CN203473237U - Support wing rib assembly for main landing gear of TB200 airplane - Google Patents
Support wing rib assembly for main landing gear of TB200 airplane Download PDFInfo
- Publication number
- CN203473237U CN203473237U CN201320418699.4U CN201320418699U CN203473237U CN 203473237 U CN203473237 U CN 203473237U CN 201320418699 U CN201320418699 U CN 201320418699U CN 203473237 U CN203473237 U CN 203473237U
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- Prior art keywords
- web
- reinforced sheet
- wing rib
- web plate
- rib assembly
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- Expired - Fee Related
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Abstract
The utility model discloses a support wing rib assembly for a main landing gear of a TB200 airplane. The wing rib assembly is formed by two wing ribs with the same size and shape through riveting in an overlapping manner, wherein each wing rib comprises a web plate and edge strips arranged on the web plate and away from the four sides of an overlapped surface, a main landing gear cross beam mounting hole is formed in the web plate, close to the upper edge strip, a reinforced sheet is arranged on the web plate, corresponding to the main landing gear cross beam mounting hole, the reinforced sheet and the edge strips are arranged at the same side of the web plate, an upper flange is arranged on the reinforced sheet and is fitted with the upper edge strip, and a lightening hole is formed in the web plate. The support wing rib assembly has reasonable structure design, the reinforced sheet is arranged on the web plate, corresponding to the mounting hole, so as to enhance the strength and the rigidity of the periphery of the mounting hole of the support wing rib assembly, therefore, the support wing rib assembly has good fatigue resistance, and the service life of the support wing rib assembly is prolonged; and besides, the lighting hole is formed in the web plate, so that the weight of the support wing rib assembly is reduced.
Description
Technical field
The utility model relates to a kind of TB200 Aircraft Main alighting gear, and particularly a kind of TB200 Aircraft Main alighting gear supports rib assemblies.
Background technology
?the original-pack main landing gear of TB200 aircraft supports rib assemblies and only in main landing gear crossbeam place mounting hole one side, the triangular aluminum reinforced sheet that one size is less is set, mounting hole top is connected upper crimp and the covering riveting that only depends on rib main component with covering, the intensity of this rib assemblies material, poor rigidity, fatigue resistance is poor, service life is short, and maintenance cost is higher.
Summary of the invention
The purpose of this utility model is just to provide a kind of reasonable in design, and intensity, rigidity are high, and fatigue resistance is good, and the TB200 Aircraft Main alighting gear of long service life supports rib assemblies.
To achieve these goals, the technical solution adopted in the utility model is such: TB200 Aircraft Main alighting gear of the present utility model supports rib assemblies, this rib assemblies is formed by the overlapping riveted joint of the identical rib of two shape sizes, described rib comprises web and is arranged on web away from the edge strip of faying surface four sides, web is provided with main landing gear crossbeam mounting hole near upper edge strip place, on described web, the position of corresponding mounting hole is provided with reinforced sheet, reinforced sheet and edge strip are arranged on web the same side, reinforced sheet is provided with crimp, upper crimp and the laminating of upper edge strip, described web is provided with lightening hole.
As preferably, described reinforced sheet is stainless steel sheet, and thickness is 1mm.
As preferably, described reinforced sheet is riveted by rivet and web.
Compared with prior art, the utility model has the advantage of: the utility model reasonable in design, on web, the position of mounting hole arranges reinforced sheet, strengthened and supported rib assemblies mounting hole intensity, rigidity around, make its fatigue resistance good, extend its service life, lightening hole has been set on web, alleviated the weight that supports rib assemblies.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is another structural representation of the present utility model.
The specific embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Referring to Fig. 1 and Fig. 2, TB200 Aircraft Main alighting gear of the present utility model supports rib assemblies, this rib assemblies is formed by the overlapping riveted joint of the identical rib of two shape sizes, described rib comprises web 1 and is arranged on web 1 away from the edge strip 2 of faying surface four sides, web 1 is provided with main landing gear crossbeam mounting hole 3 near upper edge strip 2 places, on described web 1, the position of corresponding mounting hole 3 is provided with reinforced sheet 4, reinforced sheet 4 is arranged on web the same side with edge strip 2, reinforced sheet 4 is provided with crimp, upper crimp and 2 laminatings of upper edge strip, described web 1 is provided with lightening hole 5, described reinforced sheet 4 is stainless steel sheet, thickness is 1mm, described reinforced sheet 4 is by rivet and web 1 riveted joint.
Rivet hole 6 is set on web 1, support rib assemblies is passed rivet hole 6 riveted joints by the identical rib of two shape sizes by rivet and is formed, main landing gear transom bolt is fixed in mounting hole 3, on web 1, the position of mounting hole 3 arranges reinforced sheet 4, strengthened and supported rib assemblies mounting hole 3 intensity, rigidity around, made its fatigue resistance good, extended its service life, lightening hole 5 is set on web 1, has alleviated the weight that supports rib assemblies.
Claims (3)
1. a TB200 Aircraft Main alighting gear supports rib assemblies, this rib assemblies is formed by the overlapping riveted joint of the identical rib of two shape sizes, described rib comprises web and is arranged on web away from the edge strip of faying surface four sides, web is provided with main landing gear crossbeam mounting hole near upper edge strip place, it is characterized in that: on described web, the position of corresponding mounting hole is provided with reinforced sheet, reinforced sheet and edge strip are arranged on web the same side, reinforced sheet is provided with crimp, upper crimp and the laminating of upper edge strip, described web is provided with lightening hole.
2. TB200 Aircraft Main alighting gear according to claim 1 supports rib assemblies, it is characterized in that: described reinforced sheet is stainless steel sheet, and thickness is 1mm.
3. TB200 Aircraft Main alighting gear according to claim 1 supports rib assemblies, it is characterized in that: described reinforced sheet is riveted by rivet and web.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320418699.4U CN203473237U (en) | 2013-07-15 | 2013-07-15 | Support wing rib assembly for main landing gear of TB200 airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320418699.4U CN203473237U (en) | 2013-07-15 | 2013-07-15 | Support wing rib assembly for main landing gear of TB200 airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203473237U true CN203473237U (en) | 2014-03-12 |
Family
ID=50221619
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320418699.4U Expired - Fee Related CN203473237U (en) | 2013-07-15 | 2013-07-15 | Support wing rib assembly for main landing gear of TB200 airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203473237U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3202660A1 (en) * | 2016-02-08 | 2017-08-09 | Bell Helicopter Textron Inc. | Composite rib assembly |
| CN110979725A (en) * | 2020-01-02 | 2020-04-10 | 上海蓝享机械制造有限公司 | Airplane wing rib and production process thereof |
-
2013
- 2013-07-15 CN CN201320418699.4U patent/CN203473237U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3202660A1 (en) * | 2016-02-08 | 2017-08-09 | Bell Helicopter Textron Inc. | Composite rib assembly |
| US20170225766A1 (en) * | 2016-02-08 | 2017-08-10 | Bell Helicopter Textron Inc. | Composite rib assembly |
| US10513324B2 (en) * | 2016-02-08 | 2019-12-24 | Bell Helicopter Textron Inc. | Composite rib assembly |
| US10513325B2 (en) | 2016-02-08 | 2019-12-24 | Bell Helicopter Textron Inc. | Joint member for a composite wing structure |
| CN110979725A (en) * | 2020-01-02 | 2020-04-10 | 上海蓝享机械制造有限公司 | Airplane wing rib and production process thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140312 Termination date: 20160715 |