Comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin

Abstract

The invention discloses a comprehensive evaluation method for the paint removal effect of an aluminum alloy aircraft skin, and relates to the technical field of aircraft surface treatment.The comprehensive evaluation method comprises the steps of skin paint removal macroscopic monitoring, skin paint removal microcosmic detection and skin paint removal comprehensive analysis and early warning prompt. Analyzing to obtain a macroscopic evaluation coefficient of the base body surface corresponding to the aluminum alloy aircraft, acquiring microscopic characteristics and microscopic mechanical characteristics of the base body surface corresponding to the aluminum alloy aircraft, and analyzing a microscopic evaluation coefficient of the base body surface corresponding to the aluminum alloy aircraft, so as to comprehensively judge the skin paint removal effect of the base body surface corresponding to the aluminum alloy aircraft. Therefore, the accurate paint removal effect is achieved, paint removal risk remedy is executed in time, the navigation safety of the airplane is guaranteed, the follow-up painting efficiency and quality of the aluminum alloy airplane are improved, and the navigation safety of the aluminum alloy airplane is further maintained.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft surface treatment, and in particular to a method for evaluating the paint removal effect of aluminum alloy aircraft skins. The method combines macroscopic and microscopic monitoring technologies to comprehensively evaluate the paint removal effect to ensure the quality and safety of aircraft surface treatment. Background Art

[0002] With the widespread use of aircraft in the aviation sector, ensuring flight safety has become a top priority. To ensure flight performance and safety, the original paint layer on the aircraft surface must be regularly removed to facilitate repainting. In particular, paint stripping of aluminum alloy aircraft skins requires both complete removal of the paint layer and the avoidance of damage to the aluminum alloy substrate. Therefore, effective monitoring and analysis of the paint stripping performance of aluminum alloy aircraft skins is essential.

[0003] Currently, comprehensive macro- and micro-level monitoring is commonly used to ensure the effectiveness of paint stripping on aluminum alloy aircraft. This monitoring of the aluminum alloy aircraft substrate surface ensures the effectiveness of the paint stripping process, thereby providing quality assurance for subsequent painting operations, avoiding thermal impacts and other potential issues, and further ensuring aircraft flight safety.

[0004] Prior art, for example, patent CN113732519B discloses a method for designing process parameters for laser paint removal on aluminum alloy aircraft skins. This method determines the laser paint removal parameter range through preliminary testing and then conducts laser paint removal tests using the surface composition evaluation factor as an indicator. The specific steps include: S1, using a high-power, medium-frequency laser to remove the paint layer from the aluminum alloy aircraft skin; S2, using a low-power, high-frequency laser to remove the resulting carbide deposits; and S3, determining the optimal paint removal parameters through orthogonal optimization. This technology optimizes and focuses existing laser paint removal parameters, attempting to determine the optimal paint removal process parameters using the surface composition evaluation factor.

[0005] The above-mentioned solution presents at least the following technical issues: Existing laser paint removal methods primarily focus on optimizing paint removal parameters and fail to fully consider comprehensive monitoring of the macroscopic and microscopic conditions of the aluminum alloy aircraft substrate surface. The shortcomings of existing technologies are: First, they fail to fully understand the actual conditions of the aluminum alloy substrate surface from both macroscopic and microscopic perspectives; second, they lack comprehensive analysis and evaluation of this data, making it impossible to fully assess the effectiveness of skin paint removal. Consequently, unsatisfactory paint removal results cannot be promptly identified or quickly adjusted, hindering effective quality assurance for subsequent painting operations. These issues can increase aircraft maintenance costs and even impact flight safety. Summary of the Invention

[0006] In view of the above-mentioned technical deficiencies, the purpose of the present invention is to provide a comprehensive evaluation method for the paint removal effect of aluminum alloy aircraft skins.

[0007] In order to solve the above technical problems, the present invention adopts the following technical solution: The present invention provides a comprehensive evaluation method for the paint removal effect of aluminum alloy aircraft skin, including: Step 1, macro-monitoring of skin paint removal: by monitoring the substrate surface corresponding to the aluminum alloy aircraft, the macro characteristics and macro mechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft are obtained, and then the macro evaluation coefficient of the substrate surface corresponding to the aluminum alloy aircraft is obtained by analysis.

[0008] Step 2: Microscopic inspection of skin paint removal: Perform microscopic monitoring on the substrate surface corresponding to the aluminum alloy aircraft to obtain the microscopic characteristics and micromechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft, and analyze to obtain the microscopic evaluation coefficient of the substrate surface corresponding to the aluminum alloy aircraft.

[0009] Step 3. Comprehensive analysis of skin paint removal: Based on the macro-evaluation coefficient and micro-evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft, the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is judged. When the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is unqualified, an improved method for skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is analyzed.

[0010] Step 4: Early warning: When the overall effect of paint removal on the corresponding substrate surface of the aluminum alloy aircraft is unsatisfactory, an early warning will be sent to the staff.

[0011] 1. Compared with the prior art, the beneficial effects of the present invention are as follows: the present invention provides a comprehensive evaluation method for the paint removal effect of the aluminum alloy aircraft skin, by monitoring the macro characteristics and macro mechanical characteristics of the corresponding substrate surface of the aluminum alloy aircraft, analyzing and obtaining the macro evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft, and obtaining the micro characteristics and micro mechanical characteristics of the corresponding substrate surface of the aluminum alloy aircraft, analyzing the micro evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft, thereby comprehensively evaluating the paint removal effect of the skin of the corresponding substrate surface of the aluminum alloy aircraft, thereby obtaining accurate paint removal effect, executing timely paint removal risk remediation, and ensuring the navigation safety of the aircraft.

[0012] 2. Through real-time microscopic and macroscopic monitoring and evaluation, the present invention can promptly detect potential paint removal problems on the surface of aluminum alloy aircraft substrates, prevent flight safety hazards caused by incomplete or non-standard paint removal, and significantly improve the level of flight safety assurance. By combining macroscopic and microscopic evaluation coefficients, the comprehensive evaluation method of the present invention not only makes paint removal operations more accurate, but also provides operational data support for the improvement of the paint removal process, thereby improving the efficiency, quality and safety of the overall process.

[0013] 3. By combining macro and micro data, the paint removal effect of aluminum alloy aircraft skin is comprehensively evaluated, avoiding the judgment bias caused by the single data in traditional technology, ensuring a more accurate evaluation of the paint removal effect, and providing accurate data support for subsequent painting operations, avoiding the risk of coating defects and peeling, improving the efficiency and quality of painting, and ensuring the long-term stability of the aircraft surface coating.

[0014] 4. When the paint removal effect is unsatisfactory, the present invention can promptly identify the problem and provide corresponding improvement methods, thereby achieving rapid risk remediation and ensuring the aircraft's navigation safety. Accurate evaluation of the paint removal effect reduces unnecessary repetitive operations and material waste, effectively reducing maintenance costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0016] Figure 1 The figure is a flow chart of the steps for implementing the method of the present invention. DETAILED DESCRIPTION

[0017] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0018] See also Figure 1 As shown, a comprehensive evaluation method for the paint removal effect of aluminum alloy aircraft skin includes: Step 1, macro-monitoring of skin paint removal: by monitoring the substrate surface corresponding to the aluminum alloy aircraft, the macro characteristics and macro mechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft are obtained, and then the macro evaluation coefficient of the substrate surface corresponding to the aluminum alloy aircraft is obtained by analysis.

[0019] It should be noted that the monitoring of the substrate surface corresponding to the aluminum alloy aircraft is carried out from both the macro monitoring perspective and the micro perspective, so as to achieve a comprehensive judgment of the skin removal effect of the substrate surface corresponding to the aluminum alloy aircraft from a broad perspective and a differential perspective, and obtain accurate results of the skin removal effect of the aluminum alloy aircraft.

[0020] It should be noted that the substrate surface is imaged using image analysis software, and then the residual coating area on the substrate surface corresponding to the aluminum alloy aircraft is obtained based on the known area calculation formula corresponding to the imaged graphic. The surface smoothness of the substrate surface corresponding to the aluminum alloy aircraft is obtained using a profilometer, and the area of ​​bubble spots on the substrate surface corresponding to the aluminum alloy aircraft and the adhesion between the paint film and the substrate are extracted using image analysis software.

[0021] As an optional embodiment, the macroscopic features of the substrate surface corresponding to the aluminum alloy aircraft are obtained by the following specific acquisition process: A1. Using a camera to perform corresponding monitoring on the substrate surface corresponding to the aluminum alloy aircraft, macroscopic images of the substrate surface corresponding to the aluminum alloy aircraft during each paint removal operation are collected, and the collected macroscopic images are arranged according to the order of the operations;

[0022] A2. Observe the coating on the corresponding substrate surface of the aluminum alloy aircraft under various paint removal operations. Use image processing technology to extract the coating color tone after paint stripping. Perform defect scanning on the corresponding substrate surface of the aluminum alloy aircraft, extracting scratches, depressions, and defect features corresponding to the substrate surface. Defect features manifest as bubbles and spots. Also, extract the adhesion between the paint film and the substrate, and determine the amount of separation between the paint film and the substrate after paint stripping. This completes the visual observation of the macroscopic image of the corresponding substrate surface of the aluminum alloy aircraft under various paint stripping operations.

[0023] A3. Extract the representative features of the macroscopic image to obtain the macroscopic features of the aluminum alloy aircraft's corresponding substrate surface. The macroscopic features include the coating residual area, surface finish, bubble spot distribution area, and the adhesion between the paint film and the substrate. Based on the extracted macroscopic features, the macroscopic apparent value of the aluminum alloy aircraft's corresponding substrate surface is obtained, which is recorded as β. y .

[0024] It should be noted that, through the calculation formula:

[0025]

[0026] , the macroscopic apparent value β of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation is obtained comprehensively y , y is the number of each paint removal operation, y = 1, ..., ..., n, n is any integer greater than 2, a' is the set reference coating residual area, b' is the set reference surface finish, f' is the set reference bubble spot area, d' is the set reference paint film and substrate adhesion, a y is the coating residual area on the corresponding substrate surface of the aluminum alloy aircraft after the yth paint removal operation, b y is the surface finish of the corresponding substrate surface of the aluminum alloy aircraft after the yth paint removal operation, f yis the area of ​​bubble spots on the corresponding substrate surface of the aluminum alloy aircraft during the yth paint removal operation, d y is the adhesion between the paint film and the substrate of the aluminum alloy aircraft corresponding to the substrate surface under the yth paint removal operation. z1, z2, z3, and z4 are the weight factors of the set coating residual area, surface finish, bubble spot area, and paint film-substrate adhesion, respectively. 0<z1<1, 0<z2<1, 0<z3<1, 0<z4<1.

[0027] It should be noted that the historical coating residual area of ​​the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, the historical coating residual area of ​​the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average historical coating residual area, and the average historical coating residual area is used as the reference coating residual area, the historical surface finish of the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, the historical surface finish of the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average historical surface finish, and the average historical surface finish is used as the reference surface finish, and the historical surface finish of each aluminum alloy aircraft is obtained from the database. The historical bubble spot distribution area of ​​the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, and the historical bubble spot distribution area of ​​the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average historical bubble spot distribution area, and the average historical bubble spot distribution area is used as the reference bubble spot distribution area. The historical paint film and substrate adhesion of the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, and the historical paint film and substrate adhesion of the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average paint film and substrate adhesion, and the average historical paint film and substrate adhesion is used as the reference paint film and substrate adhesion.

[0028] It should be noted that z1, z2, z3 and z4 are set based on the existing technology in the current relevant field. The values ​​of z1, z2, z3 and z4 are set based on the analysis of a large amount of data on aluminum alloy aircraft and the multi-dimensional factors in the actual scenarios of aluminum alloy aircraft. Therefore, they will not be elaborated here.

[0029] As an optional embodiment, the macroscopic mechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft are obtained, and the specific acquisition process is as follows: using an optical microscope to monitor the corresponding substrate surface of the aluminum alloy aircraft during each paint removal operation, and then obtaining a microscopic image corresponding to the substrate surface; by checking the basic appearance of the substrate surface from the microscopic image, if the substrate surface shows a convex or concave phenomenon, the roughness of the substrate surface corresponding to the aluminum alloy aircraft is extracted; at the same time, an ultrasonic detector is used to perform ultrasonic testing on the substrate surface corresponding to the aluminum alloy aircraft, and based on the feedback sound wave characteristics, the tensile strength of the substrate surface corresponding to the aluminum alloy aircraft is obtained, thereby comprehensively obtaining the macroscopic mechanical characteristics, wherein the macroscopic mechanical characteristics include roughness and tensile strength, and the macroscopic mechanical value of the substrate surface corresponding to the aluminum alloy aircraft is calculated based on the macroscopic mechanical characteristics, which is recorded as η. y .

[0030] It should be noted that an ultrasonic detector is used to perform ultrasonic testing on the corresponding substrate surface of the aluminum alloy aircraft, and the tensile strength of the corresponding substrate surface of the aluminum alloy aircraft is obtained based on the feedback sound wave characteristics: an ultrasonic detector is used to emit ultrasonic pulses to the surface of the aluminum alloy substrate, and the corresponding propagation velocity is measured. Secondly, based on the empirical formula between the sound velocity and tensile strength of aluminum alloy materials: σb = A × vn, where σb is tensile strength, v is ultrasonic sound velocity, A and n are constants related to the characteristics of aluminum alloy materials. The data corresponding to the substrate surface monitored by the ultrasonic detector is substituted into the value formula to obtain the tensile strength of the corresponding substrate surface of the aluminum alloy aircraft.

[0031] It should be noted that, through the calculation formula:

[0032] The macroscopic mechanical value η of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation is obtained comprehensively y , ξ′ is the set reference roughness, υ′ is the set reference tensile strength, ξ y is the roughness of the corresponding substrate surface of the aluminum alloy aircraft during the yth paint removal operation, υ y is the tensile strength of the corresponding substrate surface of the aluminum alloy aircraft after the yth paint removal operation, x1 and x2 are the set roughness weight factor and tensile strength weight factor, respectively, 0<x1<1, 0<x2<1.

[0033] It should also be noted that the historical roughness of the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, and the historical roughness of the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average historical roughness, and the average historical roughness is used as the reference roughness. The historical tensile strength of the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, and the historical tensile strength of the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average historical tensile strength, and the average historical tensile strength is used as the reference tensile strength.

[0034] It should also be noted that the setting process of x1 and x2 and the following weight factors is the same as the setting process of z1, z2, z3 and z4, so they will not be described in detail.

[0035] As an optional implementation, the analysis obtains the macroscopic evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft. The specific analysis process is as follows: by calculating the formula:

[0036] The macroscopic evaluation coefficient GK of the corresponding substrate surface of the aluminum alloy aircraft is obtained by analysis, β′ is the set reference macroscopic apparent value, β y is the macroscopic apparent value of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation, η′ is the set reference macroscopic mechanical value, η y is the macroscopic mechanical value of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation. p1 and p2 are the weight factors of the basic apparent value and the macroscopic mechanical value, respectively. 0<p1<1, 0<p2<1.

[0037] It should be noted again that the macroscopic apparent values ​​of the substrate surface corresponding to each historical aluminum alloy aircraft are obtained from the database, and the macroscopic apparent values ​​of the substrate surface corresponding to each historical aluminum alloy aircraft are calculated based on the average value to obtain the average macroscopic apparent values ​​of the substrate surface corresponding to each historical aluminum alloy aircraft. The historical average macroscopic apparent values ​​are used as reference macroscopic apparent values, and the macroscopic mechanical values ​​of the substrate surface corresponding to each historical aluminum alloy aircraft are obtained from the database. The macroscopic mechanical values ​​of the substrate surface corresponding to each historical aluminum alloy aircraft are calculated based on the average value to obtain the average macroscopic mechanical values ​​of the substrate surface corresponding to each historical aluminum alloy aircraft. The historical average macroscopic mechanical values ​​are used as reference macroscopic mechanical values.

[0038] Through real-time microscopic and macroscopic monitoring and evaluation, the present invention can promptly detect potential paint removal problems on the surface of aluminum alloy aircraft substrates, prevent flight safety hazards caused by incomplete or non-standard paint removal, and significantly improve the level of flight safety assurance. By combining macroscopic and microscopic evaluation coefficients, the comprehensive evaluation method of the present invention not only makes paint removal operations more accurate, but also provides operational data support for the improvement of the paint removal process, thereby improving the efficiency, quality and safety of the overall process.

[0039] Step 2: Microscopic inspection of skin paint removal: Perform microscopic monitoring on the substrate surface corresponding to the aluminum alloy aircraft to obtain the microscopic characteristics and micromechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft, and analyze to obtain the microscopic evaluation coefficient of the substrate surface corresponding to the aluminum alloy aircraft.

[0040] As an optional embodiment, the microscopic characteristics of the substrate surface corresponding to the aluminum alloy aircraft are obtained, and the specific acquisition process is as follows: by using various devices to collect the microstructure data of the substrate surface corresponding to the aluminum alloy aircraft under each paint removal operation, using an electron microscope to obtain the structural presentation of the substrate surface corresponding to the aluminum alloy aircraft under each paint removal operation, extracting the particle distribution area corresponding to the substrate surface, and using a thickness meter to collect the residual coating thickness on the substrate surface under each paint removal operation, and at the same time turning on the spectrum analyzer to analyze the composition of the substrate surface and the chemical composition generated during the paint removal process, and obtaining the corresponding coating chemical composition content and paint remover chemical composition content of the substrate surface corresponding to the aluminum alloy aircraft after the coating is removed, thereby completing the acquisition of the microstructure information of the substrate surface corresponding to the aluminum alloy aircraft, wherein the microstructure includes the particle distribution area, the residual coating thickness, the coating chemical composition content and the paint remover chemical composition content, and the microstructure value of the substrate surface corresponding to the aluminum alloy aircraft is obtained by comprehensive calculation based on the acquired microstructure, which is recorded as ω. y .

[0041] It should be noted that, through the calculation formula:

[0042]

[0043] , the microstructure value ω of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation is obtained comprehensively y , σ′ is the set reference particle distribution area, φ′ is the set reference coating residual thickness, λ′ is the set reference coating chemical composition content, ψ′ is the set reference paint remover chemical composition content, σ y is the particle distribution area on the substrate surface of the aluminum alloy aircraft under the yth paint removal operation, φ y is the residual coating thickness on the corresponding substrate surface of the aluminum alloy aircraft after the yth paint removal operation, λ y is the chemical composition content of the coating on the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation, ψ yis the chemical composition content of the paint remover on the corresponding substrate surface of the aluminum alloy aircraft during the yth paint removal operation. g1, g2, g3, and g4 are the weight factors of the set particle distribution area, the residual coating thickness, the coating chemical composition content, and the paint remover chemical composition content, respectively. 0<g1<1, 0<g2<1, 0<g3<1, 0<g4<1.

[0044] It should be noted that the historical particle distribution area of ​​the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, and the historical particle distribution area of ​​the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average historical particle distribution area, and the average historical particle distribution area is used as the reference particle distribution area; the historical coating residual thickness of the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, and the historical coating residual thickness of the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average historical coating residual thickness, and the average historical coating residual thickness is used as the reference coating residual thickness; the historical coating chemical composition content of the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, and the historical coating chemical composition content of the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average historical coating chemical composition content, and the average historical coating chemical composition content is used as the reference coating chemical composition content; the historical paint remover chemical composition content of the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, and the historical paint remover chemical composition content of the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average paint remover chemical composition content, and the average historical paint remover chemical composition content is used as the reference paint remover chemical composition content.

[0045] It should be noted that the chemical components of paint removers include chlorinated hydrocarbons, toluene and xylene.

[0046] It should be noted that the expansion direction includes intergranular expansion, transgranular expansion, crack deflection and crack bifurcation.

[0047] As an optional embodiment, the micromechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft are obtained, and the specific acquisition process is as follows: D1. Use an electron microscope to inspect the cracks on the substrate surface corresponding to the aluminum alloy aircraft under each paint removal operation. If cracks are detected on the substrate surface corresponding to the aluminum alloy aircraft, use the corresponding magnification performance of the electron microscope to amplify the cracks accordingly and obtain the corresponding expansion direction of the cracks.

[0048] D2. Use X-ray diffraction technology to scan the substrate surface corresponding to the aluminum alloy aircraft under each paint removal operation, obtain the scanning display image of the substrate surface corresponding to the aluminum alloy aircraft under each paint removal operation, and observe the material phase variable corresponding to the substrate surface after paint removal from the scanning display image. At the same time, observe the crystal structure corresponding to the substrate surface after paint removal, and extract the atomic spacing of the crystal corresponding to the substrate surface after paint removal. In summary, the micromechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft are obtained, including the material phase variable and the atomic spacing. The micromechanical characteristics are calculated based on the micromechanical characteristics to obtain the micromechanical value of the substrate surface corresponding to the aluminum alloy aircraft, which is recorded as θ y .

[0049] It should be noted that the calculation formula The micromechanical value θ of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation is obtained comprehensively y , Φ′ is the reference material phase variable, N′ is the reference atomic distance, Φ y is the material phase variable of the aluminum alloy aircraft corresponding to the substrate surface under the yth paint removal operation, N y is the atomic distance on the substrate surface of the aluminum alloy aircraft under the yth paint removal operation, r1 and r2 are the weight factors of the set material phase variable and atomic distance, respectively, 0<r1<1, 0<r2<1.

[0050] It should also be noted that the historical material phase variables of the substrate surface corresponding to each aluminum alloy aircraft are obtained from the database, the historical material phase variables of the substrate surface corresponding to each aluminum alloy aircraft are calculated based on the average value to obtain the average historical material phase variable, and the average historical material phase variable is used as the reference material phase variable, the historical atomic spacing of the substrate surface corresponding to each aluminum alloy aircraft is obtained from the database, the historical atomic spacing of the substrate surface corresponding to each aluminum alloy aircraft is calculated based on the average value to obtain the average historical atomic spacing, and the average historical atomic spacing is used as the reference atomic spacing.

[0051] As an optional embodiment, the analysis obtains the microscopic evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft. The specific analysis process is as follows: by calculating the formula:

[0052] The microscopic evaluation coefficient WJ of the corresponding matrix surface of the aluminum alloy aircraft is obtained by analysis, where ω′ is the set reference microstructure value, and ω y is the reference microstructure value of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation, θ′ is the set reference micromechanical value, θ yis the micromechanical value of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation. m1 and m2 are the weight factors of the microstructure value and the micromechanical value, respectively. 0<m1<1, 0<m2<1.

[0053] It should be noted again that the microstructure values ​​of the substrate surfaces corresponding to each historical aluminum alloy aircraft are obtained from the database, and the average microstructure values ​​of the substrate surfaces corresponding to each historical aluminum alloy aircraft are calculated based on the average value, and the average microstructure values ​​of the substrate surfaces corresponding to each historical aluminum alloy aircraft are obtained. The historical average microstructure values ​​are used as reference microstructure values, and the micromechanical values ​​of the substrate surfaces corresponding to each historical aluminum alloy aircraft are obtained from the database, and the micromechanical values ​​of the substrate surfaces corresponding to each historical aluminum alloy aircraft are calculated based on the average value, and the average micromechanical values ​​of the substrate surfaces corresponding to each historical aluminum alloy aircraft are obtained. The historical average micromechanical values ​​are used as reference micromechanical values.

[0054] By combining macro and micro data, the paint removal effect of aluminum alloy aircraft skins is comprehensively evaluated, avoiding the judgment bias caused by the singleness of data in traditional technologies, ensuring a more accurate evaluation of the paint removal effect, and providing precise data support for subsequent painting operations, avoiding the risk of coating defects and peeling, improving the efficiency and quality of painting, and ensuring the long-term stability of the aircraft surface coating.

[0055] Step 3. Comprehensive analysis of skin paint removal: Based on the macro-evaluation coefficient and micro-evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft, the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is judged. When the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is unqualified, an improved method for skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is analyzed.

[0056] As an optional embodiment, the specific analysis process of judging the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is as follows: the macro-evaluation coefficient and the micro-evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft are normalized, and the macro-evaluation coefficient and the micro-evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft after the processing are input into the aluminum alloy aircraft paint removal effect evaluation model; if the output value of the comprehensive paint removal effect coefficient of the corresponding substrate surface of the aluminum alloy aircraft is 1, it is judged that the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is unqualified, and the improvement method of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is executed; if the output value of the comprehensive paint removal effect coefficient of the corresponding substrate surface of the aluminum alloy aircraft is 0, it is judged that the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is qualified, thereby judging the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft.

[0057] As an optional implementation, the output obtains the comprehensive effect result of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft. The specific output process is as follows: by calculating the formula: The output is the comprehensive effect result ZH of the skin paint removal of the corresponding substrate surface of the aluminum alloy aircraft, GK is the macro-evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft, WJ is the micro-evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft, XS is the set reference skin paint removal effect coefficient, L1 and L2 are the weight factors of the set macro-evaluation coefficient and the weight factors of the micro-evaluation coefficient, respectively, 0<L1<1, 0<L2<1.

[0058] It should be noted that the skin paint removal effect coefficient thresholds of the corresponding substrate surfaces of each historical aluminum alloy aircraft in a qualified state of comprehensive paint removal effect are obtained from the database, and the skin paint removal effect coefficient thresholds of the corresponding substrate surfaces of each historical aluminum alloy aircraft are calculated based on the average value, thereby obtaining the average skin paint removal effect coefficient thresholds of the corresponding substrate surfaces of each historical aluminum alloy aircraft, and the average skin paint removal effect coefficient thresholds of the corresponding substrate surfaces of the historical aluminum alloy aircraft are used as the reference skin paint removal effect coefficient.

[0059] As an optional implementation method, the analysis obtains an improved method for skin paint removal on the corresponding substrate surface of an aluminum alloy aircraft. The specific analysis process is as follows: when the macro-evaluation coefficient is unqualified in the comprehensive effect of skin paint removal on the corresponding substrate surface of an aluminum alloy aircraft, macro-aspect paint removal improvements are performed on the skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft, and the paint removal equipment is replaced for the corresponding skin paint removal of the aluminum alloy aircraft or the surface of the aluminum alloy aircraft is pretreated before paint removal. At the same time, micro-aspect paint removal improvements are also performed on the skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft, and the paint remover is replaced for the corresponding skin paint removal of the aluminum alloy aircraft or the paint removal method is changed.

[0060] When the paint removal effect is unsatisfactory, the present invention can promptly discover the problem and provide corresponding improvement methods, thereby achieving rapid risk remediation and ensuring the aircraft's navigation safety. Accurate evaluation of the paint removal effect reduces unnecessary repetitive operations and material waste, effectively reducing maintenance costs.

[0061] It should be noted that the surface pretreatment includes anodizing and phosphating primer, etc.

[0062] Step 4: Early warning: When the overall effect of paint removal on the corresponding substrate surface of the aluminum alloy aircraft is unsatisfactory, an early warning will be sent to the staff.

[0063] According to an embodiment of the present invention, the macroscopic characteristics and macroscopic mechanical characteristics of the corresponding substrate surface of the aluminum alloy aircraft are monitored, and the macroscopic evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft is obtained by analysis. The microscopic characteristics and microscopic mechanical characteristics of the corresponding substrate surface of the aluminum alloy aircraft are also obtained, and the microscopic evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft is analyzed. Based on this, a comprehensive evaluation is performed on the paint removal effect of the skin corresponding substrate surface of the aluminum alloy aircraft, thereby obtaining an accurate paint removal effect, executing timely paint removal risk remediation, and ensuring the navigation safety of the aircraft.

[0064] The above content is merely an example and explanation of the concept of the present invention. Those skilled in the art may make various modifications or additions to the described specific embodiments or replace them in a similar manner. As long as they do not deviate from the concept of the invention or exceed the scope defined in this specification, they should all fall within the scope of protection of the present invention.

Claims

1. A comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin, characterized in that: include: Step 1: Macroscopic monitoring of skin paint removal: By monitoring the substrate surface corresponding to the aluminum alloy aircraft, the macroscopic characteristics and macroscopic mechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft are obtained, and then the macroscopic evaluation coefficient of the substrate surface corresponding to the aluminum alloy aircraft is obtained through analysis; Step 2: Microscopic inspection of skin paint removal: Perform microscopic monitoring on the substrate surface corresponding to the aluminum alloy aircraft to obtain the microscopic characteristics and micromechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft, and analyze and obtain the microscopic evaluation coefficient of the substrate surface corresponding to the aluminum alloy aircraft; Step 3: Comprehensive analysis of skin paint removal: Based on the macroscopic evaluation coefficient and microscopic evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft, the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is determined. If the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is unsatisfactory, an improved method for skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft is analyzed; Step 4: Early warning: When the overall effect of paint removal on the corresponding substrate surface of the aluminum alloy aircraft is unsatisfactory, an early warning will be sent to the staff.

2. A comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin according to claim 1, characterized in that: The specific process of obtaining the macroscopic features of the substrate surface corresponding to the aluminum alloy aircraft is as follows: A1. Use a camera to monitor the corresponding substrate surface of the aluminum alloy aircraft, collect macro images of the corresponding substrate surface of the aluminum alloy aircraft during each paint removal operation, and arrange the collected macro images according to the order of the operations. A2. Observe the coating on the corresponding substrate surface of the aluminum alloy aircraft under various paint removal operations. Use image processing technology to extract the coating color tone after paint stripping. Perform defect scanning on the corresponding substrate surface of the aluminum alloy aircraft, extracting scratches, depressions, and defect features corresponding to the substrate surface. Defect features manifest as bubbles and spots. Also, extract the adhesion between the paint film and the substrate, and determine the amount of separation between the paint film and the substrate after paint stripping. This completes the visual observation of the macroscopic image of the corresponding substrate surface of the aluminum alloy aircraft under various paint stripping operations. A3. Extract the representative features of the macroscopic image to obtain the macroscopic features of the aluminum alloy aircraft's corresponding substrate surface. The macroscopic features include the coating residual area, surface finish, bubble spot distribution area, and the adhesion between the paint film and the substrate. Based on the extracted macroscopic features, the macroscopic apparent value of the aluminum alloy aircraft's corresponding substrate surface is obtained, which is recorded as β. y .

3. The comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin according to claim 1, characterized in that: The specific process of obtaining the macroscopic mechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft is as follows: An optical microscope is used to monitor the corresponding substrate surface of the aluminum alloy aircraft under each paint removal operation, and then a microscopic image corresponding to the substrate surface is obtained. By observing the basic appearance of the substrate surface from the microscopic image, if the substrate surface shows a convex or concave phenomenon, the roughness of the corresponding substrate surface of the aluminum alloy aircraft is extracted. At the same time, an ultrasonic detector is used to perform ultrasonic testing on the corresponding substrate surface of the aluminum alloy aircraft, and the tensile strength of the corresponding substrate surface of the aluminum alloy aircraft is obtained based on the feedback sound wave characteristics. In this way, the macroscopic mechanical characteristics are comprehensively obtained, wherein the macroscopic mechanical characteristics include roughness and tensile strength. The macroscopic mechanical value of the corresponding substrate surface of the aluminum alloy aircraft is calculated based on the macroscopic mechanical characteristics and is recorded as η. y .

4. A comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin according to claim 3, characterized in that: The analysis yields the macroscopic evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft. The specific analysis process is as follows: By calculating the formula The macroscopic evaluation coefficient GK of the corresponding substrate surface of the aluminum alloy aircraft is obtained by analysis, where y is the number of each paint removal operation, y = 1, ..., ..., n, n is any integer greater than 2, β′ is the set reference macroscopic apparent value, β y is the macroscopic apparent value of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation, η′ is the set reference macroscopic mechanical value, η y is the macroscopic mechanical value of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation. p1 and p2 are the weight factors of the basic apparent value and the macroscopic mechanical value, respectively. 0<p1<1, 0<p2<1.

5. The comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin according to claim 1, characterized in that: The specific process of obtaining the microscopic features of the substrate surface corresponding to the aluminum alloy aircraft is as follows: By using various devices to collect the microstructure data of the corresponding substrate surface of the aluminum alloy aircraft under each paint removal operation, using an electron microscope to obtain the structural presentation of the corresponding substrate surface of the aluminum alloy aircraft under each paint removal operation, extracting the particle distribution area corresponding to the substrate surface, and using a thickness gauge to collect the residual coating thickness on the substrate surface under each paint removal operation, while turning on the spectrum analyzer to analyze the composition of the substrate surface and the chemical composition generated during the paint removal process, the corresponding coating chemical composition content and paint remover chemical composition content of the corresponding substrate surface of the aluminum alloy aircraft after the coating is removed are obtained, thereby completing the acquisition of the microstructure information of the corresponding substrate surface of the aluminum alloy aircraft, wherein the microscopic characteristics include the particle distribution area, the residual coating thickness, the coating chemical composition content and the paint remover chemical composition content, and the microstructure value of the corresponding substrate surface of the aluminum alloy aircraft is obtained by comprehensive calculation based on the obtained microscopic characteristics, which is recorded as ω. y .

6. A comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin according to claim 1, characterized in that: The specific process of obtaining the micromechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft is as follows: D1. Use an electron microscope to inspect the surface of the aluminum alloy aircraft substrate for cracks during each paint removal operation. If a crack is detected on the surface of the aluminum alloy aircraft substrate, the electron microscope's magnification capability is used to amplify the crack and determine its propagation direction. D2. Use X-ray diffraction technology to scan the substrate surface corresponding to the aluminum alloy aircraft under each paint removal operation, obtain the scanning display image of the substrate surface corresponding to the aluminum alloy aircraft under each paint removal operation, and observe the material phase variable corresponding to the substrate surface after paint removal from the scanning display image. At the same time, observe the crystal structure corresponding to the substrate surface after paint removal, and extract the atomic spacing of the crystal corresponding to the substrate surface after paint removal. In summary, the micromechanical characteristics of the substrate surface corresponding to the aluminum alloy aircraft are obtained, including the material phase variable and the atomic spacing. The micromechanical characteristics are calculated based on the micromechanical characteristics to obtain the micromechanical value of the substrate surface corresponding to the aluminum alloy aircraft, which is recorded as θ y .

7. A comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin according to claim 6, characterized in that: The analysis yields the microscopic evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft. The specific analysis process is as follows: By calculating the formula The microscopic evaluation coefficient WJ of the corresponding substrate surface of the aluminum alloy aircraft is obtained by analysis, where y is the number of each paint removal operation, y = 1, ..., ..., n, n is an arbitrary integer greater than 2, ω′ is the set reference microstructure value, ω y is the reference microstructure value of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation, θ′ is the set reference micromechanical value, θ y is the micromechanical value of the corresponding substrate surface of the aluminum alloy aircraft under the yth paint removal operation. m1 and m2 are the weight factors of the microstructure value and the micromechanical value, respectively. 0<m1<1, 0<m2<1.

8. The comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin according to claim 1, characterized in that: The specific analysis process for judging the comprehensive effect of skin paint removal on the corresponding substrate surface of an aluminum alloy aircraft is as follows: The macro-evaluation coefficient and micro-evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft are input into the aluminum alloy aircraft paint removal effect evaluation model. If the output value of the comprehensive paint removal effect coefficient of the corresponding substrate surface of the aluminum alloy aircraft is 1, it is determined that the comprehensive effect of the skin paint removal of the corresponding substrate surface of the aluminum alloy aircraft is unqualified, and the method of improving the skin paint removal of the corresponding substrate surface of the aluminum alloy aircraft is implemented. If the output value of the comprehensive paint removal effect coefficient of the corresponding substrate surface of the aluminum alloy aircraft is 0, it is determined that the comprehensive effect of the skin paint removal of the corresponding substrate surface of the aluminum alloy aircraft is qualified, thereby judging the comprehensive effect of the skin paint removal of the corresponding substrate surface of the aluminum alloy aircraft.

9. The comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin according to claim 1, characterized in that: The output obtains the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft. The specific output process is as follows: By calculating the formula The output is the comprehensive effect result ZH of the skin paint removal of the corresponding substrate surface of the aluminum alloy aircraft, GK is the macro-evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft, WJ is the micro-evaluation coefficient of the corresponding substrate surface of the aluminum alloy aircraft, XS is the set reference skin paint removal effect coefficient, L1 and L2 are the weight factors of the set macro-evaluation coefficient and the weight factors of the micro-evaluation coefficient, respectively, 0<L1<1, 0<L2<1.

10. The comprehensive evaluation method for paint removal effect of aluminum alloy aircraft skin according to claim 1, characterized in that: The above analysis results in an improved method for skin paint removal on the corresponding substrate surface of aluminum alloy aircraft. The specific analysis process is as follows: When the macro-evaluation coefficient is unqualified in the comprehensive effect of skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft, macro-paint removal improvements are performed on the skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft, and the paint removal equipment is replaced for the corresponding skin paint removal of the aluminum alloy aircraft or the surface of the aluminum alloy aircraft is pretreated before paint removal. At the same time, micro-paint removal improvements are also performed on the skin paint removal on the corresponding substrate surface of the aluminum alloy aircraft, and the paint remover is replaced for the corresponding skin paint removal of the aluminum alloy aircraft or the paint removal method is changed.

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