CN101062546A - Method for two-sided numeric controlled manufacture of large-scale integral complex constructional element - Google Patents
Method for two-sided numeric controlled manufacture of large-scale integral complex constructional element Download PDFInfo
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- CN101062546A CN101062546A CN 200710049222 CN200710049222A CN101062546A CN 101062546 A CN101062546 A CN 101062546A CN 200710049222 CN200710049222 CN 200710049222 CN 200710049222 A CN200710049222 A CN 200710049222A CN 101062546 A CN101062546 A CN 101062546A
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Abstract
The invention relates to the dual face digital controlled machining of complex structures that composed of horizontal beam components, positioned using two holes set on the process boss with compression slot set around the component, horizontally set frame component using one side of two holes to position, two process holes set on the boss which set surrounding the component with rib surface as the positioning face, cushion plate as the tool, using countersunk bolt compressing the fixed plate, horizontal set wall plate components using special vacuum sucking tool, machining from the side with less slot, then regarding it as the positioning baseline. It changes the process complexity of existing techniques. It is simple in locating, stable, simple in compression, good in universality, free from special making, avoiding component deformation, compression damage or dimension precision worsening due to clamp change. It can be co-used with other components with certain universality, economical in tooling.
Description
Technical field
The present invention relates to a kind of process of two-sided numeric controlled manufacture of large-scale integral complex constructional element.
Background technology
The airframe part belongs to the large-scale integral complex structural member in a large number, mainly be divided into frame class, beam class, wallboard class, etc. type, usually these heavy parts be processed with following two kinds of situations:
1. during the porose and plane of part self, serve as processing location benchmark normally with the peaceful web face of looking like assembly technology hole, part in the hole of part self, like this in process, need the workman to adjust compacted position while processing, manual intervention is too much, and the procedure segmentation is more, and high efficiency digital control processing is had a greatly reduced quality.
2. if part self does not have the hole, then be converted to the location, limit of part in the processing, occur easily in the processing: when part is subjected to displacement, can cause the chipping allowance sudden change, the generation cutter is crossed and is cut or break cutter; The mismachining tolerance of gulde edge or face is accumulated on the profile of following process, causes the profile precision not high, the crudy instability.
Above-mentionedly either way there is following problem simultaneously: because the multiple clamping location, process the outline position on latter two face and the size coordinating to have relatively high expectations is difficult to guarantee for twice location and installation, and easily conflict, also increase the difficulty of programming with test basis.
Summary of the invention:
Because digital control processing lay special stress on location, the large-scale integral labyrinth is especially true, therefore the purpose of this invention is to provide a kind of same benchmark orientation problem that solves the two-sided processing of large-scale integral complex structural member, to guarantee that outline position and size that twice location and installation processed on latter two face coordinate, to guarantee the profile precision.
The present invention realizes that the above-mentioned purpose technical solution is, a kind of method of two-sided numeric controlled manufacture of large-scale integral complex constructional element comprises the steps:
A. horizontal placement beam-like part, simultaneously locate with two holes, two fabrication holes are arranged on the false boss, and pressing groove is set around part;
B. horizontal placement frame class part is simultaneously located with two holes, and two fabrication holes are arranged on the false boss, false boss is arranged on the part periphery, as locating surface, uses the backing plate frock by the rib face, system countersunk head hold-down apertures is fixed the backing plate frock with dormant bolt on false boss;
C. horizontal placement wallboard class part with special-purpose vacuum suction frock, the one side that first working groove is few, processes the back with the location benchmark of this face as turn-over processing.
The present invention has following beneficial effect than prior art.
Adopt two holes simultaneously to locate, two fabrication holes are arranged on the false boss, and positioning states is better;
One side processing only need be carried out a clamping and get final product, and has changed the processing arrangement friable state of the multiple clamping of prior art scheme;
Positioning and clamping is stable simple, and state is good, is beneficial to carry out Cutting Process, as the further optimization of process tool, cutting parameter and feed path;
The part clamping element is simple, and versatility is good, need not make specially;
The employing pressing groove compresses, and it is convenient that the workman compresses part, does not need manual intervention processing, and efficient is than improving in the past;
Because clamping position need not change in process, increased the stability of part processing, avoided changing the part deformation that causes, weighing the decline with dimensional accuracy wounded because of clamping.
Because the backing plate frock is damaged little, can with other component sharing, have certain versatility, saved frock.
The specific embodiment
For beam-like part, horizontal placement beam class zero, two fabrication holes are arranged on the false boss, because several grooved features are arranged on part, and be evenly distributed substantially, adopted the method that pressing groove is set around part, the operator only needs to compress the part pressing groove before processing, need not change the clamping state of part again in process.
For frame class part: part is horizontal placement.Part adopts two holes simultaneously to locate, and two fabrication holes are arranged on the false boss, because most of rib of part at sustained height, is intended locating with the rib face.Because bigger at part, the clamping dismounting is inconvenient, adopts the backing plate frock, the part periphery is established false boss, and makes the countersunk head hold-down apertures on false boss, makes screwed hole on the backing plate, is pressed abd fixed on the backing plate frock with dormant bolt.
For wallboard class part: the horizontal placement of part.Because part is thin, very easily remove the uneven machining deformation that produces in the process because of surplus; And lack the location on the general structure and clamp the position, adopt special-purpose vacuum suction frock.Add the few one side of man-hour elder generation working groove, process the location benchmark of doing turn-over processing behind this face with this face.
With whole frame is example.This part machines on HENRY-LINE five coordinate high-speed milling machines, adopts the localization method of two holes one side, adopts the backing plate frock, the part periphery is established false boss, and on false boss, make the countersunk head hold-down apertures, and make screwed hole on the backing plate, be pressed abd fixed on the backing plate frock with dormant bolt.The operation design is directly carried out two-sided fine finishining after going up and adopting two-sided roughing, utilizes the programming of UG software high-speed module, utilizes VERICUT software to carry out machining simulation.Because the positioning and clamping state is good, the follow-up process optimization that constantly carries out, the process that has adopted spiral incision, circular arc feed and layered cutting etc. to upgrade.
This part machine adds about 4~5 days of the cycle (class Three operation, comprise cutter, frock preparations, operation turnover, measurement etc.), and before adopting the machine of traditional milling add the cycle need 15~20 days, about 4 times of efficient raisings.Current programme has realized not having the processing under artificial the intervention substantially, and working strength of workers reduces, and the crudy of part obviously improves, and this part initial workpiece fault-free is paid.
Claims (1)
1. the method for a two-sided numeric controlled manufacture of large-scale integral complex constructional element comprises the steps:
A. horizontal placement beam-like part, simultaneously locate with two holes, two fabrication holes are arranged on the false boss, and pressing groove is set around part;
B. horizontal placement frame class part is simultaneously located with two holes, and two fabrication holes are arranged on the false boss, false boss is arranged on the part periphery, as locating surface, uses the backing plate frock by the rib face, system countersunk head hold-down apertures is fixed the backing plate frock with dormant bolt on false boss;
C. horizontal placement wallboard class part with special-purpose vacuum suction frock, the one side that first working groove is few, processes the back with the location benchmark of this face as turn-over processing.
Priority Applications (1)
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CN 200710049222 CN101062546A (en) | 2007-06-01 | 2007-06-01 | Method for two-sided numeric controlled manufacture of large-scale integral complex constructional element |
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CN 200710049222 CN101062546A (en) | 2007-06-01 | 2007-06-01 | Method for two-sided numeric controlled manufacture of large-scale integral complex constructional element |
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CN 200710049222 Pending CN101062546A (en) | 2007-06-01 | 2007-06-01 | Method for two-sided numeric controlled manufacture of large-scale integral complex constructional element |
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Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
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CN101412188B (en) * | 2008-11-18 | 2010-04-14 | 西安飞机工业(集团)有限责任公司 | Control method for numerical control machining deformation of wall panel parts |
CN101704183B (en) * | 2009-12-10 | 2011-04-06 | 西安飞机工业(集团)有限责任公司 | Horizontal numerical control machining method of plane beam-type parts |
CN102581359A (en) * | 2012-03-22 | 2012-07-18 | 沈阳飞机工业(集团)有限公司 | Deformation controlling method for machining double-side multi-rib structural part |
CN102069395B (en) * | 2009-11-23 | 2012-10-10 | 西安飞机工业(集团)有限责任公司 | Numerical control machining clamping method for aircraft wing beam parts |
CN104889462A (en) * | 2015-06-17 | 2015-09-09 | 沈阳飞机工业(集团)有限公司 | Method for reducing deformation of numerical control machining plate type titanium alloy parts |
CN105382502A (en) * | 2015-11-27 | 2016-03-09 | 沈阳飞机工业(集团)有限公司 | Efficient numerical control machining method for thin and long beam type parts |
CN105436391A (en) * | 2015-12-30 | 2016-03-30 | 无锡透平叶片有限公司 | Cooling and deformation prevention tooling used after forging large-sized titanium alloy grid beam forge piece |
CN105880918A (en) * | 2014-05-16 | 2016-08-24 | 哈尔滨飞机工业集团有限责任公司 | Composite material skin digital manufacture method |
CN105964828A (en) * | 2016-03-25 | 2016-09-28 | 哈尔滨飞机工业集团有限责任公司 | Method for determining machining positioning datum of metal honeycomb plate |
CN106001715A (en) * | 2016-06-14 | 2016-10-12 | 北京航星机器制造有限公司 | Aluminum alloy U-shaped open type precise inner cavity thin-walled part technological method |
CN110385466A (en) * | 2019-08-07 | 2019-10-29 | 沈阳飞机工业(集团)有限公司 | A kind of numerical-control processing method of titanium alloy ultra-large type complex thin-wall component |
CN111842999A (en) * | 2020-07-30 | 2020-10-30 | 中煤科工集团重庆研究院有限公司 | Method for machining mounting surface of supporting plate of drilling machine |
CN113500235A (en) * | 2021-07-01 | 2021-10-15 | 贵州詹阳动力重工有限公司 | Machining method and machining clamp device for long and thin supporting piece |
CN116214097A (en) * | 2023-04-07 | 2023-06-06 | 成都森博精密机械有限公司 | Frame-shaped part processing method |
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2007
- 2007-06-01 CN CN 200710049222 patent/CN101062546A/en active Pending
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101412188B (en) * | 2008-11-18 | 2010-04-14 | 西安飞机工业(集团)有限责任公司 | Control method for numerical control machining deformation of wall panel parts |
CN102069395B (en) * | 2009-11-23 | 2012-10-10 | 西安飞机工业(集团)有限责任公司 | Numerical control machining clamping method for aircraft wing beam parts |
CN101704183B (en) * | 2009-12-10 | 2011-04-06 | 西安飞机工业(集团)有限责任公司 | Horizontal numerical control machining method of plane beam-type parts |
CN102581359A (en) * | 2012-03-22 | 2012-07-18 | 沈阳飞机工业(集团)有限公司 | Deformation controlling method for machining double-side multi-rib structural part |
CN105880918A (en) * | 2014-05-16 | 2016-08-24 | 哈尔滨飞机工业集团有限责任公司 | Composite material skin digital manufacture method |
CN104889462A (en) * | 2015-06-17 | 2015-09-09 | 沈阳飞机工业(集团)有限公司 | Method for reducing deformation of numerical control machining plate type titanium alloy parts |
CN105382502A (en) * | 2015-11-27 | 2016-03-09 | 沈阳飞机工业(集团)有限公司 | Efficient numerical control machining method for thin and long beam type parts |
CN105436391A (en) * | 2015-12-30 | 2016-03-30 | 无锡透平叶片有限公司 | Cooling and deformation prevention tooling used after forging large-sized titanium alloy grid beam forge piece |
CN105964828A (en) * | 2016-03-25 | 2016-09-28 | 哈尔滨飞机工业集团有限责任公司 | Method for determining machining positioning datum of metal honeycomb plate |
CN106001715A (en) * | 2016-06-14 | 2016-10-12 | 北京航星机器制造有限公司 | Aluminum alloy U-shaped open type precise inner cavity thin-walled part technological method |
CN110385466A (en) * | 2019-08-07 | 2019-10-29 | 沈阳飞机工业(集团)有限公司 | A kind of numerical-control processing method of titanium alloy ultra-large type complex thin-wall component |
CN110385466B (en) * | 2019-08-07 | 2021-03-19 | 沈阳飞机工业(集团)有限公司 | Numerical control machining method for titanium alloy ultra-large complex thin-wall part |
CN111842999A (en) * | 2020-07-30 | 2020-10-30 | 中煤科工集团重庆研究院有限公司 | Method for machining mounting surface of supporting plate of drilling machine |
CN113500235A (en) * | 2021-07-01 | 2021-10-15 | 贵州詹阳动力重工有限公司 | Machining method and machining clamp device for long and thin supporting piece |
CN116214097A (en) * | 2023-04-07 | 2023-06-06 | 成都森博精密机械有限公司 | Frame-shaped part processing method |
CN116214097B (en) * | 2023-04-07 | 2024-01-09 | 成都森博精密机械有限公司 | Frame-shaped part processing method |
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