CN111720435A - Device for adjusting erecting eccentricity of airplane - Google Patents
Device for adjusting erecting eccentricity of airplane Download PDFInfo
- Publication number
- CN111720435A CN111720435A CN201910201105.6A CN201910201105A CN111720435A CN 111720435 A CN111720435 A CN 111720435A CN 201910201105 A CN201910201105 A CN 201910201105A CN 111720435 A CN111720435 A CN 111720435A
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- Prior art keywords
- eccentric
- bush
- bushing
- outer liner
- aircraft
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- 238000000034 method Methods 0.000 abstract description 9
- 238000009434 installation Methods 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C25/00—Bearings for exclusively rotary movement adjustable for wear or play
- F16C25/02—Sliding-contact bearings
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The utility model belongs to the aircraft field of making especially relates to a device that is used for aircraft to erect eccentric regulation, including eccentric inner bush and eccentric outer liner, eccentric inner bush and eccentric outer liner are provided with the axle center deviation, and the aircraft plays the vertical axis and installs in eccentric inner bush, eccentric inner bush is located inside the eccentric outer liner, the outside of eccentric outer liner is provided with ordinary bush, ordinary bush passes through pressure disk and eccentric outer liner fixed connection. The application provides a design for adjusting eccentric clearance's device, solves the dismouting difficulty problem of certain novel unmanned aerial vehicle erecting the in-process to erecting the vertical axis. The difficult problem of aircraft erection shaft dismouting can be solved in inside and outside eccentric bush structural design to the dismouting requirement is satisfied in eccentric bush clearance design, and 360 degrees rotations just can guarantee the dismouting clearance in same position moreover, can satisfy its application of erecting the in-process at unmanned aerial vehicle.
Description
Technical Field
The application belongs to the field of aircraft manufacturing, and particularly relates to a device for adjusting the erecting eccentricity of an aircraft.
Background
The whole heat insulating tile that has posted of certain novel unmanned aerial vehicle fuselage, because of heat insulating tile structural feature, the aircraft lifts by crane, operation such as upset can only be connected through four standpoints of organism. Considering that the erecting shaft connected with the erecting point is convenient to disassemble and assemble with the machine body, a gap of 2-3 mm is required to be reserved between the erecting shaft and a joint bearing arranged in the erecting hole of the machine body. Therefore, a device for changing the gap position is required, and therefore, an eccentric adjustment device is important.
Disclosure of Invention
The application provides a design for adjusting eccentric clearance's device, solves the dismouting difficulty problem of certain novel unmanned aerial vehicle erecting the in-process to erecting the vertical axis.
In order to achieve the technical problem, the technical scheme adopted by the application is as follows:
a device for adjusting the erecting eccentricity of an airplane is characterized in that: the aircraft vertical shaft installation structure comprises an eccentric inner bushing and an eccentric outer bushing, wherein the eccentric inner bushing and the eccentric outer bushing are provided with shaft center deviation, an aircraft vertical shaft is installed in the eccentric inner bushing, the eccentric inner bushing is located inside the eccentric outer bushing, a common bushing is arranged outside the eccentric outer bushing, and the common bushing is fixedly connected with the eccentric outer bushing through a pressure plate.
The axis deviation of the eccentric inner bushing and the eccentric outer bushing is 1-5 mm.
The axle center deviation of eccentric interior bush and eccentric outer liner is 3 mm.
One end of the eccentric outer bushing is compressed by a large locknut.
One end of the vertical shaft penetrates through the inside of the eccentric inner bushing, and the other end of the vertical shaft is fixed with a joint bearing.
The application has the advantages that:
the application provides a design for adjusting eccentric clearance's device, solves the dismouting difficulty problem of certain novel unmanned aerial vehicle erecting the in-process to erecting the vertical axis. The difficult problem of aircraft erection shaft dismouting can be solved in inside and outside eccentric bush structural design to the dismouting requirement is satisfied in eccentric bush clearance design, and 360 degrees rotations just can guarantee the dismouting clearance in same position moreover, can satisfy its application of erecting the in-process at unmanned aerial vehicle.
Drawings
FIG. 1 is a schematic view of an eccentric bushing.
Fig. 2 eccentric bushing installation drawing.
FIG. 3 is a cross-sectional view of an eccentric bushing.
In the drawings: 1-large locknut, 2-bush, 3-vertical shaft, 4-joint bearing, 5-eccentric inner bush, 6-pressure plate, 7-connecting screw and 8-eccentric outer bush.
Detailed Description
Example 1
The device for adjusting the erection eccentricity of the airplane comprises an eccentric inner bushing 5 and an eccentric outer bushing 8, wherein the eccentric inner bushing 5 and the eccentric outer bushing 8 are provided with axis deviation, an airplane erection shaft 3 is installed in the eccentric inner bushing 5, the eccentric inner bushing 5 is located inside the eccentric outer bushing 8, a common bushing 2 is arranged outside the eccentric outer bushing 8, and the common bushing 2 is fixedly connected with the eccentric outer bushing 8 through a pressure plate 6.
The application provides a design that can be used to adjust device in eccentric clearance solves certain novel unmanned aerial vehicle and erects the in-process to the dismouting difficulty problem of playing vertical axis 3. The 3 dismouting difficulty problems of aircraft rising shaft can be solved to 2 structural design of inside and outside eccentric bush to 2 clearance designs of eccentric bush satisfy the dismouting requirement, 360 degrees rotations just can guarantee the dismouting clearance in same position moreover, can satisfy its application of erecting the in-process at unmanned aerial vehicle.
Example 2
The device for adjusting the erection eccentricity of the airplane comprises an eccentric inner bushing 5 and an eccentric outer bushing 8, wherein the eccentric inner bushing 5 and the eccentric outer bushing 8 are provided with axis deviation, an airplane erection shaft 3 is installed in the eccentric inner bushing 5, the eccentric inner bushing 5 is located inside the eccentric outer bushing 8, a common bushing 2 is arranged outside the eccentric outer bushing 8, and the common bushing 2 is fixedly connected with the eccentric outer bushing 8 through a pressure plate 6.
The axle center deviation of the eccentric inner bushing 5 and the eccentric outer bushing 8 is 1-5 mm. Preferably, the eccentric inner bushing 5 and the eccentric outer bushing 8 have an axial deviation of 3 mm.
One end of the eccentric outer bushing 8 is pressed by a large locknut 1. One end of the vertical shaft 3 passes through the inside of the eccentric inner bushing 5, and the other end of the vertical shaft 3 is fixed with a joint bearing 4.
This application designs a set of eccentric bush 2, and 3 mm's axle center deviation is designed to inside and outside eccentric bush 2, and the aircraft plays vertical axis 3 and installs in eccentric neck bush 5. The joint bearing 4 is installed at one end of the vertical shaft 3, the common bushing 2 is installed outside the eccentric bushing 2 group and fixed through the pressure plate 6, and the large locknut 1 is adopted to compress one section of the eccentric outer bushing 8, so that the problem of difficulty in dismounting the vertical shaft 3 is solved.
The application provides a design that can be used to adjust device in eccentric clearance solves certain novel unmanned aerial vehicle and erects the in-process to the dismouting difficulty problem of playing vertical axis 3. The 3 dismouting difficulty problems of aircraft rising shaft can be solved to 2 structural design of inside and outside eccentric bush to 2 clearance designs of eccentric bush satisfy the dismouting requirement, 360 degrees rotations just can guarantee the dismouting clearance in same position moreover, can satisfy its application of erecting the in-process at unmanned aerial vehicle.
Claims (5)
1. A device for adjusting the erecting eccentricity of an airplane is characterized in that: including eccentric inner bush (5) and eccentric outer liner (8), eccentric inner bush (5) and eccentric outer liner (8) are provided with the axle center deviation, and aircraft plays vertical axis (3) and installs in eccentric inner bush (5), eccentric inner bush (5) are located eccentric outer liner (8) inside, the outside of eccentric outer liner (8) is provided with ordinary bush (2), ordinary bush (2) are through pressure disk (6) and eccentric outer liner (8) fixed connection.
2. A device for aircraft departure eccentricity adjustment according to claim 1, wherein: the axis deviation of the eccentric inner bushing (5) and the eccentric outer bushing (8) is 1-5 mm.
3. A device for aircraft departure eccentricity adjustment according to claim 2, wherein: the axis deviation of the eccentric inner bushing (5) and the eccentric outer bushing (8) is 3 mm.
4. A device for aircraft departure eccentricity adjustment according to claim 1, wherein: one end of the eccentric outer bushing (8) is compressed by a large anti-loose nut (1).
5. A device for aircraft departure eccentricity adjustment according to claim 1, wherein: one end of the vertical shaft (3) penetrates through the inside of the eccentric inner bushing (5), and the other end of the vertical shaft (3) is fixed with a joint bearing (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910201105.6A CN111720435A (en) | 2019-03-18 | 2019-03-18 | Device for adjusting erecting eccentricity of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910201105.6A CN111720435A (en) | 2019-03-18 | 2019-03-18 | Device for adjusting erecting eccentricity of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111720435A true CN111720435A (en) | 2020-09-29 |
Family
ID=72562044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910201105.6A Pending CN111720435A (en) | 2019-03-18 | 2019-03-18 | Device for adjusting erecting eccentricity of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111720435A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112390137A (en) * | 2020-09-30 | 2021-02-23 | 成都飞机工业（集团）有限责任公司 | Aircraft erecting device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB215819A (en) * | 1923-02-10 | 1924-05-12 | British Thomson Houston Co Ltd | Improved means for transmitting motion from one rotating member to another arranged concentric therewith |
| DE3635569A1 (en) * | 1985-12-17 | 1987-07-09 | Polygraph Leipzig | Sliding bearing for cylinders of printing machines |
| CN101074701A (en) * | 2007-06-26 | 2007-11-21 | 中国航空工业第一集团公司成都飞机设计研究所 | Double-eccentric bushing and its adjustment |
| EP2041383B1 (en) * | 2006-06-30 | 2013-03-20 | Leifheit AG | Ground sleeve with an adjusting device |
| CN204942222U (en) * | 2015-09-22 | 2016-01-06 | 江西洪都航空工业集团有限责任公司 | A kind of eccentric bush with auto-lock function |
-
2019
- 2019-03-18 CN CN201910201105.6A patent/CN111720435A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB215819A (en) * | 1923-02-10 | 1924-05-12 | British Thomson Houston Co Ltd | Improved means for transmitting motion from one rotating member to another arranged concentric therewith |
| DE3635569A1 (en) * | 1985-12-17 | 1987-07-09 | Polygraph Leipzig | Sliding bearing for cylinders of printing machines |
| EP2041383B1 (en) * | 2006-06-30 | 2013-03-20 | Leifheit AG | Ground sleeve with an adjusting device |
| CN101074701A (en) * | 2007-06-26 | 2007-11-21 | 中国航空工业第一集团公司成都飞机设计研究所 | Double-eccentric bushing and its adjustment |
| CN204942222U (en) * | 2015-09-22 | 2016-01-06 | 江西洪都航空工业集团有限责任公司 | A kind of eccentric bush with auto-lock function |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112390137A (en) * | 2020-09-30 | 2021-02-23 | 成都飞机工业（集团）有限责任公司 | Aircraft erecting device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200929 |