CN111872415A - Aerospace fastening part lathe work mechanism - Google Patents
Aerospace fastening part lathe work mechanism Download PDFInfo
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- CN111872415A CN111872415A CN202010765518.XA CN202010765518A CN111872415A CN 111872415 A CN111872415 A CN 111872415A CN 202010765518 A CN202010765518 A CN 202010765518A CN 111872415 A CN111872415 A CN 111872415A
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- clamping
- groove
- rod
- outer cylinder
- fastening part
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B5/00—Turning-machines or devices specially adapted for particular work; Accessories specially adapted therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B25/00—Accessories or auxiliary equipment for turning-machines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Clamps And Clips (AREA)
Abstract
The invention discloses a turning mechanism for an aerospace fastening part, which comprises a base plate, a fixing hole, a clamping seat, a cylindrical groove, a circular through groove and a mounting assembly, wherein the mounting assembly is optimally arranged on the inner side of the clamping seat, and the height position of a column block is adjusted through the matching of a threaded rod and an internal thread sleeve, so that the fine adjustment of the height position of a tool bit is realized; the rotating handle is rotated to enable the rack to drive the clamping rod to move through the movement of the column rod in the groove cavity, then the cutter head is inserted into the socket, the clamping rod is inserted into a preset positioning hole in the cutter under the elastic action of the spring, and then the cutter head is rapidly fixed and positioned, so that the machining efficiency of products is accelerated.
Description
Technical Field
The invention relates to the related field of part machining, in particular to a turning mechanism for an aerospace fastening part.
Background
Aviation refers to the navigation activity of an aircraft in the earth atmosphere, aerospace refers to the navigation activity of the aircraft in the space outside the atmosphere, and aerospace greatly changes the structure of transportation; for aerospace fasteners, the machining precision requirement is high, and the machining precision is generally ensured by adopting turning.
The required shape of cutter turning play need be carried out when aerospace fastening part carries out the turning, but utilizes the bolt to fix the tool bit usually when the turning cutter installation of prior art, need change the tool bit that corresponds when processing different shapes, because the tool bit adopts the bolt fastening, is difficult for changing and the location when changing, influences the machining efficiency of product.
Disclosure of Invention
Therefore, in order to solve the above-mentioned defects, the invention provides an aerospace fastening part turning mechanism.
The invention is realized in such a way that an aerospace fastening part turning mechanism is constructed, the device comprises a base plate, fixing holes, a clamping seat, a cylindrical groove, a circular through groove and a mounting assembly, wherein two fixing holes are formed in four ends of the base plate, the clamping seat is integrally formed in the middle of the front side of the base plate, the cylindrical groove is longitudinally formed in the middle of the inner side of the clamping seat, the circular through groove is formed in the right side wall of the clamping seat, the mounting assembly is inserted into the inner side of the cylindrical groove and is fixed with the clamping seat through a bolt penetrating through the inner side of the circular through groove, the mounting assembly comprises an outer cylinder seat, a clamping groove, an adjusting structure, a connecting structure, a sliding groove and a clamping structure, the clamping groove is formed in the top of the right side wall of the outer cylinder seat, the adjusting structure is arranged on the top side inside of the outer cylinder seat, the bottom of the adjusting, the spout is seted up in urceolus seat right side wall bottom, the chucking structure runs through the spout inboard and is connected with connection structure.
Preferably, the circular through grooves are three, and the distances between the three circular through grooves are equal in pairs.
Preferably, the number of the clamping grooves is two, the shape of each clamping groove is equal to that of each circular through groove, and the distance between every two clamping grooves is equal to that between every two circular through grooves.
Preferably, the adjusting structure comprises an insert block, an internal thread sleeve, an adjusting bolt and a threaded rod, the insert block is embedded in the top side of the inner part of the outer cylinder seat, the internal thread sleeve is rotatably connected to the middle part of the inner side of the insert block, the top end of the internal thread sleeve is fixed with the adjusting bolt, the adjusting bolt is connected to the middle part of the top of the outer cylinder seat, and the threaded rod is inserted into the middle part of the internal thread sleeve and is in threaded connection with the internal thread sleeve.
Preferably, the middle part of the outer surface of the adjusting bolt is transversely provided with a circular ring piece, and the circular ring piece is inserted into the middle part of the top of the outer cylinder seat and is rotationally connected with the outer cylinder seat.
Preferably, the limiting rods are vertically fixed on the left side and the right side of the bottom of the embedded block, and the two limiting rods are bilaterally symmetrical in the middle of the outer cylinder seat.
Preferably, the connection structure comprises a column block, a reinforcing block and a socket, the top middle side of the column block is rotatably connected with the threaded rod, the right side of the column block is connected with the clamping structure, the bottom middle side of the column block is integrally formed with the reinforcing block, and the socket penetrates through the middle of the reinforcing block and is inserted into the bottom side of the middle of the column block.
Preferably, the top of the column block is provided with two limiting grooves, the inner sides of the limiting grooves are in up-and-down sliding fit with the limiting rods, a sliding sheet is integrally formed on the left side of the column block and is inserted into the inner wall of the outer cylinder base to be in up-and-down sliding fit with the inner wall.
Preferably, the clamping structure is including adjusting a section of thick bamboo, support, commentaries on classics handle and kelly, it is fixed mutually with the column block to adjust a section of thick bamboo left end face, it has the support to adjust section of thick bamboo top middle side integrated into one piece, change to rotate to connect in the support top, adjust the inside left side of a section of thick bamboo and kelly lateral sliding fit, the kelly runs through reinforcement piece and socket right side wall and rather than lateral sliding fit.
Preferably, the adjusting cylinder comprises a cylinder body, a groove cavity, a spring, a post rod, a rack, a gear and a rotating shaft rod, the groove cavity is formed in the middle of the inner side of the cylinder body, the spring is fixed on the right side of the inner wall of the groove cavity, the post rod is fixed on the left side inside the spring, the rack is embedded in the rear portion of the post rod, the rear side of the rack is meshed with the gear, a rotating shaft rod penetrates through the middle of the gear, the bottom of the rotating shaft rod is rotatably connected with the cylinder body, and the top of the rotating shaft rod penetrates through the inner side of the support.
Preferably, the clamping rod is made of tungsten steel.
Preferably, the rotating handle is made of stainless steel.
The invention has the following advantages: the invention provides an aerospace fastening part turning mechanism through improvement, and compared with the same type of equipment, the aerospace fastening part turning mechanism has the following improvements:
the method has the advantages that: according to the turning mechanism for the aerospace fastening part, the mounting assembly is optimally arranged on the inner side of the clamping seat, and the height position of the column block is adjusted through the matching of the threaded rod and the internal thread sleeve, so that the fine adjustment of the height position of the tool bit is realized; rotate and to make the rack pass through the post pole and drive the kelly removal in the groove cavity, then insert the tool bit in the socket, make the kelly insert the predetermined locating hole on the cutter under the spring action of spring, and then to tool bit quick fixation and location, the machining efficiency of product has been accelerated, it fixes the tool bit to utilize the bolt usually when having solved prior art's turning cutter installation, need change the tool bit that corresponds when processing different shapes, because the tool bit adopts the bolt fastening, be difficult for changing and the location when changing, influence the problem of product machining efficiency.
The method has the advantages that: the invention relates to an aerospace fastening part turning mechanism, wherein three circular through grooves are formed, the distance between every two of the three circular through grooves is equal, two clamping grooves are formed, the shape of each clamping groove is equal to that of each circular through groove, the distance between every two clamping grooves is equal to that of each circular through groove, an outer cylinder seat is favorably arranged at different height positions, a circular ring piece is transversely formed in the middle of the outer surface of an adjusting bolt and is inserted into the middle of the top of the outer cylinder seat to be rotatably connected with the outer cylinder seat, the adjusting bolt is favorably limited, limiting rods are vertically fixed on the left side and the right side of the bottom of an embedded block, the two limiting rods are symmetrically arranged on the middle of the outer cylinder seat in a left-right mode, two limiting grooves are formed in the top of a column block, the inner sides of the limiting grooves are in up-and-down sliding fit with the limiting rods, the limiting, and the slip sheet is inserted into the inner wall of the outer cylinder base and is in up-and-down sliding fit with the inner wall, so that the limit of the column block is facilitated.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the mounting assembly of the present invention;
FIG. 3 is a schematic structural view of an adjustment structure and a connection structure of the present invention;
FIG. 4 is a schematic structural view of the clamping mechanism of the present invention;
fig. 5 is a schematic view of the structure of the adjusting cylinder of the present invention.
Wherein: the device comprises a base plate-1, a fixing hole-2, a clamping seat-3, a cylindrical groove-4, a circular through groove-5, a mounting component-6, an outer cylinder seat-61, a clamping groove-62, an adjusting structure-63, a connecting structure-64, a sliding groove-65, a clamping structure-66, an embedded block-631, an internal thread sleeve-632, an adjusting bolt-633, a column block-641, a reinforcing block-642, a socket-643, a threaded rod-634, an adjusting cylinder-661, a support-662, a rotating handle-663, a clamping rod-664, a cylinder body-6611, a groove cavity-6612, a spring-6613, a column rod-6614, a rack-6615, a gear-6616, a rotating shaft rod-6617, a limiting rod-6331, a limiting groove-6441 and a sliding sheet-6442.
Detailed Description
The present invention will be described in detail with reference to fig. 1 to 5, and the technical solutions in the embodiments of the present invention will be clearly and completely described, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all 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 invention.
The first embodiment is as follows:
referring to fig. 1, the turning mechanism for aerospace fastening parts comprises a base plate 1, fixing holes 2, clamping seats 3, cylindrical grooves 4, circular through grooves 5 and mounting assemblies 6, wherein the base plate 1 is provided with the two fixing holes 2 at four ends, the clamping seats 3 are integrally formed in the middle of the front side of the base plate 1, the cylindrical grooves 4 are longitudinally formed in the middle of the inner sides of the clamping seats 3, the circular through grooves 5 are formed in the right side walls of the clamping seats 3, the mounting assemblies 6 are inserted into the inner sides of the cylindrical grooves 4, the mounting assemblies 6 are fixed with the clamping seats 3 through bolts penetrating through the inner sides of the circular through grooves 5, and the tool bits are quickly dismounted, replaced and positioned through the mounting assemblies 6.
Referring to fig. 2, the mounting assembly 6 of the turning mechanism for aerospace fastening parts of the present invention includes an outer cylinder base 61, a locking groove 62, an adjusting structure 63, a connecting structure 64, a sliding groove 65 and a clamping structure 66, the locking groove 62 is formed at the top of the right sidewall of the outer cylinder base 61, the adjusting structure 63 is disposed at the top side of the inner portion of the outer cylinder base 61, the bottom of the adjusting structure 63 is connected to the connecting structure 64, the connecting structure 64 is in up-and-down sliding fit with the inner wall of the outer cylinder base 61, the sliding groove 65 is formed at the bottom of the right sidewall of the outer cylinder base 61, the clamping structure 66 penetrates through the inner side of the sliding groove 65 and is connected to the connecting structure 64, and the tool bit is.
Referring to fig. 3, in the turning mechanism for aerospace fastening parts according to the present invention, the adjusting structure 63 includes an insert 631, an internal threaded sleeve 632, an adjusting bolt 633 and a threaded rod 634, the insert 631 is embedded in the top side of the outer cylinder base 61, the internal threaded sleeve 632 is rotatably connected to the middle of the inner side of the insert 631, the top end of the internal threaded sleeve 632 is fixed to the adjusting bolt 633, the adjusting bolt 633 is connected to the middle of the top of the outer cylinder base 61, the threaded rod 634 is inserted into the middle of the internal threaded sleeve 632 and is threadedly connected to the internal threaded sleeve, the connecting structure 64 includes a column 641, a reinforcing block 642 and a socket 643, the middle of the top of the column 641 is rotatably connected to the threaded rod, and the right side of the post block 641 is connected with the fastening structure 66, a reinforcing block 642 is integrally formed at the middle side of the bottom of the post block 641, a socket 643 penetrates through the middle of the reinforcing block 642 and is inserted into the bottom side of the middle of the post block 641, fine adjustment of the bit height position is achieved by the cooperation of the threaded rod 634 and the internally threaded sleeve 632.
Referring to fig. 4, the clamping structure 66 of the turning mechanism for aerospace fastening parts of the present invention includes an adjusting cylinder 661, a support 662, a rotating handle 663 and a clamping rod 664, wherein the left end surface of the adjusting cylinder 661 is fixed to the column block 641, the support 662 is integrally formed on the middle side of the top of the adjusting cylinder 661, the rotating handle 663 is rotatably connected to the top of the support 662, the left side of the inside of the adjusting cylinder 661 is in transverse sliding fit with the clamping rod 664, the clamping rod 664 penetrates through the reinforcing block 642 and the right side wall of the socket 643 and is in transverse sliding fit therewith, and the clamping rod 644 is inserted into a preset positioning hole on the tool to perform quick fixing and positioning.
Referring to fig. 5, in the turning mechanism for aerospace fastening parts of the present invention, the adjusting cylinder 661 includes a cylinder 6611, a slot 6612, a spring 6613, a post 6614, a rack 6615, a gear 6616 and a rotating shaft 6617, the slot 6612 is opened in the middle of the inner side of the cylinder 6611, the spring 6613 is fixed on the right side of the inner wall of the slot 6612, the post 6614 is fixed on the left side of the inner side of the spring 6613, the rack 6615 is embedded in the rear of the post 6614, the rear side of the rack 6615 is engaged with the gear 6616, the rotating shaft 6617 is fixed in the middle of the gear 6616, the bottom of the rotating shaft 6617 is rotatably connected with the cylinder 6611, the top of the rotating shaft 6617 is connected with the rotating handle 663 by penetrating through the inner side of the support 662, and the rod 6614 drives the locking rod 644 to.
Example two:
the invention relates to a turning mechanism for aerospace fastening parts, wherein three circular through grooves 5 are formed, the distance between every two of the three circular through grooves 5 is equal, two clamping grooves 62 are formed, the shape of each clamping groove 62 is equal to that of each circular through groove 5, the distance between every two clamping grooves 62 is equal to that of each circular through groove 5, an outer cylinder seat 61 is favorably arranged at different height positions, a circular ring piece is transversely formed in the middle of the outer surface of an adjusting bolt 633 and is inserted into the middle of the top of the outer cylinder seat 61 to be rotatably connected with the outer cylinder seat, limiting on the adjusting bolt 633 is favorably realized, limiting rods 6331 are vertically fixed on the left side and the right side of the bottom of an embedded block 631, the two limiting rods 6331 are bilaterally symmetrical in the middle of the outer cylinder seat 61, two limiting grooves 6441 are formed in the top of a column block 641, the inner sides of the limiting grooves 6441 are in up-down sliding fit with the limiting rods 6331, and the, a sliding sheet 6442 is integrally formed on the left side of the column block 641, and the sliding sheet 6442 is inserted into the inner wall of the outer cylinder seat 61 and is in up-and-down sliding fit with the inner wall, so that the column block 641 is limited.
The invention provides a turning mechanism for an aerospace fastening part through improvement, which has the following working principle;
firstly, the design is fixedly installed on a turned lathe through a fixing hole 2 on a base plate 1, and then the design is used;
secondly, the user rotates the rotating handle 663, the rotating handle 663 enables the gear 6616 to drive the rack 6615 to move through the rotating shaft rod 6617, so that the column rod 6614 enables the blocking rod 664 to retract into the inner side of the cylinder body 661 by pressing the spring 6613, and then the user inserts the tool to be used into the socket 643;
thirdly, the user releases the rotating handle 663, under the counterforce of the spring 6613, the post rod 6614 drives the blocking rod 664 to be inserted into a preset positioning hole on the cutter, so as to quickly fix and position the cutter head, and meanwhile, the rack 6615 enables the rotating handle to reset through the gear 6616 and the rotating shaft rod 6617;
fourthly, when the height position of the tool bit needs to be finely adjusted, a user rotates the adjusting bolt 633 through a wrench, the adjusting bolt 633 drives the internal thread sleeve 632 to rotate in the embedded block 631, so that the internal thread sleeve 632 moves downwards through the matching with the threaded rod 634, the threaded rod 634 moves to drive the column block 641 to move upwards and downwards in the outer cylinder seat 61 under the action of the limiting rod 6331 and the sliding piece 6442, and the socket 643 in the column block 641 drives the position of the tool bit on the vertical height to be finely adjusted;
fifth, after the adjustment and positioning are completed, the user turns the aerospace fastening part with the tool bit installed in the socket 643.
The invention provides a turning mechanism for an aerospace fastening part through improvement, wherein a mounting component 6 is optimally arranged on the inner side of a clamping seat 3, and the height position of a column block 641 is adjusted through the matching of a threaded rod 634 and an internal thread sleeve 632, so that the fine adjustment of the height position of a tool bit is realized; the rotating handle 663 is rotated to enable the rack 6615 to drive the clamping rod 664 to move through the movement of the post rod 6614 in the groove cavity 6612, then the tool bit is inserted into the socket 643, the clamping rod 644 is inserted into a preset positioning hole on the tool under the action of the elastic force of the spring 6613, and the tool bit is further quickly fixed and positioned, so that the processing efficiency of a product is accelerated, and the problems that the tool bit is usually fixed by using a bolt when the turning tool in the prior art is installed, the corresponding tool bit needs to be replaced when different shapes are processed, and the tool bit is difficult to replace and position when replaced due to the fact that the tool bit is fixed by using the bolt, and the processing efficiency of the product; the circular through grooves 5 are three, the distance between every two of the three circular through grooves 5 is equal, the number of the clamping grooves 62 is two, the shape of the clamping grooves 62 is equal to that of the circular through grooves 5, meanwhile, the distance between the two clamping grooves 62 is equal to that between every two of the circular through grooves 5, the outer cylinder base 61 can be installed at different height positions, the middle of the outer surface of the adjusting bolt 633 is transversely provided with a circular ring piece, the circular ring piece is inserted into the middle of the top of the outer cylinder base 61 and is connected with the middle in a rotating mode, the adjusting bolt 633 can be limited conveniently, the limiting rods 6331 are vertically fixed on the left side and the right side of the bottom of the embedded block 631, the two limiting rods 6331 are bilaterally symmetrical in the middle of the outer cylinder base 61, the top of the column block 641 is provided with two limiting grooves 6441, the inner sides of the limiting grooves 6441 are in up-down sliding fit with the limiting rods 6331, and the sliding sheet 6442 is inserted into the inner wall of the outer cylinder seat 61 and is in up-and-down sliding fit with the inner wall, which is beneficial to limiting the column block 641.
The basic principles and main features of the present invention and the advantages of the present invention have been shown and described, and the standard parts used in the present invention are all available on the market, the special-shaped parts can be customized according to the description and the accompanying drawings, the specific connection mode of each part adopts the conventional means of bolt and rivet, welding and the like mature in the prior art, the machinery, parts and equipment adopt the conventional type in the prior art, and the circuit connection adopts the conventional connection mode in the prior art, and the details are not described herein.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. The turning mechanism for the aerospace fastening part comprises a base plate (1), fixing holes (2), clamping seats (3), a cylindrical groove (4) and a circular through groove (5), wherein two fixing holes (2) are formed in four ends of the base plate (1), the clamping seats (3) are integrally formed in the middle of the front side of the base plate (1), the cylindrical groove (4) is longitudinally formed in the middle of the inner side of each clamping seat (3), and the circular through groove (5) is formed in the right side wall of each clamping seat (3);
the method is characterized in that: also comprises a mounting component (6), the mounting component (6) is inserted into the inner side of the cylindrical groove (4), the mounting component (6) is fixed with the clamping seat (3) through a bolt penetrating through the inner side of the circular through groove (5), the mounting component (6) comprises an outer cylinder seat (61), a clamping groove (62), an adjusting structure (63), a connecting structure (64), a sliding groove (65) and a clamping structure (66), the top of the right side wall of the outer cylinder seat (61) is provided with a clamping groove (62), the adjusting structure (63) is arranged on the top side inside the outer cylinder seat (61), the bottom of the adjusting structure (63) is connected with a connecting structure (64), and the connecting structure (64) is in up-and-down sliding fit with the inner wall of the outer cylinder seat (61), the sliding groove (65) is arranged at the bottom of the right side wall of the outer cylinder seat (61), and the clamping structure (66) penetrates through the inner side of the sliding groove (65) and is connected with the connecting structure (64).
2. The aerospace fastening part turning mechanism of claim 1, wherein: the number of the circular through grooves (5) is three, and the distances between the three circular through grooves (5) are equal in pairs.
3. The aerospace fastening part turning mechanism of claim 1, wherein: the number of the clamping grooves (62) is two, the shape of each clamping groove (62) is equal to that of each circular through groove (5), and meanwhile, the distance between every two clamping grooves (62) is equal to that between every two circular through grooves (5).
4. The aerospace fastening part turning mechanism of claim 1, wherein: adjust structure (63) including abaculus (631), internal thread cover (632), adjusting bolt (633) and threaded rod (634), abaculus (631) inlays in the inside top side of outer cylinder seat (61), abaculus (631) inboard middle part is rotated and is connected with internal thread cover (632), internal thread cover (632) top is fixed mutually with adjusting bolt (633), adjusting bolt (633) are connected in outer cylinder seat (61) top medial side, threaded rod (634) insert internal thread cover (632) medial side and rather than threaded connection.
5. The aerospace fastening part turning mechanism of claim 4, wherein: the middle part of the outer surface of the adjusting bolt (633) is transversely provided with a circular ring piece, and the circular ring piece is inserted into the middle side of the top of the outer cylinder seat (61) and is rotationally connected with the outer cylinder seat.
6. The aerospace fastening part turning mechanism of claim 4, wherein: the left side and the right side of the bottom of the embedded block (631) are vertically fixed with limiting rods (6331), and the two limiting rods (6331) are in bilateral symmetry in the middle of the outer cylinder seat (61).
7. The aerospace fastening part turning mechanism of claim 1, wherein: the connecting structure (64) comprises a column block (641), a reinforcing block (642) and a socket (643), wherein the middle side of the top of the column block (641) is rotatably connected with the threaded rod (634), the right side of the column block (641) is connected with the clamping structure (66), the reinforcing block (642) is integrally formed on the middle side of the bottom of the column block (641), and the socket (643) penetrates through the middle of the reinforcing block (642) and is inserted into the bottom side of the middle of the column block (641).
8. The aerospace fastening part turning mechanism of claim 7, wherein: the top of the column block (641) is provided with two limiting grooves (6441), the inner sides of the limiting grooves (6441) are in up-and-down sliding fit with the limiting rod (6331), the left side of the column block (641) is integrally formed with a sliding sheet (6442), and the sliding sheet (6442) is inserted into the inner wall of the outer cylinder seat (61) and is in up-and-down sliding fit with the inner wall.
9. The aerospace fastening part turning mechanism of claim 1, wherein: the clamping structure (66) comprises an adjusting cylinder (661), a support (662), a rotating handle (663) and a clamping rod (664), the left end face of the adjusting cylinder (661) is fixed with the column block (641), the support (662) is integrally formed in the middle of the top of the adjusting cylinder (661), the rotating handle (663) is rotatably connected to the top of the support (662), the left side of the inside of the adjusting cylinder (661) is in transverse sliding fit with the clamping rod (664), and the clamping rod (664) penetrates through the right side wall of the reinforcing block (642) and the right side wall of the socket (643) and is in transverse sliding fit with the reinforcing block and the right side wall of the socket (643).
10. The aerospace fastening part turning mechanism of claim 9, wherein: the adjusting cylinder (661) comprises a cylinder body (6611), a slot cavity (6612), a spring (6613), a post rod (6614), a rack (6615), a gear (6616) and a rotating shaft rod (6617), the slot cavity (6612) is formed in the middle of the inner side of the cylinder body (6611), the spring (6613) is fixed on the right side of the inner wall of the slot cavity (6612), the post rod (6614) is fixed on the left side of the inner portion of the spring (6613), the rack (6615) is embedded in the rear portion of the post rod (6614), the rear side of the rack (6615) is meshed with the gear (6616), the rotating shaft rod (6617) is fixed in the middle of the gear (6616) in a penetrating mode, the bottom of the rotating shaft rod (6617) is rotatably connected with the cylinder body (6611), and the top of the rotating shaft rod (6617) penetrates through the inner side of.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010765518.XA CN111872415B (en) | 2020-08-03 | 2020-08-03 | Aerospace fastening part lathe work mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010765518.XA CN111872415B (en) | 2020-08-03 | 2020-08-03 | Aerospace fastening part lathe work mechanism |
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| CN111872415A true CN111872415A (en) | 2020-11-03 |
| CN111872415B CN111872415B (en) | 2021-09-14 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112677349A (en) * | 2020-12-18 | 2021-04-20 | 江苏汇成光电有限公司 | Cutter changing jig of cutting machine |
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| CN109719316A (en) * | 2019-01-28 | 2019-05-07 | 苏州凯雷特精密机械有限公司 | A kind of aerospace fastener turnery processing head |
| CN210731108U (en) * | 2019-09-24 | 2020-06-12 | 苏州天音腾达机电工程有限公司 | Machining drill bit installation mechanism |
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| CN112677349A (en) * | 2020-12-18 | 2021-04-20 | 江苏汇成光电有限公司 | Cutter changing jig of cutting machine |
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