Aerodynamic optical transmission model construction method, system, equipment and medium

Abstract

The invention provides an aerodynamic optical transmission model construction method, system, device and medium, and the construction method comprises the steps: obtaining the refractive index distribution of a flow field around an aircraft, constructing a flow field lens model, obtaining the temperature distribution of an optical system, and obtaining the relative refractive index distribution of a ray tracing point; the flow field lens model and the optical lens model are combined to form an equivalent lens superposition model, the input of the equivalent lens superposition model is set parameters, refractive index distribution, temperature distribution and relative refractive index distribution of the optical system, and the output of the equivalent lens superposition model is light transmission distortion characteristics. According to the method, the flow field lens model and the optical lens model are combined to simplify the model, and the whole output process of the light in the flow field and the optical lens can be directly calculated by adopting an equivalent lens method, so that the calculation efficiency can be greatly improved.

Description

Technical Field

[0001] The present application relates to the field of optical technology, and in particular to a method, system, device and medium for constructing a pneumatic optical transmission model. Background Art

[0002] When an aircraft flies at high speed in the atmosphere, the optical window of the imaging detection system interacts with the airflow to form a flow field with non-uniform temperature and density distribution, which interferes with the image transmission of the optical imaging detection system, causing the target image to shift, blur, and jitter, as well as energy dispersion. This effect is called the aero-optical effect.

[0003] In order to study the impact of aero-optical effects on the performance of imaging detection systems, it is necessary to simulate the aero-optical effects and obtain distorted image data. Since the flow field near the optical window is affected by shock waves, boundary layers, turbulence, etc., the gas density is unevenly distributed, which affects the distribution of the gas refractive index, resulting in the deflection of the light transmission path in the flow field. Ray tracing is usually used in combination with grid discretization to calculate the light deflection in the flow field. This method requires discretization of the entire field space and cannot use existing commercial software. It generates a huge amount of calculation and data, and it is difficult to ensure the calculation accuracy. Summary of the invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, the present application aims to provide a method, system, device and medium for constructing an aerodynamic optical transmission model.

[0005] In a first aspect, the present application provides a method for constructing an aerodynamic optical transmission model, comprising the following steps:

[0006] S1. Obtain the refractive index distribution of the flow field around the aircraft;

[0007] S2. constructing a flow field lens model according to the refractive index distribution, wherein the input of the flow field lens model is the refractive index distribution, and the output is the optical path difference;

[0008] S3. Obtaining a temperature distribution of an optical system, wherein the optical system includes a plurality of optical lenses, and the temperature distribution is used to characterize the temperature of each position of each of the optical lenses;

[0009] S4. Obtaining a relative refractive index distribution of the ray tracing point according to the temperature distribution, wherein the relative refractive index distribution is the relative refractive index of the ray tracing point of each of the optical lenses;

[0010] S5. Combine the flow field lens model and the optical lens model to form an equivalent lens superposition model, wherein the input of the equivalent lens superposition model is the geometric parameters of the optical system, the refractive index distribution, the temperature distribution and the relative refractive index distribution, and the output is the light transmission distortion characteristics, wherein the optical lens model is a model of the lens group in the optical system of the aircraft.

[0011] According to the technical solution provided in the embodiment of the present application, step S1 includes the following steps:

[0012] S10. Acquire flow field information of the aircraft flow field, wherein the flow field information includes temperature, pressure and density data of the aircraft flow field;

[0013] S11. Obtaining the refractive index distribution according to the flow field information.

[0014] According to the technical solution provided in the embodiment of the present application, step S2 includes the following steps:

[0015] S21. Discretize the flow field using the finite element method to obtain multiple flow field sub-units;

[0016] S22. Obtaining a flow field lens optical structure set by a surface fitting method, wherein the flow field lens optical structure set includes all the flow field sub-units and optical structure parameters corresponding to each of the flow field sub-units, wherein the optical structure parameters include at least refractive index, thickness, and surface shape;

[0017] S23. Constructing the flow field lens model according to the arrangement of the flow field refractive index gradients and the set of flow field lens optical structures.

[0018] According to the technical solution provided in the embodiment of the present application, step S3 includes the following steps:

[0019] S31. Acquire thermal environment conditions and optical system structural parameters of the optical system, wherein the thermal environment conditions include heat flow and enthalpy value on the surface of the optical system, and the optical system structural parameters include geometric parameters and material parameters of the optical system;

[0020] S32. Obtain the temperature distribution of the optical system by performing heat transfer calculation on the thermal environment conditions and the structural parameters of the optical system.

[0021] According to the technical solution provided in the embodiment of the present application, step S4 includes the following steps:

[0022] S41. Obtaining the coordinates of the initial tracking point;

[0023] S42. Obtaining the initial tracing point temperature corresponding to the initial tracing point coordinates according to the initial tracing point coordinates and the temperature distribution;

[0024] S43. Calculate the relative refractive index of the initial tracing point according to the temperature of the initial tracing point, and record it as the relative refractive index of the initial tracing point;

[0025] S44. Obtaining the coordinates of the next tracing point according to the relative refractive index of the initial tracing point;

[0026] S45. Update the coordinates of the initial tracing point to the coordinates of the next tracing point, repeat steps S42-S45, and obtain the relative refractive index of all the light tracing points, that is, the refractive index distribution.

[0027] According to the technical solution provided in the embodiment of the present application, step S42 includes the following steps:

[0028] S421. Fitting the discrete temperature distribution into a temperature continuous function, wherein the temperature continuous function is used to characterize the temperature corresponding to the coordinates of the tracking point;

[0029] S422. Input the coordinates of the initial tracing point into the temperature continuity function to obtain the temperature of the initial tracing point.

[0030] According to the technical solution provided in the embodiment of the present application, the relative refractive index of the initial tracing point is calculated according to the temperature of the initial tracing point by the following formula:

[0031]

[0032] Where λ is the wavelength; T is the temperature of the tracing point; n r is the relative refractive index at the tracing point; n a is the absolute refractive index of the optical material; n is the absolute refractive index of the atmosphere.

[0033] In a second aspect, the present application provides a pneumatic optical transmission model construction system for implementing the pneumatic optical transmission model construction method described above, the system comprising:

[0034] a first calculation module, the first calculation module being configured to obtain a refractive index distribution of an aircraft flow field;

[0035] A first construction module, wherein the first construction module is configured to construct a flow field lens model according to the refractive index distribution, wherein the input of the flow field lens model is the refractive index distribution, and the output is an optical path difference;

[0036] A first acquisition module, wherein the first acquisition module is configured to acquire a temperature distribution of an optical system, wherein the optical system includes a plurality of optical lenses, and the temperature distribution is used to characterize a temperature at each position of each of the optical lenses;

[0037] a third calculation module, the third calculation module being configured to obtain a relative refractive index distribution of a ray tracing point according to the temperature distribution, the relative refractive index distribution being the relative refractive index of the ray tracing point of each of the optical lenses (21);

[0038] A first combination module, wherein the first combination module is configured to combine the flow field lens model and the optical lens model to form an equivalent lens superposition model, wherein the input of the equivalent lens superposition model is the geometric parameters of the optical system, the refractive index distribution, the temperature distribution and the relative refractive index distribution, and the output is the light transmission distortion characteristics, wherein the optical lens model is a model of the lens group in the optical system of the aircraft.

[0039] In a third aspect, the present application proposes a terminal device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the aerodynamic-optical transmission model construction method as described above when executing the computer program.

[0040] In a fourth aspect, the present application proposes a computer-readable storage medium having a computer program stored thereon, and when the computer program is executed by a processor, the steps of the aerodynamic-optical transmission model construction method as described above are implemented.

[0041] In summary, the present application proposes a method for constructing an aerodynamic optical transmission model, by obtaining the refractive index distribution of the flow field around the aircraft, constructing a flow field lens model, and obtaining the temperature distribution of the optical system, obtaining the relative refractive index distribution of the light tracing point, and then combining the flow field lens model and the optical lens model to form an equivalent lens superposition model, whose input is the collective parameters, refractive index distribution, temperature distribution, and relative refractive index distribution of the optical system, and the output is the light transmission distortion characteristics. The present application simplifies the model by combining the flow field lens model and the optical lens model, and adopts the method of equivalent lens, which can greatly improve the calculation efficiency by directly calculating the entire output process of light in the flow field and the optical lens. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 A flow chart of a method for constructing an aerodynamic optical transmission model provided in an embodiment of the present application;

[0043] Figure 2 A schematic diagram of the structure of the aero-optical transmission model provided in this application;

[0044] Figure 3 A schematic diagram of the structure of the terminal device provided for this application.

[0045] The text annotations in the figure represent:

[0046] 1. Flow field lens group; 11. Flow field lens; 2. Optical lens group; 21. Optical lens; 700. Computer system; 701. CPU; 702. ROM; 703. RAM; 704. Bus; 705. I / O interface; 706. Input part; 707. Output part; 708. Storage part; 709. Communication part; 710. Drive; 711. Removable media. DETAILED DESCRIPTION

[0047] The present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the relevant invention, rather than to limit the invention. It is also necessary to explain that, for ease of description, only the parts related to the invention are shown in the accompanying drawings.

[0048] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0049] Example 1

[0050] As mentioned in the background technology, the present application proposes a method for constructing an aerodynamic optical transmission model, comprising the following steps:

[0051] S1. Obtaining the refractive index distribution of the flow field around the aircraft; comprising the following steps:

[0052] S10. Acquire flow field information of the aircraft flow field, wherein the flow field information includes temperature, pressure and density data of the aircraft flow field;

[0053] Among them, the flow field around the aircraft is simulated by using the flow field simulation software Fluent, and the incoming flow data such as flight altitude, Mach number, angle of attack, etc. are input to simulate the temperature, pressure and density distribution of the flow field.

[0054] S11. Obtaining the refractive index distribution according to the flow field information;

[0055] The refractive index distribution is used to describe the spatial variation of the refractive index in the flow field. The flow field generally refers to the area formed by the flow of fluid around an object, and includes the following steps:

[0056] S111. Obtaining the air refractive index;

[0057] The air refractive index is calculated by the following formula:

[0058]

[0059] Where n0 represents the refractive index of air under standard atmospheric conditions; λ represents the wavelength, which is determined according to the band used.

[0060] S112. Calculate the refractive index distribution by the air refractive index; calculate the gas refractive index by the following formula:

[0061]

[0062] In the formula, P0 is the atmospheric pressure, T is the standard atmospheric temperature, and Pc is the water vapor pressure. The above parameters are determined according to the actual situation. g is the gas refractive index in the actual state; the gas refractive index at each point in the flow field can be calculated by the above formula, thereby obtaining the refractive index distribution.

[0063] S2. constructing a flow field lens model according to the refractive index distribution, wherein the input of the flow field lens model is the refractive index distribution and the output is the optical path difference; step S2 comprises the following steps:

[0064] S21. Discretize the flow field using the finite element method to obtain multiple flow field sub-units;

[0065] S22. Obtaining an optical structure set of the flow field lens 11 by a surface fitting method, wherein the optical structure set of the flow field lens 11 includes all the flow field sub-units and optical structure parameters corresponding to each of the flow field sub-units, wherein the optical structure parameters include at least a refractive index, a thickness, and a surface shape;

[0066] S23. Construct the flow field lens model according to the arrangement of the flow field refractive index gradient and the optical structure set of the flow field lens 11.

[0067] Among them, in actual scenes, the refractive index of the flow field in front of the optical lens is distributed in a gradient, and this arrangement is the refractive index gradient of the flow field. Figure 2 As shown, the flow field lens model includes a plurality of flow field lenses 1, and the flow field lens 1 includes a plurality of flow field lenses 11 distributed and arranged in sequence, and each of the flow field lenses 11 has different optical structure parameters. The optical path difference is the output of the flow field lens model, which reflects the difference in the light propagation path of the light in the flow field due to factors such as different refractive indices and thicknesses; it more accurately simulates the transmission and distortion of light in the entire system, and improves the accuracy and reliability of modeling.

[0068] S3. Obtaining the temperature distribution of the optical system, wherein the optical system includes a plurality of optical lenses 21, and the temperature distribution is used to characterize the temperature of each position of each of the optical lenses 21;

[0069] Among them, Figure 2As shown, the optical system includes an optical lens group 2, and the optical lens group 2 includes a plurality of optical lenses 21 distributed and arranged in sequence. Step S3 includes the following steps:

[0070] S31. Acquire thermal environment conditions and optical system structural parameters of the optical system, wherein the thermal environment conditions include heat flow and enthalpy value on the surface of the optical system, and the optical system structural parameters include geometric parameters and material parameters of the optical system;

[0071] Wherein, the optical system structural parameters are obtained through aerodynamic simulation calculation.

[0072] S32. Obtain the temperature distribution of the optical system by performing heat transfer calculation on the thermal environment conditions and the structural parameters of the optical system.

[0073] Optionally, the heat transfer calculation of the optical lens 21 is performed based on the finite element method using abaqus engineering simulation finite element software; the temperature distribution of the optical system is used to characterize the temperature conditions at each position of each optical lens 21 in the optical system.

[0074] S4. Obtaining the relative refractive index distribution of the ray tracing point according to the temperature distribution, wherein the relative refractive index distribution is the relative refractive index of the ray tracing point of each of the optical lenses 21; step S4 comprises the following steps:

[0075] S41. Obtaining the coordinates of the initial tracking point;

[0076] Among them, the coordinates of the initial tracing point are the coordinates of the initial tracing point, and the initial tracing point is the intersection of the light entering the first optical lens 21 after passing through the flow field lens 1 and the light exit surface.

[0077] S42. Obtaining the initial tracing point temperature corresponding to the initial tracing point coordinates according to the initial tracing point coordinates and the temperature distribution; Step S42 comprises the following steps:

[0078] S421. Fitting the discrete temperature distribution into a temperature continuous function, wherein the temperature continuous function is used to characterize the temperature corresponding to the coordinates of the tracking point;

[0079] S422. Input the coordinates of the initial tracing point into the temperature continuity function to obtain the temperature of the initial tracing point.

[0080] S43. Calculate the relative refractive index of the initial tracing point according to the temperature of the initial tracing point, and record it as the relative refractive index of the initial tracing point; this is achieved by the following formula:

[0081]

[0082] Where λ is the wavelength; T is the temperature of the tracing point; n r is the relative refractive index at the tracing point; n a is the absolute refractive index of the optical material; n is the absolute refractive index of the atmosphere. Substituting the temperature of the initial tracing point into formula (1) yields the relative refractive index of the initial tracing point. The absolute refractive index of the optical material is also related to the composition and thickness of the optical material, and is generally provided by the material supplier of the optical material.

[0083] Among them, a self-written program that can realize the above formula is loaded into CODE V optical software. After the optical software obtains the temperature of the initial tracing point, it returns to the self-written program to obtain the relative refractive index of the initial tracing point through calculation.

[0084] S44. Obtaining the coordinates of the next tracing point according to the relative refractive index of the initial tracing point;

[0085] Among them, the relative refractive index of the initial tracing point determines the intersection of the light ray on the second optical lens 21 and the light ray exit surface after the light ray passes through the first optical lens in the optical system, that is, the coordinates of the second tracing point.

[0086] S45. Update the coordinates of the initial tracing point to the coordinates of the next tracing point, repeat steps S42-S45, and obtain the relative refractive index of all the light tracing points, that is, the refractive index distribution.

[0087] In summary, the relative refractive index of the previous tracing point will affect the path of the light entering the next optical lens, and affect the intersection of the light and the light exit surface on the next optical lens, that is, affect the coordinates of the next tracing point; iterative calculations are performed in the CODE V optical software, and the number of iterations is determined according to the number of the optical lenses 21 in the optical system, and the number of the optical lenses 21 is determined according to actual conditions.

[0088] S5. Combining the flow field lens model and the optical lens model to form an equivalent lens superposition model, the input of the equivalent lens superposition model is the geometric parameters of the optical system, the refractive index distribution, the temperature distribution and the relative refractive index distribution, and the output is the light transmission distortion characteristics, wherein the optical lens model is a model of the lens group in the optical system of the aircraft;

[0089] Among them, the optical lens model is a lens group model of the optical imaging system on the aircraft. Since the flow field lens model constructed by the aerodynamic-optical effect is a complex physical model, it includes high temperature and high pressure, density gradient changing flow field, turbulence, shock waves and other physical phenomena. It is impossible to use existing commercial software to directly perform the coupling calculation of light transmission and flow field, and numerical simulation modeling is difficult. The grid discretization and ray tracing calculation parts of the model are huge. The present application simplifies the model by combining the flow field lens model and the optical lens model, and adopts the method of equivalent lens. The entire output process of light in the flow field and optical lens can be directly calculated by commercial software, which can greatly improve the calculation efficiency and meet the needs of engineering applications.

[0090] Example 2

[0091] On the basis of Example 1, the present application proposes a pneumatic optical transmission model construction system, which is used to implement the pneumatic optical transmission model construction method described in Example 1. The system includes:

[0092] a first calculation module, the first calculation module being configured to obtain a refractive index distribution of an aircraft flow field;

[0093] A first construction module, wherein the first construction module is configured to construct a flow field lens model according to the refractive index distribution, wherein the input of the flow field lens model is the refractive index distribution, and the output is an optical path difference;

[0094] A first acquisition module, wherein the first acquisition module is configured to acquire a temperature distribution of an optical system, wherein the optical system includes a plurality of optical lenses, and the temperature distribution is used to characterize a temperature at each position of each of the optical lenses;

[0095] a third calculation module, the third calculation module being configured to obtain a relative refractive index distribution of a ray tracing point according to the temperature distribution, the relative refractive index distribution being the relative refractive index of the ray tracing point of each of the optical lenses (21);

[0096] A first combination module, wherein the first combination module is configured to combine the flow field lens model and the optical lens model to form an equivalent lens superposition model, wherein the input of the equivalent lens superposition model is the geometric parameters of the optical system, the refractive index distribution, the temperature distribution and the relative refractive index distribution, and the output is the light transmission distortion characteristics, wherein the optical lens model is a model of the lens group in the optical system of the aircraft.

[0097] Example 3

[0098] like Figure 3As shown, the computer system 700 of the terminal device includes a CPU 701, which can perform various appropriate actions and processes according to the program stored in the ROM 702 or the program loaded from the storage part 708 to the RAM 703. In the RAM 703, various programs and data required for system operation are also stored. The CPU 701, the ROM 702 and the RAM 703 are connected to each other through the bus 704. The I / O interface 705 is also connected to the bus 704. The following components are connected to the I / O interface 705: an input part 706 including a keyboard, a mouse, etc.; an output part 707 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc. and a speaker, etc.; a storage part 708 including a hard disk, etc.; and a communication part 709 including a network interface card such as a LAN card, a modem, etc. The communication part 709 performs communication processing via a network such as the Internet. The drive is also connected to the I / O interface 705 as needed. A removable medium 711, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, or the like, is mounted on the drive 710 as needed, so that a computer program read therefrom is installed into the storage section 708 as needed.

[0099] In particular, according to the embodiments of the present application, the above reference process Figure 1 The described process can be implemented as a computer software program. For example, embodiment 3 of the present application includes a computer program product, which includes a computer program carried on a computer readable medium, and the computer program contains program code for executing the method shown in the flow chart. In such an embodiment, the computer program can be downloaded and installed from a network through a communication part, and / or installed from a removable medium. When the computer program is executed by CPU 701, the above-mentioned functions defined in the present computer system 700 are executed.

[0100] It should be noted that the computer-readable medium shown in the present application may be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present application, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, device or device. In the present application, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. This propagated data signal may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. Computer-readable signal media may also be any computer-readable medium other than computer-readable storage media, which may send, propagate or transmit a program for use by or in conjunction with an instruction execution system, apparatus or device. The program code contained on the computer-readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, optical cable, RF, etc., or any suitable combination of the above.

[0101] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments 3 of the present application. In this regard, each box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the above-mentioned module, program segment or a part of a code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a different order from the order marked in the accompanying drawings. For example, two boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram or flow chart, and the combination of the boxes in the block diagram or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0102] As another aspect, the present application also provides a computer-readable medium, which may be included in the electronic device described in the above embodiment; or may exist independently without being assembled into the electronic device. The above computer-readable medium carries one or more programs, and when the above one or more programs are executed by an electronic device, the electronic device implements the method for constructing an aerodynamic optical transmission model as described in the above embodiment.

[0103] It should be noted that, although several modules or units of the device for action execution are mentioned in the above detailed description, this division is not mandatory. In fact, according to the embodiments disclosed in the present application, the features and functions of two or more modules or units described above can be embodied in one module or unit. On the contrary, the features and functions of one module or unit described above can be further divided into being embodied by multiple modules or units.

[0104] In addition, although the steps of the method in the present application are described in a specific order in the drawings, this does not require or imply that the steps must be performed in this specific order, or that all the steps shown must be performed to achieve the desired results. Additionally or alternatively, some steps may be omitted, multiple steps may be combined into one step, and / or one step may be decomposed into multiple steps, etc.

[0105] Through the description of the above implementations, those skilled in the art can easily understand that the example implementations described here can be implemented by software, or by combining software with necessary hardware.

[0106] The above description is only a preferred embodiment of the present application and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features are replaced with (but not limited to) technical features with similar functions disclosed in the present application.

Claims

1. A method for constructing an aerodynamic optical transmission model, characterized in that: The steps include: S1. Obtain the refractive index distribution of the flow field around the aircraft; S2. constructing a flow field lens model according to the refractive index distribution, wherein the input of the flow field lens model is the refractive index distribution, and the output is the optical path difference; S3. Obtaining a temperature distribution of an optical system, wherein the optical system includes a plurality of optical lenses, and the temperature distribution is used to characterize the temperature of each position of each of the optical lenses; S4. Obtaining a relative refractive index distribution of the ray tracing point according to the temperature distribution, wherein the relative refractive index distribution is the relative refractive index of the ray tracing point of each of the optical lenses (21); S5. Combine the flow field lens model and the optical lens model to form an equivalent lens superposition model, wherein the input of the equivalent lens superposition model is the geometric parameters of the optical system, the refractive index distribution, the temperature distribution and the relative refractive index distribution, and the output is the light transmission distortion characteristics, wherein the optical lens model is a model of the lens group in the optical system of the aircraft.

2. The method for constructing an aero-optical transmission model according to claim 1, characterized in that: Step S1 includes the following steps: S10. Acquire flow field information of the aircraft flow field, wherein the flow field information includes temperature, pressure and density data of the aircraft flow field; S11. Obtaining the refractive index distribution according to the flow field information.

3. The method for constructing an aero-optical transmission model according to claim 1, characterized in that: Step S2 includes the following steps: S21. Discretize the flow field using the finite element method to obtain multiple flow field sub-units; S22. Obtaining a flow field lens optical structure set by a surface fitting method, wherein the flow field lens optical structure set includes all the flow field sub-units and optical structure parameters corresponding to each of the flow field sub-units, wherein the optical structure parameters include at least refractive index, thickness, and surface shape; S23. Constructing the flow field lens model according to the arrangement of the flow field refractive index gradients and the set of flow field lens optical structures.

4. The method for constructing an aero-optical transmission model according to claim 1, characterized in that: Step S3 includes the following steps: S31. Acquire thermal environment conditions and optical system structural parameters of the optical system, wherein the thermal environment conditions include heat flow and enthalpy value on the surface of the optical system, and the optical system structural parameters include geometric parameters and material parameters of the optical system; S32. Obtain the temperature distribution of the optical system by performing heat transfer calculation on the thermal environment conditions and the structural parameters of the optical system.

5. The method for constructing an aero-optical transmission model according to claim 1, characterized in that: Step S4 includes the following steps: S41. Obtaining the coordinates of the initial tracking point; S42. Obtaining the initial tracing point temperature corresponding to the initial tracing point coordinates according to the initial tracing point coordinates and the temperature distribution; S43. Calculate the relative refractive index of the initial tracing point according to the temperature of the initial tracing point, and record it as the relative refractive index of the initial tracing point; S44. Obtaining the coordinates of the next tracing point according to the relative refractive index of the initial tracing point; S45. Update the coordinates of the initial tracing point to the coordinates of the next tracing point, repeat steps S42-S45, and obtain the relative refractive index of all the light tracing points, that is, the refractive index distribution.

6. The method for constructing an aero-optical transmission model according to claim 5, characterized in that: Step S42 includes the following steps: S421. Fitting the discrete temperature distribution into a temperature continuous function, wherein the temperature continuous function is used to characterize the temperature corresponding to the coordinates of the tracking point; S422. Input the coordinates of the initial tracing point into the temperature continuity function to obtain the temperature of the initial tracing point.

7. The method for constructing an aero-optical transmission model according to claim 5, characterized in that: The relative refractive index of the initial tracing point is calculated according to the temperature of the initial tracing point and is realized by the following formula: Where λ is the wavelength; T is the temperature of the tracing point; n r is the relative refractive index at the tracing point; n a is the absolute refractive index of the optical material; n is the absolute refractive index of the atmosphere.

8. An aero-optical transmission model construction system, used to implement the aero-optical transmission model construction method according to any one of claims 1 to 7, characterized in that: The system includes: a first calculation module, the first calculation module being configured to obtain a refractive index distribution of an aircraft flow field; A first construction module, wherein the first construction module is configured to construct a flow field lens model according to the refractive index distribution, wherein the input of the flow field lens model is the refractive index distribution, and the output is an optical path difference; A first acquisition module, wherein the first acquisition module is configured to acquire a temperature distribution of an optical system, wherein the optical system includes a plurality of optical lenses, and the temperature distribution is used to characterize a temperature at each position of each of the optical lenses; a third calculation module, the third calculation module being configured to obtain a relative refractive index distribution of a ray tracing point according to the temperature distribution, the relative refractive index distribution being the relative refractive index of the ray tracing point of each of the optical lenses (21); A first combination module, wherein the first combination module is configured to combine the flow field lens model and the optical lens model to form an equivalent lens superposition model, wherein the input of the equivalent lens superposition model is the geometric parameters of the optical system, the refractive index distribution, the temperature distribution and the relative refractive index distribution, and the output is the light transmission distortion characteristics, wherein the optical lens model is a model of the lens group in the optical system of the aircraft.

9. A terminal device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the aero-optical transmission model construction method according to any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method for constructing an aero-optical transmission model as described in any one of claims 1 to 7 are implemented.

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