CN105057990A - Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework - Google Patents
Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework Download PDFInfo
- Publication number
- CN105057990A CN105057990A CN201510518844.XA CN201510518844A CN105057990A CN 105057990 A CN105057990 A CN 105057990A CN 201510518844 A CN201510518844 A CN 201510518844A CN 105057990 A CN105057990 A CN 105057990A
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- skeleton
- covering
- missile wing
- framework
- diffusion
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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
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- 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
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- 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 invention provides a lightweight missile wing with the integral diffusion bonding structure of an envelope and a framework and a forming method of the missile wing. By means of the structural mode of the missile wing, ribs of the framework can be distributed according to the greatest bearing strength effect, ribs inside the framework can be narrower and can be 2-4 mm, and accordingly the weight of the missile wing can be greatly reduced. The method includes the steps that the peripheries are welded with electronic beams after the envelope and the framework fit with each other, the envelope and framework blank is placed in a die and a thermoforming device to be heated, the die is closed when the set temperature is reached, proper pressure is loaded, and the envelope and the framework are pressed for a certain period in a contact mode to achieve diffusion bonding. By means of the structural mode, the weight of the missile wing can be greatly reduced, the bearing capacity is improved, and dimensional precision is high.
Description
Technical field
The invention belongs to Precision Forming Technology field, be specifically related to the overall diffusion connection method of a kind of lightweight covering skeleton missile wing part.
Background technology
Lightweight structure obtains applying more and more widely in field of aerospace, tradition missile wing part adopts frame-covering structure mostly, but this type of Titanium Alloy Wing part manufacture process is: skeleton machining, the cold bending and forming of covering, covering periphery and frame welding, covering and the position spot welding of skeleton rib.But due to spot-welding technology, skeleton rib width is restricted, and rib width at least 10mm, affects the weight of missile wing part.And other lightweight missile wing design of part form is as superplastic forming & diffusion bonding structure, although good weight loss effect can be obtained, but because technology difficulty is larger, the factor of the aspects such as the low and production efficiency of product percent of pass is low, is not used in enormous quantities at aerospace field.
Summary of the invention
The present invention proposes the overall diffusion bonding structure missile wing of a kind of covering skeleton, the distribution of skeleton rib can design according to maximum load effect by this kind of missile wing version, skeletal internal rib width can be designed as narrower rib form (2-4) mm, can greatly alleviate missile wing weight like this, covering and skeleton are realized spreading be connected after can form the lightweight missile wing part meeting instructions for use.
The technical problem that the present invention solves is the overall diffusion connection method of titanium alloy lightweight missile wing part, missile wing Element Design is frame-covering structure, skeleton rib is according to principle height aspect not producing unstability, what width can design is as far as possible narrow, skeleton leaves passage and is connected with vent line.Covering and skeleton are equipped suitable rear perimeter edge electron beam and are welded, and form closed cavity.Covering skeleton blank loads mould, puts into heat forming equipment and heats up.Arrive matched moulds after design temperature and also load convenient pressure, covering contacts the certain hour that pressurizes and realizes spreading and connect, in the process in order to prevent covering to be collapsed upon inside parts loading air pressure with skeleton.Start cooling after part diffusion connection completes, after cooling, take out part.
Concrete techniqueflow is as follows:
(1) skin part blanking, bending and forming meets the part that profile requires.
(2) carry out machine according to designing a model after skeleton casting to add, skeleton is designed with passage at wing root place.
(3) skeleton and covering are needed to carry out spreading the position be connected and carry out polishing, require surface roughness at least 3.2.
(4) electron beam welding is carried out at position of covering periphery and skeleton being sunk, and innerly forms closed cavity, can load air pressure in forming process from passage to covering inside.
(5) by covering skeleton part surface spraying antioxidant good for soldering and sealing, rationally assemble with diffusion connecting mold, and equipment of putting into heats up.
(6) matched moulds on-load pressure after arrival design temperature, covering and skeleton contact position are carried out diffusion and are connected, and in order to prevent, decrement is excessive affects accessory size, can arrange the limited block of Rational Thickness between upper/lower die.Subsiding for preventing covering in diffusion connection procedure from softening, loading argon gas at covering internal layer by carrying out hole.
(7) cooling after the regular hour, part diffusion connection completed, arrives reasonable temperature and takes out part, and put into next missile wing part and form.
Described lightweight missile wing part skeleton improves rib size, rib under the prerequisite of pressurized not unstability, width can be designed as (2-5) mm.
Described closure tonnage can be calculated by the diffusion connection area of unit pressure and covering and skeleton, TA15 Titanium Alloy Wing is that example parameter is as follows: temperature is (925 ± 5) DEG C, compressive load per unit area is (8-10) Mpa, and the diffusion connect hours is approximately 120min.
Described air pressure inside loads and can control at (0.1-0.2) Mpa, and unloads air pressure-loading after diffusion connection completes.
Beneficial effect
(1) diffusion of large scale missile wing part covering skeleton entirety can be realized connect, provide technical scheme and replenishment of process flow process.
(2) the missile wing weight that traditional skeleton covering spot-welded structures missile wing alleviates greatly is compared.Covering becomes face with the type of attachment of skeleton from point cantact and is connected, and increases missile wing load ability.
(3) compare superplastic forming & diffusion bonding structure missile wing, technological process is more simple, improves product percent of pass and production efficiency, can realize producing in enormous quantities.
Accompanying drawing explanation
The lightweight covering skeleton entirety diffusion union piece that Fig. 1 will be shaped for the present invention;
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--covering, 2--skeleton, 3--passage, 4--skeleton rib, 5--missile wing entirety diffusion connecting mold, the diffusion of 6--covering skeleton entirety connect missile wing.
Detailed description of the invention
For making object of the present invention, content and advantage clearly, below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.The overall diffusion connection method of lightweight covering skeleton missile wing part provided by the invention, comprises the following steps:
(1) skin part blanking, bending and forming meets the part that profile requires.
(2) carry out machine according to designing a model after skeleton casting to add, skeleton is designed with passage at wing root place.
(3) skeleton and covering are needed to carry out spreading the position be connected and carry out polishing, require surface roughness at least 3.2.
(4) electron beam welding is carried out at position of covering periphery and skeleton being sunk, and innerly forms closed cavity, can load air pressure in forming process from passage to covering inside.
(5) by covering skeleton part surface spraying antioxidant good for soldering and sealing, rationally assemble with diffusion connecting mold, and equipment of putting into heats up.
(6) matched moulds on-load pressure after arrival design temperature, covering and skeleton contact position are carried out diffusion and are connected, and in order to prevent, decrement is excessive affects accessory size, can arrange the limited block of Rational Thickness between upper/lower die.Subsiding for preventing covering in diffusion connection procedure from softening, loading argon gas at covering internal layer by carrying out hole.
(7) cooling after the regular hour, part diffusion connection completed, arrives reasonable temperature and takes out part, and put into next missile wing part and form.
As shown in Figure 1, for adopting the present invention to manufacture lightweight missile wing part, material is TA15 titanium alloy, accessory size greater depth 1200mm, width about 380mm.
If Fig. 2 is covering and skeleton schematic diagram, in order to further loss of weight covering carries out milling diffusion junction thickness 1.2, all the other are 0.8.Skeleton strengthening rib strip width design is 4mm, significantly reduces missile wing weight.
Covering periphery and skeleton are carried out soldering and sealing, and welds vent line, carry out assembling rear load facility with mould and heat up.Design temperature 925 DEG C, starts after arriving temperature to start diffusion connection procedure, and mould matched moulds pressurization tonnage is unit area 9Mpa, and covering skeletal internal air pressure-loading after mould matched moulds, pressure is 0.2MPa.The whole diffusion connect hours is set as 120min, starts cooling after being shaped, and after temperature is reduced to 650 DEG C-700 DEG C, part is taken out in blow-on.
Claims (1)
1. a lightweight covering skeleton missile wing entirety diffusion joint forming method, is characterized in that, comprise the following steps:
(1) skin part blanking, bending and forming meets the part that profile requires;
(2) carry out machine according to designing a model after skeleton casting to add, skeleton is designed with passage at wing root place;
(3) skeleton and covering are needed to carry out spreading the position be connected and carry out polishing, require surface roughness at least 3.2;
(4) electron beam welding is carried out at position of covering periphery and skeleton being sunk, and innerly forms closed cavity, in forming process, load air pressure from passage to covering inside;
(5) by covering skeleton part surface spraying antioxidant good for soldering and sealing, rationally assemble with diffusion connecting mold, and equipment of putting into heats up;
(6) matched moulds on-load pressure after arrival design temperature, covering and skeleton contact position are carried out diffusion and are connected, skeleton rib width is 2-4mm, temperature is 925 ± 5 DEG C, compressive load per unit area is 8-10Mpa, and the diffusion connect hours is 120min, arranges limited block between upper/lower die, load argon gas at covering internal layer by carrying out hole, air pressure inside is 0.1-0.2Mpa;
(7) part diffusion connection complete after cooling, take out part, and put into next missile wing part and form.
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 |
Publications (2)
| Publication Number | Publication Date |
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| CN105057990A true CN105057990A (en) | 2015-11-18 |
| CN105057990B 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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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN108225120A (en) * | 2018-01-09 | 2018-06-29 | 北京航空航天大学 | Frame-covering structure missile wing |
| 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 |
| CN110587103A (en) * | 2019-09-27 | 2019-12-20 | 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 |
| CN110625335A (en) * | 2019-09-02 | 2019-12-31 | 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 |
| 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 |
| CN113997014A (en) * | 2021-10-29 | 2022-02-01 | 北京星航机电装备有限公司 | Integrated forming method for titanium alloy skin with mounting part |
| CN113997015A (en) * | 2021-10-29 | 2022-02-01 | 北京星航机电装备有限公司 | Variable-thickness titanium alloy skin integrated forming method |
| CN114136156A (en) * | 2021-12-09 | 2022-03-04 | 北京星航机电装备有限公司 | Preparation method of wing rudder with hollow grid structure |
| 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 (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN108225120A (en) * | 2018-01-09 | 2018-06-29 | 北京航空航天大学 | Frame-covering structure missile wing |
| 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 |
| 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 |
| CN110625335A (en) * | 2019-09-02 | 2019-12-31 | 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 |
| CN110587103A (en) * | 2019-09-27 | 2019-12-20 | 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 |
| 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 |
| CN113997014A (en) * | 2021-10-29 | 2022-02-01 | 北京星航机电装备有限公司 | Integrated forming method for titanium alloy skin with mounting part |
| CN113997015A (en) * | 2021-10-29 | 2022-02-01 | 北京星航机电装备有限公司 | Variable-thickness titanium alloy skin integrated forming method |
| CN114136156A (en) * | 2021-12-09 | 2022-03-04 | 北京星航机电装备有限公司 | Preparation method of wing rudder with hollow grid structure |
| 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 |
| 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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