CN219075516U

CN219075516U - Aircraft combined material part assembly fixture

Info

Publication number: CN219075516U
Application number: CN202320024165.7U
Authority: CN
Inventors: 吴谦; 何崇; 黄支友
Original assignee: Jingdezhen Changhe Aviation Equipment Technology Co ltd
Current assignee: Jingdezhen Changhe Aviation Equipment Technology Co ltd
Priority date: 2023-01-05
Filing date: 2023-01-05
Publication date: 2023-05-26
Anticipated expiration: 2033-01-05

Abstract

The utility model discloses an aircraft composite material part assembly fixture which comprises a workbench and supporting legs, wherein a bearing table surface is fixedly arranged on one side surface of the top of the workbench. According to the utility model, the assembly cavity is adopted, in the actual use process, personnel can realize bearing operation of parts through the assembly cavity, and the parts can be pushed out to be attached to the surface of an airplane through pushing of the fifth hydraulic rod in the subsequent assembly operation, so that the assembly operation is performed.

Description

Aircraft combined material part assembly fixture

Technical Field

The utility model relates to the technical field of aircraft assembly tools, in particular to an aircraft composite material part assembly tool.

Background

Aircraft assembly is an important element of aircraft manufacturing. In this link, how to ensure coordination between parts and tools, and between tools and tools, and thus ensure the assembly accuracy of an aircraft is an important point in aircraft manufacturing, and many parts made of composite materials are included therein.

The prior art has the following publication numbers: CN115157191A relates to aircraft tubular part assembly and uses rotational positioning frock, relates to aircraft assembly frock technical field, and mainly used solves current aircraft assembly frock when using, and it does not normally possess rotational positioning's function, is unfavorable for the problem of aircraft tubular part assembly. The main structure is as follows: the lifting mechanism is arranged in the fixed box, the stabilizing mechanism and the rotating mechanism are arranged on the upper surface of the supporting seat, and the rotating mechanism is detachably connected with one end of the tubular part through the positioning mechanism. According to the rotary positioning tool for assembling the tubular part of the airplane, provided by the utility model, the rotary mechanism is arranged, so that the tubular part can be rotated, and an assembling work can be completed by a worker without changing an assembling position, so that the assembling work of the tubular part is more convenient, the working efficiency of the assembling of the airplane is improved, the labor intensity of the worker is reduced, and the assembling work of the airplane has certain flexibility.

The above patent still has certain drawbacks in use: the position of the tool structure used by the tool cannot be adjusted effectively, so that the assembly position of the part above the tool is fixed easily, the part can be installed at different positions on the surface of an airplane only by adjusting the position of the tool, the whole operation range is limited, and the tool structure adopts single-station operation, so that the operation of the next group of parts can be carried out after the whole operation process is required to wait for the placement and the installation of the part, the operation time is long, and the operation progress is not facilitated.

For the problems in the related art, no effective solution has been proposed at present.

Disclosure of Invention

(one) solving the technical problems

Aiming at the defects of the prior art, the utility model provides an aircraft composite material part assembly tool which has the advantages of wide assembly range, high operation efficiency and multi-station operation, thereby solving the problems in the prior art.

(II) technical scheme

In order to realize the advantages of wide assembly range, high operation efficiency and multi-station operation, the utility model adopts the following specific technical scheme:

the utility model provides an aircraft combined material part assembly fixture, includes workstation and supporting leg, workstation top one side surface position fixed mounting has the loading table face, loading table face top surface position butt has an assembly section of thick bamboo, assembly section of thick bamboo one end is connected with the carousel, carousel one end is connected with the connecting axle, the support frame has been cup jointed to the connecting axle periphery, connecting axle one end is connected with the brake motor that is located workstation top opposite side surface position through the drive belt, separate the platen in the inside intermediate position of assembly section of thick bamboo, separate platen both ends and be located assembly section of thick bamboo internal position symmetry and be equipped with the assembly chamber, slide bar is all installed to assembly chamber top surface position and separate platen surface position, slide bar periphery sliding connection has the movable seat, movable seat one end threaded connection has fixing bolt, movable seat one end fixed mounting has the fixing base, the inside intermediate position fixed mounting of fixing base bottom has the second hydraulic stem, second hydraulic stem one end is located fixing base bottom surface position and is connected with the movable rod, movable rod surface position rotates and is connected with the roller.

Further, the fifth hydraulic rods are symmetrically arranged at the positions of the inner wall surfaces of two sides of the inner part of the assembly cavity at one end of each movable rod, a push plate is fixedly arranged at one end of each fifth hydraulic rod, a first hydraulic rod is fixedly arranged at the middle position of the top surface of each push plate, a support platen is connected between the first hydraulic rods, an electric turntable is arranged at the surface position of one side of each support platen, a fixed rod is fixedly arranged at the middle position of the surface of one side of each electric turntable, a plurality of groups of third hydraulic rods are symmetrically arranged at the surface positions of two sides of each fixed rod, an inner supporting ring is fixedly arranged at one end of each third hydraulic rod, a fourth hydraulic rod is symmetrically arranged at the positions of two sides of the inner part of each electric turntable, and one end of each fourth hydraulic rod penetrates through one side of each electric turntable and is connected with the outer pressing ring.

Furthermore, supporting legs are symmetrically arranged on the two side surfaces of the bottom of the workbench.

Further, an arc groove for the rotary bearing of the assembly barrel is formed in the surface of the bearing table.

Further, the rollers are provided with a plurality of groups, the installation positions of the rollers at the two sides are the same as the rotation direction of the part, and the installation positions of the rollers at the middle position are the same as the moving direction of the part.

Further, the inner propping ring and the outer pressing ring are provided with soft cushions on the surface.

Furthermore, a channel for installing and using the connecting shaft is arranged on the surface of the supporting frame.

Further, a channel for inserting the fixing bolt is arranged on the surface of the movable seat.

(III) beneficial effects

Compared with the prior art, the utility model provides an aircraft composite material part assembly tool, which has the following beneficial effects:

(1) According to the utility model, the assembly cavity is adopted, in the actual use process, personnel can realize bearing operation of parts through the assembly cavity, and the parts can be pushed out to be attached to the surface of an airplane through pushing of the fifth hydraulic rod in the subsequent assembly operation, so that the assembly operation is performed.

(2) According to the utility model, the turntable and the electric turntable are adopted, and in the subsequent assembly process, the angle of the assembly cavity, the position of the assembly cavity and the angle of the part can be respectively adjusted through the rotation of the turntable and the rotation of the electric turntable, so that the part can be subjected to assembly operation in a larger range on the surface of the aircraft, the whole assembly range is improved, and the assembly range is wide.

Drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic structural view of an aircraft composite part assembly tooling according to the present utility model;

FIG. 2 is a schematic view of the structure of a load-bearing table of the present utility model;

FIG. 3 is a schematic view of the construction of the fitting cartridge of the present utility model;

fig. 4 is a schematic structural view of a first hydraulic lever of the present utility model.

In the figure:

1. a work table; 2. braking the motor; 3. a transmission belt; 4. a first hydraulic lever; 5. a support platen; 6. a connecting shaft; 7. a support frame; 8. a turntable; 9. an assembly chamber; 10. an assembly barrel; 11. an electric turntable; 12. a fixed rod; 13. a partition platen; 14. a fixing bolt; 15. a slide bar; 16. a movable seat; 17. a fixing seat; 18. a second hydraulic lever; 19. a moving rod; 20. a roller; 21. a third hydraulic lever; 22. an inner abutment ring; 23. support legs; 24. a load-bearing table top; 25. a fourth hydraulic lever; 26. a push plate; 27. an outer pressure ring; 28. and a fifth hydraulic lever.

Detailed Description

For the purpose of further illustrating the various embodiments, the present utility model provides the accompanying drawings, which are a part of the disclosure of the present utility model, and which are mainly used to illustrate the embodiments and, together with the description, serve to explain the principles of the embodiments, and with reference to these descriptions, one skilled in the art will recognize other possible implementations and advantages of the present utility model, wherein elements are not drawn to scale, and like reference numerals are generally used to designate like elements.

According to an embodiment of the utility model, an aircraft composite part assembly fixture is provided.

The utility model is further described with reference to the accompanying drawings and the specific embodiment, as shown in fig. 1-4, an aircraft composite material part assembly tool according to the embodiment of the utility model comprises a workbench 1 and supporting legs 23, wherein a bearing table surface 24 is fixedly arranged at the surface position of one side of the top of the workbench 1, the top surface position of the bearing table surface 24 is abutted to an assembly cylinder 10, one end of the assembly cylinder 10 is connected with a rotary table 8, one end of the rotary table 8 is connected with a connecting shaft 6, the periphery of the connecting shaft 6 is sheathed with a supporting frame 7, one end of the connecting shaft 6 is connected with a brake motor 2 positioned at the surface position of the other side of the top of the workbench 1 through a transmission belt 3, a separation platen 13 is arranged at the middle position inside the assembly cylinder 10, sliding rods 15 are symmetrically arranged at the two ends of the separation platen 13 and are respectively arranged at the inner position of the assembly cylinder 10, a movable seat 16 is connected with one end of the movable seat 16 in a threaded manner, one end of the movable seat 16 is fixedly provided with a fixed seat 17, the middle position inside the fixed seat 17 is fixedly arranged at the bottom of the fixed seat 17, one end of the movable seat 18 is fixedly provided with a second hydraulic rod 18, one end of the movable rod 19 is positioned at the bottom surface position of the fixed seat 19, and the movable rod 19 is connected with a rotary rod 20 at the surface position of the fixed seat 19.

In one embodiment, one end of the moving rod 19 is symmetrically provided with fifth hydraulic rods 28 at the inner wall surface positions of two sides inside the assembly cavity 9, one end of each fifth hydraulic rod 28 is fixedly provided with a push plate 26, the middle position of the top surface of each push plate 26 is fixedly provided with a first hydraulic rod 4, a supporting platen 5 is connected between the first hydraulic rods 4, an electric turntable 11 is arranged at the surface position of one side of the supporting platen 5, a fixed rod 12 is fixedly arranged at the middle position of one side surface of the electric turntable 11, a plurality of groups of third hydraulic rods 21 are symmetrically arranged at the surface positions of two sides of the fixed rod 12, one end of each third hydraulic rod 21 is fixedly provided with an inner supporting ring 22, two side surface positions inside the electric turntable 11 are symmetrically provided with a fourth hydraulic rod 25, and one end of each fourth hydraulic rod 25 penetrates through one side of the electric turntable 11 to be connected with the outer pressing ring 27.

In one embodiment, supporting legs 23 are symmetrically arranged on the two side surfaces of the bottom of the workbench 1, the whole device can be fixed through the supporting legs 23, the whole use stability is convenient to strengthen, and the subsequent assembly effect of the composite material parts is further improved.

In one embodiment, the surface of the bearing table 24 is provided with an arc groove for the assembly drum 10 to rotate for bearing, the arc groove facilitates the rotation of the assembly drum 10, and the assembly drum 10 can be loaded, so that the whole device is prevented from being broken, and the operation pressure of the brake motor 2 is reduced.

In one embodiment, the rollers 20 are provided with a plurality of groups, the installation positions of the rollers 20 at two sides are the same as the rotation direction of the part, the installation positions of the rollers 20 at the middle position are the same as the movement direction of the part, the rollers 20 at two sides are mainly used for facilitating the left and right rotation of the part, and the rollers 20 at the middle position serve the purpose of facilitating the in and out of the part, so that a certain difference is generated in the installation and the paying-off of the rollers 20.

In one embodiment, the inner support ring 22 and the outer pressing ring 27 are provided with soft cushions at the surface positions, and the soft cushions can effectively reduce the clamping damage effect on the parts.

In one embodiment, the support 7 is provided with a channel at a surface position for mounting the connecting shaft 6.

In one embodiment, the surface of the movable seat 16 is provided with a channel for inserting the fixing bolt 14, the channel is convenient for inserting the fixing bolt 14, the movable seat 16 can be fixed through inserting the fixing bolt 14, the movable seat is prevented from shifting after moving in place, and the clamping and bearing effects of the tubular part made of the composite material are ensured.

Working principle: in the actual use process, an operator can place an aircraft tubular part made of composite materials into the assembly cavity 9, one end of the part is inserted into the fixing rod 12 after the part enters the assembly cavity 9, at the moment, the inner propping ring 22 can be driven to firmly butt against the inside of the tubular part through the operation adjustment of the third hydraulic rod 21 at the two ends of the fixing rod 12, meanwhile, the outer surface of the part can be firmly clamped by the outer pressing ring 27 through the operation adjustment of the fourth hydraulic rod 25, the fixing effect on the tubular part can be improved through the cooperation of the inner propping ring 22 and the outer pressing ring 27, the subsequent assembly is avoided, the assembly effect is reduced, then after the fixing is completed, the moving rod 19 at the relative position can be regulated through the operation of the second hydraulic rod 18 in the assembly cavity 9, the roller 20 at the surface position can be abutted against the surface position of the part, on one hand, the fixing and supporting functions of the roller 20 are realized, the movement stability in the subsequent assembly is ensured, on the other hand, the purpose of assisting the movement of the tubular part can be achieved through the rotation of the roller 20, friction is reduced, excessive abrasion of the part is avoided, the whole assembly integrity is improved, then in the subsequent assembly process, the angle, the position and the angle of the part of the assembly cavity 9 can be respectively adjusted through the rotation of the turntable 8 and the rotation of the electric turntable 11, the assembly operation of the part can be carried out in a larger range on the surface of an airplane, the whole assembly range is improved, then the whole part can be pushed out through the operation of the fifth hydraulic rod 28, the part can be contacted with the surface position of the airplane, the assembly operation of the part is realized, and in the assembly process of the part, the new part can be placed in the unused assembly cavity 9 of another group, the subsequent assembly operation can be conveniently and directly performed, the assembly operation can be performed without waiting for the placement of the part, the waiting time during operation is reduced, the operation time can be effectively shortened, the whole operation efficiency is further improved, the assembly operation of the parts can be simultaneously performed through the two groups of assembly cavities 9 when personnel need, the whole practicability of the device is enhanced, and the device has the advantages of wide assembly range, high operation efficiency and multi-station operation.

In the present utility model, unless explicitly specified and limited otherwise, the terms "mounted," "configured," "connected," "secured," "screwed," and the like are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intermediaries, or in communication with each other or in interaction with each other, unless explicitly defined otherwise, the meaning of the terms described above in this application will be understood by those of ordinary skill in the art in view of the specific circumstances.

The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the utility model.

Claims

1. The utility model provides an aircraft combined material part assembly fixture, includes workstation (1) and supporting leg (23), its characterized in that, workstation (1) top one side surface position fixed mounting has loading table surface (24), loading table surface (24) top surface position butt has assembly section of thick bamboo (10), assembly section of thick bamboo (10) one end is connected with carousel (8), carousel (8) one end is connected with connecting axle (6), support frame (7) have been cup jointed to connecting axle (6) periphery, connecting axle (6) one end is connected with brake motor (2) that are located workstation (1) top opposite side surface position through drive belt (3), separation platen (13) are installed to assembly section of thick bamboo (10) inside intermediate position, separation platen (13) both ends are located assembly section of thick bamboo (10) inside position symmetry and are equipped with assembly chamber (9), assembly chamber (9) top surface position and separation platen (13) surface position all install fixing base (15), peripheral sliding connection has movable seat (16) of carousel (15), movable seat (16) one end is connected with screw thread (14), movable seat (16) fixed seat (17) fixed mounting slide bar (17) fixed mounting base (17), one end of the second hydraulic rod (18) is positioned at the bottom surface of the fixed seat (17) and is connected with a moving rod (19), and the surface of the moving rod (19) is rotatably connected with a roller (20).

2. The aircraft composite part assembly fixture according to claim 1, wherein a fifth hydraulic rod (28) is symmetrically arranged at one end of the moving rod (19) at the surface position of the inner wall at two sides inside the assembly cavity (9), a push plate (26) is fixedly arranged at one end of the fifth hydraulic rod (28), a first hydraulic rod (4) is fixedly arranged at the middle position of the top surface of the push plate (26), a supporting platen (5) is connected between the first hydraulic rods (4), an electric turntable (11) is arranged at one side surface position of the supporting platen (5), a fixing rod (12) is fixedly arranged at the middle position of one side surface of the electric turntable (11), a plurality of groups of third hydraulic rods (21) are symmetrically arranged at two side surface positions of the fixing rod (12), an inner supporting ring (22) is fixedly arranged at one end of the third hydraulic rod (21), a fourth hydraulic rod (25) is symmetrically arranged at two side surface positions inside the electric turntable (11), and one end of the fourth hydraulic rod (25) penetrates through one side of the electric turntable (11) to be connected with an outer part (27).

3. The aircraft composite part assembly fixture according to claim 1, wherein supporting legs (23) are symmetrically arranged on two side surfaces of the bottom of the workbench (1).

4. An aircraft composite part assembly fixture according to claim 1, wherein the surface of the bearing table (24) is provided with an arc groove for the rotary bearing of the assembly drum (10).

5. The aircraft composite part assembly fixture according to claim 1, wherein the rollers (20) are provided with a plurality of groups, the installation positions of the rollers (20) at two sides are the same as the rotation direction of the part, and the installation positions of the rollers (20) at the middle positions are the same as the movement direction of the part.

6. An aircraft composite part assembly fixture according to claim 2, wherein the inner abutment ring (22) and the outer pressure ring (27) are provided with cushions in their surface positions.

7. An aircraft composite part assembly fixture according to claim 1, wherein the support frame (7) is provided with a channel for mounting the connecting shaft (6) at the surface position.

8. An aircraft composite part assembly fixture according to claim 1, wherein the surface of the movable seat (16) is provided with a channel for the insertion of a fixing bolt (14).