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 PDF

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Publication number
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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China
Prior art keywords
main blade
main
blade
trailing edge
cut
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CN201310492664.XA
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Chinese (zh)
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CN104551533A (en
Inventor
李丽丽
杨楠楠
宋文娟
刘娟
郑宇航
康昱天
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Harbin Aircraft Industry Group Co Ltd
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Harbin Aircraft Industry Group Co Ltd
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Priority to CN201310492664.XA priority Critical patent/CN104551533B/en
Publication of CN104551533A publication Critical patent/CN104551533A/en
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/32Rotors
    • B64C27/46Blades

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

A kind of numerical-control processing method for cutting composite main blade trailing edge
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).
CN201310492664.XA 2013-10-21 2013-10-21 Numerical control machining method for composite-material main blade tailing edge Active CN104551533B (en)

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Application Number Priority Date Filing Date Title
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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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CN104551533B true CN104551533B (en) 2017-02-22

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (6)

* Cited by examiner, † Cited by third party
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

Patent Citations (6)

* Cited by examiner, † Cited by third party
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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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

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Inventor before: Yang Nannan

Inventor before: Song Wenjuan

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Inventor before: Zheng Yuhang

Inventor before: Kang Yutian