Aluminum lithium alloy for spaceflight and method for preparing proximate matter through aluminum lithium alloy

A technology of aluminum-lithium alloy and aluminum alloy, which is applied in the field of manufacturing aluminum-lithium alloy and aluminum-lithium alloy profiles, can solve the problems of high difficulty of aluminum-lithium alloy and low strength of aluminum-lithium alloy, and achieves great difficulty in solving, simple production equipment, Resolve low-intensity effects

Active Publication Date: 2018-06-12
NORTHEAST LIGHT ALLOY CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the problems of high difficulty in producing aluminum-lithium alloys in the existing process and the low strength of the produced aluminum-lithium alloys, the present invention proposes a manufacturing method for aerospace aluminum-lithium alloys and aluminum-lithium alloy profiles

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  • Aluminum lithium alloy for spaceflight and method for preparing proximate matter through aluminum lithium alloy
  • Aluminum lithium alloy for spaceflight and method for preparing proximate matter through aluminum lithium alloy

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specific Embodiment approach 1

[0030] Specific Embodiment 1: In this embodiment, the aluminum-lithium alloy for aerospace is composed of Mg, Li, Ti, Zr and Al; the mass percentages of elements in the aluminum-lithium alloy are: Mg: 5.5%-6.5%, Li: 2.2%-2.5% , Ti: 0.03% to 0.12%, Zr: 0.15% to 0.20% and the rest of Al, wherein Zr+Ti≤0.25%; the mass percentage of impurity elements is: Cu: ≤0.01%, Si: ≤0.15%, Fe : ≤0.20%.

[0031] This embodiment has the following beneficial effects:

[0032] 1. Excessive Zr in the aluminum-lithium alloy will cause the generation of coarse compounds in the alloy, thereby affecting the mechanical properties of the aluminum alloy. In this embodiment, Ti: 0.03% to 0.12%, Zr: 0.15% to 0.20%, and Zr+Ti ≤0.25%, the present invention limits the content of Zr and Ti, and also limits the total amount of Zr and Ti, wherein Zr with a content of 0.15% to 0.20% will not cause coarse compounds in the aluminum-lithium alloy At the same time, Ti with a content of 0.03% to 0.12% can supplement...

specific Embodiment approach 2

[0034] Specific embodiment two: the difference between this embodiment and specific embodiment one is: the aluminum-lithium alloy is composed of Mg, Li, Ti, Zr and Al; the mass percentage of elements in the aluminum-lithium alloy is: Mg: 6%, Li: 2.4%, Ti: 0.12%, Zr: 0.15%, and the rest of Al; the mass percentages of impurity elements are: Cu: ≤0.01%, Si: ≤0.15%, Fe: ≤0.20%. Other steps and parameters are the same as those in the first embodiment.

specific Embodiment approach 3

[0035] Specific implementation mode three: In this implementation mode, the method for preparing profiles using aluminum-lithium alloys for aerospace is carried out in the following steps:

[0036] 1. According to the mass percentage of elements: Mg: 5.5% ~ 6.5%, Li: 2.2% ~ 2.5%, Ti: 0.03% ~ 0.12%, Zr: 0.15% ~ 0.20%, Zr+Ti≤0.25% and the balance Weighing pure magnesium ingots, Al-Li master alloys, Al-Zr master alloys, Al-Ti master alloys and high-purity aluminum ingots as raw materials for Al;

[0037] 2. Add the high-purity aluminum ingot weighed in step 1 into the melting furnace, melt it at 720°C-740°C for 6-8 hours to obtain molten aluminum, cool the molten aluminum to 670°C-690°C, and then Pass protective gas into the smelting furnace, add pure magnesium ingot and Al-Li master alloy to the cooled aluminum melt and raise the temperature to 720℃~740℃, then add Al-Zr master alloy and Al-Ti master alloy, keep warm 0.5 to 1.5 hours to obtain molten aluminum alloy;

[0038] 3. R...

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Abstract

The invention relates to an aluminum lithium alloy for spaceflight and an aluminum lithium alloy proximate matter preparing method, and relates to the aluminum lithium alloy and the aluminum lithium alloy proximate matter preparing method. The aim is to solve the problems that the production difficulty of the aluminum lithium alloy is large, and the aluminum lithium alloy strength is low. The aluminum lithium alloy is composed of Mg, Li, Ti, Zr and Al, the Mg accounts for 5.5%-6.5%, the Li accounts for 2.2%-2.5%, the Ti accounts for 0.03%-0.12%, the Zr accounts for 0.15%-0.20%, the Zr+Ti is smaller than or equal to 0.25%, and the balance is the Al. The method includes the steps of raw material weighing, aluminum alloy molten liquid preparing, refining, spray forming, short bar cutting, blind die extrusion, heat extrusion, quenching, tension leveling and aging treatment. According to the aluminum lithium alloy and the aluminum lithium alloy proximate matter preparing method, through spray forming, the problems that the aluminum lithium alloy production difficulty is large, and the quality is poor are solved, the strength of extension reaches 485 Mpa, the ruled non-proportional extending strength reaches 345 Mpa, the percentage elongation after fracture reaches 10.0%, and blind die extrusion enables a casting ingot to be more compact.

Description

technical field [0001] The invention relates to a method for manufacturing an aluminum-lithium alloy and an aluminum-lithium alloy profile. Background technique [0002] With the development of my country's aerospace industry, new aluminum alloys continue to develop, and the manufacturing methods of aluminum alloys have also been optimized and improved; however, there are problems in the production of existing aluminum-lithium alloys, which are difficult and the strength of the produced aluminum-lithium alloys is low; [0003] Since the aluminum-lithium alloy is relatively active, the casting device usually uses a vacuum furnace, and gas protection is still required during the casting process. The production equipment is complicated, the operation is difficult, and the quality of the cast alloy is difficult to guarantee. Most of the existing aluminum-lithium alloys use the traditional casting process. Since the aluminum-lithium alloy is relatively active and easy to oxidize,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C21/06C22C1/03B22F3/115C22F1/047
Inventor 高新宇王国军徐涛王金花孙婧彧李浩言李维王冬成
Owner NORTHEAST LIGHT ALLOY CO LTD
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