Manufacturing method of aluminum alloy hollow section for aircraft empennage

A hollow profile and manufacturing method technology, applied in the field of hollow profile manufacturing, can solve the problems of low safety factor, low non-proportional elongation strength, low tensile strength, etc., to save machining, have no weld defects, and avoid stress cracking effect

Inactive Publication Date: 2012-12-12
NORTHEAST LIGHT ALLOY CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a method for manufacturing an aluminum alloy hollow profile for an aircraft empennage, so as to solve the problems of low tensile strength, low non-proportional elongation strength and low safety factor of existing aircraft empennage profiles

Method used

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specific Embodiment approach 1

[0011] Embodiment 1: The method of this embodiment includes the following steps: Step 1, Si: 0.7% to 1.3%, Fe≤0.5%, Cu≤0.10%, Mn: 0.40% to 0.8%, Mg: 0.40% by mass percentage % to 0.8%, Zn≤0.20%, Ti≤0.20%, and the balance is Al. Weigh aluminum alloy ingots, pure magnesium ingots, aluminum-manganese master alloys and aluminum-silicon master alloys into the drying furnace and melt to obtain aluminum melts. liquid, and then cast to obtain ingots;

[0012] Step 2. Homogenizing the ingot obtained in Step 1. The annealing temperature is 320°C-530°C, and the temperature is kept for 5-15 hours;

[0013] Step 3: Heating the aluminum alloy ingot obtained in step 2 to 350-450°C, and then putting it into a special mold to obtain a profile through needle-tip extrusion at an extrusion speed of 0.2-1.0 mm / s;

[0014] Step 4. Thread the front end of the profile with iron wire, hang it into the quenching furnace for quenching, the quenching temperature is 520°C-535°C, keep warm for 30-250 minu...

specific Embodiment approach 2

[0018] Embodiment 2: The annealing temperature of the ingot in step 2 of this embodiment is 380°C-420°C. Other implementation steps are the same as those in the first embodiment.

specific Embodiment approach 3

[0019] Specific embodiment three: the ingot heat preservation time in step two of the present embodiment is 8-10 hours. Other implementation steps are the same as those in the first embodiment.

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Abstract

The manufacturing method of an aluminum alloy hollow section for an aircraft empennage, and relates to a manufacturing method of a hollow section. The method solves the problems that the section for the traditional aircraft empennage has low tensile strength, low non-proportional extension strength and lower safety factor. The method comprises the following steps that according to the proportion of 0.7% to 1.3% by mass of Si, less than or equal to 0.5% by mass of Fe, less than or equal to 0.10% by mass of Cu, 0.40 to 0.8% by mass of Mn, 0.40% to 0.8% by mass of Mg, less than or equal to 0.20% by mass of Zn, less than or equal to 0.20% by mass of Ti, and the balance being Al, aluminum alloy ingots, pure magnesium ingots, aluminum-manganese intermediate alloy and aluminum-silicon intermediate alloy are weighed to be added to a drying furnace to obtain molten aluminum to be cast into ingots; the ingots are subjected to homogenizing annealing; the aluminum alloy ingots are extruded by a special mold and a needlepoint; the front end of the section is penetrated by an iron wire and the section is hung to a quenching furnace to be quenched; and the section is straightened. The method is used for manufacturing the aluminum alloy hollow section for the aircraft empennage.

Description

technical field [0001] The invention relates to a method for manufacturing a hollow profile. Background technique [0002] Aircraft empennage profiles used to use steel in the past. In order to reduce weight, the materials used for this profile abroad have been gradually replaced by aluminum alloys with low specific gravity and high strength since the 1970s. However, the earliest profiles used were castings with corresponding large specifications or Bars are machined. The microstructure and performance of the casting after processing cannot meet the requirements of the profile. However, 85% of the metal needs to be processed to form the shape of the bar after being processed, and the processing is difficult and time-consuming. Therefore, the manufacture of this profile must have sufficient strength, good fatigue resistance, precise inner hole size and excellent surface quality. According to the traditional extrusion process, the use requirements of the profile for the airc...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C21/02C22C1/03C22F1/043
Inventor 潘哲刘科研马琳袁丹丹姜春燕高新宇
Owner NORTHEAST LIGHT ALLOY CO LTD
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