Magnesium-lithium alloy, method of manufacturing magnesium-lithium alloy, aircraft part, and method of manufacturing aircraft part

Patent metadata

Field	Value
Publication number	US-10752981-B2
Application number	US-201615062507-A
Country	US
Kind code	B2
Filing date	Mar 7, 2016
Priority date	Mar 23, 2015
Publication date	Aug 25, 2020
Grant date	Aug 25, 2020

Abstract

According to one implementation, a magnesium-lithium alloy in which at least lithium is added to magnesium is manufactured by giving a strain to a magnesium-lithium alloy workpiece, after a solution treatment, and progressing an aging of the magnesium-lithium alloy workpiece without a heat treatment. The strain is given by a cold working. The aging is progressed after giving the strain. Further, according to one implementation, an aircraft part includes the above-mentioned magnesium-lithium alloy as a material. Further, according to one implementation, a method of manufacturing an aircraft part includes processing the above-mentioned magnesium-lithium alloy.

First claim

What is claimed is:

1. A method of manufacturing an aircraft part comprising:
giving a strain to a magnesium-lithium alloy, having a lithium content that is not less than 6 weight percent and not more than 16.0 weight percent, after a solution treatment, by a cutting work or a shot peening as a cold working, and wherein the given strain to the alloy is not less than 0.5 percent and not more than 1.5 percent;
progressing an aging of the magnesium-lithium alloy after giving the strain, without a heat treatment; and
manufacturing the aircraft part by processing the magnesium-lithium alloy after a progress of the aging.

2. The method according to claim 1 , wherein a content of the lithium is not less than 10.5 weight percent and not more than 16.0 weight percent.

3. A method of manufacturing a magnesium-lithium alloy, having a lithium content that is not less than 6 weight percent and not more than 16.0 weight percent; comprising:
performing a solution treatment of a magnesium-lithium alloy workpiece;
giving a strain to the magnesium-lithium alloy workpiece after the solution treatment, by a cold working, wherein the given strain to the alloy is not less than 0.5 percent and not more than 1.5 percent; and
progressing an aging of the magnesium-lithium alloy workpiece after giving the strain, without a heat treatment for a predetermined period of at least 168 hours.

4. The method of manufacturing the magnesium-lithium alloy according to claim 3 , wherein the predetermined period of the aging is determined to make an elapsed time after the solution treatment be not less than 1000 hours.

5. The method of manufacturing the magnesium-lithium alloy according to claim 3 , wherein the strain is given to make an amount of the strain be not less than 1.0 percent and not more than 1.5 percent.

6. The method according to claim 3 , wherein a content of the lithium is not less than 10.5 weight percent and not more than 16.0 weight percent.

Assignees

• Fuji Heavy Ind Ltd
• Subaru Corp

Inventors

• Miura Ayako

Classifications

• B62D29/008

  predominantly of light alloys, e.g. extruded · CPC title

• C22F1/06 Primary

  of magnesium or alloys based thereon · CPC title

• C22C23/00

  Alloys based on magnesium · CPC title