CN215701084U

CN215701084U - Supporting device

Info

Publication number: CN215701084U
Application number: CN202121872028.6U
Authority: CN
Inventors: 赵秋华; 仇珩宇; 张婷; 杨光磊; 陈双霁; 沈冬; 沈亚军
Original assignee: Commercial Aircraft Corp of China Ltd; Shanghai Aircraft Manufacturing Co Ltd
Current assignee: Commercial Aircraft Corp of China Ltd; Shanghai Aircraft Manufacturing Co Ltd
Priority date: 2021-08-11
Filing date: 2021-08-11
Publication date: 2022-02-01
Anticipated expiration: 2031-08-11

Abstract

The utility model belongs to the technical field of aircraft production equipment, and discloses a supporting device which comprises a supporting component, wherein a bearing surface is arranged on the supporting component and used for bearing a workpiece, and a reference hole and a plurality of eccentric holes are also formed in the supporting component; the datum assembly is arranged in the datum hole, and one end, extending out of the datum hole, of the datum assembly is used for being inserted into a pre-installation hole of the workpiece; the eccentric assembly is characterized in that a group of eccentric assemblies are installed in each eccentric hole, the eccentric assemblies can eccentrically rotate in the eccentric holes, and one ends, extending out of the eccentric holes, of the eccentric assemblies are used for inserting into positioning holes of workpieces. The eccentric assembly can supplement the position deviation of the positioning hole of the workpiece, and realize the stable connection between the supporting device and the workpiece.

Description

Supporting device

Technical Field

The utility model relates to the technical field of aircraft production equipment, in particular to a supporting device.

Background

The aircraft tail end need carry out attitude adjustment in production assembling process, so that adjust mounted position to the most suitable position, when aircraft tail end carries out attitude adjustment, current mode adopts the support frock to support, when aircraft tail end is placed on the support frock, there is not fixed connection between the two, only with the help of the frictional force realization between the contact surface and transfer the appearance operation, whole in-process supports the frock and can't realize the synchronization linkage with aircraft tail end, cause and transfer the appearance precision not high, waste time and energy, inefficiency.

SUMMERY OF THE UTILITY MODEL

One object of the present invention is: provided is a support device which can compensate the position deviation of a positioning hole of a workpiece through an eccentric component and realize the stable connection between the support device and the workpiece.

In order to achieve the purpose, the utility model adopts the following technical scheme:

a support device, comprising:

the supporting component is provided with a bearing surface, the bearing surface is used for bearing a workpiece, and the supporting component is also provided with a reference hole and a plurality of eccentric holes;

the datum assembly is arranged in the datum hole, and one end, extending out of the datum hole, of the datum assembly is used for being inserted into the pre-installation hole of the workpiece;

the eccentric assembly is arranged in each eccentric hole, the eccentric assembly can eccentrically rotate in the eccentric hole, and one end, extending out of the eccentric hole, of the eccentric assembly is used for being inserted into the positioning hole of the workpiece.

As an optional technical solution, the supporting device further includes a bearing part, the bearing part is rotatably connected with the supporting component, and the bearing part is used for adjusting the supporting position of the supporting component on the workpiece.

As an optional technical solution, the bearing is a ball bearing.

As an optional technical solution, the eccentric assembly includes an eccentric bushing and a first connecting member, and the eccentric bushing is accommodated in the eccentric hole and fixedly sleeved on the periphery of the first connecting member.

As an optional technical solution, the reference assembly includes a coaxial bushing and a second connecting member, and the coaxial bushing is received in the reference hole and is fixedly sleeved on the outer periphery of the second connecting member.

As an optional technical scheme, the supporting component comprises an adjusting plate and a supporting plate, the reference hole and the eccentric hole are formed in the adjusting plate, the bearing surface is that the supporting plate deviates from one surface of the adjusting plate, and the adjusting plate is connected with the supporting plate through a fastener.

As an optional technical solution, at least two adjusting plates and at least two supporting plates are provided.

As an optional technical solution, the supporting assembly further includes a supporting beam, and the adjusting plate and the supporting plate are both fixedly mounted on the supporting beam.

As an optional technical solution, lifting lugs are respectively arranged at two ends of the supporting beam.

As an optional technical solution, the bearing surface is an arc surface.

The utility model has the beneficial effects that:

the utility model provides a supporting device which is used for supporting a workpiece, when the supporting device moves to one side of the workpiece, a bearing surface is abutted against the workpiece, one end of a reference assembly extends into a pre-installation hole of the workpiece to realize pre-positioning, and because the distance between the pre-installation holes and positioning holes of workpieces of different types is not fixed, one end of an eccentric assembly needs to extend into the positioning hole to realize final fixed connection, an operator rotates the eccentric assembly, the eccentric assembly rotates in the eccentric hole, the axis of the eccentric assembly is superposed with the central axis of the positioning hole to realize difference compensation, so that the eccentric assembly can accurately extend into the positioning hole of the workpiece.

Drawings

The utility model is explained in further detail below with reference to the figures and examples;

FIG. 1 is a schematic diagram illustrating a first perspective view of a support device according to an embodiment;

FIG. 2 is a schematic view of another embodiment of a support device from a first perspective;

FIG. 3 is an enlarged view of a portion of FIG. 2 at position A;

fig. 4 is an exploded view of a part of the structure of the supporting device according to the embodiment.

In fig. 1 to 4:

1. a support assembly; 11. an adjusting plate; 111. a reference hole; 112. an eccentric hole; 12. a support plate; 121. a bearing surface; 13. a fastener; 14. a support beam; 15. lifting lugs;

2. a reference assembly; 21. a coaxial bushing; 22. a second connecting member;

3. an eccentric assembly; 31. an eccentric bushing; 32. a first connecting member;

4. a carrier.

Detailed Description

In order to make the technical problems solved, technical solutions adopted and technical effects achieved by the present invention clearer, the technical solutions of the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

In the description herein, it is to be understood that the terms "upper," "lower," "left," "right," and the like are based on the orientation or positional relationship shown in the drawings for convenience in description and simplicity of operation, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the present invention. Furthermore, the terms "first" and "second" are used merely for descriptive purposes and are not intended to have any special meaning.

In the description herein, references to the description of "an embodiment," "an example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the utility model. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example.

The technical scheme of the utility model is further explained by the specific implementation mode in combination with the attached drawings.

The workpiece needs to be subjected to attitude adjustment in the production, assembly and production processes, so a support tool is usually adopted for supporting, but the workpiece is not fixedly connected with the support tool, and the attitude adjustment is realized through the friction force between contact surfaces, for example, the workpiece such as an airplane shell, a frame and the like is installed on the support tool.

As shown in fig. 1, the present embodiment takes an airplane housing as an example, and provides a supporting device, which includes a supporting assembly 1, a reference assembly 2 and an eccentric assembly 3, wherein the supporting assembly 1 is provided with a bearing surface 121, the bearing surface 121 is used for bearing the airplane housing, and the supporting assembly 1 is further provided with a reference hole 111 and a plurality of eccentric holes 112; the datum assembly 2 is mounted in the datum hole 111, and one end, extending out of the datum hole 111, of the datum assembly 2 is used for being inserted into a pre-installation hole of an airplane shell; each eccentric hole 112 is provided with a group of eccentric assemblies 3, the eccentric assemblies 3 can eccentrically rotate in the eccentric holes 112, and one ends of the eccentric assemblies 3 extending out of the eccentric holes 112 are used for being inserted into positioning holes of an airplane shell.

An operator moves the supporting device to the lower part of the airplane shell to enable the bearing surface 121 to abut against the airplane shell to realize primary support, then one end of the reference component 2 extends into a pre-installation hole of the airplane shell to realize pre-positioning, the distances between the pre-installation hole and the positioning hole on the airplane shell are different due to different airplane models, in order to meet the requirements of positioning accuracy and installation efficiency improvement, the eccentric component 3 of the embodiment can eccentrically rotate in the eccentric hole 112, the axis of the eccentric component 3 is coincided with the central axis of the positioning hole by gradually rotating the eccentric component 3 to realize position difference compensation, and finally one end of the eccentric component 3 can be aligned and extended into the positioning hole, so that the fixed connection between the supporting device and the airplane shell is realized, and the supporting requirement of synchronous linkage of the airplane shell and the supporting device is met, the method is suitable for the mass production stage of the airplane shell.

In particular, in order to satisfy the support stability of the aircraft housing, in some cases, the positioning hole is provided in plurality on the aircraft housing, and since the distance between the positioning hole and the pre-installation hole depends on the model of the aircraft, when the model of the aircraft is different, the distance between the positioning hole and the pre-installation hole is different, therefore, each set of eccentric assemblies 3 can be adjusted in position in the eccentric hole 112 before being inserted into the corresponding positioning hole to compensate for the position difference.

The number of the eccentric holes 112 and the eccentric assemblies 3 can be respectively set to one, two, or three, and the specific number can be set according to actual needs, and the embodiment is not limited.

As shown in fig. 2, optionally, the supporting device further includes a bearing member 4, the bearing member 4 is rotatably connected to the supporting assembly 1, and the bearing member 4 is used for adjusting the supporting position of the supporting assembly 1 on the aircraft shell. Optionally, the carrier 4 is a ball bearing.

The movable frame drives the positioner to move to the lower side of the aircraft shell, the output end of the positioner is upwards jacked to the inner ring of the ball bearing, the aircraft shell and the supporting device can be synchronously linked when the movable frame is transferred in a production workshop or the positioner is further jacked upwards, the accuracy of posture adjustment is greatly improved, and the production efficiency is improved. And the inner ring of the ball bearing can rotate relative to the outer ring, so that when the moving frame changes the moving direction, the stable support of the support device to the aircraft shell cannot be interfered.

As shown in fig. 3, in the present embodiment, the supporting assembly 1 includes an adjusting plate 11 and a supporting plate 12, the reference hole 111 and the eccentric hole 112 are both opened on the adjusting plate 11, the bearing surface 121 is a surface of the supporting plate 12 facing away from the adjusting plate 11, and the adjusting plate 11 and the supporting plate 12 are connected by a fastener 13. The support plate 2 can support the first connecting piece 32 and the second connecting piece 22, the adjusting plate 11 can define the rotation tracks of the eccentric bushing 31 and the coaxial bushing 21, so that the reference assembly 2 and the eccentric assembly 3 can support the aircraft shell and the reference assembly 2 can realize position adjustment.

Alternatively, the fasteners 13 are screws. Avoidance holes are formed in the positions, corresponding to the reference hole 111 and the eccentric hole 112, of the support plate 12, and the avoidance holes can avoid the first connecting piece 32 or the second connecting piece 22 from being close to the airplane shell.

As shown in fig. 4, in the present embodiment, the eccentric assembly 3 includes an eccentric bushing 31 and a first connecting member 32, and the eccentric bushing 31 is received in the eccentric hole 112 and fixed to an outer circumference of the first connecting member 32. The first connecting member 32 may be selected as a bolt, and when an operator screws the bolt, the eccentric bushing 31 eccentrically rotates in the eccentric hole 112, so that the bolt can be aligned with the positioning hole of the aircraft housing.

In the present embodiment, the reference assembly 2 includes a coaxial bushing 21 and a second connecting member 22, the coaxial bushing 21 is received in the reference hole 111 and is fixedly sleeved on the outer periphery of the second connecting member 22. The second connecting member 22 may be selected as a bolt, and when the fixing connection is performed, the bolt is used for pre-positioning.

In some embodiments, as shown in fig. 1, the support device is used for supporting an arc-shaped part in the aircraft shell, the adjusting plate 11 and the support plate 12 of the support device are arranged in one, and the bearing surface 121 of the support plate 12 is an arc-shaped surface.

In other embodiments, as shown in fig. 2, the support device is used for supporting a flat portion of the aircraft shell, and the adjusting plate 11 and the support plate 12 of the support device are respectively provided with two plates to increase the support area and avoid collapse. The support assembly 1 of the support device further comprises a support beam 14, and the adjustment plate 11 and the support plate 12 are both fixedly mounted to the support beam 14. Lifting lugs 15 are respectively arranged at two ends of the supporting beam 14, so that the supporting device is conveniently lifted to a flat section of the airplane shell.

In addition, the foregoing is only the preferred embodiment of the present invention and the technical principles applied. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the utility model. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. A support device, comprising:

2. The support device of claim 1, further comprising a bearing member rotatably coupled to the support assembly, the bearing member being configured to adjust a support position of the support assembly relative to the workpiece.

3. The support device of claim 2, wherein the bearing is a ball bearing.

4. The support device of claim 1, wherein the eccentric assembly includes an eccentric bushing and a first connector, the eccentric bushing being received within the eccentric bore and secured about an outer periphery of the first connector.

5. The support device of claim 1, wherein the reference assembly includes a coaxial bushing and a second connector, the coaxial bushing being received within the reference bore and secured about an outer periphery of the second connector.

6. The support device of claim 1, wherein the support assembly comprises an adjusting plate and a support plate, the reference hole and the eccentric hole are both formed in the adjusting plate, the bearing surface is a surface of the support plate facing away from the adjusting plate, and the adjusting plate and the support plate are connected through a fastener.

7. The support device of claim 6, wherein at least two of the adjustment plate and the support plate are provided.

8. The support apparatus of claim 6, wherein the support assembly further comprises a support beam, the adjustment plate and the support plate each being fixedly mounted to the support beam.

9. The supporting device as claimed in claim 6, wherein the supporting beam is provided with lifting lugs at both ends thereof.

10. The support device of claim 6, wherein the bearing surface is an arcuate surface.