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Stress-relaxation shaping method for complicated irregular-shaped integrated wallboard

A technology of stress relaxation and integral panel, which is applied in the direction of furnace type, furnace, heat treatment furnace, etc., can solve the problems of difficult manufacturing, long production cycle, and high processing cost of aircraft panel parts, so as to improve structural efficiency and shorten production cycle Effect

Inactive Publication Date: 2011-09-21
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006]In order to overcome the disadvantages of high processing cost and long production cycle of aircraft panel parts caused by the difficulty in manufacturing complex and special-shaped integral panels with high ribs in the prior art, The present invention proposes a stress relaxation forming method for complex special-shaped integral wall panels

Method used

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  • Stress-relaxation shaping method for complicated irregular-shaped integrated wallboard
  • Stress-relaxation shaping method for complicated irregular-shaped integrated wallboard
  • Stress-relaxation shaping method for complicated irregular-shaped integrated wallboard

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] This embodiment is used for forming (750×710) mm aircraft wing high-rib strip complex special-shaped integral wall panels. The mold used in the forming is an autoclave aging forming mold. The siding material is 2124-T85 aluminum alloy. The shaping process of the present embodiment comprises the following steps:

[0029] 1. Prepare materials. The materials to be prepared include: AT200Y is used for sealing putty with a working temperature of 204°C; the vacuum bag is made of WL7400 nylon vacuum film with a working temperature of 204°C, which has a melting point of 215°C; the air felt is Airweave N-10 with a working temperature of 204°C.

[0030] 2. Clean the mold and the panel to be formed. Degrease and clean the mold and the wall to be formed with acetone.

[0031] 3. Make vacuum bags. Position the siding blank on the mold and cover it with two layers of air felt; the position of the air felt should ensure that the outer surface of the mold is well wrapped, and add ...

Embodiment 2

[0039] This embodiment is used for forming (300×300) mm aircraft wing high-rib strips with complex and special-shaped integral wall panels. The mold used in the forming is an autoclave aging forming mold. Siding material 2124-T85 aluminum alloy. The concrete steps of this embodiment are as follows:

[0040] 1. Prepare materials. Materials to be prepared include: GS-213-3 for sealing putty with a service temperature of 232°C; vacuum bag with HK7400 nylon vacuum film with a service temperature of 210°C, which has a melting point of 220°C; air felt with AIRBLEED100 / 100GREY.

[0041] 2. Clean the mold and the panel to be formed. Degrease and clean the mold and the wall to be formed with acetone.

[0042] 3. Make vacuum bags. Position the siding blank on the mold and cover with three layers of air felt; the position of the air felt should ensure that the outer surface of the mold is well wrapped, and add two layers of air felt at the sharp corners and pores on the mold and t...

Embodiment 3

[0050] This embodiment is used for forming (500×500) mm aircraft wing high-rib strips with complex and special-shaped integral wall panels. The mold used in the forming is an autoclave aging forming mold. Siding material 2124-T85 aluminum alloy. The concrete steps of this embodiment are as follows:

[0051] 1. Prepare materials. The materials to be prepared include: SM5160 for sealing putty with a service temperature of 371°C; HK8400 nylon vacuum film with a service temperature of 232°C for the vacuum bag, which has a melting point of 260°C; AIRBLEED10HA with a service temperature of 205°C for the air felt.

[0052] 2. Clean the mold and the panel to be formed. Degrease and clean the mold and the wall to be formed with acetone.

[0053] 3. Make vacuum bags. Position the siding blank on the mold and cover with three layers of air felt; the position of the air felt should ensure that the outer surface of the mold is well wrapped, and add two layers of air felt at the sharp ...

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Abstract

The invention relates to a stress-relaxation shaping method for a complicated irregular-shaped integrated wallboard, which is characterized by the steps of: positioning wallboard parts above a mold in a sealed space formed by a vacuum bag and a bottom plate of the mold, vacuumizing, and increasing the pressure of an autoclave to form a pressure difference between the inside and outside of the sealed space, so that the parts are abutted against the mold due to the external pressure so as to form the shape of mold surface. High temperature is beneficial to rapid release of the internal stress of the deformed parts so as to transform elastic deformation into plastic deformation, thus realizing stress-relaxation shaping. The invention has a simple shaping process, is convenient to operate, and overcomes the defects of high processing cost and long production period of parts such as wallboards of airplane because of the difficulty in manufacturing a high-rib complicated irregular-shaped integrated wallboard.

Description

technical field [0001] The invention relates to the field of aircraft manufacturing, and relates to a processing method for forming complex and special-shaped integral wall panels with high-rib strips for fuselage and wings. Background technique [0002] The integral wall panel is an important part of a modern aircraft. It is not only an important part of the aerodynamic shape of the aircraft, but also the main load-bearing component of the wing and fuselage. Since the ribs on the siding participate in the deformation, the difficulty of forming it increases. Aging forming technology (creep aging forming technology) is a technology developed in the early 1950s to form integral wallboard parts, that is, a forming method that uses the creep characteristics of metal to synchronize forming and aging . [0003] The invention publication number of FOROUDASTAN SAAED D and HOLMAN MITCHELL C in the United States is: EP0527570 patent "Method of developing complex tool shapes" propose...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22F1/00C22F1/04C21D8/00C21D1/00C21D9/00
Inventor 甘忠谭海兵
Owner NORTHWESTERN POLYTECHNICAL UNIV
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