CN209274892U - A kind of electronic unmanned plane of coaxial double-oar - Google Patents
A kind of electronic unmanned plane of coaxial double-oar Download PDFInfo
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- CN209274892U CN209274892U CN201822177367.7U CN201822177367U CN209274892U CN 209274892 U CN209274892 U CN 209274892U CN 201822177367 U CN201822177367 U CN 201822177367U CN 209274892 U CN209274892 U CN 209274892U
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- unmanned plane
- fuselage
- cantilever
- oar
- coaxial double
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model provides a kind of electronic unmanned plane of coaxial double-oar, including fuselage (1), two undercarriages (2), cantilever (3) and motor (4) and propeller (5), wherein, there are four the cantilevers (3), is symmetrically connected on the fuselage (1) with cross-shape layout；The end of each cantilever (3) is supported there are two the motor (4), and each motor (4) has a propeller (5)；The shaft of two motors (4) on each cantilever (3) is located on same vertical line (6).The structure of electronic unmanned plane provided herein, so that the unmanned plane has better layout structure and applicability, and load setting can be preferably carried out, optimize structure design, lift efficiency and cruise duration are improved, bigger load flying for long time can be carried.
Description
Technical field
The utility model relates to air vehicle technique field more particularly to a kind of electronic unmanned planes of more rotors, in particular to
A kind of electronic unmanned plane of coaxial double-oar.
Background technique
With the development of global general-use aviation industry, the development of various gyroplanes is also more increasing with day, especially rotor
Electronic unmanned aerial vehicle is widely used in agriculture plant protection shield, forest fire monitoring, aerophotography, land survey, consequential loss assessment
Etc. tasks.
In current electronic multi-rotor unmanned aerial vehicle product, continuation of the journey is the bottleneck that all unmanned plane developers encounter.
Battery technology makes the continuation of the journey of electronic multi-rotor unmanned aerial vehicle lasting like that without the dynamic unmanned plane of image of Buddha oil always both at home and abroad at present.In addition
The existing generally existing load level of rotor wing unmanned aerial vehicle is low, and topology layout is unreasonable, it is difficult to play the control and safety of unmanned plane
Advantage limits rotor unmanned aerial vehicle in military and monitoring field development and application.
206278267 U of CN discloses a kind of high continuation of the journey multi-rotor unmanned aerial vehicle, including drone body, drone body
It is made of horn, central plate and foot support, horn includes arm of force set, arm bar, motor cabinet, motor and blade, and motor is fixed on
On motor cabinet, blade is fixed on motor, and motor cabinet is fixed on arm bar one end, and the arm bar other end is provided with arm of force set, and
It is covered by the arm of force and is connect with central plate, difference in height is equipped between the blade on adjacent horn, adjacent blades is made to be not at same water
In plane, the centrally disposed board bottom portion of foot support；The multi-rotor unmanned aerial vehicle of the prior art is using wrong paddle mounting means in first wife
More gyroplane wheelbases are shortened on the basis of setting effectively to mitigate main screw lift, be allowed to obtain bigger cruise duration, and this reality
Additional production cost can't be generated with novel.
It is only obtained by increasing the quantity of blade however, the lift of the electronic unmanned plane of the prior art is promoted, excessively
Blade need more cantilevers, construction weight is big, low efficiency, is still difficult to promote the cruise duration of unmanned plane.
Utility model content
The technical problem to be solved by the present invention is to provide a kind of electronic unmanned planes of coaxial double-oar, before being reduced or avoided
The problem of face is previously mentioned.
In order to solve the above technical problems, the utility model proposes a kind of electronic unmanned plane of coaxial double-oar, including fuselage, two
A undercarriage, cantilever and motor and propeller, wherein there are four the cantilevers, is symmetrically connected to cross-shape layout described
On fuselage；The end of each cantilever is supported there are two the motor, and each motor has a propeller；On each cantilever
The shafts of two motors be located on same vertical line.
Preferably, the fuselage is in octagon, and the cantilever is arranged at intervals on the center of the side length of the octagon
Position.
Preferably, the fuselage interior is provided with two reinforcing beams of the decussation for connecting the cantilever.
Preferably, described two undercarriages are symmetricly set on the lower part of the fuselage, the symmetry axis of the undercarriage and institute
Reinforcing beam is stated in 45 degree of angles.
Preferably, the tie point of each undercarriage and the fuselage is located on two reinforcing beams.
Preferably, two groups of batteries are provided in the fuselage, two groups of batteries are symmetrical with the symmetry axis setting.
Preferably, the direction of rotation of two propellers of the end of each cantilever is opposite.
The structure of electronic unmanned plane provided herein, so that the unmanned plane has better layout structure and is applicable in
Property, and load setting can be preferably carried out, structure design is optimized, lift efficiency and cruise duration is improved, can take
Carry bigger load flying for long time.
Detailed description of the invention
The following drawings is only intended to make the utility model schematic illustration and explanation, does not limit the model of the utility model
It encloses.Wherein,
The three-dimensional knot of the electronic unmanned plane of coaxial double-oar of a specific embodiment according to the present utility model is shown in Fig. 1
Structure schematic diagram；
The decomposition of the electronic unmanned plane of coaxial double-oar of another specific embodiment according to the present utility model is shown in Fig. 2
Perspective view；
The fuselage of the electronic unmanned plane of coaxial double-oar of another specific embodiment according to the present utility model is shown in Fig. 3
Structural schematic diagram.
Specific embodiment
For a clearer understanding of the technical features, objectives and effects of the utility model, now compareing Detailed description of the invention
Specific embodiment of the present utility model.Wherein, identical component uses identical label.
As shown in Figure 1-3, this application provides a kind of electronic unmanned planes of coaxial double-oar, wherein root is shown in Fig. 1 Fig. 1
According to the schematic perspective view of the electronic unmanned plane of coaxial double-oar of a specific embodiment of the utility model；Fig. 2 is shown
The decomposition perspective view of the electronic unmanned plane of the coaxial double-oar of another specific embodiment according to the present utility model；Fig. 3 is shown
The airframe structure schematic diagram of the electronic unmanned plane of the coaxial double-oar of another specific embodiment according to the present utility model.
Referring to Fig. 1-3, the electronic unmanned plane of the coaxial double-oar of the application, including 1, two undercarriage 2 of fuselage, cantilever 3 and
Motor 4 and propeller 5, wherein there are four cantilevers 3, is symmetrically connected on fuselage 1 with cross-shape layout；The end of each cantilever 3
There are two motors 4, each motor 4 to have a propeller 5 for support；The shaft of two motors 4 on each cantilever 3 is located at
On same vertical line 6.
The above-mentioned electronic unmanned plane of the application using four cantilever supports, eight motors, that is, subtracts compared with the prior art
The cantilever quantity being a half, but same amount of propeller can be obtained, it can while reducing an at least semi-cantilever quantity
To obtain same lift level, construction weight is reduced, lift efficiency and cruise duration are improved, bigger load can be carried
Lotus flying for long time.In addition, the rotary shaft coaxial arrangement of two motors supported on each cantilever, can use the side of positive and negative rotation
Formula offsets the torque of two propellers, and the torque balance of each cantilever itself carries out cooperation control without other cantilevers, reduces
The complexity of manipulation can obtain better handling.Also that is, in the preferred embodiment of the application, each cantilever 3
End two propellers 5 direction of rotation it is opposite.
Preferably, as shown, the fuselage 1 of the application is in octagon, cantilever 3 is arranged at intervals on the side length of octagon
Center.The fuselage 1 of the application is in the box of octagon, and cantilever 3 is arranged in edge lengths center, the regular appearance in space
Easily layout, convenient for reducing design and manufacturing complexity, nothing can be reduced in the reinforcement structure of fuselage interior setting supporting cantilever
Man-machine production cost.
Further, fuselage 1 is internally provided with two reinforcing beams 7 of the decussation of connecting cantilever 3.Namely cross
Four cantilevers 3 of shape layout, two opposite cantilevers 3 share a reinforcing beam 7, and two reinforcing beams 7 are in the center of fuselage position
It sets to form interconnection, steadily of centre of gravity is easily controllable.
In addition, two undercarriages 2 are symmetricly set on the lower part of fuselage 1, the symmetry axis 8 and reinforcing beam 7 of undercarriage 2 are in 45 degree
Angle.As previously described, because the inside of the fuselage 1 of octagon, therefore two are arranged in cross-shape layout for two reinforcing beams 7
Reinforcing beam 7 is mutually in 90 degree of angle.For undercarriage 7 due to being symmetrical arranged, the selection of symmetry axis 8 is in 45 degree of angles with reinforcing beam 7,
So that each undercarriage 2 can be attached with two reinforcing beams 7 simultaneously.Preferably, the company of each undercarriage 2 and fuselage 1
Contact is located on two reinforcing beams 7, thus, when undercarriage 2 supports the weight of fuselage 1, undercarriage 2 and fuselage 1
The position of connection is located on reinforcing beam 7 in fact.Also that is, undercarriage 2 needs to carry the weight of entire unmanned plane, therefore its
The position being connected with fuselage 1 needs to carry out structural strengthening design, thus the position that undercarriage 2 is connected with fuselage 1 is all set
On reinforcing beam 7, it can simplify structure design, reduce construction weight.
Still further, two groups of batteries 9 are preferably arranged in fuselage 1 in order to balance the center of gravity of unmanned plane, two groups of batteries 9 are right
Claim to be arranged in symmetry axis 8, that is, two groups of batteries 9 are arranged each parallel to undercarriage 2, is guaranteeing the same of drone center of unmanned aerial vehicle balance
When, same pressure can also be applied to two undercarriages when landing, so that the unmanned plane has preferably layout knot
Structure and applicability, and load setting can be preferably carried out, optimize structure design.
In conclusion the structure of electronic unmanned plane provided herein, so that the unmanned plane has preferably layout knot
Structure and applicability, and load setting can be preferably carried out, structure design is optimized, when improving lift efficiency and continuation of the journey
Between, bigger load flying for long time can be carried.
It will be appreciated by those skilled in the art that although the utility model is described in the way of multiple embodiments
, but not each embodiment only contains an independent technical solution.So narration is in specification just for the sake of clear
For the sake of, the skilled in the art should refer to the specification as a whole is understood, and by skill involved in each embodiment
Art scheme, which is regarded as, can be combined with each other into the modes of different embodiments to understand the protection scope of the utility model.
The above descriptions are merely exemplary embodiments of the present utility model, the model being not intended to limit the utility model
It encloses.Any those skilled in the art, under the premise of not departing from the conceptions and principles of the utility model made equivalent variations,
Modification and combination, should belong to the range of the utility model protection.
Claims (7)
1. a kind of electronic unmanned plane of coaxial double-oar, including fuselage (1), two undercarriages (2), cantilever (3) and motor (4) and spiral shell
It revolves paddle (5), which is characterized in that there are four the cantilevers (3), is symmetrically connected on the fuselage (1) with cross-shape layout；Each
The end of cantilever (3) is supported there are two the motor (4), and each motor (4) has a propeller (5)；Each cantilever
(3) shaft of two motors (4) on is located on same vertical line (6).
2. the electronic unmanned plane of coaxial double-oar as described in claim 1, which is characterized in that the fuselage (1) is in octagon, institute
State the center that cantilever (3) is arranged at intervals on the side length of the octagon.
3. the electronic unmanned plane of coaxial double-oar as claimed in claim 2, which is characterized in that fuselage (1) company of being internally provided with
Connect two reinforcing beams (7) of the decussation of the cantilever (3).
4. the electronic unmanned plane of coaxial double-oar as claimed in claim 3, which is characterized in that described two undercarriages (2) symmetrically set
The lower part in the fuselage (1) is set, the symmetry axis (8) of the undercarriage (2) and the reinforcing beam (7) are in 45 degree of angles.
5. the electronic unmanned plane of coaxial double-oar as claimed in claim 4, which is characterized in that each undercarriage (2) with it is described
The tie point of fuselage (1) is located on two reinforcing beams (7).
6. the electronic unmanned plane of coaxial double-oar as claimed in claim 5, which is characterized in that be provided with two groups in the fuselage (1)
Battery (9), two groups of batteries (9) are symmetrical with the symmetry axis (8) setting.
7. the electronic unmanned plane of coaxial double-oar as described in one of claim 1-6, which is characterized in that each cantilever (3)
The direction of rotation of two propellers (5) of end is opposite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822177367.7U CN209274892U (en) | 2018-12-24 | 2018-12-24 | A kind of electronic unmanned plane of coaxial double-oar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822177367.7U CN209274892U (en) | 2018-12-24 | 2018-12-24 | A kind of electronic unmanned plane of coaxial double-oar |
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| Publication Number | Publication Date |
|---|---|
| CN209274892U true CN209274892U (en) | 2019-08-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822177367.7U Active CN209274892U (en) | 2018-12-24 | 2018-12-24 | A kind of electronic unmanned plane of coaxial double-oar |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113002764A (en) * | 2019-12-18 | 2021-06-22 | 上海峰飞航空科技有限公司 | Multi-rotor aircraft with multi-axis staggered layout |
-
2018
- 2018-12-24 CN CN201822177367.7U patent/CN209274892U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113002764A (en) * | 2019-12-18 | 2021-06-22 | 上海峰飞航空科技有限公司 | Multi-rotor aircraft with multi-axis staggered layout |
| CN113002764B (en) * | 2019-12-18 | 2023-09-05 | 上海峰飞航空科技有限公司 | Multi-rotor aircraft with multi-axis staggered layout |
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