CN105057990B - A kind of lightweight covering skeleton missile wing integrally spreads joint forming method - Google Patents
A kind of lightweight covering skeleton missile wing integrally spreads joint forming method Download PDFInfo
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- CN105057990B CN105057990B CN201510518844.XA CN201510518844A CN105057990B CN 105057990 B CN105057990 B CN 105057990B CN 201510518844 A CN201510518844 A CN 201510518844A CN 105057990 B CN105057990 B CN 105057990B
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- skeleton
- covering
- missile wing
- diffusion
- lightweight
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Classifications
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- 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
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/001—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by extrusion or drawing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The present invention proposes a kind of overall diffusion bonding structure missile wing of lightweight covering skeleton and its manufacturing process, the distribution of skeleton rib can be designed by such a missile wing structure type according to maximum load effect, skeletal internal rib width can be designed as the narrower 4mm of rib form 2, can so mitigate missile wing weight significantly.Covering is equipped suitable rear perimeter edge with skeleton and welded with electron beam, and covering skeleton blank loads mould, is put into heat forming equipment and is heated up.Matched moulds and convenient pressure is loaded after reaching design temperature, covering contact pressurization certain time with skeleton and realizes that diffusion is connected, and such a structure type missile wing can mitigate weight significantly and improve bearing capacity, and dimensional accuracy height.
Description
Technical field
The invention belongs to Precision Forming Technology field, and in particular to a kind of lightweight covering skeleton missile wing part integrally spreads
Connection method.
Background technology
Lightweight structure is increasingly widely applied in field of aerospace, and traditional missile wing part uses covering mostly
Skeleton structure, but such Titanium Alloy Wing part manufacturing process is：Skeleton is machined, the cold bending and forming of covering, covering periphery
Welded with skeleton, covering and the position spot welding of skeleton rib.But due to spot-welding technology, skeleton rib width is restricted, rib
Width at least 10mm, influences the weight of missile wing part.And such as superplastic forming diffusion of other lightweight missile wing design of part forms connects
Binding structure, although can obtain good weight loss effect, but because technology difficulty is than larger, product qualification rate is low and low production efficiency
In terms of factor, aerospace field do not obtain high-volume use.
The content of the invention
The present invention proposes a kind of overall diffusion bonding structure missile wing of covering skeleton, and such a missile wing structure type can be by bone
The distribution of frame rib is designed according to maximum load effect, and skeletal internal rib width can be designed as narrower rib form
(2-4) mm, can so mitigate missile wing weight significantly, and covering and skeleton are realized into diffusion can form to meet to use after being connected and wanted
The lightweight missile wing part asked.
Present invention solves the technical problem that being the overall diffusion connection method of titanium alloy lightweight missile wing part, missile wing part is set
It is calculated as not producing what can be designed on the principle of unstability, width in frame-covering structure, skeleton rib foundation height aspect
It is as far as possible narrow, passage is left on skeleton and is connected with vent line.Covering is equipped suitable rear perimeter edge with skeleton and carried out with electron beam
Welding, forms closed cavity.Covering skeleton blank loads mould, is put into heat forming equipment and is heated up.Reach after design temperature
Matched moulds simultaneously loads convenient pressure, and covering contacts pressurization certain time with skeleton and realizes diffusion connection, in the process in order to prevent
Covering is collapsed upon inside parts loading air pressure.Start cooling after the completion of part diffusion connection, part is taken out after cooling.
Particular technique flow is as follows：
(1) skin part blanking, bending and forming meets the part of type face requirement.
(2) it is machined out after skeleton casting according to designing a model, skeleton is designed with passage at wing root.
(3) position for being diffused connection is needed to be polished on skeleton and covering, it is desirable to surface roughness at least 3.2.
(4) covering periphery and the sagging position of skeleton are subjected to electron beam welding, closed cavity are internally formed, in forming process
In can from passage to covering inside load air pressure.
(5) by the good covering skeleton part surface spraying antioxidant of soldering and sealing, rationally assembled with diffusion connecting mold,
And be put into equipment and heated up.
(6) matched moulds on-load pressure after design temperature is reached, covering is diffused with skeleton contact position and is connected, to prevent compression
Excessive influence accessory size is measured, the limited block of Rational Thickness can be set between upper/lower die.To prevent from spreading connection procedure
Middle covering softening is collapsed, and argon gas is loaded by carrying out hole in covering internal layer.
(7) by cooling after the completion of the diffusion connection of regular hour part, reach reasonable temperature and take out part, and be put into down
One missile wing part is formed.
The lightweight missile wing part skeleton improves rib size, and rib is on the premise of the not unstability that is pressurized, and width can
To be designed as (2-5) mm.
The closure tonnage can be calculated by unit pressure and the diffusion connection area of covering and skeleton and obtained, TA15 titaniums
Parameter is as follows exemplified by alloy missile wing：Temperature is (925 ± 5) DEG C, and compressive load per unit area is (8-10) Mpa, and the diffusion Connection Time is big
About 120min.
The air pressure inside loading can be controlled in (0.1-0.2) Mpa, and unloading air pressure adds after the completion of diffusion connection
Carry.
Beneficial effect
(1) it can realize that large scale missile wing part covering skeleton integrally spreads connection there is provided technical scheme and improves work
Skill flow.
(2) the missile wing weight mitigated significantly compared to traditional skeleton covering spot-welded structures missile wing.The connection shape of covering and skeleton
Formula is changed into face connection from a contact, increases missile wing load ability.
(3) superplastic forming ＆ diffusion bonding structure missile wing is compared, technological process is simpler, improves product qualification rate and life
Efficiency is produced, production in enormous quantities can be realized.
Brief description of the drawings
Fig. 1 integrally spreads union piece for the lightweight covering skeleton of the invention to be shaped；
Fig. 2 is missile wing part covering and skeleton schematic diagram；
Fig. 3 is skeleton schematic diagram；
Fig. 4 is overall diffusion connecting framework missile wing mould schematic diagram.
In figure：1-- coverings, 2-- skeletons, 3-- passages, 4-- skeleton ribs, 5-- missile wings integrally spread connecting mold,
6-- coverings skeleton integrally spreads connection missile wing.
Embodiment
To make the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to the tool of the present invention
Body embodiment is described in further detail.The lightweight covering skeleton missile wing part that the present invention is provided integrally spreads connection side
Method, comprises the following steps：
(1) skin part blanking, bending and forming meets the part of type face requirement.
(2) it is machined out after skeleton casting according to designing a model, skeleton is designed with passage at wing root.
(3) position for being diffused connection is needed to be polished on skeleton and covering, it is desirable to surface roughness at least 3.2.
(4) covering periphery and the sagging position of skeleton are subjected to electron beam welding, closed cavity are internally formed, in forming process
In can from passage to covering inside load air pressure.
(5) by the good covering skeleton part surface spraying antioxidant of soldering and sealing, rationally assembled with diffusion connecting mold,
And be put into equipment and heated up.
(6) matched moulds on-load pressure after design temperature is reached, covering is diffused with skeleton contact position and is connected, to prevent compression
Excessive influence accessory size is measured, the limited block of Rational Thickness can be set between upper/lower die.To prevent from spreading connection procedure
Middle covering softening is collapsed, and argon gas is loaded by carrying out hole in covering internal layer.
(7) by cooling after the completion of the diffusion connection of regular hour part, reach reasonable temperature and take out part, and be put into down
One missile wing part is formed.
As shown in figure 1, for using the present invention manufacture lightweight missile wing part, material be TA15 titanium alloys, accessory size compared with
Long length 1200mm, width 380mm or so.
Such as Fig. 2 is covering and skeleton schematic diagram, in order to which further loss of weight covering carries out milling diffusion junction thickness 1.2,
Remaining is 0.8.Skeleton strengthening rib strip width design is 4mm, significantly reduces missile wing weight.
Covering periphery and skeleton are subjected to soldering and sealing, and weld vent line, load facility is carried out after being assembled with mould
Heating.925 DEG C of design temperature, reaches and starts to start diffusion connection procedure after temperature, mould matched moulds pressurization tonnage is unit area
Covering skeletal internal air pressure-loading after 9Mpa, mould matched moulds, pressure is 0.2MPa.The whole diffusion Connection Time is set as
Start cooling after the completion of 120min, shaping, temperature is reduced to after 650 DEG C -700 DEG C, part is taken out in blow-on.
Claims (1)
1. a kind of lightweight covering skeleton missile wing integrally spreads joint forming method, it is characterised in that comprise the following steps：
(1) skin part blanking, bending and forming meets the part of type face requirement；
(2) it is machined out after skeleton casting according to designing a model, skeleton is designed with passage at wing root；
(3) position for being diffused connection is needed to be polished on skeleton and covering, it is desirable to surface roughness at least 3.2；
(4) covering periphery and skeleton position of sinking are subjected to electron beam welding, are internally formed closed cavity, in forming process from
Passage loads air pressure to covering inside；
(5) by the good covering skeleton part surface spraying antioxidant of soldering and sealing, rationally assembled with diffusion connecting mold, and put
Enter equipment to be heated up；
(6) matched moulds on-load pressure after design temperature is reached, covering is diffused with skeleton contact position and is connected, and skeleton rib width is
2-4mm, temperature is 925 ± 5 DEG C, and compressive load per unit area is 8-10Mpa, and the diffusion Connection Time is between 120min, upper/lower die
Limited block is set, argon gas is loaded by carrying out hole in covering internal layer, air pressure inside is 0.1-0.2Mpa；
(7) cool after the completion of part diffusion connection, take out part, and be put into next missile wing part and be formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510518844.XA CN105057990B (en) | 2015-08-21 | 2015-08-21 | A kind of lightweight covering skeleton missile wing integrally spreads joint forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510518844.XA CN105057990B (en) | 2015-08-21 | 2015-08-21 | A kind of lightweight covering skeleton missile wing integrally spreads joint forming method |
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| Publication Number | Publication Date |
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| CN105057990A CN105057990A (en) | 2015-11-18 |
| CN105057990B true CN105057990B (en) | 2017-08-25 |
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| CN201510518844.XA Active CN105057990B (en) | 2015-08-21 | 2015-08-21 | A kind of lightweight covering skeleton missile wing integrally spreads joint forming method |
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| CN106425309A (en) * | 2016-11-14 | 2017-02-22 | 北京星航机电装备有限公司 | Method for machining and manufacturing titanium alloy folding airfoils |
| 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 |
| CN108225120B (en) * | 2018-01-09 | 2019-08-16 | 北京航空航天大学 | Frame-covering structure missile wing |
| CN109434380B (en) * | 2018-11-05 | 2020-11-13 | 北京星航机电装备有限公司 | Variable-thickness lightweight missile wing skin forming method |
| 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 |
| CN110625335B (en) * | 2019-09-02 | 2020-05-26 | 北京星航机电装备有限公司 | Welding deformation control method for high-aspect-ratio framework skin wing type component |
| CN110587103B (en) * | 2019-09-27 | 2021-05-11 | 中国航空制造技术研究院 | Welding method of ultrahigh-strength steel multi-cavity structure based on stress discrete distribution |
| CN110539138B (en) * | 2019-09-30 | 2020-07-28 | 北京星航机电装备有限公司 | Preparation method of aluminum alloy lightweight active cooling structural skin |
| CN113997014B (en) * | 2021-10-29 | 2022-12-06 | 北京星航机电装备有限公司 | Integrated forming method for titanium alloy skin with installation part |
| CN113997015B (en) * | 2021-10-29 | 2022-12-06 | 北京星航机电装备有限公司 | Variable-thickness titanium alloy skin integrated forming method |
| CN114136156B (en) * | 2021-12-09 | 2024-04-26 | 北京星航机电装备有限公司 | Preparation method of wing rudder with hollow grid structure |
| 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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| CN105057990A (en) | 2015-11-18 |
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