CN206107543U - Unmanned aerial vehicle folding mechanism that links - Google Patents
Unmanned aerial vehicle folding mechanism that links Download PDFInfo
- Publication number
- CN206107543U CN206107543U CN201621173193.1U CN201621173193U CN206107543U CN 206107543 U CN206107543 U CN 206107543U CN 201621173193 U CN201621173193 U CN 201621173193U CN 206107543 U CN206107543 U CN 206107543U
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- China
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- horn
- main body
- fuselage main
- undercarriage
- connector
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Abstract
The utility model discloses an unmanned aerial vehicle folding mechanism that links, the velometer comprises a meter body, the horn, the undercarriage, the connecting rod, first connecting piece, the second connecting piece, third connecting piece and fourth connecting piece, the inner of horn is through first connecting piece and fuselage main part rotatable coupling, the undercarriage is disposed under the horn, second connecting piece and fuselage main part rotatable coupling are passed through to the inner of undercarriage, the both ends of connecting rod are respectively through third connecting piece and fourth connecting piece and the middle part of horn and the middle part rotatable coupling of undercarriage, the horn, four -bar linkage is constituteed to undercarriage and connecting rod and fuselage main part. The utility model discloses making horn, undercarriage articulated with the fuselage main part respectively, making horn fuselage main part rotation relatively, the undercarriage is folding along with the folding linkage of horn, makes unmanned aerial vehicle horn and undercarriage have using location and retracted position to maximum reduction unmanned aerial vehicle occupation space, folding, expansion convenient and fast.
Description
Technical field
This utility model is related to unmanned air vehicle technique, more particularly to a kind of unmanned plane linkage fold mechanism.
Background technology
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Can be divided into from technical standpoint definition：Unmanned fixed-wing aircraft, unmanned VTOL machine, unmanned airship, nobody
Helicopter, unmanned multi-rotor aerocraft, unmanned parasol etc..Multi-rotor unmanned aerial vehicle is because of its simple structure, low cost, manipulation ability
It is good, can VTOL, spot hover the features such as, can various loads such as integrated GPS, moving camera complete more complicated task, because
This is widely current in the market.
The portability and reliability of unmanned plane is everybody focus of attention.On market the most volume of existing unmanned plane compared with
Greatly, without folder function, portability extreme difference, what is had has done the folder function of horn, but foot rest can not be folded when casing, foot rest compared with
Cause packing measurement(s) larger greatly, portability extreme difference.
Utility model content
The purpose of this utility model is that and provide a kind of unmanned plane linkage fold mechanism in order to solve the above problems.
This utility model is achieved through the following technical solutions above-mentioned purpose：
A kind of unmanned plane links fold mechanism, including fuselage main body, horn, undercarriage, connecting rod, the first connector, second
Connector, the 3rd connector and the 4th connector, the inner of the horn is by first connector and the fuselage main body
It is rotatably connected, the undercarriage is arranged on the lower section of the horn, the inner of the undercarriage passes through second connector
It is rotatably connected with the fuselage main body, the two ends of the connecting rod are respectively by the 3rd connector and the 4th connector
Be rotatably connected in the middle part of the middle part of the horn and the undercarriage, the horn, the undercarriage and the connecting rod with
The fuselage main body constitutes quadric chain.
Specifically, first connector includes first axle and the first ears bearing, the first ears bearing and institute
State fuselage main body to be fixedly connected, the inner of the horn is rotatably connected by the first axle with the first ears bearing
Connect；
Second connector includes second hinge and the second ears bearing, the second ears bearing and the fuselage master
Body is fixedly connected, and the inner of the undercarriage is rotatably connected by the second hinge with the second ears bearing；
3rd connector includes third hinge and the 3rd ears bearing, the 3rd ears bearing and the horn
Downside is fixedly connected, and positioned at the middle part of the horn, the first end of the connecting rod is by the third hinge and described
Three ears bearings are rotatably connected；
4th connector includes the 4th hinge and the 4th ears bearing, the 4th ears bearing and the connecting rod
Second end is fixedly connected, and the middle part of the undercarriage is rotatably connected by the 4th hinge and the 4th ears bearing；
The first ears bearing is fixedly installed on the circumference side of the fuselage main body, and the second ears bearing is fixed
The downside of the fuselage main body is arranged on, the first ears bearing is big with the distance between the axis of the fuselage main body
In the distance between the second ears bearing and axis of the fuselage main body.
Further, being provided with first connector can limit the lock part of the horn rotation, the horn and institute
The plane for stating fuselage main body place is perpendicular or parallel, and the direction of rotation of the horn is towards the lower section of the fuselage main body.
Preferably, the undercarriage is bow, and the arc core of the undercarriage is positioned close in the fuselage main body
The side of axis.
Specifically, the quantity of the horn and the undercarriage is multiple and equal along the axis of the fuselage main body
Even distribution, and be rotatably connected with the fuselage main body.
Further, the outside of first connector is provided with protecting crust, the inner and fuselage master of the protecting crust
Body is fixedly connected, and the downside of the protecting crust and lateral surface are hatch frame, and the inner of the horn passes through the opening
Structure is rotatably connected with first connector.
The beneficial effects of the utility model are：
A kind of unmanned plane linkage fold mechanism of this utility model makes horn, undercarriage be hinged with fuselage main body respectively, makes machine
Arm can be rotated relative to fuselage main body, and undercarriage is folded with horn folding linkage, and having unmanned plane horn and undercarriage makes
With position and retrieving position；It is used for unmanned plane landing as a body part, undercarriage position, horn is used；Withdrawing
Position, horn is folded under fuselage main body, and undercarriage is also folded into therewith under fuselage main body, so as to farthest reduce nobody
Machine takes up room, and folds, launches convenient and swift.
Description of the drawings
Fig. 1 is a kind of structural representation of unmanned plane linkage fold mechanism described in the utility model, is in for horn in figure
Use state；
Fig. 2 is a kind of structural representation of unmanned plane linkage fold mechanism described in the utility model, is in for horn in figure
Recovery state；
Fig. 3 is a kind of use schematic diagram of unmanned plane linkage fold mechanism described in the utility model, is in for horn in figure
Use state；
Fig. 4 is a kind of use schematic diagram of unmanned plane linkage fold mechanism described in the utility model, is in for horn in figure
Recovery state.
Specific embodiment
Below in conjunction with the accompanying drawings the utility model is described in further detail：
As depicted in figs. 1 and 2, a kind of unmanned plane of this utility model links fold mechanism, including fuselage main body 1, horn 2,
Undercarriage 4, connecting rod 3, the first connector, the second connector, the 3rd connector and the 4th connector, the inner of horn 2 is by the
A connection piece is rotatably connected with fuselage main body 1, and undercarriage 4 is arranged on the lower section of horn 2, and the inner of undercarriage 4 passes through second
Connector is rotatably connected with fuselage main body 1, and the two ends of connecting rod 3 are respectively by the 3rd connector and the 4th connector and horn 2
Middle part and the middle part of undercarriage 4 be rotatably connected, horn 2, undercarriage 4 and connecting rod 3 constitute double leval jib machine with fuselage main body 1
Structure.
Horn 2, undercarriage 4 are hinged respectively with fuselage main body 1, unmanned plane horn 2 is rotated relative to fuselage main body 1,
Undercarriage 4 is folded with the folding linkage of horn 2, is had unmanned plane horn 2 and undercarriage 4 and is used position and retrieving position；
Using position (as shown in Figure 1), horn 2 is used for unmanned plane landing as a body part, undercarriage 4；In retrieving position (such as
Shown in Fig. 2), horn 2 is folded under fuselage main body 1, and undercarriage 4 is also folded into therewith under fuselage main body 1.
First connector includes the ears bearing 10 of first axle 5 and first, and the first ears bearing 10 is fixed with fuselage main body 1
Connection, the inner of horn 2 is rotatably connected by first axle 5 with the first ears bearing 10；
Second connector includes the ears bearing 11 of second hinge 8 and second, and the second ears bearing 11 is fixed with fuselage main body 1
Connection, the inner of undercarriage 4 is rotatably connected by second hinge 8 with the second ears bearing 11；
3rd connector includes the downside of the ears bearing 13 of third hinge 6 and the 3rd, the 3rd ears bearing 13 and horn 2
It is fixedly connected, and positioned at the middle part of horn 2, the first end of connecting rod 3 is rotatably connected by third hinge 6 with the 3rd ears bearing 13
Connect；
4th connector includes the second end of the 4th hinge 7 and the 4th ears bearing 14, the 4th ears bearing 14 and connecting rod 3
It is fixedly connected, the middle part of undercarriage 4 is rotatably connected by the 4th hinge 7 with the 4th ears bearing 14；
First ears bearing 10 is fixedly installed on the circumference side of fuselage main body 1, and the second ears bearing 11 is fixedly installed on
The distance between axis of the downside of fuselage main body 1, the first ears bearing 10 and fuselage main body 1 is more than the second ears bearing
11 the distance between with the axis of fuselage main body 1.
First connector and the second connector and two important forced sections that the junction of fuselage main body 1 is the unmanned plane
12。
In order to fix the position of horn 2, appearance is relatively rotated between fuselage main body 1 during flight to prevent it,
Being provided with first connector can limit the lock part 9 of the rotation of horn 2, and the plane that horn 2 is located with fuselage main body 1 is vertical or flat
OK, the direction of rotation of horn 2 is towards the lower section of fuselage main body 1.
Undercarriage 4 is bow, and the arc core of undercarriage 4 is positioned close to the side of the axis of fuselage main body 1.
Two, 4 top of unmanned plane undercarriage hinge hole be stress point, bottom as buffer part, in unmanned plane undercarriage
Deform during 4 stress.
Undercarriage 4 adopts circular-arc-shaped design, recessed to the center position of fuselage main body 1 away from the one end of fuselage main body 1.
As shown in Figure 3 and Figure 4, the quantity of horn 2 and undercarriage 4 is multiple and uniform along the axis of fuselage main body 1
Distribution, and be rotatably connected with fuselage main body 1.
Because horn 2 is in use state, its give fuselage main body 1 provide send out lift upwards, mainly by the first connector
There is provided, therefore in order to the first connector is played a part of to reinforce and protected, the outside of the first connector is provided with protecting crust, prevents
The inner of protective case is fixedly connected with fuselage main body 1, and the downside of protecting crust and lateral surface are hatch frame, the inner of horn 2
It is rotatably connected with the first connector through hatch frame.
The technical solution of the utility model is not limited to the restriction of above-mentioned specific embodiment, every according to skill of the present utility model
The technology deformation that art scheme is made, each falls within protection domain of the present utility model.
Claims (6)
1. a kind of unmanned plane links fold mechanism, including fuselage main body and horn, it is characterised in that：Also include undercarriage, connecting rod,
First connector, the second connector, the 3rd connector and the 4th connector, the inner of the horn passes through first connector
It is rotatably connected with the fuselage main body, the undercarriage is arranged on the lower section of the horn, the inner of the undercarriage passes through
Second connector is rotatably connected with the fuselage main body, the two ends of the connecting rod respectively by the 3rd connector and
It is rotatably connected in the middle part of the middle part of the 4th connector and the horn and the undercarriage, the horn, described rises and falls
Frame and the connecting rod constitute quadric chain with the fuselage main body.
2. a kind of unmanned plane according to claim 1 links fold mechanism, it is characterised in that：First connector includes
First axle and the first ears bearing, the first ears bearing is fixedly connected with the fuselage main body, the inner of the horn
It is rotatably connected with the first ears bearing by the first axle；
Second connector includes second hinge and the second ears bearing, and the second ears bearing is solid with the fuselage main body
Fixed connection, the inner of the undercarriage is rotatably connected by the second hinge with the second ears bearing；
3rd connector includes third hinge and the 3rd ears bearing, the downside of the 3rd ears bearing and the horn
Face is fixedly connected, and positioned at the middle part of the horn, the first end of the connecting rod by the third hinge with described 3rd pair
Auricular branch seat is rotatably connected；
4th connector includes the 4th hinge and the 4th ears bearing, the 4th ears bearing and the second of the connecting rod
End is fixedly connected, and the middle part of the undercarriage is rotatably connected by the 4th hinge and the 4th ears bearing；
The first ears bearing is fixedly installed on the circumference side of the fuselage main body, and the second ears bearing is fixedly installed
In the downside of the fuselage main body, the distance between the first ears bearing and axis of the fuselage main body are more than institute
State the distance between the second ears bearing and axis of the fuselage main body.
3. a kind of unmanned plane according to claim 2 links fold mechanism, it is characterised in that：Set on first connector
Being equipped with can limit the lock part that the horn is rotated, and the plane that the horn is located with the fuselage main body is perpendicular or parallel, institute
The direction of rotation of horn is stated towards the lower section of the fuselage main body.
4. a kind of unmanned plane according to claim 2 links fold mechanism, it is characterised in that：The undercarriage is arc
Bar, the arc core of the undercarriage is positioned close to the side of the axis of the fuselage main body.
5. a kind of unmanned plane according to claim 2 links fold mechanism, it is characterised in that：The horn and described rise and fall
The quantity of frame is multiple, and is uniformly distributed along the axis of the fuselage main body, and is rotatably connected with the fuselage main body.
6. a kind of unmanned plane according to claim 2 links fold mechanism, it is characterised in that：Outside first connector
Portion is provided with protecting crust, and the inner of the protecting crust is fixedly connected with the fuselage main body, the downside of the protecting crust and outer
Side is hatch frame, and the inner of the horn is rotatably connected through the hatch frame with first connector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621173193.1U CN206107543U (en) | 2016-10-26 | 2016-10-26 | Unmanned aerial vehicle folding mechanism that links |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621173193.1U CN206107543U (en) | 2016-10-26 | 2016-10-26 | Unmanned aerial vehicle folding mechanism that links |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206107543U true CN206107543U (en) | 2017-04-19 |
Family
ID=58525563
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621173193.1U Active CN206107543U (en) | 2016-10-26 | 2016-10-26 | Unmanned aerial vehicle folding mechanism that links |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206107543U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347625A (en) * | 2016-10-26 | 2017-01-25 | 成都市优艾维机器人科技有限公司 | Unmanned aerial vehicle linkage folding mechanism |
| CN108750071A (en) * | 2018-07-17 | 2018-11-06 | 深圳市龙云创新航空科技有限公司 | A kind of more rotor horns and one folding structure of undercarriage |
-
2016
- 2016-10-26 CN CN201621173193.1U patent/CN206107543U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347625A (en) * | 2016-10-26 | 2017-01-25 | 成都市优艾维机器人科技有限公司 | Unmanned aerial vehicle linkage folding mechanism |
| CN108750071A (en) * | 2018-07-17 | 2018-11-06 | 深圳市龙云创新航空科技有限公司 | A kind of more rotor horns and one folding structure of undercarriage |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 611731 No. 1, 12 floor, No. 1, Tianfu Avenue, 1388 middle and high tech Zone, Chengdu, Sichuan. Patentee after: Chengdu best Intelligent Technology Co., Ltd. Address before: 611731 No. 1, 12 floor, No. 1, Tianfu Avenue, 1388 middle and high tech Zone, Chengdu, Sichuan. Patentee before: Chengdu Science and Technology Ltd. of You Aiwei robot |
|
| CP01 | Change in the name or title of a patent holder |