical systems.
[0010] Furthermore, in step S3, the method for carrying out cross-platform virtual joint simulation is:
[0011] S3.1: Generate a list of joint simulation communication protocols and associate the hardware devices where the two simulation models are located in the network topology, so that the aerospace electrical system software workflow simulation model can drive the aerospace electrical system simulation model to implement corresponding simulation actions and receive feedback from the aerospace electrical system simulation model;
[0012] S3.2: Add the data to be sent in the sender of the aerospace electrical system software workflow simulation model and the aerospace electrical system simulation model;
[0013] S3.3: Add the data to be received in the aerospace electrical system software workflow simulation model receiver and the aerospace electrical system simulation model;
[0014] S3.4: Repeat the electrical function simulation verification and latent path analysis driven by the aerospace electrical system software workflow simulation model, and observe whether the electrical system model can work normally in the order driven by the process model. If not, modify the aerospace electrical system simulation model and repeat this step until the electrical system model can work normally in the order driven by the process model.
[0015] S3.5: Repeat the workflow under the drive of the aerospace electrical system software workflow simulation model to observe whether the workflow can be run correctly. If not, modify the aerospace electrical system software workflow simulation model and repeat this step until the workflow can be run correctly.
[0016] S3.6: Deploy the aerospace electrical system simulation model obtained in step S3.4 and the aerospace electrical system software workflow simulation model obtained in step 3.5 in multiple PCs, simulate the simulation of multiple electrical systems, repeat steps S3.1 to S3.5, and realize the simulation of multiple electrical systems.
[0017] Furthermore, in step S3.2, the data area to be sent is added in the sender of the aerospace electrical system software workflow simulation model, and the data in the data area includes the simulation system time, simulation mode, instruction type, device serial number, switch serial number, switch status, execution time and instruction number; the data to be sent is added in the aerospace electrical system simulation model, including the system time, simulation mode, return command form, instruction processing results and result parameters.
[0018] Furthermore, in step S3.3, the data area to be received is added in the receiver of the aerospace electrical system software workflow simulation model, and the data in the data area includes the simulation system time, simulation mode, instruction type, device serial number, switch serial number, switch status, execution time and instruction number; the data to be received is added in the aerospace electrical system simulation model, including the system time, simulation mode, return command form, instruction processing results and result parameters.
[0019] Furthermore, step S1 specifically includes:
[0020] S1.1: Complete the drawing of the system electrical schematic diagram and establish the aerospace electrical system simulation model;
[0021] S1.2: Add virtual excitation to each interface of the electrical schematic to simulate the electrical function, and observe the simulation results through a virtual oscilloscope to confirm the correctness of the electrical circuit design and whether there is a hidden path;
[0022] S1.3: If the simulation results observed by the virtual oscilloscope do not meet the design requirements or there is a hidden path, modify the system electrical schematic diagram and repeat step S1.2 until the simulation results meet the design requirements and there is no hidden path.
[0023] Further, step S2 specifically includes:
[0024] S2.1: Draw a flowchart of the system workflow and establish a simulation model of the aerospace electrical system software workflow;
[0025] S2.2: Run the workflow based on the aerospace electrical system software workflow simulation model to observe whether the process can run correctly or enter an abnormal branch. If so, modify the workflow flowchart and simulate again until the process can run correctly and does not enter an abnormal branch.
[0026] Furthermore, through step S3 cross-platform virtual joint simulation, the aerospace electrical system simulation model, the aerospace electrical system software workflow simulation model, the communication protocol, the incentive, and the modification process are solidified to form the final design result.
[0027] The advantages of the present invention compared with the prior art are:
[0028] (1) In the present invention, the system demand-oriented design and simulation integration technology accelerates the simulation system construction and simulation analysis process. The system design documents are transformed from static drawings or task books into virtual systems, and an innovative development model that integrates electrical system design and simulation verification is realized, breaking the traditional inefficient model that can only be verified after the physical delivery of the system. After the system design is completed, the solution has simulation functions such as review and recalculation, system-level simulation, etc. The closed-loop iteration purpose of design and management is achieved, which includes simulation during design, optimization after simulation, and production after optimization.
[0029] (2) In the present invention, based on the graphical complex process modeling, the information flow timing flow model of the system is established, the system software process can be designed and simulated, and various simulation modes such as boundary simulation and fault injection of the system process can be performed. Before the software technical requirements are put forward, the correctness of the software technical requirements and the matching of the process and the interface can be verified, thereby reducing the time cost caused by changing the software solution design errors.
[0030] (3) In the present invention, in view of the integrated requirements of "design, simulation, and verification" of aerospace control system solutions, and in view of the difficulties and low efficiency of system model integration and debugging caused by the inconsistency of missile control system model construction processes and methods, a set of control system modeling specifications that meet the requirements of aerospace system electrical simulation + process simulation-verification is formed. BRIEF DESCRIPTION OF THE DRAWINGS
[0031] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:
[0032] Figure 1 A schematic diagram of a virtual comprehensive test method for an electrical system according to an embodiment of the present invention;
[0033] Figure 2 The present invention is a flowchart of a virtual comprehensive test method for an electrical system according to an embodiment of the present invention. DETAILED DESCRIPTION
[0034] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.
[0035] The present invention proposes a virtual comprehensive test method for electrical systems. With the optimization of the development process of system engineering as the core, the method focuses on electrical system design, system workflow design, reliability analysis, simulation verification, etc., and drives the development of a system-level hardware and system-level software design and simulation platform suitable for aerospace. It establishes an aerospace electrical system development model based on digital twins, opens up the joint simulation interface between system software and hardware, and realizes high-reliability design and multi-dimensional collaboration of the system.
[0036] The specific embodiments of the present invention are described below in conjunction with the accompanying drawings. Figure 1 , Figure 2 In the specific implementation process, the test method includes three major functions: 1) aerospace electrical system design simulation function; 2) aerospace system workflow design simulation function; 3) system cross-platform virtual joint simulation function, so that the electrical system comprehensive design and simulation software provides hardware simulation operation feedback to the system process design and simulation software, and the system process design and simulation software guides the full system simulation of the hardware action timing of the electrical system comprehensive design and simulation software.
[0037] S1: Perform aerospace electrical system design simulation
[0038] Establish a simulation model for aerospace electrical systems, and carry out comprehensive design, simulation verification, and potential path analysis of system electrical equipment.
[0039] S1.1: Complete the drawing of the system electrical schematic diagram and establish the aerospace electrical system simulation model, such as Figure 1 As shown in (1).
[0040] S1.2: Add virtual excitation at each interface of the electrical schematic to simulate the electrical function, and observe the simulation results through a virtual oscilloscope to confirm the correctness of the electrical circuit design and whether there is a hidden path.
[0041] S1.3: If the simulation results observed by the virtual oscilloscope do not meet the design requirements or there is a hidden path, modify the system electrical schematic diagram and repeat step S1.2 until the simulation results meet the design requirements.
[0042] S2: Space system workflow design simulation
[0043] Establish a simulation model of the aerospace electrical system software workflow, that is, establish the system's information flow and timing flow model, arrange the system workflow and perform simulation verification.
[0044] S2.1: Complete the flow chart of the system workflow and establish a simulation model of the aerospace electrical system software workflow, such as Figure 1 As shown in (2).
[0045] S2.2: Run the system workflow and observe whether the process can run to completion correctly or enter an abnormal branch. If so, modify the flowchart of the system workflow and re-simulate.
[0046] S3: System cross-platform virtual co-simulation
[0047] The aerospace electrical system simulation model and the electrical system software workflow simulation model are used for joint simulation. Data interaction between the two simulation models is achieved through Ethernet, and the electrical system simulation driven by the process is realized to verify the matching of software process and hardware function, and the coordination of work between multiple electrical systems.
[0048] S3.1: Generate a joint simulation communication protocol list and associate the hardware devices where the two models in the network topology are located, so that the process simulation model can drive the electrical system simulation model to implement corresponding simulation actions and receive feedback from the electrical system simulation model.
[0049] S3.2: Add the data area to be sent in the process simulation model sender, including the simulation system time (for time synchronization), simulation mode (setting priority), instruction type, device serial number, switch serial number, switch status, execution time, and instruction number (for instruction counting). The data sent by the aerospace electrical system simulation model includes system time (for time synchronization), simulation mode (setting priority), return command form, instruction processing results, and result parameters, such as Figure 1 As shown in (3).
[0050] S3.3: Add the data area to be received in the process simulation model receiver, including the simulation system time (for time synchronization), simulation mode (setting priority), instruction type, device serial number, switch serial number, switch status, execution time, and instruction number (for instruction counting). The aerospace electrical system simulation model receives data including system time (for time synchronization), simulation mode (setting priority), return command form, instruction processing results, and result parameters.
[0051] S3.4: Repeat S1.2 driven by the process simulation model, such as Figure 1 As shown in (4). During the observation process, check whether the electrical system model can work normally according to the sequence driven by the process model. If not, modify the electrical system model and repeat this step.
[0052] S3.5: Repeat the work of S2.2 driven by the process simulation model to observe whether the process flow can be completed normally. If not, modify the process simulation model and repeat this step.
[0053] S3.6: deploy corresponding electrical system simulation models and process simulation models in multiple PCs to simulate multiple electrical systems. Repeat the joint simulation steps S3.1 to S3.5 to achieve the simulation of multiple electrical systems.
[0054] Step 4: Solidify historical data
[0055] During the specific implementation process, the electrical simulation model, process simulation model, communication protocol, incentives, modification process, etc. are solidified to form the final design result.
[0056] The above-described embodiments are only preferred specific implementations of the present invention. Common changes and substitutions made by those skilled in the art within the scope of the technical solution of the present invention should be included in the protection scope of the present invention.
Claims
1. A virtual comprehensive test method for an electrical system, characterized in that: include: S1: Establish a simulation model of the aerospace electrical system, carry out electrical function simulation verification and potential path analysis, and obtain a simulation model of the aerospace electrical system that meets the design requirements and does not have potential paths; S2: Establish a simulation model of the software workflow of the aerospace electrical system, arrange the system workflow and perform simulation verification to obtain a simulation model of the software workflow of the aerospace electrical system in which the process can run correctly; S3: Based on the aerospace electrical system simulation model finally obtained in step S1 and the aerospace electrical system software workflow simulation model finally obtained in step S2, cross-platform virtual joint simulation is carried out, and data of the above two simulation models are exchanged through Ethernet to verify the matching of the process and hardware functions and the coordination of the work between multiple electrical systems.
2. The electrical system virtual comprehensive test method according to claim 1, characterized in that: In step S3, the method for carrying out cross-platform virtual joint simulation is: S3.1: Generate a list of joint simulation communication protocols and associate the hardware devices where the two simulation models are located in the network topology, so that the aerospace electrical system software workflow simulation model can drive the aerospace electrical system simulation model to implement corresponding simulation actions and receive feedback from the aerospace electrical system simulation model; S3.2: Add the data to be sent in the sender of the aerospace electrical system software workflow simulation model and the aerospace electrical system simulation model; S3.3: Add the data to be received in the aerospace electrical system software workflow simulation model receiver and the aerospace electrical system simulation model; S3.4: Repeat the electrical function simulation verification and latent path analysis driven by the aerospace electrical system software workflow simulation model, and observe whether the electrical system model can work normally in the order driven by the process model. If not, modify the aerospace electrical system simulation model and repeat this step until the electrical system model can work normally in the order driven by the process model. S3.5: Repeat the workflow under the drive of the aerospace electrical system software workflow simulation model to observe whether the workflow can be run correctly. If not, modify the aerospace electrical system software workflow simulation model and repeat this step until the workflow can be run correctly. S3.6: Deploy the aerospace electrical system simulation model obtained in step S3.4 and the aerospace electrical system software workflow simulation model obtained in step 3.5 in multiple PCs, simulate the simulation of multiple electrical systems, repeat steps S3.1 to S3.5, and realize the simulation of multiple electrical systems.
3. The electrical system virtual comprehensive test method according to claim 2, characterized in that: In step S3.2, the data area to be sent is added in the sender of the aerospace electrical system software workflow simulation model. The data in the data area includes the simulation system time, simulation mode, instruction type, device serial number, switch serial number, switch status, execution time and instruction number; the data to be sent is added in the aerospace electrical system simulation model, including the system time, simulation mode, return command form, instruction processing results and result parameters.
4. The electrical system virtual comprehensive test method according to claim 2, characterized in that: In step S3.3, the data area that needs to be received is added in the receiver of the aerospace electrical system software workflow simulation model. The data in the data area includes the simulation system time, simulation mode, instruction type, device serial number, switch serial number, switch status, execution time and instruction number; the data that needs to be received is added in the aerospace electrical system simulation model, including the system time, simulation mode, return command form, instruction processing results and result parameters.
5. The electrical system virtual comprehensive test method according to claim 1, characterized in that: Step S1 specifically includes: S1.1: Complete the drawing of the system electrical schematic diagram and establish the aerospace electrical system simulation model; S1.2: Add virtual excitation to each interface of the electrical schematic to simulate the electrical function, and observe the simulation results through a virtual oscilloscope to confirm the correctness of the electrical circuit design and whether there is a hidden path; S1.3: If the simulation results observed by the virtual oscilloscope do not meet the design requirements or there is a hidden path, modify the system electrical schematic diagram and repeat step S1.2 until the simulation results meet the design requirements and there is no hidden path.
6. The electrical system virtual comprehensive test method according to claim 1, characterized in that: Step S2 specifically includes: S2.1: Draw a flowchart of the system workflow and establish a simulation model of the aerospace electrical system software workflow; S2.2: Run the workflow based on the aerospace electrical system software workflow simulation model to observe whether the process can run correctly or enter an abnormal branch. If so, modify the workflow flowchart and simulate again until the process can run correctly and does not enter an abnormal branch.
7. The electrical system virtual comprehensive test method according to claim 1, characterized in that: After step S3 cross-platform virtual joint simulation, the aerospace electrical system simulation model, the aerospace electrical system software workflow simulation model, the communication protocol, the incentive, and the modification process are solidified to form the final design result.