Method and system for estimating target laser power density required to burn through protective materials

Abstract

The present application provides a method and system for estimating the on-target laser power density required to burn through protective materials. The method of the present application includes: constructing a tightly coupled model between fluid, structural heat transfer, and laser through several sets of protective material ablation simulation tests; using the tightly coupled model to analyze the factors affecting the laser ablation characteristics of the protective material to obtain the main influencing factors; conducting simulation tests on the main influencing factors under different working conditions to obtain the laser ablation characteristics of the protective material under different main influencing factors, and then establishing a laser ablation database for protective materials; obtaining the ablation rate required to burn through the protective material, and obtaining the on-target laser power density required to burn through the protective material through the protective material laser ablation database and the required ablation rate. The present application can quickly predict the on-target laser power density required to burn through aircraft protective materials under flight conditions, thereby providing technical support for future aircraft thermal protection design.

Description

Technical Field

[0001] The present invention relates to the technical field of cross-integration of aerodynamics and lasers, and in particular to a method and system for estimating target laser power density required for burning through protective materials. Background Art

[0002] Future warfare will be unmanned, information-based, and intelligent. Satellites, missiles, and drones will become the primary weapons of warfare, and effectively destroying them will occupy the commanding heights of the battlefield. High-energy laser weapons are directed energy weapons that use laser beams to track targets, neutralize them, or directly damage them. They offer advantages such as concentrated energy, rapid propagation, agile response, and high cost-effectiveness. Their damage mechanism and operational methods differ from those of traditional chemical energy weapons. They damage target aircraft sensors, temporarily or permanently eliminating their detection capabilities, and damage target aircraft structures, rendering them unable to complete their missions.

[0003] After a laser weapon locks onto a target aircraft, it fires a laser. The laser irradiates the aircraft's structure, causing localized high temperatures in the aircraft's protective materials, leading to ablation and even burn-through, causing the aircraft's structure to disintegrate. When designing future aircraft thermal protection, laser ablation factors, such as the laser-to-target power density required to burn through the protective material, need to be considered. Therefore, it is necessary to evaluate the protective material's ablation resistance, that is, what target laser power density will burn through the protective material. Laser ablation damage is a multidisciplinary coupling problem involving lasers, aerodynamics, and structures. Currently, the ablation rate of protective materials under flight conditions is primarily determined through wind tunnel testing and numerical calculations. However, the target laser power density required to burn through the protective material is a reverse design problem, and research on this issue is extremely limited. Therefore, there is an urgent need to establish a method for estimating the target laser power density required to burn through aircraft protective materials under flight conditions to support future aircraft thermal protection design. Summary of the Invention

[0004] The purpose of the present invention is to provide a method and system for estimating the target laser power density required for burning through protective materials, aiming to solve the above-mentioned problems in the prior art.

[0005] An embodiment of the present invention provides a method for estimating the target laser power density required to burn through a protective material, comprising:

[0006] Through several sets of protective material ablation simulation tests, a tightly coupled model between fluid, structural heat transfer, and laser was established;

[0007] The factors affecting the laser ablation characteristics of the protective material are analyzed using the tightly coupled model to obtain the main influencing factors;

[0008] Conducting simulation tests on the main influencing factors under different working conditions to obtain laser ablation characteristics of the protective material under different main influencing factors, and establishing a laser ablation database of the protective material based on the laser ablation characteristics of the protective material under different main influencing factors;

[0009] The ablation rate required for burning through the protective material is obtained, and the target laser power density required for burning through the protective material is obtained through the protective material laser ablation database and the required ablation rate.

[0010] An embodiment of the present invention provides a system for estimating the target laser power density required for burning through a protective material, comprising:

[0011] A building block for building a tightly coupled model between fluid, structural heat transfer, and laser through several sets of protective material ablation simulation tests;

[0012] An analysis module, configured to analyze factors affecting the laser ablation characteristics of the protective material using the tightly coupled model to obtain the main influencing factors;

[0013] a database module for performing simulation tests on the main influencing factors under different working conditions to obtain the laser ablation characteristics of the protective material under different main influencing factors, and establishing a laser ablation database of the protective material according to the laser ablation characteristics of the protective material under the different main influencing factors;

[0014] The estimation module is used to obtain the ablation rate required to burn through the protective material, and obtain the target laser power density required to burn through the protective material through the protective material laser ablation database and the required ablation rate.

[0015] An embodiment of the present invention also provides an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor. When the computer program is executed by the processor, the steps of the above-mentioned method for estimating the target laser power density required for burning through the protective material are implemented.

[0016] An embodiment of the present invention further provides a computer-readable storage medium storing an information transmission implementation program, which, when executed by a processor, implements the steps of the above-mentioned method for estimating the target laser power density required for burning through the protective material.

[0017] The use of the embodiments of the present invention may provide the following beneficial effects: The embodiments of the present invention establish a method for estimating the target laser power density required for burning through aircraft protective materials under flight conditions, which is used to quickly predict the target laser power density required for burning through aircraft protective materials under flight conditions, and can provide technical support for future aircraft thermal protection design. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate one or more embodiments of this specification or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments recorded in this specification. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 This is a flow chart of a method for estimating the target laser power density required to burn through a protective material according to an embodiment of the present invention;

[0020] Figure 2 is a flow chart of a method for estimating target laser power density required for burn-through of aircraft protective materials according to an embodiment of the present invention;

[0021] Figure 3 This is a flow chart of the ablation database lookup method according to an embodiment of the present invention;

[0022] Figure 4 Schematic diagram of a system for estimating the target laser power density required for burning through protective materials according to an embodiment of the present invention. DETAILED DESCRIPTION

[0023] In order to enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the technical solutions in one or more embodiments of this specification will be clearly and completely described below in conjunction with the drawings in one or more embodiments of this specification. Obviously, the described embodiments are only part of the embodiments of this specification, not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of this document.

[0024] Method Example

[0025] According to an embodiment of the present invention, a method for estimating the target laser power density required to burn through a protective material is provided. Figure 1 FIG. 1 is a flow chart of a method for estimating the target laser power density required to burn through the protective material according to an embodiment of the present invention. Figure 1 As shown, the method for estimating the target laser power density required to burn through the protective material according to an embodiment of the present invention specifically includes:

[0026] Step S101, constructing a tightly coupled model among fluid, structural heat transfer, and laser through several sets of protective material ablation simulation tests;

[0027] Step S102: Analyze the factors affecting the laser ablation characteristics of the protective material using the tightly coupled model to obtain the main influencing factors, which specifically include:

[0028] Under flight conditions, the tightly coupled model is used to analyze factors affecting the laser ablation characteristics of the protective material using a univariate analysis method to obtain several influencing factors, and sensitivity analysis is performed on the several influencing factors to obtain the main influencing factors;

[0029] The main influencing factors include the incoming flow state of the target aircraft and the laser characteristics;

[0030] The incoming flow state of the target aircraft includes flight Mach number and flight altitude;

[0031] The laser characteristics include the laser power density to the target;

[0032] Step S103, performing simulation tests on the main influencing factors under different working conditions to obtain the laser ablation characteristics of the protective material under different main influencing factors, and establishing a laser ablation database of protective materials based on the laser ablation characteristics of the protective materials under different main influencing factors, specifically including:

[0033] Taking flight Mach number, flight altitude, target laser power density and protective material laser ablation rate as variables, simulation tests were carried out under different working conditions by setting different flight Mach numbers, flight altitudes and target laser power densities. The protective material laser ablation rates under different flight Mach numbers, flight altitudes and target laser power densities were obtained, and the rates were sorted in order according to target laser power density, flight Mach number and flight altitude to establish a protective material laser ablation database.

[0034] Step S104, obtaining the ablation rate required to burn through the protective material, and obtaining the target laser power density required to burn through the protective material through the protective material laser ablation database and the required ablation rate, specifically includes:

[0035] Obtaining the thickness of the protective material and the laser irradiation time, calculating the ablation rate required to burn through the protective material using the thickness of the protective material and the laser irradiation time, and comparing the required ablation rate with the laser ablation rate in the laser ablation database of the protective material. If the required ablation rate is greater than the maximum laser ablation rate in the database, it indicates that the laser intensity of the laser is insufficient to burn through the protective material under the current laser irradiation time;

[0036] If the required ablation rate is less than the maximum laser ablation rate in the database, the current flight Mach number and flight altitude of the target aircraft are compared with the maximum flight Mach number and maximum flight altitude in the database respectively. If any value is greater than the maximum value in the database, it indicates that the flight Mach number and / or flight altitude are out of range, and the data in the protective material laser ablation database needs to be supplemented; if any value is less than the maximum value in the database, the target laser power density range is preliminarily determined based on the required ablation rate, and the target laser power density required to burn through the protective material is obtained by multiple interpolation within the target laser power density range; if both values ​​are equal to the maximum values ​​in the database, the target laser power density corresponding to the flight Mach number and flight altitude is used as the target laser power density required to burn through the protective material;

[0037] If the required ablation rate is equal to the maximum laser ablation rate in the database, the target laser power density corresponding to the laser ablation rate is used as the target laser power density required to burn through the protective material.

[0038] The above technical solution of the embodiment of the present invention is described in detail below in conjunction with the specific situation of the method for estimating the target laser power density required to burn through the protective material according to the embodiment of the present invention.

[0039] The embodiment of the present invention proposes an estimation method for the target laser power density required for laser irradiation and burn-through of aircraft protective materials under flight conditions. Based on the input parameters (the thickness of the aircraft protective material and the laser irradiation time), the output (the target laser power density required for burn-through of the aircraft protective material) can be quickly obtained, which can preliminarily evaluate the laser resistance of the protective material and provide technical support for future aircraft thermal protection design. The estimation method proposed in the embodiment of the present invention first establishes an aerodynamic / structural / laser tight coupling model to study the influence of parameters on laser ablation characteristics and determine the main influencing parameters. Then, a numerical operating condition table is designed to establish an aircraft protective material ablation rate database. Finally, the required target laser power density is obtained by multiple interpolation table lookups based on the protective material thickness and laser irradiation time.

[0040] The specific implementation steps are as follows:

[0041] 1) Laser ablation modeling of aircraft protective materials

[0042] Based on Fluent software, a tightly coupled model of compressible fluid / structural heat transfer / laser was established. The SST model was used as the turbulence model. The laser was simulated by setting a heat source at the solid-gas interface, and the ablation was simulated by the surface chemical reaction at the solid-gas interface.

[0043] 2) Effects of parameters on laser ablation characteristics of aircraft protective materials

[0044] Analyze which parameters will affect the laser ablation characteristics of aircraft protective materials, set up corresponding numerical simulation conditions, study the influence of parameters on the ablation characteristics of aircraft protective materials, and conduct parameter sensitivity analysis to find the main influencing factors.

[0045] 3) Establish a laser ablation database for aircraft protective materials

[0046] According to the determined main influencing factors, appropriate working conditions are added to obtain the laser ablation characteristics under different main influencing factors, and establish a laser ablation database for aircraft protective materials.

[0047] 4) Establish a method to estimate the target laser power density required to burn through aircraft protective materials

[0048] Based on the thickness of the aircraft protective material and the laser irradiation time, the laser ablation rate required to burn through the aircraft protective material is calculated. According to the ablation rate and flight conditions, the target laser power range is determined according to the ablation rate in the laser database. Multiple interpolations are performed according to the flight Mach number, flight altitude and ablation rate to obtain the target laser power density required to burn through the aircraft protective material.

[0049] The embodiment of the present invention establishes a method flow for estimating the target laser power density required for burning through aircraft protective materials under flight conditions, such as Figure 2 As shown, including:

[0050] 1) Based on Fluent software, for the fluid part, a density-based solver was selected, the SST turbulence model was adopted, and multi-component surface reaction was selected to simulate ablation. The surface reaction was turned on at the fluid-solid interface, and a heat source was set at the fluid-solid interface to simulate laser loading. The ablation rate was obtained by dividing the protective material consumption by the density of the protective material. The change of the ablation rate with the laser loading time was recorded. The ablation rate quickly reached a stable value with laser loading, and this stable value was used as the ablation rate under this condition.

[0051] 2) Under flight conditions, factors that may affect the ablation characteristics of protective materials include the incoming airflow state of the target aircraft (flight Mach number and flight altitude, etc.) and the laser characteristics (laser power density Q at the target). A single-variable method was used to study the influence of these parameters on the ablation characteristics of protective materials, and a sensitivity analysis of the parameters was performed. The results showed that the laser power density at the target has the greatest impact on the ablation rate, followed by the flight Mach number, and the flight altitude has the smallest impact.

[0052] 3) Set the simulation working conditions. Considering the current laser power level, the target laser power density is set to 2, 4, 6, 8, 10, 12, 16, and 20 kW / cm 2The flight altitude of the target aircraft is set to 8, 12, 16, and 23 km, and the flight Mach number is set to 2, 4, and 6. With the flight Mach number, flight altitude, target laser power density, and ablation rate as variables, the laser ablation database of protective materials is established by sorting them according to the target laser power density, flight Mach number, and flight altitude.

[0053] 4) According to the thickness of the protective material and the laser irradiation time, the ablation rate required to burn through the protective material is calculated; then, according to the ablation rate, a table is looked up in the ablation database, such as Figure 3 As shown. The specific table lookup method is as follows: first compare it with the maximum ablation rate in the database. If it is greater than the maximum ablation rate in the database, it indicates that the laser intensity level of the laser cannot make it burn through under the current laser irradiation time, and then output: "The current laser level cannot make it burn through"; if it is less than the maximum ablation rate in the database, first compare the flight Mach number and flight altitude with the flight Mach number and flight altitude in the database respectively. If it exceeds the maximum value in the database, then output: "The flight Mach number and / or flight altitude are out of range, please supplement the database data"; if the flight Mach number and flight altitude are within the database range, first search the database according to the required ablation rate and the target laser power density Q, and preliminarily determine the target. The target laser power density range is Q1-Q2; then, according to the flight Mach number Ma, the flight Mach numbers of Q1 and Q2 in the database are interpolated respectively to obtain the corresponding ablation rates of (Q1, Ma, H1), (Q2, Ma, H1) and (Q1, Ma, H2), (Q2, Ma, H2); then, according to the flight altitude H, (Q1, Ma, H1), (Q2, Ma, H1) and (Q1, Ma, H2), (Q2, Ma, H2) are interpolated respectively to obtain the ablation rates of (Q1, Ma, H) and (Q2, Ma, H); then, according to the required ablation rate R, (Q1, Ma, H) and (Q2, Ma, H) are interpolated to obtain the required target laser power density.

[0054] System Example

[0055] According to an embodiment of the present invention, a system for estimating the target laser power density required to burn through a protective material is provided. Figure 4 FIG. 1 is a schematic diagram of a system for estimating the target laser power density required to burn through the protective material according to an embodiment of the present invention. Figure 4 As shown, the system for estimating the target laser power density required to burn through the protective material according to an embodiment of the present invention specifically includes:

[0056] A construction module 40 is used to construct a tightly coupled model between fluid, structural heat transfer and laser through several sets of protective material ablation simulation tests;

[0057] The analysis module 42 is used to analyze the factors affecting the laser ablation characteristics of the protective material using the tightly coupled model to obtain the main influencing factors, specifically for:

[0058] Under flight conditions, the tightly coupled model is used to analyze factors affecting the laser ablation characteristics of the protective material using a univariate analysis method to obtain several influencing factors, and sensitivity analysis is performed on the several influencing factors to obtain the main influencing factors;

[0059] The main influencing factors include the incoming flow state of the target aircraft and the laser characteristics;

[0060] The incoming flow state of the target aircraft includes flight Mach number and flight altitude;

[0061] The laser characteristics include the laser power density to the target;

[0062] The database module 44 is used to perform simulation tests on the main influencing factors under different working conditions to obtain the laser ablation characteristics of the protective material under different main influencing factors, and to establish a laser ablation database of protective materials based on the laser ablation characteristics of the protective materials under different main influencing factors, specifically for:

[0063] Taking flight Mach number, flight altitude, target laser power density and protective material laser ablation rate as variables, simulation tests were carried out under different working conditions by setting different flight Mach numbers, flight altitudes and target laser power densities. The protective material laser ablation rates under different flight Mach numbers, flight altitudes and target laser power densities were obtained, and the rates were sorted in order according to target laser power density, flight Mach number and flight altitude to establish a protective material laser ablation database.

[0064] The estimation module 46 is used to obtain the ablation rate required to burn through the protective material, and obtain the target laser power density required to burn through the protective material through the protective material laser ablation database and the required ablation rate, specifically for:

[0065] Obtaining the thickness of the protective material and the laser irradiation time, calculating the ablation rate required to burn through the protective material using the thickness of the protective material and the laser irradiation time, and comparing the required ablation rate with the laser ablation rate in the laser ablation database of the protective material. If the required ablation rate is greater than the maximum laser ablation rate in the database, it indicates that the laser intensity of the laser is insufficient to burn through the protective material under the current laser irradiation time;

[0066] If the required ablation rate is less than the maximum laser ablation rate in the database, the current flight Mach number and flight altitude of the target aircraft are compared with the maximum flight Mach number and maximum flight altitude in the database respectively. If any value is greater than the maximum value in the database, it indicates that the flight Mach number and / or flight altitude are out of range, and the data in the protective material laser ablation database needs to be supplemented; if any value is less than the maximum value in the database, the target laser power density range is preliminarily determined based on the required ablation rate, and the target laser power density required to burn through the protective material is obtained by multiple interpolation within the target laser power density range; if both values ​​are equal to the maximum values ​​in the database, the target laser power density corresponding to the flight Mach number and flight altitude is used as the target laser power density required to burn through the protective material;

[0067] If the required ablation rate is equal to the maximum laser ablation rate in the database, the target laser power density corresponding to the laser ablation rate is used as the target laser power density required to burn through the protective material.

[0068] The embodiment of the present invention is a system embodiment corresponding to the above-mentioned method embodiment. The specific operations of each module can be understood by referring to the description of the method embodiment, which will not be repeated here.

[0069] In summary, the embodiments of the present invention have the following beneficial effects:

[0070] 1) The method for estimating the target laser power density required to burn through aircraft protective materials, established in an embodiment of the present invention, can quickly determine the target laser power density required to burn through aircraft protective materials based on the thickness of the aircraft protective materials and the laser irradiation time;

[0071] 2) Based on the target laser power density required to burn through aircraft protective materials given in the embodiments of the present invention, it is possible to quickly assess whether current protective materials can be burned through by existing laser weapons;

[0072] 3) The present invention takes into account the impact of real-world flight conditions on laser ablation of aircraft protective materials and establishes a corresponding database based on certain standard rules, accumulating data samples for laser ablation damage.

[0073] 4) The table lookup method for the aircraft protective material ablation rate database provided in the embodiment of the present invention can be extended to other characteristics or performance evaluations involving the influence of multiple parameters.

[0074] Device Example 1

[0075] An embodiment of the present invention provides an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the computer program implements the steps described in the method embodiment when executed by the processor.

[0076] Device Example 2

[0077] An embodiment of the present invention provides a computer-readable storage medium, on which a program for implementing information transmission is stored. When the program is executed by a processor, the steps described in the method embodiment are implemented.

[0078] The computer-readable storage medium in this embodiment includes, but is not limited to, ROM, RAM, magnetic disk, or optical disk.

[0079] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for estimating the target laser power density required to burn through protective materials, characterized in that include: Through several sets of protective material ablation simulation tests, a tightly coupled model between fluid, structural heat transfer, and laser was established; The factors affecting the laser ablation characteristics of the protective material are analyzed using the tightly coupled model to obtain the main influencing factors; Conducting simulation tests on the main influencing factors under different working conditions to obtain laser ablation characteristics of the protective material under different main influencing factors, and establishing a laser ablation database of the protective material based on the laser ablation characteristics of the protective material under different main influencing factors; Obtaining the ablation rate required to burn through the protective material, and obtaining the target laser power density required to burn through the protective material through the protective material laser ablation database and the required ablation rate, specifically including: Obtaining the thickness of the protective material and the laser irradiation time, calculating the ablation rate required to burn through the protective material using the thickness of the protective material and the laser irradiation time, and comparing the required ablation rate with the laser ablation rate in the laser ablation database of the protective material. If the required ablation rate is greater than the maximum laser ablation rate in the database, it indicates that the laser intensity of the laser is insufficient to burn through the protective material under the current laser irradiation time; If the required ablation rate is less than the maximum laser ablation rate in the database, the current flight Mach number and flight altitude of the target aircraft are compared with the maximum flight Mach number and maximum flight altitude in the database respectively. If any value is greater than the maximum value in the database, it indicates that the flight Mach number and / or flight altitude are out of range, and the data in the protective material laser ablation database needs to be supplemented; if any value is less than the maximum value in the database, the target laser power density range is preliminarily determined based on the required ablation rate, and the target laser power density required to burn through the protective material is obtained by multiple interpolation within the target laser power density range; if both values ​​are equal to the maximum values ​​in the database, the target laser power density corresponding to the flight Mach number and flight altitude is used as the target laser power density required to burn through the protective material; If the required ablation rate is equal to the maximum laser ablation rate in the database, the target laser power density corresponding to the laser ablation rate is used as the target laser power density required to burn through the protective material.

2. The method according to claim 1, characterized in that The factors affecting the laser ablation characteristics of protective materials were analyzed using the tightly coupled model, and the main influencing factors were found to be: Under flight conditions, the tightly coupled model is used to analyze factors affecting the laser ablation characteristics of the protective material using a univariate analysis method to obtain several influencing factors, and sensitivity analysis is performed on the several influencing factors to obtain the main influencing factors; The main influencing factors include the incoming flow state of the target aircraft and the laser characteristics; The incoming flow state of the target aircraft includes flight Mach number and flight altitude; The laser characteristics include the laser power density to the target.

3. The method according to claim 2, characterized in that Conducting simulation tests on the main influencing factors under different working conditions to obtain the laser ablation characteristics of the protective material under different main influencing factors, and establishing a laser ablation database of protective materials based on the laser ablation characteristics of the protective materials under different main influencing factors specifically includes: Taking the flight Mach number, flight altitude, target laser power density and protective material laser ablation rate as variables, simulation tests were carried out under different working conditions by setting different flight Mach numbers, flight altitudes and target laser power densities. The protective material laser ablation rates under different flight Mach numbers, flight altitudes and target laser power densities were obtained, and the rates were sorted in sequence according to the target laser power density, flight Mach number and flight altitude to establish a protective material laser ablation database.

4. A system for estimating the target laser power density required to burn through protective materials, characterized in that include: A building block for building a tightly coupled model between fluid, structural heat transfer, and laser through several sets of protective material ablation simulation tests; An analysis module, configured to analyze factors affecting the laser ablation characteristics of the protective material using the tightly coupled model to obtain the main influencing factors; a database module for performing simulation tests on the main influencing factors under different working conditions to obtain the laser ablation characteristics of the protective material under different main influencing factors, and establishing a laser ablation database of the protective material according to the laser ablation characteristics of the protective material under the different main influencing factors; The estimation module is used to obtain the ablation rate required to burn through the protective material, and obtain the target laser power density required to burn through the protective material through the protective material laser ablation database and the required ablation rate. Specifically, it is used to: Obtaining the thickness of the protective material and the laser irradiation time, calculating the ablation rate required to burn through the protective material using the thickness of the protective material and the laser irradiation time, and comparing the required ablation rate with the laser ablation rate in the laser ablation database of the protective material. If the required ablation rate is greater than the maximum laser ablation rate in the database, it indicates that the laser intensity of the laser is insufficient to burn through the protective material under the current laser irradiation time; If the required ablation rate is less than the maximum laser ablation rate in the database, the current flight Mach number and flight altitude of the target aircraft are compared with the maximum flight Mach number and maximum flight altitude in the database respectively. If any value is greater than the maximum value in the database, it indicates that the flight Mach number and / or flight altitude are out of range, and the data in the protective material laser ablation database needs to be supplemented; if any value is less than the maximum value in the database, the target laser power density range is preliminarily determined based on the required ablation rate, and the target laser power density required to burn through the protective material is obtained by multiple interpolation within the target laser power density range; if both values ​​are equal to the maximum values ​​in the database, the target laser power density corresponding to the flight Mach number and flight altitude is used as the target laser power density required to burn through the protective material; If the required ablation rate is equal to the maximum laser ablation rate in the database, the target laser power density corresponding to the laser ablation rate is used as the target laser power density required to burn through the protective material.

5. The system according to claim 4, characterized in that The analysis module is specifically used for: Under flight conditions, the tightly coupled model is used to analyze factors affecting the laser ablation characteristics of the protective material using a univariate analysis method to obtain several influencing factors, and sensitivity analysis is performed on the several influencing factors to obtain the main influencing factors; The main influencing factors include the incoming flow state of the target aircraft and the laser characteristics; The incoming flow state of the target aircraft includes flight Mach number and flight altitude; The laser characteristics include the laser power density to the target.

6. The system according to claim 5, characterized in that The database module is specifically used for: Taking the flight Mach number, flight altitude, target laser power density and protective material laser ablation rate as variables, simulation tests were carried out under different working conditions by setting different flight Mach numbers, flight altitudes and target laser power densities. The protective material laser ablation rates under different flight Mach numbers, flight altitudes and target laser power densities were obtained, and the rates were sorted in sequence according to the target laser power density, flight Mach number and flight altitude to establish a protective material laser ablation database.

7. An electronic device, characterized in that: include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the computer program is executed by the processor, the steps of the method for estimating the target laser power density required for burning through a protective material as claimed in any one of claims 1 to 3 are implemented.

8. A computer-readable storage medium, characterized in that The computer-readable storage medium stores an information transmission implementation program, and when the program is executed by a processor, the steps of the target laser power density estimation method required for burning through the protective material are implemented as described in any one of claims 1 to 3.

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