Method for manufacturing aluminum alloy rivet rod for aerospace product

Abstract

The invention relates to a method for manufacturing a high shear-resistant strength and high percentage elongation after fracture aluminum alloy rivet rod for the aerospace product, belonging to the method for manufacturing an aluminum alloy rod, and aiming to solve the problems of low non-proportional extension strength, shearing strength, tensile strength and extension at break of the existing aluminum alloy rivet rod for the aerospace product. The method comprises the following steps: (1) preparing molten alloy; (2) casting an alloy rod; (3) cutting off the cast alloy rod; (4) turning the peel of the cast alloy rod; (5) carrying out homogenizing annealing; (6) heating the cast alloy rod; (7) extruding; (8) carrying out cold-drawing by using a mold; (9) quenching; (10) straightening; and (11) aging to obtain the aluminum alloy rivet rod for the aerospace product. The aluminum alloy rivet rod manufactured by adopting the method has the tensile strength of not less than 431N / mm<2>, the non-proportional extension strength of not less than 265N / mm<2>, the extension at break of not less than 16% and the shearing strength of not less than 255N / mm<2> and meets the application requirement of the aerospace product. The method can be used for processing and manufacturing the aluminum alloy rivet for the aerospace product.

Description

technical field

[0001] The invention relates to a method for manufacturing an aluminum alloy rivet bar. Background technique

[0002] At present, a certain aerospace product in our country needs a special rivet, which requires the tensile strength of this alloy bar to reach 431N / mm 2 , non-proportional extension strength 265N / mm 2 , elongation after breaking 16%, shear strength 255N / mm 2 , but the tensile strength of the alloy produced by the existing process is 339-427N / mm 2 , elongation after breaking 10.3~14.5%, shear strength 245~253N / mm 2 , so it cannot meet the application requirements of aerospace products. Contents of the invention

[0003] The purpose of the invention is to solve the problems of low tensile strength, non-proportional elongation strength, elongation after fracture and low shear strength of existing rivet bars, and provides a manufacturing method of aluminum alloy rivet bars for aerospace.

[0004] A method for manufacturing an aluminum alloy r...

Examples

specific Embodiment approach 1

[0007] Specific Embodiment 1: The manufacturing method of an aluminum alloy rivet bar for aerospace according to the present embodiment is realized according to the following steps: 1. According to the mass percentage of elements in the aluminum alloy bar, Mg: 0.5% to 1.0%, Cr: 0.10%~0.20%, Si: 0~0.25%, Fe: 0~0.35%, Cu: 4.5%~5.2%, Mn: 0.40%~0.6%, Ti: 0.04%~0.12%, Zr: 0.1%~0.2% % and the ratio of the balance Al Weigh aluminum ingots, aluminum-manganese alloys, aluminum-zirconium alloys, aluminum-titanium alloys, aluminum-chromium alloys, copper ingots and magnesium ingots, and add them to the melting furnace. Smelting at low temperature for 3 to 4 hours to obtain molten aluminum alloy; 2. The molten aluminum alloy obtained in step 1 is cast at a casting temperature of 725°C to 750°C, a casting speed of 90mm / min to 95mm / min, and a cooling water intensity of 0.01MPa ~ 0.03MPa and cooling water temperature of 10 ℃ ~ 20 ℃ under the conditions of casting into cast rods with a diamet...

specific Embodiment approach 2

[0010] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that in step 1, the mass percentages of elements in the aluminum alloy bar are Mg: 0.7%-0.9%, Cr: 0.12%-0.16%, Si: 0.01 %~0.15%, Fe: 0.1%~0.25%, Cu: 4.6%~5.1%, Mn: 0.49%~0.55%, Ti: 0.06%~0.10%, Zr: 0.12%~0.18% and the ratio of the balance Al , weighing aluminum ingots, aluminum-manganese alloys, aluminum-zirconium alloys, aluminum-titanium alloys, aluminum-chromium alloys, copper ingots and magnesium ingots. Others are the same as in the first embodiment.

specific Embodiment approach 3

[0011] Specific embodiment 3: The difference between this embodiment and specific embodiment 1 or 2 is that in step 1, the mass percentages of elements in the aluminum alloy bar are Mg: 0.75%, Cr: 0.13%, Si: 0.06%, Fe: 0.16%, Cu: 4.79%, Mn: 0.51%, Ti: 0.084%, Zr: 0.14% and the ratio of the balance Al, weighing aluminum ingots, aluminum-manganese alloys, aluminum-zirconium alloys, aluminum-titanium alloys, aluminum-chromium alloys, Copper and Magnesium Ingots. Others are the same as in the first or second embodiment.

technical field

[0001] The invention relates to a method for manufacturing an aluminum alloy rivet bar. Background technique

[0002] At present, a certain aerospace product in our country needs a special rivet, which requires the tensile strength of this alloy bar to reach 431N / mm 2 , non-proportional extension strength 265N / mm 2 , elongation after breaking 16%, shear strength 255N / mm 2 , but the tensile strength of the alloy produced by the existing process is 339-427N / mm 2 , elongation after breaking 10.3~14.5%, shear strength 245~253N / mm 2 , so it cannot meet the application requirements of aerospace products. Contents of the invention

[0003] The purpose of the invention is to solve the problems of low tensile strength, non-proportional elongation strength, elongation after fracture and low shear strength of existing rivet bars, and provides a manufacturing method of aluminum alloy rivet bars for aerospace.

[0004] A method for manufacturing an aluminum alloy r...

Examples

specific Embodiment approach 1

[0007] Specific Embodiment 1: The manufacturing method of an aluminum alloy rivet bar for aerospace according to the present embodiment is realized according to the following steps: 1. According to the mass percentage of elements in the aluminum alloy bar, Mg: 0.5% to 1.0%, Cr: 0.10%~0.20%, Si: 0~0.25%, Fe: 0~0.35%, Cu: 4.5%~5.2%, Mn: 0.40%~0.6%, Ti: 0.04%~0.12%, Zr: 0.1%~0.2% % and the ratio of the balance Al Weigh aluminum ingots, aluminum-manganese alloys, aluminum-zirconium alloys, aluminum-titanium alloys, aluminum-chromium alloys, copper ingots and magnesium ingots, and add them to the melting furnace. Smelting at low temperature for 3 to 4 hours to obtain molten aluminum alloy; 2. The molten aluminum alloy obtained in step 1 is cast at a casting temperature of 725°C to 750°C, a casting speed of 90mm / min to 95mm / min, and a cooling water intensity of 0.01MPa ~ 0.03MPa and cooling water temperature of 10 ℃ ~ 20 ℃ under the conditions of casting into cast rods with a diamet...

specific Embodiment approach 2

[0010] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that in step 1, the mass percentages of elements in the aluminum alloy bar are Mg: 0.7%-0.9%, Cr: 0.12%-0.16%, Si: 0.01 %~0.15%, Fe: 0.1%~0.25%, Cu: 4.6%~5.1%, Mn: 0.49%~0.55%, Ti: 0.06%~0.10%, Zr: 0.12%~0.18% and the ratio of the balance Al , weighing aluminum ingots, aluminum-manganese alloys, aluminum-zirconium alloys, aluminum-titanium alloys, aluminum-chromium alloys, copper ingots and magnesium ingots. Others are the same as in the first embodiment.

specific Embodiment approach 3

[0011] Specific embodiment 3: The difference between this embodiment and specific embodiment 1 or 2 is that in step 1, the mass percentages of elements in the aluminum alloy bar are Mg: 0.75%, Cr: 0.13%, Si: 0.06%, Fe: 0.16%, Cu: 4.79%, Mn: 0.51%, Ti: 0.084%, Zr: 0.14% and the ratio of the balance Al, weighing aluminum ingots, aluminum-manganese alloys, aluminum-zirconium alloys, aluminum-titanium alloys, aluminum-chromium alloys, Copper and Magnesium Ingots. Others are the same as in the first or second embodiment.