CN110510104A - A kind of girder construction of aircraft wing - Google Patents
A kind of girder construction of aircraft wing Download PDFInfo
- Publication number
- CN110510104A CN110510104A CN201910715713.9A CN201910715713A CN110510104A CN 110510104 A CN110510104 A CN 110510104A CN 201910715713 A CN201910715713 A CN 201910715713A CN 110510104 A CN110510104 A CN 110510104A
- Authority
- CN
- China
- Prior art keywords
- frame
- unjointed
- beam frame
- ontology
- unjointed beam
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/182—Stringers, longerons
Abstract
A kind of girder construction of aircraft wing, containing by upper edge strip, lower edge strip, web, reinforce the beam ontology that forms of pillar and unjointed beam frame positioned at beam ontology front end, the unjointed beam frame is a frame-shaped construction, unjointed beam frame is connect with beam ontology, and the front end of unjointed beam frame is equipped with the interface connecting with fuselage.The front end of the girder construction of the aircraft wing of the application is equipped with unjointed beam frame, and unjointed beam frame ensure that the integrality and power transmission of spar structure；There is big opening in unjointed beam frame medium design, inlet distribution is in the big opening of unjointed beam frame；Unjointed beam frame uses integrally formed manufacture, reduces part and connector quantity, to alleviate construction weight, improves component assembling efficiency, reduce production cost；Unjointed beam frame can use aluminium alloy integral forging and forming, improve the fatigue behaviour of structure.
Description
Technical field
The present invention relates to aeroplane structure designs, are further the structure design of aircraft wing, specifically a kind of aircraft wing
Girder construction.
Background technique
The air-foil of large transport airplane and bomber is thicker, mostly uses beam type wing structure.The beam type wing knot of aircraft
Wingbar is main bearing member in structure, and wingbar bears wing overwhelming majority shearing and moment of flexure, the wingbar of usual aircraft are
The wall type structure being made of upper edge strip, lower edge strip, web and reinforcement pillar is docked in root with fuselage fixation.Wingbar and machine
Wing covering constitutes closed box structure and bears wing torque.In airplane design, outside the layout of air intake duct and the pneumatic of aircraft
Shape is related, and using the aerodynamic arrangement of wing root air inlet, the root of aircraft wing is arranged in air intake duct, and air intake duct is needed across aircraft machine
The wing, advantage of this layout is that the front face area of aircraft is small, aerodynamic drag is small, so as to promote the flying quality of aircraft.When
When aircraft uses the aerodynamic arrangement of wing root air inlet, air intake duct passes through spar, to destroy the integrality and power transmission of spar structure.
The structure of air intake duct and aircraft wing interferes, especially even more serious to the interference of the load-carrying member wingbar of wing.Such as
What guarantees air intake duct in the rational deployment of wing wing root, guarantees that the structural strength of wing is a difficulty of aeroplane structure design again
Topic.
Summary of the invention
The purpose of the present invention is to provide a kind of inlet distribution the aircraft wing of wing wing root girder construction.One kind flies
The girder construction of machine wing, which is characterized in that containing the beam ontology being made of upper edge strip, lower edge strip, web, reinforcement pillar and be located at
The unjointed beam frame of beam ontology front end, the unjointed beam frame are a frame-shaped constructions, and unjointed beam frame is connect with beam ontology, unjointed beam frame
Front end be equipped with the interface that connect with fuselage.
The unjointed beam frame contains interior reinforcing frame, outer reinforcing frame, and connection web is equipped between interior reinforcing frame, outer reinforcing frame
And reinforcing rib, the front end of the outer reinforcing frame are the interfaces connecting with fuselage, interface is equipped with butt hole, and described is outer
The both ends of the rear end of reinforcing frame each extend over out and the matched connection tail of beam ontology web.
The front end of the beam ontology is one and matched half frame-shaped construction of unjointed beam frame, and the top of half frame-shaped construction is beam
The upper edge strip of ontology, the lower part of frame-shaped construction are the lower edge strips of beam ontology, and the side of half frame-shaped construction is the web of beam ontology.
The upper edge strip of half frame-shaped construction part of beam ontology front end and the section of lower edge strip are L-types, can be with unjointed beam frame
Web be fitted and connected.
The beneficial effects of the present invention are: 1) front end of the girder construction of the aircraft wing of the application be equipped with unjointed beam frame, whole
Body beam frame ensure that the integrality and power transmission of spar structure；2) there is big opening in unjointed beam frame medium design, inlet distribution exists
In the big opening of unjointed beam frame；3) unjointed beam frame uses integrally formed manufacture, reduces part and connector quantity, to mitigate
Construction weight, improves component assembling efficiency, reduces production cost；4) unjointed beam frame can use aluminium alloy solid forging
Forming, improves the fatigue behaviour of structure.
Attached drawing is described in further detail the application with reference to embodiments.
Detailed description of the invention
Fig. 1 is aircraft wing beam assembling structure schematic diagram.
Fig. 2 is aircraft wing girder construction schematic diagram.
Fig. 3 is beam body construction schematic diagram.
Fig. 4 is unjointed beam mount structure schematic diagram.
Fig. 5 is the connection schematic diagram of beam ontology Yu unjointed beam frame.
Number explanation in figure: 1 beam ontology, 2 unjointed beam frames, edge strip on 3,4 lower edge strips, 5 webs, 6 reinforce pillars, in 7 plus
Strong frame, 8 outer reinforcing frames, 9 connection webs, 10 reinforcing ribs, 11 interfaces, 12 butt holes, 13 connect tails, 14 fuselages, 15 air intake ducts,
16 wing wallboards
Specific embodiment
Referring to attached drawing, a kind of girder construction of aircraft wing is bolted at interface 11 with fuselage 14, with wing
Siding 16 is bolted, and air intake duct 15 passes through unjointed beam frame 2.
Unjointed beam frame 2 of the girder construction of the aircraft wing of the application by beam ontology 1 and positioned at 1 front end of beam ontology forms.Beam
Ontology 1 is by upper edge strip 3, lower edge strip 4, web 5, reinforcement pillar 6 by riveting.1 front end of beam ontology is one and half frame shape knots
The section of structure, the upper edge strip 3 of half frame-shaped construction part and lower edge strip 4 is L-type, passes through rivet with the connection web 9 of unjointed beam frame 2
Connection；The web of the beam ontology 1 of half frame-shaped construction side and the connection web 9 of unjointed beam frame 2 pass through rivet interlacement.
In implementation, unjointed beam frame can be integrated machine addition shape, be also possible to aluminium alloy integral forging and forming, in embodiment
Unjointed beam frame use aluminium alloy integral forging and forming, unjointed beam frame contains interior reinforcing frame 7, outer reinforcing frame 8, interior reinforcing frame 7,
Connection web 9 is equipped between outer reinforcing frame 8 and reinforcing rib 10, the front end of the outer reinforcing frame 8 are the docking connecting with fuselage
Face 11, interface are equipped with butt hole 12, and the both ends of 8 rear end of outer reinforcing frame each extend over out to be matched with beam ontology web
Connection tail 12.
Claims (4)
1. a kind of girder construction of aircraft wing, which is characterized in that containing by upper edge strip, lower edge strip, web, reinforce pillar and form
Beam ontology and unjointed beam frame positioned at beam ontology front end, the unjointed beam frame is a frame-shaped construction, unjointed beam frame and Liang Benti
Connection, the front end of unjointed beam frame are equipped with the interface connecting with fuselage.
2. the girder construction of aircraft wing as described in claim 1, which is characterized in that the unjointed beam frame contain interior reinforcing frame,
Outer reinforcing frame, is equipped with connection web and reinforcing rib between interior reinforcing frame, outer reinforcing frame, the front end of the outer reinforcing frame be with
The interface of fuselage connection, interface are equipped with butt hole, and the both ends of the rear end of the outer reinforcing frame each extend over out and beam
The matched connection tail of ontology web.
3. the girder construction of aircraft wing as described in claim 1, which is characterized in that the front end of the beam ontology be one with it is whole
Matched half frame-shaped construction of body beam frame, the top of half frame-shaped construction are the upper edge strips of beam ontology, and the lower part of frame-shaped construction is beam sheet
The lower edge strip of body, the side of half frame-shaped construction are the webs of beam ontology.
4. the girder construction of aircraft wing as claimed in claim 3, which is characterized in that half frame-shaped construction portion of beam ontology front end
The section of the upper edge strip and lower edge strip that divide is L-type, can be fitted and connected with the web of unjointed beam frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910715713.9A CN110510104A (en) | 2019-08-02 | 2019-08-02 | A kind of girder construction of aircraft wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910715713.9A CN110510104A (en) | 2019-08-02 | 2019-08-02 | A kind of girder construction of aircraft wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110510104A true CN110510104A (en) | 2019-11-29 |
Family
ID=68625001
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910715713.9A Pending CN110510104A (en) | 2019-08-02 | 2019-08-02 | A kind of girder construction of aircraft wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110510104A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111055995A (en) * | 2019-12-31 | 2020-04-24 | 南京儒一航空机械装备有限公司 | Main beam body not easy to deform and processing technology thereof |
| CN111977026A (en) * | 2020-07-29 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Method for detecting circular opening of aircraft air inlet |
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| US4535958A (en) * | 1982-12-13 | 1985-08-20 | Hutchison Gary A | Aluminum composite spar wing structure and method of assembly |
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| CN107416183A (en) * | 2016-09-06 | 2017-12-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of spar attachment structure of aircraft wing |
| CN107571985A (en) * | 2017-08-25 | 2018-01-12 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of ultralight whole wing structure of truss-like |
| CN109131824A (en) * | 2018-09-21 | 2019-01-04 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft reinforcing frame and vertical fin girder construction |
| CN109484624A (en) * | 2018-11-29 | 2019-03-19 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of technique for aircraft composite wing spar and wing root area connection structure |
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2019
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3952973A (en) * | 1974-12-20 | 1976-04-27 | The Boeing Company | Engine mounting assembly |
| US4535958A (en) * | 1982-12-13 | 1985-08-20 | Hutchison Gary A | Aluminum composite spar wing structure and method of assembly |
| CN1435355A (en) * | 2002-12-04 | 2003-08-13 | 韩国庆 | Light buzzard-type wing jet plane and its use, and aircaft carrier using it as ship plane |
| WO2008103735A2 (en) * | 2007-02-22 | 2008-08-28 | Snow Aviation International, Inc. | Aircraft, and retrofit components therefor |
| CN202248452U (en) * | 2011-08-25 | 2012-05-30 | 山东科瑞机械制造有限公司 | Bottom skid for box beam type barracks |
| CN105289895A (en) * | 2015-11-27 | 2016-02-03 | 浙江奥利达气动工具股份有限公司 | Spray fun fixing frame |
| CN106218905A (en) * | 2016-08-03 | 2016-12-14 | 南昌白龙马航空科技有限公司 | Unmanned plane integral wing tank |
| CN107416183A (en) * | 2016-09-06 | 2017-12-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of spar attachment structure of aircraft wing |
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| CN109484624A (en) * | 2018-11-29 | 2019-03-19 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of technique for aircraft composite wing spar and wing root area connection structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111055995A (en) * | 2019-12-31 | 2020-04-24 | 南京儒一航空机械装备有限公司 | Main beam body not easy to deform and processing technology thereof |
| CN111977026A (en) * | 2020-07-29 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Method for detecting circular opening of aircraft air inlet |
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Application publication date: 20191129 |