CN112338003B - Shape correction method for manufacturing deformation of aluminum-magnesium alloy thin-wall cabin section - Google Patents

Shape correction method for manufacturing deformation of aluminum-magnesium alloy thin-wall cabin section Download PDF

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CN112338003B
CN112338003B CN202011045438.3A CN202011045438A CN112338003B CN 112338003 B CN112338003 B CN 112338003B CN 202011045438 A CN202011045438 A CN 202011045438A CN 112338003 B CN112338003 B CN 112338003B
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cabin
deformation
support tool
heat treatment
creep
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CN112338003A (en
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姜建堂
袁勇
姜浩
邵文柱
甄良
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Harbin Institute of Technology
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Harbin Institute of Technology
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D3/00—Straightening or restoring form of metal rods, metal tubes, metal profiles, or specific articles made therefrom, whether or not in combination with sheet metal parts
    • B21D3/14—Recontouring
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D11/00—Process control or regulation for heat treatments
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0006—Details, accessories not peculiar to any of the following furnaces
    • C21D9/0025—Supports; Baskets; Containers; Covers
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Forging (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)

Abstract

The invention provides a shape correction method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section, and belongs to the field of heat treatment deformation control. The invention effectively solves the problem of deformation in the manufacturing process of the existing aluminum-magnesium alloy thin-wall cabin section. The invention comprises the following steps: measuring the outline of the cabin member to form a digital model, and performing three-dimensional comparison on the digital model and an ideal cabin digital model to obtain the spatial distribution of roundness change; obtaining the material deformation and creep constitutive relation of the cabin member through a thermal simulation experiment and a creep test; designing and manufacturing an internal stay tool, and carrying out adjustable constraint on deformation positions of cabin members; establishing a finite element simulation platform to predict a stress distribution, stress-creep evolution and unloading rebound system in the constraint heat treatment process and selecting a loading position and loading strength according to the stress distribution, the stress-creep evolution and the unloading rebound; and (5) simultaneously placing the cabin member and the internal support tool into a heat treatment furnace for heat treatment. It is mainly used for shape correction and maintenance in cabin manufacturing process.

Description

Shape correction method for manufacturing deformation of aluminum-magnesium alloy thin-wall cabin section
Technical Field
The invention belongs to the field of heat treatment deformation control, and particularly relates to a shape correction method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section.
Background
The cabin-section components are main bearing components of aerospace equipment and are important bases for efficient and reliable service of the aircraft. In order to realize the accurate manufacture of complex structures such as bosses, complex rib plates and the like and achieve the design goal of high-efficiency bearing, a large number of cabin components are manufactured by using magnesium alloy and aluminum alloy thin-wall castings as blanks and adopting a machining method. Depending on the performance characteristics of the magnesium alloy/aluminum alloy and the complexity of the manufacturing process, the cabin components are easy to deform and cause out-of-tolerance deformation, can not be assembled and even can degrade service performance in the manufacturing process. Statistics show that the deformation problem of the cabin components is common, and the main deformation form is roundness deformation; analysis shows that the reasons for roundness distortion of the cabin are very complex, and the roundness distortion can be induced in the technical processes of casting cooling, solution quenching, aging treatment and the like. In view of the statistics and analysis described above, applying a load to target the component during heat treatment is the most effective technical measure to achieve shape correction and to maintain.
The basis for realizing the constrained shape correction of the cabin-section type components is to realize the accurate prediction and control of the creep process on the basis of the proper application of stress-temperature. To this end, methods need to be established that cover the overall process of shape distortion measurement-stress controlled application-material creep behavior control.
Disclosure of Invention
The invention provides a shape correction method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section, which aims to solve the problems in the prior art.
In order to achieve the above purpose, the present invention adopts the following technical scheme: a shape correction method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section comprises the following steps:
step 1: measuring the outline of the cabin member by a three-dimensional profiler to form a digital model of the outline of the cabin member, and carrying out three-dimensional comparison on the digital model of the outline of the cabin member and the digital model of an ideal cabin member to obtain the spatial distribution of roundness change;
step 2: obtaining the material deformation and creep constitutive relation of the cabin member through a thermal simulation experiment and a creep test;
step 3: designing and manufacturing an internal support tool according to the digital-analog of the outer contour of the cabin member obtained in the step 1, and carrying out adjustable constraint on the deformation position of the cabin member;
step 4: establishing a finite element simulation platform, predicting a system according to stress distribution, stress-creep evolution and unloading rebound in the constraint heat treatment process according to the data obtained in the step 2, and selecting a loading position and loading strength based on system trial calculation of the simulation platform;
step 5: and determining the constraint position and the constraint strength based on the result of the simulation platform, assembling and locking the cabin member and the internal support tool, and then placing the cabin member and the internal support tool into a heat treatment furnace for heat treatment.
Further, in the step 1, the radial profile is measured by axially different positions, so as to select the constraint loading position.
Further, the constraint loading position is a position with the largest deformation of the cabin member.
Furthermore, in the step 2, a series of stress-strain curves are obtained by performing thermal simulation experiments and creep experiments by selecting the alloy with the same heat treatment state, and the deformation and creep constitutive relation of the alloy is obtained through calculation.
Further, selecting an axial position and a radial propping position in the step 4, establishing a model of the cabin member and internal support tool assembly in a finite element simulation system, simulating loading processes of each radial position in the cabin member and internal support tool assembly and temperature rising processes of the cabin member and internal support tool assembly to obtain stress, strain and temperature distribution, simulating changes of stress and strain in the cabin member and predicting unloading rebound; the load position, load intensity, and temperature are adjusted based on the rebound prediction.
And further, naturally cooling to room temperature after the heat treatment in the step 5 is finished, dismantling the internal support tool, and checking the roundness of the section of the inner cavity of the cabin member.
Furthermore, the internal support tool is of a plane four-way or plane six-way uniformly distributed self-aligning structure, and multi-layer longitudinal assembly is carried out in the axial direction according to the shape correction requirement.
Furthermore, the inner support tool comprises a top block, a center ring and a mounting bolt, wherein the top block is connected with the center ring through the mounting bolt.
Compared with the prior art, the invention has the beneficial effects that: the invention solves the deformation problem in the manufacturing process of the existing aluminum-magnesium alloy thin-wall cabin section. The invention applies the constraint of adjustable load in the cabin member, can simultaneously realize the control of the deformation in the heat treatment process and the correction of the existing deformation, can realize the accurate manufacture of the aluminum-magnesium alloy cabin, obviously improves the manufacture efficiency of the member, and realizes the control and correction of the roundness distortion of the cabin based on the control of the heat treatment process. The axial position of the internal stay tool is adjustable, the axial direction is rotatable, and the radial displacement is adjustable, so that the flexible regulation and control of the constraint position and the constraint strength can be realized.
Drawings
FIG. 1 is a flow chart of a method for calibrating the manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section according to the invention;
FIG. 2 is a technical constitution diagram of a shape correction method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section according to the invention;
FIG. 3 is a schematic structural view of the assembled state of the cabin member and the internal stay tooling according to the present invention;
FIG. 4 is a schematic diagram of the internal stay tooling structure according to the present invention;
FIG. 5 is a graph of radial load versus calibration displacement for selected positions of a deck member according to the present invention;
fig. 6 illustrates plastic deformation of a shape-correcting cabin segment component at different temperatures according to the present invention.
1-cabin section components, 2-internal support tools, 3-ejector blocks, 4-center rings and 5-mounting bolts.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
Referring to fig. 1-6, a method for correcting the deformation of an aluminum-magnesium alloy thin-wall cabin section in the embodiment is described, which comprises the following steps:
step 1: measuring the outline of the cabin member 1 through a three-dimensional profiler to form a digital model of the outline of the cabin member 1, and carrying out three-dimensional comparison on the digital model of the outline of the cabin member 1 and an ideal cabin digital model to obtain the spatial distribution of roundness change;
step 2: obtaining the material deformation and creep constitutive relation of the cabin member 1 through a thermal simulation experiment and a creep experiment;
step 3: according to the digital-analog design and manufacturing internal support tool 2 of the outer contour of the cabin member 1 obtained in the step 1, the deformation position of the cabin member 1 is subjected to adjustable constraint;
step 4: establishing a finite element simulation platform, predicting a system according to stress distribution, stress-creep evolution and unloading rebound in the constraint heat treatment process according to the data obtained in the step 2, and selecting a loading position and loading strength based on system trial calculation of the simulation platform;
step 5: and determining the constraint position and the constraint strength based on the result of the simulation platform, assembling and locking the cabin member 1 and the internal support tool 2, and then placing the cabin member 1 and the internal support tool 2 into a heat treatment furnace for heat treatment.
Step 1 of this embodiment: the shape distortion of the cabin member 1 is measured, the constraint position is judged, the contour of the cabin member 1 is measured through a three-dimensional profiler, a digital model of the outer contour of the cabin member 1 is formed, and then the spatial distribution of roundness change is obtained through three-dimensional comparison with an ideal digital model. Step 2: and acquiring constitutive relation of deformation and creep, acquiring material parameters, and acquiring constitutive relation of the material of the cabin member 1 mainly based on a thermal simulation experiment and a creep experiment, wherein the acquisition of the constitutive relation of the deformation and the creep is required to cover different material states in order to cover the whole heat treatment process of the cabin member 1. Step 3: on the basis of the step 1, according to the deformation mode of the cabin member 1, the possible loading position and loading load are considered, the design of the internal support tool 2 is carried out to realize the adjustable constraint of the selected position, and in the process, the material selection of the internal support tool 2 should consider the temperature range of constraint shape correction, so that the internal support tool 2 is ensured to have enough strength and rigidity in the whole temperature range. Step 4: establishing a finite element simulation platform, and performing system verification to ensure the accuracy of platform simulation; thirdly, predicting stress distribution, stress-creep evolution and unloading rebound in the constraint heat treatment process based on the data obtained in the step 2; and optimizing and selecting loading positions and loading intensity based on system trial calculation of the simulation platform to realize optimal control. Step 5: and 4, on the basis of the step 4, assembling and locking the cabin section component 1 and the internal support tool 2 based on the constraint position and the constraint strength determined by the simulation design result, and then placing the cabin section component 1 and the internal support tool 2 into a heat treatment furnace for treatment.
In the step 1 of the embodiment, radial contours are measured at different axial positions, so that constraint loading positions are selected, three-dimensional contour comparison is not performed, and the scheme is mainly used for the situation that the structure is simple, but the three-dimensional contour of the cabin member 1 is difficult to measure.
Step 1 in this embodiment: testing the outer contour of the cabin member 1 through a three-dimensional profiler to form an outer contour map; the roundness change condition of the component is obtained through comparison with the cabin design digital model, and the position with the largest deformation is marked as the preselected position applied by the constraint. Step 2: carrying out thermal simulation experiments and creep experiments by selecting alloys with the same heat treatment state to obtain stress-strain curves under the conditions of wide temperature range, wide strain range and small strain quantity, and accordingly obtaining the thermal deformation and creep constitutive relation of the alloy; step 3: the inner support tool 2 of the cabin section is designed and manufactured, the inner support tool 2 is of a plane four-way or plane six-way uniform distribution self-aligning structure, multi-layer column assembly can be carried out in the axial direction according to the shape correction requirement, the inner support tool 2 comprises a top block 3, a center ring 4 and a mounting bolt 5, and the top block 3 is connected with the center ring 4 through the mounting bolt 5. The jacking blocks 3 are symmetrically or oppositely arranged in four directions or six directions and are uniformly distributed, load-adjustable constraint is applied to the inner cavity molded surface of the cabin member 1 respectively, and the size of the deformed cabin member 1 is extruded to the standard member size. Step 4: selecting an axial position and a radial propping position, establishing a model of the assembly of the cabin member 1 and the internal support tool 2 in a finite element simulation system, simulating the loading process of each radial position in the assembly of the cabin member 1 and the internal support tool 2 and the temperature raising process of the assembly of the cabin member 1 and the internal support tool 2 to obtain the temperature distribution of stress, strain and strain, simulating the change of the stress and strain in the cabin member 1 and predicting unloading rebound; and adjusting the loading position, loading intensity and temperature based on rebound prediction, and optimizing the shape correction process. Step 5: and installing an internal support tool 2 in the inner cavity of the cabin member 1, screwing in a position Shi Yading selected by the inner cavity profile of the cabin member 1 through an installation bolt 5 until the reverse bending amount determined by simulation is positive, placing the loaded cabin member 1 and the internal support tool 2 combination into a heat treatment furnace, naturally cooling to room temperature after heat treatment is finished, dismantling the internal support tool 2, and checking the roundness size of the inner cavity section of the cabin member 1.
The method for correcting the manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section provided by the invention is described in detail, and specific examples are applied to the principle and the implementation mode of the invention, and the description of the examples is only used for helping to understand the method and the core idea of the invention; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present invention, the present description should not be construed as limiting the present invention in view of the above.

Claims (5)

1. A shape correction method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section is characterized by comprising the following steps of: it comprises the following steps:
step 1: measuring the outline of the cabin member (1) through a three-dimensional profiler to form a digital model of the outline of the cabin member (1), and carrying out three-dimensional comparison on the digital model of the outline of the cabin member (1) and an ideal cabin digital model to obtain the spatial distribution of roundness change;
step 2: obtaining the material deformation and creep constitutive relation of the cabin member (1) through a thermal simulation experiment and a creep experiment; in the step 2, a series of stress-strain curves are obtained by carrying out thermal simulation experiments and creep experiments on the alloy with the same heat treatment state, and the deformation and creep constitutive relation of the alloy is obtained through calculation;
step 3: according to the digital-analog design of the outer contour of the cabin member (1) obtained in the step (1) and the manufacturing of the internal support tool (2), the deformation position of the cabin member (1) is subjected to adjustable constraint;
step 4: establishing a finite element simulation platform, predicting a system according to stress distribution, stress-creep evolution and unloading rebound in the constraint heat treatment process according to the data obtained in the step 2, and selecting a loading position and loading strength based on system trial calculation of the simulation platform;
step 5: determining constraint positions and constraint strength based on the results of the simulation platform, assembling and locking the cabin member (1) and the internal support tool (2), and then placing the cabin member (1) and the internal support tool (2) into a heat treatment furnace for heat treatment;
the inner support tool (2) is of a planar four-way or planar six-way uniform distribution self-centering structure, multi-layer longitudinal assembly is carried out in the axial direction according to the shape correction requirement, the inner support tool (2) comprises a top block (3), a center ring (4) and a mounting bolt (5), and the top block (3) is connected with the center ring (4) through the mounting bolt (5).
2. The method for correcting the manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 1, which is characterized in that: the radial profile is determined by axially varying the position in step 1, whereby the constraint loading position is selected.
3. The method for correcting the manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 2, which is characterized in that: the constraint loading position is the position with the largest deformation of the cabin member (1).
4. The method for correcting the manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 1, which is characterized in that: selecting an axial position and a radial jacking position in the step 4, establishing a model of the assembly of the cabin member (1) and the internal support tool (2) in a finite element simulation system, simulating the loading process of each radial position in the assembly of the cabin member (1) and the internal support tool (2) and the temperature rising process of the assembly of the cabin member (1) and the internal support tool (2) to obtain stress, strain and temperature distribution, simulating the change of stress and strain in the cabin member (1) and predicting unloading rebound; the load position, load intensity, and temperature are adjusted based on the rebound prediction.
5. The method for correcting the manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 1, which is characterized in that: and 5, naturally cooling to room temperature after the heat treatment is finished, dismantling the internal support tool (2), and checking the roundness of the section of the inner cavity of the cabin member (1).
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