CN101920392A - Mechanically-machining rib/diffusion connecting process for titanium alloy rudders and wing members - Google Patents
Mechanically-machining rib/diffusion connecting process for titanium alloy rudders and wing members Download PDFInfo
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- CN101920392A CN101920392A CN2010102289766A CN201010228976A CN101920392A CN 101920392 A CN101920392 A CN 101920392A CN 2010102289766 A CN2010102289766 A CN 2010102289766A CN 201010228976 A CN201010228976 A CN 201010228976A CN 101920392 A CN101920392 A CN 101920392A
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- 238000003754 machining Methods 0.000 title claims abstract description 22
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 21
- 238000009792 diffusion process Methods 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000003466 welding Methods 0.000 claims abstract description 16
- 238000003801 milling Methods 0.000 claims abstract description 8
- 239000011248 coating agent Substances 0.000 claims description 9
- 238000000576 coating method Methods 0.000 claims description 9
- 238000000465 moulding Methods 0.000 claims description 9
- 238000005554 pickling Methods 0.000 claims description 9
- 238000009413 insulation Methods 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 abstract description 5
- 230000005484 gravity Effects 0.000 abstract description 4
- 238000005406 washing Methods 0.000 abstract description 3
- 239000002253 acid Substances 0.000 abstract 1
- 230000001681 protective effect Effects 0.000 abstract 1
- 238000009423 ventilation Methods 0.000 abstract 1
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 14
- 239000007789 gas Substances 0.000 description 13
- 229910052786 argon Inorganic materials 0.000 description 7
- KRHYYFGTRYWZRS-UHFFFAOYSA-N Fluorane Chemical compound F KRHYYFGTRYWZRS-UHFFFAOYSA-N 0.000 description 4
- 238000004140 cleaning Methods 0.000 description 4
- 238000007493 shaping process Methods 0.000 description 3
- 238000010792 warming Methods 0.000 description 3
- 229910052582 BN Inorganic materials 0.000 description 2
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 description 2
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 230000002950 deficient Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229910017604 nitric acid Inorganic materials 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
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Abstract
The invention discloses a mechanically-machining rib/diffusion connecting process for titanium alloy rudders and wing members, which comprises the following steps of: 1, mechanically machining the rudders, the wing members and the ribs according to drawings; 2, performing acid washing; 3, folding the two halves of mechanically-machined rudders, the two halves of mechanically-machined wing members and the two halves of mechanically-machined ribs and welding the peripheries and a ventilation pipe; 4, mold-filling, namely, placing the rudders and the wing members coated with a parting agent in the centre of a cavity of superplastic forming equipment; 5, raising the temperature and introducing a protective gas; 6, forming, namely, (1) introducing one liter of gas with a pressure equal to 3 barometric pressures into the cavity of the parts for 5 minutes, (2) introducing one liter of gas with the pressure equal to 3 barometric pressures into the cavity of the parts for 60 minutes and (3) introducing one liter of gas with the pressure equal to 1.2 barometric pressures into the cavity of the parts for 5 minutes; 7, reducing the temperature and performing stripping; and 8, milling the external forms of the rudders and the wing members. The process has the advantages of high forming success rate, stable member quality, accurate rib position, stable gravity center position and short forming time which is only 1 to 2 hours.
Description
Technical field:
The present invention is machining titanium alloy system rudder, wing member machining rib/diffusion connecting process.
Background technology:
In aviation, the spacecraft centered rudder, wing member is normal to adopt four layers of titanium alloy plate through superplastic forming/diffusion connecting process processing, four layers of superplastic forming/diffusion connecting process of titanium alloy are: forming temperature is meant shaping dies is warming up to 910 ℃～950 ℃, at two-way shaping gas circuit input argon gas, two-layer vacuumizing simultaneously, this two-layer not separant coating position is diffused into together, in former, keep certain pressure and after the regular hour, to intermediate layer input argon gas, the air pressure of two outside layers reduces gradually, and two-layer rising was moulded shape and is connected with the diffusion of outside in the middle of this process had realized.
Rise and be moulded shape/diffusion connecting process flow process: (1) blanking: press the blanking of figure paper size, following four titanium alloy plates, monolateral high-volume 50mm requires perimeter alignment, otherwise is difficult to close grave envelope between each laminate when welding, tolerance+0.25mm; (2) location, line: by locator tabs, model line; (3) mill air channel: milling pore groove, width are 3mm～4mm, and the degree of depth is about 40%～50% of sheet thickness, a polishing flash removed after the milling; (4) pickling: plate is placed in the descaling bath, and the surface acid-washing oil removing is to guarantee panel surface cleaning, free from admixture and oxide skin; Pickling prescription: every premium on currency contains 200 milliliters～300 milliliters in 500 milliliters～550 milliliters in nitric acid and hydrofluoric acid; (5) separant coating: apply interleaving agent according to the non-diffusion join domain of drawing outline line on plate, and apply interleaving agent at pore groove and gas channels place; The interleaving agent main component is: yittrium oxide or boron nitride; (6) vent line preparation: prepare the part vent line with reference to the equipment platform size, pipeline length is placed on platform central authorities with part and is advisable, and can not there be defectives such as crackle, fracture pipeline bending position; (7) welding: adopt the argon arc welding manner to weld plate border and pipeline, check pipeline and pocket air-tightness after welding is finished; (8) dress mould: cleaning die surface, guarantee profile part free from admixture, be convenient to molding at blank outer surface and die surface separant coating, mould is put in superplastic forming equipment (Loire FSP400T titanium alloy hot former) furnace chamber middle position, underlay insulation asbestic blanket on the mould, connecting line and temperature thermocouple are closed fire door, heat up; (9) heat up: be warming up to and be shaped temperature required (the titanium alloy forming temperature is 910 ℃～950 ℃), during part to fill high purity argon protection; (10): be shaped: on superplastic forming equipment, form by facility control program.Its deficiency is: 1, superplastic forming/Diffusion Welding four-layer structure the trigonum defective occurs easily in that internal layer is super when moulding outer diffusing procedure, makes the easy groove of part appearance, causes part to scrap.2, during superplastic forming/Diffusion Welding stud, local gapped, do not have in the diffusion welding (DW), the bearing capacity of stud is reduced.3, formation of parts thickness is thin more, titanium alloy superplastic forming/Diffusion Welding four-layer structure part forming was poor more when the part forming area was big more.4, the rib of superplastic forming easily departs from, and makes the position inaccuracy of internal structure, easily influences the intensity of structure, and is bigger to the center of gravity influence of structure.5, whole manufacturing is longer the same period, and the hot forming time is long, needs 6～9 hours.。For avoiding above deficiency on four layers of superplastic forming of titanium alloy/diffusion connecting process basis, improve at the technology of making titanium alloy rudder, wing structure and to develop titanium alloys rudder, wing member machining rib/diffusion connecting process.
Summary of the invention:
The purpose of the invention provides a kind of titanium alloys rudder, wing member is shaped as the power height, titanium alloys rudder, wing member machining rib/diffusion connecting process that forming quality is stable; The purpose of the invention is to realize by following technical scheme: titanium alloys rudder, wing member machining rib/diffusion connecting process, and its step is as follows:
1), machining rudder, wing member and rib: map interlinking paper conversion;
2), pickling: rudder, wing member and rib that machining is intact carry out pickling;
3), involutory welded perimeter of rudder, wing member and rib and the vent line that two halves machining is finished;
4), dress mould: rudder, wing member outer surface and die surface separant coating after welding before the dress mould is contained in superplastic forming equipment inner chamber middle position, underlay insulation asbestic blanket on mould with rudder, the wing member of separant coating;
5), intensification and input protection gas;
6), be shaped: order is as follows:
(1) when mold temperature is raised to the assigned temperature temperature, be 1 liter gas to inner cavity of component input 1～3 atmospheric pressure, volume, 5 minutes duration;
(2) to 3 atmospheric pressure of inner cavity of component input, volume is 1 liter a gas, the continuous 60 minutes time;
(3) to inner cavity of component input 1.2 atmospheric pressure, volumes be 1 liter gas, 5 minutes duration;
7), cooling molding: mold temperature is reduced to molding below 500 ℃;
8), milling rudder, wing member profile.
The advantage of the invention: part forming success rate height, part quality is stable, groove can not occur, and the rib position is accurate, and position of centre of gravity is stable.
Description of drawings:
Fig. 1 is titanium alloys rudder, wing member inner surface structure schematic diagram;
Fig. 2 is processing the rib on rudder, the wing member inner surface and the structural representation of air channel on the titanium alloy plate.
The specific embodiment: for for example shown in Figure 1, the wing member gross thickness is 10mm according to certain wing member, and length dimension is 200mm, and width dimensions is 900mm, and titanium alloys rudder, wing member machining rib/diffusion connecting process are described in detail in detail, and its step is as follows:
1), machining rudder, wing member and rib: map interlinking paper conversion; Get two 5.1mm uniform thickness titanium alloy plates as blank, adopt the mode of digital control milling, be processed into symmetrical two, utilize CAD software CATIA to carry out the rib shape of numerical control programming processing parts inside, adopt vacuum cup and pressing plate pressing dual mode that plate is fixed in the process, guarantee machining accuracy.
Machined parameters: roughing: the speed of mainshaft is 1500 rev/mins
The tool feeding amount is 150mm/ minute
Excision amount 0.8mm
Fine finishining: the speed of mainshaft is 1000 rev/mins
The tool feeding amount is 200mm/ minute
Excision amount 0.2mm
2), pickling: rudder, wing member and rib that machining is intact carry out pickling; Pickling prescription: every premium on currency contains 200 milliliters～300 milliliters in 500 milliliters～550 milliliters in nitric acid and hydrofluoric acid; The surface acid-washing oil removing is to guarantee panel surface cleaning, free from admixture and oxide skin.
3), involutory welded perimeter of rudder, wing member and rib and the vent line that two halves machining is finished; The member of two symmetries that machining rudder, wing member and rib are processed is involutory according to benchmark, with argon arc welding soldering and sealing periphery and vent line, makes member form the pocket of a sealing;
Welding parameter: arc current: 110A
Arc voltage 10V
Welding gun argon gas charge 10L/min
After finishing, welding checks pipeline and member air-tightness.
4), dress mould: before the dress mould, the cleaning die surface is removed impurity, rudder after welding, wing member outer surface and die surface separant coating, purpose is to be convenient to molding, and the interleaving agent main component is: yittrium oxide or boron nitride are contained in superplastic forming equipment with rudder, the wing member of separant coating
(adopting ACB company to make) inner chamber middle position, underlay insulation asbestic blanket on mould; Connecting line and temperature thermocouple are closed fire door, heat up.
5), intensification and input protection gas; Shaping dies is warming up to 945 ℃, the input high purity argon.
6), be shaped: order is as follows:
(1) to inner cavity of component input 1～3 atmospheric pressure, volume is 1 liter gas, 5 minutes duration;
(2) to 3 atmospheric pressure of inner cavity of component input, volume is 1 liter a gas, the continuous 60 minutes time;
(3) to inner cavity of component input 1.2 atmospheric pressure, volumes be 1 liter gas, 5 minutes duration.
7), cooling molding: mold temperature is reduced to molding below 500 ℃;
8), milling rudder, wing member profile.Utilize CAD software CATIA to carry out numerical control programming, milling part profile.
Advantage: part forming success rate height, part quality is stable, groove can not occur, and the rib position is accurate, and position of centre of gravity is stable, and the hot forming time is short, only needs 1～2 hour.
Claims (1)
1. titanium alloys rudder, wing member machining rib/diffusion connecting process, its step is as follows:
1), machining rudder, wing member and rib: map interlinking paper conversion;
2), pickling: rudder, wing member and rib that machining is intact carry out pickling;
3), involutory welded perimeter of rudder, wing member and rib and the vent line that two halves machining is finished;
4), dress mould: rudder, wing member outer surface and die surface separant coating after welding before the dress mould is contained in superplastic forming equipment inner chamber middle position, underlay insulation asbestic blanket on mould with rudder, the wing member of separant coating;
5), intensification and input protection gas;
6), be shaped: order is as follows:
(1) to inner cavity of component input 1～3 atmospheric pressure, volume is 1 liter gas, 5 minutes duration;
(2) to 3 atmospheric pressure of inner cavity of component input, volume is 1 liter a gas, the continuous 60 minutes time;
(3) to inner cavity of component input 1.2 atmospheric pressure, volumes be 1 liter gas, 5 minutes duration;
7), cooling molding: mold temperature is reduced to molding below 500 ℃;
8), milling rudder, wing member profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102289766A CN101920392A (en) | 2010-07-16 | 2010-07-16 | Mechanically-machining rib/diffusion connecting process for titanium alloy rudders and wing members |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010102289766A CN101920392A (en) | 2010-07-16 | 2010-07-16 | Mechanically-machining rib/diffusion connecting process for titanium alloy rudders and wing members |
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| CN101920392A true CN101920392A (en) | 2010-12-22 |
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| CN2010102289766A Pending CN101920392A (en) | 2010-07-16 | 2010-07-16 | Mechanically-machining rib/diffusion connecting process for titanium alloy rudders and wing members |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102825427A (en) * | 2012-08-19 | 2012-12-19 | 什邡市明日宇航工业股份有限公司 | Manufacturing method for diffusion welding of aircraft rudder assembly |
| CN105057990A (en) * | 2015-08-21 | 2015-11-18 | 北京星航机电装备有限公司 | Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework |
| CN105149874A (en) * | 2015-08-24 | 2015-12-16 | 北京星航机电装备有限公司 | Integral forming method for titanium alloy skin with reinforcing rib structure |
| CN108161205A (en) * | 2017-12-06 | 2018-06-15 | 北京星航机电装备有限公司 | A kind of wing rudder class part electron beam welding SPF Technology |
| CN108817867A (en) * | 2018-08-20 | 2018-11-16 | 中国航空制造技术研究院 | A kind of closed manufacturing process with muscle hollow unit |
| CN110508891A (en) * | 2019-09-06 | 2019-11-29 | 中国航空制造技术研究院 | A kind of closed band muscle hollow structure manufacturing process of titanium alloy |
| CN112361894A (en) * | 2020-10-12 | 2021-02-12 | 中国运载火箭技术研究院 | Air rudder for rocket |
| CN112975287A (en) * | 2021-02-23 | 2021-06-18 | 哈尔滨工业大学 | Superplastic deformation/diffusion connection forming technology for wavy hollow skin structure part |
| CN113814655A (en) * | 2021-08-23 | 2021-12-21 | 成都飞机工业（集团）有限责任公司 | Complicated surface pneumatic loading superplastic forming diffusion bonding method |
| CN113878361A (en) * | 2021-09-30 | 2022-01-04 | 北京航星机器制造有限公司 | Processing and manufacturing die and method for special-shaped curved surface hollow skin |
| CN114180028A (en) * | 2021-12-09 | 2022-03-15 | 北京星航机电装备有限公司 | Assembly for preparing hollow grid structure wing rudder and preparation method of wing rudder |
| CN114505573A (en) * | 2022-04-20 | 2022-05-17 | 成都飞机工业（集团）有限责任公司 | Superplastic forming and diffusion bonding die and preparation method of thin-wall large-inclination-angle part |
| CN117548998A (en) * | 2023-11-21 | 2024-02-13 | 华钛空天(北京)技术有限责任公司 | Preparation method, device, equipment and medium for thin-wall cavity rudder |
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Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102825427B (en) * | 2012-08-19 | 2015-04-22 | 什邡市明日宇航工业股份有限公司 | Manufacturing method for diffusion welding of aircraft rudder assembly |
| CN102825427A (en) * | 2012-08-19 | 2012-12-19 | 什邡市明日宇航工业股份有限公司 | Manufacturing method for diffusion welding of aircraft rudder assembly |
| CN105057990A (en) * | 2015-08-21 | 2015-11-18 | 北京星航机电装备有限公司 | Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework |
| CN105057990B (en) * | 2015-08-21 | 2017-08-25 | 北京星航机电装备有限公司 | A kind of lightweight covering skeleton missile wing integrally spreads joint forming method |
| CN105149874A (en) * | 2015-08-24 | 2015-12-16 | 北京星航机电装备有限公司 | Integral forming method for titanium alloy skin with reinforcing rib structure |
| CN108161205B (en) * | 2017-12-06 | 2020-05-26 | 北京星航机电装备有限公司 | Electron beam welding superplastic forming process for wing rudder parts |
| CN108161205A (en) * | 2017-12-06 | 2018-06-15 | 北京星航机电装备有限公司 | A kind of wing rudder class part electron beam welding SPF Technology |
| CN108817867B (en) * | 2018-08-20 | 2021-03-05 | 中国航空制造技术研究院 | Forming method of closed ribbed hollow component |
| CN108817867A (en) * | 2018-08-20 | 2018-11-16 | 中国航空制造技术研究院 | A kind of closed manufacturing process with muscle hollow unit |
| CN110508891A (en) * | 2019-09-06 | 2019-11-29 | 中国航空制造技术研究院 | A kind of closed band muscle hollow structure manufacturing process of titanium alloy |
| CN112361894A (en) * | 2020-10-12 | 2021-02-12 | 中国运载火箭技术研究院 | Air rudder for rocket |
| CN112975287A (en) * | 2021-02-23 | 2021-06-18 | 哈尔滨工业大学 | Superplastic deformation/diffusion connection forming technology for wavy hollow skin structure part |
| CN112975287B (en) * | 2021-02-23 | 2022-05-20 | 哈尔滨工业大学 | Superplastic deformation/diffusion connection forming technology for wavy hollow skin structure part |
| CN113814655A (en) * | 2021-08-23 | 2021-12-21 | 成都飞机工业（集团）有限责任公司 | Complicated surface pneumatic loading superplastic forming diffusion bonding method |
| CN113814655B (en) * | 2021-08-23 | 2023-12-08 | 成都飞机工业（集团）有限责任公司 | Complex-profile pneumatic loading superplastic forming diffusion connection method |
| CN113878361B (en) * | 2021-09-30 | 2022-11-15 | 北京航星机器制造有限公司 | Processing and manufacturing die and method for special-shaped curved surface hollow skin |
| CN113878361A (en) * | 2021-09-30 | 2022-01-04 | 北京航星机器制造有限公司 | Processing and manufacturing die and method for special-shaped curved surface hollow skin |
| CN114180028A (en) * | 2021-12-09 | 2022-03-15 | 北京星航机电装备有限公司 | Assembly for preparing hollow grid structure wing rudder and preparation method of wing rudder |
| CN114180028B (en) * | 2021-12-09 | 2024-06-11 | 北京星航机电装备有限公司 | Assembly for preparing hollow grid-structure wing rudder and preparation method of wing rudder |
| CN114505573B (en) * | 2022-04-20 | 2022-07-15 | 成都飞机工业（集团）有限责任公司 | Superplastic forming and diffusion bonding die and preparation method of thin-wall large-inclination-angle part |
| CN114505573A (en) * | 2022-04-20 | 2022-05-17 | 成都飞机工业（集团）有限责任公司 | Superplastic forming and diffusion bonding die and preparation method of thin-wall large-inclination-angle part |
| CN117548998A (en) * | 2023-11-21 | 2024-02-13 | 华钛空天(北京)技术有限责任公司 | Preparation method, device, equipment and medium for thin-wall cavity rudder |
| CN117548998B (en) * | 2023-11-21 | 2024-05-07 | 华钛空天(北京)技术有限责任公司 | Preparation method, device, equipment and medium for thin-wall cavity rudder |
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Application publication date: 20101222 |