CN105252034A - Hole finishing technique for layered material of titanium alloy and aluminum alloy composite material - Google Patents
Hole finishing technique for layered material of titanium alloy and aluminum alloy composite material Download PDFInfo
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- CN105252034A CN105252034A CN201510749670.8A CN201510749670A CN105252034A CN 105252034 A CN105252034 A CN 105252034A CN 201510749670 A CN201510749670 A CN 201510749670A CN 105252034 A CN105252034 A CN 105252034A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B35/00—Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
-
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2226/00—Materials of tools or workpieces not comprising a metal
- B23B2226/27—Composites
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2228/00—Properties of materials of tools or workpieces, materials of tools or workpieces applied in a specific manner
- B23B2228/10—Coatings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Drilling Tools (AREA)
- Drilling And Boring (AREA)
Abstract
The invention discloses a hole finishing technique for a layered material of a titanium alloy and aluminum alloy composite material. After the layered material is assembled, the hole finishing technique comprises the step of utilizing an automatic feeding drill technique and a manual hole reaming technique in a coordinating manner. Furthermore, a way that one side of titanium alloy is drilled at first in drilling is guaranteed, the automatic feeding drill technique is peck drilling technique machining, and cetanol drilling lubricant is used in machining. According to the hole finishing technique, a rough hole with certain allowance is obtained at first through a specific technique. Thus, the phenomena of cutter clamping, tearing and burning can be effectively avoided, the yield can be greatly improved, and a hole penetrating through the composite layered materials and meeting the accuracy requirement can be obtained through a plurality of times of manual hole reaming technique. The hole finishing technique for the specific layered material is more reasonable, higher in efficiency, and meanwhile, the higher machining accuracy is guaranteed.
Description
Technical field
The present invention relates to a kind of process for machining, particularly relate to a kind of Drilling operation technique.
Background technology
Along with the development of aeronautical technology, the development of extraordinary new material is more and more wide, what adopt in a large number in aerospace component at present is the laminated material that titanium alloy-aluminium alloy-composite is formed, thing followed process technology requires also more and more higher, and a large amount of difficult problem adopting this new material to bring is: the process technology in transporation by plane process how solving the high accurate hole of laminated material (i.e. the laminated material that titanium alloy-aluminium alloy-composite is formed).
Wherein composite and titanium alloy are all typical difficult-to-machine materials.Heat conductivity is little, and linear expansion coefficient and elasticity recover all comparatively large, cause composite to have shrinkage cavity phenomenon; The composite of drilling simultaneously generally adopts high rotating speed and the little amount of feeding.Titanium alloy thermal conductivity coefficient is little, elasticity recovers large, chill, bonding, diffusion phenomena seriously cause Ti-alloy Drilling poor performance, and have resilience in drilling, size is unstable; So drilling titanium alloy generally adopts the slow-speed of revolution and the appropriate amount of feeding.Aluminium has a series of characteristic more excellent than other non-ferrous metals, iron and steel, plastics and timber etc., as little in density, is only 2.7g/cm
3, be about 1/3 of copper or steel; Good corrosion resistance and weatherability; Good plasticity and processing characteristics; Good thermal conductivity and electric conductivity; Coefficient of elasticity is little; Good mechanical property; Excellent casting character and welding performance; Good processability, machinability; So aluminium alloy also has reaming phenomenon.
Due to the manufacture of aircraft produce in more and more higher to technical requirement, all very high to the required precision in hole during assembling, the required precision of many holes is at 0 ~+0.01mm, thus also very high to the requirement of processing technology.Current main technique is that hole processes respectively under part status, and then assembles, and the difficulty of processing in single hole reduces, but assembly difficulty substantially increases.
If adopt auto-feed Drilling operation technique, main employings brill twists integrated knife and realizes, and cutter material is hard alloy twist drill, carries out drilling processing by the rotating speed of titanium alloy and the amount of feeding simultaneously.Due to the identical feeding of the cutter that identical method is identical of three kinds of materials, the hole of drilling processing, due to shrinkage cavity and reaming, is caused aperture inconsistent and cannot meet customer requirement.Drilling low precision, easily there is titanium alloy flange, composite ablation phenomen, simultaneously, because composite has shrinkage cavity phenomenon, titanium alloy and aluminium alloy have reaming phenomenon, and the reaming ratio of titanium alloy and aluminium alloy is different, cause the aperture requirement that cannot simultaneously meet after processing on three kinds of materials.
Summary of the invention
Technical problem to be solved by this invention is the Finish Machining Bore technique that will provide a kind of more rationally more efficient laminated material for titanium alloy Al alloy composite, ensures higher machining accuracy simultaneously.
For solving the problems of the technologies described above, technical scheme of the present invention is as follows:
A kind of Finish Machining Bore technique of the laminated material for titanium alloy Al alloy composite:
The technique of drilling after a, the assembling of employing laminated material, adopts auto-feed to bore cooperation and manually finish reams hole technique;
Described auto-feed driller skill adopts the integrated cutter that drills and reams, and after described auto-feed driller skill, the reaming allowance of reserved 1 ~ 1.5mm is to guarantee the hole precision after finish reaming hole machined;
In b, described auto-feed driller skill, pierce from titanium alloy side when guaranteeing drilling; Aperture size so just can be made to reach best;
C, described auto-feed driller skill adopt pecks brill processes;
In described auto-feed driller skill, the motion of cutter comprises radial rotary motion and axial feed motion, and the described namely described cutter of driller's skill axial feed motion in cutwork of pecking produces the fluctuating of advancing of certain frequency and amplitude; The swaging clamp phenomenon in processing can be greatly reduced like this;
In d, described auto-feed driller skill, in machining, use cetanol drilling lubricant to alleviate the ablation phenomen of composite;
E, required precision according to hole, described hole technique of manually finish reaming comprises several times and finish reams hole machined.As high-precision hole will be obtained, need to carry out fraising to laminated construction, can as required through twice or repeatedly after fraising, the extreme difference of composite and aluminium alloy and titanium alloy can control in 0.01mm; For the hole being greater than 8.0mm sandwich, can adopt boring-expanding method processing, each reaming can get 0.4mm ~ 0.8mm.
The described best diamond coated coating of the strand integrated cutter of the brill described in auto-feed driller skill, thus effectively increase cutter life.
According to processing technology of the present invention first to adopt the auto-feed driller skill of the integrated cutter that drills and reams slightly to bore the rough hole obtaining and have certain allowance, work in-process is guaranteed boring direction, is adopted and peck driller's skill and use cetanol drilling lubricant, so just can effectively avoid swaging clamp, tear, the generation of the phenomenon such as ablation, greatly improve yield rate.Then, the reaming allowance of reserved 1 ~ 1.5mm, to guarantee the hole precision after finish reaming hole machined, manually finish reams hole technique according to the required precision in hole in conjunction with several times, thus obtains the hole running through laminated composite material meeting required precision.The converted products steady quality that Finish Machining Bore technique of the present invention obtains, the precision in hole can ensure at 0 ~ 0.01mm; Finished product rate improves, and cutter life improves, thus greatly reduces production cost; Substantially increase production efficiency, alleviate labour intensity.
Detailed description of the invention
Below in conjunction with the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described.
Rapidoprint in the present embodiment is the laminated material that titanium alloy-aluminium alloy-composite is formed for aerospace component, and the drilling due to this material exists certain difficulty, and the present invention adopts following machining hole technique:
The technique of drilling after a, the assembling of employing laminated material, adopts auto-feed to bore cooperation and manually finish reams hole technique;
Described auto-feed driller skill adopts the integrated cutter that drills and reams, and after described auto-feed driller skill, the reaming allowance of reserved 1.2mm is to guarantee the hole precision after finish reaming hole machined (for being also 1 ~ 1.5mm for processing work to this reserved reaming allowance of the difference of hole required precision);
In b, described auto-feed driller skill, pierce from titanium alloy side when guaranteeing drilling;
C, described auto-feed driller skill adopt pecks brill processes;
In described auto-feed driller skill, the motion of cutter comprises radial rotary motion and axial feed motion, and the described namely described cutter of driller's skill axial feed motion in cutwork of pecking produces the fluctuating of advancing of certain frequency and amplitude; The swaging clamp phenomenon in processing can be greatly reduced like this;
In d, described auto-feed driller skill, in machining, use cetanol drilling lubricant to alleviate the ablation phenomen of composite;
E, required precision according to hole, described hole technique of manually finish reaming comprises twice and finish reams hole machined, thus the hole precision reaching trilaminate material is consistent, and reaches 0 ~+0.01mm.Due to for the difference of processing work to hole required precision, described hole technique of manually finish reaming also can comprise other several times (1 time, 3 times or 4 inferior) and finish reams hole machined, and the extreme difference of composite and aluminium alloy and titanium alloy can control in 0.01mm; For the hole being greater than 8.0mm sandwich, can adopt boring-expanding method processing, each reaming can get 0.4mm ~ 0.8mm.
Due to quite serious to the loss of cutter in this laminated material drilling processing, so the described diamond coated coating of the strand integrated cutter of the brill described in auto-feed driller skill, effectively to increase cutter life.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; change can be expected easily or replace, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should described be as the criterion with the protection domain of claim.
Claims (2)
1., for a Finish Machining Bore technique for the laminated material of titanium alloy Al alloy composite, it is characterized in that:
The technique of drilling after a, the assembling of employing laminated material, adopts auto-feed to bore cooperation and manually finish reams hole technique;
Described auto-feed driller skill adopts the integrated cutter that drills and reams, and after described auto-feed driller skill, the reaming allowance of reserved 1 ~ 1.5mm is to guarantee the hole precision after finish reaming hole machined;
In b, described auto-feed driller skill, pierce from titanium alloy side when guaranteeing drilling;
C, described auto-feed driller skill adopt pecks brill processes;
In described auto-feed driller skill, the motion of cutter comprises radial rotary motion and axial feed motion, and the described namely described cutter of driller's skill axial feed motion in cutwork of pecking produces the fluctuating of advancing of certain frequency and amplitude;
In d, described auto-feed driller skill, in machining, use cetanol drilling lubricant to alleviate the ablation phenomen of composite;
E, required precision according to hole, described hole technique of manually finish reaming comprises several times and finish reams hole machined.
2. as claimed in claim 1 for the Finish Machining Bore technique of the laminated material of titanium alloy Al alloy composite, it is characterized in that: the described diamond coated coating of the strand integrated cutter of the brill described in auto-feed driller skill.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510749670.8A CN105252034A (en) | 2015-11-06 | 2015-11-06 | Hole finishing technique for layered material of titanium alloy and aluminum alloy composite material |
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| CN201510749670.8A CN105252034A (en) | 2015-11-06 | 2015-11-06 | Hole finishing technique for layered material of titanium alloy and aluminum alloy composite material |
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| CN105252034A true CN105252034A (en) | 2016-01-20 |
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| CN201510749670.8A Pending CN105252034A (en) | 2015-11-06 | 2015-11-06 | Hole finishing technique for layered material of titanium alloy and aluminum alloy composite material |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105666039A (en) * | 2016-03-25 | 2016-06-15 | 哈尔滨飞机工业集团有限责任公司 | Quality guarantee method for manually reamed end hole of steel-aluminum interlayer piece |
| CN106647632A (en) * | 2016-12-27 | 2017-05-10 | 沈阳航空航天大学 | CFRP and titanium alloy laminated structure reamer service life prediction method |
| CN106624166A (en) * | 2016-12-27 | 2017-05-10 | 沈阳航空航天大学 | Optimization method for CFRP (carbon fiber reinforced plastics) and titanium alloy laminated structure reaming process |
| CN106825655A (en) * | 2017-01-13 | 2017-06-13 | 航天材料及工艺研究所 | A kind of multiple material aluminium alloy laminated material small hole forming method of big aspect ratio of glass fibre |
| CN107175470A (en) * | 2017-06-02 | 2017-09-19 | 中国航发南方工业有限公司 | The special-shaped deep groove processing method of titanium alloy component |
| CN107262763A (en) * | 2017-07-14 | 2017-10-20 | 哈尔滨汽轮机厂有限责任公司 | Million nuclear steam turbine stator portions set split hardfacing alloy layer pin-and-hole processing method |
| CN108044189A (en) * | 2017-12-12 | 2018-05-18 | 中航成飞民用飞机有限责任公司 | The Sandwich assemblies method for drilling of carbon fiber-containing composite material |
| CN109158955A (en) * | 2018-09-26 | 2019-01-08 | 大连理工大学 | A kind of laminated component method for drilling that machined parameters adaptively adjust |
| CN113579648A (en) * | 2021-07-21 | 2021-11-02 | 成都飞机工业（集团）有限责任公司 | Fine hole machining method for glue-containing laminated material |
| CN114535665A (en) * | 2022-04-25 | 2022-05-27 | 成都飞机工业（集团）有限责任公司 | Hole making cutter and hole making method for weak-rigidity component |
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| CN104741651A (en) * | 2015-03-17 | 2015-07-01 | 成都飞机工业（集团）有限责任公司 | Method for manufacturing holes in different-material laminated structures through automatic drilling and riveting system |
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| JP2008183626A (en) * | 2005-11-25 | 2008-08-14 | Hamamatsu Kagaku Gijutsu Kenkyu Shinkokai | Ultrasonic vibration machining method and fiber reinforced resin produced by the method |
| CN201061926Y (en) * | 2007-05-08 | 2008-05-21 | 合正科技股份有限公司 | Heat-dissipation sub-plate for high-speed drilling |
| CN101670448A (en) * | 2009-09-16 | 2010-03-17 | 大连理工大学 | Method and device of disposing holes on carbon fiber composite material and meal material which are overlapped |
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| CN103786265A (en) * | 2012-10-30 | 2014-05-14 | 宁波江丰电子材料有限公司 | Opening method of CFRP (Carbon Fiber Reinforced Plastics) and CFRP work-piece |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105666039A (en) * | 2016-03-25 | 2016-06-15 | 哈尔滨飞机工业集团有限责任公司 | Quality guarantee method for manually reamed end hole of steel-aluminum interlayer piece |
| CN106647632B (en) * | 2016-12-27 | 2018-10-19 | 沈阳航空航天大学 | The prediction technique of CFRP and titanium alloy laminated construction reaming knife service life |
| CN106647632A (en) * | 2016-12-27 | 2017-05-10 | 沈阳航空航天大学 | CFRP and titanium alloy laminated structure reamer service life prediction method |
| CN106624166A (en) * | 2016-12-27 | 2017-05-10 | 沈阳航空航天大学 | Optimization method for CFRP (carbon fiber reinforced plastics) and titanium alloy laminated structure reaming process |
| CN106825655A (en) * | 2017-01-13 | 2017-06-13 | 航天材料及工艺研究所 | A kind of multiple material aluminium alloy laminated material small hole forming method of big aspect ratio of glass fibre |
| CN107175470A (en) * | 2017-06-02 | 2017-09-19 | 中国航发南方工业有限公司 | The special-shaped deep groove processing method of titanium alloy component |
| CN107175470B (en) * | 2017-06-02 | 2019-03-05 | 中国航发南方工业有限公司 | The special-shaped deep groove processing method of titanium alloy component |
| CN107262763B (en) * | 2017-07-14 | 2019-02-26 | 哈尔滨汽轮机厂有限责任公司 | Million nuclear steam turbine stator portions cover split hardfacing alloy layer pin hole processing method |
| CN107262763A (en) * | 2017-07-14 | 2017-10-20 | 哈尔滨汽轮机厂有限责任公司 | Million nuclear steam turbine stator portions set split hardfacing alloy layer pin-and-hole processing method |
| CN108044189A (en) * | 2017-12-12 | 2018-05-18 | 中航成飞民用飞机有限责任公司 | The Sandwich assemblies method for drilling of carbon fiber-containing composite material |
| CN109158955A (en) * | 2018-09-26 | 2019-01-08 | 大连理工大学 | A kind of laminated component method for drilling that machined parameters adaptively adjust |
| CN113579648A (en) * | 2021-07-21 | 2021-11-02 | 成都飞机工业（集团）有限责任公司 | Fine hole machining method for glue-containing laminated material |
| CN114535665A (en) * | 2022-04-25 | 2022-05-27 | 成都飞机工业（集团）有限责任公司 | Hole making cutter and hole making method for weak-rigidity component |
| CN114535665B (en) * | 2022-04-25 | 2022-09-16 | 成都飞机工业（集团）有限责任公司 | Hole making method for weak rigid member |
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Application publication date: 20160120 |