CN102816958A - Manufacturing method of aluminum alloy hollow section for aircraft empennage - Google Patents
Manufacturing method of aluminum alloy hollow section for aircraft empennage Download PDFInfo
- Publication number
- CN102816958A CN102816958A CN2012103013682A CN201210301368A CN102816958A CN 102816958 A CN102816958 A CN 102816958A CN 2012103013682 A CN2012103013682 A CN 2012103013682A CN 201210301368 A CN201210301368 A CN 201210301368A CN 102816958 A CN102816958 A CN 102816958A
- Authority
- CN
- China
- Prior art keywords
- duraluminum
- manufacture
- hollow profile
- aircraft empennage
- mass
- 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
- Extrusion Of Metal (AREA)
- Forging (AREA)
Abstract
The manufacturing method of an aluminum alloy hollow section for an aircraft empennage, and relates to a manufacturing method of a hollow section. The method solves the problems that the section for the traditional aircraft empennage has low tensile strength, low non-proportional extension strength and lower safety factor. The method comprises the following steps that according to the proportion of 0.7% to 1.3% by mass of Si, less than or equal to 0.5% by mass of Fe, less than or equal to 0.10% by mass of Cu, 0.40 to 0.8% by mass of Mn, 0.40% to 0.8% by mass of Mg, less than or equal to 0.20% by mass of Zn, less than or equal to 0.20% by mass of Ti, and the balance being Al, aluminum alloy ingots, pure magnesium ingots, aluminum-manganese intermediate alloy and aluminum-silicon intermediate alloy are weighed to be added to a drying furnace to obtain molten aluminum to be cast into ingots; the ingots are subjected to homogenizing annealing; the aluminum alloy ingots are extruded by a special mold and a needlepoint; the front end of the section is penetrated by an iron wire and the section is hung to a quenching furnace to be quenched; and the section is straightened. The method is used for manufacturing the aluminum alloy hollow section for the aircraft empennage.
Description
Technical field
The present invention relates to a kind of method of manufacture of hollow profile.
Background technology
Aircraft uses steel in the past with the empennage section bar always; For weight reduction; Abroad replaced by the high duraluminum of proportion small intensity gradually from the material of the seventies as this section bar, the section bar that still uses the earliest is to form through machining with the cast member of corresponding big specification or bar.The requirement that tissue after the foundry goods processing and performance can not satisfy section bar.And bar need machine away 85% metal through the shape that is processed into section bar, and the big length consuming time of difficulty of processing.Therefore the manufacturing of this section bar must have enough intensity, and good fatigue resistance and accurate interior hole dimension and good surface quality can't guarantee the request for utilization of aircraft empennage with section bar by conventional extruded technology.
Summary of the invention
The purpose of this invention is to provide the method for manufacture of a kind of aircraft empennage, to solve the existing problem that aircraft is low with empennage section bar tensile strength, the disproportional extension strength is low and SF is lower with the duraluminum hollow profile.
The present invention solves the problems of the technologies described above the technical scheme of taking to be: said method comprising the steps of: step 1, be Si:0.7%～1.3%, Fe≤0.5% by mass percentage; Cu≤0.10%, Mn:0.40%～0.8%, Mg:0.40%～0.8%, Zn≤0.20%, Ti≤0.20% and surplus are that the ratio of Al takes by weighing aluminum alloy ingot, pure magnesium ingot, aluminium manganese master alloy and aluminium silicon master alloy and joins in the drying oven back melting and obtain aluminum melt; Through casting, obtain ingot casting again;
Step 2, the ingot casting that makes in the step 1 is carried out homogenizing annealing, annealing temperature is 320 ℃～530 ℃, is incubated 5-15 hour;
Step 3, will pass through the aluminium alloy cast ingot that step 2 makes and be heated to 350～450 ℃, and be presented to then in the particular manufacturing craft and obtain section bar through the needle point extruding, extrusion speed is 0.2～1.0mm/s;
Step 4, section bar front end are put on iron wire, winch in the quenching furnance to quench, and quenching temperature is 520 ℃-535 ℃, be incubated 30-250 minute, 10～35 ℃ of water temperatures, and the transfer time of quenching is smaller or equal to 15 seconds, and 5 minutes rears of stop are capable of hoisting in water then goes out the water surface;
Step 5, section bar are aligned on 400 tons of tension flattening machines, and the cold deformation amount during aligning is controlled at 1%～3%, then section bar fitly are placed in bin and hang and treat the timeliness stock ground, are under 165 ℃-185 ℃ the condition ageing treatment 8-10 hour in temperature.
The present invention has following beneficial effect: process for machining and manufacturing typical case in the product of the present invention combines the technology of extruded section and extruded hollow tubing; Mechanical workout is subsequently saved in product of the present invention once shaped when extruding, practices thrift 85% metal usage quantity, has improved efficient greatly; Use hollow ingot casting and extruding pin extruded hollow section bar in the production process of the present invention, do not have weld seam, avoid the in use stressed cracking of section bar.
Tensile strength, disproportional extension strength and the unit elongation of the duraluminum hollow profile of this embodiment preparation all meet the demands; And the profile shapes specification of making can change various; There is not weld defect; Stressed cracking when having avoided using, this kind section bar is fit to make the empennage of multiple aircraft and bullet.
Embodiment
Embodiment one: the method for this embodiment may further comprise the steps: step 1, be Si:0.7%～1.3%, Fe≤0.5% by mass percentage; Cu≤0.10%, Mn:0.40%～0.8%, Mg:0.40%～0.8%, Zn≤0.20%, Ti≤0.20% and surplus are that the ratio of Al takes by weighing aluminum alloy ingot, pure magnesium ingot, aluminium manganese master alloy and aluminium silicon master alloy and joins in the drying oven back melting and obtain aluminum melt; Through casting, obtain ingot casting again;
Step 2, the ingot casting that makes in the step 1 is carried out homogenizing annealing, annealing temperature is 320 ℃～530 ℃, is incubated 5-15 hour;
Step 3, will pass through the aluminium alloy cast ingot that step 2 makes and be heated to 350～450 ℃, and be presented to then in the particular manufacturing craft and obtain section bar through the needle point extruding, extrusion speed is 0.2～1.0mm/s;
Step 4, section bar front end are put on iron wire, winch in the quenching furnance to quench, and quenching temperature is 520 ℃-535 ℃, be incubated 30-250 minute, 10～35 ℃ of water temperatures, and the transfer time of quenching is smaller or equal to 15 seconds, and 5 minutes rears of stop are capable of hoisting in water then goes out the water surface;
Step 5, section bar are aligned on 400 tons of tension flattening machines, and the cold deformation amount during aligning is controlled at 1%～3%, then section bar fitly are placed in bin and hang and treat the timeliness stock ground, are under 165 ℃-185 ℃ the condition ageing treatment 8-10 hour in temperature.
Single impurity≤0.05% in the aluminium alloy extrusions of the present invention, impurity≤0.15%, the magazine in this scope is to the not influence of the hollow performance of duraluminum.
The aluminium alloy extrusions comprehensive mechanical property of the present invention's preparation is good, tensile strength >=330MPa, disproportional extension strength >=270MPa, elongation after fracture >=10%.
Embodiment two: the ingot casting annealing temperature is 380 ℃-420 ℃ in the step 2 of this embodiment.Other implementation steps are identical with embodiment one.
Embodiment three: the ingot casting soaking time is 8-10 hour in the step 2 of this embodiment.Other implementation steps are identical with embodiment one.
Embodiment four: the needle point diameter is Φ 15～Φ 150 in the step 3 of this embodiment.Other implementation steps are identical with embodiment one.
Embodiment five: quenching temperature is 520 ℃～525 ℃ in the step 4 of this embodiment.Other implementation steps are identical with embodiment one.
Embodiment six: insulation is 60 minutes in the step 4 of this embodiment.Other implementation steps are identical with embodiment one.
Embodiment seven: the temperature of timeliness is 165 ℃～170 ℃ in the step 5 of this embodiment.Other implementation steps are identical with embodiment one.
Embodiment eight: insulation is 10 hours in the step 5 of this embodiment.Other implementation steps are identical with embodiment one.
Claims (8)
1. an aircraft empennage is with the method for manufacture of duraluminum hollow profile; It is characterized in that said method comprising the steps of: step 1, be Si:0.7%～1.3%, Fe≤0.5% by mass percentage; Cu≤0.10%, Mn:0.40%～0.8%, Mg:0.40%～0.8%, Zn≤0.20%, Ti≤0.20% and surplus are that the ratio of Al takes by weighing aluminum alloy ingot, pure magnesium ingot, aluminium manganese master alloy and aluminium silicon master alloy and joins in the drying oven back melting and obtain aluminum melt; Through casting, obtain ingot casting again;
Step 2, the ingot casting that makes in the step 1 is carried out homogenizing annealing, annealing temperature is 320 ℃～530 ℃, is incubated 5-15 hour;
Step 3, will pass through the aluminium alloy cast ingot that step 2 makes and be heated to 350～450 ℃, and be presented to then in the particular manufacturing craft and obtain section bar through the needle point extruding, extrusion speed is 0.2～1.0mm/s;
Step 4, section bar front end are put on iron wire, winch in the quenching furnance to quench, and quenching temperature is 520 ℃-535 ℃, be incubated 30-250 minute, 10～35 ℃ of water temperatures, and the transfer time of quenching is smaller or equal to 15 seconds, and 5 minutes rears of stop are capable of hoisting in water then goes out the water surface;
Step 5, section bar are aligned on 400 tons of tension flattening machines, and the cold deformation amount during aligning is controlled at 1%～3%, then section bar fitly are placed in bin and hang and treat the timeliness stock ground, are under 165 ℃-185 ℃ the condition ageing treatment 8-10 hour in temperature.
2. according to the method for manufacture of the said aircraft empennage of claim 1, it is characterized in that the ingot casting annealing temperature is 380 ℃-420 ℃ in the step 2 with the duraluminum hollow profile.
According to claim 1 or 2 said aircraft empennages with the method for manufacture of duraluminum hollow profile, it is characterized in that the ingot casting soaking time is 8-10 hour in the step 2.
4. according to the method for manufacture of the said aircraft empennage of claim 1, it is characterized in that the needle point diameter is Φ 15～Φ 150 in the step 3 with the duraluminum hollow profile.
5. according to the method for manufacture of the said aircraft empennage of claim 1, it is characterized in that quenching temperature is 520 ℃～525 ℃ in the step 4 with the duraluminum hollow profile.
6. according to the method for manufacture of the said aircraft empennage of claim 1, it is characterized in that soaking time is 60 minutes in the step 4 with the duraluminum hollow profile.
7. according to the method for manufacture of the said aircraft empennage of claim 1 with the duraluminum hollow profile, the temperature that it is characterized in that timeliness in the step 5 is 165 ℃～170 ℃.
8. according to the method for manufacture of the said aircraft empennage of claim 1, it is characterized in that in the step 5 by metal insulation 10 hours with the duraluminum hollow profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012103013682A CN102816958A (en) | 2012-08-23 | 2012-08-23 | Manufacturing method of aluminum alloy hollow section for aircraft empennage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012103013682A CN102816958A (en) | 2012-08-23 | 2012-08-23 | Manufacturing method of aluminum alloy hollow section for aircraft empennage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102816958A true CN102816958A (en) | 2012-12-12 |
Family
ID=47301398
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012103013682A Pending CN102816958A (en) | 2012-08-23 | 2012-08-23 | Manufacturing method of aluminum alloy hollow section for aircraft empennage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102816958A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103614600A (en) * | 2013-11-29 | 2014-03-05 | 东北轻合金有限责任公司 | Method for manufacturing entire aluminum alloy cabin skeleton for windshield frame of advanced training plane |
| CN104726753A (en) * | 2015-03-23 | 2015-06-24 | 苏州市神龙门窗有限公司 | Preparation method of aluminum alloy section for doors/windows |
| CN105483575A (en) * | 2015-12-01 | 2016-04-13 | 北京有色金属研究总院 | Homogenizing annealing thermal treatment technology for A390 aluminum alloy cast ingot |
| CN108637607A (en) * | 2018-05-21 | 2018-10-12 | 晋西工业集团有限责任公司 | A kind of processing method of empennage frame semi-finished product |
| CN108774696A (en) * | 2018-06-20 | 2018-11-09 | 辽宁忠旺集团有限公司 | A kind of ultra-thin pipe extrudate production technology of 6 line aluminium alloys |
| CN110016577A (en) * | 2019-05-20 | 2019-07-16 | 江苏礼德铝业有限公司 | A kind of preparation method of aluminium alloy |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1542151A (en) * | 2003-11-07 | 2004-11-03 | 薛元良 | Hypereutectic silicon-aluminium alloy material and its production method |
| CN101935784A (en) * | 2010-08-30 | 2011-01-05 | 佛山市鸿金源铝业制品有限公司 | Aluminium material for contact nets on rapid transit railway and manufacturing method thereof |
| CN102275064A (en) * | 2011-05-27 | 2011-12-14 | 江苏凯伦铝业有限公司 | Production method of aluminum section frame for high-speed rail sound barrier |
| CN102489973A (en) * | 2011-12-23 | 2012-06-13 | 东北轻合金有限责任公司 | Method for manufacturing aluminum alloy hollow section for sedan bumper |
-
2012
- 2012-08-23 CN CN2012103013682A patent/CN102816958A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1542151A (en) * | 2003-11-07 | 2004-11-03 | 薛元良 | Hypereutectic silicon-aluminium alloy material and its production method |
| CN101935784A (en) * | 2010-08-30 | 2011-01-05 | 佛山市鸿金源铝业制品有限公司 | Aluminium material for contact nets on rapid transit railway and manufacturing method thereof |
| CN102275064A (en) * | 2011-05-27 | 2011-12-14 | 江苏凯伦铝业有限公司 | Production method of aluminum section frame for high-speed rail sound barrier |
| CN102489973A (en) * | 2011-12-23 | 2012-06-13 | 东北轻合金有限责任公司 | Method for manufacturing aluminum alloy hollow section for sedan bumper |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103614600A (en) * | 2013-11-29 | 2014-03-05 | 东北轻合金有限责任公司 | Method for manufacturing entire aluminum alloy cabin skeleton for windshield frame of advanced training plane |
| CN104726753A (en) * | 2015-03-23 | 2015-06-24 | 苏州市神龙门窗有限公司 | Preparation method of aluminum alloy section for doors/windows |
| CN105483575A (en) * | 2015-12-01 | 2016-04-13 | 北京有色金属研究总院 | Homogenizing annealing thermal treatment technology for A390 aluminum alloy cast ingot |
| CN108637607A (en) * | 2018-05-21 | 2018-10-12 | 晋西工业集团有限责任公司 | A kind of processing method of empennage frame semi-finished product |
| CN108774696A (en) * | 2018-06-20 | 2018-11-09 | 辽宁忠旺集团有限公司 | A kind of ultra-thin pipe extrudate production technology of 6 line aluminium alloys |
| CN110016577A (en) * | 2019-05-20 | 2019-07-16 | 江苏礼德铝业有限公司 | A kind of preparation method of aluminium alloy |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102489973B (en) | Method for manufacturing aluminum alloy hollow section for sedan bumper | |
| CN103667825B (en) | A kind of ultra-high-strength/tenacity anticorodal and manufacture method thereof | |
| CN104028961B (en) | A kind of middle strength aluminium alloy line and its production technology | |
| CN101536112B (en) | Wire conductor and process for producing the same | |
| CN102719709B (en) | Aluminium alloy wire with high strength and high electrical conductivity, and preparation method thereof | |
| CN105088113B (en) | Method for manufacturing aluminum alloy free forge piece for spaceflight | |
| CN102816958A (en) | Manufacturing method of aluminum alloy hollow section for aircraft empennage | |
| CN102876940B (en) | Manufacturing method of aluminum alloy thin plate with stable performance | |
| CN105543540B (en) | A kind of Cu-Cr-Zr alloy and preparation method thereof | |
| CN103276264B (en) | Low-cost and high-heat-strength wrought magnesium alloy and preparation method thereof | |
| CN102634705A (en) | Middle high strength aluminum alloy capable of reducing quench sensitivity, production process thereof and profile process method | |
| CN102851527B (en) | Copper-silver-magnesium alloy contact wire and preparation method thereof | |
| CN103769817B (en) | A kind of forming technology of major diameter high-strength heat-resistant magnesium alloy thick walled cylinder parts | |
| CN108103371B (en) | A kind of high-performance space flight fastener aluminium alloy wires production method | |
| CN105274408A (en) | Manufacturing method of aluminum alloy rivet wire for aerospace | |
| CN106480345A (en) | A kind of moderate strength, the manufacture method of good properties at high temperature aluminium alloy thick plate | |
| CN105200288A (en) | Ultra-high-strength Al alloy bar and production method thereof | |
| CN102864351A (en) | Aluminum profile and heating processing technology thereof | |
| CN103924142A (en) | Magnesium alloy and preparing method thereof | |
| CN107338379B (en) | A kind of magnesium-tin-zinc-aluminium-manganese wrought magnesium alloy and preparation method thereof | |
| CN104087803B (en) | A kind of creep resistance Dow metal and preparation method thereof | |
| CN102581000B (en) | Production method for rolling and cogging big cast ingot of high-carbon high-alloy cold-working die steel | |
| CN108754263A (en) | A kind of high intensity space flight aluminium lithium alloy proximate matter and preparation method thereof | |
| CN105543533B (en) | A kind of high-strength high-conductivity copper magnesium system alloy and preparation method thereof | |
| CN109554644B (en) | Aluminum alloy forging and preparation process thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20121212 |