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Deformation control method for heat treatment of airplane upper edge strip component

A technology of parts and flanges, which is applied in the field of aircraft manufacturing, can solve the problems of thermal deformation, thermal expansion and contraction, etc., and achieve the effects of improving efficiency, reasonable fixture structure, and cost saving

Active Publication Date: 2014-10-22
XI'AN AIRCRAFT INTERNATIONAL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This kind of tooling is different from ordinary machining equipment. It has to work repeatedly in the hot and cold cycle of high temperature heating and cooling, which will cause thermal expansion and contraction, and it will also face the problem of thermal deformation.

Method used

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  • Deformation control method for heat treatment of airplane upper edge strip component
  • Deformation control method for heat treatment of airplane upper edge strip component
  • Deformation control method for heat treatment of airplane upper edge strip component

Examples

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Embodiment Construction

[0019] Referring to the accompanying drawings, part 1 in the embodiment is a middle and upper edge part of a certain type of aircraft, and the material of this part is a Ti-6Al-4V forging, such as figure 1 As shown, the part is about 3 meters long, the wall thickness and rib thickness are less than 4mm, the upper surface and the lower surface of the part wing plate 2 are precision surfaces, that is, the surface that must control deformation, and there are upper vertical ribs 3 on the upper surface, There are lower vertical ribs 4 on the lower surface, and the two ends of the part are provided with process lugs 5 and positioning holes on the process lugs. The design theoretical shape data of the part is known.

[0020] In order to control the deformation of the part during heat treatment, the present invention discloses such as figure 2 In the shown control method, a deformation control fixture must first be provided, which contains a fixture body 6, a plurality of positioning...

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PUM

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Abstract

The invention relates to a deformation control method for heat treatment of airplane upper edge strip components. A component is composed of a thin wall-shaped curved wing plate and an upper vertical rib and a lower vertical rib which are disposed at a center of the wing plate, and has a known component shape. The invention also relates to a deformation control fixture. The fixture comprises a fixture body, a plurality of positioning blocks, a plurality of compression blocks and a connecting pin. The middle of an upper surface of each positioning block is provided with a an avoiding slot of a lower vertical rib at a corresponding portion of the component; and the middle of a lower surface of each compression block is provided with an avoiding slot of an upper vertical rib at a corresponding portion of the component. The deformation control fixture and the component are subjected to the heat treatment together and then separated from each other.

Description

technical field [0001] The invention belongs to the technical field of aircraft manufacturing, and relates to a heat treatment deformation control technology of parts, in particular to a method for controlling heat treatment deformation of upper edge strip parts of an aircraft. Background technique [0002] In aircraft manufacturing, there are a lot of machined parts such as upper edge strips. Most of these parts are Ti-6Al-4V forgings in the raw material state. , The lower vertical ribs are composed. With the continuous development of aircraft technology, in some large aircraft, the length of these upper edge parts is longer, the longest is 3 meters, the shape is complex, the curvature changes greatly and the wall is thin. The theoretical outer surface and vertical rib surface of these upper edge parts need to be processed by multiple CNC machining, which are CNC rough milling, semi-finish milling, finish milling and other processes. [0003] Such titanium alloy parts wil...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C21D9/00C21D11/00
Inventor 史春玲王建峰王浩军田有安
Owner XI'AN AIRCRAFT INTERNATIONAL
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