Functionalized treatment method of Ti-V-Al light memory alloy for structural connection of aerospace non-metal-matrix composites

A composite material and structural connection technology, applied in the field of aerospace composite materials, can solve problems such as low shape memory effect, and achieve the effect of improving shape memory effect

Inactive Publication Date: 2015-10-07
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem that the shape memory effect of Ti-V-Al alloy is low, and proposes a thermomechanical treatment method for improving its shape memory effect

Method used

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  • Functionalized treatment method of Ti-V-Al light memory alloy for structural connection of aerospace non-metal-matrix composites
  • Functionalized treatment method of Ti-V-Al light memory alloy for structural connection of aerospace non-metal-matrix composites

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specific Embodiment approach 1

[0029] In this embodiment, the Ti-V-Al alloy is composed of three elements: Ti, V and Al, wherein the atomic number ratio of Ti is 84%, the atomic number ratio of V is 13%, and the atomic number ratio of Al is 3. %.

[0030] In this embodiment, the Ti-13V-3Al alloy is made of sponge titanium with a purity of 99.95wt.%, 99.99wt.% V, and 99.99wt.% Al as raw materials, and is melted in a non-consumable arc melting furnace. Draw up to 5×10 -3 Prepared after Pa. In order to ensure the uniformity of the alloy composition, each ingot was turned and smelted six times and magnetically stirred.

[0031] The smelted ingot weighs about 60g after mechanical polishing to remove surface impurities. The ingot was held at 900°C for 2 hours under vacuum to homogenize the alloy composition, and then quenched into water to form thermoelastic martensite.

[0032] The heat-treated ingot is kept at 850° C. for half an hour and then hot-rolled, each down-rolling amount is 10%, and then returned t...

specific Embodiment approach 2

[0043] The difference between this embodiment and the first embodiment is that the tensile rate of the tensile test at room temperature is 3% / min.

specific Embodiment approach 3

[0045] The difference between this embodiment and specific embodiments 1 and 2 is that the solution treatment temperature is 850°C.

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Abstract

The invention discloses a functionalized treatment method of Ti-V-Al light memory alloy for structural connection of aerospace non-metal-matrix composites, and belongs to the technical field of aerospace composites. According to the method, an arc-melted Ti-V-Al alloy ingot is subjected to hot rolling after being subjected to solution treatment; the arc-melted Ti-V-Al alloy ingot is subjected to solution treatment again and quenched after having a certain thickness; then, cold rolling is performed; and the cold-rolled sample is annealed, and then the Ti-V-Al light memory alloy with an excellent shape memory effect can be obtained. By means of the method, the shape memory effect of the Ti-V-Al alloy can be substantially improved, and the completely reversible strain of the Ti-V-Al alloy reaches 7.5%, which is the maximum value except for that of TiNi alloy. The Ti-V-Al alloy which is subjected to thermal mechanical treatment is potential light memory alloy for structural connection of the composites in the aerospace field.

Description

technical field [0001] The invention relates to the technical field of aerospace composite materials, in particular to a functionalized treatment method for Ti-V-Al lightweight memory alloy used for structural connection of aerospace non-metal matrix composite materials. Background technique [0002] In the development of the aerospace industry, designers have been working on reducing the weight of aircraft. Modern non-metallic matrix composites have high specific stiffness and specific strength, and have become one of the preferred structural materials for modern aircraft. Structural weight reduction of aircraft can bring extremely considerable benefits. For example, for a small intercontinental missile warhead, if the weight is reduced by 1Kg, the range will increase by 15km when the payload remains the same. For Intelsat V, the aluminum alloy of its central load-bearing cylinder is changed to a composite material structure, which can reduce the weight by 9kg. This alone...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C1/02C22C14/00C22F1/18
Inventor 高智勇杨哲一赵兵蔡伟孙立强章茂云
Owner HARBIN INST OF TECH
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