Multi-stage test system and method for electromagnetic compatibility between whole aircraft systems

Abstract

The invention provides a multi-stage test system for the electromagnetic compatibility between whole aircraft systems, and the system comprises a test planning unit, an automatic test execution unit, a data fusion and analysis unit, and a report generation and closed-loop management unit. Wherein the test planning unit is connected with the automatic test execution unit, the data fusion and analysis unit and the report generation and closed-loop management unit. An intelligent diagnosis mechanism based on data driving is introduced, rapid positioning and reason analysis of an electromagnetic interference problem are realized through combination of multi-source data fusion and an advanced algorithm, and the problems of long troubleshooting period and high cost in a traditional method are solved.

Description

Technical Field

[0001] This invention relates to the field of avionics system testing technology, and specifically to a multi-stage testing system and method for electromagnetic compatibility between aircraft systems. Background Technology

[0002] Electromagnetic compatibility (EMC) is a critical characteristic for ensuring the safe flight of modern aircraft. Whole-system EMC testing is an indispensable part of the aircraft development process, aiming to identify and resolve electromagnetic interference issues between systems arising from subsystem integration.

[0003] Currently, traditional whole-machine EMC testing typically suffers from the following pain points: 1. The testing process is fragmented and lacks a systematic approach: Most tests are conducted manually based on experience, and each test item (such as HIRF, lightning, and ISIC) is relatively independent. There is a lack of a progressive and integrated testing process from basic to complex and from internal to external, which can easily lead to blind spots in testing.

[0004] 2. Inefficient and costly: It relies heavily on manual operation, recording and judgment, has a long testing cycle, occupies expensive test platforms (such as airplanes and darkrooms) for a long time, and has extremely high human and material costs.

[0005] 3. Difficulty in fault location: When interference occurs, due to the complexity and instantaneous nature of electromagnetic problems, it is difficult to quickly and accurately locate the interference source, coupling path and affected object using traditional methods, resulting in a long troubleshooting cycle.

[0006] 4. Disorganized data management: The massive amounts of data generated by the tests come from different instruments and at different times, lacking effective synchronization and correlation analysis methods, and the value of the data has not been fully explored.

[0007] Therefore, there is a need in this field for a whole-machine EMC testing method that can overcome the above-mentioned shortcomings and achieve high efficiency, comprehensiveness, automation and intelligence. Summary of the Invention

[0008] This invention provides a multi-stage testing system and method for electromagnetic compatibility between aircraft systems, which can solve common technical problems in the industry such as lack of systematic testing process, low degree of automation, low fault diagnosis efficiency, and scattered data management in existing aircraft-level electromagnetic compatibility testing technologies.

[0009] Technical solution: In a first aspect, this application provides a multi-stage testing system for electromagnetic compatibility between aircraft systems, including a test planning unit, an automated test execution unit, a data fusion and analysis unit, and a report generation and closed-loop management unit, wherein: The test planning unit is interconnected with the automated test execution unit, data fusion and analysis unit, and report generation and closed-loop management unit.

[0010] Specifically, the test planning unit includes a system interaction matrix generator and test case library management software, wherein: The system interaction matrix generator constructs a system interaction matrix based on the aircraft's system architecture diagram, interface control document (ICD), and security analysis results, identifies all potential "interference source-sensitive device" pairs, and automatically generates a multi-dimensional test case library; The test case library management software sends test cases to the test control host via Ethernet for execution; it receives a list of issues and rectification tracking from the report generation and closed-loop management unit, forms rectification test cases, and sends them to the test control host via Ethernet to trigger the completion of regression testing.

[0011] Specifically, the automated test execution unit includes a test control host, an instrument control module, a system adaptation module, and a data acquisition and synchronization module, among which: Test control host: The test control host retrieves test cases from the test planning unit via Ethernet, and also connects with the instrument control module, system adaptation module, and data acquisition and synchronization module via Ethernet to run test sequences and coordinate the entire test process; Instrument control module: Based on a standard bus, it controls all external test instruments, including spectrum analyzers, oscilloscopes, signal generators, and power supply monitors; System adaptation module: Through different aircraft bus interface boards and adapters, it realizes the connection with the aircraft system and realizes automatic program control, completes the sending of instructions to various subsystems of the aircraft, controls them to enter the preset working state, and completes the interface adaptation and docking of the automated execution unit and the data fusion and analysis unit. Data acquisition and synchronization module: Synchronizes all acquisition devices with a high-precision time protocol to ensure that all data has a unified time stamp.

[0012] Specifically, the data fusion and analysis unit includes a central database, a data fusion engine, and an intelligent fault diagnosis model, among which: Central Database: Stores massive amounts of raw data from all data channels, preprocesses the raw data, and aligns it based on a unified timescale; Multi-source data fusion engine: It correlates and fuses electromagnetic data, power data, system bus data, and aircraft status data based on time; it extracts key features from the central database and establishes causal relationships between different data features based on time alignment, thereby achieving the fusion of multi-source data; Intelligent fault diagnosis model: It adopts a combination of rule engine and machine learning model for diagnosis. The rule engine quickly matches known interference patterns; the machine learning model uses clustering, classification and other algorithms to mine abnormal patterns for unknown or complex interference patterns, automatically locates the interference source and coupling path, and outputs diagnostic conclusions.

[0013] Specifically, the report generation and closed-loop management unit is interconnected with the data fusion and analysis unit and the test planning unit via Ethernet. It is responsible for generating reports, visualizing data, and tracking issues, and includes a report generator, interactive visualization dashboards, and an issue tracking module. Report Generator: The report generator has built-in standardized report templates that conform to airworthiness standards and is interconnected with the central database and data fusion engine via Ethernet. When a report needs to be generated, the engine will automatically extract the data corresponding to the template from the central database and generate a standardized test report. Interactive Visual Dashboard: A comprehensive visual dashboard composed of multiple related charts, providing users with an interactive interface; Problem Tracking Module: Records, manages, and tracks the rectification of problems diagnosed by the intelligent fault diagnosis model. It feeds back the problem and rectification tracking list to the test planning unit via Ethernet, generates rectification test cases through the test case library management software, and can trigger regression testing, forming a closed-loop management of test-analysis-rectification-verification.

[0014] Secondly, this application provides a multi-stage testing method for electromagnetic compatibility between aircraft systems, characterized by comprising: Step 1: Systematic test planning. Based on the aircraft's system architecture diagram, interface control documents, and system security assessment results, a matrix analysis method is used to automatically construct a system interaction matrix based on "interference source-coupling path-sensitive source". Based on the system interaction matrix, the test planning unit automatically derives and generates a multi-dimensional test case library. Step 2: Multi-stage test execution, including ground static basic testing, static inter-system interference testing, external environment adaptability testing, and dynamic inter-system interference testing. The automated test execution unit completes the corresponding test cases in the multi-dimensional test case library, and collects various data during the process, which are then summarized in the central database. Step 3: Intelligent data fusion and fault diagnosis. A central database is established, aggregating data from all stages, excitation and measurement equipment, data acquisition equipment, and various aircraft subsystems. This data is connected to the central database via a system adaptation module. High-precision time synchronization technology is used as the keyframe for data association, and the data is cleaned and time-stamped aligned. A multi-source data fusion engine is used to fuse the data from the central database, forming a test data map. An intelligent fault diagnosis model is employed for analysis, ultimately generating a data analysis set, fault diagnosis results and report data, and recorded issues. Step 4: Automated report generation and closed-loop management. The analysis results of the data fusion and analysis unit are transmitted to the report generation and closed-loop management unit via Ethernet. The report generation and closed-loop management unit can generate detailed reports that meet the airworthiness certification requirements through the report generator.

[0015] Specifically, step 2 includes: Step 21: Conduct ground static foundation tests on the entire aircraft. The automated test execution unit receives the relevant test cases for ground static foundation tests sent by the test planning unit via Ethernet. The test control host controls the instruments to send control commands to the instrument control module and the data acquisition and synchronization module. The aircraft lap resistance is scanned and measured, and the shielding continuity and impedance of the key cables are measured. At the same time, the lap resistance of the entire aircraft and the shielding effectiveness data of the key cables are collected. Step 22: Perform static inter-system interference testing on the entire aircraft. The automated test execution unit receives the relevant test cases for static inter-system interference testing sent by the test planning unit via Ethernet. The test control host controls the system adaptation module and the instrument control module to automatically control each system on the aircraft to enter the predetermined working state. At the same time, the data acquisition and synchronization module collects the performance parameters, power network characteristics, bus data and spatial electromagnetic field data of all sensitive systems of the aircraft. Step 23: External environment adaptability test. In a dedicated test field, according to the severity level required by the corresponding electromagnetic compatibility standard, high-intensity radiation field test and lightning indirect effect transient injection test are performed. The automated test execution unit receives the relevant test cases for external environment adaptability test sent by the test planning unit via Ethernet. The test control host sends control commands to the instrument control module and the data acquisition and synchronization module, and collects aircraft system data and monitors functional status throughout the process. Step 24: Dynamic Inter-System Interference Test. With the aircraft engine running or in actual flight, the EMC performance data of the critical systems under dynamic environment and mission load conditions are continuously monitored and recorded by the airborne data recording equipment. The data recorded by the airborne data recording equipment is imported into the central database for final verification and supplementation of test results.

[0016] Specifically, step 4 also includes: The report generation and closed-loop management unit automatically records the diagnosed issues, forms an issue and rectification tracking list, and links it back to the test case library via Ethernet to trigger the execution of regression tests, forming a complete positive feedback closed loop of "test-analysis-rectification-verification".

[0017] The core innovation of this invention lies in: 1. Systematic test planning: Automatically generate a multi-dimensional test case library based on the system interaction matrix to ensure complete test coverage and eliminate omissions.

[0018] 2. Structured testing process: A four-stage progressive testing process was designed, namely "ground static test → inter-system interference → external environment test → flight verification". The logic is clear, risks are moved forward, and basic problems are exposed in advance.

[0019] 3. Full-process automation: Through an integrated automated testing system, instruments are controlled, aircraft systems are stimulated, and data is collected, significantly improving testing efficiency, consistency, and repeatability.

[0020] 4. Data-driven intelligent diagnosis: High-precision time synchronization technology is used to fuse multi-source data, and rule-based and machine learning-based data analysis models are used for intelligent fault diagnosis to quickly locate the root cause of interference.

[0021] Compared with existing technologies, this invention provides a multi-stage testing system and method for electromagnetic compatibility between aircraft systems, which has the following significant advantages: 1. Improved testing efficiency and economic benefits: Full-process automation frees testers from tedious manual operations and recording, and is expected to shorten the testing cycle by 30%-50%, greatly reducing labor costs and the time spent on expensive platforms (aircraft, darkroom).

[0022] 2. Improved test coverage and reliability: Automated test case generation based on the system interaction matrix ensures comprehensive test coverage. In particular, it can effectively discover hidden interference problems in complex scenarios such as multi-system interaction and dynamic transients, greatly improving the completeness of the test and the reliability of the results.

[0023] 3. Qualitative leap in fault diagnosis capabilities: Through data fusion and intelligent analysis, fault location is transformed from "manual guessing" to "precise location driven by data", which significantly shortens the problem investigation cycle (from days / weeks to hours / days) and reduces R&D risks and costs.

[0024] 4. Knowledge Accumulation and Process Standardization: This method solidifies expert experience into the system and algorithm, reduces dependence on others, achieves standardization of testing processes and efficient knowledge transfer, and generates standardized reports that directly support airworthiness compliance verification. Attached Figure Description

[0025] Figure 1 This is the overall flowchart of the multi-stage automated testing method described in this invention.

[0026] Figure 2 This is a schematic diagram of the structure of the multi-stage automated testing system described in this invention. Detailed Implementation

[0027] Example 1 like Figure 1 As shown, this invention proposes a multi-stage testing method for electromagnetic compatibility between aircraft systems. Through systematic test process design and data-driven intelligent analysis, it changes the traditional model that relies on manual experience. Specifically, it includes the following steps: Step 1: Systematic test planning. Based on the aircraft's system architecture diagram, Interface Control Document (ICD), and system security assessment results, a matrix analysis method is used to automatically construct a system interaction matrix based on "interference source-coupling path-sensitive source." Based on the system interaction matrix, the test planning unit can automatically derive and generate a comprehensive and logically rigorous multi-dimensional test case library.

[0028] It should be noted that the system's interaction matrix can not only identify simple pairwise interference relationships, but also analyze complex coupling relationships generated by the aircraft platform (such as power network, grounding network, and data bus).

[0029] Optionally, the multi-dimensional test case library includes single-system stimulus test cases, multi-system static and dynamic stress test cases, and failure mode test cases.

[0030] Among them, the single-system excitation test cases are used to accurately calibrate the emission characteristics of a single interference source or the immunity threshold of a single sensitive device.

[0031] Multi-system static and dynamic stress test cases are constructed, including dynamic transient stress scenarios with high-power loads (such as engine systems, electric hydraulic pumps, and anti-icing system start-stop), as well as static test scenarios involving the interconnection of multiple aircraft systems under ground power conditions.

[0032] Fault mode test cases, based on security analysis, inject specific faults to verify the EMC characteristics of the system under abnormal conditions.

[0033] Step 2: Multi-stage test execution, including ground static basic testing, static inter-system interference (ISIC) testing, external environment adaptability testing, and dynamic inter-system interference (ISIC) testing. The automated test execution unit completes the corresponding test cases in the multi-dimensional test case library, and collects various data during the process, which are then summarized in the central database.

[0034] It should be noted that the multi-stage testing follows a progressive principle of "from easy to difficult, from inside to outside, and from static to dynamic," and is carried out in four stages in sequence.

[0035] Specifically, step 2 includes: Step 21: First, perform ground static foundation testing on the entire aircraft. The automated test execution unit receives the relevant test cases for ground static foundation testing sent by the test planning unit via Ethernet. The test control host controls the instruments to send control commands to the instrument control module and the data acquisition and synchronization module. The aircraft lap resistance is scanned and measured, and the shielding continuity and impedance of the key cables are measured. At the same time, the lap resistance of the entire aircraft and the shielding effectiveness data of the key cables are collected.

[0036] Step 22: Perform static inter-system interference (ISIC) testing on the entire aircraft. The automated test execution unit receives the relevant test cases for the static inter-system interference (ISIC) test sent by the test planning unit via Ethernet. The test control host controls the system adaptation module (such as through AFDX, ARINC429, discrete I / O interface) and the instrument control module to automatically control each system on the aircraft to enter the predetermined working state. At the same time, the data acquisition and synchronization module collects the performance parameters, power network characteristics, bus data and space electromagnetic field data of all sensitive systems of the aircraft.

[0037] It should be noted that this step is the core of the test, and all operations and data collection are based on precise time-stamp synchronization.

[0038] Step 23: External environment adaptability test. In a dedicated test range, according to the severity level required by the corresponding electromagnetic compatibility standards (such as DO-160G, AC20-158), high intensity radiation field (HIRF) test and lightning indirect effect transient injection test are performed. The automated test execution unit receives the relevant test cases for external environment adaptability test sent by the test planning unit via Ethernet. The test control host sends control commands to the instrument control module and the data acquisition and synchronization module, and collects aircraft system data and monitors functional status throughout the process.

[0039] Step 24: Dynamic Inter-System Interference (ISIC) Test. With the aircraft engine running or in actual flight, the EMC performance data of the critical systems under dynamic environment and mission load conditions are continuously monitored and recorded by the airborne data recording equipment. The data recorded by the airborne data recording equipment can be imported into the central database for final verification and supplementation of test results.

[0040] It should be noted that the airborne data recording equipment is the proprietary equipment of the aircraft being tested.

[0041] Step 3: Intelligent Data Fusion and Fault Diagnosis. First, a central database is established, aggregating massive amounts of data from all stages, excitation and measurement equipment, data acquisition equipment, and various aircraft subsystems. This data is connected to the central database through a system adaptation module. High-precision time synchronization technology is used as keyframes for data association, and the data is cleaned and time-stamped aligned. A multi-source data fusion engine then fuses the data from the central database, forming a unified "test data map" with clear spatiotemporal relationships. Subsequently, an intelligent fault diagnosis model is used for analysis, including a rule engine and a machine learning model, ultimately generating a data analysis set, fault diagnosis results and report data, and recorded issues.

[0042] Among them, the rule engine has a built-in expert knowledge base, which contains the correspondence between common interference patterns, spectral characteristics and system fault manifestations, and can quickly match and alarm for known types of interference.

[0043] Among them, the machine learning model: for unknown or complex interference, unsupervised learning (such as cluster analysis) is used to discover abnormal patterns, or supervised learning is used for root cause inference. By analyzing the fused data, the model can automatically identify the interference source, locate the coupling path, and assess the severity of the interference, and finally output diagnostic results and report data.

[0044] It should be noted that the intelligent data fusion and fault diagnosis are the key technological advantages of this solution.

[0045] Step 4: Automated Report Generation and Closed-Loop Management. The analysis results from the data fusion and analysis unit are transmitted to the report generation and closed-loop management unit via Ethernet. This unit, through its report generator, produces detailed test reports that meet airworthiness certification requirements, including all test data, curves, pass / fail criteria, and diagnostic conclusions. Simultaneously, the report generation and closed-loop management unit provides an interactive visual dashboard for engineers to conduct in-depth analysis. Diagnosed issues are automatically recorded in the issue tracking module, forming an issue and rectification tracking list. This list is then linked back to the test case library via Ethernet, triggering regression testing and forming a complete positive feedback loop of "test-analysis-rectification-verification."

[0046] Example 2 like Figure 2 As shown, this invention provides a multi-stage testing system for electromagnetic compatibility between aircraft systems, including a test planning unit, an automated test execution unit, a data fusion and analysis unit, and a report generation and closed-loop management unit. Specifically, the test planning unit includes a system interaction matrix generator and test case library management software, wherein: The system interaction matrix generator constructs a system interaction matrix based on the aircraft's system architecture diagram, interface control document (ICD), and security analysis results, identifies all potential "interference source-sensitive device" pairs, and automatically generates a multi-dimensional test case library.

[0047] The test case library management software sends test cases to the test control host via Ethernet for execution. Simultaneously, the software receives a list of issues and remediation tracking from the report generation and closed-loop management unit, generates remediation test cases, and sends them to the test control host via Ethernet to trigger regression testing.

[0048] Specifically, the automated test execution unit includes a test control host, an instrument control module, a system adaptation module, and a data acquisition and synchronization module, among which: Test control host: The test control host retrieves test cases from the test planning unit via Ethernet, and also connects with the instrument control module, system adaptation module, and data acquisition and synchronization module via Ethernet to run test sequences and coordinate the entire test process.

[0049] Instrument control module: Based on standard buses such as PXI / LXI, it controls all external test instruments, including spectrum analyzers, oscilloscopes, signal generators, power supply monitors, etc.

[0050] System adaptation module: Through different aircraft bus interface boards (such as AFDX, ARINC 429) and adapters, it achieves connection with the aircraft system and realizes automatic program control, completing the sending of commands to various aircraft subsystems and controlling them to enter preset working states. At the same time, it completes the interface adaptation and docking of the automated execution unit and the data fusion and analysis unit.

[0051] Data Acquisition and Synchronization Module: Synchronizes all acquisition devices using a high-precision time protocol (such as IRIG-B) to ensure all data has a unified timescale. Acquisition devices include spectrum analyzers, signal generators, power quality analyzers, oscilloscopes, bus recorders, near-field probes, etc., responsible for acquiring response data from the physical layer and bus layer.

[0052] Specifically, the data fusion and analysis unit includes a central database, a data fusion engine, and an intelligent fault diagnosis model, among which: Central Database: Stores massive amounts of raw data from all data channels, preprocesses the raw data, and aligns it based on a unified timescale.

[0053] Multi-source data fusion engine: This engine correlates and fuses electromagnetic data, power data, system bus data, and aircraft status data based on time. It extracts key features from the central database, such as noise amplitude at specific frequencies from spectrum data, and error frame rate and specific alarm signals from bus data. Based on time alignment, the multi-source data fusion engine establishes causal relationships between different data features, achieving the fusion of multi-source data.

[0054] Intelligent Fault Diagnosis Model: The model combines a rule engine with a machine learning model for diagnosis. The rule engine quickly matches known interference patterns, while the machine learning model uses clustering, classification, and other algorithms to mine abnormal patterns that cannot be described by simple rules for unknown or complex interference patterns. It automatically locates the interference source and coupling path and outputs diagnostic conclusions.

[0055] Specifically, the report generation and closed-loop management unit is interconnected with the data fusion and analysis unit and the test planning unit via Ethernet. It is responsible for generating reports, visualizing data, and tracking issues, and includes a report generator, interactive visualization dashboards, and an issue tracking module. Report Generator: First, the report generator has built-in standardized report templates that conform to airworthiness standards and is interconnected with the central database and data fusion engine via Ethernet. When a report needs to be generated, the engine automatically extracts the data corresponding to the template from the central database to generate a standardized test report.

[0056] Interactive visualization dashboards: These are comprehensive visualization dashboards composed of multiple related charts (such as spectrograms, time series graphs, system architecture diagrams, data tables, etc.), providing users with an interactive interface. Users can explore the data in depth and view spectrograms, time series curves, correlation analysis results, etc.

[0057] Problem Tracking Module: Records, manages, and tracks the rectification of problems diagnosed by the intelligent fault diagnosis model. It feeds back the problem and rectification tracking list to the test planning unit via Ethernet, generates rectification test cases through the test case library management software, and can trigger regression testing, forming a closed-loop management of test-analysis-rectification-verification.

[0058] Example 3 The specific implementation of this invention is as follows, taking a civil aircraft as an example: First, during the test planning phase, the aircraft's Interface Control Document (ICD) file is imported. The system automatically parses and generates a system interaction matrix, identifying dozens of key interference pairs such as "weather radar" and "satellite receiver", "shortwave radio" and "integrated display system", and generating hundreds of test cases accordingly.

[0059] Next, we enter the test execution phase.

[0060] During the S21 phase, the automated test execution unit automatically scanned and measured 500 preset lap joints across the entire machine, and found 3 lap joint resistances that exceeded the tolerance, which were immediately reported.

[0061] In phase S22, the system executes test cases sequentially. When the test case "Monitoring the signal-to-noise ratio of the Global Positioning System (GPS) during maximum power scanning of the weather radar" is executed, the test control host controls the radar transmission through the control system adapter module and synchronously acquires data from the GPS receiver through the data acquisition and synchronization module. The data fusion and analysis unit detects in real time that the GPS signal-to-noise ratio has dropped beyond the threshold, automatically marks the test case as failed, and records the spectrum data and bus data at that time.

[0062] During the HIRF test in phase S23, the instrument control module of the automated test execution unit controls the antenna and power amplifier in the anechoic chamber to scan according to the predetermined field strength and frequency, while the data acquisition and synchronization module synchronously monitors the status of the aircraft system.

[0063] Then, the S3 data fusion and intelligent diagnostic phase begins. All test data (including failure data recorded in S22) is uploaded to the central database. Through time alignment, it was discovered that the moment the GPS signal-to-noise ratio dropped corresponded precisely to a specific frequency point of radar transmission, and a peak at that frequency was also present in the near-field spectrum collected at the GPS antenna feed line. Based on the "spatial radiation coupling" rule, the fault diagnosis model quickly located the root cause of the problem as radar transmission energy being spatially coupled to the GPS receiving antenna, and provided a rectification suggestion to "check the isolation between the GPS antenna and the radar antenna."

[0064] Finally, in the S4 phase, the system automatically generates a detailed test report, which includes all test results, charts, and diagnostic conclusions and rectification suggestions for the above-mentioned issues.

[0065] In summary, this invention provides a multi-stage testing system for electromagnetic compatibility between aircraft systems. It enables fully automated processing across the entire chain, from test planning, test case generation, test execution, data acquisition to intelligent analysis and report generation, significantly improving testing efficiency and result reliability, thus forming a complete testing solution. This system is an integrated platform combining hardware, software, and algorithms.

Claims

1. A multi-stage testing system for electromagnetic compatibility between aircraft systems, characterized in that, It includes a test planning unit, an automated test execution unit, a data fusion and analysis unit, and a report generation and closed-loop management unit, among which: The test planning unit is interconnected with the automated test execution unit, data fusion and analysis unit, and report generation and closed-loop management unit.

2. The multi-stage testing system according to claim 1, characterized in that, The test planning unit includes a system interaction matrix generator and test case library management software, wherein: The system interaction matrix generator constructs a system interaction matrix based on the aircraft's system architecture diagram, interface control documents, and security analysis results, identifies all potential "interference source-sensitive device" pairs, and automatically generates a multi-dimensional test case library. The test case library management software sends test cases to the test control host via Ethernet for execution; it receives a list of issues and rectification tracking from the report generation and closed-loop management unit, forms rectification test cases, and sends them to the test control host via Ethernet to trigger the completion of regression testing.

3. The multi-stage testing system according to claim 1, characterized in that, The automated test execution unit includes a test control host, an instrument control module, a system adaptation module, and a data acquisition and synchronization module, among which: Test control host: The test control host retrieves test cases from the test planning unit via Ethernet, and also connects with the instrument control module, system adaptation module, and data acquisition and synchronization module via Ethernet to run test sequences and coordinate the entire test process; Instrument control module: Based on a standard bus, it controls all external test instruments, including spectrum analyzers, oscilloscopes, signal generators, and power supply monitors; System adaptation module: Through different aircraft bus interface boards and adapters, it realizes the connection with the aircraft system and realizes automatic program control, completes the sending of instructions to various subsystems of the aircraft, controls them to enter the preset working state, and completes the interface adaptation and docking of the automated execution unit and the data fusion and analysis unit. Data acquisition and synchronization module: Synchronizes all acquisition devices with a high-precision time protocol to ensure that all data has a unified time stamp.

4. The multi-stage testing system according to claim 1, characterized in that, The data fusion and analysis unit comprises a central database, a data fusion engine, and an intelligent fault diagnosis model, among which: Central Database: Stores massive amounts of raw data from all data channels, preprocesses the raw data, and aligns it based on a unified timescale; Multi-source data fusion engine: It correlates and fuses electromagnetic data, power data, system bus data, and aircraft status data based on time; it extracts key features from the central database and establishes causal relationships between different data features based on time alignment, thereby achieving the fusion of multi-source data; Intelligent fault diagnosis model: It adopts a combination of rule engine and machine learning model for diagnosis. The rule engine quickly matches known interference patterns; the machine learning model uses clustering, classification and other algorithms to mine abnormal patterns for unknown or complex interference patterns, automatically locates the interference source and coupling path, and outputs diagnostic conclusions.

5. The multi-stage testing system according to claim 1, characterized in that, The report generation and closed-loop management unit is interconnected with the data fusion and analysis unit and the test planning unit via Ethernet. It is responsible for generating reports, visualizing data, and tracking issues. It includes a report generator, an interactive visualization dashboard, and an issue tracking module. Report Generator: The report generator has built-in standardized report templates that conform to airworthiness standards and is interconnected with the central database and data fusion engine via Ethernet. When a report needs to be generated, the engine will automatically extract the data corresponding to the template from the central database and generate a standardized test report. Interactive Visual Dashboard: A comprehensive visual dashboard composed of multiple related charts, providing users with an interactive interface; Problem Tracking Module: Records, manages, and tracks the rectification of problems diagnosed by the intelligent fault diagnosis model. It feeds back the problem and rectification tracking list to the test planning unit via Ethernet, generates rectification test cases through the test case library management software, and can trigger regression testing, forming a closed-loop management of test-analysis-rectification-verification.

6. A multi-stage testing method for electromagnetic compatibility between aircraft systems, characterized in that, The method is applied to the multi-stage testing system for electromagnetic compatibility between aircraft systems as described in any one of claims 1 to 5, and the method includes: Step 1: Systematic test planning. Based on the aircraft's system architecture diagram, interface control documents, and system security assessment results, a matrix analysis method is used to automatically construct a system interaction matrix based on "interference source-coupling path-sensitive source". Based on the system interaction matrix, the test planning unit automatically derives and generates a multi-dimensional test case library. Step 2: Multi-stage test execution, including ground static basic testing, static inter-system interference testing, external environment adaptability testing, and dynamic inter-system interference testing. The automated test execution unit completes the corresponding test cases in the multi-dimensional test case library, and collects various data during the process, which are then summarized in the central database. Step 3: Intelligent data fusion and fault diagnosis. A central database is established, aggregating data from all stages, excitation and measurement equipment, data acquisition equipment, and various aircraft subsystems. This data is connected to the central database via a system adaptation module. High-precision time synchronization technology is used as the keyframe for data association, and the data is cleaned and time-stamped aligned. A multi-source data fusion engine is used to fuse the data from the central database, forming a test data map. An intelligent fault diagnosis model is employed for analysis, ultimately generating a data analysis set, fault diagnosis results and report data, and recorded issues. Step 4: Automated report generation and closed-loop management. The analysis results of the data fusion and analysis unit are transmitted to the report generation and closed-loop management unit via Ethernet. The report generation and closed-loop management unit can generate detailed reports that meet the airworthiness certification requirements through the report generator.

7. The method according to claim 6, characterized in that, Step 2 includes: Step 21: Conduct ground static foundation tests on the entire aircraft. The automated test execution unit receives the relevant test cases for ground static foundation tests sent by the test planning unit via Ethernet. The test control host controls the instruments to send control commands to the instrument control module and the data acquisition and synchronization module. The aircraft lap resistance is scanned and measured, and the shielding continuity and impedance of the key cables are measured. At the same time, the lap resistance of the entire aircraft and the shielding effectiveness data of the key cables are collected. Step 22: Perform static inter-system interference testing on the entire aircraft. The automated test execution unit receives the relevant test cases for static inter-system interference testing sent by the test planning unit via Ethernet. The test control host controls the system adaptation module and the instrument control module to automatically control each system on the aircraft to enter the predetermined working state. At the same time, the data acquisition and synchronization module collects the performance parameters, power network characteristics, bus data and spatial electromagnetic field data of all sensitive systems of the aircraft. Step 23: External environment adaptability test. In a dedicated test field, according to the severity level required by the corresponding electromagnetic compatibility standard, high-intensity radiation field test and lightning indirect effect transient injection test are performed. The automated test execution unit receives the relevant test cases for external environment adaptability test sent by the test planning unit via Ethernet. The test control host sends control commands to the instrument control module and the data acquisition and synchronization module, and collects aircraft system data and monitors functional status throughout the process. Step 24: Dynamic Inter-System Interference Test. With the aircraft engine running or in actual flight, the EMC performance data of the critical systems under dynamic environment and mission load conditions are continuously monitored and recorded by the airborne data recording equipment. The data recorded by the airborne data recording equipment is imported into the central database for final verification and supplementation of test results.

8. The method according to claim 6, characterized in that, Step 4 also includes: The report generation and closed-loop management unit automatically records the diagnosed problems, forms a problem and rectification tracking list, and links it back to the test case library via Ethernet to trigger the execution of regression tests, forming a complete positive feedback closed loop of "test-analysis-rectification-verification".

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