CN109532036B - Full composite material wing glue joint method and full composite material wing - Google Patents
Full composite material wing glue joint method and full composite material wing Download PDFInfo
- Publication number
- CN109532036B CN109532036B CN201811422360.5A CN201811422360A CN109532036B CN 109532036 B CN109532036 B CN 109532036B CN 201811422360 A CN201811422360 A CN 201811422360A CN 109532036 B CN109532036 B CN 109532036B
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- Prior art keywords
- wing
- composite material
- skin
- lower skin
- full
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/78—Means for handling the parts to be joined, e.g. for making containers or hollow articles, e.g. means for handling sheets, plates, web-like materials, tubular articles, hollow articles or elements to be joined therewith; Means for discharging the joined articles from the joining apparatus
- B29C65/7802—Positioning the parts to be joined, e.g. aligning, indexing or centring
- B29C65/7805—Positioning the parts to be joined, e.g. aligning, indexing or centring the parts to be joined comprising positioning features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/80—General aspects of machine operations or constructions and parts thereof
- B29C66/84—Specific machine types or machines suitable for specific applications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
Abstract
The invention relates to a full composite material wing glue joint method and a full composite material wing, wherein the glue joint method comprises the following steps: firstly, placing a lower skin on a jig made of composite materials, and positioning and fixing the lower skin through lugs and positioning holes; then, gluing a front wing beam and a rear wing beam on the lower skin through adhesives; gluing wing ribs on the lower skin through an adhesive; and finally, fixing the upper skin on an upper die of an assembly tool, coating adhesives on the front beam, the rear beam and the wing ribs of the wing, closing the die and completing glue joint. Therefore, the prepared wing can be made of the composite material frame as a main bearing part, a foundation is laid for civil aviation airworthiness of domestic full-composite material main bearing members, compared with the traditional wing with a metal structure, the wing with the composite material frame has the advantages of few tools, parts and fasteners, and meanwhile, the glued connection mode has the advantage of uniform stress distribution, so that the purpose of reducing the weight of the structure by 30% is achieved, the production cost is reduced, the production period is shortened, and the product quality can be improved.
Description
Technical Field
The invention belongs to the technical field of airplane processing, and particularly relates to a full composite material wing glue joint method and a full composite material wing.
Background
At present, in the aircraft manufacturing industry at home and abroad, the wings of the aircraft all adopt a metal structure (a metal frame) as a main bearing part, the metal structure is formed by assembling a plurality of metal parts through riveting or bolt fasteners, the weight is heavy, the number of the parts is large, and the production period is long, so that the production cost of the product is obviously improved and the production period is greatly prolonged.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a full composite material wing bonding method which realizes the application of a composite material as a main bearing part, has the advantages of few tools, parts and fasteners, uniform stress distribution, weight reduction of up to 30 percent, low production cost and short production period, and a full composite material wing processed by the bonding method.
In order to solve the technical problem, the invention adopts the following technical scheme:
a method for gluing wings made of full composite materials,
firstly, placing a lower skin on a jig made of composite materials, and positioning and fixing the lower skin through lugs and positioning holes;
then, gluing a front beam and a rear beam of the wing on the lower skin through an adhesive;
gluing wing ribs on the lower skin by using an adhesive;
and finally, fixing the upper skin on an upper die of an assembly tool, coating adhesives on the front beam, the rear beam and the wing ribs of the wing, closing the die and completing glue joint.
Furthermore, the thicknesses of the adhesives of the front beam, the rear beam and the wing ribs of the wing, and the lower skin and the upper skin are 0.2 mm-2 mm.
Furthermore, when the front beam, the rear beam and the wing ribs of the wing are glued with the lower skin and the upper skin, the temperature is 15-26 ℃, and the humidity is not lower than 65%.
And further, placing the lower skin on a jig made of composite materials, and placing a laminating object on the lower skin to enable the lower skin to be attached to the jig when positioning and fixing are carried out through the lugs and the positioning holes.
The full-composite wing comprises a frame made of composite materials, an upper skin and a lower skin, wherein the upper skin and the lower skin are respectively paved on the upper side and the lower side of the frame and are fixed through adhesive bonding.
The invention has the main beneficial effects that:
by adopting the technical scheme, the composite material forming frame can be used as the main bearing part, the application of the composite material on the main bearing part is realized, the foundation is laid for domestic civil aviation airworthiness of the full composite material main bearing member, and compared with the traditional metal structure wing, the composite material wing has the advantages of fewer tools, parts and fasteners, and meanwhile, the glued connection mode has the advantage of uniform stress distribution, so that the purpose of reducing the weight of the structure by 30 percent is achieved, the production cost and the production period are reduced, and the product quality can be improved.
Drawings
FIG. 1 is a schematic flow chart of an embodiment of a method for bonding an all-composite airfoil according to the present invention;
fig. 2 is a schematic structural view of an all-composite airfoil according to the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in fig. 1 and 2:
the full composite material wing glue joint method comprises a frame 1, an upper skin (not shown in the figure) and a lower skin 2, wherein the frame 1 is made of composite materials, the frame is made of composite material parts such as a wing front beam 11, a wing rear beam 12 and a wing rib 13 in an integral co-curing mode, and the upper skin and the lower skin 2 are respectively paved on the upper side and the lower side of the frame and are glued and fixed through adhesives. The specific gluing method comprises the following steps: firstly, placing a lower skin 2 on a jig 1 made of composite materials, and positioning and fixing the lower skin through lugs and positioning holes; then, gluing a front wing beam 11 and a rear wing beam 12 on the lower skin 2 through adhesives; then, gluing the wing ribs 13 on the lower skin 2 through an adhesive; and finally, fixing the upper skin on an upper die of an assembly tool, coating adhesives on the front wing beam 11, the rear wing beam 12 and the wing ribs 13, closing the dies and completing gluing. The thicknesses of the adhesives of the wing front beam 11, the wing rear beam 12 and the wing rib 13, the lower skin 2 and the upper skin are preferably 0.2 mm-2 mm, and when the wing front beam 11, the wing rear beam 12 and the wing rib 13 are glued with the lower skin 2 and the upper skin, the temperature is 15-26 ℃, and the humidity is not lower than 65%.
Therefore, the full composite material wing can use the composite material frame as the main bearing part, realizes the application of the composite material on the main bearing part (the structural consumption of the composite material on the airplane exceeds 90 percent), lays a foundation for civil aviation airworthiness of domestic full composite material main bearing members, and compared with the traditional metal structure wing, has the advantages of less tools, parts and fasteners, and simultaneously has the advantage of uniform stress distribution in a bonding connection mode, thereby achieving the purpose of reducing the weight of the structure by 30 percent, reducing the production cost and the production period and simultaneously improving the quality of the product.
In addition, when the lower skin 2 is placed on the jig 1 made of the composite material and is positioned and fixed through the lugs and the positioning holes, a pressing member (such as a sand bag) is placed on the lower skin 2, so that the lower skin 2 can be better attached to the jig 1.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention.
Claims (1)
1. A full composite material wing glue joint method is characterized in that the full composite material wing comprises a frame, an upper skin and a lower skin which are made of composite materials; the profile frame is used as a main bearing part and is manufactured by a wing front beam, a wing rear beam and a wing rib composite material part in an integral co-curing mode; the upper skin and the lower skin are respectively laid on the upper side and the lower side of the jig and are fixed by adhesive in a bonding way;
the glue joint method of the full composite material wing specifically comprises the following steps:
firstly, placing a lower skin on a jig made of composite materials, positioning and fixing the lower skin through lugs and positioning holes, and simultaneously placing a laminating material on the lower skin to enable the lower skin to be attached to the jig;
then, gluing a front beam and a rear beam of the wing on the lower skin through an adhesive;
gluing wing ribs on the lower skin by using an adhesive;
finally, fixing the upper skin on an upper die of an assembly tool, coating adhesives on a front wing beam, a rear wing beam and wing ribs, closing the dies and completing gluing;
the thickness of the adhesive between the front wing beam, the rear wing beam and the wing rib of the wing and the lower skin and the upper skin is 0.2-2 mm, and when the front wing beam, the rear wing beam and the wing rib of the wing are glued with the lower skin and the upper skin, the temperature is 15-26 ℃, and the humidity is not lower than 65%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811422360.5A CN109532036B (en) | 2018-11-27 | 2018-11-27 | Full composite material wing glue joint method and full composite material wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811422360.5A CN109532036B (en) | 2018-11-27 | 2018-11-27 | Full composite material wing glue joint method and full composite material wing |
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| Publication Number | Publication Date |
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| CN109532036A CN109532036A (en) | 2019-03-29 |
| CN109532036B true CN109532036B (en) | 2022-07-15 |
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| CN201811422360.5A Active CN109532036B (en) | 2018-11-27 | 2018-11-27 | Full composite material wing glue joint method and full composite material wing |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111745985A (en) * | 2020-07-09 | 2020-10-09 | 中航通飞华南飞机工业有限公司 | Full-composite material aileron glue joint method and full-composite material aileron |
| CN111762336A (en) * | 2020-07-09 | 2020-10-13 | 中航通飞华南飞机工业有限公司 | Full-composite material flap and gluing method thereof |
| CN111907087B (en) * | 2020-07-10 | 2022-02-01 | 航天特种材料及工艺技术研究所 | Forming assembly tool and manufacturing method for composite unmanned aerial vehicle horizontal tail |
| CN115416392A (en) * | 2022-09-22 | 2022-12-02 | 中国航空制造技术研究院 | Glue joint deformation control method for composite material sandwich structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03104799A (en) * | 1989-09-20 | 1991-05-01 | Fuji Heavy Ind Ltd | Manufacture of composite material blade |
| CN103448901A (en) * | 2012-05-30 | 2013-12-18 | 波音公司 | Bonded composite airfoil and fabrication method |
| 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 |
| CN105508142A (en) * | 2014-10-15 | 2016-04-20 | 株洲时代新材料科技股份有限公司 | Multi-girder structure large size wind power blade and production method thereof |
| CN108454820A (en) * | 2018-02-08 | 2018-08-28 | 珠海诚然科技服务有限公司 | A kind of integrated compound girder construction of unmanned plane wing |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8851422B2 (en) * | 2012-08-28 | 2014-10-07 | The Boeing Company | Bonded composite aircraft wing |
| US10391751B2 (en) * | 2016-04-20 | 2019-08-27 | The Boeing Company | Spatial reference film in core-stiffened composite |
| CN108216570B (en) * | 2017-12-14 | 2023-08-18 | 中航(成都)无人机系统股份有限公司 | Main wing surface structure of high aspect ratio wing |
-
2018
- 2018-11-27 CN CN201811422360.5A patent/CN109532036B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03104799A (en) * | 1989-09-20 | 1991-05-01 | Fuji Heavy Ind Ltd | Manufacture of composite material blade |
| CN103448901A (en) * | 2012-05-30 | 2013-12-18 | 波音公司 | Bonded composite airfoil and fabrication method |
| CN105508142A (en) * | 2014-10-15 | 2016-04-20 | 株洲时代新材料科技股份有限公司 | Multi-girder structure large size wind power blade and production method thereof |
| 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 |
| CN108454820A (en) * | 2018-02-08 | 2018-08-28 | 珠海诚然科技服务有限公司 | A kind of integrated compound girder construction of unmanned plane wing |
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| CN109532036A (en) | 2019-03-29 |
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