CN105563014A - Combined manufacturing method for large-scale integrated metal structure part - Google Patents
Combined manufacturing method for large-scale integrated metal structure part Download PDFInfo
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- CN105563014A CN105563014A CN201410535725.0A CN201410535725A CN105563014A CN 105563014 A CN105563014 A CN 105563014A CN 201410535725 A CN201410535725 A CN 201410535725A CN 105563014 A CN105563014 A CN 105563014A
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- forging
- metal structure
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- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Abstract
The invention aims to provide a manufacturing method for a large-scale metal structure part. By adopting the method, the defects of a traditional manufacturing technology are overcome and the shortage of large-size materials and large-tonnage equipment is covered so that the manufacturing problem of the large-scale integrated metal structure of a plane can be solved and meanwhile the design requirements of the plane can be met. According to the method, the step-by-step forging technology and the laser rapid prototyping technology are combined, the advantages of the two technologies can be brought into full play, and hence the manufacturing method of the large-scale metal structure part can be obtained. The method specifically comprises the steps that the integrated metal structure part is divided into two parts manufactured through the step-by-step forging technology and the laser rapid prototyping technology, step-by-step forging is adopted for the body part, the laser rapid prototyping technology is adopted for the other parts, and the integrated structure part meeting the design requirements can be obtained ultimately.
Description
Technical field
The invention belongs to aircraft manufacturing technical field, relate to a kind of combination manufacturing method of band large-scale metal integral structure component.
Background technology
Along with the development of Aerobiz and the progress of technology, adopt metallic monoliths to become a kind of trend, especially for large aircraft, overall structure to raising Aircraft life, alleviate construction weight there is remarkable benefit.Metal material overall structure many employings forging manufactures.At present, it is domestic that to obtain by conventional FMT the large-scale integral structure met design requirement very difficult, mainly forging equipment, Forging Technology and raw material are had higher requirement, namely require that specifications of raw materials is larger, forging equipment has enough forging abilities, controls harsher to Forging Technology.
Summary of the invention
The object of the invention is to: the manufacture method that the object of the invention is to propose a kind of band large-scale metal structural member, it can overcome the drawback of traditional manufacturing technology, make up the deficiency of large gauge material and large-tonnage equipment, to solve the integrally-built manufacturing issue of aircraft band large-scale metal, meet airplane design requirement simultaneously.
Technical scheme of the present invention is: a kind of combination manufacturing method of band large-scale metal integral structure component, comprises the following steps:
(1) raw material of the same trade mark are chosen: flat-die forging bar, laser fast forming powder material;
(2) metallic monoliths part is divided into ear portion and entity part in addition, for entity part, according to specification and capacity of equipment, design substep open die forgings figure, is divided into some parts by its forging, the forging of substep piecemeal;
(3) roughing is carried out to substep open die forgings, obtain the matrix surface can implementing laser fast forming;
(4) adopt laser fast forming manufacture technics auricle position, dusty material is successively piled up by the method especially by laser melting coating, obtains the nearly body containing auricle;
(5) carry out machining by detail drawing size, remove two-part excess stock;
(6) heat-treat and surface treatment by detail drawing requirement, complete part manufacture.
The invention has the beneficial effects as follows:
Substep Forging Technology and laser fast forming technique combine by the present invention, play the respective advantage of two kinds of techniques, realize the manufacture method of band large-scale metal structural member.Tool has the following advantages: 1, reduce manufacturing cost 2, shorten the process-cycle 3, improve stock utilization 4, without the need to mould.
Detailed description of the invention
Below the present invention is described in further details.Embodiment selects a kind of Typical Aircraft structure (the sheet frame class part of large-scale band auricle boss), conventional flat-die forging technique is adopted if simple, need forging can contain the entity part of whole part, for such open die forgings, there is following problem: one is need to increase to specifications of raw materials; Two is need forging equipment tonnage to increase, and forging thickness is large, and flat-die forging distortion is insufficient, cannot ensure forging performance; Three is forged rear needs to carry out a large amount of going material machining.From above, adopt conventional FMT to manufacture entity, not only high to raw material, equipment requirement, and raw material, forging and machine to add expense all very large, the process-cycle is long.Adopt the manufacture method that the present invention proposes, key step is as follows:
(1) raw material of the same trade mark are chosen: flat-die forging bar, laser fast forming powder material;
(2) metallic monoliths part is divided into ear portion and entity part in addition, for entity part, according to specification and capacity of equipment, design substep open die forgings figure, is divided into some parts by its forging, the forging of substep piecemeal;
(3) roughing is carried out to substep open die forgings, obtain the matrix surface can implementing laser fast forming;
(4) adopt laser fast forming manufacture technics auricle position, dusty material is successively piled up by the method especially by laser melting coating, obtains the nearly body containing auricle;
(5) carry out machining by detail drawing size, remove two-part excess stock;
(6) heat-treat and surface treatment by detail drawing requirement, complete part manufacture.
Claims (1)
1. a combination manufacturing method for band large-scale metal integral structure component, comprises the following steps:
(1) raw material of the same trade mark are chosen: flat-die forging bar, laser fast forming powder material;
(2) metallic monoliths part is divided into ear portion and entity part in addition, for entity part, according to specification and capacity of equipment, design substep open die forgings figure, is divided into some parts by its forging, the forging of substep piecemeal;
(3) roughing is carried out to substep open die forgings, obtain the matrix surface can implementing laser fast forming;
(4) adopt laser fast forming manufacture technics auricle position, dusty material is successively piled up by the method especially by laser melting coating, obtains the nearly body containing auricle;
(5) carry out machining by detail drawing size, remove two-part excess stock;
(6) heat-treat and surface treatment by detail drawing requirement, complete part manufacture.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535725.0A CN105563014A (en) | 2014-10-11 | 2014-10-11 | Combined manufacturing method for large-scale integrated metal structure part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535725.0A CN105563014A (en) | 2014-10-11 | 2014-10-11 | Combined manufacturing method for large-scale integrated metal structure part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105563014A true CN105563014A (en) | 2016-05-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410535725.0A Pending CN105563014A (en) | 2014-10-11 | 2014-10-11 | Combined manufacturing method for large-scale integrated metal structure part |
Country Status (1)
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106513679A (en) * | 2016-11-30 | 2017-03-22 | 沈阳航空航天大学 | Laser additive manufacturing method applied to large-sized metal part |
| CN108296715A (en) * | 2018-01-30 | 2018-07-20 | 华中科技大学 | A method of using forging and increasing material manufacturing combined shaping metal large-scale component |
| CN109128169A (en) * | 2018-10-16 | 2019-01-04 | 北京锐海三维科技有限公司 | A kind of large size high-performance metal part Direct Laser Fabrication Technology |
| CN111390082A (en) * | 2020-03-19 | 2020-07-10 | 燕山大学 | Device and process for forging medium plate blank |
| CN111761058A (en) * | 2020-05-25 | 2020-10-13 | 沈阳精合数控科技开发有限公司 | Sectional forming method and system for laser deposition manufacturing technology and terminal equipment |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030145466A1 (en) * | 2002-02-04 | 2003-08-07 | Jeong-Hoon Baek | Method for manufacturing alloy wheel for automobile |
| CN101658895A (en) * | 2009-03-19 | 2010-03-03 | 无锡透平叶片有限公司 | Local loading forming method of thick plate of TA19 titanium alloy engine case of aero-engine |
| CN102133698A (en) * | 2011-02-17 | 2011-07-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for manufacturing airplane metal integrated structure |
| CN102626849A (en) * | 2012-04-17 | 2012-08-08 | 常熟市旋力轴承钢管有限公司 | Preparation method of roll for punching round steel |
-
2014
- 2014-10-11 CN CN201410535725.0A patent/CN105563014A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030145466A1 (en) * | 2002-02-04 | 2003-08-07 | Jeong-Hoon Baek | Method for manufacturing alloy wheel for automobile |
| CN101658895A (en) * | 2009-03-19 | 2010-03-03 | 无锡透平叶片有限公司 | Local loading forming method of thick plate of TA19 titanium alloy engine case of aero-engine |
| CN102133698A (en) * | 2011-02-17 | 2011-07-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for manufacturing airplane metal integrated structure |
| CN102626849A (en) * | 2012-04-17 | 2012-08-08 | 常熟市旋力轴承钢管有限公司 | Preparation method of roll for punching round steel |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106513679A (en) * | 2016-11-30 | 2017-03-22 | 沈阳航空航天大学 | Laser additive manufacturing method applied to large-sized metal part |
| CN106513679B (en) * | 2016-11-30 | 2018-10-19 | 沈阳航空航天大学 | A kind of laser gain material manufacturing method suitable for band large-scale metal part |
| CN108296715A (en) * | 2018-01-30 | 2018-07-20 | 华中科技大学 | A method of using forging and increasing material manufacturing combined shaping metal large-scale component |
| CN109128169A (en) * | 2018-10-16 | 2019-01-04 | 北京锐海三维科技有限公司 | A kind of large size high-performance metal part Direct Laser Fabrication Technology |
| CN111390082A (en) * | 2020-03-19 | 2020-07-10 | 燕山大学 | Device and process for forging medium plate blank |
| CN111390082B (en) * | 2020-03-19 | 2021-03-16 | 燕山大学 | Device and process for forging medium plate blank |
| CN111761058A (en) * | 2020-05-25 | 2020-10-13 | 沈阳精合数控科技开发有限公司 | Sectional forming method and system for laser deposition manufacturing technology and terminal equipment |
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Application publication date: 20160511 |