Electromagnetic pulse protection capability assessment method and device, and electronic equipment

Abstract

The invention provides an electromagnetic pulse protection capability assessment method and device, and electronic equipment. The method comprises the steps of carding a plurality of electromagnetic introduction points corresponding to an aircraft body structure; establishing a protection capability evaluation function corresponding to each electromagnetic introduction point; obtaining an evaluation weight corresponding to each electromagnetic introduction point; and fitting the protection capability evaluation function corresponding to each electromagnetic introduction point through the evaluation weight, and determining an electromagnetic pulse protection capability index corresponding to the whole aircraft body structure. According to the method, the overall electromagnetic pulse protection capability of the aircraft body structure is determined by fitting the protection capabilities of different electromagnetic introduction points corresponding to the aircraft body structure, and quantitative correlation of subsequent analysis of the aircraft protection capability and the cost, weight and volume of protection measures can be effectively supported.

Description

Technical Field

[0001] The present application relates to the technical field of electromagnetic pulse protection capability assessment, and in particular to an electromagnetic pulse protection capability assessment method, device and electronic equipment. Background Art

[0002] Under electromagnetic pulse environment conditions, electronic equipment inside the aircraft is extremely susceptible to interference or even damage, resulting in flight mission failure. The aircraft body structure is the primary checkpoint for electromagnetic pulse protection. Therefore, studying the electromagnetic protection capability of the aircraft body structure is of great significance to evaluating the survivability of the aircraft system in an electromagnetic environment.

[0003] Among the existing evaluation methods for the electromagnetic pulse protection capability of aircraft airframe structures, most methods generally only focus on the shielding effectiveness of a single local structure against electromagnetic pulses. At the same time, there is no further differential analysis of the electromagnetic pulse protection capabilities of different local structures corresponding to the aircraft airframe, and there is a lack of evaluation strategies for the electromagnetic pulse protection capability of the entire aircraft airframe structure.

[0004] In actual engineering applications, it is impossible to obtain quantitative data on the improvement of the electromagnetic pulse protection measures on the overall protection capability of the aircraft body structure, which makes it impossible to accurately carry out further protection design, and it is impossible to effectively support the subsequent analysis of the quantitative relationship between the aircraft's electromagnetic pulse protection capability and the cost, weight, and volume of the protection measures. Summary of the invention

[0005] In view of this, the purpose of the present application is to at least provide an electromagnetic pulse protection capability evaluation method, device and electronic equipment, by fitting the protection capabilities of different electromagnetic introduction points corresponding to the aircraft body structure, to determine the electromagnetic pulse protection capability of the entire aircraft body structure, which can effectively support the subsequent analysis of the quantitative relationship between the aircraft protection capability and the cost, weight and volume of protection measures.

[0006] This application mainly includes the following aspects:

[0007] In a first aspect, an embodiment of the present application provides a method for evaluating electromagnetic pulse protection capability, the method comprising: sorting out multiple electromagnetic introduction points corresponding to the aircraft body structure; establishing a protection capability evaluation function corresponding to each electromagnetic introduction point; obtaining an evaluation weight corresponding to each electromagnetic introduction point; fitting the protection capability evaluation function corresponding to each electromagnetic introduction point through the evaluation weight, and determining the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

[0008] In one possible implementation, the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure is determined in the following manner: for each electromagnetic introduction point, the following processing is performed: obtaining the standard shielding effectiveness index corresponding to the electromagnetic introduction point; determining the actual shielding effectiveness index corresponding to the electromagnetic introduction point based on the protection data of the electromagnetic introduction point against electromagnetic pulses; bringing the standard shielding effectiveness index and the actual shielding effectiveness index corresponding to the electromagnetic introduction point into the protection capability evaluation model corresponding to the electromagnetic introduction point to determine the shielding performance index corresponding to the electromagnetic introduction point; performing weighted summation of the shielding performance index corresponding to each electromagnetic introduction point according to the evaluation weight corresponding to each electromagnetic introduction point to determine the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

[0009] In a possible implementation, the shielding performance index corresponding to each electromagnetic introduction point is determined in the following manner: according to the protection importance corresponding to the electromagnetic introduction point, the protection safety margin index corresponding to the electromagnetic introduction point is determined; the protection safety margin index, standard shielding effectiveness index and actual shielding effectiveness index corresponding to the electromagnetic introduction point are brought into the protection capability evaluation model corresponding to the electromagnetic introduction point to determine the shielding performance index corresponding to the electromagnetic introduction point.

[0010] In a possible implementation, the actual shielding effectiveness index corresponding to each electromagnetic introduction point is determined by: determining the body structure type corresponding to the electromagnetic introduction point; and determining the actual shielding effectiveness index corresponding to the electromagnetic introduction point according to the body structure type corresponding to the electromagnetic introduction point.

[0011] In a possible embodiment, the body structure type includes at least windows and holes and doors and gaps, wherein the actual shielding effectiveness index corresponding to each electromagnetic introduction point is determined in the following manner: if the body structure type corresponding to the electromagnetic introduction point is determined to be a window and hole type, then the geometric center of the electromagnetic introduction point is used as a reference point, and in combination with given incident conditions, an electromagnetic pulse protection capability test is performed at a preset test point corresponding to the reference point to obtain the actual shielding effectiveness index of the electromagnetic introduction point against the electromagnetic pulse, and the preset test point is located at a preset distance in the normal direction inside the reference point; if the body structure type corresponding to the electromagnetic introduction point is determined to be a door and gap type, then the center point of each seam corresponding to the electromagnetic introduction point is used as a reference point, and in combination with given incident conditions, an electromagnetic pulse protection capability test is performed at a preset test point corresponding to each reference point to obtain the actual shielding effectiveness index of the electromagnetic introduction point against the electromagnetic pulse.

[0012] In a possible implementation, the protection capability evaluation function corresponding to the electromagnetic introduction point is:

[0013]

[0014] Among them, SEi-y Represents the standard shielding effectiveness index corresponding to the i-th electromagnetic introduction point, SE i-f represents the actual shielding effectiveness index corresponding to the i-th electromagnetic introduction point, S i represents the protection safety margin index corresponding to the i-th electromagnetic introduction point, f(SE i-t ,SE i-f ) represents the shielding performance index of the i-th electromagnetic introduction point against electromagnetic pulses.

[0015] In a possible implementation manner, the sum of the evaluation weights corresponding to the electromagnetic introduction points is 1.

[0016] In a second aspect, an embodiment of the present application further provides an electromagnetic pulse protection capability evaluation device, the device comprising:

[0017] The combing module is used to count the multiple electromagnetic introduction points corresponding to the aircraft body structure; the establishment module is used to establish the protection capability evaluation function corresponding to each electromagnetic introduction point; the acquisition module is used to obtain the evaluation weight corresponding to each electromagnetic introduction point; the determination module is used to fit the protection capability evaluation function corresponding to each electromagnetic introduction point through the evaluation weight, and determine the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

[0018] In a third aspect, an embodiment of the present application further provides an electronic device, comprising: a processor, a memory and a bus, wherein the memory stores machine-readable instructions executable by the processor, and when the electronic device is running, the processor and the memory communicate through the bus, and the machine-readable instructions are executed by the processor to execute the steps of the method for evaluating electromagnetic pulse protection capability in the above-mentioned first aspect or any possible implementation manner of the first aspect.

[0019] In a fourth aspect, an embodiment of the present application further provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the steps of evaluating the electromagnetic pulse protection capability in the above-mentioned first aspect or any possible implementation manner of the first aspect are executed.

[0020] The embodiment of the present application provides an evaluation method, device and electronic equipment for electromagnetic pulse protection capability, including: combing multiple electromagnetic introduction points corresponding to the aircraft body structure; establishing a protection capability evaluation function corresponding to each electromagnetic introduction point; obtaining an evaluation weight corresponding to each electromagnetic introduction point; fitting the protection capability evaluation function corresponding to each electromagnetic introduction point through the evaluation weight, and determining the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure. The present application determines the electromagnetic pulse protection capability of the entire aircraft body structure by fitting the protection capabilities of different electromagnetic introduction points corresponding to the aircraft body structure, which can effectively support the subsequent analysis of the quantitative correlation between the aircraft protection capability and the cost, weight and volume of the protection measures.

[0021] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, preferred embodiments are specifically cited below and described in detail with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 One of the flow charts of an electromagnetic pulse protection capability evaluation method provided in an embodiment of the present application is shown;

[0024] Figure 2 A second flowchart of a method for evaluating electromagnetic pulse protection capability provided in an embodiment of the present application is shown;

[0025] Figure 3 A functional module diagram of an electromagnetic pulse protection capability evaluation device provided in an embodiment of the present application is shown;

[0026] Figure 4 A schematic structural diagram of an electronic device provided in an embodiment of the present application is shown. DETAILED DESCRIPTION

[0027] To make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. It should be understood that the drawings in the present application only serve the purpose of explanation and description and are not used to limit the scope of protection of the present application. In addition, it should be understood that the schematic drawings are not drawn in real proportion. The flowchart used in this application shows the operations implemented according to some embodiments of the present application. It should be understood that the operations of the flowchart can be implemented out of sequence, and the steps without logical context can be reversed in order or implemented simultaneously. In addition, those skilled in the art, under the guidance of the content of the present application, can add one or more other operations to the flowchart, or remove one or more operations from the flowchart.

[0028] In addition, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application claimed for protection, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without making creative work belong to the scope of protection of the present application.

[0029] Most of the existing electromagnetic protection evaluation methods for aircraft airframe structures focus on the shielding effectiveness of a single local structure. They do not consider the differences in the evaluation of electromagnetic pulse protection capabilities of different local structures, and lack an overall evaluation strategy for the airframe structure.

[0030] Specifically, in actual engineering applications, it is impossible to obtain quantitative data on the improvement of the electromagnetic pulse protection measures on the overall protection capability of the aircraft airframe structure, which makes it impossible to accurately further optimize the electromagnetic pulse protection of the entire airframe structure, making it impossible to effectively support the subsequent analysis of the quantitative relationship between the aircraft's protection capability and the cost, weight, and volume of the protection measures.

[0031] Based on this, the embodiments of the present application provide an electromagnetic pulse protection capability evaluation method, device and electronic equipment, which can determine the electromagnetic pulse protection capability of the entire aircraft body structure by fitting the protection capabilities of different electromagnetic introduction points corresponding to the aircraft body structure, and can effectively support the subsequent analysis of the quantitative relationship between the aircraft protection capability and the cost, weight and volume of the protection measures, as follows:

[0032] See also Figure 1 , Figure 1 FIG. 1 is a flow chart showing a method for evaluating electromagnetic pulse protection capability provided by an embodiment of the present application. Figure 1 As shown, the method provided in the embodiment of the present application comprises the following steps:

[0033] S100, combing through a plurality of electromagnetic introduction points corresponding to the aircraft body structure.

[0034] S200, establishing a protection capability evaluation function corresponding to each electromagnetic introduction point.

[0035] S300: Obtain an evaluation weight corresponding to each electromagnetic introduction point.

[0036] S400. Fitting the protection capability evaluation function corresponding to each electromagnetic introduction point by means of the evaluation weight, and determining the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

[0037] In a preferred embodiment, the aircraft body structure is a local body structure of the entire aircraft, such as an aircraft cockpit, and the electromagnetic introduction points are multiple corresponding local body structures of the aircraft body structure. Taking the aircraft cockpit as an example, the multiple electromagnetic introduction points corresponding to it include but are not limited to at least one cockpit windshield and a boarding door. In the present application, a structural information file corresponding to the aircraft body structure is first obtained, and the structural information file includes multiple electromagnetic introduction points corresponding to the aircraft body structure. In step S100 of the present application, it is necessary to first parse the multiple electromagnetic introduction points in the structural information file and number the multiple electromagnetic introduction points.

[0038] Furthermore, in step S200, based on the shielding effectiveness index data corresponding to each electromagnetic introduction point, a protection capability evaluation function corresponding to each electromagnetic introduction point is established. The protection capability evaluation function indicates the corresponding relationship between the shielding effectiveness index data corresponding to the electromagnetic introduction point and the shielding performance index. The shielding performance index reflects the protection capability of the electromagnetic introduction point against electromagnetic pulses.

[0039] In step S300, the evaluation weight corresponding to each electromagnetic introduction point is predetermined according to the importance of the electromagnetic introduction point in the analysis of the overall electromagnetic pulse protection capability of the aircraft body structure.

[0040] Preferably, the sum of the evaluation weights corresponding to the electromagnetic introduction points is 1.

[0041] Furthermore, in step S400, the evaluation weights corresponding to each electromagnetic introduction point are combined to fit the protection capability evaluation function corresponding to each electromagnetic introduction point, so as to obtain the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

[0042] In steps S100 to S400 of the present application, the electromagnetic pulse protection capabilities of different electromagnetic introduction points corresponding to the aircraft body structure are quantified through a protection capability evaluation function, and further a differential analysis is performed on the influence of the electromagnetic protection capabilities corresponding to different electromagnetic introduction points on the pulse protection capability of the entire aircraft body structure to obtain an evaluation weight corresponding to each electromagnetic introduction point, and the electromagnetic pulse protection capabilities corresponding to the quantified different electromagnetic introduction points are fitted in combination with the corresponding evaluation weights of the electromagnetic introduction points to obtain an electromagnetic pulse protection capability index that can reflect the electromagnetic pulse protection capability of the entire aircraft body structure, that is, a global evaluation result of the electromagnetic pulse protection capability of the aircraft body structure is obtained, which not only facilitates the subsequent further precise design of the pulse protection measures of the overall aircraft body structure, but also can effectively support the subsequent analysis of the quantitative relationship between the aircraft protection capability and the cost, weight, and volume of the protection measures.

[0043] In a preferred embodiment, the shielding effectiveness index data includes a standard actual shielding effectiveness index and an actual shielding effectiveness index, see Figure 2 , Figure 2 FIG2 shows a second flow chart of a method for evaluating electromagnetic pulse protection capability provided by an embodiment of the present application. Figure 2 As shown, step S400 includes:

[0044] S4001. For each electromagnetic introduction point, obtain a standard shielding effectiveness index corresponding to the electromagnetic introduction point.

[0045] S4002. For each electromagnetic introduction point, according to the protection data of the electromagnetic introduction point against electromagnetic pulses, determine the actual shielding effectiveness index corresponding to the electromagnetic introduction point.

[0046] S4003. For each electromagnetic introduction point, the standard shielding effectiveness index and the actual shielding effectiveness index corresponding to the electromagnetic introduction point are brought into the protection capability evaluation model corresponding to the electromagnetic introduction point to determine the shielding performance index corresponding to the electromagnetic introduction point.

[0047] S4004. Perform weighted summation of the shielding performance index corresponding to each electromagnetic introduction point according to the evaluation weight corresponding to each electromagnetic introduction point, and determine the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

[0048] In step S4001, the entire aircraft is divided into multiple aircraft body structures, each of which corresponds to an electromagnetic pulse protection standard file. The electromagnetic pulse protection standard file includes a standard shielding effectiveness index corresponding to each electromagnetic introduction point in the aircraft body structure. The present application obtains the electromagnetic pulse protection standard file corresponding to the aircraft body structure to parse out the standard shielding effectiveness index corresponding to each electromagnetic introduction point from the corresponding electromagnetic pulse protection standard file. Specifically, for the i-th electromagnetic introduction point corresponding to the aircraft body structure, the corresponding standard shielding effectiveness index is SE i-t .

[0049] In step S4002, for each electromagnetic introduction point, it is necessary to perform an electromagnetic pulse protection capability test on the electromagnetic introduction point according to a preset test standard to obtain the electromagnetic pulse protection data of the electromagnetic introduction point, and then further combine the protection data to calculate and determine the actual shielding effectiveness index corresponding to the electromagnetic introduction point. Specifically, for the i-th electromagnetic introduction point corresponding to the aircraft body structure, the actual shielding effectiveness index corresponding to it is SE i-f .

[0050] In a preferred embodiment, step S4002 includes:

[0051] For each electromagnetic introduction point: determine the body structure type corresponding to the electromagnetic introduction point, and according to the body structure type corresponding to the electromagnetic introduction point, determine the actual shielding effectiveness index corresponding to the electromagnetic introduction point.

[0052] In a specific embodiment, different body structure types are pre-created, and different body structure types correspond to different calculation strategies for actual shielding effectiveness indicators. The body structure types include but are not limited to at least one of the following items: windows and holes and hatches and gaps. In the present application, the electromagnetic introduction points are classified according to the different structural attributes corresponding to the electromagnetic introduction points, and the body structure type corresponding to each electromagnetic introduction point is determined. Based on the body structure type corresponding to the electromagnetic introduction point, the corresponding calculation strategy is called to further calculate and determine the actual shielding effectiveness indicator corresponding to the electromagnetic introduction point.

[0053] In another preferred embodiment, step S4002 further includes:

[0054] For each electromagnetic introduction point, the body structure type corresponding to the electromagnetic introduction point is determined to be a window or hole. The geometric center of the electromagnetic introduction point is used as a reference point. Combined with the given incident conditions, an electromagnetic pulse protection test is performed at a preset test point corresponding to the reference point to obtain the actual shielding effectiveness index of the electromagnetic introduction point against the electromagnetic pulse. The preset test point is located at a preset distance in the normal direction inside the reference point.

[0055] In the present application, the given incident conditions include but are not limited to the incident direction and the polarization angle, the preset distance can be set to 30cm, and when the electromagnetic pulse protection test is performed at the preset test point, multiple electromagnetic pulse protection tests can be performed, and the multiple given incident conditions corresponding to the multiple electromagnetic pulse protection tests are different. In this way, the protection data corresponding to the electromagnetic introduction point can be obtained, and the protection data includes the shielding effectiveness data obtained from each electromagnetic pulse protection test performed at the preset test point of the electromagnetic introduction point. The actual shielding effectiveness index is determined by the target shielding effectiveness data among the multiple shielding effectiveness data, wherein the target shielding effectiveness data is the shielding effectiveness data reflecting the worst electromagnetic pulse protection capability of the electromagnetic introduction point.

[0056] For each electromagnetic introduction point, the body structure type corresponding to the electromagnetic introduction point is determined to be a hatch and gap type. The center point of each seam corresponding to the electromagnetic introduction point is taken as a reference point. Combined with the given incident conditions, an electromagnetic pulse protection test is performed at the preset test point corresponding to each reference point to obtain the actual shielding effectiveness index of the electromagnetic introduction point against electromagnetic pulses.

[0057] As mentioned above, when determining the actual shielding effectiveness index corresponding to the electromagnetic introduction points such as hatches and gaps, the electromagnetic pulse protection test performed at each reference point is similar to that for the electromagnetic introduction points such as windows and holes, which will not be elaborated here. The difference is that it is ultimately necessary to determine the target shielding effectiveness data among all the shielding effectiveness data corresponding to multiple reference points, and further determine the actual shielding effectiveness index based on the target shielding effectiveness data.

[0058] In a preferred embodiment, step S4003 includes:

[0059] For each electromagnetic introduction point, the following processing is performed: according to the protection importance corresponding to the electromagnetic introduction point, the protection safety margin index corresponding to the electromagnetic introduction point is determined; the protection safety margin index, standard shielding effectiveness index and actual shielding effectiveness index corresponding to the electromagnetic introduction point are brought into the protection capability evaluation model corresponding to the electromagnetic introduction point to determine the shielding performance index corresponding to the electromagnetic introduction point.

[0060] Specifically, according to the normalization principle, the protection capability evaluation function corresponding to the electromagnetic introduction point is established as follows:

[0061]

[0062] Among them, SE i-t Represents the standard shielding effectiveness index corresponding to the i-th electromagnetic introduction point, SE i-f represents the actual shielding effectiveness index corresponding to the i-th electromagnetic introduction point, S i represents the protection safety margin index corresponding to the i-th electromagnetic introduction point, f(SE i-t , S.E. i-f ) is the protection capability evaluation function corresponding to the i-th electromagnetic introduction point, which represents the shielding performance index of the i-th electromagnetic introduction point against electromagnetic pulses.

[0063] Specifically, in this application, for the i-th electromagnetic introduction point, when SE i-f >SE i-t When f(SE i-t , S.E. i-f )=1.

[0064] When SE i-t -S i <SE i-f <SE i-t hour,

[0065] When SE i-f <SE i-t -S i When f(SE i-t , S.E. i-f )=0.

[0066] In step S4004, for the i-th electromagnetic introduction point, its corresponding evaluation weight is expressed as Q i .

[0067] In a preferred embodiment, the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure is determined by the following formula:

[0068]

[0069] In this formula, F represents the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure, n represents the number of electromagnetic introduction points corresponding to the entire aircraft body structure, and Q i represents the i-th electromagnetic introduction point and its corresponding evaluation weight, f(SE i-t ,SE i-f ) represents the shielding performance index corresponding to the i-th electromagnetic introduction point.

[0070] in,

[0071] In the past, structural protection capability assessments were mostly based on the absolute value of their shielding effectiveness, while ignoring the differences in different structural evaluation systems. This application takes into account the standard shielding effectiveness index corresponding to the electromagnetic introduction point, and uses the difference between the actual shielding effectiveness index and the standard shielding effectiveness index as the basis for assessing the protection capability of the entire aircraft body structure, which is more in line with actual engineering needs.

[0072] Based on the same application concept, the embodiments of the present application also provide an electromagnetic pulse protection capability evaluation device corresponding to the electromagnetic pulse protection capability evaluation method provided in the above embodiments. Since the principle of solving the problem by the device in the embodiments of the present application is similar to the electromagnetic pulse protection capability evaluation method in the above embodiments of the present application, the implementation of the device can refer to the implementation of the method, and the repeated parts will not be repeated.

[0073] See also Figure 3 , Figure 3 FIG. 1 shows a functional module diagram of an electromagnetic pulse protection capability evaluation device provided in an embodiment of the present application. Figure 3 As shown, the device comprises:

[0074] A combing module 500 is used to count multiple electromagnetic introduction points corresponding to the aircraft body structure;

[0075] Establishing module 510, used to establish a protection capability evaluation function corresponding to each electromagnetic introduction point;

[0076] An acquisition module 520 is used to acquire an evaluation weight corresponding to each electromagnetic introduction point;

[0077] The determination module 530 is used to fit the protection capability evaluation function corresponding to each electromagnetic introduction point through the evaluation weight to determine the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

[0078] Based on the same application idea, please refer to Figure 4 , Figure 4 FIG. 1 shows a schematic diagram of the structure of an electronic device provided in an embodiment of the present application. Figure 4As shown, the electronic device 600 includes: a processor 610, a memory 620 and a bus 630. The memory 620 stores machine-readable instructions executable by the processor 610. When the electronic device 600 is running, the processor 610 and the memory 620 communicate through the bus 630. The machine-readable instructions are executed by the processor 610 when running, such as the steps of the electromagnetic pulse protection capability evaluation method provided in any of the above embodiments.

[0079] Based on the same application concept, an embodiment of the present application also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the steps of the electromagnetic pulse protection capability evaluation method provided in the above embodiment are executed.

[0080] Those skilled in the art can clearly understand that, for the convenience and simplicity of description, the specific working process of the system and device described above can refer to the corresponding process in the aforementioned method embodiment, and will not be repeated here. In the several embodiments provided in the present application, it should be understood that the disclosed system, device and method can be implemented in other ways. The device embodiments described above are merely schematic. For example, the division of units is only a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some communication interfaces, indirect coupling or communication connection of devices or units, which can be electrical, mechanical or other forms.

[0081] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0082] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.

[0083] If the function is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a non-volatile computer-readable storage medium that is executable by a processor. Based on this understanding, the technical solution of the present application, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium, including a number of instructions to enable a computer device (which can be a personal computer, server, or network device, etc.) to execute all or part of the steps of the various embodiments of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM), random access memory (RAM), disk or optical disk, etc., various media that can store program codes.

[0084] The above are only specific implementations of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A method for evaluating electromagnetic pulse protection capability, characterized in that: The method comprises: Sort out multiple electromagnetic introduction points corresponding to the aircraft body structure; Establish a protection capability evaluation function corresponding to each electromagnetic introduction point; Obtain the evaluation weight corresponding to each electromagnetic introduction point; The protection capability evaluation function corresponding to each electromagnetic introduction point is fitted by the evaluation weight to determine the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

2. The method according to claim 1, characterized in that The EMP protection capability index corresponding to the entire aircraft structure is determined by: For each electromagnetic introduction point, the following processing is performed: obtaining a standard shielding effectiveness index corresponding to the electromagnetic introduction point; Determine the actual shielding effectiveness index corresponding to the electromagnetic introduction point according to the protection data of the electromagnetic introduction point against the electromagnetic pulse; Bringing the standard shielding effectiveness index corresponding to the electromagnetic introduction point and the actual shielding effectiveness index into the protection capability evaluation model corresponding to the electromagnetic introduction point to determine the shielding performance index corresponding to the electromagnetic introduction point; According to the evaluation weight corresponding to each electromagnetic introduction point, the shielding performance index corresponding to each electromagnetic introduction point is weighted and summed to determine the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

3. The method according to claim 2, characterized in that The shielding performance index corresponding to each electromagnetic introduction point is determined by: According to the protection importance level corresponding to the electromagnetic introduction point, determine the protection safety margin index corresponding to the electromagnetic introduction point; The protection safety margin index, the standard shielding effectiveness index and the actual shielding effectiveness index corresponding to the electromagnetic introduction point are brought into the protection capability evaluation model corresponding to the electromagnetic introduction point to determine the shielding performance index corresponding to the electromagnetic introduction point.

4. The method according to claim 2, characterized in that: The actual shielding effectiveness index corresponding to each electromagnetic introduction point is determined by the following method: Determine the body structure type corresponding to the electromagnetic introduction point; According to the body structure type corresponding to the electromagnetic introduction point, the actual shielding effectiveness index corresponding to the electromagnetic introduction point is determined.

5. The method according to claim 4, characterized in that The aircraft structure types at least include windows and holes and doors and gaps. Among them, the actual shielding effectiveness index corresponding to each electromagnetic introduction point is determined by the following method: Determine that the body structure type corresponding to the electromagnetic introduction point is a window or hole type, then take the geometric center of the electromagnetic introduction point as the reference point, and in combination with the given incident conditions, perform an electromagnetic pulse protection capability test at a preset test point corresponding to the reference point to obtain the actual shielding effectiveness index of the electromagnetic introduction point against the electromagnetic pulse, wherein the preset test point is located at a preset distance in the normal direction inside the reference point; It is determined that the fuselage structure type corresponding to the electromagnetic introduction point is a hatch and gap type. The center point of each seam corresponding to the electromagnetic introduction point is taken as a reference point. Combined with the given incident conditions, an electromagnetic pulse protection capability test is performed at the preset test point corresponding to each reference point to obtain the actual shielding effectiveness index of the electromagnetic introduction point against electromagnetic pulses.

6. The method according to claim 3, characterized in that The protection capability evaluation function corresponding to the electromagnetic introduction point is: Among them, SE i-t Represents the standard shielding effectiveness index corresponding to the i-th electromagnetic introduction point, SE i-f represents the actual shielding effectiveness index corresponding to the i-th electromagnetic introduction point, S i represents the protection safety margin index corresponding to the i-th electromagnetic introduction point, f(SE i-t ,SE i-f ) represents the shielding performance index of the i-th electromagnetic introduction point against electromagnetic pulses.

7. The method according to claim 2, characterized in that The sum of the evaluation weights corresponding to each electromagnetic introduction point is 1.

8. An electromagnetic pulse protection capability assessment device, characterized in that: The device comprises: A combing module is used to count multiple electromagnetic introduction points corresponding to the aircraft body structure; Establishing a module for establishing a protection capability evaluation function corresponding to each electromagnetic introduction point; An acquisition module, used for acquiring an evaluation weight corresponding to each electromagnetic introduction point; The determination module is used to fit the protection capability evaluation function corresponding to each electromagnetic introduction point through the evaluation weight, and determine the electromagnetic pulse protection capability index corresponding to the entire aircraft body structure.

9. An electronic device, characterized in that: include: A processor, a memory and a bus, wherein the memory stores machine-readable instructions executable by the processor, and when the electronic device is running, the processor and the memory communicate through the bus, and the machine-readable instructions are executed by the processor to execute the steps of the electromagnetic pulse protection capability assessment method as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps of the method for evaluating the electromagnetic pulse protection capability as described in any one of claims 1 to 7 are executed.

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