Electromagnetic pulse environmental risk analysis method, device and computer equipment

Abstract

This application relates to an electromagnetic pulse environment risk analysis method, apparatus, computer equipment, and storage medium. The method comprises the following steps: determining each target device in an aircraft based on the corresponding failure state type of all devices in the aircraft, where the target device refers to the device that will be affected by the electromagnetic pulse environment; establishing an electromagnetic pulse irradiation environment, and determining the environmental value of each target device in the electromagnetic pulse irradiation environment; conducting a simulation test on each target device based on the corresponding environmental value of each target device, and determining the test results; and determining the safety analysis results of each target device based on the test results. Using the simulated environmental quantity as the test input and the test as the primary basis for the evaluation results at each level, the simulation process will be organically combined with the test process in the future, making the overall process more complete and avoiding the limitations of pure testing and pure theoretical analysis. Furthermore, through graded assessment, the assessment process is more standardized and its compliance is verified, making it more targeted than a more general verification method.

Description

Technical Field

[0001] The present application relates to the field of testing technology, and in particular to an electromagnetic pulse environment risk analysis method, apparatus, computer equipment, storage medium, and computer program product. Background Art

[0002] An electromagnetic pulse (EMP) is a sudden, broadband, high-intensity pulse of electromagnetic radiation generated by a nuclear explosion. It can cause electronic equipment to malfunction or even permanently damage it through coupling pathways such as apertures, cables, and antennas. Therefore, an EMP environment is a typical environment aircraft are likely to encounter in actual battlefields and represents a specific risk that could impact aircraft safety. For aircraft, the ability to operate normally and successfully complete strategic missions in an EMP environment is a key indicator of mission reliability and safety.

[0003] In related technologies, aircraft structures are first classified by structural form and electromagnetic coupling pathway, and several typical structural types are selected for analysis of their strong electromagnetic pulse protection characteristics. Then, field strength data for typical structures at different locations on the entire aircraft surface are obtained under full-aircraft irradiation. Finally, simulation results for the entire aircraft and typical structures are summarized. All of this data is derived from software simulations, without experimental verification, making it impossible to assess the practical applicability of the simulation results. Summary of the Invention

[0004] Based on this, it is necessary to provide a safe and reliable electromagnetic pulse environment risk analysis method, device, computer equipment, computer-readable storage medium and computer program product to address the above technical problems.

[0005] In a first aspect, the present application provides a method for analyzing electromagnetic pulse environmental risks. The method comprises:

[0006] Identify each target device in the aircraft based on the corresponding failure status type of all devices in the aircraft. Target devices are devices that may be affected by the electromagnetic pulse environment. The failure status type indicates the type of safety impact that a device failure would have on the aircraft.

[0007] Establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0008] Conduct simulation tests on each target device based on the environmental value corresponding to each target device and determine the test results;

[0009] Based on the test results, determine the safety analysis results of each target device.

[0010] In one embodiment, an aircraft is equipped with a plurality of systems, each system corresponding to a plurality of devices in the aircraft; accordingly, determining each target device in the aircraft based on the failure state type corresponding to all devices in the aircraft includes:

[0011] According to the failure state type corresponding to any device, determine all failure state bottom events of the system corresponding to any device;

[0012] The minimum cut set of all failure state bottom events is calculated, and the equipment affected by the electromagnetic pulse environment in the minimum cut set is taken as the target equipment.

[0013] In one embodiment, a simulation test is performed on each target device according to the environmental value corresponding to each target device to determine the test result, including:

[0014] Determine the test type corresponding to each target device according to the failure state type corresponding to each target device, where the failure state type corresponds to at least one test type;

[0015] The environmental value corresponding to each target device is used as the test value, and the test is performed according to the test type and test value corresponding to each target device to determine the test result.

[0016] In one embodiment, determining a security analysis result of each target device based on the test results includes:

[0017] Determine the safety requirements for each target device based on the test type corresponding to each target device;

[0018] Compare the test results of each target device with the corresponding safety requirements of each target device to determine the safety analysis results.

[0019] In one embodiment, the test type includes at least one of the following three types: device-level test, system-level test, and aircraft-level test;

[0020] Equipment-level testing refers to testing the equipment, system-level testing refers to testing the system corresponding to the equipment, and aircraft-level testing refers to testing the entire aircraft.

[0021] In one embodiment, establishing an electromagnetic pulse irradiation environment and determining an environmental value of each target device in the electromagnetic pulse irradiation environment includes:

[0022] Acquire target electromagnetic pulse signals that meet preset requirements, simulate the corresponding aircraft model based on the target electromagnetic pulse signals, and determine the simulated electromagnetic field strength value of each target device at each preset time;

[0023] Determining the peak value of the simulated electromagnetic field intensity of each target device according to the simulated electromagnetic field intensity value of each target device at each preset time;

[0024] The environmental value of each target device is calculated based on the simulated electromagnetic field intensity peak value of each target device.

[0025] In a second aspect, the present application also provides an electromagnetic pulse environmental risk analysis device. The device comprises:

[0026] a first determination module configured to determine each target device in the aircraft based on the failure status type corresponding to all devices in the aircraft, wherein the target device is a device that may be affected by the electromagnetic pulse environment, and the failure status type is used to indicate the type of safety impact caused by the device failure on the aircraft;

[0027] The second determination module is used to establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0028] A third determination module is used to perform a simulation test on each target device according to the environmental value corresponding to each target device and determine the test result;

[0029] The fourth determination module is used to determine the security analysis result of each target device according to the test results.

[0030] In a third aspect, the present application further provides a computer device. The computer device includes a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the following steps are performed:

[0031] Identify each target device in the aircraft based on the corresponding failure status type of all devices in the aircraft. Target devices are devices that may be affected by the electromagnetic pulse environment. The failure status type indicates the type of safety impact that a device failure would have on the aircraft.

[0032] Establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0033] Conduct simulation tests on each target device based on the environmental value corresponding to each target device and determine the test results;

[0034] Based on the test results, determine the safety analysis results of each target device.

[0035] In a fourth aspect, the present application further provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the following steps:

[0036] Identify each target device in the aircraft based on the corresponding failure status type of all devices in the aircraft. Target devices are devices that may be affected by the electromagnetic pulse environment. The failure status type indicates the type of safety impact that a device failure would have on the aircraft.

[0037] Establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0038] Conduct simulation tests on each target device based on the environmental value corresponding to each target device and determine the test results;

[0039] Based on the test results, determine the safety analysis results of each target device.

[0040] In a fifth aspect, the present application further provides a computer program product. The computer program product includes a computer program that, when executed by a processor, implements the following steps:

[0041] Identify each target device in the aircraft based on the corresponding failure status type of all devices in the aircraft. Target devices are devices that may be affected by the electromagnetic pulse environment. The failure status type indicates the type of safety impact that a device failure would have on the aircraft.

[0042] Establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0043] Conduct simulation tests on each target device based on the environmental value corresponding to each target device and determine the test results;

[0044] Based on the test results, determine the safety analysis results of each target device.

[0045] The aforementioned electromagnetic pulse environmental risk analysis method, apparatus, computer equipment, storage medium, and computer program product identify each target device in the aircraft based on the corresponding failure state type of all devices in the aircraft. Target devices are devices that are susceptible to the electromagnetic pulse environment, and the failure state type indicates the type of safety impact a device failure would have on the aircraft. An electromagnetic pulse irradiation environment is established to determine the environmental value of each target device under the electromagnetic pulse irradiation environment. Based on the corresponding environmental value of each target device, simulation tests are conducted on each target device to determine the test results. Based on the test results, a safety analysis result for each target device is determined. By using the simulated environmental values ​​as test inputs and the tests as the primary basis for the evaluation results at each level, the simulation and testing processes are organically integrated, resulting in a more comprehensive overall process and avoiding the limitations of pure testing and theoretical analysis. Furthermore, through a tiered assessment process, the assessment process is more standardized. The safety level assessment process involved in this method is divided into the equipment, system, and aircraft levels, with tests conducted and compliance verified at each level, making it more targeted than more general verification methods. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 This is an application environment diagram of an electromagnetic pulse environmental risk analysis method in one embodiment;

[0047] Figure 2 1 is a flow chart of an electromagnetic pulse environment risk analysis method according to an embodiment;

[0048] Figure 3 A schematic diagram of an electromagnetic pulse environment in one embodiment;

[0049] Figure 4 A schematic flow chart of an electromagnetic pulse environmental risk analysis method according to another embodiment;

[0050] Figure 5 Schematic diagram of a flow chart of an electromagnetic pulse environment risk analysis method in another embodiment;

[0051] Figure 6 This is a structural block diagram of an electromagnetic pulse environment risk analysis device in one embodiment;

[0052] Figure 7 FIG. 1 is a diagram showing the internal structure of a computer device in one embodiment. DETAILED DESCRIPTION

[0053] In order to make the purpose, technical solutions and advantages of this application more clear, the following further describes this application in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain this application and are not intended to limit this application.

[0054] An electromagnetic pulse (EMP) is a sudden, broadband, high-intensity pulse of electromagnetic radiation generated by a nuclear explosion. It can cause electronic equipment to malfunction or even permanently damage it through coupling pathways such as apertures, cables, and antennas. Therefore, an EMP environment is a typical environment aircraft are likely to encounter in actual battlefields and represents a specific risk that could impact aircraft safety. For aircraft, the ability to operate normally and successfully complete strategic missions in an EMP environment is a key indicator of mission reliability and safety.

[0055] In related technologies, aircraft structures are first classified by structural form and electromagnetic coupling pathway, and several typical structural types are selected for analysis of their strong electromagnetic pulse protection characteristics. Then, field strength data for typical structures at different locations on the entire aircraft surface are obtained under full-aircraft irradiation. Finally, simulation results for the entire aircraft and typical structures are summarized. All of this data is derived from software simulations, without experimental verification, making it impossible to assess the practical applicability of the simulation results.

[0056] The electromagnetic pulse environment risk analysis method provided in the embodiment of the present application can be applied to Figure 1 In the application environment shown. Among them, the terminal 102 communicates with the server 104 through the network. The data storage system can store data that the server 104 needs to process. The data storage system can be integrated on the server 104, or it can be placed on the cloud or other network servers. Among them, the terminal 102 can be, but is not limited to, various personal computers, laptops, smart phones, tablets, Internet of Things devices and portable wearable devices. The Internet of Things devices can be smart speakers, smart TVs, smart air conditioners, smart car-mounted devices, etc. Portable wearable devices can be smart watches, smart bracelets, head-mounted devices, etc. The server 104 can be implemented as an independent server or a server cluster consisting of multiple servers.

[0057] In one embodiment, Figure 2 As shown in the figure, a method for electromagnetic pulse environmental risk analysis is provided, which is applied to Figure 1 Taking the server 104 in the example as an example, the following steps are included:

[0058] Step 202: Determine each target device in the aircraft based on the corresponding failure status type of all devices in the aircraft. The target device is a device that may be affected by the electromagnetic pulse environment. The failure status type indicates the type of safety impact that a device failure would have on the aircraft.

[0059] The failure state type refers to the state of functional failure of the aircraft caused by equipment failure or equipment combination failure. The failure state of the aircraft is analyzed according to the failure state impact level definition table 1. Aircraft systems can be divided into A system and B system according to the severity level of the failure state. Among them, Class A systems are defined as systems whose functional failure will hinder the aircraft from continuing to fly and land safely, that is, Class I failure state; systems whose functional failure will seriously reduce the performance of the aircraft or the flight crew's ability to handle adverse operating conditions are defined as Class B systems, including Class II failure state. Both types of systems are critical systems, and the equipment within them is all target equipment. Therefore, based on the analysis of the aircraft's Class I and Class II failure states, the equipment among all aircraft equipment that needs to be affected by the electromagnetic pulse environment is obtained.

[0060] Table 1 Definition of failure status impact level

[0061]

[0062] It should be noted that before analyzing the specific risks of the aircraft in the electromagnetic pulse environment, a failure risk analysis (FHA) and a safety design and analysis (PSSA) will be conducted on the aircraft and its systems. Therefore, on this basis, the aircraft can be divided into multiple areas according to the overall area division of the aircraft. Then, it is analyzed whether the failure or combination of failures of the equipment in each area will lead to Class I or Class II failure states, thereby determining the key systems and equipment that need to undergo electromagnetic pulse environment compliance verification.

[0063] Step 204: Establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0064] Among them, the electromagnetic pulse irradiation environment refers to the environment formed by the radiation of electromagnetic pulse waves that meet the conditions. For example, it is mentioned in the requirements for electromagnetic emission and sensitivity of aircraft systems. Figure 3 The electromagnetic pulse environment shown in the time domain waveform shows a rise time of approximately 10 ns, a duration (half-peak interval) of approximately 10-30 ns, and a peak electric field strength of 50-100 kV / m. The frequency domain waveform shows a spectrum ranging from DC to 100 MHz (or from 0 to 150 MHz, with 99.9% of the energy below 100 MHz).

[0065] The environmental measurement value of a device refers to the electromagnetic pulse radiation that the device will be exposed to in an electromagnetic pulse environment. Specifically, the entire geometric model of the aircraft is simulated in simulation software, and the electromagnetic pulse simulation signal is used to scan the fuselage. The probe function in the simulation software is used to measure the field strength distribution of each target device, and then the environmental measurement value of each target device is calculated using the shielding effectiveness calculation formula.

[0066] Step 206, performing a simulation test on each target device according to the environmental value corresponding to each target device, and determining the test result;

[0067] It is understood that after simulating each target device to determine the corresponding environmental value, relevant testing is required to confirm the accuracy of the environmental value and verify the device's electromagnetic pulse safety requirements through test results. The electromagnetic pulse safety requirements are determined based on the function of the system in which the device is located.

[0068] Step 208: Determine the security analysis result of each target device based on the test results.

[0069] Specifically, the test results are compared with the specific indicators in the EMP safety requirements to obtain safety analysis results. The safety analysis results can also be used to obtain EMP safety design improvement measures.

[0070] In the method provided in the above embodiment, each target device in the aircraft is identified based on the corresponding failure status type of all devices in the aircraft. Target devices are devices that are affected by the electromagnetic pulse environment, and the failure status type indicates the type of safety impact a device failure would have on the aircraft. An electromagnetic pulse irradiation environment is established to determine the environmental measurement value of each target device in the electromagnetic pulse irradiation environment. Based on the corresponding environmental measurement value of each target device, a simulation test is conducted on each target device to determine the test result. Based on the test result, a safety analysis result for each target device is determined. By using the simulated environmental measurement as the test input and the test as the primary basis for the evaluation results at each level, the simulation and test processes are organically integrated, resulting in a more complete overall process and avoiding the limitations of pure testing and theoretical analysis. Furthermore, through a hierarchical assessment process, the assessment process is more standardized. The safety level assessment process involved in this method is divided into the device level, system level, and aircraft level, with tests conducted and compliance verified at each level, making it more targeted than more general verification methods.

[0071] In one embodiment, the aircraft is equipped with a plurality of systems, each system corresponding to a plurality of devices in the aircraft; accordingly, see Figure 4 , according to the failure status type corresponding to all devices in the aircraft, determine each target device in the aircraft, including:

[0072] Step 402, based on the failure status type corresponding to any device, determine all failure status bottom events of the system corresponding to any device;

[0073] A bottom event refers to the lowest-level event when analyzing aircraft functional failures using a fault tree analysis method. Fault count analysis involves first selecting the system failure with the greatest impact as the top-level event, then gradually decomposing the cause of the system failure into intermediate events until the basic events that cannot or do not need to be decomposed are identified as bottom-level events, thereby forming a tree-like logic diagram. More generally, fault tree analysis uses the fault tree as a foundation to analyze the types of bottom-level events that influence the occurrence of the top-level event and their relative impact. It is understood that in this embodiment, the corresponding device failure is an event. By performing a fault tree analysis on the system where the target device resides, the critical devices in that system can be identified when performing a fault count analysis on the aircraft system.

[0074] Step 404 : Calculate the minimum cut set of all failure state bottom events, and take the devices affected by the electromagnetic pulse environment in the minimum cut set as target devices.

[0075] A cut set, also called a cut-off set or cutoff set, is the set of basic events that lead to the occurrence of the top event. In other words, the occurrence of a set of basic events in the fault tree that can cause the top event is called a cut set. The minimum set of basic events that can cause the top event is called a minimum cut set. In simple terms, a system is constructed through the structured combination of basic modules. However, a failure in one module does not necessarily result in a system failure (here, we define system failure as the inability to complete the system's designed function). For example, a building does not collapse if a brick is lost. Although the building is missing a brick, it still functions as a habitable building without collapsing. However, if certain modules fail, the system will no longer function properly. The set consisting of these specific modules is called a cut set. Therefore, a minimum cut set is defined as one in which any basic module is removed from the cut set, rendering it no longer a cut set. This cut set is called a minimum cut set.

[0076] Specifically, by drawing a fault tree, we find the bottom events contained in the failure state type corresponding to the system where the equipment is located, and calculate the minimum cut set of the bottom event set; based on the above minimum cut set, we filter out the systems containing electronic / electrical equipment and determine the list of critical systems and equipment.

[0077] In the method provided in the above embodiment, all failure state bottom events of the system corresponding to any device are determined based on the failure state type corresponding to any device. The minimum cut set of all failure state bottom events is calculated, and the devices affected by the electromagnetic pulse environment in the minimum cut set are selected as target devices. Using simulation environment variables as test inputs and testing as the primary basis for evaluation results at each level, the simulation and testing processes will be organically integrated in the future, making the overall process more complete and avoiding the limitations of pure testing and pure theoretical analysis. Furthermore, through a hierarchical assessment, the assessment process is more standardized. The safety level assessment process involved in this method is divided into the device level, system level, and aircraft level. Testing is conducted at each level and compliance is verified, making it more targeted than more general verification methods.

[0078] In one embodiment, a simulation test is performed on each target device according to the environmental value corresponding to each target device to determine the test result, including:

[0079] Determine the test type corresponding to each target device according to the failure state type corresponding to each target device, where the failure state type corresponds to at least one test type;

[0080] The environmental value corresponding to each target device is used as the test value, and the test is performed according to the test type and test value corresponding to each target device to determine the test result.

[0081] The test type refers to the scope of the equipment test. The safety level of the aircraft and its systems' EMP protection design is assessed based on the determined EMP analysis targets, aircraft-level simulations, and related test results. For Class A systems, compliance verification is required at the equipment, system, and aircraft levels; for Class B systems, only the equipment itself may be tested.

[0082] Specifically, the EMP environmental value of each target device in step 206 is used as the test value, and the target device is used as the test object to conduct the following tests to verify the compliance of each level of EMP safety requirements and obtain the aircraft EMP safety assessment level results. The specific requirements for each level of safety assessment are as follows:

[0083] ① Conduct equipment-level EMP compliance testing to verify the equipment's compliance with EMP safety requirements. Conduct EMP testing according to the test methods specified in the standard, and verify the equipment's EMP compliance based on the test results.

[0084] ② Conduct system-level EMP compliance verification to verify compliance with EMP safety requirements. Based on the results of the equipment EMP compliance analysis, it is recommended to conduct EMP testing of the integrated system. Class A system EMP testing refers to standard requirements and is conducted using a zoned irradiation method based on simulated or measured EMP environmental conditions in different areas. If system-level EMP testing space is limited, threat irradiation testing can be conducted on any fully functional subsystem.

[0085] ③ Conduct aircraft-level EMP compliance verification to verify compliance with EMP safety requirements. Since domestic testing conditions for full-scale EMP testing are currently unavailable, aircraft-level EMP compliance analysis utilizes simulation to determine whether the aircraft's EMP protection meets requirements. For practical purposes, shielding materials for most electronic products are considered effective only if their shielding effectiveness reaches at least 35dB within the 30-1000MHz frequency range. EMP energy is primarily concentrated in the low-frequency band below 300MHz.

[0086] In one embodiment, based on the test results, a security analysis result of each target device is determined, including:

[0087] Determine the safety requirements for each target device based on the test type corresponding to each target device;

[0088] Compare the test results of each target device with the corresponding safety requirements of each target device to determine the safety analysis results.

[0089] In one embodiment, the test type includes at least one of the following three types: device-level test, system-level test, and aircraft-level test;

[0090] Equipment-level testing refers to testing the equipment, system-level testing refers to testing the system corresponding to the equipment, and aircraft-level testing refers to testing the entire aircraft.

[0091] In the method provided in the above embodiment, the test type corresponding to each target device is determined based on the failure state type corresponding to each target device, and the failure state type corresponds to at least one test type; the environmental quantity value corresponding to each target device is used as the test quantity value, and the test is carried out according to the test type and test quantity value corresponding to each target device to determine the test result. According to the test type corresponding to each target device, the safety requirements corresponding to each target device are determined; the test results of each target device are compared with the safety requirements corresponding to each target device to determine the safety analysis results. With the simulation environment quantity as the test input and the test as the main basis for the evaluation results of each level, the simulation process and the test process will be organically combined in the future, the overall process will be more complete, and the limitations of pure experiments and pure theoretical analysis will be avoided. In addition, through hierarchical assessment, the assessment process is more standardized. The safety level assessment process involved in this method is divided into equipment level, system level, and aircraft level. Tests are carried out at different levels and their compliance is verified. It is more targeted than the general verification method.

[0092] In one embodiment, see Figure 5 , establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment, including:

[0093] Step 502: Acquire a target electromagnetic pulse signal that meets preset requirements, simulate a model corresponding to the aircraft based on the target electromagnetic pulse signal, and determine a simulated electromagnetic field strength value of each target device at each preset time.

[0094] Step 504, determining the simulated electromagnetic field intensity peak value of each target device according to the simulated electromagnetic field intensity value of each target device at each preset time;

[0095] Step 506 : Calculate the environmental value of each target device according to the simulated electromagnetic field intensity peak value of each target device.

[0096] The full aircraft geometry model serves as the basis for electromagnetic pulse simulation analysis. It retains the various aircraft structures, including doors, windows, and vents. For doors, gap models are created. For windows, plexiglass is used with appropriate electromagnetic shielding measures. Shielding mesh is installed for vents.

[0097] A bi-exponential function waveform with a peak value of E0 was used as the target electromagnetic pulse (EMP) signal. By observing the electric field intensity distribution within the aircraft at eight moments: t1 = 0 μs, t2 = 0.05 μs, t3 = 0.1 μs, t4 = 0.2 μs, t5 = 0.3 μs, t6 = 0.4 μs, t7 = 0.5 μs, and t8 = 1 μs, as this plane wave swept across the fuselage, 3D dynamic simulation results were generated. This allowed the identification of compartments with significant fluctuations in electric field intensity, key areas affected by the EMP, and weak links with poor shielding effectiveness. Probes were placed in each compartment to obtain environmental measurements within the EMP environment. Furthermore, because fuel vapors within fuel tanks and the aerial refueling system could ignite when reaching a certain energy level, potentially causing fires or explosions, probes were installed within the fuel tanks on the fuselage and wings, as well as within the aerial refueling system. Specifically, probes were installed within the refueling system and the fuel tank.

[0098] Then, a double exponential function waveform with a peak value of E0 is used as the target electromagnetic pulse signal. The field strength distribution at each probe at eight moments, namely t1 = 0μs, t2 = 0.05μs, t3 = 0.1μs, t4 = 0.2μs, t5 = 0.3μs, t6 = 0.4μs, t7 = 0.5μs and t8 = 1μs, is observed during the process of this plane wave sweeping across the fuselage to determine the simulated electromagnetic field strength value corresponding to each preset moment of the target device.

[0099] A target device is a point on an aircraft. The dynamic change of the field intensity of the probe corresponding to the target device during the duration of the electromagnetic pulse plane wave signal is obtained. Combined with the calculation formula of shielding effectiveness, the peak value of the simulated electromagnetic field intensity of the target device is calculated:

[0100]

[0101] Among them, SE is the shielding effectiveness of the device under test (dB), which is the environmental value at that point; E0 is the received electric field strength without a shielding structure, which is the peak field strength value of the electromagnetic pulse simulation signal source; E1 is the received electric field strength with a shielding structure, which is the peak electric field strength value obtained by simulation at that point.

[0102] In the method provided in the above embodiment, a target electromagnetic pulse signal that meets preset requirements is obtained. Based on the target electromagnetic pulse signal, the corresponding aircraft model is simulated to determine the simulated electromagnetic field strength value of each target device at each preset time; based on the simulated electromagnetic field strength value of each target device at each preset time, the simulated electromagnetic field strength peak value of each target device is determined; and based on the simulated electromagnetic field strength peak value of each target device, the environmental quantity value of each target device is calculated. By using simulated environmental quantities as test inputs and testing as the primary basis for evaluation results at each level, the simulation and testing processes will be organically integrated in the future, making the overall process more complete and avoiding the limitations of pure testing and pure theoretical analysis. Furthermore, through a hierarchical assessment, the assessment process is more standardized. The safety level assessment process involved in this method is divided into the equipment level, system level, and aircraft level, and tests are conducted and their compliance is verified at each level, making it more targeted than general verification methods.

[0103] It should be understood that, although the steps in the flowcharts of the above embodiments are shown in sequence as indicated by the arrows, these steps are not necessarily performed in the order indicated by the arrows. Unless otherwise specified herein, there is no strict order restriction on the execution of these steps, and these steps can be performed in other orders. Moreover, at least a portion of the steps in the flowcharts of the above embodiments may include multiple steps or multiple stages, and these steps or stages are not necessarily performed at the same time, but can be performed at different times. The execution order of these steps or stages is not necessarily to be performed in sequence, but can be performed in turn or alternately with other steps or at least a portion of steps or stages in other steps.

[0104] Based on the same inventive concept, embodiments of the present application also provide an electromagnetic pulse environment risk analysis device for implementing the aforementioned electromagnetic pulse environment risk analysis method. The solution provided by this device is similar to the solution described in the aforementioned method. Therefore, the specific limitations of one or more of the following embodiments of the electromagnetic pulse environment risk analysis device can be found in the aforementioned limitations of the electromagnetic pulse environment risk analysis method and will not be further elaborated here.

[0105] In one embodiment, Figure 6 As shown, an electromagnetic pulse environment risk analysis device is provided, comprising: a first determination module 601, a second determination module 602, a third determination module 603 and a fourth determination module 604, wherein:

[0106] A first determining module 601 is configured to determine each target device in the aircraft based on the failure status type corresponding to all devices in the aircraft. The target device is a device that may be affected by the electromagnetic pulse environment. The failure status type indicates the type of safety impact that a device failure would have on the aircraft.

[0107] The second determination module 602 is used to establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0108] The third determining module 603 is used to perform a simulation test on each target device according to the environmental value corresponding to each target device and determine the test result;

[0109] The fourth determining module 604 is configured to determine a security analysis result of each target device according to the test result.

[0110] In one embodiment, the first determining module 601 is further configured to:

[0111] According to the failure state type corresponding to any device, determine all failure state bottom events of the system corresponding to any device;

[0112] The minimum cut set of all failure state bottom events is calculated, and the equipment affected by the electromagnetic pulse environment in the minimum cut set is taken as the target equipment.

[0113] In one embodiment, the third determining module 603 is further configured to:

[0114] Determine the test type corresponding to each target device according to the failure state type corresponding to each target device, where the failure state type corresponds to at least one test type;

[0115] The environmental value corresponding to each target device is used as the test value, and the test is performed according to the test type and test value corresponding to each target device to determine the test result.

[0116] In one embodiment, the fourth determining module 604 is further configured to:

[0117] Determine the safety requirements for each target device based on the test type corresponding to each target device;

[0118] Compare the test results of each target device with the corresponding safety requirements of each target device to determine the safety analysis results.

[0119] In one embodiment, the third determining module 603 is further configured to: the test type includes at least one of the following three types, the following three types are respectively a device-level test, a system-level test, and an aircraft-level test;

[0120] Equipment-level testing refers to testing the equipment, system-level testing refers to testing the system corresponding to the equipment, and aircraft-level testing refers to testing the entire aircraft.

[0121] In one embodiment, the second determining module 602 is further configured to:

[0122] Acquire target electromagnetic pulse signals that meet preset requirements, simulate the corresponding aircraft model based on the target electromagnetic pulse signals, and determine the simulated electromagnetic field strength value of each target device at each preset time;

[0123] Determining the peak value of the simulated electromagnetic field intensity of each target device according to the simulated electromagnetic field intensity value of each target device at each preset time;

[0124] The environmental value of each target device is calculated based on the simulated electromagnetic field intensity peak value of each target device.

[0125] Each module in the aforementioned electromagnetic pulse environmental risk analysis device can be implemented in whole or in part through software, hardware, or a combination thereof. Each module can be embedded in or independent of a processor within a computer device in hardware form, or can be stored in a computer device memory in software form, allowing the processor to call and execute the corresponding operations of each module.

[0126] In one embodiment, a computer device is provided. The computer device may be a server, and its internal structure diagram may be as follows: Figure 7 As shown. The computer device includes a processor, a memory, and a network interface connected via a system bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program, and a database. The internal memory provides an environment for the operation of the operating system and computer program in the non-volatile storage medium. The database of the computer device is used to store electromagnetic pulse environment measurement data of the device. The network interface of the computer device is used to communicate with an external terminal via a network connection. When the computer program is executed by the processor, an electromagnetic pulse environment risk analysis method is implemented.

[0127] Those skilled in the art will understand that Figure 7 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than shown in the figure, or combine certain components, or have a different component arrangement.

[0128] In one embodiment, a computer device is provided, including a memory and a processor, wherein a computer program is stored in the memory, and when the processor executes the computer program, the following steps are implemented:

[0129] Identify each target device in the aircraft based on the corresponding failure status type of all devices in the aircraft. Target devices are devices that may be affected by the electromagnetic pulse environment. The failure status type indicates the type of safety impact that a device failure would have on the aircraft.

[0130] Establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0131] Conduct simulation tests on each target device based on the environmental value corresponding to each target device and determine the test results;

[0132] Based on the test results, determine the safety analysis results of each target device.

[0133] In one embodiment, an aircraft is equipped with a plurality of systems, each system corresponding to a plurality of devices in the aircraft; accordingly, when a processor executes the computer program, the processor further implements the following steps:

[0134] According to the failure state type corresponding to any device, determine all failure state bottom events of the system corresponding to any device;

[0135] The minimum cut set of all failure state bottom events is calculated, and the equipment affected by the electromagnetic pulse environment in the minimum cut set is taken as the target equipment.

[0136] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0137] Determine the test type corresponding to each target device according to the failure state type corresponding to each target device, where the failure state type corresponds to at least one test type;

[0138] The environmental value corresponding to each target device is used as the test value, and the test is performed according to the test type and test value corresponding to each target device to determine the test result.

[0139] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0140] Determine the safety requirements for each target device based on the test type corresponding to each target device;

[0141] Compare the test results of each target device with the corresponding safety requirements of each target device to determine the safety analysis results.

[0142] In one embodiment, when the processor executes the computer program, the following steps are further implemented: the test type includes at least one of the following three types, the following three types are respectively equipment-level test, system-level test and aircraft-level test;

[0143] Equipment-level testing refers to testing the equipment, system-level testing refers to testing the system corresponding to the equipment, and aircraft-level testing refers to testing the entire aircraft.

[0144] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0145] Acquire target electromagnetic pulse signals that meet preset requirements, simulate the corresponding aircraft model based on the target electromagnetic pulse signals, and determine the simulated electromagnetic field strength value of each target device at each preset time;

[0146] Determining the peak value of the simulated electromagnetic field intensity of each target device according to the simulated electromagnetic field intensity value of each target device at each preset time;

[0147] The environmental value of each target device is calculated based on the simulated electromagnetic field intensity peak value of each target device.

[0148] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the following steps are implemented:

[0149] Identify each target device in the aircraft based on the corresponding failure status type of all devices in the aircraft. Target devices are devices that may be affected by the electromagnetic pulse environment. The failure status type indicates the type of safety impact that a device failure would have on the aircraft.

[0150] Establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0151] Conduct simulation tests on each target device based on the environmental value corresponding to each target device and determine the test results;

[0152] Based on the test results, determine the safety analysis results of each target device.

[0153] In one embodiment, an aircraft is equipped with a plurality of systems, each system corresponding to a plurality of devices in the aircraft; accordingly, when the computer program is executed by a processor, the following steps are further implemented:

[0154] According to the failure state type corresponding to any device, determine all failure state bottom events of the system corresponding to any device;

[0155] The minimum cut set of all failure state bottom events is calculated, and the equipment affected by the electromagnetic pulse environment in the minimum cut set is taken as the target equipment.

[0156] In one embodiment, when the computer program is executed by a processor, the following steps are further implemented:

[0157] Determine the test type corresponding to each target device according to the failure state type corresponding to each target device, where the failure state type corresponds to at least one test type;

[0158] The environmental value corresponding to each target device is used as the test value, and the test is performed according to the test type and test value corresponding to each target device to determine the test result.

[0159] In one embodiment, when the computer program is executed by a processor, the following steps are further implemented:

[0160] Determine the safety requirements for each target device based on the test type corresponding to each target device;

[0161] Compare the test results of each target device with the corresponding safety requirements of each target device to determine the safety analysis results.

[0162] In one embodiment, when the computer program is executed by the processor, the following steps are further implemented: the test type includes at least one of the following three types, the following three types are respectively equipment-level test, system-level test and aircraft-level test;

[0163] Equipment-level testing refers to testing the equipment, system-level testing refers to testing the system corresponding to the equipment, and aircraft-level testing refers to testing the entire aircraft.

[0164] In one embodiment, when the computer program is executed by a processor, the following steps are further implemented:

[0165] Acquire target electromagnetic pulse signals that meet preset requirements, simulate the corresponding aircraft model based on the target electromagnetic pulse signals, and determine the simulated electromagnetic field strength value of each target device at each preset time;

[0166] Determining the peak value of the simulated electromagnetic field intensity of each target device according to the simulated electromagnetic field intensity value of each target device at each preset time;

[0167] The environmental value of each target device is calculated based on the simulated electromagnetic field intensity peak value of each target device.

[0168] In one embodiment, a computer program product is provided, comprising a computer program, which, when executed by a processor, implements the following steps:

[0169] Identify each target device in the aircraft based on the corresponding failure status type of all devices in the aircraft. Target devices are devices that may be affected by the electromagnetic pulse environment. The failure status type indicates the type of safety impact that a device failure would have on the aircraft.

[0170] Establish an electromagnetic pulse irradiation environment and determine the environmental value of each target device under the electromagnetic pulse irradiation environment;

[0171] Conduct simulation tests on each target device based on the environmental value corresponding to each target device and determine the test results;

[0172] Based on the test results, determine the safety analysis results of each target device.

[0173] In one embodiment, an aircraft is equipped with a plurality of systems, each system corresponding to a plurality of devices in the aircraft; accordingly, when the computer program is executed by a processor, the following steps are further implemented:

[0174] According to the failure state type corresponding to any device, determine all failure state bottom events of the system corresponding to any device;

[0175] The minimum cut set of all failure state bottom events is calculated, and the equipment affected by the electromagnetic pulse environment in the minimum cut set is taken as the target equipment.

[0176] In one embodiment, when the computer program is executed by a processor, the following steps are further implemented:

[0177] Determine the test type corresponding to each target device according to the failure state type corresponding to each target device, where the failure state type corresponds to at least one test type;

[0178] The environmental value corresponding to each target device is used as the test value, and the test is performed according to the test type and test value corresponding to each target device to determine the test result.

[0179] In one embodiment, when the computer program is executed by a processor, the following steps are further implemented:

[0180] Determine the safety requirements for each target device based on the test type corresponding to each target device;

[0181] Compare the test results of each target device with the corresponding safety requirements of each target device to determine the safety analysis results.

[0182] In one embodiment, when the computer program is executed by the processor, the following steps are further implemented: the test type includes at least one of the following three types, the following three types are respectively equipment-level test, system-level test and aircraft-level test;

[0183] Equipment-level testing refers to testing the equipment, system-level testing refers to testing the system corresponding to the equipment, and aircraft-level testing refers to testing the entire aircraft.

[0184] In one embodiment, when the computer program is executed by a processor, the following steps are further implemented:

[0185] Acquire target electromagnetic pulse signals that meet preset requirements, simulate the corresponding aircraft model based on the target electromagnetic pulse signals, and determine the simulated electromagnetic field strength value of each target device at each preset time;

[0186] Determining the peak value of the simulated electromagnetic field intensity of each target device according to the simulated electromagnetic field intensity value of each target device at each preset time;

[0187] The environmental value of each target device is calculated based on the simulated electromagnetic field intensity peak value of each target device.

[0188] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, stored data, displayed data, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties.

[0189] Those skilled in the art will appreciate that all or part of the processes in the above-mentioned embodiment methods can be implemented by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, database or other media used in the embodiments provided in this application may include at least one of non-volatile and volatile memory. Non-volatile memory may include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetic random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory may include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM). The database involved in the various embodiments provided herein may include at least one of a relational database and a non-relational database. Non-relational databases may include, but are not limited to, distributed databases based on blockchains. The processor involved in the various embodiments provided herein may be, but are not limited to, a general-purpose processor, a central processing unit, a graphics processing unit, a digital signal processor, a programmable logic unit, a data processing logic unit based on quantum computing, and the like.

[0190] The technical features of the above embodiments can be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0191] The above-described embodiments merely represent several implementation methods of the present application. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present application. It should be noted that a person of ordinary skill in the art may make various modifications and improvements without departing from the spirit of the present application, and these modifications and improvements fall within the scope of protection of the present application. Therefore, the scope of protection of the present application shall be determined by the appended claims.

Claims

1. A method for analyzing electromagnetic pulse environmental risk, characterized in that: The method comprises: determining each target device in the aircraft based on failure status types corresponding to all devices in the aircraft, wherein the target device refers to a device that may be affected by the electromagnetic pulse environment, and the failure status type indicates the type of safety impact caused by the device failure on the aircraft; Establishing an electromagnetic pulse irradiation environment and determining an environmental value of each target device under the electromagnetic pulse irradiation environment; Conduct simulation tests on each target device based on the environmental value corresponding to each target device and determine the test results; Based on the test results, a safety analysis result of each target device is determined.

2. The method according to claim 1, characterized in that The aircraft is equipped with a plurality of systems, each system corresponding to a plurality of devices in the aircraft; accordingly, determining each target device in the aircraft according to the failure state type corresponding to all devices in the aircraft includes: Determine all failure status bottom events of the system corresponding to any device according to the failure status type corresponding to the device; The minimum cut set of all failure state bottom events is calculated, and the equipment affected by the electromagnetic pulse environment in the minimum cut set is used as the target equipment.

3. The method according to claim 2, characterized in that The step of performing a simulation test on each target device according to the environmental value corresponding to each target device and determining the test result includes: Determining a test type corresponding to each target device according to a failure state type corresponding to each target device, wherein the failure state type corresponds to at least one test type; The environmental value corresponding to each target device is used as the test value, and the test is performed according to the test type and test value corresponding to each target device to determine the test result.

4. The method according to claim 3, characterized in that Determining the security analysis results of each target device based on the test results includes: Determine the safety requirements for each target device based on the test type corresponding to each target device; Compare the test results of each target device with the corresponding safety requirements of each target device to determine the safety analysis results.

5. The method according to claim 3, characterized in that The test type includes at least one of the following three types, the following three types are equipment-level test, system-level test and aircraft-level test; The device-level test refers to testing the device, the system-level test refers to testing the system corresponding to the device, and the aircraft-level test refers to testing the entire aircraft.

6. The method according to claim 1, wherein The step of establishing an electromagnetic pulse irradiation environment and determining an environmental value of each target device under the electromagnetic pulse irradiation environment includes: Acquire a target electromagnetic pulse signal that meets preset requirements, simulate a model corresponding to the aircraft based on the target electromagnetic pulse signal, and determine a simulated electromagnetic field strength value of each target device at each preset time; Determining the peak value of the simulated electromagnetic field intensity of each target device according to the simulated electromagnetic field intensity value of each target device at each preset time; The environmental value of each target device is calculated based on the simulated electromagnetic field intensity peak value of each target device.

7. An electromagnetic pulse environmental risk analysis device, characterized in that: The device comprises: a first determining module configured to determine each target device in the aircraft based on a failure status type corresponding to all devices in the aircraft, wherein the target device is a device that may be affected by an electromagnetic pulse environment, and the failure status type indicates a type of safety impact caused to the aircraft by a device failure; A second determination module is configured to establish an electromagnetic pulse irradiation environment and determine an environmental value of each target device under the electromagnetic pulse irradiation environment; A third determination module is used to perform a simulation test on each target device according to the environmental value corresponding to each target device and determine the test result; The fourth determining module is used to determine the security analysis result of each target device according to the test result.

8. A computer device comprising a memory and a processor, wherein the memory stores a computer program, wherein: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 6 are implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

10. A computer program product comprising a computer program, characterized in that When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

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