CN102581211B - Cold forming method for integral aluminum alloy pull rod of aircraft - Google Patents
Cold forming method for integral aluminum alloy pull rod of aircraft Download PDFInfo
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- CN102581211B CN102581211B CN201210023448.6A CN201210023448A CN102581211B CN 102581211 B CN102581211 B CN 102581211B CN 201210023448 A CN201210023448 A CN 201210023448A CN 102581211 B CN102581211 B CN 102581211B
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Abstract
The invention belongs to cold forming technology, and relates to an improved method for machining an integral aluminum alloy pull rod of an aircraft. The method is characterized in that cold forming includes the steps: selecting pipe specifications; feeding; forming a thin-wall section (1); removing allowance; and forming a transitional section (2) and a thickening a necking section (3). By the aid of the cold forming method for the integral aluminum alloy pull rod of the aircraft, process steps are simplified, the problem of high-precision control is avoided, the strength and the corrosion resistance of the aluminum alloy pull rod are improved, dimensional accuracy and coaxial accuracy of a formed part are ensured, the quality of the aluminum alloy pull rod is stabilized, and product qualification rate and machining efficiency are increased.
Description
Technical field
The invention belongs to cold forming technology, relate to the improvement to airborne vehicle integral aluminum alloy pull bar processing method.
Prior art
The integral aluminum alloy pull bar that advanced airborne vehicle adopts is referring to Fig. 1, the wall ratio two ends of middle thin segment 1 to thicken reducing section 3 thin, the conventional manufacturing process of large wall thickness structure that two ends thicken reducing section 3 to be needed is difficult to realization.Current manufacturing process is: adopt first heat to thicken, the thermoforming process method of pyrocondensation mouth completes shaping again.Hot forming is very accurate to the temperature control requirement in part forming district, and the too low shaping form that will cause of temperature is not in place; Overheated, burning that excess Temperature will cause, the intensity, plasticity that makes aluminium alloy especially toughness significantly reduces.And naturally cooling after heating, can make the intensity of aluminium alloy and corrosion stability reduce.In addition, after shaping, the dimensional accuracy of part and coaxial precision are all very low, and often appearance such as diameter of bore, reducing section axial length and pull bar total length equidimension is overproof, causes part quality unstable, and part qualification rate and working (machining) efficiency are very low.
Summary of the invention
The object of the invention is: propose a kind of airborne vehicle integral aluminum alloy pull bar cold forming processing method, to simplify processing step, improve intensity and the corrosion stability of aluminum alloy pull rod, ensure dimensional accuracy and the coaxial precision of part after being shaped, stablize the quality of aluminum alloy pull rod, improve product percent of pass and working (machining) efficiency.
Technical scheme of the present invention is: cold forming method for integral aluminum alloy pull rod of aircraft, the aluminum alloy pull rod of formed thereby is hollow pipe fitting, it is made up of with the changeover portion 2 that is connected thin segment 1 and thickens reducing section 3 the reducing section 3 that thickens at middle thin segment 1, two ends; the changeover portion 2 at thin segment 1 two ends and thicken the symmetrical configuration of reducing section 3, and the endoporus that thickens reducing section 3 has internal thread; It is characterized in that, the step of cold forming is as follows:
1, select materials in the tube specification: the aluminium alloy materials in the tube of selecting external diameter and wall thickness to be all greater than thin segment 1 are raw material, form woollen through cutting, the outer diameter D 0 of aluminium alloy materials in the tube is calculated as follows, and unit is mm:
D0＝D+2t0+1.....................................................................(1)
In formula:
D is the external diameter of thin segment 1, and unit is mm;
T0 is the wall thickness of aluminium alloy materials in the tube, and unit is mm;
The wall thickness t0 of aluminium alloy materials in the tube is calculated as follows:
In formula:
T is the wall thickness that thickens reducing section 3, and unit is mm;
D1 is the external diameter that thickens reducing section 3, and unit is mm;
The wall thickness t that thickens reducing section 3 is calculated as follows:
In formula:
D1 is the internal diameter that thickens reducing section 3 internal threads, and unit is mm;
2, blanking: length blanking in accordance with regulations, and by sharp corner deburring chamfering inside and outside pipe termination;
3, shaping thin segment 1: shape thin segment 1 by swaging, woollen is clamped in and on feed mechanism, is first delivered to after Working position with the feeding of 800mm/min speed, in woollen, be inserted with plug, utilize attenuate to swage mould to the attenuation of swaging of the middle part of woollen, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, makes external diameter, wall thickness and the length of the middle part of woollen reach the dimensions that drawing specifies;
4, go surplus: excision two ends process allowance, makes woollen total length consistent with part total length;
5, shaping changeover portion 2 and thicken reducing section 3: first carry out the reducing that thickens of woollen one end: woollen is clamped on feed mechanism and with the feeding of 500mm/min speed, utilize reducing to swage mould to the reducing of swaging of part one end, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, make one end of woollen form changeover portion 2 and thicken reducing section 3, ensure changeover portion 2 and the dimensional requirement that thickens reducing section 3; After reducing, excision thickens the surplus of reducing section 3; Then, carry out according to the method described above the reducing that thickens of the woollen other end.
Advantage of the present invention is: proposed a kind of airborne vehicle integral aluminum alloy pull bar cold forming processing method, simplify processing step, avoid a difficult problem for high accuracy control problem, intensity and the corrosion stability of aluminum alloy pull rod are improved, dimensional accuracy and the coaxial precision of part after being shaped are ensured, stablize the quality of aluminum alloy pull rod, improved product percent of pass and working (machining) efficiency.
Brief description of the drawings
Fig. 1 is a kind of structural representation of integral aluminum alloy pull bar of existing airborne vehicle employing.
Detailed description of the invention
Below the present invention is described in further details.Cold forming method for integral aluminum alloy pull rod of aircraft, the aluminum alloy pull rod of formed thereby is hollow pipe fitting, it is made up of with the changeover portion 2 that is connected thin segment 1 and thickens reducing section 3 the reducing section 3 that thickens at middle thin segment 1, two ends; the changeover portion 2 at thin segment 1 two ends and thicken the symmetrical configuration of reducing section 3, and the endoporus that thickens reducing section 3 has internal thread; It is characterized in that, the step of cold forming is as follows:
1, select materials in the tube specification: the aluminium alloy materials in the tube of selecting external diameter and wall thickness to be all greater than thin segment 1 are raw material, form woollen through cutting, the outer diameter D 0 of aluminium alloy materials in the tube is calculated as follows, and unit is mm:
D0＝D+2t0+1..........................................................................(1)
In formula:
D is the external diameter of thin segment 1, and unit is mm;
T0 is the wall thickness of aluminium alloy materials in the tube, and unit is mm;
The wall thickness t0 of aluminium alloy materials in the tube is calculated as follows:
In formula:
T is the wall thickness that thickens reducing section 3, and unit is mm;
D1 is the external diameter that thickens reducing section 3, and unit is mm;
The wall thickness t that thickens reducing section 3 is calculated as follows:
In formula:
D1 is the internal diameter that thickens reducing section 3 internal threads, and unit is mm;
2, blanking: length blanking in accordance with regulations, and by sharp corner deburring chamfering inside and outside pipe termination;
3, shaping thin segment 1: shape thin segment 1 by swaging, woollen is clamped in and on feed mechanism, is first delivered to after Working position with the feeding of 800mm/min speed, in woollen, be inserted with plug, utilize attenuate to swage mould to the attenuation of swaging of the middle part of woollen, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, makes external diameter, wall thickness and the length of the middle part of woollen reach the dimensions that drawing specifies;
4, go surplus: excision two ends process allowance, woollen total length is consistent with part total length;
5, shaping changeover portion 2 and thicken reducing section 3: first carry out the reducing that thickens of woollen one end: woollen is clamped on feed mechanism and with the feeding of 500mm/min speed, utilize reducing to swage mould to the reducing of swaging of part one end, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, make one end of woollen form changeover portion 2 and thicken reducing section 3, ensure changeover portion 2 and the dimensional requirement that thickens reducing section 3; After reducing, excision thickens the surplus of reducing section 3; Then, carry out according to the method described above the reducing that thickens of the woollen other end.
Embodiment 1
In the manufacture of A type helicopter control system integral aluminum alloy pull bar, apply the present invention.
Accessory size: D=28mm, t=1mm, D1=14mm, d1=8mm, overall length L=1085mm, thickens reducing segment length l=18mm
Part material: 2017A-O
Implementation step:
1, select materials in the tube specification: by the analysis to part pattern, select rational specifications of raw materials, not the aluminium alloy pipe consistent with part middle part external diameter, wall thickness that adopts thermoforming process to adopt, but adopt compared with part middle part external diameter, aluminium alloy pipe that wall thickness is larger.Former G28 × 1mm the tubing for thermoforming of certain part, existing cold formability G32 × 2mm tubing.
2, blanking: press MAT'L specification and check pipe, then length blanking in accordance with regulations, and deburring inside and outside pipe termination, outer surface are fallen to R2.
3, shaping thin segment 1: shape thin segment 1 by swaging, woollen is clamped in and on feed mechanism, is first delivered to after Working position with the feeding of 800mm/min speed, in woollen, be inserted with plug, utilize attenuate to swage mould to the attenuation of swaging of the middle part of woollen, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, makes the external diameter of the middle part of woollen reach 28mm, wall thickness reaches 1mm, and length reaches 916mm.
4, go surplus: excision two ends process allowance, woollen total length is 1085mm.
5, shaping changeover portion 2 and thicken reducing section 3: first carry out the reducing that thickens of woollen one end: woollen is clamped on feed mechanism and with the feeding of 500mm/min speed, utilize reducing to swage mould to the reducing of swaging of part one end, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, make one end of woollen form changeover portion 2 and thicken reducing section 3, ensure changeover portion 2 and the dimensional requirement that thickens reducing section 3, thicken reducing section external diameter and reach 14mm, wall thickness reaches 3mm; After reducing, excision thickens the surplus of reducing section 3, ensures to thicken reducing segment length l=18mm; That then, carries out according to the method described above the woollen other end thickens reducing and excision remainder punching.
Embodiment 2
In the manufacture of Type B helicopter control system integral aluminum alloy pull bar, apply the present invention.
Accessory size: D=25mm, t=1mm, D1=15.5mm, d1=8mm, overall length L=579mm, thickens reducing segment length l=18mm
Part material: 2017A-O
Implementation step:
1, select materials in the tube specification: by the analysis to part pattern, select rational specifications of raw materials, adopted G30 × 2.8mm tubing.
2, blanking: press MAT'L specification and check pipe, then length blanking in accordance with regulations, and deburring inside and outside pipe termination, outer surface are fallen to R2.
3, shaping thin segment 1: shape thin segment 1 by swaging, woollen is clamped in and on feed mechanism, is first delivered to after Working position with the feeding of 800mm/min speed, in woollen, be inserted with plug, utilize attenuate to swage mould to the attenuation of swaging of the middle part of woollen, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, makes the external diameter of the middle part of woollen reach 25mm, wall thickness reaches 1mm, and length reaches 452.5mm.
4, go surplus: excision two ends process allowance, woollen total length is 579mm.
5, shaping changeover portion 2 and thicken reducing section 3: first carry out the reducing that thickens of woollen one end: woollen is clamped on feed mechanism and with the feeding of 500mm/min speed, utilize reducing to swage mould to the reducing of swaging of part one end, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, make one end of woollen form changeover portion 2 and thicken reducing section 3, ensure changeover portion 2 and the dimensional requirement that thickens reducing section 3, thicken reducing section external diameter and reach 15.5mm, wall thickness reaches 3.8mm; After reducing, excision thickens the surplus of reducing section 3, ensures to thicken reducing segment length l=18mm; That then, carries out according to the method described above the woollen other end thickens reducing and excision remainder punching.
Embodiment 3
In the manufacture of C type helicopter control system integral aluminum alloy pull bar, apply the present invention.
Accessory size: D=32mm, t=2.5mm, D1=20mm, d1=12mm, overall length L=237mm, thickens reducing segment length l=18mm
Part material: 2A12-O
Implementation step:
1, select materials in the tube specification: by the analysis to part pattern, select rational specifications of raw materials, adopted G35 × 3.5mm tubing.
2, blanking: press MAT'L specification and check pipe, then length blanking in accordance with regulations, and deburring inside and outside pipe termination, outer surface are fallen to R2.
3, shaping thin segment 1: shape thin segment 1 by swaging, woollen is clamped in and on feed mechanism, delivers to Working position, in woollen, be inserted with plug, utilize attenuate to swage mould to the attenuation of swaging of the middle part of woollen, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, makes the external diameter of the middle part of woollen reach 32mm, wall thickness reaches 2.5mm, and length reaches 86.7mm.
4, go surplus: excision two ends process allowance, woollen total length is 237mm.
5, shaping changeover portion 2 and thicken reducing section 3: first carry out the reducing that thickens of woollen one end: woollen is clamped on feed mechanism and with the feeding of 500mm/min speed, utilize reducing to swage mould to the reducing of swaging of part one end, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, make one end of woollen form changeover portion 2 and thicken reducing section 3, ensure changeover portion 2 and the dimensional requirement that thickens reducing section 3, thicken reducing section external diameter and reach 20mm, wall thickness reaches 4.6mm; After reducing, excision thickens the surplus of reducing section 3, ensures to thicken reducing segment length l=18mm; That then, carries out according to the method described above the woollen other end thickens reducing and excision remainder punching.
Claims (1)
1. cold forming method for integral aluminum alloy pull rod of aircraft, the aluminum alloy pull rod of formed thereby is hollow pipe fitting, it is made up of with the changeover portion [2] that is connected thin segment [1] and thickens reducing section [3] the reducing section [3] that thickens at middle thin segment [1], two ends; the changeover portion [2] at thin segment [1] two ends and thicken the symmetrical configuration of reducing section [3], and the endoporus that thickens reducing section [3] has internal thread; It is characterized in that, the step of cold forming is as follows:
1.1, select materials in the tube specification: the aluminium alloy materials in the tube of selecting external diameter and wall thickness to be all greater than thin segment [1] are raw material, form woollen through cutting, the outer diameter D 0 of aluminium alloy materials in the tube is calculated as follows, and unit is mm:
D0＝D+2t0+1........................................................................(1)
In formula:
D is the external diameter of thin segment [1], and unit is mm;
T0 is the wall thickness of aluminium alloy materials in the tube, and unit is mm;
The wall thickness t0 of aluminium alloy materials in the tube is calculated as follows:
In formula:
T is for thickening the wall thickness of reducing section [3], and unit is mm;
D1 is for thickening the external diameter of reducing section [3], and unit is mm;
The wall thickness t that thickens reducing section [3] is calculated as follows:
In formula:
D1 is for thickening the internal diameter of reducing section [3] internal thread, and unit is mm;
1.2, blanking: length blanking in accordance with regulations, and by sharp corner deburring chamfering inside and outside pipe termination;
1.3, shaping thin segment [1]: shape thin segment [1] by swaging, woollen is clamped in and on feed mechanism, is first delivered to after Working position with the feeding of 800mm/min speed, in woollen, be inserted with plug, utilize attenuate to swage mould to the attenuation of swaging of the middle part of woollen, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, makes external diameter, wall thickness and the length of the middle part of woollen reach the dimensions that drawing specifies;
1.4, go surplus: excision two ends process allowance, makes woollen total length consistent with part total length;
1.5, shaping changeover portion [2] and thicken reducing section [3]: first carry out the reducing that thickens of woollen one end: woollen is clamped on feed mechanism and with the feeding of 500mm/min speed, utilize reducing to swage mould to the reducing of swaging of part one end, speed of mainshaft 120r/min, outer shroud rotating speed 260r/min, make one end of woollen form changeover portion [2] and thicken reducing section [3], guarantee changeover portion [2] and thicken the dimensional requirement of reducing section [3]; After reducing, excision thickens the surplus of reducing section [3]; Then, carry out according to the method described above the reducing that thickens of the woollen other end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210023448.6A CN102581211B (en) | 2012-02-02 | 2012-02-02 | Cold forming method for integral aluminum alloy pull rod of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210023448.6A CN102581211B (en) | 2012-02-02 | 2012-02-02 | Cold forming method for integral aluminum alloy pull rod of aircraft |
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| Publication Number | Publication Date |
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| CN102581211A CN102581211A (en) | 2012-07-18 |
| CN102581211B true CN102581211B (en) | 2014-08-06 |
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| CN201210023448.6A Expired - Fee Related CN102581211B (en) | 2012-02-02 | 2012-02-02 | Cold forming method for integral aluminum alloy pull rod of aircraft |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103192985B (en) * | 2012-01-10 | 2016-01-06 | 江苏希西维轴承有限公司 | Aircraft Novel integral structure pull bar |
| CN104493035A (en) * | 2014-11-24 | 2015-04-08 | 西安创新精密仪器研究所 | Rotary swaging method for processing pull rods |
| CN105710266B (en) * | 2016-04-06 | 2017-07-25 | 乐清市弘德金属有限公司 | Electric hammer drill cold-heading part moulding process |
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| DE4430068A1 (en) * | 1994-08-30 | 1996-03-07 | Plettac Ag | Process for manufacturing scaffolding tubes |
| CN1672827A (en) * | 2004-03-22 | 2005-09-28 | 乔治·A·米切尔公司 | Method for producing metal ball bar |
| CN1684783A (en) * | 2002-09-26 | 2005-10-19 | 费尔斯有限公司 | Method and device for the production of a tubular workpiece, particularly a shock absorber piston rod, and such a workpiece |
| CN101060942A (en) * | 2004-11-20 | 2007-10-24 | Gkn动力传动国际有限公司 | Reduction of tubes by means of a graduated mandrel for producing tubular shafts with an undercut in an operation |
| CN101176905A (en) * | 2003-12-22 | 2008-05-14 | 本田技研工业株式会社 | Method of forming member,valve guide and method of forming the same and method of forming tubular member |
| CN101389921A (en) * | 2006-02-23 | 2009-03-18 | 斯特姆鲁格公司 | Composite firearm barrels |
-
2012
- 2012-02-02 CN CN201210023448.6A patent/CN102581211B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4430068A1 (en) * | 1994-08-30 | 1996-03-07 | Plettac Ag | Process for manufacturing scaffolding tubes |
| CN1684783A (en) * | 2002-09-26 | 2005-10-19 | 费尔斯有限公司 | Method and device for the production of a tubular workpiece, particularly a shock absorber piston rod, and such a workpiece |
| CN101176905A (en) * | 2003-12-22 | 2008-05-14 | 本田技研工业株式会社 | Method of forming member,valve guide and method of forming the same and method of forming tubular member |
| CN1672827A (en) * | 2004-03-22 | 2005-09-28 | 乔治·A·米切尔公司 | Method for producing metal ball bar |
| CN101060942A (en) * | 2004-11-20 | 2007-10-24 | Gkn动力传动国际有限公司 | Reduction of tubes by means of a graduated mandrel for producing tubular shafts with an undercut in an operation |
| CN101389921A (en) * | 2006-02-23 | 2009-03-18 | 斯特姆鲁格公司 | Composite firearm barrels |
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