CN108216570A - A kind of high aspect ratio wing main plane structure - Google Patents
A kind of high aspect ratio wing main plane structure Download PDFInfo
- Publication number
- CN108216570A CN108216570A CN201711340922.7A CN201711340922A CN108216570A CN 108216570 A CN108216570 A CN 108216570A CN 201711340922 A CN201711340922 A CN 201711340922A CN 108216570 A CN108216570 A CN 108216570A
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- China
- Prior art keywords
- aspect ratio
- high aspect
- main plane
- carbon fibre
- adhesive
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/182—Stringers, longerons
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The present invention is a kind of high aspect ratio wing main plane structure, belongs to aviation field.It is made of honeycomb interlayer wainscot 1, shape for hat reinforcement lower wall panels 2, boxlike girder 3, rear wall 4, skins front edges 5, rib 6 and adhesive 7, the honeycomb interlayer wainscot 1 shapes sandwich for panel, lightweight paper honeycomb co-curing inside and outside carbon fibre composite.The shape for hat reinforcement lower wall panels 2 are carbon fibre composite covering, foam core integrally curing shapes shape for hat reinforced structure.The boxlike girder 3 is glued co-curing for carbon fibre composite and shapes integrated structure.Wall 4, skins front edges 5, rib 6 are carbon fibre composite pressure plate structure after described.The adhesive 7 is normal temperature cure paste adhesive.Each component using corresponding structure type, has given full play to composite material loss of weight advantage, has efficiently solved the contradiction of high aspect ratio wing main plane structure high-mechanic and light weight according to respective bearing behavior.
Description
Technical field
The invention belongs to aviation fields, and in particular to a kind of high aspect ratio wing main plane structure.
Background technology
Long endurance unmanned aircraft is due to the rigors in voyage, endurance and economy, generally using high aspect ratio wing,
To obtain larger lift resistance ratio.Main plane structure is the main bearing structure of high aspect ratio wing, in addition to bearing local pneumatic load,
Also to transmit full machine integrity moment and torque.In order to further increase voyage and extend cruise duration, construction weight requires as possible
Gently.High-mechanic and light weight are conflicts, and difficulty is brought to structure design.For middle low speed high aspect ratio unmanned plane, machine
The wing is generally beam type light-skinned structure form, and upper and lower covering is relatively thin, is mainly used for pneumatically tieing up shape；Girder is mostly I-shaped
Beam, for transmitting integrity moment and shearing；It is generally assembled into the form of mechanical connection between covering and inner skeleton up and down
It is whole, see Fig. 1.The form is more mature, but has the following disadvantages：
(1) there is high aspect ratio wing upper surface to be pressurized serious, the loading characteristic of the main tension in lower surface, upper covering it is steady
Qualitative question protrude, thin skin dimension shape effect it is poor, need more rib for collect aerodynamic loading and auxiliary dimension shape, pay compared with
Big weight cost；
(2) the wing box torsional property that I-shaped girder and thin skin are formed is poor, is unfavorable for the transmission of torque；
(3) the assembling form integration level of mechanical connection is low, and assembly work amount is big, and the period is long, of high cost, largely connects
Weight can not be ignored shared by fitting.
Invention content
Technical solution：
A kind of high aspect ratio wing main plane structure, by honeycomb interlayer wainscot (1), shape for hat reinforcement lower wall panels (2), boxlike
Girder (3), rear wall (4), skins front edges (5), rib (6) and adhesive (7) composition, the honeycomb interlayer wainscot (1) are carbon
Panel, lightweight paper honeycomb co-curing forming sandwich inside and outside fibrous composite；The shape for hat reinforcement lower wall panels (2) are fine for carbon
Tie up composite material skin, foam core integrally curing forming shape for hat reinforced structure.
Honeycomb interlayer wainscot (1), shape for hat reinforcement lower wall panels (2) are carried out whole between inner skeleton using adhesive (7)
Bodyization is glued assembling.
The boxlike girder (3) is glued co-curing for carbon fibre composite and shapes integrated structure；The rear wall (4),
Skins front edges (5), rib (6) are carbon fibre composite pressure plate structure.
The adhesive (7) is normal temperature cure paste adhesive.
Technique effect and advantage
(1) honeycomb interlayer wainscot has the characteristics that itself bending stiffness is high, light-weight, is conducive to improve top airfoil compression
Stability and dimension shape effect；
(2) lower wall panels can increase dimension shape effect using shape for hat reinforced structure, give full play to multiple because being primarily subjected to tensile load
Condensation material thin skin loss of weight advantage；
(3) lower wall panels, which preferably tie up shape ability, on can allow the quantity of rib to be greatly decreased, and mitigate construction weight；
(4) boxlike girder uses co-curing monolithic molding, for bearing most integrity moments, torque and shearing, tool
There is preferable bending-twisting performance；
(5) it is glued assembly method entirely and improves structure integration level, reduce assembly work amount, is conducive to shorten and develop
Period reduces cost, further loss of weight；
(6) each component, using corresponding structure type, has given full play to composite material loss of weight according to respective bearing behavior
Advantage efficiently solves the contradiction of high aspect ratio wing main plane structure high-mechanic and light weight.
Description of the drawings
Fig. 1 is low speed high aspect ratio unmanned plane wing main plane structure schematic diagram in tradition；
Fig. 2 is a kind of high aspect ratio wing main plane structure sectional view of the present invention；
Fig. 3 is a kind of high aspect ratio wing main plane structure schematic diagram of the present invention；
Fig. 4 is a kind of high aspect ratio wing main plane structure assembling schematic diagram of the present invention；
Fig. 5 completes final schematic diagram for a kind of high aspect ratio wing main plane structure assembling of the present invention.
Wall, 5- skins front edges, 6- after 1- honeycomb interlayers wainscot, 2- shape for hat reinforcements lower wall panels, 3- boxlikes girder, 4- in figure
Rib, 7- adhesives；
Specific embodiment
A kind of high aspect ratio wing main plane structure of the present invention recommend to carry out as follows parts manufacture and
Assembling, is shown in Fig. 4, Fig. 5：
(1) parts respectively solidified forming is respectively formed described in；
(2) boxlike girder 3, rear wall 4, skins front edges 5, rib 6 described in are assembled into internal overall skeleton by tooling；
(3) adhesive 7 is uniformly coated in internal overall skeleton upper surface, completion and honeycomb in 7 construction period of adhesive
The splicing of interlayer wainscot 1；
(4) adhesive 7 is uniformly coated in internal overall skeleton lower surface, completion and shape for hat in 7 construction period of adhesive
The splicing of reinforcement lower wall panels 2；
(5) the required contact of adhesive curing is applied by tooling snap-gauge or molding, adhesive is waited for complete curing.
Claims (4)
1. a kind of high aspect ratio wing main plane structure, by honeycomb interlayer wainscot (1), shape for hat reinforcement lower wall panels (2), boxlike master
Beam (3), rear wall (4), skins front edges (5), rib (6) and adhesive (7) composition, it is characterised in that：The honeycomb interlayer upper wall
Plate (1) shapes sandwich for panel, lightweight paper honeycomb co-curing inside and outside carbon fibre composite；The shape for hat reinforcement lower wall panels
(2) it is carbon fibre composite covering, foam core integrally curing shapes shape for hat reinforced structure.
2. a kind of high aspect ratio wing main plane structure according to claim 1, it is characterised in that：Honeycomb interlayer wainscot
(1), shape for hat reinforcement lower wall panels (2) carry out integration splicing assembling between inner skeleton using adhesive (7).
3. a kind of high aspect ratio wing main plane structure according to claim 1, it is characterised in that：The boxlike girder
(3) it is glued co-curing for carbon fibre composite and shapes integrated structure；Wall (4), skins front edges (5), rib (6) are after described
Carbon fibre composite pressure plate structure.
4. a kind of high aspect ratio wing main plane structure according to claim 1 or 2, it is characterised in that：The adhesive
(7) it is normal temperature cure paste adhesive.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711340922.7A CN108216570B (en) | 2017-12-14 | 2017-12-14 | Main wing surface structure of high aspect ratio wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711340922.7A CN108216570B (en) | 2017-12-14 | 2017-12-14 | Main wing surface structure of high aspect ratio wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108216570A true CN108216570A (en) | 2018-06-29 |
| CN108216570B CN108216570B (en) | 2023-08-18 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711340922.7A Active CN108216570B (en) | 2017-12-14 | 2017-12-14 | Main wing surface structure of high aspect ratio wing |
Country Status (1)
| Country | Link |
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| CN (1) | CN108216570B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109532036A (en) * | 2018-11-27 | 2019-03-29 | 中航通飞华南飞机工业有限公司 | A kind of full composite material wing adhering method and full composite material wing |
| 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 |
| CN110510145A (en) * | 2019-08-30 | 2019-11-29 | 中国民用航空飞行学院 | Three beam type composite wing overall structures of one kind and its moulding technique |
| CN110667818A (en) * | 2019-09-30 | 2020-01-10 | 西北工业大学 | Cell-like air column wing skin |
| GB2575633A (en) * | 2018-07-16 | 2020-01-22 | Bae Systems Plc | Wing structure |
| CN112249300A (en) * | 2020-10-22 | 2021-01-22 | 航天特种材料及工艺技术研究所 | Carbon fiber composite material airfoil leading edge structure |
| CN112339986A (en) * | 2020-09-22 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Skin skeleton integrated intermediate-temperature rapid molding composite material structure and method |
| CN113978699A (en) * | 2021-11-16 | 2022-01-28 | 天津爱思达航天科技有限公司 | Front edge lightweight structure |
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| CN202177502U (en) * | 2011-08-15 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Large aspect ratio wing transonic flutter model |
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| CN103448901A (en) * | 2012-05-30 | 2013-12-18 | 波音公司 | Bonded composite airfoil and fabrication method |
| CN104249811A (en) * | 2014-08-29 | 2014-12-31 | 中国运载火箭技术研究院 | Aircraft wing suitable for shuttling back and forth aerosphere |
| CN204368409U (en) * | 2014-12-19 | 2015-06-03 | 成都飞机设计研究所 | A kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing |
| CN106114819A (en) * | 2016-07-22 | 2016-11-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of composite airfoil structure |
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| EP0256916A1 (en) * | 1986-07-28 | 1988-02-24 | AEROSPATIALE Société Nationale Industrielle | Composite blade with a double spar and torsional box and with a honeycomb sandwich layered coating, and production process |
| CN202177502U (en) * | 2011-08-15 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Large aspect ratio wing transonic flutter model |
| CN102411652A (en) * | 2011-08-15 | 2012-04-11 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining sectional dimension of rectangular beam with lugs |
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| CN103448901A (en) * | 2012-05-30 | 2013-12-18 | 波音公司 | Bonded composite airfoil and fabrication method |
| CN104249811A (en) * | 2014-08-29 | 2014-12-31 | 中国运载火箭技术研究院 | Aircraft wing suitable for shuttling back and forth aerosphere |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2575633A (en) * | 2018-07-16 | 2020-01-22 | Bae Systems Plc | Wing structure |
| GB2575633B (en) * | 2018-07-16 | 2022-06-01 | Bae Systems Plc | Wing structure |
| 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 |
| CN109532036A (en) * | 2018-11-27 | 2019-03-29 | 中航通飞华南飞机工业有限公司 | A kind of full composite material wing adhering method and full composite material wing |
| CN110510145A (en) * | 2019-08-30 | 2019-11-29 | 中国民用航空飞行学院 | Three beam type composite wing overall structures of one kind and its moulding technique |
| CN110667818A (en) * | 2019-09-30 | 2020-01-10 | 西北工业大学 | Cell-like air column wing skin |
| CN112339986A (en) * | 2020-09-22 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Skin skeleton integrated intermediate-temperature rapid molding composite material structure and method |
| CN112249300A (en) * | 2020-10-22 | 2021-01-22 | 航天特种材料及工艺技术研究所 | Carbon fiber composite material airfoil leading edge structure |
| CN112249300B (en) * | 2020-10-22 | 2022-02-15 | 航天特种材料及工艺技术研究所 | Carbon fiber composite material airfoil leading edge structure |
| CN113978699A (en) * | 2021-11-16 | 2022-01-28 | 天津爱思达航天科技有限公司 | Front edge lightweight structure |
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|---|---|
| CN108216570B (en) | 2023-08-18 |
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Effective date of registration: 20210305 Address after: 611731, No. four, West core road, hi tech West District, Sichuan, Chengdu Applicant after: AVIC (Chengdu) UAV System Co.,Ltd. Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Applicant before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |
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