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A heat treatment deformation control method and control fixture for aircraft slide rail parts

A technology for parts and fixtures, applied in the field of aircraft manufacturing, can solve problems such as thermal deformation, thermal expansion and contraction, and achieve the effects of improving efficiency, reasonable fixture structure and cost saving

Active Publication Date: 2016-02-24
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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  • A heat treatment deformation control method and control fixture for aircraft slide rail parts
  • A heat treatment deformation control method and control fixture for aircraft slide rail parts
  • A heat treatment deformation control method and control fixture for aircraft slide rail parts

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Embodiment Construction

[0018] Referring to accompanying drawing, the part in the embodiment is the slide rail class part of the neutral rib contour of certain model aircraft, and the material of this part is Ti-6Al-4V forging, as figure 1 As shown, the part 1 is composed of a thin-walled planar wing 3 and two vertical ribs 2 of equal height passing through the wing. The theoretical shape of the part is known. Since the part is about 3 meters long, the wall thickness and the thickness of the vertical rib are less than 4mm, the upper and lower surfaces of the plane wing plate 3 of the part and the two sides of the vertical rib 2 are precision surfaces, that is, the surface where deformation must be controlled. The vertical rib is perpendicular to the plane wing plate, and the root of the vertical rib is the stress concentration point. When the stress is released , the vertical ribs will be greatly deformed.

[0019] In order to control the deformation of the part during heat treatment, the present inv...

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Abstract

The invention relates to a deformation control method for heat treatment of an airplane sliding rail component, particularly of high sliding rail components such as vertical ribs with complex and irregular shape, large curvature change, large volume and thin wall. The invention also relates to a deformation control fixture. An upper surface of a positioning platform of the fixture has a theoretical shape identical to a lower surface of a component planar wing plate. A shape-keeping space of the vertical ribs of the component is formed between a positioning block and a positioning core. A wedge-shaped block is used to press a press bar tightly in cooperation of a connecting hole on a vertical column. 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 technology for heat treatment deformation control of parts, in particular to a method for heat treatment deformation control of slide rail parts of equal height to aircraft vertical ribs. Background technique [0002] The slide rail parts with the same height as the vertical ribs of the aircraft have a thin structure, and most of them are deep groove structures with large planes and vertical ribs, and the heights between the vertical ribs are equal. The length is long and belongs to thin-walled parts. Numerical control processing is required for many times, and multiple processes such as rough milling, semi-finish milling, and fine milling are performed. [0003] During the mechanical processing of parts, great internal stress will be generated. If these internal stresses are not effectively released, the parts will be seriously deformed, or hidden dangers will be...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C21D9/00C21D11/00
Inventor 史春玲杜红王浩军田有安
Owner XI'AN AIRCRAFT INTERNATIONAL
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