CN207523939U - Multi-rotor unmanned aerial vehicle - Google Patents
Multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN207523939U CN207523939U CN201721543517.0U CN201721543517U CN207523939U CN 207523939 U CN207523939 U CN 207523939U CN 201721543517 U CN201721543517 U CN 201721543517U CN 207523939 U CN207523939 U CN 207523939U
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- unmanned aerial
- aerial vehicle
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Abstract
The utility model provides a multi-rotor unmanned aerial vehicle, which comprises a streamline fuselage, a plurality of rotor arms arranged on the streamline fuselage and a foot rest arranged below the streamline fuselage; when the unmanned aerial vehicle is horizontally placed, the head of the streamline fuselage upwarps a certain angle relative to the horizontal plane; the radial cross-section of rotor horn is oval along the horn. This many rotor unmanned aerial vehicle is when carrying out the flight of low latitude year, reducible flight resistance to bring extra lift, thereby improved flight duration, also improved the carry load.
Description
Technical field
The utility model belongs to low-latitude flying technical field more particularly to a kind of multi-rotor unmanned aerial vehicle.
Background technology
Multi-rotor unmanned aerial vehicle is a kind of miniature self-service flight for having the flexible flying quality advantage such as vertical lift, hovering
Device has practicability more better than fixed-wing unmanned plane in some environments.It is provided by the motor of multiple circumferences
Lift adjusts posture by changing variable rotor speed, and position control is further realized by adjusting posture, excellent with hovering performance
It is different, mobile flexibly, compact mechanical structure, high part reliability the advantages that, therefore all have in military and civilian field wide
Application prospect.
By the development of several years, has there is variform in multi-rotor unmanned aerial vehicle, but there are still it is universal the defects of, such as
Carry ability is on the weak side, and the mission payload that most of multi-rotor unmanned aerial vehicles can only carry within 3 kilograms performs task, since design is managed
It reads and falls behind, carry mode is single, has rigors to task device；On the other hand, it is limited by the energy density of lithium battery, nothing
Method realizes and cruises for a long time which limits the highly effectives of multi-rotor unmanned aerial vehicle.
Current small and medium size unmanned aerial vehicles, multiaxis（With six axis typical case）Most of application scenarios are occupied, however it is most of
Multi-rotor unmanned aerial vehicle in the aerodynamics problem for being designed without considering shape, so cruise when have larger resistance, pole
Big wastes energy, reduces cruise duration.
Utility model content
The technical problem to be solved by the utility model is to provide a kind of multi-rotor unmanned aerial vehicle, can effectively reduce nothing
Resistance during man-machine flight improves cruising ability and carry load.
In order to solve the above-mentioned technical problem, the utility model provides a kind of multi-rotor unmanned aerial vehicle, it may include：
Streamline fuselage, multiple rotor horns on the streamline fuselage and mounted on the streamlined machine
Foot stool below body；
When the unmanned plane is horizontal positioned, the head of the streamline fuselage with respect to the horizontal plane upwarps certain angle；
The rotor horn is ellipse along the section of horn radial direction.
In an alternate embodiment of the invention, the streamline fuselage is made of upper and lower two semiellipse structures to form.
In an alternate embodiment of the invention, the radius of curvature on the streamline fuselage head is more than the radius of curvature of its tail portion.
In an alternate embodiment of the invention, the radius of curvature of two semiellipse structures up and down differs.
In an alternate embodiment of the invention, 5 degree to 30 degree be the angle ranging from.
In an alternate embodiment of the invention, the end of the rotor horn far from the streamline fuselage is equipped with motor, described
Motor outer wrapping motor protecting cover.
In an alternate embodiment of the invention, the foot stool is detachable foot stool.
In an alternate embodiment of the invention, the multi-rotor unmanned aerial vehicle of the utility model includes six rotor horns.
The advantageous effect of the utility model embodiment is：The multi-rotor unmanned aerial vehicle is when carrying out low latitude delivery flight, band
The fairshaped fuselage design of level inclination, can reduce flight resistance, and bring additional lift, continuous so as to improve flight
Boat ability also improves carry load.
Description of the drawings
It 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 some embodiments of the utility model, for those of ordinary skill in the art, in the premise not made the creative labor
Under, it can also be obtained according to these attached drawings other attached drawings.
Fig. 1 is the 3D structure diagrams of one embodiment of the utility model multi-rotor unmanned aerial vehicle.
Fig. 2 is the front view of one embodiment of the utility model multi-rotor unmanned aerial vehicle.
Fig. 3 is the utility model multi-rotor unmanned aerial vehicle forward schematic diagram in the air.
Specific embodiment
The explanation of following embodiment is refer to the attached drawing, can be to the particular implementation implemented to example the utility model
Example.
The utility model provides a kind of multi-rotor unmanned aerial vehicle, construction as shown in Figure 1, including：Streamline fuselage 1, more rotations
Wing horn 2 and foot stool 3.
As an example, the present embodiment is unfolded to introduce by taking six rotor wing unmanned aerial vehicles as an example.The fuselage 1 of six rotor wing unmanned aerial vehicle uses
Airflow design, is made of upper and lower two semiellipses camber structure and upper and lower two elliptical radius of curvature are different.In fuselage 1
The organic bin port cover 11 in top；There are one umbrella warehouse lid 12, inside placement parachutes for 11 rear end of cabin lid at top.Such as Fig. 2 institutes
Show, the arc curvature radius R1 on the head of fuselage 1 is significantly greater than the arc curvature radius R2 of tail portion, and horizontal positioned in unmanned plane
When, fuselage head with respect to the horizontal plane upwarps certain angle, the horizontal tilt angle that fuselage head upwarps in the present embodiment
It it is 10 degree, certainly in other alternative-embodiments, which can be the optional range of 5 degree of -30 degree, can be according to fuselage
1 actual weight determines.Resistance during unmanned plane during flying can be greatly reduced using above streamlined and level inclination design for fuselage 1
Power, and certain air lift can also be obtained in flight, so as to promote flight cruising ability and carry weight by a relatively large margin.
When unmanned plane moves ahead in the air, fuselage 1 keeps horizontal substantially, and certain level inclination is then presented in wing, as shown in figure 3, this
The offline mode of sample, meets aerodynamic principle, is reduced flight resistance, so as to reduce the loss of energy, is further promoted
The ability of continuation of the journey.
6 horns 2 are uniformly distributed according to 60 degree of circumference angle in the border of fuselage 1, the section of horn 2 radially is ellipse
Circle structure, helps further to reduce air drag；Motor 21 is connected in the end of horn 2, electricity is enclosed with outside motor 21
Machine protective cover 23 installs propeller 22 on motor 21.
Two dismountable foot stools 3 are assigned in the lower section of fuselage 1, it, can be by its foot after the unmanned plane grounding in handling process
Frame 3 removes, and space is carried convenient for saving.
Certain above example is only for example, in other alternative-embodiments, more than fuselage 1, horn 2 and foot stool
3 design is also applicable on the unmanned plane of other quantity rotor.
By above description it is found that the advantageous effect of the utility model embodiment is：The multi-rotor unmanned aerial vehicle is being carried out
When low latitude delivers flight, the fairshaped fuselage design with level inclination can reduce flight resistance, and bring additional liter
Power so as to improve flight cruising ability, also improves carry load.
Above disclosed is only the utility model preferred embodiment, cannot limit the utility model with this certainly
Interest field, therefore equivalent variations made according to the utility model claims still belong to the range that the utility model is covered.
Claims (8)
1. a kind of multi-rotor unmanned aerial vehicle, which is characterized in that including：
Streamline fuselage, multiple rotor horns on the streamline fuselage and under the streamline fuselage
The foot stool of side；
When the unmanned plane is horizontal positioned, the head of the streamline fuselage with respect to the horizontal plane upwarps certain angle；
The rotor horn is ellipse along the section of horn radial direction.
2. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that the streamline fuselage is ellipse by upper and lower two and half
Circle structures to form composition.
3. multi-rotor unmanned aerial vehicle according to claim 2, which is characterized in that the radius of curvature on the streamline fuselage head
More than the radius of curvature of its tail portion.
4. multi-rotor unmanned aerial vehicle according to claim 2, which is characterized in that the curvature of two semiellipse structures up and down
Radius differs.
5. according to the multi-rotor unmanned aerial vehicle described in any one of claim 1-4, which is characterized in that the angle ranging from 5 degree to 30
Degree.
6. multi-rotor unmanned aerial vehicle according to claim 5, which is characterized in that the rotor horn is far from the streamlined machine
The end of body is equipped with motor, the motor outer wrapping motor protecting cover.
7. multi-rotor unmanned aerial vehicle according to claim 6, which is characterized in that the foot stool is detachable foot stool.
8. multi-rotor unmanned aerial vehicle according to claim 7, which is characterized in that including six rotor horns.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721543517.0U CN207523939U (en) | 2017-11-18 | 2017-11-18 | Multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721543517.0U CN207523939U (en) | 2017-11-18 | 2017-11-18 | Multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207523939U true CN207523939U (en) | 2018-06-22 |
Family
ID=62582957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721543517.0U Active CN207523939U (en) | 2017-11-18 | 2017-11-18 | Multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207523939U (en) |
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2017
- 2017-11-18 CN CN201721543517.0U patent/CN207523939U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220701 Address after: 518000 electric power dispatching and communication building, 4020 Shennan East Road, Luohu District, Shenzhen, Guangdong Patentee after: Shenzhen Power Supply Co.,Ltd. Address before: 518000 electric power dispatching and communication building, 4020 Shennan East Road, Luohu District, Shenzhen, Guangdong Patentee before: Shenzhen Power Supply Co.,Ltd. Patentee before: AEROSPACE SCIENCE & INDUSTRY SHENZHEN (Group) Co.,Ltd. |
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| TR01 | Transfer of patent right |