CN112195377A - Aluminum alloy section bar for airplane cabin door and preparation method thereof - Google Patents
Aluminum alloy section bar for airplane cabin door and preparation method thereof Download PDFInfo
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- CN112195377A CN112195377A CN202010815960.9A CN202010815960A CN112195377A CN 112195377 A CN112195377 A CN 112195377A CN 202010815960 A CN202010815960 A CN 202010815960A CN 112195377 A CN112195377 A CN 112195377A
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/026—Alloys based on aluminium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
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Abstract
An aircraft cabin door aluminum alloy section and a preparation method thereof belong to the field of aerospace aluminum alloy manufacturing, and comprise the following components in percentage by mass: 5.5-7.5% of Zn, 2.5-3.5% of Mg, 0.2-0.5% of Sm, 0.2-0.5% of Mn and 0.2-0.5% of Zr, and the balance of Al and inevitable impurities. According to the invention, by controlling the content of Sm in the aluminum alloy, the finally prepared aluminum alloy is ensured to have uniform microstructure and smaller grain size, the basal plane texture is converted into the rare earth texture, the non-basal plane slippage opening is promoted, high plasticity is shown, the elongation of the aluminum alloy is up to 12%, the plasticity is improved without sacrificing the strength, but the tensile strength of the alloy is improved, the preparation method is simple, only one-time traditional extrusion is needed, no complex processing technology is needed, the transportability is strong, and the method is convenient to realize in industry.
Description
Technical Field
The invention belongs to the field of manufacturing of aluminum alloy for aerospace, and particularly relates to an aluminum alloy section for an aircraft cabin door and a preparation method thereof.
Background
The passenger cabin door structure is an indispensable component of a civil aircraft fuselage structure and generally comprises floor cross beams, longitudinal beams, pillars and lateral pressure relief structures. The cross beam of the cabin door bears heavy load, needs to be connected with the longitudinal beam, the strut and the frame of the fuselage respectively, and is a more key structure. Compared with other parts of the fuselage, the cross beam structure has definite functions and clear stress, has fewer related structures around and cannot cause catastrophic accidents generally. However, the floor beam structure, especially the floor beam structure, has basically constant section shape, longer length and more number of parts, and can save working hours, reduce weight, remarkably improve production efficiency and product stability and finally reduce cost by selecting proper structural forms and materials. The section forms can be mainly divided into a C type, a Z type and an I type, and the structural materials comprise 7000 series and 2000 series traditional aluminum alloy sections.
At present, based on Al-Zn-Mg series alloy, a proper amount of alloy elements are added for micro-alloying, and then the strength and the plasticity of the aluminum alloy are further improved through solid solution strengthening, precipitation phase forming and dispersion strengthening. However, the strength and plasticity of aluminum alloy can not be increased by alloying modification alone, and the application of aluminum alloy in most engineering is not satisfied. In order to promote the wider use of wrought aluminum alloy and further obtain ultra-fine grain structure and excellent mechanical properties, domestic and foreign trades mostly adopt large plastic deformation technical means to obtain aluminum alloy materials with better properties through grain refinement, deformation strengthening and other mechanisms.
However, the existing aluminum alloy is not fine enough in grain, an aluminum alloy casting is easy to produce shrinkage cavity and segregation, the mechanical property is not ideal, the requirements of parts such as aerospace and the like on light high-strength materials cannot be met, and the utilization field of the aluminum alloy is limited.
Disclosure of Invention
The invention provides an aluminum alloy section bar of an airplane cabin door and a preparation method thereof, which are used for overcoming the defects in the prior art.
The invention is realized by the following technical scheme:
an aluminum alloy section bar for an airplane cabin door comprises the following substances in percentage by mass: 5.5-7.5% of Zn, 2.5-3.5% of Mg, 0.2-0.5% of Sm, 0.2-0.5% of Mn and 0.2-0.5% of Zr, and the balance of Al and inevitable impurities.
The aluminum alloy section for the aircraft door comprises Fe, Si and Cu.
The aluminum alloy profile for the aircraft door is characterized in that the mass of the impurities is less than 0.02 percent of the total mass.
A preparation method of an aluminum alloy section of an airplane cabin door comprises the following steps:
the method comprises the following steps: accurately weighing aluminum, zinc, magnesium, samarium, manganese and zirconium according to the proportion, and feeding the aluminum, zinc, magnesium, samarium, manganese and zirconium into a preheating kettle for preheating;
step two: feeding aluminum, zinc, magnesium and manganese into a melting kettle for melting, heating to 700-;
step three: adding the raw materials in small amount for multiple times, simultaneously starting a stirring paddle for stirring, removing impurities after all metals are molten, raising the temperature to 740-750 ℃, uniformly stirring, cooling to obtain an alloy liquid, introducing the alloy liquid into a mold for casting to obtain a cast aluminum alloy block;
step four: machining, namely sawing and turning the obtained cast aluminum alloy block for later use;
step five: homogenizing, heating the aluminum alloy casting blank to 300-500 ℃, preserving heat for 6-12 hours, and extruding to obtain an extruded section.
According to the preparation method of the aluminum alloy section bar for the airplane cabin door, the purity of aluminum, zinc, magnesium, samarium, manganese and zirconium is more than 99.9%.
In the preparation method of the aluminum alloy section for the aircraft door, the preheating temperature of the preheating kettle in the first step is 320-.
In the preparation method of the aluminum alloy section for the aircraft door, the aluminum alloy melt in the third step is cooled to 690-700 ℃.
In the preparation method of the aluminum alloy section for the aircraft door, the mold is preheated to 200-300 ℃ during casting in the third step.
In the fifth step of the preparation method of the aluminum alloy section for the aircraft door, the extrusion ratio is 8-22, the extrusion speed is 0.5-2.0mm/s, and the extrusion temperature is 400-.
The invention has the advantages that: according to the invention, by controlling the content of Sm in the aluminum alloy, the finally prepared aluminum alloy is ensured to be uniform in microstructure and smaller in grain size, the basal plane texture is converted into the rare earth texture, the non-basal plane slippage opening is promoted, the high plasticity is expressed, the elongation of the aluminum alloy is up to 12%, and the improvement of the plasticity does not sacrifice the strength, but improves the tensile strength of the alloy. In addition, the raw materials used for preparing the aluminum alloy are low in cost, the plasticity of the aluminum alloy can be obviously changed by only adding a small amount of rare earth elements, the preparation method is simple, only one-time traditional extrusion is needed, no complex processing technology is needed, the transportability is strong, and the method is convenient to realize in industry.
Drawings
In order to make the object, technical scheme and beneficial effect of the invention more clear, the invention provides the following drawings for explanation:
FIG. 1 is a photograph of a sample of an aluminum alloy in example 1 of the present invention.
FIG. 2 is a photograph of a sample of an aluminum alloy in example 2 of the present invention.
FIG. 3 is a photograph of a sample of an aluminum alloy in example 3 of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention.
Example 1
The method comprises the following steps: accurately weighing aluminum, zinc, magnesium, samarium, manganese and zirconium according to the mass percent of 5.5 percent of Zn, 2.5 percent of Mg, 0.2 percent of Sm, 0.2 percent of Mn and 0.2 percent of Zr and the balance of Al, and feeding the aluminum, the zinc, the magnesium, the samarium, the manganese and the zirconium into a preheating kettle for preheating;
step two: feeding aluminum, zinc, magnesium and manganese into a melting kettle for melting, heating to 700 ℃ after melting, and adding samarium and zirconium;
step three: adding the raw materials in small amount for multiple times, starting a stirring paddle for stirring, removing impurities after all metals are molten, raising the temperature to 740 ℃, uniformly stirring, cooling to obtain an alloy liquid, introducing the alloy liquid into a mold for casting to obtain a cast aluminum alloy block;
step four: machining, namely sawing and turning the obtained cast aluminum alloy block for later use;
step five: homogenizing, heating the aluminum alloy casting blank to 400 ℃, preserving heat for 8 hours, and extruding to obtain an extruded section.
Example 2
The method comprises the following steps: accurately weighing aluminum, zinc, magnesium, samarium, manganese and zirconium according to the mass percent of 6.5 percent of Zn, 3.0 percent of Mg, 0.35 percent of Sm, 0.35 percent of Mn and 0.35 percent of Zr and the balance of Al, and feeding the aluminum, the zinc, the magnesium, the samarium, the manganese and the zirconium into a preheating kettle for preheating;
step two: feeding aluminum, zinc, magnesium and manganese into a melting kettle for melting, heating to 700 ℃ after melting, and adding samarium and zirconium;
step three: adding the raw materials in small amount for multiple times, starting a stirring paddle for stirring, removing impurities after all metals are molten, raising the temperature to 740 ℃, uniformly stirring, cooling to obtain an alloy liquid, introducing the alloy liquid into a mold for casting to obtain a cast aluminum alloy block;
step four: machining, namely sawing and turning the obtained cast aluminum alloy block for later use;
step five: homogenizing, heating the aluminum alloy casting blank to 400 ℃, preserving heat for 8 hours, and extruding to obtain an extruded section.
Example 3
The method comprises the following steps: accurately weighing aluminum, zinc, magnesium, samarium, manganese and zirconium according to the mass percent of 7.5 percent of Zn, 3.5 percent of Mg, 0.5 percent of Sm, 0.5 percent of Mn and 0.5 percent of Zr and the balance of Al, and feeding the aluminum, the zinc, the magnesium, the samarium, the manganese and the zirconium into a preheating kettle for preheating;
step two: feeding aluminum, zinc, magnesium and manganese into a melting kettle for melting, heating to 700 ℃ after melting, and adding samarium and zirconium;
step three: adding the raw materials in small amount for multiple times, starting a stirring paddle for stirring, removing impurities after all metals are molten, raising the temperature to 740 ℃, uniformly stirring, cooling to obtain an alloy liquid, introducing the alloy liquid into a mold for casting to obtain a cast aluminum alloy block;
step four: machining, namely sawing and turning the obtained cast aluminum alloy block for later use;
step five: homogenizing, heating the aluminum alloy casting blank to 400 ℃, preserving heat for 8 hours, and extruding to obtain an extruded section.
Performance detection
The Al-Zn-Mg series aluminum alloy products produced by the Nanshan aluminum industry are selected as a comparison example, and the performance comparison table I shows that:
| serial number | Tensile strength (MPa) | Yield strength (MPa) | Elongation (%) |
| Example 1 | 625 | 530 | 9.3 |
| Example 2 | 632 | 539 | 8.7 |
| Example 3 | 627 | 521 | 10 |
| Comparative example | 470 | 412 | 7 |
Watch 1
As can be seen from the table I, the aluminum alloys of examples 1 to 3 have higher tensile strength and higher plasticity, and under the condition of improving plasticity, the tensile strength of the alloys is improved without sacrificing the strength, so that the transportability is strong, and the realization in the industry is facilitated.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (9)
1. An aircraft hatch door aluminum alloy section bar which characterized in that: the material composition comprises the following components in percentage by mass: 5.5-7.5% of Zn, 2.5-3.5% of Mg, 0.2-0.5% of Sm, 0.2-0.5% of Mn and 0.2-0.5% of Zr, and the balance of Al and inevitable impurities.
2. An aircraft door aluminium alloy section according to claim 1, wherein: the impurities comprise Fe, Si and Cu.
3. An aircraft door aluminium alloy section according to claim 1, wherein: the mass of the impurities is less than 0.02 percent of the total mass.
4. The preparation method of the aluminum alloy section bar of the airplane cabin door is characterized by comprising the following steps of: the method comprises the following steps:
the method comprises the following steps: accurately weighing aluminum, zinc, magnesium, samarium, manganese and zirconium according to the proportion, and feeding the aluminum, zinc, magnesium, samarium, manganese and zirconium into a preheating kettle for preheating;
step two: feeding aluminum, zinc, magnesium and manganese into a melting kettle for melting, heating to 700-;
step three: adding the raw materials in small amount for multiple times, simultaneously starting a stirring paddle for stirring, removing impurities after all metals are molten, raising the temperature to 740-750 ℃, uniformly stirring, cooling to obtain an alloy liquid, introducing the alloy liquid into a mold for casting to obtain a cast aluminum alloy block;
step four: machining, namely sawing and turning the obtained cast aluminum alloy block for later use;
step five: homogenizing, heating the aluminum alloy casting blank to 300-500 ℃, preserving heat for 6-12 hours, and extruding to obtain an extruded section.
5. The method for preparing an aluminum alloy section for an aircraft door according to claim 4, wherein the method comprises the following steps: the purities of the aluminum, the zinc, the magnesium, the samarium, the manganese and the zirconium are all more than 99.9 percent.
6. The method for preparing an aluminum alloy section for an aircraft door according to claim 4, wherein the method comprises the following steps: the preheating temperature of the preheating kettle in the first step is 320-360 ℃.
7. The method for preparing an aluminum alloy section for an aircraft door according to claim 4, wherein the method comprises the following steps: the aluminum alloy melt in the third step is cooled to 690-700 ℃.
8. The method for preparing an aluminum alloy section for an aircraft door according to claim 4, wherein the method comprises the following steps: and in the third step, the mould is preheated to 200-300 ℃ during casting.
9. The method for preparing an aluminum alloy section for an aircraft door according to claim 4, wherein the method comprises the following steps: in the fifth step, the extrusion ratio is 8-22, the extrusion speed is 0.5-2.0mm/s, and the extrusion temperature is 400-.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114480930A (en) * | 2020-11-13 | 2022-05-13 | 烟台南山学院 | Aluminum alloy section for passenger car body framework and preparation method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2805282A1 (en) * | 2000-02-23 | 2001-08-24 | Gerzat Metallurg | METHOD FOR MANUFACTURING ALLOY PRESSURE HOLLOW BODIES A1ZNMGCU |
| WO2020068199A2 (en) * | 2018-06-20 | 2020-04-02 | NanoAI LLC | HIGH-PERFORMANCE Al-Zn-Mg-Zr BASE ALUMINUM ALLOYS FOR WELDING AND ADDITIVE MANUFACTURING |
| CN111020309A (en) * | 2019-09-23 | 2020-04-17 | 山东南山铝业股份有限公司 | High-strength wrought aluminum alloy containing rare earth samarium and preparation method thereof |
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- 2020-08-14 CN CN202010815960.9A patent/CN112195377A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2805282A1 (en) * | 2000-02-23 | 2001-08-24 | Gerzat Metallurg | METHOD FOR MANUFACTURING ALLOY PRESSURE HOLLOW BODIES A1ZNMGCU |
| WO2020068199A2 (en) * | 2018-06-20 | 2020-04-02 | NanoAI LLC | HIGH-PERFORMANCE Al-Zn-Mg-Zr BASE ALUMINUM ALLOYS FOR WELDING AND ADDITIVE MANUFACTURING |
| CN111020309A (en) * | 2019-09-23 | 2020-04-17 | 山东南山铝业股份有限公司 | High-strength wrought aluminum alloy containing rare earth samarium and preparation method thereof |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114480930A (en) * | 2020-11-13 | 2022-05-13 | 烟台南山学院 | Aluminum alloy section for passenger car body framework and preparation method thereof |
| CN114480930B (en) * | 2020-11-13 | 2023-01-31 | 烟台南山学院 | Aluminum alloy section for passenger car body framework and preparation method thereof |
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Application publication date: 20210108 |