A multi-system cooperative stress relieving and straightening device and method for independently controlling partitions of an aircraft wing plate welded component

Abstract

The application provides a multi-system coordinated stress relieving and straightening device and method for independent control of different zones of an aircraft wing plate welding component, which comprises a cooling module, a clamping module, a stress and temperature monitoring module, a central control module and an integrated tooling table, the cooling module and the clamping module are connected with the central control module through independent sensors, the independent and accurate control of the cooling channels and the clamping force of different zones is realized, and thus the accurate and flexible stress deformation regulation and control are realized. During formal welding, the cooling module and the clamping module of different zones automatically adjust the flow rates of the cooling liquid and the cooling gas according to the change of the temperature field in the zones, meanwhile, the central control module analyzes the data of the cooling module and the clamping module, ensures the best cooperation of the two modules, and thus the real-time and accurate stress regulation and control of each zone are realized. The device and the method can reduce the welding stress of the aircraft wing plate welding component to the greatest extent, and high-quality welding products are obtained.

Description

Technical Field

[0001] This invention relates to the field of welding stress and deformation technology, and in particular to a multi-system collaborative stress relief and straightening device and method for independent zone control of welded components for aircraft wing plates. Background Technology

[0002] In the aerospace field, welding technology is one of the most commonly used processing methods in the manufacture of aircraft wing components due to its advantages such as significant weight reduction, high production efficiency, and ease of automation. However, an unavoidable problem in the welding of aircraft wing components is the high welding stress, which can easily cause deformation and cracking of the welded components. In actual welding, the generation of welding stress and deformation is due to uneven heating of different parts of the workpiece near the heat source during welding. After experiencing localized heating and rapid cooling, thermal expansion occurs, while no thermal expansion occurs in areas far from the heat source. Therefore, thermal expansion deformation is hindered, resulting in welding deformation and residual stress after welding. Therefore, reducing the temperature gradient in different areas by controlling the temperature field is the most effective means to solve the problem of excessive residual stress and deformation after welding.

[0003] Currently, in actual production processes, to reduce post-weld residual stress and deformation and improve welding efficiency, in-process cooling methods are commonly used, such as water spraying and immersion. Water spraying offers better cooling, but the spraying of water is a relatively complex phenomenon, making precise control difficult. This can lead to insufficient or excessive cooling at the joint, resulting in uneven welding. Immersion is less effective, its core principle being overall cooling to reduce the temperature gradient and thus stress and deformation. However, its drawback is the difficulty in achieving precise control through zoned methods. Furthermore, high costs and the difficulty in automating these methods also limit their development.

[0004] In summary, there is an urgent need for a device and method capable of precisely zoning and controlling the stress and deformation of welded aircraft wingplate components. This would allow for flexible adjustment of parameters and schemes based on the stress and deformation conditions of different parts, thereby improving the stress relief and deformation control effects. The device of this invention employs independent control of different regions and coordinated operation of multiple systems, achieving both flexibility and precision in stress and deformation control during the welding process. This has significant guiding and application value for advancing the field of automated stress relief and deformation control. Summary of the Invention

[0005] To address the shortcomings of the existing technology, this invention aims to provide a multi-system collaborative stress relief and straightening device and method for independently controlling the zones of aircraft wingplate welded components. This addresses issues such as excessive residual stress and severe welding deformation in aircraft wingplate welded components, which make it difficult to meet service requirements. The device of this invention can achieve independent and precise control of cooling channels and clamping forces in different areas, thereby achieving accurate stress regulation. At the same time, the equipment is simple and easy to operate.

[0006] To achieve the above objectives, the present invention provides a multi-system collaborative stress relief and straightening device and method for independently controlled zoned control of welded components of aircraft wing plates, specifically including:

[0007] The cooling module is used to cool the aircraft wingplate to be welded in sections during the welding process. It includes a cooling copper block, coolant channels, cooling gas channels, and a cooling medium storage and circulation system. The cooling copper block has serpentine grooves and arrayed through holes inside, which are used to house the serpentine coolant channels and the arrayed gas channels, respectively. The cooling medium storage and circulation system is connected to the coolant channels and cooling gas channels through connecting transmission pipes.

[0008] The coolant channels are divided into left and right sides. The channels on the same side are connected in series, and the channels on opposite sides are connected in parallel, which is used to cool the welded components of the aircraft wing plates on the left and right sides in sections.

[0009] The cooling gas channels are arranged in a 6×9 array, with each group consisting of 3×1 channels, for a total of 18 groups. The 18 groups of gas channels are connected in parallel, dividing the weldment into 18 corresponding regions. Precise temperature control of each region of the weldment is achieved by adjusting the cooling gas flow rate of each group.

[0010] The cooling medium storage and circulation system consists of a coolant tank, a cooling gas cylinder, a box-type coolant circulation device, and connecting transmission pipelines. The pipeline connected to the cooling gas channel is equipped with a proportional valve to achieve individual control of the cooling gas flow rate in each channel, and the pipeline connected to the cooling liquid channel is equipped with a throttle valve to achieve precise control of the coolant. The connecting transmission pipelines are used for connecting the various devices of the cooling module.

[0011] The clamping module is used to fix the aircraft wingplate welding components during the welding process. It includes clamping columns, pressure plates, motors and transmission devices. The clamping columns are installed on both sides of the integrated tooling table, with 9 on each side and a total of 18. Each clamping column is equipped with a pressure plate. Each clamping column is independently controlled by a corresponding motor and transmission device. The motor and transmission device are connected to the central control system to realize the individual adjustment of the clamping force at different positions of the aircraft wingplate welding components.

[0012] The stress and temperature monitoring module is used to monitor the stress and temperature of various parts of the aircraft wing plate welded components in real time. It includes a stress sensor and an infrared thermometer. The stress sensor is installed on the pressure plate to measure the stress changes during the welding process and convert them into electrical signals, which are then transmitted to the central control system for analysis. The infrared thermometer is placed near the integrated workbench to monitor the temperature of the weld in real time and transmit the obtained data to the central control system.

[0013] The central control system, used for data storage and coordinated control of various modules, includes an expert database, a data analyzer, and a central controller. The expert database contains information on raw materials, welding processes, and temperature and stress field distributions during the welding process for various aircraft wingplate welding components, serving as a reference for adjusting real-time monitoring data during the welding process. The data analyzer, connected to the stress and temperature detection module, processes the data acquired by the sensors and transmits it to the central controller in real time, enabling data interaction and sharing between the cooling and clamping modules. The central controller, connected to both the cooling and clamping modules, analyzes the real-time monitored data and, using the data stored in the expert database as a reference, adjusts the parameters of the cooling and clamping modules to ensure optimal synergy, thereby achieving automatic control of the temperature and stress fields during the welding process.

[0014] An integrated tooling table is used to assemble various modules and devices. The upper part is uniformly coated with a heat-conducting medium to increase the heat exchange efficiency and contact area between the tooling table and the aircraft wing welding components. During the welding process, the heat is quickly carried away to control stress and deformation.

[0015] Furthermore, the central control system is connected to the cooling module and the clamping module. Based on the real-time monitoring of temperature and stress field data during the welding process, it controls the execution state of the central controller in real time, thereby achieving independent control of the cooling system and the clamping system. The central control system is equipped with appropriate algorithms and logic. Through data sharing between the cooling module and the clamping module, the central controller uses a PID controller algorithm to calculate the outputs of the clamping module and the cooling module, collaboratively controlling the clamping force and cooling airflow, thereby achieving precise machining and efficient cooling of the aircraft wingplate welded components. The formula is as follows:

[0016]

[0017] Where u(t) represents the controller output, e(t) represents the deviation (i.e. the difference between the expected value and the actual value), and Kp, Ki, and Kd represent the proportional, integral, and derivative coefficients, respectively.

[0018] Furthermore, the data in the expert database originates from the temperature field, stress field, and deformation during welding under different materials, thicknesses, processes, and welding parameters, as simulated in the early stages. Simultaneously, experimental research was conducted to verify the simulation results, revise and improve the model and simulation process. Based on the improved model and simulation method, the temperature field-stress field correspondence was established, the flow rates of cooling gas and coolant to reduce the welding stress field under real-time temperature distribution were calculated, and the clamping force distribution data of the clamping module required under real-time stress distribution was calculated. In this way, a database of temperature-stress-clamping force correspondence was established, which was imported into the central controller and updated in real time on the display.

[0019] Furthermore, the cooling gas column pipes in the device can be adjusted according to the actual welding situation. When performing short-time high-heat input welding, such as high-power laser welding, the number of cooling gas pipes near the weld seam can be increased, and the stress reduction effect can be improved by increasing the feedback frequency of the switching valve. When performing special path welding, such as laser oscillation welding, stress and deformation can be controlled by designing cooling gas pipes near the oscillation path.

[0020] Furthermore, the coolant includes, but is not limited to, water. The type of coolant can be adjusted during spot welding and formal welding processes that serve a fixing function. The cooling gas connection and transmission pipeline has three layers: an outer insulation layer, a middle moisture-proof layer, and an inner insulation layer. The coolant connection and transmission pipeline is made of nylon-like plastic and is used for coolant transmission. The end of the coolant transmission pipeline is connected to a box-type coolant circulation device and uses an interference fit to prevent leakage.

[0021] Furthermore, after welding, the clamping columns are subjected to stress release to maintain their shape. The post-weld shape retention refers to increasing the clamping pressure of each clamping column by 500-1000N after welding, under the clamping force distribution at the time of welding completion, and fixing the aircraft wing plate welded components for 12-24 hours. Under restraint conditions, the residual stress of the aircraft wing plate welded components is released to control deformation.

[0022] Furthermore, the derivation formula for stress is as follows:

[0023]

[0024] Where σ is the stress (Pa), W is the tensile or compressive load (kg), and A is the cross-sectional area under load (mm²). 2 );

[0025] Furthermore, it employs a multi-system collaborative stress relief and straightening device with independent subsystem control to achieve independent and precise control of cooling channels and clamping forces in different areas, and to maximize control of welding stress and post-weld deformation of aircraft wingplate welded components. Its features include:

[0026] Pre-welding parameter adjustment preparation involves retrieving the type of cooling liquid, cooling liquid flow rate, type of cooling gas, and cooling gas flow rate required for spot welding and formal welding under the combined parameters, and determining the combined coordination mode of cooling gas and clamping device.

[0027] Spot welding is performed on the components used to fix the aircraft wing plates. After spot welding is completed, the coolant in the coolant pipes and the cooling gas behind the cooling pipes are evacuated.

[0028] During the formal welding process, the temperature and stress detection module monitors the temperature and stress distribution in different areas of the weldment in real time and transmits the data to the central controller of the central control system. The central controller automatically obtains the adjustment strategies for parameters such as coolant flow rate, cooling gas flow rate, and clamping force distribution of the cooling module and clamping module by comparing with the expert database, and transmits the commands to the cooling module and clamping module respectively to adjust the temperature field and stress field of the welding in real time. The above three systems work together until the welding is completed, and together achieve the purpose of reducing or even eliminating stress and straightening.

[0029] Post-weld shape retention is achieved by continuously clamping the welded aircraft wing components with pressure plates, thereby releasing post-weld stress and controlling deformation of the workpiece.

[0030] The beneficial technical effects of this invention are as follows:

[0031] To address the unavoidable problems of excessive residual stress and severe welding deformation in aircraft wingplate welded components during the welding process in the aerospace field, which prevent them from meeting service requirements, and to further address the shortcomings of existing stress relief and straightening methods such as low precision, poor synergy, and lack of unified standards, this paper proposes a multi-system collaborative stress relief and straightening device and method for aircraft wingplate welded components with independent zone control. By precisely controlling the cooling and clamping modules in different zones, independent and precise control of the cooling channels and clamping forces in different areas is achieved, thereby realizing stress and deformation control with both flexibility and precision. Under the multi-system collaborative working mode, the goal of reducing or even eliminating stress and straightening is achieved. After welding, the aircraft wingplate welded components are subjected to post-weld shape preservation to release residual stress and control post-weld deformation, ultimately obtaining high-quality, high-performance welded products with short production cycles. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of the overall structure of a multi-system collaborative stress relief and straightening device for independently controlled zoned control of welded components of aircraft wing plates, as described in this invention.

[0033] Figure 2 This is a schematic diagram of the internal structure of the water-cooled copper block in a multi-system collaborative stress relief and straightening device for independent zoned control of welded components of aircraft wing plates, as described in this invention.

[0034] Figure 3 This is a schematic diagram of the bottom structure of an integrated tooling table for a multi-system collaborative stress relief and straightening device with independent zoned control of welded components for aircraft wing plates, as described in this invention.

[0035] Figure 4 This is a flowchart illustrating the database acquisition process in a multi-system collaborative stress relief and straightening device for independent zoned control of welded components of aircraft wing plates, as described in this invention.

[0036] Figure 5 This is a flowchart illustrating the operation of a multi-system collaborative stress relief and straightening device and method for independent zoned control of welded components of aircraft wing plates, as described in this invention.

[0037] Attached reference numerals: 100 is the cooling module, 200 is the clamping module, 300 is the stress and temperature monitoring module, 400 is the central control system, and 500 is the integrated tooling table.

[0038] 101 is a cooling copper block, 102 is a serpentine groove, 103 is an array of through holes, 104 is a serpentine coolant channel, 105 is an array of gas channels, 106 is a connecting transmission pipe, 107 is a coolant tank, 108 is a cooling gas cylinder, 109 is a box-type coolant circulation device, 201 is a clamping column, 202 is a pressure plate, 203 is a motor and transmission device, 301 is a stress sensor, and 302 is an infrared thermometer. Detailed Implementation

[0039] Reference Figure 1 , Figure 2 , Figure 3 As shown, this invention relates to a multi-system collaborative stress relief and straightening device and method for independently controlled zoned welding of aircraft wingplate components. The stress relief and straightening device includes a cooling module, a clamping module, a stress and temperature monitoring module, a central control module, and an integrated tooling table. The cooling module includes a cooling copper block, a coolant channel, a cooling gas channel, and a cooling medium storage and circulation system. The cooling medium storage and circulation system is divided into a coolant tank, a cooling gas cylinder, a box-type coolant circulation device, and connecting transmission pipelines. The clamping module includes a clamping column, a pressure plate, a motor, and a transmission device. The stress and temperature monitoring module includes a stress sensor and an infrared thermometer.

[0040] Reference Figure 4 , Figure 5As shown, this invention relates to a multi-system collaborative stress relief and straightening device and method for independently controlled zoned welding of aircraft wingplate components. The stress relief and straightening method involves pre-welding parameter preparation, specifically retrieving the type of coolant, coolant flow rate, type of cooling gas, and cooling gas flow rate required for spot welding and formal welding under combined parameters, and determining the combined collaborative mode of the cooling gas and clamping device. Spot welding is then performed to fix the workpiece. After spot welding, the coolant in the coolant pipe and the cooling gas after the pipe are evacuated. Formal welding then commences, with the temperature and stress detection module monitoring the aircraft wingplate welding components in real time during the welding process. The temperature and stress distribution in different areas are transmitted to the central controller of the central control system. The central controller compares the data with an expert database to automatically obtain adjustment strategies for parameters such as coolant flow rate, cooling gas flow rate, and clamping force distribution of the cooling and clamping modules. Commands are then transmitted to the cooling and clamping modules to adjust the temperature and stress fields of the welding in real time. The three systems work together until the welding is completed to reduce or even eliminate stress and achieve the goal of straightening. Finally, post-weld shape retention is performed by continuously clamping the welded aircraft wing panel components with pressure plates to achieve post-weld stress release and deformation control of the workpiece.

[0041] The following example illustrates the complete assembly and use process of this invention using a multi-system collaborative stress relief and straightening device and method for independent zone control of welded components of aircraft wing plates.

[0042] The material parameters and heat source parameters of the aircraft wing plate welding components are input into the database of the central control module. The system then retrieves the type of cooling liquid, cooling liquid flow rate, type of cooling gas, and cooling gas flow rate required for spot welding and formal welding under the combined parameters, and determines the combined coordination mode of the cooling gas and clamping device.

[0043] For spot welding used to secure the workpiece, open the valve of the cooling gas cylinder and the valve of the coolant tank before spot welding. Once it is confirmed that there are no leaks in the pipes, begin spot welding. After spot welding is complete, evacuate the coolant from the coolant pipes and the cooling gas from the cooling pipes.

[0044] Click the start button on the human-computer interaction display screen to begin welding. During the welding process, the temperature and stress detection module monitors the temperature and stress distribution in different areas of the weldment in real time, transmitting the data to the central controller of the central control system. The central controller compares the data with an expert database to automatically obtain adjustment strategies for parameters such as coolant flow rate, cooling gas flow rate, and clamping force distribution of the cooling and clamping modules, and transmits commands to the cooling and clamping modules respectively to adjust the temperature and stress fields of the welding in real time. The above three systems work together until the welding is completed, jointly achieving the goal of reducing or even eliminating stress and correcting the shape.

[0045] After welding, an additional clamping pressure of 1500N is applied to the workpiece using a clamping device, and it is fixed for 18 hours. Under restraint conditions, the residual stress of the aircraft wing plate welded component is released to control deformation.

[0046] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. For those skilled in the art, based on the concept of the present invention, there will be changes in specific implementation methods and application scope. The content of this specification should not be construed as a limitation of the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A multi-system collaborative stress relief and straightening device for independently controlled zoned control of welded components of aircraft wing plates, characterized in that, Specifically, it includes: The cooling module (100) is used to cool the aircraft wingplate to be welded in sections during the welding process. It includes a cooling copper block (101), a coolant channel, a cooling gas channel, and a cooling medium storage and circulation system. The cooling copper block (101) is provided with a serpentine groove (102) and an array of through holes (103) inside, which are used to place the serpentine coolant channel (104) and the array of gas channels (105) respectively. The cooling medium storage and circulation system is connected to the coolant channel and the cooling gas channel through a connecting transmission pipe (106). The coolant channels are divided into left and right sides. The channels on the same side are connected in series, and the channels on opposite sides are connected in parallel, which is used to cool the welded components of the aircraft wing plates on the left and right sides in sections. The cooling gas channels are arranged in a 6×9 array, with each group consisting of 3×1 channels, for a total of 18 groups. The 18 groups of cooling gas channels are connected in parallel, dividing the weldment into 18 corresponding areas. Precise temperature control of each area of ​​the weldment is achieved by adjusting the cooling gas flow rate of each group. The cooling medium storage and circulation system is divided into a coolant tank (107), a cooling gas cylinder (108), a box-type coolant circulation device (109), and a connecting transmission pipeline (106). The pipeline connected to the cooling gas channel is equipped with a proportional valve to achieve individual control of the cooling airflow in each channel, and the pipeline connected to the cooling liquid channel is equipped with a throttle valve to achieve precise control of the coolant. The connecting transmission pipeline is used for connecting the various devices of the cooling module. The cooling gas connection and transmission pipeline has three layers: an outer heat insulation layer, a middle moisture-proof layer, and an inner heat insulation layer. The cooling liquid connection and transmission pipeline is made of nylon-like plastic and is used for the transmission of coolant. The end of the coolant transmission pipeline is connected to the box-type coolant circulation device and is fitted with an interference fit to prevent leakage. The clamping module (200) is used to fix the aircraft wingplate welding components during the welding process. It includes clamping columns (201), pressure plates (202), motors and transmission devices (203). The clamping columns (201) are installed on both sides of the integrated tooling table (500), with 9 on each side and a total of 18. The clamping columns (201) are equipped with pressure plates (202). Each clamping column is independently controlled by a corresponding motor and transmission device (203). The motor and transmission device are connected to the central control system (400) to realize the individual adjustment of the clamping force at different positions of the aircraft wingplate welding components. The stress and temperature monitoring module (300) is used to monitor the stress and temperature of various parts of the aircraft wing plate welded components in real time. It includes a stress sensor (301) and an infrared thermometer (302). The stress sensor (301) is installed on the pressure plate (202) to measure the stress changes during the welding process and convert them into electrical signals, and transmit these signals to the central control system (400) for analysis. The infrared thermometer (302) is placed near the integrated tooling table (500) to monitor the temperature of the weld in real time and transmit the obtained data to the central control system (400). The central control system (400) is used to store data and coordinate the control of various modules, including an expert database, a data analyzer, and a central controller. The expert database contains raw materials, welding processes, and temperature and stress field distributions of various aircraft wing plate welding components, serving as a reference for adjusting real-time monitoring data during the welding process. The data analyzer is connected to the stress and temperature monitoring module (300), and transmits the data acquired by the sensors to the central controller in real time after processing, realizing data interaction and sharing between the cooling module and the clamping module. The central controller is connected to the cooling module and the clamping module, and by analyzing the real-time detected data and using the data stored in the expert database as a reference, adjusts the parameters of the cooling module and the clamping module to achieve automatic control of the temperature and stress fields during the welding process. An integrated tooling table (500) is used to assemble various modules and devices. The upper part is uniformly coated with a heat-conducting medium to increase the heat exchange efficiency and contact area between the tooling table and the aircraft wing welding components. During the welding process, the heat is quickly carried away to control stress and deformation.

2. The multi-system collaborative stress relief and straightening device for independently controlled zoned control of welded components of aircraft wing plates according to claim 1, characterized in that, The central control system is connected to the cooling module and the clamping module. Based on real-time monitoring of temperature and stress field data during welding, it controls the execution state of the central controller in real time, thereby achieving independent control of the cooling system and the clamping system. The central control system incorporates algorithms and logic. Through data sharing between the cooling module and the clamping module, the central controller uses a PID controller algorithm to calculate the outputs of the clamping and cooling modules, collaboratively controlling the clamping force and cooling air flow rate. The formula is as follows: ； Where u(t) represents the controller output, e(t) represents the deviation, i.e., the difference between the expected value and the actual value, and K p K i K d These represent the proportional, integral, and differential coefficients, respectively.

3. The multi-system collaborative stress relief and straightening device for independently controlled zoned control of welded components of aircraft wing plates according to claim 1, characterized in that, The data in the expert database comes from previous simulations of temperature, stress, and deformation during welding under different materials, thicknesses, processes, and welding parameters. Experimental studies were also conducted to verify the simulation results, correct and improve the model and simulation process. Based on the improved model and simulation method, the temperature-stress field correspondence was established, the flow rates of cooling gas and coolant to reduce the welding stress field under real-time temperature distribution were calculated, and the clamping force distribution data of the clamping module required under real-time stress distribution was calculated. In this way, a database of temperature-stress-clamping force correspondence was established, which was imported into the central controller and updated in real time on the display.

4. The multi-system collaborative stress relief and straightening device for independently controlled zoned control of welded components of aircraft wing plates according to claim 1, characterized in that, The cooling gas columnar pipes are adjusted according to the actual welding conditions. When high-power laser welding is performed, the number of cooling gas pipes near the weld seam is increased, and the stress reduction effect is enhanced by increasing the feedback frequency of the switching valve. When laser oscillation welding is performed, stress and deformation are controlled by designing cooling gas pipes near the oscillation path.

5. The multi-system collaborative stress relief and straightening device for independently controlled zoned control of welded components of aircraft wing plates according to claim 1, characterized in that, During spot welding and formal welding, which are performed for fixation, the type of coolant is adjusted.

6. The multi-system collaborative stress relief and straightening device for independently controlled zoned control of welded components of aircraft wing plates according to claim 1, characterized in that, After welding, the clamping columns are used to maintain the shape by stress release. Post-weld shape maintenance refers to increasing the clamping pressure of each clamping column by 500-1000N after welding, under the clamping force distribution at the time of welding completion, and fixing the aircraft wing plate welded components for 12-24 hours. Under restraint conditions, the residual stress of the aircraft wing plate welded components is released to control deformation.

7. The multi-system collaborative stress relief and straightening device for independently controlled zoned control of welded components of aircraft wing plates according to claim 1, characterized in that, The derivation formula for stress is: ； Where σ is the stress (Pa), W is the tensile or compressive load (kg), and A is the cross-sectional area under load (mm²). 2 ).

8. A multi-system collaborative stress relief and straightening method for independently controlled zoned welding components of aircraft wingplates, applied to the multi-system collaborative stress relief and straightening device for independently controlled zoned welding according to any one of claims 1-7, for achieving independent and precise control of cooling channels and clamping forces in different regions, and maximizing control of welding stress and post-weld deformation of aircraft wingplate welding components, characterized in that... include: Pre-welding parameter adjustment preparation involves retrieving the type of cooling liquid, cooling liquid flow rate, type of cooling gas, and cooling gas flow rate required for spot welding and formal welding under the combined parameters, and determining the combined coordination mode of cooling gas and clamping device. Spot welding is performed on the components used to fix the aircraft wing plates. After spot welding is completed, the coolant in the coolant pipes and the cooling gas behind the cooling pipes are evacuated. During the formal welding process, the temperature and stress detection module monitors the temperature and stress distribution in different areas of the weldment in real time and transmits the data to the central controller of the central control system. The central controller automatically obtains the adjustment strategies for the coolant flow rate, cooling gas flow rate, and clamping force distribution of the cooling module and clamping module by comparing with the expert database, and transmits the commands to the cooling module and clamping module respectively to adjust the temperature field and stress field of the welding in real time. The three systems work together until the welding is completed, and together achieve the purpose of reducing or even eliminating stress and straightening. Post-weld shape retention is achieved by continuously clamping the welded aircraft wing components with pressure plates, thereby releasing post-weld stress and controlling deformation of the workpiece.

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