CN104551533B - Numerical control machining method for composite-material main blade tailing edge - Google Patents
Numerical control machining method for composite-material main blade tailing edge Download PDFInfo
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- CN104551533B CN104551533B CN201310492664.XA CN201310492664A CN104551533B CN 104551533 B CN104551533 B CN 104551533B CN 201310492664 A CN201310492664 A CN 201310492664A CN 104551533 B CN104551533 B CN 104551533B
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- main blade
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- trailing edge
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- 239000002131 composite material Substances 0.000 title claims abstract description 9
- 238000003754 machining Methods 0.000 title abstract description 10
- 238000005520 cutting process Methods 0.000 claims abstract description 26
- 238000000034 method Methods 0.000 claims abstract description 9
- 229910001651 emery Inorganic materials 0.000 claims description 13
- 238000003672 processing method Methods 0.000 claims description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N copper Chemical compound 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data:image/svg+xml;base64,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 [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
- 239000010949 copper Substances 0.000 claims description 3
- 238000003801 milling Methods 0.000 claims description 3
- 238000010030 laminating Methods 0.000 claims 1
- 238000004458 analytical method Methods 0.000 abstract description 6
- 238000005516 engineering process Methods 0.000 abstract description 5
- 238000011112 process operation Methods 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 description 3
- 241000143392 Oar Species 0.000 description 2
- 239000000428 dust Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
Classifications
-
- 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
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
Abstract
The invention relates to a numerical control machining method for cutting a helicopter main blade, in particular to a numerical control machining method for the composite-material main blade tailing edge. The cutting linearity of the main blade tailing edge is guaranteed completely by the numerical control machining method. According to process progress analysis, compared with the manual operation, the method has the advantages that the digital machining technology is adopted, so that the stability and reproducibility of the chord length can be guaranteed completely; according to process operation analysis, the composite-material main blade tailing edge cutting operation is completed by the digital machining technology, the producing efficiency is improved greatly, fault maintenance caused by man-made factors is avoided, and labor cost can be saved; according to operation feasibility analysis, a special operator is in charge of operating the digital machining equipment and grasping the whole process of operation, the requirements of operators are lowered, work intensity is reduced for workers, the stability of product quality is guaranteed, and the machining efficiency is improved.
Description
Technical field
The present invention relates to a kind of numerical-control processing method of cutting Helicopter Main blade, it is particularly well-suited to cut composite master
The method of blade.
Background technology
The main blade of existing composite at present, after the completion of the molding of main blade, is rule in blade rear edge surface using frock,
Using manual method, main blade trailing edge is cut.Not only working (machining) efficiency is low and dust cannot be inhaled completely for hand cut
Walk, seriously polluted, the main blade trailing edge linearity after simultaneously processing cannot ensure dimensional requirement, need to carry out secondary polishing plus
Work, and have that cutting efficiency is low, main blade trailing edge linearity is bad after cutting assumes that waveform, cut edge burr are more etc. to be lacked
Fall into.
Content of the invention
The object of the invention：
The purpose of the present invention is to ensure that the edge quality of the stability of cutting, the repeatability of data and cutting.
Technical scheme：
The first step：Determine the tangential width of fixation required by main blade with specific scribing tooling, draw trailing edge line of cut line；
Second step：Main blade 9 is removed to above platen, slowly falls in the middle of clamp system and detent mechanism
On worktable support；
3rd step：Main blade 9 positioning and clamping.Latch is inserted in blade root bushing through hole, blade tip is placed directly in base master
On locating piece 8；
4th step：Place for spacing snap ring 3, slowly tighten the main locating piece of side 4, just paste with main blade 9 surface
It is combined into standard；
5th step：Tighten hand wheel type gripping block 5, equally just fit with main blade 9 surface and be defined, it is to avoid cause blade position
The generation deviation put；
6th step：By the main locating piece of side 4 and hand wheel type gripping block 5, substantially main blade 9 is positioned,
Tighten side auxiliary positioning block 6 and hand wheel type gripping block 7, the main blade of auxiliary clamp again；
7th step：Design requirement according to main blade 9 inputs call parameter in procedure, such as the overall length of main blade 9,
The data such as the chord length of main blade 9；
8th step：Start lathe, carry out program initialization；
9th step：Emery wheel 2 is filled and is positioned over after knife at the trailing edge line of cut pulling, cutting local trailing edge, observe actual cutting
Cut deviation at position and line, adjust the position of cutter by deviation；
Tenth step：Lathe dry running, observes whether emery wheel 2 can cut through main blade 9 trailing edge and lathe in running
Cutting head whether can collide with main blade 9.If main blade 9 trailing edge can not be cut through by emery wheel 2, return to the 9th step
Again emery wheel 2 is filled knife；If the cutting head of lathe is collided with main blade 9, return to second step and readjust main oar
The position of leaf 9；Do not collide, carry out the 11st step；
11st step：Main blade trailing edge copper mesh part is cut；
12nd step：Main blade mid portion is cut；
13rd step：Tool changing, first passes through and visually carries out to knife, and after good position, the main blade of milling 9 is near the residue of circular arc
Part；
14th step：Complete digital control processing, main blade 9 is dismantled.
The technique effect that the present invention reaches：
The present invention has been completely secured linearity after main blade trailing edge cutting.From process flow perspective analysis, with respect to artificial
Operation, using Digital manufacturing technology, can guarantee stability and the repeatability of chord length completely；From technological operation angle analysis, adopt
Complete the work of composite main blade trailing edge cutting with Digital manufacturing technology, greatly improve production efficiency, more avoid
The fault repair that human factor causes, thus save labour cost；From operation possibility angle analysis, special messenger is had to be responsible for operand
Word process equipment, grasps whole flow processs of operation.Requirement to operator reduces, and the work reducing workman is strong
Degree, it is ensured that product quality is stable, improves working (machining) efficiency.
Accompanying drawing and the brief description of accompanying drawing
Fig. 1 is positioning datum and the clipping variation structural representation of the present invention；
Wherein：1 lathe cutting head
2 emery wheels
3 snap rings
The main locating piece of 4 sides
5 hand wheel type gripping blocks
6 side auxiliary positioning blocks
7 hand wheel type gripping blocks
The main locating piece in 8 bases
9 main blades
Above-mentioned 3～8 is the main composition part of fixture.
Specific embodiment
Referring to Fig. 1, composite main blade trailing edge cutting numerical-control processing method specific implementation step is as follows：
The first step：Determine the tangential width of fixation required by main blade with specific scribing tooling, draw trailing edge line of cut line；
Second step：Main blade 9 is removed to above platen, slowly falls in the middle of clamp system and detent mechanism
On worktable support；
3rd step：Main blade 9 positioning and clamping.Latch is inserted in blade root bushing through hole, blade tip is placed directly in base master
On locating piece 8；
4th step：Place for spacing snap ring 3, slowly tighten the main locating piece of side 4, just paste with main blade 9 surface
It is combined into standard；
5th step：Tighten hand wheel type gripping block 5, equally just fit with main blade 9 surface and be defined, it is to avoid cause blade position
The generation deviation put；
6th step：By the main locating piece of side 4 and hand wheel type gripping block 5, substantially main blade 9 is positioned,
Tighten side auxiliary positioning block 6 and hand wheel type gripping block 7, the main blade of auxiliary clamp again；
7th step：Design requirement according to main blade 9 inputs call parameter in procedure, such as the overall length of main blade 9,
The data such as the chord length of main blade 9；
8th step：Start lathe, carry out program initialization；
9th step：Emery wheel 2 is filled and is positioned over after knife at the trailing edge line of cut pulling, cutting local trailing edge, observe actual cutting
Cut deviation at position and line, adjust the position of cutter by deviation；
Tenth step：Lathe dry running, observes whether emery wheel 2 can cut through main blade 9 trailing edge and lathe in running
Cutting head whether can collide with main blade 9.If main blade 9 trailing edge can not be cut through by emery wheel 2, return to the 9th step
Again emery wheel 2 is filled knife；If the cutting head of lathe is collided with main blade 9, return to second step and readjust main oar
The position of leaf 9；Do not collide then continuation the 11st step；
11st step：Main blade trailing edge copper mesh part is cut；
12nd step：Main blade mid portion is cut；
13rd step：Tool changing, first passes through and visually carries out to knife, and after good position, the main blade of milling 9 is near the residue of circular arc
Part；
14th step：Complete digital control processing, main blade 9 is dismantled.
Claims (2)
1. a kind of numerical-control processing method for cutting composite main blade trailing edge it is characterised in that concrete procedure of processing such as
Under：
The first step：Determine the tangential width of fixation required by main blade with specific scribing tooling, draw trailing edge line of cut；
Second step：Main blade (9) is removed to above platen, slowly in the middle of clamp system and detent mechanism, falls to work
On station supports；
3rd step：Main blade (9) positioning and clamping；Latch is inserted in blade root bushing through hole, it is main fixed that blade tip is placed directly in base
On position block (8)；
4th step：Place for spacing snap ring (3), slowly tighten the main locating piece of side (4), with main blade (9) surface just
Laminating is defined；
5th step：Tighten hand wheel type gripping block (5), equally just fit and be defined with main blade (9) surface, it is to avoid cause blade position
The generation deviation put；
6th step：By the main locating piece of side (4) and hand wheel type gripping block (5), substantially main blade (9) is determined
Position, then tighten side auxiliary positioning block (6) and the second hand wheel type gripping block (7), the main blade of auxiliary clamp；
7th step：Design requirement according to main blade (9) inputs call parameter in procedure；
8th step：Start lathe, carry out program initialization；
9th step：Emery wheel (2) is filled and is positioned at the trailing edge line of cut pulling after knife, cutting local trailing edge, observe actual cutting
Deviation at position and line, is adjusted the position of cutter by deviation；
Tenth step：Lathe dry running, observes whether emery wheel (2) can cut through main blade (9) trailing edge and lathe in running
Cutting head whether can collide with main blade (9)；If main blade (9) trailing edge can not be cut through by emery wheel (2), return to
Emery wheel (2) is filled knife by the 9th step again；If the cutting head of lathe is collided with main blade (9), return to second step weight
Newly adjust the position of main blade (9)；Do not collide, carry out the 11st step；
11st step：Main blade trailing edge copper mesh part is cut；
12nd step：Main blade mid portion is cut；
13rd step：Tool changing, first passes through and visually carries out to knife, and after good position, the main blade of milling (9) is near the remainder of circular arc
Point；
14th step：Complete digital control processing, main blade (9) dismounting.
2. numerical-control processing method as claimed in claim 1 it is characterised in that：7th step |input paramete includes main blade (9)
Overall length, the chord length of main blade (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310492664.XA CN104551533B (en) | 2013-10-21 | 2013-10-21 | Numerical control machining method for composite-material main blade tailing edge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310492664.XA CN104551533B (en) | 2013-10-21 | 2013-10-21 | Numerical control machining method for composite-material main blade tailing edge |
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| Publication Number | Publication Date |
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| CN104551533A CN104551533A (en) | 2015-04-29 |
| CN104551533B true CN104551533B (en) | 2017-02-22 |
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| CN110842488B (en) * | 2019-11-28 | 2021-04-30 | 河南航天液压气动技术有限公司 | Cam machining method |
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| CN103111812A (en) * | 2013-03-14 | 2013-05-22 | 北重阿尔斯通（北京）电气装备有限公司 | Processing method of turbine axial blade |
| CN103317371A (en) * | 2013-07-17 | 2013-09-25 | 大连理工大学 | Adjustable clamp used for numerical control machining of helicopter composite material rotor blade |
-
2013
- 2013-10-21 CN CN201310492664.XA patent/CN104551533B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006026962A1 (en) * | 2004-09-10 | 2006-03-16 | Mtu Aero Engines Gmbh | Method for producing a gas turbine rotor comprising integral hollow blades |
| CN201109035Y (en) * | 2007-09-24 | 2008-09-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Special-purpose fixture |
| CN102554556A (en) * | 2010-12-14 | 2012-07-11 | 上海船厂船舶有限公司 | Machining method for eliminating wear of propeller hub and blades of adjustable propeller device |
| CN102962654A (en) * | 2012-11-22 | 2013-03-13 | 哈尔滨汽轮机厂有限责任公司 | Processing method for no-crown guide blade of steam turbine |
| CN103111812A (en) * | 2013-03-14 | 2013-05-22 | 北重阿尔斯通（北京）电气装备有限公司 | Processing method of turbine axial blade |
| CN103317371A (en) * | 2013-07-17 | 2013-09-25 | 大连理工大学 | Adjustable clamp used for numerical control machining of helicopter composite material rotor blade |
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| CN104551533A (en) | 2015-04-29 |
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Inventor after: Li Lili Inventor after: Liu Jianbo Inventor after: Li Ye Inventor after: Yang Nannan Inventor after: Song Wenjuan Inventor after: Liu Juan Inventor after: Zheng Yuhang Inventor after: Kang Yutian Inventor before: Li Lili Inventor before: Yang Nannan Inventor before: Song Wenjuan Inventor before: Liu Juan Inventor before: Zheng Yuhang Inventor before: Kang Yutian |