CN217097447U - Aircraft stiffening rib processing frock - Google Patents
Aircraft stiffening rib processing frock Download PDFInfo
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- CN217097447U CN217097447U CN202220875143.7U CN202220875143U CN217097447U CN 217097447 U CN217097447 U CN 217097447U CN 202220875143 U CN202220875143 U CN 202220875143U CN 217097447 U CN217097447 U CN 217097447U
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Abstract
The utility model relates to a processing frock technical field specifically is an aircraft stiffening rib processing frock. The utility model discloses, comprises a workbench, stop device and auxiliary device, the last fixed surface of workstation installs the mounting panel, the upper surface of mounting panel is provided with stop device, stop device includes the motor, motor fixed mounting is at the upper surface of mounting panel, the last fixed surface of mounting panel installs two first fixed plates, rotate between two first fixed plates and install the pivot, the one end of pivot and the output fixed mounting of motor, the fixed surface of pivot installs the baffle, the fixed surface that the mounting panel was kept away from to the baffle installs the bottom plate, the surface rotation that the mounting panel was kept away from to the baffle is installed the second screw rod, the thread bush is installed to the surface thread of second screw rod. The problem of frock clamp in the existing market in use, can not adjust anchor clamps centre gripping angle, anchor clamps are fixed insecure, bring the puzzlement for the operator is solved.
Description
Technical Field
The utility model relates to a processing frock technical field especially relates to an aircraft stiffening rib processing frock.
Background
The machining tool refers to a general name of various tools used in the manufacturing process, when the existing tool clamp is used, the clamping angle of the clamp cannot be adjusted, the clamp is not fixed firmly, and troubles are brought to operators, particularly, the machining tool for the stiffening ribs of the airplane needs to be machined in multiple angles, and therefore the machining tool clamp convenient for angle adjustment is provided.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving and having frock clamp in use on the existing market among the prior art, can not adjust anchor clamps centre gripping angle, anchor clamps are fixed insecure, bring the shortcoming of puzzlement for the operator, and an aircraft stiffening rib processing frock that proposes.
In order to achieve the above purpose, the utility model adopts the following technical scheme: an aircraft stiffening rib processing tool comprises a workbench, a limiting device and an auxiliary device, wherein the upper surface of the workbench is fixedly provided with a mounting plate, the upper surface of the mounting plate is provided with the limiting device, the limiting device comprises a motor, the motor is fixedly arranged on the upper surface of the mounting plate, the upper surface of the mounting plate is fixedly provided with two first fixing plates, a rotating shaft is rotatably arranged between the two first fixing plates, one end of the rotating shaft is fixedly arranged with the output end of the motor, the surface of the rotating shaft is fixedly provided with a baffle, the baffle is far away from the surface of the mounting plate and is provided with a bottom plate, the baffle is far away from the surface of the mounting plate and is rotatably provided with a second screw rod, the surface thread of the second screw rod is provided with a thread sleeve, the outer surface of the thread sleeve is fixedly provided with a pressing plate, the surface of the bottom plate is fixedly provided with a limiting rod, the limiting rod penetrates through the pressing plate in a sliding mode; the stiffening rib is clamped through the pressing plate, the stability of the stiffening rib is increased, and the baffle is driven to rotate through the motor, so that the clamping angle of the clamp is convenient for multi-angle processing of the stiffening rib.
Preferably, two second fixing plates are fixedly mounted on the surface, far away from the mounting plate, of the baffle plate, first screws are connected to the surfaces of the second fixing plates in a threaded manner, and push plates are rotatably mounted on the surfaces, close to each other, of the two first screws; can carry out the preprocessing to the stiffening rib through two push pedals, avoid when the clamp plate is fixed the stiffening rib, the stiffening rib takes place to slide.
Preferably, the push plates are slidably mounted on the upper surface of the base plate, and anti-skid pads are fixedly mounted on the surfaces, close to each other, of the two push plates; through the surface mounting at the push pedal there is the protection pad for the push pedal is more stable when extruding stiffening rib.
Preferably, the upper surface of the mounting plate is provided with two first sliding grooves, first sliding blocks are slidably mounted in the first sliding grooves, connecting rods are rotatably mounted on the surfaces of the first sliding blocks, free ends of the connecting rods are rotatably mounted with the baffle, and springs are fixedly mounted between the first sliding blocks and the first sliding grooves; the baffle can be further supported through the connecting rod, and the stability of the baffle is improved.
Preferably, a handle is fixedly mounted on the surface of the second screw rod, which is far away from the baffle plate, and the diameter of the handle is larger than that of the second screw rod; make to rotate the second screw rod more convenient through the handle, can carry on spacingly to the clamp plate simultaneously, avoid the clamp plate to take place to break away from.
Preferably, an auxiliary device is arranged on the side face of the mounting plate, the auxiliary device comprises a base plate, the base plate is fixedly mounted on the side face of the mounting plate, a support rod is fixedly mounted on the surface of the base plate, a second slide block is fixedly mounted on the lower surface of the support rod, a second slide groove is formed in the upper surface of the workbench, the second slide block is slidably mounted inside the second slide groove, and two second screws are arranged on the upper surface of the mounting plate; the mounting plate can be limited by sliding the two second sliding blocks in the second sliding grooves, and the stability of the mounting plate is improved.
Preferably, limiting plates are mounted on two sides of the workbench, and first screws are arranged on the outer surfaces of the limiting plates; avoid the mounting panel to take place to break away from through the limiting plate, through dismantling the limiting plate, be convenient for dismantle and maintain the mounting panel simultaneously.
Compared with the prior art, the utility model discloses an advantage lies in with positive effect:
in the utility model, when the stiffening rib of the airplane is processed, the stiffening rib is firstly placed on the upper surface of the bottom plate, then the first screw rod is rotated to drive the push plates to move, the stiffening ribs can be extruded through the two push plates, thereby pre-clamping the stiffening rib, preventing the stiffening rib from sliding before processing and being used as a rigid subsequent clamp, then the second screw rod is rotated to drive the thread sleeve to move, the thread sleeve drives the pressing plate to move, the stiffening rib is clamped through the pressing plate, the stability of the stiffening rib is increased, then loosen the push pedal, can process stiffening rib this moment, simultaneously, when needs carry out angle processing to stiffening rib, can pass through starter motor this moment, the motor drives the pivot and rotates, and the pivot drives the baffle and rotates to can adjust stiffening rib's angle, make work more convenient, improve work efficiency.
Drawings
FIG. 1 is a schematic perspective view of a tooling for machining an aircraft stiffening rib according to the present invention;
FIG. 2 is a schematic structural view of a point A in FIG. 1 of the present invention;
FIG. 3 is a schematic structural view of a limiting device of a tooling for processing an aircraft stiffening rib according to the present invention;
FIG. 4 is a schematic structural view of a portion B of the tooling for machining the stiffening rib of the aircraft shown in FIG. 1 according to the present invention;
fig. 5 is a schematic structural view of an auxiliary device of an aircraft stiffening rib processing tool provided by the present invention.
Illustration of the drawings: 1. a work table; 2. a limiting device; 201. a motor; 202. a rotating shaft; 203. a first fixing plate; 204. a baffle plate; 205. a connecting rod; 206. a first screw; 207. a second fixing plate; 208. pushing the plate; 209. a second screw; 210. a threaded sleeve; 211. pressing a plate; 212. a limiting rod; 213. a first slider; 214. a first chute; 215. a spring; 3. an auxiliary device; 31. a support bar; 32. a backing plate; 33. a second chute; 34. a second slider; 35. a first screw; 36. a limiting plate; 37. a second screw; 4. mounting a plate; 5. a base plate.
Detailed Description
Referring to fig. 1-5, the present invention provides a technical solution: the utility model provides an aircraft stiffening rib processing frock, includes workstation 1, stop device 2 and auxiliary device 3, and the last fixed surface of workstation 1 installs mounting panel 4, and the upper surface of mounting panel 4 is provided with stop device 2.
The specific arrangement and function of the limiting means 2 and the auxiliary means 3 will be described in detail below.
In this embodiment: the limiting device 2 comprises a motor 201, the motor 201 is fixedly installed on the upper surface of the installation plate 4, two first fixing plates 203 are fixedly installed on the upper surface of the installation plate 4, a rotating shaft 202 is rotatably installed between the two first fixing plates 203, one end of the rotating shaft 202 is fixedly installed with the output end of the motor 201, a baffle plate 204 is fixedly installed on the surface of the rotating shaft 202, a bottom plate 5 is fixedly installed on the surface of the baffle plate 204 far away from the installation plate 4, a second screw 209 is rotatably installed on the surface of the baffle plate 204 far away from the installation plate 4, a threaded sleeve 210 is installed on the surface of the second screw 209, a pressing plate 211 is fixedly installed on the outer surface of the threaded sleeve 210, a limiting rod 212 is fixedly installed on the surface of the bottom plate 5, and the limiting rod 212 penetrates through the pressing plate 211 in a sliding manner; press from both sides tight stiffening rib through clamp plate 211, increase stiffening rib's stability, drive baffle 204 through motor 201 simultaneously and rotate to anchor clamps centre gripping angle is convenient for carry out multi-angle processing to stiffening rib.
Specifically, two second fixing plates 207 are fixedly mounted on the surface of the baffle 204 far away from the mounting plate 4, first screws 206 are connected to the surface of the second fixing plates 207 in a threaded manner, and push plates 208 are rotatably mounted on the surfaces of the two first screws 206 close to each other; the stiffening ribs can be preprocessed by the two push plates 208, so that the stiffening ribs are prevented from sliding when the pressure plates 211 fix the stiffening ribs.
Specifically, the push plates 208 are slidably mounted on the upper surface of the bottom plate 5, and the anti-slip pads are fixedly mounted on the surfaces of the two push plates 208 close to each other.
In this embodiment: by mounting a protective pad on the surface of the push plate 208, the push plate 208 is made more stable when it presses against the stiffener.
Specifically, two first sliding grooves 214 are formed in the upper surface of the mounting plate 4, a first sliding block 213 is slidably mounted in the first sliding grooves 214, a connecting rod 205 is rotatably mounted on the surface of the first sliding block 213, the free end of the connecting rod 205 is rotatably mounted with the baffle 204, and a spring 215 is fixedly mounted between the first sliding block 213 and the first sliding grooves 214; the baffle 204 can be further supported by the connecting rod 205, and the stability of the baffle 204 is increased.
Specifically, a handle is fixedly arranged on the surface of the second screw 209 far away from the baffle 204, and the diameter of the handle is larger than that of the second screw 209; make through the handle to rotate second screw 209 more convenient, can carry on spacingly to clamp plate 211 simultaneously, avoid clamp plate 211 to take place to break away from.
In this embodiment: the auxiliary device 3 is arranged on the side face of the mounting plate 4, the auxiliary device 3 comprises a base plate 32, the base plate 32 is fixedly arranged on the side face of the mounting plate 4, a support rod 31 is fixedly arranged on the surface of the base plate 32, a second sliding block 34 is fixedly arranged on the lower surface of the support rod 31, a second sliding groove 33 is formed in the upper surface of the workbench 1, the second sliding block 34 is slidably arranged in the second sliding groove 33, and two second screws 37 are arranged on the upper surface of the mounting plate 4; the mounting plate 4 can be limited by sliding the two second sliding blocks 34 in the second sliding grooves 33, and the stability of the mounting plate 4 is improved.
Specifically, limiting plates 36 are mounted on two sides of the workbench 1, and first screws 35 are arranged on the outer surfaces of the limiting plates 36.
In this embodiment: the mounting plate 4 is prevented from being separated by the limiting plate 36, and meanwhile, the mounting plate 4 is convenient to detach and maintain by detaching the limiting plate 36.
The working principle is as follows: when the aircraft stiffening rib is machined, firstly, the stiffening rib is placed on the upper surface of the bottom plate 5, then the first screw rod 206 is rotated, the first screw rod 206 drives the push plate 208 to move, the stiffening rib can be extruded through the two push plates 208, so that the stiffening rib is pre-clamped, the stiffening rib is prevented from sliding before machining, a rigid subsequent clamp is used, then the second screw rod 209 is rotated, the second screw rod 209 drives the threaded sleeve 210 to move, the threaded sleeve 210 drives the pressing plate 211 to move, the stiffening rib is clamped through the pressing plate 211, the stability of the stiffening rib is increased, then the push plates 208 are loosened, the stiffening rib can be machined at the moment, meanwhile, when the stiffening rib needs to be machined at the diagonal angle, the motor 201 can be started, the motor 201 drives the rotating shaft 202 to rotate, the rotating shaft 202 drives the baffle 204 to rotate, so that the angle of the stiffening rib can be adjusted, make work more convenient, improve work efficiency, when the stiffening rib need remove by pressing from both sides after tight, this moment can be through removing mounting panel 4, mounting panel 4 can drive whole anchor clamps and remove, it can be spacing to carry out mounting panel 4 through two second sliders 34 sliding in the inside of second spout 33 simultaneously, increase mounting panel 4's stability, then through rotating second screw 37, make mounting panel 4 fix the upper surface at workstation 1, avoid adding the skew that takes place man-hour, influence the machining precision, make the stiffening rib can remove to processing apparatus front end simultaneously, make processing more convenient.
Claims (7)
1. The utility model provides an aircraft stiffening rib processing frock, includes workstation (1), stop device (2) and auxiliary device (3), its characterized in that: the upper surface of workstation (1) is fixed and is installed mounting panel (4), the upper surface of mounting panel (4) is provided with stop device (2), stop device (2) include motor (201), motor (201) fixed mounting is at the upper surface of mounting panel (4), the upper surface fixed mounting of mounting panel (4) has two first fixed plates (203), two rotate between first fixed plate (203) and install pivot (202), the one end of pivot (202) and the output fixed mounting of motor (201), the fixed surface of pivot (202) installs baffle (204), the fixed surface that mounting panel (4) were kept away from to baffle (204) installs bottom plate (5), the fixed surface that mounting panel (4) were kept away from to baffle (204) rotates and installs second screw rod (209), the surface thread mounting of second screw rod (209) has thread bush (210), the outer fixed surface of thread bush (210) installs clamp plate (211), the fixed surface of bottom plate (5) installs gag lever post (212), gag lever post (212) slide and run through clamp plate (211).
2. The aircraft stiffener processing tool of claim 1, characterized in that: the surface fixed mounting that mounting panel (4) were kept away from in baffle (204) has two second fixed plates (207), the surperficial threaded connection of second fixed plate (207) has first screw rod (206), two the surperficial rotation that first screw rod (206) are close to each other installs push pedal (208).
3. The aircraft stiffener processing tool of claim 2, characterized in that: the push plates (208) are slidably mounted on the upper surface of the base plate (5), and anti-slip pads are fixedly mounted on the surfaces, close to each other, of the two push plates (208).
4. The aircraft stiffener processing tool of claim 1, characterized in that: two first spouts (214) have been seted up to the upper surface of mounting panel (4), the inside slidable mounting of first spout (214) has first slider (213), the surface rotation of first slider (213) installs connecting rod (205), the free end and the baffle (204) of connecting rod (205) rotate the installation, fixed mounting has spring (215) between first slider (213) and first spout (214).
5. The aircraft stiffener processing tool of claim 1, characterized in that: the surface of the second screw rod (209) far away from the baffle (204) is fixedly provided with a handle, and the diameter of the handle is larger than that of the second screw rod (209).
6. The aircraft stiffener processing tool of claim 1, characterized in that: the side of mounting panel (4) is provided with auxiliary device (3), auxiliary device (3) include backing plate (32), backing plate (32) fixed mounting is in the side of mounting panel (4), the fixed surface of backing plate (32) installs bracing piece (31), the lower fixed surface of bracing piece (31) installs second slider (34), second spout (33) have been seted up to the upper surface of workstation (1), second slider (34) slidable mounting is in the inside of second spout (33), the upper surface of mounting panel (4) is provided with two second screws (37).
7. The aircraft stiffener processing tool of claim 6, characterized in that: limiting plates (36) are mounted on two sides of the workbench (1), and first screws (35) are arranged on the outer surfaces of the limiting plates (36).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220875143.7U CN217097447U (en) | 2022-04-12 | 2022-04-12 | Aircraft stiffening rib processing frock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220875143.7U CN217097447U (en) | 2022-04-12 | 2022-04-12 | Aircraft stiffening rib processing frock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217097447U true CN217097447U (en) | 2022-08-02 |
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ID=82582173
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220875143.7U Active CN217097447U (en) | 2022-04-12 | 2022-04-12 | Aircraft stiffening rib processing frock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217097447U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116252262A (en) * | 2023-05-10 | 2023-06-13 | 四川省嘉绮瑞航空装备有限公司 | Positioning tool suitable for aircraft parts |
| CN116673762A (en) * | 2023-06-19 | 2023-09-01 | 江苏先锋精密科技股份有限公司 | Vertical machining center fixture |
| CN116985083A (en) * | 2023-09-26 | 2023-11-03 | 同方新材料科技(南通)有限公司 | Jig plate for assisting LED circuit design |
-
2022
- 2022-04-12 CN CN202220875143.7U patent/CN217097447U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116252262A (en) * | 2023-05-10 | 2023-06-13 | 四川省嘉绮瑞航空装备有限公司 | Positioning tool suitable for aircraft parts |
| CN116673762A (en) * | 2023-06-19 | 2023-09-01 | 江苏先锋精密科技股份有限公司 | Vertical machining center fixture |
| CN116673762B (en) * | 2023-06-19 | 2023-11-21 | 江苏先锋精密科技股份有限公司 | Vertical machining center fixture |
| CN116985083A (en) * | 2023-09-26 | 2023-11-03 | 同方新材料科技(南通)有限公司 | Jig plate for assisting LED circuit design |
| CN116985083B (en) * | 2023-09-26 | 2023-12-12 | 同方新材料科技(南通)有限公司 | Jig plate for assisting LED circuit design |
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