The method of obtaining products from an alloy of aluminum-magnesium-lithium

 

The invention relates to a method of manufacturing structural parts of aircraft alloy aluminum-magnesium-lithium. This method is carried out by obtaining an aluminum alloy containing the following components, wt.%: magnesium 3,0-6,0, lithium 0,4-3,0, zinc up to 2.0, to 1.0 manganese, silver 0.5, iron 0.3, si 0.3, copper to 0,3,0,02-0,5 at least one element selected from the group consisting of scandium 0,010-0,40, hafnium 0,010-0.25, titanium 0,010-0.25 vanadium 0,010-0,30, neodymium 0,010-0,20, zirconium 0,020-0,25, chrome 0,020-0.25, yttrium from 0.005 to 0.20, beryllium is 0.0002-0.1, aluminum and inevitable impurities else casting the alloy into an ingot, pre-heating the ingot, hot rolling the preheated ingot in the hot rolled intermediate product, followed by cold rolling of the hot rolled intermediate product as in length and width, with a total reduction in thickness of the hot rolled intermediate product during cold rolling, at least 15%, followed by heating the cold-rolled product in solid solution in the temperature range from 465 to 565With an excerpt from 0.15 to 8 hours and then cooled processed by heating in the solid solution of cold-rolled product to a temperature below 150to the direction L, as well as having the minimum value of fracture toughness Kwith80 MPam1/2in the direction T-L for samples with a Central crack used to determine the fracture toughness, of a width of 400 mm Technical result of the invention is to provide a method of producing products with a high value of fracture toughness, and low anisotropy of mechanical properties. 3 N. and 8 C.p. f-crystals, 2 ill., 8 table.

The invention relates to a method of producing an alloy of aluminum-magnesium-lithium low anisotropy of mechanical properties, and further, the invention relates to the use of the obtained product for structural aircraft parts.

In this invention under the thin sheet material is understood rolled product having a thickness of not less than 1.3 mm and 6.3 mm, Cm, also Aluminium Standard and Data, the Aluminium Association, Chapter 5 Terminology, 1997. Under the current or flat disc is a three-dimensional object, having, by definition, the length (usually casting direction in the case of (semi)continuous casting), width and thickness, where the width is equal to or greater than the thickness.

It is well known that the addition of lithium as an alloying agent for aluminum alloys leads to useful mechanical properties. Alumina-lithium alloys exhibit high stiffness and strength with a significant decrease in the density. Therefore, these types of alloys are used as structural materials in the aviation and aerospace fields. Examples are known of al-Li alloys include alloy AA (UK), alloys A and AA (USA) and alloy 01420 (Russia).

There are problems with both of al-Li alloys, and alloys of aluminum-magnesium-lithium, in particular in the anisotropy of mechanical properties and fracture toughness. The values of fracture toughness in the direction of the T-L is significantly lower than the strength at break in the main direction, for example in the direction of the L-T.

Some other alloys, Al-Li, was found in the earlier literature will be mentioned below.

In WO-92/03583 offered the alloy used in the construction of aircraft and buildings aircraft that have low density. Composition, wt.%:

MD 0.5 to 10.0, the preference is,0

the rest of the aluminum,

provided that the total amount of alloying elements does not exceed 12,0, and provided that if the content of MD varies from 7.0 to 10.0, the content of Li may not exceed 2.5% and the content of Zn may not exceed 2.0%.

The specified alloy necessarily involves a certain amount of silver. In the manufacture of sheet material from the specified aluminum alloy uses standard processing modes.

In GB-A-2146353 features alloy having high electrical resistance and excellent formability used in structures affected by strong magnetic fields, nuclear reactors and the like. Composition, wt.%:

MD of 1.0 to 8.0, preferably 2,0-7,0

Li 0,05-1,0

at least one element selected from the group consisting of

Ti 0,05-0,20

Cr 0,05-0,40

Zr 0,05-0,30

V 0,05-0,35

W 0,05-0,30

Mn 0,05-2,0

the remainder aluminum and incidental impurities.

In addition, this alloy may contain Bi in the range of 0.05 to 0.50 wt.%. In the manufacture of sheet material from the specified aluminum alloy used in standard processing parameters.

In DE-A-1558491 described the improvement of alloy 1420 (Russia) mentioned above, the alloy contains, wt%:

MD 4-7

Li 1,5-2,6

its receipt, described alloy consists of, by weight.%:

Li 1,0-5,0

one or more element selected from the group consisting of

Zr 0,05-0,3

Cr 0,05-0,30

Mn 0,05-1,5

V 0,05-0,3

Ti 0,005-0,1

the rest of the aluminum.

In the manufacture of sheet material such aluminum alloy uses standard processing modes.

In view of the shortcomings of al-Li alloys and alloys aluminum-magnesium-lithium in relation to the fracture toughness has been necessary to provide a method of enhancing T-L fracture toughness for these types of alloys. Responding to this need, this invention provides such a method, which significantly increases the fracture toughness of the alloys of the aluminum-magnesium-lithium in the direction T-L, increasing their suitability for a larger number of industrial applications, in particular for use as structural materials of aircraft.

In accordance with the invention offer a method of producing an alloy of aluminum-magnesium-lithium, which is characterized by low anisotropy of mechanical properties, containing successive stages:

(a) obtaining an aluminum alloy consisting of by weight.%:

MD 3,0-6,0

Li 0,4-3,0

Zn-2.0

MP-1.0

Hell 0.5

Fe 0.3

Si 0.3

Si 0.3

0,02-0,5 at least is from 0.005 to 0.20 and Be is 0.0002-0,10), the remainder aluminum and unavoidable impurities;

(b) casting aluminum alloy into an ingot;

(c) preheating the ingot;

(d) hot rolling the preheated ingot in the hot rolled intermediate product;

(e) cold rolling hot rolled intermediate product in both directions along the length and width with an overall decrease in the thickness of the hot rolled intermediate product during cold rolling, at least 15%;

(f) heating the cold-rolled product in solid solution in the temperature range from 465 to 565With an excerpt from 0.15 to 8 hours;

(g) cooling the treated by heating in solid solution cold-rolled product to a temperature below 150With a cooling rate of at least 0,2C/C;

(h) aging the cooled product to obtain a sheet or sheet products having a minimum yield strength of 260 MPa and a minimum tensile strength of the negative pressure of 400 MPa, at least in the directions L and LT, a minimum yield strength of 230 MPa and a minimum tensile strength at a vacuum of 380 MPa in the direction at an angle of 45to the direction L, as well as having a minimum the NII T-L for samples with a Central crack, used to determine the fracture toughness (panels CST), width 400 mm

According to the invention, it is now possible to obtain a sheet product or a thin sheet product of the specified type with given mechanical properties, with properties much more isotropic than in the drawing process. In particular, this method allows you to improve the actual properties of the product in the direction of T. another advantage of this method is that it allows you to get a much broader thin sheet products, such as width up to 2.5 m, in comparison with conventional methods of stretching.

In one embodiment of the method according to the invention the product may be coated. Such clad products are the basis of the alumina-magnesium-lithium alloy, which is more in detail described above, and coating at least one side of the base, such a coating typically has a higher purity (greater percentage of aluminum in comparison with the base), which, in particular, enhances the appearance and protects the base from corrosion. Coatings include, but are not limited to, practically pure aluminum or aluminum containing not more than 0.1 or 1% of druguse type 1000, type 1100, type 1200 and type 1300. In addition, the alloy AA 7072 containing zinc (from 0.8% to 1.3%), may serve as a cover, and alloys of series alloys AA, such as 6003 or 6253, usually containing more than 1% of alloying elements, can serve as cover. Other alloys can also be used as cover if they provide, in particular, sufficient General corrosion protection alloy base. A cladding layer or layers are usually much thinner than the base, every one of them is from 0.5 to 15 or 20, or possibly up to 25% of the total thickness of the composite. A cladding layer is often about 0.5 to 12% of the total thickness of the composite.

Pre-heating the ingot before hot rolling is usually performed at a temperature in the range from 360 to 500With in one or several stages. In any case, preheating reduces the segregation of alloying elements in the material in the form of an ingot and dissolve soluble elements such as Li. If processing is performed below 360C, effect of homogenization is inadequate. Moreover, due to a substantial increase in the deformation resistance of the ingot industrial hot rolling don is carried out between 1 and 24 hours, preferably between 5 and 20 hours and more preferably between 8 and 15 hours. Preferably preheating is carried out at a temperature in the range from 400 to 470S, more preferably from 410 to 450C and most preferably from 420 to 440C.

Usually prior to hot rolling with the rolled surfaces of both types of products as clad and non-clad remove the surface layer to remove areas of segregation under the molding surface of the ingot.

The process of hot rolling method according to the invention preferably includes hot rolling the preheated ingot in both directions along the length and width. During the process of hot rolling to the direction of rolling can be modified alternative more than once. Hot rolling is preferably carried out at a temperature varying from 270 to 470C. it Was found beneficial effects on the properties of the final product, if after the final stage of hot rolling, the product has a temperature above 270With, preferably above 300C and more preferably above 330C for from 1 to 24 hours, more preferably in the range from 410 to 450C and most preferably in the range from 420 to 440With, the Preferred time is in the range from 5 to 20 hours, and more preferably in the range from 7 to 15 hours. This procedure re-heating is repeated before each subsequent stage rolling until then, until you get the desired intermediate caliber. Using the method of hot rolling achieve more improved mechanical properties, such as a more isotropic structure of the final product.

If necessary during the hot rolling process in accordance with the invention, the intermediate product may be cut into subscale for conducting hot rolling in both directions along the length and width.

Preferably hot rolled intermediate product release before cold rolling the steel to improve machinability. Vacation is preferably carried out at a temperature in the range from 360 to 470S, and more preferably from 380 to 420C. the Time when the vacation is in the range from 0.5 to 8 hours, preferably from 0.5 to 3 hours. Odpem air cooling.

To obtain a laminated sheet products in accordance with the invention, the product is subjected to cold working cold rolling in both directions along the length and width to the final desired caliber of the product, including reducing the thickness of at least 15%. Almost the maximum thickness reduction during cold rolling is approximately 90% due to the destruction of a thin sheet or plate without intermediate leave. Preferably the degree of cold rolling is from 20 to 50% at each stage, preferably from 20 to 40% at each stage. Using the method of cold rolling, as described above, in particular, achieve improved mechanical properties by reducing the anisotropy and, in addition, achieves a better balance between the yield stress in the direction 45to the direction L, the limit of tensile strength and elongation.

During cold rolling laminated product may be subjected to intermediate tempering to improve the workability of cold rolled products. Intermediate tempering is preferably carried out at a temperature in the range from 300 to 500S, more preferably from 350 to 450

Cold rolled sheet product in accordance with the invention is then subjected to heating in the solid solution is typically at a temperature in the range from 465 to 565C, preferably from 490 to 540With exposure times ranging from 0.15 to 8 hours, preferably with exposure times ranging from 0.5 to 3 hours and most preferably from 0.8 to 2 hours, during which the excess dissolved phase to the maximum extent possible at this temperature.

Next, to provide the desired strength and fracture toughness that is required by the end product, and operations to obtain such a product, the product should be cooled below 150When the cooling rate is at least 0,2With/s, preferably at a cooling rate of at least 1With a/C, usually with rapid air cooling. With a combination of relatively high temperature exposure and a relatively long exposure time and the indicated cooling rates achieved by improving the elongation of the final product. It was also found that the resulting product is almost free from lines of Ladera type A. in Addition, improved thermal stability of the product received.

After cooling the released product and before artificial ageing product may be elongated, preferably at room temperature for no more than 3% of the original length or processed or otherwise deformed to give the product of the treatment effect equivalent to stretching no more than 3% of the original length. Preferably, the extrusion is in the range of 0.3 to 2.5%, more preferably from 0.5 to 1.5% of its original length. It is assumed that the effect of treatment involves rolling and forging, as well as other processing operations. It was found that when pulling products in this invention are reduced residual stresses and improves the flatness of the product, as well as improving the susceptibility to aging.

A suitable process of artificial aging method corresponding to the present invention, given in the application for the patent WO-99/15708, which is given here as a reference.

It should be noted that the method known from US-A-4151013 for receiving the sheets from which taiwania, includes the stages of:

(a) heating the sheet to a temperature within 455-565With, preferably within 480-510C for holding time of 0.5 to 10 minutes;

(b) cooling the sheet below 175With a predetermined speed Q;

(c) extruding a sheet of 0.25-1% of the original length.

However, this document does not mention the use of this method for alloys of Al-Mg-Li and are not further mentioned that with a longer exposure time in the range from 0.15 to 8 hours, as specified according to the invention, it is also possible to avoid the appearance of lines of Ladera type a and, in addition, you can improve the value of fracture toughness Kwithand elongation of the finished product. Nothing is said about the fact that the improved resistance to crack propagation.

After the product is processed and released, it can be subjected to aging to provide a combination of strength and fracture toughness and resistance to crack propagation, which is very important for aircraft parts. The product may be subjected to aging in a natural way typically at ambient temperature and an alternative product may be subjected to artificial eastview temperature in the range from 65 to 205With over a period of time sufficient to further increase the yield strength.

Further, it should be noted that the product obtained in accordance with the invention, may be any conventional treatments incomplete aging, known from the prior art. Also as mentioned here the only stage of aging, the means and multiple stages of aging, such as two - or three-stage aging, and the pulling equivalent processing can be used before or even after part of such multiple stages.

In a preferred variant of the method in accordance with the invention, the resulting product has a minimum fracture toughness of T-Lwithequal to 90 MPafor panels CST width of 400 mm and more preferably equal to 95 MPa. In the literature published in America,withmaterial is often referred Toarror the apparent fracture toughness.

In a preferred variant of the method in accordance with the invention, the resulting product has a minimum ultimate tensile strength of 430 MPa, at least in the directions of L - and LT - and more pre is asthenia in the direction 45to L is equal to 390 MPa and more preferably equal to 400 MPa.

In a preferred variant of the method in accordance with the invention, the resulting product has a minimum yield strength of 300 MPa or more, at least in the directions of L - and LT-, and more preferably at least 315 MPa or more, and most preferably at least 330 MPa or more in these areas. Preferably a minimum yield strength in the direction 45to L is equal to 250 MPa or more, and more preferably equal to 260 MPa or more, and most preferably equal to 270 MPa or more.

In another embodiment of the method in accordance with the invention, the resulting product has a minimum yield strength of 400 MPa or more in the direction L, and a minimum yield strength of 370 MPa or more in the direction of LT-, and a minimum yield strength of 330 MPa or more in the direction 45to L.

The reasons for restrictions on the content of alloying elements in the aluminum-magnesium-lithium alloy obtained by the method according to the invention, described below. All compositions are given in mass percent.

MD is the first element that increases the strength without increasing density. The content of SB is below 3% does not require the ing the formation of faults. The preferred content of SB is between 4.3 and 5.5% and more preferably between 4.7 and 5.3 percent as a compromise between processability and durability.

Li is also an important alloying element and gives the product a low density, high strength, good weldability and very good natural susceptibility to hardening. The preferred content of Li is in the range from 1.0 to 2.2%, more preferably from 1.3 to 2.0% and most preferably from 1.5 to 1.8% as a compromise between processability and durability.

Zinc as an alloying element may be present in the product according to the invention to impart to the increased susceptibility to dispersion hardening and corrosion resistance. The zinc content above 1.5% does not provide good weldability, and increases density. The preferred zinc content is 0.05 to 1.5%, and more preferably is 0.2 to 1.0%.

MP may be present in amounts up to 1.0%. The preferred content of the MP is in the range from 0.02 to 0.5%, and more preferably from 0.02 to 0.25%. Within these limits, the addition of manganese allows you to manage granular structure.

Si is preferably not added to the product, because copper degrades cor is but to exceed 0.3%, while the preferred maximum is 0.20%, and most preferably the maximum content is 0.05 percent.

Sc may be present in amounts up to 0.4% to increase the strength of the product and improve the weldability of the product by reducing sensitivity to hot break during welding, it increases the recrystallization temperature and increases the ability to control grain structure. The limits of the preferred content vary from 0.01% to 0/08%, and more preferably from 0.02 to 0.08% as a compromise between durability and manufacturability. Elements having similar effect, such as neodymium, cerium and yttrium, or mixtures thereof can be used instead of, or in mixture with scandium without changing the essence of the product according to this invention.

Zr is preferably introduced as a recrystallization inhibitor and preferably is in the range of 0.02 to 0.25%, more preferably in the range of 0.02 to 0.15%, and most preferably from 0.05 to 0.12%. Despite the fact that for alumina-magnesium-lithium alloys can use other modifiers grit, Zirconia is the most effective for alloys of this type. Elements having similar effect, such as chromium, manganese, is observed without changing the essence of the product according to this invention.

You can add an expensive alloying element silver, which is often used in this type of alloys. Although it can be entered in normal limits up to 0.5%, and preferably up to 0.3%, it may not lead to a significant improvement of the properties, but may increase susceptibility to hardening, which is extremely useful when welding.

Iron and silicon, each may be present in the maximum amounts of up to 0.3% of their total content. Preferably, these impurities were present only in trace quantities, within the iron content be 0.15% and silicon 0,12% and more preferably of 0.10% and 0.10%, respectively.

It is believed that traces of sodium and hydrogen also has a harmful effect on the properties (in particular, fracture toughness) alumina-magnesium-lithium alloys and must be maintained at the lowest practicable levels, for example of the order of from 15 to 30 M. D. (0,0015-0,0030%) for sodium and less than 15 M. D. (0,0015%), and preferably less than 1.0 M. D. (0,0001%) for hydrogen. The remainder of the alloy, of course, is aluminum and incidental impurities. Typically, each element is an impurity present in a maximum amount of 0.05%, and the total content of impurities maximum is 0.15%.

The invention also consists of the components of the aircraft, such as aircraft skin, and also for the production of casings bottom of the wing and, in addition, can be used for covering the fuselage of the aircraft.

EXAMPLES

The invention will be further illustrated by several limiting examples.

Example 1

On an industrial scale made three bars, two of which were made in accordance with the invention, and one made for comparison. Three of the ingot a, b and C (compositions given in table 1) having a size of 35014502500 mm preheat up to 395C for approximately 8 hours, and then subjected to hot rolling in the direction of their width to an intermediate thickness 153 mm with subsequent preheating to 395C for approximately 8 hours and subjected to hot rolling in the direction of their length to an intermediate thickness of 9 mm After hot rolling hot rolled intermediate product is subjected to heat treatment, maintaining product 100 minutes at 395With subsequent air cooling. At the next stage, the material of the ingot And subjected to cold rolling in the direction it W the cold rolling in the direction of its length to the same intermediate thickness. Next, the ingot And subjected to cold rolling in the direction of its length to an intermediate thickness of 6.1 mm, and then to a final thickness of 4.6 mm Between stages of cold rolling the intermediate product release at 395C for 100 minutes followed by air cooling. The material of the bars b and C are initially subjected to cold rolling in the direction of their length and width, respectively, from 9 mm to 6.1 mm, subjected to heat development, and then cold rolling in the direction of their length from 6.1 to 4.6 mm

Then both cold-rolled material ingots a and b are heated solid solution at 530With 1 hour and then cooled below 150Using air cooling at an average cooling rate of 0.3C/C, whereas the material of the ingot is treated in the same way, but heating in solid solution is carried out at 480C for 1 hour. Cold-rolled sheets, heated in a solid solution, pulling at room temperature by 0.8% of their original length. After pulling the sheet product is subjected to aging in a three-stage process of aging, consisting of 6 hours at 85S, 12 h, Beny in table 2.

After ageing investigate the mechanical properties of the sheets as a function of direction, for each the results are shown in tables 3 and 4; all results are averaged for the three studied samples. To determine the lengthening of the size of the sample: l0=50 mm, b0=12.5 mm, d0=4,6 mm Further investigate the characteristics of the propagation of cracks in the sheet materials, the results are shown in Fig.1 in the direction of the T-L and compared with the results of the main strip of material 2024. In Fig.2 presents the characteristics of the propagation of cracks in the direction of the L-T and compared with the results of the main strip of material 2024. Also we investigated thermal stability of materials during exposure for 300 hours at 95With, and then was measured Towithonly in the direction T-L; the results are shown in table 5. Next sheet materials were investigated for the presence of lines of Ladera and it was found that both the sheet material from ingot a and b do not have lines of Ladera type a and type b, whereas in the material of the ingot shown the presence of lines of Ladera type A.

From the results shown in table 3, it can be seen that the materials obtained in accordance with the invention (bars a and C), imeche for materials of the bars a and C allowable stress (NAM) above, on all fronts. The elongation as a function of direction is much more balanced for materials of the bars a and C than for the material of the ingot, and the balance for the material of the ingot And better than for the material of the ingot C.

From the results of table 4 can be seen that the fracture toughness increases for high temperature heating in the solid solution. Next, you can see that the materials obtained by the method according to the invention, even have a few more improved and more balanced fracture toughness of that, it seems, is a consequence of the applied rolling.

According to the results of table 5, we can see that the materials that were subjected to heating in solid solution at 530(Materials of the bars a and b), have good thermal stability, the results remain unchanged, while the material is subjected to heating in solid solution at 480With shows lower values Forwithapproximately 9%.

From the results shown in Fig.1, the critical T-L direction of the test can be seen that both materials have comparable or better performance in the propagation of cracks than the material 2024. Next, you can see that the material of the SL is Alenia test the resistance to crack propagation is improved due to the higher temperature heating in solid solution.

From the results in Fig.2 for the L-T direction test, you can see that the higher the heating temperature for the solid solution can significantly improve the resistance to crack propagation material. In the direction of the test material from an ingot In shows better results than the material of the bars a and C, which may be due to the direction of rolling and is in agreement with expectations.

Example 2

Analogously to example 1 on an industrial scale made three ingots (billets D, E and F), one of which was made in accordance with the invention, and two are made for comparison. The chemical composition of all three ingots having initial dimensions of 35014502500 mm, identical and are shown in table 6. The processing method is similar to that specified in example 1 and summarized in table 7. For heating in solid solution after cold rolling was carried out using two different temperatures, namely 530C and 515C.

After the holidays were isignia temperature heat treatment in solution; all results are averaged over three investigated samples. To determine the lengthening of the size of the sample: l0=50 mm, b0=12.5 mm, d0=4,6 mm

According to the results of table 8 we can see that the material obtained in accordance with the invention (strand D), has a much more isotropic mechanical properties compared to materials of the bars E and F, in particular the elongation is much more balanced. Next, you can see that the method according to the invention leads to a significantly large values of allowable stress. From these results we can see that the higher the temperature of heat treatment in solution leads to better mechanical properties after tempering.

After a detailed description of the invention the person skilled in the art it is clear that there are numerous changes and modifications of the present invention, not inconsistent with the letter and spirit of the invention, which is expressed by the claims appended hereinafter.

Claims

1. The method of obtaining products from an alloy based on aluminum containing magnesium, lithium, which contains the following components, wt.%: magnesium - 3,0-6,0, Li - 0,4-3,0, zinc - to 2.0, manganese - 1,0, silver - 0.5, iron - 0.3, silicon - 0.3, copper - 0.3, 0,02-0,5 at least one element selected from the group consisting of scandium - 0,010-0,40, hafnium - 0,010-0.25, titanium - 0,010-0.25 vanadium - 0,010-0,30, neodymium - 0,010-0,20, zirconium - 0,020-0,25, chrome - 0,020-0,25, yttrium is from 0.005 to 0.20, beryllium - is 0.0002-0.1, aluminum and inevitable impurities rest prior to hot rolling the ingot in the hot rolled intermediate product conduct pre-heating the ingot, followed by cold rolling of the hot rolled intermediate product in both directions along the length and width, with a total reduction in thickness of the hot rolled intermediate product during cold rolling of at least 15%, followed by heating the cold-rolled product in solid solution in the temperature range from 465 to 565With an excerpt from 0.15 to 8 h and then cooled processed by heating in the solid solution of cold-rolled product to a temperature below 150With a cooling rate of at least 0,2C/C and aging the cooled product to obtain a sheet or sheet products having a minimum yield strength of 260 MPa and min is the input of 230 MPa and a minimum ultimate tensile strength of 380 MPa in the direction at an angle of 45to the direction L, as well as having the minimum value of fracture toughness KWith80 MPa m1/2in the direction T-L for samples with a Central crack used to determine the fracture toughness, of a width of 400 mm

2. The method according to p. 1, characterized in that the preheated ingot is subjected to hot rolling in both directions along the length and width.

3. The method according to p. 1 or 2, characterized in that the magnesium content is in the range from 4.3 to 5.5 wt.%.

4. The method according to any of paragraphs.1-3, characterized in that the lithium content is in the range from 1.0 to 2.2 wt.%.

5. The method according to any of paragraphs.1-4, characterized in that the zinc content is in the range of 0.2 to 1.0 wt.%.

6. The method according to any of paragraphs.1-5, characterized in that the alloy contains at least scandium in an amount of from 0.01 to 0.08 wt.%.

7. The method according to p. 6, characterized in that the alloy further comprises at least zirconium in amounts of from 0.02 to 0.025 wt.%.

8. The method according to any of paragraphs.1-7, characterized in that it is intended to obtain the skin of the airplane.

9. The method according to any of paragraphs.1-7, characterized in that it is designed for covering the lower part of the wings of the aircraft.

10. Glider aerospace apparatus, manufacture of Sivka plane, made from an alloy based on aluminum, characterized in that it is made by a method according to any of paragraphs.1-7.

 

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FIELD: alloy metallurgy.

SUBSTANCE: invention relates to deformable, thermally strengthened, highly technologically effective, corrosion-resistant welding alloys based on the system Al-Mg-Si and articles made of thereof. The proposed alloy and article made of thereof comprise the following components, wt.-%: magnesium, 0.3-1.2; silicon, 0.3-1.7; manganese, 0.15-1.1; calcium, 0.05-0.; sodium, 0.0002-0.01, and at least one metal taken among the group comprising copper, iron, zirconium and chrome, 0.02-1.0, and aluminum, the balance. Invention provides the development of deformable alloy based on the system Al-Mg-Si and article made of this alloy that show enhanced technological effectiveness at cold stampings by extrusion and improved workability by cutting.

EFFECT: improved and valuable properties of alloy and article.

3 cl, 3 tbl, 1 ex

FIELD: metallurgy of aluminum-based alloys on base of Al-Mg-Mn system for manufacture of armored semi-finished products and articles for aviation and shipbuilding and other civil equipment.

SUBSTANCE: proposed alloy contains the following components, mass-%: magnesium, 4.2-6.5; manganese, 0.5-1.2; zinc, up to 0.2; chromium, up to 0.2; titanium, up to 0.15; silicon, up to 0.25; iron, up to 0.3; copper, up to 0.1; zirconium, 0.05-0.3 and at least one element selected from group containing: scandium, 0.05-0.3; beryllium, 0.0001-0.01; yttrium, 0.001-0.1; neodymium, 0.001-0.1; cerium, 0.001-0.1, the remainder being aluminum. Proposed alloy and articles made from it possesses high resistance to ballistic action of various projectiles due to optimal strength characteristics, optimal structure and plasticity characteristics.

EFFECT: high resistance to ballistic action of projectiles; enhanced corrosion resistance and weldability; reduced mass.

3 cl, 1 dwg, 3 tbl, 3 ex

FIELD: nonferrous metallurgy.

SUBSTANCE: invention is intended for use in metallurgy, mechanical engineering, and aircraft industry, in particular for manufacturing honeycomb structures. Alloy is composed of, wt %: magnesium 8-10, manganese 0.1-0.15, zirconium 0.15-0.2, cobalt 0.05-0.2, boron 0.005-0.007, beryllium 0.001-0.02, iron 0.15-0.2, silicon 0.15-0.2, titanium 0.1-0.2, aluminum - the balance. Ingot for manufacturing structural foil is obtained by semicontinuous casting in rotary crystallizer at volumetric cooling 4-20°C/sec. Structural foil manufacturing process comprises homogenization, hot rolling, annealing, cold rolling followed by annealing in air atmosphere, second cold rolling followed by annealing, and final cold rolling.

EFFECT: increased strength of alloy at ambient and elevated temperatures and improved processability un rolling stage.

3 cl, 3 tbl

FIELD: metallurgy.

SUBSTANCE: said utility invention relates to the manufacture of products of a rolled aluminium alloy highly resistant to damage. The method involves casting an ingot with a chemical composition selected from the group consisting of AA2000, AA5000, AA6000, and AA7000 alloys, homogenisation and/or heating of the ingot after casting, hot rolling of the ingot into a hot-rolled product and, optionally, cold rolling of the hot-rolled product into a cold-rolled product. After the hot rolling, the hot-rolled product is cooled from the hot-rolling mill output temperature (Tout) to 150°C or lower, at a controlled cooling rate decreasing within the set range according to a continuous cooling curve determined using the following expression: T(t)=50-(50-Tout)eα-t, where T(t) is the cooling temperature (°C) as a function of the cooling time (hours), t is the cooling time (hours), and α is a parameter determining the cooling rate, within a range of -0.09±0.05 (hr-1).

EFFECT: enhanced impact strength; resistance to growth of fatigue cracks, and corrosion resistance without strength deterioration.

19 cl, 7 tbl, 1 dwg, 2 ex

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