A mobile tooling system for aircraft wing pulsing production and interfacing method

Abstract

The application relates to a movable tool system for wing pulsation production of an airplane and an interface method, and belongs to the technical field of aviation manufacturing tools. The movable tool system comprises a supporting mechanism, a moving mechanism, a shape-keeping mechanism and a suspension mechanism. The supporting mechanism comprises a main jig and two rows of bottom end positioning components, a containing cavity is formed between the two rows of bottom end positioning components, the main jig is provided with a positioning fitting part, and the main jig is installed with a wing framework. The moving mechanism comprises multiple groups of moving components distributed in the containing cavity, and the moving components drive the main jig to move. The shape-keeping mechanism comprises a shape-keeping jig, a lifting ring, shape-keeping positioning components and shape-keeping clamping components which are all arranged on the shape-keeping jig, the lifting ring is arranged on the top of the shape-keeping jig, the shape-keeping positioning components are matched with the positioning fitting part, and the shape-keeping clamping components clamp a wing skin. The suspension mechanism comprises a connecting frame and multiple groups of suspension components, the connecting frame is in a U shape and is arranged on the main jig in a covering mode, the suspension components are distributed at two ends of the connecting frame and are used for supporting the lifting ring. The application has the effects of improving the assembly flexibility and turnover efficiency of the wing.

Description

Technical Field

[0001] This application relates to the field of tooling technology in aerospace manufacturing, and in particular to a movable tooling system and interface method for producing aircraft wing pulsations. Background Technology

[0002] In the field of aerospace manufacturing, wing assembly is a crucial link in aircraft manufacturing, and its technological development has a vital impact on the entire aerospace industry. The assembly of medium and large-sized unmanned aerial vehicles (UAVs) occupies an important position in the industry's development, and the quality of its assembly processes directly affects the production quality and capacity of the UAVs.

[0003] Currently, the assembly of medium and large-sized UAVs generally adopts a fixed-station assembly process, which relies on a rigid connection between a traditional jig and the foundation. The traditional jig plays a supporting and positioning role in the wing assembly process, ensuring that each wing component is in the correct position during assembly.

[0004] However, the fixed-station assembly process relies on the rigid connection between the traditional jig and the foundation, resulting in poor tooling flexibility and difficulty in adapting to the assembly requirements of different wing models. At the same time, this fixed production layout leads to low product turnover efficiency and difficulties in human-machine collaboration. During peak production periods, the proportion of non-value-added labor hours caused by station-based production is too high, which seriously restricts the increase in production capacity. Summary of the Invention

[0005] To improve the flexibility and turnaround efficiency of wing assembly, this application provides a movable tooling system and interface method for the production of aircraft wings in a pulsating manner.

[0006] Firstly, the movable tooling system for producing aircraft wing pulsation data provided in this application adopts the following technical solution:

[0007] A movable tooling system for producing pulsed aircraft wings includes: a support mechanism comprising a main frame and two rows of bottom positioning components, the two rows of bottom positioning components being disposed at the bottom of the main frame and spaced apart to form a receiving cavity between them; the bottom positioning components being used to mate with a positioning structure set on the ground; the main frame being provided with positioning mating parts and used to install the wing frame; a moving mechanism comprising multiple sets of moving components distributed in the receiving cavity; the moving components being used to support the main frame and drive the main frame to move; and a shape-holding mechanism. The conformal fitting mechanism includes a conformal fitting frame, a lifting ring, a conformal fitting positioning component, and a conformal fitting clamping component. The lifting ring is located on the top of the conformal fitting frame. The conformal fitting positioning component and the conformal fitting clamping component are both located on the conformal fitting frame. The conformal fitting positioning component corresponds to and positions the positioning mating part. The conformal fitting clamping component is used to clamp the wing skin. The conformal fitting frame is used to cooperate with the main conformal fitting frame to assemble the wing skin with the wing skeleton. The suspension mechanism includes a connecting frame and multiple sets of suspension components. The connecting frame is U-shaped and covers the upper end of the main conformal fitting frame. The multiple sets of suspension components are distributed at both ends of the connecting frame. Each suspension component includes a support plate and a support... The system comprises a support column, a rotating bracket, an actuating component, a locking component, a telescopic pushing component, and a limiting component. The support plate is mounted on the connecting frame. One end of the support column is connected to the support plate, and the other end extends away from the support plate. The support column supports the lifting ring and has a through-hole groove. The rotating bracket is located on one side of the support column, with its first end connected to the support plate. The middle part of the actuating component is rotatably connected to the second end of the rotating bracket, and the first end of the actuating component slides into the through-hole groove. The fixed end of the telescopic pushing component is located on the side of the rotating bracket away from the support column. The support plate is fixedly connected to the telescopic pusher. The telescopic end of the telescopic pusher selectively abuts against the first end of the actuating member. The telescopic pusher is used to push the first end of the actuating member to make the actuating member rotate in the forward direction. The locking member is provided at the second end of the actuating member. When the lifting ring pushes the first end of the actuating member to rotate in the reverse direction, the locking member is used to prevent the lifting ring from disengaging from the support column. The limiting member is movably provided in the mounting groove of the support plate. The telescopic end of the telescopic pusher cooperates with the limiting member. The limiting member is used to selectively engage with the first end of the actuating member. The extension of the telescopic pusher is used to drive the limiting member to release the limiting of the lifting ring.

[0008] By adopting the above technical solution, the two rows of bottom positioning components in the support mechanism are located at the bottom of the main frame and spaced apart to form a receiving cavity. The bottom positioning components cooperate with the positioning structure set on the ground to accurately position the main frame, ensuring the installation accuracy of the tooling system. Multiple sets of moving components of the moving mechanism are distributed in the receiving cavity, which can stably support the main frame and drive the main frame to move, realizing the flexible transfer of the tooling system between different workstations, improving assembly flexibility and production efficiency. The positioning mating parts on the main frame cooperate with the conforming positioning components of the conforming mechanism, providing a basis for the accurate mating of the conforming frame. The wing skeleton is installed on the main frame, and the conforming clamping components clamp the wing skin. The conforming frame in the conforming mechanism cooperates with the suspension mechanism through the lifting ring. The conforming positioning components and the positioning mating parts of the main frame are accurately positioned, so that the wing skin on the conforming frame and the wing skeleton on the main frame are assembled together, ensuring clamping effect and assembly accuracy. The connecting frame of the suspension mechanism is U-shaped and installed on the upper end of the main frame. The suspension components at both ends can reliably support the lifting rings of the form-forming frame. The telescopic pusher can push the actuating component to rotate forward, thereby actuating the lifting ring, so that the lifting ring can easily detach from the support column, facilitating the disassembly of the form-forming frame. When installing the lifting ring, it can push the actuating component to rotate in the reverse direction. The locking component restricts the lifting ring from detaching from the support column when the actuating component rotates in the reverse direction, thus fixing the lifting ring. The limiting component cooperates with the telescopic pusher and can selectively engage with the first end of the actuating component. The extension of the telescopic pusher causes the limiting component to release the limit, allowing the actuating component to rotate forward, thereby making it easy to push out the lifting ring. The retraction of the telescopic pusher resets the limiting component. During the process of the lifting ring being fitted onto the outer circumference of the support column, it can push the actuating component to rotate in the opposite direction, thereby enabling the first end of the actuating component to push the upper end of the limiting component, thus allowing the limiting component to limit the first end of the actuating component. When the telescopic pusher is not extended, the limiting component can maintain its limiting effect on the first end of the actuating component, and the locking component can maintain its locking effect on the lifting ring, thus achieving reliable installation of the lifting ring and flexible control of the rotation of the actuating component. This facilitates the installation and disassembly of the formwork frame, while also reducing the problems of reduced installation accuracy, installation stability, and reliability caused by the detachable design.

[0009] Optionally, the telescopic pusher has a pusher at its telescopic end, and the limiting member includes an elastic part, a movable wedge, and a limiting block. The movable wedge is slidably disposed in the mounting groove. The two ends of the elastic part are respectively connected to the bottom of the mounting groove and the movable wedge. The pusher is used to push the inclined surface of the movable wedge. The limiting block is disposed at the end of the movable wedge away from the elastic part. The limiting block is used to selectively limit the actuating member. When the telescopic end of the telescopic pusher extends, it compresses the elastic part, causing the limiting block to release the limiting of the actuating member. The telescopic end of the telescopic pusher pushes the first end of the actuating member to the first side of the limiting block near the support column. When the telescopic end of the telescopic pusher retracts and resets, the limiting block protrudes from the support plate to restrict the forward rotation of the actuating member through the second side of the limiting block.

[0010] By adopting the above technical solution, the pushing part of the telescopic pusher end can push the moving wedge block to slide in the mounting groove, so that the elastic part is compressed or restored. The elastic part provides elastic support for the sliding of the moving wedge block and resets it. When the telescopic pusher extends, the pusher pushes the inclined surface of the moving wedge, compressing the elastic part. This, in turn, causes the limiting block to release the limiting of the actuating member. The telescopic pusher pushes the first end of the actuating member to the first side of the limiting block near the support column, allowing the actuating member to rotate forward to actuate the lifting ring, making it easy for the lifting ring to detach from the support column. During the installation of the lifting ring onto the outer periphery of the support column, the lifting ring can push the first end of the actuating member to rotate in the opposite direction. At the same time, the telescopic pusher retracts and resets, and the elastic part pushes the moving wedge to reset, causing the limiting block to protrude from the support plate. The first end of the actuating member can also push the limiting block towards the bottom of the mounting groove to compress the elastic part. Thus, the limiting block positions the first end of the actuating member on the second side of the limiting block away from the support column, restricting the forward rotation of the actuating member. At this time, the locking part limits the lifting ring, ensuring that the lifting ring will not detach from the support column when stable installation is required, thus ensuring the safety and reliability of the suspension mechanism for the stable suspension and operation of the conformal frame.

[0011] Optionally, the limiting block has a right-angled triangle cross-section, and the inclined surface of the limiting block is located on its first side and faces the support column. When the lifting ring is fitted onto the support column, it is used to cause the actuating member to rotate in the opposite direction and push the inclined surface of the limiting block towards the bottom of the mounting groove until the first end of the actuating member passes over the limiting block and reaches the second side of the limiting block. The first end of the actuating member abuts against the limiting block, which is used to restrict the second end of the actuating member from rotating forward away from the clearance groove.

[0012] By adopting the above technical solution, the limiting block has a right-angled triangular cross-section with its inclined surface facing the support column. When the lifting ring pushes the actuating component to rotate in the opposite direction, the first end of the actuating component can push the inclined surface of the limiting block, causing the limiting block to move towards the bottom of the mounting groove. After the first end of the actuating component passes the limiting block, the limiting block returns to its original position and protrudes from the support plate, restricting the second end of the actuating component from rotating forward away from the clearance groove. This achieves the limiting of the actuating component, restricting its forward rotation and preventing the lifting ring from detaching from the support column, thereby preventing the lifting ring from accidentally detaching from the support column and ensuring the stability and reliability of the suspension mechanism during operation. When it is necessary for the actuating component to rotate forward, the telescopic pusher pushes the limiting block towards the bottom of the mounting groove, releasing the limiting effect on the first end of the actuating component. The telescopic pusher then pushes the first end of the actuating component, allowing it to rotate forward, facilitating the lifting ring to detach from the support column and achieving quick disassembly.

[0013] Optionally, the support column is provided with a protrusion on its outer periphery. The side of the protrusion away from the support plate is used to abut against the lifting ring. The protrusion is spaced apart from the support plate to limit the minimum distance between the lifting ring and the support plate.

[0014] By adopting the above technical solution, the protrusions on the outer periphery of the support column are used to abut and support the lifting ring, limiting the position of the lifting ring on the support column; the protrusions are spaced apart from the support plate, which can limit the minimum distance between the lifting ring and the support plate, so that the lifting ring is in a suitable position, and thus the first end of the actuating component can smoothly actuate the lifting ring, making it easy for the lifting ring to detach from the support column, ensuring the smooth suspension and detachment operation of the formwork frame.

[0015] Optionally, the shape-holding mechanism includes a pressurizing component, which includes an inflatable rubber strip, an inflatable connector, and a receiving frame. The shape-holding frame has a groove, and the receiving frame is disposed in the groove. One end of the receiving frame is open, and the inflatable rubber strip is disposed in the receiving frame. One end of the inflatable connector is connected to the inflatable rubber strip, and the other end of the inflatable connector is used to connect to the inflation drive structure. The wing skin is disposed at the opening of the receiving frame, so that the inflatable rubber strip pressurizes the wing skin installed on the shape-holding frame after inflation.

[0016] By adopting the above technical solution, the pressurizing component in the conformal molding mechanism has its receiving frame set within the groove of the conformal molding frame, which can protect and position the inflatable rubber strip. The inflatable rubber strip is located within the receiving frame. When the inflation connector connects to the inflation drive structure and inflates the rubber strip, the rubber strip expands. Since the wing skin is located at the opening of the receiving frame, the expanded rubber strip can pressurize the wing skin installed on the conformal molding frame, making the wing skin and wing frame more reliably connected and ensuring the assembly quality of the wing skin and frame.

[0017] Optionally, the bottom positioning component includes a first positioning element, a second positioning element, and a third positioning element. The first column of bottom positioning components consists of the first positioning element, the second positioning element, and the third positioning element in sequence, and the arrangement order of the second column of bottom positioning components is the opposite of that of the first column of bottom positioning components.

[0018] By adopting the above technical solution, the bottom positioning assembly includes a first positioning component, a second positioning component, and a third positioning component arranged in a specific order, with the two rows of bottom positioning components arranged in opposite directions. This layout allows the bottom positioning components to precisely cooperate with the positioning structure set on the ground, flexibly adapting to different positioning requirements. Furthermore, the reverse arrangement improves stability, thereby ensuring the stability and accuracy of the entire tooling system during ground positioning. This, in turn, ensures precision during wing assembly, laying the foundation for high-precision wing assembly.

[0019] Optionally, the first positioning element, the second positioning element, and the third positioning element are respectively a floating zero-point positioner, a zero-point positioner, and a cup-cone positioner.

[0020] By adopting the above technical solutions, the zero-point positioner can achieve a precise positioning reference, providing accurate initial positioning for the entire tooling system; the floating zero-point positioner can adaptively compensate for errors, and can adjust for minor deviations during the positioning process, making the positioning more accurate; the cup cone positioner can play a role in auxiliary positioning and stable support, enhancing the stability of positioning. When used together, the three can achieve rapid and accurate positioning, ensuring the assembly accuracy of the wing frame and wing skin.

[0021] Optionally, the main frame is provided with a main locator for clamping the wing frame. The conforming mechanism is provided in two sets, which are respectively installed on both sides of the wing frame. The side of the conforming frame closer to the wing frame is used to clamp the wing skin to assemble the wing skin with the wing frame.

[0022] By adopting the above technical solution, the main locator on the main frame can clamp the wing skeleton to ensure that the wing skeleton is fixed in position during the assembly process; two sets of conforming mechanisms are respectively installed on both sides of the wing skeleton, and the conforming frame of the conforming mechanism can clamp the wing skin on the side closer to the wing skeleton, which can accurately fit the wing skin and the wing skeleton, realize the efficient assembly of the wing skeleton and the wing skin, and ensure the assembly quality of the wing.

[0023] Optionally, it also includes a grating displacement sensor, which is detachably mounted on the main frame and is used to monitor the deformation of the support mechanism in real time.

[0024] By adopting the above technical solution, the grating displacement sensor is detachably mounted on the main frame, enabling real-time monitoring of the deformation of the support mechanism during the operation of the tooling system. This facilitates the timely detection of minute deformations in the support mechanism caused by bearing the wing, preventing deformation accumulation from affecting the wing assembly accuracy and ensuring the wing assembly quality. Simultaneously, the detachable mounting method allows the grating displacement sensor to be easily removed from the main frame when not in use or when replacement or maintenance is required, improving the convenience and flexibility of equipment maintenance.

[0025] Secondly, the interface method of the movable tooling system for producing aircraft wing pulsation provided in this application adopts the following technical solution:

[0026] An interface method for a movable tooling system used in the production of aircraft wing pulses is disclosed. The method includes: tooling transfer, where a support mechanism is moved to a preset position via a moving mechanism, and a bottom positioning component engages with a positioning and mating structure on the ground; wing frame clamping, where the wing frame is clamped onto the main frame; skin clamping, where the skin is positioned and connected to one side of a conformal frame; assembly, where the conformal frame is hoisted to one side of the main frame, positioning and connecting the conformal frame to the main frame, and assembling the skin with the wing frame; pressurization and holding, where air is inflated into the inflatable rubber strip to reliably connect the skin to the wing frame; and transfer to the next workstation, where the support mechanism is moved to the next workstation via the moving mechanism, and the bottom positioning component re-engages with another set of positioning and mating structures on the ground.

[0027] By adopting the above technical solutions, in the tooling transfer step, the moving mechanism can drive the support mechanism to move, so that the bottom positioning component can be accurately positioned with the ground positioning structure, providing an accurate foundation for subsequent operations; the wing frame clamping step can firmly clamp the wing frame onto the main frame, ensuring its accurate position; the skin clamping step positions and connects the skin to one side of the conformal frame, ensuring the correct placement of the skin; the assembly step positions and connects the conformal frame with the main frame, realizing the assembly of the skin and the wing frame; the pressurization and holding step inflates the inflatable strips to reliably connect the skin and the wing frame, ensuring assembly quality; after the assembly at this station is completed, the moving mechanism drives the support mechanism and the necessary structures such as the wing frame and skin on it to the next station, and once again uses the bottom positioning component to cooperate with the ground positioning at the next station, adapting to pulsed production, realizing rapid flow between stations, shortening working time, and improving production cycle.

[0028] In summary, this application includes at least one of the following beneficial technical effects:

[0029] 1. Precise positioning ensures assembly quality: The bottom positioning component adopts a combination structure of floating zero-point positioner, zero-point positioner and cup cone positioner, which can achieve rapid and accurate positioning, adaptive error compensation, and ensure the assembly accuracy of wing frame and wing skin.

[0030] 2. Adapt to pulsating production and improve efficiency: Multiple sets of moving components of the moving mechanism are distributed in the receiving cavity, supporting and driving the main frame to move, adapting to pulsating production lines, realizing rapid flow between stations, and simplifying the positioning and clamping process of each link, shortening working time and improving production cycle.

[0031] 3. Stable structure and reliable load-bearing capacity: The main frame forms a rigid load-bearing body, and the bottom positioning components are scientifically distributed to ensure structural stability during assembly and storage, avoiding deformation that could affect accuracy;

[0032] 4. Excellent shape retention and pressurization effect: The shape retention mechanism is equipped with a pressurization component. After the inflatable rubber strip is inflated, it pressurizes the wing skin, so that the skin is reliably connected to the wing frame;

[0033] 5. Convenient hoisting of the formwork frame: The suspension mechanism can easily place the formwork frame on the main frame. The telescopic push component and the limiting component cooperate to allow the lifting ring to detach or be locked to the support column;

[0034] 6. Real-time deformation monitoring: By detachably installing a grating displacement sensor on the main frame, the deformation of the support mechanism can be monitored in real time. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the hidden suspension mechanism of a movable tooling system for producing aircraft wing pulsation according to an embodiment of this application.

[0036] Figure 2 This is a schematic diagram of the suspension mechanism assembly according to an embodiment of this application.

[0037] Figure 3 This is a schematic diagram of the distribution of the bottom positioning components in an embodiment of this application.

[0038] Figure 4 This is an exploded view of the hidden suspension mechanism of the movable tooling system for producing aircraft wing pulsation according to an embodiment of this application.

[0039] Figure 5 This is a schematic diagram of a mobile component according to an embodiment of this application.

[0040] Figure 6 This is a schematic diagram of the conforming mechanism according to an embodiment of this application.

[0041] Figure 7 This is a schematic diagram of the conformal mechanism and the wing skin assembly according to an embodiment of this application.

[0042] Figure 8yes Figure 7 A schematic diagram of the cross-section at point AA.

[0043] Figure 9 This is a schematic diagram of the suspension mechanism according to an embodiment of this application.

[0044] Figure 10 This is a schematic diagram of a suspension assembly according to an embodiment of this application.

[0045] Figure 11 This is a front view of the suspension assembly with the lifting ring installed according to an embodiment of this application.

[0046] Figure 12 yes Figure 11 The cross-sectional view at point BB.

[0047] Explanation of reference numerals in the attached figures:

[0048] 100. Wing skin;

[0049] 1. Support mechanism; 11. Main frame; 111. Main positioner; 12. Bottom positioning assembly; 121. First positioning component; 122. Second positioning component; 123. Third positioning component; 13. Receiving cavity;

[0050] 2. Moving mechanism; 21. Moving component;

[0051] 3. Shaping mechanism; 31. Shaping frame; 311. Groove; 32. Lifting ring; 33. Shaping positioning component; 34. Shaping clamping component; 341. Pneumatic clamping cylinder; 342. Vacuum suction cup; 35. Pressurization component; 351. Inflatable rubber strip; 352. Inflatable connector; 353. Receiving frame;

[0052] 4. Suspension mechanism; 41. Connecting frame; 42. Suspension assembly; 421. Support plate; 4211. Mounting groove; 422. Support column; 4221. Clearance groove; 4222. Protrusion; 423. Rotating bracket; 424. Actuating component; 425. Locking component; 426. Telescopic pushing component; 4261. Pushing part; 427. Limiting component; 4271. Elastic part; 4272. Moving wedge; 4273. Limiting block. Detailed Implementation

[0053] The following is in conjunction with the appendix Figure 1 - Appendix Figure 12 This application will be further described in detail below. In this embodiment, unless otherwise specified, "connection", "linking", and "fixing" are interpreted broadly, including fixed connection, detachable connection, connection to form an integral structure, mechanical connection, electrical connection, direct connection, indirect connection through an intermediary, internal connection, and interaction between two components, etc., and can be understood according to the specific circumstances.

[0054] In this application, unless otherwise expressly specified and limited, "above" or "below" a second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, in the description of this embodiment, terms such as "above," "below," "left," and "right," etc., are based on the orientation or positional relationships shown in the accompanying drawings and are used only for ease of description and simplification of operation. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Unless otherwise stated, directional terms such as "inner" and "outer" used in this application refer to the outline of the corresponding component itself.

[0055] like Figure 1 and Figure 2 As shown, in a first aspect, this application discloses a movable tooling system (hereinafter referred to as the "tooling system") for the production of aircraft wing pulses. The tooling system includes a support mechanism 1, a moving mechanism 2, a shape-maintaining mechanism 3, a suspension mechanism 4, and a grating displacement sensor (not shown in the figure). By adopting a collaborative operation scheme of the support, moving, shape-maintaining, and suspension mechanisms 4, it achieves the effect of precise and efficient assembly of the wing skin 100 of the UAV wing with the wing frame and flexible movement of the tooling.

[0056] The tooling system comprises several components: a support mechanism 1 for mounting the wing frame and positioning it on the ground, providing a stable foundation and precise positioning; a moving mechanism 2 supporting the main frame 11 of the support mechanism 1 and moving it, allowing for flexible tooling movement; a shape-holding mechanism 3 clamping and holding the wing skin 100 in place, cooperating with the main frame 11 to achieve rapid and precise assembly of the wing skin 100 and the wing frame; a suspension mechanism 4 for convenient support and release of the shape-holding frame 31; and a grating displacement sensor, such as a grating sensor, detachably mounted on the main frame 11 for real-time monitoring of the deformation of the support mechanism 1, ensuring stability and precision during assembly. The various mechanisms within this tooling system work together to achieve the beneficial effects of precise positioning, efficient assembly, flexible movement, and real-time monitoring of the deformation of the support mechanism 1.

[0057] like Figure 1 and Figure 2As shown, the support mechanism 1 includes a main frame 11 and two rows of bottom positioning components 12. The main frame 11 consists of longitudinal beams, crossbeams, and support members. The crossbeams are arranged along the spanwise direction of the wing, and the longitudinal beams are arranged along the chord direction of the wing and welded perpendicularly to the crossbeams. The support members are fixedly connected to the longitudinal beams by welding. The main frame 11 can be made of Q345B low-alloy high-strength steel. This structural design can enhance the stability and load-bearing capacity of the main frame 11. After welding, the main frame 11 undergoes aging treatment to eliminate internal stress. Key positioning components are made of 45# steel with heat treatment. The tooling system has detachable grating displacement sensors installed at key positions to monitor the deformation of the tooling during movement and operation in real time.

[0058] The main frame 11 is equipped with positioning fittings and main positioners 111 for positioning the leading-edge spars, trailing-edge spars, wing ribs, and wing skin 100 of the wing. Specifically, main positioners 111 are installed on all four sides of the main frame 11, and the main positioners 111 are used to clamp the wing skeleton. The main positioners 111 can be selected from suitable existing structures as needed, such as wing skeleton positioners, positioning parts and clamping parts for aircraft assembly jigs, etc., as long as they can achieve the positioning and precise clamping of the wing skeleton. In this tooling system, a laser tracker target ball can also be set on the main frame 11 as a global calibration reference; the specific structure can be selected from existing technologies.

[0059] like Figure 1 , Figure 2 and Figure 3 As shown, the main frame 11 has two types of support structures fixed to its lower part: positioning legs and storage legs. The tops of both types of legs jointly support the rectangular frame. Columns are symmetrically arranged on the rectangular frame as longitudinal beams, and diagonal braces are added between the columns and the rectangular frame as support members to improve structural stability. I-beam crossbeams are mounted on the tops of the columns, forming the rigid load-bearing main body of the main frame 11. The storage legs only serve the function of storing the tooling system, have no positioning devices, and are evenly distributed below the rectangular frame.

[0060] Two rows of bottom positioning components 12 are located at the bottom of the positioning legs of the main frame 11, and the two rows of bottom positioning components 12 are spaced apart, thereby forming a receiving cavity 13 between the two rows of bottom positioning components 12. The bottom positioning component 12 includes a first positioning element 121, a second positioning element 122, and a third positioning element 123. One row of bottom positioning components 12 consists of two first positioning elements 121, one second positioning element 122, and one third positioning element 123 in sequence. The arrangement order of the other row of bottom positioning components 12 is the opposite of the first row to improve stability. The first positioning element 121, the second positioning element 122, and the third positioning element 123 are a floating zero-point locator, a zero-point locator, and a cup-cone locator, respectively. The zero-point locator has high positioning accuracy and can ensure the precise positioning of the main frame 11 with the ground; the floating zero-point locator can adaptively compensate for errors and improve the flexibility of positioning; the cup-cone locator can play a role in auxiliary positioning and support. These positioning components work in conjunction with the corresponding positioning structures set on the ground to ensure the stability and accurate positioning of the main frame 11 on the ground.

[0061] like Figure 1 , Figure 2 and Figure 3 As shown, the zero-point positioner can be a zero-point positioning system, and the floating zero-point positioner is a structure of the zero-point positioning system. The zero-point positioner can be the LQNC-20, and the floating zero-point positioner can be the FD200-FD200-J-20. The zero-point positioning system constructs an integrated functional system of "positioning-locking-anti-lifting," which can both achieve a rigid connection between the tooling and the ground positioning structure and eliminate assembly gaps through dynamic pressure compensation. It is used to achieve a rigid connection between the tooling system and the ground positioning structure and to prevent lifting; the anti-lifting function prevents the tooling system from lifting during operation. The cup-cone positioner is a commonly used coarse positioning structure, with a tapered pin on one side and a tapered hole on the other, with a taper of 1:50. It is used to achieve positioning of the tooling system and the ground positioning structure, with a repeatability accuracy of ±0.03mm. Since there are existing technologies for zero-point positioners, floating zero-point positioners, and cup cone positioners, they will not be described in detail here. It is understood that the corresponding positioning structure set on the ground and the bottom positioning component 12 are corresponding structures to realize the positioning function. Since they are all existing technologies, they will not be described in detail here. Existing structures can be selected for application.

[0062] like Figure 1 , Figure 2 and Figure 3As shown, in this embodiment, the tooling system has eight positioning legs, symmetrically distributed in two rows of four. The four positioning legs in one row are arranged sequentially from number one to four. Positioning leg number one is equipped with a guide post and a cup-cone locator at its lower end; positioning leg number two is equipped with a zero-point locator at its lower end; and positioning legs number three and four are each equipped with a floating zero-point locator at their lower ends. The locator configuration of the other row of positioning legs is centrally symmetrical with the above arrangement. After the AGV carrying the main frame 11 moves to the designated assembly station, it relies on the positioning legs of the main frame 11 to achieve precise positioning: the guide post of positioning leg number one in one row first inserts into the station's positioning hole to achieve coarse positioning, with the cup-cone locator assisting in positioning; subsequently, the zero-point locator of positioning leg number two completes rigid positioning, and the floating zero-point locators of positioning legs number three and four adaptively compensate for assembly errors, ensuring the horizontal stability of the main frame; the other row of positioning legs operates synchronously according to the centrally symmetrical positioning logic, while the storage legs only play an auxiliary support role and do not participate in positioning.

[0063] like Figure 1 , Figure 4 and Figure 5 As shown, after the main frame 11 completes its positioning, the operator uses the main locators 111 on all four sides of the main frame 11 to clamp and fix the wing skeleton from multiple directions, ensuring that the spatial attitude of the wing skeleton meets the assembly accuracy requirements. Specifically, the moving mechanism 2 includes multiple sets of moving components 21, which are distributed in the receiving cavity 13 and are used to support the main frame 11 and move it. The moving components 21 can be AGVs (Automated Guided Vehicles) intelligent handling robots with lifting functions. They have automatic navigation and movement functions and can accurately move the main frame 11 to a designated position according to a preset route. Specifically, the AGV is provided with a first interface, and the main frame 11 is provided with a second interface. The first interface is used to dock with the second interface to realize the connection between the AGV and the main frame 11, so as to improve reliability. The application of the mobile component 21 enables the tooling system to adapt to the aircraft wing pulse production line. With AGV carrying and transfer as the core flow method, the efficient assembly of the wing is achieved through the step-by-step operation of "positioning-clamping-shaping". This improves the flow efficiency between different workstations during the assembly process, thereby increasing the assembly efficiency and making the tooling system more suitable for the aircraft wing pulse production line.

[0064] like Figure 1 , Figure 2 and Figure 6As shown, specifically, the conformal fitting mechanism 3 includes a conformal fitting frame 31, a lifting ring 32, a conformal fitting positioning component 33, a conformal fitting clamping component 34, and a pressure component 35. The lifting ring 32 is located on the top of the conformal fitting frame 31, facilitating hoisting by the suspension mechanism 4. Both the conformal fitting positioning component 33 and the conformal fitting clamping component 34 are located on the conformal fitting frame 31. The conformal fitting positioning component 33 corresponds to and engages with the positioning mating parts on the main conformal fitting frame 11, ensuring precise alignment between the conformal fitting frame 31 and the main conformal fitting frame 11. The conformal fitting positioning component 33 may include several positioners, the type of which is not limited, including but not limited to zero-point positioners. The positioning mating parts are structures that cooperate with the positioners to achieve positioning. The conformal fitting clamping component 34 is used to clamp the wing skin 100, and can employ pneumatic grippers, hydraulic grippers, etc., providing sufficient clamping force to ensure that the wing skin 100 does not move during assembly. Specifically, the conformal clamping assembly 34 includes a vacuum suction cup 342 and a pneumatic clamping cylinder 341. The vacuum suction cup 342 adsorbs the wing skin 100, and the pneumatic clamping cylinder 341 clamps and positions the wing skin 100 onto the conformal frame 31. This allows the conformal frame 31 to align with the wing skeleton through its assembly with the main conformal frame 11. The pneumatic clamping cylinder 341 can be an existing structure, such as a piston cylinder in a clamping device.

[0065] In this embodiment, the conformal frame 31 is mounted on both sides of the main frame 11. Its connection to the main frame 11 is achieved through multiple sets of conformal positioning components 33. These components include, but are not limited to, zero-point locators, cup cone locators, floating zero-point locators, and guide posts. For example, a zero-point locator can be installed at each of the two diagonal positions of the conformal frame 31, with a cup cone locator next to each zero-point locator; a floating zero-point locator can be installed at each of the other two diagonal positions of the conformal frame 31; a cup cone locator can be installed at the upper and lower center of the conformal frame 31; and floating zero-point locators can be evenly distributed at the remaining positions. This combination of zero-point locators and floating zero-point locators ensures that the conformal frame 31 is evenly stressed and stably mounted on the main frame. The conformal frame 31 is equipped with multiple clamping plates, and vacuum suction cups 342 are mounted on these plates for adsorbing and fixing the wing skin 100.

[0066] like Figure 6 , Figure 7 and Figure 8As shown, the pressurization assembly 35 includes an inflatable rubber strip 351, an inflation connector 352, and a receiving frame 353. The formwork 31 has a groove 311, the receiving frame 353 is located within the groove 311, and the inflatable rubber strip 351 is located within the receiving frame 353. One end of the inflation connector 352 is connected to the inflatable rubber strip 351, and the other end is used to connect to the inflation drive structure. When air is inflated into the inflatable rubber strip 351, the inflatable rubber strip 351 expands and pressurizes the wing skin 100, ensuring a reliable connection between the wing skin 100 and the wing frame. Specifically, the inflation drive structure can employ an air source, an air source processing triplet, and a solenoid valve structure to control the inflation amount of the inflatable rubber strip 351; the inflatable rubber strip 351 can be an inflatable sealing ring or an airbag; the inflatable rubber strip 351 is located on a retaining plate. The conformal mechanism 3 has two sets, which are respectively installed on both sides of the wing frame. The conformal frame 31 is used to clamp the wing skin 100 on the side closer to the wing frame, so as to realize the assembly of the wing skin 100 and the wing frame.

[0067] like Figure 1 , Figure 6 and Figure 8 As shown, after the wing skin 100 is positioned with the conformal positioning assembly 33 (such as positioning pins) and conformal frame 31, the wing skin 100 is fixed by vacuum suction cup 342 on one side of the clamping plate. The shape characteristics of the conformal frame 31 ensure the shape accuracy of the wing skin 100, providing support for the subsequent assembly of the wing skin 100 with the wing frame. The conformal frame 31 is then hoisted to both sides of the main frame 11 using hooks on the two conformal frames 31. Guide posts on the conformal frame 31 are used to connect and guide with guide sleeves and other guiding structures on the main frame 11. A zero-point locator is then used to achieve precise positioning of the conformal frame 31 and the main frame 11. The floating zero-point locator adaptively compensates for the connection gap, ensuring uniform force distribution and stable side mounting on the conformal frame 31. After being inflated with gas, the inflatable rubber strip 351 further enhances the reliability of the connection between the wing skin 100 and the wing frame. By setting a shape-holding frame 31 that can be separated from the main shape frame 11, the side-mounted shape-holding frame 31 is easy to disassemble and assemble, and the main positioner 111 is adaptable to multiple specifications. The design of the lifting ring 32 and the vacuum suction cup 342 simplifies the operation steps, reduces labor intensity and general cost, and is easy to operate and highly versatile.

[0068] like Figure 1 , Figure 2 and Figure 9 As shown, specifically, the suspension mechanism 4 includes a connecting frame 41 and multiple sets of suspension components 42. The connecting frame 41 is U-shaped and covers the upper end of the main frame 11, and can be connected to the main frame 11 by bolts. The two ends of the U-shape extend vertically. The multiple sets of suspension components 42 are respectively distributed at both ends of the connecting frame 41, so that both ends can be used to suspend the main frame 11, thereby enabling both sides of the wing skeleton to be assembled with the wing skin 100, improving efficiency. In this embodiment, there are four suspension components 42.

[0069] like Figure 10 , Figure 11 and Figure 12 As shown, the suspension assembly 42 includes a support plate 421, a support column 422, a rotating bracket 423, a toggle member 424, a locking member 425, a telescopic pusher member 426, and a limiting member 427.

[0070] like Figure 1 , Figure 10 and Figure 12 As shown, a support plate 421 is connected to a connecting frame 41. One end of a support column 422 is connected to the support plate 421, and the other end extends away from the support plate 421 to support the lifting ring 32. The support column 422 has a clearance groove 4221 extending through both ends. A rotating bracket 423 is located on one side of the support column 422, and the first end of the rotating bracket 423 is connected to the support plate 421. The middle part of the actuating member 424 is rotatably connected to the second end of the rotating bracket 423, so that the first end of the actuating member 424 slides in cooperation with the clearance groove 4221. The fixed end of the telescopic pushing member 426 is located on the side of the rotating bracket 423 away from the support column 422, and its telescopic end is provided with a pushing part 4261. The fixed end of the telescopic pusher 426 is fixedly connected to the support plate 421. The telescopic end of the telescopic pusher 426 selectively abuts against the first end of the actuating member 424. The telescopic pusher 426 pushes the first end of the actuating member 424, causing the first end of the actuating member 424 to be located on the side of the rotation center near the support plate 421 and move towards the clearance groove 4221, i.e., to rotate in the forward direction, so as to assist in actuating the lifting ring 32, making it easier for the lifting ring 32 to disengage from the support column 422. The locking member 425 is provided at the second end of the actuating member 424. During the process of installing the lifting ring 32 onto the support column 422, the lifting ring 32 can push the first end of the actuating member 424 to rotate in the reverse direction, so that the locking member 425 on the second end of the actuating member 424 can rotate to a position that restricts the lifting ring 32 from disengaging from the support column 422. The actuating member 424 and the rotating bracket 423 are rotatably connected by a damping shaft. The damping shaft adopts an existing structure to prevent the actuating member 424 from rotating arbitrarily.

[0071] The limiting member 427 includes an elastic part 4271, a movable wedge 4272, and a limiting block 4273. The support plate 421 is provided with an installation groove 4211. The movable wedge 4272 is slidably disposed in the installation groove 4211. The two ends of the elastic part 4271 are respectively connected to the bottom of the installation groove 4211 and the movable wedge 4272. The limiting block 4273 is disposed at the end of the movable wedge 4272 away from the elastic part 4271. The telescopic end of the telescopic pusher 426 cooperates with the limiting member 427. When the telescopic pusher 426 extends, the pushing part 4261 pushes the inclined surface of the moving wedge block 4272, causing the elastic part 4271 to compress. The limiting block 4273 releases the limiting of the actuating member 424. Furthermore, the telescopic end of the telescopic pusher 426 can push the first end of the actuating member 424 to the first side of the limiting block 4273 near the support column 422. When the telescopic pusher 426 retracts and resets, the limiting block 4273 protrudes from the support plate 421, and the forward rotation of the actuating member 424 can be restricted by the second side of the limiting block 4273. When the lifting ring 32 is fitted onto the support column 422, the lifting ring 32 pushes the first end of the actuating member 424 to rotate in the opposite direction. After the first end of the actuating member 424 passes the limiting block 4273 and reaches the second side of the limiting block 4273, the elastic part 4271 is released from compression, and the limiting block 4273 protrudes from the support plate 421, thereby restricting the forward rotation of the actuating member 424 and preventing the second end of the actuating member 424 from detaching the lifting ring 32 from the support column 422. It can be understood that in the initial state of the suspension assembly 42, the first end of the actuating member 424 is located on the first side of the limiting member 427, so that the lifting ring 32 can push the first end of the actuating member 424 to rotate in the opposite direction during installation.

[0072] like Figure 1 , Figure 10 and Figure 12As shown, the cross-section of the limiting block 4273 is a right-angled triangle, with the inclined surface located on its first side and facing the support column 422. The first end of the actuating member 424 is initially located on the first side of the limiting block 4273 away from the telescopic pusher 426. When the lifting ring 32 is fitted onto the support column 422, the lifting ring 32 pushes the first end of the actuating member 424 to rotate in the opposite direction, which can push the inclined surface of the limiting block 4273, causing the limiting block 4273 to move towards the bottom of the mounting groove 4211, until the first end of the actuating member 424 passes over the limiting block 4273 and reaches the second side of the limiting block 4273. At this time, the first end of the actuating member 424 abuts against the second side of the limiting block 4273 and is locked by the limiting block 4273, which is used to restrict the second end of the actuating member 424 from rotating in the forward direction away from the clearance groove 4221. Thus, the locking member 425 at the second end of the actuating member 424 can restrict the lifting ring 32 from disengaging from the support column 422. Furthermore, a protrusion 4222 is provided on the outer periphery of the support column 422, and the protrusion 4222 is spaced apart from the support plate 421. The lifting ring 32 is sleeved on the side of the protrusion 4222 away from the support plate 421, which is used to abut the lifting ring 32 and limit the minimum distance between the lifting ring 32 and the support plate 421, so that there is a gap between the lifting ring 32 and the support plate 421, so that the first end of the actuating member 424 can actuate the lifting ring 32, thereby making it easier for the lifting ring 32 to detach from the support column 422. When the first end of the actuating member 424 is located on the second side of the limiting block 4273 along the extension direction of the axis of the support column 422, the lifting ring 32 can be located on the side of the protrusion 4222 away from the support plate 421 and the side of the locking member 425 close to the support plate 421. At this time, the lifting ring 32 is sleeved on the outer periphery of the support column 422, and the locking member 425 can prevent the lifting ring 32 from accidentally detaching from the support column 422.

[0073] The distance between the rotation center of the actuating element 424 and the support plate 421 is greater than the minimum distance between the lifting ring 32 and the support plate 421. This allows the lifting ring 32, when installed on the support column 422, to push the first end of the actuating element 424, causing the first end of the actuating element 424 to push the limiting block 4273 towards the bottom of the mounting groove 4211, thus achieving a locking effect. Furthermore, when it is necessary to release the limit, the pushing part 4261 of the telescopic pusher 426 first pushes the limiting member 427 to release the limit. Then, the telescopic end of the telescopic pusher 426 contacts and pushes the first end of the actuating element 424 to rotate forward, so that the actuating element 424 can rotate forward after the limiting member 427 moves towards the bottom of the mounting groove 4211, avoiding interference. The telescopic pusher 426 can be of different types, such as an electric push rod or a hydraulic push rod. Electric actuators offer advantages such as high control precision and fast response speed, making them suitable for scenarios requiring high operational accuracy. Hydraulic actuators, on the other hand, feature high output force, meeting the lifting requirements of heavier conformal frames 31. On the same suspension assembly 42, the protrusion 4222 and the actuating element 424 are circumferentially offset. Actuating elements 424 and similar structures can be installed on both sides of a support column 422, with two sets of actuating elements 424 symmetrically arranged without interference; the specific dimensions can be determined as needed. It is understood that, initially, the first end of the actuating element 424 is located on the side of the limiting block 4273 away from the telescopic pusher 426, so that the actuating element 424 can rotate in the opposite direction when the lifting ring 32 is installed.

[0074] Understandably, the tooling system also includes necessary structures for connection, support, drive, positioning, limiting and control functions to enable the tooling system to operate normally; the shape, size, material and quantity of each part of the tooling system can be determined as needed to achieve the corresponding functions.

[0075] On the other hand, this embodiment also relates to an interface method for a movable tooling system used in aircraft wing pulsation production, applied to the aforementioned tooling system, comprising the following steps:

[0076] S1. Tooling transfer: The moving mechanism 2 moves the support mechanism 1 to a preset position, and the bottom positioning component 12 engages with the positioning structure on the ground. In this step, the moving mechanism 2 can be an AGV (Automated Guided Vehicle), which uses a pre-set navigation system to accurately move the support mechanism 1 to the designated position. The floating zero-point positioner, zero-point positioner, and cup cone positioner in the bottom positioning component 12 closely engage with the corresponding positioning structure on the ground to ensure accurate positioning of the tooling.

[0077] S2. Wing frame clamping: Clamp the wing frame onto the main frame 11. The main locator 111 on the main frame 11 can be a pneumatic chuck or a hydraulic chuck, which can quickly and accurately clamp the wing frame and ensure the stability of the frame during the assembly process.

[0078] S3. Skin clamping: Positioning the wing skin 100 and connecting it to one side of the conformal frame 31. The conformal positioning component 33 and the conformal clamping component 34 on the conformal frame 31 function. The conformal positioning component 33 achieves precise positioning of the wing skin 100 by correspondingly engaging with the positioning mating parts on the main frame 11. The conformal clamping component 34 uses pneumatic or mechanical grippers to firmly clamp the wing skin 100 onto the conformal frame 31.

[0079] S4. Assembly: The conformal frame 31 is hoisted to one side of the main frame 11, positioning and connecting the conformal frame 31 with the main frame 11, thus assembling the wing skin 100 with the wing frame. The suspension assembly 42 of the suspension mechanism 4 supports the conformal frame 31 on one side of the main frame 11. Through the precise cooperation of the positioning fitting and the conformal positioning assembly 33, the conformal frame 31 and the main frame 11 are accurately aligned, thereby assembling the wing skin 100 with the wing frame.

[0080] S5. Pressurization and maintenance: Inflate the inflatable rubber strip 351 to reliably connect the wing skin 100 to the wing frame. The inflation drive structure inflates the inflatable rubber strip 351 through the inflation connector 352. After the inflatable rubber strip 351 expands, it applies uniform pressure to the wing skin 100, ensuring that the wing skin 100 and the wing frame fit tightly together and achieve a reliable connection.

[0081] S6. Transfer to the next workstation. After assembly and pressurization, the moving mechanism 2 is restarted. The moving mechanism 2 moves the support mechanism 1 to the next workstation and repositions it with another new positioning and mating structure on the ground through the bottom positioning component 12. This moves the tooling system with the assembled wing to the next production workstation, preparing for the assembly of the next process, until the entire wing assembly process is completed.

[0082] The implementation principle of this embodiment is as follows: Through the coordinated work of various mechanisms, the tooling system achieves precise and efficient assembly of the wing skin 100 and the wing frame, as well as flexible movement of the tooling, while simultaneously monitoring the deformation of the support mechanism 1 in real time. The support mechanism 1, through its rational structural design and combination of various positioning components, provides stable support and precise positioning; the moving mechanism 2, using the moving component 21, allows the tooling to be flexibly moved according to production needs; the conforming mechanism 3, through the conforming positioning component 33, the conforming clamping component 34, and the pressurizing component 35, ensures the assembly accuracy and reliability of the wing skin 100 and the wing frame; the suspension mechanism 4, through its ingenious mechanical structure, enables convenient hoisting and release of the conforming frame 31; and the grating displacement sensor provides real-time feedback on the deformation of the support mechanism 1, ensuring the stability of the assembly process. This interface method, through a series of orderly steps, achieves efficient assembly of the wing skin 100 and the wing frame, and flexible movement of the tooling system. Each step works closely together, utilizing the functions of each mechanism in the tooling system to ensure the accuracy and stability of the assembly process. This tooling system and method improves assembly quality and production efficiency while reducing labor intensity and production costs.

[0083] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A movable tooling system for producing aircraft wing pulsations, characterized in that, include: The support mechanism (1) includes a main frame (11) and two rows of bottom positioning components (12). The two rows of bottom positioning components (12) are located at the bottom of the main frame (11) and are spaced apart to form a receiving cavity (13) between the two rows of bottom positioning components (12). The bottom positioning components (12) are used to cooperate with the positioning structure set on the ground. The main frame (11) is provided with positioning fitting parts and is used to install the wing frame. The moving mechanism (2) includes multiple sets of moving components (21), which are distributed in the receiving cavity (13). The moving components (21) are used to support the main frame (11) and drive the main frame (11) to move. The conforming mechanism (3) includes a conforming frame (31), a lifting ring (32), a conforming positioning component (33), and a conforming clamping component (34). The lifting ring (32) is located on the top of the conforming frame (31). The conforming positioning component (33) and the conforming clamping component (34) are both located on the conforming frame (31). The conforming positioning component (33) is positioned in accordance with the positioning mating part. The conforming clamping component (34) is used to clamp the wing skin (100). The conforming frame (31) is used to cooperate with the main frame (11) so that the wing skin (100) is assembled with the wing skeleton. The suspension mechanism (4) includes a connecting frame (41) and multiple sets of suspension components (42). The connecting frame (41) is U-shaped and covers the upper end of the main frame (11). The multiple sets of suspension components (42) are distributed at both ends of the connecting frame (41). Each suspension component (42) includes a support plate (421), a support column (422), a rotating bracket (423), a toggle element (424), a locking element (425), a telescopic push element (426), and a limiting element (427). The support plate (421) is mounted on the connecting frame (41). The support column (422) is mounted on the connecting frame (41). One end of the support column (422) is connected to the support plate (421), and the other end of the support column (422) extends away from the support plate (421). The support column (422) is used to support the lifting ring (32). The support column (422) is provided with a clearance groove (4221) that extends through both ends. The rotating bracket (423) is located on one side of the support column (422). The first end of the rotating bracket (423) is connected to the support plate (421). The middle part of the actuating member (424) is rotatably connected to the second end of the rotating bracket (423). The first end of the actuating member (424) is connected to the support plate (421). The telescopic pusher (426) slides in conjunction with the clearance groove (4221). The fixed end of the telescopic pusher (426) is located on the side of the rotating bracket (423) away from the support column (422). The telescopic pusher (426) is fixedly connected to the support plate (421). The telescopic end of the telescopic pusher (426) selectively abuts against the first end of the actuating member (424). The telescopic pusher (426) is used to push the first end of the actuating member (424) to make the actuating member (424) rotate in the forward direction. The locking member (425) is located at the second end of the actuating member (424). The lifting ring... (32) When the first end of the actuating member (424) is pushed to rotate in the opposite direction, the locking member (425) is used to restrict the lifting ring (32) from disengaging from the support column (422). The limiting member (427) is movably disposed in the mounting groove (4211) of the support plate (421). The telescopic end of the telescopic pusher (426) cooperates with the limiting member (427). The limiting member (427) is used to selectively engage with the first end of the actuating member (424). The extension of the telescopic pusher (426) is used to drive the limiting member (427) to release the limiting of the lifting ring (32).

2. The movable tooling system for producing aircraft wing pulsations according to claim 1, characterized in that, The telescopic pusher (426) has a pusher (4261) at its telescopic end. The limiting member (427) includes an elastic part (4271), a movable wedge (4272), and a limiting block (4273). The movable wedge (4272) is slidably disposed in the mounting groove (4211). The two ends of the elastic part (4271) are respectively connected to the bottom of the mounting groove (4211) and the movable wedge (4272). The pusher (4261) is used to push the inclined surface of the movable wedge (4272). The limiting block (4273) is disposed at the end of the movable wedge (4272) away from the elastic part (4271). 3) Used to selectively limit the toggle member (424). When the telescopic end of the telescopic push member (426) extends, it compresses the elastic part (4271), causing the limiting block (4273) to release the toggle member (424) from the limiting block. The telescopic end of the telescopic push member (426) pushes the first end of the toggle member (424) to the first side of the limiting block (4273) near the support column (422). When the telescopic end of the telescopic push member (426) retracts and resets, the limiting block (4273) protrudes from the support plate (421) to restrict the forward rotation of the toggle member (424) through the second side of the limiting block (4273).

3. The movable tooling system for producing aircraft wing pulsations according to claim 2, characterized in that, The limiting block (4273) has a right-angled triangle cross section. The inclined surface of the limiting block (4273) is located on its first side and faces the support column (422). When the lifting ring (32) is fitted onto the support column (422), it is used to make the actuating member (424) rotate in the opposite direction and push the inclined surface of the limiting block (4273) towards the bottom of the mounting groove (4211) until the first end of the actuating member (424) passes over the limiting block (4273) and reaches the second side of the limiting block (4273). The first end of the actuating member (424) abuts against the limiting block (4273) to restrict the second end of the actuating member (424) from rotating forward away from the clearance groove (4221).

4. The movable tooling system for producing aircraft wing pulsations according to claim 1, characterized in that, The support column (422) has a protrusion (4222) on its outer periphery. The side of the protrusion (4222) away from the support plate (421) is used to abut against the lifting ring (32). The protrusion (4222) and the support plate (421) are spaced apart to limit the minimum distance between the lifting ring (32) and the support plate (421).

5. The movable tooling system for producing aircraft wing pulsations according to claim 1, characterized in that, The shape-holding mechanism (3) includes a pressurizing component (35), which includes an inflatable rubber strip (351), an inflatable connector (352), and a receiving frame (353). The shape-holding frame (31) has a groove (311), and the receiving frame (353) is located in the groove (311). One end of the receiving frame (353) is open, and the inflatable rubber strip (351) is located in the receiving frame (353). One end of the inflatable connector (352) is connected to the inflatable rubber strip (351), and the other end of the inflatable connector (352) is used to connect to the inflation drive structure. The wing skin (100) is located at the opening of the receiving frame (353), so that the inflatable rubber strip (351) is inflated and pressurizes the wing skin (100) installed on the shape-holding frame (31).

6. The movable tooling system for producing aircraft wing pulsations according to claim 1, characterized in that, The bottom positioning component (12) includes a first positioning element (121), a second positioning element (122) and a third positioning element (123). The first column of bottom positioning components (12) consists of the first positioning element (121), the second positioning element (122) and the third positioning element (123) in sequence. The arrangement order of the second column of bottom positioning components (12) is the opposite of that of the first column of bottom positioning components (12).

7. The movable tooling system for producing aircraft wing pulsations according to claim 6, characterized in that, The first positioning element (121), the second positioning element (122), and the third positioning element (123) are respectively a floating zero-point positioner, a zero-point positioner, and a cup-cone positioner.

8. The movable tooling system for producing aircraft wing pulsations according to claim 1, characterized in that, The main frame (11) is provided with a main locator (111), which is used to clamp the wing frame. The conforming mechanism (3) is provided in two sets, which are respectively installed on both sides of the wing frame. The conforming frame (31) is used to clamp the wing skin (100) on the side closer to the wing frame so as to assemble the wing skin (100) with the wing frame.

9. The movable tooling system for producing aircraft wing pulsations according to claim 1, characterized in that, It also includes a grating displacement sensor, which is detachably mounted on the main frame (11) and is used to monitor the deformation of the support mechanism (1) in real time.

10. An interface method for a movable tooling system used in aircraft wing pulsation production, characterized in that, The movable tooling system for producing aircraft wing pulsations, as described in any one of claims 1-9, comprises an interface method including: Tooling transfer: the supporting mechanism (1) is moved to the preset position by the moving mechanism (2), and the bottom positioning component (12) is positioned and engaged with the positioning and engaging structure on the ground. Wing frame clamping: The wing frame is clamped onto the main frame (11); Skin clamping, positioning and attaching the skin to one side of the conformal frame (31); Assembly: Hoist the conformal frame (31) to one side of the main frame (11) to position and connect the conformal frame (31) and the main frame (11), so that the skin and the wing frame are assembled. Pressurization is maintained, and air is inflated into the inflatable rubber strip (351) to reliably connect the skin to the wing frame; The support mechanism (1) is moved to the next work station by the moving mechanism (2), and then repositioned and engaged with another set of positioning and engaging structures on the ground by the bottom positioning component (12).

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