Positioning and clamping device and method

Abstract

The invention belongs to the technical field of aircraft assembly, and discloses a positioning and clamping device and method.The positioning and clamping device comprises a supporting bottom plate, a clamping plate and a supporting platen, the supporting bottom plate is arranged at the bottom of the device, the supporting platen is arranged in the middle of the upper portion of the supporting bottom plate, and movable sliding grooves are formed in the lower portions of the left side and the right side of the supporting platen correspondingly; a second hydraulic oil cylinder is arranged in the movable sliding groove, a movable sliding seat is arranged at the extending end of the second hydraulic oil cylinder, a supporting guide rod is arranged on the side, away from the second hydraulic oil cylinder, of the movable sliding seat, a supporting vertical plate is arranged above the movable sliding seat, and a fixing plate is arranged on the inner side of the upper end of the supporting vertical plate. Clamping plates are arranged at the front end and the rear end of the driving box correspondingly, a plurality of supporting springs are arranged on the side, away from the fixing plate, of the driving box, pressing plates are arranged on the sides, away from the driving box, of the supporting springs, the pressing plates are elastically connected with the driving box through the supporting springs, and therefore stable clamping of any part of the aircraft component is achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft assembly, and particularly relates to a positioning and clamping device and method. Background Technique

[0002] Aircraft assembly is an important link in aircraft manufacturing. Aircraft assembly is a process of accurately positioning each part or subassembly according to the product technical requirements and assembling them into a component or product using specified connection methods. The aircraft manufacturing coordination method that ensures the coordination between part and part, part and tooling, and tooling and tooling, and thus ensures the assembly accuracy, is an important feature of aircraft manufacturing. During the aircraft assembly process, positioning and clamping tools are required.

[0003] Currently, the main problems of the positioning and clamping devices at the production site are as follows: Due to the insufficient clamping area, there may be a risk of shaking and slipping during assembly, and it is not easy to adjust the angle of the component, which affects the assembly efficiency and progress. For this reason, we propose a positioning and clamping device. Summary of the Invention

[0004] The technical problem to be solved by the present invention is that the existing clamping device has an insufficient clamping area, there may be a risk of shaking and slipping during assembly, and it is not easy to adjust the angle of the component, which affects the assembly efficiency and progress. The present invention proposes a positioning and clamping device and method.

[0005] The technical solution of the present invention is as follows: In a first aspect, the present invention provides a positioning and clamping device, and the device includes: a support bottom plate 1, a clamping plate 8, and a support table plate 18. The bottom of the device is provided with the support bottom plate 1, the support table plate 18 is arranged in the middle above the support bottom plate 1, movable chutes 16 are respectively opened below the left and right sides of the support table plate 18, a second hydraulic cylinder 17 is arranged inside the movable chutes 16, a movable slide seat 15 is arranged at the extending end of the second hydraulic cylinder 17, a support guide rod 14 is arranged on the side of the movable slide seat 15 away from the second hydraulic cylinder 17, a support vertical plate 2 is arranged above the movable slide seat 15, a fixing plate 9 is arranged on the inner side of the upper end of the support vertical plate 2, clamping plates 8 are arranged at the front and rear ends of a driving box 31, a plurality of support springs 24 are arranged on the side of the driving box 31 away from the fixing plate 9, a pressing plate 23 is arranged on the side of the support springs 24 away from the driving box 31, and the pressing plate 23 is elastically connected to the driving box 31 through the support springs 24.

[0006] Further, The second hydraulic cylinder 17 is fixedly connected to the movable slide base 15. The movable slide base 15 is partially adapted to the movable chute 16. The movable slide base 15 is fixedly connected to the support guide rod 14. The support guide rod 14 passes through the inner wall of the support bottom plate 1. The movable slide base 15 is fixedly connected to the support vertical plate 2. Under the action of the second hydraulic cylinder 17, the movable slide base 15 moves horizontally in the movable chute 16. With the cooperation of the support guide rod 14, the two support vertical plates 2 are driven to approach each other, and under the elastic force of the support spring 24, the pressing plate 23 clamps the aircraft component on both sides.

[0007] Further, An movable slide rod 5 is arranged inside the support vertical plate 2. An movable slide sleeve 3 is sleeved in the middle of the movable slide rod 5. A fixed plate 9 is arranged on the inner side near the upper end of the support vertical plate 2. A first hydraulic cylinder 6 is arranged below the fixed plate 9. A support frame 4 is arranged below the first hydraulic cylinder 6. The first hydraulic cylinder 6 is fixedly connected to the support frame 4. The support frame 4 is fixedly connected to the movable slide sleeve 3. The movable slide sleeve 3 is partially adapted to the movable slide rod 5. Under the action of the first hydraulic cylinder 6, the support frame 4 moves vertically. With the mutual cooperation of the movable slide sleeve 3 and the movable slide rod 5, the clamping plate 8 clamps the aircraft component on the support table plate 18 and adjusts the assembly height of the aircraft component after clamping and positioning.

[0008] Further, A second servo motor 13 is arranged below the support frame 4. A second bevel gear 12 is arranged above the second servo motor 13. A first bevel gear 11 is arranged on the side of the second bevel gear 12 away from the movable slide sleeve 3. A rotating disk 10 is arranged on the side of the first bevel gear 11 away from the movable slide sleeve 3. A driving box 31 is arranged on the side of the rotating disk 10 away from the first bevel gear 11. The second servo motor 13 is fixedly connected to the second bevel gear 12. The second bevel gear 12 is meshed with the first bevel gear 11. The first bevel gear 11 is fixedly connected to the rotating disk 10. The rotating disk 10 is fixedly connected to the driving box 31. Under the action of the second servo motor 13, the second bevel gear 12 drives the first bevel gear 11 to rotate, so that the rotating disk 10 and the driving box 31 rotate, and the clamping plate 8 is adjusted to move to a suitable clamping angle for the aircraft component.

[0009] Further, Clamping plates 8 are provided at both the front and rear ends of the driving box 31. A first servo motor 7 is provided on the top of the driving box 31. A second worm gear 25 is provided below the first servo motor 7. A second worm 26 is provided on one side of the second worm gear 25. First worms 20 are provided at both the front and rear ends of the second worm 26. First worm gears 21 are provided on the sides of the two first worms 20 away from each other. An active gear 27 is provided below the first worm gear 21. An active rack 29 is provided on the side of the active gear 27 away from the first worm 20. An active rod 28 is provided on the side of the active rack 29 away from the active gear 27. A guiding chute 30 is formed inside the active rod 28. An active guide rod 19 is provided inside the guiding chute 30; The first servo motor 7 is fixedly connected to the second worm gear 25. The second worm gear 25 is meshed with the second worm 26. The second worm 26 is fixedly connected to the first worm 20. The first worm 20 is meshed with the first worm gear 21. The first worm gear 21 is fixedly connected to the active gear 27. The active gear 27 is meshed with the active rack 29. The active rack 29 is fixedly connected to the active rod 28. The active rod 28 is fixedly connected to the clamping plate 8. The clamping plate 8 is fixedly connected to the active guide rod 19. The active guide rod 19 is locally adapted to the guiding chute 30.

[0010] Furthermore, Under the action of the first servo motor 7, the second worm gear 25 rotates, causing the second worm 26 to drive the first worm 20 to rotate, driving the first worm gear 21 and the active gear 27 to rotate, and causing the active rack 29 and the active rod 28 to move back and forth, driving the clamping plates 8 at both ends to approach or move away from each other, and the clamping plates 8 clamp the aircraft component front and back.

[0011] Furthermore, A rubber pad 22 is provided on the inner wall of the clamping plate 8. The clamping plate 8 is adhesively bonded to the rubber pad 22.

[0012] In a second aspect, the present invention provides a positioning and clamping method, which is applied to the device described above. The method includes: First, place the aircraft component on the support platen 18. Under the action of the first hydraulic cylinder 6, the support frame 4 moves vertically. With the mutual cooperation of the movable sliding sleeve 3 and the movable sliding rod 5, the height of the clamping plate 8 is adjusted to clamp the aircraft component on the support platen 18; Then, under the action of the second hydraulic cylinder 17, the movable sliding seat 15 moves horizontally in the movable chute 16. With the cooperation of the support guide rod 14, the support vertical plates 2 on both sides are driven to approach each other, and under the elastic force of the support spring 24, the pressing plate 23 can clamp the aircraft component on both sides; After the action of the first servo motor 7, the second worm gear 25 rotates, causing the second worm 26 to drive the first worm 20 to rotate, driving the first worm gear 21 and the movable gear 27 to rotate, and causing the movable rack 29 and the movable rod 28 to move back and forth, driving the clamping plates 8 at both ends to approach or move away from each other. At the same time, the movable guide rod 19 slides in the guiding chute 30 to strengthen the supporting force for the clamping plate 8, and the clamping plate 8 clamps the aircraft component back and forth; Finally, after the action of the second servo motor 13, the second bevel gear 12 drives the first bevel gear 11 to rotate, causing the rotating disk 10 and the driving box 31 to rotate, and adjusting the clamping plate 8 to move to a suitable clamping angle for the aircraft component.

[0013] The beneficial effects of the present application are as follows: 1. Through the action of the first hydraulic cylinder of the present invention, the vertical movement of the support frame can be realized. With the mutual cooperation of the movable sliding sleeve and the movable sliding rod, it is convenient to clamp the aircraft component on the support table board, and the assembly height of the aircraft component can be adjusted after clamping and positioning.

[0014] 2. Through the action of the second hydraulic cylinder of the present invention, the lateral movement of the movable sliding seat in the movable chute can be realized. With the cooperation of the support guide rod, the two support vertical plates are driven to approach each other, and under the elastic force of the support spring, finally the pressing plate clamps the aircraft component on both sides.

[0015] 3. Through the action of the first servo motor of the present invention, the second worm gear rotates, causing the second worm to drive the first worm to rotate, which can drive the first worm gear and the movable gear to rotate, and cause the movable rack and the movable rod to move back and forth, driving the clamping plates at both ends to approach or move away from each other. At the same time, the movable guide rod slides in the guiding chute to strengthen the supporting force for the clamping plate, reduce shaking, and the clamping plate can clamp the aircraft component back and forth. The rubber pad increases the friction force to prevent the aircraft component from shaking and falling during assembly.

[0016] 4. Through the action of the second servo motor of the present invention, the second bevel gear drives the first bevel gear to rotate, which can realize the rotation of the rotating disk and the driving box, and finally adjust the aircraft component to a suitable assembly angle. Description of the Drawings

[0017] Figure 1 It is a front view structural schematic diagram of the present invention; Figure 2 It is for the present invention Figure 1 A top view structural schematic diagram at the driving box in; Figure 3 It is an overall structural schematic diagram of the present invention.

[0018] In the figure: 1. Support bottom plate; 2. Support vertical plate; 3. Movable sliding sleeve; 4. Support frame; 5. Movable sliding rod; 6. First hydraulic cylinder; 7. First servo motor; 8. Clamping plate; 9. Fixed plate; 10. Rotating disk; 11. First bevel gear; 12. Second bevel gear; 13. Second servo motor; 14. Support guide rod; 15. Movable sliding seat; 16. Movable chute; 17. Second hydraulic cylinder; 18. Support table plate; 19. Movable guide rod; 20. First worm; 21. First worm gear; 22. Rubber pad; 23. Pressing plate; 24. Support spring; 25. Second worm gear; 26. Second worm; 27. Movable gear; 28. Movable rod; 29. Movable rack; 30. Guide chute; 31. Driving box. Detailed implementation mode

[0019] The following further describes the present application in detail with reference to the accompanying drawings of the embodiments.

[0020] As Figure 1 、 Figure 2 and Figure 3 shown, the present invention provides a positioning and clamping device, including a support bottom plate 1, a clamping plate 8 and a support table plate 18. The bottom of the clamping device is provided with a support bottom plate 1, the middle above the support bottom plate 1 is provided with a support table plate 18, movable chutes 16 are respectively opened below the left and right sides of the support table plate 18, a second hydraulic cylinder 17 is arranged inside the movable chutes 16, the extending end of the second hydraulic cylinder 17 is provided with a movable sliding seat 15, a support guide rod 14 is arranged on the side of the movable sliding seat 15 far away from the second hydraulic cylinder 17, a support vertical plate 2 is arranged above the movable sliding seat 15, a fixed plate 9 is arranged on the inner side of the upper end of the support vertical plate 2, a plurality of support springs 24 are arranged on the side of the driving box 31 far away from the fixed plate 9, a pressing plate 23 is arranged on the side of the support springs 24 far away from the driving box 31, and the pressing plate 23 is elastically connected with the driving box 31 through the support springs 24. The second hydraulic cylinder 17 is fixedly connected with the movable sliding seat 15, the movable sliding seat 15 is locally adapted to the movable chutes 16, the movable sliding seat 15 is fixedly connected with the support guide rod 14, the support guide rod 14 passes through the inner wall of the support bottom plate 1, the movable sliding seat 15 is fixedly connected with the support vertical plate 2. Under the action of the second hydraulic cylinder 17, the movable sliding seat 15 moves horizontally in the movable chutes 16. With the cooperation of the support guide rod 14, the two support vertical plates 2 are driven to approach each other, and under the elastic force of the support springs 24, the pressing plate 23 can clamp the aircraft component on both sides.

[0021] As Figure 1As shown in the figure, further, an active sliding rod 5 is arranged inside the supporting vertical plate 2. An active sliding sleeve 3 is sleeved in the middle of the active sliding rod 5. On the inner side near the upper end of the supporting vertical plate 2, a fixing plate 9 is arranged. Below the fixing plate 9, a first hydraulic cylinder 6 is arranged. Below the first hydraulic cylinder 6, a supporting frame 4 is arranged. The first hydraulic cylinder 6 is fixedly connected to the supporting frame 4. The supporting frame 4 is fixedly connected to the active sliding sleeve 3. The active sliding sleeve 3 is locally adapted to the active sliding rod 5. Under the action of the first hydraulic cylinder 6, the supporting frame 4 moves vertically. With the mutual cooperation of the active sliding sleeve 3 and the active sliding rod 5, it is convenient to clamp the aircraft components on the supporting table plate 18 and adjust the assembly height of the aircraft components after clamping and positioning.

[0022] As Figure 1 shown in the figure, further, a second servo motor 13 is arranged below the supporting frame 4. Above the second servo motor 13, a second bevel gear 12 is arranged. On the side of the second bevel gear 12 away from the active sliding sleeve 3, a first bevel gear 11 is arranged. On the side of the first bevel gear 11 away from the active sliding sleeve 3, a rotating disc 10 is arranged. On the side of the rotating disc 10 away from the first bevel gear 11, a driving box 31 is arranged. The second servo motor 13 is fixedly connected to the second bevel gear 12. The second bevel gear 12 is meshed with the first bevel gear 11. The first bevel gear 11 is fixedly connected to the rotating disc 10. The rotating disc 10 is fixedly connected to the driving box 31. Under the action of the second servo motor 13, the second bevel gear 12 drives the first bevel gear 11 to rotate, so that the rotating disc 10 and the driving box 31 rotate, and the clamping plate 8 can be adjusted to move to a suitable clamping angle for the aircraft component.

[0023] As Figure 2As shown in the figure, further, clamping plates 8 are provided at both the front and rear ends of the driving box 31. Rubber pads 22 are provided on the inner walls of the clamping plates 8. A first servo motor 7 is provided on the top of the driving box 31. A second worm gear 25 is provided below the first servo motor 7. A second worm 26 is provided on one side of the second worm gear 25. First worms 20 are provided at both the front and rear ends of the second worm 26. First worm gears 21 are provided on the sides of the two first worms 20 that are away from each other. An active gear 27 is provided below the first worm gear 21. An active rack 29 is provided on the side of the active gear 27 that is away from the first worm 20. An active rod 28 is provided on the side of the active rack 29 that is away from the active gear 27. A guiding chute 30 is formed inside the active rod 28. An active guide rod 19 is provided inside the guiding chute 30. The first servo motor 7 is fixedly connected to the second worm gear 25. The second worm gear 25 is meshed with the second worm 26. The second worm 26 is fixedly connected to the first worm 20. The first worm 20 is meshed with the first worm gear 21. The first worm gear 21 is fixedly connected to the active gear 27. The active gear 27 is meshed with the active rack 29. The active rack 29 is fixedly connected to the active rod 28. The active rod 28 is fixedly connected to the clamping plate 8. The clamping plate 8 is fixedly connected to the active guide rod 19. The active guide rod 19 is partially adapted to the guiding chute 30. The clamping plate 8 is adhesively bonded to the rubber pad 22. Under the action of the first servo motor 7, the second worm gear 25 rotates, causing the second worm 26 to drive the first worm 20 to rotate, which can drive the first worm gear 21 and the active gear 27 to rotate, and cause the active rack 29 and the active rod 28 to move forward and backward, driving the clamping plates 8 at both ends to approach or move away from each other. At the same time, the active guide rod 19 slides in the guiding chute 30, strengthening the supporting force for the clamping plate 8 and reducing the shaking. The clamping plate 8 can clamp the aircraft components front and back. The rubber pad 22 increases the friction force to prevent the aircraft components from shaking and falling during assembly.

[0024] Working principle: First, place the aircraft component on the support platen 18. Under the action of the first hydraulic cylinder 6, the support frame 4 moves vertically. With the mutual cooperation of the movable sliding sleeve 3 and the movable sliding rod 5, the height of the clamping plate 8 is adjusted to facilitate clamping of the aircraft component on the support platen 18. Then, under the action of the second hydraulic cylinder 17, the movable slide base 15 moves horizontally in the movable chute 16. With the cooperation of the support guide rod 14, the two support vertical plates 2 are driven to approach each other. Under the elastic force of the support spring 24, the pressing plate 23 can clamp the aircraft component from both sides. After that, under the action of the first servo motor 7, the second worm gear 25 rotates, causing the second worm 26 to drive the first worm 20 to rotate, which can drive the first worm gear 21 and the movable gear 27 to rotate, and cause the movable rack 29 and the movable rod 28 to move back and forth, driving the two end clamping plates 8 to approach or move away from each other. At the same time, the movable guide rod 19 slides in the guide chute 30 to strengthen the supporting force for the clamping plate 8 and reduce shaking. The clamping plate 8 can clamp the aircraft component from the front and back. The rubber pad 22 increases the friction force to prevent the aircraft component from shaking and falling during assembly. Finally, under the action of the second servo motor 13, the second bevel gear 12 drives the first bevel gear 11 to rotate, enabling the rotating disk 10 and the drive box 31 to rotate, and finally adjusting the clamping plate 8 to the appropriate clamping angle for the aircraft component.

[0025] 1. Under the action of the first hydraulic cylinder of the present invention, the vertical movement of the support frame can be realized. With the mutual cooperation of the movable sliding sleeve and the movable sliding rod, it is convenient to clamp the aircraft component on the support platen, and the assembly height of the aircraft component can be adjusted after clamping and positioning.

[0026] 2. Under the action of the second hydraulic cylinder of the present invention, the horizontal movement of the movable slide base in the movable chute can be realized. With the cooperation of the support guide rod, the two support vertical plates are driven to approach each other, and under the elastic force of the support spring, finally the pressing plate clamps the aircraft component from both sides.

[0027] 3. Under the action of the first servo motor of the present invention, the second worm gear rotates, causing the second worm to drive the first worm to rotate, which can drive the first worm gear and the movable gear to rotate, and cause the movable rack and the movable rod to move back and forth, driving the two end clamping plates to approach or move away from each other. At the same time, the movable guide rod slides in the guide chute to strengthen the supporting force for the clamping plate and reduce shaking. The clamping plate can clamp the aircraft component from the front and back. The rubber pad increases the friction force to prevent the aircraft component from shaking and falling during assembly.

[0028] 4. Under the action of the second servo motor of the present invention, the second bevel gear drives the first bevel gear to rotate, enabling the rotating disk and the drive box to rotate, and finally realizing the adjustment of the aircraft component to the appropriate assembly angle.

Claims

1. A positioning and clamping device, characterized in that, The device includes: a support bottom plate (1), a clamping plate (8), and a support table plate (18). The bottom of the device is provided with a support bottom plate (1), and a support table plate (18) is arranged in the middle above the support bottom plate (1). Activity sliding grooves (16) are respectively opened below the left and right sides of the support table plate (18). A second hydraulic cylinder (17) is arranged inside the activity sliding grooves (16). An activity sliding seat (15) is arranged at the extending end of the second hydraulic cylinder (17). A support guide rod (14) is arranged on the side of the activity sliding seat (15) away from the second hydraulic cylinder (17). A support vertical plate (2) is arranged above the activity sliding seat (15). A fixing plate (9) is arranged on the inner side near the upper end of the support vertical plate (2). Clamping plates (8) are arranged at the front and rear ends of a driving box (31). A plurality of support springs (24) are arranged on the side of the driving box (31) away from the fixing plate (9). A pressing plate (23) is arranged on the side of the support springs (24) away from the driving box (31). The pressing plate (23) is elastically connected to the driving box (31) through the support springs (24).

2. The positioning and clamping device according to claim 1, wherein the second hydraulic cylinder (17) is fixedly connected to the activity sliding seat (15). The activity sliding seat (15) is locally adapted to the activity sliding grooves (16). The activity sliding seat (15) is fixedly connected to the support guide rod (14). The support guide rod (14) penetrates through the inner wall of the support bottom plate (1). The activity sliding seat (15) is fixedly connected to the support vertical plate (2). Under the action of the second hydraulic cylinder (17), the activity sliding seat (15) moves horizontally in the activity sliding grooves (16). With the cooperation of the support guide rod (14), the two support vertical plates (2) are driven to approach each other, and under the elastic force of the support springs (24), the pressing plate (23) clamps the aircraft component on both sides.

3. The positioning and clamping device according to claim 2, wherein an activity sliding rod (5) is arranged inside the support vertical plate (2). An activity sliding sleeve (3) is sleeved in the middle of the activity sliding rod (5). A fixing plate (9) is arranged on the inner side near the upper end of the support vertical plate (2). A first hydraulic cylinder (6) is arranged below the fixing plate (9). A support frame (4) is arranged below the first hydraulic cylinder (6). The first hydraulic cylinder (6) is fixedly connected to the support frame (4). The support frame (4) is fixedly connected to the activity sliding sleeve (3). The activity sliding sleeve (3) is locally adapted to the activity sliding rod (5). Under the action of the first hydraulic cylinder (6), the support frame (4) moves vertically. With the mutual cooperation of the activity sliding sleeve (3) and the activity sliding rod (5), the clamping plates (8) clamp the aircraft component on the support table plate (18), and the assembly height of the aircraft component is adjusted after clamping and positioning.

4. The positioning and clamping device according to claim 3, wherein A second servo motor (13) is arranged below the support frame (4). A second bevel gear (12) is arranged above the second servo motor (13). A first bevel gear (11) is arranged on the side of the second bevel gear (12) away from the movable sliding sleeve (3). A rotating disc (10) is arranged on the side of the first bevel gear (11) away from the movable sliding sleeve (3). A driving box (31) is arranged on the side of the rotating disc (10) away from the first bevel gear (11). The second servo motor (13) is fixedly connected to the second bevel gear (12). The second bevel gear (12) is meshed and connected to the first bevel gear (11). The first bevel gear (11) is fixedly connected to the rotating disc (10). The rotating disc (10) is fixedly connected to the driving box (31). Under the action of the second servo motor (13), the second bevel gear (12) drives the first bevel gear (11) to rotate, so that the rotating disc (10) and the driving box (31) rotate, and the clamping plate (8) is adjusted to move to a suitable clamping angle for the aircraft component.

5. The positioning and clamping device according to claim 4, wherein Clamping plates (8) are arranged at both the front and rear ends of the driving box (31). A first servo motor (7) is arranged on the top of the driving box (31). A second worm gear (25) is arranged below the first servo motor (7). A second worm (26) is arranged on one side of the second worm gear (25). First worms (20) are arranged at both the front and rear ends of the second worm (26). First worm gears (21) are arranged on the sides of the two first worms (20) away from each other. A movable gear (27) is arranged below the first worm gear (21). A movable rack (29) is arranged on the side of the movable gear (27) away from the first worm (20). A movable rod (28) is arranged on the side of the movable rack (29) away from the movable gear (27). A guiding chute (30) is formed inside the movable rod (28). A movable guide rod (19) is arranged inside the guiding chute (30). The first servo motor (7) is fixedly connected to the second worm gear (25). The second worm gear (25) is meshed and connected to the second worm (26). The second worm (26) is fixedly connected to the first worm (20). The first worm (20) is meshed and connected to the first worm gear (21). The first worm gear (21) is fixedly connected to the movable gear (27). The movable gear (27) is meshed and connected to the movable rack (29). The movable rack (29) is fixedly connected to the movable rod (28). The movable rod (28) is fixedly connected to the clamping plate (8). The clamping plate (8) is fixedly connected to the movable guide rod (19). The movable guide rod (19) is partially adapted to the guiding chute (30).

6. The positioning and clamping device according to claim 5, wherein Under the action of the first servo motor (7), the second worm gear (25) rotates, causing the second worm (26) to drive the first worm (20) to rotate, driving the first worm gear (21) and the movable gear (27) to rotate, and causing the movable rack (29) and the movable rod (28) to move back and forth, driving the two clamping plates (8) to approach or move away from each other, and the clamping plates (8) clamp the aircraft component back and forth.

7. A positioning and clamping device according to claim 1, characterized in that A rubber pad (22) is provided on the inner wall of the clamping plate (8), and the clamping plate (8) is bonded to the rubber pad (22).

8. A positioning and clamping method, characterized in that The method is applied to the device according to any one of claims 1-7, and the method includes: First, place the aircraft component on the support platen (18). Under the action of the first hydraulic cylinder (6), the support frame (4) moves vertically. With the mutual cooperation of the movable sliding sleeve (3) and the movable sliding rod (5), the height of the clamping plate (8) is adjusted to clamp the aircraft component on the support platen (18); Then, under the action of the second hydraulic cylinder (17), the movable sliding seat (15) moves horizontally in the movable sliding groove (16). With the cooperation of the support guide rod (14), the two support vertical plates (2) are driven to approach each other, and under the elastic force of the support spring (24), the pressing plate (23) can clamp the aircraft component on both sides; After that, under the action of the first servo motor (7), the second worm gear (25) rotates, causing the second worm (26) to drive the first worm (20) to rotate, driving the first worm gear (21) and the movable gear (27) to rotate, and causing the movable rack (29) and the movable rod (28) to move back and forth, driving the two clamping plates (8) to approach or move away from each other. At the same time, the movable guide rod (19) slides in the guide chute (30) to strengthen the supporting force on the clamping plate (8), and the clamping plate (8) clamps the aircraft component back and forth; Finally, under the action of the second servo motor (13), the second bevel gear (12) drives the first bevel gear (11) to rotate, causing the rotating disk (10) and the driving box (31) to rotate, and adjusting the clamping plate (8) to move to a suitable clamping angle for the aircraft component.

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