CN218364289U

CN218364289U - Assembly fixture of frame airplane beam assembly

Info

Publication number: CN218364289U
Application number: CN202222732192.8U
Authority: CN
Inventors: 刘永; 申桂英; 李威; 钱小东
Original assignee: Dongfeng Special Equipment Technology Co ltd
Current assignee: Dongfeng Special Equipment Technology Co ltd
Priority date: 2022-10-13
Filing date: 2022-10-13
Publication date: 2023-01-24
Anticipated expiration: 2032-10-13

Abstract

The utility model discloses an assembly fixture of a frame airplane beam assembly, which comprises a working platform, a first clamping mechanism, a second clamping mechanism and a control mechanism, wherein the first clamping mechanism is arranged on the working platform and can clamp and support a beam in the middle of the frame airplane beam assembly; the second clamping mechanism is connected to the working platform in a sliding mode, the distance between the second clamping mechanism and the first clamping mechanism is adjustable, and clamping and limiting of the sheet body on the side portion of the airplane beam assembly can be achieved; the control mechanism is arranged on the working platform and can drive the first clamping mechanism and the second clamping mechanism to clamp the airplane beam assembly. The utility model discloses in having been applied to actual production, it is obvious according to the feedback result of use, improved production efficiency greatly, realized the compatible sharing of many varieties product, reduced personnel's operation intensity of labour.

Description

Assembly fixture of frame airplane beam assembly

Technical Field

The utility model relates to a frame aircraft roof beam assembly technical field, concretely relates to frame aircraft roof beam assembly's assembly fixture.

Background

The frame airplane beam assembly 1 is composed of a beam 11 and a plurality of sheets 12 (a left front sheet, a left rear sheet, a right front sheet and a right rear sheet), and is commonly called an airplane beam assembly because of being similar to a wing, as shown in fig. 1. In frame aircraft roof beam assembly field, the counterpoint of each part adopts the manual work to counterpoint usually, presss from both sides tightly through the active grab manual work, has that personnel intensity of labour is big, the assembly precision is low, production efficiency is little etc. not enough.

SUMMERY OF THE UTILITY MODEL

The utility model provides a pair of frame aircraft roof beam assembly's assembly fixture, fine solution the manual assembly precision low problem that above-mentioned reason leads to, greatly reduced workman intensity of labour, improved production efficiency.

In order to solve the technical problem, the utility model discloses a following technical scheme realizes:

the utility model provides a frame aircraft roof beam assembly's assembly fixture, assembly fixture includes:

a working platform;

the first clamping mechanism is arranged on the working platform and used for clamping and supporting a cross beam in the middle of the airplane beam assembly;

the second clamping mechanism is connected to the working platform in a sliding mode, the distance between the second clamping mechanism and the first clamping mechanism is adjustable, and the second clamping mechanism is used for clamping and limiting the sheet body on the side portion of the airplane beam assembly;

and the control mechanism is used for driving the first clamping mechanism and the second clamping mechanism to clamp the airplane beam assembly.

Preferably, the first clamping mechanism comprises a fixed seat, a supporting seat and a first clamping assembly; the supporting seat is fixed on the top surface of the fixed seat and used for installing and positioning the cross beam; the first clamping assembly is fixed on the top surface of the fixed seat and used for clamping the cross beam.

Furthermore, the supporting seat is provided with a first positioning pin which can be matched with the positioning hole in the cross beam.

Further, the first clamping component comprises a turning cylinder, a transmission arm and a pressing claw, the turning cylinder is fixed on the fixed seat, the output end of the turning cylinder is fixedly connected with the transmission arm, the other end of the transmission arm extends towards the side where the supporting seat is located and is fixedly connected with the pressing claw, and the pressing claw is located above the supporting seat.

Further, first clamping component includes rotatory lift cylinder and pressure head, rotatory lift cylinder is fixed in on the fixing base, rotatory lift cylinder output with pressure head fixed connection, rotatory lift cylinder can drive the pressure head goes up and down along vertical direction and rotates along the horizontal direction, in order to realize right the clamp of crossbeam is tight.

Still further, the rotary lifting cylinder is positioned between the supporting seat and the overturning cylinder.

Preferably, the second clamping mechanism comprises two second clamping assemblies which are oppositely arranged at the left side and the right side of the first clamping mechanism, and the distance between the two second clamping assemblies is adjustable; each second clamp assembly comprises a movable box, a driving assembly and a clamping connecting rod, the bottom of the movable box is connected with the working platform in a sliding mode, the driving assembly is arranged in the movable box and is in transmission connection with the clamping connecting rod, and the other end of the clamping connecting rod can extend out of the movable box; the driving assembly can drive the clamping connecting rod to move along the horizontal direction and swing along the vertical direction so as to clamp the sheet body.

Furthermore, the driving assembly comprises a horizontal cylinder and a vertical cylinder, and the clamping connecting rod is provided with a horizontally arranged slotted hole; the horizontal air cylinders are horizontally arranged, and the output ends of the horizontal air cylinders are rotationally connected with the clamping connecting rods; the vertical air cylinders are vertically arranged, the output ends of the vertical air cylinders are provided with bearings, and the bearings are embedded in the elongated slots and are in sliding connection with the elongated slots.

Furthermore, a variable-pitch assembly is arranged between the two second clamping assemblies and comprises a telescopic cylinder, a head connecting seat capable of being fixedly connected with one of the second clamping assemblies is arranged at the output end of the telescopic cylinder, and a tail connecting seat capable of being fixedly connected with the other second clamping assembly is arranged at the other end of the telescopic cylinder.

Furthermore, a positioning clamp is arranged on the outer side wall, close to the first clamping mechanism, of the moving box, the positioning clamp comprises a template and a second positioning pin, and the second positioning pin is matched with the positioning hole in the sheet body.

Compared with the prior art, the utility model, following advantage and beneficial effect have:

the utility model discloses in having been applied to actual production, it is obvious according to the feedback result of use, improved production efficiency greatly, realized the compatible sharing of many varieties product, reduced personnel's operation intensity of labour.

The first clamping mechanism of the utility model is used for auxiliary clamping of the beam, and the clamping process is realized by the action of the rotary lifting cylinder or the overturning cylinder, thus improving the stability and accuracy of product assembly; the second clamping mechanism is used for auxiliary clamping of the sheet body, and the horizontal cylinder, the vertical cylinder and the variable pitch assembly act to further realize a clamping process, so that the structure is flexible to apply, small in occupied space, capable of realizing compatible production of various products, greatly reducing the labor intensity of personnel operation, and convenient and quick to operate in a one-key mode; the variable pitch component is convenient for taking and placing workpieces, and can realize multi-product compatible production through variable pitch; the positioning clamp realizes the compatible production of multiple varieties through different clamping fixtures, and the replacement is convenient and quick; the control mechanism is mainly used for controlling the actions of all the pneumatic executive components and realizing the normal operation of the assembly machine.

Drawings

FIG. 1 is a schematic structural view of the frame airplane beam assembly of the present invention;

fig. 2 is a schematic view of the assembly tool of the present invention;

fig. 3 is a schematic perspective view of the assembly fixture of the present invention;

fig. 4 is a schematic perspective view of the first clamping mechanism of the present invention;

fig. 5 is a schematic side view of the first clamping mechanism of the present invention;

fig. 6 is a schematic top view of the first clamping mechanism of the present invention;

fig. 7 is a schematic perspective view of a second clamping assembly according to the present invention;

fig. 8 is a schematic perspective view of the second clamping assembly of the present invention with the outer casing removed;

fig. 9 is a schematic top view of the second clamping assembly of the present invention with the housing removed;

fig. 10 is a schematic structural view of the positioning jig of the present invention;

fig. 11 is a schematic structural view of the pitch-variable assembly of the present invention;

fig. 12 is a schematic structural view of the assembly tool for assembling the airplane beam assembly according to the present invention;

fig. 13 is the utility model discloses assembly fixture assembles the spatial structure sketch map of aircraft roof beam assembly.

Reference numbers in the figures: 1. an aircraft spar assembly; 11. a cross beam; 12. a sheet body; 2. a working platform; 3. a first clamping mechanism; 31. a fixed seat; 32. a supporting seat; 33. a first clamping assembly; 321. a first positioning pin; 331a, a turnover cylinder; 332a, a drive arm; 333a, pressing claws; 331b, a rotary lifting cylinder; 332b, an indenter; 4. a second clamping mechanism; 41. a second clamping assembly; 411. a mobile box; 412. a drive assembly; 413. clamping the connecting rod; 414. a pitch change assembly; 415. positioning a clamp; 416. fixing a pin shaft; 4121. a horizontal cylinder; 4122. a vertical cylinder; 4123. a bearing; 4124. a long slot hole; 4141. a telescopic cylinder; 4142. a head connecting seat; 4143. a tail connecting seat; 4151. a template; 4152. a second positioning pin; 5. a control mechanism; 6. a stop member.

Detailed Description

In order to make the technical solution of the present invention better understood by those skilled in the art, the following description of the preferred embodiments of the present invention is given with reference to the accompanying examples, but it should be understood that the drawings are for illustrative purposes only and are not to be construed as limiting the patent; for the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted. The positional relationships depicted in the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.

As shown in fig. 2-13, the utility model provides an assembly fixture of frame airplane beam assembly.

Specifically, please refer to fig. 2 and 3:

the assembly tool comprises a working platform 2, a first clamping mechanism 3, a second clamping mechanism 4 and a control mechanism 5, wherein the first clamping mechanism 3 is arranged on the working platform 2 and can clamp and support a cross beam 11 in the middle of an airplane beam assembly 1; the second clamping mechanism 4 is connected to the working platform 2 in a sliding manner, the distance between the second clamping mechanism and the first clamping mechanism 3 is adjustable, and clamping and limiting can be realized on the sheet body 12 at the side part of the airplane beam assembly 1; the control mechanism 5 is arranged on the working platform 2 and can drive the first clamping mechanism 3 and the second clamping mechanism 4 to clamp the airplane beam assembly 1.

Referring to fig. 4-6, in one embodiment:

the first clamping mechanism 3 comprises a fixed seat 31, a supporting seat 32 and a first clamping assembly 33, wherein the supporting seat 32 is fixed on the top surface of the fixed seat 31 and is used for installing and positioning the cross beam 11; the first clamping assembly 33 is fixed to the top surface of the fixed seat 31 for clamping the cross beam 11. The supporting seat 32 is provided with a first positioning pin 321 which can be matched with the positioning hole on the beam 11.

With the above structure, the clamping action of the first clamping assembly 33 can assist in clamping the cross beam 11 positioned on the supporting seat 32, and lays the foundation for the subsequent assembly of the sheet 12.

Referring to fig. 4-6, in one embodiment:

the first clamping assembly 33 includes a turning cylinder 331a, a driving arm 332a and a pressing claw 333a, the turning cylinder 331a is fixed on the fixing base 31, an output end of the turning cylinder 331a is fixedly connected with the driving arm 332a, the other end of the driving arm 332a extends to the side of the supporting base 32 and is fixedly connected with the pressing claw 333a, and the pressing claw 333a is located above the supporting base 32.

According to the above structure design, the pressing claw 333a can move downwards under the driving of the turning cylinder 331a to press the cross beam 11 positioned on the supporting seat 32, so as to achieve the purpose of clamping the cross beam 11.

Referring to fig. 4-6, in one embodiment:

the first clamping assembly 33 comprises a rotary lifting cylinder 331b and a pressure head 332b, the rotary lifting cylinder 331b is fixed on the fixing base 31, an output end of the rotary lifting cylinder 331b is fixedly connected with the pressure head 332b, and the rotary lifting cylinder 331b can drive the pressure head 332b to lift along a vertical direction and rotate along a horizontal direction so as to clamp the beam 11. Wherein, the number of the rotary lifting cylinders 331b and the pressure heads 332b is set to 2 respectively, and the two sets are oppositely arranged.

According to the structural design, when the cross beam 11 needs to be clamped, the rotary lifting cylinder 331b is started, the pressure head 332b is lifted first, then the pressure head 332b is rotated, the front end of the pressure head 332b is located above the cross beam 11, then the pressure head 332b is lowered to press the cross beam 11 downwards, and after the aircraft beam assembly 1 is assembled, the pressure head 332b is restored to the original state.

Referring to fig. 4-6, in one embodiment:

in order to be suitable for products with different specifications, the rotary lifting cylinder 331b and the overturning cylinder 331a can also be arranged at the top of the fixed seat 31, wherein the rotary lifting cylinder 331b is located between the overturning cylinder 331a and the supporting seat 32, the driving arm 332a and the pressing claw 333a pass over the overturning cylinder 331a, the operation of the overturning cylinder 331a is not affected by the existence of the rotary lifting cylinder 331b, and when the rotary lifting cylinder 331b needs to be operated independently, the driving arm 332a and the pressing claw 333a can be overturned backwards to provide an operation space for the clamping action of the rotary lifting cylinder 331 b.

Referring to fig. 7-8, in one embodiment:

the second clamping mechanism 4 comprises two second clamping assemblies 41 which are oppositely arranged at the left side and the right side of the first clamping mechanism 3, and the distance between the two second clamping assemblies 41 is adjustable; each second clamp assembly comprises a moving box 411, a driving assembly 412 and a clamping connecting rod 413, the bottom of the moving box 411 is connected with the working platform 2 in a sliding mode, the driving assembly 412 is arranged inside the moving box 411 and is in transmission connection with the clamping connecting rod 413, and the other end of the clamping connecting rod 413 can extend out of the moving box 411; drive assembly 412 can drive clamp link 413 to move horizontally and swing vertically to effect clamping of sheet 12.

The movable box 411 and the working platform 2 can be slidably connected through a sliding rail and a sliding groove, and a stopping component 6 is arranged on the working platform 2 on one side of the two second clamping assemblies 41 far away from the first clamping mechanism 3, so that the movable box 411 is prevented from being separated from the rail. A distance-changing assembly 414 is arranged between the two second clamping assemblies 41, and the distance between the two second clamping assemblies 41 can be adjusted.

Referring to fig. 7-8, in one embodiment:

the driving assembly 412 comprises a horizontal cylinder 4121 and a vertical cylinder 4122, and a horizontally arranged long slot 4124 is formed on the clamping connecting rod 413; the horizontal cylinder 4121 is horizontally arranged, and the output end of the horizontal cylinder is rotatably connected with the clamping connecting rod 413; the vertical cylinder 4122 is vertically arranged, and the output end thereof is provided with a bearing 4123, and the bearing 4123 is embedded in and slidably connected with the slotted hole 4124.

Wherein, the clamping link 413 is an L-shaped clamping link 413, the slotted hole 4124 is arranged on the long edge, the short edge can hook the sheet body 12 backwards to limit the sheet body 12, thereby clamping the sheet body 12. Specifically, each moving box 411 is provided with two sets of clamping links 413 which are arranged up and down, each set of clamping links 413 is composed of 2 clamping links 413, and the two sets of clamping links 413 are arranged up and down symmetrically. And the same number of horizontal cylinders 4121 and vertical cylinders 4122 as the number of the clamp links 413 are provided to perform the clamping action of the clamp links 413.

According to the above structure design, when the sheet 12 needs to be clamped, the horizontal cylinder 4121 is started to move the 2 sets of clamping links 413 to the outside of the box, and then the vertical cylinder 4122 is started to apply downward and upward forces to the upper and lower sets of clamping links 413 respectively, so that the clamping links 413 rotate relative to the horizontal cylinder 4121, and the short sides of the clamping links 413 rotate inward to clamp the sheet 12.

Referring to fig. 10, in an embodiment:

the outer side wall of the moving box 411 close to the first clamping mechanism 3 is provided with a fixed pin 416, the fixed pin 416 is used for installing a positioning clamp 415, the positioning clamp 415 comprises a template 4151 and a second positioning pin 4152, and the second positioning pin 4152 is matched with a positioning hole on the sheet body 12.

According to the above structure design, the positioning fixture 415 is detachably connected to the movable box 411, so that the corresponding positioning fixture 415 can be replaced for different products, and the application range is wide.

Referring to fig. 11, in an embodiment:

the pitch-variable assembly 414 comprises a telescopic cylinder 4141, the telescopic cylinder 4141 is horizontally arranged, the output end of the telescopic cylinder 4141 is provided with a head connecting seat 4142 fixedly connected with one of the second clamping assemblies 41, and the other end is provided with a tail connecting seat 4143 fixedly connected with the other second clamping assembly 41.

According to the structural design, the length of the telescopic cylinder 4141 in the horizontal direction is adjusted, so that the distance between the two second clamping assemblies 41 is adjustable. When the sheet body 12 needs to be clamped, the telescopic rod of the telescopic cylinder 4141 is retracted, so that the distance between the two second clamping assemblies 41 is reduced, the clamping work is performed close to the sheet body 12, and after the assembly is completed, the telescopic rod of the telescopic cylinder 4141 is extended, so that the distance between the two second clamping assemblies 41 is increased, and the taking-out of a workpiece is not influenced.

In the present invention, the turning cylinder 331a, the rotary lifting cylinder 331b, the horizontal cylinder 4121, the vertical cylinder 4122, the telescopic cylinder 4141 and the control mechanism 5 have specific structures, working principles, and control manners and spatial arrangements that may be involved, which are selected conventionally in the field, and should not be regarded as the innovation point of the present embodiment, and to those skilled in the art, they can be understood, and the present embodiment patent is not further detailed specifically.

According to the utility model discloses a description and attached drawing, the field technical personnel make or use very easily the utility model discloses a frame aircraft roof beam assembly's assembly fixture to can produce the positive effect that the utility model discloses record.

The above is only the preferred embodiment of the present invention, not to the limitation of the present invention in any form, all the technical matters of the present invention all fall into the protection scope of the present invention to any simple modification and equivalent change of the above embodiments.

Claims

1. The utility model provides an assembly fixture of frame aircraft roof beam assembly which characterized in that, assembly fixture includes:

a work platform (2);

the first clamping mechanism (3) is arranged on the working platform (2) and is used for clamping and supporting a cross beam (11) in the middle of the airplane beam assembly (1);

the second clamping mechanism (4) is connected to the working platform (2) in a sliding manner, has adjustable distance with the first clamping mechanism (3), and is used for clamping and limiting the sheet body (12) at the side part of the airplane beam assembly (1);

and a control mechanism (5) for driving the first clamping mechanism (3) and the second clamping mechanism (4) to clamp the airplane girder assembly (1).

2. The assembly fixture of frame aircraft beam assembly of claim 1, characterized in that: the first clamping mechanism (3) comprises a fixed seat (31), a supporting seat (32) and a first clamping assembly (33); the supporting seat (32) is fixed on the top surface of the fixed seat (31) and used for installing and positioning the cross beam (11); the first clamping assembly (33) is fixed on the top surface of the fixed seat (31) and used for clamping the cross beam (11).

3. The assembly fixture of frame aircraft beam assembly of claim 2, characterized in that: the supporting seat (32) is provided with a first positioning pin (321) which can be matched with a positioning hole in the cross beam (11).

4. The assembly fixture of frame aircraft beam assembly of claim 2, characterized in that: the first clamping component (33) comprises a turnover cylinder (331 a), a transmission arm (332 a) and a pressing claw (333 a), the turnover cylinder (331 a) is fixed on the fixed seat (31), the output end of the turnover cylinder (331 a) is fixedly connected with the transmission arm (332 a), the other end of the transmission arm (332 a) extends to the side where the supporting seat (32) is located and is fixedly connected with the pressing claw (333 a), and the pressing claw (333 a) is located above the supporting seat (32).

5. The assembly fixture of frame aircraft beam assembly of claim 2, characterized in that: the first clamping assembly (33) comprises a rotary lifting cylinder (331 b) and a pressure head (332 b), the rotary lifting cylinder (331 b) is fixed on the fixed seat (31), the output end of the rotary lifting cylinder (331 b) is fixedly connected with the pressure head (332 b), and the rotary lifting cylinder (331 b) can drive the pressure head (332 b) to lift along the vertical direction and rotate along the horizontal direction so as to clamp the cross beam (11).

6. The assembly fixture of frame aircraft beam assembly of claim 5, characterized in that: the rotary lifting cylinder (331 b) is positioned between the supporting seat (32) and the overturning cylinder (331 a).

7. The assembly fixture of frame aircraft beam assembly of claim 1, characterized in that: the second clamping mechanism (4) comprises two second clamping assemblies (41) which are oppositely arranged at the left side and the right side of the first clamping mechanism (3), and the distance between the two second clamping assemblies (41) is adjustable; each second clamping assembly comprises a moving box (411), a driving assembly (412) and a clamping connecting rod (413), the bottom of the moving box (411) is connected with the working platform (2) in a sliding mode, the driving assembly (412) is arranged inside the moving box (411) and is in transmission connection with the clamping connecting rod (413), and the other end of the clamping connecting rod (413) can extend out of the moving box (411); the drive assembly (412) can drive the clamping link (413) to move in the horizontal direction and to swing in the vertical direction so as to clamp the sheet body (12).

8. The assembly fixture of frame aircraft beam assembly of claim 7, characterized in that: the driving assembly (412) comprises a horizontal cylinder (4121) and a vertical cylinder (4122), and the clamping connecting rod (413) is provided with a horizontally-arranged long slotted hole (4124); the horizontal cylinder (4121) is horizontally arranged, and the output end of the horizontal cylinder is rotationally connected with the clamping connecting rod (413); the vertical cylinder (4122) is vertically arranged, the output end of the vertical cylinder is provided with a bearing (4123), and the bearing (4123) is embedded in the slotted hole (4124) and is connected with the slotted hole in a sliding mode.

9. The assembly tooling of the frame aircraft beam assembly of claim 7, characterized in that: a variable-pitch assembly (414) is arranged between the two second clamping assemblies (41), the variable-pitch assembly (414) comprises a telescopic cylinder (4141), the output end of the telescopic cylinder (4141) is provided with a head connecting seat (4142) fixedly connected with one of the second clamping assemblies (41), and the other end of the telescopic cylinder (4141) is provided with a tail connecting seat (4143) fixedly connected with the other second clamping assembly (41).

10. The assembly fixture of frame aircraft beam assembly of claim 7, characterized in that: the outer side wall of the moving box (411) close to the first clamping mechanism (3) is provided with a positioning clamp (415), the positioning clamp (415) comprises a template (4151) and a second positioning pin (4152), and the second positioning pin (4152) is matched with a positioning hole in the sheet body (12).