CN207157489U - A kind of horizontal folding mechanism applied to aircraft - Google Patents
A kind of horizontal folding mechanism applied to aircraft Download PDFInfo
- Publication number
- CN207157489U CN207157489U CN201721117182.6U CN201721117182U CN207157489U CN 207157489 U CN207157489 U CN 207157489U CN 201721117182 U CN201721117182 U CN 201721117182U CN 207157489 U CN207157489 U CN 207157489U
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- CN
- China
- Prior art keywords
- sleeve pipe
- horizontal folding
- horn
- main
- main sleeve
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Abstract
The utility model discloses a kind of horizontal folding mechanism applied to aircraft, including：Horn, described horn one end set mounting seat, and the mounting seat is used to assemble the Power Component for providing power for rotor craft；With the main sleeve pipe of horn other end socket, the main sleeve pipe is rotatably connected the fuselage in rotor craft；The fuselage of the rotor craft is provided with locking member, and main sleeve pipe is fixed on the fuselage of the rotor craft by the locking member under deployed condition.The utility model is because using after horizontal folding horn horizontal folding, volume significantly reduces, it is easier to stores, the ability of the structure confrontation aircraft Z-direction vibrations of horizontal folding greatly improves.
Description
Technical field
The utility model belongs to rotor craft technical field, is related to a kind of horizontal folding mechanism applied to aircraft,
Especially facilitate the folding storage of rotor craft horn.
Background technology
The folding mode of existing rotor craft horn and fuselage is more by the way of umbrella folding.It is folded along horn.
Aircraft after folding in this way, is still not easy to store because horn is longer, after folding.Simultaneously as umbrella folded structure
The snap fit on fuselage can only be leaned on to block the folded piece on horn and produce lateral pull.Held very much using rear snap fit and folded piece for a long time
Easily wear.Cause the gap of horn and fuselage junction to become big, so that fuselage vibrations become big during flight, influence flight peace
Entirely.
The content of the invention
The purpose of this utility model is to provide a kind of horizontal folding mechanism applied to aircraft, solves in the prior art
The problem of existing.
Technical scheme is used by the utility model：
A kind of horizontal folding mechanism applied to aircraft, including：
Horn, described horn one end set mounting seat, and the mounting seat is used to assemble provides power for rotor craft
Power Component；
With the main sleeve pipe of horn other end socket, the main sleeve pipe is rotatably connected the fuselage in rotor craft；
The fuselage of the rotor craft is provided with locking member, and main sleeve pipe is fixed on institute by the locking member under deployed condition
State on the fuselage of rotor craft.
In a preferred embodiment of the present utility model, the main sleeve pipe passes through the first screw connection with the horn.
In a preferred embodiment of the present utility model, in addition to locking sleeve and locking sleeve pipe, the locking sleeve
Rotate and be tightened on main sleeve pipe successively with locking sleeve pipe.
In a preferred embodiment of the present utility model, the main sleeve pipe includes main union body, the main union body
The lateral wall of one end is provided with external screw thread, and the other end is provided with the screw mounting flange fixed with first screw, the master
Sleeve pipe can rotate around first screw.
In a preferred embodiment of the present utility model, positioning is additionally provided with the lateral wall of the main union body and is lacked
Mouthful, the locking member blocks the locating notch so that main sleeve pipe is fixed on the fuselage of the rotor craft.
In a preferred embodiment of the present utility model, the inner surface of the locking sleeve has internal thread, the interior spiral shell
The external screw thread of line and the main sleeve pipe is connected.
In a preferred embodiment of the present utility model, the main sleeve pipe, locking sleeve and locking sleeve pipe are in integrally cylinder
Shape.
In a preferred embodiment of the present utility model, the locking member section is in crescent shape, and two locking members coordinate
Main sleeve pipe is fixed.
By using above technical scheme, technique effect of the present utility model：
The utility model is because using after horizontal folding horn horizontal folding, volume significantly reduces, it is easier to stores, it is horizontal
The ability of the structure confrontation aircraft Z-direction vibrations of folding greatly improves.
Brief description of the drawings
Fig. 1 a are deployed condition schematic diagram of the present utility model.
Fig. 1 b are deployed condition schematic diagram of the present utility model.
Fig. 2 a are the partial enlarged drawing of deployed condition of the present utility model.
Fig. 2 b are the partial enlarged drawing of folded state of the present utility model.
Fig. 3 is the structural representation of main sleeve pipe of the present utility model.
Fig. 4 is the structural representation of locking member of the present utility model.
Embodiment
The utility model is described in detail with reference to the accompanying drawings and detailed description.
Shown in reference picture 1a, Fig. 1 b and Fig. 2 a, Fig. 2 b, a kind of horizontal folding mechanism applied to aircraft, including：Machine
Arm 4, described horn one end set mounting seat 5, and the mounting seat is used to assemble the Power Component for providing power for rotor craft；
With the main sleeve pipe 1 of horn other end socket, the main sleeve pipe 1 is rotatably connected the fuselage in rotor craft；
The fuselage of the rotor craft is provided with locking member 9, and the locking member 9 fixes main sleeve pipe 1 under deployed condition
In on the fuselage of the rotor craft.Further, the main sleeve pipe 1 passes through the first screw connection with the horn 4.
The utility model also includes locking sleeve 2 and locking sleeve pipe 3, and the locking sleeve 2 and locking sleeve pipe 3 rotate successively
It is tightened on main sleeve pipe 1.
Shown in reference picture 3, wherein main sleeve pipe 1 includes main union body 10, the lateral wall of one end of the main union body is set
There is external screw thread 101, the other end is provided with the screw mounting flange 102 fixed with first screw, and the main sleeve pipe can be around institute
State the rotation of the first screw.Locating notch 103 is additionally provided with the lateral wall of main union body 10, it is described fixed that the locking member 9 blocks
Position breach is so that main sleeve pipe is fixed on the fuselage of the rotor craft.
The inner surface of locking sleeve described above has internal thread, and the external screw thread of the internal thread and the main sleeve pipe coordinates company
Connect.And the inner surface of locking sleeve has internal thread, the external screw thread of the internal thread and the main sleeve pipe is connected.
Shown in reference picture 4, for the ease of assembling, the main sleeve pipe, locking sleeve and locking sleeve pipe are integrally cylindrical in shape.And lock
The tight section of part 9 is in crescent shape, and two locking members, which coordinate, fixes main sleeve pipe.
Before and after being folded such as figure the utility model aircraft shown in comparison diagram, aircraft milling machine arm uses the side of horizontal folding
Formula.Volume after folding diminishes, and is easy to store.
Fuselage is connected with horn by horizontal folding mechanism, and its part integrally forms as follows：
Main sleeve pipe 1, material are aluminium alloy.Entirety is cylindrical in shape, and one end band external screw thread, the other end carries rectangular indentation；Tail end
With upper and lower two screw mounting flanges, there is through hole centre.
Locking sleeve 2, material are aluminium alloy；Entirety is cylindrical in shape, and there is annular knurl line outer surface, and inner surface has internal thread, with master
The external screw thread matching of sleeve pipe 1；
Locking sleeve pipe 3, material are aluminium alloy.Entirety is cylindrical in shape, and there is annular knurl line outer surface, and inner surface has internal thread, with master
The external screw thread matching of sleeve pipe 1；
Horn 4, material are carbon fiber.Circular tube shaped, it is hollow.External diameter matches with the internal diameter of main sleeve pipe 1；Mounting seat 5, material are
Aluminium alloy；The Power Component screw 6 of power is provided for rotor craft for assembling, material is carbon steel；Rotating shaft screw 7, material
For carbon steel；Fastening screw 8, material are carbon steel；
Threaded locking member 9, material are aluminium alloy, and section is in crescent shape.There are two tapped through holes one end, separately
One end is threaded halfpipe locking position；Fuselage 10 is carbon plate, and material is carbon fiber, and there is mounting hole on its surface.With main sleeve pipe 1
Pass through screw connection with threaded locking member 9.
Horn part is made up of following part：
Main sleeve pipe 1 is connected with horn 4 by screw 6；Locking sleeve 2 and locking sleeve pipe 3, are sequentially sleeved on horn 4；Motor
Mounting seat 5 is screwed on horn 4；
Horn part is connected by rotating shaft screw 7 with fuselage 10, and rotating shaft screw 7 is through fuselage carbon 10, main sleeve pipe 1 tail end
It is fixed after through hole.Threaded locking member 9 is fixed on fuselage by fastening screw.
The utility model uses horizontal folding structure, connects fuselage and the horn part of rotor craft.With rotating shaft screw 7
Centered on, by rotating horn, control the folding between main sleeve pipe 1 and threaded locking member 9 realize the folding of horn with
Open.Locking sleeve 2, locking sleeve pipe 3 are used for carrying out quick locking in the form of threaded sleeve.
Horn opening procedure is as follows：
As shown in Fig. 3 folded state schematic diagrames, under folded state, the horn assembled is in horizontal positioned.Its with it is threaded
Locking member 9 on top view shape form an angle.Now hold horn, by its around the shaft screw 7 to threaded locking member 9
Direction rotates, untill both tight fits.Now locking sleeve 2 and locking sleeve pipe 3 are rotated successively and are tightened to main sleeve pipe 1.It is complete
Into the opening action of horn.
Horn folding process is as follows：
As shown in Fig. 4 open mode schematic diagrames, under open mode, the horn assembled is in oblique placement.Its with it is threaded
Locking member 9, locking sleeve 2, locking sleeve pipe 3 fit together.First, locking sleeve 2, locking sleeve pipe 3 are rotated to pine successively
Open.Horn is now held, screw 7 rotates to the opposite direction of threaded locking member 9 around the shaft by it, extremely horizontal positioned.Complete
The opening action of horn.
The utility model is because using after horizontal folding horn horizontal folding, volume significantly reduces, it is easier to stores, it is horizontal
The ability of the structure confrontation aircraft Z-direction vibrations of folding greatly improves.
Claims (8)
- A kind of 1. horizontal folding mechanism applied to aircraft, it is characterised in that including：Horn, described horn one end set mounting seat, and the mounting seat is used to assemble the power for providing power for rotor craft Component；With the main sleeve pipe of horn other end socket, the main sleeve pipe is rotatably connected the fuselage in rotor craft；The fuselage of the rotor craft is provided with locking member, and main sleeve pipe is fixed on the rotation by the locking member under deployed condition On the fuselage of rotor aircraft.
- A kind of 2. horizontal folding mechanism applied to aircraft according to claim 1, it is characterised in that the main sleeve pipe Pass through the first screw connection with the horn.
- 3. a kind of horizontal folding mechanism applied to aircraft according to claim 1, it is characterised in that also include locking Sleeve pipe and locking sleeve pipe, the locking sleeve and locking sleeve pipe rotate successively to be tightened on main sleeve pipe.
- A kind of 4. horizontal folding mechanism applied to aircraft according to claim 2, it is characterised in that the main sleeve pipe Including main union body, the lateral wall of one end of the main union body is provided with external screw thread, and the other end is provided with and first spiral shell The fixed screw mounting flange of silk, the main sleeve pipe can rotate around first screw.
- A kind of 5. horizontal folding mechanism applied to aircraft according to claim 4, it is characterised in that the main sleeve pipe Locating notch is additionally provided with the lateral wall of body, the locking member blocks the locating notch so that main sleeve pipe is fixed on into the rotation On the fuselage of rotor aircraft.
- A kind of 6. horizontal folding mechanism applied to aircraft according to claim 4 or 5, it is characterised in that the lock The inner surface of tight set pipe has internal thread, and the external screw thread of the internal thread and the main sleeve pipe is connected.
- A kind of 7. horizontal folding mechanism applied to aircraft according to claim 1, it is characterised in that the main set Pipe, locking sleeve and locking sleeve pipe are integrally cylindrical in shape.
- A kind of 8. horizontal folding mechanism applied to aircraft according to claim 1, it is characterised in that the locking member Section is in crescent shape, and two locking members, which coordinate, fixes main sleeve pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721117182.6U CN207157489U (en) | 2017-09-01 | 2017-09-01 | A kind of horizontal folding mechanism applied to aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721117182.6U CN207157489U (en) | 2017-09-01 | 2017-09-01 | A kind of horizontal folding mechanism applied to aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207157489U true CN207157489U (en) | 2018-03-30 |
Family
ID=61719338
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721117182.6U Active CN207157489U (en) | 2017-09-01 | 2017-09-01 | A kind of horizontal folding mechanism applied to aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207157489U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112339985A (en) * | 2020-11-24 | 2021-02-09 | 易瓦特科技股份公司 | Unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle |
-
2017
- 2017-09-01 CN CN201721117182.6U patent/CN207157489U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112339985A (en) * | 2020-11-24 | 2021-02-09 | 易瓦特科技股份公司 | Unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: Room 504, Block E, HUanpu science and Technology Industrial Park, 211 tianguba Road, high tech Zone, Xi'an City, Shaanxi Province, 710000 Patentee after: Tudou Data Technology Group Co.,Ltd. Address before: Room 504, Block E, HUanpu science and Technology Industrial Park, 211 tianguba Road, high tech Zone, Xi'an City, Shaanxi Province, 710000 Patentee before: SHAANXI TUDOU DATA TECHNOLOGY Co.,Ltd. |