Fixing tool for aircraft shell machining

Abstract

The utility model discloses a fixing tool for aircraft shell machining, which comprises a bottom frame, a pressing assembly, a fixing adjusting mechanism, a pressing clamping mechanism and a clamping auxiliary mechanism, the fixing adjusting mechanism comprises an inclined supporting plate, a hydraulic cylinder, a moving plate, a sliding sleeve, a sliding rod and a fixing plate, the pressing and clamping mechanism comprises a clamping pipe, a clamping rod, a transverse moving frame, a clamping groove, a rotating ring, a radian groove and a radian plate, the clamping auxiliary mechanism comprises a threaded ring, a slope ring, an elastic plate, an extending block and a pressing groove, and the combination of a hydraulic cylinder and a moving plate allows accurate position adjustment to adapt to aircraft shells of different sizes; and the stability of the movable plate in the adjusting process is ensured through cooperation of a sliding sleeve and a sliding rod, fixed mounting and dismounting of the pressing assembly are achieved, a plurality of fixing points are provided for selection through clamping holes, and the applicability and flexibility of the device are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of fixing tooling, and more particularly to a fixing tooling for machining an aircraft shell. Background Art

[0002] A fixed tool for aircraft shell processing is a special device designed for precise positioning and fixation during the aircraft shell manufacturing process. This tool can ensure that the aircraft shell maintains a stable and precise position during the processing, thereby improving processing accuracy and efficiency.

[0003] In the existing technology, firstly, some devices lack the ability to adjust the position and cannot adapt to aircraft shells of different sizes. It is difficult to accurately control the position of the clamping assembly and cannot quickly adjust the workpiece position according to processing requirements. They can only process workpieces of fixed sizes. Each time a workpiece of a different size is replaced, the entire tooling may need to be replaced. Secondly, some devices cannot firmly fix the aircraft shell. The workpiece may loosen or fall off during processing. Unstable fixation of the workpiece will directly affect the processing quality. Other temporary fixing methods may need to be used, which increases the difficulty of operation and makes it difficult to quickly adapt to workpieces of different shapes and sizes. Finally, some devices may generate vibration during high-speed processing, affecting the processing accuracy. The lack of quick locking and unlocking functions increases the operation time. There is no additional fixing protection, which increases the work risk. Utility Model Content

[0004] (1) Technical problems solved

[0005] In response to the problems existing in the prior art, the present invention provides a fixing tool for processing an aircraft shell to solve the technical problems mentioned in the background art, such as the lack of position adjustment capability of the device and the inability of the device to firmly fix the aircraft shell.

[0006] (2) Technical solution

[0007] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a fixed tooling for processing an aircraft shell, comprising a base frame, a clamping assembly, a fixed adjustment mechanism, a clamping and clamping mechanism and a clamping auxiliary mechanism, wherein the fixed adjustment mechanism comprises a diagonal support plate, a hydraulic cylinder, a movable plate, a sliding sleeve, a sliding rod and a fixed plate, wherein the hydraulic cylinder is fixedly mounted on the top end of the diagonal support plate, the bottom of the movable plate is cooperatively connected with one end of the hydraulic cylinder, the sliding sleeve is mounted on the bottom of the movable plate, the sliding rod is fixedly mounted on the top end surface of the diagonal support plate, and the sliding sleeve is slidably mounted on the sliding rod The fixing plate is fixedly mounted on the top end face of the hydraulic cylinder, and the clamping and clamping mechanism includes a clamping tube, a clamping rod, a transverse frame, a clamping groove, a rotating ring, an arc groove and an arc plate. The clamping rod can be extended into the interior of the clamping tube, and the clamping groove is arranged on the side of the clamping rod. The transverse frame is laterally movable and is arranged on the outer wall of the clamping tube. The rotating ring is limited and rotatably mounted on the outer wall of the clamping tube. The arc plate is mounted on one end of the transverse frame, and the arc groove is arranged on the inner wall of the rotating ring. The arc plate rotates in the arc groove, driving the transverse frame to extend into or away from the clamping groove.

[0008] The utility model is further configured as follows: the clamping auxiliary mechanism includes a threaded ring, a slope ring, an elastic plate, an insertion block and a clamping groove; the threaded ring is threadedly connected to the outer wall of the clamping tube; the slope ring is connected to the bottom end of the threaded ring; the elastic plate is rotatably mounted on the outer wall of the clamping tube; the insertion block is mounted at one end of the elastic plate; the clamping groove is arranged at the top side end of the rotating ring; the inner wall of the slope ring can be pressed toward the outer end of the elastic plate; the insertion block is inserted into the clamping groove to fix the rotating ring.

[0009] The utility model is further configured such that a diagonal support frame is installed on the top end surface of the base frame, and the bottom of the diagonal support plate is fixedly connected with one end of the diagonal support frame. The diagonal support frame provides stable support for the diagonal support plate, thereby enhancing the stability of the overall structure.

[0010] The utility model is further configured such that a fixing sleeve is installed at the bottom of the fixing plate, and the fixing sleeve is fixedly installed on the guide rod, and the fixing sleeve provides an additional fixing point to enhance the stability of the fixing plate.

[0011] The utility model is further configured such that the fixed plate and the movable plate are provided with snap-in holes, and multiple groups of snap-in holes are provided, and one end of the snap-in rod can be detachably connected with different snap-in holes. The snap-in holes provide multiple fixing point options, thereby increasing the applicability and flexibility of the device.

[0012] The utility model is further configured such that side plates are installed on both sides of the clamping assembly, a connecting plate is installed on the bottom end of the side wall of the clamping tube, and one end of the connecting plate is cooperatively connected with the top end of the side plate. The side plates and the connecting plate enhance the connection stability of the clamping tube and improve the overall structural strength.

[0013] The utility model is further configured such that one end of the clamping rod is mounted on the fixed plate and the movable plate through the clamping hole, and one end of the clamping rod extends through the side plate and cooperates with the clamping tube for quick clamping. The clamping tube and the clamping rod provide a reliable clamping function to ensure the stability of the aircraft shell during the processing.

[0014] The utility model is further configured such that a support ring is installed on the top end face of the connecting plate, a connecting pipe is installed on the bottom of the rotating ring, and the top of the support ring is contacted and connected with the bottom of the connecting pipe. The support ring and the connecting pipe provide stable support for the rotating ring, reducing vibration and wear.

[0015] (3) Beneficial effects

[0016] Compared with the prior art, the present invention provides a fixed tooling for aircraft shell processing, which has the following beneficial effects:

[0017] The utility model is provided with a fixed adjustment mechanism. The combination of the hydraulic cylinder and the movable plate allows precise position adjustment to adapt to aircraft shells of different sizes. The cooperation of the sliding sleeve and the sliding rod ensures the stability of the movable plate during the adjustment process. The hydraulic cylinder provides precise position control and improves processing accuracy. The hydraulic system makes the adjustment process simple and fast, and can easily adapt to workpieces of different sizes and shapes.

[0018] The utility model is provided with a clamping and clamping mechanism to realize the fixed installation and disassembly of the clamping assembly. The clamping hole provides multiple fixing point options, which increases the applicability and flexibility of the device. The design of the clamping rod and the clamping tube realizes quick clamping. The cooperation between the transverse moving frame and the clamping groove provides a stable fixing effect. The design of the rotating ring and the arc groove allows flexible adjustment of the clamping position. The clamping or release can be completed by rotating the rotating ring. The cooperation between the arc plate and the arc groove realizes precise lateral positioning.

[0019] The utility model is provided with a clamping auxiliary mechanism, which provides additional fixing protection and further enhances stability. The design of the threaded ring allows fine adjustment of the fixing force, and the design of the slope ring realizes fast locking and unlocking. Through the cooperation of the clamping groove and the insertion block, the vibration during the processing is effectively reduced, the vibration and wear are reduced, and the service life of the equipment is extended. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the overall structure of the device in the present invention when not in use;

[0021] Figure 2 This is a structural diagram of the fixed adjustment mechanism in the present utility model;

[0022] Figure 3 This is a structural diagram of a fixed adjustment mechanism of part of the present invention;

[0023] Figure 4 It is a structural diagram of the clamping mechanism and the auxiliary clamping mechanism in the utility model;

[0024] Figure 5 It is a schematic diagram of the internal structure of the clamping mechanism and the auxiliary clamping mechanism in the utility model.

[0025] In the figure: 1. Base frame; 2. Clamping assembly; 3. Diagonal support plate; 4. Hydraulic cylinder; 5. Moving plate; 6. Sliding sleeve; 7. Sliding rod; 8. Fixed plate; 9. Clamping tube; 10. Clamping rod; 11. Transverse frame; 12. Clamping groove; 13. Rotating ring; 14. Curved groove; 15. Curved plate; 16. Threaded ring; 17. Slope ring; 18. Elastic plate; 19. Insert block; 20. Clamping groove; 21. Diagonal support frame; 22. Fixed sleeve; 23. Clamping hole; 24. Side plate; 25. Connecting plate; 26. Support ring; 27. Connecting pipe. DETAILED DESCRIPTION

[0026] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0027] It should be noted that, unless otherwise specified, all technical and scientific terms used in this application have the same meaning as commonly understood by ordinary technicians in the technical field to which this application belongs.

[0028] In the present invention, unless otherwise specified, directions such as "up" and "down" are usually relative to the directions shown in the drawings, or relative to the vertical, perpendicular or gravity direction; similarly, for ease of understanding and description, "left" and "right" are usually relative to the left and right shown in the drawings; "inside" and "outside" refer to the inside and outside relative to the outline of each component itself, but the above-mentioned direction words are not used to limit the present invention.

[0029] See also Figure 1-Figure 5A fixed tooling for aircraft shell processing includes a chassis 1, a clamping assembly 2, a fixed adjustment mechanism, a clamping and clamping mechanism and a clamping auxiliary mechanism. The fixed adjustment mechanism includes a diagonal support plate 3, a hydraulic cylinder 4, a movable plate 5, a sliding sleeve 6, a sliding rod 7 and a fixed plate 8. The hydraulic cylinder 4 is fixedly mounted on the top end of the diagonal support plate 3, the bottom of the movable plate 5 is connected with one end of the hydraulic cylinder 4, the sliding sleeve 6 is mounted on the bottom of the movable plate 5, the sliding rod 7 is fixedly mounted on the top end surface of the diagonal support plate 3, the sliding sleeve 6 is on the sliding rod 7, and the fixed plate 8 is fixedly mounted on the top end surface of the hydraulic cylinder 4. The mechanism includes a clamping tube 9, a clamping rod 10, a transverse frame 11, a clamping groove 12, a rotating ring 13, an arc groove 14 and an arc plate 15. The clamping rod 10 can be extended into the interior of the clamping tube 9. The clamping groove 12 is arranged on the side of the clamping rod 10. The transverse frame 11 is arranged on the outer wall of the clamping tube 9 for horizontal movement. The rotating ring 13 is arranged on the outer wall of the clamping tube 9 for limited rotation. The arc plate 15 is installed at one end of the transverse frame 11. The arc groove 14 is arranged on the inner wall of the rotating ring 13. The arc plate 15 rotates in the arc groove 14, driving the transverse frame 11 to extend into or away from the clamping groove 12.

[0030] When the cam 14 is in the upright position, the cam 15 is in the upright position, and the cam 16 is in the upright position, so that the cam 17 can move upward and downward, and the cam 18 can move downward and downward, thereby achieving the desired effect.

[0031] The clamping auxiliary mechanism includes a threaded ring 16, a slope ring 17, an elastic plate 18, an insertion block 19 and a clamping groove 20. The threaded ring 16 is threadedly connected to the outer wall of the clamping tube 9, the slope ring 17 is connected to the bottom end of the threaded ring 16, the elastic plate 18 is rotatably mounted on the outer wall of the clamping tube 9, the insertion block 19 is mounted on one end of the elastic plate 18, and the clamping groove 20 is arranged at the top side end of the rotating ring 13. The inner wall of the slope ring 17 can be pressed toward the outer end of the elastic plate 18, and the insertion block 19 is inserted into the clamping groove 20 to fix the rotating ring 13.

[0032] In this embodiment, the threaded ring 16 is rotated to move up and down on the outer wall of the clamping tube 9. The threaded ring 16 drives the slope ring 17 to move. The inner wall of the slope ring 17 is pressed against the outer end of the elastic plate 18. The elastic plate 18 is deformed and pushes the insertion block 19. The insertion block 19 enters the clamping groove 20 at the top of the rotating ring 13, fixing the rotating ring 13. The threaded ring 16 can be rotated in the opposite direction to release the fixation.

[0033] See also Figure 1-Figure 5 As a supplementary embodiment of a fixed tooling for aircraft shell processing of a fixed adjustment mechanism, a pressing and clamping mechanism and a clamping auxiliary mechanism: the top end surface of the chassis 1 is installed with an oblique support frame 21, and the bottom of the oblique support plate 3 is fixedly connected with one end of the oblique support frame 21, the bottom of the fixed plate 8 is installed with a fixed sleeve 22, and the fixed sleeve 22 is fixedly installed on the guide rod, the fixed plate 8 and the movable plate 5 are provided with clamping holes 23, and the clamping holes 23 are provided with multiple groups, and one end of the clamping rod 10 can be detachably connected with different clamping holes 23, and the pressing group Lateral plates 24 are installed on both sides of component 2, and a connecting plate 25 is installed at the bottom end of the side wall of the clamping tube 9, and one end of the connecting plate 25 is matched with the top end of the lateral plate 24. One end of the clamping rod 10 is installed on the fixed plate 8 and the movable plate 5 through the clamping hole 23, and one end of the clamping rod 10 extends through the lateral plate 24 and is quickly clamped with the clamping tube 9. A support ring 26 is installed on the top end surface of the connecting plate 25, and a connecting tube 27 is installed at the bottom of the rotating ring 13, and the top of the support ring 26 is matched with the bottom of the connecting tube 27 for contact connection.

[0034] More specifically, by controlling the hydraulic cylinder 4, adjusting the position of the movable plate 5 and controlling the size of the fixed platform, the pressing assembly 2 reaches a suitable working position, and the cooperation of the sliding sleeve 6 and the sliding rod 7 is used to ensure the smoothness of the movement process. The clamping rod 10 is inserted into the appropriate clamping holes 23 on the fixed plate 8 and the movable plate 5. Through the cooperation of the radian groove 14 and the radian plate 15, the transverse frame 11 is extended into the clamping groove 12 of the clamping rod 10 to achieve preliminary clamping and fixing. The threaded ring 16 is rotated to move the slope ring 17 downward, and the slope ring 17 is pressed toward The elastic plate 18 pushes the insertion block 19 into the clamping groove 20 of the rotating ring 13 to achieve secondary fixation of the rotating ring 13, enhance the overall stability, and realize rapid installation and disassembly between the clamping component 2 and the movable plate 5 and the fixed plate 8. The aircraft shell is firmly fixed on the tooling. If the position of the clamping component 2 needs to be adjusted, the threaded ring 16 is rotated in the opposite direction to release the fixation of the clamping auxiliary mechanism, release the clamping, take out the clamping rod 10, select the appropriate clamping hole 23 to reinstall the clamping rod 10, and handle aircraft shells of different sizes.

[0035] In summary, when the overall equipment is in use or running: when the operation of the fixed adjustment mechanism is required, the hydraulic cylinder 4 is started to push the movable plate 5 up and down, and the movable plate 5 slides on the slide rod 7 through the sliding sleeve 6 to ensure smooth movement. The fixed plate 8 is fixed on the top of the hydraulic cylinder 4 to provide stable support for the clamping assembly 2. By controlling the hydraulic cylinder 4, the position of the movable plate 5 can be accurately adjusted, thereby adjusting the position of the clamping assembly 2, and then adjusting the space size of the clamping platform.

[0036] When it is necessary to clamp the clamping mechanism, the clamping assembly 2 and the movable plate 5 and the fixed plate 8 can be quickly installed and disassembled. The clamping rod 10 is inserted into the clamping tube 9, and the rotating ring 13 is rotated to drive the arc groove 14 to rotate. The arc plate 15 in the arc groove 14 rotates accordingly, driving the transverse frame 11 to move. The transverse frame 11 moves laterally, extending into or away from the slot 12 on the clamping rod 10. When the transverse frame 11 extends into the slot 12, the clamping and fixing are achieved. When the transverse frame 11 is away from the slot 12, the clamping is released.

[0037] When the auxiliary mechanism needs to be clamped, the threaded ring 16 is rotated to move up and down on the outer wall of the clamping tube 9. The threaded ring 16 drives the slope ring 17 to move. The inner wall of the slope ring 17 is pressed against the outer end of the elastic plate 18. The elastic plate 18 is deformed and pushes the insertion block 19. The insertion block 19 enters the clamping groove 20 at the top of the rotating ring 13 to fix the rotating ring 13. The threaded ring 16 can be rotated in the opposite direction to release the fixation.

[0038] By controlling the hydraulic cylinder 4, adjusting the position of the movable plate 5 and controlling the size of the fixed platform, the pressing assembly 2 reaches a suitable working position. The cooperation of the sliding sleeve 6 and the sliding rod 7 is used to ensure the smoothness of the movement process. The clamping rod 10 is inserted into the appropriate clamping holes 23 on the fixed plate 8 and the movable plate 5. Through the cooperation of the radian groove 14 and the radian plate 15, the transverse frame 11 is extended into the clamping groove 12 of the clamping rod 10 to achieve preliminary clamping and fixing. The threaded ring 16 is rotated to move the slope ring 17 downward, and the slope ring 17 is pressed against the elastic plate. 18, push the insertion block 19 into the clamping groove 20 of the rotating ring 13 to achieve secondary fixation of the rotating ring 13, enhance the overall stability, and realize rapid installation and disassembly between the clamping component 2 and the movable plate 5 and the fixed plate 8. The aircraft shell is firmly fixed on the tooling. If the position of the clamping component 2 needs to be adjusted, rotate the threaded ring 16 in the opposite direction to release the fixation of the clamping auxiliary mechanism, release the clamping, take out the clamping rod 10, select the appropriate clamping hole 23 to reinstall the clamping rod 10, and handle aircraft shells of different sizes.

[0039] In all the schemes mentioned above, the connection between the two components can be selected according to actual conditions by welding, bolt and nut connection, bolt or screw connection or other well-known connection methods, which will not be listed here one by one. In the above, all fixed connections are preferably welded. Although the embodiments of the present invention have been shown and described, it can be understood by ordinary technicians in this field that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the attached claims and their equivalents.

Claims

1. A fixture for machining an aircraft shell, comprising a base frame (1), a clamping assembly (2), a fixing adjustment mechanism, a clamping and connecting mechanism, and a clamping auxiliary mechanism, wherein: The fixed adjustment mechanism comprises a diagonal support plate (3), a hydraulic cylinder (4), a movable plate (5), a sliding sleeve (6), a sliding rod (7) and a fixed plate (8), wherein the hydraulic cylinder (4) is fixedly mounted on the top end of the diagonal support plate (3), the bottom of the movable plate (5) is cooperatively connected with one end of the hydraulic cylinder (4), the sliding sleeve (6) is mounted on the bottom of the movable plate (5), the sliding rod (7) is fixedly mounted on the top end surface of the diagonal support plate (3), and the fixed plate (8) is fixedly mounted on the top end surface of the hydraulic cylinder (4). The clamping and connecting mechanism comprises a clamping tube (9), a clamping rod (10), a transverse moving frame (11), a clamping groove (12), a rotating ring (13), an arc groove (14) and an arc plate (15), the clamping rod (10) can be extended into the interior of the clamping tube (9), the clamping groove (12) is set on the side of the clamping rod (10), the transverse moving frame (11) is set on the outer wall of the clamping tube (9) for horizontal movement, the rotating ring (13) is limited and rotated on the outer wall of the clamping tube (9), the arc plate (15) is installed at one end of the transverse moving frame (11), and the arc groove (14) is set on the inner wall of the rotating ring (13).

2. The fixed tool for machining an aircraft shell according to claim 1, characterized in that: The clamping auxiliary mechanism includes a threaded ring (16), a slope ring (17), an elastic plate (18), an insertion block (19) and a pressing groove (20), the threaded ring (16) is threadedly connected to the outer wall of the clamping tube (9), the slope ring (17) is connected to the bottom end of the threaded ring (16), the elastic plate (18) is rotatably mounted on the outer wall of the clamping tube (9), the insertion block (19) is mounted on one end of the elastic plate (18), and the pressing groove (20) is set at the top side end of the rotating ring (13), the inner wall of the slope ring (17) can be pressed toward the outer end of the elastic plate (18), and the insertion block (19) is inserted into the pressing groove (20) to fix the rotating ring (13).

3. The fixed tool for machining an aircraft shell according to claim 1, characterized in that: The top end surface of the base frame (1) is provided with an oblique support frame (21), and the bottom of the oblique support plate (3) is fixedly connected with one end of the oblique support frame (21).

4. The fixed tool for machining an aircraft shell according to claim 1, characterized in that: A fixing sleeve (22) is installed on the bottom of the fixing plate (8), and the fixing sleeve (22) is fixedly installed on the guide rod.

5. The fixed tool for machining an aircraft shell according to claim 1, characterized in that: The fixed plate (8) and the movable plate (5) are provided with snap-fit ​​holes (23), and there are multiple groups of snap-fit ​​holes (23). One end of the snap-fit ​​rod (10) can be detachably connected with different snap-fit ​​holes (23).

6. The fixed tool for machining an aircraft shell according to claim 5, characterized in that: Side plates (24) are installed on both sides of the clamping assembly (2), and a connecting plate (25) is installed at the bottom end of the side wall of the clamping tube (9), and one end of the connecting plate (25) is matched and connected to the top end of the side plate (24).

7. The fixed tool for machining an aircraft shell according to claim 6, characterized in that: One end of the clamping rod (10) is mounted on the fixed plate (8) and the movable plate (5) through the clamping hole (23), and one end of the clamping rod (10) extends through the lateral plate (24) and cooperates with the clamping tube (9) for a quick clamping arrangement.

8. The fixed tool for machining an aircraft shell according to claim 6, characterized in that: A support ring (26) is installed on the top end surface of the connecting plate (25), a connecting pipe (27) is installed on the bottom of the rotating ring (13), and the top of the support ring (26) is in contact with the bottom of the connecting pipe (27).

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