CN213164282U

CN213164282U - Variable clamping fixture based on aircraft structural part

Info

Publication number: CN213164282U
Application number: CN202021810310.7U
Authority: CN
Inventors: 巨浩; 水佑裕; 张友志
Original assignee: Jiangsu Maixinlin Aviation Technology Co ltd
Current assignee: Jiangsu Maixinlin Aviation Technology Co ltd
Priority date: 2020-08-26
Filing date: 2020-08-26
Publication date: 2021-05-11
Anticipated expiration: 2030-08-26

Abstract

The utility model discloses a variable clamping anchor clamps based on aircraft structure, including elevating gear, the horizontal sliding device of setting on elevating gear, the trailing type clamping device of setting on horizontal sliding device, elevating gear and horizontal sliding device drive horizontal migration and vertical removal on the vertical plane of trailing type clamping device realization, trailing type clamping device includes the clamping cylinder, be provided with the clamping plate on the cylinder push rod of clamping cylinder, the outside of clamping plate is provided with the clamping piece that is matrix distribution, the clamping piece inserts in the clamping board, set up and compression spring between clamping piece and the clamping board. The utility model discloses a variable clamping anchor clamps can carry out the centre gripping to aircraft structure and the form of using of same aircraft structure of difference fixedly.

Description

Variable clamping fixture based on aircraft structural part

Technical Field

The utility model relates to a spare part processing field, concretely relates to variable clamping anchor clamps of aircraft structure.

Background

For large parts such as frame beam rib parts in airplane structural parts, the frame beam rib parts are extremely easy to deform in the machining process due to the complex structure and large size and belong to thin-wall parts, and the precision is difficult to guarantee. For aircraft structural members, it is often necessary to provide tooling bosses around the part in order to ensure the rigidity of the part during machining. The processing rigidity of the part can be increased by adding the process boss, and the processing quality of the part is improved. But the craft boss increases the workload of the craft personnel in the early stage. The process personnel need to spend a large amount of time to set the position of the process boss, and meanwhile, the avoidance of the process boss needs to be considered when the processing program is compiled, so that the programming difficulty is increased, and the programming efficiency is reduced. Similarly, the process bosses are arranged around the part, so that the size of a part blank is increased, and the processing cost of the part is increased.

The device capable of replacing the process boss is needed to fix the aircraft structural part, and the aircraft structural part needs to be processed in multiple steps, so that the state of a workpiece is dynamically changed in the processing process, and the clamping position and the clamping state can be automatically adjusted along with the state of the workpiece.

Disclosure of Invention

The to-be-solved technical problem of the utility model is to provide a variable clamping anchor clamps based on aircraft structure can carry out the centre gripping to the aircraft structure of difference and the form of using of same aircraft structure fixed.

In order to solve the technical problem, the utility model provides a variable clamping anchor clamps based on aircraft structure, including elevating gear, the horizontal sliding device of setting on elevating gear, the trailing type clamping device of setting on horizontal sliding device, elevating gear and horizontal sliding device drive horizontal migration and vertical removal on the vertical plane of trailing type clamping device, trailing type clamping device includes the clamping cylinder, be provided with the clamping plate on the cylinder push rod of clamping cylinder, the outside of clamping plate is provided with the clamping piece that is matrix distribution, the clamping piece inserts in the clamping plate, set up and compression spring between clamping piece and the clamping plate.

In a preferred embodiment of the present invention, the lifting device further comprises a cylinder, a threaded connector, a lifting shaft, a sealing ring, a first gas/liquid inlet/outlet hole, and a second gas/liquid inlet/outlet hole, wherein the threaded connector is used for connecting the horizontal sliding device; the lifting shaft is arranged in the cylinder body, the lower end of the lifting shaft is sleeved with a sealing ring which can move in the cylinder body along with the lifting shaft, the upper end of the lifting shaft is sleeved in the sealing ring fixed in the cylinder body, the threaded connector is positioned at the upper end of the lifting shaft, and when the lifting shaft works, the lifting shaft is lifted by controlling the sequence of gas/liquid inlet and outlet of the first gas/liquid inlet and outlet hole and the sequence of gas/liquid inlet and outlet of the second gas/liquid inlet and outlet hole in the cylinder.

The utility model discloses a preferred embodiment, further include horizontal sliding device is connected with the lift axle through threaded connection head including setting up the horizontal sliding platform on the lift axle, is provided with the slide rail on horizontal sliding platform, be provided with the clamping platform on the slide rail, trailing type clamping device sets up on the clamping platform, one side of slide rail is provided with the actuating cylinder that drives that promotes the clamping platform.

The utility model discloses a preferred embodiment, further include the clamping piece includes the connecting rod and sets up the round platform at the connecting rod both ends, set up the deep hole groove that supplies the clamping piece to pass in the clamping inboard, the through-hole department diameter in deep hole groove is greater than the connecting rod diameter, is less than the round platform diameter, the compression spring cover is established on the connecting rod, compression spring one end butt is on the clamping board, and the other end butt is on the round platform.

In a preferred embodiment of the present invention, the distance between the circular truncated cones of two adjacent clamping blocks is less than 2cm

In a preferred embodiment of the present invention, a rubber ferrule is disposed at an end of the clamping block.

In a preferred embodiment of the present invention, it further comprises a pressing plate protruding from the clamping plate is disposed on the top of the clamping plate.

The utility model discloses a preferred embodiment, further include be provided with pressure sensor and pressure signal collector on the clamp plate.

The utility model has the advantages that:

the utility model discloses a trailing type clamping device adopts the clamping piece that is matrix distribution on the clamping plate, decomposes into the clamping piece of a plurality of punctiform with holistic platelike clamping plate, at the in-process of pressing from both sides tight fixed aircraft structure spare, can cave in into with aircraft structure spare assorted shape to can carry out the centre gripping to the aircraft structure spare of difference and same aircraft structure spare with the form fixed, make the application scope of clamping device can increase, the effectual commonality that improves the clamping device, and the utility model discloses a trailing type clamping device installs on elevating gear and horizontal sliding device, can adjust suitable clamping position in vertical and horizontal direction according to the shape of aircraft structure spare.

Drawings

Fig. 1 is a schematic diagram of the overall mechanism of the variable clamping fixture based on the aircraft structural member of the present invention;

fig. 2 is a schematic front structural view of the clamping plate of the present invention;

fig. 3 is a schematic side view of the clamping plate of the present invention;

fig. 4 is a schematic structural view of the lifting device of the present invention;

fig. 5 is a schematic structural view of the horizontal sliding device of the present invention.

The reference numbers in the figures illustrate: 1. a lifting device; 11. a cylinder body; 12. a threaded connector; 13. a lifting shaft; 14. a seal ring; 15. a first gas/liquid access port; 16. a second gas/liquid access port; 2. a horizontal sliding device; 21. a horizontal sliding platform; 22. a slide rail; 23. clamping the platform; 24. a driving cylinder; 3. a follow-up clamping device; 31. clamping the cylinder; 32. installing a clamping plate; 321. a deep hole groove; 322. a through hole; 33. installing a clamping block; 331. a connecting rod; 332. a circular truncated cone; 34. a compression spring; 35; rubber wrapping heads; 4. pressing a plate; 5. a pressure sensor; 6. and a pressure signal collector.

Detailed Description

The present invention is further described with reference to the following drawings and specific embodiments so that those skilled in the art can better understand the present invention and can implement the present invention, but the embodiments are not to be construed as limiting the present invention.

Referring to fig. 1-2, an embodiment of the present invention based on an aircraft structural member includes a lifting device 1, a horizontal sliding device 2 disposed on the lifting device 1, and a following clamping device 3 disposed on the horizontal sliding device 2, wherein the lifting device 1 and the horizontal sliding device 2 drive the following clamping device 3 to realize horizontal movement and vertical movement on a vertical plane, the following clamping device 3 is driven by the lifting device 1 and the horizontal sliding device 2 to move to a position suitable for clamping the aircraft structural member, the following clamping device 3 includes a clamping cylinder 31, a clamping plate 32 is disposed on a cylinder push rod of the clamping cylinder 31, clamping blocks 33 densely distributed in a matrix are disposed on an outer side of the clamping plate 32, the clamping blocks 33 are inserted into the clamping plate 32, a compression spring 34 is disposed between the clamping blocks 33 and the clamping plate 32, after reaching the position suitable for clamping the aircraft structural part, the clamping cylinder 31 is started, the cylinder push rod of the clamping cylinder 31 drives the clamping plate 32 to move to the clamping position on the aircraft structural part, and the integral platy clamping plate 32 is decomposed into a plurality of punctiform clamping blocks 33, so that the clamping plate can be sunken into a shape matched with the aircraft structural part in the process of clamping and fixing the aircraft structural part, and the aircraft structural part is clamped and fixed.

Specifically, the variable clamping fixture based on the aircraft structural member in this embodiment may be disposed on one side of the aircraft structural member, the other side is an abutting platform of the aircraft structural member, the aircraft structural member is clamped and fixed on one side, two variable clamping fixtures of this embodiment may also be disposed on two sides of the aircraft structural member in a mirror image manner, and the aircraft structural member is clamped and fixed from two sides by the two variable clamping fixtures.

Referring to fig. 3, in order to realize the movement of the clamping block 33 on the clamping plate 32, the clamping block 33 includes a connecting rod 331 and round tables 332 disposed at two ends of the connecting rod 331, a deep hole slot 321 for the clamping block 31 to pass through is disposed in the clamping plate 32, the diameter of the through hole of the deep hole slot 321 is greater than that of the connecting rod 331 and smaller than that of the round table 332, the compression spring 34 is sleeved on the connecting rod 331, one end of the compression spring 34 abuts against the clamping plate 32, and the other end abuts against the round table 332, in the clamping process, in order to protect the aircraft structural member and prevent the rigid friction between the clamping block 33 and the aircraft structural member, a rubber ferrule 35 is disposed at the end of the clamping block 33.

Specifically, in order to match the changeable shape structure of the aircraft structural member, the clamping blocks 33 distributed in a matrix manner are ensured to be densely distributed as much as possible, and the distance between the circular truncated cones 332 on two adjacent clamping blocks 33 is less than 5 cm.

Specifically, in order to ensure that the follow-up clamping device 3 can clamp an aircraft structural member, a pressing plate 4 protruding out of the clamping plate is arranged at the top of the clamping plate 33, a pressure sensor 5 and a pressure signal collector 6 are arranged on the pressing plate 4, the follow-up clamping device 3 is lifted through the lifting device 1, then the aircraft structural member is placed below the pressing plate 4, the lifting device 1 drives the follow-up clamping device 3 downwards to descend until the pressing plate 4 abuts against the aircraft structural member, the pressure sensor 5 receives a signal at the moment, the signal is transmitted to the pressure signal collector 6 to be displayed, the lifting device 1 stops moving, and at the moment, the clamping plate 32 of the follow-up clamping device 3 can be ensured to be in contact with the aircraft structural member.

Referring to fig. 4, the lifting device 1 comprises a cylinder 11, a threaded connector 12, a lifting shaft 13, a sealing ring 14, a first gas/liquid inlet/outlet hole 15 and a second gas/liquid inlet/outlet hole 16, wherein the threaded connector 12 is used for connecting the horizontal sliding device 2; the lifting shaft 13 is arranged in the cylinder body 11, the lower end of the lifting shaft is sleeved with a sealing ring 14 which can move in the cylinder body along with the lifting shaft, the upper end of the lifting shaft is sleeved in the sealing ring 14 fixed in the cylinder body 11, the threaded connector 12 is positioned at the upper end of the lifting shaft 13, and when the lifting shaft 13 works, the lifting shaft 13 is lifted by controlling the sequence of gas/liquid inlet and outlet of the first gas/liquid inlet and outlet hole 15 and the second gas/liquid inlet and outlet hole 16 in the cylinder body 11, so that the purpose of quickly and greatly adjusting the height of the follow-up clamping device 3 is realized.

Referring to fig. 5, specifically, the horizontal sliding device 2 includes a horizontal sliding platform 21 disposed on the lifting shaft 13, and is connected to the lifting shaft 13 through a threaded connector 12, a slide rail 22 is disposed on the horizontal sliding platform 21, a clamping platform 23 is disposed on the slide rail 22, the following clamping device 3 is disposed on the clamping platform 23, a driving cylinder 24 for pushing the clamping platform 23 is disposed on one side of the slide rail 22, and the driving cylinder 24 pushes the clamping platform 23, so as to drive the following clamping device 3 to reach a suitable clamping position.

The above-mentioned embodiments are merely preferred embodiments for fully illustrating the present invention, and the scope of the present invention is not limited thereto. Equivalent substitutes or changes made by the technical personnel in the technical field on the basis of the utility model are all within the protection scope of the utility model. The protection scope of the present invention is subject to the claims.

Claims

1. The variable clamping fixture based on the aircraft structural part is characterized by comprising a lifting device, a horizontal sliding device arranged on the lifting device and a follow-up clamping device arranged on the horizontal sliding device, wherein the lifting device and the horizontal sliding device drive the follow-up clamping device to realize horizontal movement and vertical movement on a vertical plane, the follow-up clamping device comprises a clamping cylinder, a clamping plate is arranged on a cylinder push rod of the clamping cylinder, clamping blocks distributed in a matrix mode are arranged on the outer side of the clamping plate, the clamping blocks are inserted into a clamping plate, and a compression spring is arranged between the clamping block and the clamping plate.

2. The variable clamping fixture based on aircraft structural parts of claim 1, wherein the lifting device comprises a cylinder body, a threaded connector, a lifting shaft, a sealing ring, a first gas/liquid inlet/outlet hole and a second gas/liquid inlet/outlet hole, wherein the threaded connector is used for connecting the horizontal sliding device; the lifting shaft is arranged in the cylinder body, the lower end of the lifting shaft is sleeved with a sealing ring which can move in the cylinder body along with the lifting shaft, the upper end of the lifting shaft is sleeved in the sealing ring fixed in the cylinder body, the threaded connector is positioned at the upper end of the lifting shaft, and when the lifting shaft works, the lifting shaft is lifted by controlling the sequence of gas/liquid inlet and outlet of the first gas/liquid inlet and outlet hole and the sequence of gas/liquid inlet and outlet of the second gas/liquid inlet and outlet hole in the cylinder.

3. The aircraft structural part-based variable clamping fixture as claimed in claim 2, wherein the horizontal sliding device comprises a horizontal sliding platform arranged on the lifting shaft, the horizontal sliding platform is connected with the lifting shaft through a threaded connector, a sliding rail is arranged on the horizontal sliding platform, a clamping platform is arranged on the sliding rail, the follow-up clamping device is arranged on the clamping platform, and a driving cylinder for pushing the clamping platform is arranged on one side of the sliding rail.

4. The variable clamping fixture based on the aircraft structural part as claimed in claim 1, wherein the clamping block comprises a connecting rod and a circular truncated cone arranged at two ends of the connecting rod, a deep hole groove for the clamping block to pass through is formed in the clamping plate, the diameter of a through hole of the deep hole groove is larger than that of the connecting rod and smaller than that of the circular truncated cone, the compression spring is sleeved on the connecting rod, one end of the compression spring abuts against the clamping plate, and the other end of the compression spring abuts against the circular truncated cone.

5. The convertible clamping fixture of claim 4, wherein the distance between the circular truncated cones on two adjacent clamping blocks is less than 5 cm.

6. The convertible clamping vise of claim 1 wherein the clamping block is provided with a rubber ferrule at the end.

7. The convertible clamping fixture for aircraft structural members as claimed in claim 1, wherein said clamping plate is provided with a pressing plate protruding from the top thereof.

8. The aircraft structural member-based convertible clamping fixture of claim 7, wherein the pressure plate is provided with a pressure sensor and a pressure signal collector.