Quantitative evaluation method for composite material patching and cementing maintenance surface water film test

Abstract

The invention discloses a quantitative evaluation method for a composite material patching and cementing maintenance surface water film test, and relates to the technical field of maintenance surface water films, and the quantitative evaluation method comprises the steps of 1, test preparation, 2, contact angle measurement and 3, maintenance surface evaluation. In the first step of test preparation, the defects of scratches, hole pitches and eroded damaged surfaces of the surfaces of the metal components of the airplane are found in time, then corresponding matched patches can be screened in time, the surface repairing problem of the airplane is solved, the service life of the airplane is prolonged, and the operation risk and maintenance cost of the airplane are reduced. In the step 2, in contact angle measurement, the number of broken water films is reduced, the cleanliness of the surface of the patch is improved, the problem that the adhesion force is reduced is solved, then the quality and reliability of the repaired composite material component are improved, the safety risk caused by inaccurate cleanliness is reduced, and the safety of an aircraft structure is improved.

Description

Technical Field

[0001] The invention relates to the technical field of surface water film repair, and in particular to a quantitative evaluation method for a surface water film test of a composite material repaired by patching and bonding. Background Art

[0002] Composite materials have been widely used in many fields such as aerospace, automobiles, and ships due to their excellent properties such as high strength, low density, and good corrosion resistance. However, during the use of composite components, they will inevitably suffer various damages, such as impact damage, delamination, scratches, etc. Patching and adhesive repair has emerged as a common and effective composite damage repair technology. It can restore the mechanical properties of damaged components to a certain extent and extend their service life. As an effective means of evaluating surface properties, the water film test has long attracted much attention in the field of composite material repair. Therefore, it is necessary to analyze the quantitative evaluation method of the water film test on the surface of composite material patching and adhesive repair.

[0003] Existing technology, such as the invention patent application with publication number CN111998794B, discloses a method for measuring and evaluating the surface topography of composite repair adhesive bonds on general aviation aircraft. The method comprises preparing a reference surface and a bonding surface to be evaluated for aircraft composite structural repair adhesive bonds; selecting a small area based on the reference surface and the bonding surface to be evaluated, obtaining the 3D geometric topography of the small area; constructing characteristic curves for measuring and evaluating the topography of the reference surface and the surface to be evaluated; and evaluating the geometric topography of the bonding surface to be evaluated. The characteristic distribution curves of the invention better reflect the detailed geometric features of the surface. By comparing the differences between the three characteristic curves of the reference bonding surface geometry and the geometric topography, the method achieves quantitative measurement and evaluation of the geometric topography of bonding surfaces with different manual polishing processes, significantly improving the control of the airworthiness maintenance process of composite structures.

[0004] Based on the above solutions, it can be found that the existing quantitative evaluation method of water film test on the surface of composite material patching and adhesive repair can meet the basic requirements, but it also has some potential defects and challenges, which are specifically reflected in the following aspects:

[0005] First, existing technologies often lack a high degree of analysis for composite material matching patches for aircraft metal components. Traditional testing methods often focus on evaluating a single performance and lack a comprehensive consideration of the aircraft's overall compatibility. These methods are unable to timely select the appropriate matching patches based on surface scratches, hole spacing, and eroded damaged surfaces of aircraft metal components. This in turn affects aircraft surface repairs, shortens aircraft service life, and increases operational risks and maintenance costs.

[0006] 2. The existing technology does not pay enough attention to the water film compliance index of each surface of the aircraft composite material matching patch. Due to the inaccurate analysis of the water film appearance index and water film rupture index of each surface of the aircraft composite material matching patch, there is a lack of attention to water film experiments, which increases the number of water film ruptures, reduces the cleanliness of the patch surface, and leads to a decrease in adhesion strength, which in turn reduces the quality and reliability of the composite material components after repair, increases the safety risks caused by inaccurate cleanliness, and affects the safety of the aircraft structure. Summary of the Invention

[0007] The purpose of the present invention is to provide a quantitative evaluation method for a water film test on a surface of a composite material repaired by patching and bonding, thereby solving the problems existing in the background technology.

[0008] To solve the above technical problems, the present invention adopts the following technical solution: The present invention provides a quantitative evaluation method for the water film test on the surface of composite material patching and adhesive repair, including step one, test preparation, step two, contact angle measurement and step three, repair surface evaluation.

[0009] Step 1. Test preparation: Use a metal analyzer to detect the damaged surfaces of the metal components of the aircraft to be repaired, obtain damage data of each surface of the aircraft's metal components, analyze the damage index of each surface of the aircraft's metal components, and then screen composite material matching patches for each damaged surface of the aircraft's metal components to obtain composite material matching patches for each damaged surface of the aircraft's metal components.

[0010] Step 2: Contact angle measurement: Based on the obtained composite material matching patches for each damaged surface of the aircraft, each area of ​​the composite material matching patch on each damaged surface is polished, and each measurement droplet is placed on each area of ​​the composite material matching patch to form each contact angle of each area of ​​the composite material matching patch on each damaged surface, and then the water film conformity index of each area of ​​the composite material matching patch of the aircraft is analyzed.

[0011] Step 3: Repair surface assessment: Based on the water film compliance index of each area of ​​the aircraft's composite material matching patch, determine whether the water film in each area of ​​the aircraft's composite material matching patch is qualified. If qualified, repair the aircraft's metal components. If unqualified, issue an early warning.

[0012] Furthermore, the damage index of each surface of the metal component of the aircraft is specifically analyzed by the following method: based on the obtained damage data of each surface of the metal component of the aircraft, wherein the damage data includes: the number of surface scratches, the hole spacing and the surface erosion damage area, the damage index of each surface of the metal component of the aircraft is analyzed, and the specific calculation formula is: θ n =q n +w n , where qn Expressed as the physical damage index of each surface of the aircraft's metal components, w n It is represented as the chemical damage index of each surface of the metal component of the aircraft, n is represented as the surface number of the metal component of the aircraft, n=1, 2, ..., o, and o is the number of surfaces.

[0013] Furthermore, the physical damage index of the surface of the metal component of the aircraft is specifically analyzed by: based on the obtained number of scratches and hole spacing on each surface of the metal component of the aircraft, and extracting the reference number of scratches and reference hole spacing on each surface of the metal component of the aircraft from the database, analyzing the physical damage index of the surface of the metal component of the aircraft, and the specific calculation formula is: Among them, x n 'Represents the reference number of scratches on the nth surface of the aircraft's metal component, x n Expressed as the number of scratches on the nth surface of the aircraft's metal components, c n ' represents the reference hole distance of the nth surface of the aircraft metal component, c n Expressed as the hole spacing on the nth surface of the aircraft's metal components.

[0014] Furthermore, the chemical damage index of each surface of the aircraft's metal components is specifically analyzed by: based on the obtained surface erosion damage area of ​​each surface of the aircraft's metal components, and extracting the surface erosion damage reference area of ​​each surface of the aircraft's metal components from the database, analyzing the chemical damage index of each surface of the aircraft's metal components, the specific calculation formula is: Among them, i n It is expressed as the surface erosion damage area of ​​the nth surface of the aircraft's metal component, i n 'It is represented as the surface erosion damage reference area of ​​the nth surface of the aircraft's metal component.

[0015] Furthermore, the screening of composite material matching patches for damaged surfaces of metal components of an aircraft is specifically analyzed by the following method: historical usage data of each composite material matching patch stored in a database, wherein the historical usage data includes damage indexes of each surface of metal components historically used on each aircraft, matching composite material matching patches corresponding to the damage indexes of each surface of the metal components of the aircraft, and thereby obtaining composite material matching patches for each damaged surface of the metal components of the aircraft.

[0016] Furthermore, the specific analysis method for the contact angles of each region of the composite material matching patch for each damaged surface is as follows: based on the obtained composite material matching patch for each damaged surface of the metal component of the aircraft, the composite material matching patch for each damaged surface of the metal component of the aircraft is placed on a horizontal measuring table, ionized water is dripped on the surface of the composite material matching patch using a micro syringe, and after a thin layer of water film is coated on the surface of the composite material matching patch, the patch is placed in the measurement area of ​​an interferometer, and the parameters of the interferometer are adjusted so that the light beam is vertically irradiated on the water film surface to form the contact angles of each region of the composite material matching patch for each damaged surface, and the water film data of each region of the composite material matching patch of the aircraft is obtained by analyzing the interference fringes of the reflected light on each contact angle, and then the water film conformity index of each region of the composite material matching patch of the aircraft is analyzed.

[0017] Furthermore, the water film conformity index of each region of the aircraft composite material matching patch is specifically analyzed by: based on the obtained water film data of each region of the aircraft composite material matching patch, wherein the water film data of each region includes: the minimum height, maximum height, humidity value, number of bubbles in the water film, and number of cracks in the water film of each region of the aircraft composite material matching patch, the water film conformity index of each region of the aircraft composite material matching patch is analyzed, and the specific calculation formula is: α f =D f +A f , where D f A is the water film appearance index of the fth region of the aircraft composite matching patch, f denoted as the water film rupture index of the fth region of the composite material matching patch of the aircraft, f denoted as the number of the region of the composite material matching patch of the aircraft, and f denoted as the number of regions.

[0018] Furthermore, the water film appearance index of each region of the aircraft composite material matching patch is specifically analyzed by the following method: based on the obtained minimum thickness, maximum thickness, and humidity value of the water film of each region of the aircraft composite material matching patch, the maximum height and minimum height of the water film of each region are subtracted to obtain the thickness of the water film of each region, and the reference thickness and reference humidity value of the water film of each region of the aircraft composite material matching patch are extracted from the database to further analyze the water film appearance index of each region of the aircraft composite material matching patch. The specific calculation formula is: Among them, b f Denote the thickness of the water film in the fth region of the aircraft composite matching patch, b f ' represents the reference thickness of the water film in the fth region of the aircraft composite matching patch, k f Denotes the humidity value of the water film in the fth region of the aircraft composite matching patch, kf ' represents the reference humidity value of the water film in the fth region of the aircraft's composite matching patch.

[0019] Furthermore, the water film rupture index of each region of the aircraft composite material matching patch is specifically analyzed by: based on the obtained number of bubbles and cracks in the water film of each region of the composite material matching patch, a reference number of bubbles and a reference number of cracks in the water film of each region are extracted from a database, and then the water film rupture index of each region of the aircraft composite material matching patch is analyzed. The specific calculation formula is: Among them, t f The number of bubbles in the water film of the fth region of the composite matching patch of the aircraft, t f ' represents the reference number of bubbles in the water film of the fth region of the aircraft composite matching patch, y f The number of cracks in the water film of the fth region of the aircraft composite patch is expressed as f f ' represents the reference number of cracks in the water film of the fth region of the aircraft composite matching patch.

[0020] Furthermore, the specific analysis method for judging whether the water film of each area of ​​the composite material matching patch of the aircraft is qualified is as follows: based on the obtained water film compliance index of each area of ​​the composite material matching patch of the aircraft, the water film compliance index of each area of ​​the composite material matching patch of the aircraft is compared with the water film compliance index safety range of each area of ​​the composite material matching patch of the aircraft stored in the database; if the water film compliance index of a certain area of ​​the composite material matching patch of the aircraft is within the water film compliance index safety range, it means that the water film of the composite material matching patch of the aircraft in this area is qualified, and the metal components of the aircraft are repaired, and the cleaning effect index of the corresponding repair surface is screened; if the water film compliance index of a certain area of ​​the composite material matching patch of the aircraft is not within the water film compliance index safety range, it means that the water film of the composite material matching patch of the aircraft in this area is unqualified, an early warning prompt is issued, and the staff is reminded to perform a secondary cleaning of the composite material matching patch and re-execute steps two and three.

[0021] The beneficial effects of the present invention are as follows: in step one, test preparation, the damaged surfaces of the metal components of the aircraft to be repaired are detected by a metal analyzer to obtain surface data of the metal components of the aircraft, the damage index of the surfaces of the metal components of the aircraft is analyzed, and then the corresponding composite materials are screened as patch materials to obtain composite material matching patches of the metal components of the aircraft, and scratches, hole spacing and eroded damaged surface defects on the surfaces of the metal components of the aircraft are discovered in time, and then the corresponding matching patches can be screened in time, thereby improving the surface repair of the aircraft, extending the service life of the aircraft, and reducing the operating risks and maintenance costs of the aircraft.

[0022] In step 2, contact angle measurement, based on the obtained composite material matching patch of the metal component of the aircraft, the surface of the composite material matching patch is polished, and each measurement liquid is dropped on the surface of the matching patch to form the contact angle of each surface of the composite material matching patch, and then the water film compliance index of each surface of the composite material matching patch of the aircraft is analyzed, which increases the importance of water film experiments, reduces the number of water film ruptures, improves the cleanliness of the patch surface, and reduces the occurrence of the problem of decreased adhesion strength, thereby improving the quality and reliability of the composite material component after maintenance, reducing the safety risks caused by inaccurate cleanliness, and improving the safety of the aircraft structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] 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.

[0024] Figure 1 The figure is a flow chart of the steps for implementing the method of the present invention. DETAILED DESCRIPTION

[0025] 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.

[0026] Reference Figure 1 As shown, the present invention provides a quantitative evaluation method for a water film test on a composite material patching and adhesive repair surface, comprising: step one, test preparation, step two, contact angle measurement, and step three, repair surface evaluation.

[0027] Step 1. Test preparation: Use a metal analyzer to detect the damaged surfaces of the metal components of the aircraft to be repaired, obtain damage data of each surface of the aircraft's metal components, analyze the damage index of each surface of the aircraft's metal components, and then screen composite material matching patches for each damaged surface of the aircraft's metal components to obtain composite material matching patches for each damaged surface of the aircraft's metal components.

[0028] It should be noted that the composite material matching patches for the damaged surfaces of the metal components of the aircraft are screened, wherein the composite material matching patches include material performance values ​​and shape matching values, and the composite material matching patches with the highest matching degree corresponding to the damaged surfaces of the metal components of the aircraft are screened as the composite material matching patches for the damaged surfaces of the metal components of the aircraft.

[0029] In the above embodiment, the damage index of each surface of the metal component of the aircraft is specifically analyzed by the following method: based on the obtained damage data of each surface of the metal component of the aircraft, wherein the damage data includes: the number of surface scratches, the hole spacing and the surface erosion damage area, the damage index of each surface of the metal component of the aircraft is analyzed, and the specific calculation formula is: θ n =q n +w n , where q n Expressed as the physical damage index of each surface of the aircraft's metal components, w n It is represented as the chemical damage index of each surface of the metal component of the aircraft, n is represented as the surface number of the metal component of the aircraft, n=1, 2, ..., o, and o is the number of surfaces.

[0030] In the above embodiment, the physical damage index of the surface of the metal component of the aircraft is specifically analyzed by: based on the obtained number of scratches and hole spacing on each surface of the metal component of the aircraft, and extracting the reference number of scratches and reference hole spacing on each surface of the metal component of the aircraft from the database, analyzing the physical damage index of the surface of the metal component of the aircraft, the specific calculation formula is: Among them, x n 'Represents the reference number of scratches on the nth surface of the aircraft's metal component, x n Expressed as the number of scratches on the nth surface of the aircraft's metal components, c n ' represents the reference hole distance of the nth surface of the aircraft metal component, c n Expressed as the hole spacing on the nth surface of the aircraft's metal components.

[0031] It should be noted that the hole spacing refers to the average hole spacing of multiple hole spacings.

[0032] In the above embodiment, the chemical damage index of each surface of the aircraft's metal components is expressed as follows: based on the obtained surface erosion damage area of ​​each surface of the aircraft's metal components, and by extracting the surface erosion damage reference area of ​​each surface of the aircraft's metal components from the database, the chemical damage index of each surface of the aircraft's metal components is analyzed. The specific calculation formula is: Among them, i n It is expressed as the surface erosion damage area of ​​the nth surface of the aircraft's metal component, i n'It is represented as the surface erosion damage reference area of ​​the nth surface of the aircraft's metal component.

[0033] In step one, test preparation, the damaged surfaces of the metal components of the aircraft to be repaired are detected by a metal analyzer to obtain surface data of the metal components of the aircraft, and the damage index of the metal components of the aircraft is analyzed. Then, the corresponding composite materials are selected as patch materials to obtain composite material matching patches of the metal components of the aircraft. The scratches, hole spacing and eroded damaged surface defects of the metal components of the aircraft are discovered in time, and the corresponding matching patches can be selected in time, which improves the surface repair of the aircraft, extends the service life of the aircraft, and reduces the operating risks and maintenance costs of the aircraft.

[0034] Step 2: Contact angle measurement: Based on the obtained composite material matching patches for each damaged surface of the aircraft, each area of ​​the composite material matching patch on each damaged surface is polished, and each measurement droplet is placed on each area of ​​the composite material matching patch to form each contact angle of each area of ​​the composite material matching patch on each damaged surface, and then the water film conformity index of each area of ​​the composite material matching patch of the aircraft is analyzed.

[0035] In the above embodiment, the specific analysis method for screening the composite material matching patches for each damaged surface of the metal components of the aircraft is as follows: historical usage data of each composite material matching patch stored in a database, wherein the historical usage data includes damage indexes of each surface of the metal components used in each aircraft, matching the composite material matching patches corresponding to the damage indexes of each surface of the metal components of the aircraft, and then obtaining the composite material matching patches for each damaged surface of the metal components of the aircraft.

[0036] In the above embodiment, the specific analysis method for the contact angles of each region of the composite material matching patch formed on each damaged surface is as follows: based on the obtained composite material matching patch of each damaged surface of the metal component of the aircraft, the composite material matching patch of each damaged surface of the metal component of the aircraft is placed on a horizontal measuring table, and ion water is dripped on the surface of the composite material matching patch using a micro syringe. After a thin layer of water film is coated on the surface of the composite material matching patch, the patch is placed in the measurement area of ​​an interferometer, and the parameters of the interferometer are adjusted so that the light beam is vertically irradiated on the water film surface to form the contact angles of each region of the composite material matching patch on each damaged surface, and the water film data of each region of the composite material matching patch of the aircraft is obtained by analyzing the interference fringes of the reflected light on each contact angle, and then the water film conformity index of each region of the composite material matching patch of the aircraft is analyzed.

[0037] In the above embodiment, the water film conformity index of each region of the aircraft composite material matching patch is specifically analyzed by: based on the obtained water film data of each region of the aircraft composite material matching patch, wherein the water film data of each region includes: the minimum height, maximum height, humidity value, number of bubbles in the water film, and number of cracks in the water film of each region of the aircraft composite material matching patch, the water film conformity index of each region of the aircraft composite material matching patch is analyzed, and the specific calculation formula is: α f =D f +A f , where D f A is the water film appearance index of the fth region of the aircraft composite matching patch, f denoted as the water film rupture index of the fth region of the composite material matching patch of the aircraft, f denoted as the number of the region of the composite material matching patch of the aircraft, and f denoted as the number of regions.

[0038] In the above embodiment, the specific analysis method for the water film appearance index of each region of the aircraft composite material matching patch is as follows: based on the obtained minimum thickness, maximum thickness, and humidity value of the water film of each region of the aircraft composite material matching patch, the maximum height and minimum height of the water film of each region are subtracted to obtain the thickness of the water film of each region, and the reference thickness and reference humidity value of the water film of each region of the aircraft composite material matching patch are extracted from the database to further analyze the water film appearance index of each region of the aircraft composite material matching patch. The specific calculation formula is: Among them, b f Denote the thickness of the water film in the fth region of the aircraft composite matching patch, b f ' represents the reference thickness of the water film in the fth region of the aircraft composite matching patch, k f Denotes the humidity value of the water film in the fth region of the aircraft composite matching patch, k f ' represents the reference humidity value of the water film in the fth region of the aircraft's composite matching patch.

[0039] In the above embodiment, the specific analysis method for the water film rupture index of each region of the composite material matching patch of the aircraft is as follows: based on the obtained number of bubbles and cracks in the water film of each region of the composite material matching patch, a reference number of bubbles and a reference number of cracks in the water film of each region are extracted from a database, and then the water film rupture index of each region of the composite material matching patch of the aircraft is analyzed. The specific calculation formula is: Among them, t f The number of bubbles in the water film of the fth region of the composite matching patch of the aircraft, t f' represents the reference number of bubbles in the water film of the fth region of the aircraft composite matching patch, y f The number of cracks in the water film of the fth region of the aircraft composite patch is expressed as f f ' represents the reference number of cracks in the water film of the fth region of the aircraft composite matching patch.

[0040] In step 2, contact angle measurement, based on the obtained composite material matching patch of the metal component of the aircraft, the surface of the composite material matching patch is polished, and each measurement liquid is dropped on the surface of the matching patch to form the contact angle of each surface of the composite material matching patch, and then the water film compliance index of each surface of the composite material matching patch of the aircraft is analyzed, which increases the importance of water film experiments, reduces the number of water film ruptures, improves the cleanliness of the patch surface, and reduces the occurrence of the problem of decreased adhesion strength, thereby improving the quality and reliability of the composite material component after maintenance, reducing the safety risks caused by inaccurate cleanliness, and improving the safety of the aircraft structure.

[0041] Step 3: Repair surface assessment: Based on the water film compliance index of each area of ​​the aircraft's composite material matching patch, determine whether the water film in each area of ​​the aircraft's composite material matching patch is qualified. If qualified, repair the aircraft's metal components. If unqualified, issue an early warning.

[0042] In the above embodiment, the specific analysis method for judging whether the water film of each area of ​​the composite material matching patch of the aircraft is qualified is as follows: based on the obtained water film compliance index of each area of ​​the composite material matching patch of the aircraft, the water film compliance index of each area of ​​the composite material matching patch of the aircraft is compared with the water film compliance index safety range of each area of ​​the composite material matching patch of the aircraft stored in the database; if the water film compliance index of a certain area of ​​the composite material matching patch of the aircraft is within the water film compliance index safety range, it means that the water film of the composite material matching patch of the aircraft in this area is qualified, and the metal components of the aircraft are repaired, and the cleaning effect index of the corresponding repair surface is screened; if the water film compliance index of a certain area of ​​the composite material matching patch of the aircraft is not within the water film compliance index safety range, it means that the water film of the composite material matching patch of the aircraft in this area is unqualified, an early warning prompt is issued, and the staff is reminded to perform a secondary cleaning of the composite material matching patch and re-execute steps two and three.

[0043] It should be noted that when conducting a water film test, the results of the water film test can provide guidance for cleaning work. For example, if the water film test reveals that the water film thickness in a certain area of ​​the surface is abnormal or the contact angle does not meet the requirements, this area can be cleaned again in a targeted manner. The cleaned surface is then subjected to a water film test, and further cleaning is performed based on the test results. This process is repeated until the water film test results meet the requirements, ensuring that the aircraft repair surface reaches the ideal state. For example, for surfaces repaired by composite patching and bonding, good cleaning and accurate water film testing can ensure the quality of the bonding, because a clean surface allows the adhesive to better bond with the base material, and the water film test can verify whether the surface meets the bonding conditions.

[0044] The above contents are merely examples and explanations 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 by the present invention, they should all fall within the scope of protection of the present invention.

Claims

1. A quantitative evaluation method for the water film test on the surface of composite material patching and adhesive repair, characterized by: include: Step 1: Test preparation: Using a metal analyzer, inspect each damaged surface of the aircraft's metal component to be repaired to obtain damage data for each surface of the aircraft's metal component, analyze the damage index of each surface of the aircraft's metal component, and then select composite material matching patches for each damaged surface of the aircraft's metal component to obtain composite material matching patches for each damaged surface of the aircraft's metal component; Step 2: Contact angle measurement: Based on the obtained composite material matching patches for each damaged surface of the aircraft, each area of ​​the composite material matching patch on each damaged surface is polished, and each measurement liquid droplet is placed on each area of ​​the composite material matching patch to form each contact angle of each area of ​​the composite material matching patch on each damaged surface, and then the water film conformity index of each area of ​​the composite material matching patch of the aircraft is analyzed; Step 3: Repair surface assessment: Based on the water film compliance index of each area of ​​the aircraft's composite material matching patch, determine whether the water film in each area of ​​the aircraft's composite material matching patch is qualified. If qualified, repair the aircraft's metal components. If unqualified, issue an early warning.

2. The quantitative evaluation method for the water film test on the surface of composite material patching and adhesive repair according to claim 1 is characterized in that: The specific analysis method for the damage index of each surface of the metal component of the aircraft is as follows: Based on the damage data of each surface of the aircraft's metal components, including the number of surface scratches, hole spacing, and surface erosion damage area, the damage index of each surface of the aircraft's metal components is analyzed. The specific calculation formula is: θ n =q n +w n , where q n Expressed as the physical damage index of each surface of the aircraft's metal components, w n It is represented as the chemical damage index of each surface of the metal component of the aircraft, n is represented as the surface number of the metal component of the aircraft, n=1, 2, ..., o, and o is the number of surfaces.

3. The quantitative evaluation method for the water film test on the surface of composite material patching and adhesive repair according to claim 2 is characterized in that: The physical damage index of the surface of the metal component of the aircraft is specifically analyzed by the following method: Based on the obtained number of scratches and hole spacing on each surface of the aircraft's metal components, and extracting the reference number of scratches and reference hole spacing on each surface of the aircraft's metal components from the database, the physical damage index of the surface of the aircraft's metal components is analyzed. The specific calculation formula is: Among them, x n 'Represented as the reference number of scratches on the nth surface of the metal component of the aircraft, x n Expressed as the number of scratches on the nth surface of the aircraft's metal components, c n ' represents the reference hole distance of the nth surface of the aircraft metal component, c n Expressed as the hole spacing on the nth surface of the aircraft's metal components.

4. The quantitative evaluation method for water film test on composite material patching and adhesive repair surface according to claim 2, characterized in that: The chemical damage index of each surface of the metal components of the aircraft is expressed as follows: Based on the obtained surface erosion damage area of ​​each surface of the aircraft's metal components and the surface erosion damage reference area of ​​each surface of the aircraft's metal components extracted from the database, the chemical damage index of each surface of the aircraft's metal components is analyzed. The specific calculation formula is: Among them, i n It is expressed as the surface erosion damage area of ​​the nth surface of the aircraft's metal component, i n 'It is expressed as the surface erosion damage reference area of ​​the nth surface of the aircraft's metal component.

5. The quantitative evaluation method for water film test on composite material patching and adhesive repair surface according to claim 1, characterized in that: The specific analysis method for screening composite material matching patches for damaged surfaces of metal components of aircraft is as follows: The database stores historical usage data of each composite material matching patch, where the historical usage data includes the surface damage index of each metal component used in each aircraft, and the composite material matching patch corresponding to the surface damage index of the metal component of the matching aircraft, thereby obtaining the composite material matching patch for each damaged surface of the metal component of the aircraft.

6. The quantitative evaluation method for water film test on composite material patching and adhesive repair surface according to claim 5, characterized in that: The specific analysis method for the contact angles of each region of the composite material matching patch forming each damaged surface is as follows: Based on the obtained composite material matching patches of each damaged surface of the metal components of the aircraft, the composite material matching patches of each damaged surface of the metal components of the aircraft are placed on a horizontal measuring table, and ion water is dripped on the surface of the composite material matching patch using a micro syringe. After the surface of the composite material matching patch is coated with a thin layer of water film, it is placed in the measurement area of ​​the interferometer, and the parameters of the interferometer are adjusted so that the light beam is vertically irradiated on the water film surface to form contact angles of each area of ​​the composite material matching patch on each damaged surface, and the water film data of each area of ​​the composite material matching patch of the aircraft is obtained by analyzing the interference fringes of the reflected light on each contact angle, and then the water film compliance index of each area of ​​the composite material matching patch of the aircraft is analyzed.

7. The quantitative evaluation method for water film test on composite material patching and adhesive repair surface according to claim 6, characterized in that: The specific analysis method of the water film compliance index of each area of ​​the composite material matching patch of the aircraft is as follows: Based on the water film data of each region of the aircraft composite material matching patch obtained, wherein the water film data of each region includes: the minimum height, maximum height, humidity value, number of bubbles in the water film, and number of cracks in the water film of each region of the aircraft composite material matching patch, the water film compliance index of each region of the aircraft composite material matching patch is analyzed, and the specific calculation formula is: α f =D f +A f , where D f A is the water film appearance index of the fth region of the aircraft composite matching patch, f denoted as the water film rupture index of the fth region of the composite material matching patch of the aircraft, f denoted as the number of the region of the composite material matching patch of the aircraft, and f denoted as the number of regions.

8. The quantitative evaluation method for water film test on composite material surface repair by patching and adhesive bonding according to claim 7, characterized in that: The specific analysis method of the water film appearance index of each area of ​​the composite material matching patch of the aircraft is as follows: Based on the minimum thickness, maximum thickness and humidity of the water film in each area of ​​the aircraft's composite material matching patch, the maximum height and minimum height of the water film in each area are subtracted to obtain the thickness of the water film in each area. The reference thickness and reference humidity of the water film in each area of ​​the aircraft's composite material matching patch are extracted from the database, and the water film appearance index of each area of ​​the aircraft's composite material matching patch is analyzed. The specific calculation formula is: Among them, b f Denote the thickness of the water film in the fth region of the aircraft composite matching patch, b f ' represents the reference thickness of the water film in the fth region of the aircraft composite matching patch, k f Denotes the humidity value of the water film in the fth region of the aircraft composite matching patch, k f ' represents the reference humidity value of the water film in the fth region of the aircraft's composite matching patch.

9. The quantitative evaluation method for water film test on composite material patching and adhesive repair surface according to claim 7, characterized in that: The specific analysis method of the water film rupture index of each area of ​​the composite material matching patch of the aircraft is as follows: Based on the obtained number of bubbles and cracks in the water film of each area of ​​the composite material matching patch, the reference number of bubbles and cracks in the water film of each area are extracted from the database, and then the water film rupture index of each area of ​​the composite material matching patch of the aircraft is analyzed. The specific calculation formula is: Among them, t f The number of bubbles in the water film of the fth region of the composite matching patch of the aircraft, t f ' represents the reference number of bubbles in the water film of the fth region of the aircraft composite matching patch, y f The number of cracks in the water film of the fth region of the aircraft composite patch is expressed as f f ' represents the reference number of cracks in the water film of the fth region of the aircraft composite matching patch.

10. The quantitative evaluation method for water film test on composite material patching and adhesive repair surface according to claim 1, characterized in that: The specific analysis method for judging whether the water film in each area of ​​the aircraft composite material matching patch is qualified is as follows: Based on the obtained water film compliance index of each area of ​​the composite material matching patch of the aircraft, the water film compliance index of each area of ​​the composite material matching patch of the aircraft is compared with the water film compliance index safety range of each area of ​​the composite material matching patch of the aircraft stored in the database. If the water film compliance index of a certain area of ​​the composite material matching patch of the aircraft is within the water film compliance index safety range, it means that the water film of the composite material matching patch of the aircraft in this area is qualified, and the metal components of the aircraft are repaired, and the cleaning effect index of the corresponding repair surface is screened. If the water film compliance index of a certain area of ​​the composite material matching patch of the aircraft is not within the water film compliance index safety range, it means that the water film of the composite material matching patch of the aircraft in this area is unqualified, and an early warning prompt is issued, and the staff is reminded to perform a secondary cleaning of the composite material matching patch and re-execute steps two and three.

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