Method for analyzing optical performance of optical window of hypersonic aircraft and related device

Abstract

The invention provides an optical performance analysis method for an optical window of a hypersonic flight vehicle, and the method comprises the steps: obtaining the optical window of the hypersonic flight vehicle before deformation in a first model; in the simulation model, obtaining the deformed optical window of the hypersonic aircraft; analyzing the optical window before and after deformation to obtain the optical performance degradation degree of the optical window in the external flow field environment; wherein the simulation model is an aircraft grid model after deformation parameter interaction of a first model and a second model, the first model is an aircraft grid model of a hypersonic aircraft, and the second model is an external flow field grid model of an external flow field environment where the hypersonic aircraft is located. According to the method, the analysis precision of the optical performance degradation degree of the optical window of the hypersonic aircraft in the external flow field environment can be improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of optical technology, and in particular to a method for analyzing optical performance of an optical window of a hypersonic aircraft and related devices. BACKGROUND

[0002] With the development of technology, the flight speed of a hypersonic aircraft is constantly increasing, and optical components such as a seeker of the hypersonic aircraft are facing severe challenges. On the one hand, due to the significant aerodynamic heating phenomenon under the action of the hypersonic flight, the seeker of the aircraft is prone to structural fracture and deformation under extreme high temperature and strong aerodynamic load. On the other hand, high temperature not only changes the physical properties (such as refractive index) of the material, but also causes the thickness of the infrared window on the seeker to change and the temperature gradient to be abnormal, thereby seriously affecting the optical performance and working precision of the optical components such as the seeker. Therefore, it is urgent to analyze and study the influence of thermal load on the imaging of the infrared window under real working conditions. SUMMARY

[0003] In view of the above, the purpose of the present application is to provide a method for analyzing optical performance of an optical window of a hypersonic aircraft and related devices.

[0004] To achieve the above purpose, the present application provides a method for analyzing optical performance of an optical window of a hypersonic aircraft, comprising:

[0005] In the first model, an optical window of a hypersonic aircraft before deformation is obtained;

[0006] In the simulation model, an optical window of a hypersonic aircraft after deformation is obtained;

[0007] The optical windows before and after deformation are analyzed to obtain a degree of degradation of optical performance of the optical window under an external flow field environment;

[0008] The simulation model is a grid model of the aircraft after interaction of deformation parameters of the first model and the second model, the first model is a grid model of the hypersonic aircraft, and the second model is an external flow field grid model of an external flow field environment in which the hypersonic aircraft is located.

[0009] Further, the analysis of the optical windows before and after deformation to obtain the degree of degradation of optical performance of the optical window under the external flow field environment comprises:

[0010] Optical path difference analysis is performed on the optical windows before and after deformation to obtain an optical path difference parameter;

[0011] An evaluation function index of the optical window under the external flow field environment is determined based on the optical path difference parameter;

[0012] Determine the optical performance degradation degree of the optical window in the external flow field environment based on the evaluation function index.

[0013] Further, the optical path difference analysis of the optical window before and after deformation is performed to obtain an optical path difference parameter, including:

[0014] The refractive index of the optical window before and after deformation is analyzed to obtain the refractive index distribution of the optical window before and after deformation.

[0015] The optical path difference parameter of the optical window before and after deformation is obtained based on the refractive index distribution of the optical window before and after deformation.

[0016] Further, the construction process of the simulation model includes:

[0017] Based on the structural characteristics and material characteristics of the hypersonic vehicle, a vehicle grid model of the hypersonic vehicle is established;

[0018] Based on the external flow field environment in which the hypersonic vehicle is located, an external flow field grid model is established;

[0019] The aircraft grid model and the external flow field grid model are interacted with deformation parameters, and the aircraft grid model after the deformation parameter interaction is taken as the simulation model.

[0020] Further, the deformation parameters include thermal load and structural parameters, wherein the thermal load is the thermal load received by the aircraft grid model in the external flow field grid model, and the structural parameters are the structural parameters generated by the aircraft grid model under the action of the thermal load;

[0021] The aircraft grid model and the external flow field grid model are interacted with deformation parameters, and the aircraft grid model after the deformation parameter interaction is taken as the simulation model, including:

[0022] Based on the aircraft grid model, a structural parameter calculation module is constructed, and based on the external flow field grid model, a thermal load calculation module is constructed;

[0023] The connection relationship between the structural parameter calculation module and the thermal load calculation module is constructed;

[0024] The structural parameters of the aircraft grid model calculated by the structural parameter calculation module and the thermal load acting on the aircraft grid model calculated by the thermal load calculation module are interacted with deformation parameters, and the aircraft grid model after the deformation parameter interaction is taken as the simulation model.

[0025] Further, the structure parameter calculated by the structure parameter calculation module and the thermal load acting on the aircraft grid model calculated by the thermal load calculation module are interacted with deformation parameters, and the aircraft grid model after the deformation parameter interaction is taken as the simulation model, comprising:

[0026] The structure parameter of the aircraft grid model is calculated by the structure parameter calculation module;

[0027] The deformation parameter interaction step is executed: the structure parameter is input into the thermal load calculation module to obtain the thermal load of the aircraft grid model in the external flow field grid model; the thermal load is input into the structure parameter calculation module to obtain the new structure parameter of the aircraft grid model after deformation under the action of the thermal load;

[0028] The new structure parameter is input into the thermal load calculation module, and the deformation parameter interaction step is repeatedly executed until the new structure parameter meets the preset condition;

[0029] The aircraft grid model corresponding to the new structure parameter is taken as the simulation model.

[0030] Further, the preset condition is that the difference between the new structure parameter and the last structure parameter is within a preset range.

[0031] Further, the thermal load calculation module is fluent software.

[0032] Further, the structure deformation calculation module is Abaqus software.

[0033] Further, the evaluation function index includes PV value, RMS value, X-axis tilt amount and Y-axis tilt amount.

[0034] Based on the same inventive concept, the disclosure also provides an optical performance analysis device for an optical window of a hypersonic aircraft, comprising:

[0035] A first acquisition module is configured to acquire the optical window of the hypersonic aircraft before deformation in a first model;

[0036] A second acquisition module is configured to acquire the optical window of the hypersonic aircraft after deformation in a simulation model;

[0037] An analysis module is configured to analyze the optical window before and after deformation to obtain the optical performance degradation degree of the optical window under the external flow field environment;

[0038] The simulation model is a vehicle grid model after deformation parameter interaction of a first model and a second model, the first model is a vehicle grid model of a hypersonic vehicle, and the second model is an external flow field grid model of an external flow field environment in which the hypersonic vehicle is located.

[0039] Based on the same inventive concept, the present disclosure also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and running on the processor, wherein the processor implements the method as described above when executing the program. Based on the same inventive concept, the present disclosure also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable by the processor, wherein the processor implements the method as described above when executing the computer program.

[0040] Based on the same inventive concept, the present disclosure also provides a non-transitory computer readable storage medium, which stores computer instructions for causing a computer to execute the method as described above.

[0041] As can be seen from the above, the method for analyzing optical performance of an optical window of a hypersonic vehicle provided by the present application establishes a vehicle grid model of the hypersonic vehicle before deformation and a vehicle grid model of the hypersonic vehicle after deformation in an external flow field environment, and obtains the optical window of the hypersonic vehicle before deformation and after deformation respectively, to analyze the optical window before and after deformation, obtain the optical performance degradation degree of the optical window of the hypersonic vehicle in the external flow field environment, and realize the analysis of the imaging influence degree of the optical window of the hypersonic vehicle in the external flow field environment. Furthermore, the establishment of the external flow field grid model of the external flow field environment and the vehicle grid model of the hypersonic vehicle and the realization of deformation parameter interaction facilitate the improvement of the analysis accuracy of the optical performance degradation degree of the optical window of the hypersonic vehicle in the external flow field environment. On this basis, the present application is beneficial to the optical performance correction of the optical window in practical application, avoids the influence of the optical performance degradation of the optical window on the working accuracy of the hypersonic vehicle, and facilitates the research on the improvement of the optical performance of the optical window of the hypersonic vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0042] In order to more clearly illustrate the technical solutions in the present application or the related art, the drawings needed in the embodiments or the related art description will be briefly introduced. Obviously, the drawings in the following description are only embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creative labor.

[0043] Figure 1A flow structure schematic diagram of an optical performance analysis method of a hypersonic vehicle optical window according to an embodiment of the present application is shown in FIG. 1.

[0044] Figure 2 A structure schematic diagram of an optical performance analysis device of a hypersonic vehicle optical window according to an embodiment of the present application is shown in FIG. 2.

[0045] Figure 3 A structure schematic diagram of an electronic device according to an embodiment of the present application is shown in FIG. 3. DETAILED DESCRIPTION

[0046] To make the objectives, technical solutions and advantages of the present application clearer, the present application will be further described in detail below with reference to the embodiments and the accompanying drawings.

[0047] It should be noted that, unless otherwise defined, the technical terms or scientific terms used in the embodiments of the present application should be understood as the common meanings understood by those with ordinary skills in the art to which the present application belongs. The terms "first", "second", and similar terms used in the embodiments of the present application do not represent any order, number, or importance, but are only used to distinguish different components. The terms "include", "contain", and similar terms mean that the elements or objects before the terms encompass the elements or objects listed after the terms and their equivalents, without excluding other elements or objects. The terms "connect" or "connected" and similar terms do not mean physical or mechanical connections, but can include electrical connections, whether direct or indirect. The terms "up", "down", "left", "right", and the like only represent relative positional relationships, and when the absolute positions of the described objects change, the relative positional relationships may also change accordingly.

[0048] High-speed vehicles play a very key role in modern warfare. As their flight speed continues to increase, when they reach hypersonic speed, the optical key components such as the seeker head on them face unprecedented severe challenges: on the one hand, due to the significant phenomenon of shock-induced aerodynamic heating, the front end of the vehicle is prone to structural rupture and deformation under extreme high temperature and strong aerodynamic load; on the other hand, high temperature not only changes the physical properties (such as refractive index) of the material, but also causes the thickness of the infrared window to change and the temperature gradient to be abnormal, thereby seriously affecting the working accuracy of the guidance system.

[0049] However, when analyzing the imaging law of the infrared window on the seeker under the thermal environment, only the overall temperature of the infrared window is considered, and the problem of uneven distribution of temperature in the surface, cross-section and other directions in the flight working condition is not analyzed completely. The uneven distribution of temperature will lead to uneven deformation and stress distribution, which will affect the imaging performance of the infrared window. At the same time, the deformation of the infrared window in the harsh environment will also affect its structure and further cause the degradation of its imaging quality. Various factors cause the existing imaging analysis of the infrared window to be unable to well simulate the damage degradation phenomenon caused by the thermal load of the infrared window in the real harsh working environment.

[0050] Based on this, the application provides an optical performance analysis method and related device for an optical window of a hypersonic aircraft, to simulate the thermal load and deformation of the optical window of the hypersonic aircraft under the corresponding external flow field environment, and to analyze the thermal load of the deformed hypersonic aircraft again to simulate the final deformation result of the hypersonic aircraft under the corresponding external flow field environment, so as to analyze the optical performance degradation of the optical window of the deformed hypersonic aircraft, which is beneficial to improve the deformation precision and further improve the analysis precision of the optical window.

[0051] The embodiments of the application will be described in detail below with reference to the accompanying drawings.

[0052] In some embodiments, an optical performance analysis method for an optical window of a hypersonic aircraft, as shown in Figure 1 , comprises:

[0053] Step S100, in a first model, an optical window of a hypersonic aircraft before deformation is obtained;

[0054] Specifically, the first model is a grid model of the aircraft established based on the initial static environment of the hypersonic aircraft, and the optical window is located on the hypersonic aircraft. When the first model is established, the optical window and the material and structure of other structures of the hypersonic aircraft are considered, so that the optical window obtained in the first model is a process of extracting the optical window.

[0055] Step S200, in a simulation model, an optical window of a hypersonic aircraft after deformation is obtained;

[0056] Specifically, the simulation model is an aircraft grid model simulating the high-speed aircraft in an operating environment (i.e., a corresponding external flow field environment), and the simulation model is an aircraft grid model obtained after the first model and the second model are deformed and interacted, and the second model is an external flow field environment in which the high-speed aircraft is located in the operating environment (including a stress field determined based on flight speed and flight height, a temperature field determined based on external temperature, etc.), and the simulation model can simulate the deformation of the high-speed aircraft in the external flow field environment in the operating process, that is, the simulation model, and the optical window in the simulation model after deformation in the external flow field environment is the process of extracting the optical window.

[0057] In step S300, the optical window before and after deformation is analyzed to obtain the optical performance degradation degree of the optical window in the external flow field environment.

[0058] The simulation model is an aircraft grid model obtained after the first model and the second model are deformed and interacted, the first model is an aircraft grid model of the high-speed aircraft, and the second model is an external flow field grid model of the external flow field environment in which the high-speed aircraft is located.

[0059] Specifically, the optical windows before and after deformation are analyzed by ray tracing method respectively to obtain the change of imaging parameters of the optical window after deformation relative to the optical window before deformation, and the optical performance degradation degree of the optical window in the external flow field environment is determined based on the size of the change.

[0060] Specifically, the optical windows before and after deformation are analyzed by ray tracing method respectively to obtain the change of imaging parameters of the optical window after deformation relative to the optical window before deformation, and the optical performance degradation degree of the optical window in the external flow field environment is determined based on the size of the change.

[0061] In the embodiment, the optical window of the hypersonic vehicle before deformation and the optical window of the hypersonic vehicle after deformation in the external flow field environment are obtained based on the establishment of the vehicle grid model of the hypersonic vehicle before deformation and the vehicle grid model of the hypersonic vehicle after deformation in the external flow field environment, and the optical window before deformation and the optical window after deformation are analyzed to obtain the optical performance degradation degree of the optical window of the hypersonic vehicle in the external flow field environment, so that the imaging influence degree analysis of the optical window of the hypersonic vehicle in the external flow field environment is realized, and the establishment of the external flow field grid model of the external flow field environment and the vehicle grid model of the hypersonic vehicle and the realization of the deformation parameter interaction are beneficial to improving the analysis accuracy of the optical performance degradation degree of the optical window of the hypersonic vehicle in the external flow field environment. On this basis, the optical performance correction of the optical window in the actual application process is facilitated, the working accuracy of the hypersonic vehicle is avoided due to the performance degradation of the optical window, and the research on the optical performance improvement of the optical window of the hypersonic vehicle is facilitated.

[0062] In some embodiments, step S300: analyzing the optical window before and after deformation to obtain the optical performance degradation degree of the optical window in the external flow field environment, comprises:

[0063] Step S301, optical path difference analysis is performed on the optical window before and after deformation to obtain an optical path difference parameter.

[0064] Specifically, the optical path of the optical window before and after deformation is determined based on the ray tracing method, the optical path of the optical window after deformation is compared with the optical path of the optical window before deformation, and the optical path difference parameter is obtained.

[0065] Step S302, determining an evaluation function index of the optical window in the external flow field environment based on the optical path difference parameter.

[0066] Specifically, the optical path difference parameter includes a plurality of optical path difference distribution conditions of the optical window, and based on the optical path difference distribution condition, the evaluation function index corresponding to the wave pattern of the optical window after deformation can be calculated.

[0067] Illustratively, the evaluation function index includes a PV value, an RMS value, an X-axis tilt amount, and a Y-axis tilt amount. PV (Peak-to-Veally) is from peak to valley, which refers to the difference between the maximum value (the highest point of the surface shape) and the minimum value (the lowest point of the surface shape) of the element in the element surface shape error matrix, RMS (root mean square) is the root mean square, which refers to the flatness of the element surface shape.

[0068] Step S303, determining the optical performance degradation degree of the optical window in the external flow field environment based on the evaluation function index.

[0069] Specifically, the evaluation function index is used to evaluate the optical performance degradation degree of the optical window, and the closer the evaluation function index is to 0, the lower the optical performance degradation degree of the optical window.

[0070] For example, the optical performance of a hypersonic vehicle in an external flow field environment is analyzed, and the evaluation function index obtained is shown in Table 1; the optical performance of a hypersonic vehicle in another external flow field environment is analyzed, and the evaluation function index obtained is shown in Table 2.

[0071] Table 1

[0072]

[0073] Table 2

[0074]

[0075] From the values in Table 1 and Table 2, it can be seen that the optical performance degradation degree of the optical window corresponding to Table 1 is greater than that of the optical window corresponding to Table 2.

[0076] In this embodiment, by analyzing the optical path difference of the optical window before and after deformation, the evaluation function index of the optical window after deformation is obtained on this basis, the optical performance degradation degree of the optical window after deformation is determined through the evaluation function index, and by comparing the optical path of the optical window before and after deformation, the imaging deviation of the optical window is analyzed to obtain the optical performance degradation degree of the optical window after deformation, and the optical performance of the optical window after deformation is accurately analyzed.

[0077] In some embodiments, step S301: analyzing the optical path difference of the optical window before and after deformation to obtain an optical path difference parameter, comprises:

[0078] Step S301A, analyzing the refractive index of the optical window before and after deformation to obtain the refractive index distribution of the optical window before and after deformation;

[0079] Specifically, by analyzing the refractive index of the optical window before and after deformation, the refractive index distribution of the optical window before and after deformation is obtained. The optical window before and after deformation is a model, and due to deformation, the refractive index distribution of the optical window before and after deformation is not the same. By analyzing the optical window before and after deformation, the refractive index distribution of the optical window before and after deformation can be obtained.

[0080] Step S301B, obtaining the optical path difference parameter of the optical window before and after deformation based on the refractive index distribution of the optical window before and after deformation.

[0081] Specifically, the optical path of the optical window before deformation is obtained by ray tracing analysis based on the refractive index distribution of the optical window before deformation, the optical path of the optical window after deformation is obtained by ray tracing analysis based on the refractive index distribution of the optical window after deformation, and the optical path difference parameter of the optical window after deformation and the optical window before deformation is obtained by subtracting the optical path of the optical window after deformation from the optical path of the optical window before deformation. On this basis, the optical performance degradation degree of the optical window after deformation is evaluated.

[0082] It should be noted that the refractive index analysis and the calculation of the optical path difference parameter can be performed in the commercial software zemax, and the evaluation function index based on the optical path difference parameter can also be obtained by the commercial software zemax. That is, the evaluation function index of the optical window after deformation can be obtained by the commercial software zemax.

[0083] In this embodiment, the optical path difference parameter is obtained based on the refractive index distribution. By ray tracing analysis and calculation of the optical window before and after deformation, the optical path difference parameter can be quickly obtained, which is beneficial to improve the analysis efficiency of the method.

[0084] In some embodiments, the construction process of the simulation model comprises:

[0085] Step S400, establishing an aircraft grid model of a hypersonic aircraft based on the structural characteristics and material characteristics of the hypersonic aircraft.

[0086] Specifically, the hypersonic aircraft is modeled according to its structural characteristics and material characteristics, and the cross-sectional direction is then divided into grids by equal division, and the grid of the head part of the optical window of the hypersonic aircraft is encrypted (the number of grids is increased), and the boundary layer grid is drawn to improve the deformation accuracy of the aircraft grid model, thereby improving the accuracy of determining the optical performance degradation degree of the optical window. In addition, the tail end of the hypersonic aircraft is sparsely processed to save computing resources.

[0087] It should be noted that in order to improve the accuracy of the deformed optical window, the aircraft grid model of the hypersonic aircraft is established. This model can simulate the constraint conditions of the optical window in the real situation, so that the deformation accuracy is higher.

[0088] For example, the aircraft grid model of the hypersonic aircraft is established in the commercial software ABAQUS.

[0089] Step S500, based on the external flow field environment where the hypersonic vehicle is located, an external flow field grid model is established;

[0090] Specifically, according to the external flow field environment such as pressure environment and temperature environment where the hypersonic vehicle is located during operation, an external flow field grid model is established, which comprehensively interacts with the high speed, atmospheric pressure, flight speed, external temperature and other parameters of the hypersonic vehicle during operation, to obtain an external flow field grid model simulating the external flow field environment.

[0091] For example, the corresponding external flow field grid model of the external flow field environment is set in the commercial software fluent.

[0092] Step S600, the aircraft grid model and the external flow field grid model are interacted with deformation parameters, and the aircraft grid model after the interaction of deformation parameters is taken as the simulation model.

[0093] Specifically, the aircraft grid model is subjected to a certain thermal load in the external flow field grid model, and the aircraft grid model generates corresponding deformation based on the thermal load, so as to realize the interaction of thermal load and deformation parameters of the aircraft grid model, and the aircraft grid model after the interaction of deformation parameters is the model simulating the hypersonic vehicle in the external flow field environment, which is the simulation model.

[0094] For example, after setting the external flow field grid model in the commercial software fluent, the aircraft grid model is input into the software, and the thermal load received by each coordinate of the aircraft grid model, i.e. the thermal load distribution of the aircraft grid model, can be calculated. Based on this, the thermal load distribution is input into the commercial software ABAQUS, and the new coordinates of each coordinate of the aircraft grid model after receiving the thermal load can be calculated, and based on the new coordinates, the aircraft grid model after deformation can be obtained.

[0095] In this embodiment, the simulation model is obtained by the interaction of deformation parameters between the aircraft grid model and the external flow field grid model, the simulation model simulates the thermal load and deformation of the hypersonic vehicle in the external flow field environment, and then the optical performance of the deformed optical window of the hypersonic vehicle is analyzed, which is beneficial to improve the analysis accuracy.

[0096] In some embodiments, the deformation parameters include thermal load and structural parameters, wherein the thermal load is the thermal load received by the aircraft grid model in the external flow field grid model, and the structural parameters are the structural parameters generated by the aircraft grid model under the action of the thermal load.

[0097] Step S600: the aircraft grid model and the external flow field grid model are deformed parameter interaction, and the deformed parameter interaction aircraft grid model is taken as the simulation model, comprising:

[0098] Step S601, based on the aircraft grid model to build structure parameter calculation module, based on the external flow field grid model to build thermal load calculation module;

[0099] Specifically, after establishing the aircraft grid model, the structure parameter calculation module is constructed to calculate the structure parameters of the aircraft grid model under the action of the corresponding thermal load; after establishing the external flow field grid model, the thermal load calculation module is constructed to calculate the thermal load generated by the external flow field grid model on the aircraft grid model in the external flow field grid model.

[0100] Exemplarily, the aircraft grid model is established in the commercial software ABAQUS, that is, a structure parameter calculation module can be established based on the structure parameters and material parameters in the aircraft grid model, so that when the thermal load is input into the structure parameter calculation module, the deformed structure parameters are quickly calculated, and the deformed aircraft grid model is obtained.

[0101] The external flow field grid model is established in the commercial software fluent, that is, a thermal load calculation module can be established based on the pressure flow field, temperature flow field and the like in the external flow field grid model, so that when the outer surface coordinate information of the aircraft grid model is input into the thermal load calculation module, the thermal load received by each outer surface of the aircraft grid model is quickly calculated.

[0102] Step S602, the connection relationship between the structure parameter calculation module and the thermal load calculation module is constructed;

[0103] Specifically, in order to improve the information transmission speed of the structure parameter calculation module and the thermal load calculation module, the connection relationship between the structure parameter calculation module and the thermal load calculation module is constructed to realize the rapid interaction of the deformation parameters obtained by the structure parameter calculation module and the thermal load calculation module.

[0104] Step S603, the structure parameters of the aircraft grid model calculated by the structure parameter calculation module and the thermal load acting on the aircraft grid model calculated by the thermal load calculation module are deformed parameter interaction, and the deformed parameter interaction aircraft grid model is taken as the simulation model.

[0105] Specifically, the structure parameter and the thermal load are quickly interacted through the connection relationship between the structure parameter calculation module and the thermal load calculation module, and the aircraft grid model obtained after the deformation parameter interaction is the simulation model.

[0106] In the embodiment, the structure parameter is calculated by the structure calculation module, the thermal load is calculated by the thermal load calculation module, and the structure parameter and the thermal load are quickly interacted through the connection relationship between the structure calculation module and the thermal load calculation module, which is beneficial to improving the interaction speed and effect of the aircraft grid model and the external flow field grid model.

[0107] In some embodiments, the structure parameter of the aircraft grid model calculated by the structure parameter calculation module and the thermal load acting on the aircraft grid model calculated by the thermal load calculation module are interacted in deformation parameters, and the aircraft grid model after the deformation parameter interaction is taken as the simulation model, including:

[0108] In step S603A, the structure parameter of the aircraft grid model is calculated by the structure parameter calculation module.

[0109] Specifically, the structure parameter of the aircraft grid model is calculated by the structure parameter calculation module. When the thermal load acting on the aircraft grid model is not obtained, the structure parameter calculated by the structure parameter calculation module is the original structure parameter of the aircraft grid model.

[0110] In step S603B, a deformation parameter interaction step is performed: the structure parameter is input into the thermal load calculation module to obtain the thermal load acting on the aircraft grid model in the external flow field grid model; and the thermal load is input into the structure parameter calculation module to obtain the new structure parameter of the aircraft grid model after deformation under the action of the thermal load.

[0111] Specifically, the thermal load acting on the aircraft grid model in the external flow field grid model is calculated by inputting the structure parameter into the thermal load calculation module, and the new structure parameter of the aircraft grid model after deformation under the action of the thermal load is calculated by inputting the thermal load into the structure parameter calculation module, that is, the first deformation of the aircraft grid model.

[0112] In step S603C, the new structure parameter is input into the thermal load calculation module, and the deformation parameter interaction step is repeatedly performed until the new structure parameter meets the preset condition.

[0113] Specifically, the new structure parameter is a structure parameter corresponding to the deformed aircraft grid model, the new structure parameter is input into the thermal load calculation module, and the thermal load borne by the deformed aircraft grid model in the external flow field grid model can be calculated, and then the structure calculation module is input based on the thermal load, and the updated structure parameter of the aircraft grid model is obtained again. Thus, the cycle is repeated until the new structure parameter corresponding to the aircraft grid model meets the preset condition, and the aircraft grid model corresponding to the structure parameter is the structure parameter of the simulation model.

[0114] For example, the preset condition is that the difference between the new structure parameter and the last structure parameter is within a preset range, that is, after at least one iteration of the deformation parameter, the change of the structure parameter of the aircraft grid model obtained compared with the last structure parameter is within a preset range, the deformation of the aircraft grid model is stable, that is, the aircraft grid model corresponding to the structure parameter is in a stable state of the hypersonic aircraft simulated in the external flow field environment, and the simulation accuracy of the optical window in the aircraft grid model and the hypersonic aircraft in the external flow field environment is high.

[0115] In step S603D, the aircraft grid model corresponding to the new structure parameter is taken as the simulation model.

[0116] Specifically, the aircraft grid model obtained based on the new structure parameter is the simulation model.

[0117] In the embodiment, the deformation parameter iteration process is an interactive constraint process of the structure parameter and the thermal load, until the new structure parameter meets the preset condition, the aircraft grid model corresponding to the new structure parameter is the simulation model, the deformation iteration process truly simulates the dynamic change process of the structure of the hypersonic aircraft in the external flow field environment, and the accuracy of the simulation model can be improved.

[0118] In some embodiments, the preset condition is that the difference between the new structure parameter and the last structure parameter is within a preset range.

[0119] Specifically, the preset range is used to constrain the difference between the new structure parameter and the last structure parameter, and the new structure parameter within the preset range indicates that the change of the new structure parameter compared with the last structure parameter is small, and the aircraft grid model corresponding to the new structure parameter can be determined as the aircraft grid model completed with the deformation parameter iteration, that is, the simulation model.

[0120] For example, the difference between the new structure parameter and the previous structure parameter can be a root mean square difference, and the preset range can be a range value, and the boundary value of the range value can be a limited root mean square difference value.

[0121] In some embodiments, the thermal load calculation module is fluent software.

[0122] Specifically, the thermal load calculation module is located in the fluent software, and the thermal load calculation module can calculate the thermal load of each coordinate of the structure corresponding to the structure parameter based on the input structure parameter.

[0123] In some embodiments, the structure deformation calculation module is Abaqus software.

[0124] Specifically, the structure deformation calculation module is Abaqus software, and the process of building the structure deformation calculation module is the process of parameter setting of the structure deformation calculation module.

[0125] In some embodiments, the evaluation function indicators include PV value, RMS value, X-axis tilt amount and Y-axis tilt amount.

[0126] Specifically, the PV value, the RMS value, the X-axis tilt amount and the Y-axis tilt amount are parameters for evaluating the imaging offset amount of the optical window, and the PV value, the RMS value, the X-axis tilt amount and the Y-axis tilt amount are offset conditions of the deformed optical window imaging compared with the undeformed optical window imaging, and the optical performance degradation index of the deformed optical window is more accurate based on this.

[0127] It should be noted that the method of the embodiments of the present application can be executed by a single device, such as a computer or a server, etc. The method of the embodiments of the present application can also be applied to a distributed scenario, and completed by multiple devices cooperating with each other. In this distributed scenario, one of the multiple devices can only execute one or more steps in the method of the embodiments of the present application, and the multiple devices can interact with each other to complete the method.

[0128] It should be noted that some embodiments of the present application have been described above. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims can be performed in a different order than the order described above and still achieve desirable results. In addition, the processes depicted in the figures do not necessarily require the particular order shown, or sequential order, to achieve the desired results. In certain implementations, multitasking and parallel processing can be advantageous.

[0129] Based on the same inventive concept, the present application also provides an optical performance analysis device for a hypersonic vehicle optical window, corresponding to the method of any of the above embodiments.

[0130] Reference Figure 2 , the device comprises:

[0131] The first acquisition module 100 is configured to acquire an optical window of a hypersonic aircraft before deformation in a first model;

[0132] The second acquisition module 200 is configured to acquire an optical window of a hypersonic aircraft after deformation in a simulation model;

[0133] The analysis module 300 is configured to analyze the optical window before and after deformation to obtain the optical performance degradation degree of the optical window under the external flow field environment;

[0134] The simulation model is a vehicle grid model after the first model and the second model deformation parameter interaction, the first model is a vehicle grid model of a hypersonic aircraft, and the second model is an external flow field grid model of an external flow field environment of the hypersonic aircraft.

[0135] For the convenience of description, the above device is described as various modules in function. Of course, in the implementation of the present application, the functions of each module can be implemented in the same or multiple software and / or hardware.

[0136] The device of the above embodiment is used to implement the corresponding method in any of the above embodiments, and has the beneficial effects of the corresponding method embodiment, which will not be repeated here.

[0137] Based on the same inventive concept, corresponding to any of the above embodiment methods, the present application also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the method of any one of the above embodiments.

[0138] Figure 3 A more specific hardware structure schematic diagram of an electronic device provided by the present embodiment is shown, which can include: a processor 1010, a memory 1020, an input / output interface 1030, a communication interface 1040 and a bus 1050. The processor 1010, the memory 1020, the input / output interface 1030 and the communication interface 1040 are connected with each other through the bus 1050 for communication within the device.

[0139] The processor 1010 can be implemented by a general-purpose CPU (Central Processing Unit), a microprocessor, an ASIC (Application Specific Integrated Circuit), or one or more integrated circuits, etc., for executing relevant programs to implement the technical solutions provided by the embodiments of the present specification.

[0140] The memory 1020 can be implemented by a ROM (Read Only Memory), a RAM (Random Access Memory), a static storage device, a dynamic storage device, etc. The memory 1020 can store an operating system and other application programs, and when the technical solutions provided by the embodiments of the present specification are implemented by software or firmware, the relevant program codes are stored in the memory 1020 and called and executed by the processor 1010.

[0141] The input / output interface 1030 is configured to connect input / output modules to implement information input and output. The input / output modules can be configured as components in the device (not shown in the figure) or externally connected to the device to provide corresponding functions. The input devices can include a keyboard, a mouse, a touch screen, a microphone, various sensors, etc., and the output devices can include a display, a speaker, a vibrator, an indicator light, etc.

[0142] The communication interface 1040 is configured to connect a communication module (not shown in the figure) to implement communication interaction between the device and other devices. The communication module can realize communication through a wired manner (such as USB, network cable, etc.) or through a wireless manner (such as mobile network, WIFI, Bluetooth, etc.).

[0143] The bus 1050 includes a channel for transmitting information between various components (such as the processor 1010, the memory 1020, the input / output interface 1030, and the communication interface 1040) of the device.

[0144] It should be noted that although the above device only shows the processor 1010, the memory 1020, the input / output interface 1030, the communication interface 1040, and the bus 1050, in the specific implementation process, the device can also include other components necessary for normal operation. In addition, those skilled in the art can understand that the above device can also only include components necessary for implementing the technical solutions of the embodiments of the present specification, and does not necessarily include all the components shown in the figure.

[0145] The electronic device of the above embodiments is used to implement the corresponding method in any of the preceding embodiments, and has the beneficial effects of the corresponding method embodiments, which are not described here again.

[0146] Based on the same inventive concept, the present application also provides a non-transitory computer readable storage medium storing computer instructions for causing a computer to perform the method of any of the above embodiments.

[0147] The computer readable medium of the embodiments can include permanent and non-permanent, removable and non-removable media, which can store information by any method or technology. The information can be computer readable instructions, data structures, program modules or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, compact disc read-only memory (CD-ROM), digital versatile disc (DVD) or other optical storage, magnetic cassette, magnetic tape disk storage or other magnetic storage devices, or any other non-transmission medium that can be used to store information accessible by a computing device.

[0148] The computer instructions stored in the storage medium of the above embodiments are used to cause the computer to perform the method of any of the above embodiments, and have the beneficial effects of the corresponding method embodiments, which are not repeated here.

[0149] Based on the same concept, the present application also provides a computer program product comprising computer program instructions for causing a computer to perform the method of any of the above embodiments when the computer program instructions are run on the computer, having the beneficial effects of the corresponding method embodiments, which are not repeated here.

[0150] It can be understood that before using the technical solutions of various embodiments in the present disclosure, the type of personal information involved, the scope of use, the scene of use, etc. will be informed to the user in a proper manner, and the authorization of the user will be obtained.

[0151] For example, in response to receiving the user's active request, the user is sent prompt information to explicitly prompt the user that the operation requested to be performed will require the acquisition and use of the user's personal information. Thus, the user can voluntarily choose whether to provide personal information to the software or hardware such as electronic devices, application programs, servers or storage media that perform the technical solutions of the present disclosure according to the prompt information.

[0152] As an optional but non-limiting implementation manner, in response to accepting the active request of the user, the manner of sending the prompt information to the user may be, for example, a pop-up window manner, in which the prompt information may be presented in a text manner. In addition, the pop-up window may also carry a selection control for the user to select "agree" or "disagree" to provide the personal information to the electronic device.

[0153] It can be understood that the above notification and user authorization obtaining process is only illustrative, and does not limit the implementation manners of the present disclosure, and other manners meeting the relevant laws and regulations can also be applied to the implementation manners of the present disclosure.

[0154] It should be understood by those skilled in the art that the above discussion of any embodiment is only exemplary and is not intended to limit the scope of the present application to these examples; under the idea of the present application, the technical features in the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other changes of different aspects of the embodiments of the present application as described above, which are not provided in details for the sake of brevity.

[0155] In addition, in order to simplify the description and discussion, and so as not to make the embodiments of the present application difficult to understand, the known power / ground connections of integrated circuit (IC) chips and other components can or can not be shown in the provided drawings. In addition, the devices can be shown in the form of block diagrams in order to avoid making the embodiments of the present application difficult to understand, and this also takes into account the fact that the details of the implementation of these block diagram devices are highly dependent on the platform to be implemented in the embodiments of the present application (i.e., these details should be fully within the understanding of those skilled in the art). Where specific details (e.g., circuitry) are set forth in order to describe an illustrative embodiment of the present application, it will be apparent to those skilled in the art that the embodiments of the present application can be practiced without these specific details or with an implementation varying from these specific details. Therefore, these descriptions should be considered as illustrative rather than limiting.

[0156] Although the present application has been described in conjunction with specific embodiments thereof, many alternatives, modifications and variations will be apparent to those skilled in the art in light of the foregoing description. For example, other memory architectures (e.g., dynamic RAM (DRAM)) can use the embodiments discussed.

[0157] The embodiments of the present application are intended to cover all such alternatives, modifications and variations as falling within the broad scope of the application claimed. Accordingly, any omission, modification, equivalent replacement, improvement, etc. made within the spirit and principle of the embodiments of the present application should be included in the protection scope of the present application.

Claims

1. A method for analyzing the optical performance of a hypersonic vehicle optical window, characterized in that: include: In the first model, an optical window of the hypersonic vehicle before deformation is obtained; In the simulation model, the optical window of the hypersonic vehicle after deformation is obtained; Analyzing the optical window before and after deformation to obtain the degree of optical performance degradation of the optical window under an external flow field environment; Among them, the simulation model is an aircraft mesh model after the deformation parameters of the first model and the second model interact, the first model is the aircraft mesh model of the hypersonic aircraft, and the second model is the external flow field mesh model of the external flow field environment in which the hypersonic aircraft is located.

2. The method according to claim 1, characterized in that The analyzing the optical window before and after deformation to obtain the degree of optical performance degradation of the optical window under an external flow field environment includes: Performing optical path difference analysis on the optical window before and after deformation to obtain optical path difference parameters; Determining an evaluation function index of the optical window in an external flow field environment based on the optical path difference parameter; The degree of optical performance degradation of the optical window in an external flow field environment is determined based on the evaluation function index.

3. The method according to claim 2, characterized in that The optical path difference analysis of the optical window before and after deformation to obtain optical path difference parameters includes: Performing a refractive index analysis on the optical window before and after deformation to obtain a refractive index distribution of the optical window before and after deformation; The optical path difference parameters of the optical window before and after deformation are obtained based on the refractive index distribution of the optical window before and after deformation.

4. The method according to claim 1, wherein The construction process of the simulation model includes: Establishing a hypersonic aircraft mesh model based on the structural and material properties of the hypersonic aircraft; Establishing an external flow field grid model based on the external flow field environment in which the hypersonic aircraft is located; The aircraft grid model and the external flow field grid model are subjected to deformation parameter interaction, and the aircraft grid model after the deformation parameter interaction is used as the simulation model.

5. The method according to claim 4, characterized in that The deformation parameters include thermal loads and structural parameters, wherein the thermal loads are thermal loads received by the aircraft grid model within the external flow field grid model, and the structural parameters are structural parameters generated by the aircraft grid model under the action of the thermal loads; The step of performing deformation parameter interaction between the aircraft grid model and the external flow field grid model, and using the aircraft grid model after the deformation parameter interaction as the simulation model, comprises: Building a structural parameter calculation module based on the aircraft grid model, and building a thermal load calculation module based on the external flow field grid model; Establishing a connection relationship between the structural parameter calculation module and the thermal load calculation module; The structural parameters of the aircraft grid model calculated by the structural parameter calculation module and the thermal load acting on the aircraft grid model calculated by the thermal load calculation module are subjected to deformation parameter interaction, and the aircraft grid model after the deformation parameter interaction is used as the simulation model.

6. The method according to claim 5, characterized in that The step of performing deformation parameter interaction on the structural parameters of the aircraft grid model calculated by the structural parameter calculation module and the thermal load acting on the aircraft grid model calculated by the thermal load calculation module, and using the aircraft grid model after the deformation parameter interaction as the simulation model, includes: The structural parameters of the aircraft grid model are calculated by a structural parameter calculation module; Executing a deformation parameter interaction step: inputting the structural parameters into the thermal load calculation module to obtain a thermal load of the aircraft mesh model in the external flow field mesh model; inputting the thermal load into the structural parameter calculation module to obtain new structural parameters of the aircraft mesh model after deformation under the thermal load; Inputting the new structural parameters into the thermal load calculation module, and repeatedly performing the deformation parameter interaction step until the new structural parameters meet the preset conditions; The aircraft grid model corresponding to the new structural parameters is used as the simulation model.

7. The method according to claim 6, characterized in that The preset condition is that the difference between the new structural parameter and the previous structural parameter is within a preset range.

8. The method according to claim 5, characterized in that The thermal load calculation module is Fluent software.

9. The method according to claim 5, characterized in that The structural deformation calculation module is Abaqus software.

10. The method according to claim 2, characterized in that The evaluation function indicators include PV value, RMS value, X-axis tilt and Y-axis tilt.

11. An optical performance analysis device for an optical window of a hypersonic vehicle, characterized in that: include: A first acquisition module is configured to acquire, in a first model, an optical window of the hypersonic aircraft before deformation; A second acquisition module is configured to acquire an optical window of the hypersonic aircraft after deformation in the simulation model; an analysis module configured to analyze the optical window before and after deformation to obtain a degree of degradation of the optical performance of the optical window under an external flow field environment; Among them, the simulation model is an aircraft mesh model after the deformation parameters of the first model and the second model interact, the first model is the aircraft mesh model of the hypersonic aircraft, and the second model is the external flow field mesh model of the external flow field environment in which the hypersonic aircraft is located.

12. An electronic device comprising a memory, a processor, and a computer program stored in the memory and running on the processor, characterized in that: When the processor executes the program, the method according to any one of claims 1 to 10 is implemented.

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