CN212683206U - Turning clamp for aircraft wall plate - Google Patents
Turning clamp for aircraft wall plate Download PDFInfo
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- CN212683206U CN212683206U CN202021245391.0U CN202021245391U CN212683206U CN 212683206 U CN212683206 U CN 212683206U CN 202021245391 U CN202021245391 U CN 202021245391U CN 212683206 U CN212683206 U CN 212683206U
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Abstract
The utility model provides an overturning fixture for aircraft wallboards. An aircraft panel turn-over clamp comprising: a base plate; the two fixing plates are fixedly arranged on the top of the bottom plate; the two rotating shafts are respectively and rotatably installed on the outer walls of the two sides, close to each other, of the two fixing plates, and the ends, far away from each other, of the two rotating shafts extend out of the two fixing plates; the first belt pulley is fixedly sleeved on any one of the rotating shafts; the motor is fixedly arranged on the top of the bottom plate; the second belt pulley is fixedly sleeved on the output shaft of the motor; the belt is sleeved on the first belt pulley and the second belt pulley. The utility model provides an aircraft wallboard's turn-over anchor clamps have easy operation, and labour saving and time saving can carry out the advantage of turn-over and centre gripping to aircraft wallboard by oneself.
Description
Technical Field
The utility model relates to an aircraft wallboard technical field especially relates to an aircraft wallboard's turn-over anchor clamps.
Background
In the aircraft manufacturing industry, in particular the large aircraft manufacturing industry, a blank of a large wall panel needs to be milled flat on two sides before being processed, and especially a wall panel part processed on two sides needs to be turned over for one time or more times.
At present, when the large and heavy parts are turned, the turning operation process is complicated, the consumed time is long, and the workpieces are easily damaged.
Therefore, there is a need to provide a turnover jig for an aircraft panel to solve the above-mentioned technical problems.
SUMMERY OF THE UTILITY MODEL
The utility model provides a technical problem provide an easy operation, labour saving and time saving can carry out the turn-over anchor clamps of the aircraft wallboard of turn-over and centre gripping to the aircraft wallboard by oneself.
In order to solve the technical problem, the utility model provides an aircraft wallboard's turn-over anchor clamps, include: a base plate; the two fixing plates are fixedly arranged on the top of the bottom plate; the two rotating shafts are respectively and rotatably installed on the outer walls of the two sides, close to each other, of the two fixing plates, and the ends, far away from each other, of the two rotating shafts extend out of the two fixing plates; the first belt pulley is fixedly sleeved on any one of the rotating shafts; the motor is fixedly arranged on the top of the bottom plate; the second belt pulley is fixedly sleeved on the output shaft of the motor; the belt is sleeved on the first belt pulley and the second belt pulley; the rotating frames are fixedly arranged at two ends of the two rotating shafts, which are close to each other; and the two clamping mechanisms are arranged in the rotating frame.
Preferably, any one of the clamping mechanisms comprises a C-shaped frame, a threaded rod, two fixed blocks, a fixed rod, an installation block, two connecting rods, two sliding blocks and two clamping blocks, the C-shaped frame is fixedly arranged on the inner wall of the top of the rotating frame, the bottom of the C-shaped frame is fixedly connected with the inner wall of the bottom of the rotating frame, the threaded rod is rotatably arranged on the C-shaped frame, the two fixing blocks are fixedly arranged on the outer wall of one side of the C-shaped frame, dead lever fixed mounting is two on the outer wall of one side of fixed block, installation piece threaded sleeve establishes on the threaded rod, two the connecting rod is all articulated to be installed on the installation piece, two the slider is all the slip cap and is established on the dead lever, two the connecting rod is kept away from the one end of installation piece respectively with two the slider is articulated to be connected, two grip blocks respectively fixed mounting be two on the outer wall of one side of slider.
Preferably, the outer wall of one side of each of the two clamping blocks, which is close to each other, is fixedly provided with an anti-skid pad.
Preferably, seted up flutedly on one side outer wall of dead lever, the threaded rod extends to in the recess, the opening has been seted up on the C type frame, the threaded rod is kept away from the one end of recess extends to the C type frame is outer and fixed mounting has the knob, fixed cover is equipped with two first bearings on the threaded rod, two first bearing respectively with the inner wall of opening and the inner wall fixed connection of recess.
Preferably, two fixed ports are respectively formed in the two fixed plates, a second bearing is fixedly sleeved on each of the two rotating shafts, and the outer rings of the two second bearings are respectively fixedly connected with the inner walls of the two fixed ports.
Preferably, any one of the clamping mechanisms comprises a hydraulic cylinder, a support frame, a push rod, two hinged blocks, two first connecting rods, two second connecting rods, two connecting blocks and two L-shaped rods, the hydraulic cylinder is fixedly mounted on the inner wall of one side of the rotating frame, the support frame is fixedly mounted on the inner wall of the top of the rotating frame, the bottom of the support frame is fixedly connected with the inner wall of the bottom of the rotating frame, the push rod is fixedly sleeved on the output shaft of the hydraulic cylinder, the two hinged blocks are slidably sleeved on the push rod, the two first connecting rods are respectively hinged on the outer wall of one side of the two hinged blocks, one ends of the two first connecting rods, which are far away from the two hinged blocks, are hinged with the support frame, the two second connecting rods are respectively hinged on the outer wall of one side of the two hinged blocks, which are far away from the two first connecting rods, the two joint blocks are fixedly mounted on the support frame, the L-shaped rods are slidably mounted on the two joint blocks respectively, and one ends, far away from the two hinge blocks, of the second joint rods are hinged to the L-shaped rods respectively.
Preferably, an avoiding opening is formed in the outer wall of one side of the supporting frame, and the output shaft of the hydraulic cylinder penetrates through the avoiding opening and is in sliding connection with the inner wall of the avoiding opening.
Preferably, two rubber pads are fixedly arranged on the outer wall of one side of the L-shaped rod close to each other
Preferably, two sliding holes are respectively formed in the two connecting blocks, and the two L-shaped rods respectively penetrate through the two sliding holes and are slidably connected with the inner walls of the two sliding holes.
Compared with the prior art, the utility model provides an aircraft wallboard's turn-over anchor clamps have following beneficial effect:
the utility model provides a turn-over anchor clamps of aircraft wallboard only needs to twist with the hand and moves the knob or start the pneumatic cylinder and just can carry out the centre gripping to the aircraft wallboard, has the stable centre gripping of aircraft wallboard, labour saving and time saving's advantage, and starter motor, motor drive rotate the frame and rotate, just can turn over the aircraft wallboard by oneself, and operation process is simple, uses manpower sparingly and carries out the physical power and the time of turn-over to the aircraft wallboard.
Drawings
Fig. 1 is a schematic structural view of a first embodiment of a turnover fixture for an aircraft panel according to the present invention;
FIG. 2 is an enlarged schematic view of portion A shown in FIG. 1;
fig. 3 is a schematic view of a second embodiment of a turn-over clamp for an aircraft panel according to the present invention;
fig. 4 is an enlarged schematic view of a portion B shown in fig. 3.
Reference numbers in the figures: 1. a base plate; 2. a fixing plate; 3. a rotating shaft; 4. a first pulley; 5. a motor; 6. a second pulley; 7. a belt; 8. rotating the frame; 9. a C-shaped frame; 10. a threaded rod; 11. a fixed block; 12. fixing the rod; 13. mounting blocks; 14. a connecting rod; 15. a slider; 16. a clamping block; 17. a hydraulic cylinder; 18. a support frame; 19. a push rod; 20. a hinged block; 21. a first engagement rod; 22. a second engagement rod; 23. a joining block; 24. an L-shaped rod.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and embodiments.
First embodiment
Referring to fig. 1-2, in a first embodiment of the present invention, a turnover jig for an aircraft panel includes: a base plate 1; the two fixing plates 2 are fixedly arranged at the top of the bottom plate 1; the two rotating shafts 3 are respectively and rotatably installed on the outer walls of the two sides, close to each other, of the two fixing plates 2, and the ends, far away from each other, of the two rotating shafts 3 extend out of the two fixing plates 2; the first belt pulley 4 is fixedly sleeved on any one of the rotating shafts 3; the motor 5 is fixedly arranged on the top of the bottom plate 1; the second belt pulley 6 is fixedly sleeved on the output shaft of the motor 5; the belt 7 is sleeved on the first belt pulley 4 and the second belt pulley 6; the rotating frames 8 are fixedly arranged at two ends, close to each other, of the two rotating shafts 3; and the two clamping mechanisms are arranged in the rotating frame 8.
Any one of the clamping mechanisms comprises a C-shaped frame 9, a threaded rod 10, two fixed blocks 11, a fixed rod 12, an installation block 13, two connecting rods 14, two sliders 15 and two clamping blocks 16, wherein the C-shaped frame 9 is fixedly installed on the inner wall of the top of the rotating frame 8, the bottom of the C-shaped frame 9 is fixedly connected with the inner wall of the bottom of the rotating frame 8, the threaded rod 10 is rotatably installed on the C-shaped frame 9, the two fixed blocks 11 are fixedly installed on the outer wall of one side of the C-shaped frame 9, the fixed rod 12 is fixedly installed on the outer wall of one side of the two fixed blocks 11, the installation block 13 is in threaded sleeve connection with the threaded rod 10, the two connecting rods 14 are hinged and installed on the installation block 13, the two sliders 15 are in sliding sleeve connection with the fixed rod 12, and one end of the two connecting rods 14 far away from the installation block 13 is respectively in hinged connection with the, two clamping blocks 16 are respectively and fixedly arranged on the outer wall of one side of the two sliding blocks 15.
And anti-skid pads are fixedly arranged on the outer wall of one side of each clamping block 16, which is close to each other.
Set up flutedly on one side outer wall of dead lever 12, threaded rod 10 extends to in the recess, the opening has been seted up on the C type frame 9, threaded rod 10 keeps away from the one end of recess extends to C type frame 9 is outer and fixed mounting has the knob, fixed cover is equipped with two first bearings on the threaded rod 10, two first bearing respectively with the inner wall of opening and the inner wall fixed connection of recess.
Fixed ports are respectively formed in the two fixing plates 2, two second bearings are fixedly sleeved on the rotating shafts 3, and the outer rings of the two second bearings are fixedly connected with the inner walls of the two fixed ports respectively.
In this embodiment:
the first step is as follows: when stabilizing the centre gripping to the aircraft wallboard, put the aircraft wallboard between four grip blocks 16, then twist manual knob with the hand, the knob drives installation piece 13 and moves on threaded rod 10, installation piece 13 drives two connecting rod 14 motions, two connecting rod 14 drive two sliders 15 and move on dead lever 12, two sliders 15 drive two grip blocks 16 motions, two grip blocks 16 drive two slipmat motions, thereby just can stabilize the centre gripping to the aircraft wallboard, the reverse rotation knob, the application above-mentioned principle can be known, just can dismantle the aircraft wallboard.
The second step is that: when the aircraft wallboard is turned, the motor 5 is started, the motor 5 drives the second belt pulley 6 to rotate, the second belt pulley 6 drives the belt 7 to rotate, the belt 7 drives the first belt pulley 4 to rotate, the first belt pulley 4 drives the rotating shaft 3 to rotate, so that the rotating shaft 3 drives the rotating frame 8 to rotate, and the aircraft wallboard is turned automatically.
Compared with the prior art, the utility model provides an aircraft wallboard's turn-over anchor clamps have following beneficial effect: the aircraft wallboard can be stably clamped only by twisting the knob by hand, the motor 5 is started, the motor 5 drives the rotating frame 8 to rotate, the aircraft wallboard can be turned over by self, and the operation process is simple, time-saving and labor-saving.
Second embodiment:
based on the turn-over clamp of the aircraft panel provided by the first embodiment of the application, the second embodiment of the application provides another turn-over clamp of the aircraft panel. The second embodiment is merely a preferred way of the first embodiment, and the implementation of the second embodiment does not affect the implementation of the first embodiment alone.
The second embodiment of the present invention will be further explained with reference to the drawings and the embodiments.
Referring to fig. 3-4 in combination, in a second embodiment of the turning clamp for an aircraft panel according to the second embodiment of the present application, each of the clamping mechanisms includes a hydraulic cylinder 17, a supporting frame 18, a pushing rod 19, two hinged blocks 20, two first connecting rods 21, two second connecting rods 22, two connecting blocks 23, and two L-shaped rods 24, the hydraulic cylinder 17 is fixedly installed on an inner wall of one side of the rotating frame 8, the supporting frame 18 is fixedly installed on an inner wall of a top portion of the rotating frame 8, a bottom portion of the supporting frame 18 is fixedly connected with an inner wall of a bottom portion of the rotating frame 8, the pushing rod 19 is fixedly installed on an output shaft of the hydraulic cylinder 17, both of the hinged blocks 20 are slidably installed on the pushing rod 19, and both of the first connecting rods 21 are respectively and hingedly installed on an outer wall of one side of the two hinged blocks 20, two first joint pole 21 is kept away from two the one end of articulated piece 20 all with support frame 18 is articulated to be connected, two second joint pole 22 is articulated respectively and is installed two articulated piece 20 is kept away from two on the outer wall of one side of first joint pole 21, two join the equal fixed mounting of piece 23 on support frame 18, two L type pole 24 is respectively slidable mounting two join on the piece 23, two second joint pole 22 is kept away from two the one end of articulated piece 20 respectively with two L type pole 24 is articulated to be connected.
An avoiding opening is formed in the outer wall of one side of the supporting frame 18, and an output shaft of the hydraulic cylinder 17 penetrates through the avoiding opening and is in sliding connection with the inner wall of the avoiding opening.
And rubber pads are fixedly arranged on the outer wall of one side of each L-shaped rod 24, which is close to each other.
Two sliding holes are respectively formed in the two connecting blocks 23, and the two L-shaped rods 24 respectively penetrate through the two sliding holes and are slidably connected with the inner walls of the two sliding holes.
In this embodiment:
when the aircraft wallboard is stably clamped, the aircraft wallboard is placed between the four L-shaped rods 24, then the hydraulic cylinder 17 is started, the output shaft of the hydraulic cylinder 17 pushes the push rod 19, the push rod 19 drives the two hinging blocks 20 to move towards the mutually approaching direction under the action of the two first connecting rods 21, meanwhile, the two hinging blocks 20 drive the two L-shaped rods 24 to move towards the mutually approaching direction on the two connecting blocks 23 under the action of the two second connecting rods 22, so that the two rubber pads move towards the mutually approaching direction, the aircraft wallboard is tightly clamped by the rubber pads, when the aircraft wallboard does not need to be stably clamped, otherwise, the aircraft wallboard can be disassembled by applying the principle, and compared with the first embodiment, the second embodiment is more time-saving and labor-saving.
The above only is the embodiment of the present invention, not limiting the scope of the present invention, all the equivalent structures or equivalent processes of the present invention are used in the specification and the attached drawings, or directly or indirectly applied to other related technical fields, and the same principle is included in the protection scope of the present invention.
Claims (9)
1. An aircraft panel turn-over clamp, comprising:
a base plate;
the two fixing plates are fixedly arranged on the top of the bottom plate;
the two rotating shafts are respectively and rotatably installed on the outer walls of the two sides, close to each other, of the two fixing plates, and the ends, far away from each other, of the two rotating shafts extend out of the two fixing plates;
the first belt pulley is fixedly sleeved on any one of the rotating shafts;
the motor is fixedly arranged on the top of the bottom plate;
the second belt pulley is fixedly sleeved on the output shaft of the motor;
the belt is sleeved on the first belt pulley and the second belt pulley;
the rotating frames are fixedly arranged at two ends of the two rotating shafts, which are close to each other;
and the two clamping mechanisms are arranged in the rotating frame.
2. The aircraft panel turn-over fixture of claim 1, wherein any one of the clamping mechanisms comprises a C-shaped frame, a threaded rod, two fixed blocks, a fixed rod, a mounting block, two connecting rods, two sliding blocks and two clamping blocks, the C-shaped frame is fixedly mounted on the inner wall of the top of the rotating frame, the bottom of the C-shaped frame is fixedly connected with the inner wall of the bottom of the rotating frame, the threaded rod is rotatably mounted on the C-shaped frame, the two fixed blocks are fixedly mounted on the outer wall of one side of the C-shaped frame, the fixed rod is fixedly mounted on the outer wall of one side of the two fixed blocks, the mounting block is in threaded fit on the threaded rod, the two connecting rods are in hinged fit on the mounting block, the two sliding blocks are in sliding fit on the fixed rod, and one ends of the two connecting rods, which are far away from the mounting block, are in hinged connection with the two sliding, and the two clamping blocks are respectively and fixedly arranged on the outer wall of one side of the two sliding blocks.
3. The aircraft panel turn-over clamp of claim 2, wherein a non-slip mat is fixedly mounted on the outer wall of one side of each of the two clamping blocks adjacent to each other.
4. The aircraft panel turn-over clamp of claim 2, wherein a groove is formed in an outer wall of one side of the fixing rod, the threaded rod extends into the groove, a through hole is formed in the C-shaped frame, one end of the threaded rod, which is far away from the groove, extends out of the C-shaped frame and is fixedly provided with a knob, and two first bearings are fixedly arranged on the threaded rod and are fixedly connected with an inner wall of the through hole and an inner wall of the groove respectively.
5. The aircraft panel turn-over clamp of claim 1, wherein two fixing holes are respectively formed on two fixing plates, a second bearing is fixedly sleeved on each of the two rotating shafts, and outer rings of the two second bearings are respectively fixedly connected with inner walls of the two fixing holes.
6. The aircraft panel turn-over fixture of claim 1, wherein any one of the clamping mechanisms comprises a hydraulic cylinder, a support frame, a push rod, two hinged blocks, two first connecting rods, two second connecting rods, two connecting blocks and two L-shaped rods, the hydraulic cylinder is fixedly mounted on one side inner wall of the rotating frame, the support frame is fixedly mounted on the top inner wall of the rotating frame, the bottom of the support frame is fixedly connected with the bottom inner wall of the rotating frame, the push rod is fixedly sleeved on the output shaft of the hydraulic cylinder, the two hinged blocks are slidably sleeved on the push rod, the two first connecting rods are respectively and hingedly mounted on one side outer wall of the two hinged blocks, one ends of the two first connecting rods, which are far away from the two hinged blocks, are hinged to the support frame, and the two second connecting rods are respectively and hingedly mounted on the two hinged blocks, which are far away from the two first connecting rods On the outer wall of one side of pole, two join the piece all fixed mounting in on the support frame, two L type pole slidable mounting respectively two join on the piece, two the second links up the pole and keeps away from two the one end of articulated piece respectively with two L type pole is articulated to be connected.
7. The turn-over clamp for the aircraft wall panel according to claim 6, wherein an evasion port is formed on an outer wall of one side of the support frame, and the output shaft of the hydraulic cylinder penetrates through the evasion port and is slidably connected with an inner wall of the evasion port.
8. The aircraft panel turn-over clamp of claim 6, wherein a rubber pad is fixedly mounted on the outer wall of the side where the two L-shaped bars are close to each other.
9. The aircraft panel turn-over clamp of claim 6, wherein two of the connecting blocks are respectively provided with a sliding hole, and two of the L-shaped rods respectively penetrate through the two sliding holes and are slidably connected with inner walls of the two sliding holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021245391.0U CN212683206U (en) | 2020-07-01 | 2020-07-01 | Turning clamp for aircraft wall plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021245391.0U CN212683206U (en) | 2020-07-01 | 2020-07-01 | Turning clamp for aircraft wall plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212683206U true CN212683206U (en) | 2021-03-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021245391.0U Active CN212683206U (en) | 2020-07-01 | 2020-07-01 | Turning clamp for aircraft wall plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212683206U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114951733A (en) * | 2022-07-06 | 2022-08-30 | 特阀江苏流体机械制造有限公司 | Positioning tool for valve manufacturing |
-
2020
- 2020-07-01 CN CN202021245391.0U patent/CN212683206U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114951733A (en) * | 2022-07-06 | 2022-08-30 | 特阀江苏流体机械制造有限公司 | Positioning tool for valve manufacturing |
| CN114951733B (en) * | 2022-07-06 | 2024-02-27 | 特阀江苏流体机械制造有限公司 | Positioning tool for valve manufacturing |
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