Method and system for optimizing curing process parameters of aviation drag reduction films for various substrates

Abstract

The present invention provides a method and system for optimizing the curing process parameters of aviation drag reduction films for various substrates, and relates to the field of data processing technology. By activating a light-heat combined curing process, the substrate data of the substrate is read, the surface curing index of the aviation drag reduction film is established, the light curing parameters are configured, the surface state data of the aviation drag reduction film after light curing is collected, the temperature change gradient is set using the base state data, the thermal curing is divided into stages, the stage temperature change gradient is self-optimized according to the feedback data of the temperature monitoring point, the feedback constraint, and the stage division result, the light curing is enhanced, and the curing production of the aviation drag reduction film is completed. The technical problem of inaccurate temperature control and uneven curing in the curing process of the aviation drag reduction film in the prior art is solved. The technical effect of accurately controlling the temperature of the curing process of the aviation drag reduction film and improving the uniformity of curing is achieved, thereby enhancing the overall drag reduction performance of the drag reduction film.

Description

Technical Field

[0001] The present invention relates to the technical field of data processing, and in particular to a method and system for optimizing curing process parameters of aviation drag-reducing films for various substrates. Background Art

[0002] Aviation drag reduction film is a multi-layer composite film material with a fine microstructure on the surface. It is attached to the surface of the aircraft and reduces friction resistance by changing the micro-turbulent flow structure of the boundary layer on the surface of the aircraft. It can improve the aerodynamic performance of the aircraft, improve the fuel efficiency of the aircraft, and reduce carbon emissions. However, in the traditional production process of drag reduction film, the curing process is one of the key links, and it often uses a unified parameter setting, which leads to problems such as inaccurate temperature control and uneven curing during the curing process, which in turn affects the drag reduction performance and quality of the drag reduction film.

[0003] The prior art has technical problems such as inaccurate temperature control and uneven curing during the curing process of aviation drag reduction films, which leads to reduced drag reduction performance. Summary of the invention

[0004] The present application provides a method and system for optimizing the curing process parameters of aviation drag reduction films for various substrates, which is used to solve the technical problems in the prior art of inaccurate temperature control and uneven curing during the curing process of aviation drag reduction films, resulting in reduced drag reduction performance.

[0005] In view of the above problems, the present application provides a method and system for optimizing the curing process parameters of aviation drag reduction films for various substrates.

[0006] The first aspect of the present application provides a method for optimizing the curing process parameters of an aviation drag reducing film for various substrates, the method comprising: activating a light-heat combined curing process and reading substrate data of the substrate; establishing a surface curing index of the aviation drag reducing film according to the substrate data, and configuring light curing parameters through the surface curing index and the substrate data; executing the light curing process with the light curing parameters, and calling a sensor group to collect the surface state data of the aviation drag reducing film after light curing to establish ground state data; setting the initial temperature and target temperature of thermal curing through the substrate data, and setting the temperature change gradient using the ground state data; dividing the thermal curing into stages, and establishing feedback constraints mapped to the stage division results, the stage division results including an initial stage, an intermediate stage, and a final stage; configuring temperature monitoring points for the aviation drag reducing film, self-optimizing the stage temperature change gradient according to the feedback data of the temperature monitoring points, the feedback constraints, and the stage division results, and performing light curing enhancement after the thermal curing is completed to complete the curing production of the aviation drag reducing film.

[0007] The second aspect of the present application provides an aviation drag reduction film curing process parameter optimization system for various substrates, the system comprising: a substrate data acquisition module, the substrate data acquisition module is used to activate the light-heat combined curing process and read the substrate data of the substrate; a light curing parameter configuration module, the light curing parameter configuration module is used to establish the surface curing index of the aviation drag reduction film according to the substrate data, and configure the light curing parameters through the surface curing index and the substrate data; a base state data establishment module, the base state data establishment module is used to execute the light curing process with the light curing parameters, and call the sensor group to collect the surface state data of the aviation drag reduction film after light curing, and establish the base state data; a temperature A temperature setting module, the temperature setting module is used to set the initial temperature and target temperature of thermal curing through the substrate data, and use the ground state data to set the temperature change gradient; a feedback constraint establishment module, the feedback constraint establishment module is used to divide the thermal curing into stages, and establish feedback constraints mapped to the stage division results, the stage division results include an initial stage, an intermediate stage and a final stage; a curing production module, the curing production module is used to configure the temperature monitoring points of the aviation drag reduction film, self-optimize the stage temperature change gradient according to the feedback data of the temperature monitoring points, feedback constraints, and stage division results, and perform light curing enhancement after the thermal curing is completed to complete the curing production of the aviation drag reduction film.

[0008] One or more technical solutions provided in this application have at least the following technical effects or advantages:

[0009] The method provided in the embodiment of the present application activates the light-heat combined curing process, reads the substrate data of the substrate, establishes the surface curing index of the aviation drag reduction film according to the substrate data, configures the light curing parameters according to the surface curing index and the substrate data, performs the light curing process according to the light curing parameters, and calls the sensor group to collect the surface state data of the aviation drag reduction film after light curing, establishes the base state data, sets the initial temperature and target temperature of the heat curing according to the substrate data, and uses the base state data to set the temperature change gradient, divides the heat curing into stages, and establishes feedback constraints mapped to the stage division results, the stage division results include the initial stage, the intermediate stage and the final stage, configures the temperature monitoring point of the aviation drag reduction film, performs the stage temperature change gradient self-optimization according to the feedback data of the temperature monitoring point, the feedback constraint, and the stage division result, and performs light curing enhancement after the heat curing is completed, and completes the curing production of the aviation drag reduction film. The technical effect of accurately controlling the temperature of the aviation drag reduction film curing process and improving the curing uniformity, thereby enhancing the overall drag reduction performance of the drag reduction film and improving the quality of the drag reduction film is achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0011] Figure 1 A schematic diagram of the process flow of the method for optimizing the curing process parameters of aviation drag reduction films for various substrates provided in this application;

[0012] Figure 2 A schematic diagram of the structure of the aviation drag reduction film curing process parameter optimization system for various substrates provided in this application.

[0013] Description of reference numerals: substrate data acquisition module 11 , photocuring parameter configuration module 12 , base state data establishment module 13 , temperature setting module 14 , feedback constraint establishment module 15 , curing production module 16 . DETAILED DESCRIPTION

[0014] This application provides a method and system for optimizing the curing process parameters of aviation drag reduction films for various substrates, which is used to solve the technical problem in the prior art that the temperature control of the aviation drag reduction film curing process is not accurate, the curing is not uniform, and thus the drag reduction performance is reduced. The technical effect of accurately controlling the temperature of the aviation drag reduction film curing process and improving the uniformity of curing is achieved, thereby enhancing the overall drag reduction performance of the drag reduction film and improving the quality of the drag reduction film.

[0015] Below, the technical solutions in the present invention will be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments of the present invention. It should be understood that the present invention is not limited to the example embodiments described herein. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. It should also be noted that, for the convenience of description, only the parts related to the present invention are shown in the accompanying drawings, rather than all of them.

[0016] Embodiment 1, as Figure 1 As shown, the present application provides a method for optimizing curing process parameters of aviation drag reduction films for various substrates, the method comprising:

[0017] Activate the combined light-heat curing process and read the substrate data of the substrate.

[0018] Specifically, the light-heat combined curing process of the drag reduction film is first started and activated. The light-heat combined curing process integrates two technologies, light curing and heat curing, and includes three steps: the first stage of light curing, the heat curing stage and the secondary light curing. The light curing technology uses light of a specific wavelength to trigger a chemical reaction inside the material to achieve rapid curing. The heat curing controls the temperature and time to make the material reach a stable curing state in a wider area. In the first stage of light curing, a lower intensity light curing is first performed to ensure the initial shaping of the material and avoid flow; the heat curing stage is performed by gradually increasing the temperature to ensure the deep curing and structural stability of the material; after the heat curing is completed, the secondary light curing is used to finely process the surface or enhance the surface performance. Through the light-heat combined curing process, the characteristics of light curing and heat curing can be fully utilized to achieve a faster, more uniform and more stable curing effect, and it is suitable for resin coating on the surface of a variety of substrates and the surface structure has strong weather resistance. At the same time, the substrate data of the substrate is obtained from the substrate product specifications, technical manuals, substrate test reports and other documents. The substrate data includes material type, thickness, light transmittance, heat resistance, surface roughness, etc., and the material types are PET, TPU, PVC, etc. Obtaining the substrate data provides reliable data support for the subsequent optimization of the curing process parameters of the aviation drag reduction film.

[0019] The surface curing index of the aviation drag reduction film is established according to the substrate data, and the light curing parameters are configured according to the surface curing index and the substrate data.

[0020] Specifically, after obtaining the substrate data, the physical properties, chemical composition, thickness and other related data of the substrate data are analyzed in detail, and the surface curing index of the aviation drag reduction film is established based on the analysis results. The surface curing index refers to the specific requirements for evaluating the surface curing quality of the aviation drag reduction film, such as the required curing depth, curing speed and smoothness of the surface after curing. Then, according to the surface curing index and substrate data, the light curing parameters are configured. The light curing parameters are the key settings of the light curing process, including the intensity, wavelength, irradiation time, etc. of the light, which affect the curing quality of the drag reduction film. By configuring the light curing parameters, it is ensured that the drag reduction film can be completely cured and the surface smoothness meets the requirements.

[0021] Furthermore, configuring the photocuring parameters through the surface curing index and the substrate data also includes: parsing the surface curing index to obtain a curing depth index, a curing speed index, and a smoothness constraint index; using the curing depth index, the curing speed index, and the smoothness constraint index as collaborative control targets, calling the substrate data through a finite element analysis tool, executing control fitting of the collaborative control target, and configuring the photocuring parameters according to the control fitting results.

[0022] Specifically, the surface curing index is first analyzed to obtain three core indicators: curing depth index, curing speed index and smoothness constraint index. The curing depth index refers to the curing thickness that the surface layer of the material should reach during the photocuring process, which determines the strength and durability of the aviation drag reduction film; the curing speed index refers to the speed of the photocuring reaction, that is, the rate of formation of the curing layer per unit time, which affects the surface uniformity of the aviation drag reduction film; the smoothness constraint index refers to the smoothness of the surface of the drag reduction film after curing, which affects the aerodynamic performance of the aviation drag reduction film. Then, the curing depth index, curing speed index and smoothness constraint index are used as collaborative control targets, and the mutual influence and balance between the three core indicators are comprehensively considered. The finite element analysis tool is used to call the substrate data to perform photocuring simulation and analysis. The finite element analysis tool is a software tool that simulates real physical systems based on mathematical approximation methods. It can accurately simulate the physical behavior of materials by discretizing complex problems into small units.

[0023] During the simulation process, the interaction between multiple control targets is calculated and simulated according to the substrate data, and the light curing parameters are continuously adjusted to obtain the optimal light curing parameter combination that can simultaneously meet the requirements of curing depth, speed and smoothness, that is, the control fitting result. Finally, according to the control fitting result, the light curing parameters are configured to achieve precise control and optimization of the complex curing process, ensuring that all indicators of the drag reduction film meet the expected standards during the curing process and ensuring the quality of the final product.

[0024] The photocuring process is performed with the photocuring parameters, and the sensor group is called to collect the surface state data of the aviation drag reduction film after photocuring to establish the base state data.

[0025] Specifically, the photocuring process is started according to the configured photocuring parameters. After the photocuring process is completed, the sensor group deployed on the aviation drag reduction film production line is called to collect the surface state data of the aviation drag reduction film. The sensor group includes various types of sensors, such as temperature sensors, surface morphology sensors, optical sensors, etc., which can capture various state information of the surface of the aviation drag reduction film from all directions and angles. The surface state data includes but is not limited to the surface temperature, smoothness, thickness and other information of the drag reduction film after curing. And based on the surface state data, the base state data is established. The base state data is used to measure the performance consistency and stability of the aviation drag reduction film, provide the necessary feedback basis for the subsequent thermal curing stage, and ensure that further optimization and adjustment can be made according to the actual surface state during the thermal curing process.

[0026] The initial temperature and target temperature of thermal curing are set by the substrate data, and the temperature change gradient is set by the base state data.

[0027] The thermal curing is divided into stages, and feedback constraints mapped to the stage division results are established. The stage division results include an initial stage, an intermediate stage, and a final stage.

[0028] Specifically, according to the substrate data, the initial temperature and target temperature of thermal curing are set, wherein the initial temperature is the temperature setting at the beginning of thermal curing, which is determined by the characteristics of the substrate, such as the thermal properties of the material. The target temperature is the final temperature during the thermal curing process to ensure that the resin can be fully cured at this temperature while avoiding irreversible thermal deformation or degradation of the substrate. The initial thermal state and surface characteristics of the drag reduction film are analyzed using the ground state data, and the temperature change gradient is set. By setting the temperature change gradient, the stability of the thermal curing process can be ensured, so as to accurately control the temperature of the aviation drag reduction film curing process and improve the uniformity of curing.

[0029] Furthermore, the thermal curing is divided into stages, namely the initial stage, the intermediate stage and the final stage. In the initial stage, the temperature gradually rises from the initial temperature and the curing begins. At this time, the temperature change is relatively gentle, mainly to allow the substrate to gradually adapt to the thermal curing environment. When entering the intermediate stage, the temperature gradually approaches the target temperature, the curing speed is accelerated, and the internal structure of the material begins to form. In the final stage, the target temperature is reached and maintained for a period of time to ensure the complete curing of the entire material and eliminate any potential internal stress. In order to ensure the curing effect of each stage, a feedback constraint corresponding to the stage division result is established. The feedback constraint is a mechanism for dynamic adjustment based on the real-time feedback data of each thermal curing stage (such as the data of the temperature monitoring point, the ground state change, etc.). Through the coordination of stage division and feedback constraints, it can be ensured that the temperature and curing effect of each stage of thermal curing reach the optimal state, improve the uniformity of curing, thereby enhancing the overall drag reduction performance of the drag reduction film and improving the overall curing quality of the aviation drag reduction film.

[0030] Configure temperature monitoring points for the aviation drag reduction film, perform self-optimization of the stage temperature change gradient based on the feedback data, feedback constraints, and stage division results of the temperature monitoring points, and perform photocuring enhancement after thermal curing to complete the curing production of the aviation drag reduction film.

[0031] Specifically, by configuring temperature monitoring points distributed at different positions of the aviation drag reduction film, the temperature data of the drag reduction film is monitored in real time. After obtaining the real-time temperature data, the temperature change gradient is dynamically adjusted according to these feedback data, feedback constraints and stage division results, that is, the stage temperature change gradient is self-optimized to ensure uniform temperature distribution during the curing process and avoid local overheating or insufficient temperature. After the thermal curing is completed, light curing enhancement is carried out, and the surface performance of the drag reduction film is enhanced through further light curing steps, so that the curing effect of the aviation drag reduction film is more perfect, and the curing production of the aviation drag reduction film is completed. This optimization method can be applied to a variety of substrates, ensuring the precise control of the entire process of the aviation drag reduction film from light curing to thermal curing and then to light curing, thereby improving the performance and quality of the aviation drag reduction film.

[0032] Furthermore, the configuration of the temperature monitoring points of the aviation drag reduction film performs self-optimization of the stage temperature change gradient according to the feedback data, feedback constraints and stage division results of the temperature monitoring points, and also includes: obtaining the topological structure data of the aviation drag reduction film, configuring the matrix grid according to the topological structure data, and using the matrix grid to distribute the temperature monitoring points, the temperature monitoring points including first dimension monitoring points and second dimension monitoring points, the first dimension monitoring points are surface monitoring points, and the second dimension monitoring points are bottom layer monitoring points; using the temperature monitoring equipment to collect the temperature data of the temperature monitoring points, using the collection results as feedback data, evaluating the internal and external responses of the temperature through the first dimension monitoring points and the second dimension monitoring points corresponding to the same matrix grid, and generating a response penalty coefficient; obtaining the curing stage of the current thermal curing, matching the stage division results according to the curing stage, calling the feedback constraints to compensate for the response penalty coefficient, and updating the stage temperature change gradient according to the compensation results.

[0033] Specifically, the topological structure data of the aviation drag reduction film is obtained by means of three-dimensional scanning technology, computer-aided design, etc., and the topological structure data includes the surface shape, hierarchical distribution and material composition of the drag reduction film. Then, according to the topological structure data, a matrix grid is configured, and the matrix grid divides the surface and interior of the aviation drag reduction film into multiple small units for more accurate temperature monitoring. Through the matrix grid, the temperature monitoring points are divided into first-dimensional monitoring points and second-dimensional monitoring points. The first-dimensional monitoring points are set on the surface layer of the drag reduction film and are responsible for collecting the temperature data of the surface layer. The second-dimensional monitoring points are located at the bottom layer of the drag reduction film and are used for bottom-layer temperature monitoring. In order not to affect the structural integrity and performance of the material, the bottom-layer monitoring points choose to use small and thin embedded temperature sensors, such as ultra-thin thermocouples or micro temperature sensors, non-contact or low-invasive sensors, such as optical fiber temperature sensors or patch sensors, and optical fiber Bragg grating sensors, etc. These sensors can accurately measure the temperature without causing additional burden or damage to the material itself.

[0034] The temperature data of the temperature monitoring point is collected in real time by the temperature monitoring equipment, and the collected temperature data is used as feedback data. The internal and external response evaluation of the temperature is performed through the data of the corresponding surface layer (first dimension monitoring point) and the bottom layer (second dimension monitoring point) in the same matrix grid. The internal and external response evaluation is used to evaluate the difference in temperature changes between the surface layer and the bottom layer of the drag reduction film, and the response penalty coefficient is calculated through these differences. The response penalty coefficient is used to quantify the uneven temperature distribution during the curing process and to determine whether the temperature change needs to be adjusted. The higher the coefficient, the more uncoordinated the internal and external temperature response. According to the curing stage of the current thermal curing, the pre-set stage division results are automatically matched. Each curing stage has its specific process parameters and expected temperature change pattern. By calling the feedback constraints that match the current stage, the response penalty coefficient is adjusted and compensated to eliminate the problem of unbalanced internal and external temperature responses. Finally, according to the compensated results, the temperature change gradient of the current stage is automatically updated to ensure that the temperature change in the next thermal curing process is more stable and the curing quality is further optimized. The temperature monitoring points are configured by topological structure data, the temperature data is collected for internal and external response evaluation, and the temperature gradient in the curing process is adaptively optimized through the feedback constraint mechanism, which can ensure that the temperature control of the drag reduction film in each curing stage reaches the best state.

[0035] Furthermore, configuring the matrix grid with the topological structure data also includes: using the topological structure data to identify the material center and material edge of the aviation drag reduction film, and establishing a gradient penalty coefficient based on the material center identification results and the material edge identification results; and completing the matrix grid configuration after penalizing the initial matrix grid with the gradient penalty coefficient based on the initial matrix grid of the aviation drag reduction film size distribution in the topological structure.

[0036] Specifically, by analyzing the surface curvature, thickness distribution, and stress concentration area of ​​the topological structure data, the material center and material edge of the aviation drag reduction film are identified. The material center refers to a relatively stable and uniform area in the geometric position of the aviation drag reduction film, which has high structural strength and uniformity. The material edge refers to the edge area of ​​the aviation drag reduction film, which has the characteristics of fast edge heat dissipation and easy formation of cold spots, and the monitoring density needs to be increased. Then, the gradient penalty coefficient is generated according to the characteristic difference between the material center identification result and the material edge identification result. The gradient penalty coefficient is a penalty mechanism based on regional characteristics, which adjusts the control of curing parameters by evaluating the response of different regions (such as the center and the edge) to temperature and pressure during the curing process. The edge area has the characteristics of fast heat dissipation and easy formation of cold spots, so a higher penalty coefficient is required for additional adjustment. On the contrary, the gradient change of the material center is small, and the penalty coefficient is relatively low. In this way, the temperature and pressure control of different regions can be dynamically optimized in the subsequent curing process to ensure the uniformity of the curing quality.

[0037] Then, based on the size distribution in the topological structure of the aviation drag reduction film, an initial matrix grid is generated. Through gridding, the entire film can be divided into multiple small units, so that each small unit can be independently monitored and controlled during the curing process. After the initial matrix grid is generated, the gradient penalty coefficient is used to adjust the matrix grid. By applying the gradient penalty coefficients of different regions to each unit of the grid, it is ensured that the density and distribution of the grid can better reflect the characteristics of each part of the drag reduction film. For example, due to the high penalty coefficient in the edge area, the grid density needs to be appropriately increased to achieve more refined temperature control during the curing process. After the penalty and adjustment of the initial matrix grid, the final matrix grid configuration is obtained, which can more accurately reflect the characteristics of the center and edge of the material, and provide an accurate basis for subsequent temperature monitoring and feedback control, ensuring that the aviation drag reduction film can be effectively temperature controlled and optimized at all stages of the curing process.

[0038] Furthermore, the method of penalizing the initial matrix grid with the gradient penalty coefficient to complete the matrix grid configuration also includes: configuring a verification trigger threshold for the thermally sensitive area; authenticating the thermally sensitive area of ​​the aviation drag reduction film with the verification trigger threshold to generate an authentication result; and compensating the penalized initial matrix grid according to the authentication result to complete the matrix grid configuration.

[0039] Specifically, the thermally sensitive area refers to the area where the aviation drag reduction film is very sensitive to temperature changes during the curing process, including the edge or weak area of ​​the drag reduction film. The verification trigger threshold is a critical value set according to material properties, historical test data and engineering experience, which is used to determine whether a certain area belongs to a thermally sensitive area. After setting the verification trigger threshold, the verification trigger threshold is used to authenticate the thermally sensitive area of ​​the aviation drag reduction film. Through real-time temperature acquisition and data feedback, the performance data of the aviation drag reduction film under different temperature conditions is obtained and compared with the set verification trigger threshold. If the change in the performance parameters of a certain area exceeds the threshold when the temperature changes, the area is certified as a thermally sensitive area. According to the certification results, the initial matrix grid after the penalty is compensated, and the certified thermally sensitive areas are more accurately temperature controlled and optimized to ensure that these areas will not cause defects due to temperature changes during the subsequent curing process. For example, for thermally sensitive areas, the grid units can be encrypted to make the monitoring more detailed, so that temperature anomalies can be discovered and resolved more quickly in real-time feedback. Through these compensations, the configuration of the matrix grid is further optimized. Completing the matrix grid configuration provides a precise feedback mechanism for temperature control of the curing process, which can ensure that the curing quality of the aviation drag reduction film at each stage meets the expected standards.

[0040] Furthermore, the photo-curing enhancement after the completion of thermal curing also includes: establishing a curing state evaluation index, performing data monitoring of the aviation drag reduction film after performing thermal curing, performing a curing evaluation of the data monitoring results according to the curing state evaluation index, and generating a first evaluation result; establishing a surface temperature evaluation index, the surface temperature evaluation index is an interval evaluation index, and the surface temperature evaluation index is used to evaluate the surface temperature state of the data monitoring results to establish a second evaluation result; establishing a surface state uniformity evaluation index, and using the surface state uniformity evaluation index to evaluate the surface uniformity of the data monitoring results to establish a third evaluation result; and confirming the completion of thermal curing according to the first evaluation result, the second evaluation result, and the third evaluation result.

[0041] Specifically, a curing state evaluation index is established to measure the overall curing quality of the aviation drag reduction film during the thermal curing process. The curing state evaluation index includes key parameters such as curing depth, curing speed, and internal stress distribution of the material, which are used to reflect the integrity and uniformity of the curing. After the thermal curing is completed, the data monitoring results of the aviation drag reduction film, such as the temperature, deformation, surface state and other information of the drag reduction film, are obtained through real-time data monitoring. The data monitoring results are analyzed and compared according to the curing state evaluation index to generate a first evaluation result, which reflects the overall curing of the drag reduction film during the thermal curing process. A surface temperature evaluation index is established. The surface temperature evaluation index adopts an interval evaluation index, that is, a reasonable temperature range is set. Through the interval evaluation index, the fluctuation of the surface temperature of the drag reduction film during the thermal curing process can be evaluated. The data monitoring results are compared with the surface temperature evaluation index to determine whether the data is within a reasonable temperature range, and a second evaluation result is generated. The second evaluation result reflects whether the surface temperature of the drag reduction film is within a reasonable range. Further, a surface state uniformity evaluation index is established, and the surface state uniformity evaluation index is used to evaluate the smoothness and uniformity of the surface of the drag reduction film after curing. The data monitoring results are compared with the surface state uniformity evaluation index to obtain a third evaluation result, which reflects whether the smoothness and uniformity of the drag reduction film surface meet the requirements. Finally, through the first evaluation results, the second evaluation results and the third evaluation results, a comprehensive evaluation is made on whether the thermal curing process of the aviation drag reduction film has achieved the expected effect, that is, according to multiple key dimensions such as curing state, surface temperature and surface uniformity, the quality of the curing process of the drag reduction film after thermal curing is comprehensively evaluated and certified. When all evaluation results meet the requirements, the thermal curing is confirmed to be completed. If any evaluation result does not meet the standard, the curing process needs to be adjusted or re-cured to ensure that the final drag reduction film meets the requirements, thereby ensuring that the thermal curing process of the aviation drag reduction film meets the quality standards and improves the performance and quality of the aviation drag reduction film.

[0042] Furthermore, the internal and external response evaluation of the temperature is performed through the first dimension monitoring points and the second dimension monitoring points corresponding to the same matrix grid to generate the response penalty coefficient, and further includes: establishing a response penalty coefficient evaluation formula to calculate the response penalty coefficient, as follows: ;in, Characterization time The response penalty coefficient under Represents the total number of monitoring points in each dimension. The number of all monitoring points is , Represents the position points within the matrix grid, the position points There are two corresponding monitoring points, namely the first dimension monitoring point and the second dimension monitoring point , Characterizing location points The temperature difference, is the desired temperature difference target, Characterizing location points The weight of .

[0043] Specifically, by establishing a response penalty coefficient evaluation formula, the response penalty coefficient is calculated to quantify the temperature difference of the aviation drag reduction film at different positions. The response penalty coefficient evaluation formula is: ;in, Characterization time The response penalty coefficient under is used to evaluate the temperature response of aviation drag reduction films at different locations. Represents the total number of monitoring points in each dimension. The number of all monitoring points is , Represents the position points within the matrix grid, the position points There are two corresponding monitoring points, namely the first dimension monitoring point and the second dimension monitoring point , Characterizing location points The temperature difference, is the desired temperature difference target, Characterizing location points The weight of .

[0044] This formula can be used to calculate each time point The response penalty coefficients of all the locations in the matrix grid are calculated. The actual temperature difference of each location is compared with the preset expected temperature difference, and the weight of the location is used to calculate the actual temperature difference of each location. To adjust the degree of influence at different positions, thereby ensuring uniform internal and external temperatures of the aviation drag reduction film, achieving high-quality curing effects, and improving the quality and overall performance of the drag reduction film.

[0045] Embodiment 2, based on the same inventive concept as the method for optimizing the curing process parameters of aviation drag reduction films for various substrates in the above embodiment, Figure 2 As shown, the present application provides an aviation drag reduction film curing process parameter optimization system for various substrates, wherein the system comprises:

[0046] A substrate data acquisition module 11, the substrate data acquisition module 11 is used to activate the light-heat combined curing process and read the substrate data of the substrate; a light curing parameter configuration module 12, the light curing parameter configuration module 12 is used to establish the surface curing index of the aviation drag reduction film according to the substrate data, and configure the light curing parameters through the surface curing index and the substrate data; a base state data establishment module 13, the base state data establishment module 13 is used to execute the light curing process with the light curing parameters, and call the sensor group to collect the surface state data of the aviation drag reduction film after light curing, and establish the base state data; a temperature setting module 14, the temperature setting module 14 is used to The substrate data sets the initial temperature and target temperature of thermal curing, and uses the ground state data to set the temperature change gradient; a feedback constraint establishment module 15, the feedback constraint establishment module 15 is used to divide the thermal curing into stages, and establish feedback constraints mapped to the stage division results, the stage division results include an initial stage, an intermediate stage and a final stage; a curing production module 16, the curing production module 16 is used to configure the temperature monitoring points of the aviation drag reduction film, and self-optimize the stage temperature change gradient according to the feedback data of the temperature monitoring points, feedback constraints, and stage division results, and perform photocuring enhancement after the thermal curing is completed to complete the curing production of the aviation drag reduction film.

[0047] Furthermore, the curing production module 16 is also used to perform the following steps: obtaining the topological structure data of the aviation drag reduction film, configuring a matrix grid according to the topological structure data, and using the matrix grid to distribute temperature monitoring points, the temperature monitoring points include first dimension monitoring points and second dimension monitoring points, the first dimension monitoring points are surface monitoring points, and the second dimension monitoring points are bottom layer monitoring points; using temperature monitoring equipment to collect temperature data of temperature monitoring points, using the collection results as feedback data, and evaluating the internal and external responses of the temperature through the first dimension monitoring points and the second dimension monitoring points corresponding to the same matrix grid to generate a response penalty coefficient; obtaining the curing stage of the current thermal curing, matching the stage division result according to the curing stage, calling the feedback constraint to compensate for the response penalty coefficient, and updating the stage temperature change gradient according to the compensation result.

[0048] Furthermore, the curing production module 16 is also used to perform the following steps: using the topological structure data to identify the material center and material edge of the aviation drag reduction film, and establishing a gradient penalty coefficient based on the material center identification results and the material edge identification results; based on the initial matrix grid of the aviation drag reduction film size distribution in the topological structure, the initial matrix grid is penalized using the gradient penalty coefficient to complete the matrix grid configuration.

[0049] Furthermore, the curing production module 16 is also used to perform the following steps: configure a verification trigger threshold of a heat-sensitive area; use the verification trigger threshold to authenticate the heat-sensitive area of ​​the aviation drag reduction film and generate an authentication result; and compensate the initial matrix grid after the penalty according to the authentication result to complete the matrix grid configuration.

[0050] Furthermore, the photocuring parameter configuration module 12 is also used to perform the following steps: analyze the surface curing index to obtain the curing depth index, curing speed index, and smoothness constraint index; use the curing depth index, curing speed index, and smoothness constraint index as collaborative control targets, call the substrate data through the finite element analysis tool, perform control fitting of the collaborative control targets, and configure the photocuring parameters according to the control fitting results.

[0051] Furthermore, the curing production module 16 is also used to perform the following steps: establish a curing state evaluation index, perform data monitoring of the aviation drag reduction film after performing thermal curing, perform a curing evaluation of the data monitoring results according to the curing state evaluation index, and generate a first evaluation result; establish a surface temperature evaluation index, the surface temperature evaluation index is an interval evaluation index, and the surface temperature evaluation index is used to evaluate the surface temperature state of the data monitoring results to establish a second evaluation result; establish a surface state uniformity evaluation index, and use the surface state uniformity evaluation index to evaluate the surface uniformity of the data monitoring results to establish a third evaluation result; and confirm the completion of thermal curing according to the first evaluation result, the second evaluation result, and the third evaluation result.

[0052] Furthermore, the curing production module 16 is further used to perform the following steps: establish a response penalty coefficient evaluation formula to calculate the response penalty coefficient, as follows: ;in, Characterization time The response penalty coefficient under The total number of monitoring points in each dimension is , Represents the position points within the matrix grid, the position points There are two corresponding monitoring points, namely the first dimension monitoring point and the second dimension monitoring point , Characterizing location points The temperature difference, is the desired temperature difference target, Characterizing location points The weight of .

[0053] The above description is only a preferred embodiment of the present application and is not intended to limit the present application. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

[0054] This specification and the drawings are merely exemplary illustrations of the present application and are deemed to cover any and all modifications, variations, combinations or equivalents within the scope of the present application. Obviously, a person skilled in the art may make various modifications and variations to the present application without departing from the scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the present application and its equivalents, the present application intends to include these modifications and variations.

Claims

1. A method for optimizing curing process parameters of aviation drag reduction films for various substrates, characterized in that: The method comprises: Activate the light-heat combined curing process and read the substrate data of the substrate; Establishing a surface curing index of the aviation drag reduction film according to the substrate data, and configuring light curing parameters according to the surface curing index and the substrate data; Executing the photocuring process with the photocuring parameters, and calling the sensor group to collect the surface state data of the aviation drag reduction film after photocuring, and establishing the base state data; The initial temperature and target temperature of thermal curing are set by the substrate data, and the temperature change gradient is set by the base state data; Divide the thermal curing into stages and establish feedback constraints mapped to the stage division results, wherein the stage division results include an initial stage, an intermediate stage, and a final stage; Configure temperature monitoring points for aviation drag reduction film, perform self-optimization of stage temperature change gradient according to feedback data, feedback constraints, and stage division results of temperature monitoring points, and perform light curing enhancement after thermal curing is completed to complete the curing production of aviation drag reduction film; The temperature monitoring points of the aviation drag reduction film are configured, and the stage temperature change gradient is self-optimized according to the feedback data of the temperature monitoring points, the feedback constraints, and the stage division results, and further includes: Acquire the topological structure data of the aviation drag reduction film, configure the matrix grid according to the topological structure data, and use the matrix grid to distribute the temperature monitoring points, wherein the temperature monitoring points include first dimension monitoring points and second dimension monitoring points, wherein the first dimension monitoring points are surface monitoring points, and the second dimension monitoring points are bottom layer monitoring points; The temperature data of the temperature monitoring points are collected by temperature monitoring equipment, and the collected results are used as feedback data. The internal and external responses of the temperature are evaluated through the first dimension monitoring points and the second dimension monitoring points corresponding to the same matrix grid to generate a response penalty coefficient. Get the curing stage of the current thermal curing, match the stage division result according to the curing stage, call the feedback constraint to compensate the response penalty coefficient, and update the stage temperature change gradient according to the compensation result.

2. The method for optimizing curing process parameters of aviation drag reduction films for various substrates according to claim 1, characterized in that: The topological structure data configuration matrix grid also includes: Using the topological structure data to identify the material center and material edge of the aviation drag reduction film, and establishing a gradient penalty coefficient according to the material center identification results and the material edge identification results; According to the initial matrix grid of the aviation drag reduction film size distribution in the topological structure, the initial matrix grid is penalized by using a gradient penalty coefficient to complete the matrix grid configuration.

3. The method for optimizing curing process parameters of aviation drag reduction films for various substrates according to claim 2, characterized in that: After the initial matrix grid is penalized by the gradient penalty coefficient, the matrix grid configuration is completed, and the following steps are further included: Configure the verification trigger threshold for heat-sensitive areas; Utilizing the verification trigger threshold to perform thermal sensitive area authentication on the aviation drag reduction film, and generating an authentication result; The penalized initial matrix grid is compensated according to the authentication result to complete the matrix grid configuration.

4. The method for optimizing curing process parameters of aviation drag reduction films for various substrates according to claim 1, characterized in that: The configuring of light curing parameters by using the surface curing index and substrate data also includes: Analyze the surface curing index to obtain the curing depth index, curing speed index, and smoothness constraint index; The curing depth index, curing speed index and smoothness constraint index are used as collaborative control targets, the substrate data is called through a finite element analysis tool, control fitting of the collaborative control targets is performed, and light curing parameters are configured according to the control fitting results.

5. The method for optimizing curing process parameters of aviation drag reduction films for various substrates according to claim 1, characterized in that: The photo-curing enhancement after the heat curing is completed also includes: Establishing a curing state evaluation index, performing data monitoring of the aviation drag reduction film after performing thermal curing, performing a curing evaluation of the data monitoring result according to the curing state evaluation index, and generating a first evaluation result; Establishing a surface temperature evaluation index, wherein the surface temperature evaluation index is an interval evaluation index, and using the surface temperature evaluation index to evaluate the surface temperature state of the data monitoring result to establish a second evaluation result; Establishing a surface state uniformity evaluation index, using the surface state uniformity evaluation index to evaluate the surface uniformity of the data monitoring results, and establishing a third evaluation result; The completion of thermal curing is confirmed based on the first evaluation result, the second evaluation result, and the third evaluation result.

6. The method for optimizing curing process parameters of aviation drag reduction films for various substrates according to claim 1, characterized in that: The step of evaluating the internal and external responses of the temperature by using the first dimension monitoring points and the second dimension monitoring points corresponding to the same matrix grid to generate a response penalty coefficient also includes: A response penalty coefficient evaluation formula is established to calculate the response penalty coefficient, as follows: ； in, Characterization time The response penalty coefficient under Represents the total number of monitoring points in each dimension. The number of all monitoring points is , Represents the position points within the matrix grid, the position points There are two corresponding monitoring points, namely the first dimension monitoring point and the second dimension monitoring point , Characterizing location points The temperature difference, , is the desired temperature difference target, Characterizing location points The weight of .

7. The curing process parameter optimization system for aviation drag reduction films for various substrates is characterized by: The steps for implementing the method according to any one of claims 1 to 6 include: A substrate data acquisition module, the substrate data acquisition module is used to activate the light-heat combined curing process and read the substrate data of the substrate; A light curing parameter configuration module, the light curing parameter configuration module is used to establish a surface curing index of the aviation drag reduction film according to the substrate data, and configure light curing parameters according to the surface curing index and the substrate data; A base state data establishment module, the base state data establishment module is used to perform the light curing process with the light curing parameters, and call the sensor group to collect the surface state data of the aviation drag reduction film after light curing, and establish the base state data; A temperature setting module, the temperature setting module is used to set the initial temperature and target temperature of thermal curing according to the substrate data, and to set the temperature change gradient according to the base state data; A feedback constraint establishment module, the feedback constraint establishment module is used to divide the thermal curing into stages and establish feedback constraints mapped to the stage division results, the stage division results include an initial stage, an intermediate stage and a final stage; The curing production module is used to configure the temperature monitoring points of the aviation drag reduction film, self-optimize the stage temperature change gradient according to the feedback data of the temperature monitoring points, feedback constraints, and stage division results, and perform light curing enhancement after the thermal curing is completed to complete the curing production of the aviation drag reduction film.

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