CN102862021A - Method for manufacturing rudder assembly of aircraft by laser welding - Google Patents
Method for manufacturing rudder assembly of aircraft by laser welding Download PDFInfo
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- CN102862021A CN102862021A CN2012102946470A CN201210294647A CN102862021A CN 102862021 A CN102862021 A CN 102862021A CN 2012102946470 A CN2012102946470 A CN 2012102946470A CN 201210294647 A CN201210294647 A CN 201210294647A CN 102862021 A CN102862021 A CN 102862021A
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- laser welding
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Abstract
The invention relates to a method for machining a rudder assembly of an aircraft, in particular to a method for manufacturing a rudder assembly of an aircraft by laser welding. The method comprises the following steps of: (1) blanking; (2) machining and forming; (3) performing alkaline degreasing; (4) performing alkali washing; (5) performing acid washing; (6) washing; (7) drying; (8) performing laser welding; and (9) performing fine milling, so that the contour dimension meets the design requirement of the product. By the method, the problem of cracking of resistance roll welding edges of the rudder assembly is solved. The process for the rudder assembly by the laser welding plays an active role in the popularization and application of a laser welding rudder assembly in spacecrafts.
Description
Technical field
The present invention relates to a kind of aircraft rudder module processing method, particularly a kind of manufacture method of aircraft rudder assembly Laser Welding.
Background technology
The structure that aircraft rudder assembly often adopts skeleton 1 to add covering 2 realizes, such as Fig. 1, Fig. 2, shown in Figure 3, manufacture method is to adopt machining process rudder skeleton 1, hot-forming covering 2, then adopt electric resistance welding that covering 2 is welded on the skeleton 1, the mid portion of covering adopts resistance spot welding, and the covering edge adopts resistance seam welding.The rudder assembly that this mode is processed into is in actual hypersonic flight, because the effect of flight resistance, resistance seam welding edge part branch cracking causes the unstable of aircraft flight process.
This shows that above-mentioned existing aircraft rudder assembly still has deficiency, and demands urgently further being improved on manufacture method.
Because the deficiency that the manufacture method of above-mentioned existing aircraft rudder assembly exists, the inventor is based on being engaged in for many years abundant practical experience and professional knowledge of this type of product design manufacturing, and the utilization of cooperation scientific principle, positive research and innovation in addition is in the hope of founding a kind of manufacture method of new aircraft rudder assembly.Through constantly research, design, and after repeatedly studying and improving, finally create the present invention who has practical value.
Summary of the invention
Main purpose of the present invention is, provides a kind of manufacture method of aircraft rudder assembly Laser Welding for the above-mentioned deficiency of prior art, solves the manufacturing process problem of the Laser Welding of rudder assembly.
The object of the invention to solve the technical problems realizes by the following technical solutions.
The manufacture method of a kind of aircraft rudder assembly Laser Welding that proposes according to the present invention may further comprise the steps:
(1) blanking is pressed the blanking of figure paper size with titanium alloy sheet;
(2) covering is hot-forming, the plate thermal forming that 1.0-2.0mm is thick is to drawing requirement, profile is evenly brushed protection alcohol graphite solution, air-dry slightly polish with the 600# fine sandpaper afterwards, adjust the mould upper and lower mould and keep clearance between punch and die 35-50mm, mould is warmed up to 550-750 ℃, adds press-fitting mould, insulation 5-30min;
(3) frame machine add-on type adopts the machine add-on type with sheet material, for ease of the assembling of covering and skeleton, around the inboard of skeleton process for the recessed ledge frame of placing covering;
(4) electrochemical deoiling, degreasing fluid prescription: Na
3PO
412H
2O45-60g/L, Na
2CO
310H
2O:40-50g/L, Na
2SiO
320-35g/L, water surplus; Solution temperature 60-90 ℃, oil removing time 15-20min removes surperficial grease;
(5) alkali cleaning, the prescription of alkali wash water: NaOH500-700g/L, NaNO
2150-250g/L, water surplus; Solution temperature 90-100 ℃, alkali cleaning time 20-120min;
(6) pickling, the prescription of pickle: HNO3(65%-68%), and HF(40%), water surplus, solution temperature 18-45 ℃, pickling time 1-15min removes oxide on surface;
(7) washed with de-ionized water is adopted in washing, oven dry, and temperature 30-60 ℃, ensure sufficient water and flow into rinse bath, should adopt flushing at last wash phase, not contaminated to guarantee piece surface; In being arranged, the drying baker of air blast dries, and bake out temperature 100-150 ℃, time 20-30min;
(8) assembling covers the enterprising luggage of the good skeleton of machined with titanium alloy covering and joins fit-up gap, edge 0.20mm;
(9) Laser Welding, middle skeleton and covering adopt the laser penetration weldering, skeleton edge and covering adopt laser butt welding, laser power: 1.0-2.0KW, focal length 100-120mm, defocusing amount :-0.1mm, speed of welding: 900-1200mm/min, gas flow: He:15-20ml/min, Ar:14-25ml/min.
The object of the invention to solve the technical problems also can be applied to the following technical measures to achieve further.
The manufacture method of aforesaid aircraft rudder assembly Laser Welding, wherein step (3) described around the recessed amount that processes for the step of placing covering of the inboard of skeleton be 0.5mm.
The manufacture method of aforesaid aircraft rudder assembly Laser Welding, wherein the described alkali cleaning time of step (5) is 80-120min.
The manufacture method of aforesaid aircraft rudder assembly Laser Welding, wherein the described solution temperature 30-45 of step (6) ℃, pickling time 5-10min.
The manufacture method of aforesaid aircraft rudder assembly Laser Welding, wherein the trade mark of titanium alloy plate is TC4 or TA3 or TA15.
The present invention specifically provides a kind of manufacture method of spacecraft rudder assembly Laser Welding, has solved the problem of rudder assembly resistance seam welding edge part branch cracking.The technique of rudder assembly laser weld provided by the present invention, Laser Welding rudder assembly is played a positive role applying of spacecraft, and through the fluorescent penetrant inspection, surface and interior welds quality meet the Aero-Space welding standard, the product design requirement can be satisfied, the product design requirement can be satisfied.
Above-mentioned explanation only is the general introduction of technical solution of the present invention, for can clearer understanding technological means of the present invention, and can be implemented according to the content of specification, and for above and other purpose of the present invention, feature and advantage can be become apparent, below especially exemplified by preferred embodiment, and the cooperation accompanying drawing, be described in detail as follows.
Description of drawings
Fig. 1 is the skeleton structure schematic diagram of the present invention's aircraft rudder assembly of constructing.
Fig. 2 is that the A of Fig. 1 is to view.
Fig. 3 is the stressed-skin construction schematic diagram of the present invention's aircraft rudder assembly of constructing.
Fig. 4 is the construction procedure figure of the manufacture method of aircraft rudder assembly Laser Welding of the present invention.
The specific embodiment
See also shown in Figure 4ly, the manufacture method of a kind of aircraft rudder assembly Laser Welding of preferred embodiment of the present invention may further comprise the steps:
A kind of manufacture method of aircraft rudder assembly Laser Welding may further comprise the steps:
(1) blanking is pressed the blanking of figure paper size with titanium alloy sheet;
(2) covering is hot-forming, the plate thermal forming that 1.0-2.0mm is thick is to drawing requirement, profile is evenly brushed protection alcohol graphite solution, air-dry slightly polish with the 600# fine sandpaper afterwards, adjust the mould upper and lower mould and keep clearance between punch and die 35-50mm, mould is warmed up to 550-750 ℃, adds press-fitting mould, insulation 5-30min takes out the moulding covering after the cooling;
(3) frame machine add-on type adopts the machine add-on type with sheet material, mills the up and down symmetrical profile that is processed into as shown in the figure, for ease of the assembling of covering and skeleton, around the inboard of skeleton process for the recessed ledge frame of placing covering;
(4) electrochemical deoiling, degreasing fluid prescription: Na
3PO
412H
2O45-60g/L, Na
2CO
310H
2O:40-50g/L, Na
2SiO
320-35g/L, water surplus; Solution temperature 60-90 ℃, oil removing time 15-20min removes surperficial grease;
(5) alkali cleaning, the prescription of alkali wash water: NaOH500-700g/L, NaNO
2150-250g/L, water surplus; Solution temperature 90-100 ℃, alkali cleaning time 20-120min;
(6) pickling, the prescription of pickle: HNO3(65%-68%), and HF(40%), water surplus, solution temperature 18-45 ℃, pickling time 1-15min removes oxide on surface;
(7) washed with de-ionized water is adopted in washing, oven dry, and temperature 30-60 ℃, ensure sufficient water and flow into rinse bath, should adopt flushing at last wash phase, not contaminated to guarantee piece surface; In being arranged, the drying baker of air blast dries, and bake out temperature 100-150 ℃, time 20-30min;
(8) assembling covers the enterprising luggage of the good skeleton of machined with titanium alloy covering and joins fit-up gap, edge 0.20mm;
(9) Laser Welding, middle skeleton and covering adopt the laser penetration weldering, skeleton edge and covering adopt laser butt welding, laser power: 1.0-2.0KW, focal length 100-120mm, defocusing amount :-0.1mm, speed of welding: 900-1200mm/min, gas flow: He:15-20ml/min, Ar:14-25ml/min.
Step (3) described around the recessed amount that processes for the step of placing covering of the inboard of skeleton be 0.5mm.
The described alkali cleaning time of step (5) is 80-120min.
The described solution temperature 30-45 of step (6) ℃, pickling time 5-10min.
The trade mark of titanium alloy plate is TC4 or TA3 or TA15.
The above, it only is preferred embodiment of the present invention, be not that the present invention is done any pro forma restriction, although the present invention discloses as above with preferred embodiment, yet be not to limit the present invention, any those skilled in the art, within not breaking away from the technical solution of the present invention scope, when the technology contents that can utilize above-mentioned announcement is made a little change or is modified to the equivalent embodiment of equivalent variations, in every case be the content that does not break away from technical solution of the present invention, any simple modification that foundation technical spirit of the present invention is done above embodiment, equivalent variations and modification all still belong in the scope of technical solution of the present invention.
Claims (5)
1. the manufacture method of an aircraft rudder assembly Laser Welding may further comprise the steps:
(1) blanking is pressed the blanking of figure paper size with titanium alloy sheet;
(2) covering is hot-forming, the plate thermal forming that 1.0-2.0mm is thick is to drawing requirement, profile is evenly brushed protection alcohol graphite solution, air-dry slightly polish with the 600# fine sandpaper afterwards, adjust the mould upper and lower mould and keep clearance between punch and die 35-50mm, mould is warmed up to 550-750 ℃, adds press-fitting mould, insulation 5-30min;
(3) frame machine add-on type adopts the machine add-on type with sheet material, for ease of the assembling of covering and skeleton, around the inboard of skeleton process for the recessed ledge frame of placing covering;
(4) electrochemical deoiling, degreasing fluid prescription: Na
3PO
412H
2O45-60g/L, Na
2CO
310H
2O:40-50g/L, Na
2SiO
320-35g/L, water surplus; Solution temperature 60-90 ℃, oil removing time 15-20min removes surperficial grease;
(5) alkali cleaning, the prescription of alkali wash water: NaOH500-700g/L, NaNO
2150-250g/L, water surplus; Solution temperature 90-100 ℃, alkali cleaning time 20-120min;
(6) pickling, the prescription of pickle: HNO3(65%-68%), and HF(40%), water surplus, solution temperature 18-45 ℃, pickling time 1-15min removes oxide on surface;
(7) washed with de-ionized water is adopted in washing, oven dry, and temperature 30-60 ℃, ensure sufficient water and flow into rinse bath, should adopt flushing at last wash phase, not contaminated to guarantee piece surface; In being arranged, the drying baker of air blast dries, and bake out temperature 100-150 ℃, time 20-30min;
(8) assembling covers the enterprising luggage of the good skeleton of machined with titanium alloy covering and joins fit-up gap, edge 0.20mm;
(9) Laser Welding, middle skeleton and covering adopt the laser penetration weldering, skeleton edge and covering adopt laser butt welding, laser power: 1.0-2.0KW, focal length 100-120mm, defocusing amount :-0.1mm, speed of welding: 900-1200mm/min, gas flow: He:15-20ml/min, Ar:14-25ml/min.
2. the manufacture method of aircraft rudder assembly Laser Welding according to claim 1, it is characterized in that step (3) described around the recessed amount that processes for the step of placing covering of the inboard of skeleton be 0.5mm.
3. the manufacture method of aircraft rudder assembly Laser Welding according to claim 1 is characterized in that the described alkali cleaning time of step (5) is 80-120min.
4. the manufacture method of aircraft rudder assembly Laser Welding according to claim 1 is characterized in that the described solution temperature 30-45 of step (6) ℃, pickling time 5-10min.
5. the manufacture method of aircraft rudder assembly Laser Welding according to claim 1, the trade mark that it is characterized in that titanium alloy plate is TC4 or TA3 or TA15.
Priority Applications (1)
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| CN2012102946470A CN102862021A (en) | 2012-08-19 | 2012-08-19 | Method for manufacturing rudder assembly of aircraft by laser welding |
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| CN2012102946470A CN102862021A (en) | 2012-08-19 | 2012-08-19 | Method for manufacturing rudder assembly of aircraft by laser welding |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103212550A (en) * | 2013-04-24 | 2013-07-24 | 哈尔滨飞机工业集团有限责任公司 | Aluminum alloy airplane skin cleaning method before spot welding |
| CN103521917A (en) * | 2013-11-05 | 2014-01-22 | 什邡市明日宇航工业股份有限公司 | Diffusion welding manufacturing method of titanium alloy special-shaped wing |
| CN103522022A (en) * | 2013-11-05 | 2014-01-22 | 什邡市明日宇航工业股份有限公司 | Method for manufacturing titanium alloy special-shaped wing and adopted welding tool |
| CN103521941A (en) * | 2013-10-14 | 2014-01-22 | 西安航空动力股份有限公司 | Welding method of hollow aluminum alloy structure |
| CN103537789A (en) * | 2013-11-05 | 2014-01-29 | 什邡市明日宇航工业股份有限公司 | Discharge plasma diffusion welding manufacture method for Laval nozzles |
| CN104128745A (en) * | 2014-06-26 | 2014-11-05 | 北京航天新风机械设备有限责任公司 | Machining process technique for aluminum alloy control plane |
| CN107717224A (en) * | 2017-09-26 | 2018-02-23 | 北京普惠三航科技有限公司 | The processing method of the hollow lightweight aerofoil of titanium alloy |
| CN108098255A (en) * | 2017-11-30 | 2018-06-01 | 江西洪都航空工业集团有限责任公司 | A kind of TA15 titanium alloys frame class parts machining process |
| CN108672935A (en) * | 2018-07-25 | 2018-10-19 | 北京航星机器制造有限公司 | A kind of large size, thin walled weak rigid titanium alloy rudder wing structure method for laser welding |
| CN109465547A (en) * | 2018-11-30 | 2019-03-15 | 上海航天精密机械研究所 | Double light beam laser mirror image welding method |
| CN111360399A (en) * | 2018-12-26 | 2020-07-03 | 航天海鹰(哈尔滨)钛业有限公司 | Laser welding forming method for titanium alloy control surface |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103212550A (en) * | 2013-04-24 | 2013-07-24 | 哈尔滨飞机工业集团有限责任公司 | Aluminum alloy airplane skin cleaning method before spot welding |
| CN103212550B (en) * | 2013-04-24 | 2016-02-17 | 哈尔滨飞机工业集团有限责任公司 | Cleaning method before a kind of Aluminum alloy airplane skin spot welding |
| CN103521941A (en) * | 2013-10-14 | 2014-01-22 | 西安航空动力股份有限公司 | Welding method of hollow aluminum alloy structure |
| CN103521917A (en) * | 2013-11-05 | 2014-01-22 | 什邡市明日宇航工业股份有限公司 | Diffusion welding manufacturing method of titanium alloy special-shaped wing |
| CN103522022A (en) * | 2013-11-05 | 2014-01-22 | 什邡市明日宇航工业股份有限公司 | Method for manufacturing titanium alloy special-shaped wing and adopted welding tool |
| CN103537789A (en) * | 2013-11-05 | 2014-01-29 | 什邡市明日宇航工业股份有限公司 | Discharge plasma diffusion welding manufacture method for Laval nozzles |
| CN103537789B (en) * | 2013-11-05 | 2016-02-10 | 什邡市明日宇航工业股份有限公司 | Convergent-divergent channel plasma discharging diffusion welding (DW) manufacture method |
| CN104128745A (en) * | 2014-06-26 | 2014-11-05 | 北京航天新风机械设备有限责任公司 | Machining process technique for aluminum alloy control plane |
| CN107717224A (en) * | 2017-09-26 | 2018-02-23 | 北京普惠三航科技有限公司 | The processing method of the hollow lightweight aerofoil of titanium alloy |
| CN107717224B (en) * | 2017-09-26 | 2020-04-07 | 北京普惠三航科技有限公司 | Processing method of titanium alloy hollow lightweight airfoil |
| CN108098255A (en) * | 2017-11-30 | 2018-06-01 | 江西洪都航空工业集团有限责任公司 | A kind of TA15 titanium alloys frame class parts machining process |
| CN108098255B (en) * | 2017-11-30 | 2019-09-13 | 江西洪都航空工业集团有限责任公司 | A kind of TA15 titanium alloy frame class parts machining process |
| CN108672935A (en) * | 2018-07-25 | 2018-10-19 | 北京航星机器制造有限公司 | A kind of large size, thin walled weak rigid titanium alloy rudder wing structure method for laser welding |
| CN109465547A (en) * | 2018-11-30 | 2019-03-15 | 上海航天精密机械研究所 | Double light beam laser mirror image welding method |
| CN111360399A (en) * | 2018-12-26 | 2020-07-03 | 航天海鹰(哈尔滨)钛业有限公司 | Laser welding forming method for titanium alloy control surface |
| CN111360399B (en) * | 2018-12-26 | 2022-01-04 | 航天海鹰(哈尔滨)钛业有限公司 | Laser welding forming method for titanium alloy control surface |
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Application publication date: 20130109 |