CN209290677U - Multi-rotor unmanned aerial vehicle - Google Patents
Multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN209290677U CN209290677U CN201822161133.3U CN201822161133U CN209290677U CN 209290677 U CN209290677 U CN 209290677U CN 201822161133 U CN201822161133 U CN 201822161133U CN 209290677 U CN209290677 U CN 209290677U
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- fuselage
- propeller
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Abstract
The utility model discloses a kind of multi-rotor unmanned aerial vehicles, including fuselage and multiple first horns being mounted on fuselage, first horn is equipped with the first propeller and drives the first engine of the first propeller motion, and the first angle of the longitudinal axis axis of the rotation axis axis and fuselage of the first propeller is 5 ° -10 °.Since there are the first angles for the rotation axis axis and the longitudinal axis axis of fuselage of the first propeller, and then multi-rotor unmanned aerial vehicle first propeller in flight course generates component in the horizontal direction, the Heading control for realizing auxiliary multi-rotor unmanned aerial vehicle, so that the Heading control accuracy of multi-rotor unmanned aerial vehicle improves.
Description
Technical field
The utility model relates to air vehicle technique field, in particular to a kind of multi-rotor unmanned aerial vehicle.
Background technique
Unmanned plane refers to the not manned aircraft using radio robot and self-contained program's control device.As China is low
The all-round opening in empty field, multi-rotor unmanned aerial vehicle since its cost of manufacture is cheap, it is easy to operate the features such as, be widely used in army
The multiple fields such as thing, civil and scientific research.
Traditional multi-rotor unmanned aerial vehicle includes fuselage and multiple first horns for being mounted on fuselage, wherein the first horn packet
The first propeller is included, each first propeller passes through corresponding first engine driving, wherein the rotation axis axis of the first propeller
Line is overlapped with the longitudinal axis axis of fuselage, and for multi-rotor unmanned aerial vehicle in flight, the rotation of the first propeller provides lift.Meanwhile tradition
Multi-rotor unmanned aerial vehicle, by propeller rotational torque carry out Heading control, control moment is smaller, on relatively large unmanned plane
In application, response flexibility is insufficient.
Utility model content
The purpose of the utility model is to provide a kind of multi-rotor unmanned aerial vehicle, the flight reliability of the multi-rotor unmanned aerial vehicle is mentioned
It is high.
To achieve the above object, the utility model provides a kind of multi-rotor unmanned aerial vehicle, including fuselage and is mounted on the machine
Multiple first horns with it, first horn are equipped with the first of the first propeller and driving first propeller motion
First angle of engine, the longitudinal axis axis of the rotation axis axis and fuselage of first propeller is 5 ° -10 °.
Preferably, the first angle of the longitudinal axis axis of the rotation axis axis and fuselage of first propeller be 7 ° or
8°。
Preferably, first engine is arranged in the end of first horn, described first on first horn
The axis of propeller is overlapped with the output shaft axis of first engine.
It preferably, further include the first horn reinforcing rod for connecting two neighboring first horn end.
Preferably, first horn is even number, and all first horns are circumferentially uniformly distributed along the fuselage.
It preferably, further include the second horn, second horn is equipped with the second propeller and driving second spiral
Second engine of paddle movement, first horn and second horn are even number, with described on second horn
The longitudinal axis axis of fuselage is that center line is arranged oppositely, and first horn is set by center line opposite direction of the longitudinal axis axis of the fuselage
It sets, the rotation axis axis of second propeller and the longitudinal axis axis of the fuselage are parallel.
Preferably, the longitudinal axis axis of the rotation axis axis of first propeller and the fuselage is different surface beeline.
Preferably, the rotation axis axis for two the first propellers being arranged oppositely forms the second angle, second angle
Degree be two times of the first angle degree.
Preferably, first engine is dynamic first engine of oil.
It preferably, further include cable sleeve that both ends are connect with first horn end and the fuselage respectively, it is described
It is equipped in cable sleeve for the oil pipe to the first engine oil transportation.
In the above-mentioned technical solutions, multi-rotor unmanned aerial vehicle provided by the utility model includes fuselage and is mounted on fuselage
Multiple first horns, the first horn are equipped with the first propeller and drive the first engine of the first propeller motion, the first spiral shell
The first angle for revolving the rotation axis axis of paddle and the longitudinal axis axis of fuselage is 5 ° -10 °.
As can be seen from the above description, in multi-rotor unmanned aerial vehicle provided by the present application, due to the rotation axis of the first propeller
There are the first angle, i.e. the first propeller tilt settings for the longitudinal axis axis of axis and fuselage, and then multi-rotor unmanned aerial vehicle is being flown
The first propeller generates component in the horizontal direction in the process, the Heading control of auxiliary multi-rotor unmanned aerial vehicle is realized, so that more
The Heading control accuracy of rotor wing unmanned aerial vehicle improves.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is the embodiments of the present invention, for those of ordinary skill in the art, without creative efforts, also
Other attached drawings can be obtained according to the attached drawing of offer.
Fig. 1 is the partial structurtes portion of multi-rotor unmanned aerial vehicle provided by the utility model embodiment；
Fig. 2 is the structural schematic diagram of multi-rotor unmanned aerial vehicle provided by the utility model embodiment.
Wherein in Fig. 1-2: 1- fuselage, the first propeller of 2-, the first engine of 3-, the first horn of 4- reinforcing rod, 5- first
Horn support rod, the first horn of 6-.
Specific embodiment
The core of the utility model is to provide a kind of multi-rotor unmanned aerial vehicle, and the flight reliability of the multi-rotor unmanned aerial vehicle mentions
It is high.
It is with reference to the accompanying drawing and real in order to make those skilled in the art more fully understand the technical solution of the utility model
Applying mode, the utility model is described in further detail.
Fig. 1 and Fig. 2 are please referred to, in a specific embodiment, more rotors that the utility model specific embodiment provides
Unmanned plane includes multiple first horns 6 of fuselage 1 and installation on the fuselage 1, and the first horn 6 is equipped with the first propeller 2 and drives
First engine 3 of dynamic first propeller 2 movement, specifically, the first propeller 2 and the first engine 3 are installed in the first machine
On arm 6, the first angle a of the longitudinal axis axis of the rotation axis axis and fuselage 1 of the first propeller 2 is 5 ° -10 °, specifically, first
First angle a of the longitudinal axis axis of the rotation axis axis and fuselage 1 of propeller 2 is 6 °, 7 °, 8 ° or 9 ° etc., and middle fuselage 1 is indulged
Axis axis is the axis on vertical direction.Specifically, the top of the first propeller 2 can to fuselage direction close to or far from.
Specifically, the first horn 6 can be odd number, the first horn 6 is circumferentially uniformly distributed along fuselage 1, specifically, first
Horn 6 can be three, for the ease of control multi-rotor unmanned aerial vehicle stationarity, it is preferred that the first horn 6 be even number, first
Horn 6 is circumferentially uniformly distributed along fuselage 1.Specifically, the first horn 6 can be four or six etc., when the first horn 6 six
When, six the first horns 6 are circumferentially uniformly distributed along fuselage 1.
In a further mode of operation, multi-rotor unmanned aerial vehicle further includes the second horn, and second horn is equipped with the second spiral
Paddle and the second engine for driving the second propeller motion, the first horn 6 and the second horn are even number, on the second horn with
The longitudinal axis axis of fuselage 1 is that center line is arranged oppositely, and the first horn 6 is arranged oppositely using the longitudinal axis axis of fuselage 1 as center line, the
The rotation axis axis of two propellers and the longitudinal axis axis of fuselage 1 are parallel, wherein the rotation axis axis of the first propeller in same group
Line is preferably simultaneously to the longitudinal axis axis direction setting close to or far from fuselage.It is preferred that along circumferentially-adjacent two the first horns 6 of fuselage
Between be equipped with second horn.
As can be seen from the above description, in the multi-rotor unmanned aerial vehicle provided by the application specific embodiment, due to the first spiral shell
The rotation axis axis of paddle 2 and the longitudinal axis axis of fuselage 1 are revolved there are the first angle, and then multi-rotor unmanned aerial vehicle is the in flight course
One propeller 2 generates component in the horizontal direction, realizes the Heading control of auxiliary multi-rotor unmanned aerial vehicle so that more rotors nobody
The flight reliability of machine improves.
Since the first propeller 2 is located at 6 end of the first horn, for the ease of assembling, it is preferable that the setting of the first engine 3 exists
The end of first horn 6, wherein the end of the first horn 6 refers to the side on the first horn 6 far from fuselage 1.
For the ease of power output, it is preferable that the output of the axis of the first propeller 2 and the first engine 3 on the first horn 6
Axis axis is overlapped, in use, directly the first propeller 2 can be mounted on the output shaft of the first engine 3.
Preferably, which further includes the first horn support rod for connecting 6 end of the first horn and fuselage 1.
Specifically, the first horn support rod tilts upward setting the first horn 6 of support, extend the service life of multi-rotor unmanned aerial vehicle.
Further, which further includes the first horn reinforcing rod for connecting two neighboring first horn, 6 end
4, since the first engine 3 and the first propeller 2 are generally arranged at 6 end of the first horn, gravity is larger, by two neighboring
The first horn reinforcing rod 4 is added in first horn, 6 end, so that the first horn 6 connection of multi-rotor unmanned aerial vehicle forms reticular structure,
And then integral strength is improved, further extend the service life of multi-rotor unmanned aerial vehicle.In order to reduce resistance, it is preferable that the first horn
Reinforcing rod 4 is cylindrical straight rod structure.
While proof strength, in order to lower overall weight, it is preferable that the first horn and/or the first horn support rod and/
Or first horn reinforcing rod be hollow stem.
Specifically, the top of 2 rotation axis of the first propeller can be to close fuselage 1 close to or far from specific first spiral shell
Rotation 2 rotation axis axis of paddle can intersect with the longitudinal axis axis of fuselage 1.Due to the rotation axis axis and fuselage 1 of the first propeller 2
The intersection setting of longitudinal axis axis can generate additional in the fuselage datum institute component for being parallel to horn planar, and component is direction
Or the component far from fuselage, this component will not generate effect of the manipulation, will lead to power dissipation.In another embodiment,
As shown in Figure 1, the longitudinal axis axis of the rotation axis axis of the first propeller 2 and fuselage 1 can be different surface beeline.
Preferably, the rotation axis axis for two the first propellers 2 being arranged oppositely forms the second angle, the degree of the second angle
Number is two times of the first angle degree.
On the basis of above-mentioned each scheme, it is preferable that the first engine 3 is dynamic first engine of oil, certainly specifically used
In the process, the first engine 3 can also be worked by controlling electric energy.
When the first engine is dynamic first engine of oil, it is preferable that the multi-rotor unmanned aerial vehicle further includes both ends respectively with the
The cable sleeve 5 that one horn, 6 end and fuselage 1 connect, cable sleeve 5 is interior to be equipped with for the oil pipe to 3 oil transportation of the first engine,
The case where cable and oil pipe are arranged in cable sleeve 5, external substance damage cable and oil pipe are avoided.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.
The foregoing description of the disclosed embodiments can be realized professional and technical personnel in the field or using originally practical new
Type.Various modifications to these embodiments will be readily apparent to those skilled in the art, and determine herein
The General Principle of justice can be realized in other embodiments without departing from the spirit or scope of the present utility model.Cause
This, the present invention will not be limited to the embodiments shown herein, and is to fit to and principles disclosed herein
The widest scope consistent with features of novelty.
Claims (10)
1. a kind of multi-rotor unmanned aerial vehicle, including fuselage (1) and the first horn (6) being mounted on the fuselage (1), described first
Horn (6) is equipped with the first engine (3) of the first propeller (2) and driving the first propeller (2) movement, and feature exists
In the first angle of the longitudinal axis axis of the rotation axis axis and fuselage (1) of first propeller (2) is 5 ° -10 °.
2. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that the rotation axis axis of first propeller (2)
First angle of line and the longitudinal axis axis of the fuselage (1) is 7 ° or 8 °.
3. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that first engine (3) is arranged described
The end of first horn (6), the axis of first propeller (2) and first engine (3) on first horn (6)
Output shaft axis be overlapped.
4. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that further include two neighboring first machine of connection
The first horn reinforcing rod (4) of arm (6) end.
5. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that first horn (6) is even number, is owned
First horn (6) is circumferentially uniformly distributed along the fuselage (1).
6. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that it further include the second horn, second horn
It is equipped with the second engine of the second propeller and driving second propeller motion, first horn (6) and described the
Two horns are even number, are arranged oppositely using the longitudinal axis axis of the fuselage (1) as center line on second horn, and described
One horn (6) is arranged oppositely using the longitudinal axis axis of the fuselage (1) as center line, the rotation axis axis of second propeller with
The longitudinal axis axis of the fuselage (1) is parallel.
7. multi-rotor unmanned aerial vehicle according to claim 5, which is characterized in that the rotation axis axis of first propeller (2)
Line and the longitudinal axis axis of the fuselage (1) are different surface beeline.
8. multi-rotor unmanned aerial vehicle according to claim 7, which is characterized in that two the first propellers (2) being arranged oppositely
Rotation axis axis form the second angle, the degree of second angle is two times of the first angle degree.
9. multi-rotor unmanned aerial vehicle according to claim 1 to 8, which is characterized in that first engine (3)
For dynamic first engine of oil.
10. multi-rotor unmanned aerial vehicle according to claim 9, which is characterized in that further include both ends respectively with first machine
The cable sleeve (5) of arm (6) end and the fuselage (1) connection, the cable sleeve (5) is interior to be equipped with for sending out to described first
The oil pipe of motivation (3) oil transportation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822161133.3U CN209290677U (en) | 2018-12-21 | 2018-12-21 | Multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822161133.3U CN209290677U (en) | 2018-12-21 | 2018-12-21 | Multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209290677U true CN209290677U (en) | 2019-08-23 |
Family
ID=67656021
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822161133.3U Active CN209290677U (en) | 2018-12-21 | 2018-12-21 | Multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN209290677U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436311A (en) * | 2018-12-21 | 2019-03-08 | 辽宁壮龙无人机科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN116280206A (en) * | 2023-03-22 | 2023-06-23 | 深圳技术大学 | Magnetic attraction type logistics unmanned aerial vehicle |
-
2018
- 2018-12-21 CN CN201822161133.3U patent/CN209290677U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436311A (en) * | 2018-12-21 | 2019-03-08 | 辽宁壮龙无人机科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN116280206A (en) * | 2023-03-22 | 2023-06-23 | 深圳技术大学 | Magnetic attraction type logistics unmanned aerial vehicle |
| CN116280206B (en) * | 2023-03-22 | 2024-01-12 | 深圳技术大学 | Magnetic attraction type logistics unmanned aerial vehicle |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: No. 76-45, Shenbei Road, Shenbei New District, Shenyang City, Liaoning Province 110000 Patentee after: Liaoning Dazhuang UAV Technology Co.,Ltd. Address before: 110136 Shenbei Road, Shenbei New Area, Shenyang, Liaoning, No. 76-43 (A gate) Patentee before: LIAONING ZHUANGLONG UNMANNED AERIAL VEHICLE TECHNOLOGY Co.,Ltd. |
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| CP03 | Change of name, title or address |