CN214322621U - Auxiliary supporting device for machining aviation thin-walled part - Google Patents
Auxiliary supporting device for machining aviation thin-walled part Download PDFInfo
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- CN214322621U CN214322621U CN202120438481.XU CN202120438481U CN214322621U CN 214322621 U CN214322621 U CN 214322621U CN 202120438481 U CN202120438481 U CN 202120438481U CN 214322621 U CN214322621 U CN 214322621U
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- walled part
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Abstract
The application discloses an auxiliary supporting device for machining of an aviation thin-walled part, and relates to the technical field of machining of aviation thin-walled parts. The clamping position can be adjusted at will, the device is suitable for various machining stations, and can be used in cooperation with a clamp, the main body part of the aviation thin-walled part is prevented from being machined in a suspended mode, the rigidity of the aviation thin-walled part in the machining process is greatly improved, machining deformation is reduced, and machining quality is improved. The auxiliary supporting device comprises a base, a clamp, a first upright post assembly, a second upright post assembly and a locking assembly; the first end of the first stand column assembly is connected to the base through a first spherical universal joint, the first end of the second stand column assembly is connected with the clamp holder through a second spherical universal joint, the second end of the first stand column assembly and the second end of the second stand column assembly are connected to the locking assembly, the locking assembly can lock the first stand column assembly and/or the second stand column assembly, and the clamp holder is used for clamping a main body part of an aviation thin-walled part to be machined.
Description
Technical Field
The application relates to the technical field of aviation thin-walled workpiece machining, in particular to an auxiliary supporting device for machining an aviation thin-walled workpiece.
Background
With the continuous development of aerospace industry, high-performance thin-wall parts are widely applied to the aerospace field. Because the aviation thin-wall part mostly works under severe working conditions such as high temperature, high pressure, large load and the like, materials such as titanium alloy and the like with high strength, good corrosion resistance and high heat resistance are mostly used, but the materials of the type are generally higher in machining difficulty, and in addition, because the aviation thin-wall part has the characteristics of complex profile, thin wall, low rigidity, narrow and small machining space and the like, higher requirements are put forward for machining.
For example, when a blade is machined, due to the fact that a machining space is narrow, the base of the blade is generally clamped through a clamp in the prior art, the main body part of the upper portion of the blade is completely suspended for machining, due to the fact that the rigidity of the blade is small, machining deformation is prone to occurring in the machining process, surface quality is affected, excessive cutting can occur in serious conditions, and workpieces are scrapped.
SUMMERY OF THE UTILITY MODEL
The embodiment of the application provides an auxiliary supporting device for aviation thin-walled workpiece processing, can adjust clamping position wantonly, is applicable to multiple machining station to can use with anchor clamps cooperation, avoid the unsettled processing of aviation thin-walled workpiece main part position, thereby improve the rigidity in the aviation thin-walled workpiece course of working greatly, reduce the processing deformation, improve processingquality.
In order to achieve the above purpose, an embodiment of the present application provides an auxiliary supporting device for machining an aviation thin-walled part, including a base; the clamp holder is used for clamping the main body part of the aviation thin-walled part to be processed; the first end of the first upright post assembly is connected to the base through a first ball joint, and the first end of the second upright post assembly is connected to the clamp holder through a second ball joint; and the second end of the first stand column assembly and the second end of the second stand column assembly are connected to the locking assembly, and the locking assembly can lock the first stand column assembly and/or the second stand column assembly.
Furthermore, the first spherical universal joint comprises a ball seat and a ball head, one end of the ball seat is provided with a groove matched with the ball head, and the other end of the ball seat is provided with a first through hole communicated with the groove; the structure of the second ball joint is the same as that of the first ball joint.
Further, the first column assembly comprises a connecting pipe, a locking shaft and a gasket sleeve; the first end of the connecting pipe is connected with the first ball universal joint, and the second end of the connecting pipe is connected with the side wall of the gasket sleeve; a second through hole is formed in the side wall of the gasket outer sleeve; the locking shaft is arranged in the connecting pipe and can move along the axial direction of the connecting pipe, and one end of the locking shaft penetrates through the first through hole, the connecting pipe and the second through hole in sequence and then tightly pushes or loosens a ball head in the first ball universal joint; the structure of the second upright post component is the same as that of the first upright post component.
Furthermore, a stepped hole is formed in the gasket outer sleeve; the locking assembly comprises a locking bolt and two tapered washers; the locking bolt comprises a nut, two threaded sections and a polished rod section, and the polished rod section is positioned between the two threaded sections; the inner holes of the two conical gaskets and the small holes of the gasket outer sleeves are respectively provided with an inner thread matched with the outer thread of the thread section, after the two conical gaskets and the two gasket outer sleeves are respectively connected with the corresponding thread sections, at least one part of each conical gasket is positioned in the corresponding gasket outer sleeve.
Further, the clamp is driven by a driving mechanism to clamp or release the aviation thin-walled piece to be processed.
Furthermore, the holder comprises a fixed frame and two rubber clamping plates, two sides of the fixed frame are respectively connected with a first end of at least one first connecting rod, a second end of the first connecting rod is connected with the rubber clamping plates, a second connecting rod is arranged between the two first connecting rods, and two ends of the second connecting rod are respectively hinged to the middle part of one of the first connecting rods; the middle part of the second connecting rod is connected with the driving mechanism through a pull rod.
Further, the driving mechanism comprises a clamping shaft, a gear and a rack, wherein the gear is arranged at the small end of the clamping shaft; the first end of the rack is meshed with the gear, the second end of the rack is connected with the pull rod, the extending direction of the rack is overlapped with the axis of the pull rod, and the rack is connected with the fixed rack in a sliding mode.
Furthermore, a third anti-skidding line is arranged on the clamping surface of the rubber clamping plate.
Further, the base is of a hollow cube structure, an electromagnetic relay is arranged in the base, and when the electromagnetic relay is electrified, the bottom surface and the side surface of the base are both magnetic.
Furthermore, an anti-skid groove is formed in the outer circular surface of the nut; a first anti-skid grain is arranged on the outer circular surface of the ball seat; and second anti-skid grains are arranged on the outer circular surface of the large end of the clamping shaft.
Compared with the prior art, the application has the following beneficial effects:
1. the clamp holder of the embodiment in the application is connected with the base through two spherical universal joints, can rotate at any angle, can adjust the clamping position as required, is suitable for various machining stations, can be used in cooperation with the clamp, avoids the suspended machining of the main body part of the aviation thin-walled part, greatly improves the rigidity of the aviation thin-walled part in the machining process, reduces the machining deformation, and improves the machining quality.
2. The clamping plate in the embodiment of the application is an elastic rubber plate, is suitable for aviation thin-wall parts with complex curved surface appearances such as blades and the like, and cannot damage the surface of a workpiece.
3. The clamping surface of the rubber clamping plate in the embodiment of the application is provided with the anti-slip lines, so that the reliability of clamping can be improved.
4. The base in the embodiment of the application is internally provided with the electromagnetic relay, the bottom surface and the side surface of the base can be provided with magnetism, and the supporting device can be fixed at any position of the workbench.
5. This application embodiment locks two ball universal joints simultaneously or respectively through a set of locking Assembly, and the hand-operated rotation locking bolt can lock ball universal joint, and it is very convenient to operate.
6. The actuating mechanism in this application embodiment is including pressing from both sides tight axle, gear and rack, and the main aspects of manual rotation clamp shaft can drive the holder and press from both sides tightly or loosen the work piece, and is practical more nimble, convenient.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an auxiliary supporting device for machining an aviation thin-walled part according to an embodiment of the application;
FIG. 2 is a schematic structural diagram of a first column assembly in the auxiliary supporting device for machining the aviation thin-walled part according to the embodiment of the application;
FIG. 3 is a schematic structural diagram of a ball seat of a first ball universal joint in an auxiliary supporting device for machining an aviation thin-walled part according to an embodiment of the application;
FIG. 4 is a schematic structural diagram of a locking assembly in the auxiliary supporting device for machining the aviation thin-walled part according to the embodiment of the application;
fig. 5 is a schematic view of a connecting structure of a holder and a driving mechanism in an auxiliary supporting device for machining an aviation thin-walled part according to an embodiment of the application.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the 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 application.
In the description of the present application, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and thus should not be construed as limiting the present application.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; the specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless otherwise specified.
Referring to fig. 1, the embodiment of the application provides an auxiliary supporting device for machining an aviation thin-walled part, and the auxiliary supporting device comprises a base 1, a clamp 8, a first stand column assembly 2, a second stand column assembly 3 and a locking assembly 6. The first end of the first upright post component 2 is connected to the base 1 through a first spherical universal joint 4, and the first end of the second upright post component 3 is connected with a clamp holder 8 for clamping the main body part of the aviation thin-walled part to be processed through a second spherical universal joint 5; the second end of first stand subassembly 2 and the second end of second stand subassembly 3 are all connected on locking assembly 6, and locking assembly 6 can be alone with first stand subassembly 2 or the locking of second stand subassembly 3, or with first stand subassembly 2 or the locking of second stand subassembly 3 simultaneously.
With reference to fig. 1, the base 1 is a hollow cube structure, and an electromagnetic relay (not shown) is disposed inside the base, and a boss is disposed on a side surface of the base, and a knob switch and a control mark are disposed on the boss. The knob switch is used for controlling the on-off of the electromagnetic relay. Before processing aviation thin-walled spare, place this application embodiment auxiliary stay device in workstation optional required position, then, the position of manual rotatory knob to "opening", electromagnetic relay circular telegram, the bottom surface and the side of base 1 all have magnetism, and at this moment, this application embodiment auxiliary stay device can be firm adsorb on the workstation. After processing is accomplished, manual rotation knob to the position of "closing", electromagnetic relay outage, the bottom surface and the side of base 1 all lose magnetism, can easily remove this application embodiment auxiliary stay device, the reliable operation is convenient.
Referring to fig. 1 and 3, the first ball joint 4 includes a ball seat 41 and a ball head 42, one end of the ball seat 41 is provided with a groove 411 adapted to the ball head 42, and the other end of the ball seat 41 is provided with a first through hole (not shown) communicating with the groove 411. The ball seat 41 is made of plastic, and for the convenience of installation, a first anti-slip pattern 412 is further disposed on an outer circumferential surface of the ball seat 41.
The structure of the second ball joint 5 is the same as that of the first ball joint 4 and will not be described in detail here.
Referring to fig. 1 and 2, the first pillar assembly 2 includes a connection pipe 22, a locking shaft 21, and a washer housing 23. The connection pipe 22 is not cylindrical, a first end of the connection pipe 22 is connected to the first ball joint 4, and a second end of the connection pipe 22 is connected to a side wall of the washer casing 23. The side wall of the washer jacket 23 is provided with a second through hole 231, the locking shaft 21 is arranged in the connecting pipe 22 and can move along the axial direction of the connecting pipe 22, and one end of the locking shaft 21 sequentially penetrates through the first through hole, the connecting pipe 22 and the second through hole 231 and then tightly pushes or loosens the ball head 42 in the first ball universal joint 4. The structure of the second column assembly 3 is the same as that of the first column assembly 2 and will not be described in detail here.
Referring to fig. 1 and 4, the locking assembly 6 includes a locking bolt 61 and two tapered washers 62. Wherein lock bolt 61 includes a nut 611, two threaded segments 612, and a rod segment 613, rod segment 613 being located intermediate threaded segments 612. A stepped hole is formed in the gasket outer sleeve 23, inner holes of the two conical gaskets 62 and small holes of the gasket outer sleeve 23 are respectively provided with inner threads matched with the outer threads of the threaded section 612, and after the two conical gaskets 62 and the two gasket outer sleeves 23 are respectively connected with the corresponding threaded sections 612, at least one part of each conical gasket 62 is positioned in the corresponding gasket outer sleeve 23. The outer circumferential surface of the nut 611 is provided with an anti-slip groove, whereby it is more convenient to screw the lock bolt 61.
Referring to fig. 1, when the first column assembly 2 needs to be locked, the first column assembly 2 is fixed, and the nut 611 of the locking bolt 61 is manually screwed, the locking bolt 61 drives the tapered washer 62 to move axially, and the large end of the tapered washer 62 is closer to the second through hole 231 of the washer casing 23, and pushes the locking shaft 21 to move toward the ball 42 until the ball 42 is pressed tightly, and the first column assembly 2 is locked. The locking of the second mast assembly 3 is the same as the locking of the first mast assembly 2 and will not be described in detail here.
Referring to fig. 1 and 5, the clamper 8 includes a fixed frame 81 and two rubber clamping plates 83. The two sides of the fixed frame 81 are connected with the first ends of the two first connecting rods 82, the second ends of the first connecting rods 82 are hinged with the rubber clamping plates 83, the second connecting rods 84 are arranged between the two first connecting rods 82 positioned on the inner side, the two ends of each second connecting rod 84 are hinged to the middle of one of the first connecting rods 82 positioned on the inner side, and the middle of each second connecting rod 84 is connected with the driving mechanism 7 through a pull rod 85. The driving mechanism 7 can drive the clamper 8 to clamp or release the thin-wall part to be processed. The rubber jaw 83 is a triangular plate, and the first link 82 is connected to one of the sides of the triangular plate. For more reliable clamping, a third anti-slip texture 831 is arranged on the clamping surface of the rubber clamping plate 83. The rubber clamping plate 83 has elasticity, is suitable for aviation thin-wall parts with complicated curved surface appearances such as blades and the like, and cannot damage the surface of a workpiece.
When a workpiece needs to be clamped, the clamping shaft 71 is rotated, the gear 72 drives the rack 73 to slide in the sliding groove and move in the direction away from the rubber clamping plate 83, the pull rod 85 drives the second connecting rod 84 to move in the direction away from the rubber clamping plate 83, and the second connecting rod 84 drives the first connecting rod 82 to move inwards until the rubber clamping plate 83 clamps the workpiece. When it is desired to release the workpiece, the gripper 8 can be released by rotating the gripping shaft 71 in the opposite direction.
With continued reference to fig. 1 and 5, the drive mechanism 7 includes a clamp shaft 71, a gear 72, and a rack 73. Wherein the clamp shaft 71 is a stepped shaft, and a gear 72 is provided on a small end of the clamp shaft 71. The first end of the rack 73 is meshed with the gear 72, the second end of the rack 73 is connected with the pull rod 85, and the extending direction of the rack 73 is coincided with the axis of the pull rod 85. The fixed frame 81 is provided with a sliding groove, the bottom of the rack 73 is provided with a sliding block, and the rack 73 can slide along the sliding groove of the fixed frame 81. The outer circumference of the large end of the clamping shaft 71 is provided with second anti-slip threads 711, whereby it is more convenient to screw the clamping shaft 71.
When the device is used, the knob is manually rotated to the 'on' position, the base 1 is fixed on the workbench, then the first upright post component 2 and the second upright post component 3 are adjusted to rotate the clamp holder 8 to the appropriate non-interference position, then the clamping shaft 71 is rotated to clamp the rubber clamping plate 83 on the side edge of the main body part of the aviation thin-walled part, and finally the locking bolt 61 is rotated to fix the whole auxiliary supporting device and start processing. And when the clamping position is machined, the supporting device is readjusted to clamp the machined position or other unprocessed positions of the main body part of the aviation thin-wall part.
The auxiliary supporting device can rotate at any angle, is suitable for various machining stations, and is wide in application range.
The above is only an embodiment of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions within the technical scope of the present disclosure should be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. An auxiliary supporting device for machining an aviation thin-walled part is characterized by comprising:
a base;
the clamp holder is used for clamping the main body part of the aviation thin-walled part to be processed;
the first end of the first upright post assembly is connected to the base through a first ball joint, and the first end of the second upright post assembly is connected to the clamp holder through a second ball joint;
and the second end of the first stand column assembly and the second end of the second stand column assembly are connected to the locking assembly, and the locking assembly can lock the first stand column assembly and/or the second stand column assembly.
2. An auxiliary support device for the machining of an aerospace thin-walled part according to claim 1,
the first spherical universal joint comprises a ball seat and a ball head, one end of the ball seat is provided with a groove matched with the ball head, and the other end of the ball seat is provided with a first through hole communicated with the groove;
the structure of the second ball joint is the same as that of the first ball joint.
3. An auxiliary support device for the machining of an aerospace thin-walled part according to claim 2,
the first upright post assembly comprises a connecting pipe, a locking shaft and a gasket sleeve;
the first end of the connecting pipe is connected with the first ball universal joint, and the second end of the connecting pipe is connected with the side wall of the gasket sleeve; a second through hole is formed in the side wall of the gasket outer sleeve;
the locking shaft is arranged in the connecting pipe and can move along the axial direction of the connecting pipe, and one end of the locking shaft penetrates through the first through hole, the connecting pipe and the second through hole in sequence and then tightly pushes or loosens a ball head in the first ball universal joint;
the structure of the second upright post component is the same as that of the first upright post component.
4. An auxiliary support device for machining an aerospace thin-walled part according to claim 3, wherein,
a step hole is formed in the gasket outer sleeve;
the locking assembly comprises a locking bolt and two tapered washers;
the locking bolt comprises a nut, two threaded sections and a polished rod section, and the polished rod section is positioned between the two threaded sections;
the inner holes of the two conical gaskets and the small holes of the gasket outer sleeves are respectively provided with an inner thread matched with the outer thread of the thread section, after the two conical gaskets and the two gasket outer sleeves are respectively connected with the corresponding thread sections, at least one part of each conical gasket is positioned in the corresponding gasket outer sleeve.
5. An auxiliary supporting device for machining an aviation thin-walled part according to claim 4, wherein the clamp is driven by a driving mechanism to clamp or release the aviation thin-walled part to be machined.
6. An auxiliary support device for the machining of an aerospace thin-walled part according to claim 5,
the clamp holder comprises a fixed rack and two rubber clamping plates, the two sides of the fixed rack are respectively connected with the first end of at least one first connecting rod, the second end of the first connecting rod is connected with the rubber clamping plates, a second connecting rod is arranged between the two first connecting rods, and the two ends of the second connecting rod are respectively hinged to the middle part of one of the first connecting rods; the middle part of the second connecting rod is connected with the driving mechanism through a pull rod.
7. The auxiliary support device for machining an aerospace thin-walled part according to claim 6, wherein the driving mechanism comprises a clamping shaft, a gear and a rack, and the gear is arranged at the small end of the clamping shaft; the first end of the rack is meshed with the gear, the second end of the rack is connected with the pull rod, the extending direction of the rack is overlapped with the axis of the pull rod, and the rack is connected with the fixed rack in a sliding mode.
8. An auxiliary supporting device for machining an aviation thin-walled part according to claim 6, wherein a third anti-skidding line is arranged on the clamping surface of the rubber clamping plate.
9. The auxiliary supporting device for machining the aviation thin-walled part according to any one of claims 1 to 8, wherein the base is of a hollow cube structure, an electromagnetic relay is arranged in the base, and when the electromagnetic relay is powered on, the bottom surface and the side surface of the base are both magnetic.
10. The auxiliary supporting device for machining the aviation thin-walled workpiece according to claim 7, wherein an anti-skid groove is formed in the outer circular surface of the nut; a first anti-skid grain is arranged on the outer circular surface of the ball seat; and second anti-skid grains are arranged on the outer circular surface of the large end of the clamping shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120438481.XU CN214322621U (en) | 2021-03-01 | 2021-03-01 | Auxiliary supporting device for machining aviation thin-walled part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120438481.XU CN214322621U (en) | 2021-03-01 | 2021-03-01 | Auxiliary supporting device for machining aviation thin-walled part |
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| Publication Number | Publication Date |
|---|---|
| CN214322621U true CN214322621U (en) | 2021-10-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120438481.XU Expired - Fee Related CN214322621U (en) | 2021-03-01 | 2021-03-01 | Auxiliary supporting device for machining aviation thin-walled part |
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| Country | Link |
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| CN (1) | CN214322621U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113955619A (en) * | 2021-11-10 | 2022-01-21 | 中国原子能科学研究院 | Hoisting device |
-
2021
- 2021-03-01 CN CN202120438481.XU patent/CN214322621U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113955619A (en) * | 2021-11-10 | 2022-01-21 | 中国原子能科学研究院 | Hoisting device |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20211001 |