A fixture for machining complex surface workpieces in aerospace applications

Abstract

This invention relates to a machining fixture for complex-shaped aerospace workpieces, belonging to the aerospace machining field. The fixture includes a support transmission frame, two sets of opposing flexible clamping modules, and an auxiliary positioning device. The flexible clamping modules are mounted on the support transmission frame, and the auxiliary positioning device is bolted to the base of the support transmission frame. Each flexible clamping module mainly consists of a pin body, a flexible clamping upper housing, and a spring. The pin body partially protrudes from the flexible clamping upper housing; a spring is installed at the lower end of the pin body and fixed in the flexible clamping lower housing. After the pin body slides a certain distance, it can be locked by a self-locking bolt. Space is provided at the track housing of the support transmission frame. This invention is applicable to machining centers and can position and clamp complex-shaped workpieces without damaging their surface, improving machining efficiency.

Description

Technical Field

[0001] This invention relates to a fixture for machining complex surface workpieces in aerospace applications, and relates to the field of aerospace machining. Background Technology

[0002] With the development of the modern aviation industry, in order to meet increasingly stringent aerodynamic performance requirements, the configurations of various complex aerospace surface workpieces are becoming increasingly complex, and the operating conditions are becoming increasingly harsh. Consequently, the difficulty and technological requirements for machining and manufacturing complex surface workpieces are also increasing. Currently, more and more complex surface components are being used in new-generation fighter jets and large civil airliners; aero-engine blades are a typical example of such complex surface components. For the manufacturing process of these complex aerospace surface workpieces, aerospace workpiece fixtures are essential equipment for manufacturing and assembling aerospace parts. The fixture design and manufacturing level of an aerospace company represents its aircraft manufacturing level and is one of the key technologies in aircraft manufacturing. Currently, there are complete dedicated fixtures for specific models and specifications of complex aerospace surface workpieces in the industry. However, under certain size and specification limitations, it is impossible to use a single dedicated fixture to machine and clamp multiple different types or specifications of complex surface workpieces. This affects fixture design, manufacturing time, and materials, thereby increasing product manufacturing costs. Furthermore, while general-purpose fixtures are widely used in the industry, they can only clamp flat surfaces. For the manufacturing process of complex aerospace-grade workpieces, the irregular, curved surfaces of these workpieces mean that using a general-purpose clamping plate with planar contact can easily result in point-to-surface contact. This not only affects clamping quality but can also easily lead to deformation or even cracks due to excessive planar clamping force, resulting in scrap. Secondly, when the workpiece blank to be machined also has a complex surface shape, it is impossible to accurately find the required positioning reference on the complex surface blank. Moreover, it cannot be guaranteed that the positioning position will be accurate every time a general-purpose fixture is used to clamp a complex surface workpiece, which can significantly impact machining quality. Summary of the Invention

[0003] The purpose of this invention is to provide a machining fixture for complex aerospace surface workpieces to solve the problems of poor applicability and machining quality associated with machining complex aerospace surface workpieces, as mentioned in the background art. To achieve the above objective, this invention provides the following technical solution:

[0004] A fixture for machining complex-shaped aerospace workpieces includes a support transmission frame, two sets of oppositely arranged flexible clamping modules, and an auxiliary positioning device. The flexible clamping modules are mounted on the support transmission frame, and the auxiliary positioning device is bolted to the base of the support transmission frame.

[0005] The flexible clamp module mainly consists of an ejector pin body, a flexible clamp upper housing, and a spring. The ejector pin body is partially exposed outside the flexible clamp upper housing. A spring is installed at the lower end of the ejector pin body and is fixed in the flexible clamp lower housing. After the ejector pin body slides a certain distance, it can be locked by a self-locking bolt. Space is left at the track housing supporting the transmission frame.

[0006] One set of flexible clamp modules is fixed to the support transmission frame via the lower housing of the flexible clamp, and another set of flexible clamp modules is fixed to the support transmission frame via the base.

[0007] Furthermore, a spring is installed at the lower end of the ejector pin body, and the spring is fixed in the lower housing of the flexible clamp. After the ejector pin body slides a certain distance, it can be locked by a self-locking bolt. The self-locking bolt leaves a certain space at the track housing of the supporting transmission frame, and can be tightened and loosened using a hex wrench. The lower housing of the flexible clamp in the other flexible clamp module is replaced with a base structure supporting the transmission frame. Other structures and principles are the same as those in the flexible clamp module, so they will not be described in detail.

[0008] The present invention relates to a machining fixture for complex aerospace workpieces, the fixture comprising a support transmission frame, a flexible fixture module, and an auxiliary positioning device.

[0009] The support transmission frame is composed of an upper cover block, a lead screw housing, a base, a track housing, a split lead screw, and a linear bearing seat. The support transmission frame is mechanically connected by positioning pins and bolts, and the support transmission frame is cuboid in shape.

[0010] The flexible clamp module includes a flexible clamp cover plate, an ejector pin body, a flexible clamp upper housing, and a flexible furniture lower housing. Two sets of flexible clamp modules are vertically mounted on the support transmission frame with the ejector pin bodies facing each other.

[0011] The auxiliary positioning device includes positioning blocks A and B, weight structures A and B, an auxiliary positioning base, and positioning pins. The auxiliary positioning base of the auxiliary positioning device is mechanically connected to the base of the supporting transmission frame by bolts.

[0012] In the machining fixture for complex aerospace surface workpieces described in this invention, two support rods in the auxiliary positioning device are respectively installed at specific positions on the auxiliary positioning base. Weight blocks A and B are respectively installed on the support rods, and weight blocks A and B are connected to the support rods via a hole-shaft fit. Weight blocks A and B are mainly used to support positioning blocks A and B, which are locked to the support rods by bolts. By replacing weight blocks A and B with different heights, and thus adjusting the height of positioning blocks A and B, the position of the complex surface workpiece within the overall fixture can be adjusted.

[0013] In the machining fixture for complex aerospace surface workpieces described in this invention, the auxiliary positioning base of the auxiliary positioning device contains a protruding structure B. The protruding structure B cooperates with the groove structure below the base of the support transmission frame to form a slide rail-like structure, so that the support transmission frame can slide along the protruding structure B in the auxiliary positioning device.

[0014] In the machining fixture for complex aerospace surface workpieces described in this invention, the supporting transmission frame includes a lead screw housing and a split lead screw. The split lead screw consists of split lead screw A and split lead screw B, which are connected by bolts. Split lead screw A has a cross-shaped protrusion at its lower end, and split lead screw B has a cross-shaped groove at its upper end. Split lead screw B has a trapezoidal thread structure, and its lower end is interference-fitted with a linear bearing seat. The upper cover is connected to split lead screw A. The linear bearing seat is bolted to the base.

[0015] In the machining fixture for complex aerospace workpieces described in this invention, the split-type lead screw of the supporting transmission frame and the flexible clamping module (structure A) are combined to form a vise-like structure. By rotating the hexagonal countersunk hole on the split-type lead screw A, the flexible clamping module is driven to move up and down within the supporting transmission frame. The flexible clamping cover plate of the flexible clamping module and the track housing of the supporting transmission frame are connected by fastening bolts to form a slide rail structure. This slide rail structure provides auxiliary support and locking function when the flexible clamping module moves up and down within the supporting transmission frame.

[0016] In the machining fixture for complex aerospace surface workpieces described in this invention, the internal structure of the lead screw housing of the supporting transmission frame is a split-type lead screw structure. The split-type lead screw consists of split-type lead screw A and split-type lead screw B, with split-type lead screw B having a trapezoidal thread structure. The upper cover block is connected to split-type lead screw A, and split-type lead screw A and split-type lead screw B are connected by bolts. Split-type lead screw A has a cross-shaped protrusion at its lower end, and split-type lead screw B has a cross-shaped groove at its upper end. The two are connected by bolts, and the lower part of split-type lead screw B is interference-fitted with the linear bearing seat. The linear bearing seat is bolted to the base.

[0017] The beneficial effects of this invention are as follows:

[0018] 1) This invention is applicable to machining centers and can position and clamp complex surface workpieces without damaging their surface, thereby improving machining efficiency. It can clamp different types of complex aerospace surface workpieces under certain size conditions. The overall device is easy to use and install.

[0019] 2) The complex curved surface reference of the aerospace complex surface workpiece can be converted into the regular surface precision reference of the fixture shell of the present invention, which further simplifies the machining process, reduces the machining error caused by insufficient reference accuracy, and improves the machining quality.

[0020] Other features and advantages of the present invention will be described in detail in part in the following detailed description. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall structure of the device for machining complex aerospace surface workpieces according to the present invention.

[0022] Figure 2 This is a side view of the overall device for machining complex aerospace surface workpieces as described in this invention.

[0023] Figure 3 This is a top view of the overall device for machining complex aerospace surface workpieces as described in this invention.

[0024] Figure 4 This is a schematic diagram of the main structure of the support transmission frame device for machining complex aerospace surface workpieces as described in this invention.

[0025] Figure 5 This is a schematic diagram of the main view of the support transmission frame device for machining complex aerospace surface workpieces according to the present invention, viewed in cross-section along the centerline.

[0026] Figure 6 This is a side view of the support transmission frame device for machining complex aerospace surface workpieces as described in this invention.

[0027] Figure 7 This is a top view of the support transmission frame device for machining complex aerospace surface workpieces as described in this invention.

[0028] Figure 8 This is a schematic diagram of the main structure of the flexible fixture module for machining complex aerospace surface workpieces as described in this invention.

[0029] Figure 9 This is a schematic diagram of the main view of the support transmission frame device for machining complex aerospace surface workpieces according to the present invention, viewed in cross-section along the centerline.

[0030] Figure 10 This is a side view of the flexible fixture module for machining complex aerospace workpieces as described in this invention.

[0031] Figure 11 This is a top view of the flexible fixture module for machining complex aerospace surface workpieces as described in this invention.

[0032] Figure 12 This is a schematic diagram of the main structure of the auxiliary positioning device for machining complex aerospace surface workpieces as described in this invention.

[0033] Figure 13 This is a schematic diagram of the auxiliary positioning device for machining complex aerospace surface workpieces according to the present invention, viewed from the front view along the centerline.

[0034] Figure 14 This is a side view of the auxiliary positioning device for machining complex aerospace surface workpieces as described in this invention.

[0035] Figure 15 This is a top view schematic diagram of the auxiliary positioning device for machining complex aerospace workpieces as described in this invention:

[0036] Figure 16 This is a schematic diagram of the isometric view structure of a turbine blade machining fixture for complex aerospace surface workpieces provided in an embodiment of the present invention;

[0037] Figure 17 This is a schematic diagram of the main structure of the device for mounting turbine blades on a machining fixture for complex aerospace surface workpieces, provided in an embodiment of the present invention.

[0038] Figure 18 This is a schematic diagram of the main view along the centerline of the device for mounting turbine blades on a machining fixture for complex aerospace surface workpieces provided in an embodiment of the present invention.

[0039] Figure 19 This is a side view of the device for mounting turbine blades on a machining fixture for complex aerospace surface workpieces, provided in an embodiment of the present invention.

[0040] Figure 20 This is a top view of the device for mounting turbine blades on a machining fixture for complex aerospace surface workpieces, provided in an embodiment of the present invention.

[0041] The diagram includes: 1. Support transmission frame; 2. Flexible clamp module; 3. Auxiliary positioning device; 4. Fastening bolt; 5. Upper cover block; 6. Lead screw housing; 7. Base; 8. Track housing; 9. Split lead screw A; 10. Split lead screw B; 11. Linear bearing seat; 12. Drain bolt; 13. Self-locking bolt; 14. Flexible clamp cover plate; 15. Ejector pin body; 16. Flexible clamp upper housing; 17. Flexible clamp lower housing; 18. Positioning block A; 19. Weight structure A; 20. Auxiliary positioning base; 21. Positioning pin; 22. Support rod; 23. Positioning block B; 24. Weight structure B; 25. Turbine blade. Detailed Implementation

[0042] In order to solve the problems existing in the current technology, such as Figure 1 As shown, the present invention provides a fixture for machining complex surface workpieces in aerospace applications, characterized by comprising the following parts:

[0043] The internal structure of the lead screw housing 6 supporting the transmission frame 1 is a split-type lead screw structure, consisting of split-type lead screw A9 and split-type lead screw B10. The upper cover block 5 is connected to the split-type lead screw A9. The lower end of the split-type lead screw A9 has a cross-shaped protrusion, and the upper end of the split-type lead screw B10 has a cross-shaped groove. The two are connected by bolts. The lower part of the split-type lead screw B10 is interference-fitted with the linear bearing housing 11. The linear bearing housing 11 is bolted to the base 7, such as... Figure 5 As shown;

[0044] Furthermore, the split-type lead screw of the supporting transmission frame 1 and the structure A with trapezoidal threaded holes on the lower housing of the flexible clamp module 2 combine to form a vise-like structure, allowing the flexible clamp module 2 to move vertically up and down within the supporting transmission frame 1 by rotating the hexagonal countersunk hole on the split-type lead screw A9. The flexible clamp cover plate 14 of the flexible clamp module 2 and the track housing 8 of the supporting transmission frame 1 are connected by fastening bolts 4 to form a slide rail structure. This slide rail structure provides auxiliary support and locking function when the flexible clamp module 2 moves up and down within the supporting transmission frame 1. Figure 5 As shown;

[0045] The flexible clamp module 2 mainly consists of a pin body 15, an upper flexible clamp housing 16, a lower flexible clamp housing 17, and a spring. The upper and lower housings fit together to form an internal cavity structure. Part of the pin body 15 protrudes from the upper flexible clamp housing and can slide vertically. A spring is installed at the lower end of the pin body 15 and is fixed in the lower flexible clamp housing. After the pin body slides a certain distance, it can be locked by a self-locking bolt 13. The self-locking bolt 13 leaves a certain space at the track housing 8 of the supporting transmission frame 1, allowing for tightening and loosening operations using a hex wrench. In another flexible clamp module, the lower flexible clamp housing 17 is replaced with the base 7 structure of the supporting transmission frame 1. Other structures and principles are the same as the flexible clamp module, so they will not be described in detail. See... Figures 7-10 As shown;

[0046] In the auxiliary positioning device 3, two support rods 22 are respectively installed at specific positions on the auxiliary positioning base 20. Weights A and B are respectively installed on the support rods 22, and are connected to the support rods 22 via a hole-shaft fit. Weights A and B mainly support positioning blocks A and B, which are locked to the support rods by bolts. By replacing weights A and B with different heights, the height of positioning blocks A and B can be adjusted, thereby adjusting the position of the complex-shaped workpiece in the overall fixture. The auxiliary positioning base 20 of the auxiliary positioning device 3 contains a protruding structure B. The protruding structure B cooperates with the groove structure below the base 7 of the support transmission frame 1 to form a slide rail-like structure, allowing the support transmission frame 1 to slide along the protruding structure B within the auxiliary positioning device 3. Figures 11-15 As shown; Example 1

[0047] Please refer to Figures 1-20 A fixture for machining complex aerospace workpieces includes a support transmission frame 1, a flexible fixture module 2, an auxiliary positioning device 3, fastening bolts 4, an upper cover block 5, a lead screw housing 6, a base 7, a track housing 8, a split lead screw A9, a split lead screw B10, a linear bearing seat 11, a drain bolt 12, a self-locking bolt 13, a flexible fixture cover plate 14, an ejector pin body 15, a flexible fixture upper housing 16, a flexible fixture lower housing 17, a positioning block A18, a counterweight structure A19, an auxiliary positioning base 20, a positioning pin 21, a support rod 22, a positioning block B23, a counterweight structure B24, and a turbine blade 25.

[0048] This embodiment takes a turbine blade 25, a typical complex-shaped workpiece, as an example. The use of the machining fixture for complex-shaped aerospace workpieces includes the following steps:

[0049] S1: The entire assembly of the support transmission frame 1 and the flexible clamp module 2, hereinafter referred to as the blade tooling, is installed on the auxiliary positioning device 3 along the protruding structure B on the auxiliary positioning base 20. Using a hex wrench, the split screw is rotated to move the upper flexible clamp module 2 vertically downward, pressing the lower flexible clamp module 2, compressing the pin bodies 15 of both to their limit positions. The self-locking bolts of the flexible clamp module 2 are used to lock the pin bodies 15 of the two sets of flexible clamp modules 2. Rotating the split screw causes the upper flexible clamp module 2 to move upward, separating the two sets of flexible clamp modules 2 and reaching the farthest distance.

[0050] Further, the turbine blade 25 is inserted from one side of the blade fixture along positioning blocks A or B. After insertion, the position of the turbine blade 25 is adjusted so that the blade mounting plate is in close contact with positioning blocks A and B. Then, the turbine blade 25 is positioned using the positioning pin 21, completing the positioning function of the auxiliary positioning device 3. After positioning, the self-locking structure of the upper flexible clamping module 2 is released, allowing the spring inside the ejector pin 15 to return to its natural length. The entire turbine blade is then positioned and locked. During the locking process, the blade is initially pre-positioned to ensure that the approximate installation angle of the blade does not change significantly after each clamping.

[0051] S2: After completing S1, use a hex wrench to rotate the split screw to move the upper flexible clamp module 2 vertically downward. When the ejector pin 15 of the upper flexible clamp module 2 completely covers the turbine blade 25 facing away from the blade profile, lock the upper flexible clamp module 2 to keep the ejector pin 15 in its current state. At this time, release the lower flexible clamp module 2 so that the spring inside the ejector pin 15 of the lower flexible clamp module 2 returns to its natural length. Then rotate the split screw to move the upper flexible clamp module 2 further downward, compressing the ejector pin 15 of the lower flexible clamp module 2 downward. When the ejector pin 15 is compressed to completely cover the turbine blade 25 facing away from the blade profile, use the self-locking bolt 13 to lock the lower flexible clamp module 2 to keep the ejector pin 15 in its current state. Finally, continue to rotate the split lead screw to apply a certain load to the turbine blade 25 located between the two sets of locked flexible clamp modules 2, so that the turbine blade 25 is fully clamped, and at the same time, the fastening bolt 4 is locked onto the track housing 8 of the auxiliary positioning device 3.

[0052] S3: After the blade is fully clamped, remove the auxiliary positioning device 3 from the device in S2. Treat the turbine blade 25 and the blade fixture as a whole (hereinafter referred to as the machining entity). Select three planes on the blade fixture with good dimensional tolerances, form and position tolerances as reference planes. The coordinate system formed by these three planes is the reference coordinate system. Use a 3D solid scanner to scan the three selected planes and the turbine blade 25 to form a point cloud data model. Process and model the point cloud data into a 3D solid model. During the processing, prioritize the processing of the three reference planes selected in S2 to ensure their accuracy.

[0053] S4: Import the entity composed of the three reference planes obtained after reverse modeling, the blade point cloud data obtained by scanning, and the blade theoretical 3D model into the data comparison software. Perform the best fitting and alignment operation between the blade point cloud data model and the blade 3D theoretical model to obtain the overall model composed of the blade theoretical entity and the blade point cloud data in the determined 3D reference coordinate system.

[0054] S5: Using the obtained overall model, where the scanned point cloud data model is the blank, the theoretical entity model is the processed model, and the machining coordinate system is the reference coordinate system composed of the three reference planes selected in S3 above, the machining is programmed in the CNC machining software.

[0055] S6: Install the machined entity into the machining center, set the tool to the origin of the reference coordinate system formed by the three reference planes scanned by S2, input the machining programming code of S5 into the machining center, and then machining can be performed.

[0056] Working principle:

[0057] When using this fixture for machining complex aerospace-grade workpieces, firstly according to Figures 1-15The entire assembly of the support transmission frame 1 and the flexible clamping module 2, hereinafter referred to as the complex surface workpiece fixture, is installed on the auxiliary positioning device 3 along the protruding structure B on the auxiliary positioning base 20. Using a hex wrench, the split screw is rotated to move the upper flexible clamping module 2 vertically downward, pressing the lower flexible clamping module 2, compressing the pin bodies 15 of both to their limit positions. The self-locking bolts of the flexible clamping module 2 are used to lock the pin bodies 15 of the two sets of flexible clamping modules 2. Rotating the split screw again moves the upper flexible clamping module 2 upward, causing the two sets of flexible clamping modules 2 to separate and reach their maximum distance. Further, the complex-shaped workpiece is placed along the positioning block A or B from one side of the complex-shaped workpiece fixture. After placement, the position of the complex-shaped workpiece is adjusted so that the positioning position of the complex-shaped workpiece is close to the positioning blocks A and B. Then, the positioning pin 21 is used to position the complex-shaped workpiece, thus completing the positioning function of the auxiliary positioning device 3 for the complex-shaped workpiece. After positioning, the self-locking structure of the upper flexible clamping module 2 is released, so that the spring inside the ejector pin body 15 returns to its natural length. Using a hex wrench, rotate the split-type screw to move the upper flexible clamping module 2 vertically downwards. When the ejector pin 15 of the upper flexible clamping module 2 completely covers one side of the complex-shaped workpiece, lock the upper flexible clamping module 2, keeping the ejector pin 15 in its current state. At this point, release the lower flexible clamping module 2, allowing the spring inside the ejector pin 15 of the lower flexible clamping module 2 to return to its natural length. Rotate the split-type screw again to move the upper flexible clamping module 2 further downwards, compressing the ejector pin 15 of the lower flexible clamping module 2 downwards. When the ejector pin 15 completely covers the other side of the complex-shaped workpiece, lock the lower flexible clamping module 2 using the self-locking bolt 13, keeping the ejector pin 15 in its current state. Finally, continue rotating the split-type screw to apply a certain load to the complex-shaped workpiece located between the two locked flexible clamping modules 2, completely clamping the workpiece. Simultaneously, lock the fastening bolt 4 onto the central support flexible clamping track housing 8 of the auxiliary positioning device 3. Secondly, the auxiliary positioning device 3 is removed from the device. The complex-shaped workpiece and its fixture are considered as a whole (hereinafter referred to as the machining entity). Three planes with good dimensional tolerances, geometric tolerances, and positional tolerances on the complex-shaped workpiece fixture are selected as reference planes, and the coordinate system formed by these three planes is the reference coordinate system. A 3D solid scanner is used to scan the three selected planes and the complex-shaped workpiece to form a point cloud data model. The point cloud data is then processed and modeled into a 3D solid model. During the processing, the three reference planes selected above are processed first to ensure their accuracy.The solid entity composed of three reference planes obtained after reverse modeling, along with the scanned point cloud data of the complex-shaped workpiece and the theoretical 3D model of the complex-shaped workpiece, are imported into data comparison software. The point cloud data model of the complex-shaped workpiece is then best-fitted and aligned with the 3D theoretical model of the complex-shaped workpiece, resulting in a unified model in a defined 3D reference coordinate system, composed of the theoretical solid entity and the aligned point cloud data of the complex-shaped workpiece. The obtained unified model is then used for machining programming. The scanned point cloud data model serves as the blank, the theoretical solid model as the machined model, and the machining coordinate system is the reference coordinate system composed of the three selected reference planes. The tool setting point is selected at the origin of the reference coordinate system composed of the three scanned reference planes. Finally, the machining programming code is input into the machining center for machining.

[0058] The contents not described in detail in this specification are existing technologies known to those skilled in the art.

[0059] This invention enables the positioning and clamping of complex-shaped workpieces without damaging their surfaces, improving processing efficiency. It can clamp different types of complex aerospace workpieces within a certain size range, and the overall device is easy to use and install. Furthermore, it can convert the complex curved surface datum of aerospace workpieces into a regular, precise datum surface of the fixture housing of this invention, further simplifying the processing technology and reducing processing errors caused by insufficient datum precision, thus improving processing quality.

[0060] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. An aeronautical complex profile workpiece machining jig, characterized by: The clamp comprises a support transmission frame (1), two groups of upper and lower flexible clamp modules (2) arranged oppositely, and an auxiliary positioning device (3), the flexible clamp module is installed on the support transmission frame (1), the auxiliary positioning device (3) is connected with the base (7) of the support transmission frame (1) through bolts, The flexible clamp module (2) comprises a thimble body (15), a flexible clamp upper shell (16), a flexible clamp lower shell, and a spring; the thimble body (15) is partially exposed outside the flexible clamp upper shell and can slide in the up-down direction; the thimble body (15) is installed with the spring at the lower end, the spring is fixed in the flexible clamp lower shell, and the thimble body can be locked through the self-locking bolt (13) after sliding for a distance; the track shell (8) of the support transmission frame (1) is left with space, the flexible clamp cover plate (14) of the flexible clamp module (2) is connected with the track shell (8) of the support transmission frame (1) through the fastening bolt (4) to form a slide rail structure, and the slide rail structure plays an auxiliary supporting role and a locking role when the flexible clamp module (2) moves up and down in the support transmission frame (1); The upper flexible clamp module (2) is slidably arranged on the support transmission frame (1) through the flexible clamp lower shell (17), and the lower flexible clamp module (2) is fixed on the support transmission frame (1) through the base (7); The two support rods (22) in the auxiliary positioning device (3) are respectively installed on the auxiliary positioning base (20), the scale blocks A and B are respectively installed on the support rods (22), the scale blocks A and B are connected with the support rods (22) through hole shaft cooperation, the scale blocks A and B are used for supporting the positioning blocks A and B, and the positioning blocks A and B are locked through bolts and the support rods; the height of the positioning blocks A and B can be adjusted by replacing the scale blocks A and B of different heights, so that the position of the complex profile workpiece positioned in the overall clamp can be adjusted; The auxiliary positioning base (20) of the auxiliary positioning device (3) comprises a protruding structure B, the protruding structure B is matched with the groove structure below the base (7) of the support transmission frame (1) to form a slide rail structure, so that the support transmission frame (1) can slide along the protruding structure B in the auxiliary positioning device (3).

2. The clamp of claim 1, wherein: The support transmission frame (1) comprises a screw shell (6) and a split screw; the split screw is composed of a split screw A (9) and a split screw B (10), the split screw A (9) and the split screw B (10) are connected through bolts, the lower end of the split screw A is provided with a cross-shaped protrusion, and the upper end of the split screw B is provided with a cross-shaped groove; the split screw B is provided with a trapezoidal thread structure, the lower end of the split screw B is matched with the linear bearing seat (11) through interference, the upper cover block (5) is connected with the split screw A (9), and the linear bearing seat (11) is connected with the base (7) through bolts.

3. The clamp of claim 2, wherein: The split screw of the support transmission frame (1) is combined with the flexible clamp module (2) to form a vise structure; the flexible clamp module (2) can be moved up and down in the support transmission frame (1) by rotating the hexagonal countersunk hole on the split screw A (9).

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