CN103658475B - A kind of aircraft two-crew cockpit lid skeleton solid forging method - Google Patents
A kind of aircraft two-crew cockpit lid skeleton solid forging method Download PDFInfo
- Publication number
- CN103658475B CN103658475B CN201310612007.4A CN201310612007A CN103658475B CN 103658475 B CN103658475 B CN 103658475B CN 201310612007 A CN201310612007 A CN 201310612007A CN 103658475 B CN103658475 B CN 103658475B
- Authority
- CN
- China
- Prior art keywords
- insulation
- blank
- size
- tons
- stove
- 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
Landscapes
- Forging (AREA)
Abstract
The present invention relates to a kind of aircraft two-crew cockpit lid skeleton solid forging method, belong to heat processing technique technical field. the bar of preparation LD5 material, 430 DEG C～450 DEG C of heating by electric cookers, insulation 9h～15h, after coming out of the stove at 5000 tons of hydraulic press free forgings to given size, after blank air cooling, shape processing endoporus and the blank shape of blank, then by blank 430 DEG C～450 DEG C of heating by electric cookers, insulation 6h～12h, after coming out of the stove on 10000 tons of hydraulic presses integral forging and forming, after checking that by overall model size is qualified, solution treatment in electric furnace, temperature is 509 DEG C～515 DEG C, insulation 2h～2.5h, after coming out of the stove quench water temperature control at 70 DEG C～80 DEG C to reduce forging quenching distortion, on 5000 tons of hydraulic presses, carry out size subsequently and be remedied to design size, then timeliness in electric furnace, temperature is 514 DEG C～520 DEG C, insulation 8h～15h, time interval < 6h between quenching and timeliness.
Description
Technical field
The present invention relates to a kind of aircraft two-crew cockpit lid skeleton solid forging method, belong to heat processing technique technical field.
Background technology
Without aircraft two-crew cockpit lid skeleton solid forging precedent, domestic various canopy skeleton is all the combining structure that multiple parts combine both at home and abroad. The canopy skeleton of the T50 machine of S. Korea and the USA's cooperation research and development is composite material, and abroad the canopy skeleton of other aircrafts mostly is and combines opening structure backward. Aircraft Double-seat canopy skeleton was forged to frontal arc frame, middle arc frame, backarc frame process for forging respectively in the past, by three arc frames and the both sides section combination canopy skeleton that is formed by connecting. The canopy skeleton poor rigidity of sub-assembly setting down, poor stability, yielding, easily cause limit, canopy glass transparent part hole crackle, and the production cycle is long, part life is short.
Summary of the invention
The object of the invention is to realize aircraft two-crew cockpit lid skeleton integral forging and forming, solve setting down canopy skeleton poor rigidity, yielding, assembly coordination and interchangeability is poor, easily cause functional limitation's property such as limit, canopy glass transparent part hole crackle.
To achieve these goals, the present invention adopts following technical scheme:
A kind of aircraft two-crew cockpit lid skeleton solid forging method, comprises following method step:
A), the bar of preparation LD5 material, 430 DEG C～450 DEG C of heating by electric cookers, insulation 9h～15h, after coming out of the stove at 5000 tons of hydraulic press free forgings to given size, after blank air cooling, according to shape processing endoporus and the blank shape of blank, then by blank 430 DEG C～450 DEG C of heating by electric cookers, insulation 6h～12h, after coming out of the stove on 10000 tons of hydraulic presses integral forging and forming, after checking that by overall model size is qualified, solution treatment in electric furnace, temperature is 509 DEG C～515 DEG C, insulation 2h～2.5h, after coming out of the stove quench water temperature control at 70 DEG C～80 DEG C to reduce forging quenching distortion, on 5000 tons of hydraulic presses, carry out size subsequently and be remedied to design size, then timeliness in electric furnace, temperature is 514 DEG C～520 DEG C, insulation 8h～15h, time interval < 6h between quenching and timeliness,
B), press number of components die topography entirety model inspection appearance and size.
Beneficial effect of the present invention:
Aircraft two-crew cockpit lid skeleton solid forging method of the present invention, has started the domestic and international aircraft Double-seat canopy skeleton solid forging beginning, has realized two-crew cockpit lid skeleton integral forging and forming. Aircraft Double-seat canopy skeleton adopts the scheme of solid forging, reduce and finish the number of components, reduced passenger cabin skeleton overall weight, good rigidly, streamline is complete, reduce the difficulty of assembly coordination, can avoid because sub-assembly is out of shape the serious quality problems that limit, transparent member hole is cracked, improve combination property and the service life of passenger cabin skeleton.
Brief description of the drawings
Fig. 1 is the blank schematic diagram in the present invention;
Fig. 2 is number of components die topography entirety model schematic diagram in the present invention.
Detailed description of the invention
Describe the present invention below in conjunction with accompanying drawing 1,2:
A kind of aircraft two-crew cockpit lid skeleton solid forging method, comprises following method step:
A), the bar of preparation LD5 material, 430 DEG C～450 DEG C of heating by electric cookers, insulation 9h～15h, after coming out of the stove at 5000 tons of hydraulic press free forgings to given size, after blank air cooling, press shape processing endoporus and the blank shape of blank in Fig. 1, then by blank 430 DEG C～450 DEG C of heating by electric cookers, insulation 6h～12h, after coming out of the stove on 10000 tons of hydraulic presses integral forging and forming, after checking that by overall model size is qualified, solution treatment in electric furnace, temperature is 509 DEG C～515 DEG C, insulation 2h～2.5h, after coming out of the stove quench water temperature control at 70 DEG C～80 DEG C to reduce forging quenching distortion, on 5000 tons of hydraulic presses, carry out size subsequently and be remedied to design size, then timeliness in electric furnace, temperature is 514 DEG C～520 DEG C, insulation 8h～15h, time interval < 6h between quenching and timeliness,
B), press number of components die topography entirety model inspection appearance and size. Three arc frame exterior templates and setting angle are shown in Fig. 2.
Claims (1)
1. an aircraft two-crew cockpit lid skeleton solid forging method, is characterized in that comprising following method step:
A), the bar of preparation LD5 material, 430 DEG C～450 DEG C of heating by electric cookers, insulation 9h～15h, after coming out of the stove at 5000 tons of hydraulic press free forgings to given size, after blank air cooling, according to shape processing endoporus and the blank shape of blank, then by blank 430 DEG C～450 DEG C of heating by electric cookers, insulation 6h～12h, after coming out of the stove on 10000 tons of hydraulic presses integral forging and forming, after checking that by overall model size is qualified, solution treatment in electric furnace, temperature is 509 DEG C～515 DEG C, insulation 2h～2.5h, after coming out of the stove quench water temperature control at 70 DEG C～80 DEG C to reduce forging quenching distortion, on 5000 tons of hydraulic presses, carry out size subsequently and be remedied to design size, then timeliness in electric furnace, temperature is 514 DEG C～520 DEG C, insulation 8h～15h, time interval < 6h between quenching and timeliness,
B), press number of components die topography entirety model inspection appearance and size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310612007.4A CN103658475B (en) | 2013-11-28 | 2013-11-28 | A kind of aircraft two-crew cockpit lid skeleton solid forging method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310612007.4A CN103658475B (en) | 2013-11-28 | 2013-11-28 | A kind of aircraft two-crew cockpit lid skeleton solid forging method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103658475A CN103658475A (en) | 2014-03-26 |
| CN103658475B true CN103658475B (en) | 2016-05-11 |
Family
ID=50297938
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310612007.4A Active CN103658475B (en) | 2013-11-28 | 2013-11-28 | A kind of aircraft two-crew cockpit lid skeleton solid forging method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103658475B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103984800B (en) * | 2014-04-17 | 2017-04-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for analyzing influence of asymmetrical edge assembling on canopy stress |
| CN103995920A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Edge connection degumming analysis method for flexible connection structure |
| CN104386241B (en) * | 2014-11-04 | 2016-08-17 | 江西洪都航空工业集团有限责任公司 | A kind of protective cover of aircraft cabin lid perspex transparent part |
| CN105728613B (en) * | 2014-12-12 | 2017-10-31 | 陕西宏远航空锻造有限责任公司 | A kind of free forging method of font forging |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4048836A (en) * | 1972-09-28 | 1977-09-20 | Wyman-Gordon Company | Forming and heat treating process |
| CN101185954A (en) * | 2007-12-19 | 2008-05-28 | 河南中光学集团有限公司 | Aluminum alloy special-shaped member equivalent temperature precision forging technique method |
| CN102335704A (en) * | 2011-09-22 | 2012-02-01 | 哈尔滨哈飞工业有限责任公司 | Method for forging and forming structural parts of wheel chair rack |
| CN102352474A (en) * | 2011-10-31 | 2012-02-15 | 哈尔滨中飞新技术股份有限公司 | Forging and heat treatment method of 2A50 aluminium alloy die forging |
| CN102392158A (en) * | 2011-11-22 | 2012-03-28 | 东北轻合金有限责任公司 | Manufacturing method of engine aluminium alloy piston die forging |
| CN102644039A (en) * | 2011-02-17 | 2012-08-22 | 北京有色金属研究总院 | Preparation method of high-quality 6061 aluminium alloy forging for semiconductor equipment |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09249951A (en) * | 1996-03-12 | 1997-09-22 | Nippon Light Metal Co Ltd | Production of aluminum forged product having fine structure |
| KR101044899B1 (en) * | 2009-09-11 | 2011-06-28 | 주식회사 센트랄 | Forging method for aluminum |
-
2013
- 2013-11-28 CN CN201310612007.4A patent/CN103658475B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4048836A (en) * | 1972-09-28 | 1977-09-20 | Wyman-Gordon Company | Forming and heat treating process |
| CN101185954A (en) * | 2007-12-19 | 2008-05-28 | 河南中光学集团有限公司 | Aluminum alloy special-shaped member equivalent temperature precision forging technique method |
| CN102644039A (en) * | 2011-02-17 | 2012-08-22 | 北京有色金属研究总院 | Preparation method of high-quality 6061 aluminium alloy forging for semiconductor equipment |
| CN102335704A (en) * | 2011-09-22 | 2012-02-01 | 哈尔滨哈飞工业有限责任公司 | Method for forging and forming structural parts of wheel chair rack |
| CN102352474A (en) * | 2011-10-31 | 2012-02-15 | 哈尔滨中飞新技术股份有限公司 | Forging and heat treatment method of 2A50 aluminium alloy die forging |
| CN102392158A (en) * | 2011-11-22 | 2012-03-28 | 东北轻合金有限责任公司 | Manufacturing method of engine aluminium alloy piston die forging |
Non-Patent Citations (2)
| Title |
|---|
| 2A14铝合金等温模锻成型技术;陈利华等;《新技术新工艺》;20130630(第6期);第30-32页 * |
| 大型座舱骨架整体成形有限元模拟及实验研究;孙前江等;《中国机械工程》;20111031;第22卷(第20期);第2503-2506页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103658475A (en) | 2014-03-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103658475B (en) | A kind of aircraft two-crew cockpit lid skeleton solid forging method | |
| CN102500733B (en) | Forging method for efficiently healing internal hole-type defects of steel ingot | |
| CN102389933B (en) | High-frequency heating hydraulic double-head upsetting device with automatically feeding function and using method thereof | |
| CN103526144B (en) | TC17 titanium alloy large size bar free forging method | |
| CN104162616B (en) | Thermonuclear fusion heap ears U-shaped forging forging method | |
| CN102581188B (en) | Method for machining TC4-DT titanium alloy large-specification slab forged piece | |
| CN103658477A (en) | Forging process of titanium alloy blades | |
| CN103668027A (en) | Quasi beta forging process for TC25 titanium alloy | |
| CN102172750B (en) | Magnesium alloy construction member step temperature forming method | |
| CN103331572A (en) | Once forming of die forging crane wheel | |
| CN201195372Y (en) | Foam case mould | |
| CN105414435B (en) | Isothermal die-forging forming die and method for 7A09 aluminum alloy rocker arm provided with long walls, deep ribs and box-shaped ball head | |
| CN204067895U (en) | Combined outdoor box assembled structure base | |
| CN104624899A (en) | Forging improving method of 200-kilogram-level TC4-DT titanium alloy | |
| CN104148560A (en) | Airtight forging method for aluminum alloy forge piece | |
| CN204770110U (en) | Compound fine blanking die utensil of flange | |
| CN103008516A (en) | Steel-ball continuous-heating forming upsetting machine | |
| CN104139146B (en) | The closed type cover die of contact base | |
| CN203003028U (en) | Steel ball continuous heating forming upsetting machine | |
| CN103878278A (en) | Titanium alloy die forging forming method | |
| CN202779783U (en) | Powder metallurgy die using hot oil die bottom groove to heat | |
| CN103022851B (en) | At the Novel copper-aluminium rebound production process of aluminium sheet one end double-sided copper-clad | |
| CN202079214U (en) | Closed sleeve die | |
| CN104646578A (en) | Isothermal forging method for titanium alloy whole frame-shaped piece | |
| CN104174801A (en) | Device for forging nuclear power hydraulic damper cylinder |
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 |