CN112338003A - 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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Publication number
CN112338003A
CN112338003A CN202011045438.3A CN202011045438A CN112338003A CN 112338003 A CN112338003 A CN 112338003A CN 202011045438 A CN202011045438 A CN 202011045438A CN 112338003 A CN112338003 A CN 112338003A
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China
Prior art keywords
cabin section
cabin
deformation
component
aluminum
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CN202011045438.3A
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CN112338003B (en
Inventor
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

Abstract

The invention provides a shape correcting 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 component to form a digital model and comparing the digital model with an ideal cabin digital model in three dimensions to obtain the spatial distribution of roundness change; obtaining the material deformation and creep constitutive relation of the cabin section component through a thermal simulation experiment and a creep experiment; designing and manufacturing an internal bracing tool, and carrying out adjustable constraint on deformation positions of cabin section components; establishing a finite element simulation platform to carry out systematic prediction on stress distribution, stress-creep evolution and unloading resilience in the constraint heat treatment process, and selecting a loading position and loading strength according to the systematic prediction; and simultaneously placing the cabin section component and the internal support tool into a heat treatment furnace for heat treatment. It is mainly used for shape correction and maintenance in the manufacturing process of the cabin section.

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 correcting method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section.
Background
The cabin components are main bearing components of aerospace equipment and are important foundations for efficient and reliable service of aircrafts. In order to realize the accurate manufacture of the complex structures such as the lug boss, the complex rib plate and the like and achieve the design goal of high-efficiency bearing, a large amount of magnesium alloy and aluminum alloy thin-wall castings are used as blanks for cabin-section components and are manufactured by a machining method. The cabin part is easy to deform and cause deformation out of tolerance, assembly failure and even service performance degradation in the manufacturing process depending on the performance characteristics of the magnesium alloy/aluminum alloy and the complexity of the manufacturing process. Statistics shows that the deformation problem of the cabin type components is common, and the main deformation form is roundness distortion; analysis shows that the reason for roundness distortion of the cabin section is 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 above statistics and analysis, targeted constraint of the component by applying loads during heat treatment is the most effective technical measure to achieve shape correction and retention.
The basis of the realization of the constraint correction of the cabin-section-type components is to realize accurate prediction and control of a creep process on the basis of proper application of stress-temperature. For this reason, it is necessary to establish a method that covers the whole process of "shape distortion measurement-stress controllable application-material creep behavior control".
Disclosure of Invention
The invention provides a shape correcting method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section, aiming at solving the problems in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme: a shape correcting method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section comprises the following steps:
step 1: measuring the outer contour of the cabin section component through a three-dimensional profile instrument to form a digital model of the outer contour of the cabin section component, and performing three-dimensional comparison on the digital model of the outer contour of the cabin section component and an ideal cabin section digital model to obtain the spatial distribution of roundness change;
step 2: obtaining the material deformation and creep constitutive relation of the cabin section component through a thermal simulation experiment and a creep experiment;
and step 3: designing and manufacturing an inner support tool according to the numerical model of the outer contour of the cabin section component obtained in the step 1, and carrying out adjustable constraint on the deformation position of the cabin section component;
and 4, step 4: establishing a finite element simulation platform, carrying out systematic prediction on stress distribution, stress-creep evolution and unloading resilience 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 systematic trial calculation of the simulation platform;
and 5: and determining a constraint position and a constraint strength based on the result of the simulation platform to assemble and lock the cabin component and the inner support tool, and then putting the cabin component and the inner support tool into a heat treatment furnace for heat treatment.
Further, the radial profile is determined at different axial positions in step 1, so that the constraint loading position is selected.
Further, the constraint loading position is a position where the deformation amount of the cabin section component is maximum.
Furthermore, in the step 2, an alloy in the same heat treatment state is selected to perform a thermal simulation experiment and a creep experiment to obtain a series stress-strain curve, and the deformation and creep constitutive relation of the alloy is obtained through calculation.
Further, in the step 4, an axial position and a radial jacking position are selected, a model of the cabin component and the inner support tooling assembly is established in a finite element simulation system, a loading process of each radial position in the cabin component and the inner support tooling assembly and a temperature rise process of the cabin component and the inner support tooling assembly are simulated, temperature distribution of stress, strain and temperature distribution are obtained, changes of stress and strain in the cabin component are simulated, and unloading resilience is predicted; the loading position, loading intensity and temperature are adjusted based on the springback prediction.
Further, after the heat treatment in the step 5 is finished, naturally cooling to room temperature, removing the inner support tool, and checking the roundness size of the section of the inner cavity of the cabin component.
Furthermore, the inner support tool is a plane four-way or plane six-way uniformly distributed self-abutting structure, and multi-layer longitudinal assembly is carried out in the axial direction according to the shape correction requirement.
Furthermore, the internal stay 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 component, 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 manufacturing efficiency of the component, and realizes the control and the correction of the roundness distortion of the cabin based on the control of the heat treatment process. The axial position of the adopted internal support tool is adjustable, the axial rotation is realized, 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 shape correction method for manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section according to the invention;
FIG. 2 is a technical composition 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 an assembled state of a cabin segment component and an inner supporting tool according to the present invention;
FIG. 4 is a schematic structural view of the inner support tool of the present invention;
FIG. 5 is a graph of radial load versus profile displacement for selected locations of a nacelle component according to the present invention;
FIG. 6 is a graph illustrating plastic deformation of a cabin segment component during shape correction at different temperatures according to the present invention.
1-cabin section component, 2-internal support tool, 3-top block, 4-center ring and 5-mounting bolt.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely explained below with reference to the drawings in the embodiments of the present invention.
Referring to fig. 1-6, the embodiment is described, and a method for correcting the manufacturing deformation of an aluminum-magnesium alloy thin-wall cabin section comprises the following steps:
step 1: measuring the outline of the cabin section component 1 by a three-dimensional profile instrument to form a digital model of the outline of the cabin section component 1, and comparing the digital model of the outline of the cabin section component 1 with an ideal cabin section digital model in three dimensions to obtain the spatial distribution of roundness change;
step 2: obtaining the material deformation and creep constitutive relation of the cabin component 1 through a thermal simulation experiment and a creep experiment;
and step 3: designing and manufacturing an inner support tool 2 according to the numerical model of the outer contour of the cabin component 1 obtained in the step 1, and carrying out adjustable constraint on the deformation position of the cabin component 1;
and 4, step 4: establishing a finite element simulation platform, carrying out systematic prediction on stress distribution, stress-creep evolution and unloading resilience 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 systematic trial calculation of the simulation platform;
and 5: and determining a constraint position and constraint strength based on the result of the simulation platform to assemble and lock the cabin component 1 and the inner support tool 2, and then putting the cabin component 1 and the inner support tool 2 into a heat treatment furnace for heat treatment.
This example includes step 1: measuring the shape distortion of the cabin section component 1, judging the constraint position, measuring the outline of the cabin section component 1 through a three-dimensional profile instrument to form a digital model of the outline of the cabin section component 1, and then obtaining the spatial distribution of roundness change through three-dimensional comparison with an ideal digital model. Step 2: acquiring the constitutive relation of deformation and creep, acquiring material parameters, and acquiring the material constitutive relation of the cabin section component 1 mainly based on a thermal simulation experiment and a creep test, wherein in order to cover the whole heat treatment process of the cabin section component 1, the acquisition of the deformation and creep relation must cover different material states. And step 3: on the basis of the step 1, according to the deformation mode of the cabin component 1, possible loading positions and loading loads are considered, the inner support tool 2 is designed to achieve adjustable constraint of the selected position, in the process, the temperature range of constraint and correction is considered for material selection of the inner support tool 2, and the inner support tool 2 is guaranteed to have enough strength and rigidity in the full temperature range. And 4, step 4: establishing a finite element simulation platform and carrying out system verification to ensure the accuracy of platform simulation; then, based on the data obtained in the step 2, carrying out systematic prediction on stress distribution, stress-creep evolution and unloading resilience in the constraint heat treatment process; and performing optimal selection of loading positions and loading strength based on system trial calculation of the simulation platform to realize optimal control. And 5: and 4, on the basis of the simulation design result, assembling and locking the cabin section component 1 and the inner support tool 2 based on the constraint position and the constraint strength determined by the simulation design result, and then putting the cabin section component 1 and the inner support tool 2 into a heat treatment furnace for treatment.
In the step 1 of the embodiment, the radial profile is determined through different axial positions, so that the constraint loading position is selected, and no three-dimensional profile comparison is performed.
Step 1 in this example: testing the outer contour of the cabin component 1 by a three-dimensional profile instrument to form an outer contour diagram; and obtaining the roundness change condition of the component by comparing with the cabin section design digital model, and marking the position with the maximum deformation as a preselected position for constraint application. Step 2: selecting alloys in the same heat treatment state to perform a thermal simulation experiment and a creep experiment, obtaining a stress-strain curve under the conditions of a wide temperature range, a wide strain range and a small strain amount, and accordingly obtaining the thermal deformation and creep constitutive relation of the alloys; and step 3: the cabin section inner supporting tool 2 is designed and manufactured, the inner supporting tool 2 is of a plane four-way or plane six-way uniformly distributed self-opposite-top structure, multi-layer longitudinal assembly can be carried out in the axial direction according to shape correction requirements, the inner supporting 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 arranged in four directions or six directions in opposite directions and are uniformly distributed, load-adjustable constraint is respectively applied to the molded surface of the inner cavity of the cabin component 1, and the size of the deformed cabin component 1 is extruded to the size of a standard component. And 4, step 4: selecting an axial position and a radial jacking position in the step 4, establishing a model of a cabin component 1 and inner support tool 2 combination in a finite element simulation system, simulating the loading process of each radial position in the cabin component 1 and inner support tool 2 combination and the temperature rise process of the cabin component 1 and inner support tool 2 combination to obtain stress, strain and temperature distribution, simulating the change of the stress and strain in the cabin component 1 and predicting unloading resilience; and adjusting the loading position, the loading strength and the temperature based on the springback prediction, and optimizing the shape correction process. And 5: installing an inner support tool 2 in the inner cavity of the cabin section component 1, screwing in through an installation bolt 5 to apply pressure and jacking to a selected position of the molded surface of the inner cavity of the cabin section component 1 to a reversely bent amount determined by simulation, placing the loaded cabin section component 1 and the inner support tool 2 combination into a heat treatment furnace, naturally cooling to room temperature after the heat treatment is finished, removing the inner support tool 2, and checking the roundness size of the section of the inner cavity of the cabin section component 1.
The shape correcting method for manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section provided by the invention is described in detail, a specific example is applied in the method to explain the principle and the implementation mode of the invention, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.

Claims (8)

1. A shape correcting 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 section component (1) through a three-dimensional profile instrument to form a digital model of the outline of the cabin section component (1), and performing three-dimensional comparison on the digital model of the outline of the cabin section component (1) and an ideal cabin section digital model to obtain the spatial distribution of roundness change;
step 2: obtaining the material deformation and creep constitutive relation of the cabin section component (1) through a thermal simulation experiment and a creep experiment;
and step 3: designing and manufacturing an inner support tool (2) according to the numerical model of the outer contour of the cabin section component (1) obtained in the step (1), and carrying out adjustable constraint on the deformation position of the cabin section component (1);
and 4, step 4: establishing a finite element simulation platform, carrying out systematic prediction on stress distribution, stress-creep evolution and unloading resilience 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 systematic trial calculation of the simulation platform;
and 5: and determining a constraint position and constraint strength based on the result of the simulation platform to assemble and lock the cabin section component (1) and the inner support tool (2), and then putting the cabin section component (1) and the inner support tool (2) into a heat treatment furnace for heat treatment.
2. The shape correcting method for manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 1, characterized by comprising the following steps of: in the step 1, the radial profile is measured at different axial positions, so that a constraint loading position is selected.
3. The shape correcting method for manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 2, characterized by comprising the following steps of: the constraint loading position is the position where the deformation of the cabin component (1) is maximum.
4. The shape correcting method for manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 1, characterized by comprising the following steps of: in the step 2, the alloy in the same heat treatment state is selected to perform a thermal simulation experiment and a creep experiment to obtain a serialized stress-strain curve, and the deformation and creep constitutive relation of the alloy is obtained through calculation.
5. The shape correcting method for manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 1, characterized by comprising the following steps of: selecting an axial position and a radial jacking position in the step 4, establishing a model of a cabin component (1) and inner support tooling (2) combination in a finite element simulation system, simulating the loading process of each radial position in the cabin component (1) and inner support tooling (2) combination and the temperature rise process of the cabin component (1) and inner support tooling (2) combination to obtain stress, strain and temperature distribution, simulating the change of the stress and strain in the cabin component (1) and predicting unloading resilience; the loading position, loading intensity and temperature are adjusted based on the springback prediction.
6. The shape correcting method for manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 1, characterized by comprising the following steps of: and 5, naturally cooling to room temperature after the heat treatment in the step 5, removing the inner support tool (2), and checking the roundness size of the section of the inner cavity of the cabin section component (1).
7. The shape correcting method for manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 1, characterized by comprising the following steps of: the inner support tool (2) is of a plane four-way or plane six-way uniformly-distributed self-butting structure, and multi-layer longitudinal assembly is carried out in the axial direction according to the shape correction requirement.
8. The shape correcting method for manufacturing deformation of the aluminum-magnesium alloy thin-wall cabin section according to claim 7, characterized by comprising the following steps of: 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).
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113235026A (en) * 2021-04-29 2021-08-10 中南大学 Deformation control method for magnesium alloy cabin casting heat treatment process
CN113642129A (en) * 2021-08-24 2021-11-12 山东大学 Workpiece correction load rapid application and deformation finite element acquisition method
CN114134304A (en) * 2021-10-29 2022-03-04 航天材料及工艺研究所 Large-specification 2195 aluminum lithium alloy spinning shell heat treatment deformation control tool and method
CN114734279A (en) * 2022-03-31 2022-07-12 江阴市博汇机械成套设备有限公司 Micro-digital correction fixture and correction method for cylindricity error of thin-wall sleeve
CN114834769A (en) * 2022-07-05 2022-08-02 北京凌空天行科技有限责任公司 Deformation-preventing storage tool for carrier rocket cabin
CN117272552A (en) * 2023-11-23 2023-12-22 中南大学 Barrel thermal correction method and barrel thermal correction tool design method

Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1315074A1 (en) * 1985-07-01 1987-06-07 Казанский Авиационный Институт Им.А.Н.Туполева Method of rotary moulding and sizing of annular parts
JPH10166056A (en) * 1997-11-07 1998-06-23 Kawasaki Heavy Ind Ltd Spring back predicting method for age forming
JP2008297931A (en) * 2007-05-29 2008-12-11 Toshiba Corp Method of correcting deformation of gas turbine high temperature part
JP2009079495A (en) * 2007-09-25 2009-04-16 Toshiba Corp Deformation-correction method for gas-turbine component
CN202655402U (en) * 2012-07-17 2013-01-09 中国葛洲坝集团股份有限公司 Device for adjusting roundness of penstock and supporting penstock
JP2014018828A (en) * 2012-07-18 2014-02-03 Nippon Steel & Sumikin Engineering Co Ltd Device for correcting pipe material
CN105779748A (en) * 2014-12-24 2016-07-20 北京有色金属研究总院 Aging strengthened alloy ring creep aging shape correcting method
CN106148862A (en) * 2015-04-17 2016-11-23 首都航天机械公司 Large cylindrical tubular aluminium alloy castings creep ageing heat treatment method
CN206701987U (en) * 2017-04-26 2017-12-05 山西晋西精密机械有限责任公司 A kind of cylindrical member finely tunes rounding device
CN107471617A (en) * 2017-08-16 2017-12-15 航天材料及工艺研究所 A kind of composite bay section shape righting tool and straightening method
CN107617654A (en) * 2017-09-11 2018-01-23 洛阳乾中新材料科技有限公司 The bearing calibration of casting circularity and the correcting tool using this method
CN107639151A (en) * 2017-09-18 2018-01-30 上海航天精密机械研究所 A kind of large scale annular element digitlization flexible forming apparatus and method
CN107866491A (en) * 2017-12-06 2018-04-03 哈尔滨工业大学 A kind of aluminium alloy plate class member freezes manufacturing process
CN108118271A (en) * 2017-12-08 2018-06-05 北京星航机电装备有限公司 A kind of allotype aluminum alloy bay section method for controlling heat treatment deformation
CN109112446A (en) * 2018-09-13 2019-01-01 湖北三江航天红阳机电有限公司 Large thin-wall high strength alumin ium alloy bipyramid diamond shape entirety cabin shell precision casting molding method
CN111451380A (en) * 2020-04-08 2020-07-28 上海交通大学 High-temperature alloy double-ring multi-support-plate thin-wall casting accurate thermal shape correcting die and method
CN111674566A (en) * 2020-05-25 2020-09-18 哈尔滨工业大学 Adjustable inner support restraining device for controlling roundness of cabin section component

Patent Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1315074A1 (en) * 1985-07-01 1987-06-07 Казанский Авиационный Институт Им.А.Н.Туполева Method of rotary moulding and sizing of annular parts
JPH10166056A (en) * 1997-11-07 1998-06-23 Kawasaki Heavy Ind Ltd Spring back predicting method for age forming
JP2008297931A (en) * 2007-05-29 2008-12-11 Toshiba Corp Method of correcting deformation of gas turbine high temperature part
JP2009079495A (en) * 2007-09-25 2009-04-16 Toshiba Corp Deformation-correction method for gas-turbine component
CN202655402U (en) * 2012-07-17 2013-01-09 中国葛洲坝集团股份有限公司 Device for adjusting roundness of penstock and supporting penstock
JP2014018828A (en) * 2012-07-18 2014-02-03 Nippon Steel & Sumikin Engineering Co Ltd Device for correcting pipe material
CN105779748A (en) * 2014-12-24 2016-07-20 北京有色金属研究总院 Aging strengthened alloy ring creep aging shape correcting method
CN106148862A (en) * 2015-04-17 2016-11-23 首都航天机械公司 Large cylindrical tubular aluminium alloy castings creep ageing heat treatment method
CN206701987U (en) * 2017-04-26 2017-12-05 山西晋西精密机械有限责任公司 A kind of cylindrical member finely tunes rounding device
CN107471617A (en) * 2017-08-16 2017-12-15 航天材料及工艺研究所 A kind of composite bay section shape righting tool and straightening method
CN107617654A (en) * 2017-09-11 2018-01-23 洛阳乾中新材料科技有限公司 The bearing calibration of casting circularity and the correcting tool using this method
CN107639151A (en) * 2017-09-18 2018-01-30 上海航天精密机械研究所 A kind of large scale annular element digitlization flexible forming apparatus and method
CN107866491A (en) * 2017-12-06 2018-04-03 哈尔滨工业大学 A kind of aluminium alloy plate class member freezes manufacturing process
CN108118271A (en) * 2017-12-08 2018-06-05 北京星航机电装备有限公司 A kind of allotype aluminum alloy bay section method for controlling heat treatment deformation
CN109112446A (en) * 2018-09-13 2019-01-01 湖北三江航天红阳机电有限公司 Large thin-wall high strength alumin ium alloy bipyramid diamond shape entirety cabin shell precision casting molding method
CN111451380A (en) * 2020-04-08 2020-07-28 上海交通大学 High-temperature alloy double-ring multi-support-plate thin-wall casting accurate thermal shape correcting die and method
CN111674566A (en) * 2020-05-25 2020-09-18 哈尔滨工业大学 Adjustable inner support restraining device for controlling roundness of cabin section component

Non-Patent Citations (8)

* Cited by examiner, † Cited by third party
Title
《钣金技术》编写组: "《工人普及读物 钣金技术》", vol. 1, 30 April 1974, 国防工业出版社, pages: 232 - 233 *
吴诗惇主编: "《冲压工艺及模具设计》", vol. 1, 31 January 2002, 西北工业大学出版社, pages: 23 *
宋洋: "网状Ti5Si3/TiAl基复合材料热变形与蠕变行为研究", 《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅰ辑》 *
宋洋: "网状Ti5Si3/TiAl基复合材料热变形与蠕变行为研究", 《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅰ辑》, no. 2, 15 February 2018 (2018-02-15), pages 19 - 20 *
徐建军;王伟;杨吟飞;史春玲;陶杰;: "Ti6Al4V钛合金薄壁件热校形试验研究", 组合机床与自动化加工技术, no. 10 *
王清运: "大型舱段校正机构设计与仿真分析", 《机械设计》 *
王清运: "大型舱段校正机构设计与仿真分析", 《机械设计》, vol. 36, no. 11, 30 November 2019 (2019-11-30), pages 25 - 31 *
蒋庄德等主编: "《西安交通大学本科"十三五"规划教材 普通高等教育机械类专业"十三五"规划教材 机械精度设计基础》", vol. 1, 31 August 2017, 西安交通大学出版社, pages: 175 - 177 *

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