CN105965217A - Method for machining and shaping eight joint parts synchronously - Google Patents
Method for machining and shaping eight joint parts synchronously Download PDFInfo
- Publication number
- CN105965217A CN105965217A CN201610531710.6A CN201610531710A CN105965217A CN 105965217 A CN105965217 A CN 105965217A CN 201610531710 A CN201610531710 A CN 201610531710A CN 105965217 A CN105965217 A CN 105965217A
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- Prior art keywords
- joint part
- joint
- machining
- processing
- shaping
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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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- 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
Abstract
The invention discloses a method for machining and shaping eight joint parts synchronously and belongs to the field of aircraft part manufacturing. According to the technical scheme, multi-piece one-step centralized machining and shaping are conducted on important connecting pieces, of the same structure, of large series aircrafts, and the requirement of digitalized mass production is met. The method has the beneficial effects that one-step machining and shaping are conducted on the joint parts through control over the links such as procedure detailing and simplification and process optimization, the production cycle is shortened, cost input is reduced, and thus the requirements of three-dimensional digitalization process design, site visualization and numerical control machining for mass production of MBD are met; in order to boost the three-dimensional digitalization process design and site visualization technologies of joint part MBD, traditional singular part machining patterns are eliminated, the product manufacturing cycle is shortened, repeated technological processes are reduced, and human errors are effectively avoided; multiple systems are integrated to provide instructions to produce the joint parts accurately, conveniently and rapidly in the production process; product safety and quality are improved; and the requirement of mass production of aircrafts is met.
Description
Technical field
The invention belongs to aircraft joint part number processing, manufacture field, relate to big-and-middle-sized series aircraft phase
The isostructural series-produced requirement of ordinary couplings part.
Background technology
Joint part is the of paramount importance part of aircraft, subjects each parts of aircraft and is connected with each other and stress effect,
Joint part quantity required needed for aircraft, kind are the most, the most each zero, the size shape of assembly, structure
Form, loading conditions, mode of transfer force etc. are the most different；The present invention is mainly identical to dimensional structure
Joint part proposes processing method simultaneously, it is possible to realizes the concentrated processing manufacture simultaneously of many parts, sufficiently meets
Batch production requirement, advances the three-dimensional digital technological design of MBD and visualization of presence technology applied research and reality
Execute, it is achieved that product design, technological design, the concurrent job of Fixture Design, shorten the product manufacturing cycle,
Decrease process of repeatedly assembling, human error can be prevented effectively from；Integrated by multiple systems, meets MBD
Three-dimensional digital technological design and the requirement of visualization of presence technology, make the Information Number of design, technique, production
More unobstructed according to circulation；In process of production by three-dimensional digital technological design Instructing manufacture accurate, convenient；
It is effectively guaranteed the quality of product；Process upstream letter is provided for systems such as the quality management of enterprise, production managemenies
Breath is supported.Solid foundation is established for enhancing the core competitiveness of enterprises.
Summary of the invention
Goal of the invention:
For advancing three-dimensional digital technological design and the visualization of presence technology of joint part MBD, eliminate tradition single
The part cooked mode of one, shortens the product manufacturing cycle, decreases technical process repeatedly, is prevented effectively from artificial
Mistake；Integrated by multiple systems, instructs joint part production the most accurate, convenient；Improve
Product safety, quality；Meet the requirement of aircraft batch production.
Technical scheme:
A kind of 8 joint parts processing molding method simultaneously, it is characterised in that described 8 joint parts are divided into
Left member and two parts of right member, left member is by the identical joint part 1 of structure, joint part 22, joint zero
Part 33, joint part 44 form, right member by the identical joint part 55 of structure, joint part 66,
Joint part 77, joint part 88 form, and described left member, right member collectively constitute a machining cell；Should
The enforcement step of method is as follows:
(1) materials behavior and the dimensions of blank needed for 8 joint parts are determined；
(2) Digit Control Machine Tool using more than three coordinates implements processing, and it determines the program of also processing datum such as
Under:
The first step: processing 9-datum level；
Second step: processing 10-front boss, hole, curved surface and profile；
3rd step: by joint part 1, joint part 22, joint part 33, joint part 44, connect
Totally 8 the part cuttings of head part 55, joint part 66, joint part 77, joint part 88 separate,
Mend simultaneously and bore side opening；
4th step: pincers worker carries out surfacing.
Beneficial effect:
Advantages of the present invention: can meet and advance and expand the development of MBD technology, utilize simulation video, AO
With three-dimensional work step guide field, it is analyzed according to processing, the assembling situation of product structure simultaneously, it is ensured that quality,
Security reliability, practicality, efficiency, implement joint part machine-shaping simultaneously to product structure.Pass through
The present invention disclosure satisfy that production technology and the processing of high-efficiency, the manufacture means of advanced person.
Same tip part has been carried out reasonably distributing by the present invention, by refinement, simple flow and optimization technique
Deng Absent measures, butt joint part is processed and formed at one time simultaneously, shortens the production cycle, decreases cost
Put into, thus meet the three-dimensional digital technological design of MBD, visualization of presence and numerical control manufacturing batch requirement,
Improve processing, the assembly precision of part, reduce Product processing difficulty, it is easy to the popularization of similar products.
Disclosure satisfy that joint part production the most accurate, convenient；Improve product safety, quality；Lifting flies
The ability of machine batch production.
Figure of description
Fig. 1 is 8 joint part schematic diagram front views of one-shot forming；
Fig. 2 is 8 joint part schematic diagram left views of one-shot forming；
Fig. 3 is former single-piece work joint part schematic diagram front view；
Fig. 4 is former single-piece work joint part schematic diagram left view；
Wherein: 1,2,3,4 is left member joint part；5,6,7,8 is right member joint part, and 9 are
Joint part datum level；10 is joint part front；11 is former single-piece work joint part schematic diagram front view；
12 is former single-piece work joint part schematic diagram left view；Chain-dotted line portion is boule portions.
Detailed description of the invention
Below present configuration is described in further detail
First molding while that " joint part machine-shaping simultaneously " can assembling multiple same structure size parts,
Thus meet part every dimensional accuracy coherence request, it is simple to reduce part machinery difficulty of processing and realize numeral
Change, the requirement of mechanization, it is possible to sufficiently improve processing, assembly precision, the minimizing processing work of one-tenth several times
Time.Aircraft support part was by separately machined in the past, and the most directly impact is the cycle of aircraft manufacturing, root
According to the construction features of this part, open die forging or pretensioning plate can be used as blank, carry out typesetting as shown in Figure 1,
Selected reference, allowance, cut size, false boss etc., work out 8 one-shot forming digital process rule
Journey,
First determine materials behavior and the dimensions of blank needed for this part, use the numerical control machine of more than three coordinates
Bed can implement processing, determines and its program of processing datum is as follows:
The first step: processing 9-datum level；
Second step: processing 10-front boss, hole, curved surface and profile；
3rd step: by joint part 1, joint part 22, joint part 33, joint part 44, connect
Totally 8 the part cuttings of head part 55, joint part 66, joint part 77, joint part 88 separate,
Mend simultaneously and bore side opening；
4th step: pincers worker carries out joint part surfacing.
Claims (1)
1. 8 joint parts processing molding method simultaneously, it is characterised in that described 8 joints zero
Part is divided into left member and two parts of right member, and left member is by the identical joint part one (1) of structure, joint
Part two (2), joint part three (3), joint part four (4) form, and right member is identical by structure
Joint part five (5), joint part six (6), joint part seven (7), joint part eight (8)
Composition, described left member, right member collectively constitute a machining cell；The method to realize step as follows:
(1) materials behavior and the dimensions of blank needed for 8 joint parts are determined；
(2) Digit Control Machine Tool using more than three coordinates implements processing, and it determines the program of also processing datum such as
Under:
The first step: processing 9-datum level；
Second step: processing 10-front boss, hole, curved surface and profile；
3rd step: by joint part one (1), joint part two (2), joint part three (3), joint
Part four (4), joint part five (5), joint part six (6), joint part seven (7), connect
Totally 8 the part cuttings of head part eight (8) separate, and mend simultaneously and bore side opening；
4th step: pincers worker carries out surfacing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610531710.6A CN105965217A (en) | 2016-07-06 | 2016-07-06 | Method for machining and shaping eight joint parts synchronously |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610531710.6A CN105965217A (en) | 2016-07-06 | 2016-07-06 | Method for machining and shaping eight joint parts synchronously |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105965217A true CN105965217A (en) | 2016-09-28 |
Family
ID=56954804
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610531710.6A Pending CN105965217A (en) | 2016-07-06 | 2016-07-06 | Method for machining and shaping eight joint parts synchronously |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105965217A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110877188A (en) * | 2018-09-05 | 2020-03-13 | 中航贵州飞机有限责任公司 | Machining method for airplane box part |
| CN112935707A (en) * | 2019-12-10 | 2021-06-11 | 中航贵州飞机有限责任公司 | Machining method for airplane support type parts |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202763486U (en) * | 2012-07-10 | 2013-03-06 | 浙江巨峰汽车零部件有限公司 | Processing clamping device for automobile parts |
| CN103538715A (en) * | 2013-10-14 | 2014-01-29 | 航天特种材料及工艺技术研究所 | Composite material pi-type lug interface and integral co-curing forming method |
| US20140353426A1 (en) * | 2013-05-29 | 2014-12-04 | Airbus Operations (Sas) | Aircraft comprising an improved connection zone between a front beam and a front lower fuselage section |
| CN104889777A (en) * | 2015-04-29 | 2015-09-09 | 成都爱乐达航空设备制造有限公司 | Multi-surface machining device of aviation aluminum plate type part and machining method |
| CN105414903A (en) * | 2015-12-23 | 2016-03-23 | 常熟市淼泉压缩机配件有限公司 | Improved technology for processing small-sized thin plate type part |
-
2016
- 2016-07-06 CN CN201610531710.6A patent/CN105965217A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202763486U (en) * | 2012-07-10 | 2013-03-06 | 浙江巨峰汽车零部件有限公司 | Processing clamping device for automobile parts |
| US20140353426A1 (en) * | 2013-05-29 | 2014-12-04 | Airbus Operations (Sas) | Aircraft comprising an improved connection zone between a front beam and a front lower fuselage section |
| CN103538715A (en) * | 2013-10-14 | 2014-01-29 | 航天特种材料及工艺技术研究所 | Composite material pi-type lug interface and integral co-curing forming method |
| CN104889777A (en) * | 2015-04-29 | 2015-09-09 | 成都爱乐达航空设备制造有限公司 | Multi-surface machining device of aviation aluminum plate type part and machining method |
| CN105414903A (en) * | 2015-12-23 | 2016-03-23 | 常熟市淼泉压缩机配件有限公司 | Improved technology for processing small-sized thin plate type part |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110877188A (en) * | 2018-09-05 | 2020-03-13 | 中航贵州飞机有限责任公司 | Machining method for airplane box part |
| CN112935707A (en) * | 2019-12-10 | 2021-06-11 | 中航贵州飞机有限责任公司 | Machining method for airplane support type parts |
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160928 |