CN103612076B - Large aircraft rib class part by numerical control processing method - Google Patents
Large aircraft rib class part by numerical control processing method Download PDFInfo
- Publication number
- CN103612076B CN103612076B CN201310654567.6A CN201310654567A CN103612076B CN 103612076 B CN103612076 B CN 103612076B CN 201310654567 A CN201310654567 A CN 201310654567A CN 103612076 B CN103612076 B CN 103612076B
- Authority
- CN
- China
- Prior art keywords
- sides
- listrium
- web
- rib
- roughing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
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
- B23P13/00—Making metal objects by operations essentially involving machining but not covered by a single other subclass
- B23P13/02—Making metal objects by operations essentially involving machining but not covered by a single other subclass in which only the machining operations are important
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
A kind of method of large aircraft rib class part by numerical control processing, be divided into roughing and two stages of fine finishining, machined by four stations, roughing first surface is vallecular cavity face, with all vallecular cavities of layer mode of priority successively roughing, enough surpluses are stopped bottom vallecular cavity, roughing second is rib datum level, all sites stays even roughing surplus, fine finishining first surface is rib datum level, after fine finishining is complete, again revises two ends locating hole, fine finishining second is vallecular cavity face, is finally separated the passing hole position on both sides listrium gap portions technique connecting plate and web.
Description
Technical field
The present invention relates to Computerized Numerical Control processing technology field, particularly about the numerical-control processing method of large aircraft rib class part.
Background technology
Rib class part is the quasi-representative part on aircraft, is generally distributed on wing, complex structure, One's name is legion, is one of major part forming aircraft wing.Rib class part is generally bilateral structure, and one side is rib datum level, and structure is simple; Another side complex structure, usually has groove, T-shaped muscle, lightening core, stud, sink, the structure such as step, precision holes; Both sides are the hyperboloid listrium with wide-angle breach.
Rib class part high efficient and reliable ground manufactures very important to aircraft development.Especially along with the maximization of aircraft development, rib class part also maximizes gradually, complicated, and occurred some new manufacture difficult problems, main manifestations is the phenomenons such as distortion is large, clamping difficulty is large, cutting chatter is serious, working (machining) efficiency is low.Particularly when the width dimensions of rib is greater than 1 meter, when length is greater than 4 meters, structural strain's amount increases, and the distortion of arching upward especially in the middle part of part has a strong impact on the reliability of clamping; Meanwhile, both sides listrium and connected web, with breach on a large scale, greatly reduce the rigidity at this position, cause cutting chatter, manufacture difficulty is increased greatly.
Object of the present invention is intended to overcome above difficulty, realizes the stable digital control processing of large aircraft rib class part.
Summary of the invention
The invention discloses a kind of method to the processing of large aircraft rib class part by numerical control.
A method for large aircraft rib class part by numerical control processing, the digital control processing of part is divided into roughing and two stages of fine finishining, is machined, it is characterized in that comprising following content by four stations:
1) roughing first surface is vallecular cavity face, clamping adopts both sides to compress mode, prefabricated lower planes is wanted before roughing, two ends locating hole, make multiple bolt hole, the passing hole of position distribution on part web, on the breach of both sides listrium and the unnecessary woollen of two ends, counter boring on bolt hole, the degree of depth is as the criterion can sink to respective bolt, with all vallecular cavities of layer mode of priority successively roughing, enough surpluses are stopped bottom vallecular cavity, the rigidity adding man-hour for second web keeps, part web thickness and institute's made allowance thickness sum is made to be not less than 10mm, even surplus is stayed in side, except two ends, the retained cylinder process area in all bolt hole positions, height maintains an equal level with woollen, playing a supportive role of man-hour is added for second web, listrium equal milling in both sides becomes nick shaped, notch depth is to web position, the gap portions of both sides listrium retains web processes connecting plate, the web at listrium position, both sides is made to keep connecting, become as a whole, all studs, the top margin of listrium is not processed, remain a height, simultaneously, stud mills out some breach be evenly distributed, indentations bottom is about 3mm higher than the top of part stud, two ends clout is preserved for compressing,
2) roughing second is rib datum level, clamping adopts both sides to compress mode, processing sequence is counter boring on both side edges plate height, both sides listrium breach, rib datum level, both sides listrium profile, bolt hole, all sites stays even roughing surplus, equally, the gap portions of both sides listrium retains web processes connecting plate and does not process, the milling of two ends clout to and rib datum level contour;
3) roughing complete after be separated the unnecessary woollen in both sides by pincers worker;
4) fine finishining first surface is rib datum level, the clamping of this station adopts rib class component sharing clamping platform to carry out, workpiece is located on shared clamping platform with two ends locating hole, within six square bolts sink to bolt hole compress, the order of bolt presses is first middle, rear both sides, after compressing, bolt will lower than rib datum level, the processing sequence of fine finishining first surface is both side edges plate height, both sides listrium width, rib datum level, both sides listrium profile, shape in the listrium of both sides, after fine finishining is complete, again two ends locating hole is revised, equally, the gap portions of both sides listrium retains web processes connecting plate and does not process,
5) fine finishining second is vallecular cavity face, the clamping of this station adopts Special vacuum frock, workpiece is located in Special vacuum frock with two ends locating hole, within six square bolts sink to bolt hole compress, and with vacuum suction, the processing sequence that fine finishining is second is shape, stud thickness, web hole in both side edges plate height, both sides listrium width, stud height, vallecular cavity web, both sides listrium, is finally separated the passing hole position on both sides listrium gap portions technique connecting plate and web.
Beneficial effect of the present invention is, efficiently solve the problems such as large aircraft rib class part bulk deformation in digital control processing is large, clamping is difficult, Hanging sectionally processing cutting chatter, working (machining) efficiency are low by above process, realize large aircraft rib class part and stablize, process efficiently.
Below in conjunction with embodiment accompanying drawing, this invention is described in further detail.
Accompanying drawing explanation
Fig. 1 is roughing vallecular cavity face schematic diagram;
Stud top margin and technical gaps schematic diagram when Fig. 2 is roughing vallecular cavity face;
Fig. 3 is roughing rib datum level and fine finishining rib datum level schematic diagram;
Fig. 4 is fine finishining rib datum level schematic cross-section;
Fig. 5 is fine finishining vallecular cavity face schematic diagram;
Fig. 6 is fine finishining vallecular cavity face schematic cross-section.
Number description: the passing hole on 1 bolt hole in counter boring, 2 bolts hole, 3 locating holes, 4 platform of machine tools, 5 workpiece woollens, 6 cylinder process areas, 7 listriums, 8 technique connecting plates, 9 studs, 10 workpiece, 11 stud top technical gaps, 12 vallecular cavity webs, 13 stud top margin, 14 rib datum levels, 15 rib class component sharing clamping platforms, 16 listrium profiles, 17 listriums in shape, 18 on six square bolts, the unnecessary woollen of 19 two ends, 20 Special vacuum frocks, 21 webs, 22 web holes
Specific embodiment
Present embodiment describes a kind of method to the processing of large aircraft rib class part by numerical control, process equipment is large-scale five coordinate high-speed gantry milling machines, and lathe possesses general-purpose platform.Woollen is aluminum alloy pretensioning plate, and width dimensions is greater than 1 meter, and length is greater than 4 meters, thickness 70mm; Part web thickness 1 ~ 3mm, stud and listrium thickness 2 ~ 3mm.This processing method is undertaken by following four stations:
Roughing first surface is vallecular cavity face, sees Fig. 1, Fig. 2.Clamping adopts both sides to compress mode, does not adopt special tooling.Prefabricated lower planes, two ends locating hole 3 (through hole) is wanted before roughing.Make some bolts hole 2, on the breach of the passing hole of position distribution on part web, both sides listrium 7 and the unnecessary woollen of two ends.Counter boring 1 on bolt hole, the degree of depth is as the criterion can sink to respective bolt.With all vallecular cavity webs 12 of layer mode of priority successively roughing, stop enough surpluses bottom vallecular cavity, make part web thickness and institute's made allowance thickness sum be not less than 10mm, even surplus 3mm is stayed in side.Except two ends, the retained diameter in all bolt hole positions is the cylinder process area 6 of Ф 25, and height maintains an equal level with woollen (what add man-hour for second web opens supporting role).Both sides listrium 7 all milling becomes nick shaped, and notch depth is to web position.The gap portions of both sides listrium retains web processes connecting plate 8, makes the web at listrium position, both sides keep connecting, becomes as a whole.The top margin of all studs 9, listrium 7 is not processed, and remains a height, and meanwhile, stud 9 mills out some horizontal, longitudinal breach 11, is roughly uniformly distributed, indentations bottom is higher than the top 3mm of part stud 9, gap width 20mm.Two ends clout is preserved for compressing.
Roughing second is rib datum level, sees Fig. 3.Clamping adopts both sides to compress mode, does not adopt special tooling.Processing sequence is counter boring 1 on both side edges plate height, both sides listrium breach, rib datum level 14, both sides listrium profile 16, bolt hole.All sites stays even roughing surplus.Equally, the gap portions reservation web processes connecting plate 8 of both sides listrium 7 is not processed.The milling of two ends clout to and rib datum level 14 contour.
The unnecessary woollen in both sides is separated by pincers worker after roughing is complete.
Fine finishining first surface is rib datum level, sees Fig. 3, Fig. 4.The clamping of this station adopts rib class component sharing clamping platform 15 to carry out.Workpiece 10 is located on shared clamping platform 15 with two ends locating hole 3, within six square bolts 18 sink to bolt hole 2 and compress.The order that interior six square bolts 18 compress is first middle, and rear both sides, to eliminate distortion of arching upward.After compression, in all, six square bolts are by 18 lower than rib datum level 14, can not cause interference to processing.The processing sequence of fine finishining first surface is shape 17 in both sides listrium 7 height, both sides listrium width, rib datum level 14, both sides listrium profile 16, both sides listrium.After fine finishining is complete, again revise two ends locating hole 3.Equally, the gap portions reservation web processes connecting plate 8 of both sides listrium 7 is not processed.
Fine finishining second is vallecular cavity face, sees Fig. 5, Fig. 6.The clamping of this station adopts Special vacuum frock 20.Workpiece 10 is located in Special vacuum frock 20 with two ends locating hole 3, within six square bolts 18 sink to bolt hole 2 and compress, and with vacuum suction.The processing sequence that fine finishining is second is shape 17, all studs 9 thickness, web hole 22 in both sides listrium 7 height, both sides listrium width, all studs 9 height, vallecular cavity web 12, both sides listrium, is finally separated passing hole 21 position on both sides listrium gap portions technique connecting plate 8 and web.
Claims (1)
1. a method for large aircraft rib class part by numerical control processing, the digital control processing of part is divided into roughing and two stages of fine finishining, is machined, it is characterized in that comprising following content by four stations:
1) roughing first surface is vallecular cavity face, clamping adopts both sides to compress mode, prefabricated lower planes is wanted before roughing, two ends locating hole, make multiple bolt hole, the passing hole of position distribution on part web, on the breach of both sides listrium and the unnecessary woollen of two ends, counter boring on bolt hole, the degree of depth is as the criterion can sink to respective bolt, with all vallecular cavities of layer mode of priority successively roughing, enough surpluses are stopped bottom vallecular cavity, the rigidity adding man-hour for second web keeps, part web thickness and institute's made allowance thickness sum is made to be not less than 10mm, even surplus is stayed in side, except two ends, the retained cylinder process area in all bolt hole positions, height maintains an equal level with woollen, playing a supportive role of man-hour is added for second web, listrium equal milling in both sides becomes nick shaped, notch depth is to web position, the gap portions of both sides listrium retains web processes connecting plate, the web at listrium position, both sides is made to keep connecting, become as a whole, all studs, the top margin of listrium is not processed, remain a height, simultaneously, stud mills out some breach be evenly distributed, indentations bottom is about 3mm higher than the top of part stud, two ends clout is preserved for compressing,
2) roughing second is rib datum level, clamping adopts both sides to compress mode, processing sequence is counter boring on both side edges plate height, both sides listrium breach, rib datum level, both sides listrium profile, bolt hole, all sites stays even roughing surplus, equally, the gap portions of both sides listrium retains web processes connecting plate and does not process, the milling of two ends clout to and rib datum level contour;
3) roughing complete after be separated the unnecessary woollen in both sides by pincers worker;
4) fine finishining first surface is rib datum level, the clamping of this station adopts rib class component sharing clamping platform to carry out, workpiece is located on shared clamping platform with two ends locating hole, within six square bolts sink to bolt hole compress, the order of bolt presses is first middle, rear both sides, after compressing, bolt will lower than rib datum level, the processing sequence of fine finishining first surface is both side edges plate height, both sides listrium width, rib datum level, both sides listrium profile, shape in the listrium of both sides, after fine finishining is complete, again two ends locating hole is revised, equally, the gap portions of both sides listrium retains web processes connecting plate and does not process,
5) fine finishining second is vallecular cavity face, the clamping of this station adopts Special vacuum frock, workpiece is located in Special vacuum frock with two ends locating hole, within six square bolts sink to bolt hole compress, and with vacuum suction, the processing sequence that fine finishining is second is shape, stud thickness, web hole in both side edges plate height, both sides listrium width, stud height, vallecular cavity web, both sides listrium, is finally separated the passing hole position on both sides listrium gap portions technique connecting plate and web.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310654567.6A CN103612076B (en) | 2013-12-04 | 2013-12-04 | Large aircraft rib class part by numerical control processing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310654567.6A CN103612076B (en) | 2013-12-04 | 2013-12-04 | Large aircraft rib class part by numerical control processing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103612076A CN103612076A (en) | 2014-03-05 |
| CN103612076B true CN103612076B (en) | 2016-01-20 |
Family
ID=50162810
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310654567.6A Active CN103612076B (en) | 2013-12-04 | 2013-12-04 | Large aircraft rib class part by numerical control processing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103612076B (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103934492A (en) * | 2014-04-04 | 2014-07-23 | 中航沈飞民用飞机有限责任公司 | Milling method capable of evenly releasing milling stress of skin machine |
| CN104259774B (en) * | 2014-09-09 | 2017-02-15 | 黄河科技学院 | Plane wing titanium alloy thin-wall web efficient numerical control machining technology |
| CN106623990A (en) * | 2017-01-24 | 2017-05-10 | 天津航天长征火箭制造有限公司 | Accurate machining method for large-diameter aluminum alloy non-uniform section frame ring |
| CN107617853A (en) * | 2017-08-23 | 2018-01-23 | 成都飞机工业（集团）有限责任公司 | A kind of processing method of stainless sheet steel part thickness control |
| CN111203707A (en) * | 2018-11-22 | 2020-05-29 | 成都飞机工业（集团）有限责任公司 | Titanium alloy sheet machining deformation control method |
| CN110238606A (en) * | 2019-06-18 | 2019-09-17 | 成都飞机工业（集团）有限责任公司 | A kind of processing method of the open vallecular cavity of web part |
| CN110480284B (en) * | 2019-09-17 | 2021-04-27 | 成都飞机工业（集团）有限责任公司 | Processing method of web plate notch structure |
| CN113600878A (en) * | 2021-08-10 | 2021-11-05 | 沈阳华天航空机械有限公司 | Numerical control machining method for airplane wide-rib parts |
| CN116551335B (en) * | 2023-07-07 | 2023-10-03 | 成都飞机工业（集团）有限责任公司 | L-shaped part machining method and L-shaped part |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0518435D0 (en) * | 2005-09-09 | 2005-10-19 | Airbus Uk Ltd | Improvements in computer-aided design of a component |
| CN100513064C (en) * | 2007-09-11 | 2009-07-15 | 西安飞机工业（集团）有限责任公司 | Numerically controlled processing method for plane wing rib beam part |
| 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 |
| CN101905343A (en) * | 2010-08-05 | 2010-12-08 | 西安飞机工业（集团）有限责任公司 | Digital control processing method of thin-wall T-shaped rib |
| CN102229056A (en) * | 2011-06-14 | 2011-11-02 | 西安飞机工业（集团）有限责任公司 | Method for pressing and machining numerical control machining part |
-
2013
- 2013-12-04 CN CN201310654567.6A patent/CN103612076B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN103612076A (en) | 2014-03-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103612076B (en) | Large aircraft rib class part by numerical control processing method | |
| CN107052715B (en) | A kind of large size Integral Wing Panel numerical-control processing method | |
| CN201544052U (en) | Adjustable multi-layer drilling tool | |
| CN105081682A (en) | Machining process method for complex support parts | |
| CN103056614B (en) | Method for processing curved surface sector-shaped section frame | |
| CN108044399A (en) | A kind of base of digital-controlled machine tool damping device | |
| CN103056599B (en) | The preparation method of the shaping loose piece of a kind of precision many continuous castings blade wax mould blade | |
| CN204748012U (en) | Double multiway type machining center | |
| CN207464785U (en) | A kind of double Z axis numerically-controlled machine tools of double main shafts of achievable automatic tool changer | |
| CN207077057U (en) | Electrode integration module | |
| CN203343760U (en) | Spindle sleeve finish machining jig | |
| CN201399526Y (en) | Standing stamping machine capable of being arranged and integrated | |
| CN102728878B (en) | Numerical control curved surface profile processing Z-shaped process connection method | |
| CN205363248U (en) | Turning and milling lathe | |
| CN203792044U (en) | Fixing tool for machining conductors | |
| CN203649407U (en) | Long plug pin lathe | |
| CN208303981U (en) | A kind of five axis carving and milling machines | |
| CN203185007U (en) | Mould angle machining tool | |
| CN102430899A (en) | Numerical control machining method for support parts | |
| CN204621030U (en) | Milling equipment inserted by a kind of sand mold | |
| CN207057633U (en) | A kind of more main spindle numerical control vertical lathes of thin space | |
| CN207272680U (en) | Numerical control high-precision car, rolling all-in-one machine | |
| CN206527574U (en) | A kind of numerical controlled machinery moves feeder assembly with cutter | |
| CN215699206U (en) | Shield body segmentation welded fastening frock of adjustable difference in height | |
| CN104339185A (en) | Sectional machining structure of large stamping die set |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
|
| CP03 | Change of name, title or address | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210611 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |
|
| TR01 | Transfer of patent right |