CN106938310A - The finish forge processing method of aviation aircraft connecting seat - Google Patents
The finish forge processing method of aviation aircraft connecting seat Download PDFInfo
- Publication number
- CN106938310A CN106938310A CN201710176637.XA CN201710176637A CN106938310A CN 106938310 A CN106938310 A CN 106938310A CN 201710176637 A CN201710176637 A CN 201710176637A CN 106938310 A CN106938310 A CN 106938310A
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- forging
- blank
- finish forge
- stove
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/06—Methods for forging, hammering, or pressing; Special equipment or accessories therefor for performing particular operations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K29/00—Arrangements for heating or cooling during processing
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Forging (AREA)
Abstract
The finish forge processing method of aviation aircraft connecting seat, 1）Raw material prepare：Using LF6 rust-preventing aluminum alloys；2）Mold design：Mold system is made up of upper and lower mould and die holder, and cavity design is finish forge size；3）Production process：Mould is preheated to 360 ± 10 DEG C before forging, 8~10h of preheating time, blank heating is incubated 1.5~2h, forging of then coming out of the stove to 470 ± 5 DEG C；Blank basic forming after One-time forging, it is air-cooled after forging, carry out polishing and repair wound, remove surface spikes, fold；Come out of the stove after second fiery 470 ± 5 DEG C of Forge Heating temperature, 0.5~1.0h of soaking time, blank to temperature forging, finish forge is molded, air-cooled after forging；Pickling removes surface oil stain and oxide-film after the completion of blank, forms direct machining finished product after the completion of smooth, clean and tidy black skin, blank.Process of the present invention is simple, low cost of manufacture, long service life, stable work in work, and product qualified rate brings up to more than 99%.
Description
Technical field
The present invention relates to a kind of finish forge processing method of aviation aircraft connecting seat, belong to forging manufacturing technology field.
Background technology
Aviation aircraft is high speed aircraft interior important feature part with connecting seat, and it act as fixing internal electronics device
Part, at present country's every profession and trade production is mainly rough-cast shaping, is machined into finished product after heat treatment again.
Because traditional handicraft use exist inside cast member, casting ingot shrinkage cavity, be mingled with, stomata, slag inclusion and oxidation
Etc. after many Product processings of defect in the exposed venthole of finished surface, the defect such as be mingled with, cause gas leakage after finished product pressure testing, scrap,
Internal flaw greatly reduces finished product scrappage after product safety performance, and blank processing and, more than 50%, both have lost processing charges
And have lost blank expense again, improve production cost.
The content of the invention
It is to be solved by this invention to be:Casting ingot internal flaw is more, in the exposed venthole of finished surface, folder after processing
The defect such as miscellaneous, causes gas leakage after finished product pressure testing, scraps, technical problem of the scrappage more than 50%.
In order to solve the above technical problems, the present invention is realized using following technical scheme：
The finish forge processing method of aviation aircraft connecting seat, comprises the following steps：
1）Raw material prepare：Using LF6 rust-preventing aluminum alloys, by GB/T3191-2010 standard purchase prices, the bars of φ 60, former material are used
Material reviews chemical composition, mechanical property, high and low times of tissue；
2）Mold design：Mold system is made up of upper and lower mould and die holder, and cavity design is finish forge size；
3）Production process：Mould is preheated to 360 ± 10 DEG C before forging, 8~10h of preheating time, blank heating to 470 ± 5 DEG C,
It is incubated 1.5~2h, forging of then coming out of the stove；Blank basic forming after One-time forging, it is air-cooled after forging, carry out polishing and repair wound, remove
Surface spikes, folding；Second fiery 470 ± 5 DEG C of Forge Heating temperature, 0.5~1.0h of soaking time, blank to forging of coming out of the stove after warm
Make, finish forge shaping is air-cooled after forging；Pickling removes surface oil stain and oxide-film after the completion of blank, forms smooth, clean and tidy blank
Direct machining finished product after the completion of face, blank.
Using the beneficial effect of above-mentioned technical proposal:
1st, casting is changed to forging molding by the present invention, and finished product cast inside tissue is produced into the forging tissue of densification,
The forging produced forms uniform and smooth surface, its dense internal organization, continuous, the far superior to former work of high and low times of tissue grading
Skill, the part bearing capacity after processing improves product qualified rate after more than 80%, machining than existing cast assembly and brought up to
More than 99%, and due to using precision forging, dimensional accuracy is high, and machine chips processing is few；
2nd, raw material selection forging LF6 rust-preventing aluminum alloys of the present invention, the blank of production is not required to heat treatment, direct blanking during production
Heating can be produced, it is not necessary to melting, the process such as vacuumize, cast, and shortened production procedure, saved heat treatment expense；Together
When, wrought aluminium material completely eliminates the inherent shortcoming of casting aluminium material, in the absence of defect genetic phenomenon；
3rd, the present invention have production process simple, high yield rate, manufacturing cost is relatively low, service life is longer, stable work in work,
Safe and reliable the advantages of.
Embodiment
Embodiment one
Production process：Mould is preheated to 355 DEG C before forging, preheating time 9.5h, blank heating is incubated 1.6h, so to 475 DEG C
After come out of the stove forging；Blank basic forming after One-time forging, it is air-cooled after forging, carry out polishing and repair wound, remove surface spikes, fold；
Come out of the stove after second fiery 465 DEG C of Forge Heating temperature, soaking time 0.8h, blank to temperature forging, finish forge is molded, air-cooled after forging；Hair
Pickling removes surface oil stain and oxide-film after the completion of base, forms direct machining after the completion of smooth, clean and tidy black skin, blank
Finished product.
Embodiment two
Production process：Mould is preheated to 360 DEG C before forging, preheating time 8.5h, blank heating is incubated 1.8h, so to 470 DEG C
After come out of the stove forging；Blank basic forming after One-time forging, it is air-cooled after forging, carry out polishing and repair wound, remove surface spikes, fold；
Come out of the stove after second fiery 470 DEG C of Forge Heating temperature, soaking time 0.9h, blank to temperature forging, finish forge is molded, air-cooled after forging；Hair
Pickling removes surface oil stain and oxide-film after the completion of base, forms direct machining after the completion of smooth, clean and tidy black skin, blank
Finished product.
Embodiment three
Production process：Mould is preheated to 365 DEG C before forging, preheating time 9h, blank heating is incubated 1.6h, then to 475 DEG C
Come out of the stove forging；Blank basic forming after One-time forging, it is air-cooled after forging, carry out polishing and repair wound, remove surface spikes, fold；The
Come out of the stove after two fiery 475 DEG C of Forge Heating temperature, soaking time 0.7h, blank to temperature forging, finish forge is molded, air-cooled after forging；Blank
After the completion of pickling remove surface oil stain and oxide-film, formed after the completion of smooth, clean and tidy black skin, blank directly machining into
Product.
The production process of the present invention：
Blanking → railway carriage → forging → pickling → machining → detection experiment.
The forging physicochemical property of the present invention：
1）Product forging chemical composition mass fraction table is as follows：
2）Product mechanical performance：σ b >=305MPa, σ p0.2 >=127, δ 5 >=14.0%.
3）Dimensional gaughing：Make full-scale inspection.
4）Flaw detection：It is PT, 100% dyeing inspection in forging surface, it is desirable to the defect such as surface flawless, folding, pit.
Claims (1)
1. the finish forge processing method of empty aircraft connecting seat, it is characterized in that, this method comprises the following steps：
1）Raw material prepare：Using LF6 rust-preventing aluminum alloys, by GB/T3191-2010 standard purchase prices, the bars of φ 60, former material are used
Material reviews chemical composition, mechanical property, high and low times of tissue；
2）Mold design：Mold system is made up of upper and lower mould and die holder, and cavity design is finish forge size；
3）Production process：Mould is preheated to 360 ± 10 DEG C before forging, 8~10h of preheating time, blank heating to 470 ± 5 DEG C,
It is incubated 1.5~2h, forging of then coming out of the stove；Blank basic forming after One-time forging, it is air-cooled after forging, carry out polishing and repair wound, remove
Surface spikes, folding；Second fiery 470 ± 5 DEG C of Forge Heating temperature, 0.5~1.0h of soaking time, blank to forging of coming out of the stove after warm
Make, finish forge shaping is air-cooled after forging；Pickling removes surface oil stain and oxide-film after the completion of blank, forms smooth, clean and tidy blank
Direct machining finished product after the completion of face, blank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710176637.XA CN106938310B (en) | 2017-03-23 | 2017-03-23 | The finish forge processing method of aviation aircraft connecting seat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710176637.XA CN106938310B (en) | 2017-03-23 | 2017-03-23 | The finish forge processing method of aviation aircraft connecting seat |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106938310A true CN106938310A (en) | 2017-07-11 |
| CN106938310B CN106938310B (en) | 2018-06-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710176637.XA Active CN106938310B (en) | 2017-03-23 | 2017-03-23 | The finish forge processing method of aviation aircraft connecting seat |
Country Status (1)
| Country | Link |
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| CN (1) | CN106938310B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109732023A (en) * | 2018-12-27 | 2019-05-10 | 桂林理工大学 | A method of control Al-alloy casing isothermal precision forging process size rebound |
| CN110076280A (en) * | 2019-05-29 | 2019-08-02 | 遵义航天新力精密铸锻有限公司 | A kind of aviation aircraft empennage processing technology |
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| JPH06248400A (en) * | 1993-02-23 | 1994-09-06 | Sumitomo Metal Ind Ltd | Method for forging aluminum alloy |
| JP2004084058A (en) * | 2002-06-27 | 2004-03-18 | Kobe Steel Ltd | Method for producing aluminum alloy forging for transport structural material and aluminum alloy forging |
| CN101559471A (en) * | 2009-05-22 | 2009-10-21 | 哈尔滨工业大学 | Aluminum alloy complex disc part isothermal precision forging process method |
| CN102441630A (en) * | 2011-09-15 | 2012-05-09 | 河南理工大学 | Near net shape process for aluminum alloy parts of prosthetic knee of human body |
| CN102642120A (en) * | 2012-05-02 | 2012-08-22 | 兰溪市同力机械有限公司 | Manufacturing process of dining-table support supporting arm |
| CN102825208A (en) * | 2012-08-31 | 2012-12-19 | 芜湖禾田汽车工业有限公司 | Forging and forming process of aluminum alloy car control arm |
| WO2014010678A1 (en) * | 2012-07-12 | 2014-01-16 | 昭和電工株式会社 | Method for manufacturing semifinished product for case body of hard disk drive device, and semifinished product for case body |
| CN104357716A (en) * | 2014-11-26 | 2015-02-18 | 农彩丽 | Heat-resistant and anti-creep aluminium-magnesium alloy and preparation process thereof |
| EP3018226A1 (en) * | 2014-11-05 | 2016-05-11 | Constellium Valais SA (AG, Ltd) | Ultra high strength products forged from 6xxx aluminium alloys having excellent corrosion resistance |
| CN106238641A (en) * | 2016-08-11 | 2016-12-21 | 江苏亚太安信达铝业有限公司 | A kind of forging method of passenger car aluminium alloy chaining part |
-
2017
- 2017-03-23 CN CN201710176637.XA patent/CN106938310B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1127740A (en) * | 1965-03-04 | 1968-09-18 | Ver Leichtmetallwerke Gmbh | A method of making forged parts |
| JPH06248400A (en) * | 1993-02-23 | 1994-09-06 | Sumitomo Metal Ind Ltd | Method for forging aluminum alloy |
| JP2004084058A (en) * | 2002-06-27 | 2004-03-18 | Kobe Steel Ltd | Method for producing aluminum alloy forging for transport structural material and aluminum alloy forging |
| CN101559471A (en) * | 2009-05-22 | 2009-10-21 | 哈尔滨工业大学 | Aluminum alloy complex disc part isothermal precision forging process method |
| CN102441630A (en) * | 2011-09-15 | 2012-05-09 | 河南理工大学 | Near net shape process for aluminum alloy parts of prosthetic knee of human body |
| CN102642120A (en) * | 2012-05-02 | 2012-08-22 | 兰溪市同力机械有限公司 | Manufacturing process of dining-table support supporting arm |
| WO2014010678A1 (en) * | 2012-07-12 | 2014-01-16 | 昭和電工株式会社 | Method for manufacturing semifinished product for case body of hard disk drive device, and semifinished product for case body |
| CN102825208A (en) * | 2012-08-31 | 2012-12-19 | 芜湖禾田汽车工业有限公司 | Forging and forming process of aluminum alloy car control arm |
| EP3018226A1 (en) * | 2014-11-05 | 2016-05-11 | Constellium Valais SA (AG, Ltd) | Ultra high strength products forged from 6xxx aluminium alloys having excellent corrosion resistance |
| CN104357716A (en) * | 2014-11-26 | 2015-02-18 | 农彩丽 | Heat-resistant and anti-creep aluminium-magnesium alloy and preparation process thereof |
| CN106238641A (en) * | 2016-08-11 | 2016-12-21 | 江苏亚太安信达铝业有限公司 | A kind of forging method of passenger car aluminium alloy chaining part |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109732023A (en) * | 2018-12-27 | 2019-05-10 | 桂林理工大学 | A method of control Al-alloy casing isothermal precision forging process size rebound |
| CN109732023B (en) * | 2018-12-27 | 2020-07-31 | 桂林理工大学 | Method for controlling size rebound in isothermal finish forging process of aluminum alloy shell |
| CN110076280A (en) * | 2019-05-29 | 2019-08-02 | 遵义航天新力精密铸锻有限公司 | A kind of aviation aircraft empennage processing technology |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106938310B (en) | 2018-06-05 |
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