CN104816837A - Aluminum alloy skin digital assembly method - Google Patents
Aluminum alloy skin digital assembly method Download PDFInfo
- Publication number
- CN104816837A CN104816837A CN201510230174.1A CN201510230174A CN104816837A CN 104816837 A CN104816837 A CN 104816837A CN 201510230174 A CN201510230174 A CN 201510230174A CN 104816837 A CN104816837 A CN 104816837A
- Authority
- CN
- China
- Prior art keywords
- covering
- skin
- knock hole
- aluminum alloy
- riveted joint
- 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.)
- Pending
Links
Landscapes
- Insertion Pins And Rivets (AREA)
Abstract
The invention relates to an aluminum alloy skin digital assembly method, and belongs to the field of aircraft manufacturing. In the prior art, when skin is assembled, the position is adjusted by workers according to experience, so that assembly accuracy is low; when the position of skin is not accurate, the skin and a framework will be staggered in shape, moreover, because of the shape error of the skin, riveting deformation is big, and the appearance of an aircraft body is poor; the quality of butt joints of the skin is poor; manual lineation is big in error and low in repeat accuracy and efficiency; when no tools are provided, allowance is polished manually on the site of riveting, the efficiency is low, the quality is poor, and the noise is high. According to the aluminum alloy skin digital assembly method, the digital technological lug positioning technology is adopted, skin can be clamped in place at a time, and repeated adjustment is not needed; besides technological lugs, the edges of the skin are net edges, and on-site allowance polishing is not needed; the assembly efficiency and the assembly quality can be greatly improved.
Description
Technical field
The invention belongs to aircraft manufacturing field, relate to a kind of aluminum alloy outer cover numeric terminal method particularly.
Background technology
Before use numerical DC speed technology, aluminum alloy outer cover does not have technical lug knock hole; Cover edges retains the surplus of one fixed width outward; At riveted joint erecting yard, lead-covering is not accurately located in assembly tooling, and workman adjusts covering position by rule of thumb, and the postpone of accreditation adjusted position, tightens covering and fuselage framework with clamp, the rope that rises, clamp, join and get out rivet hole, plugs spring pin location; Mark edge line by hand, determine the surplus that will remove, then pull down covering, on-the-spot manual grinding falls covering surplus.
If covering is not accurately located, with workman's experience adjustments position, assembly precision is low; Skin shape and frame configuration dislocation will definitely not caused in covering position, add the shape error of covering itself, and cause rivet deformation large, fuselage presentation quality is poor; Covering butt seam is of poor quality; Manual line error is large, and repeatable accuracy is low, and efficiency is low; When not having frock, rivet on-the-spot manual grinding surplus, efficiency is low, of poor quality, and noise is large.
Summary of the invention
The present invention adopts digital process auricle location technology, and covering can put in place by clamped one time, does not need repeatedly to adjust; Except technical lug, cover edges is clean limit, does not need field polish surplus; Can greatly improve efficiency of assembling and assembly quality.
Covering is made two or more knock hole, utilizes these knock holees accurately to locate covering on riveted joint assembling fixture, so just not be used in riveted joint scene and repeatedly adjust covering position; Clamping need not be with surplus to the covering on fixture.But be do not allow at will to increase knock hole within cover edges line.Therefore imagine and knock hole is set in flat plate margin district.
Concrete steps are as follows:
Step one, employing digitizing technique manufacture stretching tire and riveted joint assembling fixture, stretching tire gets out technical lug knock hole with glass-felt plastic pressing plate drill jig in covering surplus district, described technical lug knock hole is selected in the little and symmetrical region that Curvature varying is little of skin drawing shaping and deformation, and the quantity of described knock hole is at least two;
Step 2, by knock hole, covering is positioned on stretching tire, by the covering line of cut (EOP) on stretching tire, covering is switched to clean limit size, but retain technical lug; By knock hole, covering is navigated on riveted joint assembling fixture, join the rivet hole got out between covering and frame beam, and locate with spring pin;
Step 3, pull down covering, excision auricle;
Step 4, again install on fixture, by spring pin registration riveting nail;
Step 5, installation rivet, complete riveted joint assembling.
Aging method needs manual line, and line precision is low, and repeatable accuracy is low; Scribe step is not had in new mode; Aging method riveted joint scene manual grinding covering surplus under the prerequisite not having frock; New mode only need polish off technical lug, polishing work capacity only have aging method less than 1%.
Efficiency of assembling and assembly quality is improve by assembly method of the present invention.Covering can be realized produce exchange and use exchange.For the assembling of covering digitalisation automatic Drilling/Riveting provides failure-free position fixing system.
Accompanying drawing explanation
Fig. 1 is aluminum alloy outer cover, relative position relation schematic diagram between stretching tire and glass-felt plastic pressing plate;
Fig. 2 is covering bore state on stretching tire;
Fig. 3 bores skin technology auricle knock hole on stretching tire;
Fig. 4 is state (surplus region does not all illustrate) after the boring of covering blank;
Fig. 5 is the state after covering trimming;
Fig. 6 is covering positioning states on assembling fixture;
Fig. 7 is skin technology auricle location detail drawing.
1-stretching tire; 2-aluminum alloy outer cover; 3-glass-felt plastic pressing plate; Technical lug knock hole drill jig on 4-pressing plate; 5-knock hole; 6-covering surplus region; 7-technical lug; 8-technical lug hole locator
Detailed description of the invention
A kind of aluminum alloy outer cover numeric terminal method of the present invention, its detailed process is as follows:
Step 1: get out technical lug knock hole on stretching tire
Adopt digitizing technique manufacture stretching tire and riveted joint assembling fixture, stretching tire gets out technical lug knock hole with glass-felt plastic pressing plate drill jig in covering surplus district, described technical lug knock hole is selected in the little and symmetrical region that Curvature varying is little of skin drawing shaping and deformation, thinks that covering subsequent processing operations provides locating and machining benchmark and assembling and positioning benchmark accurately; In addition, because stretching tire and pressing plate drill jig employ Digitized manufacturing means, thus ensure that technical lug knock hole and covering geometric configuration hight coordinate, as shown in Figure 1,2,3, 4;
Step 2: covering location trimming
By knock hole, covering is positioned on digitalisation stretching tire, by glass-felt plastic platen edge, covering is switched to clean limit size, reserve technical lug; As shown in Figure 4; Cover edges is checked by the covering line of cut on stretching tire.Other products hole can be got out by stretching tire and glass-felt plastic pressing plate.
The present invention utilizes covering line of cut (EOP) on stretching tire and pressing plate, thus ensures that cover edges and knock hole are coordinated.
Step 3: covering assembling and positioning
By the aluminum alloy outer cover with technical lug hole, by knock hole, covering is navigated on riveted joint numeric terminal fixture, join the rivet hole got out between covering and frame beam, and locate with spring pin.
The assembling and positioning benchmark (being also machining benchmark) that the present invention utilizes formative stage to obtain, under the prerequisite that benchmark is constant, by accurate for covering clamping on riveted joint assembling fixture, thus ensure that the architectural feature such as shape, edge, hole of covering is consistent with the relative position hight coordinate of the frame beam of body, ensure that covering exchanges from shaping, that trimming is bored into assembling production, and finally ensure that covering uses exchange; As shown in Figure 5;
Step 4: excision technical lug
Pull down covering, excision technical lug; As shown in Figure 6;
Step 5: covering riveting assembles
Again installed on housing construction by the covering removing technical lug, with spring pin location, riveter is followed closely, and completes riveted joint assembling.
In addition, the material of stretching tire is cast iron or epoxy plastics, numerical control machining; The glass-felt plastic pressing plate manufacture method of stretching tire: get covering material thick (sheet lead) discard on mould tire, bedding and padding adopt wet method paste glass steel formwork; After glass steel formwork solidification, get out the macropore for inlay auricle knock hole drill bushing thereon; By knock hole (numerical control bore hole) the filling drill bushing (with epoxy resin) of the correspondence on stretching tire; The edge of pressing plate manufactures by the covering line of cut of stretching tire.See Fig. 3.
Described technical lug knock hole will be selected in the little symmetrical zone line of skin drawing shaping and deformation, the region that Curvature varying is little, and knock hole quantity at least two.To avoid, because skin morph makes pilot hole axes relative position change greatly, causing location difficulty.Optional one of knock hole lining on the steady arm of assembly tooling is normal apertures, and second knock hole lining is long circular sleeve, and the 3rd lining (if there is) is macropore lining.Location difficulty can be avoided.
In addition, the position of technical lug knock hole should be determined by assembly tooling designer and propose, and hole bit data is submitted to stretching tire Fixture Design person.To ensure that knock hole is coordinated.
Claims (1)
1. an aluminum alloy outer cover numeric terminal method, is characterized in that, comprises the following steps:
Step one, employing digitizing technique manufacture stretching tire and riveted joint assembling fixture, stretching tire gets out technical lug knock hole with glass-felt plastic pressing plate drill jig in covering surplus district, described technical lug knock hole is selected in the little and symmetrical region that Curvature varying is little of skin drawing shaping and deformation, and the quantity of described knock hole is at least two;
Step 2, by knock hole, covering is positioned on stretching tire, by the covering line of cut on stretching tire, covering is switched to clean limit size, but retain technical lug; By knock hole, covering is navigated on riveted joint assembling fixture, join the rivet hole got out between covering and frame beam, and locate with spring pin;
Step 3, pull down covering, excision auricle;
Step 4, again install on fixture, by spring pin registration riveting nail;
Step 5, installation rivet, complete riveted joint assembling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510230174.1A CN104816837A (en) | 2015-05-07 | 2015-05-07 | Aluminum alloy skin digital assembly method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510230174.1A CN104816837A (en) | 2015-05-07 | 2015-05-07 | Aluminum alloy skin digital assembly method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104816837A true CN104816837A (en) | 2015-08-05 |
Family
ID=53727368
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510230174.1A Pending CN104816837A (en) | 2015-05-07 | 2015-05-07 | Aluminum alloy skin digital assembly method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104816837A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105710270A (en) * | 2016-04-01 | 2016-06-29 | 中航飞机股份有限公司西安飞机分公司 | Process for eliminating riveting gap of thin aircraft web |
| CN106239034A (en) * | 2016-08-19 | 2016-12-21 | 成都飞机工业（集团）有限责任公司 | A kind of method accurately pressing direction of normal hand-made hole on curved surface |
| CN108326521A (en) * | 2018-02-26 | 2018-07-27 | 中国电子科技集团公司第五十四研究所 | A kind of production method of high-precision single-curved surface aluminum alloy outer cover |
| CN112475404A (en) * | 2020-11-20 | 2021-03-12 | 昌河飞机工业（集团）有限责任公司 | Frock of covering milling appearance |
| CN112935349A (en) * | 2019-12-10 | 2021-06-11 | 中航贵州飞机有限责任公司 | Method for machining accurate lead hole on skin of training machine |
| CN113644371A (en) * | 2021-08-19 | 2021-11-12 | 湖南汽车工程职业学院 | Manufacturing method of lightweight aluminum alloy battery bracket of new energy automobile |
| CN115502663A (en) * | 2022-09-26 | 2022-12-23 | 沈阳飞机工业（集团）有限公司 | Preparation method of large-scale fork-shaped skin contour |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080245468A1 (en) * | 2006-12-13 | 2008-10-09 | Honda Motor Co., Ltd. | Method for assembling main wing made of aluminum alloy |
| CN103847981A (en) * | 2014-03-17 | 2014-06-11 | 沈阳飞机工业（集团）有限公司 | Assembly and inspection method of dual-curvature skin type part |
| CN103950552A (en) * | 2014-04-25 | 2014-07-30 | 浙江大学 | Digitized correcting method for assembly deformation of aircraft panels based on six-shaft numerical control positioner |
| CN104176270A (en) * | 2014-09-16 | 2014-12-03 | 沈阳飞机工业（集团）有限公司 | Fast locating method for skin at butt joint portion of aircraft components |
-
2015
- 2015-05-07 CN CN201510230174.1A patent/CN104816837A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080245468A1 (en) * | 2006-12-13 | 2008-10-09 | Honda Motor Co., Ltd. | Method for assembling main wing made of aluminum alloy |
| CN103847981A (en) * | 2014-03-17 | 2014-06-11 | 沈阳飞机工业（集团）有限公司 | Assembly and inspection method of dual-curvature skin type part |
| CN103950552A (en) * | 2014-04-25 | 2014-07-30 | 浙江大学 | Digitized correcting method for assembly deformation of aircraft panels based on six-shaft numerical control positioner |
| CN104176270A (en) * | 2014-09-16 | 2014-12-03 | 沈阳飞机工业（集团）有限公司 | Fast locating method for skin at butt joint portion of aircraft components |
Non-Patent Citations (1)
| Title |
|---|
| 林美安: "飞机机身装配工艺及仿真技术研究", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105710270A (en) * | 2016-04-01 | 2016-06-29 | 中航飞机股份有限公司西安飞机分公司 | Process for eliminating riveting gap of thin aircraft web |
| CN106239034A (en) * | 2016-08-19 | 2016-12-21 | 成都飞机工业（集团）有限责任公司 | A kind of method accurately pressing direction of normal hand-made hole on curved surface |
| CN108326521A (en) * | 2018-02-26 | 2018-07-27 | 中国电子科技集团公司第五十四研究所 | A kind of production method of high-precision single-curved surface aluminum alloy outer cover |
| CN112935349A (en) * | 2019-12-10 | 2021-06-11 | 中航贵州飞机有限责任公司 | Method for machining accurate lead hole on skin of training machine |
| CN112935349B (en) * | 2019-12-10 | 2022-12-09 | 中航贵州飞机有限责任公司 | Method for machining accurate lead hole on skin of training machine |
| CN112475404A (en) * | 2020-11-20 | 2021-03-12 | 昌河飞机工业（集团）有限责任公司 | Frock of covering milling appearance |
| CN113644371A (en) * | 2021-08-19 | 2021-11-12 | 湖南汽车工程职业学院 | Manufacturing method of lightweight aluminum alloy battery bracket of new energy automobile |
| CN113644371B (en) * | 2021-08-19 | 2023-03-10 | 湖南汽车工程职业学院 | Manufacturing method of lightweight aluminum alloy battery bracket of new energy automobile |
| CN115502663A (en) * | 2022-09-26 | 2022-12-23 | 沈阳飞机工业（集团）有限公司 | Preparation method of large-scale fork-shaped skin contour |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104816837A (en) | Aluminum alloy skin digital assembly method | |
| CN105880918A (en) | Composite material skin digital manufacture method | |
| CN105035354A (en) | Composite material skin net edge coordination tools and assembling method for skins | |
| CN104943849A (en) | Manufacturing method of aluminum skin honeycomb sandwich floor | |
| CN102328231B (en) | Flexible clamp for numerical-control processing and application thereof | |
| CN105729834A (en) | Production method for assembling hole of composite material part | |
| CN105423970B (en) | A kind of localization method of casing support plate manufacture | |
| CN101992582B (en) | Cooperative machining method for large sandwich component | |
| CN110802376B (en) | Multi-station airplane wing box assembling method | |
| CN109530764B (en) | Sawtooth aircraft skin clamping and numerical control appearance milling method | |
| CN105290475A (en) | Method for milling titanium alloy fan blade profiles | |
| CN108788208B (en) | Boring method for machining intersection angle box hole system | |
| CN104907766B (en) | A kind of GT processing method of connecting rod | |
| CN110153896B (en) | Method for rapidly and stably cutting rough edges of forge pieces by water | |
| CN204075878U (en) | A kind of machined secondary benchmark conversion equipment | |
| CN204893447U (en) | Far and near light adjustment sheet hydraulically operated fixture of car headlight | |
| CN112935349B (en) | Method for machining accurate lead hole on skin of training machine | |
| CN208230629U (en) | A kind of adjustment cushion block gets fixture ready | |
| CN204338916U (en) | The turning chuck clamps of a kind of union elbow | |
| CN203918503U (en) | A kind of pallet | |
| CN205465165U (en) | Aircraft component locator that connects in parallel | |
| CN204524840U (en) | A kind of inclination axle journal processing tool | |
| CN208991597U (en) | A kind of spring hoop forming jig | |
| CN205043189U (en) | Half contour machining blade | |
| CN109571024A (en) | A kind of medium block parts processing tooling and method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150805 |
|
| WD01 | Invention patent application deemed withdrawn after publication |