CN210023321U - Aviation part deformation corrector - Google Patents
Aviation part deformation corrector Download PDFInfo
- Publication number
- CN210023321U CN210023321U CN201920324123.9U CN201920324123U CN210023321U CN 210023321 U CN210023321 U CN 210023321U CN 201920324123 U CN201920324123 U CN 201920324123U CN 210023321 U CN210023321 U CN 210023321U
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- placing groove
- controller
- groove
- hydraulic
- hydraulic cylinder
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Abstract
The utility model discloses an aviation part deformation corrector, which comprises a support frame, a support table and a controller, wherein the upper end of the support frame is connected with a hydraulic synchronizer, a controller and a support table, the lower end of the support frame is connected with a first hydraulic cylinder and a second hydraulic cylinder, the upper end of the controller is provided with a display screen and a control key, the upper end of the support table is provided with a first placing groove and a second placing groove, the two ends of the first placing groove are provided with a first limit clamping groove, the upper end of the first limit clamping groove is provided with a first threaded hole, the two ends of the second placing groove are provided with a second limit clamping groove, the upper end of the second limit clamping groove is provided with a support column, the utility model has the function of correcting the aviation part deformation, the first hydraulic cylinder is utilized to provide the correct part value, and the first hydraulic cylinder and the second hydraulic cylinder are enabled to carry out stable and safe action on the value through the hydraulic synchronizer, the purpose of correcting the parts is achieved.
Description
Technical Field
The utility model relates to an aviation part warp and corrects technical field, specifically is an aviation part warp unscrambler.
Background
Through years of development of the aviation industry in China, a complete system is formed, the aviation part deformation corrector has independent development capability, airplanes are complete in types, serial production is realized, related matched products are complete, the part bending deformation frequently occurs in the production and processing process of aviation parts, the part bending deformation is usually represented as cutter relieving, over-cutting, local bending and the like, the size of the part bending deformation corrector is limited near the contact area of a cutter and a workpiece, and the aviation part deformation corrector is designed for solving the problems in the prior art.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the production and processing in-process that has aviation part among the prior art, the condition of part bending deformation often takes place, and generally represent for cutter relieving, cross-cut, local bending etc. its yardstick is limited in near the contact area of cutter and work piece, in order to solve the problem that exists among the prior art, and provide an aviation part and warp the unscrambler.
In order to achieve the above object, the utility model provides a following technical scheme: including support frame, brace table and controller, the support frame upper end is connected and is provided with hydraulic pressure synchronous ware, controller and brace table, the support frame lower extreme is connected and is provided with first pneumatic cylinder and second pneumatic cylinder, the controller upper end is provided with display screen and control key, the brace table upper end is provided with first standing groove and second standing groove, first standing groove both ends are provided with first spacing draw-in groove, first spacing draw-in groove upper end is provided with first screw hole, second standing groove both ends are provided with the spacing draw-in groove of second, the spacing draw-in groove upper end of second is provided with the second screw hole, the brace table lower extreme is provided with the support column.
Preferably, the first hydraulic cylinder and the second hydraulic cylinder are connected with the support frame through positioning bolts and flange plates, and the first hydraulic cylinder and the second hydraulic cylinder are electrically connected with the hydraulic synchronizer.
Preferably, the controller is a PLC controller, the controller is externally connected with a power supply, and the controller is electrically connected with the hydraulic synchronizer.
Preferably, the supporting platform is connected with the supporting frame through a welding technology, the first placing groove and the second placing groove in the upper end of the supporting platform are used for placing aviation parts, and the first placing groove and the second placing groove can be replaced according to different aviation parts.
Preferably, the first placing groove and the second placing groove are the same placing groove.
Preferably, the first limiting clamping groove and the second limiting clamping groove are higher than the corresponding first placing groove and the second placing groove.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses have the effect of correcting to aviation part deformation, utilize first pneumatic cylinder to provide the numerical value of correct part, make first pneumatic cylinder and second pneumatic cylinder carry out steady safe action to this numerical value through hydraulic pressure synchronizer, reach the purpose of correcting the part.
Drawings
Fig. 1 is the utility model discloses aviation part distorts unscrambler overall structure elevation.
Fig. 2 is the utility model discloses aviation part distorts the overall structure side view of unscrambler.
Fig. 3 is the overall structure diagram of the supporting table of the present invention.
In the figure: 1-support frame, 2-hydraulic synchronizer, 3-first hydraulic cylinder, 4-second hydraulic cylinder, 5-support table, 6-support column, 7-controller, 8-display screen, 9-control key, 10-first placing groove, 11-second placing groove, 12-first limiting clamping groove, 13-second limiting clamping groove, 14-first threaded hole and 15-second threaded hole.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-3, the present invention provides a technical solution: the device comprises a support frame 1, a support table 5 and a controller 7, wherein the upper end of the support frame 1 is connected with a hydraulic synchronizer 2, the controller 7 and the support table 5, the controller 7 is a PLC controller, the controller 7 is electrically connected with the hydraulic synchronizer 2, the hydraulic synchronizer 2 can enable a first hydraulic cylinder 3 and a second hydraulic cylinder 4 to move at the same displacement or the same speed, the lower end of the support frame 1 is connected with the first hydraulic cylinder 3 and the second hydraulic cylinder 4, the first hydraulic cylinder 3 is used for pressing down aviation parts in a first placing groove 10 so as to obtain the value of a correct aviation part, the second hydraulic cylinder 4 is used for correcting deformed aviation parts, the upper end of the controller 7 is provided with a display screen 8 and a control key 9, the upper end of the support table 5 is provided with a first placing groove 10 and a second placing groove 11, and the first placing groove 10 and the second placing groove 11 are placing grooves with the same structure, first 10 both ends of first standing groove are provided with first spacing draw-in groove 12, first spacing draw-in groove 12 upper end is provided with first screw hole 14, 11 both ends of second standing groove are provided with the spacing draw-in groove 13 of second, and first spacing draw-in groove 12 and the spacing draw-in groove 13 of second all are used for fixed aviation part, the spacing draw-in groove 13 upper end of second is provided with second screw hole 15, the 5 lower extremes of brace table are provided with support column 6, and support column 6 plays the effect to brace table 5 support.
The utility model discloses a theory of operation does: the user first needs to place the aviation part intact, without deformation, in the first placement tank 10, and then to place the deformed aviation part in the second placement tank 11, then the limit blocks are respectively placed in the first limit clamp groove 12 and the second limit clamp groove 13, after being fixed in the first threaded hole 14 and the second threaded hole 15 through the stopper respectively by fixing bolts, finally, a power supply is connected with the controller 7 externally, the controller 7 is in an operating state, the controller 7 controls the first hydraulic cylinder 3 to press down, the intact and non-deformable aviation parts are adjusted to take a determined numerical value, then the first hydraulic cylinder 3 is reset, the controller 7 controls the hydraulic synchronizer 2 to enable the first hydraulic cylinder 3 and the second hydraulic cylinder 4 to move at the same displacement and speed, and the deformed aviation parts are corrected, so that the correction purpose is achieved.
It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (6)
1. The utility model provides an aviation part distorts unscrambler, includes support frame (1), brace table (5) and controller (7), its characterized in that: the hydraulic pressure synchronous device is characterized in that a hydraulic synchronizer (2), a controller (7) and a supporting table (5) are connected and arranged at the upper end of the supporting frame (1), a first hydraulic cylinder (3) and a second hydraulic cylinder (4) are connected and arranged at the lower end of the supporting frame (1), a display screen (8) and a control key (9) are arranged at the upper end of the controller (7), a first placing groove (10) and a second placing groove (11) are arranged at the upper end of the supporting table (5), first limiting clamping grooves (12) are arranged at two ends of the first placing groove (10), first threaded holes (14) are arranged at the upper end of the first limiting clamping grooves (12), second limiting clamping grooves (13) are arranged at two ends of the second placing groove (11), second threaded holes (15) are arranged at the upper end of the second limiting clamping grooves (13), and a supporting column (6) is.
2. The aerospace component deformation corrector of claim 1, wherein: first pneumatic cylinder (3) and second pneumatic cylinder (4) all pass through positioning bolt and ring flange joint support frame (1), first pneumatic cylinder (3) and second pneumatic cylinder (4) all with hydraulic pressure synchronous ware (2) electric connection.
3. The aerospace component deformation corrector of claim 1, wherein: the controller (7) is a PLC controller, the controller (7) is externally connected with a power supply, and meanwhile the controller (7) is electrically connected with the hydraulic synchronizer (2).
4. The aerospace component deformation corrector of claim 1, wherein: the supporting table (5) is connected with the supporting frame (1) through a welding technology.
5. The aerospace component deformation corrector of claim 1, wherein: the first placing groove (10) and the second placing groove (11) are the same.
6. The aerospace component deformation corrector of claim 1, wherein: the first limiting clamping groove (12) and the second limiting clamping groove (13) are higher than the corresponding first placing groove (10) and the second placing groove (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920324123.9U CN210023321U (en) | 2019-03-14 | 2019-03-14 | Aviation part deformation corrector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920324123.9U CN210023321U (en) | 2019-03-14 | 2019-03-14 | Aviation part deformation corrector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210023321U true CN210023321U (en) | 2020-02-07 |
Family
ID=69354910
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920324123.9U Active CN210023321U (en) | 2019-03-14 | 2019-03-14 | Aviation part deformation corrector |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210023321U (en) |
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2019
- 2019-03-14 CN CN201920324123.9U patent/CN210023321U/en active Active
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