Method for repairing cracks of aviation structural part

Abstract

The invention discloses an aviation structural part crack repairing method which comprises the steps that a to-be-repaired structure of an aviation structural part is determined, and a crack is located in the to-be-repaired structure; determining a structural strength loss state caused by the crack; determining process parameters of the repair process according to the structural strength capable of being recovered by the repair process; a reinforcing plate with the same outline as the to-be-repaired structure is manufactured; performing a repair process on the reinforcing plate based on the process parameters; and the reinforcing plate is installed on the to-be-repaired structure. By means of the repairing method, crack damage generated in the operation process of the aviation structural part can be effectively repaired, the maintenance cost of the aviation structural part is effectively reduced, and the maintenance cost is reduced to 30% of the replacement cost. And long-term waiting for purchasing new parts from foreign countries is avoided, the maintenance period of the aviation structural parts is shortened and is reduced to 30%-50% of the replacement period, and the maintenance efficiency of the aviation structural parts is remarkably improved.

Description

Technical Field

[0001] The present application relates to the technical field of aviation device repair, and in particular to a method for repairing cracks in aviation structural parts. Background Art

[0002] Aviation structural components are prone to cracking and other damage due to the loads they bear. For example, sliding doors are a key component of civil aircraft engine nacelles, serving as a protective shield for the engine core and guiding the propulsion airflow. The lower longitudinal beam is a crucial load-bearing structure for the sliding door, connecting the inner and outer cylinders. Due to the high stresses it bears, it is highly susceptible to cracking and other damage.

[0003] In the prior art, cracks in aircraft structural components are repaired by replacing the entire lower longitudinal beam with a new part. Currently, most domestic transport aircraft are manufactured overseas. The high pricing of new parts, coupled with additional transportation and tariff costs, significantly increases repair costs. Furthermore, the transportation of new parts from abroad, coupled with customs clearance delays, prolongs the entire sliding door repair cycle, resulting in a longer repair cycle, which is not conducive to market-based economic maintenance, increases the repair cycle, and reduces maintenance efficiency. Summary of the Invention

[0004] This application aims to solve at least one of the technical problems existing in the prior art or related art.

[0005] The technical solution of the present application proposes a method for repairing cracks in aviation structural parts, which includes: determining a structure of the aviation structural part to be repaired, where the crack is located in the structure to be repaired; determining a state of structural strength loss caused by the crack; determining process parameters of the repair process based on the structural strength that can be restored by the repair process; making a reinforcement plate with the same contour as the structure to be repaired; performing a repair process on the reinforcement plate based on the process parameters; and installing the reinforcement plate on the structure to be repaired.

[0006] In some technical solutions provided in this application, the steps of making a reinforcing plate with the same contour as the structure to be repaired specifically include: making the reinforcing plate using a metal plate; bending the reinforcing plate according to the shape of the structure to be repaired; and inspecting the reinforcing plate to ensure that the reinforcing plate has no cracks.

[0007] In some technical solutions provided in the present application, the step of performing a repair process on the reinforcement plate based on process parameters specifically includes: performing solution heat treatment and aging treatment on the reinforcement plate.

[0008] In some technical solutions provided in the present application, after the steps of performing solution heat treatment and aging treatment on the reinforcing plate, the further step includes: repairing the deformation of the reinforcing plate so that the shape of the reinforcing plate matches the shape of the structure to be repaired.

[0009] In some technical solutions provided in the present application, the steps of performing a repair process on the reinforcing plate based on process parameters specifically include: performing PAA phosphoric acid anodizing treatment on the reinforcing plate and performing Boegel surface treatment on the structure to be repaired; and applying an adhesive film on the mating surfaces of the reinforcing plate and / or the structure to be repaired during the bonding time.

[0010] Some technical solutions provided herein include, before fabricating a reinforcement plate with the same contour as the structure to be repaired, removing cracks from the structure to be repaired. This step specifically includes: machining a stop hole at the end of the crack; milling the crack along its extension direction to form a milling groove, with the end of the milling groove connected to the stop hole; and removing burrs and sharp edges from the stop hole and the milling groove.

[0011] In some technical solutions provided in the present application, the steps of performing a repair process on the reinforcement plate based on process parameters specifically include: filling the crack-stop holes and milling grooves through a supporting adhesive film.

[0012] In some technical solutions provided in the present application, the reinforcing plate and the structure to be repaired are respectively provided with a first mounting hole and a second mounting hole. The step of installing the reinforcing plate on the structure to be repaired specifically includes: fitting the reinforcing plate to the structure to be repaired so that the first mounting hole and the second mounting hole are opposite to each other; and passing the fastener through the first mounting hole and the second mounting hole.

[0013] In some technical solutions provided in the present application, after determining the process parameters of the repair process based on the structural strength that can be restored by the repair process, it also includes: making a test piece made of the same material as the reinforcing plate; executing the process steps on the test piece; and performing a mechanical property test on the test piece.

[0014] In some technical solutions provided in the present application, the step of performing a mechanical property test on a test piece specifically includes: performing a tensile test on the test piece under a room temperature test state and a high temperature test state, respectively.

[0015] Compared with the related art, the present invention has at least the following beneficial effects:

[0016] The repair method of the present invention can effectively repair crack damage incurred during the operation of aviation structural parts. After calculation and analysis, maintenance personnel perform a repair process on the reinforcement plate, so that the structural strength of the aviation structural part after the reinforcement plate repair is equal to or higher than the original structural strength. This repair method can be applied to crack damage in aviation structural parts with complex shapes and different locations, and has a wide range of applicability. In addition, it effectively reduces the maintenance cost of aviation structural parts, reducing the maintenance cost to 30% of the replacement cost. It avoids the long wait for purchasing new parts from abroad, shortens the maintenance cycle of aviation structural parts, and reduces the maintenance cycle to 30% to 50% of the replacement cycle, significantly improving the maintenance efficiency of aviation structural parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of some embodiments below. The accompanying drawings are for illustration purposes only and are not to be considered as limiting the present application. The same reference numerals are used throughout the accompanying drawings to denote the same components. In the accompanying drawings:

[0018] Figure 1 A schematic flow chart of a method for repairing cracks in aviation structural parts according to an embodiment of the present application;

[0019] Figure 2 This is a schematic diagram of an aviation structural component before repair according to an embodiment of the present application;

[0020] Figure 3 A schematic diagram of an aviation structural component after repair according to an embodiment of the present application;

[0021] Figure 4 A front view of a test piece according to an embodiment of the present application;

[0022] Figure 5 A schematic structural diagram of a test piece according to an embodiment of the present application;

[0023] Figure 6 This is a process flow chart of a method for repairing cracks in aviation structural parts according to an embodiment of the present application.

[0024] in, Figures 2 to 5 The corresponding relationship between the reference numerals and component names is as follows:

[0025] 100. Aviation structural parts; 110. Structure to be repaired; 200. Reinforcement plates; 300. Fasteners; 400. Test pieces. DETAILED DESCRIPTION

[0026] In order to better understand the above technical solution, the technical solution of the embodiment of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiment of the present application and the specific features in the embodiment are detailed descriptions of the technical solution of the embodiment of the present application, rather than limitations on the technical solution of the present application. In the absence of conflict, the embodiment of the present application and the technical features in the embodiment can be combined with each other.

[0027] The embodiment of the present application provides a method for repairing cracks in aviation structural parts, such as Figure 1 、 Figure 2 and Figure 3 As shown, the method for repairing cracks in the aviation structural component includes:

[0028] Step 101, determining a structure to be repaired of an aviation structural component, wherein the crack is located in the structure to be repaired;

[0029] Step 102, determining the structural strength loss state caused by the crack;

[0030] Step 103, determining the process parameters of the repair process according to the structural strength that can be restored by the repair process;

[0031] Step 105 , making a reinforcement plate having the same profile as the structure to be repaired;

[0032] Step 106 , performing a repair process on the reinforcement plate based on the process parameters;

[0033] Step 107: Install the reinforcement plate on the structure to be repaired.

[0034] In this embodiment, the aviation structure 100 may be the lower longitudinal beam of a sliding door. A crack is formed on the aviation structure 100. Maintenance personnel determine the area to be repaired of the aviation structure based on the location of the crack, and determine a specified distance range around the crack as the area to be repaired. The aviation structure within the area to be repaired is the structure 110 to be repaired.

[0035] Maintenance personnel control the computing device to calculate the amount of structural strength loss caused by crack damage based on the material, crack location, and crack size of the aircraft structural component, thereby determining the structural strength loss status of the aircraft structural component. Any process parameter of the repair process corresponds to the structural strength that can be restored. Maintenance personnel control the computing device to analyze the structural strength that can be restored by the repair material under the repair process, ensuring that the total structural strength that can be restored by all repair processes is greater than the amount of structural strength loss, thereby determining the process parameters of the repair process. The process parameters include the time and temperature involved in the repair process. The process parameters of the repair process are set through multiple strength calculations and fatigue assessments. Theoretical calculation analysis is used to ensure the recovery effect of structural strength. Through theoretical calculation analysis of the repair plan, the degree of damage and the recovery strength are quantified to ensure that the repair process can compensate for the structural strength loss and restore the original structural strength.

[0036] For example, the structural strength loss state can be divided into a high loss state, a medium loss state, and a low loss state based on the amount of structural strength loss, and the structural strength that can be restored by the process parameters can be divided into low structural strength, medium structural strength, and high structural strength. When the structural strength loss state is a high loss state, the repair process uses the process parameters corresponding to the high structural strength; when the structural strength loss state is a low loss state, the repair process uses the process parameters corresponding to the low structural strength.

[0037] Maintenance personnel use repair materials to fabricate a reinforcement plate 200 with the same contour as the structure to be repaired, ensuring that the boundaries of the reinforcement plate 200 and the structure to be repaired 110 coincide. Maintenance personnel then perform a repair process on the reinforcement plate based on process parameters, ensuring that the repaired reinforcement plate can compensate for the missing structural strength. Maintenance personnel then securely install the processed reinforcement plate to the structure to be repaired, ensuring that the reinforcement plate covers the structure. The reinforcement plate installed on the aviation structure can restore the original structural shape of the structure to be repaired. After repair, the aviation structure can continue to undergo maintenance such as inspection, cleaning, and repair in accordance with the aircraft maintenance manual, without affecting the use of the original continuing airworthiness documents.

[0038] The repair method of the present invention can effectively repair crack damage incurred during the operation of aviation structural parts. After calculation and analysis, maintenance personnel perform a repair process on the reinforcement plate, so that the structural strength of the aviation structural part after the reinforcement plate repair is equal to or higher than the original structural strength. This repair method can be applied to crack damage in aviation structural parts with complex shapes and different locations, and has a wide range of applicability. In addition, it effectively reduces the maintenance cost of aviation structural parts, reducing the maintenance cost to 30% of the replacement cost. It avoids the long wait for purchasing new parts from abroad, shortens the maintenance cycle of aviation structural parts, and reduces the maintenance cycle to 30% to 50% of the replacement cycle, significantly improving the maintenance efficiency of aviation structural parts.

[0039] In some embodiments provided herein, step 105 of manufacturing a reinforcement plate having the same profile as the structure to be repaired specifically includes:

[0040] Step 1051, using a metal plate to make a reinforcement plate;

[0041] Step 1052 , bending the reinforcement plate according to the shape of the structure to be repaired;

[0042] Step 1053 , inspect the reinforcement plate to ensure that there are no cracks in the reinforcement plate.

[0043] In this embodiment, a specific method for making a reinforcement plate is provided. The reinforcement plate is made of a metal plate, and the material of the metal plate includes a metal material or a chemical material that meets international civil aviation maintenance standards, thereby ensuring the reliability of the maintenance material. The material of the metal plate is the same as or similar to the material of the aviation structural component, so that the structural strength of the reinforcement is more likely to reach the original structural strength. For example, the metal plate can be an aluminum plate, and the aluminum plate can be a bare aluminum plate of model AL2024. The material of the metal plate is an industry standard material, which makes the maintenance material have the advantages of low price, large inventory, and fast delivery.

[0044] As you can understand, aviation structural components often have curved structures. The reinforcement plate is bent and formed using the contours of the structure to be repaired as a template to ensure it conforms to the structure. Detailed visual inspection and fluorescent penetrant inspection are used to ensure the reinforcement plate is free of cracks, prevent structural defects, and ensure its structural strength.

[0045] In some embodiments provided herein, step 106 of performing a repair process on the reinforcement plate based on the process parameters specifically includes:

[0046] Step 1061 , performing solution heat treatment and aging treatment on the reinforcement plate.

[0047] In this embodiment, specific steps of the repair process are provided. The maintenance personnel perform heat treatment operations on the reinforcement plate. Specifically, the maintenance personnel use solution heat treatment and aging treatment on the reinforcement plate according to the mechanical properties of the metal plate. Solution treatment refers to a heat treatment process in which the reinforcement plate is heated to a high-temperature single-phase region and maintained at a constant temperature so that the excess phase is fully dissolved into the solid solution and then rapidly cooled to obtain a supersaturated solid solution. Aging treatment refers to treating a material or object in a specific way within a certain period of time to improve its performance. Aging treatment includes natural aging and artificial aging. Natural aging is to place the reinforcement plate in a natural environment such as outdoors for a long time so that the residual stress inside the reinforcement plate is gradually released. Artificial aging is to accelerate the elimination of residual stress inside the reinforcement plate through heating, cooling and other process means. The heat treatment operation can improve the strength, hardness and toughness of the reinforcement plate, improve the mechanical properties of the reinforcement plate, reduce the risk of deformation and cracking, ensure the dimensional accuracy and stability of the reinforcement plate, and improve the quality and service life of the reinforcement plate.

[0048] In some embodiments provided herein, after step 1061 of performing solution heat treatment and aging treatment on the reinforcement plate, the method further includes:

[0049] Step 1062 , repairing the deformation of the reinforcing plate so that the shape of the reinforcing plate matches the shape of the structure to be repaired.

[0050] In this embodiment, a subsequent operation after heat treatment is provided. The reinforcement plate is prone to slight deformation after heat treatment. Maintenance personnel fine-tune the slight deformation of the reinforcement plate to make it conform to the contour of the structure to be repaired. This ensures that the reinforcement plate fits more closely with the structure to be repaired during subsequent installation operations, ensuring the installation effect of the reinforcement plate.

[0051] In some embodiments provided herein, step 106 of performing a repair process on the reinforcement plate based on the process parameters specifically includes:

[0052] Step 1063 , performing PAA phosphoric acid anodizing treatment on the reinforcing plate and performing Boegel surface treatment on the structure to be repaired;

[0053] Step 1064 , during the bonding time, apply adhesive film to the mating surfaces of the reinforcement plate and / or the structure to be repaired.

[0054] In this embodiment, specific steps of the repair process are provided. After step 1062, the maintenance personnel perform surface treatment on the reinforcing plate and the structure to be repaired. Specifically, the maintenance personnel perform PAA (Phosphoric Acid Anodizing) phosphoric acid anodizing treatment on the reinforcing plate, and perform Boegel surface treatment on the mating surface of the structure to be repaired. It should be noted that phosphoric acid anodizing is a technology that uses phosphoric acid as an electrolyte to generate an oxide film on the surface of aluminum and aluminum alloys through an electrochemical method. The oxide film formed by phosphoric acid anodizing has a porous structure with uniform pore size and thin wall, and the average pore size is about 15 nanometers to 25 nanometers, which significantly improves the adhesion and mechanical anchoring effect of the adhesive film in the subsequent bonding operation of the reinforcing plate. For example, the adhesion of the reinforcing plate can reach level 0 (no falling off).

[0055] Boegel's surface treatment technology, based on micro-arc oxidation, creates a dense ceramic oxide layer on the surface of the repaired structure through an electrochemical process. Applying a high voltage to the electrolyte creates micro-arc discharges on the surface of the repaired structure, forming a ceramic coating that is metallurgically bonded to the substrate. This coating combines high hardness with corrosion resistance, enhancing the surface's resistance to wear, corrosion, and fatigue, and improving the peel strength and corrosion resistance of the repaired area. Furthermore, it strengthens the bond between the adhesive film and the repaired structure during subsequent bonding operations.

[0056] Maintenance personnel apply adhesive film within the bonding time range. The adhesive film has an anti-corrosion and adhesion-promoting effect on the reinforcing plate and the structure to be repaired, thereby improving the reliability of the connection between the reinforcing plate and the structure to be repaired and ensuring the durability and reliability of the repaired structure.

[0057] In some embodiments provided in the present application, before the step 105 of making a reinforcing plate with the same profile as the structure to be repaired, the method further includes:

[0058] Step 104, removing cracks from the structure to be repaired;

[0059] Step 104 of removing cracks from the structure to be repaired specifically includes:

[0060] Step 1041, processing a stop hole at the end of the crack;

[0061] Step 1042: milling the crack along the crack extension direction to form a milling groove, and connecting the end of the milling groove to the crack stop hole;

[0062] Step 1043, removing burrs and sharp edges of the crack stop holes and milling grooves.

[0063] In this embodiment, specific steps for removing crack damage are provided. Maintenance personnel use processing machinery to remove crack damage from the structure to be repaired. The maintenance personnel machine a crack stop hole at the end of the crack, where the hole diameter is larger than the crack width. A milling groove is then machined along the extension direction of the crack, where the length of the milling groove is greater than or equal to the length of the crack, to remove existing damage and prevent further crack expansion. Maintenance personnel remove burrs and sharp edges at the crack hole and milling groove cut locations, and conduct a detailed visual inspection of the crack hole and milling groove cut locations to confirm that there are no cracks at the cut locations. While removing the crack damage, the outline of the structure to be repaired is ensured to be intact, avoiding damage to the outline of the structure to be repaired.

[0064] In some embodiments provided herein, step 106 of performing a repair process on the reinforcement plate based on the process parameters specifically includes:

[0065] Step 1065 , filling the crack-stop holes and the milling grooves with the support film.

[0066] This embodiment provides specific steps for the repair process. After step 1064, maintenance personnel perform a thermal adhesive repair, using a support film to fill the crack arrest holes and milled grooves. For example, the support film can be made of the same material as the adhesive film, such as a cabin film adhesive or resin. The support film improves the adhesive strength at the damaged location, enhancing the repair's durability.

[0067] After the reinforcement plate is installed, the supporting film is cured at a preset temperature and for a preset time. After the curing is completed, the maintenance personnel remove the excess adhesive film and confirm the reliability of the bonding through visual inspection and tapping inspection.

[0068] In some embodiments provided in this application, Figure 3 As shown, the reinforcing plate and the structure to be repaired are respectively provided with a first mounting hole and a second mounting hole. Step 107 of mounting the reinforcing plate on the structure to be repaired specifically includes:

[0069] Step 1071 , attaching the reinforcement plate to the structure to be repaired so that the first mounting hole and the second mounting hole face each other;

[0070] Step 1072 , insert the fastener through the first mounting hole and the second mounting hole.

[0071] This embodiment provides a method for installing a reinforcement plate. In step 1051 of fabricating the reinforcement plate, maintenance personnel machine a first mounting hole in the reinforcement plate and a second mounting hole at a corresponding location on the structure to be repaired. After the reinforcement plate covers the area to be repaired, with the first mounting hole facing the second mounting hole, maintenance personnel insert a fastener 300 through the first and second mounting holes. For example, the fastener can be a pin. The fastener can meet the connection strength requirements of the repair structure, and the reinforcement plate is attached to the structure to be repaired through the fastener. This ensures the durability and reliability of the repaired structure, improving its service safety.

[0072] Step 107 also includes: bonding the reinforcement plate to the structure to be repaired by means of an adhesive film, so that the fastener connection method can be combined with the adhesive connection method to achieve a double connection method, further improving the reliability of the reinforcement plate installation.

[0073] In some embodiments provided in this application, Figure 4 and Figure 5 As shown, after step 103 of determining the process parameters of the repair process according to the structural strength that can be restored by the repair process, the following steps are further included:

[0074] Step 205: making a test piece made of the same material as the reinforcing plate;

[0075] Step 206, performing process steps on the test piece;

[0076] Step 207: Perform a mechanical property test on the test piece.

[0077] This embodiment provides a step for preparing a test piece. While performing step 105, maintenance personnel simultaneously fabricate a test piece made of the same material as the reinforcement plate. Furthermore, during step 106, the test piece is simultaneously subjected to heat treatment, surface treatment, and thermal bonding using the same process parameters and steps as the reinforcement plate, ensuring process consistency between the test piece and the reinforcement plate. Mechanical property testing is performed on the test piece to ensure the reliability of the entire repair process and verify its ability to restore the original structural strength.

[0078] Step 205 specifically includes: making an initial test board, cutting the initial test board into a plurality of test pieces, and the test pieces are rectangular in shape to facilitate processing and manufacturing of the test pieces.

[0079] In some embodiments provided herein, step 206 of performing a mechanical property test on the test piece specifically includes:

[0080] Step 2061 : Performing a tensile test on the test piece in a room temperature test state and a high temperature test state respectively.

[0081] This embodiment provides a test method for a test piece. Since the service temperatures of aviation structural components include room temperature and elevated temperatures, with elevated temperatures exceeding room temperature, maintenance personnel perform tensile tests on the test piece in both room temperature and elevated temperature conditions according to a predetermined repair process to simulate the service environment of the reinforcement plate. This results in test results that are more closely aligned with actual usage and improves the accuracy of the test operation.

[0082] In a specific embodiment, Figure 6 As shown, theoretical analysis and calculations ensure that the repair process can restore the original structural strength. Crack arrest holes are drilled and grooves are milled into the cracks. Heat treatment and forming processes are used to create reinforcement plates with complex contours. Surface treatment provides corrosion protection and adhesion support for thermal bonding repairs. The reinforcement plates are then attached to the structure to be repaired using thermal bonding with adhesive films. Mechanical property testing of test pieces ensures the reliability of the repair process. The specific process steps are as follows:

[0083] (1) Theoretical calculation and analysis: Calculate the structural strength loss caused by crack damage, analyze the structural strength that can be restored by repair materials, and determine the process parameters.

[0084] (2) Machining to remove damage: Drill crack holes and mill grooves for cracks, remove burrs and sharp edges, and conduct a detailed visual inspection of the cut area to confirm that there are no cracks.

[0085] (3) Making reinforcement plates: Use aluminum plates to make reinforcement plates, bend and shape the repair parts using the original structural outline as a template, and conduct detailed visual and fluorescent penetrant inspections to ensure that there are no cracks.

[0086] (4) Heat treatment reinforcement plate: Based on the mechanical properties of the aluminum plate, the standard heat treatment process is selected, using solution heat treatment + aging treatment to improve the mechanical properties of the repaired part. After heat treatment, the slight deformation of the repaired part is fine-tuned to make it conform to the contour of the structure to be repaired.

[0087] (5) Surface treatment of the reinforcement plate and the structure to be repaired: PAA phosphoric acid anodizing treatment is performed on the reinforcement plate, Boegel surface treatment is performed on the original structure mating surface, and bonding primer is applied within the specified time range.

[0088] (6) Thermal bonding repair: Use a support film to install the repaired part and cure it at the specified temperature and holding time. After curing, remove the excess resin and confirm the bonding reliability by visual inspection and tapping.

[0089] (7) Test piece production: simultaneous production in step (3), simultaneous heat treatment in step (4), simultaneous surface treatment in step (5), and simultaneous thermal bonding in step (6) ensures consistency with the repair process.

[0090] (8) Mechanical properties test: Considering that the service temperature of the original structure is divided into room temperature test and high temperature test, the mechanical properties test pieces are subjected to tensile test according to the prescribed test process.

[0091] In the present invention, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The term "plurality" refers to two or more, unless expressly limited otherwise. Terms such as "installed," "connected," "connected," and "fixed" should be interpreted broadly. For example, "connected" can mean a fixed connection, a detachable connection, or an integral connection; "connected" can mean a direct connection or an indirect connection through an intermediary. Those skilled in the art will understand the specific meanings of these terms in the present invention based on specific circumstances.

[0092] In the description of the present invention, it should be understood that the directions or positional relationships indicated by terms such as "up", "down", "left", "right", "front" and "back" are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or unit referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they should not be understood as limiting the present invention.

[0093] Throughout this specification, terms such as "one embodiment," "some embodiments," and "specific embodiments" mean that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0094] The above are merely some embodiments of the present invention and are not intended to limit the present invention. Those skilled in the art will readily appreciate that the present invention is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A method for repairing cracks in aviation structural parts, characterized in that: include: determining a structure to be repaired of the aviation structural component, wherein the crack is located in the structure to be repaired; determining a structural strength loss state caused by the crack; Determining process parameters of the repair process according to the structural strength that can be restored by the repair process; Making a reinforcing plate having the same profile as the structure to be repaired; performing the repair process on the reinforcement plate based on the process parameters; The reinforcement plate is installed on the structure to be repaired.

2. The method for repairing cracks in aviation structural parts according to claim 1, characterized in that: The step of making a reinforcement plate having the same profile as the structure to be repaired specifically includes: The reinforcing plate is made of a metal plate; bending the reinforcing plate according to the shape of the structure to be repaired; The reinforcement plate is inspected to ensure that the reinforcement plate has no cracks.

3. The method for repairing cracks in aviation structural parts according to claim 1, characterized in that: The step of performing the repair process on the reinforcing plate based on the process parameters specifically includes: The reinforcing plate is subjected to solution heat treatment and aging treatment.

4. The method for repairing cracks in aviation structural parts according to claim 3, characterized in that: After the steps of performing solution heat treatment and aging treatment on the reinforcing plate, the method further comprises: The deformation of the reinforcing plate is repaired so that the shape of the reinforcing plate matches the shape of the structure to be repaired.

5. The method for repairing cracks in aviation structural parts according to claim 1, characterized in that: The step of performing the repair process on the reinforcing plate based on the process parameters specifically includes: performing PAA phosphoric acid anodizing treatment on the reinforcing plate and performing Boegel surface treatment on the structure to be repaired; During the bonding time, an adhesive film is applied to the mating surfaces of the reinforcing plate and / or the structure to be repaired.

6. The method for repairing cracks in aviation structural parts according to claim 1, characterized in that: Before the step of making a reinforcing plate with the same profile as the structure to be repaired, the method further comprises: removing the cracks in the structure to be repaired; The step of removing the cracks in the structure to be repaired specifically includes: Processing a crack stop hole at the end of the crack; Milling the crack along the extension direction of the crack to form a milling groove in the crack, with the end of the milling groove connected to the crack stop hole; The burrs and sharp edges of the crack stop holes and the milling grooves are removed.

7. The method for repairing cracks in aviation structural parts according to claim 6, characterized in that: The step of performing the repair process on the reinforcing plate based on the process parameters specifically includes: The crack-stop hole and the milling groove are filled with a supporting adhesive film.

8. The method for repairing cracks in aviation structural parts according to any one of claims 1 to 7, characterized in that: The reinforcing plate and the structure to be repaired are respectively provided with a first mounting hole and a second mounting hole, and the step of mounting the reinforcing plate on the structure to be repaired specifically includes: Attach the reinforcing plate to the structure to be repaired so that the first mounting hole and the second mounting hole face each other; Pass a fastener through the first mounting hole and the second mounting hole.

9. The method for repairing cracks in aviation structural parts according to any one of claims 1 to 7, characterized in that: After the step of determining the process parameters of the repair process according to the structural strength that can be restored by the repair process, the method further includes: Making a test piece made of the same material as the reinforcing plate; performing the process steps on the test piece; The test piece is subjected to a mechanical property test.

10. The method for repairing cracks in aviation structural parts according to claim 9, characterized in that: The step of performing a mechanical property test on the test piece specifically includes: The test piece is subjected to a tensile test under room temperature and high temperature test conditions, respectively.

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