CN112547826A - Magnesium alloy forming method with gradient temperature and rate field - Google Patents
Magnesium alloy forming method with gradient temperature and rate field Download PDFInfo
- Publication number
- CN112547826A CN112547826A CN202011544188.8A CN202011544188A CN112547826A CN 112547826 A CN112547826 A CN 112547826A CN 202011544188 A CN202011544188 A CN 202011544188A CN 112547826 A CN112547826 A CN 112547826A
- Authority
- CN
- China
- Prior art keywords
- magnesium alloy
- forming
- temperature
- pass
- component
- 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.)
- Granted
Links
- 229910000861 Mg alloy Inorganic materials 0.000 title claims abstract description 36
- 238000000034 method Methods 0.000 title claims abstract description 28
- 238000003825 pressing Methods 0.000 claims abstract description 21
- 230000008569 process Effects 0.000 claims abstract description 14
- 238000001125 extrusion Methods 0.000 claims abstract description 7
- 238000005266 casting Methods 0.000 claims abstract description 6
- 238000004455 differential thermal analysis Methods 0.000 claims abstract description 6
- 230000007704 transition Effects 0.000 claims abstract description 6
- 239000000956 alloy Substances 0.000 claims abstract description 3
- 230000003746 surface roughness Effects 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- RPNUMPOLZDHAAY-UHFFFAOYSA-N Diethylenetriamine Chemical compound NCCNCCN RPNUMPOLZDHAAY-UHFFFAOYSA-N 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/02—Making uncoated products
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Extrusion Of Metal (AREA)
Abstract
The invention discloses a magnesium alloy forming method of a gradient temperature and rate field, which comprises the following steps: extruding the casting blank, wherein the extrusion ratio is more than 5; measuring the lowest phase transition temperature T1 of the magnesium alloy material through differential thermal analysis; determining the assembly forming times N according to the shape characteristics of the component, wherein N is more than or equal to 2; the temperature Tn = T1-120N/N of the forming blank of the nth pass, the temperature Tn = T1-120+120N/N of the forming die of the nth pass, and N is more than or equal to 1; and in the nth forming process, the pressing rate S =20-12N/N of the hydraulic press. The invention solves the problem of low isothermal forming performance of the magnesium alloy empennage component, and the prepared empennage component has excellent surface quality, good strength and toughness and excellent comprehensive performance.
Description
Technical Field
The invention relates to a method for forming a cylindrical aircraft empennage component, in particular to a method for forming magnesium alloy in a gradient temperature and velocity field.
Background
The magnesium alloy has the characteristics of low density, high specific strength, excellent electromagnetic shielding performance and the like, and has wide application in the fields of aerospace, national defense and military industry, automobiles, electronics and the like. Compared with cast magnesium alloy, the wrought magnesium alloy has higher strength and wider application range, but the prior wrought magnesium alloy member has the main problems in the preparation process: firstly, forgings are not refined, plate/rod machines are mostly adopted for addition forming, and due to the discontinuity of a deformation flow line, the performance is low, the preparation period is long, and the cost is high; and secondly, for a complex component, a multi-pass forming method is required, but different magnesium alloy and aluminum alloy are subjected to multi-pass heating forming, so that the performance is gradually reduced, namely, the performance is reduced once every time the heating forming is carried out, and the final service performance of the component is deteriorated.
Among the prior art, document CN206123180U discloses an aluminum extrusion tail wing cylinder inner circle processing tool, including a positioning cylinder and a locking screw, the inner diameter of the positioning cylinder matches with the outer diameter of the cylindrical portion of the extruded tail wing cylinder product, the inner ring surface of the positioning cylinder is outwardly opened with six axial grooves matching with the outer circumferential axial ridges of the extruded tail wing cylinder product, wherein, the three axial grooves and the outer circumferential axial ridges of the extruded tail wing cylinder product are in small clearance fit, in addition, the three axial grooves and the outer circumferential axial ridges of the extruded tail wing cylinder product are in large clearance fit, and the axial ridges of the small clearance fit and the axial ridges of the large clearance fit are alternately arranged. However, the performance of the empennage extruded by the tool is still relatively common.
Disclosure of Invention
The invention aims to provide a magnesium alloy forming method with gradient temperature and velocity fields, which is used for preparing a magnesium alloy empennage component with excellent performance.
In order to achieve the above object, the present invention adopts the following technical solutions.
A magnesium alloy forming method with gradient temperature and velocity fields is characterized by comprising the following steps:
step 1, extruding a casting blank, wherein the extrusion ratio is more than 5;
step 2, measuring the lowest phase transition temperature T1 of the magnesium alloy material through differential thermal analysis;
step 3, determining the assembly shape times N according to the shape characteristics of the component, wherein N is more than or equal to 2;
step 4, the temperature Tn = T1-120N/N of the forming blank of the nth pass, the temperature Tn = T1-120+120N/N of the forming die of the nth pass, and N is more than or equal to 1;
step 5, in the nth-pass forming process, the pressing rate S =20-12N/N of the hydraulic press;
the component is an AZ80 magnesium alloy component or an Mg-Gd-Y magnesium alloy component.
Preferably, the member is a tail member, and the number of times of assembly forming N is equal to the number of the tail.
Has the advantages that: the invention solves the problem of low isothermal forming performance of the magnesium alloy empennage component, and the prepared empennage component has excellent surface quality, good strength and toughness and excellent comprehensive performance.
Detailed Description
The present invention is further illustrated but the following examples are only for the purpose of helping understanding the principle of the present invention and the core idea thereof and are not intended to limit the scope of the present invention. It should be noted that modifications to the invention as described herein, which do not depart from the principles of the invention, are intended to be within the scope of the claims which follow.
Example 1
A magnesium alloy forming method of gradient temperature and velocity field specifically adopts AZ80 magnesium alloy blank to prepare a cylindrical aircraft empennage component, the number of empennages is two, and the steps are as follows:
step 1, extruding a casting blank with an extrusion ratio of 6;
step 2, measuring the lowest phase transition temperature T1=420 ℃ in the magnesium alloy through differential thermal analysis;
step 3, designing a forming process according to the shape and the number of the empennages, and determining the total forming times 2;
step 4, according to the nth-pass forming blank temperature Tn = T1-120N/N and the nth-pass forming die temperature
Tn = T1-120+120N/N ", determining the process temperature, specifically, the temperature of the 1 st-pass forming blank is 360 ℃, and the temperature of the 1 st-pass forming die is 360 ℃; the temperature of the 2 nd-pass formed blank is 300 ℃, and the temperature T of the 2 nd-pass forming dien=420℃；
Determining the pressing rate of the hydraulic machine according to the pressing rate S =20-12N/N of the hydraulic machine in the forming process of the nth pass, wherein the pressing rate of the hydraulic machine is 14mm/S in the forming process of the 1 st pass; and in the 2 nd forming process, the pressing rate of the hydraulic press is S =8 mm/S.
The mechanical property test of the obtained aircraft empennage component is carried out, the tensile strength is 379MPa, the elongation after fracture is 10.0 percent, and the surface roughness grade of the component is IT9 grade.
Example 2
A magnesium alloy forming method of gradient temperature and velocity field specifically adopts Mg-8.5Gd-4.5Y-0.7 Zn-0.4 Zr magnesium alloy blank to prepare a cylindrical aircraft empennage component, the number of empennages is four, and the steps are as follows:
step 1, extruding a casting blank with an extrusion ratio of 12;
step 2, measuring the lowest phase transition temperature T1=520 ℃ in the magnesium alloy through differential thermal analysis;
step 3, designing a forming process according to the shape and the number of the empennages, and determining the total forming times N = 4;
step 4, determining the process temperature according to the nth-pass forming blank temperature Tn = T1-120N/N and the nth-pass forming die temperature Tn = T1-120+120N/N, wherein specifically, the 1 st-pass forming blank temperature is 490 ℃, and the 1 st-pass forming die temperature is 430 ℃; the temperature of the 2 nd-pass formed blank is 460 ℃, and the temperature of the 2 nd-pass forming die is 460 ℃; the temperature of the 3 rd-pass formed blank is 430 ℃, and the temperature of the 3 rd-pass formed die is 490 ℃; the temperature of the 4 th-pass formed blank is 400 ℃, and the temperature of the 4 th-pass formed die is 520 ℃;
and determining the pressing rate of the hydraulic machine according to the pressing rate S =20-12N/N of the hydraulic machine in the N-th-pass forming process, wherein the pressing rate of the hydraulic machine for the 1-pass forming is 17mm/S, the pressing rate of the hydraulic machine for the 2-nd-pass forming is 14mm/S, the pressing rate of the hydraulic machine for the 3-rd-pass forming is 11mm/S, and the pressing rate of the hydraulic machine for the 4-th-pass forming is 8 mm/S.
The mechanical property test of the obtained aircraft empennage member is carried out, the tensile strength is 493MPa, the elongation after fracture is 11.3%, and the surface roughness grade of the member is IT9 grade.
Example 3
A magnesium alloy forming method of gradient temperature and velocity field specifically adopts Mg-7.8Gd-4.6Y-0.4Zn-0.2Zr magnesium alloy blank to prepare a cylindrical aircraft empennage component, the number of empennages is six, and the steps are as follows:
step 1, extruding a casting blank, wherein the extrusion ratio is 15;
step 2, measuring the lowest phase transition temperature T1=520.3 ℃ in the magnesium alloy through differential thermal analysis;
step 3, designing a forming process according to the shape and the number of the empennages, and determining the total forming times N = 6;
step 4, determining the process temperature according to the nth-pass forming blank temperature Tn = T1-120N/N and the nth-pass forming die temperature Tn = T1-120+120N/N, wherein the 1 st-pass forming blank temperature is 500.3 ℃, and the 1 st-pass forming die temperature is 420.3 ℃; the temperature of the 2 nd-pass forming blank is 480.3 ℃, and the temperature of the 2 nd-pass forming die is 440.3 ℃; the temperature of the 3 rd-pass formed blank is 460.3 ℃, and the temperature of the 3 rd-pass formed die is 460.3 ℃; the temperature of the 4 th-pass formed blank is 440.3 ℃, and the temperature of the 4 th-pass forming die is 480.3 ℃; the temperature of the 5 th-pass formed blank is 420.3 ℃, and the temperature of the 5 th-pass forming die is 500.3 ℃; the temperature of the 6 th-pass formed blank is 400.3 ℃, and the temperature of the 6 th-pass forming die is 520.3 ℃;
and determining the pressing rate of the hydraulic machine according to the pressing rate S =20-12N/N of the hydraulic machine in the nth-pass forming process, wherein the pressing rate of the hydraulic machine for the 1 st-pass forming is 18mm/S, the pressing rate of the hydraulic machine for the 2 nd-pass forming is 16mm/S, the pressing rate of the hydraulic machine for the 3 rd-pass forming is 14mm/S, the pressing rate of the hydraulic machine for the 4 th-pass forming is 12mm/S, the pressing rate of the hydraulic machine for the 5 th-pass forming is 10mm/S, and the pressing rate of the hydraulic machine for the 6 th-pass forming is 8 mm/S.
The mechanical property test of the obtained aircraft empennage component is carried out, the tensile strength is 498MPa, the elongation after fracture is 11.4 percent, and the surface roughness grade of the component is IT9 grade.
Claims (3)
1. A magnesium alloy forming method with gradient temperature and velocity fields is characterized by comprising the following steps:
step 1, extruding a casting blank, wherein the extrusion ratio is more than 5;
step 2, measuring the lowest phase transition temperature T1 of the magnesium alloy material through differential thermal analysis;
step 3, determining the assembly shape times N according to the shape characteristics of the component, wherein N is more than or equal to 2;
step 4, the temperature Tn = T1-120N/N of the forming blank of the nth pass, the temperature Tn = T1-120+120N/N of the forming die of the nth pass, and N is more than or equal to 1;
step 5, in the nth-pass forming process, the pressing rate S =20-12N/N of the hydraulic press;
the component is an AZ80 magnesium alloy component or an Mg-Gd-Y magnesium alloy component.
2. The magnesium alloy forming method according to claim 1, characterized in that: the structural member is a tail wing structural member of the cylindrical aircraft, and the number of assembly forming times N is equal to the number of tail wings of the cylindrical aircraft.
3. The magnesium alloy forming method according to claim 1 or 2, characterized in that: the Mg-Gd-Y magnesium alloy component is a Mg-8.5Gd-4.5Y-0.7 Zn-0.4 Zr magnesium alloy component or a Mg-7.8Gd-4.6Y-0.4Zn-0.2Zr magnesium alloy component.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011544188.8A CN112547826B (en) | 2020-12-24 | 2020-12-24 | Magnesium alloy forming method with gradient temperature and rate field |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011544188.8A CN112547826B (en) | 2020-12-24 | 2020-12-24 | Magnesium alloy forming method with gradient temperature and rate field |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112547826A true CN112547826A (en) | 2021-03-26 |
| CN112547826B CN112547826B (en) | 2022-11-11 |
Family
ID=75031058
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011544188.8A Active CN112547826B (en) | 2020-12-24 | 2020-12-24 | Magnesium alloy forming method with gradient temperature and rate field |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112547826B (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101020201A (en) * | 2007-03-16 | 2007-08-22 | 清华大学 | Semi-solid multi-blank extruding process and apparatus for forming double-layer composite pipe |
| CN101121980A (en) * | 2007-09-20 | 2008-02-13 | 王仁辉 | Technique for processing high-strength high-tractility magnesium alloy member |
| CN101716593A (en) * | 2009-12-04 | 2010-06-02 | 湖南大学 | Magnesium alloy sheet rolling method |
| CN101857936A (en) * | 2010-07-05 | 2010-10-13 | 重庆大学 | Method for preparing magnesium alloy |
| CN102304685A (en) * | 2011-10-13 | 2012-01-04 | 中国兵器工业第五九研究所 | Preparation method of fine grain magnesium alloy |
| CN103240292A (en) * | 2013-04-12 | 2013-08-14 | 河南理工大学 | Production method and device for magnesium alloy thin-wall pipe |
| CN103388115A (en) * | 2012-05-07 | 2013-11-13 | 中国兵器工业第五九研究所 | Preparation method of high-toughness magnesium alloy bar |
| CN104162555A (en) * | 2014-05-28 | 2014-11-26 | 哈尔滨工业大学（威海） | Semi-solid thixotropic-plastic compound forming method |
| CN106607665A (en) * | 2015-10-23 | 2017-05-03 | 中国兵器工业第五九研究所 | Forming method for magnesium alloy component |
| CN108624830A (en) * | 2018-04-18 | 2018-10-09 | 长沙新材料产业研究院有限公司 | A kind of magnesium alloy structural part and its extruding production |
| US20200269298A1 (en) * | 2019-02-22 | 2020-08-27 | Qilu University Of Technology | Preparation method for a high-strength extruded profile of mg-zn-sn-mn alloy |
-
2020
- 2020-12-24 CN CN202011544188.8A patent/CN112547826B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101020201A (en) * | 2007-03-16 | 2007-08-22 | 清华大学 | Semi-solid multi-blank extruding process and apparatus for forming double-layer composite pipe |
| CN101121980A (en) * | 2007-09-20 | 2008-02-13 | 王仁辉 | Technique for processing high-strength high-tractility magnesium alloy member |
| CN101716593A (en) * | 2009-12-04 | 2010-06-02 | 湖南大学 | Magnesium alloy sheet rolling method |
| CN101857936A (en) * | 2010-07-05 | 2010-10-13 | 重庆大学 | Method for preparing magnesium alloy |
| CN102304685A (en) * | 2011-10-13 | 2012-01-04 | 中国兵器工业第五九研究所 | Preparation method of fine grain magnesium alloy |
| CN103388115A (en) * | 2012-05-07 | 2013-11-13 | 中国兵器工业第五九研究所 | Preparation method of high-toughness magnesium alloy bar |
| CN103240292A (en) * | 2013-04-12 | 2013-08-14 | 河南理工大学 | Production method and device for magnesium alloy thin-wall pipe |
| CN104162555A (en) * | 2014-05-28 | 2014-11-26 | 哈尔滨工业大学（威海） | Semi-solid thixotropic-plastic compound forming method |
| CN106607665A (en) * | 2015-10-23 | 2017-05-03 | 中国兵器工业第五九研究所 | Forming method for magnesium alloy component |
| CN108624830A (en) * | 2018-04-18 | 2018-10-09 | 长沙新材料产业研究院有限公司 | A kind of magnesium alloy structural part and its extruding production |
| US20200269298A1 (en) * | 2019-02-22 | 2020-08-27 | Qilu University Of Technology | Preparation method for a high-strength extruded profile of mg-zn-sn-mn alloy |
Non-Patent Citations (2)
| Title |
|---|
| 代帅等: "热挤压Mg-6Zn-xCu-0.6Zr(x=0,0.5,1.0,1.5)合金的显微组织及力学性能", 《热加工工艺》 * |
| 曹凤红等: "Zn、Y质量比对半连铸ZK系镁合金组织与性能的影响", 《特种铸造及有色合金》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112547826B (en) | 2022-11-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105358270A (en) | Methods for producing forged products and other worked products | |
| CN107803407B (en) | A kind of automobile batteries packet frame thin-walled big cross section hollow profile production technology | |
| CN103862228B (en) | A kind of preparation processing method of aluminum matrix composite large thin-wall housing | |
| CN113560362B (en) | High-performance magnesium alloy variable-section extrusion-torsion composite processing device and preparation process thereof | |
| Śliwa et al. | Metal forming of lightweight magnesium alloys for aviation applications | |
| US20160108505A1 (en) | Method for producing starting material for cutting | |
| RU2347648C2 (en) | Reinforced composite mechanical part and method of its fabrication | |
| CN109772922A (en) | A kind of crowded upsetting mold squeezes upsetting processing method and magnesium alloy center collet | |
| CN102601147B (en) | Mould for multi-blank equal-channel angular welding extruded molded pipe | |
| CN103962487A (en) | Large-scale solid-forging metal framework with lugs and manufacturing method thereof | |
| CN111715714B (en) | Rotary extrusion forming method for aluminum-magnesium alloy cup-shaped piece | |
| CN105171356A (en) | Machining method of high-precision and large-diameter ultralong and ultrathin shell | |
| CN110883124A (en) | Extrusion-rolling integrated forming method of titanium alloy continuous casting tube blank | |
| CN115351109A (en) | Magnesium alloy extrusion die and extrusion method | |
| CN112547826B (en) | Magnesium alloy forming method with gradient temperature and rate field | |
| CN109622648B (en) | Asymmetric continuous large-deformation extrusion forming method for magnesium alloy | |
| CN106881369B (en) | A kind of two-way composite extrusion die and extrusion process of magnesium alloy plate and belt | |
| CN106011514A (en) | Ultra-high-strength Ti-based composite material preparation method by repeated equal-channel 45-degree equal-channel angular pressing | |
| CN105970129A (en) | Low-stress manufacturing process for eliminating anisotropism of 2A12 aluminum alloy forging | |
| CN109675947A (en) | A kind of continuous soldering pressing method of the repetition of Refining Mg Alloy crystal grain | |
| CN202498093U (en) | Mould for extrusion forming of tubes | |
| US20150246393A1 (en) | Method of manufacturing connecting rod by using semi-closed sinter forging | |
| CN111715720B (en) | Rotary extrusion forming die for aluminum-magnesium alloy cup-shaped piece | |
| CN110756710B (en) | Preparation method of deep blind hole component | |
| Choi et al. | Forming of the precision aluminum tube for a light weight propeller shaft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240322 Address after: 400039 Chongqing Jiulongpo Yuzhou Road No. 33 Patentee after: Southwest Institute of technology and engineering of China Ordnance Equipment Group Country or region after: China Address before: 400039 Chongqing Jiulongpo Yuzhou Road No. 33 Patentee before: NO 59 Research Institute OF CHINA ORDNACE INDUSTRY Country or region before: China |
|
| TR01 | Transfer of patent right |