CN108284961B - Double-station aircraft nacelle - Google Patents
Double-station aircraft nacelle Download PDFInfo
- Publication number
- CN108284961B CN108284961B CN201810057288.4A CN201810057288A CN108284961B CN 108284961 B CN108284961 B CN 108284961B CN 201810057288 A CN201810057288 A CN 201810057288A CN 108284961 B CN108284961 B CN 108284961B
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- Prior art keywords
- nacelle
- hinge
- fixed
- pod
- crank
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- 238000009434 installation Methods 0.000 description 2
- 241000271566 Aves Species 0.000 description 1
- 241000272201 Columbiformes Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention discloses a double-station aircraft nacelle, which belongs to the field of aircraft accessories and comprises a nacelle fixed end and a nacelle movable end, wherein a fixed hook is arranged on the nacelle fixed end, a limiting surface is arranged between the nacelle fixed end and the nacelle movable end, a first hinge fixed column is arranged on the side edge of the nacelle fixed end, a first limiting hole is arranged below the first hinge fixed column, a second hinge fixed column is arranged on the side edge of the nacelle movable end, and a second limiting hole is arranged above the second hinge fixed column. According to the invention, the aircraft nacelle is divided into the fixed end and the movable end, the hinge device is added between the fixed end and the movable end to realize adjustment of the nacelle working direction, and the bolt with elastic force is added between the hinge device and the nacelle to realize final positioning and fastening between the nacelle two parts.
Description
Technical Field
The invention belongs to the field of aircraft accessories, and particularly relates to a double-station aircraft nacelle.
Background
Humans have long had the ideal flying in the air like birds, and mechanical pigeons manufactured by Alhitis in ancient Greek, flying to Australia, kongming lights in China and kites all have a relationship, and the development of modern aircraft benefits from the great leap of science and technology brought by the industrial revolution of the 19 th century. In the 19 th century, attempts to break through the air tie have been made, but all have failed. With the invention and widespread use of internal combustion engines, flying in air is increasingly possible. In 1903, the Laider brother in the United states first manufactured an aircraft capable of flying in the United states and achieved the dream of flying. Subsequently, aircraft and their related science and technology have been rapidly developed.
At present, an aircraft is usually required to mount various cabins to meet various task demands, the working states and directions of the cabins are mostly fixed, the utility is single, more cabins are required to be arranged for executing more complex tasks, the cost is increased, the transportation is inconvenient, and the cabins have great limitation and bring various inconveniences.
Disclosure of Invention
The object of the present invention is to provide a double station aircraft pod in order to solve the above-mentioned problems.
The invention realizes the above purpose through the following technical scheme:
the utility model provides an aircraft nacelle of duplex position, includes nacelle stiff end and nacelle expansion end, be provided with the fixed couple on the nacelle stiff end, the nacelle stiff end with be provided with the spacing face between the nacelle expansion end, nacelle stiff end side is provided with first hinge fixed column, first hinge fixed column below is provided with first spacing hole, nacelle expansion end side is provided with the second hinge fixed column, second hinge fixed column top is provided with the spacing hole of second, first hinge fixed column with install hinge mechanism between first spacing hole with second hinge fixed column and the spacing hole of second, be provided with fastening nut on the hinge mechanism, hinge mechanism comprises first crank, second crank, bolt main part, spring and bolt seat, first crank with the second crank passes through the bolt bulk phase is connected, be provided with on the bolt main part the spring, bolt main part externally mounted the bolt seat.
In the structure, in one working mode, the movable end of the nacelle is horizontally placed by pulling the hinge mechanism, the limiting surface is connected with the wider surface of the movable end of the nacelle, in the second working mode, the limiting surface is contacted with the narrower surface of the movable end of the nacelle by pulling the hinge mechanism, and in both working modes, the form of the invention is fixed through the bolt main body, the spring and the bolt seat, so that a working nacelle installation station is provided for an aircraft.
In order to further improve the service performance of the invention, the fixed hooks are nested and assembled with the fixed ends of the nacelle, and the number of the fixed hooks is two.
In order to further improve the usability of the invention, the nacelle fixed end is fixedly connected with the first hinge fixed column, and two side surfaces of the nacelle fixed end are respectively provided with one first hinge fixed column and two first limiting holes.
In order to further improve the usability of the invention, the movable end of the nacelle is fixedly connected with the second hinge fixing column, and two side surfaces of the movable end of the nacelle are respectively provided with one second hinge fixing column and two second limiting holes.
In order to further improve the usability of the hinge mechanism, the hinge mechanism is respectively connected with the first hinge fixing column, the first limiting hole, the second hinge fixing column and the second limiting hole in an assembling way.
In order to further improve the usability of the invention, the first crank and the second crank can rotate around the bolt main body, the bolt main body is nested and connected with the spring, and the bolt main body is fixedly connected with the bolt seat.
The beneficial effects are that: according to the invention, the aircraft nacelle is divided into the fixed end and the movable end, the hinge device is added between the fixed end and the movable end to realize adjustment of the nacelle working direction, and the bolt with elastic force is added between the hinge device and the nacelle to realize final positioning and fastening between the nacelle two parts.
Drawings
FIG. 1 is an exploded view of a duplex aircraft pod according to the present invention;
FIG. 2 is an exploded view of the hinge mechanism of a duplex aircraft pod of the present invention;
FIG. 3 is a perspective view of the operational state one of a duplex aircraft pod according to the present invention;
fig. 4 is a perspective view of a two-station aircraft pod according to the invention in a second operating mode.
The reference numerals are explained as follows: 1. a nacelle fixed end; 2. a fixed hook; 3. a first hinge fixing post; 4. a first limiting hole; 5. a limiting surface; 6. a nacelle movable end; 7. a second hinge fixing post; 8. a second limiting hole; 9. a fastening nut; 10. a hinge mechanism; 1001. a first crank; 1002. a second crank; 1003. a latch body; 1004. a spring; 1005. a latch base.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
as shown in fig. 1-4, a double-station aircraft nacelle comprises a nacelle fixed end 1 and a nacelle movable end 6, wherein a fixed hook 2 is arranged on the nacelle fixed end 1, a limiting surface 5 is arranged between the nacelle fixed end 1 and the nacelle movable end 6, a first hinge fixed column 3 is arranged on the side edge of the nacelle fixed end 1, a first limiting hole 4 is arranged below the first hinge fixed column 3, a second hinge fixed column 7 is arranged on the side edge of the nacelle movable end 6, a second limiting hole 8 is arranged above the second hinge fixed column 7, a hinge mechanism 10 is arranged between the first hinge fixed column 3 and the first limiting hole 4 and between the second hinge fixed column 7 and the second limiting hole 8, a fastening nut 9 is arranged on the hinge mechanism 10, the hinge mechanism 10 is composed of a first crank 1001, a second crank 1002, a bolt main body 1003, a spring 1004 and a bolt seat 1005, the first crank 1001 is connected with the second crank 1002 through the bolt main body 1003, the spring 1004 is arranged on the bolt main body 1003, and the bolt main body is externally provided with the bolt seat 1005.
In the above structure, in one operation mode, the movable end 6 of the nacelle is horizontally placed by pulling the hinge mechanism 10, and the limit surface 5 is contacted with the wider surface of the movable end 6 of the nacelle, in the second operation mode, the limit surface 5 is contacted with the narrower surface of the movable end 6 of the nacelle by pulling the hinge mechanism 10, and in both operation modes, the form of the invention is fixed by the bolt body 1003, the spring 1004 and the bolt seat 1005, so as to provide an operation nacelle installation station for an aircraft.
In order to further improve the usability of the invention, the fixed hooks 2 are assembled and connected with the nacelle fixed end 1 in a nesting manner, the fixed hooks 2 are two in number, the fixed hooks 2 can be used for hoisting the adapting device and used for completing various tasks, the nacelle fixed end 1 is fixedly connected with the first hinge fixed post 3, two side surfaces of the nacelle fixed end 1 are respectively provided with the first hinge fixed post 3 and two first limiting holes 4, the nacelle movable end 6 is fixedly connected with the second hinge fixed post 7, two side surfaces of the nacelle movable end 6 are respectively provided with the second hinge fixed post 7 and two second limiting holes 8, the hinge mechanism 10 is respectively assembled and connected with the first hinge fixed post 3, the first limiting holes 4 and the second hinge fixed post 7 and the second limiting holes 8, the first hinge fixed post 3, the first limiting holes 4 and the second hinge fixed post 7 can be used for fixing the hinge mechanism 10, the nacelle fixed end 1 and the nacelle movable end 6 can be adjusted in relative positions by pulling the fixed hinge mechanism 10, the first crank 1001 and the second crank movable end 1002 can rotate around the main body 1003, the nacelle movable end 1 can be fixedly connected with the nacelle movable end 1004 through the elastic fastening seat and the nacelle movable seat 1005, and the nacelle movable end 1 can be fixedly connected with the nacelle movable seat 1 through the elastic fastening seat and the elastic fixing seat 1005.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims.
Claims (6)
1. An aircraft pod with double stations, characterized by: comprises a pod fixed end (1) and a pod movable end (6), wherein a fixed hook (2) is arranged on the pod fixed end (1), a limiting surface (5) is arranged between the pod fixed end (1) and the pod movable end (6), a first hinge fixed column (3) is arranged on the side edge of the pod fixed end (1), a first limiting hole (4) is arranged below the first hinge fixed column (3), a second hinge fixed column (7) is arranged on the side edge of the pod movable end (6), a second limiting hole (8) is arranged above the second hinge fixed column (7), a hinge mechanism (10) is arranged between the first hinge fixed column (3) and the second hinge fixed column (7) and the second limiting hole (8), a fastening nut (9) is arranged on the hinge mechanism (10), the hinge mechanism (10) comprises a first crank (1001), a second crank (1003), a bolt main body (1003), a spring (1004) and a bolt seat (1003), the first crank (1003) is connected with the second crank (1003) through the bolt (1003), the latch body (1003) is externally mounted with the latch boss (1005).
2. A dual-station aircraft pod according to claim 1, wherein: the fixed hooks (2) are connected with the pod fixed end (1) in a nested and assembled mode, and the number of the fixed hooks (2) is two.
3. A dual-station aircraft pod according to claim 1, wherein: the nacelle fixed end (1) is fixedly connected with the first hinge fixed column (3), and one first hinge fixed column (3) and two first limiting holes (4) are respectively arranged on the side surfaces of two sides of the nacelle fixed end (1).
4. A dual-station aircraft pod according to claim 1, wherein: the nacelle moving end (6) is fixedly connected with the second hinge fixing columns (7), and one second hinge fixing column (7) and two second limiting holes (8) are respectively arranged on two side surfaces of the nacelle moving end (6).
5. A dual-station aircraft pod according to claim 1, wherein: the hinge mechanism (10) is respectively connected with the first hinge fixing column (3), the first limiting hole (4), the second hinge fixing column (7) and the second limiting hole (8) in an assembling mode.
6. A dual-station aircraft pod according to claim 1, wherein: the first crank (1001) and the second crank (1002) can rotate around the bolt main body (1003), the bolt main body (1003) is connected with the spring (1004) in a nested mode, and the bolt main body (1003) is fixedly connected with the bolt seat (1005).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810057288.4A CN108284961B (en) | 2018-01-22 | 2018-01-22 | Double-station aircraft nacelle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810057288.4A CN108284961B (en) | 2018-01-22 | 2018-01-22 | Double-station aircraft nacelle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108284961A CN108284961A (en) | 2018-07-17 |
| CN108284961B true CN108284961B (en) | 2023-10-31 |
Family
ID=62835422
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810057288.4A Active CN108284961B (en) | 2018-01-22 | 2018-01-22 | Double-station aircraft nacelle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108284961B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AT53717B (en) * | 1910-11-08 | 1912-05-25 | Luft Verkehrs Gmbh | Suspension of nacelles for aircraft. |
| US5755403A (en) * | 1995-05-24 | 1998-05-26 | Societe Nationale Industrielle Et Aerospitiale | Aircraft motor pod including a pivotable pod cowling |
| AU2003264626A1 (en) * | 1998-08-06 | 2004-01-08 | Jean-Francois Tardy | Device suspended to a carrier for rescuing people or equipment |
| CN202464136U (en) * | 2012-02-15 | 2012-10-03 | 武汉华中天经光电系统有限公司 | Photoelectric nacelle |
| KR20130110890A (en) * | 2012-03-30 | 2013-10-10 | 현대중공업 주식회사 | Foldable gondola |
| US9296470B1 (en) * | 2013-03-12 | 2016-03-29 | The Boeing Company | Deployable apparatus for use with air vehicles |
| CN207843342U (en) * | 2018-01-22 | 2018-09-11 | 深圳市科卫泰实业发展有限公司 | A kind of aircraft gondola of double-station |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8128026B2 (en) * | 2007-07-12 | 2012-03-06 | David Barbour Shelton | Removable cargo pod with lifting mechanism and open top |
| US9470468B2 (en) * | 2014-02-24 | 2016-10-18 | Falkor Sid, Inc. | Handguard with integrated pod and firearm |
-
2018
- 2018-01-22 CN CN201810057288.4A patent/CN108284961B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AT53717B (en) * | 1910-11-08 | 1912-05-25 | Luft Verkehrs Gmbh | Suspension of nacelles for aircraft. |
| US5755403A (en) * | 1995-05-24 | 1998-05-26 | Societe Nationale Industrielle Et Aerospitiale | Aircraft motor pod including a pivotable pod cowling |
| AU2003264626A1 (en) * | 1998-08-06 | 2004-01-08 | Jean-Francois Tardy | Device suspended to a carrier for rescuing people or equipment |
| CN202464136U (en) * | 2012-02-15 | 2012-10-03 | 武汉华中天经光电系统有限公司 | Photoelectric nacelle |
| KR20130110890A (en) * | 2012-03-30 | 2013-10-10 | 현대중공업 주식회사 | Foldable gondola |
| US9296470B1 (en) * | 2013-03-12 | 2016-03-29 | The Boeing Company | Deployable apparatus for use with air vehicles |
| CN207843342U (en) * | 2018-01-22 | 2018-09-11 | 深圳市科卫泰实业发展有限公司 | A kind of aircraft gondola of double-station |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108284961A (en) | 2018-07-17 |
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