CN105149874A - Integral forming method for titanium alloy skin with reinforcing rib structure - Google Patents
Integral forming method for titanium alloy skin with reinforcing rib structure Download PDFInfo
- Publication number
- CN105149874A CN105149874A CN201510523845.3A CN201510523845A CN105149874A CN 105149874 A CN105149874 A CN 105149874A CN 201510523845 A CN201510523845 A CN 201510523845A CN 105149874 A CN105149874 A CN 105149874A
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- Prior art keywords
- panel
- reinforcement
- skin
- face plate
- reinforcing rib
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/16—Arc welding or cutting making use of shielding gas
Abstract
The invention provides an integral forming method for titanium alloy skin with a reinforcing rib structure and belongs to the technical field of integral forming. The problem of welding deformation caused by a thermal forming/spot welding method is solved, and the problem of hard diffusion quality control in two-plate superplastic forming/diffusion bonding integral forming is solved. According to the method, a skin face plate, a reinforcing rib face plate and a stripping face plate are formed through the thermal forming process; a scribe contour gauge for coating of soldering stopping agents is prepared, the positions of gas pipe grooves are scribed on the three face plates, and soldering stopping agent coating areas are scribed on the inner side of the skin face plate and the outer side of the reinforcing rib face plate according to the shape of the scribe contour gauge. Argon is introduced to the space between the stripping face plate and the reinforcing rib face plate, and diffusion bonding between the skin face plate and the reinforcing rib face plate is completed; argon is introduced to the space between the skin face plate and the reinforcing rib face plate to achieve superplastic forming of reinforcing ribs. The integral forming method adopting superplastic forming/diffusion bonding of the three plates is provided, and the titanium alloy skin with the reinforcing rib structure is formed integrally at a time.
Description
Technical field
The invention belongs to monolithic molding technical field, relate to the large covering combined shaping method of a kind of titanium alloy cabin, this combined precision manufacturing process is suitable for the accurate forming method of the large covering of titanium alloy multi-layer sheet complicated shape cabin body, more specifically refers to the complicated shape covering with reinforcing rib structure.
Background technology
For the curved surface class cabin body skin part with reinforcement, Conventional processing methods domestic is at present that spot welding is connected to form overall class part after hot forming curved surface class covering and reinforcement respectively, or by two-ply superplastic forming/diffusion connecting overall shaping.After the shortcoming of hot forming+spot welding method is spot welding reinforcement, skin-covering face distortion is comparatively large, and room temperature cannot be eliminated, and overall thermal school shape realizes more difficult.Connect for superplastic forming/diffusion, if only rely on mechanical pressure to originate as diffusion pressure, because the precision coupling between fixture for forming is difficult to realize, Diffusion Welding is second-rate; And adopt mechanical pressure and gas pressure to carry out diffusion to be connected, then must to ensure the excellent sealing between mould and plate, because skin shape drafting angle is less, during frock matched moulds, sealing effectiveness is difficult to ensure, easily causes diffusion welding process failure.Need to propose a kind of integral forming method, carry out the titanium alloy covering of processing belt reinforcing rib structure, to avoid the generation of the problems referred to above.
Summary of the invention
The present invention solve technical problem be propose a kind of for the integral forming method with reinforcing rib structure titanium alloy covering, i.e. a kind of manufacturing process adopting three ply board superplastic forming/diffusion to connect, for the monolithic molding with reinforcing rib structure titanium alloy covering, overcome welding deformation that hot forming/spot welding method causes and the diffusing qualities that two-ply superplastic forming/diffusion connecting overall is shaped is difficult to the problems such as control.This combined precision manufacturing process is suitable for the accurate forming method of the large covering of titanium alloy multi-layer sheet complicated shape cabin body.
Technical scheme of the present invention is: a kind of for the integral forming method with reinforcing rib structure titanium alloy covering, step is as follows:
1) forming shaped blank, peels off panel, reinforcement panel and skin panel three profile consistent;
2) for the preparation of the face mold of only solder flux coating, profile and the forming blank profile of face mold are completely the same, and it is hollow out that face mold and cabin body cover corresponding reinforcement region;
3) face mold is alignd with stripping panel, reinforcement panel and skin panel respectively, carry out surrounding to fix, the reinforcement panel extrados side of face mold void region, the skin panel intrados side of face mold void region, rules to the border of void region; And the tracheae slot between three deck panels is put and is rule;
4) add by tracheae groove scribing position machine tube seat of giving vent to anger, the tube seat degree of depth is no more than the half of sheet thickness;
5) pickling three panels, remove greasy dirt and the impurity on surface, and air-dry to the surface after pickling;
6) the only solder flux coating zone coating only solder flux in the region of reinforcement panel, skin panel line; And the tracheae slot between three deck panels is put, coating is solder flux only; And by peel off panel both sides, reinforcement panel intrados side and skin panel extrados side except the only solder flux of coating on the extra-regional region of soldering and sealing of surrounding;
7) three deck panels applying only solder flux are carried out alignment stationary positioned;
8) three deck panels surrounding soldering and sealing are carried out;
9) at breather pipe groove position welding breather pipe;
10) punch die inner chamber coating only solder flux, is placed in punch, die by stripping panel good for soldering and sealing, reinforcement panel and skin panel; Punch die is wherein identical with profile with the radian of cabin body covering, punch has and the position of reinforcement, shape, groove that size is identical;
11) installation pipeline, the punch that is installed, die, put into stove, closes fire door and heat up;
12) when punch, die are warming up to temperature 920 DEG C ± 20 DEG C, pressurization, to argon gas logical between stripping panel and reinforcement panel, pressurize 1 hour, carries out the Diffusion Welding of skin panel and reinforcement panel, peels off panel superplastic forming; Backward skin panel and reinforcement panel between pass into argon gas, pressurize 0.2 hour, reinforcement panel superplastic forming;
13), after Diffusion Welding and superplastic forming, stop heating, continue to pass into argon gas, until be cooled to 200 DEG C between skin panel and reinforcement panel;
14) part is taken out, air cooling;
15) remove piece surface, remove and peel off panel.
The skin panel, reinforcement panel and the stripping panel that are used for superplastic forming/diffusion and connect is formed by heat forming technology, for the preparation of the face mold of only solder flux coating, three deck panels are drawn a tracheae slot put, and inside skin panel, reinforcement panels outside marks only solder flux coating zone by model shape.Add ventilation by gas circuit scribing position machine and escape pipe slot is put.Pickling three panels, by scribing position in painting only solder flux.Argon arc welding soldering and sealing three ply board, and weld ventilation nozzle.Enter stove intensification pressurization, to argon gas logical between stripping panel and reinforcement panel, complete skin panel and be connected with the diffusion of reinforcement panel; The superplastic forming of reinforcement is realized to argon gas logical between skin panel and reinforcement panel.After part takes out, machine adds removal surplus, removes and peels off panel, the final band reinforcing rib structure titanium alloy covering part obtaining precision form.
Technique effect of the present invention is:
Patent of the present invention proposes the integral forming method adopting three ply board superplastic forming/diffusion to connect, achieve Integratively forming belt reinforcing rib structure titanium alloy covering, the welding deformation effectively avoiding hot forming/spot welding method to cause and the two-ply superplastic forming/diffusion connecting overall diffusing qualities brought that is shaped is difficult to the problems such as control.
Accompanying drawing explanation
Fig. 1 a, 1b, 1c are top view, front view, the left view of covering class design of part of the present invention respectively.
Fig. 2 is that method of the present invention must stop flux coating area schematic (dash area) eventually.
Fig. 3 is skin panel of the present invention and reinforcement panel dispersion welding process schematic diagram.
Fig. 4 is reinforcement panel superplastic forming process schematic of the present invention.
Wherein, 1 is cabin body covering, and 2 is reinforcement, and 3 is non-diffusing welding zone territory, 4 is diffusion welding (DW) region, and 5 for peeling off panel, and 6 is reinforcement panel, 7 is skin panel, and 8 is (superplastic forming/diffusion connects) punch, and 9 is (superplastic forming/diffusion connects) die.
Detailed description of the invention
Below in conjunction with Fig. 1 a, Fig. 1 b, the present invention will be further described for Fig. 1 c, Fig. 2, Fig. 3, Fig. 4:
The present invention is a kind of for the integral forming method with reinforcing rib structure titanium alloy covering, comprises the following steps:
1) by heat forming technology, forming shaped blank, namely peel off panel 5, reinforcement panel 6 and skin panel 7, three's profile is consistent.
2) according to the position of part reinforcement on covering, for the preparation of the face mold of only solder flux coating, profile and the forming blank profile of model are completely the same.It is hollow out that model and cabin body cover corresponding reinforcement region.
3) face mold is alignd with stripping panel 5, reinforcement panel 6 and skin panel 7 respectively, carry out surrounding with arc pincers to fix, reinforcement panel 6 (reinforcement region, place) the extrados side of face mold void region, skin panel 7 (reinforcement region, place) the intrados side of face mold void region, rule in the border of carrying out void region, as stopping solder flux coating zone in border; And the tracheae slot between three deck panels is put and is rule.Two-way tracheae for tracheae groove a: road is between reinforcement panel 6 and skin panel 7, another road is between stripping panel 5 and reinforcement panel 6, and two-way tracheae one end is communicated with outside, and other end connection is positioned at reinforcement region.
4) add by tracheae groove scribing position machine tube seat of giving vent to anger, the tube seat degree of depth is no more than the half of sheet thickness.
5) pickling three panels, remove greasy dirt and other impurity on surface, and with hair-dryer to the table after pickling
Quick-air-drying is carried out in face.
6) the only solder flux coating zone coating only solder flux in the region that reinforcement panel 6, skin panel 7 are rule; And the tracheae slot between three deck panels is put, coating is solder flux only; And will the extra-regional region coating of the soldering and sealing except the surrounding only solder flux process of two sides inside and outside panel 5, reinforcement panel 6 intrados side and skin panel 7 extrados side be peeled off.The soldering and sealing region of surrounding is used for stripping panel 5, reinforcement panel 6 surrounding to weld, and reinforcement panel 6, skin panel 7 surrounding are welded, and forms airtight space.
7) three deck panels applying only solder flux are carried out alignment stationary positioned with arc pincers, prevent dislocation.
8) adopt the method for argon arc welding welding to carry out three deck panels surrounding soldering and sealing, form a soldering and sealing entirety.Need to carry out back of the body gas shielded in the process of welding.
9) at breather pipe groove position welding breather pipe.
10) punch 8, die 9 are identical with profile with the radian of cabin body covering, punch 8 have and the position of reinforcement, shape, groove that size is identical; The coating of punch 8, die 9 inner chamber stops solder flux, stripping panel 5 good for soldering and sealing, reinforcement panel 6 and skin panel 7 is placed in punch 8, die 9, and punch 8 is avoided in attention, breather pipe damages by pressure by die 9.
11) install tracheae, the punch 8 that is installed, die 9, put into stove, closes fire door and heat up.
12) when punch 8, die 9 are warming up to temperature 920 DEG C ± 20 DEG C, pressurization, to 0.5MPa argon gas logical between stripping panel 5 and reinforcement panel 6, pressurize 1 hour, carry out skin panel 7 to be connected with the diffusion of reinforcement panel 6, skin panel 7 and reinforcement panel 6 weld together, and peel off reinforcement region, panel 5 place superplastic forming, form reinforcement cavity; To passing into argon gas (logical 1.5MPa argon gas) between skin panel 7 and reinforcement panel 6, pressurize 0.2 hour, the superplastic forming of reinforcement panel 6, realizes reinforcement panel 6 and forms reinforcement.
13), after Diffusion Welding and superplastic forming, stop heating, continue to pass into 0.05MPa argon gas between skin panel 7 and reinforcement panel 6, until be cooled to 200 DEG C.
14) part is taken out, air cooling.
15) piece surface is removed.
16) remove stripping panel 5, final acquisition is with reinforcing rib structure titanium alloy covering part.
Claims (1)
1. for the integral forming method with reinforcing rib structure titanium alloy covering, it is characterized in that, the step of the method is as follows:
1) forming shaped blank, peels off panel (5), reinforcement panel (6) and skin panel (7) three's profile consistent;
2) for the preparation of the face mold of only solder flux coating, profile and the forming blank profile of face mold are completely the same, and it is hollow out that face mold and cabin body cover corresponding reinforcement region;
3) face mold is alignd with stripping panel (5), reinforcement panel (6) and skin panel (7) respectively, carry out surrounding to fix, reinforcement panel (6) the extrados side of face mold void region, skin panel (7) the intrados side of face mold void region, rules to the border of void region; And the tracheae slot between three deck panels is put and is rule;
4) add by tracheae groove scribing position machine tube seat of giving vent to anger, the tube seat degree of depth is no more than the half of sheet thickness;
5) pickling three panels, remove greasy dirt and the impurity on surface, and air-dry to the surface after pickling;
6) the only solder flux coating zone coating only solder flux in the region that reinforcement panel (6), skin panel (7) are rule; And the tracheae slot between three deck panels is put, coating is solder flux only; And will peel off the inside and outside two sides of panel (5), reinforcement panel (6) intrados side and skin panel (7) extrados side except the only solder flux of coating on the extra-regional region of soldering and sealing of surrounding;
7) three deck panels applying only solder flux are carried out alignment stationary positioned;
8) three deck panels surrounding soldering and sealing are carried out;
9) at breather pipe groove position welding breather pipe;
10) punch (8), die (9) inner chamber coating only solder flux, be placed on stripping panel (5) good for soldering and sealing, reinforcement panel (6) and skin panel (7) in punch (8), die (9); Punch (8) die (9) is wherein identical with profile with the radian of cabin body covering, punch (8) has and the position of reinforcement, shape, groove that size is identical;
11) installation pipeline, the punch that is installed (8), die (9), put into stove, closes fire door and heat up;
12) when punch (8), die (9) are warming up to temperature 920 DEG C ± 20 DEG C, pressurization, to argon gas logical between stripping panel (5) and reinforcement panel (6), pressurize 1 hour, carry out skin panel (7) and the Diffusion Welding of reinforcement panel (6), peel off panel (5) superplastic forming; Backward skin panel (7) and reinforcement panel (6) between pass into argon gas, pressurize 0.2 hour, reinforcement panel (6) superplastic forming;
13), after Diffusion Welding and superplastic forming, stop heating, continue to pass into argon gas, until be cooled to 200 DEG C between skin panel (7) and reinforcement panel (6);
14) part is taken out, air cooling;
15) remove piece surface, remove and peel off panel (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510523845.3A CN105149874A (en) | 2015-08-24 | 2015-08-24 | Integral forming method for titanium alloy skin with reinforcing rib structure |
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| CN201510523845.3A CN105149874A (en) | 2015-08-24 | 2015-08-24 | Integral forming method for titanium alloy skin with reinforcing rib structure |
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| CN201510523845.3A Pending CN105149874A (en) | 2015-08-24 | 2015-08-24 | Integral forming method for titanium alloy skin with reinforcing rib structure |
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Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106224751A (en) * | 2016-08-24 | 2016-12-14 | 中国航天科技集团公司长征机械厂 | A kind of large-scale eyelid covering using dovetail to connect cuts brill model |
| CN106271439A (en) * | 2016-08-30 | 2017-01-04 | 北京普惠三航科技有限公司 | The superplastic forming of the heat-resisting eyelid covering of titanium alloy/diffusion joint forming method |
| CN108127247A (en) * | 2017-12-11 | 2018-06-08 | 北京星航机电装备有限公司 | The simple inlet duct and air inlet method of a kind of superplastic forming/diffusion connection |
| 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 |
| CN108688196A (en) * | 2018-06-22 | 2018-10-23 | 西安飞机工业（集团）有限责任公司 | A kind of forming method and molding die of technique for aircraft composite siding |
| CN109158842A (en) * | 2018-10-31 | 2019-01-08 | 北京普惠三航科技有限公司 | The processing technology of aerofoil is reinforced in a kind of titanium alloy lightweight |
| CN109175917A (en) * | 2018-10-31 | 2019-01-11 | 北京普惠三航科技有限公司 | The manufacturing method of aerofoil is reinforced in a kind of titanium alloy lightweight |
| CN109203423A (en) * | 2017-07-06 | 2019-01-15 | 中国航空制造技术研究院 | A method of improving SPF/DB three-decker forming quality |
| CN109434380A (en) * | 2018-11-05 | 2019-03-08 | 北京星航机电装备有限公司 | A kind of Varying-thickness lightweight missile wing covering manufacturing process |
| CN110539138A (en) * | 2019-09-30 | 2019-12-06 | 北京星航机电装备有限公司 | Preparation method of aluminum alloy lightweight active cooling structural skin |
| CN110561054A (en) * | 2019-09-30 | 2019-12-13 | 北京星航机电装备有限公司 | forming method of high-temperature alloy fairing with reinforcing rib structure |
| CN111660000A (en) * | 2020-06-08 | 2020-09-15 | 上海交通大学 | Synchronous superplastic deformation diffusion bonding method for aluminum alloy multilayer plates |
| CN112846643A (en) * | 2020-12-08 | 2021-05-28 | 北京星航机电装备有限公司 | Forming method and forming device for titanium alloy thin-wall hollow structure |
| CN113333935A (en) * | 2021-04-30 | 2021-09-03 | 成都飞机工业（集团）有限责任公司 | Curved web surface titanium alloy superplastic forming-diffusion bonding blank preparation method |
| CN113751590A (en) * | 2021-09-15 | 2021-12-07 | 北京航星机器制造有限公司 | Titanium alloy four-layer structure forming method and mold assembly |
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| CN106271439B (en) * | 2016-08-30 | 2019-08-16 | 北京普惠三航科技有限公司 | The superplastic forming of the heat-resisting covering of titanium alloy/diffusion joint forming method |
| CN109203423A (en) * | 2017-07-06 | 2019-01-15 | 中国航空制造技术研究院 | A method of improving SPF/DB three-decker forming quality |
| CN109203423B (en) * | 2017-07-06 | 2019-07-19 | 中国航空制造技术研究院 | A method of improving SPF/DB three-decker forming quality |
| 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 |
| 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 |
| CN108127247A (en) * | 2017-12-11 | 2018-06-08 | 北京星航机电装备有限公司 | The simple inlet duct and air inlet method of a kind of superplastic forming/diffusion connection |
| CN108127247B (en) * | 2017-12-11 | 2020-06-30 | 北京星航机电装备有限公司 | Simple air inlet device and air inlet method for superplastic forming/diffusion connection |
| CN108688196A (en) * | 2018-06-22 | 2018-10-23 | 西安飞机工业（集团）有限责任公司 | A kind of forming method and molding die of technique for aircraft composite siding |
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| CN109158842A (en) * | 2018-10-31 | 2019-01-08 | 北京普惠三航科技有限公司 | The processing technology of aerofoil is reinforced in a kind of titanium alloy lightweight |
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| CN110561054B (en) * | 2019-09-30 | 2020-11-13 | 北京星航机电装备有限公司 | Forming method of high-temperature alloy fairing with reinforcing rib structure |
| CN110539138A (en) * | 2019-09-30 | 2019-12-06 | 北京星航机电装备有限公司 | Preparation method of aluminum alloy lightweight active cooling structural skin |
| CN110561054A (en) * | 2019-09-30 | 2019-12-13 | 北京星航机电装备有限公司 | forming method of high-temperature alloy fairing with reinforcing rib structure |
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