CN203473239U - Mounting base for main landing gear of TB20 airplane - Google Patents
Mounting base for main landing gear of TB20 airplane Download PDFInfo
- Publication number
- CN203473239U CN203473239U CN201320418744.6U CN201320418744U CN203473239U CN 203473239 U CN203473239 U CN 203473239U CN 201320418744 U CN201320418744 U CN 201320418744U CN 203473239 U CN203473239 U CN 203473239U
- Authority
- CN
- China
- Prior art keywords
- mounting base
- boss
- mount pad
- base body
- pad body
- 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 - Fee Related
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Abstract
The utility model discloses a mounting base for a main landing gear of a TB20 airplane. The mounting base comprises a mounting base body, wherein a boss is arranged at the middle part of the upper surface of the mounting base body, a reinforcing rib is arranged at the connecting position of the boss and the mounting base body, a bushing hole is formed in the boss and extends to the bottom of the mounting base body, bushings are arranged at the upper part and the lower part in the bushing hole respectively, the bushing is in interference fitting with the boss, and a mounting hole is formed in the mounting base body. The mounting base has reasonable structure design, the reinforcing rib is arranged at the connecting position of the boss and the mounting base body, so that the rigidity of the mounting base is increased, the stress concentration tendency is reduced, and the capacity of bearing effective load is improved; and besides, the boss and the mounting base body are formed by aluminium alloy through once forging, therefore, the static strength and the fatigue resistance of the mounting base are improved; and the bushing is made of aluminium-copper-zinc material, thereby having high strength and long service life.
Description
Technical field
The utility model relates to a kind of TB20 Aircraft Main alighting gear, particularly a kind of TB20 Aircraft Main alighting gear mount pad.
Background technology
?tB20 Aircraft Main alighting gear mount pad is load parts important in TB20 Aircraft Main landing gear, when this type aircraft of maintenance, on most aircrafts of finding to overhaul, this assembly is by crackle in various degree, and it is also all identical that crackle produces position, all appear at " R " corner in its arc transition region, both sides, shaft hole bottom, changing has the mount pad element of crackle need be from external import, expensive, can not meet people's requirement.
Summary of the invention
The purpose of this utility model is just to provide a kind of reasonable in design, bears payload capability high, the TB20 Aircraft Main alighting gear mount pad of long service life.
To achieve these goals, the technical solution adopted in the utility model is such: TB20 Aircraft Main alighting gear mount pad of the present utility model, comprise mount pad body, described mount pad body upper surface middle part is provided with boss, and boss and mount pad body junction are provided with reinforced rib, and boss is provided with bush hole, bush hole extends to mount pad body bottom, in bush hole, top and the bottom are provided with respectively lining, lining and boss interference fit, and described mount pad body is provided with mounting hole.
As preferably, described boss and mount pad body adopt forging molding of aluminum alloy.
As preferably, described lining adopts aluminium zinc-copper material to make.
Compared with prior art, the utility model has the advantage of: the utility model reasonable in design, boss and mount pad body junction are provided with reinforced rib, have increased the intensity of mount pad, have reduced the concentrated tendency of stress, improved the ability of bearing capacity weight, boss and mount pad body adopt forging molding of aluminum alloy, improve its static strength and fatigue resistance, and lining adopts aluminium zinc-copper material to make, its intensity is high, long service life.
Accompanying drawing explanation
Fig. 1 is 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, TB20 Aircraft Main alighting gear mount pad of the present utility model, comprise mount pad body 1, described mount pad body 1 upper surface middle part is provided with boss 2, boss 2 is provided with reinforced rib 5 with mount pad body 1 junction, boss 2 is provided with bush hole, bush hole extends to mount pad body 1 bottom, in bush hole, top and the bottom are provided with respectively lining 3, lining 3 and boss 2 interference fit, described mount pad body 1 is provided with mounting hole 4, and described boss 2 adopts forging molding of aluminum alloy with mount pad body 1, and described lining 3 adopts aluminium zinc-copper material to make.
During use, main landing gear can pack in the axis hole of mount pad in the rotating shaft of holding bar, boss 2 is provided with reinforced rib 5 with mount pad body 1 junction, has increased the intensity of mount pad, has reduced the concentrated tendency of stress, improved the ability of bearing capacity weight, boss 2 adopts forging molding of aluminum alloy with mount pad body 1, improves its static strength and fatigue resistance, and lining 3 adopts aluminium zinc-copper material to make, its intensity is high, long service life.
Claims (3)
1. a TB20 Aircraft Main alighting gear mount pad, comprise mount pad body, it is characterized in that: described mount pad body upper surface middle part is provided with boss, boss and mount pad body junction are provided with reinforced rib, boss is provided with bush hole, and bush hole extends to mount pad body bottom, and in bush hole, top and the bottom are provided with respectively lining, lining and boss interference fit, described mount pad body is provided with mounting hole.
2. TB20 Aircraft Main alighting gear mount pad according to claim 1, is characterized in that: described boss and mount pad body adopt forging molding of aluminum alloy.
3. TB20 Aircraft Main alighting gear mount pad according to claim 1, is characterized in that: described lining adopts aluminium zinc-copper material to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320418744.6U CN203473239U (en) | 2013-07-15 | 2013-07-15 | Mounting base for main landing gear of TB20 airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320418744.6U CN203473239U (en) | 2013-07-15 | 2013-07-15 | Mounting base for main landing gear of TB20 airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203473239U true CN203473239U (en) | 2014-03-12 |
Family
ID=50221621
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320418744.6U Expired - Fee Related CN203473239U (en) | 2013-07-15 | 2013-07-15 | Mounting base for main landing gear of TB20 airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203473239U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104210652A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Landing gear connecting structure |
| CN105564640A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Method for reducing course vibration of nose landing gear |
| CN112173083A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Tail undercarriage attach fitting |
-
2013
- 2013-07-15 CN CN201320418744.6U patent/CN203473239U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104210652A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Landing gear connecting structure |
| CN105564640A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Method for reducing course vibration of nose landing gear |
| CN112173083A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Tail undercarriage attach fitting |
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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 |