CN103272908A - Stretch forming method for titanium skin part - Google Patents
Stretch forming method for titanium skin part Download PDFInfo
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- CN103272908A CN103272908A CN2013102329697A CN201310232969A CN103272908A CN 103272908 A CN103272908 A CN 103272908A CN 2013102329697 A CN2013102329697 A CN 2013102329697A CN 201310232969 A CN201310232969 A CN 201310232969A CN 103272908 A CN103272908 A CN 103272908A
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Abstract
The invention relates to a stretch forming method for a titanium skin part. According to the technical scheme, a titanium skin part blank is placed on a skin stretching machine, aluminum strips are glued at the upper end and the lower end of the titanium skin part blank, and the titanium skin part blank is clamped by jaws of the skin stretching machine through the aluminum strips; and the titanium skin part blank stretched towards two sides is driven by the jaws of the skin stretching machine to achieve a yield strength, and the titanium skin part blank is coated on a stretch die till completely fitting the profile faces of the stretch die. Property of being clamped of the black is improved, slipping when a part is clamped by the jaws of the stretching machine is prevented, pull force on the part is even and stable, qualified parts can be produced successfully, requirements of actual production are guaranteed, and qualified-product rate is high.
Description
Technical field
The present invention relates to the method for stretch forming of aircraft skin, relate to the method for a kind of titanium alloy skin part stretch forming particularly.
Background technology
On the airframe, as shown in Figure 1, it is the aircraft skin part of titanium alloy hyperbolic degree that six prong materials are arranged, and size is about δ 0.8 * 1200 * 600.According to original process technology, part blank directly is placed in the jaw of stretching-machine, by jaw blank is applied pulling force, make blank produce non-homogeneous stress and elongation strain, blank and pull-shaped mould binding face are expanded gradually thereupon, until fitting fully with pull-shaped model face.In actual production process, find that titanium alloy component exists the back springback capacity that is shaped big, problem such as can't repair by hand, therefore after these six aircraft skin part processing were shaped, all there were phenomenons such as in various degree wave, distortion in the surface, and the part of gross distortion need be scrapped new system, the residue part can only be paid according to defective work, so both delay the part production cycle, reduced the service life of part again, thereby cause the flight time of normal aircraft to reduce.
Summary of the invention
In order to solve hyperbolic degree titanium alloy skin part, the problem that springback capacity is big after stretch forming, wave, twisted phenomena appear in piece surface the invention provides a kind of method that improves the titanium alloy skin part stretch forming of product percent of pass.
To achieve these goals, the technical solution used in the present invention is: the method for a kind of titanium alloy skin part stretch forming, step is as follows: titanium alloy skin part blank is placed on the covering stretching-machine, with the end of titanium alloy skin part blank each glued aluminum strip up and down, covering stretching-machine jaw is by aluminum strip clamping titanium alloy skin part blank; The covering stretching-machine drives titanium alloy skin part blank by jaw and is stretched to yield strength to both sides, titanium alloy skin part blank is coated on the pull-shaped mould, until fitting fully with pull-shaped model face.Preferably, the process allowance of 80mm and each glued aluminum strip of upper and lower surface are herein respectively strengthened in the end of titanium alloy skin part blank.
The titanium alloy skin part is in skin stretch forming field ubiquity shaping difficulty, the bad problem of surface quality.In a large amount of tension tests, carried out surveying record for the A of as shown in Figure 1 hyperbolic degree titanium alloy skin part, the percentage elongation in B zone, as shown in table 1, through data are analyzed, assert that material is bigger in longitudinal strain and the edge longitudinal strain numerical difference between distance of middle part, is to cause part to play the inside principal element of wave.The external factor that causes this phenomenon is studied, think that influencing the factor of material deformation is that titanium alloy component hardness is bigger, skid during stretching-machine jaw clamping part forming, cause the inhomogeneous result of tensile force, therefore the present invention has designed, respectively strengthen the process allowance of 80mm at the two ends of titanium alloy component blank, and each glued aluminum strip of upper and lower surface herein.
Table 1
| ? | A-quadrant percentage elongation % | B zone percentage elongation % | A, B zone percentage elongation ratio | Part quality |
| |
3 | 2.3 | 1.3 | Better |
| Second part | 2.8 | 2.2 | 1.27 | Better |
| The 3rd part | 2.8 | 2.3 | 1.22 | Better |
| The 4th part | 2.8 | 1.6 | 1.75 | Bad |
| The 5th part | 2.7 | 1.6 | 1.69 | Bad |
| The 6th part | 2.9 | 1.7 | 1.7 | Bad |
The invention has the beneficial effects as follows: by respectively strengthen the process allowance of 80mm at the two ends of titanium alloy skin part blank, and each glued aluminum strip of upper and lower surface herein, stretching-machine has increased frictional force by the softer aluminum strip of clamping, improved the clamping of blank, prevent the phenomenon that stretching-machine jaw clamping part skids, the tension uniform that part is subjected to is steady, successfully produces up-to-standard part, guaranteed demand of practical production, the qualification rate of product can reach more than 90%.
Description of drawings
Fig. 1 is the structural representation of hyperbolic degree titanium alloy skin part.
Fig. 2 is the form schematic diagram of glued aluminum strip and the clamping of stretching-machine jaw.
The specific embodiment
The method of 1 one kinds of titanium alloy skin parts of embodiment stretch forming
1) titanium alloy skin part blank (2) is placed in the centre position of covering stretching-machine workbench, to guarantee that in the stretch forming process, tensile force can reach the technical parameter requirement;
2) jaw (1) relatively preferably is transferred to the stretching-machine centre position, the chucking power of stretching-machine is even when being conducive to processing parts;
The process allowance of 80mm is respectively strengthened in the end of titanium alloy skin part blank (2), and each glued aluminum strip (3) of upper and lower surface herein, covering stretching-machine jaw (1) is by aluminum strip clamping titanium alloy skin part blank; The covering stretching-machine drives titanium alloy skin part blank by jaw and is stretched to yield strength to both sides, titanium alloy skin part blank is coated on the pull-shaped mould, until fitting fully with pull-shaped model face.
Claims (2)
1. the method for titanium alloy skin part stretch forming, it is characterized in that step is as follows: titanium alloy skin part blank (2) is placed on the covering stretching-machine, with the end of titanium alloy skin part blank each glued aluminum strip (3) up and down, covering stretching-machine jaw (1) is by aluminum strip clamping titanium alloy skin part blank; The covering stretching-machine drives titanium alloy skin part blank by jaw and is stretched to yield strength to both sides, titanium alloy skin part blank is coated on the pull-shaped mould, until fitting fully with pull-shaped model face.
2. the method for a kind of titanium alloy skin part as claimed in claim 1 stretch forming is characterized in that: the process allowance of 80mm and each glued aluminum strip of upper and lower surface are herein respectively strengthened in the end of titanium alloy skin part blank.
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| CN2013102329697A CN103272908A (en) | 2013-06-13 | 2013-06-13 | Stretch forming method for titanium skin part |
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| CN2013102329697A CN103272908A (en) | 2013-06-13 | 2013-06-13 | Stretch forming method for titanium skin part |
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| CN103272908A true CN103272908A (en) | 2013-09-04 |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103801609A (en) * | 2014-03-03 | 2014-05-21 | 沈阳飞机工业（集团）有限公司 | Stretch-bending forming method for aircraft skin part |
| CN104014999A (en) * | 2014-06-12 | 2014-09-03 | 沈阳飞机工业（集团）有限公司 | Aluminum alloy skin stretching forming method |
| CN104443426A (en) * | 2014-10-08 | 2015-03-25 | 中国航空工业集团公司北京航空制造工程研究所 | Aircraft titanium alloy frame beam type part manufacturing method |
| CN104492899A (en) * | 2014-07-31 | 2015-04-08 | 贵州航天风华精密设备有限公司 | Stretching process for novel high-strength corrosion-resistant aluminum alloy |
| CN104971975A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Skin forming technology combining stretching and stamping |
| CN105479119A (en) * | 2016-01-06 | 2016-04-13 | 天津航天长征火箭制造有限公司 | Forming process of 5M-grade storage tank spherical melon petal |
| CN105618544A (en) * | 2014-10-28 | 2016-06-01 | 哈尔滨飞机工业集团有限责任公司 | Stretch forming technical method for high-temperature alloy materials |
| CN106311851A (en) * | 2016-10-19 | 2017-01-11 | 中航飞机股份有限公司西安飞机分公司 | Overcoming method for drawing defects of large length-width ratio flat tube part |
| CN106623576A (en) * | 2016-12-28 | 2017-05-10 | 西南铝业（集团）有限责任公司 | Double-sided gear block, stretcher jaw antiskid structure and stretching process |
| CN107470433A (en) * | 2017-07-04 | 2017-12-15 | 西安飞机工业（集团）有限责任公司 | A kind of method of stretch forming of curved surface aircraft skin part |
| CN110695180A (en) * | 2019-10-08 | 2020-01-17 | 江西洪都航空工业集团有限责任公司 | Large aircraft skin blank structure and skin stretch forming method |
| CN110936109A (en) * | 2019-11-22 | 2020-03-31 | 西安飞机工业（集团）有限责任公司 | Large-size titanium alloy skin composite forming method |
| CN114193352A (en) * | 2021-11-19 | 2022-03-18 | 北京星航机电装备有限公司 | Elastic tensioning tool for weak-rigidity skin parts |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103801609A (en) * | 2014-03-03 | 2014-05-21 | 沈阳飞机工业（集团）有限公司 | Stretch-bending forming method for aircraft skin part |
| CN104014999A (en) * | 2014-06-12 | 2014-09-03 | 沈阳飞机工业（集团）有限公司 | Aluminum alloy skin stretching forming method |
| CN104014999B (en) * | 2014-06-12 | 2016-11-23 | 沈阳飞机工业（集团）有限公司 | A kind of aluminum alloy outer cover stretch forming method |
| CN104492899A (en) * | 2014-07-31 | 2015-04-08 | 贵州航天风华精密设备有限公司 | Stretching process for novel high-strength corrosion-resistant aluminum alloy |
| CN104443426B (en) * | 2014-10-08 | 2016-06-08 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of Titanium Alloy Aircraft frame beam-like part manufacture method |
| CN104443426A (en) * | 2014-10-08 | 2015-03-25 | 中国航空工业集团公司北京航空制造工程研究所 | Aircraft titanium alloy frame beam type part manufacturing method |
| CN105618544A (en) * | 2014-10-28 | 2016-06-01 | 哈尔滨飞机工业集团有限责任公司 | Stretch forming technical method for high-temperature alloy materials |
| CN104971975A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Skin forming technology combining stretching and stamping |
| CN104971975B (en) * | 2015-07-15 | 2017-07-21 | 江西洪都航空工业集团有限责任公司 | It is a kind of to stretch the covering forming technology being combined with punching press |
| CN105479119A (en) * | 2016-01-06 | 2016-04-13 | 天津航天长征火箭制造有限公司 | Forming process of 5M-grade storage tank spherical melon petal |
| CN106311851A (en) * | 2016-10-19 | 2017-01-11 | 中航飞机股份有限公司西安飞机分公司 | Overcoming method for drawing defects of large length-width ratio flat tube part |
| CN106311851B (en) * | 2016-10-19 | 2018-11-16 | 中航飞机股份有限公司西安飞机分公司 | A kind of aspect is than half flat tube part drawing defect conquering method |
| CN106623576A (en) * | 2016-12-28 | 2017-05-10 | 西南铝业（集团）有限责任公司 | Double-sided gear block, stretcher jaw antiskid structure and stretching process |
| CN106623576B (en) * | 2016-12-28 | 2018-10-16 | 西南铝业（集团）有限责任公司 | Stretcher jaw anti-skid structure and drawing process |
| CN107470433A (en) * | 2017-07-04 | 2017-12-15 | 西安飞机工业（集团）有限责任公司 | A kind of method of stretch forming of curved surface aircraft skin part |
| CN110695180A (en) * | 2019-10-08 | 2020-01-17 | 江西洪都航空工业集团有限责任公司 | Large aircraft skin blank structure and skin stretch forming method |
| CN110936109A (en) * | 2019-11-22 | 2020-03-31 | 西安飞机工业（集团）有限责任公司 | Large-size titanium alloy skin composite forming method |
| CN114193352A (en) * | 2021-11-19 | 2022-03-18 | 北京星航机电装备有限公司 | Elastic tensioning tool for weak-rigidity skin parts |
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Application publication date: 20130904 |