Clamping device for research and development of flexible tool of aviation structural part

Abstract

The utility model relates to the technical field of aviation structural part machining, in particular to a clamping device for aviation structural part flexible tool research and development, which comprises a workbench, the top of an eccentric wheel is rotatably connected with a linkage rod, the inner side of a translation seat is fixedly connected with a buffer part, and a clamping plate is arranged outside the translation seat. A micro air pump is fixedly installed outside the clamping plate, and a vacuum suction cup set is fixedly connected to the inner side of the clamping plate. According to the clamping device for research and development of the flexible tool of the aviation structural part, an eccentric wheel is controlled by a gear motor to drive a linkage rod to eccentrically rotate, so that two translation seats synchronously move oppositely or oppositely, the distance is adjusted, the aviation structural part is placed into a clamping plate, a supporting rod is used for driving a hinge block to slide to extrude a buffer spring, and the extrusion force of the translation seats on the structural part is relieved; and meanwhile, the micro air pump vacuumizes the vacuum suction cup set, the structural part is firmly adsorbed and prevented from being separated due to stress, and therefore the flexible clamping effect is conveniently provided for the structural part.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation structural parts processing, in particular to a clamping device for the research and development of flexible tooling for aviation structural parts. Background Art

[0002] Since aviation structural parts have different shapes and structures, they usually need to be fixed during processing to prevent the position or angle of the structural parts from shifting, causing deviations in the processing accuracy and affecting the subsequent use of the structural parts. At this time, it is necessary to use flexible tooling clamping devices to clamp and fix the aviation structural parts, thereby further improving the efficiency of the fixing processing.

[0003] After searching, it was found that a utility model patent with Chinese patent publication number CN215037586U disclosed a clamping device for the research and development of flexible tooling for aviation structural parts manufacturing systems. The flexible tooling clamping device in the utility model patent uses a mechanical arm to clamp the structural parts on the conveyor belt, and then uses an inductive sensor to control the clamping assembly to clamp and fix the structural parts. However, there is no buffer structure inside the clamping assembly on the mechanical arm, and the inductive sensor is located at the top of the clamping assembly, which can drive the clamping mechanism to clamp and move the parts, but cannot provide a flexible clamping effect for the clamping assembly, and cannot effectively avoid the situation where the mechanical arm power is too large to cause damage to the surface of the structural parts. Therefore, the flexible clamping effect of the mechanical arm in the clamping device for the research and development of flexible tooling for aviation structural parts manufacturing systems needs to be further improved, and thus a clamping device for the research and development of flexible tooling for aviation structural parts is proposed. Utility Model Content

[0004] In view of the shortcomings of the prior art, the utility model provides a clamping device for the research and development of flexible tooling for aviation structural parts, which has the advantage of being able to provide a flexible and buffered clamping effect for structural parts. It solves the problem that the clamping device for the research and development of flexible tooling for aviation structural parts manufacturing system in the above-mentioned background technology clamps the structural parts through a mechanical arm and a clamping assembly, but the clamping assembly lacks a buffer assembly inside and cannot provide a flexible clamping effect for the structural parts.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: A clamping device for the research and development of flexible tooling for aviation structural parts, comprising a workbench, the top of which is provided with a flexible clamping structure;

[0006] The flexible clamping structure includes an eccentric wheel, a connecting rod, a guide plate, a translation seat, a buffer, a clamping plate, a micro air pump and a vacuum suction cup group. The inner bottom wall of the workbench is rotatably connected to the eccentric wheel, the top of the eccentric wheel is rotatably connected to the connecting rod, the top of the workbench is fixedly connected to the guide plate, the top of the workbench is slidably connected to the translation seat, the inner side of the translation seat is fixedly connected to the buffer, the outside of the translation seat is provided with a clamping plate, the outside of the clamping plate is fixedly installed with a micro air pump, and the inner side of the clamping plate is fixedly connected to the vacuum suction cup group.

[0007] Furthermore, a reduction motor is fixedly installed at the bottom of the workbench, and the bottom of the workbench is rotatably connected to two No. 1 pulleys, the two No. 1 pulleys are connected through a No. 1 belt transmission, the output end of the reduction motor is fixedly connected to the bottom of one of the No. 1 pulleys, and the top outer side of the other No. 1 pulley is fixedly connected to a driving gear, and the right side of the bottom of the workbench is rotatably connected to a driven gear, and the outer ring gear of the driven gear is meshed with the outer ring gear of the driving gear

[0008] Furthermore, the inner bottom wall of the workbench is rotatably connected with two No. 2 pulleys, both of which are double-headed pulley structures, the top of the driven gear is fixedly connected to the bottom of one of the No. 2 pulleys, the top of one of the No. 1 pulleys is fixedly connected to the bottom of another No. 2 pulley, there are four eccentric wheels, and the bottoms of the four eccentric wheels are fixedly connected with No. 3 pulleys, and the four No. 3 pulleys are respectively connected to the top outer sides and bottom outer sides of the two No. 2 pulleys through four No. 2 belts.

[0009] Furthermore, the top of the workbench is provided with four slide grooves, the number of the translation seats is two, the number of the connecting rods is four, and the four connecting rods are rotatably connected to the bottom of the two translation seats through slide grooves at one end away from the four eccentric wheels.

[0010] Furthermore, the number of the guide plates is four, the inner sides of the four guide plates are each provided with a rail groove, the interior of each rail groove is slidably connected with a roller plate, and the four roller plates are respectively fixedly connected to the front and rear sides of the two guide plates.

[0011] Furthermore, two vertical grooves are provided on opposite sides of the two translation seats, and the number of the buffer members is four. The four buffer members all include spring rods located inside the four vertical grooves. The four spring rods are all buffer spring and screw rod sleeve-type structures. The outsides of the four screw rods are slidably connected with two hinge blocks, and the outside of each hinge block is hinged with a support rod.

[0012] Furthermore, there are two clamping plates, and both are L-shaped structures. The eight support rods are hinged to the opposite sides of the two clamping plates at the end away from the hinge block. There are two micro air pumps and two vacuum suction cup groups. The two micro air pumps are located on the opposite sides of the two clamping plates. Ventilation grooves are provided inside the two clamping plates. The two vacuum suction cup groups are connected to the two ventilation grooves on the sides facing the clamping plates.

[0013] Beneficial Effects

[0014] Compared with the prior art, the technical solution of this application has the following beneficial effects:

[0015] The clamping device used in the research and development of flexible tooling for aviation structural parts controls the eccentric wheel through a reduction motor to drive the connecting rod to rotate eccentrically, so that the two translation seats move synchronously towards or away from each other, adjust the clamping distance, put the aviation structural parts into the clamping plate, and use the support rod to drive the hinge block to slide and squeeze the buffer spring to reduce the squeezing force of the translation seat on the structural parts. At the same time, the micro air pump draws vacuum on the vacuum suction cup group to firmly adsorb the structural parts to prevent them from being detached under force, thereby providing a flexible clamping effect for the structural parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a three-dimensional schematic diagram of the workbench structure of the utility model;

[0017] Figure 2 for Figure 1 Cross-sectional view of perspective;

[0018] Figure 3 for Figure 2 Top view of the eccentric wheel structure

[0019] Figure 4 for Figure 2 Bottom view of the eccentric wheel structure in perspective;

[0020] Figure 5 for Figure 2 A schematic diagram of the enlarged structure in the middle.

[0021] In the figure: 1. workbench; 2. flexible clamping structure; 201. eccentric wheel; 202. connecting rod; 203. guide plate; 204. translation seat; 205. buffer; 2051. spring rod; 2052. hinge block; 2053. support rod; 206. clamping plate; 207. micro air pump; 208. vacuum suction cup group; 3. reduction motor. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0023] See also Figure 1-5 A clamping device for the research and development of flexible tooling for aviation structural parts includes a workbench 1, a flexible clamping structure 2 is arranged on the top of the workbench 1, a reduction motor 3 is fixedly installed on the bottom of the workbench 1, and the reduction motor 3 drives one of the No. 1 pulleys, and one of the No. 1 pulleys drives another No. 1 pulley, so that the driving gear on the other No. 1 pulley meshes with the driven gear to rotate.

[0024] The flexible clamping structure 2 includes an eccentric wheel 201, a linkage rod 202, a guide plate 203, a translation seat 204, a buffer 205, a clamping plate 206, a micro air pump 207 and a vacuum suction cup group 208. The inner bottom wall of the workbench 1 is rotatably connected with the eccentric wheel 201, and the top of one No. 1 pulley and the driven gear are respectively connected with the two No. 2 pulleys, so that the rotation directions of the two No. 2 pulleys are opposite. The top of the eccentric wheel 201 is rotatably connected with the linkage rod 202, and the two No. 2 pulleys are respectively connected to the four eccentric wheels 201 through the No. 3 pulley, so that the rotation directions of two eccentric wheels 201 are opposite to those of the other two eccentric wheels 201. The top of the workbench 1 is fixedly connected There is a guide plate 203, and the top of the workbench 1 is slidably connected to a translation seat 204. The eccentric rotation of the connecting rod 202 drives the two translation seats 204 to move towards or away from each other. The inner side of the translation seat 204 is fixedly connected with a buffer 205. The outer side of the translation seat 204 is provided with a clamping plate 206, and the clamping plate 206 is connected to the translation seat 204 through the buffer 205 to provide a flexible clamping effect for the clamping plate 206. A micro air pump 207 is fixedly installed on the outside of the clamping plate 206, and a vacuum suction cup group 208 is fixedly connected to the inner side of the clamping plate 206. The micro air pump 207 draws vacuum from the vacuum suction cup group 208 to make the clamping plate 206 stably fit on the outer side of the structural member.

[0025] according to Figure 2 and Figure 3 as well as Figure 4 As shown, the bottom of the workbench 1 is rotatably connected to two No. 1 pulleys driven by a No. 1 belt. The reduction motor 3 drives one of the No. 1 pulleys to make the two No. 1 pulleys rotate synchronously. The driving gear outside the other No. 1 pulley is meshed with a driven gear. At this time, the rotation direction of the driven gear is opposite to the rotation direction of the two No. 1 pulleys.

[0026] according to Figure 2 and Figure 3 as well as Figure 4 As shown, the inner bottom wall of the workbench 1 is rotatably connected to two No. 2 pulleys, and the top and bottom of the No. 2 pulleys are both pulley structures. The bottoms of the two No. 2 pulleys are respectively connected to the top of one of the No. 1 pulleys and the top of the driven gear, so that the rotation directions of the two No. 2 pulleys are opposite. At the same time, the bottoms of the four eccentric wheels 201 are respectively connected to the top and bottom of the two No. 2 pulleys through the No. 3 pulley. At this time, two of the eccentric wheels 201 rotate in the opposite direction to the other two eccentric wheels 201.

[0027] according to Figure 1 and Figure 2 As shown, the four connecting rods 202 are rotatably connected to the bottom of the two translation seats 204 respectively, so that the two translation seats 204 move toward or away from each other along the slide groove on the top of the workbench 1, and the rail grooves inside the four guide plates 203 are slidably connected with roller plates, and the guide plates 203 and the roller plates are used to provide a stable guiding effect for the movement of the two translation seats 204.

[0028] according to Figure 2 and Figure 5 As shown, the buffer component 205 includes a spring rod 2051, a hinge block 2052 and a support rod 2053. The spring rod 2051 is a combination structure of a buffer spring and a screw rod, and the buffer spring is located at the top and bottom ends of the screw rod. The outside of the screw rod is slidably connected with two hinge blocks 2052. One side of the hinge block 2052 is connected to one end of the buffer spring, and the hinge block 2052 is hinged to the clamping plate 206 through the support rod 2053. When the clamping plate 206 is in contact with the outer side of the aviation structure, its reaction force will push the support rod 2053, causing the hinge block 2052 to slide toward the side of the buffer spring, squeezing the buffer spring to cause it to undergo elastic deformation, and converting the dynamic potential energy of the squeezing into the elastic potential energy of the spring, thereby achieving the flexible clamping effect of the clamping plate 206 on the aviation structure.

[0029] according to Figure 2 and Figure 5 As shown, the two micro air pumps 207 are respectively located on the opposite sides of the two L-shaped structure clamping plates 206, and the two vacuum suction cup groups 208 are respectively fixedly connected to the inner walls of the two clamping plates 206, and the micro air pump 207 draws vacuum on the vacuum suction cup groups 208 through the ventilation grooves, so that the clamping plates 206 are firmly attached to the outer side of the structural parts, preventing the structural parts from being separated from the clamping plates 206 after being subjected to external forces.

[0030] In summary, the clamping device for the research and development of flexible tooling for aviation structural parts, according to the size of the aviation structural parts, controls the No. 1 pulley through the reduction motor 3, and uses one of the No. 1 pulleys and the driven gear to connect with the No. 2 pulley, and the No. 2 pulley is respectively connected to the four eccentric wheels 201 in transmission, so that two of the eccentric wheels 201 rotate in opposite directions with the other two eccentric wheels 201, and the eccentric wheels 201 are connected to the translation seat 204 through the connecting rod 202, so that the two translation seats 204 move synchronously in opposite directions or back to back, adjust the clamping distance, put the aviation structural parts into the inner side of the clamping plate 206, and when the translation seat 204 drives the clamping plate 206 to be tightly attached When closed on the outside of the structural part, the support rod 2053 is used to drive the hinge block 2052 to slide and squeeze the buffer spring, thereby reducing the squeezing force of the translation seat 204 on the outside of the structural part, and at the same time, the micro air pump 207 is used to draw a vacuum on the vacuum suction cup group 208 to firmly fit the clamping plate 206 on the outside of the structural part to prevent the structural part from being forced to separate, thereby facilitating the provision of a flexible clamping effect for the structural part, and solving the problem that the clamping device for the development of flexible tooling for the aviation structural part manufacturing system in the above-mentioned background technology clamps the structural part through a mechanical arm and a clamping assembly, but the clamping assembly lacks a buffer assembly and cannot provide a flexible clamping effect for the structural part.

[0031] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0032] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A clamping device for the development of flexible tooling for aviation structural parts, comprising a workbench (1), characterized in that: A flexible clamping structure (2) is provided on the top of the workbench (1); The flexible clamping structure (2) comprises an eccentric wheel (201), a linkage rod (202), a guide plate (203), a translation seat (204), a buffer (205), a clamping plate (206), a micro air pump (207) and a vacuum suction cup group (208); the inner bottom wall of the workbench (1) is rotatably connected to the eccentric wheel (201); the top of the eccentric wheel (201) is rotatably connected to the linkage rod (202); A guide plate (203) is fixedly connected to the top, a translation seat (204) is slidably connected to the top of the workbench (1), a buffer member (205) is fixedly connected to the inner side of the translation seat (204), a clamping plate (206) is arranged outside the translation seat (204), a micro air pump (207) is fixedly installed outside the clamping plate (206), and a vacuum suction cup group (208) is fixedly connected to the inner side of the clamping plate (206).

2. A clamping device for the development of flexible tooling for aviation structural parts according to claim 1, characterized in that: A reduction motor (3) is fixedly installed at the bottom of the workbench (1), and two No. 1 pulleys are rotatably connected to the bottom of the workbench (1), and the two No. 1 pulleys are connected via a No. 1 belt transmission. The output end of the reduction motor (3) is fixedly connected to the bottom of one of the No. 1 pulleys, and a driving gear is fixedly connected to the top outer side of the other No. 1 pulley. A driven gear is rotatably connected to the right side of the bottom of the workbench (1), and the outer gear ring of the driven gear is meshed with the outer gear ring of the driving gear.

3. A clamping device for the development of flexible tooling for aviation structural parts according to claim 2, characterized in that: The inner bottom wall of the workbench (1) is rotatably connected to two No. 2 pulleys, both of which are double-headed pulley structures, the top of the driven gear is fixedly connected to the bottom of one of the No. 2 pulleys, the top of one of the No. 1 pulleys is fixedly connected to the bottom of another No. 2 pulley, the number of the eccentric wheels (201) is four, the bottoms of the four eccentric wheels (201) are fixedly connected to the No. 3 pulleys, and the four No. 3 pulleys are respectively connected to the top outer sides and the bottom outer sides of the two No. 2 pulleys through four No. 2 belts.

4. The clamping device for the development of flexible tooling for aviation structural parts according to claim 1 is characterized in that: The top of the workbench (1) is provided with four slide grooves, the number of the translation seats (204) is two, the number of the connecting rods (202) is four, and the four connecting rods (202) are rotatably connected to the bottom of the two translation seats (204) through slide grooves at one end away from the four eccentric wheels (201).

5. The clamping device for the development of flexible tooling for aviation structural parts according to claim 1 is characterized in that: There are four guide plates (203), the inner sides of the four guide plates (203) are each provided with a rail groove, the interior of each rail groove is slidably connected to a roller plate, and the four roller plates are respectively fixedly connected to the front and rear sides of the two guide plates (203).

6. The clamping device for the development of flexible tooling for aviation structural parts according to claim 1, characterized in that: Two vertical slots are provided on opposite sides of the two translation seats (204), and the number of the buffer members (205) is four. The four buffer members (205) each include a spring rod (2051) located inside the four vertical slots. The four spring rods (2051) are all buffer spring and screw rod sleeve-type structures. The outside of the four screw rods is slidably connected to two hinge blocks (2052), and the outside of each hinge block (2052) is hinged to a support rod (2053).

7. A clamping device for the development of flexible tooling for aviation structural parts according to claim 6, characterized in that: There are two clamping plates (206), and both are L-shaped structures. The eight support rods (2053) are hinged to the opposite sides of the two clamping plates (206) at one end away from the hinge block (2052). There are two micro air pumps (207) and two vacuum suction cup groups (208). The two micro air pumps (207) are located on the opposite sides of the two clamping plates (206). Ventilation grooves are provided inside the two clamping plates (206). The two vacuum suction cup groups (208) are connected to the two ventilation grooves on one side facing the clamping plates (206).

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