CN203793615U - Comb-shaped joint structure - Google Patents
Comb-shaped joint structure Download PDFInfo
- Publication number
- CN203793615U CN203793615U CN201420155718.3U CN201420155718U CN203793615U CN 203793615 U CN203793615 U CN 203793615U CN 201420155718 U CN201420155718 U CN 201420155718U CN 203793615 U CN203793615 U CN 203793615U
- Authority
- CN
- China
- Prior art keywords
- wing
- comb
- fuselage
- wallboard
- pectination
- 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.)
- Expired - Lifetime
Links
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 230000005540 biological transmission Effects 0.000 abstract description 4
- 238000009434 installation Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
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- Joining Of Building Structures In Genera (AREA)
Abstract
The utility model relates to a comb-shaped connection structure. A comb-shaped joint groove 3 in a rectangular or square shape is machined on the connecting part of a fuselage panel 1 and a wing panel 2, and a through bolt hole 5 is machined between a connecting surface and the comb-shaped joint groove 3 for installing bolts; the fuselage panel 1 and the wing panel 2 are connected through the bolts, and wing ribs 4 are arranged below a connecting position for providing support so as to ensure the strength and rigidity of the structure; the wing ribs 4 and the fuselage panel 1 are connected through the bolts. The comb-shaped connection structure disclosed by the utility model can substitute the traditional lug connecting mode, is uniform and direct in load transmission by connecting a wing with a fuselage by adopting a plurality of bolts in similar comb shapes, prevents the phenomenon of load concentration and reduces the self weight of the structure.
Description
Technical field
The utility model relates to a kind of pectination joint design.
Background technology
In prior art, aircraft wing is connected with fuselage by several auricle joints mostly, and the distributed load on wing changes concentrated load into after the transmission of structure wing structure, by auricle joint, concentrated load is delivered to and on fuselage, disperses balance.Because needs bear very large concentrated load, the volume of auricle joint is larger, and weight is heavier, and not only cost is high, and installation and maintenance are also very inconvenient.
Utility model content
For the problems referred to above, the utility model provides a kind of pectination connection structure that replaces auricle joint, thicken in the connecting portion part of fuselage wallboard 1 and wing wallboard 2, machine adds and to be shaped as oblong or square pectination joint groove 3, between joint face and pectination joint groove 3, be processed with the bolt hole 5 of perforation, for hold-down bolt, fuselage wallboard 1 is bolted with wing wallboard 2, junction arranged beneath has rib 4, ensure the strength and stiffness of structure, rib 4 is bolted with fuselage wallboard 1.
The alternative traditional auricle type of attachment of the utility model, adopts multiple bolts of similar " comb " shape to carry out being connected of wing and fuselage, and load transmission evenly, directly, is avoided the appearance of concentrated load phenomenon, has reduced dead load.
Brief description of the drawings
Fig. 1 is overall structure schematic diagram of the present utility model.
Detailed description of the invention
Also by reference to the accompanying drawings the utility model is described in further detail below by specific embodiment.Concrete implementation process is as described below:
Description of reference numerals: 1. fuselage wallboard; 2. wing wallboard; 3. pectination joint groove; 4. rib; 5. bolt hole.
As shown in Figure 1, the utility model proposes a kind of pectination joint design, comprise fuselage wallboard 1, wing wallboard 2, pectination joint groove 3 and rib 4.Wherein, pectination joint groove 3 is rectangle or square, is separately positioned on fuselage wallboard 1 and wing wallboard 2 coupling end separately, is provided with the bolt hole 5 of perforation between joint face and pectination joint groove 3.Fuselage wallboard 1 and wing wallboard 2 are bolted, and junction arranged beneath is useful on the rib 4 of support and connection structure, and rib 4 is bolted with fuselage wallboard 1.
The utility model is implemented according to following step:
1) according to design load, determine the quantity of pectination joint groove 3, namely determine the quantity of tie bolt.
2) fuselage wallboard 1 and wing wallboard 2 linkage section are separately carried out to part thickening, to ensure the structural strength of junction.
3) add pectination joint groove 3 at fuselage wallboard 1 and wing wallboard 2 connection terminal separately, groove presents oblong or square, and size will facilitate the installation of bolt.
4) bolt hole 5 that processing connects between joint face and pectination joint groove 3.
5) fuselage wallboard 1 and wing wallboard 2 are bolted.
6) rib 4 is set below connection structure, junction is provided support, rib 4 is bolted with fuselage wallboard 1.
It is the description to the utility model embodiment that foregoing should be understood to, but not is the concrete restriction to the utility model protection domain.
The alternative traditional auricle type of attachment of the utility model, adopt multiple bolts of similar " comb " shape to carry out being connected of wing and fuselage, load transmission evenly, directly, avoid the appearance of concentrated load phenomenon, reduced dead load, quick and easy for installation, the labour intensity alleviating, enhance productivity, be easy to promote the use of, there is larger practical value.
Claims (1)
1. a pectination joint design, is characterized in that: described pectination joint design comprises fuselage wallboard (1), wing wallboard (2), pectination joint groove (3), rib (4) and bolt hole (5);
Described pectination joint groove (3) is rectangle or square, is separately positioned on described fuselage wallboard (1) and wing wallboard (2) coupling end separately, is provided with the bolt hole (5) of perforation between joint face and pectination joint groove (3); Described fuselage wallboard (1) and wing wallboard (2) are bolted, and junction arranged beneath is useful on the rib (4) of support and connection structure, and described rib (4) is connected with fuselage wallboard (1) bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420155718.3U CN203793615U (en) | 2014-04-01 | 2014-04-01 | Comb-shaped joint structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420155718.3U CN203793615U (en) | 2014-04-01 | 2014-04-01 | Comb-shaped joint structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203793615U true CN203793615U (en) | 2014-08-27 |
Family
ID=51375855
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420155718.3U Expired - Lifetime CN203793615U (en) | 2014-04-01 | 2014-04-01 | Comb-shaped joint structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203793615U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105035356A (en) * | 2015-08-18 | 2015-11-11 | 江西洪都航空工业集团有限责任公司 | Multipoint coplane high-precision hole axis matching aircraft component butt joint coordination method |
| CN106043661A (en) * | 2016-06-08 | 2016-10-26 | 江西洪都航空工业集团有限责任公司 | Manual fuselage and wing quick butt joint method |
-
2014
- 2014-04-01 CN CN201420155718.3U patent/CN203793615U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105035356A (en) * | 2015-08-18 | 2015-11-11 | 江西洪都航空工业集团有限责任公司 | Multipoint coplane high-precision hole axis matching aircraft component butt joint coordination method |
| CN106043661A (en) * | 2016-06-08 | 2016-10-26 | 江西洪都航空工业集团有限责任公司 | Manual fuselage and wing quick butt joint method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140827 |