CN202138536U - Integral wing oil tank sealing structure - Google Patents
Integral wing oil tank sealing structure Download PDFInfo
- Publication number
- CN202138536U CN202138536U CN 201120188898 CN201120188898U CN202138536U CN 202138536 U CN202138536 U CN 202138536U CN 201120188898 CN201120188898 CN 201120188898 CN 201120188898 U CN201120188898 U CN 201120188898U CN 202138536 U CN202138536 U CN 202138536U
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- integral
- sealing
- oil tank
- wing
- tank
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Abstract
The utility model belongs to the technical field of an integral airplane oil tank and particularly relates to an integral oil tank sealing structure. According to the structure, a plurality of small covering gaps are used to replace an integral large covering cap on an upper wing surface of the integral oil tank; a sealing strip is paved between a skin and a beam edge strip and an end rib of a wing skeleton, wherein the beam edge strip and the end rib of the wing skeleton are riveted; and the sealing strip can be subject to lap joint. Due to the structure, the sealing time for the oil tank is saved, the working efficiency is improved by 60%, only the small covering gap at the corresponding position needs to be opened during the maintenance, the maintenance and the examination are facilitated, and the operation time is saved; meanwhile, as sealing adhesives are no longer used during the sealing, the weight of the structure is reduced.
Description
Technical field
The utility model belongs to overall aircraft fuel tank technical field, particularly relates to a kind of integral tank hermetically-sealed construction.
Background technology
Aircraft fuel tank has three types usually, and different aircrafts can have different selections, comprises integral tank (wing or fuselage), flexible bag and independent fuel tank (wing or fuselage additional fuel tank).Integral tank is in wing or airframe structure, to arrange a kind of sealed module, and its inner space can make full use of, and makes fuel capacity increase on the machine, and fuel oil system weight reduces relatively.But the reliability of integral wing tank is lower, is difficult to guarantee to have good leak tightness, and the difficulty of repairing the back is big being damaged.For the leak tightness that improves integral tank suitably adopts long integral panel, its length preferably length with whole mailbox is suitable, and adopts the integral panel of big width as far as possible, to reduce the quantity of joint and fastener perforate.The junction should be coated with sealant and hermetically-sealed construction is arranged.Existing integral tank hermetically-sealed construction adopts grooved seal usually, promptly on beam edge strip and fuel tank end rib, sealed groove is set, and in sealed groove, injects sealant or filling with sealant band.But the method is time-consuming, effort, and it is bigger that its sealing effectiveness is influenced by assembly clearance, and the sealing once success rate is low.
Summary of the invention
The purpose of the utility model is: the utility model is a kind of under the prerequisite that keeps the fuel tank sealing property, the structure of increasing work efficiency.Help maintenance inspection; Reduce structural weight.The utility model has reduced the production cycle under the prerequisite that keeps the fuel tank sealing property, improved work efficiency.
The technical scheme of the utility model is:
A kind of integral wing tank hermetically-sealed construction, this structure uses a plurality of small caps to replace whole big flap at the top airfoil of integral tank, between wing skeleton beam edge strip, end rib and the covering of riveted joint, is covered with a sealing band, and sealing band allows overlap joint.
The utility model has the advantages that:
Compare with traditional integral tank seal form and to have following advantage: saved the fuel tank leak free time, increased work efficiency 60%; The small cap that only need open the relevant position when safeguarding gets final product, and is beneficial to safeguard and inspection, saves the operating time.Simultaneously, no longer need use sealant during owing to sealing, reduce the weight of structure.
Description of drawings
Accompanying drawing 1 is the injecting glue sealed structural representation, and wherein, 1 is covering, and 2 is fuel tank, and 3 is wing skeleton;
Accompanying drawing 2 is the adhesive tape sealing structural representation;
Accompanying drawing 3 is the utility model structural representation; Wherein, 4 is sealing band.
The specific embodiment
With the cancellation of the sealed groove on beam edge strip and the fuel tank end rib, use a plurality of small caps to replace whole big flap at top airfoil, flap adopts seal profile with a mouthful frame junction, helps maintenance inspection.A kind of integral wing tank hermetically-sealed construction; This structure uses a plurality of small caps to replace whole big flap at the top airfoil of integral tank; Between wing skeleton beam edge strip, end rib and the covering of riveted joint, be covered with a sealing band; The width of sealing band is 35mm, and sealing band allows overlap joint, and the length of overlap joint is 20-30mm.
Claims (2)
1. an integral wing tank hermetically-sealed construction is characterized in that, this structure uses a plurality of small caps to replace whole big flap at the top airfoil of integral tank, between wing skeleton beam edge strip, end rib and the covering of riveted joint, is covered with a sealing band, and sealing band allows overlap joint.
2. integral wing tank hermetically-sealed construction as claimed in claim 1 is characterized in that, described sealant band width is 35mm, and the length of overlap joint is 20-30mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120188898 CN202138536U (en) | 2011-06-03 | 2011-06-03 | Integral wing oil tank sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120188898 CN202138536U (en) | 2011-06-03 | 2011-06-03 | Integral wing oil tank sealing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202138536U true CN202138536U (en) | 2012-02-08 |
Family
ID=45549610
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120188898 Expired - Fee Related CN202138536U (en) | 2011-06-03 | 2011-06-03 | Integral wing oil tank sealing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202138536U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9102393B2 (en) | 2012-03-22 | 2015-08-11 | Airbus Operations Limited | Seal assembly for an aircraft wing |
| CN105221748A (en) * | 2015-08-25 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of encapsulating method of aircraft integral tank |
| CN106585957A (en) * | 2016-12-14 | 2017-04-26 | 中航通飞研究院有限公司 | Composite wing integral oil tank and manufacturing method thereof |
| CN109305328A (en) * | 2018-11-12 | 2019-02-05 | 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 wing box and aircraft |
| CN109677586A (en) * | 2019-01-18 | 2019-04-26 | 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 web, aircraft wing and aircraft |
-
2011
- 2011-06-03 CN CN 201120188898 patent/CN202138536U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9102393B2 (en) | 2012-03-22 | 2015-08-11 | Airbus Operations Limited | Seal assembly for an aircraft wing |
| CN105221748A (en) * | 2015-08-25 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of encapsulating method of aircraft integral tank |
| CN106585957A (en) * | 2016-12-14 | 2017-04-26 | 中航通飞研究院有限公司 | Composite wing integral oil tank and manufacturing method thereof |
| CN106585957B (en) * | 2016-12-14 | 2023-03-31 | 中航通飞研究院有限公司 | Composite material wing integral oil tank and manufacturing method thereof |
| CN109305328A (en) * | 2018-11-12 | 2019-02-05 | 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 wing box and aircraft |
| CN109305328B (en) * | 2018-11-12 | 2024-01-16 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Wing box and aircraft |
| CN109677586A (en) * | 2019-01-18 | 2019-04-26 | 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 web, aircraft wing and aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120208 Termination date: 20160603 |