A seakeeping electromagnetic signature pre-test system, method and medium

Abstract

This application relates to an airworthiness electromagnetic characteristic pre-testing system, method, and medium, belonging to the field of airworthiness testing technology for airborne equipment. The airworthiness electromagnetic characteristic pre-testing system includes: a magnetic effect safety pre-testing module, which determines or verifies the deployment position of airborne equipment that does not interfere with nearby equipment; a power input safety pre-testing module, which simulates and verifies the working state of airborne equipment under different extreme conditions in the aviation operating environment; a voltage spike safety pre-testing module, which tests the performance of airborne equipment when its power line receives spike interference; and a main control connection module, which regulates the operating condition simulation parameters, test interaction progress, and simulation test results of each test module according to the airworthiness electromagnetic characteristic test standards, and generates an airworthiness electromagnetic characteristic test report. Through the main control connection module, based on scenario simulation algorithms and synchronous control technology, the magnetic effect, power input, and voltage spike test modules are integrated to realize automated, multi-dimensional pre-testing and data fusion of the electromagnetic characteristics of airborne equipment.

Description

Technical Field

[0001] This application relates to the field of airworthiness testing technology for airborne equipment, and in particular to an airworthiness electromagnetic characteristics pre-testing system, method and medium. Background Technology

[0002] When airborne equipment operates in lightning or complex electromagnetic environments, it is susceptible to magnetic interference, power fluctuations, voltage spikes, and other factors, which can lead to malfunctions, loss of control, or even serious accidents such as accidental triggering of fuses. According to the RTCA / DO-160G standard, airborne equipment must pass three core electromagnetic characteristic tests—magnetic effects, power input, and voltage spikes—to obtain airworthiness certification.

[0003] Existing patents disclose a novel online testing system for airborne electrical equipment under mechanical conditions. Specifically, it is an online testing method capable of detecting potential reversible failures of airborne electrical equipment in mechanical environments. The system includes a main control computer, an optical fiber communication module, a switch network module, a data acquisition module, a signal conditioning module, a test interface module, and a test power supply module. It detects reversible failures of the tested object, meeting the testing requirements of new airborne electrical equipment under mechanical conditions. It can cover various models of tested airborne electrical equipment, exhibiting high versatility and standardization. The fully automated testing process significantly reduces the testing workload and greatly improves testing efficiency. It is a novel online testing system characterized by high stability, strong versatility, strong scalability, rich functionality, convenient operation, high testing accuracy, stable and reliable test results, and high cost-effectiveness.

[0004] The existing technical solutions mentioned above have the following drawbacks: 1. Existing test systems lack integrated design, test equipment is scattered and occupies a large area, test scenarios need to be switched frequently, operation is cumbersome and inefficient; 2. Test accuracy and automation are insufficient, manual configuration of test parameters and switching of circuit topology are prone to human error, data acquisition and analysis are separated, it is difficult to quickly generate standardized test reports, and it cannot meet the iterative needs of design-verification-improvement in the development stage of airborne equipment. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this application is to provide an airworthiness electromagnetic characteristic pre-testing system, method, and medium. Through modular integrated design, it integrates three types of airworthiness electromagnetic characteristic tests—magnetic effect, power input, and voltage spike—into one system, eliminating the need for separate equipment switching, greatly simplifying test operations, improving test efficiency, and meeting the rapid iterative verification needs of airborne equipment development.

[0006] This was achieved using the following technical solutions: In a first aspect, this application provides an airworthiness electromagnetic characteristics pre-testing system, comprising: The magnetic effect safety pre-test module has a bidirectional connection between the signal communication terminal and the first communication terminal of the main control connection module. It is used to determine or verify the deployment position of the airborne equipment so as not to interfere with the nearby equipment. The power input safety pre-test module is bidirectionally connected to the second communication terminal of the main control module, and is used to simulate and verify the working status of airborne equipment under different extreme conditions in the aviation operating environment. The voltage spike safety pre-test module is bidirectionally connected to the third communication terminal of the main control module and is used to test the performance of airborne equipment when the power line receives spike interference. The main control module is used to adjust the operating condition simulation parameters, test interaction progress, and simulation test results of the above-mentioned safety pre-test modules according to the airworthiness electromagnetic characteristics test standards, and generate an airworthiness electromagnetic characteristics test report.

[0007] By adopting the above technical solution, and integrating magnetic effect, power input and voltage spike test modules through the main control connection module based on scenario simulation algorithm and synchronous control technology, the electromagnetic characteristics of airborne equipment can be automatically and multi-dimensionally pre-tested and data fused, and finally a test report that meets airworthiness standards can be generated, which significantly improves the comprehensiveness, efficiency and reliability of the test.

[0008] Furthermore, the magnetic effect safety pre-test module includes: The magnetic orientation detection unit is used to detect the azimuth angle of the magnetic effect generated by airborne equipment and nearby equipment. The magnetic field calibration unit is used to measure the strength of the ambient magnetic field and provide reference magnetic field data for airworthiness electromagnetic characteristic testing; The magnetic field generating unit is used to generate a standard alternating magnetic field in different frequency ranges to simulate interference sources. The magnetic field sensing unit is used to detect or measure the alternating magnetic field strength of interference sources, airborne equipment, and nearby equipment in different frequency ranges. The positioning verification unit is used to determine and verify the deployment location of airborne equipment based on the magnetic effect azimuth, ambient magnetic field strength, and alternating magnetic field strength.

[0009] By adopting the above technical solution, based on multi-source sensor data fusion and controllable electromagnetic environment construction algorithm, and by integrating magnetic direction detection, magnetic field calibration and generation, and multi-frequency point induction measurement, the automated and precise closed-loop verification of the electromagnetic compatibility deployment location of airborne equipment is realized, which significantly improves the reliability, adaptability and positioning accuracy of the test.

[0010] Furthermore, the power input safety pre-test module includes: The power supply characteristic simulation power supply unit is used to generate different input power for airborne equipment in a simulated aviation operating environment. The test configuration control unit is used to configure different airborne equipment, equipment accessories and circuits according to the airworthiness electromagnetic characteristics test items, and to build the test circuit topology. The power supply characteristic analysis unit is used to perform AC and DC parameter testing and power supply characteristic analysis on the input power supply according to the test circuit topology. The test, verification and evaluation unit is used to control the above units to complete the power input safety pre-test under different transient and extreme conditions.

[0011] By adopting the above technical solutions, based on parameterized power supply simulation algorithms and dynamic topology reconstruction technology, the input power supply under different transient and extreme conditions in the aviation environment is simulated. Combined with AC / DC characteristic analysis algorithms, in-depth evaluation of equipment performance is achieved, thereby constructing an automated, multi-scenario closed-loop verification system for power input safety, which significantly improves the coverage, accuracy and efficiency of testing.

[0012] Furthermore, the voltage spike safety pre-test module includes: The spike signal generation unit is used to generate corresponding spike voltage waveforms based on different voltage waveform parameters; The spike signal test unit is used to generate spike test signals and construct spike test procedures based on transient pulse waveform tests combined with spike voltage waveforms. The signal calibration test unit is used to perform anti-interference calibration on the spike test signal to obtain a standard spike signal; The digital oscilloscope unit is used to monitor airborne equipment and obtain equipment operation signals by combining the peak test procedure with standard peak signals.

[0013] By adopting the above technical solution, adjustable peak voltages are generated based on parameterized waveform synthesis and precise timing control algorithms. Filter calibration and real-time monitoring and analysis technologies are used to achieve automated closed-loop verification of anti-interference capabilities, significantly improving the accuracy, efficiency, and reliability of the test.

[0014] Furthermore, the main control connection module includes: The test analysis unit is used to analyze the airworthiness electromagnetic characteristics test and extract the electromagnetic characteristics test process; Extraction and classification units are used to extract parameters and classify operating conditions in the electromagnetic characteristic test process to obtain operating condition simulation parameters. The hardware determination unit is used to screen test hardware based on operating condition simulation parameters and equipment identification, and to build an airborne equipment monitoring architecture. The parameter control unit is used to correct the operating condition simulation parameters according to the airworthiness electromagnetic characteristics test standards and the airborne equipment monitoring architecture to obtain the corrected operating condition parameters. The process monitoring unit is used to perform safety tests on airborne equipment based on the corrected operating parameters and to collect the test interaction progress of the airborne equipment. The test clustering unit is used to cluster the test interaction progress according to the test type, obtain several test progress tables, and extract the corresponding test progress identifiers. The evaluation and verification unit is used to determine the equipment operation signals based on the test pass criteria and test progress indicators, obtain the simulated test results, and generate an airworthiness electromagnetic characteristics test report.

[0015] By adopting the above technical solution, based on the airworthiness standard analysis and multi-source test data fusion algorithm, and through the coordinated control of the magnetic effect, power input and voltage spike test units by the main control module, the multi-physics field and multi-condition closed-loop verification and automated evaluation of the electromagnetic characteristics of airborne equipment can be realized, which significantly improves the comprehensiveness, accuracy and airworthiness compliance efficiency of the test.

[0016] Furthermore, the process monitoring unit includes: The parameter parsing layer is used to decompose the modified operating condition parameters according to the operating condition type and extract the operating condition test signal; The topology identification layer is used to identify and switch the test signals under operating conditions according to the airworthiness electromagnetic characteristics test standards to obtain the test topology configuration. The waveform synthesis layer is used to generate test input waveforms based on the test signals and corresponding test equipment. The collaborative auxiliary layer is used to decouple and filter the test input waveform according to the test topology to obtain a dedicated test waveform. The test access layer is used to perform safety tests on airborne equipment based on dedicated test waveforms, forming phased test nodes. The hierarchical monitoring layer is used to monitor the timing of stage test nodes and obtain the stage operation status of the equipment; The dynamic tracking layer is used to provide interactive feedback and data collection on the phase operation status, record equipment response data and key test events, and form a test interaction progress.

[0017] By adopting the above technical solutions, test parameter parsing, topology reconstruction and waveform generation are realized based on timing control and dynamic scheduling algorithms. Multi-channel data acquisition and status tracking algorithms are used to monitor equipment response and key events in real time, ultimately forming a closed-loop test interaction progress feedback mechanism, which significantly improves the automation, refinement and collaborative management level of the test process.

[0018] Further, the evaluation and verification unit includes: The task binding layer is used to bind the test pass criteria to the device timestamp based on the test progress indicator, thus forming the test time criteria; The topology configuration layer is used to switch the test topology configuration according to the test items, and in conjunction with the decoupling filter component, generate the target test configuration and output the target test signal; The synchronous acquisition layer is used to test airborne equipment based on target test signals and extract equipment operating signals; The judgment and comparison layer is used to extract the corresponding test time criteria based on the test items and compare them item by item with the steady-state range, transient occurrence time, duration and / or recovery time of the equipment operation signal; If all time test criteria are passed, the current airborne equipment is deemed qualified; otherwise, the current airborne equipment is deemed unqualified, and the equipment failure mode is recorded. The report generation layer is used to encapsulate the simulation test results, test item list, and equipment operation signals in a time sequence to generate an airworthiness electromagnetic characteristics test report.

[0019] By adopting the above technical solution, based on time alignment and feature comparison algorithms, and by accurately matching test criteria and equipment response signals, combined with decoupling filtering and multi-channel synchronous acquisition technology, automated judgment and failure mode recording are achieved, and finally a structured test report is generated, which significantly improves the accuracy, automation level and traceability of the test results.

[0020] Secondly, this application also provides a method for pre-testing airworthiness electromagnetic characteristics, which adopts the following technical solution; A method for pre-testing airworthiness electromagnetic characteristics includes: The system detects the azimuth angle of the magnetic effects generated by airborne and nearby equipment, measures the ambient magnetic field strength, and generates a standard alternating magnetic field in different frequency ranges to simulate interference sources. Detect or measure the alternating magnetic field strength of interference sources, airborne equipment, and nearby equipment in different frequency ranges; The deployment location of airborne equipment is determined and verified based on the magnetic effect azimuth, ambient magnetic field strength, and alternating magnetic field strength. In a simulated aviation operating environment, different input power supplies are generated for airborne equipment. Based on the test items, different airborne equipment and lines are configured and the test circuit topology is constructed. Based on the test circuit topology, AC and DC parameters of the input power supply are tested and power supply characteristics are analyzed. Based on different voltage waveform parameters, corresponding peak voltage waveforms are generated, and combined with transient pulse waveform experiments, peak test signals are generated to construct a peak test process; The spike test signal is calibrated, and the airborne equipment is monitored in conjunction with the spike test process to obtain the equipment operation signal; Based on the operating condition type, analyze the airworthiness electromagnetic characteristic test, extract the electromagnetic characteristic test process, and obtain the operating condition simulation parameters; Based on the operating condition simulation parameters and equipment identification, test hardware was selected, and an airborne equipment monitoring architecture was constructed. Based on the airworthiness electromagnetic characteristics test standards and the airborne equipment monitoring architecture, the modified operating condition simulation parameters were obtained. Safety tests were conducted on the airborne equipment based on the corrected operating parameters, and the test interaction progress of the airborne equipment was collected. Cluster the test interaction progress according to the test type to obtain several test progress tables, and extract the corresponding test progress identifiers. Based on the test pass criteria and test progress indicators, the equipment operation signals are judged to obtain the simulated test results and generate an airworthiness electromagnetic characteristics test report.

[0021] By adopting the above technical solution, based on parametric simulation and multi-physics field collaborative control algorithm, and integrating magnetic effect, power input and voltage spike test modules, the system can realize comprehensive closed-loop verification and evaluation of the electromagnetic characteristics of airborne equipment in aviation environment through automated construction of test topology, dynamic correction of operating parameters, and synchronous acquisition and analysis of equipment response. This significantly improves the automation level, coverage and airworthiness compliance efficiency of the test.

[0022] Thirdly, this application also provides a storage medium storing at least one instruction, at least one program, code set, or instruction set, wherein the at least one instruction, at least one program, code set, or instruction set is loaded and executed by a processor to implement the airworthiness electromagnetic characteristics pre-testing method as described above.

[0023] In summary, the beneficial technical effects of this application are as follows: By integrating magnetic effect, power input and voltage spike test modules through the main control connection module based on scenario simulation algorithm and synchronous control technology, the system realizes automated, multi-dimensional pre-testing and data fusion of electromagnetic characteristics of airborne equipment, and finally generates a test report that meets airworthiness standards, which significantly improves the comprehensiveness, efficiency and reliability of the test. Based on timing control and dynamic scheduling algorithms, test parameter parsing, topology reconstruction and waveform generation are realized. Multi-channel data acquisition and status tracking algorithms are used to monitor equipment response and key events in real time, and finally a closed-loop test interaction progress feedback mechanism is formed, which significantly improves the automation, refinement and collaborative management level of the test process. By using high-precision testing equipment and automated control software, precise control of test parameters, synchronous acquisition and real-time analysis of test data are achieved, resulting in high testing accuracy, effectively reducing human error, and ensuring the reliability and consistency of test results. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the airworthiness electromagnetic characteristics pre-testing system in this application; Figure 2 This is a schematic diagram of the main control connection module in this application; Figure 3 This is a schematic diagram of the process monitoring unit in this application; Figure 4 This is a schematic diagram of the structure of the evaluation and verification unit in this application; Figure 5 This is a flowchart illustrating the airworthiness electromagnetic characteristic pre-testing method in this application. Detailed Implementation

[0025] The present application will be further described in detail below with reference to the accompanying drawings.

[0026] Reference Figure 1 This application discloses an airworthiness electromagnetic characteristics pre-testing system, comprising: The magnetic effect safety pre-test module has a bidirectional connection between the signal communication terminal and the first communication terminal of the main control connection module. It is used to determine or verify the deployment position of the airborne equipment so as not to interfere with the nearby equipment. The power input safety pre-test module is bidirectionally connected to the second communication terminal of the main control module, and is used to simulate and verify the working status of airborne equipment under different extreme conditions in the aviation operating environment. The voltage spike safety pre-test module is bidirectionally connected to the third communication terminal of the main control module and is used to test the performance of airborne equipment when the power line receives spike interference. The main control module is used to adjust the operating condition simulation parameters, test interaction progress, and simulation test results of the above-mentioned safety pre-test modules according to the airworthiness electromagnetic characteristics test standards, and generate an airworthiness electromagnetic characteristics test report.

[0027] In this embodiment, the magnetic effect safety pre-test module is used to determine the minimum safe installation distance between airborne equipment and a magnetic compass / magnetic flux gate. It includes a high-precision compass, a calibration kit, and magnetic effect testing accessories. The high-precision compass is model HEC366, with an azimuth measurement range of 360°, an angular resolution of 0.1°, and a measurement repeatability of ±0.1% (RMS), accurately capturing the magnetic deflection signal generated by the equipment. The calibration kit is model TM4300B, with a magnetic field measurement range of ±100μT and a measurement accuracy of ±1%, used for system calibration before testing. The magnetic effect testing accessories include a ring sensor (4cm diameter, 51 turns) and a magnetic field ring (12cm diameter, 20 turns), covering a frequency range of 25Hz to 100kHz, adaptable to magnetic effect testing of airborne equipment of different sizes. During testing, the main control unit controls the device under test (EUT) to be powered on and in maximum magnetic deflection mode. Magnetic deflection data is collected in real time by the high-precision compass, and combined with the magnetic field calibration data from the calibration kit, the minimum safe distance between the EUT and the magnetic sensor is automatically calculated. The power input safety pre-test module simulates the power input environment of airborne equipment to verify its stability under different power conditions. It includes a power supply characteristic simulation unit, a test configuration control unit, a power characteristic acquisition and analysis unit, and a test verification and evaluation unit. The power supply characteristic simulation unit uses the FDP-3300 high-precision power quality simulator, supporting two power types: 28VDC (output power ≥3kW) and 270VDC (output power ≥30kW). It has a voltage slew rate ≥3V / µs and a DC ripple voltage ≤300mVrms (270VDC) and ≤100mVrms (28VDC). It can simulate 13 types of power input scenarios, including normal steady-state voltage, pulsating voltage, transient interruptions, and surge voltage. The test configuration control unit includes a voltage distortion generator, a configuration topology switching device, and a resistive simulated load device. The voltage distortion generator can produce a distortion spectrum of 10Hz~200kHz with a distortion amplitude of 0~10V. The RMS topology switching device uses a high-voltage DC contactor to automatically switch between three topologies: conventional testing, voltage distortion testing, and resistive load connection. The switching time is ≤5s, and the main circuit current carrying capacity is ≥150A. The power characteristic acquisition and analysis unit uses a PXES-2590 data acquisition host and a ZDL5000 high sampling rate data acquisition module. The voltage test range is ±800V, the current test range is 0~1000A, and the sampling rate is ≥2MS / s / channel. It synchronously acquires parameters such as voltage, current, and frequency and performs time-domain and frequency-domain analysis. The test verification and evaluation unit uses TestManager software, which has a built-in complete waveform library and can automatically control the collaborative work of each unit to generate standardized test reports. The voltage spike safety pre-test module is used to verify the airborne equipment's ability to withstand power line voltage spikes, and includes a voltage spike generator, digital oscilloscope, spike signal test software, and test accessories. The voltage spike generator uses the FSG6000 model, with an output voltage continuously adjustable from 0 to 1000V and a 40% transient overvoltage capability. It can generate two standard spike waveforms (waveform 1: rise time ≤ 2μs, pulse width ≥ 10μs; waveform 2: rise time ≤ 2μs, pulse width ≥ 5μs), with a spike repetition frequency of 1 to 20 times / s and source impedances of 2Ω±10% and 50Ω±10%. The digital oscilloscope uses the SDS5034X model, with 4 channels, an analog bandwidth of 350MHz, and a sampling rate of 5GS / s. It is used in conjunction with a high-voltage differential probe (range ±1000V) to accurately capture spike signals. The test accessories include a 10μF±20% non-polarized feedthrough capacitor, a 5Ω / 50Ω calibration resistor module, and a LISN artificial power network with a maximum continuous current ≥100A, used to suppress power supply interference and calibrate test signals. During testing, the spike signal testing software can set spike parameters, control the generator output signal, collect the response data of the device under test through an oscilloscope, and automatically compare it with the standard curve to complete the evaluation.

[0028] The main control module uses an industrial control computer (processor i7 / E5 or higher, memory ≥16GB, hard disk ≥8TB) and integrates system control software to configure test parameters, schedule test processes, and centrally store and analyze data for the three subsystems. The control software supports user management, task management, and report management functions. It can automatically select test standards, test items, and test sequences according to test requirements, display test data and waveforms in real time, and automatically generate a standardized report containing test parameters, waveforms, and analysis results after the test is completed.

[0029] Preferably, the magnetic effect safety pre-test module includes: The magnetic orientation detection unit is used to detect the azimuth angle of the magnetic effect generated by airborne equipment and nearby equipment. The magnetic field calibration unit is used to measure the strength of the ambient magnetic field and provide reference magnetic field data for airworthiness electromagnetic characteristic testing; The magnetic field generating unit is used to generate a standard alternating magnetic field in different frequency ranges to simulate interference sources. The magnetic field sensing unit is used to detect or measure the alternating magnetic field strength of interference sources, airborne equipment, and nearby equipment in different frequency ranges. The positioning verification unit is used to determine and verify the deployment location of airborne equipment based on the magnetic effect azimuth, ambient magnetic field strength, and alternating magnetic field strength.

[0030] In this embodiment, the magnetic direction detection unit first uses a three-axis fluxgate sensor array to accurately detect the azimuth angle of the background magnetic field at the location of the spare attitude gyroscope to be installed at the nose of the aircraft, and identifies the location of low-frequency magnetic disturbances generated by the hydraulic lines and landing gear door motors in the vicinity. Subsequently, the magnetic field calibration unit measures the ambient magnetic field strength of the area in an interference-free environment in the hangar with a range of 1mT (measured to be approximately 48.2μT), providing accurate reference magnetic field data for subsequent comparisons. The magnetic field generation unit then simulates and generates a standard alternating magnetic field (e.g., amplitude of 200nT at 10Hz and amplitude of 350nT at 60Hz) in the key frequency range of 1Hz to 400Hz using a Helmholtz coil to reproduce electromagnetic interference scenarios under conditions such as landing gear retraction and extension, and high-frequency communication transmission.

[0031] The magnetic field sensing unit synchronously monitors the intensity of the induced magnetic field at the gyroscope installation location under different frequency excitations and finds that its response increases abnormally near 90Hz (reaching 3.8 times the reference value). After comprehensively comparing the magnetic effect azimuth angle, environmental reference, and induction intensity data, the positioning verification unit determines that the location has fallen into the strong influence zone of the hydraulic pump leakage magnetic field (the threshold is set at ±2.0 times the reference value). It is recommended to move the gyroscope installation location 28 cm longitudinally backward along the fuselage to avoid this magnetically sensitive point, thereby ensuring the absolute reliability of the aircraft's heading and attitude data in the real flight environment.

[0032] Preferably, the power input safety pre-test module includes: The power supply characteristic simulation power supply unit is used to generate different input power for airborne equipment in a simulated aviation operating environment. The test configuration control unit is used to configure different airborne equipment, equipment accessories and circuits according to the airworthiness electromagnetic characteristics test items, and to build the test circuit topology. The power supply characteristic analysis unit is used to perform AC and DC parameter testing and power supply characteristic analysis on the input power supply according to the test circuit topology. The test, verification and evaluation unit is used to control the above units to complete the power input safety pre-test under different transient and extreme conditions.

[0033] In this embodiment, during the airworthiness certification test of the avionics system of a new regional jet, the power supply characteristic simulation power supply unit first generates various input power conditions for the flight management computer according to the DO-160G standard, including normal steady state (28V DC), voltage surge (+20% for 50ms), voltage drop (-30% for 100ms), and frequency change (360Hz-800Hz scan) transient waveforms. Subsequently, the test configuration control unit automatically switches the configuration connection between airborne equipment and different accessories (such as spare instruments and servos) and cables (shielded / unshielded) through a solid-state relay matrix according to the requirements of the electromagnetic compatibility test, constructing a complete test circuit topology including power lines, signal lines, and ground loops.

[0034] Based on this, the power characteristic analysis unit used a high-precision power analyzer to perform real-time testing and analysis of the AC and DC parameters of the input power supply (such as the effective value of ripple voltage, harmonic distortion rate, and power factor). It was found that when the 270V high-voltage DC bus dropped at the moment of simulated engine startup, the voltage at the computer input terminal dropped to 18V (below the preset first voltage threshold of 19V) and triggered the reset protection. Finally, the test verification and evaluation unit comprehensively controlled each unit to complete all 12 transient and extreme operating condition power input safety pre-tests. The verification results showed that the device can work normally within a voltage fluctuation range of ±15% (preset safety range). If it exceeds this range (such as voltage below 16V or above 32V), it will automatically switch to safety protection mode, providing complete power characteristic verification data for subsequent airworthiness review.

[0035] Preferably, the voltage spike safety pre-test module includes: The spike signal generation unit is used to generate corresponding spike voltage waveforms based on different voltage waveform parameters; The spike signal test unit is used to generate spike test signals and construct spike test procedures based on transient pulse waveform tests combined with spike voltage waveforms. The signal calibration test unit is used to perform anti-interference calibration on the spike test signal to obtain a standard spike signal; The digital oscilloscope unit is used to monitor airborne equipment and obtain equipment operation signals by combining the peak test procedure with standard peak signals.

[0036] In this embodiment: the spike signal generation unit sets voltage waveform parameters (rise time 2μs, pulse width 10μs, amplitude +600V and -300V) according to the requirements of Section 17 of DO-160G to generate spike voltage waveforms simulating lightning induction and inductive load switching; then the spike signal testing unit couples the generated spike waveform to the 28V DC power input terminal of the flight control computer according to the transient pulse waveform test procedure to construct a complete spike test procedure (applied 50 times each for positive and negative polarities, with an interval of 1 second); the signal calibration test unit performs anti-interference calibration on the test signal through a 50Ω impedance matching network and a common-mode filter circuit to ensure that the spike waveform distortion rate injected into the device is less than 5% (preset calibration tolerance), and obtains a standard spike signal; the digital oscilloscope unit monitors the device operation signal in real time at a sampling rate of 100MHz and records the power supply voltage waveform at each spike injection (observed three device resets, corresponding to spike amplitudes exceeding the preset first tolerance threshold +350V), providing key test data for subsequent power interface protection design improvements.

[0037] Preferably, refer to Figure 2 The main control connection module includes: The test analysis unit is used to analyze the airworthiness electromagnetic characteristics test and extract the electromagnetic characteristics test process; Extraction and classification units are used to extract parameters and classify operating conditions in the electromagnetic characteristic test process to obtain operating condition simulation parameters. The hardware determination unit is used to screen test hardware based on operating condition simulation parameters and equipment identification, and to build an airborne equipment monitoring architecture. The parameter control unit is used to correct the operating condition simulation parameters according to the airworthiness electromagnetic characteristics test standards and the airborne equipment monitoring architecture to obtain the corrected operating condition parameters. The process monitoring unit is used to perform safety tests on airborne equipment based on the corrected operating parameters and to collect the test interaction progress of the airborne equipment. The test clustering unit is used to cluster the test interaction progress according to the test type, obtain several test progress tables, and extract the corresponding test progress identifiers. The evaluation and verification unit is used to determine the equipment operation signals based on the test pass criteria and test progress indicators, obtain the simulated test results, and generate an airworthiness electromagnetic characteristics test report.

[0038] In this embodiment, the main control module comprehensively coordinates various electromagnetic compatibility tests: the test analysis unit first analyzes the electromagnetic characteristic test items required by the RTCA / DO-160G standard, extracting a complete test process covering power spikes, radio frequency susceptibility, and electrostatic discharge; the extraction and classification unit extracts parameters and classifies operating conditions from this process, obtaining operating condition simulation parameters including voltage spike amplitude (±600V), frequency scan range (2MHz-1GHz), and discharge voltage (8kV contact / 15kV air); the hardware determination unit automatically selects and allocates test hardware such as spike generators, radio frequency power amplifiers, and electrostatic discharge guns based on these parameters and the equipment identification of the flight control computer under test, constructing a suitable airborne equipment monitoring frame. The system is structured as follows: The parameter control unit corrects the operating condition simulation parameters (e.g., modulating the RF field strength to 1kHz 80% AM) based on the test severity levels specified in the DO-160G standard (e.g., RF field strength corresponding to the equipment installation area is 20V / m), obtaining corrected operating condition parameters. The process monitoring unit performs safety tests on the airborne equipment based on the corrected parameters, collecting and displaying the interactive progress of each test in real time (e.g., "Peak test executed 30 / 50 times"). The test clustering unit clusters the interactive progress according to the test type, generating several test progress tables such as conducted sensitivity and radiated sensitivity, and extracts the corresponding test progress identifiers. The evaluation and verification unit uses preset test pass criteria (e.g., no equipment reset during test, communication bit error rate ≤10%). -6 The system automatically determines the equipment's operating signals based on power supply voltage fluctuations of ≤±5%, and ultimately generates an airworthiness electromagnetic characteristics test report containing 18 test results and 3 suggested rectification items.

[0039] Preferably, refer to Figure 3 The process monitoring unit includes: The parameter parsing layer is used to decompose the modified operating condition parameters according to the operating condition type and extract the operating condition test signal; The topology identification layer is used to identify and switch the test signals under operating conditions according to the airworthiness electromagnetic characteristics test standards to obtain the test topology configuration. The waveform synthesis layer is used to generate test input waveforms based on the test signals and corresponding test equipment. The collaborative auxiliary layer is used to decouple and filter the test input waveform according to the test topology to obtain a dedicated test waveform. The test access layer is used to perform safety tests on airborne equipment based on dedicated test waveforms, forming phased test nodes. The hierarchical monitoring layer is used to monitor the timing of stage test nodes and obtain the stage operation status of the equipment; The dynamic tracking layer is used to provide interactive feedback and data collection on the phase operation status, record equipment response data and key test events, and form a test interaction progress.

[0040] In this embodiment, the process monitoring unit performs fine-grained control over the correction parameters (such as frequency scan range 80MHz-1GHz, field strength 20V / m, modulation mode 1kHz 80%AM) throughout the entire process: the parameter analysis layer first decomposes the correction parameters into specific test signals according to the operating condition type, and extracts key parameters such as sweep step size (1%), dwell time (2 seconds), and polarization mode (alternating vertical / horizontal); the topology identification layer automatically identifies and switches to the test topology configuration of "antenna-power amplifier-field strength probe" according to the DO-160G test standard; the waveform synthesis layer is based on the test signal parameters... The system calls a vector signal generator to generate a compliant RF modulation waveform (e.g., a field strength of 20V / m at 500MHz). The collaborative auxiliary layer decouples and filters the waveform using a high-pass filter (cutoff frequency 30MHz) to remove low-frequency interference and obtain a dedicated test waveform. The test access layer radiates this waveform to the airborne equipment via an antenna, forming stage test nodes based on frequency points. The hierarchical monitoring layer performs timing monitoring of each stage node every 5 minutes to obtain the equipment's stage operating status (e.g., "CPU load is normal at 500MHz, communication bit error rate rises to 10⁻⁻⁻⁶ at 600MHz"). 4 The dynamic tracking layer provides real-time feedback and collects this response data, recording key test events (such as when the bit error rate exceeds a preset threshold of 10⁻). 5 (Automatic marking of anomalies) ultimately forms a test progress report containing test results for 18 frequency points and 3 anomaly records.

[0041] Preferably, refer to Figure 4 Evaluation and verification unit, including: The task binding layer is used to bind the test pass criteria to the device timestamp based on the test progress indicator, thus forming the test time criteria; The topology configuration layer is used to switch the test topology configuration according to the test items, and in conjunction with the decoupling filter component, generate the target test configuration and output the target test signal; The synchronous acquisition layer is used to test airborne equipment based on target test signals and extract equipment operating signals; The judgment and comparison layer is used to extract the corresponding test time criteria based on the test items and compare them item by item with the steady-state range, transient occurrence time, duration and / or recovery time of the equipment operation signal; If all time test criteria are passed, the current airborne equipment is deemed qualified; otherwise, the current airborne equipment is deemed unqualified, and the equipment failure mode is recorded. The report generation layer is used to encapsulate the simulation test results, test item list, and equipment operation signals in a time sequence to generate an airworthiness electromagnetic characteristics test report.

[0042] In this embodiment, the qualification criteria parameters for this project are automatically loaded from the standard database, including: voltage / frequency limit values ​​(normal / abnormal / emergency steady-state upper and lower limits), modulation amplitude (e.g., voltage modulation 2.5Vrms, frequency modulation 4Hz), distortion spectrum amplitude table (amplitude limits for each harmonic), distortion coefficient limit (e.g., 0.05), DC component limit (±0.1V), transient amplitude and time envelope (e.g., normal voltage transient, abnormal frequency transient 480Hz / 4.68s), interruption / power failure time (50ms, 7s), and reverse polarity protection requirements (no damage or physical reverse connection protection measures). Create a test progress identifier to record information such as the current test phase, elapsed execution time, remaining time, and number of event triggers. Bind the progress identifier to a real-time clock for subsequent time-related criteria such as "not less than the specified time".

[0043] Based on the test requirements, the control system automatically switches to the corresponding test configuration (normal, distortion test, resistive load connection) and connects the necessary decoupling filter components (50μH coil, 10μF / 100μF feedthrough capacitor). Configuration is completed within ≤5 seconds using a high-power contactor matrix, and hardware interlocking and status detection ensure line safety.

[0044] The high-voltage / low-voltage DC source or three-phase intermediate frequency source (AFV-315AYT) outputs the main voltage (e.g., 115V / 400Hz) according to the test requirements; for voltage modulation (SVF104), frequency modulation (SVF105), voltage distortion spectrum (SVF106), voltage distortion coefficient (SVF107), and DC component (SVF108), the required waveforms are generated by the low-frequency signal generator, audio power amplifier, and isolation coupling transformer and superimposed on the main circuit.

[0045] For transients (SVF109, 302, 303, 110) and interruptions (SVF201, 601), the control is achieved by rapidly switching the contactor or by dynamically adjusting the auxiliary source.

[0046] For reverse polarity (SVF603), test by switching the line polarity or applying a reverse voltage.

[0047] Steady-state tests (SVF102, 301, 401): Verify whether the equipment can start normally and operate continuously under the upper and lower limits of voltage / frequency (NLSS / NHSS, ALSS / AHSS, ELSS / EHSS). Judgment criteria: The equipment's operating status signals (such as relay activation, stable output) remain normal; there is no protective shutdown, no performance degradation, and no damage.

[0048] Modulation tests (SVF104, 105): Verify that the device performance remains stable under 2.5Vrms voltage modulation or 4Hz frequency modulation. Judgment criteria: Output voltage / current fluctuations are within the allowable range of the specific specification. Key performance indicators (such as voltage regulation accuracy and frequency tracking error) do not exceed the limits.

[0049] Distortion Test (SVF106, 107): Verifies that the equipment operates normally under the preset distortion spectrum (amplitude of each harmonic) or distortion coefficient of 0.05. Judgment Criteria: The measured distortion waveform is consistent with the standard requirements (through closed-loop control of the distortion generator). The distortion increment of the equipment output waveform does not exceed the limit specified in the dedicated specification.

[0050] DC component test (SVF108): Verify that the equipment shows no saturation or abnormal heating when ±0.1V DC is superimposed. Judgment criterion: If the measured value of the DC component in the AC circuit is ≤0.1V, the equipment is working normally.

[0051] Transient tests (SVF109, 302, 110, 303): Verify equipment performance during and after voltage / frequency transients. Judgment criteria: Transient amplitude and time conform to the standard curve. The equipment should not reset or be damaged during the transient, and should automatically return to normal performance after recovery.

[0052] Interruption / Power Outage Test (SVF201, 601): Verifies the device's recovery capability after a 50ms switching interruption or a 7s power outage. Judgment criteria: During the power outage, the device maintains a specific state according to dedicated specifications (e.g., memory retention). It automatically resumes normal operation after power is restored, without manual intervention.

[0053] Reverse polarity test (SVF603): Verifies that the device is not damaged or has physical reverse protection measures when reverse connected. Judgment criteria: The device does not smoke or burn after reverse connection, or confirms that the input terminal has a reverse protection diode / mechanical foolproof design. The device should still work normally after restoring the correct polarity.

[0054] If all individual criteria are met, the result is deemed "qualified"; if any criterion is not met, the result is deemed "unqualified", and the specific failure mode is recorded.

[0055] The general criterion of "no damage or unsafe condition" is confirmed by real-time monitoring of current / temperature / smoke sensors to ensure there are no abnormalities.

[0056] Reference Figure 5 This application discloses a method for pre-testing airworthiness electromagnetic characteristics, comprising: S1: Detect the azimuth angle of the magnetic effect generated by airborne equipment and nearby equipment, measure the ambient magnetic field strength, generate a standard alternating magnetic field in different frequency ranges, and simulate interference sources. S2: Detect or measure the alternating magnetic field strength of interference sources, airborne equipment and nearby equipment in different frequency ranges; S3: Determine and verify the deployment location of airborne equipment based on the magnetic effect azimuth, ambient magnetic field strength, and alternating magnetic field strength; S4: Generate different input power supplies for airborne equipment under simulated aviation operating environment, configure different airborne equipment and lines according to test items, and build test circuit topology; S5: Perform AC and DC parameter tests and power characteristic analysis on the input power supply according to the test circuit topology; S6: Generate the corresponding peak voltage waveform based on different voltage waveform parameters, and combine it with transient pulse waveform test to generate peak test signal and construct peak test process; S7: Calibrate the spike test signal and, in conjunction with the spike test process, monitor the airborne equipment to obtain the equipment operation signal; S8: Analyze the airworthiness electromagnetic characteristic test according to the operating condition type, extract the electromagnetic characteristic test process, and obtain the operating condition simulation parameters; S9: Select test hardware based on operating condition simulation parameters and equipment identification, and build an airborne equipment monitoring architecture; S10: Based on the airworthiness electromagnetic characteristics test standard and combined with the airborne equipment monitoring architecture, the operating condition simulation parameters are corrected to obtain the corrected operating condition parameters; S11: Conduct safety tests on airborne equipment based on the corrected operating parameters and collect the test interaction progress of the airborne equipment; S12: Cluster the test interaction progress according to the test type to obtain several test progress tables and extract the corresponding test progress identifiers; S13: Based on the test pass criteria and test progress indicators, determine the equipment operation signals, obtain the simulation test results, and generate an airworthiness electromagnetic characteristics test report.

[0057] In this embodiment: First, the magnetic effect azimuth angle generated by nearby equipment such as hydraulic pumps is detected by a three-axis fluxgate sensor (e.g., 50Hz power frequency interference exists in the 35° direction). The ambient magnetic field strength (48.2μT) is measured as a reference. A standard alternating magnetic field (200nT at 10Hz) is generated in the 1Hz-400Hz frequency range to simulate interference sources. At the same time, the alternating magnetic field strength of each device at different frequencies is detected (it is found that the response at 90Hz is 3.8 times the reference). Based on this, the flight control computer is moved 28cm backward to avoid magnetically sensitive points. Then, the power supply characteristics are simulated by the power supply unit to generate normal (28V DC) and transient conditions (voltage surge +20%, drop -30%) for the equipment according to DO-160G. The configuration control unit is tested. The test circuit topology is constructed by automatically switching between shielded and unshielded cable configurations. The power characteristic analysis unit tests and finds that the device resets when the voltage drops to 18V (below the first voltage threshold of 19V). The spike signal generation unit generates spike waveforms with a rise time of 2μs and an amplitude of +600V / -300V. After calibration (distortion rate <5%), these waveforms are injected into the power supply. The digital oscilloscope unit records three device resets when the amplitude exceeds the +350V threshold. The main control connection module analyzes the DO-160G standard to extract operating parameters (e.g., RF field strength 20V / m), filters and constructs the test architecture, corrects the parameters, and performs safety tests on the device. Test progress is collected (e.g., 30 / 50 cycles completed), and clustering is used to generate test progress tables for conducted sensitivity, etc. Finally, based on pass / fail criteria (e.g., bit error rate ≤10%), the test is completed. -6 The system determines the operating signal based on voltage fluctuations ≤ ±5%, and generates a complete airworthiness electromagnetic characteristic test report containing 18 test results and 3 suggested rectification items.

[0058] This application discloses a storage medium storing at least one instruction, at least one program, code set, or instruction set, wherein the at least one instruction, at least one program, code set, or instruction set is loaded and executed by a processor to implement the airworthiness electromagnetic characteristics pre-testing method as described above.

[0059] The embodiments described in this specific implementation are preferred embodiments of this application and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A seakeeping electromagnetic signature pre-test system, characterized by, include: The magnetic effect safety pre-test module has a bidirectional connection between the signal communication terminal and the first communication terminal of the main control connection module. It is used to determine or verify the deployment position of the airborne equipment so as not to interfere with the nearby equipment. The power input safety pre-test module is bidirectionally connected to the second communication terminal of the main control connection module, and is used to simulate and verify the working status of airborne equipment under different extreme conditions in the aviation operating environment. The voltage spike safety pre-test module has a signal communication terminal that is bidirectionally connected to the third communication terminal of the main control connection module, and is used to test the performance of the airborne equipment when the power line receives spike interference. The main control module is used to adjust the operating condition simulation parameters, test interaction progress and simulation test results of the above-mentioned safety pre-test modules according to the airworthiness electromagnetic characteristics test standards, and generate an airworthiness electromagnetic characteristics test report.

2. The airworthiness electromagnetic signature pre-test system of claim 1, wherein, The magnetic effect safety pre-test module includes: The magnetic orientation detection unit is used to detect the azimuth angle of the magnetic effect generated by airborne equipment and nearby equipment. The magnetic field calibration unit is used to measure the strength of the ambient magnetic field and provide reference magnetic field data for airworthiness electromagnetic characteristic testing; The magnetic field generating unit is used to generate a standard alternating magnetic field in different frequency ranges to simulate interference sources. A magnetic field sensing unit is used to detect or measure the alternating magnetic field strength of the interference source, airborne equipment, and nearby equipment in different frequency ranges. The positioning verification unit is used to determine and verify the deployment position of the airborne equipment based on the magnetic effect azimuth, the ambient magnetic field strength, and the alternating magnetic field strength.

3. The airworthiness electromagnetic characteristics pre-testing system according to claim 1, characterized in that, The power input safety pre-test module includes: The power supply characteristic simulation power supply unit is used to generate different input power for airborne equipment in a simulated aviation operating environment. The test configuration control unit is used to configure different airborne equipment, equipment accessories and circuits according to the airworthiness electromagnetic characteristics test items, and to build the test circuit topology. The power supply characteristic analysis unit is used to perform AC and DC parameter testing and power supply characteristic analysis on the input power supply according to the test circuit topology. The test, verification and evaluation unit is used to control the above units to complete the power input safety pre-test under different transient and extreme conditions.

4. The airworthiness electromagnetic characteristics pre-testing system according to claim 1, characterized in that, The voltage spike safety pre-test module includes: The spike signal generation unit is used to generate corresponding spike voltage waveforms based on different voltage waveform parameters; The spike signal test unit is used to generate a spike test signal and construct a spike test process based on the transient pulse waveform test combined with the spike voltage waveform. The signal calibration test unit is used to perform anti-interference calibration on the spike test signal to obtain a standard spike signal. The digital oscilloscope unit is used to monitor the airborne equipment and obtain the equipment operation signal according to the spike test procedure and the standard spike signal.

5. The airworthiness electromagnetic characteristics pre-testing system according to claim 1, characterized in that, The main control connection module includes: The test analysis unit is used to analyze the airworthiness electromagnetic characteristics test and extract the electromagnetic characteristics test process; An extraction and classification unit is used to extract parameters and classify operating conditions in the electromagnetic characteristic test process to obtain operating condition simulation parameters. The hardware determination unit is used to screen test hardware based on the operating condition simulation parameters and equipment identification, and to construct an airborne equipment monitoring architecture. The parameter control unit is used to correct the operating condition simulation parameters according to the airworthiness electromagnetic characteristics test standard and the airborne equipment monitoring architecture to obtain the corrected operating condition parameters. The process monitoring unit is used to perform safety tests on airborne equipment based on the corrected operating condition parameters and to collect the test interaction progress of the airborne equipment. The test clustering unit is used to cluster the test interaction progress according to the test type to obtain several test progress tables and extract the corresponding test progress identifiers. The evaluation and verification unit is used to determine the equipment operation signals based on the test pass criteria and the test progress indicators, obtain the simulated test results, and generate an airworthiness electromagnetic characteristics test report.

6. The airworthiness electromagnetic characteristics pre-testing system according to claim 5, characterized in that, The process monitoring unit includes: The parameter parsing layer is used to decompose the modified operating condition parameters according to the operating condition type and extract the operating condition test signal; The topology identification layer is used to identify and switch the test signals under the operating conditions according to the airworthiness electromagnetic characteristics test standards to obtain the test topology configuration; The waveform synthesis layer is used to generate test input waveforms based on the test signal under the operating conditions and the corresponding test equipment. A collaborative auxiliary layer is used to decouple and filter the test input waveform according to the test topology to obtain a dedicated test waveform. The test access layer is used to perform safety tests on airborne equipment based on the dedicated test waveforms, forming phased test nodes. A hierarchical monitoring layer is used to monitor the timing of the stage test nodes to obtain the stage operation status of the equipment; The dynamic tracking layer is used to provide interactive feedback and data collection on the operational status of the aforementioned stages, record device response data and key test events, and form a test interaction progress.

7. The airworthiness electromagnetic characteristic pre-testing system according to claim 5, characterized in that, The evaluation and verification unit includes: The task binding layer is used to bind the test pass criteria to the device timestamp based on the test progress indicator, thus forming the test time criteria; The topology configuration layer is used to switch the test topology configuration according to the test items, and in conjunction with the decoupling filter component, generate the target test configuration and output the target test signal; The synchronous acquisition layer is used to test the airborne equipment based on the target test signal and extract the equipment operation signal; The comparison layer is used to extract the corresponding test time criteria according to the test items and compare them item by item with the steady-state range, transient occurrence time, duration and / or recovery time of the device operation signal; If all time test criteria are passed, the current airborne equipment is deemed qualified; otherwise, the current airborne equipment is deemed unqualified, and the equipment failure mode is recorded. The report generation layer is used to perform time-series encapsulation of the simulation test results, the test item list, and the operating signals of the equipment to generate an airworthiness electromagnetic characteristics test report.

8. A method for pre-testing airworthiness electromagnetic characteristics, applied to the system described in any one of claims 1-7, characterized in that, include: Detect the azimuth angle of the magnetic effect generated by airborne equipment and nearby equipment, and measure the strength of the ambient magnetic field; A standard alternating magnetic field is generated in different frequency ranges to simulate an interference source; Detect or measure the alternating magnetic field strength of the interference source, airborne equipment, and nearby equipment in different frequency ranges; The deployment location of the airborne equipment is determined and verified based on the magnetic effect azimuth, the ambient magnetic field strength, and the alternating magnetic field strength. In a simulated aviation operating environment, different input power supplies are generated for airborne equipment. Based on the test items, different airborne equipment and lines are configured and the test circuit topology is constructed. Based on the test circuit topology, the input power supply is subjected to AC and DC parameter testing and power supply characteristic analysis. Based on different voltage waveform parameters, corresponding peak voltage waveforms are generated, and combined with transient pulse waveform experiments, peak test signals are generated to construct a peak test process; The spike test signal is calibrated, and the airborne equipment is monitored in conjunction with the spike test procedure to obtain the equipment operation signal.

9. The airworthiness electromagnetic characteristic pre-testing method according to claim 8, characterized in that, The method further includes: Based on the operating condition type, analyze the airworthiness electromagnetic characteristic test, extract the electromagnetic characteristic test process, and obtain the operating condition simulation parameters; Based on the simulated operating conditions parameters and equipment identification, test hardware is selected, and an airborne equipment monitoring architecture is constructed. Based on the airworthiness electromagnetic characteristics test standard and the airborne equipment monitoring architecture, the operating condition simulation parameters are corrected to obtain the corrected operating condition parameters. The airborne equipment is subjected to safety testing based on the corrected operating parameters, and the test interaction progress of the airborne equipment is collected. The test interaction progress is clustered according to the test type to obtain several test progress tables, and the corresponding test progress identifiers are extracted. Based on the test pass criteria and the test progress indicators, the equipment operation signals are judged to obtain the simulated test results and generate an airworthiness electromagnetic characteristics test report.

10. A storage medium storing at least one instruction, at least one program, a code set, or an instruction set, wherein the at least one instruction, the at least one program, the code set, or the instruction set is loaded and executed by a processor to implement the airworthiness electromagnetic characteristics pre-testing method as described in any one of claims 8-9.

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