CN103612076A - Method for numerical control machining of large aircraft rib parts - Google Patents
Method for numerical control machining of large aircraft rib parts Download PDFInfo
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- CN103612076A CN103612076A CN201310654567.6A CN201310654567A CN103612076A CN 103612076 A CN103612076 A CN 103612076A CN 201310654567 A CN201310654567 A CN 201310654567A CN 103612076 A CN103612076 A CN 103612076A
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- 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
Abstract
A method for numerical control machining of large aircraft rib parts comprises a rough machining stage and a finish machining stage and is finished through four machining stations. The first rough machining face is a groove cavity face, rough machining of all of groove cavities is performed in a layer priority mode, and enough allowances are reserved at the bottoms of the groove cavities. The second rough machining face is a rib datum plane, and even rough machining allowances are reserved at all of positions. The finish machining face is a rib datum plane, positioning holes at two ends are re-adjusted after finish machining is finished, the second finish machining face is a groove cavity face, and finally process connecting plates at the gap positions of two-side edge plates and through hole positions of a web plate are separated.
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, and 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, simple in structure; Another side complex structure, conventionally 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 is manufactured very important to aircraft development.Especially along with the maximization of aircraft development, rib class part is maximization, complicated gradually also, has occurred the manufacture difficult problem that some are new, and main manifestations is the phenomenons such as distortion is large, clamping difficulty is large, cutting chatter is serious, working (machining) efficiency is low.Particularly the width dimensions when rib is greater than 1 meter, and when length is greater than 4 meters, structural strain's amount increases, and especially the distortion of arching upward at part middle 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, and 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, by four stations, is machined, and it is characterized in that comprising following content:
1) roughing first surface is vallecular cavity face, clamping adopts both sides to compress mode, before roughing, want prefabricated upper lower plane, two ends locating hole, make a plurality of bolts hole, position distribution is passed through hole on part web, on the unnecessary woollen of the breach of both sides listrium and 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 successively roughing of layer mode of priority, enough surpluses (rigidity that adds man-hour for second web keeps) are stopped in vallecular cavity bottom, make part web thickness and institute's made allowance thickness sum be not less than 10mm, even surplus is stayed in side, except two ends, the retained cylinder process area in all bolts hole position, height maintains an equal level (for second web, adding the supporting role of opening in man-hour) with woollen, 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, make the web of both side edges board position keep connecting, become as a whole, all studs, the top surplus of listrium is not processed, remain a height, simultaneously, on stud, mill out some breach that are evenly distributed, breach bottom is higher than the about 3mm in top of part stud, two ends clout is preserved for compressing,
2) second of roughing 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 does not process, the milling of two ends clout to and rib datum level contour;
3) roughing complete after by the unnecessary woollen in the separated both sides of 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, with interior six square bolts, sinking to bolt hole compresses, the order that bolt compresses is first middle, rear both sides, after compressing, bolt will be 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 revise two ends locating hole, equally, the gap portions of both sides listrium retains web processes connecting plate and does not process,
5) second of fine finishining 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, with interior six square bolts, sinking to bolt hole compresses, and with vacuum suction, the processing sequence that fine finishining is second is shape in both side edges plate height, both sides listrium width, stud height, vallecular cavity web, both sides listrium, stud thickness, web hole, on last separated both sides listrium gap portions technique connecting plate and web, passes through position, hole.
Beneficial effect of the present invention is, by above process, effectively solved the problems such as large aircraft rib class part bulk deformation in digital control processing is large, clamping is difficult, Hanging sectionally is processed cutting chatter, working (machining) efficiency is low, realized 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 surplus 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: counter boring on 1 bolt hole, 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 rib parts, 11 stud top technical gaps, 12 vallecular cavity webs, 13 stud top surpluses, 14 rib datum levels, 15 rib class component sharing clamping platforms, 16 listrium profiles, shape in 17 listriums, six square bolts in 18, the unnecessary woollen of 19 two ends, 20 Special vacuum frocks, on 21 webs, pass through hole, 22 web holes
Specific embodiment
The present embodiment has been described a kind of method to the processing of large aircraft rib class part by numerical control, and 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.Before roughing, want prefabricated upper lower plane, two ends locating hole 3(through hole).Make some bolts hole 2, on the breach that passes through hole, both sides listrium 7 and the unnecessary woollen of two ends of position distribution on part web.On bolt hole, counter boring 1, and the degree of depth is as the criterion can sink to respective bolt.With all vallecular cavity webs 12 of successively roughing of layer mode of priority, enough surpluses are stopped in vallecular cavity bottom, make part web thickness and institute's made allowance thickness sum be not less than 10mm, and even surplus 3mm is stayed in side.Except two ends, the retained diameter in all bolts hole position is the cylinder process area 6 of Ф 25, and height maintains an equal level (for second web, adding the supporting role of opening in man-hour) with woollen.The equal milling of both sides listrium 7 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 of both side edges board position keep connecting, and becomes as a whole.The top surplus of all studs 9, listrium 7 is not processed, and remains a height, meanwhile, mills out some horizontal, longitudinal breach 11 on stud 9, is roughly uniformly distributed, and breach bottom is higher than the top 3mm of part stud 9, gap width 20mm.Two ends clout is preserved for compressing.
Second of roughing 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 of both sides listrium 7 reservation web processes connecting plate 8 is not processed.The milling of two ends clout to and rib datum level 14 contour.
After roughing is complete by the unnecessary woollen in the separated both sides of pincers worker.
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, sinks to bolt hole 2 compress with interior six square bolts 18.The order that interior six square bolts 18 compress is first middle, and rear both sides, to eliminate the distortion of arching upward.After compression, all interior six square bolts lower than rib datum level 14, can not cause interference to processing by 18.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 of both sides listrium 7 reservation web processes connecting plate 8 is not processed.
Second of fine finishining 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, and with interior 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 in both sides listrium 7 height, both sides listrium width, all studs 9 height, vallecular cavity web 12, both sides listrium, all studs 9 thickness, web hole 22, on last separated both sides listrium gap portions technique connecting plate 8 and web, passes through 21 positions, hole.
Claims (1)
1. the method that large aircraft rib class part by numerical control is processed, the digital control processing of part is divided into roughing and two stages of fine finishining, by four stations, is machined, and it is characterized in that comprising following content:
1) roughing first surface is vallecular cavity face, clamping adopts both sides to compress mode, before roughing, want prefabricated upper lower plane, two ends locating hole, make a plurality of bolts hole, position distribution is passed through hole on part web, on the unnecessary woollen of the breach of both sides listrium and 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 successively roughing of layer mode of priority, enough surpluses (rigidity that adds man-hour for second web keeps) are stopped in vallecular cavity bottom, make part web thickness and institute's made allowance thickness sum be not less than 10mm, even surplus is stayed in side, except two ends, the retained cylinder process area in all bolts hole position, height maintains an equal level (for second web, adding the supporting role of opening in man-hour) with woollen, 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, make the web of both side edges board position keep connecting, become as a whole, all studs, the top surplus of listrium is not processed, remain a height, simultaneously, on stud, mill out some breach that are evenly distributed, breach bottom is higher than the about 3mm in top of part stud, two ends clout is preserved for compressing,
2) second of roughing 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 does not process, the milling of two ends clout to and rib datum level contour;
3) roughing complete after by the unnecessary woollen in the separated both sides of 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, with interior six square bolts, sinking to bolt hole compresses, the order that bolt compresses is first middle, rear both sides, after compressing, bolt will be 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 revise two ends locating hole, equally, the gap portions of both sides listrium retains web processes connecting plate and does not process,
5) second of fine finishining 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, with interior six square bolts, sinking to bolt hole compresses, and with vacuum suction, the processing sequence that fine finishining is second is shape in both side edges plate height, both sides listrium width, stud height, vallecular cavity web, both sides listrium, stud thickness, web hole, on last separated both sides listrium gap portions technique connecting plate and web, passes through position, hole.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN104259774A (en) * | 2014-09-09 | 2015-01-07 | 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 |
| 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 |
| CN110480284A (en) * | 2019-09-17 | 2019-11-22 | 成都飞机工业（集团）有限责任公司 | A kind of web notch arrangement processing method |
| 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 |
| 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 |
| CN116551335A (en) * | 2023-07-07 | 2023-08-08 | 成都飞机工业（集团）有限责任公司 | L-shaped part machining method and L-shaped part |
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| 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 |
| CN104259774A (en) * | 2014-09-09 | 2015-01-07 | 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 |
| CN110480284A (en) * | 2019-09-17 | 2019-11-22 | 成都飞机工业（集团）有限责任公司 | A kind of web notch arrangement processing method |
| 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 |
| CN116551335A (en) * | 2023-07-07 | 2023-08-08 | 成都飞机工业（集团）有限责任公司 | L-shaped part machining method and L-shaped part |
| 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 |
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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. |
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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. |