Ultrasonic impact assisted creep aging precise shape correction method and device

Abstract

The present invention provides an ultrasonic impact assisted creep aging precise correction method and device. The correction method includes the following steps: the sheet material completes creep aging treatment under the condition of using preset creep aging process parameters to obtain a preformed component; the three-dimensional surface data of the preformed component is collected and compared with the target surface data to determine the non-standard area of ​​the preformed component; the three-dimensional surface data and the target surface data both include corresponding curvature data; according to the curvature difference type of the non-standard area, ultrasonic impact is used to correct the non-standard area on the opposite side of the target correction direction of the preformed component. The above correction method uses ultrasonic impact for correction to improve the forming accuracy of the local area, introduces a large dislocation density inside the impact area, improves the local material mechanical properties, and optimizes the overall service performance of the material. The ultrasonic impact correction method can perform follow-up impact on small angle areas and complex bending areas, and the impact range is larger.

Description

Technical Field

[0001] The invention relates to the technical field of nonferrous metal creep aging forming and manufacturing, and in particular to an ultrasonic impact assisted creep aging precise shaping method and device. Background Art

[0002] The rapid upgrading of aerospace equipment, the significant increase in carrying capacity, the overall lightweight of equipment, and the reduction of production costs have brought higher challenges to the development of key bearing parts of aerospace equipment, which has also prompted the innovation of manufacturing technology for large complex curvature ribbed integral wall panels of important fuselage parts such as wings and tanks, which account for 30% of the total weight. Creep aging forming technology, as a form-integrated manufacturing technology, combines the creep and aging strengthening characteristics of aluminum alloys, improves material properties while forming components, and has the advantages of low damage, high forming accuracy, good stability and high repeatability. It is currently widely used in the field of integral manufacturing of large components.

[0003] The creep aging forming process usually places the sheet on the mold for vacuum bag sealing, applies pressure to the sheet by vacuuming, and gradually makes the sheet close to the mold surface. At the same time, further pressure is provided in the autoclave to ensure that the sheet is film-attached and provide the required heat treatment temperature. However, in the creep aging forming process of the above-mentioned large-scale complex curvature ribbed integral wall panel, there are often problems such as insufficient surface accuracy after a single creep aging forming, wavy defects or substandard accuracy in local areas, and small local creep due to complex ribbed structures, which ultimately lead to low overall component accuracy and low production efficiency.

[0004] At present, sheet metal pre-rolling and press-bending processes are widely used in engineering to try to solve such problems. For example, the Chinese patent with the authorization announcement number CN115091129B of Sichuan Aerospace Changzheng Equipment Manufacturing Co., Ltd. discloses a rolling and shaping process method for aluminum alloy wall panels. The method disclosed in the patent is to roll and shape the aluminum alloy wall panels by rolling, milling, reverse deformation rolling, and point-by-point pressurization. However, due to the size of the three-axis rolling bed equipment, it is impossible to pre-process and form large and complex components that exceed the size of the rolling equipment. At the same time, for complex high-rib wall panels, pre-rolling and forming in local areas is difficult, and it is easy to cause the component ribs to become unstable and buckle or even crack due to uneven force on the ribs during rolling forming in the grid cavity. The Chinese patent with the authorization announcement number CN105689549B of Shanghai Aerospace Precision Machinery Research Institute is named as the integrated bending and clamping die and use method for creep aging shaping process. The method disclosed in the patent is to design a set of integrated bending and clamping dies, and convert the longitudinal force of the punch stroke into horizontal extrusion force for the component after creep aging through a wedge-shaped transmission mechanism, so as to realize the mechanization of the bending process and the clamping process. However, it is also limited by the size of the equipment and cannot shape the local area of ​​larger components anytime and anywhere. At the same time, the bending shaping process usually requires multiple repeated experiments, and the shaping efficiency is low. And the production cost may increase due to inaccurate selection of process parameters.

[0005] In recent years, the laser shock forming process has gradually developed. By impacting the surface of the material with laser, the internal grains are refined and residual compressive stress is generated inside the material to achieve the effect of surface correction. Ningbo University's Chinese patent application with publication number CN116372010A discloses a method of auxiliary creep aging forming by laser shock to achieve high-precision preforming. In the patent, the local area of ​​the component is impacted by laser to achieve preforming of the component, providing a surface basis for subsequent creep aging forming. However, due to the pulse energy and frequency of the laser, the manufacturing efficiency of laser shock forming is relatively low, and due to the design of optical equipment, extremely high requirements are placed on the stability of the laser generator, which greatly increases the manufacturing cost. More importantly, since the pulsed laser cannot be transmitted through optical fiber, if the laser angle is to be changed, it can only be done through reflection, so it is inconvenient to impact and form small angles and wavy areas.

[0006] Therefore, it is urgent to propose a new process for accurately correcting the unformed areas in large and complex creep aging formed components to solve the technical problems of sheet metal surface defects and substandard bending accuracy caused by one-time creep aging forming. Summary of the invention

[0007] The main purpose of the present invention is to provide an ultrasonic impact assisted creep aging accurate shape correction method to solve the technical problems of sheet metal surface defects and substandard bending accuracy occurring in a single creep aging forming process.

[0008] To achieve the above object, the present invention provides an ultrasonic impact assisted creep aging precise shape correction method, comprising the following steps:

[0009] The sheet material completes creep aging treatment under the condition of adopting preset creep aging process parameters to obtain a preformed component.

[0010] The three-dimensional profile data of the preformed component is collected and compared with the target profile data to determine the non-standard area of ​​the preformed component with respect to curvature. The three-dimensional profile data and the target profile data both include corresponding curvature data.

[0011] According to the type of curvature difference of the non-standard area, ultrasonic impact is used to correct the non-standard area on the opposite side of the target correction direction of the preformed component until the three-dimensional surface data of the non-standard area meets the standard.

[0012] According to an embodiment of the present application, the step of determining the ultrasonic process parameters of the ultrasonic impact includes:

[0013] According to the three-dimensional structure of the impact head in ultrasonic impact and the three-dimensional structure of the modeling area in the preformed component, the three-dimensional structure of the impact head and the three-dimensional model of the component are established respectively, and the modeling area at least includes the non-standard area.

[0014] Based on the three-dimensional structure of the impact head and the three-dimensional model of the component, the Johnson-Cook model is used to perform dynamic impact finite element analysis to perform simulation and determine the ultrasonic process parameters. The Johnson-Cook model is:

[0015] ;

[0016] Wherein, A is the yield strength of the preformed component, B is the hardening modulus of the preformed component, C is the strain rate constant of the preformed component, m is the temperature softening coefficient of the preformed component, and n is the hardening index of the preformed component. T0 is the reference temperature. m is the melting point temperature of the preformed component.

[0017] According to an embodiment of the present application, the step of determining the ultrasonic process parameters by performing simulation based on the three-dimensional structure of the impact head and the three-dimensional model of the component by using the Johnson-Cook model to perform dynamic impact finite element analysis includes:

[0018] The three-dimensional structure of the impact head and the three-dimensional model of the component are imported into the simulation software.

[0019] The Johnson-Cook model is used to perform dynamic impact finite element analysis to simulate the simulation correction results of the three-dimensional model of the component under the impact of the three-dimensional structure of the impact head under different ultrasonic process conditions.

[0020] The simulation correction result matching the target profile data is determined, and the ultrasonic process conditions corresponding to the simulation correction result are used as ultrasonic process parameters.

[0021] According to an embodiment of the present application, the step of correcting the non-standard area by ultrasonic impact on the opposite side of the target correction direction of the preformed component according to the curvature difference type of the non-standard area includes:

[0022] If the curvature difference type of the non-standard area is the under-bending type, the first ultrasonic process parameter of the ultrasonic impact is determined according to the under-bending amount of the non-standard area, and the first ultrasonic process parameter includes at least one of the ultrasonic frequency, the impact angle, and the impact amplitude.

[0023] On the side opposite to the direction where the curvature of the non-standard area is increased, ultrasonic impact is used to correct the shape of the non-standard area based on the first ultrasonic process parameters.

[0024] According to an embodiment of the present application, the step of correcting the non-standard area by ultrasonic impact on the opposite side of the target correction direction of the preformed component according to the curvature difference type of the non-standard area includes:

[0025] If the curvature difference type of the non-standard area is an over-bending type, the second ultrasonic process parameter of the ultrasonic impact is determined according to the over-bending amount of the non-standard area, and the second ultrasonic process parameter includes at least one of the ultrasonic frequency, the impact angle, and the impact amplitude.

[0026] On the side of the non-standard area in the opposite direction of reducing the curvature, ultrasonic impact is used to correct the shape of the non-standard area based on the second ultrasonic process parameters.

[0027] According to an embodiment of the present application, the step of correcting the non-standard area by ultrasonic impact on the opposite side of the target correction direction of the preformed component includes:

[0028] A flexible isolation layer is arranged on the opposite side of the target shaping direction of the preformed component, and the non-standard area is shaped by ultrasonic impact under the condition of isolation of the flexible isolation layer.

[0029] According to an embodiment of the present application, the forming path of the ultrasonic impact is set according to the structure of the non-standard area, the size of the impact head and the position distribution of the impact head when it is ejected.

[0030] The impact duration of the ultrasonic impact is set according to the thickness of the non-standard area.

[0031] According to an embodiment of the present application, the method for determining the preset creep aging process parameters includes:

[0032] The material constitutive equation of the sheet material is fitted until the error between the fitted creep curve and the experimental creep curve is less than 5%, and the fitted constitutive equation is obtained.

[0033] The creep aging forming of the sheet material is simulated based on the fitted constitutive equation to obtain preset creep aging process parameters. The preset creep aging process parameters include creep time, creep temperature, creep stress, heating rate and loading rate.

[0034] According to an embodiment of the present application, the step of completing creep aging treatment of the sheet material under the condition of using preset creep aging process parameters includes:

[0035] The sheet material and the mold are sealed with a vacuum bag, and after the vacuum bag is evacuated to make the sheet material and the mold fit together, the whole is placed in an autoclave, and the parameters are set according to the preset creep aging process parameters to perform creep aging treatment.

[0036] The present application also provides an ultrasonic impact assisted creep aging precise shape correction device, comprising:

[0037] The creep aging treatment mechanism is used to complete the creep aging treatment of the sheet material under the condition of adopting preset creep aging process parameters to obtain a preformed component.

[0038] The data acquisition mechanism is used to acquire the three-dimensional surface data of the preformed component.

[0039] The ultrasonic impact mechanism is used to impact the non-standard area for correction according to the curvature difference type of the non-standard area on the opposite side of the target correction direction of the preformed component, until the three-dimensional surface data of the non-standard area meets the standard.

[0040] The central integrated controller is electrically connected to the creep aging treatment mechanism, and is used to set preset creep aging process parameters and transmit them to the creep aging treatment mechanism. The central integrated controller is electrically connected to the data acquisition mechanism, and is used to receive the three-dimensional profile data of the preformed component, compare it with the target profile data, and determine the substandard area of ​​the preformed component. The central integrated controller is electrically connected to the ultrasonic impact mechanism, and is used to determine the ultrasonic process parameters of the ultrasonic impact.

[0041] In the above-mentioned ultrasonic impact-assisted creep aging precise shaping method, ultrasonic impact is used for shaping according to the type of curvature difference in the non-standard area. The ultrasonic excitation source drives the impact head to vibrate and impact the material surface at high speed, forming a plastic deformation layer on the surface of the preformed component, refining the surface grains, and improving the mechanical properties of the material. At the same time, compressive stress is introduced into the interior of the preformed component, so that the metal material in the impact area extends to both sides, and the impact area of ​​the preformed component bends and deforms, repairing the unformed area, improving the forming accuracy of the local area, and assisting the overall formability of the metal creep aging. After the preformed component is ultrasonically impacted, a large dislocation density is introduced into the impact area, which improves the local material mechanical properties and optimizes the overall service performance of the material. In addition, the ultrasonic impact shaping method can perform follow-up impact on small angle areas and complex bending areas, and has a wider range of applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. 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 the structures shown in these drawings without paying creative work.

[0043] Figure 1 This is a flow chart of an ultrasonic impact assisted creep aging precise shape correction method according to an embodiment of the present application;

[0044] Figure 2 is a flow chart of determining ultrasonic process parameters of ultrasonic impact according to an embodiment of the present application;

[0045] Figure 3 is a flow chart of determining the ultrasonic process parameters through simulation in one embodiment of the present application;

[0046] Figure 4 It is a flow chart of a method for determining preset creep aging process parameters according to an embodiment of the present application;

[0047] Figure 5 It is a detailed flow chart of an ultrasonic impact assisted creep aging precise shape correction method according to an embodiment of the present application;

[0048] Figure 6 This is a flow chart of ultrasonic impact correction of a preformed component according to one embodiment of the present application;

[0049] Figure 7 It is a preformed component with curvature according to one embodiment of the present application;

[0050] Figure 8 yes Figure 7Schematic diagram of the non-compliant areas and the determined impact paths on the preformed component from a top view.

[0051] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with the implementation methods and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0052] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work are within the scope of protection of the present invention.

[0053] It should be noted that all directional indications (such as up, down, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0054] In addition, in the present invention, the descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features.

[0055] Furthermore, the technical solutions between the various embodiments of the present invention may be combined with each other, but this must be based on the fact that they can be implemented by ordinary technicians in the field. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0056] The present invention provides a method for accurate shape correction by ultrasonic impact assisted creep aging, referring to Figure 1 , including the following steps:

[0057] S100: The sheet material completes creep aging treatment under the condition of using preset creep aging process parameters to obtain a preformed component.

[0058] In this step, the sheet material is not limited to a flat plate, but also includes a wall plate with a rib height and a bent plate with a certain curvature. Meanwhile, the curvature of the sheet material is not limited to a single curve.

[0059] In order to facilitate the shape correction and reduce the influence of impurities or oxides on the surface of the sheet, in some embodiments, the sheet is pre-treated, such as polishing the surface of the sheet, wiping it with alcohol, and drying it for use. The sheet that has not been pre-treated can be called the original sheet. If the sheet itself is relatively clean, the pre-treatment process does not need to be performed.

[0060] Among them, the surface polishing treatment includes, but is not limited to, manual polishing with sandpaper, local polishing with an angle grinder, and local electrolytic polishing.

[0061] Creep aging treatment mainly includes two stages: loading stage and creep aging forming stage. For example, the sheet is placed on the mold for vacuum bag sealing, and pressure is applied to the flat sheet by vacuuming, so that the sheet gradually approaches the mold surface, and further pressure is provided in the autoclave to ensure the sheet is film-bonded and provide the required heat treatment temperature.

[0062] The process parameters of the specific processing steps of the creep aging treatment of the present application are not specifically limited. For example, the sheet material is treated accordingly according to the conventional creep aging treatment process, or the conventional creep aging treatment process is adjusted, such as adjusting the specific process parameters. Therefore, accordingly, the preset creep aging process parameters can be conventional creep aging process parameters, or can be adjusted creep aging process parameters.

[0063] In some embodiments, the creep aging process parameters include parameters specifically including creep temperature, creep holding time, gas pressure loading amount, gas pressure loading rate, heating rate, gas pressure unloading rate, and cooling rate.

[0064] S200: Collecting three-dimensional profile data of the preformed component, comparing it with target profile data, and determining the non-standard area of ​​the preformed component with respect to curvature. Both the three-dimensional profile data and the target profile data include corresponding curvature data.

[0065] After the creep aging treatment is completed, the sheet material is formed into a preformed component. The preformed component has a part of the area that is difficult to form, such as the skin area in the wall panel, or the area that has not reached the target state due to various reasons.

[0066] Exemplarily, the preformed component is taken out from the autoclave, and the surface of the preformed component is scanned by a three-dimensional optical measurement system to obtain three-dimensional surface data, which includes curvature data.

[0067] In some embodiments, the 3D optical measurement system includes a 3D laser scanner, a dynamic tracker, and a calibrator. The measurement content of the 3D optical measurement system includes characteristic information such as holes, characteristic points, edge lines, waist lines, section lines, R angles, and also includes bending accuracy information, such as curvature data.

[0068] In some more specific embodiments, the three-dimensional optical measurement system has a measurement coverage range of 0-6000 mm in length, 0-4000 mm in width, and 0-2000 mm in height.

[0069] The target surface data is the design data of the target component or the target product in three-dimensional space. The target surface data can be pre-stored data or data that is re-entered during comparison.

[0070] The data types of the target surface data and the three-dimensional surface data include various types. Exemplarily, the data type is graphic data, and the graphic difference between the target surface data and the three-dimensional surface data is found by graphic processing software, and the non-standard graphic area in the corresponding graphic of the three-dimensional surface data is determined, and then marked (such as with a marker) on the surface of the preformed component, and then ultrasonic impact is performed on the marked area of ​​the preformed component to complete the shape correction process.

[0071] Alternatively, after determining the non-standard graphic area in the graphics corresponding to the three-dimensional surface data, the surface of the preformed component is not marked, but the corresponding information is processed to generate position information of the non-standard area, which is input into the ultrasonic impact mechanism. The ultrasonic impact mechanism impacts the corresponding area of ​​the preformed component according to the position information to complete the shape correction processing.

[0072] Exemplarily, the data type is position data, such as coordinates. The coordinate difference between the target profile data and the three-dimensional profile data is found through mathematical software, and the non-standard coordinates in the corresponding graph of the three-dimensional profile data are determined, and then marked (such as with a marker) on the surface of the preformed component, and subsequently ultrasonic impact is performed on the marked area of ​​the preformed component to complete the shape correction process.

[0073] Alternatively, after determining the non-standard coordinates in the graphics corresponding to the three-dimensional surface data, the position information of the non-standard area is not marked on the surface of the preformed component, but is input into the ultrasonic impact mechanism. The ultrasonic impact mechanism impacts the corresponding area of ​​the preformed component according to the position information to complete the correction process.

[0074] Taking the unqualified curvature as an example, the curvature data of a certain place of the preformed component is inconsistent with the curvature data of the target surface, and the area of ​​the preformed component at that place is the unqualified area.

[0075] S300: According to the curvature difference type of the non-standard area, ultrasonic impact is used to correct the non-standard area on the opposite side of the target correction direction of the preformed component until the three-dimensional surface data of the non-standard area meets the standard.

[0076] The types of curvature differences include over-bending and under-bending. The actual deformation direction of the non-standard area during the correction process is opposite to the impact direction of the ultrasonic impact on the non-standard area. Therefore, it is necessary to reasonably select the impact direction of the ultrasonic impact on the non-standard area based on this characteristic and the type of curvature difference.

[0077] During the ultrasonic impact process, the preformed component can be separated from the mold, taken out and placed separately on the fetal membrane (the mold generated according to the target profile) for shape correction, or it can be directly subjected to ultrasonic impact on the creep mold.

[0078] If the curvature data of a certain place of the preformed component is greater than the curvature data of the target profile, the curvature difference type of the unqualified area is over-bending.

[0079] The goal of shaping when cornering is to reduce the curvature. Therefore, the target shaping direction of cornering is the direction of compressing the curvature. Ultrasonic impact is performed in the opposite direction of the target shaping direction (or impact), such as impacting from top to bottom, that is, impacting in the direction of a larger curvature. After the impact, under the action of residual compressive stress, the two sides of the impact area inside the preformed component material apply pressure to the impact area, which is equivalent to squeezing the middle, causing the impact area to move upward, thereby achieving the effect of reducing the curvature.

[0080] If the curvature data of a certain place of the preformed component is less than the curvature data of the target profile, the curvature difference type of the unqualified area is under-curvature.

[0081] The goal of the underbending shaping is to increase the curvature. Therefore, the target shaping direction of the underbending is the direction of increasing the curvature. The ultrasonic impact is performed in the opposite direction of the target shaping direction, such as from bottom to top, that is, in the direction of smaller curvature. After the impact, under the action of residual compressive stress, the two sides of the impact area inside the preformed component material apply pressure to the impact area, which is equivalent to squeezing the middle, so that the impact area moves downward, thereby achieving the effect of increasing the curvature.

[0082] Regardless of the above situation, after setting the ultrasonic impact parameters, ultrasonic impact calibration is carried out. Ultrasonic impact parameters include ultrasonic frequency, impact frequency, impact duration, impact amplitude, impact head size, impact angle, etc.

[0083] After the shape correction is completed, the component surface is scanned again with 3D optical detection and compared with the target surface. If the detected surface does not reach the target surface, ultrasonic impact correction is required again until it is finally qualified. If the detected surface is qualified, the aerospace standard component with excellent forming accuracy and performance is finally obtained.

[0084] The beneficial effects of the present invention include:

[0085] 1. The ultrasonic excitation source drives the impact head to vibrate and impact the material surface at high speed, forming a plastic deformation layer on the surface of the preformed component, refining the surface grains, improving the mechanical properties of the material, and introducing compressive stress into the component, so that the metal material in the impact area extends to both sides, the impact area of ​​the component bends and deforms, repairs the unformed area, improves the forming accuracy of the local area, and helps the overall formability of non-ferrous metals during creep aging.

[0086] 2. Ultrasonic impact forming relies on the high-speed vibrating impact head to impact the surface of the preformed component to achieve the effect of forming and strengthening. It belongs to the category of cold processing and will not cause thermal effects on the material.

[0087] 3. The ultrasonic impact shaping method used in the present invention performs ultrasonic impact shaping on the area that has not reached the forming accuracy after the first creep aging forming, so that the area that has not reached the forming accuracy can achieve a small deformation opposite to the impact direction, improve the overall forming accuracy of the component, avoid secondary creep aging forming, reduce the manufacturing process, and improve the overall forming efficiency of the component.

[0088] 4. The ultrasonic impact forming equipment has a relatively simple structure and can be held handheld or fixed on mechanical automation equipment for impact forming. The production cost is lower and the equipment is more convenient to use.

[0089] 5. Compared with roll bending or press bending, after the component is subjected to ultrasonic impact, a large dislocation density is introduced inside the impact area, which improves the local material mechanical properties and optimizes the overall service performance of the material.

[0090] 6. Compared with laser shock forming, the ultrasonic shock shaping method can perform follow-up impact on small-angle areas and complex curved areas, with a larger impact range.

[0091] 7. Ultrasonic impact correction is a method for correcting the difficult-to-form areas on components after one creep aging forming. The difficult-to-form areas are also areas with greater stress, which are prone to buckling and even cracking. After ultrasonic impact, the surface structure of the difficult-to-form areas is denser, and the ductility and fatigue resistance of the material are improved. The correction process effectively inhibits the occurrence of unstable cracking, avoids the risk of component scrapping, and reduces production costs.

[0092] In the above-mentioned ultrasonic impact-assisted creep aging precise shaping method, ultrasonic impact is used for shaping according to the type of curvature difference in the non-standard area. The ultrasonic excitation source drives the impact head to vibrate and impact the material surface at high speed, forming a plastic deformation layer on the surface of the preformed component, refining the surface grains, and improving the mechanical properties of the material. At the same time, compressive stress is introduced into the interior of the preformed component, so that the metal material in the impact area extends to both sides, and the impact area of ​​the preformed component bends and deforms, repairing the unformed area, improving the forming accuracy of the local area, and assisting the overall formability of the metal creep aging. After the preformed component is ultrasonically impacted, a large dislocation density is introduced into the impact area, which improves the local material mechanical properties and optimizes the overall service performance of the material. In addition, the ultrasonic impact shaping method can perform follow-up impact on small angle areas and complex bending areas, and the impact range is wider.

[0093] In some embodiments, reference Figure 2 The step of determining the ultrasonic process parameters of the ultrasonic impact comprises:

[0094] S310: According to the three-dimensional structure of the impact head in the ultrasonic impact and the three-dimensional structure of the modeling area in the preformed component, respectively establish the three-dimensional structure of the impact head and the three-dimensional model of the component, wherein the modeling area at least includes the non-standard area.

[0095] The impact heads ejected by ultrasonic impact include many types, such as pill-shaped impact heads and needle-shaped impact heads. Taking the needle-shaped impact head as an example, the needle-shaped impact head is referred to as a striker. The distribution and diameter of the striker can be set as needed. For example, if the area of ​​the non-compliant area is large, multiple rows of strikers with larger diameters are arranged. By way of example, the total number of strikers is 10, which are arranged in 3 rows in the impact head in a 3-4-3 arrangement, and the striker diameter is 2 mm. If the area of ​​the non-compliant area is small, a single row of strikers with smaller diameters is arranged. By way of example, the total number of strikers is 5, the strikers are arranged in 1 row, and the striker diameter is 1 mm.

[0096] A three-dimensional model of the ultrasonic impact pin is established. In some cases, the three-dimensional model established for the preformed component includes only the non-standard area, that is, it is established only based on the three-dimensional structure of the non-standard area, such as extracting the three-dimensional data of the non-standard area of ​​the preformed component to establish the model, so as to simplify the component model as a whole. In other cases, the modeling area includes other areas in addition to the non-standard area, for example, the modeling area is a complete preformed component, that is, it is established based on the three-dimensional structure of the entire preformed component, such as extracting the key dimensions and three-dimensional data of the entire preformed component to establish the model.

[0097] S320: Based on the three-dimensional structure of the impact head and the three-dimensional model of the component, a dynamic impact finite element analysis is performed using a Johnson-Cook model to perform simulation and determine the ultrasonic process parameters.

[0098] The Johnson-Cook model is:

[0099] ;

[0100] Wherein, A is the yield strength of the preformed component, B is the hardening modulus of the preformed component, C is the strain rate constant of the preformed component, m is the temperature softening coefficient of the preformed component, and n is the hardening index of the preformed component. T0 is a reference temperature, such as room temperature. m is the melting point temperature of the preformed component. are the stress of the preformed component and the strain of the preformed component respectively.

[0101] The simulation software includes ABAQUS, Marc, etc., and any one of them can be used for simulation model. Due to the characteristics of ultrasonic impact velocity discontinuity and high frequency and high strain impact, the Johnson-Cook model is selected as the constitutive model for solving the material.

[0102] In this embodiment, by determining the ultrasonic process parameters in this simulation manner, a better correction effect can be achieved, and the correction can be completed by one ultrasonic impact as much as possible.

[0103] In some embodiments, reference Figure 3 The step of determining the ultrasonic process parameters by performing a simulation based on the three-dimensional structure of the impact head and the three-dimensional model of the component and using the Johnson-Cook model to perform dynamic impact finite element analysis includes:

[0104] S321: Importing the impact head three-dimensional structure and the component three-dimensional model into simulation software.

[0105] For example, the above models are respectively imported into simulation software such as ABAQUS and Marc.

[0106] S322: A dynamic impact finite element analysis is performed using the Johnson-Cook model to simulate the simulation correction results of the three-dimensional model of the component under the impact of the three-dimensional structure of the impact head under different ultrasonic process conditions.

[0107] Specifically, when different ultrasonic process conditions (eg, impact velocity of the striker, diameter of the striker, impact duration, etc.) are adjusted during the simulation process, the three-dimensional model of the component impacts the three-dimensional structure of the impact head, producing different simulation correction results.

[0108] In the specific simulation process, according to the uneven distribution of residual stress in the thickness direction, the surrounding constraint boundary conditions are modified to free boundaries, and the static deformation results of the components after stress release are calculated, which are the simulation results of the preformed components after ultrasonic impact.

[0109] S323: Determine the simulation correction result that matches the target profile data, and use the ultrasonic process conditions corresponding to the simulation correction result as ultrasonic process parameters.

[0110] By analyzing the influence of different ultrasonic process conditions on the curvature radius of components with different thicknesses, and combining the simulation results with the accuracy comparison of the target surface, for example, the optimal ultrasonic process conditions suitable for component correction can be used as ultrasonic process parameters for subsequent actual ultrasonic impact.

[0111] In the above embodiment, this method can more quickly and accurately find ultrasonic process parameters with better correction effect, thereby improving the accuracy of the component.

[0112] In some embodiments, the step of correcting the non-standard area by ultrasonic impact on the opposite side of the target correction direction of the preformed component includes:

[0113] A flexible isolation layer is provided on the opposite side of the target shaping direction of the preformed component, and the non-standard area is shaped by ultrasonic impact under the condition of isolation of the flexible isolation layer. Exemplarily, the thickness of the flexible isolation layer is 0.5-5 mm.

[0114] The material of the flexible isolation layer includes but is not limited to cloth, cotton, silicone, and rubber. In some specific embodiments, the flexible isolation layer is 2 mm thick black rubber.

[0115] In some embodiments, the step of correcting the non-standard area by ultrasonic impact on the opposite side of the target correction direction of the preformed component according to the curvature difference type of the non-standard area includes:

[0116] If the curvature difference type of the non-standard area is the under-bending type, the first ultrasonic process parameter of the ultrasonic impact is determined according to the under-bending amount of the non-standard area, and the first ultrasonic process parameter includes at least one of the ultrasonic frequency, the impact angle, and the impact amplitude.

[0117] On the opposite side of the non-standard area where the curvature is increased, the non-standard area is shaped by ultrasonic impact based on the first ultrasonic process parameter. In a specific embodiment, the underbending amount of the non-standard area of ​​the preformed component is -4.8mm, and the accuracy of the non-standard area after impact shaping is -0.4mm, which is basically up to standard.

[0118] In some embodiments, the step of correcting the non-standard area by ultrasonic impact on the opposite side of the target correction direction of the preformed component according to the curvature difference type of the non-standard area includes:

[0119] If the curvature difference type of the non-standard area is an over-bending type, the second ultrasonic process parameter of the ultrasonic impact is determined according to the over-bending amount of the non-standard area, and the second ultrasonic process parameter includes at least one of the ultrasonic frequency, the impact angle, and the impact amplitude.

[0120] On the opposite side of the non-standard area where the curvature is reduced, the non-standard area is shaped by ultrasonic impact based on the second ultrasonic process parameter. In a specific embodiment, the bending amount of the non-standard area of ​​the preformed component is +3.6mm, and the accuracy of the non-standard area after impact shaping is +0.5mm, which is basically up to standard.

[0121] In some embodiments, the forming path of the ultrasonic impact is set according to the structure of the non-standard area, the size of the impact head and the position distribution of the impact head when it is ejected. The impact duration of the ultrasonic impact is set according to the thickness of the non-standard area.

[0122] For ribbed wall panel components, different ultrasonic impact parameters are designed according to the rib height and thickness, and the impact path is planned in advance to ensure that the under-bending areas at different thickness positions meet the standards.

[0123] For example, Figure 7 and Figure 8 shown. Figure 7 is a preformed component with a curvature, Figure 8 yes Figure 7 Schematic diagram of the preformed component from a top view after marking the non-compliant areas and planning the impact path. Figure 8 The rectangular area marked by A inside is the non-standard area, and the broken line L with an arrow in the non-standard area is the forming path, i.e., the impact path. The forming path is a reciprocating motion along a certain direction of the preformed component in the non-standard area, covering the entire non-standard area.

[0124] Different from roll bending and press bending, ultrasonic impact can change the deformation of the local difficult-to-form area by adjusting the ultrasonic frequency, impact angle, and impact amplitude, which technically guarantees the forming accuracy of the local area. Different from laser impact forming, ultrasonic impact can form the difficult-to-form area at any angle, and realizes the formability of the local difficult area from the equipment.

[0125] In some embodiments, reference Figure 4 , the method for determining the preset creep aging process parameters includes:

[0126] S110: Fitting the material constitutive equation of the sheet material until the error between the fitted creep curve and the experimental creep curve is less than 5%, thereby obtaining the fitted constitutive equation.

[0127] The material constitutive equation of the sheet material can be obtained by querying the data, and creep aging and basic mechanical properties experimental tests can be carried out on the same material of the sheet material to construct the material constitutive equation.

[0128] For example, the same material as the original sheet is used for creep aging and basic mechanical property experimental tests to obtain the creep and mechanical properties of the material under different temperatures and stresses. The creep data at a suitable temperature is used as the original data to construct the material constitutive equation, and the constitutive equation is fitted by mathematical software to ensure that the error between the fitted creep curve and the experimental creep curve is less than 5%.

[0129] Among them, the basic experimental parameters of mechanical properties include yield stress, tensile stress, elongation, hardness, and loading rate. Mathematical software includes MATLAB, Scilab, FreeMat, etc.

[0130] S120: Based on the fitted constitutive equation, the creep aging forming of the sheet is simulated to obtain preset creep aging process parameters. The preset creep aging process parameters include creep time, creep temperature, creep stress, heating rate and loading rate.

[0131] For example, the fitted constitutive equation is written through a subroutine and then imported into the simulation software to simulate the creep aging forming process of the sheet metal. The actual sheet metal forming process parameters in the autoclave (such as pressure 0.8-2MPa, temperature 140℃-200℃, duration 0.5-12h) and the mold surface are added as boundary conditions to obtain the preliminary creep aging forming results, and the results are compared with the target surface to obtain the pre-formed area that cannot reach the target surface by creep aging process alone and the underbending or overbending amount that needs to be compensated. Simulation software includes ANSYS, Comsol, Marc, etc.

[0132] In some embodiments, the step of completing creep aging treatment of the sheet material under the condition of using preset creep aging process parameters includes:

[0133] The sheet material and the mold are sealed with a vacuum bag, and after the vacuum bag is evacuated to make the sheet material and the mold fit together, the whole is placed in an autoclave, and the parameters are set according to the preset creep aging process parameters to perform creep aging treatment.

[0134] For example, the vacuum bag seals the sheet and the mold by using heat-resistant glue to tightly adhere the vacuum bag to the mold surface. 1 / 3-1 / 10 of the length of each side of the sealed sheet needs to be adhered to the vacuum bag itself to prevent the vacuum bag from being tight. For example, the adhesion height is 10mm-200mm. The parameters in the actual creep aging treatment are set according to the creep aging basic experiment and simulation results.

[0135] Take a specific embodiment as an example for explanation. The surface treated sheet is wrapped with breathable felt, and the breathable felt is fixed to the sheet with high temperature tape, and then placed on a stainless steel mold manufactured according to the rebound profile obtained by the simulation software. A vacuum nozzle is placed on the sheet, the position of the sheet is adjusted, and then high temperature resistant adhesive strips are attached around the mold, and a vacuum bag is laid on top. The sheet and the mold are sealed with a vacuum bag so that the sheet is in a closed space manufactured by the vacuum bag and the mold profile. The sealed interior is evacuated to fit the sheet and the mold. The mold is then placed in an autoclave as a whole, and the creep aging process parameters are set. The autoclave body is first pressurized, and the temperature is raised after reaching the set pressure. After reaching the target temperature, the temperature is kept constant to enter the creep aging preforming stage.

[0136] After completing creep aging forming, the air pressure in the autoclave is unloaded, the temperature is gradually lowered, the autoclave door is opened, the mold is pushed out as a whole, the vacuum bag attached to the mold surface is removed, the air felt and vacuum nozzle on the surface of the component are removed, and the component pretreated by creep forming is taken out after the component rebounds to obtain a preformed component.

[0137] In some embodiments, the mold profile is designed based on a target profile and a result of a creep aging simulation and springback during a simulation process.

[0138] The present application also provides an ultrasonic impact assisted creep aging precise correction device, which includes a creep aging treatment mechanism, a data acquisition mechanism, an ultrasonic impact mechanism and a central integrated controller.

[0139] The creep aging treatment mechanism is used to complete the creep aging treatment of the sheet material under the condition of using the preset creep aging process parameters to obtain the preformed component. Referring to the above content, the creep aging treatment mechanism includes a hot press, and its specific structure is not repeated here.

[0140] The data acquisition mechanism is used to collect the three-dimensional surface data of the preformed component. The data acquisition mechanism includes a three-dimensional optical measurement system, and its specific structure and function refer to the relevant description of the ultrasonic impact assisted creep aging precise correction method mentioned above, which will not be repeated here.

[0141] The ultrasonic impact mechanism is used to impact the non-standard area on the opposite side of the target correction direction of the preformed component according to the curvature difference type of the non-standard area to correct the shape until the three-dimensional surface data of the non-standard area meets the standard. The specific structure and function of the ultrasonic impact mechanism refer to the relevant description of the ultrasonic impact assisted creep aging precise correction method mentioned above, which will not be repeated here.

[0142] The central integrated controller is electrically connected to the creep aging treatment mechanism, and is used to set preset creep aging process parameters and transmit them to the creep aging treatment mechanism. The central integrated controller is electrically connected to the data acquisition mechanism, and is used to receive the three-dimensional profile data of the preformed component, compare it with the target profile data, and determine the substandard area of ​​the preformed component. The central integrated controller is electrically connected to the ultrasonic impact mechanism, and is used to determine the ultrasonic process parameters of the ultrasonic impact.

[0143] The above-mentioned ultrasonic impact assisted creep aging precise shaping device can realize the above-mentioned ultrasonic impact assisted creep aging precise shaping method, and therefore has the corresponding beneficial effects of the shaping method, which will not be described in detail.

[0144] In order to more clearly describe the technical solution of the present application, a detailed embodiment is described below as an example.

[0145] Example:

[0146] A precise shape correction method for ultrasonic impact assisted creep aging, referring to Figure 5 , including the following steps:

[0147] Q1: The plate material is a 30mm thick 7xxx series high-strength aluminum alloy plate, the heat treatment state is over-aging state, the plate size is 1500mm×700mm, and the plate surface is milled to produce vertical cross ribs with a height of 12mm and a thickness of 8mm. The plate surface is polished, wiped with alcohol, and dried for use.

[0148] The material constitutive equation of the sheet material is fitted until the error between the fitted creep curve and the experimental creep curve is less than 5%, and the fitted constitutive equation is obtained. The creep aging forming of the sheet material is simulated based on the fitted constitutive equation to obtain the preset creep aging process parameters: the process parameters for forming in the autoclave (pressure 0.8-2MPa, temperature 140℃-200℃, time 0.5-12h).

[0149] Q2: Wrap the surface treated sheet with breathable felt, fix the breathable felt on the sheet with high temperature tape, and then place it on a stainless steel mold made according to the springback profile obtained by the simulation software. The mold has an overall size of 2500mm×1500mm×800mm, the mold base and profile are made of Q345 steel, the profile roughness is Ra1.5, the maximum working pressure is 2.2MPa, and the maximum working temperature is 300℃.

[0150] Place a vacuum nozzle on the sheet, adjust the position of the sheet, and then stick high-temperature resistant adhesive strips around the mold, and lay a vacuum bag on top, and use the vacuum bag to seal the sheet and the mold. The sealing method is to use heat-resistant adhesive to tightly adhere the vacuum bag to the mold surface. The vacuum bag needs to be adhered to itself for 1 / 3-1 / 10 of the length of one side of each sealed sheet to prevent the vacuum bag from being tight. The vacuum bag's self-adhesion height is 10mm-200mm.

[0151] The sheet is placed in a closed space made by the vacuum bag and the mold surface, and the sealed interior is evacuated to make the sheet fit the mold, and then the mold is placed in the autoclave as a whole. The effective space inside the vacuum autoclave is φ4000mm×6000mm.

[0152] According to the preset creep aging process parameters, the creep aging process parameters are set. First, the hot press tank is pressurized, and the temperature is raised after reaching the set pressure. After reaching the temperature, the creep aging pre-forming stage is entered. The creep aging forming temperature is 185℃, the temperature fluctuation is ±2℃, the heating rate is 2.5℃ / min, the creep aging high temperature insulation time is 1.8h, and the vacuum loading rate is 0.2bar / min.

[0153] Q3: After completing the creep aging forming of Q2, unload the air pressure in the autoclave, gradually cool it down, open the door, push out the mold as a whole, remove the vacuum bag attached to the mold surface, remove the breathable felt and vacuum nozzle on the surface of the component, and take out the component after creep forming pretreatment after the component rebounds, that is, the preformed component.

[0154] The component surface is inspected and scanned using a three-dimensional optical measurement system and compared with the target profile to determine the local area that does not reach the target profile and the required underbending amount, and the unformed area is marked on the component surface.

[0155] Q4: According to the three-dimensional structure of the impact head in the ultrasonic impact and the three-dimensional structure of the modeling area in the preformed component, the three-dimensional structure of the impact head and the three-dimensional model of the component are established respectively.

[0156] Based on the three-dimensional structure of the impact head and the three-dimensional model of the component, the Johnson-Cook model is used to perform dynamic impact finite element analysis for simulation; the Johnson-Cook model is:

[0157] ;

[0158] Wherein, A is the yield strength of the preformed component, B is the hardening modulus of the preformed component, C is the strain rate constant of the preformed component, m is the temperature softening coefficient of the preformed component, and n is the hardening index of the preformed component; T0 is the reference temperature; T m is the melting point temperature of the preformed component. In 7xxx high-strength aluminum alloy, the parameters A, B, C, m, and n are selected to be 480MPa, 684MPa, 0.0083, 1.7, and 7.3 respectively. T0 is 180℃, T m It is 670℃.

[0159] The simulation correction result matching the target profile data is determined, and the ultrasonic process conditions corresponding to the simulation correction result are used as ultrasonic process parameters.

[0160] Place an isolation layer above the marked unformed area of ​​the component, set the ultrasonic process parameters, including ultrasonic frequency, impact frequency, impact duration, impact amplitude, impact head size, and impact angle, and carry out ultrasonic impact correction. The specific parameters are as follows: ultrasonic frequency is 20KHz, impact frequency is 3000 times / minute, impact duration is 1h, impact amplitude is full wavelength 50μm, impact head (striker) size is 2mm in diameter, the number of impact heads is 2 rows of 5 (2+3), and the impact angle is 90°.

[0161] After the correction is completed, the component surface is scanned in three dimensions optically and compared with the target surface. If the detected surface does not reach the target surface, ultrasonic impact correction is required again. If the detected surface is qualified, a component that meets aerospace standards with excellent forming accuracy and performance is finally obtained. Figure 6 It is a schematic diagram of the ultrasonic impact precise correction of the ribbed component after preforming, including component ribs 1, component skin 2, ultrasonic impact head 3, striker 4, and flexible isolation layer 5.

[0162] The above technical solutions of the present invention are only preferred embodiments of the present invention, and the patent scope of the present invention is not limited thereto. All equivalent structural changes made by using the contents of the present invention specification and drawings under the technical concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. An ultrasonic impact assisted creep aging precise shape correction method, characterized in that: The following steps are involved: The sheet material completes creep aging treatment under the condition of using preset creep aging process parameters to obtain a preformed component; Collecting three-dimensional profile data of the preformed component, comparing it with target profile data, and determining the area of ​​the preformed component that does not meet the standard in terms of curvature; The three-dimensional profile data and the target profile data both include corresponding curvature data; According to the type of curvature difference of the non-standard area, on the opposite side of the target shaping direction of the preformed component, ultrasonic impact is used to shape the non-standard area until the three-dimensional surface data of the non-standard area meets the standard; The step of determining the ultrasonic process parameters of the ultrasonic impact comprises: According to the three-dimensional structure of the impact head in the ultrasonic impact and the three-dimensional structure of the modeling area in the preformed component, respectively establish the three-dimensional structure of the impact head and the three-dimensional model of the component, wherein the modeling area at least includes the non-standard area; Based on the three-dimensional structure of the impact head and the three-dimensional model of the component, the Johnson-Cook model is used to perform dynamic impact finite element analysis to perform simulation and determine the ultrasonic process parameters; the Johnson-Cook model is: ； Wherein, A is the yield strength of the preformed component, B is the hardening modulus of the preformed component, C is the strain rate constant of the preformed component, m is the temperature softening coefficient of the preformed component, and n is the hardening index of the preformed component; T is the actual temperature of the preformed component; T0 is the reference temperature; T m is the melting point temperature of the preformed component; σ is the engineering stress of the preformed component; ε is the engineering strain of the preformed component; is the actual strain rate of the preformed component; is a reference strain rate of the preformed component; The step of performing simulation based on the three-dimensional structure of the impact head and the three-dimensional model of the component by using the Johnson-Cook model to perform dynamic impact finite element analysis to determine the ultrasonic process parameters includes: Importing the impact head three-dimensional structure and the component three-dimensional model into simulation software; The Johnson-Cook model is used to perform dynamic impact finite element analysis to simulate the simulation correction results of the three-dimensional model of the component under the impact of the three-dimensional structure of the impact head under different ultrasonic process conditions; The simulation correction result that matches the target profile data is determined, and the ultrasonic process conditions corresponding to the simulation correction result are used as ultrasonic process parameters.

2. The ultrasonic impact assisted creep aging precise shape correction method according to claim 1 is characterized in that: The step of correcting the non-standard area by ultrasonic impact on the opposite side of the target correction direction of the preformed component according to the curvature difference type of the non-standard area comprises: If the curvature difference type of the non-standard area is an under-bending type, determining a first ultrasonic process parameter of the ultrasonic impact according to the under-bending amount of the non-standard area, wherein the first ultrasonic process parameter includes at least one of an ultrasonic frequency, an impact angle, and an impact amplitude; On the side opposite to the direction where the curvature of the non-standard area is increased, ultrasonic impact is used to correct the shape of the non-standard area based on the first ultrasonic process parameters.

3. The ultrasonic impact assisted creep aging precise shape correction method according to claim 1 is characterized in that: The step of correcting the non-standard area by ultrasonic impact on the opposite side of the target correction direction of the preformed component according to the curvature difference type of the non-standard area comprises: If the curvature difference type of the non-standard area is an over-bending type, determining a second ultrasonic process parameter of the ultrasonic impact according to the over-bending amount of the non-standard area, the second ultrasonic process parameter including at least one of an ultrasonic frequency, an impact angle, and an impact amplitude; On the side of the non-standard area in the opposite direction of reducing the curvature, ultrasonic impact is used to correct the shape of the non-standard area based on the second ultrasonic process parameters.

4. The ultrasonic impact assisted creep aging precise shape correction method according to claim 1 is characterized in that: The step of correcting the non-standard area by ultrasonic impact on the opposite side of the target correction direction of the preformed component comprises: A flexible isolation layer is arranged on the opposite side of the target shaping direction of the preformed component, and the non-standard area is shaped by ultrasonic impact under the condition of isolation of the flexible isolation layer.

5. The ultrasonic impact assisted creep aging precise shape correction method according to claim 1, characterized in that: The forming path of the ultrasonic impact is set according to the structure of the non-standard area, the size of the impact head and the position distribution of the impact head when it is ejected; The impact duration of the ultrasonic impact is set according to the thickness of the non-standard area.

6. The ultrasonic impact assisted creep aging precise shape correction method according to claim 1 is characterized in that: The method for determining the preset creep aging process parameters includes: The material constitutive equation of the sheet material is fitted until the error between the fitted creep curve and the experimental creep curve is less than 5%, and the fitted constitutive equation is obtained; Based on the fitted constitutive equation, the creep aging forming of the sheet is simulated to obtain preset creep aging process parameters; the preset creep aging process parameters include creep time, creep temperature, creep stress, heating rate and loading rate.

7. The ultrasonic impact assisted creep aging precise shape correction method according to claim 6, characterized in that: The step of completing creep aging treatment of the sheet material under the condition of using preset creep aging process parameters includes: The sheet material and the mold are sealed with a vacuum bag, and after the vacuum bag is evacuated to make the sheet material and the mold fit together, the whole is placed in an autoclave, and the parameters are set according to the preset creep aging process parameters to perform creep aging treatment.

8. An ultrasonic impact assisted creep aging precise shape correction device, characterized in that: include: A creep aging treatment mechanism is used to complete creep aging treatment of the sheet material under the condition of using preset creep aging process parameters to obtain a preformed component; A data acquisition mechanism, used for acquiring three-dimensional surface data of the preformed component; An ultrasonic impact mechanism is used to impact the non-standard area on the opposite side of the target shaping direction of the preformed component according to the type of curvature difference of the non-standard area to correct the shape until the three-dimensional surface data of the non-standard area meets the standard; A central integrated controller is electrically connected to the creep aging treatment mechanism, and is used to set preset creep aging process parameters and transmit them to the creep aging treatment mechanism; the central integrated controller is electrically connected to the data acquisition mechanism, and is used to receive the three-dimensional profile data of the preformed component, compare it with the target profile data, and determine the substandard area of ​​the preformed component; the central integrated controller is electrically connected to the ultrasonic impact mechanism, and is used to determine the ultrasonic process parameters of the ultrasonic impact; The step of determining the ultrasonic process parameters of the ultrasonic impact comprises: According to the three-dimensional structure of the impact head in the ultrasonic impact and the three-dimensional structure of the modeling area in the preformed component, respectively establish the three-dimensional structure of the impact head and the three-dimensional model of the component, wherein the modeling area at least includes the non-standard area; Based on the three-dimensional structure of the impact head and the three-dimensional model of the component, the Johnson-Cook model is used to perform dynamic impact finite element analysis to perform simulation and determine the ultrasonic process parameters; the Johnson-Cook model is: ； Wherein, A is the yield strength of the preformed component, B is the hardening modulus of the preformed component, C is the strain rate constant of the preformed component, m is the temperature softening coefficient of the preformed component, and n is the hardening index of the preformed component; T is the actual temperature of the preformed component; T0 is the reference temperature; T m is the melting point temperature of the preformed component; σ is the engineering stress of the preformed component; ε is the engineering strain of the preformed component; is the actual strain rate of the preformed component; is a reference strain rate of the preformed component; The step of performing simulation based on the three-dimensional structure of the impact head and the three-dimensional model of the component by using the Johnson-Cook model to perform dynamic impact finite element analysis to determine the ultrasonic process parameters includes: Importing the impact head three-dimensional structure and the component three-dimensional model into simulation software; The Johnson-Cook model is used to perform dynamic impact finite element analysis to simulate the simulation correction results of the three-dimensional model of the component under the impact of the three-dimensional structure of the impact head under different ultrasonic process conditions; The simulation correction result that matches the target profile data is determined, and the ultrasonic process conditions corresponding to the simulation correction result are used as ultrasonic process parameters.

Images