CN206144655U - Many rotor unmanned aerial vehicle engine cooling device and many rotor unmanned aerial vehicle - Google Patents
Many rotor unmanned aerial vehicle engine cooling device and many rotor unmanned aerial vehicle Download PDFInfo
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- CN206144655U CN206144655U CN201621169997.4U CN201621169997U CN206144655U CN 206144655 U CN206144655 U CN 206144655U CN 201621169997 U CN201621169997 U CN 201621169997U CN 206144655 U CN206144655 U CN 206144655U
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Abstract
The utility model relates to an unmanned air vehicle technique field discloses a many rotor unmanned aerial vehicle engine cooling device and many rotor unmanned aerial vehicle. Wherein the outer cooler bin of engine is located including being located the inside just cover of fuselage to many rotor unmanned aerial vehicle engine cooling device, including the wing pipe assembly of first wing pipe and second wing pipe, manages communicating water pump and is connected respectively in the controller of engine and water pump with cooler bin and first wing pipe / second wing. The utility model discloses a many rotor unmanned aerial vehicle include many rotor unmanned aerial vehicle engine cooling device. The utility model discloses the design of first wing pipe and second wing pipe can make full use of unmanned aerial vehicle the afterbody space, the while can increase the heat radiating area of coolant liquid as far as, on the basis in the unmanned helicopter afterbody space of make full use of, can be better carry out cooling to the engine, make the work of unmanned helicopter safer.
Description
Technical field
This utility model is related to unmanned air vehicle technique field, more particularly to a kind of multi-rotor unmanned aerial vehicle engine cooling apparatus and
Multi-rotor unmanned aerial vehicle.
Background technology
Multi-rotor unmanned aerial vehicle use in daily life is more and more extensive, existing with the multiple rotors of engine driving
In the course of the work, the operating of its high engine speeds can produce amount of heat to multi-rotor unmanned aerial vehicle, only with body high-speed mobile without
Method carries out sufficiently natural air cooled, such as cannot timely and effectively radiate, and easily makes engine overheat and breaks down, or even causes
The crash of multi-rotor unmanned aerial vehicle, produces huge economic loss.
Therefore, in order to obtain good radiating effect, it usually needs for the cooling system that electromotor installs complexity additional, not only increase
The unnecessary heavy burden of unmanned plane is added, has reduced the efficiency of unmanned plane, reduced unmanned plane cruising time, and safeguarded very not
Just.
And in existing multi-rotor unmanned aerial vehicle structure rotor arm be mainly designed to rotor is installed, rotor arm generally passes through
Canalis pterygoideus is connected with fuselage, and with certain length, the drive mechanism of each rotor is each independently arranged in corresponding rotor arm.
But the space at this design rotor arm is completely utilized, and only serves the effect for supporting rotor.
Utility model content
The purpose of this utility model is to provide a kind of multi-rotor unmanned aerial vehicle engine cooling apparatus, is making full use of many rotations
On the basis of wing unmanned plane trailing space, preferably electromotor can be cooled down, make the work of multi-rotor unmanned aerial vehicle
It is safer.
Another object of the present utility model is to provide a kind of multi-rotor unmanned aerial vehicle, including above-mentioned multi-rotor unmanned aerial vehicle is started
Machine chiller.
It is that, up to this purpose, this utility model is employed the following technical solutions：A kind of multi-rotor unmanned aerial vehicle engine cooling apparatus,
Including：
Cooler bin, is arranged on the electromotor outside of multi-rotor unmanned aerial vehicle, and inside is contained with coolant, for electromotor
Cooled down；
Some groups of canalis pterygoideus components, respectively between the fuselage and each rotor of multi-rotor unmanned aerial vehicle, including the first canalis pterygoideus
With the second canalis pterygoideus, first canalis pterygoideus and the second canalis pterygoideus of every group of canalis pterygoideus component be interconnected near one end of rotor, and the other end wears
On fuselage and connect cooler bin；
Water pump, is connected with cooler bin, while connect with the first canalis pterygoideus or the second canalis pterygoideus, for the first canalis pterygoideus or second
Canalis pterygoideus pumps coolant；
Controller, in fuselage, and is connected to electromotor and water pump.
Preferably, the water pump is provided with one, it is total that the first canalis pterygoideus of some groups of canalis pterygoideus components is communicated in first jointly
Pipe, the second canalis pterygoideus is communicated in the second house steward jointly, and the water pump is communicated in first wing by the first house steward or the second house steward
Pipe or the second canalis pterygoideus.
Preferably, being provided with inlet and liquid outlet on the cooler bin, the inlet is communicated in the first house steward not
One end of the first canalis pterygoideus is connected, the liquid outlet is communicated in one end that the second house steward does not connect the second canalis pterygoideus by water pump.
Preferably, the water pump is provided with multiple, it is provided with the cooler bin and a pair of some groups of canalis pterygoideus components 1
The some groups of inlets answered and liquid outlet；
Per group of inlet is communicated in the first canalis pterygoideus, and per group of liquid outlet is communicated in the second canalis pterygoideus by water pump.
Preferably, the multi-rotor unmanned aerial vehicle engine cooling apparatus also include being arranged on electromotor and being connected to control
The temperature-detecting device of device processed, for detecting the operating temperature of the electromotor.
Preferably, the canalis pterygoideus component also includes the 3rd canalis pterygoideus, described 3rd canalis pterygoideus one end is connected to fuselage, sets in it
There is the drive mechanism of the connection rotor and electromotor.
Preferably, the first canalis pterygoideus of each canalis pterygoideus component and the second canalis pterygoideus level and it is symmetrical be located on fuselage, the 3rd
Canalis pterygoideus is horizontally placed at the lower section of the first canalis pterygoideus and the second canalis pterygoideus and its axis is located at the symmetrical plane of the first canalis pterygoideus and the second canalis pterygoideus
On.
Preferably, the first canalis pterygoideus of each canalis pterygoideus component and the second canalis pterygoideus length are identical, the length of the 3rd canalis pterygoideus is more than the
One canalis pterygoideus, and the length difference of the 3rd canalis pterygoideus and the first canalis pterygoideus is more than the length of rotor blade.
Preferably, the 3rd canalis pterygoideus of each canalis pterygoideus component is horizontally disposed with, the first canalis pterygoideus and the second canalis pterygoideus are inclined and symmetrical
Positioned at the lower section of the 3rd canalis pterygoideus, and one end that the first canalis pterygoideus and the second canalis pterygoideus are connected is fixed on the 3rd canalis pterygoideus near the one of rotor
End.
To reach another object, this utility model additionally provides a kind of multi-rotor unmanned aerial vehicle, including many rotations as above
Wing unmanned vehicle engine chiller.
Multi-rotor unmanned aerial vehicle engine cooling apparatus of the present utility model are by the first canalis pterygoideus and the second canalis pterygoideus near rotor
One end is interconnected, and the other end is communicated in cooler bin, the coolant in cooler bin can be delivered to into first wing by water pump
In pipe and the second canalis pterygoideus, a closed circulation path is formed, by the setting of the first canalis pterygoideus and the second canalis pterygoideus, on the one hand be make use of
The canalis pterygoideus space (space i.e. between fuselage and rotor) of existing multi-rotor unmanned aerial vehicle, it is to avoid the waste in the canalis pterygoideus space；Separately
On the one hand, by the first canalis pterygoideus and the second canalis pterygoideus, by increasing capacitance it is possible to increase the area of dissipation of coolant so that coolant and outside air
Heat exchange is more abundant, and then preferably electromotor is cooled down, and improves the service life of electromotor, makes many rotors
The work of unmanned plane is safer.
Multi-rotor unmanned aerial vehicle of the present utility model, including multi-rotor unmanned aerial vehicle engine cooling apparatus as above,
On the basis of making full use of canalis pterygoideus space, preferably engine cool can be lowered the temperature, improve the service life of electromotor, be made
The work of multi-rotor unmanned aerial vehicle is safer.
Description of the drawings
Fig. 1 is the top view of this utility model embodiment one；
Fig. 2 is the front view of this utility model embodiment one；
Fig. 3 is the top view of this utility model embodiment two；
Fig. 4 is the front view of this utility model embodiment two.
In figure：
1st, cooler bin；11st, inlet；12nd, liquid outlet；2nd, canalis pterygoideus component；21st, the first canalis pterygoideus；22nd, the second canalis pterygoideus；23rd,
Three canalis pterygoideus；3rd, water pump；4th, temperature-detecting device；5th, electromotor；6th, fuselage；7th, rotor.
Specific embodiment
Further illustrate the technical solution of the utility model below in conjunction with the accompanying drawings and by specific embodiment.
Embodiment one
A kind of multi-rotor unmanned aerial vehicle engine cooling apparatus are present embodiments provided, as depicted in figs. 1 and 2, including：Cooling
Case 1, some groups of canalis pterygoideus components 2, water pump 3 and controllers.
Above-mentioned cooler bin 1, is arranged on the outside of electromotor 5 of multi-rotor unmanned aerial vehicle, and inside is contained with coolant, for right
Electromotor 5 is cooled down.Specifically, the casing of the cooler bin 1 of the present embodiment can be coated on the outside setting of electromotor 5, so as to
In the comprehensive cooling to electromotor 5.
Above-mentioned some groups of canalis pterygoideus components 2, respectively between the fuselage 6 and each rotor 7 of multi-rotor unmanned aerial vehicle, including the
One canalis pterygoideus 21 and the second canalis pterygoideus 22, first canalis pterygoideus 21 and the second canalis pterygoideus 22 of every group of canalis pterygoideus component 2 is mutual near one end of rotor 7
Connection, the other end is arranged on fuselage 6 and connects cooler bin 1.
Above-mentioned water pump 3, is connected with cooler bin 1, while connect with the first canalis pterygoideus 21 or the second canalis pterygoideus 22, for first
21 or second canalis pterygoideus of canalis pterygoideus 22 pumps coolant.
Controller noted above, in fuselage 6, and is connected to electromotor 5 and water pump 3.
Specifically, above-mentioned water pump 3 is provided with one, and an inlet 11 and a liquid outlet are provided with cooler bin 1
12.First canalis pterygoideus 21 of above-mentioned some groups of canalis pterygoideus components 2 is communicated in first house steward's (not shown) jointly, and the second canalis pterygoideus 22 is total to
With second house steward's (not shown) is communicated in, inlet 11 is communicated in one end that the first house steward does not connect the first canalis pterygoideus 21, goes out
Liquid mouth 12 is then communicated in one end that the second house steward does not connect the second canalis pterygoideus 22 by water pump 3.Coolant in cooler bin 1 passes through water
The Jing liquid outlets 12 of pump 3 are delivered to the second house steward, subsequently branch to each second canalis pterygoideus 22 by the second house steward, and then cause cooling
Liquid carries out heat exchange with the external world, and the first canalis pterygoideus of Jing 21 converges into the first house steward with after, enters cold by the first house steward Jing inlets 11
But case 1, to proceed cooling to electromotor 5.
It is understood that above-mentioned water pump 3 can also be provided with multiple (not shown)s, it is now corresponding on cooler bin 1
Be provided with multigroup inlet 11 and liquid outlet 12, wherein per group of inlet 11 is respectively communicated with canalis pterygoideus group corresponding thereto
First canalis pterygoideus 21 of part 2, per group of liquid outlet 12 is respectively communicated with canalis pterygoideus component 2 corresponding thereto by a water pump 3
Second canalis pterygoideus 22.
Realize being delivered to the coolant Rapid Circulation in cooler bin 1 in second canalis pterygoideus 22 by the setting of water pump 3,
In order to preferably realize the heat exchange of coolant and the external world.
Specifically, multi-rotor unmanned aerial vehicle engine cooling apparatus of the present utility model also include be arranged on electromotor 5 and
The temperature-detecting device 4 of controller is connected to, for detecting the operating temperature of the electromotor 5.
In the present embodiment, Fig. 1 and Fig. 2 is can refer to, above-mentioned canalis pterygoideus component 2 also includes the 3rd canalis pterygoideus 23, the 3rd canalis pterygoideus 23
One end is connected to fuselage 6, and the other end is provided with rotor 7, and the drive mechanism of connection rotor 7 and electromotor 5, this enforcement are provided with it
In example, above-mentioned drive mechanism is power transmission shaft, and electromotor 5 drives rotor 7 to rotate by power transmission shaft.The setting of the 3rd canalis pterygoideus 23, enters
One step make use of the space between fuselage 6 and rotor 7, and can preferably protect drive mechanism.
Specifically, first canalis pterygoideus 21 and the level of the second canalis pterygoideus 22 of each canalis pterygoideus component 2 and it is symmetrical be located on fuselage 6,
3rd canalis pterygoideus 23 is horizontally placed at the lower section of the first canalis pterygoideus 21 and the second canalis pterygoideus 22 and its axis is located at the first canalis pterygoideus 21 and second wing
On the symmetrical plane of pipe 22, meanwhile, the first canalis pterygoideus 21 is identical with the length of the second canalis pterygoideus 22, and the length of the 3rd canalis pterygoideus 23 is more than first
Canalis pterygoideus 21, and the length difference of the 3rd canalis pterygoideus 23 and the first canalis pterygoideus 21 prevents the 3rd canalis pterygoideus 23 more than the length of the blade of rotor 7
On rotor 7 operationally interfered by the first canalis pterygoideus 21 and the second canalis pterygoideus 22.
Closed circulation path, the He of the first canalis pterygoideus 21 are formed between the canalis pterygoideus 21 of above-mentioned cooler bin 1 and first and the second canalis pterygoideus 22
The setting of the second canalis pterygoideus 22, both make use of the space between fuselage 6 and rotor 7, it is to avoid the waste in the canalis pterygoideus space, again could
Increase the area of dissipation of coolant so that coolant is more abundant with the heat exchange of outside air, can preferably to the shape that works
The electromotor 5 of state is cooled down, and extends the service life of electromotor 5, makes the work of multi-rotor unmanned aerial vehicle safer.
The setting of water pump 3, for the coolant in above-mentioned closed circulation path circulation power is provided, and makes coolant in above-mentioned envelope
Flowing, improves the radiating efficiency of coolant in closed loop path.
When multi-rotor unmanned aerial vehicle engine cooling apparatus in the present embodiment work, will be subsidiary by water pump 3 by controller
The coolant of high temperature is exported from the liquid outlet 12 of cooler bin 1, through the second canalis pterygoideus 22 and the first canalis pterygoideus 21, under multiple rotors 7
Gas washing stream is air-cooled and external environment condition cooling effect under, the high temperature coolant for flowing through the first canalis pterygoideus 21 and the second canalis pterygoideus 22 drops rapidly
Temperature, the coolant Jing inlet 11 after cooling is back in cooler bin 1, and continuation is cooled down to electromotor 5, by above-mentioned first canalis pterygoideus
21 and second canalis pterygoideus 22 setting, enabling to the coolant in cooler bin 1 can circulate, and constantly with each rotor
7 downwash flows and external environment condition do heat exchange.And first canalis pterygoideus 21 and the second canalis pterygoideus 22 be arranged on rationally using the He of fuselage 6
Between rotor 7 on the basis of space, the area of dissipation of coolant is increased, it is more preferable to the cooling radiating effect of electromotor 5, make nothing
The work of people's helicopter is safer.
During coolant is to the circulating cooling of electromotor 5, working condition is detected by temperature-detecting device 4 by controller
The temperature of lower electromotor 5, when detected temperature is less than corresponding preset value, water pump 3 is not actuated, during higher than preset value,
Start water pump 3, during to electromotor 5 by below high temperature cooling to preset value, water pump 3 is closed down, so as to reach the effect of energy-conservation.Its
In, when the temperature detected by temperature-detecting device 4 is higher than corresponding preset value, start water pump 3, and according to detected
The size of temperature, by water pump 3 flow velocity of the coolant in above-mentioned closed circulation path is accordingly adjusted, and is made to the cold of electromotor 5
But radiating effect more preferably, makes work of many rotors without liter machine safer.
Embodiment two
As shown in Figure 3 and Figure 4, another kind of multi-rotor unmanned aerial vehicle engine cooling apparatus are present embodiments provided, itself and reality
It is in place of the difference for applying example one：3rd canalis pterygoideus 23 is horizontally disposed with, and the first canalis pterygoideus 21 and the second canalis pterygoideus 22 are inclined and symmetrical position
In the lower section of the 3rd canalis pterygoideus 23, and one end that the first canalis pterygoideus 21 is connected with the second canalis pterygoideus 22 is fixed on the 3rd canalis pterygoideus 23 near rotation
One end of the wing 7, is connected to one end of cooler bin 1 and is located on fuselage 6 so that the first canalis pterygoideus 21, the second canalis pterygoideus 22 and the 3rd
It is in class triangular structure between canalis pterygoideus 23, further enhances the intensity of multi-rotor unmanned aerial vehicle, improves multi-rotor unmanned aerial vehicle and fly
Capable stability, make use of the space between fuselage 6 and rotor 7, and can preferably protect drive mechanism.
The said structure of the first canalis pterygoideus 21, the second canalis pterygoideus 22 and the 3rd canalis pterygoideus 23 is arranged, and makes the support to rotor 7 more steady
It is fixed, the anti-twisted power that the balance rotation of main rotor 7 is produced preferably is supported away from working order lower operation is more to make multi-rotor unmanned aerial vehicle
Steadily, meanwhile, compared to embodiment one, between the first canalis pterygoideus 21, the second canalis pterygoideus 22 and the 3rd canalis pterygoideus 23 between be separated with it is certain away from
From, the first canalis pterygoideus 21 and the second canalis pterygoideus 22 and extraneous contact area are increased, more preferable radiating effect can be played.
Remaining structure is identical with embodiment one, repeats no more.
This utility model additionally provides a kind of multi-rotor unmanned aerial vehicle, including above-described embodiment one or many rotations in embodiment two
Wing unmanned vehicle engine chiller.
Obviously, above-described embodiment of the present utility model is used for the purpose of clearly explanation this utility model example, and
It is not the restriction to embodiment of the present utility model.For those of ordinary skill in the field, in described above
On the basis of can also make other changes in different forms.There is no need to give all of embodiment
It is exhaustive.All any modification, equivalent and improvement made within spirit of the present utility model and principle etc., should be included in
Within this utility model scope of the claims.
Claims (10)
1. a kind of multi-rotor unmanned aerial vehicle engine cooling apparatus, it is characterised in that include：
Cooler bin (1), is arranged on electromotor (5) outside of multi-rotor unmanned aerial vehicle, and inside is contained with coolant, for starting
Machine (5) is cooled down；
Some groups of canalis pterygoideus components (2), respectively between the fuselage (6) and each rotor (7) of multi-rotor unmanned aerial vehicle, including first
Canalis pterygoideus (21) and the second canalis pterygoideus (22), first canalis pterygoideus (21) and the second canalis pterygoideus (22) of every group of canalis pterygoideus component (2) is near rotor (7)
One end be interconnected, the other end is arranged on fuselage (6) and connects cooler bin (1)；
Water pump (3), is connected with cooler bin (1), while connect with the first canalis pterygoideus (21) or the second canalis pterygoideus (22), for first
Canalis pterygoideus (21) or the second canalis pterygoideus (22) pumping coolant；
Controller, in fuselage (6), and is connected to electromotor (5) and water pump (3).
2. multi-rotor unmanned aerial vehicle engine cooling apparatus according to claim 1, it is characterised in that the water pump (3) sets
It is equipped with one；
First canalis pterygoideus (21) of some groups of canalis pterygoideus components (2) is communicated in the first house steward jointly, and the second canalis pterygoideus (22) is communicated in jointly
Second house steward, the water pump (3) is communicated in first canalis pterygoideus (21) or the second canalis pterygoideus by the first house steward or the second house steward
(22)。
3. multi-rotor unmanned aerial vehicle engine cooling apparatus according to claim 2, it is characterised in that set on the cooler bin
It is equipped with inlet (11) and liquid outlet (12)；
The inlet (11) is communicated in one end that the first house steward does not connect the first canalis pterygoideus (21), and the liquid outlet passes through water pump
(3) it is communicated in one end that the second house steward does not connect the second canalis pterygoideus (22).
4. multi-rotor unmanned aerial vehicle engine cooling apparatus according to claim 1, it is characterised in that the water pump (3) sets
Be equipped with it is multiple, be provided with the cooler bin (1) with the one-to-one some groups of inlets (11) of some groups of canalis pterygoideus components (2) and
Liquid outlet (12)；
Per group of inlet (11) is communicated in the first canalis pterygoideus (21), and per group of liquid outlet (12) is communicated in second by water pump (3)
Canalis pterygoideus (22).
5. multi-rotor unmanned aerial vehicle engine cooling apparatus according to claim 1-4 any one, it is characterised in that also wrap
The temperature-detecting device (4) for being arranged on electromotor (5) and being connected to controller is included, for detecting the work of the electromotor (5)
Make temperature.
6. multi-rotor unmanned aerial vehicle engine cooling apparatus according to claim 5, it is characterised in that the canalis pterygoideus component
(2) the 3rd canalis pterygoideus (23) is also included, described 3rd canalis pterygoideus (23) one end is connected to fuselage (6), is provided with it described in connection and starts
The drive mechanism of machine (5) and rotor (7).
7. multi-rotor unmanned aerial vehicle engine cooling apparatus according to claim 6, it is characterised in that every group of canalis pterygoideus component
(2) the first canalis pterygoideus (21) and the second canalis pterygoideus (22) level and it is symmetrical be located on fuselage (6), the 3rd canalis pterygoideus (23) level is put
In the lower section of the first canalis pterygoideus (21) and the second canalis pterygoideus (22) and its axis is located at the right of the first canalis pterygoideus (21) and the second canalis pterygoideus (22)
Claim in plane.
8. multi-rotor unmanned aerial vehicle engine cooling apparatus according to claim 7, it is characterised in that every group of canalis pterygoideus component
(2) the first canalis pterygoideus (21) is identical with the second canalis pterygoideus (22) length, and the length of the 3rd canalis pterygoideus (23) is more than the first canalis pterygoideus (21), and
3rd canalis pterygoideus (23) is more than the length of rotor (7) blade with the length difference of the first canalis pterygoideus (21).
9. multi-rotor unmanned aerial vehicle engine cooling apparatus according to claim 6, it is characterised in that per group of each canalis pterygoideus component
(2) the 3rd canalis pterygoideus (23) is horizontally disposed with, and the first canalis pterygoideus (21) and the second canalis pterygoideus (22) incline and be symmetrically located in the 3rd canalis pterygoideus
(23) lower section, and one end that the first canalis pterygoideus (21) is connected with the second canalis pterygoideus (22) is fixed on the 3rd canalis pterygoideus (23) near rotor
(7) one end.
10. a kind of multi-rotor unmanned aerial vehicle, it is characterised in that including the multi-rotor unmanned aerial vehicle described in claim 1-9 any one
Engine cooling apparatus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621169997.4U CN206144655U (en) | 2016-10-26 | 2016-10-26 | Many rotor unmanned aerial vehicle engine cooling device and many rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621169997.4U CN206144655U (en) | 2016-10-26 | 2016-10-26 | Many rotor unmanned aerial vehicle engine cooling device and many rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206144655U true CN206144655U (en) | 2017-05-03 |
Family
ID=58622914
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621169997.4U Active CN206144655U (en) | 2016-10-26 | 2016-10-26 | Many rotor unmanned aerial vehicle engine cooling device and many rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206144655U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106437997A (en) * | 2016-10-26 | 2017-02-22 | 天津曙光天成科技有限公司 | Cooling device for engine of multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle |
| CN107176288A (en) * | 2017-05-25 | 2017-09-19 | 成都川通达科技有限公司 | A kind of energy-saving unmanned plane |
| CN107226213A (en) * | 2017-06-02 | 2017-10-03 | 成都川通达科技有限公司 | A kind of high efficiency and heat radiation unmanned plane |
| CN107310733A (en) * | 2017-06-02 | 2017-11-03 | 成都川通达科技有限公司 | A kind of unmanned plane |
-
2016
- 2016-10-26 CN CN201621169997.4U patent/CN206144655U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106437997A (en) * | 2016-10-26 | 2017-02-22 | 天津曙光天成科技有限公司 | Cooling device for engine of multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle |
| CN107176288A (en) * | 2017-05-25 | 2017-09-19 | 成都川通达科技有限公司 | A kind of energy-saving unmanned plane |
| CN107226213A (en) * | 2017-06-02 | 2017-10-03 | 成都川通达科技有限公司 | A kind of high efficiency and heat radiation unmanned plane |
| CN107310733A (en) * | 2017-06-02 | 2017-11-03 | 成都川通达科技有限公司 | A kind of unmanned plane |
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