CN104046873A - Deforming magnesium alloy for aviation - Google Patents
Deforming magnesium alloy for aviation Download PDFInfo
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- CN104046873A CN104046873A CN201410307412.XA CN201410307412A CN104046873A CN 104046873 A CN104046873 A CN 104046873A CN 201410307412 A CN201410307412 A CN 201410307412A CN 104046873 A CN104046873 A CN 104046873A
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- hafnium
- iridium
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Abstract
The invention discloses a deforming magnesium alloy for aviation, which is composed of the following components in percentage by weight: 86.4-90.9% of magnesium, 3.7-4.6% of zinc, 2.6-3.5% of zirconium, 1.3-2.3% of yttrium, 0.9-1.8% of hafnium and 0.5-1.4% of iridium. By adding the zinc, zirconium, yttrium, hafnium and iridium into the magnesium-base alloy, the deforming magnesium alloy has the characteristics of high specific strength, high specific elastic modulus, favorable heat dissipation property, favorable shock absorptivity, high impact load capacity and favorable corrosion resistance.
Description
Technical field
The present invention relates to a kind of alloy, be specifically related to a kind of aviation wrought magnesium alloys.
Background technology
Magnesium alloy is to add other elementary composition alloys taking magnesium as base.Be mainly used in the industrial sectors such as Aeronautics and Astronautics, transport, chemical industry, rocket.In practical metal, be the lightest metal, the proportion of magnesium is approximately 2/3 of aluminium, is 1/4 of iron.It is the lightest metal in practical metal, high strength, high rigidity.Along with the constant growth of productivity, the user demand of industrial magnesium alloy improves constantly, and existing magnesium alloy cannot meet the user demand in market gradually.
Summary of the invention
The object of the present invention is to provide that a kind of specific tenacity is high, larger than Young's modulus, good heat dissipation, shock absorbing is good, the loading capacity that withstands shocks large, the aviation wrought magnesium alloys of corrosion resistance and good.
Technical scheme of the present invention is, a kind of aviation wrought magnesium alloys, described aviation is combined by magnesium, zinc, zirconium, yttrium, hafnium and six kinds of metal ingredients of iridium with wrought magnesium alloys, described aviation is respectively with the shared weight percent of each composition in wrought magnesium alloys: described magnesium accounts for 86.4%-90.9%, described zinc accounts for 3.7%-4.6%, and described zirconium accounts for 2.6%-3.5%, and described yttrium accounts for 1.3%-2.3%, described hafnium accounts for 0.9%-1.8%, and described iridium accounts for 0.5%-1.4%.
In a preferred embodiment of the present invention, described aviation is specially with the shared weight percent of each composition in wrought magnesium alloys: described magnesium accounts for 90.4%, and described zinc accounts for 3.8%, described zirconium accounts for 2.7%, described yttrium accounts for 1.4%, and described hafnium accounts for 1.1%, and described iridium accounts for 0.6%.
In a preferred embodiment of the present invention, described aviation is specially with the shared weight percent of each composition in wrought magnesium alloys: described magnesium accounts for 86.9%, and described zinc accounts for 4.5%, described zirconium accounts for 3.4%, described yttrium accounts for 2.2%, and described hafnium accounts for 1.7%, and described iridium accounts for 1.3%.
Of the present invention is a kind of aviation wrought magnesium alloys, by add the metallic elements such as zinc, zirconium, yttrium, hafnium and iridium in the Magnuminium taking magnesium as base, has specific tenacity high, larger than Young's modulus, good heat dissipation, shock absorbing is good, the loading capacity that withstands shocks is large, the feature of corrosion resistance and good.
Embodiment
Below preferred embodiment of the present invention is described in detail, thereby so that advantages and features of the invention can be easier to be it will be appreciated by those skilled in the art that, protection scope of the present invention is made to more explicit defining.
Of the present invention is a kind of aviation wrought magnesium alloys, described aviation is combined by magnesium, zinc, zirconium, yttrium, hafnium and six kinds of metal ingredients of iridium with wrought magnesium alloys, described aviation is respectively with the shared weight percent of each composition in wrought magnesium alloys: described magnesium accounts for 86.4%-90.9%, described zinc accounts for 3.7%-4.6%, described zirconium accounts for 2.6%-3.5%, described yttrium accounts for 1.3%-2.3%, and described hafnium accounts for 0.9%-1.8%, and described iridium accounts for 0.5%-1.4%.
Further, described aviation is specially with the shared weight percent of each composition in wrought magnesium alloys: described magnesium accounts for 90.4%, and described zinc accounts for 3.8%, and described zirconium accounts for 2.7%, and described yttrium accounts for 1.4%, and described hafnium accounts for 1.1%, and described iridium accounts for 0.6%.
Further, described aviation is specially with the shared weight percent of each composition in wrought magnesium alloys: described magnesium accounts for 86.9%, and described zinc accounts for 4.5%, and described zirconium accounts for 3.4%, and described yttrium accounts for 2.2%, and described hafnium accounts for 1.7%, and described iridium accounts for 1.3%.
In addition, can be by regulating the Different Weight per-cent of each composition in alloy, the alloy property height obtaining is differed.
Of the present invention is a kind of aviation wrought magnesium alloys, by add the metallic elements such as zinc, zirconium, yttrium, hafnium and iridium in the Magnuminium taking magnesium as base, has specific tenacity high, larger than Young's modulus, good heat dissipation, shock absorbing is good, the loading capacity that withstands shocks is large, the feature of corrosion resistance and good.
The foregoing is only the specific embodiment of the present invention; but protection scope of the present invention is not limited to this; any those of ordinary skill in the art are in the disclosed technical scope of the present invention; the variation that can expect without creative work or replacement, within all should being encompassed in protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain that claims were limited.
Claims (3)
1. an aviation wrought magnesium alloys, it is characterized in that: described aviation wrought magnesium alloys is combined by magnesium, zinc, zirconium, yttrium, hafnium and six kinds of metal ingredients of iridium, described aviation is respectively with the shared weight percent of each composition in wrought magnesium alloys: described magnesium accounts for 86.4%-90.9%, described zinc accounts for 3.7%-4.6%, described zirconium accounts for 2.6%-3.5%, described yttrium accounts for 1.3%-2.3%, and described hafnium accounts for 0.9%-1.8%, and described iridium accounts for 0.5%-1.4%.
2. aviation wrought magnesium alloys according to claim 1, it is characterized in that: described aviation shared weight percent of each composition in wrought magnesium alloys is specially: described magnesium accounts for 90.4%, described zinc accounts for 3.8%, described zirconium accounts for 2.7%, described yttrium accounts for 1.4%, described hafnium accounts for 1.1%, and described iridium accounts for 0.6%.
3. aviation wrought magnesium alloys according to claim 1, it is characterized in that: described aviation shared weight percent of each composition in wrought magnesium alloys is specially: described magnesium accounts for 86.9%, described zinc accounts for 4.5%, described zirconium accounts for 3.4%, described yttrium accounts for 2.2%, described hafnium accounts for 1.7%, and described iridium accounts for 1.3%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410307412.XA CN104046873A (en) | 2014-07-01 | 2014-07-01 | Deforming magnesium alloy for aviation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410307412.XA CN104046873A (en) | 2014-07-01 | 2014-07-01 | Deforming magnesium alloy for aviation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104046873A true CN104046873A (en) | 2014-09-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410307412.XA Pending CN104046873A (en) | 2014-07-01 | 2014-07-01 | Deforming magnesium alloy for aviation |
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| CN (1) | CN104046873A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106350720A (en) * | 2016-10-17 | 2017-01-25 | 南京镐极信息技术有限公司 | Heat-resisting cast magnesium alloy containing hafnium and preparation method thereof |
| CN107201470A (en) * | 2017-05-10 | 2017-09-26 | 上海大学 | A kind of magnesium alloy for having high heat dispersion, excellent mechanical performances concurrently and preparation method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101405417A (en) * | 2006-03-20 | 2009-04-08 | 国立大学法人熊本大学 | High-strength high-toughness magnesium alloy and method for producing the same |
| JP2013252538A (en) * | 2012-06-07 | 2013-12-19 | Kumamoto Univ | Joining method of magnesium alloy and joint structure of magnesium alloy |
-
2014
- 2014-07-01 CN CN201410307412.XA patent/CN104046873A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101405417A (en) * | 2006-03-20 | 2009-04-08 | 国立大学法人熊本大学 | High-strength high-toughness magnesium alloy and method for producing the same |
| JP2013252538A (en) * | 2012-06-07 | 2013-12-19 | Kumamoto Univ | Joining method of magnesium alloy and joint structure of magnesium alloy |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106350720A (en) * | 2016-10-17 | 2017-01-25 | 南京镐极信息技术有限公司 | Heat-resisting cast magnesium alloy containing hafnium and preparation method thereof |
| CN107201470A (en) * | 2017-05-10 | 2017-09-26 | 上海大学 | A kind of magnesium alloy for having high heat dispersion, excellent mechanical performances concurrently and preparation method thereof |
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Application publication date: 20140917 |