CN201914456U - Aerofoil structure with high aspect ratio - Google Patents
Aerofoil structure with high aspect ratio Download PDFInfo
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- CN201914456U CN201914456U CN2010206771382U CN201020677138U CN201914456U CN 201914456 U CN201914456 U CN 201914456U CN 2010206771382 U CN2010206771382 U CN 2010206771382U CN 201020677138 U CN201020677138 U CN 201020677138U CN 201914456 U CN201914456 U CN 201914456U
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- aerofoil
- back rest
- axle beam
- aerofoil profile
- covering
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Abstract
The utility model relates to an aerofoil structure with high aspect ratio and the manufacturing method. The aerofoil structure is characterized in that an advancing edge, a forebeam, a middle beam, a back beam and a trailing edge are sequentially arranged; an upper covering and a lower covering are respectively laid on the upside and the underside; styrofoam is filled respectively between the advancing edge and the forebeam and between the back beam and the trailing edge; cellular type sandwiches are fixedly glued among the forebeam, the middle beam and the back beam; the forebeam, the middle beam and the back beam at the root of the aerofoil are connected with a joint; and a cushion block is fixed on a wingtip of the aerofoil. Through adopting the measures that the styrofoam and the cellular type sandwiches are filled in an inner chamber of the aerofoil, the structural strength and rigidity of the aerofoil are improved and the structural weight is relieved, and meanwhile by fully using the supporting rigidity of the foaming agent and the cellular type sandwiches, the aerofoil is taken as a male mold to be integrally formed so as to lesson the difficulties in fetching the male mold and the aerofoil achieves light weight.
Description
Technical field
The utility model relates to aircraft aerofoil profile structure, particularly a kind of high aspect ratio airfoil structure.
Background technology
The aerofoil of aircraft mainly is to produce lift, and balance aircraft inertia loading is to realize maneuvering flight.Traditional high aspect ratio aerofoil profile is generally single-beam formula or two-beam type structure, is made up of members such as (forward and backward) girder, rib, coverings, and girder, rib are main load-carrying member, and covering bears the load of fraction.This traditional structural pattern mainly contains following shortcoming: aerofoil profile is thinner usually, and number of parts is many, and assembly space is little, requires very high on the technical merit of technology and assembling; The aerofoil profile moment of flexure is mainly born by girder, and the structure utilization ratio is lower, Heavy Weight, and strength of material requires high, and Root Stress is concentrated bigger, and the jointing difficult design; The torsion stiffness of single closed chamber or open profile is little, easily twists to disperse and aeroelasticity problem such as flutter.
The utility model content
The purpose of this utility model is: three beams were arranged before, during and after high aspect ratio aerofoil profile girder was taked, and at aerofoil profile inner chamber filling-foam glue and cellular type core, improve the structural strength and the rigidity of aerofoil profile, alleviate structural weight, two closed chamber structures of three beams and covering formation simultaneously effectively improve the bending resistance torsion stiffness of aerofoil profile, non-primary load bearing position adopts glass-reinforced plastic material to be easy to moulding, and in light weight.
For achieving the above object, the technical solution adopted in the utility model is: a kind of high aspect ratio airfoil structure, comprise: front-axle beam, central sill, the back rest, joint, cellular type core, foamed glue, last covering, following covering, leading edge, trailing edge, cushion block, it is characterized in that, leading edge, front-axle beam, central sill, the back rest, trailing edge is docile and obedient arrangement, and the top and following covering that is laid with respectively, following covering, between leading edge and the front-axle beam, the back rest and trailing edge are filled with foamed glue respectively, front-axle beam, central sill, fixing glue is connected to cellular type core between the back rest, the front-axle beam of aerofoil profile root, central sill, back rest jointing, the wing tip of aerofoil profile is fixed with cushion block.
The obtained beneficial effect of the utility model is:
1, with traditional structural pattern ratio, structure of the present utility model is more succinct, the employing carbon fiber composite material does not have the nail forming technique, and structure does not have the rib member, and assembly technology is simple, convenient, can further alleviate airfoil structure weight;
2, Applicable scope is wider, is applicable to various high aspect ratio aerofoil profiles, according to type application target and stressing conditions, by carbon fiber composite material shop layer optimal design, changes aerofoil profile joint design material, improves the structural strength and the rigidity of aerofoil profile;
3, the topology layout power transmission is simple, directly, and two closed chamber sections have effectively improved aerofoil profile bending resistance and antitorque strong, rigidity, has simplified the type of attachment with the aerofoil profile joint, has improved the aeroelasticity problem of high aspect ratio aerofoil profile.
Description of drawings
Fig. 1 is a structural plan of the present utility model scheme drawing.
Fig. 2 be among Fig. 1 A-A to the structure cutaway view.
Fig. 3 be among Fig. 1 B-B to the structure cutaway view.
Fig. 4 be among Fig. 1 B-B to another version cutaway view.
Among the figure: covering, 9-leading edge, 10-trailing edge, 11-cushion block under 1-front-axle beam, 2-central sill, the 3-back rest, 4-joint, 5-cellular type core, 6-foamed glue, the last covering of 7-, the 8-.
The specific embodiment
Now the utility model is described in further detail in conjunction with the accompanying drawings and embodiments, referring to Fig. 1, Fig. 2 and Fig. 3, a kind of high aspect ratio airfoil structure, comprise: front-axle beam 1, central sill 2, the back rest 3, joint 4, cellular type core 5, foamed glue 6, last covering 7, following covering 8, leading edge 9, trailing edge 10, cushion block 11, leading edge 9, front-axle beam 1, central sill 2, the back rest 3, trailing edge 10 is docile and obedient arrangement, and the top and following covering 7 that is laid with respectively, following covering 8, between leading edge 9 and the front-axle beam 1, the back rest 3 is filled with foamed glue 6 respectively with trailing edge 10, front-axle beam 1, central sill 2, fixing glue is connected to cellular type core 5 between the back rest 3, the front-axle beam 1 of aerofoil profile root, central sill 2, the back rest 3 jointings 4, the wing tip of aerofoil profile is fixed with cushion block 11.
The high aspect ratio aerofoil profile is the one-piece construction that composite material is made, wherein front-axle beam 1, central sill 2, the back rest 3 form the two closed chamber structures of carbon fiber layer plywood with the part of last covering 7, following covering 8, joint 4 is a titanium alloy structure, and leading edge 9, trailing edge 10, cushion block 11 are glass fibre reinforced plastic structure; Front-axle beam 1 and the back rest 3 cross sections are " U " font, and central sill 2 cross sections are " worker " font.As Fig. 2, Fig. 3.
The high aspect ratio aerofoil profile is the one-piece construction that composite material is made, wherein front-axle beam 1, central sill 2, the back rest 3 form the two closed chamber structures of carbon fiber layer plywood with the part of last covering 7, following covering 8, joint 4 is a titanium alloy structure, and leading edge 9, trailing edge 10, cushion block 11 are glass fibre reinforced plastic structure; Front-axle beam 1, the back rest 3, central sill 2 cross sections are " worker " font.As Fig. 4.
High aspect ratio composite material aerofoil profile adopts apleuria three girder structure schemes, three beams and covering are by mold pressing second bonding integration moulding, whole aerofoil profile becomes an integral type load-carrying construction, and three beams and covering have formed two closed chamber structures simultaneously, effectively improve the torsion stiffness of aerofoil profile.Take measure at aerofoil profile inner chamber filling-foam glue and cellular type core, improve the structural strength and the rigidity of aerofoil profile, alleviate structural weight, make full use of the support stiffness of foaming agent and cellular type core simultaneously, it is carried out moulding together as formpiston, reduced the problem of getting the formpiston difficulty.Aerofoil profile leading edge and trailing edge are non-primary load bearing position, adopt glass-reinforced plastic material to be easy to moulding, and in light weight.
Claims (1)
1. high aspect ratio airfoil structure, comprise: front-axle beam [1], central sill [2], the back rest [3], joint [4], cellular type core [5], foamed glue [6], last covering [7], following covering [8], leading edge [9], trailing edge [10], cushion block [11], it is characterized in that, leading edge [9], front-axle beam [1], central sill [2], the back rest [3], trailing edge [10] is docile and obedient arrangement, and the top and following covering [7] that is laid with respectively, following covering [8], between leading edge [9] and the front-axle beam [1], the back rest [3] is filled with foamed glue [6] respectively with trailing edge [10], front-axle beam [1], central sill [2], fixing glue is connected to cellular type core [5] between the back rest [3], the front-axle beam of aerofoil profile root [1], central sill [2], the back rest [3] jointing [4], the wing tip of aerofoil profile are fixed with cushion block [11].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206771382U CN201914456U (en) | 2010-12-23 | 2010-12-23 | Aerofoil structure with high aspect ratio |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206771382U CN201914456U (en) | 2010-12-23 | 2010-12-23 | Aerofoil structure with high aspect ratio |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201914456U true CN201914456U (en) | 2011-08-03 |
Family
ID=44414264
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010206771382U Expired - Fee Related CN201914456U (en) | 2010-12-23 | 2010-12-23 | Aerofoil structure with high aspect ratio |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201914456U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108016602A (en) * | 2017-12-20 | 2018-05-11 | 北航（四川）西部国际创新港科技有限公司 | Honeycomb structure wing and aircraft |
| CN109902330A (en) * | 2018-11-12 | 2019-06-18 | 中航通飞研究院有限公司 | A kind of aerofoil and its strength calculation method of no stringer and rib web |
-
2010
- 2010-12-23 CN CN2010206771382U patent/CN201914456U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108016602A (en) * | 2017-12-20 | 2018-05-11 | 北航（四川）西部国际创新港科技有限公司 | Honeycomb structure wing and aircraft |
| CN108016602B (en) * | 2017-12-20 | 2024-04-02 | 北航（四川）西部国际创新港科技有限公司 | Honeycomb wing and aircraft |
| CN109902330A (en) * | 2018-11-12 | 2019-06-18 | 中航通飞研究院有限公司 | A kind of aerofoil and its strength calculation method of no stringer and rib web |
| CN109902330B (en) * | 2018-11-12 | 2023-09-12 | 中航通飞华南飞机工业有限公司 | Airfoil without stringers and rib webs and strength calculation method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: JIANGXI HONGDU TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: HONGDU AVIATION INDUSTRY GROUP CO., TD., JIANGXI PROV. Effective date: 20140814 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 330000 NANCHANG, JIANGXI PROVINCE TO: 330096 NANCHANG, JIANGXI PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20140814 Address after: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee after: Jiangxi Hongdu Technology Co., Ltd. Address before: 330000 Jiangxi city of Nanchang province Qingyunpu new bridge Patentee before: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. |
|
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000160 Denomination of utility model: High-aspect-ratio wing type structure and manufacturing method thereof Granted publication date: 20110803 License type: Exclusive License Record date: 20140709 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| EC01 | Cancellation of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000160 Date of cancellation: 20141202 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20151229 Address after: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee after: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Address before: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee before: Jiangxi Hongdu Technology Co., Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110803 Termination date: 20161223 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |