CN109305328A - A kind of wing box and aircraft - Google Patents
A kind of wing box and aircraft Download PDFInfo
- Publication number
- CN109305328A CN109305328A CN201811341709.2A CN201811341709A CN109305328A CN 109305328 A CN109305328 A CN 109305328A CN 201811341709 A CN201811341709 A CN 201811341709A CN 109305328 A CN109305328 A CN 109305328A
- Authority
- CN
- China
- Prior art keywords
- wing
- sealing
- plate
- edge strip
- web
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 claims abstract description 41
- 244000309464 bull Species 0.000 claims description 8
- 239000000295 fuel oil Substances 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 4
- 238000012545 processing Methods 0.000 abstract description 3
- 239000002828 fuel tank Substances 0.000 description 10
- 238000010586 diagram Methods 0.000 description 6
- 230000000007 visual effect Effects 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/34—Tanks constructed integrally with wings, e.g. for fuel or water
Abstract
The present invention relates to aircraft wing technical field, disclosing a kind of wing box and aircraft, wing box includes connector, spar and rib, and spar includes wing plate and the connecting plate for being connected to wing plate two sides, and wing plate and connecting plate are in angle setting；Connector includes interconnection and vertically disposed web and edge strip, and the both ends of web are provided with sealing, and sealing protrudes from the end setting of edge strip, and sealing is arranged close to the side of edge strip and edge strip far from the flush of web；Edge strip fits in the inner surface of wing plate far from the side of web, and is fixedly connected with wing plate, and the side wall of sealing fits in wing plate and connecting plate, and web is fixedly connected with rib.Sealing is added on connector, makes no longer the presence of gap between connector and spar, has blocked fuel oil leak, do not increase parts count and difficulty of processing simultaneously, change is only made in the structure type of original connector, this connecting-piece structure form is simple and reliable, easy to process, and assembles simple.
Description
Technical field
The present invention relates to aircraft wing technical field more particularly to a kind of wing box and aircrafts.
Background technique
The wing boxes of wings of aircraft are surrounded by upper and lower siding, forward and backward beam (spar) and rib, and wing box is also the fuel tank of aircraft,
It mainly include that Center Wing Tank, oil sump tank, outer wing fuel tank and spilling fuel tank, fuel tank are divided by sealing ribs and semitight rib
Every.Rib is mainly used for supporting covering to maintain aerodynamic configuration simultaneously reinforced wallboard stability, load is diffused into wing box, to be
Road under the overall leadership provides support etc..In order to guarantee the assembling capacity and sealing performance of wing box, generally needed in rib and front and rear beam junction
Design an independent part, the i.e. dress of rib-beam connection 10 (specific structure is as shown in Figure 1) control rib 30 and spar 20
With gap, guarantee the sealing performance of fuel tank.Wherein, rib-beam connection 10 includes web 101 interconnected and edge strip 102,
The length of median ventral plate 101 is less than the length of edge strip 102, and both ends are obliquely installed.
As shown in Figures 2 and 3, when connecting for sealing rib 30 and spar 20, prior art is usually in rib
30 are further added by sealing cornual plate 40, want to meet the sealing of fuel tank with 20 junction of spar in addition to original rib-beam connection 10
It asks.But due to common rib-beam connection 10 and the matching problem in rib 30, sealing 40 structure of cornual plate, rib-beam connection 10
There are gap (as shown in the A in Fig. 2 and Fig. 3) between web 101 and spar 20, the sealing of fuel tank not can be well protected
Property, it is easy to produce fuel oil leak.
Therefore, a kind of wing box and aircraft are needed, to solve the above technical problems.
Summary of the invention
The purpose of the present invention is to provide a kind of wing box and aircrafts, to solve the above technical problems, make connector and spar
Between no longer there is gap, blocked fuel oil leak.
To achieve this purpose, the present invention adopts the following technical scheme:
Technical solution one: a kind of wing box, comprising: connector, spar and rib, the spar include wing plate and be connected to institute
The connecting plate of wing plate two sides, the wing plate and the connecting plate is stated to be arranged in angle；
The connector includes interconnection and vertically disposed web and edge strip, the both ends of the web are provided with sealing
Portion, the sealing protrude from the end setting of the edge strip, side and the edge strip of the sealing close to the edge strip
Flush far from the web is arranged；
The edge strip fits in the inner surface of the wing plate far from the side of the web, and fixes and connect with the wing plate
It connects, the side wall of the sealing fits in the wing plate and the connecting plate, and the web is fixedly connected with rib.
Preferably, sealing cornual plate is also connected between the spar and rib, described one side of sealing cornual plate fits in
The connecting plate, a side adjacent with the side fit in the wing plate, and a surface of the sealing cornual plate fits in
The rib.
Preferably, it is provided with filleted corner on the inside of the wing plate and connecting plate junction, the sealing is provided with and institute
State the bull nose that filleted corner matches.
Preferably, the small 1-2mm of radius of the radius of the bull nose filleted corner.
Preferably, distance of the end of the edge strip away from the filleted corner start line is 0.2-0.5mm.
Preferably, the cross sectional shape of the connector is T-type or L-type.
Preferably, the two sides up and down of the spar are connected separately with wainscot and lower wall panels.
A kind of technical solution two: aircraft comprising wing box as described above.
Beneficial effects of the present invention: sealing is added on connector in the present invention, is made between connector and spar no longer
There are gap, fuel oil leak has been blocked, while not having increased parts count and difficulty of processing, only in the structure type of original connector
On make change, this connecting-piece structure form is simple and reliable, easy to process, and assembles simple.Furthermore the oil of aircraft can be met
Case overall structure is simple, assembles high efficient and reliable, and this structure is lower to the operation and maintenance requirement of fuel tank.
Detailed description of the invention
Fig. 1 is prior art middle rib-beam connection structural schematic diagram；
Fig. 2 is the partial structural diagram at a visual angle of prior art middle rib-beam connection, spar and rib；
Fig. 3 is the partial structural diagram at another visual angle of prior art middle rib-beam connection, spar and rib；
Fig. 4 is the structural schematic diagram of connector provided by the invention；
Fig. 5 is the partial structural diagram at a visual angle of connector provided by the invention, spar and rib；
Fig. 6 is the partial structural diagram at another visual angle of connector provided by the invention, spar and rib.
In figure: 10, rib-beam connection；101, web；102, edge strip；20, spar；30, rib；40, cornual plate is sealed；
1, connector；11, edge strip；12, web；121, sealing；
2, spar；21, wing plate；22, connecting plate；
3, rib；4, cornual plate is sealed.
Specific embodiment
To further illustrate the technical scheme of the present invention below with reference to the accompanying drawings and specific embodiments.
As shown in Figures 4 to 6, present embodiment discloses a kind of wing box comprising connector 1, spar 2, rib 3 and sealing
Cornual plate 4.
Wherein, connector 1 includes interconnection and vertically disposed web 12 and edge strip 11, the both ends of web 12 are respectively provided with
There is sealing 121, sealing 121 protrudes from the end setting of edge strip 11, and sealing 121 is first close to the side of edge strip 11
Face, surface of the edge strip 11 far from web 12 is the second face, and the first face and the second face are coplanar with.Connector 1 in the present embodiment
Cross sectional shape is preferably T shape, in other embodiments can also be L shape.
Spar 2 includes wing plate 21 and the connecting plate 22 for being connected to 21 two sides of wing plate, and wing plate 21 is set with connecting plate 22 in angle
It sets.It is formed with filleted corner on the inside of wing plate 21 and 22 junction of connecting plate, the end of sealing 121 is provided with filleted corner and matches
Bull nose.
Edge strip 11 fits in the inner surface of wing plate 21 far from the surface of web 12, and is fixedly connected with wing plate 21.Sealing
121 bull nose fits in the filleted corner of spar 2, i.e. the side wall of sealing 121 fits in the interior table of wing plate 21 and connecting plate 22
Face.Web 12 fits in the setting of rib 3, and is fixedly connected with rib 3.The wherein radius of bull nose 1- small compared with the radius of filleted corner
2mm, the radius of bull nose is less than 1.5mm compared with the radius of filleted corner in the present embodiment.The length of edge strip 11 is less than the length of wing plate 21
Degree, and the distance of the threshold value filleted corner start line of edge strip 11 is 0.2-0.5mm, is 0.3mm in the present embodiment.
One side of sealing cornual plate 4 fits in connecting plate 22, and a side adjacent with the side fits in wing plate 21,
Smooth connection between the two sides, and junction and the filleted corner of spar 2 match, and just fit in the filleted corner of spar 2
The inner wall at place.One surface of sealing cornual plate 4 fits in rib 3, and is fixedly connected with rib 3.
Be connected with wainscot (not shown) between the connecting plate 22 of two spars, 2 top, the connecting plate 22 of lower section it
Between be connected with lower wall panels (not shown).
Sealing 121 is added on connector 1, is made no longer there is gap between connector 1 and spar 2, has been blocked fuel oil leakage
Road, while not increasing parts count and difficulty of processing, change, this connection are only made in the structure type of original connector 1
1 structure type of part is simple and reliable, easy to process, and assembles simple.Furthermore the fuel tank overall structure that can meet aircraft is simple, assembly
High efficient and reliable, and this structure is lower to the operation and maintenance requirement of fuel tank.
The present embodiment also discloses a kind of aircraft, and which employs wing box as described above.
Obviously, the above embodiment of the present invention is just for the sake of clearly illustrating examples made by the present invention, and being not is pair
The restriction of embodiments of the present invention.For those of ordinary skill in the art, may be used also on the basis of the above description
To make other variations or changes in different ways.There is no necessity and possibility to exhaust all the enbodiments.It is all this
Made any modifications, equivalent replacements, and improvements etc., should be included in the claims in the present invention within the spirit and principle of invention
Protection scope within.
Claims (8)
1. a kind of wing box, comprising: connector (1), spar (2) and rib (3), which is characterized in that
The spar (2) includes wing plate (21) and the connecting plate (22) for being connected to the wing plate (21) two sides, the wing plate (21)
It is arranged with the connecting plate (22) in angle；
The connector (1) includes being connected with each other and vertically disposed web (12) and edge strip (11), and the two of the web (12)
End is provided with sealing (121), and the sealing (121) protrudes from the end setting of the edge strip (11), the sealing
(121) it is arranged close to the side of the edge strip (11) and the edge strip (11) far from the flush of the web (12)；
The edge strip (11) fits in the inner surfaces of the wing plate (21) far from the side of the web (12), and with the wing plate
(21) it is fixedly connected, the side wall of the sealing (121) fits in the wing plate (21) and the connecting plate (22), the web
(12) it is fixedly connected with rib (3).
2. wing box according to claim 1, which is characterized in that be also connected with sealing between the spar (2) and rib (3)
Cornual plate (4), (4) sides of the sealing cornual plate fit in the connecting plate (22), the side patch adjacent with the side
Together in the wing plate (21), a surface of sealing cornual plate (4) fits in the rib (3).
3. wing box according to claim 1, which is characterized in that the inside of the wing plate (21) and connecting plate (22) junction
It is provided with filleted corner, the sealing (121) is provided with the bull nose to match with the filleted corner.
4. wing box according to claim 3, which is characterized in that the radius of the bull nose is small compared with the radius of the filleted corner
1-2mm。
5. wing box according to claim 4, which is characterized in that the end of the edge strip (11) is away from the filleted corner start line
Distance range be 0.2-0.5mm.
6. wing box according to claim 1, which is characterized in that the cross sectional shape of the connector (1) is T-type or L-type.
7. wing box according to claim 1, which is characterized in that the two sides up and down of the spar (2) are connected separately with upper wall
Plate and lower wall panels.
8. a kind of aircraft, which is characterized in that it includes such as the described in any item wing box of claim 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811341709.2A CN109305328B (en) | 2018-11-12 | 2018-11-12 | Wing box and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811341709.2A CN109305328B (en) | 2018-11-12 | 2018-11-12 | Wing box and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109305328A true CN109305328A (en) | 2019-02-05 |
| CN109305328B CN109305328B (en) | 2024-01-16 |
Family
ID=65222758
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811341709.2A Active CN109305328B (en) | 2018-11-12 | 2018-11-12 | Wing box and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109305328B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525631A (en) * | 2019-08-22 | 2019-12-03 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | It is a kind of can prepsetting gap sealing structure and fastening method |
| WO2020239715A1 (en) * | 2019-05-28 | 2020-12-03 | Airbus Operations Limited | Rib mounting assembly |
| CN112623190A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft stable face box section interfacing apparatus |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020239715A1 (en) * | 2019-05-28 | 2020-12-03 | Airbus Operations Limited | Rib mounting assembly |
| CN110525631A (en) * | 2019-08-22 | 2019-12-03 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | It is a kind of can prepsetting gap sealing structure and fastening method |
| CN110525631B (en) * | 2019-08-22 | 2021-06-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Sealing structure with preset gap and fastening method |
| CN112623190A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft stable face box section interfacing apparatus |
| CN112623190B (en) * | 2020-12-29 | 2023-11-21 | 中国航空工业集团公司西安飞机设计研究所 | Butt joint device for box sections of plane stabilizer |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109305328B (en) | 2024-01-16 |
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