A universal clamping and positioning device for milling machines for processing aircraft structural components

Abstract

This invention discloses a universal clamping and positioning device for milling machines used in machining aircraft structural parts, relating to the field of aircraft structural part clamping and positioning technology. It includes a worktable and a fixed base on top of the worktable. The top surface of the fixed base has multiple storage slots, each containing a cross brace. Diagonal bracing assemblies are located at the four corners of the cross brace. A lifting mechanism is located in the lower part of the storage slots. A linkage assembly is located inside the transmission cavity. A transmission assembly is located inside the drive box. This invention, through the cooperation of the fixed base, the cross brace, and the diagonal bracing assemblies, facilitates stable positioning and fixing of aircraft structural parts of different shapes and with arched bottoms. Furthermore, through the cooperation of the linkage assembly and the lifting mechanism, it can not only effectively support and limit the arched bottom of the aircraft structure but also adapt to aircraft structural parts of different sizes for localized circumferential positioning and bottom support operations, significantly improving the support effect of the milling machine when milling aircraft structural parts.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural component clamping and positioning technology, and in particular to a universal clamping and positioning device for milling machines used in machining aircraft structural components. Background Technology

[0002] Aircraft structural components are characterized by a wide variety of types and small-batch production, with complex structures and diverse forms. In the manufacturing process of aircraft structural components, in order to meet the requirements of CNC machining, each type of workpiece needs to use a specific special milling machine clamping device, which increases material costs, labor costs, equipment costs, etc., and seriously increases manufacturing costs.

[0003] Existing milling machine clamping and positioning devices require a boss structure for bottom support of thin-walled frame-type aircraft structural parts when clamping and positioning them. This requires drilling through holes in the boss structure for machining the aircraft structural parts, and removing the boss after machining before the milling machine clamping and positioning device can be used to clamp and install aircraft structural parts of different shapes. While this method of adding a boss to the milling machine clamping and positioning device has the advantage of ensuring workpiece stability and machining accuracy during machining, the number of bosses needs to be reasonably controlled. If the boss is misaligned, it cannot effectively support and limit the arched bottom of the aircraft structural part, easily causing workpiece deformation exceeding tolerances during machining, making it difficult to guarantee machining accuracy. It also affects machining efficiency, and the milling machine clamping and positioning device needs to be changed between different processes during the machining of the same structural part, which consumes a lot of machining time, reduces machining efficiency and equipment utilization, and restricts the production speed of aircraft structural parts. Therefore, a universal milling machine clamping and positioning device for aircraft structural parts that can solve the above problems is proposed. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of existing technologies by proposing a universal clamping and positioning device for milling machines used in machining aircraft structural parts.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a universal clamping and positioning device for milling machine for machining aircraft structural parts, comprising a worktable and a fixed base disposed on the top of the worktable. The top surface of the fixed base has multiple evenly spaced storage slots, and each storage slot contains a vertically movable cross brace for limiting the positioning of the aircraft structural parts. The four corners of the cross brace are provided with automatically retractable diagonal brace assemblies. The lower part of each storage slot contains a lifting mechanism for raising and lowering the cross brace. One side of the lower part of the fixed base has multiple horizontally arranged transmission cavities equidistantly spaced, and each transmission cavity contains a linkage assembly for synchronously driving the multiple lifting mechanisms. The other side of the lower part of the fixed base is equipped with a drive box, which contains a transmission assembly for driving the linkage assembly.

[0006] Preferably, the diagonal brace assembly includes a fixing block fixed to the bottom corner of the cross brace, a torsion spring hinge seat mounted on the top of the fixing block, and an outwardly extending column mounted on the torsion spring hinge seat. The outwardly extending column is wider at the top and narrower at the bottom. When the outwardly extending column is stored inside the storage groove, it is in contact with the outer wall of the cross brace and applies pressure to the torsion spring hinge seat. The outer wall of the outwardly extending column is smooth and slides against the inner wall of the storage groove.

[0007] Preferably, the top of the cross brace is provided with a cross-shaped rubber plate, and the top of the outward column is provided with a rectangular rubber plate. The top edges of the cross-shaped rubber plate and the rectangular rubber plate are both arc-shaped, and the cross-shaped rubber plate and the rectangular rubber plate have an injection cavity inside, and the injection cavity is filled with buffer solution to two-thirds of the cavity volume. The top surface of the cross brace and the outward column is flush with the top surface of the fixing seat. Both the cross-shaped rubber plate and the rectangular rubber plate extend out of the receiving groove.

[0008] Preferably, the lifting mechanism includes an annular telescopic seat fixedly disposed in the middle of the bottom surface of the receiving groove, a lead screw vertically movably disposed in the inner ring of the annular telescopic seat, a threaded channel opened on the bottom surface of the cross support, and multiple splined cylinders rotatably disposed on the top surface of the transmission cavity. The rod of the lead screw extends into the threaded channel of the cross support. A stabilizing cylinder is fixedly connected to the bottom end of the splined cylinder, and a driven bevel tooth that cooperates with the connecting component is horizontally fixed to the bottom end of the stabilizing cylinder. A return component for the lead screw to return is provided inside the stabilizing cylinder.

[0009] Preferably, the bottom end of the lead screw is movably inserted into the spline cylinder and is fixedly connected to a spline shaft that is vertically and movably inserted into the spline cylinder, and the height of the spline shaft and the spline cylinder is half that of the cross rubber plate.

[0010] Preferably, the return assembly includes a stabilizing plate horizontally movably disposed within the upper part of the stabilizing cylinder and a return spring vertically fixed to the bottom of the stabilizing plate, the bottom end of the return spring being fixedly connected to the inner bottom surface of the stabilizing cylinder; the bottom end of the spline shaft being rotatably connected to the top surface of the stabilizing plate.

[0011] Preferably, the linkage component includes a drive shaft that is laterally rotatable in the lower part of the transmission cavity and a plurality of active bevel teeth that are equidistantly fixed on the drive shaft, wherein the active bevel teeth mesh with the driven bevel teeth for transmission; ventilation openings are provided at the four corners of the bottom of the storage cavity, and an air inlet is provided at the upper part of one end of the transmission cavity; an installation opening is provided vertically at the top of the fixing block, and a fan is provided in the upper part of the installation opening, and a dustproof mesh frame is provided in the lower part of the installation opening.

[0012] Preferably, the drive assembly includes a worm gear that rotates longitudinally in the upper part of the drive housing, a plurality of worm wheels that mesh equidistantly with the lower part of the worm gear, and a handwheel installed at the front end of the worm gear. One end of each drive shaft movably penetrates into the drive housing and is fixedly connected to the worm wheel. A servo motor for rotating the worm gear is provided at the upper rear end of the drive housing.

[0013] Preferably, the bottom of the fixed base is horizontally fixed with multiple guide rails that mate with the guide grooves on the top surface of the workbench, and each guide rail has a positioning bolt installed at one end for locking and limiting the fixed base.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: The present invention, through the cooperation of the fixed base with the cross brace and diagonal brace components, facilitates stable positioning and fixing of aircraft structural components of different shapes and with arched bottoms, effectively improving the versatility of the device when clamping and fixing aircraft structural components of different shapes and sizes; furthermore, through the cooperation of the linkage component and the lifting mechanism, it can not only effectively support and limit the bottom of the arched aircraft structure, but also adapt to the local circumferential limiting and bottom support operations of aircraft structural components of different sizes; it significantly improves the support effect of the milling machine when milling aircraft structural components, effectively avoiding thin-walled aircraft structures... During milling, insufficient support at the bottom arch can cause structural components to bend downwards; this effectively improves the protection of aircraft structural components during milling; the outward-extending columns at the four corners of the cross brace effectively increase the support area of ​​the cross brace for the aircraft structural components after it is raised, and the outward-extending columns can also perform local limiting operations on the aircraft structural components; the cooperation between the fixing block and the fan facilitates that each storage slot can face the processed aircraft structural components for air cooling, avoiding changes in the physical properties of the materials due to overheating during milling, and improving the cooling effect of the aircraft structural components during processing. Attached Figure Description

[0015] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this application, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings:

[0016] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0017] Figure 2 This is a schematic diagram of the overall structure of the present invention from another perspective;

[0018] Figure 3 This is a perspective view of the fixing base structure of the present invention;

[0019] Figure 4 This is a schematic diagram of the fixing base and guide rail structure of the present invention;

[0020] Figure 5 This is a schematic diagram of the arrangement of multiple cross braces according to the present invention;

[0021] Figure 6 This is a schematic diagram of the multi-drive shaft structure of the present invention;

[0022] Figure 7 This is a schematic diagram of the position structure of the transmission shaft and worm gear of the present invention;

[0023] Figure 8 This is a schematic diagram of the transmission shaft and worm gear from another perspective.

[0024] Figure 9 This is a schematic diagram of the drive shaft and one of the cross braces of the present invention;

[0025] Figure 10 This is a schematic diagram of the meshing state of the driven bevel tooth and the driving bevel tooth of the present invention;

[0026] Figure 11 This is a schematic diagram of the diagonal brace component and the cross brace structure of the present invention;

[0027] Figure 12 This is a schematic diagram of the cross brace and stabilizing cylinder structure of the present invention;

[0028] Figure 13 This is a schematic diagram of the bottom structure of the fixing block of the present invention;

[0029] Figure 14 This is a schematic diagram of the cross brace, splined cylinder, and stabilizing cylinder structure of the present invention;

[0030] Figure 15 This is a partial structural diagram of the lifting structure and return assembly of the present invention;

[0031] Figure 16 This is a partial structural diagram of the inclined bracing assembly and lifting mechanism of the present invention;

[0032] Figure 17 This is a schematic diagram of the spline shaft and spline cylinder meshing state structure of the present invention.

[0033] The components in the diagram are numbered as follows: 1. Workbench; 2. Fixed base; 3. Guide rail; 4. Positioning bolt; 5. Drive box; 6. Cross brace; 7. Fixed block; 8. Outward column; 9. Cross rubber plate; 10. Rectangular rubber plate; 11. Ring-type telescopic base; 12. Lead screw; 13. Splined cylinder; 14. Stabilizing cylinder; 15. Driven bevel gear; 16. Splined shaft; 17. Stabilizing plate; 18. Return spring; 19. Fan; 20. Dustproof mesh frame; 21. Drive shaft; 22. Active bevel gear; 23. Worm gear; 24. Worm wheel; 25. Handwheel; 26. Servo motor. Detailed Implementation

[0034] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0035] Example 1: See Figures 1 to 17 A universal clamping and positioning device for milling machines used for machining aircraft structural parts includes a worktable 1 and a fixed base 2 located on top of the worktable 1. Multiple guide rails 3, which mate with guide grooves on the top surface of the worktable 1, are horizontally fixed to the bottom of the fixed base 2. Each guide rail 3 has a positioning bolt 4 at one end for locking and limiting the fixed base 2. The cooperation between the guide rails 3 and the positioning bolts 4 facilitates effective limiting and fixing of the fixed base 2, which is slidably mounted on the top of the worktable 1, preventing slippage during machining. Multiple storage slots are evenly distributed on the top surface of the fixed base 2, and each storage slot contains a vertically movable cross brace 6 for limiting the aircraft structural parts. The four corners of the cross brace 6 are equipped with automatically retractable diagonal brace assemblies. The lower part of the storage slot is equipped with a lifting mechanism for raising and lowering the cross brace 6; multiple horizontally arranged transmission cavities are equidistantly opened on one side of the lower part of the fixed base 2, and the transmission cavities are equipped with linkage components for synchronous driving of multiple lifting mechanisms; a drive box 5 is installed on the other side of the lower part of the fixed base 2, and the drive box 5 is equipped with a transmission component for driving the linkage component; through the cooperation of the fixed base 2 with the cross brace 6 and the diagonal brace component, it is convenient to stably limit and fix aircraft structural parts of different shapes and those with arched bottoms, which greatly improves the support effect of the milling machine for milling aircraft structural parts, and effectively avoids the situation where thin-walled aircraft structural parts bend down due to insufficient support at the arched bottom during milling.

[0036] In this invention, the diagonal bracing assembly includes a fixing block 7 fixed to the bottom corner of the cross brace 6, a torsion spring hinge seat mounted on the top of the fixing block 7, and an outwardly extending column 8 mounted on the torsion spring hinge seat. The outwardly extending column 8 is wider at the top and narrower at the bottom. When the outwardly extending column 8 is stored inside the storage groove, it fits against the outer wall of the cross brace 6. The top surface of the cross brace 6 and the outwardly extending column 8 is in a star shape within the storage groove. The outwardly extending column 8 applies pressure to the torsion spring hinge seat. The outer wall of the outwardly extending column 8 is smooth and slides against the inner wall of the storage groove. The top of the cross brace 6 is provided with a cross-shaped rubber plate 9, and the top of the outwardly extending column 8 is provided with a rectangular rubber plate 10. The cross-shaped rubber plate 9 and the rectangular rubber plate 10 fit together. The top edges of the rectangular rubber plate 10 are all arc-shaped, and the cross rubber plate 9 and the rectangular rubber plate 10 have injection cavities inside, and the injection cavities are filled with buffer solution to two-thirds of the cavity volume; the top surfaces of the cross brace 6 and the outward-extending column 8 are flush with the top surface of the fixed base 2; and both the cross rubber plate 9 and the rectangular rubber plate 10 extend out of the storage groove; this can effectively improve the protection effect of aircraft structural components during milling; through the outward-extending columns 8 at the four corners of the cross brace 6, the support area of ​​the cross brace 6 for the aircraft structural components after it is raised can be effectively increased, and through the outward-extending columns 8, the aircraft structural components can also be partially limited.

[0037] In this invention, the lifting mechanism includes an annular telescopic seat 11 fixedly disposed in the middle of the bottom surface of the receiving groove, a lead screw 12 vertically movably disposed in the inner ring of the annular telescopic seat 11, a threaded channel opened on the bottom surface of the cross support 6, and a plurality of splined cylinders 13 rotatably disposed on the top surface of the transmission cavity. The rod of the lead screw 12 extends into the threaded channel of the cross support 6. A stabilizing cylinder 14 is fixedly connected to the bottom end of the splined cylinder 13, and a driven bevel tooth 15 cooperating with the connecting component is horizontally fixedly connected to the bottom end of the stabilizing cylinder 14. A return component for the lead screw 12 to return is provided inside the stabilizing cylinder 14. The bottom end of the lead screw 12 movably penetrates into the splined cylinder 13 and is fixedly connected to the splined cylinder. The spline shaft 16 is vertically movable and the height of the spline shaft 16 and the spline cylinder 13 is half that of the cross rubber plate 9; the return assembly includes a stabilizing plate 17 horizontally movable in the upper part of the stabilizing cylinder 14 and a return spring 18 vertically fixed to the bottom of the stabilizing plate 17, the bottom end of the return spring 18 being fixed to the inner bottom surface of the stabilizing cylinder 14; the bottom end of the spline shaft 16 is rotatably connected to the top surface of the stabilizing plate 17; and through the cooperation of the linkage assembly and the lifting mechanism, it can not only effectively support and limit the bottom of the arched aircraft structure, but also adapt to the local circumferential limiting and bottom support operations of aircraft structural components of different sizes.

[0038] Example 2: The technical solution is basically the same as that of Example 1, except that, as Figure 5 , Figure 6 , Figure 7 , Figure 8 , Figure 9As shown, the linkage assembly includes a drive shaft 21 that rotates laterally in the lower part of the transmission cavity and multiple active bevel teeth 22 that are equidistantly fixed on the drive shaft 21. The active bevel teeth 22 mesh with the driven bevel teeth 15 for transmission. Ventilation openings are provided at the four corners of the bottom of the storage cavity, and an air inlet is provided at the upper part of one end of the transmission cavity. A mounting opening is provided vertically at the top of the fixing block 7, and a fan 19 is provided in the upper part of the mounting opening, while a dustproof mesh frame 20 is provided in the lower part of the mounting opening. Air blowing channels are reserved at the four corners inside the storage slot. Through the cooperation of the fixing block 7 and the fan 19, it is easy to make each storage slot... All slots are oriented towards the machined aircraft structural parts for air cooling, preventing the aircraft structural parts from overheating during milling and causing changes in the material's physical properties, thus improving the cooling effect during the machining of the aircraft structural parts; the drive assembly includes a worm 23 that rotates longitudinally in the upper part of the drive housing 5, multiple worm wheels 24 that mesh equidistantly with the lower part of the worm 23, and a handwheel 25 installed at the front end of the worm 23. One end of each drive shaft 21 is movably inserted into the interior of the drive housing 5 and fixedly connected to the worm wheel 24; a servo motor 26 for rotating the worm 23 is provided at the upper rear end of the drive housing 5.

[0039] Working principle: In this embodiment, the present invention also proposes a method for using a universal clamping and positioning device for milling machines to process aircraft structural parts, including the following steps:

[0040] Step 1: First, install the worktable 1 on the linear feed seat of the milling machine. Then, install the fixed seat 2 with the drive box 5 on the top of the worktable 1. Use the positioning bolts 4 to limit and lock the guide rail 3 at the bottom of the fixed seat 2. Then, electrically connect the servo motor 26 and the fan 19 to the external control equipment. Next, place the aircraft structural parts to be processed on the top of the fixed seat 2.

[0041] Step 2: When the aircraft structural component is placed on the fixed seat 2, since the tops of the cross-shaped rubber plate 9 and the rectangular rubber plate 10 are higher than the top surface of the fixed seat 2, the bottom of the aircraft structural component can be prevented from rigidly impacting the top of the fixed seat 2 when the aircraft structural component is placed, thus improving the protective effect of the aircraft structural component during placement.

[0042] Step 3: At this time, some of the cross-shaped rubber plates 9 and rectangular rubber plates 10 will be pressed by the aircraft structural components. The pressed cross-shaped rubber plates 9 will press the cross brace 6 to descend. As the cross brace 6 descends, it will press the lead screw 12 to descend into the splined cylinder 13. When the lead screw 12 descends, it will push the splined shaft 16 to descend, thereby causing the splined shaft 16 to disengage from the splined cylinder 13. As a result, the cross brace 6, after being pressed down, will not rise due to the transmission of the splined cylinder 13. Furthermore, under the action of the return spring 18, the support force of the cross brace 6 and the outward column 8 on the aircraft structural components can also be improved.

[0043] Step four: Then, start the servo motor 26 to drive the worm gear 23 to rotate. The rotating worm gear 23 drives the worm wheel 24 to rotate. When multiple worm wheels 24 rotate synchronously, they will drive multiple drive shafts 21 to rotate in reverse. After the drive shafts 21 rotate, they will drive multiple stabilizing cylinders 14 to rotate in reverse through the meshing of the driving bevel gear 22 and the driven bevel gear 15. When the stabilizing cylinders 14 rotate in reverse, they will drive the splined cylinder 13 to rotate. At this time, the cross support 6 under pressure will not enter the splined cylinder 13 because the internal screw 12 disengages from the splined shaft 16 and the splined cylinder 13. The cross brace 6, which is not pressed down by the aircraft structural components, will be lifted up by the splined cylinder 13 driving the splined shaft 16 to rotate. The rotating splined shaft 16 will drive the lead screw 12 to rotate. When the lead screw 12 rotates, the cross brace 6 with the diagonal brace assembly can be lifted up from the storage slot. As the cross brace 6 is gradually lifted up, the outward-extending columns 8 at the four corners of the cross brace 6, which are hinged by torsion spring hinge seats, will also gradually extend outward, thereby increasing the support area of ​​the cross brace 6 after it is lifted up. The outward-extending columns 8 can also perform local limiting operations on the aircraft structural components.

[0044] Step 5: If the bottom of the aircraft structural component arches upward, the gradually rising cross brace 6 will press against the bottom of the aircraft structural component with the cross rubber plate 9 at its top. As the aircraft structure gradually applies pressure to the cross brace 6, the cross brace 6 can then apply pressure to the lead screw 12 in the opposite direction, thereby causing the lead screw 12 to push the spline shaft 16 down, causing the spline shaft 16 to disengage from the spline cylinder 13. Therefore, after the cross brace 6 rises a certain distance, it provides abutment support to the bottom of the aircraft structural component and can further provide effective limiting support to the bottom of the aircraft structural component.

[0045] Step six: After the multiple cross braces 6 are raised around the aircraft structural component and at the bottom of the suspended area, they provide a stable and fixed function for the aircraft structural component placed on the fixed base 2. When the milling machine performs milling on the fixed aircraft structural component, the fan 19 inside the fixed block 7 is activated to blow air upwards, which facilitates uniform air cooling of the bottom of the aircraft structural component. This prevents the aircraft structural component from overheating during milling and causing changes in the physical properties of the material, thus improving the cooling effect of the aircraft structural component during processing.

[0046] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A general clamping and positioning device for milling machine of aircraft structure, comprising a worktable and a fixed seat arranged on the top of the worktable, characterized in that: The top surface of the fixed base is evenly provided with multiple storage slots, and each storage slot is vertically movable with a cross brace for limiting the position of aircraft structural components. The four corners of the cross brace are provided with automatically retractable diagonal brace assemblies. The lower part of the storage slot is provided with a lifting mechanism for raising and lowering the cross brace. The lower part of one side of the fixed base is provided with multiple horizontally placed transmission cavities at equal intervals, and the transmission cavities are provided with linkage components for synchronously driving multiple lifting mechanisms. The lower part of the other side of the fixed base is equipped with a drive box, and the drive box is provided with a transmission component for driving the linkage component. The diagonal bracing assembly includes a fixing block fixed at the bottom corner of the cross brace, a torsion spring hinge seat installed on the top of the fixing block, and an outward-extending column installed on the torsion spring hinge seat. The outward-extending column is wider at the top and narrower at the bottom. When the outward-extending column is stored inside the storage groove, it is in contact with the outer wall of the cross brace. The outward-extending column is in a state of pressure on the torsion spring hinge seat. The outer wall of the outward-extending column is smooth and slides against the inner wall of the storage groove. The top of the cross brace is provided with a cross-shaped rubber plate, and the top of the outward column is provided with a rectangular rubber plate. The top edges of both the cross-shaped rubber plate and the rectangular rubber plate are arc-shaped, and the cross-shaped rubber plate and the rectangular rubber plate have injection cavities inside, and the injection cavities are filled with buffer solution to two-thirds of the cavity volume. The top surfaces of the cross brace and the outward column are flush with the top surface of the fixing base. Both the cross-shaped rubber plate and the rectangular rubber plate extend out of the storage groove. The lifting mechanism includes an annular telescopic seat fixed in the middle of the bottom surface of the receiving groove, a lead screw vertically movable in the inner ring of the annular telescopic seat, a threaded channel opened in the bottom surface of the cross support, and multiple splined cylinders rotatably disposed in the top surface of the transmission cavity. The rod of the lead screw extends into the threaded channel of the cross support. A stabilizing cylinder is fixedly connected to the bottom end of the splined cylinder, and a driven bevel tooth that cooperates with the connecting component is horizontally fixed to the bottom end of the stabilizing cylinder. A return component for the lead screw to return is provided inside the stabilizing cylinder. The bottom end of the lead screw is movably inserted into the inside of the spline cylinder and is fixedly connected to a spline shaft that is vertically and movably inserted into the spline cylinder. The height of the spline shaft and the spline cylinder is half of the cross rubber plate. The return assembly includes a stabilizing plate horizontally movable inside the upper part of the stabilizing cylinder and a return spring vertically fixed to the bottom of the stabilizing plate. The bottom end of the return spring is fixed to the inner bottom surface of the stabilizing cylinder; the bottom end of the spline shaft is rotatably connected to the top surface of the stabilizing plate.

2. The universal fixture for a milling machine for machining aircraft structures according to claim 1, characterized in that: The linkage component includes a drive shaft that rotates laterally in the lower part of the transmission cavity and multiple active bevel teeth that are fixedly sleeved on the drive shaft at equal intervals. The active bevel teeth mesh with the driven bevel teeth for transmission. Ventilation openings are provided at the four corners of the bottom of the storage slot, and an air inlet is provided at the upper part of one end of the transmission cavity. An installation opening is provided vertically at the top of the fixing block, and a fan is provided in the upper part of the installation opening, while a dustproof mesh frame is provided in the lower part of the installation opening.

3. The universal fixture for a milling machine for machining aircraft structures according to claim 2, characterized in that: The transmission assembly includes a worm gear that rotates longitudinally in the upper part of the drive box, multiple worm wheels that mesh equidistantly with the lower part of the worm gear, and a handwheel installed at the front end of the worm gear. One end of each transmission shaft is movably inserted into the drive box and fixedly connected to the worm wheel. A servo motor for rotating the worm gear is provided at the upper rear end of the drive box.

4. The universal fixture for a milling machine for machining aircraft structures according to claim 1, characterized in that: The bottom of the fixing seat is transversely fixed with a plurality of guide rails matched with the guide groove on the top surface of the workbench, and one end of each guide rail is provided with a positioning bolt for locking and limiting the fixing seat.

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