A method for simulating and evaluating lightning effects of a low-conductivity composite aircraft

Abstract

A lightning effect simulation evaluation method of a low-conductivity composite aircraft, comprising: analyzing the structure size and material properties of each component of the aircraft and the subsequent simulation object to be carried out in view of the lightning effect simulation requirements and the aircraft requiring lightning partition simulation; collecting the material parameters of each component involved in the simulation; constructing an electromagnetic simulation model of the aircraft according to the material parameters of each component on the basis of the analysis of the simulation object; applying an electrostatic field outside the electromagnetic simulation model of the aircraft to perform a lightning attachment point simulation of the aircraft; changing the direction of the electrostatic field, observing and recording the charge distribution on the surface of the aircraft in multiple simulation results, and giving the analysis result of the lightning attachment point by comprehensively analyzing all directions; obtaining the lightning partition according to the analysis result of the lightning attachment point; performing lightning effect simulation on the electromagnetic simulation model of the aircraft according to the lightning attachment point and the lightning partition; and analyzing the lightning effect simulation result in combination with the lightning effect simulation requirements.

Description

Technical Field

[0001] This invention relates to a method for simulating and evaluating the lightning effect of a low-conductivity composite material aircraft. The method involves simulating and evaluating the lightning effect when such an aircraft encounters lightning while flying in the air, but does not involve the working state of such an aircraft when parked on the ground. It belongs to the field of electromagnetic environment effect technology. Background Technology

[0002] Lightning's hazards to aircraft, rockets, and other aerospace vehicles can be categorized into direct and indirect effects. Direct lightning effects occur when lightning strikes an aircraft directly, causing damage such as punctures, melting, and structural deformation of the outer shell. Indirect lightning effects refer to the powerful electromagnetic pulse field generated during the high-current discharge of lightning when it strikes the aircraft's outer shell, which can affect or damage electronic equipment inside the aircraft.

[0003] Traditional aircraft have metal outer shells, and the corresponding lightning effect simulations mainly focus on the changes in electric field distribution caused by large currents, as well as the cable pulse current and voltage caused by ground wire coupling and field line coupling. The lightning zones given in industry standards can be referenced in the simulation, and the current calculation method is relatively simple.

[0004] Currently, aircraft extensively utilize carbon fiber composite materials to achieve lighter weight and higher strength. However, these materials are often designed without considering their electrical properties, such as conductivity. Actual testing has revealed that the conductivity of carbon fiber composites is significantly lower than that of traditional metallic materials, and they exhibit anisotropic electrical properties, rendering traditional lightning effect simulation and evaluation methods inapplicable.

[0005] Aircraft may be struck by lightning during takeoff and cloud cover. Lightning is a common natural phenomenon that generates a large pulse of current with an extremely fast rise time and short duration during discharge, while simultaneously radiating transient electromagnetic fields into space. Modern aircraft extensively use composite materials for their outer shells. These materials have electrical conductivity several orders of magnitude lower than traditional metallic materials and exhibit anisotropy, resulting in different effects from conventional models when struck by lightning. Summary of the Invention

[0006] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a simulation evaluation method for the lightning effect of low-conductivity composite material aircraft. For low-conductivity composite materials, the equivalent conductivity is given through theoretical calculation and simulation, a lightning attachment point prediction model is constructed, a parallel transmission line lightning injection simulation model is constructed, and the lightning effect simulation evaluation is completed.

[0007] The technical solution of this invention is: a method for simulating and evaluating the lightning effect of a low-conductivity composite material aircraft, comprising:

[0008] Simulation Object Analysis: For the simulation requirements of lightning effects and the aircraft that need to carry out lightning zone simulation, analyze the structural dimensions and material properties of each component of the aircraft, and the simulation objects to be carried out in the future;

[0009] Composite material parameters: Collect material parameters for each component involved in the simulation;

[0010] Constructing the aircraft model: Based on the analysis of the simulation object, an electromagnetic simulation model of the aircraft is constructed according to the material parameters of each component;

[0011] Lightning attachment point analysis of aircraft: An electrostatic field is applied to the outside of the electromagnetic simulation model of the aircraft to simulate the lightning attachment point of the aircraft; the direction of the electrostatic field is changed, and the charge distribution on the surface of the aircraft is observed and recorded in the results of multiple simulations. The analysis results of the lightning attachment point are given by combining all directions.

[0012] Lightning zone analysis for aircraft: Lightning zones are obtained based on the analysis results of lightning attachment points;

[0013] Lightning effect simulation: Based on the lightning attachment point and lightning zone, lightning effect simulation is performed on the electromagnetic simulation model of the aircraft;

[0014] Evaluation of lightning effect simulation results: Based on the requirements of lightning effect simulation, the simulation results of lightning effect are analyzed.

[0015] Furthermore, methods for simulating lightning attachment points on aircraft include:

[0016] A parallel plate discharge structure is established based on the aircraft's external dimensions, and an equally spaced electrostatic field is applied to the aircraft.

[0017] Based on the grid of the aircraft, the simulation results of the charge density of each grid are given, the positions of the top 1% of points with the largest absolute value of charge density are recorded, the charge distribution is obtained, and then the lightning attachment points on the aircraft are obtained, thus completing the simulation of the lightning attachment points on the aircraft.

[0018] Furthermore, the size and spacing of the flat plates should be greater than three times the length of the aircraft.

[0019] Furthermore, an electrostatic field is applied to the aircraft at 30° intervals.

[0020] Furthermore, 37 electrostatic field sources were set in a hemispherical direction, with the electrostatic field voltage set to 1000kV and the space set to vacuum.

[0021] Furthermore, the material parameters of each component involved in the simulation include the electrical parameters of the low-conductivity braided carbon fiber composite material; the electrical parameters of the low-conductivity braided carbon fiber composite material are derived from the microstructure to obtain the equivalent electrical parameters of the fiber bundle, and the electrical parameters of the equivalent uniform material are obtained by modeling the periodic braiding structure and fitting the parameters through parameter sweeping.

[0022] Furthermore, the electrical parameters of the low-conductivity braided carbon fiber composite material are that the bulk conductivity of the braided carbon fiber composite material after integral processing and molding is less than 1000 S / m.

[0023] Furthermore, the method for simulating the lightning effect includes:

[0024] Establish a parallel transmission line structure to inject lightning current;

[0025] Based on the results of lightning zoning, determine the magnitude and waveform of the lightning current to be injected at the lightning current injection point, and load the corresponding lightning current.

[0026] An observation surface for induced electric field, induced magnetic field, and surface current is set on the structure of interest. Voltage observation points and current observation points are set on the core wire port and shielding layer of the cable of interest.

[0027] For lightning current inflow points, discharge points, and cable ports, denser meshing should be used, while for the aircraft body structure model, relatively sparse meshing should be used.

[0028] A computer-readable storage medium storing a computer program, wherein the computer program, when executed by a processor, implements the steps of the lightning effect simulation evaluation method for a low-conductivity composite material aircraft.

[0029] A lightning effect simulation and evaluation device for a low-conductivity composite material aircraft includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the steps of the lightning effect simulation and evaluation method for the low-conductivity composite material aircraft.

[0030] The advantages of this invention compared to the prior art are:

[0031] (1) This invention derives the equivalent electrical parameters of fiber bundles through microstructure, and models them according to their periodic braided structure. The electrical parameters of the equivalent uniform material are obtained by parameter scanning fitting, which provides input for setting the electrical parameters of low conductivity braided composite materials in the system-level model, so that the equivalent material of the aircraft shell in the system-level model can correctly reflect its electrical performance.

[0032] (2) This invention simulates the charge accumulation on the surface of an aircraft using a parallel plate discharge structure, and provides a simulation method for lightning attachment points on an aircraft.

[0033] (3) The present invention injects lightning current by establishing a parallel transmission line structure, so that the magnitude of the lightning current injection is consistent with the expected value, and the injection value will not deviate from the expectation due to the excessive impedance of the aircraft. Attached Figure Description

[0034] Figure 1 This is a schematic diagram of the method flow of the present invention;

[0035] Figure 2 This is a simplified schematic diagram of the fiber bundle model of the present invention;

[0036] Figure 3 This is a simulation diagram of the woven carbon fiber composite material of the present invention;

[0037] Figure 4 This is a simulation diagram of the lightning attachment point of the aircraft of the present invention;

[0038] Figure 5 This is a schematic diagram of the simulated electrostatic field direction at the lightning attachment point of the aircraft in this invention;

[0039] Figure 6 This is a schematic diagram of the parallel transmission line structure of the present invention injecting lightning current. Detailed Implementation

[0040] To better understand the above technical solutions, the technical solutions of this application will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments of this application and the specific features in the embodiments are detailed descriptions of the technical solutions of this application, rather than limitations on the technical solutions of this application. In the absence of conflict, the embodiments of this application and the technical features in the embodiments can be combined with each other.

[0041] The following description, in conjunction with the accompanying drawings, provides a more detailed explanation of the lightning effect simulation and evaluation method for a low-conductivity composite material aircraft provided in this application. Specific implementation methods may include (e.g.) Figures 1-6 As shown):

[0042] Simulation Object Analysis: For the simulation requirements of lightning effects and the aircraft that need to carry out lightning zone simulation, analyze the structural dimensions and material properties of each component of the aircraft, and the simulation objects to be carried out in the future;

[0043] Composite material parameters: Collect material parameters for each component involved in the simulation;

[0044] Constructing the aircraft model: Based on the analysis of the simulation object, an electromagnetic simulation model of the aircraft is constructed according to the material parameters of each component;

[0045] Lightning attachment point analysis of aircraft: An electrostatic field is applied to the outside of the electromagnetic simulation model of the aircraft to simulate the lightning attachment point of the aircraft; the direction of the electrostatic field is changed, and the charge distribution on the surface of the aircraft is observed and recorded in the results of multiple simulations. The analysis results of the lightning attachment point are given by combining all directions.

[0046] Lightning zone analysis for aircraft: Lightning zones are obtained based on the analysis results of lightning attachment points;

[0047] Lightning effect simulation: Based on the lightning attachment point and lightning zone, lightning effect simulation is performed on the electromagnetic simulation model of the aircraft;

[0048] Evaluation of lightning effect simulation results: Based on the requirements of lightning effect simulation, the simulation results of lightning effect are analyzed.

[0049] Furthermore, methods for simulating lightning attachment points on aircraft include:

[0050] A parallel plate discharge structure is established based on the aircraft's external dimensions, and an equally spaced electrostatic field is applied to the aircraft.

[0051] Based on the grid of the aircraft, the simulation results of the charge density of each grid are given, the positions of the top 1% of points with the largest absolute value of charge density are recorded, the charge distribution is obtained, and then the lightning attachment points on the aircraft are obtained, thus completing the simulation of the lightning attachment points on the aircraft.

[0052] In one possible implementation, the size and spacing of the flat plates should be greater than three times the length of the aircraft.

[0053] Optionally, in one possible implementation, an electrostatic field is applied to the aircraft at 30° intervals.

[0054] Optionally, 37 electrostatic field sources are set in the hemispherical direction, with the electrostatic field voltage set to 1000kV and the space set to vacuum.

[0055] Furthermore, the material parameters of each component involved in the simulation include the electrical parameters of the low-conductivity braided carbon fiber composite material; the electrical parameters of the low-conductivity braided carbon fiber composite material are derived from the microstructure to obtain the equivalent electrical parameters of the fiber bundle, and the electrical parameters of the equivalent uniform material are obtained by modeling the periodic braided structure and fitting the parameters through a sweep parameter.

[0056] In one possible implementation, the electrical parameters of the low-conductivity braided carbon fiber composite material are that the bulk conductivity of the braided carbon fiber composite material after integral processing and molding is less than 1000 S / m.

[0057] Furthermore, the method for simulating the lightning effect includes:

[0058] Establish a parallel transmission line structure to inject lightning current;

[0059] Based on the results of lightning zoning, determine the magnitude and waveform of the lightning current to be injected at the lightning current injection point, and load the corresponding lightning current.

[0060] An observation surface for induced electric field, induced magnetic field, and surface current is set on the structure of interest. Voltage observation points and current observation points are set on the core wire port and shielding layer of the cable of interest.

[0061] For lightning current inflow points, discharge points, and cable ports, denser meshing should be used, while for the aircraft body structure model, relatively sparse meshing should be used.

[0062] The solution provided in this application embodiment specifically includes the following steps:

[0063] 1. Simulation Object Analysis

[0064] For aircraft that require lightning zone simulation, analyze the structural dimensions and material properties (metal, composite materials, glass, rubber, etc.) of each component of the aircraft, as well as the simulation objects to be carried out subsequently (electromagnetic distribution, cable voltage and current).

[0065] 2. Composite material parameters

[0066] Collect the material parameters of each component involved in the simulation. For carbon fiber composites, anisotropic electrical conductivity and dielectric constant should be provided. Generally, experiments should be conducted to obtain the relevant parameters. The following is a simulation method for the electrical performance parameters of braided carbon fiber composites.

[0067] In this invention, the low-conductivity composite material refers to braided carbon fiber composite material. The manufacturing process of this type of material generally involves: preparing a bundle of carbon fibers into a fiber bundle, the fiber bundle containing carbon fiber filaments and a fixing slurry; the fiber volume content in the fiber bundle is defined as the fiber volume percentage; braiding the fiber bundle on a braiding machine according to specified warp and weft threads, the braiding method can be plain weave, twill weave, satin weave, etc.; and pressing and curing the multiple layers of fabric to form a braided carbon fiber composite material. This invention provides a simulation method for the equivalent conductivity and dielectric constant of this type of braided carbon fiber composite material.

[0068] The model of a single fiber bundle is as follows: Figure 2 As shown, a fixed number of carbon fibers and slurry are processed at a predetermined volume ratio to form thin, long fiber bundles. The model of a single fiber bundle can be simplified to a three-layer structure, as shown... Figure 2 As shown. Layers 1 and 3 are slurry, and their electrical performance parameters can be directly substituted. Layer 2 is a mixture of slurry and carbon fiber.

[0069]

[0070]

[0071]

[0072] Where ε m ε is the dielectric constant of the slurry.f σ is the dielectric constant of carbon fiber. f Let g be the carbon fiber conductivity and g be the carbon fiber volume content. The equivalent conductivity and dielectric constant of the fiber bundle in the direction parallel to and perpendicular to the carbon fiber can be estimated using the above formula.

[0073] A plain weave method is used to process fiber bundles into fabric. A periodic structure is set in simulation software to model the fabric according to its weave method and number of layers. The electrical properties of the fabric are then simulated. The modeling method is as follows: Figure 3 As shown, the transmittance and reflectance of the periodic structure were calculated using simulation software.

[0074] The simulation model is set as a uniform material, and the equivalent conductivity and dielectric constant of the material are set. Then, a parameter sweep fitting is performed to make the transmittance and reflectance of the uniform material match the simulation results of the fabric as much as possible. The optimal solution given by the parameter sweep is the equivalent conductivity and dielectric constant of the composite material.

[0075] 3. Construct an aircraft model

[0076] Based on the analysis of the simulation object, an electromagnetic simulation model of the aircraft is constructed. The model should be built to a 1:1 scale, ensuring that the appearance is as consistent as possible with the real aircraft. The composite materials of the main structure should be set according to the composite material parameters from the previous step. The model should also include the main metal structures inside the aircraft, as well as the cable models involved in the simulation analysis.

[0077] 4. Analysis of Lightning Attachment Points on Aircraft

[0078] An electrostatic field is applied outside the aircraft model to simulate the electric field environment near the aircraft before a lightning strike. The charge distribution on the aircraft surface is observed in the simulation results. Areas with higher charge density are more prone to air breakdown and thus more likely to induce a lightning strike. The charge density of all surfaces is ranked, and the top 1% of areas with the highest charge density are defined as high-probability regions.

[0079] The direction of the electrostatic field will be changed, and the surface charge density distribution will be recalculated. The analysis results of the lightning attachment point will be given by combining all directions.

[0080] The lightning attachment point is the point of contact when a lightning leader first strikes an aircraft. This invention proposes a method for simulating the lightning attachment point.

[0081] First, establish a parallel plate discharge structure based on the aircraft's external dimensions. The size and spacing of the plates should be greater than three times the length of the aircraft. Figure 4 As shown. An electrostatic field is applied to the aircraft at 30° intervals. Due to the aircraft's left-right symmetry, 37 electrostatic field sources are set up in hemispherical directions, as shown. Figure 5As shown. The electrostatic field voltage is set to 1000kV, and the space is set to vacuum since air breakdown is not considered.

[0082] The simulation results are based on the grid of the aircraft, providing the charge density simulation results for each grid and recording the positions of the top 1% of points with the largest absolute charge density.

[0083] The direction of the electrostatic field will be changed, and the surface charge density distribution will be recalculated. The number of times a high-probability region appears at each location in all directions will be counted; the higher the number, the greater the likelihood that it will become a lightning attachment point.

[0084] 5. Lightning Zoning Analysis of Aircraft

[0085] Lightning zoning is a regional division based on the probability of lightning attachment, the probability of the attachment point location changing over time, and the conduction characteristics of lightning current.

[0086] For typical aircraft lightning zones, refer to HB6129-1987 or relevant industry standards.

[0087] The lightning zone of a typical rocket needs to be estimated based on its flight speed, altitude, and lightning leader velocity.

[0088] 6. Lightning Effect Simulation

[0089] Based on the lightning attachment point and lightning zone, the lightning current inflow and discharge points are selected on the physical structure model, and a conductive path of a parallel transmission line is arranged between the lightning current inflow and discharge points. This invention proposes a method for injecting lightning current into a parallel transmission line structure, such as... Figure 6 As shown, the parallel transmission line structure is a cylindrical structure. The distance between each face of the cylinder and the aircraft should be more than three times the length of the aircraft. At least one transmission line is arranged every 30° in the 360° direction to form a conductive path.

[0090] The parallel transmission line structure injects lightning current, which ensures that the injected lightning current matches the expected value, without the injected value deviating from the expectation due to excessively high aircraft impedance.

[0091] A lightning current excitation signal is set at the point where the lightning current flows in; the excitation signal is generally in the form of a double exponential pulse. The current waveform is generally set according to the waveforms specified in GJB1389A-2005. Considering that the simulation should cover the most severe conditions, only the A-wave / Ah-wave is generally loaded. For circuits that may produce superposition effects within the port, the simulation of multiple impulses and multiple pulse groups corresponding to the D-wave and H-wave should be considered. The B-wave and C-wave are generally used to simulate the thermal effects of current and are generally not involved in the simulation of indirect lightning effects.

[0092] For electromagnetic field distribution simulation, observation surfaces for lightning-induced electric field, lightning-induced magnetic field, and lightning surface current are set on the structure of interest. For cable effect simulation, voltage and current observation points are set at the core terminals and shielding layer of the cable of interest.

[0093] Taking into account factors such as simulation accuracy, simulation speed, and hardware conditions, the mesh should be densified for lightning current inflow points, discharge points, and cable ports, while a relatively sparse mesh can be used for the missile / rocket body structure model.

[0094] 7. Evaluation of Lightning Effect Simulation Results

[0095] Based on the purpose of the simulation, the simulation results are analyzed to determine their rationality and correctness, and analytical conclusions are given.

[0096] This application provides a computer-readable storage medium storing computer instructions that, when executed on a computer, cause the computer to perform... Figure 1 The method described.

[0097] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product implemented on one or more computer-usable storage media (including, but not limited to, disk storage and optical storage) containing computer-usable program code.

[0098] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0099] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0100] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0101] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

[0102] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for lightning effect simulation evaluation of a low- conductivity composite aircraft, characterized in that, The method comprises the following steps: Analysis of simulation objects: analyzing the structure size and material properties of each component of the aircraft, and the simulation objects to be simulated subsequently, according to the lightning effect simulation requirements and the aircrafts requiring lightning partition simulation; Material parameters of the composite: collecting the material parameters of each component participating in the simulation; Construction of an aircraft model: constructing an electromagnetic simulation model of the aircraft according to the material parameters of each component on the basis of the analysis of the simulation objects; Analysis of lightning attachment points of the aircraft: performing a lightning attachment point simulation of the aircraft by applying an electrostatic field to the outside of the electromagnetic simulation model of the aircraft; changing the direction of the electrostatic field, observing and recording the charge distribution on the surface of the aircraft in multiple simulation results, and giving an analysis result of the lightning attachment points according to all directions; Lightning partition analysis of the aircraft: obtaining the lightning partition according to the analysis result of the lightning attachment points; Lightning effect simulation: performing a lightning effect simulation on the electromagnetic simulation model of the aircraft according to the lightning attachment points and the lightning partition; Evaluation of the simulation result of the lightning effect: analyzing the simulation result of the lightning effect in combination with the lightning effect simulation requirements; The method of the lightning effect simulation comprises the following steps: Establishing a parallel transmission line structure to inject a lightning current; Determining the lightning current level and waveform to be injected at the injection point of the lightning current according to the result of the lightning partition, and loading the corresponding lightning current; Setting an induced electric field observation surface, an induced magnetic field observation surface and a surface current observation surface on the structure of interest, and setting voltage observation points and current observation points on the core line port and the shielding layer of the cable of interest; Using a dense grid to divide the lightning current inflow point, the discharge point and the cable port, and using a relatively sparse grid to divide the aircraft body structure model.

2. The method for lightning effect simulation evaluation of a low- conductivity composite aircraft according to claim 1, characterized in that, The method of simulating the lightning attachment points of the aircraft comprises the following steps: Establishing a parallel plate discharge structure according to the size of the aircraft, and applying an equal-interval electrostatic field to the aircraft; According to the grid division of the aircraft, giving the charge density simulation result of each grid, recording the positions of the top 1% points with the largest absolute value of charge density, obtaining the charge distribution, and further obtaining the lightning attachment points on the aircraft, thereby completing the simulation of the lightning attachment points of the aircraft.

3. The method of claim 2, wherein, The size and spacing of the parallel plates should be greater than 3 times the length of the aircraft.

4. The method of claim 2, wherein, The electrostatic field is applied to the aircraft at intervals of 30°.

5. The method of claim 2, wherein, 37 hemispherical direction electrostatic field sources are set, the electrostatic field voltage is set to 1000kV, and the space is set to vacuum.

6. The method of claim 1, wherein, The material parameters of each component participating in the simulation include the electrical parameters of low-conductivity woven carbon fiber composite materials; the electrical parameters of the low-conductivity woven carbon fiber composite materials are derived from the equivalent electrical parameters of the fiber bundle through microstructure, and the electrical parameters of the equivalent uniform material are obtained through sweep parameter fitting according to the periodic weaving structure modeling.

7. The method of claim 6, wherein, The low-conductivity woven carbon fiber composite material has a bulk conductivity of less than 1000S / m after being processed and formed as a whole.

8. A computer-readable storage medium storing a computer program, the computer program comprising instructions that, when executed by a computer, cause the computer to perform the method of any one of claims 1-7. The computer program is executed by the processor to realize the steps of the method according to any one of claims 1-7.

9. A low conductivity composite aircraft lightning effect simulation evaluation apparatus comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: The processor executes the computer program to realize the steps of the method according to any one of claims 1-7.

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