CN105945652B - Decision method for aerospace component processing cutting parameter - Google Patents
Decision method for aerospace component processing cutting parameter Download PDFInfo
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- CN105945652B CN105945652B CN201610576534.8A CN201610576534A CN105945652B CN 105945652 B CN105945652 B CN 105945652B CN 201610576534 A CN201610576534 A CN 201610576534A CN 105945652 B CN105945652 B CN 105945652B
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- web
- side wall
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- corner
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- 238000012545 processing Methods 0.000 title claims abstract description 48
- 238000000034 method Methods 0.000 title claims abstract description 15
- 210000003205 muscle Anatomy 0.000 claims abstract description 13
- 238000003801 milling Methods 0.000 claims description 27
- 238000003754 machining Methods 0.000 claims description 7
- RLLPVAHGXHCWKJ-IEBWSBKVSA-N (3-phenoxyphenyl)methyl (1s,3s)-3-(2,2-dichloroethenyl)-2,2-dimethylcyclopropane-1-carboxylate Chemical compound CC1(C)[C@H](C=C(Cl)Cl)[C@@H]1C(=O)OCC1=CC=CC(OC=2C=CC=CC=2)=C1 RLLPVAHGXHCWKJ-IEBWSBKVSA-N 0.000 claims description 3
- 230000001788 irregular Effects 0.000 claims description 3
- 210000001015 abdomen Anatomy 0.000 claims 1
- 238000007665 sagging Methods 0.000 abstract description 3
- 230000008092 positive effect Effects 0.000 abstract description 2
- 238000013461 design Methods 0.000 description 2
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 206010044565 Tremor Diseases 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- 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
- B23Q17/00—Arrangements for observing, indicating or measuring on machine tools
- B23Q17/20—Arrangements for observing, indicating or measuring on machine tools for indicating or measuring workpiece characteristics, e.g. contour, dimension, hardness
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Milling Processes (AREA)
Abstract
The invention discloses a kind of decision method for aerospace component processing cutting parameter, trial cut part includes web and is arranged on five-axis robot face, three axial planes and the three axle row sections on web periphery；Corner is formed between structural member edge strip and edge strip or rib and rib；It is high that the top area of structural member rib and edge strip forms muscle；The rib and edge strip of structural member form side wall；The sagging boss of web and shallow corner are set on the inside of three axial planes, independent muscle is set in the middle part of web, is set on the inside of three axle row sections and closes angle and wedge angle greatly, deep corner is set beside five-axis robot face.Compared with prior art, the positive effect of the present invention is：The trial cut part of the present invention can require high aerospace component trial cut model by high, surface quality of workpieces as complex-shaped, thin-walled, size and position accuracy demand, accurate cutting parameter can be provided for aerospace component process using this trial cut part, be advantageous to save processing cost.
Description
Technical field
The present invention relates to a kind of trial cut part and its decision method judged for aerospace component processing cutting parameter.
Background technology
With the fast development of aviation, avigation piece quantity cumulative year after year to be processed, and wanted for crudy
Ask also more strict.Thus, it is more strict for the sets requirement of the processing cutting parameter closely bound up with crudy.
The decision method of processing cutting parameter mainly provides experience ginseng by veteran numerical control programming personnel at present
Number, then verified using trial cut part mould processing.And wherein the design of trial cut part model selects for the cutting parameter that part is processed
Influence significantly, accurately and reliably join because only that being only before formal processing by the authenticated parameter of actual machine test
Number.And traditional trial cut part model can not intactly reflect the architectural feature of avigation piece.
The content of the invention
In order to overcome the disadvantages mentioned above of prior art, the invention provides one kind to be used for aerospace component processing cutting parameter
The trial cut part and its decision method of judgement, the principal character of aerospace component (frame class part) more can be comprehensively embodied, it is right
It is more reliable and quick in the selection of processing cutting parameter and optimization for specifying lathe.
The technical solution adopted for the present invention to solve the technical problems is：One kind is used for aerospace component processing cutting parameter
The trial cut part of judgement, including web and the five-axis robot face, three axial planes and the three axle row sections that are arranged on web periphery；Structural member edge
Corner is formed between bar and edge strip or rib and rib；It is high that the top area of structural member rib and edge strip forms muscle；Structural member
Rib and edge strip form side wall；The sagging boss of web and shallow corner are set on the inside of three axial planes, independent muscle is set in the middle part of web,
Set on the inside of three axle row sections and close angle and wedge angle greatly, deep corner is set beside five-axis robot face.
Present invention also offers a kind of decision method for aerospace component processing cutting parameter, including following content：
The cutter that actionradius is less than or equal to knuckle radius carries out flank milling to corner；Processing mode for wedge angle is
Side wall surplus first is removed using big cutter, the cutter progress layer for reusing radius less than or equal to knuckle radius is cut；For deep corner
The processing mode cut using back taper knife layer, flank milling mode is used for shallow corner；
It is that shear blade processing is carried out in the case where roughing side wall leaves surplus for the high processing mode of muscle；
For the processing mode of side wall：When it is more than 90 ° with web angle, cut using three axle layers or five axle balance staff sides
The processing mode of sword milling；When it is with web angle=90 °, using the processing mode of side edge milling；When itself and web angle
During 90 ° of ＜, using the processing mode of five axle balance staff side edge millings；Independent muscle side wall uses the flank milling mode of small cutting-in；
The processing mode cut for the side wall of irregular Curvature varying be present using row；For continuous curvature change be present
Side wall use five axle flank milling modes；
When the base angle that side wall and web are formed is fillet, using the nose of an ox knife clean-up machining mode of corresponding bottom radius；When
When the base angle that side wall is formed with web is right angle, using flat-bottomed cutter clean-up machining mode.
Compared with prior art, the positive effect of the present invention is：The trial cut part of the present invention can be used as complex-shaped, thin
Wall, size and position accuracy demand are high, surface quality of workpieces requires high aerospace component trial cut model, utilize this trial cut part energy
Accurate cutting parameter enough is provided for aerospace component process, is advantageous to save processing cost.
Brief description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is the structural representation of the present invention.
Embodiment
A kind of trial cut part judged for aerospace component processing cutting parameter, as shown in figure 1, including：Wedge angle 1, muscle are high
2nd, five-axis robot face 3, deep corner 4, independent muscle 5, three axial planes 6, web sink boss 7, shallow corner 8, close angle 9 greatly, three axle rows are cut
Face 10 etc..Wherein：
Five-axis robot face 3, three axial planes 6 and three axle row sections 10 are arranged on web periphery, and web is set in the inner side of three axial plane 6
Sunk boss 7 and shallow corner 8, and independent muscle 5 is set in the middle part of web, is set in the inner side of three axle row section 10 and is closed angle 9 and wedge angle greatly
1, on the side of five-axis robot face 3, deep corner 4 is set.
The invention also discloses a kind of decision method for aerospace component processing cutting parameter, including following content：
Corner is formed between part edge strip and edge strip or rib and rib, wedge angle is defined as 60 ° of corner ＜.It is right
In the processing mode of general corner：The cutter that actionradius is less than or equal to knuckle radius carries out flank milling to corner；And for
First to remove side wall surplus using big cutter, the cutter for reusing radius less than or equal to knuckle radius enters the processing mode of wedge angle 1
Row layer is cut.Corner has been distinguished because corner depth is different again simultaneously, when corner depth is more than or equal to the title of four times of diameters of corner
Be deep corner (deep chamber), it is on the contrary then be referred to as shallow corner (shallow cavity)；The processing side cut for the deep generally use back taper knife layer of corner 4
Formula, and shallow corner 8 then uses in general flank milling mode.
The high 2 signified top area for rib and edge strip of muscle, its width is typically in 1.5~2mm, and it is typically in roughing side
Wall carries out shear blade processing in the case of leaving surplus.
The thickness of side wall (including rib and edge strip) is all 1.5~2mm, belongs to thin-walled parts, it is from web because angle is different
And processing mode is otherwise varied.When angle is more than 90 °, side wall is referred to as angle of release face, otherwise angle=90 ° are referred to as three axles
Face, 90 ° of angle ＜ are referred to as to close edged surface.It is that three axle layers are cut or five axle balance staff side edges for its conventional processing mode of angle of release face
Milling；The conventional processing mode of three axial planes 6 is side edge milling；And close edged surface when its close angle it is smaller when, the processing mode that uses for
Layer is carried out using back taper knife to cut or using five axle balance staff side edge millings；And close angle it is larger when its processing mode that (closes angle 9 in Fig. 1 greatly)
To use five axle balance staff side edge millings.Independent muscle 5 without support in process because easily trembling in Fig. 1, using small cutting-in
Flank milling mode.
There is irregular Curvature varying in partial sidewall face, can not be with flank milling in place, therefore such side wall is used
The processing mode cut of row, three axle row sections 10 are such machined surface in Fig. 1., can when side wall has continuous Curvature varying
In place, it is referred to as into ruled surface using five axle flank millings, the five-axis robot face 3 in Fig. 1 is such machined surface.
Side wall forms base angle with web, is using corresponding base angle R for its conventional processing mode that base angle is fillet
Nose of an ox knife clean-up machining；For base angle for right angle, its processing mode used is uses flat-bottomed cutter clean-up machining.
When boss on web surface be present, boss being arranged to island during milling web, being avoided herein, subsequently milling again
Boss top surface, the nose of an ox knife back chipping for the R angles around boss using corresponding base angle R, such as the sagging boss 7 of web in Fig. 1.
The present invention operation principle be：By a kind of trial cut model of aerospace component of design, it is determined for
Cutting parameter used by specified machine tooling class cutting zone.Trial cut blank is placed on lathe by operator, through excessive
Secondary trial cut, which obtains, processes that each machining area is reasonable and efficient machined parameters (such as amount of feeding, the speed of mainshaft, back engagement of the cutting edge etc.),
So as to ensure that the machined parameters that lathe uses in the formal part of following process are rationally effective, the crudy and machine of part are improved
The stock-removing efficiency of bed.
Claims (2)
- A kind of 1. decision method for aerospace component processing cutting parameter, it is characterised in that：Including following content：The cutter that actionradius is less than or equal to knuckle radius carries out flank milling to the corner of non-wedge angle；For the processing side of wedge angle Formula first to remove side wall surplus using big cutter, cut by the cutter progress layer for reusing radius less than or equal to knuckle radius；For depth Corner uses the processing mode that back taper knife layer is cut, and flank milling mode is used for shallow corner；It is that shear blade processing is carried out in the case where roughing side wall leaves surplus for the high processing mode of muscle；For the processing mode of side wall：When it is more than 90 ° with web angle, cut using three axle layers or five axle balance staff side edge millings The processing mode cut；When it is with web angle=90 °, using the processing mode of side edge milling；When it is 90 ° with web angle ＜ When, using the processing mode of five axle balance staff side edge millings；Independent muscle side wall uses the flank milling mode of small cutting-in；The processing mode cut for the side wall of irregular Curvature varying be present using row；For the side of continuous curvature change be present Wall uses five axle flank milling modes；When the base angle that side wall and web are formed is fillet, using the nose of an ox knife clean-up machining mode of corresponding bottom radius；Work as side wall When the base angle formed with web is right angle, using flat-bottomed cutter clean-up machining mode.
- 2. the decision method according to claim 1 for aerospace component processing cutting parameter, it is characterised in that：Work as abdomen Boss in plate face be present, boss is arranged to island during milling web, avoid herein, subsequently milling boss top surface again, it is right Base angle around boss is using the nose of an ox knife back chipping for corresponding to bottom radius.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610576534.8A CN105945652B (en) | 2016-07-21 | 2016-07-21 | Decision method for aerospace component processing cutting parameter |
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| CN201610576534.8A CN105945652B (en) | 2016-07-21 | 2016-07-21 | Decision method for aerospace component processing cutting parameter |
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| Publication Number | Publication Date |
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| CN105945652A CN105945652A (en) | 2016-09-21 |
| CN105945652B true CN105945652B (en) | 2018-02-06 |
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| CN113182567B (en) * | 2021-03-31 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Method for rapid trial cutting and cutting parameter optimization of numerical control milling cutter |
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| JP3662087B2 (en) * | 1997-02-26 | 2005-06-22 | オリンパス株式会社 | Curved surface cutting method |
| CN102789200B (en) * | 2012-08-21 | 2014-04-09 | 南京航空航天大学 | Integrated airplane structural part numerical-control machining capacity test model and application thereof |
| CN104722819A (en) * | 2015-03-17 | 2015-06-24 | 什邡市明日宇航工业股份有限公司 | High-efficiency cutting processing method of aluminium-alloy aerospace structure part |
| CN205870136U (en) * | 2016-07-21 | 2017-01-11 | 四川明日宇航工业有限责任公司 | A trial cut spare that is used for aeronautical structure spare processing cutting parameter to judge |
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Address after: 618400 Sichuan Deyang Shifang Economic Development Zone (Ling Jie Park) blue sky Road No. 3 Patentee after: Sichuan Xinhang Titanium Technology Co.,Ltd. Address before: 618400 Sichuan Deyang Shifang Economic Development Zone (Ling Jie Park) blue sky Road No. 3 Patentee before: SICHUAN FUTURE AEROSPACE INDUSTRIAL Co.,Ltd. |