CN105081677A - Machining method of intensive rib-structure integral panel parts - Google Patents
Machining method of intensive rib-structure integral panel parts Download PDFInfo
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- CN105081677A CN105081677A CN201410188571.2A CN201410188571A CN105081677A CN 105081677 A CN105081677 A CN 105081677A CN 201410188571 A CN201410188571 A CN 201410188571A CN 105081677 A CN105081677 A CN 105081677A
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- intensive
- machining
- integral panel
- natrual ageing
- roughing
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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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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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
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention belongs to the technical field of machining, and particularly relates to a machining method of intensive rib-structure integral panel parts. The machining method of the intensive rib-structure integral panel parts is characterized by comprising the following steps of rough material blanking, fiber breaking, natural aging, rough machining, natural aging, semi finish machining, natural aging, online detecting, numerical control program correcting, finish machining, size detecting, follow-up process and delivery. According to the machining method disclosed by the invention, the deformation is reduced to a large extent, the batch production state of parts is stable and is enabled to be within a receiving range of an engineering drawing or an engineering design, the line production of machining multiple parts on a single machine tool can be realized, the production efficiency is greatly increased, and the reproducibility of a technology is ensured.
Description
Technical field
The invention belongs to Machining Technology field, particularly relate to a kind of integral panel class method of processing parts.
Background technology
One side profile, it is one of important feature adopted in aircraft development that the integrated machine of single-sided structure form adds wall plate parts, is used for the key positions such as the wing of aircraft.Large-scale wallboard due to size large, processing clearance very high (95% material removing rate), it is very important for carrying out control to the distortion in process.In existing process continuous process, integrated machine adds wall-board product by surplus removal several times, open form chamber slot machining, layering processing and frock clamping position, material internal stress and traditional processing proposal machining stress fully do not discharge, maximum distortion (warpage, torsion etc.) can not be there is in the short time, but Stress Release after placing a period of time remnants, part status will there will be moderate finite deformation, to be there is larger stress in confined state, affect aeronautical product quality.
The content of invention
The object of invention
When utilizing the minimum use Special processing tooling of prior art condition and equipment, redesign a set of reliably integral wall plate processing scheme.
The technical scheme of invention
Intensive bead structures integral panel class method of processing parts, the step of this method is as follows:
Woollen blanking → fiber destruction → natrual ageing → roughing → natrual ageing → semifinishing → natrual ageing → on-line checkingi → numerical control program correction → fine finishining → dimension control → subsequent handling → payment.
Described fiber destruction is: 45 ° of staggered milling grooves are opened on woollen surface.
Described natrual ageing is: the time is 14 days, ensures that part has three supporting surfaces at least, turn-over natrual ageing after the 8th day during placement.
Described roughing requires to carry out twice, and first time stays 8 to 15mm surplus apart from part noumenon, and second time 3 to 5mm, ensures after roughing that profile both sides surplus is consistent.
Between described per pass tooling step, time interval controls is in 24 hours.
The effect of invention
By starting with from the elimination of raw material (laminated plate material) stress, will the Stress Release of part deformation (warpage, torsion etc.) be caused to be reduced to minimum before processing.Again by the reasonable setting of process program, and control in conjunction with on-line checkingi and timeliness, overcome the large and wild effect of the machining deformation of wall plate parts, the process program of wall plate parts is fixed up, the scheme of less technologist determines the formulation time, enhance productivity, and improve product quality and qualification rate.
Concrete implementing process flow process is implemented according to this programme completely, experiment effect is well made, deflection declines to a great extent, parts batch production status is stablized, can ensure in the range of receiving of engineering drawing or design, can single lathe more than one piece continuous productive process, substantially increase production efficiency, and ensure the reproducibility of technique.
Detailed description of the invention
Intensive bead structures integral panel class method of processing parts, this method process conditions are as follows:
Process equipment: numerical control five-axis machine lathe (high speed milling lathe);
Tooling device: vacuum suction frock (plane and External Shape profile each a set of) and clamp jig;
Software merit rating: line processing inspection software PowerInspector and CATIAV5;
Engineering drawing requires: web and rib thickness deviation are ± 0.15mm, and rib height tolerance is ± 0.2mm, and profile rigging position profile tolerance requires 0.5mm, and warpage is not more than 5mm, has not allowed to agitate;
Woollen is selected: its woollen adopts full-scale large-scale pre-stretched aluminum plate material.
Intensive bead structures integral panel class method of processing parts, the step of this method is as follows:
Woollen blanking → fiber destruction → natrual ageing → roughing → natrual ageing → semifinishing → natrual ageing → on-line checkingi (vacuum suction frock and part semi-finished product) → numerical control program correction → fine finishining → dimension control → subsequent handling → payment.
This programme for after fiber destruction, roughing, after roughing and semifinishing, part processing turnover process time of placing and place the control and requirement that require to rationalize, main contents requirement is as follows:
This programme fiber destruction adopts along the staggered milling groove of machine direction 45 °, tradition is opened measuring tank chamber, Dayu mode and is compared relatively, and removal amount reduces, and release stress effect is suitable, version for any rib dense degree is all applicable, and staggered groove schematic diagram is as Fig. 1; Because part both sides metal removal rate is different, and it is less according to the woollen size that design is given, increase without stud face allowance to greatest extent, and adopt woollen fiber destruction to carry out broken line (broken line angle is less than 45 °) to stud face, broken line dodges part body, and symmetry arranges as far as possible.
Roughing requires to carry out twice, and first time stays 8 to 15mm surplus apart from part noumenon, and second time 3 to 5mm, ensures after roughing that profile both sides surplus is consistent.
After removing surplus fiber destruction, roughing, between roughing and semifinishing operation, the enough weathering time to be ensured, natural aging time is 14 days (at least three supporting surfaces, turn-over natrual ageing after 8th day), between per pass tooling step, time interval controls is in 24 hours.
The parked state such as part is processed, to be checked need control modes of emplacement and time.Part parked state need lie on sleeper (at least three supporting surfaces are forbidden after fine finishining being placed on sleeper) or dull and stereotyped (or special) transfer car(buggy); Vacuum suction frock adopts full-scale profile frock, during fine finishining structural plane, Single Maintenance is carried out to vacuum suction frock profile, according to theoretical profile numerical programming program, fine finishining is carried out to frock profile, processing capacity controls within 0.20mm thickness, and during guarantee fine finishining, frock profile is in good condition.
Profile and inner chamber fine finishining will complete several times, will check the deformation of technique secondary support surface before each processing, if there is distortion to want renovation technique supplemental support; Need after Finishing Parts Machining to carry out on-line measurement by under part Working position (former lathe) vacuum adsorption state and free state to stud face profile, judge mismachining tolerance and part deformation situation, and with online Survey Software analysis, according to analysis result, final step work step program is revised and adjusted, carry out last fine finishining (correction) processing.
Dimension control (avoid freely place under, be out of shape under Action of Gravity Field) must be completed in 7 days after part processing.
This programme has carried out more than one piece confirmatory experiment by selecting certain fixed wing aircraft fuel tank wallboard typical part as experimental piece.Concrete implementing process flow process is implemented according to this programme completely, experiment effect is well made, deflection declines to a great extent, parts batch production status is stablized, can ensure in the range of receiving of engineering drawing or design, can single lathe more than one piece continuous productive process, substantially increase production efficiency, and ensure the reproducibility of technique.
Accompanying drawing explanation
Fig. 1 broken line schematic diagram;
Fig. 2 part profile vacuum suction frock form schematic diagram;
Fig. 3 part is view in profile vacuum suction frock.
Claims (3)
1. intensive bead structures integral panel class method of processing parts, it is characterized in that, the step of this method is as follows:
Woollen blanking → fiber destruction → natrual ageing → roughing → natrual ageing → semifinishing → natrual ageing → on-line checkingi → numerical control program correction → fine finishining → dimension control → subsequent handling → payment;
Described fiber destruction is: 45 ° of staggered milling grooves are opened on woollen surface;
Described natrual ageing is: the time is 14 days, ensures that part has three supporting surfaces at least, turn-over natrual ageing after the 8th day during placement.
2. intensive bead structures integral panel class method of processing parts as claimed in claim 1, it is characterized in that, described roughing requires to carry out twice, and first time stays 8 to 15mm surplus apart from part noumenon, second time 3 to 5mm, ensures after roughing that profile both sides surplus is consistent.
3. intensive bead structures integral panel class method of processing parts as claimed in claim 1, it is characterized in that, between described per pass tooling step, time interval controls is in 24 hours.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410188571.2A CN105081677A (en) | 2014-05-07 | 2014-05-07 | Machining method of intensive rib-structure integral panel parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410188571.2A CN105081677A (en) | 2014-05-07 | 2014-05-07 | Machining method of intensive rib-structure integral panel parts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105081677A true CN105081677A (en) | 2015-11-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410188571.2A Pending CN105081677A (en) | 2014-05-07 | 2014-05-07 | Machining method of intensive rib-structure integral panel parts |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105382312A (en) * | 2015-11-26 | 2016-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Finish machining weight control method for two-sided thin-wall numerical control milling machine workpiece |
| CN111112957A (en) * | 2020-01-07 | 2020-05-08 | 中国航空工业集团公司北京航空精密机械研究所 | Machining method for reducing deformation of hollow aluminum alloy part |
| CN111531333A (en) * | 2020-05-11 | 2020-08-14 | 三河建华高科有限责任公司 | Method for processing special-shaped thin-wall shell part |
Citations (4)
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|---|---|---|---|---|
| US20030054182A1 (en) * | 1998-09-11 | 2003-03-20 | The Boeing Company | Method for coating faying surfaces of aluminum-alloy components and faying surfaces coated thereby |
| CN101670462A (en) * | 2009-09-29 | 2010-03-17 | 江西洪都航空工业集团有限责任公司 | Wall plate processing technology for hyperboloid thin wall |
| CN101988146A (en) * | 2009-07-31 | 2011-03-23 | 中国商用飞机有限责任公司 | Creep age forming method of integral wing panel |
| CN103192266A (en) * | 2013-04-03 | 2013-07-10 | 哈尔滨理工大学 | Extruding and rolling composite forming device and method of integral panel skin with ribs |
-
2014
- 2014-05-07 CN CN201410188571.2A patent/CN105081677A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030054182A1 (en) * | 1998-09-11 | 2003-03-20 | The Boeing Company | Method for coating faying surfaces of aluminum-alloy components and faying surfaces coated thereby |
| CN101988146A (en) * | 2009-07-31 | 2011-03-23 | 中国商用飞机有限责任公司 | Creep age forming method of integral wing panel |
| CN101670462A (en) * | 2009-09-29 | 2010-03-17 | 江西洪都航空工业集团有限责任公司 | Wall plate processing technology for hyperboloid thin wall |
| CN103192266A (en) * | 2013-04-03 | 2013-07-10 | 哈尔滨理工大学 | Extruding and rolling composite forming device and method of integral panel skin with ribs |
Non-Patent Citations (1)
| Title |
|---|
| 张安顺等: "超大型壁板类零件加工变形控制技术", 《航空制造技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105382312A (en) * | 2015-11-26 | 2016-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Finish machining weight control method for two-sided thin-wall numerical control milling machine workpiece |
| CN111112957A (en) * | 2020-01-07 | 2020-05-08 | 中国航空工业集团公司北京航空精密机械研究所 | Machining method for reducing deformation of hollow aluminum alloy part |
| CN111531333A (en) * | 2020-05-11 | 2020-08-14 | 三河建华高科有限责任公司 | Method for processing special-shaped thin-wall shell part |
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Application publication date: 20151125 |