CN213764645U - Aviation spare part fixture - Google Patents
Aviation spare part fixture Download PDFInfo
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- CN213764645U CN213764645U CN202022274102.6U CN202022274102U CN213764645U CN 213764645 U CN213764645 U CN 213764645U CN 202022274102 U CN202022274102 U CN 202022274102U CN 213764645 U CN213764645 U CN 213764645U
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Abstract
The utility model provides an aviation spare part fixture, the purpose is solved current fixture and is leaded to thin wall pipe fitting class aviation spare part to take place the technical problem of sunken deformation easily. The adopted technical scheme is as follows: an aviation part clamping mechanism comprises a first rotating seat, a second rotating seat and a third rotating seat, wherein the first rotating seat is driven by a first servo motor to rotate left and right; a first mounting seat is mounted on the surface of the first rotating seat, and is provided with a first bulge matched with the inner periphery of the aviation part; the first bulge is matched with a first abutting piece driven by the first cylinder to abut against aviation parts. The utility model discloses can support its inner wall when centre gripping aviation spare part to effectively avoid aviation spare part to take place sunken deformation in the centre gripping in-process.
Description
Technical Field
The utility model relates to an aviation spare part processing equipment technical field, concretely relates to aviation spare part fixture.
Background
In the field of the aeronautical industry, the quality requirements are higher than those of common workpieces because the parts are finally used in a relatively harsh environment. In the process of producing and processing aviation parts, the machining and assembling of the aviation parts in pipe fitting type are often involved. When the aviation parts are machined or assembled, the aviation parts are generally clamped and fixed through a chuck, and clamping jaws of the chuck tightly abut against the outer peripheral wall of the aviation parts, so that the aviation parts are kept fixed. When the pipe wall of the aviation part is thin, the clamping part is easy to dent due to pressure, so that weak deformation occurs. Because the use environment of the aviation parts is harsh, even if the aviation parts are slightly deformed, the quality of the aviation parts can be seriously influenced, and certain potential safety hazards exist in the subsequent use process of the aviation parts. Therefore, there is a need to develop a clamping mechanism which can prevent the deformation of the aviation components such as pipes.
Disclosure of Invention
An object of the utility model is to provide an aviation spare part fixture, it can effectively avoid pipe fitting class aviation spare part to take place to warp at the clamping process.
In order to achieve the above object, the utility model adopts the following technical scheme:
an aircraft component clamping mechanism comprising:
the first rotating seat is driven by the first servo motor to rotate left and right;
the first mounting seat is detachably mounted on the upper surface of the first rotating seat and is provided with a first bulge matched with the inner periphery of the aviation part;
the first abutting piece is driven by the first cylinder and matched with the first bulge to abut against the aviation parts;
the second rotating seat is driven by the second servo motor to rotate left and right;
the second mounting seat is detachably mounted on the upper surface of the second rotating seat and is provided with a second bulge matched with the inner periphery of the aviation part;
the second abutting piece is driven by the second cylinder and matched with the second bulge to abut against the aviation parts;
the second mounting seat is positioned at the right lower part of the first mounting seat, and a sliding groove for guiding the aviation part from the first mounting seat to the second mounting seat is arranged between the first mounting seat and the second mounting seat.
Optionally, a protective cover is arranged on the upper surface of the sliding chute, and the protective cover and the sliding chute enclose a limiting cavity with two through ends; the inner diameter of the limiting cavity is gradually reduced from the feeding end to the discharging end.
Optionally, the first abutting part comprises a first connecting part fixedly connected with the first cylinder and a first abutting part for abutting against the outer wall of the aviation part; the abutting surface of the first abutting portion is matched with the outer wall of the aviation part.
Optionally, a plurality of first abutting pieces are arranged and evenly distributed around the first protrusion; the first servo motor and the first air cylinder are arranged on the first workbench.
Optionally, the second abutting piece and the first abutting piece are the same in structure.
Optionally, a plurality of second fastening pieces are arranged and uniformly distributed around the second protrusion; and the second servo motor and the second air cylinder are arranged on the second workbench.
Optionally, the upper surface of the first workbench is provided with two first bosses extending in the left-right direction, and a first accommodating groove for accommodating the first rotating seat is formed at an interval between the two first bosses; the first servo motor and the first cylinder are arranged on the first boss.
Optionally, the upper surface of the second workbench is provided with two second bosses extending in the left-right direction, and a second accommodating groove for accommodating the second rotating seat is formed at an interval between the two second bosses; and the second servo motor and the second air cylinder are arranged on the second boss.
The utility model discloses a theory of operation does: the first bulges are vertically upward, and the bottom end of the pipe fitting type aviation part is sleeved on the peripheries of the first bulges. Through the first piece of propping of first cylinder drive and moving towards first arch, can cooperate first arch to support the fastening fixedly to aviation spare part. And after the milling mechanism finishes processing the upper section of the aviation part, loosening the first abutting piece. The second rotating seat and the second mounting seat are driven to rotate towards the left by the second servo motor, so that the second protrusion faces the discharge end of the sliding groove and is parallel to the sliding groove. Then drive first rotating seat and first mount pad through first servo motor and rotate towards the right side, make first arch towards the feed end of spout. The aviation spare part can follow the spout and slide to the second arch to the cover is established at the protruding periphery of second. Then, the second rotating seat and the second mounting seat are driven to rotate towards the right through a second servo motor, so that the second protrusion is vertically upward, and the aviation parts are abutted and fixed through the cooperation of the second abutting piece and the second protrusion; namely, the unmachined section of the aviation part can be machined by the milling mechanism.
Therefore, the utility model has the advantages that: the first protrusion and the second protrusion can support the inner periphery of the aviation part, so that the aviation part is effectively prevented from deforming under the pressing of the first abutting piece and the second abutting piece. In addition, the clamping process of the aviation parts is simple, the parameters of the first servo motor, the first air cylinder, the second servo motor and the second air cylinder are set, the process and the automatic clamping of the aviation parts can be realized, the automatic line production is convenient to carry out, the processing efficiency is improved, and the labor intensity is reduced. In addition, when carrying out processing operations such as assembly welding to aviation spare part, also can pass through the utility model discloses it is fixed to carry out the centre gripping to aviation spare part.
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 view of the present invention;
fig. 2 is a top view of the present invention;
FIG. 3 is a schematic structural diagram of a first worktable;
FIG. 4 is a schematic structural view of the chute;
FIG. 5 is a schematic view of the assembly of the first rotating base and the first mounting base;
FIG. 6 is a schematic view of a first abutment member;
reference numerals: 1. a first rotating base; 2. a first servo motor; 3. a first mounting seat; 4. a first protrusion; 5. a first abutment member; 6. a first cylinder; 7. a second rotating base; 8. a second servo motor; 9. a second mounting seat; 10. a second protrusion; 11. a second abutment member; 12. a second cylinder; 13. a chute; 14. a shield; 15. a first connection portion; 16. a first abutting portion; 17. a first table; 18. a second table; 19. a first boss.
Detailed Description
In the following, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the present invention. Accordingly, the drawings and description are to be regarded as illustrative in nature, and not as restrictive.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship indicated based on the orientation or positional relationship shown in fig. 1, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
Furthermore, 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 invention, "a plurality" means two or more unless specifically limited otherwise.
Embodiments of the present invention will be described in detail below with reference to fig. 1 to 6.
The embodiment of the utility model provides an aviation spare part fixture, this fixture includes:
and a first rotating base 1 which is driven by a first servo motor 2 to rotate left and right.
The first mounting seat 3 is detachably mounted on the upper surface of the first rotating seat 1 and is provided with a first bulge 4 matched with the inner periphery of the aviation part; it should be understood that the height of the first projection 4 is less than or equal to half the height of the aeronautical component. The shape of the outer periphery of the first bulge 4 is matched with the shape of the inner periphery of the aviation part, and the first bulge can be circular, oval or polygonal. First mount pad 3 can dismantle with first rotation seat 1 and be connected, can change first mount pad 3 according to the shape of aviation spare part to make the shape of first arch 4 and aviation spare part phase-match.
And the first abutting piece 5 is driven by the first cylinder 6 and matched with the first bulge 4 to form abutting on the aviation part.
And a second rotary base 7 which is driven by a second servo motor 8 to rotate left and right.
A second mounting seat 9 detachably mounted on the upper surface of the second rotating seat 7 and provided with a second protrusion 10 matched with the inner periphery of the aviation component; it should be understood that the height of the second projection 10 is less than or equal to half the height of the aircraft component. The shape of the outer periphery of the second protrusion 10 is matched with the shape of the inner periphery of the aviation part, and the second protrusion can be circular, oval or polygonal. The second mounting seat 9 is detachably connected with the second rotating seat 7, and the second mounting seat 9 can be replaced according to the shape of the aviation part, so that the shape of the second protrusion 10 is matched with the shape of the aviation part.
The second abutting piece 11 is driven by a second air cylinder 12 and matched with the second bulge 10 to abut against the aviation parts;
the second mounting seat 9 is located at the lower right of the first mounting seat 3, and a sliding groove 13 for guiding the aviation component from the first mounting seat 3 to the second mounting seat 9 is arranged between the first mounting seat and the second mounting seat.
Set forth below the utility model discloses an embodiment makes first arch 4 vertical up, establishes the bottom cover of pipe fitting class aviation spare part in first arch 4's periphery. Through the first piece 5 that supports of first cylinder 6 drive and remove towards first arch 4, can cooperate first arch 4 to support the fastening fixedly to aviation spare part. After the machining of the upper section of the aircraft component is completed by the milling mechanism, the first abutment member 5 is released. The second rotating seat 7 and the second mounting seat 9 are driven to rotate towards the left by the second servo motor 8, so that the second protrusion 10 faces the discharge end of the chute 13 and is parallel to the chute 13. Then, the first rotating base 1 and the first mounting base 3 are driven by the first servo motor 2 to rotate towards the right, so that the first protrusion 4 faces the feeding end of the sliding chute 13. The aviation part slides to the second protrusion 10 along the sliding groove 13 and is sleeved on the periphery of the second protrusion 10. Then, the second rotating seat 7 and the second mounting seat 9 are driven to rotate towards the right by the second servo motor 8, so that the second protrusion 10 is vertically upward, and the aviation parts are abutted and fixed by the cooperation of the second abutting piece 11 and the second protrusion 10; namely, the unmachined section of the aviation part can be machined by the milling mechanism. The utility model discloses a first arch 4 can constitute the support to the interior week of aviation spare part with the protruding 10 of second to effectively avoid the aviation spare part to take place the deformation under first supporting 5 and the pressing of second supporting 11. In addition, the clamping process of the aviation parts is simple, parameters of the first servo motor 2, the first air cylinder 6, the second servo motor 8 and the second air cylinder 12 are set, the process and automatic clamping of the aviation parts can be realized, the automatic line production is facilitated, the machining efficiency is improved, and the labor intensity is reduced. In addition, when carrying out processing operations such as assembly welding to aviation spare part, also can pass through the utility model discloses it is fixed to carry out the centre gripping to aviation spare part.
In one embodiment provided by the application, a protective cover 14 is arranged on the upper surface of the sliding chute 13, and the protective cover 14 and the sliding chute 13 enclose a limiting cavity with two through ends; the inner diameter of the limiting cavity is gradually reduced from the feeding end to the discharging end. It will be appreciated that the two ends of the shroud 14 should be shorter than the two ends of the chute 13 to enable the aircraft component to rotate with the first projection 4 into the feed end of the chute 13 and with the second projection 10 out of the discharge end of the chute 13. The internal diameter of spacing chamber reduces from the feed end to the discharge end gradually, both can avoid the aviation spare part to drop into chute 13 when following the feed end and deviate from, can retrain the aviation spare part again, can be with the protruding 10 coaxial alignments of second when making the aviation spare part slide the discharge end. In addition, the minimum inner diameter of the limiting cavity can be the same as the outer diameter of the aviation part.
In one embodiment of the present application, the first abutment member 5 comprises a first connecting portion 15 fixedly connected to the first cylinder 6 and a first abutment portion 16 for forming abutment against the outer wall of the aircraft component; the abutting surface of the first abutting portion 16 is matched with the outer wall of the aviation part.
In one embodiment given in the present application, the first abutting elements 5 are provided in plurality and evenly distributed around the first protrusion 4; the first servo motor 2 and the first cylinder 6 are mounted on a first table 17. It will be appreciated that when the first protrusions 4 are directed vertically upwards, said first abutment members 5 are evenly distributed around the circumference of the first protrusions 4.
In one embodiment presented herein, the second abutment member 11 is identical in construction to the first abutment member 5.
In one embodiment given in the present application, the second fastening member 11 is provided in plurality and evenly distributed around the second protrusion 10; the second servo motor 8 and the second cylinder 12 are mounted on a second table 18. It will be appreciated that when the second projection 10 is directed vertically upwards, said second abutment members 11 are evenly distributed around the circumference of the second projection 10.
In one embodiment of the present application, the upper surface of the first worktable 17 has two first bosses 19 extending in the left-right direction, and the space between the two first bosses 19 forms a first receiving groove for receiving the first rotating base 1; the first servo motor 2 and the first cylinder 6 are mounted on the first boss 19. It should be understood that one side of the front and back sides of the first rotating base 1 is fixedly connected to the rotating shaft of the first servo motor 2, and the other side is provided with a shaft portion, and is connected to the first boss 19 through a bearing sleeved on the shaft portion.
In one embodiment of the present application, the upper surface of the second worktable 18 has two second bosses extending in the left-right direction, and the space between the two second bosses forms a second receiving groove for receiving the second rotating base 7; the second servo motor 8 and the second cylinder 12 are mounted on the second boss. It should be understood that the structure and the installation manner of the second rotating base 7 are similar to those of the first rotating base 1, and are not described in detail herein.
Although specific embodiments of the present invention have been described above, it will be appreciated by those skilled in the art that changes and modifications may be made to these embodiments without departing from the principles and spirit of the invention, and these changes and modifications are intended to fall within the scope of the invention.
Claims (8)
1. The utility model provides an aviation spare part fixture which characterized in that includes:
the first rotating seat (1) is driven by the first servo motor (2) to rotate left and right;
the first mounting seat (3) is detachably mounted on the upper surface of the first rotating seat (1) and is provided with a first protrusion (4) matched with the inner periphery of the aviation part;
the first abutting piece (5) is driven by the first cylinder (6) and matched with the first bulge (4) to form abutting on the aviation parts;
a second rotating base (7) which is driven by a second servo motor (8) to rotate left and right;
a second mounting seat (9) which is detachably mounted on the upper surface of the second rotating seat (7) and is provided with a second bulge (10) matched with the inner periphery of the aviation part;
the second abutting piece (11) is driven by a second cylinder (12) and matched with the second bulge (10) to form abutting on the aviation part;
the second mounting seat (9) is positioned at the lower right part of the first mounting seat (3), and a sliding groove (13) for guiding the aviation part from the first mounting seat (3) to the second mounting seat (9) is arranged between the second mounting seat and the first mounting seat.
2. The aircraft component clamping mechanism of claim 1, wherein: a protective cover (14) is arranged on the upper surface of the sliding groove (13), and the protective cover (14) and the sliding groove (13) enclose a limiting cavity with two through ends; the inner diameter of the limiting cavity is gradually reduced from the feeding end to the discharging end.
3. The aircraft component clamping mechanism of claim 1 or 2, wherein: the first abutting piece (5) comprises a first connecting part (15) fixedly connected with the first cylinder (6) and a first abutting part (16) for abutting against the outer wall of the aviation part; the abutting surface of the first abutting part (16) is matched with the outer wall of the aviation part.
4. The aircraft component clamping mechanism of claim 3, wherein: the first abutting pieces (5) are arranged in a plurality and are uniformly distributed around the first protrusion (4); the first servo motor (2) and the first air cylinder (6) are arranged on a first workbench (17).
5. The aircraft component clamping mechanism of claim 3, wherein: the second abutting piece (11) is the same as the first abutting piece (5) in structure.
6. The aircraft component clamping mechanism of claim 5, wherein: the second abutting pieces (11) are arranged in plurality and are uniformly distributed around the second protrusion (10); the second servo motor (8) and the second air cylinder (12) are arranged on a second workbench (18).
7. The aircraft component clamping mechanism of claim 4, wherein: the upper surface of the first workbench (17) is provided with two first bosses (19) extending along the left-right direction, and a first accommodating groove for accommodating the first rotating seat (1) is formed at the interval between the two first bosses (19); the first servo motor (2) and the first air cylinder (6) are arranged on the first boss (19).
8. The aircraft component clamping mechanism of claim 6, wherein: the upper surface of the second workbench (18) is provided with two second bosses extending along the left-right direction, and a second accommodating groove for accommodating the second rotating seat (7) is formed at intervals between the two second bosses; and the second servo motor (8) and the second air cylinder (12) are arranged on the second boss.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022274102.6U CN213764645U (en) | 2020-10-13 | 2020-10-13 | Aviation spare part fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022274102.6U CN213764645U (en) | 2020-10-13 | 2020-10-13 | Aviation spare part fixture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213764645U true CN213764645U (en) | 2021-07-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022274102.6U Active CN213764645U (en) | 2020-10-13 | 2020-10-13 | Aviation spare part fixture |
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| CN (1) | CN213764645U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114986129A (en) * | 2022-05-09 | 2022-09-02 | 中国人民解放军第五七一九工厂 | Clamping structure and method for decomposing aero-engine bleed air connector |
-
2020
- 2020-10-13 CN CN202022274102.6U patent/CN213764645U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114986129A (en) * | 2022-05-09 | 2022-09-02 | 中国人民解放军第五七一九工厂 | Clamping structure and method for decomposing aero-engine bleed air connector |
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Address after: 610000 Baiyun Road, East Industrial District, Xindu District, Chengdu City, Sichuan Province Patentee after: Chengdu Dajin HangTai Technology Co.,Ltd. Address before: 610000 Baiyun Road, East Industrial District, Xindu District, Chengdu City, Sichuan Province Patentee before: SICHUAN DAJIN STAINLESS STEEL CO.,LTD. |