CN107128508B - A kind of straight wing forming method - Google Patents
A kind of straight wing forming method Download PDFInfo
- Publication number
- CN107128508B CN107128508B CN201710266353.XA CN201710266353A CN107128508B CN 107128508 B CN107128508 B CN 107128508B CN 201710266353 A CN201710266353 A CN 201710266353A CN 107128508 B CN107128508 B CN 107128508B
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- Prior art keywords
- wing
- girder
- support construction
- hot hole
- metal material
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Abstract
A kind of straight wing forming method of the present invention belongs to aircraft manufacturing technical field.Technical solution of the present invention: firstly, being designed to the wing to be manufactured, corresponding mold then is produced according to airfoil cross-section.Finally, heating the material to the recrystallization temperature of the material using hot hole extrusion process, then under the uneven action of compressive stress of three-dimensional, squeeze out material from the aperture of mold or gap, final molding.It is an advantage of the invention that wing one-pass molding, does not need individually to process part, improves manufacturing speed；Using hot hole extrusion forming, no waste of material；The auxiliary moulds such as type frame are not needed, cost has been saved, and facilitate remodeling；Wing one-pass molding does not need secondary assembly, saves cost of labor, while itself is whole, intensity improves.
Description
Technical field
A kind of straight wing forming method of the present invention belongs to aircraft manufacturing technical field.
Background technique
Traditional wing manufacturing method is, first using the method for machining, to produce the wings such as rib, girder, leading edge
Then structural member is matched each part in the enterprising luggage of assembly jig by riveting process.Pacify in the wing frame assembled again
Fill wing tank and a pipeline.Again by sheet metal process, wing cover is produced, riveting assembly is then carried out.This mode
Be disadvantageous in that: needs are machined each part, and working efficiency is lower, and progress is slower；Most parts take cutting
Processing, stock utilization is lower, wastes lot of materials；Need the Operational preparations equipment such as a large amount of molds and type frame, early-stage preparations
Time is longer, and is not easy midway and changes；Most of to use riveting process, cost of labor is excessively high；It can only be using drawing in enclosure space
Fourth of the twelve Earthly Branches technique, intensity are lower；Higher to operator's technical requirements, total quality is unstable.
Summary of the invention
The object of the invention: being to provide that a kind of simple process, save the cost, efficiency is higher, operation is simple for Field of Aviation Manufacturing
Just, the stable wing manufacturing method of quality.
Technical solution of the present invention: a kind of straight wing forming method, the method take following steps:
(1) aircraft wing structure is designed, in wing interior design wing support construction, wing support construction is along machine
The spanwise of the wing is arranged, and inside wing；Wing support construction includes girder parallel to each other, the back rest, if girder, after
The distance between beam adds several auxiliary beams between girder, the back rest farther out, then, and auxiliary beam is also arranged along the spanwise of wing, and
Inside wing, and it is parallel with girder；
(2) according to the cross sectional shape perpendicular to wing girder direction of aircraft wing, wing support construction and wing are made
The hot hole extrusion molding dies of covering can make minor adjustment according to the property and parameter of different materials.
(3) after metal material being heated to recrystallization temperature, with press machine by the metal material after heating from the hot hole
It is squeezed out in extrusion molding dies, after the metal material cooling and solidifying after extrusion, forms the one of wing support construction and wing cover
Body structure.
The invention has the advantages that
1) wing one-pass molding does not need individually to process part, improves manufacturing speed.
2) hot hole extrusion forming, no waste of material are used.
3) auxiliary moulds such as type frame are not needed, cost has been saved, and facilitate remodeling.
4) wing one-pass molding does not need secondary assembly, saves cost of labor, while itself is whole, intensity improves.
5) enclosure space one-pass molding does not need later-stage secondary processing.
6) numerical control of manufacturing process whole process is completed, and quality is stable, controllable.
Detailed description of the invention
Fig. 1 is hot hole extrusion die cross section
Fig. 2 is finished product isometric views
Specific embodiment
The present invention will be described in detail with reference to the accompanying drawing.
A kind of straight wing forming method, the method take following steps:
(1) aircraft wing structure is designed, in wing interior design wing support construction, wing support construction is along machine
The spanwise of the wing is arranged, and inside wing；Wing support construction includes girder parallel to each other, the back rest, if girder, after
The distance between beam adds several auxiliary beams between girder, the back rest farther out, then, and auxiliary beam is also arranged along the spanwise of wing, and
Inside wing, and it is parallel with girder；In the position of important guarantee shape, bearing diagonal can be increased, to guarantee shape,
In rudder face and wing link position, setting support can directly intercept rudder face on finished product wing.
(2) according to the cross sectional shape perpendicular to wing girder direction of aircraft wing, wing support construction and wing are made
The hot hole extrusion molding dies of covering；
(3) after metal material being heated to recrystallization temperature, with press machine by the metal material after heating from the hot hole
It is squeezed out in extrusion molding dies, after the metal material cooling and solidifying after extrusion, forms the one of wing support construction and wing cover
Body structure.
Embodiment one
Wing cover is designed as 1mm thickness, main beam design 1/3rd positions before wing chord length, thickness 5mm；The back rest is set
Meter one third position, thickness 5mm after wing chord length；Girder is parallel with the back rest；It is parallel with girder between girder and the back rest
Two auxiliary cantilever thickness 2mm are set；In back rest rear direction, two auxiliary cantilever thickness 2mm are arranged in parallel with auxiliary beam；Wherein close to the back rest
The setting of auxiliary beam in rudder face and wing junction, convenient directly interception rudder face；In girder close to leading edge side, auxiliary beam is set；Together
When the bearing diagonal of covering is extended out on the auxiliary beam, to guarantee that skins front edges are indeformable.Then, hanging down according to aircraft wing
Directly in the cross sectional shape in wing girder direction, the hot hole extrusion molding dies of wing support construction and wing cover are made.Using
The magnesium-aluminium alloy material of Chengdu Qing Yuanfan magnesium company production, is heated to recrystallization temperature, using 500 tonnes of press machines, will heat
Metal material afterwards is squeezed out from the hot hole extrusion molding dies, after the metal material cooling and solidifying after extrusion, forms wing
The integral structure of support construction and wing cover.
Claims (1)
1. a kind of straight wing forming method, which is characterized in that the method takes following steps:
(1) aircraft wing structure is designed, in wing interior design wing support construction, wing support construction is along wing
Spanwise setting, and inside wing；Wing support construction includes girder parallel to each other, the back rest, if girder, the back rest it
Between distance farther out, then add several auxiliary beams between girder, the back rest, auxiliary beam is also arranged along the spanwise of wing, and runs through
Inside wing, and it is parallel with girder；
(2) according to the cross sectional shape perpendicular to wing girder direction of aircraft wing, wing support construction and wing cover are made
Hot hole extrusion molding dies；
(3) after metal material being heated to recrystallization temperature, the metal material after heating is squeezed from the hot hole with press machine
It is squeezed out in molding die, after the metal material cooling and solidifying after extrusion, forms the one knot of wing support construction and wing cover
Structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710266353.XA CN107128508B (en) | 2017-04-21 | 2017-04-21 | A kind of straight wing forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710266353.XA CN107128508B (en) | 2017-04-21 | 2017-04-21 | A kind of straight wing forming method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107128508A CN107128508A (en) | 2017-09-05 |
| CN107128508B true CN107128508B (en) | 2019-11-15 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710266353.XA Active CN107128508B (en) | 2017-04-21 | 2017-04-21 | A kind of straight wing forming method |
Country Status (1)
| Country | Link |
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| CN (1) | CN107128508B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112792152A (en) * | 2020-12-14 | 2021-05-14 | 北京航星机器制造有限公司 | Skin extrusion cold-pressing air-bulging forming method with active cooling channel |
| CN112977802A (en) * | 2021-02-26 | 2021-06-18 | 珠海天晴航空航天科技有限公司 | Integrated control surface connecting structure, manufacturing method and unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2495836Y (en) * | 2001-04-24 | 2002-06-19 | 胡德诚 | Airplane wing like blade made of composite material |
| US6513757B1 (en) * | 1999-07-19 | 2003-02-04 | Fuji Jukogyo Kabushiki Kaisha | Wing of composite material and method of fabricating the same |
| CN101342942B (en) * | 2008-08-21 | 2011-01-12 | 马献林 | Disposal solidifying and forming technique for frame and outer panel skin of wing profile |
| CN103342167A (en) * | 2013-05-18 | 2013-10-09 | 大连理工大学 | Method for making scaled composite material wing model |
| CN103407173A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Integrally-forming method of wing made of fiber reinforced resin matrix composites |
| CN105398563A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Wing of membrane structure |
-
2017
- 2017-04-21 CN CN201710266353.XA patent/CN107128508B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6513757B1 (en) * | 1999-07-19 | 2003-02-04 | Fuji Jukogyo Kabushiki Kaisha | Wing of composite material and method of fabricating the same |
| CN2495836Y (en) * | 2001-04-24 | 2002-06-19 | 胡德诚 | Airplane wing like blade made of composite material |
| CN101342942B (en) * | 2008-08-21 | 2011-01-12 | 马献林 | Disposal solidifying and forming technique for frame and outer panel skin of wing profile |
| CN103342167A (en) * | 2013-05-18 | 2013-10-09 | 大连理工大学 | Method for making scaled composite material wing model |
| CN103407173A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Integrally-forming method of wing made of fiber reinforced resin matrix composites |
| CN105398563A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Wing of membrane structure |
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| Publication number | Publication date |
|---|---|
| CN107128508A (en) | 2017-09-05 |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |