A forming and processing device and method for aircraft composite material parts

Abstract

The present invention discloses a forming and processing device and method for aircraft composite material parts, and relates to the technical field of parts processing equipment. The forming and processing device for aircraft composite material parts comprises a support plate, a stamping mechanism, a baffle, a transmission assembly and a lifting structure. The forming and processing device and method for aircraft composite material parts can drive a rotating rod, a rotating roller and a conveyor belt to rotate through the cooperation of the stamping mechanism and the transmission assembly, and can drive the conveyor belt to move the parts, and automatically convey the parts to between the upper film and the lower film of the stamping mechanism, so as to realize automatic loading of the parts, and there is no need for the staff to extend their hands between the upper film and the lower film to load the parts, so as to avoid the staff's hands being pinched by the device, thereby improving the safety of the device, and after the parts are stamped and formed, the stamped parts can also be moved out from between the upper film and the lower film, so as to realize automatic unloading of the parts, so as to realize multiple uses of one machine, reduce the number of motors, and reduce the cost of the device.

Description

Technical Field

[0001] The present invention relates to the technical field of parts processing equipment, and in particular to a forming processing device and method for aircraft composite parts. Background Art

[0002] Aircraft are assembled from many parts. During the reproduction process of some aircraft parts, the parts need to be stamped to ensure that the parts can be assembled accurately.

[0003] Chinese patent document CN207839733U discloses a punching device, which includes: a punch bed, the punch bed includes a punch and a base; a male mold, the male mold is fixed to the punch; a female mold, a convex circle is provided on the female mold, and the convex circle is arranged opposite to the male mold; and a laser device. The laser device is fixed to the base, and the laser device includes at least three laser heads, and at least three of the laser heads are aligned with different positions on the circumference of the convex circle. By aligning at least three laser heads with different positions on the circumference of the convex circle, when the raw material sheet is placed on the convex circle, the laser device can locate the position of the convex circle on the upper surface of the raw material sheet, so that the polishing area of ​​the raw material sheet can be more easily aligned with the convex circle, which greatly improves the processing accuracy and production efficiency.

[0004] However, during the process of loading parts by the above device, if the worker's hands are not removed from between the female mold and the male mold in time, the worker's hands may be easily pinched by the device, which poses a certain safety hazard. Summary of the invention

[0005] The object of the present invention is to provide a molding processing device and method for aircraft composite material parts to solve the problems raised in the above background technology.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a forming and processing device for aircraft composite material parts, comprising a support plate, side plates are fixedly installed on the front and rear sides of the support plate, two groups of side plates are rotatably installed with two groups of rotating rods, rollers are fixedly installed on the outer walls of the two groups of rotating rods, the middle of the two groups of rotating rollers are concavely arranged, and the outer walls of the two groups of rotating rollers are sleeved with conveyor belts, and also includes a stamping mechanism installed between the two groups of side plates, the stamping mechanism is used to stamp parts, two side baffles are fixedly installed between the two groups of side plates, the baffles are located on both sides of the stamping mechanism, during the operation of the device, the hands of the staff are prevented from extending between the upper film and the lower film, avoiding the possibility of injury to the staff, and further improving the safety of the device, a transmission component installed on the rotating rod and the stamping mechanism, through the transmission component, the stamping mechanism can also drive the conveyor belt to automatically transport the parts to the bottom of the stamping mechanism during the stamping and forming of the parts, and a lifting structure is installed between the two groups of side plates, and the bottom of the lifting structure is provided with a movable wheel, which is used to drive the movable wheel to lift and lower.

[0007] Preferably, the stamping mechanism includes a servo motor, an eccentric rod, a linkage rod, a mounting plate, an upper membrane and a lower membrane, the servo motor is fixedly mounted on the rear side of a group of side plates, the eccentric rod is rotatably mounted on the two groups of side plates, the linkage rod is rotatably mounted on the outer wall of the eccentric rod, one end of the linkage rod is hingedly mounted on the top of the mounting plate, a mounting groove is provided at the bottom of the mounting plate, the upper membrane is located in the mounting groove, the support plate is provided with a mounting opening, the lower membrane is located in the mounting opening, and the output shaft of the servo motor is fixedly mounted on one end of the eccentric rod.

[0008] Preferably, guide rails are fixedly installed between the two groups of side panels, and the front and rear sides of the mounting plate are slidably installed on the guide rails.

[0009] Preferably, the mounting plate and the upper membrane are each provided with four groups of mounting holes, bolts A are arranged in the four groups of mounting holes, and nuts A are threadedly mounted on the outer wall of each group of bolts A.

[0010] Preferably, four groups of bolts B are fixedly installed on the bottom of the support plate, nuts B are threadedly installed on the outer walls of the four groups of bolts B, and the four groups of nuts B are in contact with the bottom of the lower membrane.

[0011] Preferably, the transmission assembly includes a rotating shaft, a synchronous wheel, a synchronous belt, a full-tooth gear and a toothless gear. The rotating shaft is rotatably mounted on the front side of another set of side plates. There are two sets of synchronous wheels, which are respectively fixedly mounted on the outer wall of the rotating shaft and the outer wall of the eccentric rod. The synchronous belt is sleeved on the two sets of synchronous wheels, and the synchronous belt is meshed with the two sets of synchronous wheels. The full-tooth gear is fixedly mounted on the outer wall of a set of rotating rods, and the toothless gear is fixedly mounted on the outer wall of the rotating shaft, and the toothless gear is meshed with the full-tooth gear. When the stamping mechanism is used to stamp parts, the rotating rod, The rotation of the rollers and the conveyor belt can drive the conveyor belt to move the parts, and automatically transport the parts to between the upper film and the lower film of the stamping mechanism, so that the parts can be automatically loaded. There is no need for the staff to put their hands between the upper film and the lower film to load the parts, which avoids the staff's hands being pinched by the device, thereby improving the safety of the device. Moreover, after the parts are stamped and formed, the stamped parts can also be moved out from between the upper film and the lower film, and the parts can be automatically unloaded, thus realizing multiple uses of one machine, reducing the number of motors, and reducing the cost of the device.

[0012] Preferably, the lifting structure includes guide rods, an I-beam, a two-way threaded rod, a threaded block, a push-pull rod and a crank, the guide rods having four groups are respectively fixedly mounted on adjacent side walls of two groups of side panels, the I-beam is slidably mounted on the outer walls of the four groups of guide rods, the two-way threaded rods are rotatably mounted on the two groups of side panels, two groups of threaded blocks are threadedly mounted on the outer walls of the two-way threaded rods, two groups of push-pull rods are respectively fixedly mounted on the bottom of the two groups of threaded blocks, and the other ends of the two groups of push-pull rods are hingedly mounted on the top of the I-beam, and the crank is fixedly mounted on one end of the two-way threaded rod, which can drive the movable wheel to lift and lower. When the device needs to be moved, the movable wheel is located below the side panel to drive the movable wheel to move the device; when the device is used, the movable wheel is located above the side panel to drive the side panel to contact the ground to prevent the device from moving and ensure the normal operation of the device.

[0013] Preferably, one group of the side panels is provided with an opening, a material guide trough is fixedly installed in the opening, the material guide trough is located at the bottom of the lower film, and a waste box is placed at the bottom of the material guide trough.

[0014] Preferably, the conveyor belt is provided with a parts opening, and parts are placed on the top of the support plate, and the parts are located inside the parts opening.

[0015] A forming processing method for aircraft composite material parts, wherein the parts are placed in a part opening, and a servo motor is started. The output shaft of the servo motor drives an eccentric rod and a synchronous wheel to rotate. The rotation of the eccentric rod drives a linkage rod to lift and lower a mounting plate and an upper film. The descent of the upper film drives the upper film to punch the parts, and the parts are punched and formed. The rotating synchronous wheel drives another set of synchronous wheels, a rotating shaft, and a toothless gear to rotate through a synchronous belt. The rotation of the toothless gear can drive the full-tooth gear, a rotating rod, a rotating roller, and a conveyor belt to rotate intermittently. After the parts are punched, the next set of parts can be transported between the upper film and the lower film, and the next set of parts is punched and formed. The waste parts after punching fall into a material guide trough through the lower film, slide along the material guide trough into a waste box, and the parts after punching and forming fall into one side of a side plate as the conveyor belt rotates, thereby realizing automatic unloading.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] (1) The forming and processing device and method of aircraft composite material parts use a stamping mechanism to stamp the parts, and then through the coordinated use of a transmission component, it can also drive the rotating rod, the rotating roller, and the conveyor belt to rotate, and can drive the conveyor belt to move the parts, and automatically convey the parts to between the upper film and the lower film of the stamping mechanism, so as to realize automatic loading of the parts, and there is no need for the staff to put their hands between the upper film and the lower film to load the parts, so as to avoid the staff's hands being pinched by the device, thereby improving the safety of the device, and after the parts are stamped and formed, the stamped parts can also be moved out from between the upper film and the lower film, so as to realize automatic unloading of the parts, so as to realize multi-purpose use of one machine, reduce the number of motors, and reduce the cost of the device.

[0018] (2) The aircraft composite material parts forming and processing device and method use a baffle to prevent the hands of workers from reaching between the upper film and the lower film during the operation of the device, thereby avoiding the possibility of injury to the workers and further improving the safety of the device.

[0019] (3) The molding and processing device and method of aircraft composite material parts can drive the movable wheels to move up and down through the lifting structure. When the device needs to be moved, the movable wheels are located below the side panels and the movable wheels are driven to move the device. When the device is in use, the movable wheels are located above the side panels and the side panels are driven to contact the ground to prevent the device from moving and ensure the normal operation of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The present invention is further described below in conjunction with the accompanying drawings and embodiments:

[0021] Figure 1 It is a structural schematic diagram of the present invention;

[0022] Figure 2 It is a structural schematic diagram of another side of the present invention;

[0023] Figure 3 It is a structural schematic diagram of the lower membrane of the present invention;

[0024] Figure 4 It is a structural schematic diagram of the lifting structure of the present invention;

[0025] Figure 5 for Figure 4 Front view of

[0026] Figure 6 is a cross-sectional view of a mounting plate of the present invention;

[0027] Figure 7 It is a cross-sectional view of the support plate of the present invention.

[0028] : 1. side plate; 2. support plate; 3. rotating rod; 4. rotating roller; 5. conveyor belt; 6. parts opening; 7. parts; 8. servo motor; 9. eccentric rod; 10. linkage rod; 11. mounting plate; 12. upper film; 13. guide rail; 14. rotating shaft; 15. synchronous wheel; 16. synchronous belt; 17. full-tooth gear; 18. lower film; 19. bolt A; 20. nut A; 21. bolt B; 22. nut B; 23. material guide trough; 24. waste box; 25. guide rod; 26. I-beam; 27. movable wheel; 28. bidirectional threaded rod; 29. ​​threaded block; 30. push-pull rod; 31. crank; 32. baffle. DETAILED DESCRIPTION

[0029] This section will describe in detail the specific embodiments of the present invention. The preferred embodiments of the present invention are shown in the accompanying drawings. The purpose of the accompanying drawings is to supplement the description of the text part of the specification with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the present invention, but it cannot be understood as a limitation on the scope of protection of the present invention.

[0030] See also Figure 1-7The present invention provides a technical solution: a forming and processing device for aircraft composite material parts, comprising a support plate 2, side plates 1 are fixedly installed on the front and rear sides of the support plate 2, two groups of side plates 1 are rotatably installed with two groups of rotating rods 3, rollers 4 are fixedly installed on the outer walls of the two groups of rotating rods 3, the middle of the two groups of rotating rollers 4 are concavely arranged, and the outer walls of the two groups of rotating rollers 4 are sleeved with conveyor belts 5, and also includes a stamping mechanism installed between the two groups of side plates 1, the stamping mechanism is used to stamp the parts, and the two side baffles 32 are fixedly installed between the two groups of side plates 1, and the baffles 32 are located at the stamping mechanism. On both sides, during the operation of the device, the hands of the staff are prevented from extending between the upper film 12 and the lower film 18, thereby avoiding the possibility of injury to the staff and further improving the safety of the device. The transmission components installed on the rotating rod 3 and the stamping mechanism can drive the conveyor belt 5 to automatically transport the parts to the bottom of the stamping mechanism during the stamping forming of the parts by the stamping mechanism. The lifting structure installed between the two sets of side panels 1 has a movable wheel 27 at the bottom of the lifting structure, which is used to drive the movable wheel 27 to lift and lower.

[0031] The stamping mechanism includes a servo motor 8, an eccentric rod 9, a linkage rod 10, a mounting plate 11, an upper membrane 12 and a lower membrane 18. The servo motor 8 is fixedly installed on the rear side of a group of side plates 1, the eccentric rod 9 is rotatably installed on the two groups of side plates 1, the linkage rod 10 is rotatably installed on the outer wall of the eccentric rod 9, one end of the linkage rod 10 is hingedly installed on the top of the mounting plate 11, a mounting groove is provided at the bottom of the mounting plate 11, the upper membrane 12 is located in the mounting groove, the support plate 2 is provided with a mounting opening, the lower membrane 18 is located in the mounting opening, and the output shaft of the servo motor 8 is fixedly installed on one end of the eccentric rod 9.

[0032] A guide rail 13 is fixedly installed between the two sets of side plates 1 , and the front and rear sides of the mounting plate 11 are slidably installed on the guide rail 13 .

[0033] The mounting plate 11 and the upper membrane 12 are both provided with four groups of mounting holes, and bolts A19 are arranged in the four groups of mounting holes. A nut A20 is threadedly mounted on the outer wall of each group of bolts A19.

[0034] Four groups of bolts B21 are fixedly installed on the bottom of the support plate 2 . The outer walls of the four groups of bolts B21 are all threadedly installed with nuts B22 , and the four groups of nuts B22 are all in contact with the bottom of the lower membrane 18 .

[0035] The transmission assembly includes a rotating shaft 14, a synchronous wheel 15, a synchronous belt 16, a full-tooth gear 17 and a missing-tooth gear. The rotating shaft 14 is rotatably mounted on the front side of another set of side plates 1. There are two sets of synchronous wheels 15 that are respectively fixedly mounted on the outer wall of the rotating shaft 14 and the outer wall of the eccentric rod 9. The synchronous belt 16 is sleeved on the two sets of synchronous wheels 15, and the synchronous belt 16 is meshed with the two sets of synchronous wheels 15. The full-tooth gear 17 is fixedly mounted on the outer wall of a set of rotating rods 3, and the missing-tooth gear is fixedly mounted on the outer wall of the rotating shaft 14, and the missing-tooth gear is meshed with the full-tooth gear 17. When the stamping mechanism is used to stamp parts, the rotating shaft 14 can be driven to rotate. The rod 3, the roller 4 and the conveyor belt 5 rotate, which can drive the conveyor belt 5 to move the part 7, and automatically transport the part 7 to between the upper film 12 and the lower film 18 of the stamping mechanism, so as to realize automatic loading of the part 7, and there is no need for the staff to put their hands between the upper film 12 and the lower film 18 for loading, so as to avoid the staff's hands being pinched by the device, thereby improving the safety of the device, and after the part 7 is stamped and formed, the stamped part 7 can also be punched out from between the upper film 12 and the lower film 18, so as to realize automatic unloading of the part 7, thereby realizing multi-purpose use of one machine, reducing the number of motors, and reducing the cost of the device.

[0036] The lifting structure includes a guide rod 25, an I-shaped frame 26, a bidirectional threaded rod 28, a threaded block 29, a push-pull rod 30 and a crank 31. The guide rod 25 has four groups fixedly installed on the adjacent side walls of the two groups of side panels 1, the I-shaped frame 26 is slidably installed on the outer walls of the four groups of guide rods 25, the bidirectional threaded rod 28 is rotatably installed on the two groups of side panels 1, the threaded block 29 has two groups, both of which are threadedly installed on the outer walls of the bidirectional threaded rod 28, the push-pull rod 30 has two groups, respectively fixedly installed on the bottom of the two groups of threaded blocks 29, and the two push-pull The other end of the rod 30 is hingedly mounted on the top of the I-frame 26, and the crank 31 is fixedly mounted on one end of the bidirectional threaded rod 28, which can drive the movable wheel 27 to rise and fall. When the device needs to be moved, the movable wheel 27 is located below the side panel 1, and the movable wheel 27 is driven to move the device. When the device is used, the movable wheel 27 is located above the side panel 1, and the side panel 1 is driven to contact the ground to prevent the device from moving and ensure the normal operation of the device.

[0037] One set of side plates 1 is provided with an opening, in which a material guide trough 23 is fixedly installed. The material guide trough 23 is located at the bottom of the lower film 18 , and a waste box 24 is placed at the bottom of the material guide trough 23 .

[0038] The conveyor belt 5 is provided with a parts opening 6 , and a parts 7 is placed on the top of the support plate 2 , and the parts 7 are located inside the parts opening 6 .

[0039] A forming processing method for aircraft composite material parts, wherein a part 7 is placed in a part opening 6, and a servo motor 8 is started. The output shaft of the servo motor 8 drives an eccentric rod 9 and a synchronous wheel 15 to rotate. The rotation of the eccentric rod 9 drives a linkage rod 10 to lift a mounting plate 11 and an upper film 12. The lowering of the upper film 12 drives the upper film 12 to stamp the part 7, and the part 7 is stamped and formed. The rotating synchronous wheel 15 drives another set of synchronous wheels 15, a rotating shaft 14, and a toothless gear through a synchronous belt 16. The wheel rotates, and the rotation of the toothless gear can drive the full-tooth gear 17, the rotating rod 3, the rotating roller 4, and the conveyor belt 5 to rotate intermittently. After the parts 7 are stamped, the next group of parts 7 can be transported between the upper film 12 and the lower film 18, and the next group of parts 7 are stamped and formed. The waste parts after stamping fall into the guide trough 23 through the lower film 18, and slide along the guide trough 23 into the waste box 24. The parts 7 after stamping and forming will fall into one side of the side plate 1 as the conveyor belt 5 rotates, realizing automatic unloading.

[0040] Working principle: Place the upper film 12 in the installation groove, and use bolts A19 and nuts A20 to install the upper film 12 on the installation plate 11. Place the lower film 18 in the installation opening, and use bolts B21 and nuts B22 to install the lower film 18 on the support plate 2. Then place the part 7 in the part opening 6, and start the servo motor 8. The output shaft of the servo motor 8 drives the eccentric rod 9 and the synchronous wheel 15 to rotate. The rotation of the eccentric rod 9 drives the linkage rod 10 to lift the installation plate 11 and the upper film 12. The descent of the upper film 12 drives the upper film 12 to punch the part 7, and the part 7 is punched and formed. , and the rotating synchronous wheel 15 drives another set of synchronous wheels 15, the rotating shaft 14, and the toothless gear to rotate through the synchronous belt 16. The rotation of the toothless gear can drive the full-tooth gear 17, the rotating rod 3, the rotating roller 4, and the conveyor belt 5 to rotate intermittently. After the parts 7 are stamped, the next set of parts 7 can be transported between the upper film 12 and the lower film 18, and the next set of parts 7 are stamped and formed. The waste parts after stamping fall into the guide trough 23 through the lower film 18, and slide along the guide trough 23 into the waste box 24. After stamping and forming, the parts 7 will fall into one side of the side plate 1 as the conveyor belt 5 rotates, realizing automatic unloading.

[0041] The embodiments of the present invention are described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Various changes can be made within the knowledge scope of ordinary technicians in the technical field without departing from the purpose of the present invention.

Claims

1. A molding processing device for aircraft composite material parts, comprising a support plate (2), the front and rear sides of the support plate (2) are both fixedly mounted with side plates (1), two sets of side plates (1) are rotatably mounted with two sets of rotating rods (3), the outer walls of the two sets of rotating rods (3) are both fixedly mounted with rotating rollers (4), the middle of the two sets of rotating rollers (4) are concavely arranged, and the outer walls of the two sets of rotating rollers (4) are sleeved with conveyor belts (5), characterized in that: Also includes: A stamping mechanism installed between two sets of side plates (1), the stamping mechanism being used to stamp parts; Two side baffles (32) fixedly mounted between the two sets of side plates (1), the baffles (32) being located on both sides of the stamping mechanism; A transmission assembly installed on the rotating rod (3) and the punching mechanism, through which the punching mechanism can drive the conveyor belt (5) to automatically transport the parts to the bottom of the punching mechanism during the punching process of the parts; A lifting structure is installed between two sets of side panels (1), and a movable wheel (27) is arranged at the bottom of the lifting structure, and the lifting structure is used to drive the movable wheel (27) to lift.

2. The molding and processing device for aircraft composite material parts according to claim 1, characterized in that: The punching mechanism comprises a servo motor (8), an eccentric rod (9), a linkage rod (10), a mounting plate (11), an upper film (12) and a lower film (18), wherein the servo motor (8) is fixedly mounted on the rear side of a group of side plates (1), the eccentric rod (9) is rotatably mounted on two groups of side plates (1), the linkage rod (10) is rotatably mounted on the outer wall of the eccentric rod (9), one end of the linkage rod (10) is hingedly mounted on the top of the mounting plate (11), a mounting groove is provided at the bottom of the mounting plate (11), the upper film (12) is located in the mounting groove, the support plate (2) is provided with a mounting opening, the lower film (18) is located in the mounting opening, and the output shaft of the servo motor (8) is fixedly mounted on one end of the eccentric rod (9).

3. The molding and processing device for aircraft composite material parts according to claim 2, characterized in that: A guide rail (13) is fixedly mounted between the two sets of side plates (1), and the front and rear sides of the mounting plate (11) are slidably mounted on the guide rail (13).

4. The molding and processing device for aircraft composite material parts according to claim 3, characterized in that: The mounting plate (11) and the upper membrane (12) are each provided with four groups of mounting holes, bolts A (19) are arranged in the four groups of mounting holes, and a nut A (20) is threadedly mounted on the outer wall of each group of bolts A (19).

5. The molding and processing device for aircraft composite material parts according to claim 4, characterized in that: Four groups of bolts B (21) are fixedly mounted on the bottom of the support plate (2), nuts B (22) are threadedly mounted on the outer walls of the four groups of bolts B (21), and the four groups of nuts B (22) are in contact with the bottom of the lower membrane (18).

6. The molding and processing device for aircraft composite material parts according to claim 5, characterized in that: The transmission assembly comprises a rotating shaft (14), a synchronous wheel (15), a synchronous belt (16), a full-tooth gear (17) and a toothless gear. The rotating shaft (14) is rotatably mounted on the front side of another set of side plates (1). The synchronous wheel (15) has two sets, which are respectively fixedly mounted on the outer wall of the rotating shaft (14) and the outer wall of the eccentric rod (9). The synchronous belt (16) is sleeved on the two sets of synchronous wheels (15), and the synchronous belt (16) is meshed with the two sets of synchronous wheels (15). The full-tooth gear (17) is fixedly mounted on the outer wall of one set of rotating rods (3). The toothless gear is fixedly mounted on the outer wall of the rotating shaft (14), and the toothless gear is meshed with the full-tooth gear (17).

7. The molding and processing device for aircraft composite material parts according to claim 6, characterized in that: The lifting structure comprises a guide rod (25), an I-shaped frame (26), a bidirectional threaded rod (28), a threaded block (29), a push-pull rod (30) and a crank (31). The guide rod (25) has four groups and is respectively fixedly mounted on adjacent side walls of two groups of side plates (1). The I-shaped frame (26) is slidably mounted on the outer walls of the four groups of guide rods (25). The bidirectional threaded rod (28) is rotatably mounted on the two groups of side plates (1). The threaded block (29) has two groups and is both threadedly mounted on the outer walls of the bidirectional threaded rod (28). The push-pull rod (30) has two groups and is respectively fixedly mounted on the bottom of the two groups of threaded blocks (29). The other ends of the two groups of push-pull rods (30) are both hingedly mounted on the top of the I-shaped frame (26). The crank (31) is fixedly mounted on one end of the bidirectional threaded rod (28).

8. The molding and processing device for aircraft composite material parts according to claim 7, characterized in that: One group of the side plates (1) is provided with an opening, in which a material guide trough (23) is fixedly installed. The material guide trough (23) is located at the bottom of the lower film (18), and a waste box (24) is placed at the bottom of the material guide trough (23).

9. The molding and processing device for aircraft composite material parts according to claim 8, characterized in that: The conveyor belt (5) is provided with a parts opening (6), a part (7) is placed on the top of the support plate (2), and the part (7) is located on the inner side of the parts opening (6).

10. The method for forming a composite material part of an aircraft according to claim 9, characterized in that: The part (7) is placed in the part opening (6), and the servo motor (8) is started. The output shaft of the servo motor (8) drives the eccentric rod (9) and the synchronous wheel (15) to rotate. The rotation of the eccentric rod (9) drives the linkage rod (10) to lift the mounting plate (11) and the upper film (12). The lowering of the upper film (12) drives the upper film (12) to punch the part (7), thereby punching the part (7). The rotating synchronous wheel (15) drives another set of synchronous wheels (15), the rotating shaft (14), and the toothless gear to rotate through the synchronous belt (16). The rotation of the toothed gear can drive the full-toothed gear (17), the rotating rod (3), the rotating roller (4), and the conveyor belt (5) to rotate intermittently. After the parts (7) are punched, the next group of parts (7) can be transported between the upper film (12) and the lower film (18) to be punched and formed. The waste parts after punching fall into the guide trough (23) through the lower film (18) and slide along the guide trough (23) into the waste box (24). The parts (7) after punching and forming will fall into one side of the side plate (1) as the conveyor belt (5) rotates, thereby realizing automatic unloading.

Images