CN102628122B - Magnesium, manganese and copper based light alloy material for large airplane devices - Google Patents
Magnesium, manganese and copper based light alloy material for large airplane devices Download PDFInfo
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- CN102628122B CN102628122B CN2012101237941A CN201210123794A CN102628122B CN 102628122 B CN102628122 B CN 102628122B CN 2012101237941 A CN2012101237941 A CN 2012101237941A CN 201210123794 A CN201210123794 A CN 201210123794A CN 102628122 B CN102628122 B CN 102628122B
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Abstract
The invention provides a magnesium, manganese and copper based light alloy material for large airplane devices. The alloy comprises the following components by weight percentage: 0.3-0.8% of magnesium, 1.0-2.0% of manganese, 29-31% of zinc and balance of copper. Manganese with proper amount is added in on the basis of traditional magnesium-added copper-based alloy, so that ductility of the material is ensured, and simultaneously hardness of the alloy is properly improved, and tubular materials or rod materials can be prevented from deforming when being extruded. Zinc content is simultaneously greatly improved to 29-31%, cost of materials is reduced, and simultaneously lightness, ductility and tensile property of the alloy are maintained. Further specific gravity of zinc is relatively small, and copper is replaced by proper amount of copper so that self weight of the material can be reduced, and the quality requirements for light accessories of large airplane device products can be met. Simultaneously the structure that wires of magnesium and copper alloy can only be produced singly is broken, and various rod materials and tube materials can be produced.
Description
Technical field
The present invention relates to the alloy field, relate in particular to a kind of large aircraft equipment magnesium copper-manganese base light alloy material.
Background technology
The copper base alloy that adds magnesium is light alloy material commonly used in large aircraft equipment industry, it has good lightweight and ductility, be widely used in the stressed part that various deep-draws and bending are manufactured, as pin, rivet, packing ring, nut, conduit, weather gage, screen cloth, heat sink part etc.Traditional magnesium copper base alloy that adds, as the GB QMg0.8 trade mark, add the magnesium copper base alloy, contain 0.002% tin, each zinc, iron and lead of 0.005%, 0.06% nickel and the copper of surplus, yet existing GB adds the magnesium copper base alloy and has good ductility, and hardness is lower, generally be no more than 70HB, when this alloy in the situation that diameter is greater than 9mm, yielding after extruded bars or tubing, yield rate generally is no more than 30%.So.After can only producing the blank material below ￠ 9mm with continuous casting, through finish draw, make the wire rod of all kinds of specifications, so adding magnesium copper alloy, can only, with wire cut, can't supply with all kinds of bars or tubing form, so can't meet the demand of just growing large aircraft equipment industry this kind.
Summary of the invention
The purpose of this invention is to provide a kind of have lightweight and ductility, again can be with the large aircraft equipment of bar and tubing supply magnesium copper-manganese base light alloy material.
In order to achieve the above object, the present invention adopts following technical scheme:
A kind of large aircraft equipment, with magnesium copper-manganese base light alloy material, is characterized in that, in this alloy compositions, comprises magnesium, manganese, zinc and copper, and each component composition of its interalloy is respectively by weight percentage: magnesium 0.3-0.8%, and manganese 1.0-2.0%, zinc 29-31%, surplus is copper.
Further, each component composition of alloy is respectively by weight percentage: magnesium 0.3%, and manganese 1.0%, zinc 29%, surplus is copper.
Further, each component composition of alloy is respectively by weight percentage: magnesium 0.5%, and manganese 1.5%, zinc 30%, surplus is copper.
Further, each component composition of alloy is respectively by weight percentage: magnesium 0.8%, and manganese 2.0%, zinc 31%, surplus is copper.
A kind of above-mentioned large aircraft equipment making method of magnesium copper-manganese base light alloy material comprises the following steps:
I. by proportioning, Dian Xie Tong ﹑ Mei ﹑ Meng ﹑ zinc is placed in main frequency furnace, is heated to 1650 ℃-1750 ℃ and after fusing, is incubated to 1680 ℃ fully;
Ii. adopt horizontal continuity vibrational casting method to be cast as solid alloy pig;
Iii. solid alloy pig is positioned in the box type vacuum annealing furnace and anneals, be placed on naturally cooling in air;
Iv. cooled copper ingot is removed surperficial oxide skin with light ingot machine, after be placed in the alloy pig process furnace;
V. adopt the alloy pig after hydraulic extrusion press will heat to be squeezed into alloy bar material or tubing;
Vi. after pushing, product carries out eddy current test.
Further, the annealing time in step I ii. is 3.3-3.5 hour, and annealing temperature is 480 ℃-490 ℃.
Further, the furnace temp in step I v. is controlled at 660 ℃-680 ℃.
Further, in step vi., the eddy current test gain is 33dB, and phase place is 129Deg, is filtered into 17N, and frequency is 5.4KHz.
Advantage of the present invention and beneficial effect:
Large aircraft equipment provided by the invention magnesium copper-manganese base light alloy material, on the basis of traditional copper base alloy that adds magnesium, add appropriate manganese, when guaranteeing material ductility, suitable put forward heavy alloyed hardness, indeformable when preventing extruded tube or bar.Simultaneously significantly promote the content of zinc to 29-31%, the lightweight, ductility and the tensile property that when reducing material cost, have kept alloy, and the proportion of zinc is smaller, with appropriate zinc, replace copper and help to reduce the weight of material own, more be conducive to the specification of quality of large aircraft equipment product to the lightweight accessory.Break simultaneously the general layout that original magnesium copper alloy can only single production wire rod, also can produce all kinds of bars and tubing.
Embodiment
In order to make purpose of the present invention, technical scheme and advantage clearer, below in conjunction with drawings and Examples, the present invention is further elaborated.Should be appreciated that specific embodiment described herein, only in order to explain the present invention, is not intended to limit the present invention.
A kind of large aircraft equipment, with magnesium copper-manganese base light alloy material, comprises magnesium, manganese, zinc and copper in this alloy compositions, each component composition of its interalloy is respectively by weight percentage: magnesium 0.3-0.8%, and manganese 1.0-2.0%, zinc 29-31%, surplus is copper.
Further, each component composition of alloy is respectively by weight percentage: magnesium 0.3%, and manganese 1.0%, zinc 29%, surplus is copper.
Further, each component composition of alloy is respectively by weight percentage: magnesium 0.5%, and manganese 1.5%, zinc 30%, surplus is copper.
Further, each component composition of alloy is respectively by weight percentage: magnesium 0.8%, and manganese 2.0%, zinc 31%, surplus is copper.
A kind of making method of above-mentioned large aircraft equipment magnesium copper-manganese base light alloy material comprises the following steps:
I. by proportioning, Dian Xie Tong ﹑ Mei ﹑ Meng ﹑ zinc is placed in main frequency furnace, is heated to 1650 ℃-1750 ℃ and after fusing, is incubated to 1680 ℃ fully;
Ii. adopt horizontal continuity vibrational casting method to be cast as solid alloy pig;
Iii. solid alloy pig is positioned in the box type vacuum annealing furnace and anneals, be placed on naturally cooling in air;
Iv. cooled copper ingot is removed surperficial oxide skin with light ingot machine, after be placed in the alloy pig process furnace;
V. adopt the alloy pig after hydraulic extrusion press will heat to be squeezed into alloy bar material or tubing;
Vi. after pushing, product carries out eddy current test.
Further, the annealing time in step I ii. is 3.3-3.5 hour, and annealing temperature is 480 ℃-490 ℃.
Further, the furnace temp in step I v. is controlled at 660 ℃-680 ℃.
Further, in step vi., the eddy current test gain is 33dB, and phase place is 129Deg, is filtered into 17N, and frequency is 5.4KHz.
Large aircraft equipment provided by the invention magnesium copper-manganese base light alloy material, on traditional basis that adds the magnesium copper base alloy, added appropriate manganese, and the zinc that will wherein contain significantly is promoted to 29-31%, this kind magnesium copper-manganese base alloy has good lightweight and ductility, wire rod not only can be produced, also all kinds of bars and tubing can be produced.The parameter of having described in following table between wire rod, bar and the tubing that adopts alloy production of the present invention compares.
Table 1
Embodiment 1
A kind of large aircraft equipment is respectively magnesium 0.3% by weight percentage with magnesium copper-manganese base light alloy material, each component composition of this alloy, manganese 1.0%, and zinc 29%, surplus is copper.
The above-mentioned large aircraft equipment making method of magnesium copper-manganese base light alloy material comprises the following steps:
I. press magnesium 0.3%, manganese 1.0%, zinc 29%, surplus is that the proportioning of copper is placed in Dian Xie Tong ﹑ Mei ﹑ Meng ﹑ zinc in main frequency furnace, is heated to 1650 ℃-1750 ℃ and after fusing, is incubated to 1680 ℃ fully;
Ii. adopt horizontal continuity vibrational casting method to be cast as solid alloy pig; Its external diameter is that 130mm, length are 450mm.
Iii. solid alloy pig is positioned over to annealing 3.3-3.5 hour in the box type vacuum annealing furnace, annealing temperature is controlled at 480 ℃-490 ℃, and the alloy pig after then annealing, from annealing furnace, taking out, is placed in the air naturally cooling;
Iv. cooled copper ingot is removed surperficial oxide skin fully with light ingot machine, external diameter is machined to 127mm by 130mm, after be placed in the alloy pig process furnace, heating and temperature control is at 660 ℃-680 ℃;
V. adopt the alloy pig after 1800 tons of extrusion machines of hydraulic pressure will heat to be squeezed into alloy bar material or the tubing that external diameter is 40-50mm, tube wall thickness generally is more than or equal to 5mm;
Vi. after pushing, product carries out eddy current test, gains as 33dB, and phase place is 129Deg, is filtered into 17N, and frequency is 5.4KHz, the finished product packing warehouse-in.
Through overtesting, lightweight, the ductility of the above alloy all are largely increased, in conjunction with deformation rate, also having obtained larger improvement.As shown in table 1, its diameter of general wire rod is in the 0.35mm left and right, for the unannealed state of cold working, its tensile strength is in the 780MPa left and right, elongation is not less than 0.45%, deformation rate is usually in 46 left and right, and large aircraft equipment provided by the invention magnesium copper-manganese base alloy, during for bar, its diameter is 10-30mm, during for tubing, can reach 20-50mm, and its hardness level is also higher than wire rod, simultaneously, during for bar, its tensile strength is increased to 850MPa, elongation significantly is promoted to and is not less than 1.6%, deformation rate is promoted to 52, equally, during for tubing, its tensile strength also can reach 658MPa, elongation further is promoted to 2.1%, deformation rate also reaches 57.Visible, no matter large aircraft equipment provided by the present invention, with magnesium copper-manganese base alloy, is that ductility or tensile property have all obtained significantly improving.
Embodiment 2
A kind of large aircraft equipment is respectively magnesium 0.5% by weight percentage with magnesium copper-manganese base light alloy material, each component composition of this alloy, manganese 1.5%, and zinc 30%, surplus is copper.
The above-mentioned large aircraft equipment making method of magnesium copper-manganese base light alloy material comprises the following steps:
I. press magnesium 0.5%, manganese 1.5%, zinc 30%, surplus is that the proportioning of copper is placed in Dian Xie Tong ﹑ Mei ﹑ Meng ﹑ zinc in main frequency furnace, is heated to 1650 ℃-1750 ℃ and after fusing, is incubated to 1680 ℃ fully;
Ii. adopt horizontal continuity vibrational casting method to be cast as solid alloy pig; Its external diameter is that 130mm, length are 450mm.
Iii. solid alloy pig is positioned over to annealing 3.3-3.5 hour in the box type vacuum annealing furnace, annealing temperature is controlled at 480 ℃-490 ℃, and the alloy pig after then annealing, from annealing furnace, taking out, is placed in the air naturally cooling;
Iv. cooled copper ingot is removed surperficial oxide skin fully with light ingot machine, external diameter is machined to 127mm by 130mm, after be placed in the alloy pig process furnace, heating and temperature control is at 660 ℃-680 ℃;
V. adopt the alloy pig after 1800 tons of extrusion machines of hydraulic pressure will heat to be squeezed into alloy bar material or the tubing that external diameter is 40-50mm, tube wall thickness generally is more than or equal to 5mm;
Vi. after pushing, product carries out eddy current test, gains as 33dB, and phase place is 129Deg, is filtered into 17N, and frequency is 5.4KHz, the finished product packing warehouse-in.
Through overtesting, lightweight, the ductility of the above alloy all are largely increased, in conjunction with deformation rate, also having obtained larger improvement.As shown in table 1, its diameter of general wire rod is in the 0.35mm left and right, for the unannealed state of cold working, its tensile strength is in the 780MPa left and right, elongation is not less than 0.45%, deformation rate is usually in 46 left and right, and large aircraft equipment provided by the invention magnesium copper-manganese base alloy, during for bar, its diameter is 10-30mm, during for tubing, can reach 20-50mm, and its hardness level is also higher than wire rod, simultaneously, during for bar, its tensile strength is increased to 850MPa, elongation significantly is promoted to and is not less than 1.6%, deformation rate is promoted to 52, equally, during for tubing, its tensile strength also can reach 658MPa, elongation further is promoted to 2.1%, deformation rate also reaches 57.Visible, no matter large aircraft equipment provided by the present invention, with magnesium copper-manganese base alloy, is that ductility or tensile property have all obtained significantly improving.
Embodiment 3
A kind of large aircraft equipment is respectively magnesium 0.8% by weight percentage with magnesium copper-manganese base light alloy material, each component composition of this alloy, manganese 2.0%, and zinc 31%, surplus is copper.
The above-mentioned large aircraft equipment making method of magnesium copper-manganese base light alloy material comprises the following steps:
I. press magnesium 0.8%, manganese 2.0%, zinc 31%, surplus is that the proportioning of copper is placed in Dian Xie Tong ﹑ Mei ﹑ Meng ﹑ zinc in main frequency furnace, is heated to 1650 ℃-1750 ℃ and after fusing, is incubated to 1680 ℃ fully;
Ii. adopt horizontal continuity vibrational casting method to be cast as solid alloy pig; Its external diameter is that 130mm, length are 450mm.
Iii. solid alloy pig is positioned over to annealing 3.3-3.5 hour in the box type vacuum annealing furnace, annealing temperature is controlled at 480 ℃-490 ℃, and the alloy pig after then annealing, from annealing furnace, taking out, is placed in the air naturally cooling;
Iv. cooled copper ingot is removed surperficial oxide skin fully with light ingot machine, external diameter is machined to 127mm by 130mm, after be placed in the alloy pig process furnace, heating and temperature control is at 660 ℃-680 ℃;
V. adopt the alloy pig after 1800 tons of extrusion machines of hydraulic pressure will heat to be squeezed into alloy bar material or the tubing that external diameter is 40-50mm, tube wall thickness generally is more than or equal to 5mm;
Vi. after pushing, product carries out eddy current test, gains as 33dB, and phase place is 129Deg, is filtered into 17N, and frequency is 5.4KHz, the finished product packing warehouse-in.
Through overtesting, lightweight, the ductility of the above alloy all are largely increased, in conjunction with deformation rate, also having obtained larger improvement.As shown in table 1, its diameter of general wire rod is in the 0.35mm left and right, for the unannealed state of cold working, its tensile strength is in the 780MPa left and right, elongation is not less than 0.45%, deformation rate is usually in 46 left and right, and large aircraft equipment provided by the invention magnesium copper-manganese base alloy, during for bar, its diameter is 10-30mm, during for tubing, can reach 20-50mm, and its hardness level is also higher than wire rod, simultaneously, during for bar, its tensile strength is increased to 850MPa, elongation significantly is promoted to and is not less than 1.6%, deformation rate is promoted to 52, equally, during for tubing, its tensile strength also can reach 658MPa, elongation further is promoted to 2.1%, deformation rate also reaches 57.Visible, no matter large aircraft equipment provided by the present invention, with magnesium copper-manganese base alloy, is that ductility or tensile property have all obtained significantly improving.
The foregoing is only preferred embodiment of the present invention, not be used for limiting practical range of the present invention; If do not break away from the spirit and scope of the present invention, the present invention is modified or is equal to replacement, all should be encompassed in the middle of the protection domain of the claims in the present invention.
Claims (5)
1. the making method of a large aircraft equipment use magnesium copper-manganese base light alloy material, is characterized in that, comprises the following steps:
I. be respectively by weight percentage magnesium 0.3-0.8%, manganese 1.0-2.0%, zinc 29-31%, surplus is that the proportioning of copper is placed in Dian Xie Tong ﹑ Mei ﹑ Meng ﹑ zinc in main frequency furnace, is heated to 1650 ℃-1750 ℃ and after fusing, is incubated to 1680 ℃ fully;
Ii. adopt horizontal continuity vibrational casting method to be cast as solid alloy pig;
Iii. solid alloy pig is positioned in the box type vacuum annealing furnace and anneals, be placed on naturally cooling in air;
Iv. cooled copper ingot is removed surperficial oxide skin with light ingot machine, after be placed in the alloy pig process furnace;
V. adopt the alloy pig after hydraulic extrusion press will heat to be squeezed into alloy bar material or tubing;
Vi. after pushing, product carries out eddy current test.
2. making method according to claim 1, is characterized in that, the annealing time in step I ii. is 3.3-3.5 hour, and annealing temperature is 480 ℃-490 ℃.
3. making method according to claim 1, is characterized in that, the furnace temp in step I v. is controlled at 660 ℃-680 ℃.
4. making method according to claim 1, is characterized in that, in step vi., the eddy current test gain is 33dB, and phase place is 129Deg, is filtered into 17N, and frequency is 5.4KHz.
5. a large aircraft equipment of being manufactured by the described either method of claim 1-4 is with magnesium copper-manganese base light alloy material.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101008057A (en) * | 2007-01-22 | 2007-08-01 | 苏州金桨节能与环保科技有限公司 | Alloy material for water treatment of spinning industry and its preparing process |
| CN101787461A (en) * | 2010-03-02 | 2010-07-28 | 路达(厦门)工业有限公司 | Environment-friendly manganese brass alloy and manufacturing method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101008057A (en) * | 2007-01-22 | 2007-08-01 | 苏州金桨节能与环保科技有限公司 | Alloy material for water treatment of spinning industry and its preparing process |
| CN101787461A (en) * | 2010-03-02 | 2010-07-28 | 路达(厦门)工业有限公司 | Environment-friendly manganese brass alloy and manufacturing method thereof |
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