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A processing method of titanium alloy closing end

A processing method, titanium alloy technology, applied in the aerospace field, can solve problems such as inability to process, large residual stress, bulging, etc., and achieve the effects of improving product qualification rate, good molding quality, and high precision

Inactive Publication Date: 2008-04-09
NO 510 INST THE FIFTH RES INST OFCHINA AEROSPAE SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, spinning and hot stamping are commonly used at home and abroad as the forming method of the head. The material is titanium alloy. Due to the poor ductility of the material, the strength and hardness are very high, it is not suitable for the spinning processing method, and the spinning processing is easy in Surface defects are formed on the surface of the processed workpiece, which affects the fatigue performance of the product, and it is difficult to meet the reliability requirements of aerospace pressure vessels; hot stamping generally uses the method of heating the head blank once and stamping it once, and the blank cannot be processed. Any protection, this method will seriously oxidize the raw materials during the heating process, and will cause overburning and other phenomena. Due to one-time stamping and forming, the deformation of each part of the material will be uneven, and local "bulging" and collapse will easily occur, and the residual stress will be relatively large. , affecting subsequent machining, for stamping parts with large deformation, it cannot be repaired or processed, and the product qualification rate is difficult to guarantee

Method used

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  • A processing method of titanium alloy closing end

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0019] Processing of Φ1240 Titanium Alloy Hemispherical Head

[0020] ①. Fabrication of blanks: Select 18mm thick titanium alloy plates with a diameter of Φ1800mm for blanking, and turn the periphery to complete the production of blank 6.

[0021] ②. Constituent components: place the material piece 6 on one side in the groove plate 7 corresponding in size and shape, cover the other side of the material piece 6 with a cover plate 8 corresponding in size and shape, and weld the cover plate 8 and the periphery of the groove plate 7 , making up the component.

[0022] ③. Determine the punching die: select the outer diameter of the punch as Φ1207mm; the inner diameter of the pull ring 2 is Φ1325mm; the punch 1 is fixed on the guide post of the punch press, the pull ring 2 is installed in the seat ring 3, and the seat ring 3 is fixed on the seat pier 4 On, the seat pier 4 is fixed on the workbench of the punch press.

[0023] ④, Heating, stamping and forming: put the component int...

Embodiment 2

[0027] Hot Stamping Processing of Φ330 Titanium Alloy Hemispherical Head

[0028] ①. Fabrication of blanks: select 8 mm thick titanium alloy plates with a diameter of Φ540 mm for blanking, and turn the periphery to complete the production of blank 6.

[0029] ②. Constituent components: place the material piece 6 on one side in the groove plate 7 corresponding in size and shape, cover the other side of the material piece 6 with a cover plate 8 corresponding in size and shape, and weld the cover plate 8 and the periphery of the groove plate 7 , making up the component.

[0030] ③. Determine the punching die: select the outer diameter of the punch as Φ300mm; the inner diameter of the pull ring 2 is Φ360mm; the punch 1 is fixed on the guide post of the punch press, the pull ring 2 is installed in the seat ring 3, and the seat ring 3 is fixed on the seat pier 4 On, the seat pier 4 is fixed on the workbench of the punch press.

[0031] ④, Heating, stamping and forming: Put the com...

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Abstract

The invention discloses a processing method of a titanium alloy end socket. The invention is characterized in that a stamping component is protected by utilizing a clamping plate, a suitable ram head and a suitable lift-ring are selected, and the specified stamping temperature, the stamping speed and the stamping times are given to perform hot stamping processing to a work piece, and an inner profile and an outer profile of the product after the hot stamping is ensured to meet the requirement of subsequent processing; the hot processing is performed after the stamping. The invention mainly used for the processing of the titanium alloy end socket of the casing of a satellite tank, the end socket material processed is smooth, the shape is well, and the percent of pass is high.

Description

technical field [0001] The invention belongs to the field of aerospace technology, and relates to a method for manufacturing a shell of a satellite propellant storage tank, in particular to a processing method for a titanium alloy head. Background technique [0002] As the propellant storage, management and supply components of space vehicles such as satellites, the propellant tank has been widely used in spacecraft systems. The propellant tank includes two parts: the tank shell and the propellant management device. Among them, the tank shell is used to contain and seal the storage of the propellant. During the working process, the tank shell bears a certain working pressure. The tank shell for space application is composed of a hemispherical head and a cylindrical section. [0003] Among them, the molding of the head needs to be formed by sheet metal, and then finished into a thin-walled shell, which requires high molding precision of the shell, and the formed surface shoul...

Claims

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Application Information

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IPC IPC(8): B23P15/00F02K9/32
Inventor 周阳
Owner NO 510 INST THE FIFTH RES INST OFCHINA AEROSPAE SCI & TECH
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