CN107900421A - For processing the ladder drilling reamer of aircraft skin rivet hole - Google Patents
For processing the ladder drilling reamer of aircraft skin rivet hole Download PDFInfo
- Publication number
- CN107900421A CN107900421A CN201711442688.9A CN201711442688A CN107900421A CN 107900421 A CN107900421 A CN 107900421A CN 201711442688 A CN201711442688 A CN 201711442688A CN 107900421 A CN107900421 A CN 107900421A
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- cylinder
- land
- chip
- ladder
- chip space
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- 238000005553 drilling Methods 0.000 title claims abstract description 27
- 230000007704 transition Effects 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims description 14
- 238000013016 damping Methods 0.000 claims description 12
- 238000000227 grinding Methods 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000007796 conventional method Methods 0.000 abstract description 3
- 238000005520 cutting process Methods 0.000 description 9
- 238000010586 diagram Methods 0.000 description 4
- 241000220317 Rosa Species 0.000 description 3
- 230000007812 deficiency Effects 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 238000007514 turning Methods 0.000 description 2
- 241001074085 Scophthalmus aquosus Species 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B51/00—Tools for drilling machines
- B23B51/009—Stepped drills
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B51/00—Tools for drilling machines
- B23B51/08—Drills combined with tool parts or tools for performing additional working
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2251/00—Details of tools for drilling machines
- B23B2251/40—Flutes, i.e. chip conveying grooves
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2251/00—Details of tools for drilling machines
- B23B2251/48—Chip breakers
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Drilling Tools (AREA)
Abstract
The present invention provides the ladder drilling reamer for processing aircraft skin rivet hole, it can solve the problems, such as that processing efficiency is low, production cost is high, processing quality can not be met the requirements existing for existing conventional method processing.Cutter hub includes the first cylinder and the second cylinder to link into an integrated entity with one heart from front to back, and the diameter D1 of the first cylinder is less than the diameter D2 of the second cylinder；Two are offered on the outer circumferential surface of first cylinder and forms two sword valves along the first chip space of central symmetry and in the outer circumferential surface of the first cylinder, two are provided with the outer circumferential surface of second cylinder along the second chip space of central symmetry, two first chip spaces in the first cylindrical periphery face are all extended on the second cylindrical periphery face, the first chip space on second cylinder is depended on the second chip space to be connected, two the first chip spaces on second cylinder, two the second chip spaces split the outer circumferential surface of the second cylinder to form two Zhou Ren, each sword valve on first cylinder is connected with all swords on corresponding second cylinder by the transition of ladder angle, core thickness d1=0.25D1~0.35D1 of first chip space, core thickness d2=0.25D2~0.35D2 of second chip space, and d1 is less than d2.
Description
Technical field
The present invention relates to field of machining, particularly for the ladder drilling reamer of processing aircraft skin rivet hole.
Background technology
Riveted structure has good bonding strength and reliability, is most important connection mode in aircraft assembling, rivets
Account for more than 70% of all connection modes in aircraft.Riveting is mainly used for the covering position of aircraft, if aircraft skin is with covering
Connection between skin, between covering and frame, between covering and rib and between covering and other components, while it is also applied to crossbeam
Assembling, rib, frame, reinforcing rib and analyse bar accessory of the assembling with being connected, on various parts installation and plurality of branch
Engagement of support member and other components etc..
Riveted structure is one of component easily to fail on aircaft configuration, it is not only the key position of static strength check,
And the key position that fatigue life checks, therefore the processing quality of rivet hole is particularly important.
Rivet hole machined on the arc surface of traditional rivet hole machined particularly aircraft skin is all first on arc surface
One facet of milling, then bores rivet hole with drill bit, then with reamer ream rivet hole, then processes fillet surface with rose reamer；
At present using this conventional method in the rivet hole machined of aircraft skin, since it is needed using drill bit, reamer, rose reamer point
Do not process successively, it is more not only take up tool magazine warehouse compartment, and frequently tool changing causes that productive temp is low, processing efficiency is low, is produced into
This height；Rivet hole machined especially on arc surface, usually occurs what chamfering centerline hole cannot be overlapped with datum hole center line
Problem, it is poor that this results in stepped hole concentricity, position degree；In addition normal drill bit has been adopted, reamer is drilled and when ream exports
Easily produce burr and the roughness of hole surface is poor, and the cutting of the big surplus of rose reamer can often produce knife phenomenon of shaking, sternly
Crushing knife even breaking is easily produced during weight, seriously affects production safety.
Sometimes for the cost of charp tool is saved, one can be designed stepped chamfers are bored, it is disposable to process rivet hole and fillet surface；But
More than more than 2 times footpaths of reducing ratio, using the design of conventional step drill, the across back that the first ladder often occurs during fabrication is special
Not narrow, cutter poor rigidity, cannot then meet the straightness requirement of rivet hole；And in order to ensure the across back of the first ladder, second
The radial rake of ladder is especially big, and can so shake knife phenomenon again when processing rivet Hole chamfering, thus can not also ensure riveting
The processing quality of nail.
The content of the invention
In view of the above-mentioned problems, the present invention provides the ladder drilling reamer for processing aircraft skin rivet hole, it can be solved
The problem of processing efficiency is low, production cost is high, processing quality can not be met the requirements existing for existing conventional method processing.
Its technical solution is that, for processing the ladder drilling reamer of aircraft skin rivet hole, it includes the handle of a knife of a diameter of D3
The cutter hub of the handle of a knife front end is integratedly arranged on one heart, and the cutter hub includes the first circle to link into an integrated entity with one heart from front to back
Column and the second cylinder, the diameter D1 of first cylinder are less than the diameter D2 of second cylinder, it is characterised in that：Described first
Cylinder is bit head, and second cylinder is reamer portion, and two are offered along central symmetry on the outer circumferential surface of first cylinder
First chip space simultaneously forms two sword valves in the outer circumferential surface of first cylinder, and two are provided with the outer circumferential surface of second cylinder
Along the second chip space of central symmetry, two first chip spaces in the first cylindrical periphery face are all extended to outside second cylinder
On side face, the first chip space on second cylinder is depended on second chip space to be connected, and two on second cylinder
The each chip space of bar, two the second chip spaces split the outer circumferential surface of second cylinder to form two Zhou Ren, first circle
Each sword valve on column is connected with all swords on corresponding second cylinder by the transition of ladder angle, first chip removal
Core thickness d1=0.25D1~0.35D1 of groove, core thickness d2=0.25D2~0.35D2 of second chip space, and d1 is less than d2.
Further, the front end nose part of first cylinder is equipped with vertex angle theta, the vertex angle theta angular range 150 °~
170°。
Further, the front end nose part of first cylinder is equipped with point of a knife chamfered edge with sword valve corner.
Further, two sword valve top surface both ends on first cylinder are equipped with the first land and the 3rd land, top
Face center section is equipped with the second land, wherein first land is cylindrical edge band, second land and the 3rd land are
On first cylindrical surface, grinding relief angle α is formed, and the circle diameter D4 where second land, the 3rd land is less than described
The circle diameter D1 of first land.
Further, the ladder angle is more rear knife face structures, the ladder angle and the adjoiner of second chip space
Equipped with the vibration damping land being arc-shaped, the relief angle of the vibration damping land is 2 °~5 °, the width d of the vibration damping land for 0.05~
0.1mm。
Further, chip-breaker is respectively equipped with two ladder angles, one of them described ladder angle is equipped with one
Chip-breaker, another described ladder angle are equipped with two chip-breakers.
The beneficial effects of the present invention are：
(1) its cutter hub is made of the first cylinder to link into an integrated entity with one heart from front to back and the second cylinder and the first cylinder
Diameter D1 is less than the diameter D2 of the second cylinder so as to be split into step-like compound tool, and the first cylinder is as bit head, second
For cylinder as reamer portion, time processing can complete drilling, ream and chamfer machining, effectively improve processing beat, improve processing
Efficiency, it is few to take tool magazine warehouse compartment；
(2) the first chip space opened up on its first cylinder is extended on the second cylinder and with being opened on the second cylinder
Second chip space depends on connection, and the core thickness d1 of the first chip space is less than the core thickness d2 of the second chip space, i.e., which employs common groove not
Deng core thickness structure, therefore it can effectively strengthen cutter rigidity while the cutting ability of cutter and chip removal performance is not influenced；While the
Core thickness d1=0.25D1~0.35D1 of one chip space, core thickness d2=0.25D2~0.35D2 of the second chip space, i.e., two rows
Bits groove can further enhance the rigidity of ladder drilling reamer with corresponding different body diameter design core thickness respectively；
The front end of (3) first cylinders employs angular range in 150 °~170 ° of big apex angle theta structure, it can be effective
Preventing on arc surface drilling to bore inclined, wearing larger or crushing knife phenomenon at outer rim turning point during so as to by avoiding drilling so that
Suffered radial cutting force balances as far as possible on drill bit, reduces the deflection deformation of drill bit generation；
(4) it at the switching of the first cylinder front end nose part and sword valve equipped with point of a knife chamfered edge by improving outside cutting edge
Intensity at edge turning point, reduces thermic load, so that aperture burr occurs and influences the dress of manufactured head when effectively preventing from boring rivet hole
Match somebody with somebody；
(5) two sword valves of its first cylinder are respectively equipped with three lands, and the first land therein is cylindrical edge band, and
Second land and the 3rd land are to be formed in first cylindrical surface grinding relief angle α, and where the second land, the 3rd land
Circle diameter D4 is less than the circle diameter D1 of first land, it is thus possible to so that the first cylinder as bit head is whole
Formed and supported in hole wall in the range of sword valve, reduce swinging and reducing the friction with contact surface in drilling, therefore can increase substantially
Straightness and roughness in hole；
(6) the ladder angle that its first cylinder is connected with the second cylinder can be strengthened firm at chamfering using more rear knife face structures
Property, prevent in the big surplus cutting of rivet orifice chamfer, since rigid deficiency causes vibration even crushing knife；And ladder angle and second
The vibration damping land being arc-shaped that the adjoiner of chip space is set, effective damping effect can be played in working angles, is carried
Roughness in high rivet hole；
(7) it is respectively equipped with chip-breaker on two ladder angles, and one of ladder angle is equipped with a chip-breaker, another
One ladder angle is equipped with two chip-breakers, by using the asymmetrical design of this chip-breaker, effectively reduces chamfering and cuts
The knife that shakes of generation when cutting, further increases quality in the hole of processed rivet hole.
Brief description of the drawings
Fig. 1 is the structure diagram that the present invention is used to process the ladder drilling reamer of aircraft skin rivet hole；
Fig. 2 is the dimensional structure diagram that the present invention is used to process the ladder drilling reamer of aircraft skin rivet hole；
Fig. 3 be Fig. 1 A to enlarged structure schematic diagram；
Fig. 4 is close-up schematic view at the B in Fig. 3；
Fig. 5 is C-C in Fig. 4 to diagrammatic cross-section；
Fig. 6 is the partial enlargement structural representation of the first cylinder in the present invention；
Fig. 7 is the schematic diagram of the front end point of a knife of the first cylinder in the present invention；
Fig. 8 is close-up schematic view at the E in Fig. 7.
Reference numeral：10- cutter hubs, the first cylinders of 11-, 111- sword valves, 112- point of a knife chamfered edges, the first lands of 113-, 114-
Second land, the 3rd lands of 115-, the second cylinders of 12-, 121- weeks sword, 13- ladders angle, 14- vibration damping lands, 15- chip-breakers,
20- handle of a knifes, the first chip spaces of 31-, the second chip spaces of 32-.
Embodiment
See Fig. 1, the present invention is used for the ladder drilling reamer for processing aircraft skin rivet hole, it includes the handle of a knife 20 of a diameter of D3
The cutter hub 10 of handle of a knife front end is integratedly arranged on one heart, and cutter hub 10 includes the first cylinder 11 to link into an integrated entity with one heart from front to back
With the second cylinder 12, the diameter D1 of the first cylinder 11 is less than the diameter D2 of the second cylinder 12；First cylinder 11 is bit head, second
Cylinder 12 is reamer portion, and two are offered on the outer circumferential surface of the first cylinder 11 along the first chip space of central symmetry 31 and in the first circle
The outer circumferential surface of column 11 forms two sword valves 111, and two are provided with along the second chip space of central symmetry on the outer circumferential surface of the second cylinder 12
32, two the first chip spaces 31 of 11 outer circumferential surface of the first cylinder are all extended on 12 outer circumferential surface of the second cylinder, on the second cylinder 12
The first chip space 31 depend on and be connected with the second chip space 32, two the first chip spaces 31, two second on the second cylinder 12
Chip space 32 splits the outer circumferential surface of the second cylinder 12 to form two all swords 121, each sword valve 111 on the first cylinder 11 with
All swords 121 on corresponding 12 second cylinder are connected by 13 transition of ladder angle, the core thickness d1=of the first chip space 31
0.25D1~0.35D1, core thickness d2=0.25D2~0.35D2 of the second chip space 32, and d1 is less than d2.Lead to according to traditional rank
Terraced drilling reamer design method, if on the basis of the second cylinder D2, designs same core thickness, the land of the first cylinder D1 can be caused special
It is not narrow, cutter poor rigidity；And if on the basis of the first cylinder D1, design that same core is thick, the land of the second cylinder D2 can be caused
It is very wide, chip space very little；Therefore the present invention can increase the rigidity of ladder drilling reamer according to the diameter design core thickness of different cylinders.
See Fig. 6, the front end nose part of the first cylinder 11 is equipped with vertex angle theta, and vertex angle theta angular range is at 150 °~170 °；First
The front end nose part of cylinder 11 is equipped with point of a knife chamfered edge 112 with 111 corner of sword valve.
The design of generally conventional land, since the deficiency of support can cause the axis in whole hole constantly to deviate, so as to cause
The distortion of hole shape；And then the design of some lands, 6 lands can be set on two sword valves, i.e., each sword valve is equipped with three
Land, but since this three lands are formed on cylindrical surface, so in drilling process, larger supporting surface can increase brill
The friction of head and contact surface, reduces the cutting ability of cutter.And in the present invention, see Fig. 7 and Fig. 8, two on the first cylinder 11
111 top surface both ends of sword valve are equipped with the first land 113 and the 3rd land 115, top surface center section are equipped with the second land 114, its
In the first land 113 be cylindrical edge band that circle diameter is D1, the second land 114 and the 3rd land 115 are on the first cylindrical surface
11 grinding relief angle α are formed, and the circle diameter D4 where the second land 114, the 3rd land 115 is less than the circle of the first land 113
All diameter D1；The design of this land of the present invention causes drill bit is formed in the range of whole sword valve in hole wall to support, in drilling
When reduce and swing, and reduce the friction of drill bit and contact surface, straightness and roughness in hole can be increased substantially.
See Fig. 2 and Fig. 3, Fig. 4 and Fig. 5, ladder angle 13 is more rear knife face structures, it can strengthen the rigidity at chamfering, prevent
In the big surplus cutting of rivet hole orifice chamfer, since rigid deficiency causes collapsing for vibration even cutter scarce；Ladder angle 13 and
The adjoiner of two chip spaces 32 is equipped with the vibration damping land 14 being arc-shaped, and the relief angle of vibration damping land 14 is 2 °~5 °, vibration damping land
14 width d is 0.05~0.1mm, plays the effectiveness in vibration suppression in working angles, improves roughness in rivet hole.
In existing rivet hole process, when the reducing ratio of the drilling reamer for processing is more than 3, i.e., it ought use
When the ratio of the diameter D1 of first cylinder 11 of drilling reamer and the diameter D2 of the second cylinder 12 are more than 3, it is especially bright that it processes vibration
It is aobvious, processed rivet internal surface of hole can be caused to have decorative pattern, can not meet matching requirements；Ladder drilling reamer of the present invention is employed two
Chip-breaker 15 is respectively equipped with a 13 ladder angle, sees Fig. 3, and one of ladder angle 13 is equipped with a chip-breaker 15, another
A ladder angle 13 is equipped with two chip-breakers 15, and the mode of this asymmetric design, it is produced when can reduce chamfer cutting
The knife that shakes, further improve quality in the hole of processed rivet hole.
The specific implementation to the present invention is described in detail above, but content is only the preferable embodiment party of the invention
Case, it is impossible to be construed as limiting the practical range of the invention.All impartial changes made according to the invention application range
Change and improvement etc., should all still belong within the patent covering scope of the present invention.
Claims (6)
1. for processing the ladder drilling reamer of aircraft skin rivet hole, it include the handle of a knife of a diameter of D3 (20) and it is concentric integratedly
Cutter hub (10) arranged on the handle of a knife (20) front end, the cutter hub (10) include the first circle to link into an integrated entity with one heart from front to back
Column (11) and the second cylinder (12), the diameter D1 of first cylinder (11) are less than the diameter D2 of second cylinder (12), its
It is characterized in that：First cylinder (11) is bit head, and second cylinder (12) is reamer portion, first cylinder (11)
Two are offered on outer circumferential surface and forms two along the first chip space of central symmetry (31) and in the outer circumferential surface of first cylinder (11)
A sword valve (111), two are provided with the outer circumferential surface of second cylinder (12) along the second chip space of central symmetry (32), and described
Two first chip spaces (31) of one cylinder (11) outer circumferential surface are all extended on the second cylinder (12) outer circumferential surface, and described second
The first chip space (31) on cylinder (12) is depended on second chip space (32) to be connected, and two on second cylinder (12)
The outer circumferential surface of second cylinder (12) is split to form two Zhou Ren by the first chip space of bar (31), two the second chip spaces (32)
(121), each sword valve (111) on first cylinder (11) and the Zhou Ren on corresponding second cylinder (12)
(121) connected by ladder angle (13) transition, core thickness d1=0.25D1~0.35D1 of first chip space (31) is described
Core thickness d2=0.25D2~0.35D2 of second chip space (32), and d1 is less than d2.
2. the ladder drilling reamer according to claim 1 for being used to process aircraft skin rivet hole, it is characterised in that：Described
The front end nose part of one cylinder (11) is equipped with vertex angle theta, and the vertex angle theta angular range is at 150 °~170 °.
3. the ladder drilling reamer according to claim 1 or 2 for being used to process aircraft skin rivet hole, it is characterised in that：Institute
The front end nose part and sword valve (111) corner for stating the first cylinder (11) are equipped with point of a knife chamfered edge.
4. the ladder drilling reamer according to claim 3 for being used to process aircraft skin rivet hole, it is characterised in that：Described
The top surface both ends of two sword valves (111) on one cylinder (11) are equipped with the first land (113) and the 3rd land (115), top surface
Center section is equipped with the second land (114), wherein the cylindrical edge band that it is D1 that first land (113), which is circle diameter, described
Second land (114) and the 3rd land (115) are to be formed in the periphery grinding relief angle α of first cylinder (11), and institute
Circle diameter D4 where stating the second land (114), the 3rd land (115) is less than the circle diameter of first land (113)
D1。
5. the ladder drilling reamer according to claim 4 for being used to process aircraft skin rivet hole, it is characterised in that：The rank
Terraced angle (13) is knife face structures after more, and the adjoiner of the ladder angle (13) and second chip space (32) is equipped with being arc-shaped
Vibration damping land (14), the relief angle of the vibration damping land (14) is 2 °~5 °, the width d of the vibration damping land (14) for 0.05~
0.1mm。
6. the ladder drilling reamer according to claim 5 for being used to process aircraft skin rivet hole, it is characterised in that：Two institutes
To state and chip-breaker (15) is respectively equipped with ladder angle (13), one of them described ladder angle (13) is equipped with a chip-breaker (15),
Another described ladder angle (13) is equipped with two chip-breakers (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711442688.9A CN107900421B (en) | 2017-12-27 | 2017-12-27 | Stepped drilling reamer for machining aircraft skin rivet holes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711442688.9A CN107900421B (en) | 2017-12-27 | 2017-12-27 | Stepped drilling reamer for machining aircraft skin rivet holes |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107900421A true CN107900421A (en) | 2018-04-13 |
| CN107900421B CN107900421B (en) | 2024-04-02 |
Family
ID=61871550
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711442688.9A Active CN107900421B (en) | 2017-12-27 | 2017-12-27 | Stepped drilling reamer for machining aircraft skin rivet holes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107900421B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108465852A (en) * | 2018-06-14 | 2018-08-31 | 江门市中刀精密科技有限公司 | A kind of brill milling hinge composite cutter |
| CN110860722A (en) * | 2019-10-21 | 2020-03-06 | 广东鼎泰高科精工科技有限公司 | Stepped drill for processing high-temperature alloy |
| CN113458472A (en) * | 2021-07-15 | 2021-10-01 | 江门市中刀精密科技有限公司 | Multi-step multi-profile coating forming reaming milling cutter |
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| CN202162425U (en) * | 2011-07-28 | 2012-03-14 | 锑玛(苏州)精密工具有限公司 | Drilling-reaming composite tool |
| CN102794486A (en) * | 2012-08-22 | 2012-11-28 | 浙江大学 | Compound tool applicable to high-speed and accurate holing on aircraft panel |
| CN203541645U (en) * | 2013-11-14 | 2014-04-16 | 武汉泰尔斯刀具有限公司 | Step drill bit for machining guiding hole |
| CN204053031U (en) * | 2014-09-29 | 2014-12-31 | 神龙汽车有限公司 | A kind of carbide alloy drilling reamer |
| CN204194898U (en) * | 2014-09-28 | 2015-03-11 | 上海奥林汽车安全***有限公司 | Integrate the step drill of boring and chamfering function |
| CN205519810U (en) * | 2016-04-25 | 2016-08-31 | 锑玛（苏州）精密工具股份有限公司 | Special chip removal ladder downwards of steel part bores |
| CN107008952A (en) * | 2017-05-31 | 2017-08-04 | 山东大学 | A kind of lamination thin plate drilling cutter with bradawl and counter boring chip breaking structure |
| CN207695692U (en) * | 2017-12-27 | 2018-08-07 | 苏州阿诺精密切削技术有限公司 | A kind of ladder drilling reamer for processing aircraft skin rivet hole |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN202162425U (en) * | 2011-07-28 | 2012-03-14 | 锑玛(苏州)精密工具有限公司 | Drilling-reaming composite tool |
| CN102794486A (en) * | 2012-08-22 | 2012-11-28 | 浙江大学 | Compound tool applicable to high-speed and accurate holing on aircraft panel |
| CN203541645U (en) * | 2013-11-14 | 2014-04-16 | 武汉泰尔斯刀具有限公司 | Step drill bit for machining guiding hole |
| CN204194898U (en) * | 2014-09-28 | 2015-03-11 | 上海奥林汽车安全***有限公司 | Integrate the step drill of boring and chamfering function |
| CN204053031U (en) * | 2014-09-29 | 2014-12-31 | 神龙汽车有限公司 | A kind of carbide alloy drilling reamer |
| CN205519810U (en) * | 2016-04-25 | 2016-08-31 | 锑玛（苏州）精密工具股份有限公司 | Special chip removal ladder downwards of steel part bores |
| CN107008952A (en) * | 2017-05-31 | 2017-08-04 | 山东大学 | A kind of lamination thin plate drilling cutter with bradawl and counter boring chip breaking structure |
| CN207695692U (en) * | 2017-12-27 | 2018-08-07 | 苏州阿诺精密切削技术有限公司 | A kind of ladder drilling reamer for processing aircraft skin rivet hole |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108465852A (en) * | 2018-06-14 | 2018-08-31 | 江门市中刀精密科技有限公司 | A kind of brill milling hinge composite cutter |
| CN110860722A (en) * | 2019-10-21 | 2020-03-06 | 广东鼎泰高科精工科技有限公司 | Stepped drill for processing high-temperature alloy |
| CN113458472A (en) * | 2021-07-15 | 2021-10-01 | 江门市中刀精密科技有限公司 | Multi-step multi-profile coating forming reaming milling cutter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107900421B (en) | 2024-04-02 |
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