CN211468768U - Unmanned aerial vehicle with coaxial double propellers - Google Patents
Unmanned aerial vehicle with coaxial double propellers Download PDFInfo
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- CN211468768U CN211468768U CN201921775222.5U CN201921775222U CN211468768U CN 211468768 U CN211468768 U CN 211468768U CN 201921775222 U CN201921775222 U CN 201921775222U CN 211468768 U CN211468768 U CN 211468768U
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- 230000001681 protective effect Effects 0.000 claims abstract description 40
- 230000005484 gravity Effects 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 229910052799 carbon Inorganic materials 0.000 claims 1
- 239000000835 fiber Substances 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 15
- 239000003381 stabilizer Substances 0.000 abstract description 13
- 238000000034 method Methods 0.000 description 9
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 230000032683 aging Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/24—Coaxial rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/08—Geodetic or other open-frame structures
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
- B64C17/02—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus
- B64C17/06—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus by gyroscopic apparatus
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/06—Adjustable control surfaces or members, e.g. rudders with two or more independent movements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/30—Balancing hinged surfaces, e.g. dynamically
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The utility model discloses an unmanned aerial vehicle of coaxial double-oar, this unmanned aerial vehicle includes the protective housing, the screw subassembly, first stabilizer ring, the second stabilizer ring, the installation pole, drive assembly and control surface subassembly, the protective housing is fretwork honeycomb, the screw subassembly is established in the protective housing, two screws including coaxial setting, the direction of rotation of two screws is opposite, first stabilizer ring rotationally connects on the protective housing, the second stabilizer ring rotationally connects on first stabilizer ring, the both ends of installation pole all rotationally link to each other with the second stabilizer ring, drive assembly establishes on the installation pole, drive assembly links to each other with drive screw subassembly with screw subassembly and rotates, the control surface subassembly links to each other with the installation pole, and be located drive assembly's below, the control surface subassembly is configured as the flight gesture of the unmanned aerial vehicle of the coaxial double-oar of adjustment. This unmanned aerial vehicle of coaxial double-oar can reduce the probability of paddle damage, can guarantee unmanned aerial vehicle's aerodynamic efficiency and flight stability again.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to an unmanned aerial vehicle of coaxial double-oar.
Background
At present, many rotor unmanned aerial vehicle adopt the paddle to expose the setting usually, and the paddle exposes the setting and has promoted the risk of paddle damage. Certainly, in order to reduce the damage probability of the blades, a blade cover is arranged on the outer side of each blade of a part of multi-rotor unmanned aerial vehicle. But in the use discovery, the paddle cover that adds though can reduce the paddle and damage the probability, has reduced unmanned aerial vehicle's aerodynamic efficiency and flight stability.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an unmanned aerial vehicle of coaxial double-oar, this unmanned aerial vehicle of coaxial double-oar can reduce the probability of paddle damage, can guarantee unmanned aerial vehicle's aerodynamic efficiency and flight stability again.
For realizing the technical effect, the utility model discloses an unmanned aerial vehicle of coaxial double-oar's technical scheme as follows:
a coaxial, twin-bladed drone, comprising: the protective shell is of a hollow honeycomb structure; the propeller assembly is arranged in the protective shell and comprises two propellers which are coaxially arranged, the rotating directions of the two propellers are opposite, and the first balance ring is rotatably connected to the protective shell; a second gimbal ring rotatably coupled to the first gimbal ring; the two ends of the mounting rod are rotatably connected with the second balance ring; the driving assembly is arranged on the mounting rod and is connected with the propeller assembly so as to drive the propeller assembly to rotate; a control surface assembly coupled to the mounting posts and located below the drive assembly, the control surface assembly configured to adjust a flight attitude of the coaxial, double-bladed drone.
In some embodiments, the coaxial twin-bladed drone further comprises a control panel connected to the mounting bar, the control surface assembly being connected below the control panel.
In some embodiments, the control surface assembly comprises: a cross bar including two bars arranged crosswise, the crossing center of the two bars being on the extension line of the rotation axis of the propeller assembly; the number of the control surfaces is four, and two rotatable control surfaces are arranged on each rod piece.
In some embodiments, the angle between the two rods is 90 °.
In some embodiments, the first gimbal ring and the second gimbal ring are circular rings, the first gimbal ring having a diameter equal to a diameter of the second gimbal ring.
In some embodiments, the length of the mounting bar is equal to the diameter of the second gimbal, and the rotational axis of the propeller assembly passes through the center of gravity of the mounting bar.
In some embodiments, the first gimbal has two first rotating shafts, each of the two first rotating shafts is a cylinder, one end of each of the first rotating shafts is connected to the protective casing, and the axes of the two first rotating shafts are arranged in a collinear manner and pass through the center of the first gimbal.
In some embodiments, the second balance ring has two second rotating shafts, both of which are cylindrical, one end of each second rotating shaft is connected to the first balance ring, and the axes of the two second rotating shafts are arranged in a collinear manner and pass through the center of the second balance ring.
In some embodiments, the protective shell is a carbon fiber piece.
The utility model discloses an unmanned aerial vehicle of coaxial double-oar owing to have the protective housing that forms to fretwork honeycomb structure, can reduce screw assembly's damage probability, can guarantee screw assembly's aerodynamic performance again betterly. In addition, the gyroscope system that first stabilizer ring, second stabilizer ring and installation pole constitute can make the screw subassembly can not take place crooked at the in-process that unmanned aerial vehicle flies, has guaranteed unmanned aerial vehicle's flight stability.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
Fig. 1 is a schematic view of the coaxial double-oar unmanned aerial vehicle provided by the embodiment of the present invention.
Reference numerals:
1. a protective shell;
2. a propeller assembly;
3. a first gimbal ring; 31. a first rotating shaft;
4. a second gimbal ring; 41. a second rotating shaft;
5. mounting a rod;
6. a drive assembly;
7. a control surface assembly; 71. a cross bar; 72. a control surface.
Detailed Description
In order to make the technical problem solved by the present invention, the technical solution adopted by the present invention and the technical effect achieved by the present invention clearer, the technical solution of the present invention will be further explained by combining the drawings and by means of the specific implementation manner.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
Furthermore, features defined as "first" and "second" may explicitly or implicitly include one or more of the features for distinguishing between descriptive features, non-sequential, non-trivial and non-trivial. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The following describes a specific structure of a coaxial twin-oar unmanned aerial vehicle according to an embodiment of the present invention with reference to fig. 1.
As shown in figure 1, the utility model discloses a coaxial double-oar unmanned aerial vehicle includes protective housing 1, screw subassembly 2, first gimbal 3, second gimbal 4, installation pole 5, drive assembly 6 and control surface subassembly 7, protective housing 1 is a hollow honeycomb structure, screw subassembly 2 is established in protective housing 1, including two screws of coaxial arrangement, the direction of rotation of two screws is opposite, first gimbal 3 is rotationally connected on protective housing 1, second gimbal 4 is rotationally connected on first gimbal 3, both ends of installation pole 5 are rotationally connected with second gimbal 4, drive assembly 6 is established on installation pole 5, drive assembly 6 links to each other with screw subassembly 2 in order to drive screw subassembly 2 to rotate, control surface subassembly 7 links to each other with installation pole 5, and below the drive assembly 6, a control surface assembly 7 is configured to adjust the flight attitude of the coaxial twin-bladed drone.
It can be understood that the utility model discloses an unmanned aerial vehicle has protective housing 1, and screw subassembly 2 is located protective housing 1, and from this, protective housing 1 can play the effect of protection screw subassembly 2. And fretwork honeycomb's protective housing 1 has reduced the influence of protective housing 1 to the aerodynamic performance of screw subassembly 2, has guaranteed the aerodynamic performance of screw subassembly 2 better.
In addition, since the first balance ring 3 is rotatably provided on the protective case 1, the second balance ring 4 is rotatably coupled to the first balance ring 3, and both ends of the mounting rod 5 are rotatably coupled to the second balance ring 4. Thus, the first gimbal ring 3, the second gimbal ring 4, and the mounting rod 5 constitute one gyroscope. Like this, unmanned aerial vehicle is at the flight in-process, and the existence of gyroscope system makes screw subassembly 2 can not take place crooked all the time, has guaranteed coaxial two-way unmanned aerial vehicle's flight stability.
The utility model discloses an unmanned aerial vehicle of coaxial double-oar owing to have the protective housing 1 that forms to fretwork honeycomb structure, can reduce screw subassembly 2's damage probability, can guarantee screw subassembly 2's aerodynamic performance again betterly. In addition, the gyroscope system that first stabilizer ring 3, second stabilizer ring 4 and installation pole 5 constitute can make propeller component 2 can not take place crooked at the in-process that unmanned aerial vehicle flies, has guaranteed unmanned aerial vehicle's flight stability.
It should supplement the explanation the utility model discloses well drive assembly 6 comprises two brushless motor, is connected two motor bearings through motor cabinet and coaxial connecting piece, and one commentaries on classics motor installation changes the screw, and another screw is installed to the reversal motor. From this, the rotation direction of two screws is opposite to the rotational speed of two screws can be inequality, can control unmanned aerial vehicle's yaw gesture through the rotational speed difference of adjusting two screws.
In some embodiments, as shown in fig. 1, the coaxial twin-bladed drone further comprises a control panel connected to the mounting bar 5, the control surface assembly 7 being connected below the control panel. It can be understood that, be equipped with unmanned aerial vehicle's control system on the control panel, can make things convenient for controlling unmanned aerial vehicle like this, also can in time transmit the data of establishing the sensor on unmanned aerial vehicle and gathering, better improved unmanned aerial vehicle's practicality and ageing.
In some embodiments, as shown in fig. 1, the control surface assembly 7 comprises a crossbar 71 and control surfaces 72, the crossbar 71 comprising two bars arranged crosswise, the crossing centre of the two bars being on the extension of the rotation axis of the propeller assembly 2, the number of control surfaces 72 being four, and two rotatable control surfaces 72 being provided on each bar. It can be understood that the four operation faces can adjust the rolling attitude and the pitching attitude of the unmanned aerial vehicle under the action of the airflow generated by the rotation of the propeller component 2, so that the flight attitude of the unmanned aerial vehicle can be well adjusted.
In some embodiments, as shown in fig. 1, the angle between the two rods is 90 °. From this, can avoid four operation faces to take place to interfere at the rotation in-process to guarantee the adjustment of control surface subassembly 7 to unmanned aerial vehicle flight attitude better.
In some embodiments, as shown in fig. 1, the first balancing ring 3 and the second balancing ring 4 are circular rings, and the diameter of the first balancing ring 3 is equal to the diameter of the second balancing ring 4. From this, whole unmanned aerial vehicle's flight stability has been promoted.
In some embodiments, as shown in fig. 1, the length of the mounting rod 5 is equal to the diameter of the second gimbal 4, and the rotational axis of the propeller assembly 2 passes through the center of gravity of the mounting rod 5. It can be understood that, because the first gimbal 3 and the second gimbal 4 are circular rings with equal diameters, and the length of the mounting rod 5 is equal to the diameter of the second gimbal 4, the rotation axis of the propeller assembly 2 passes through the center of gravity of the mounting rod 5, so that the propeller assembly 2 and the control surface assembly 7 are ensured to be located at the central position of the protective shell 1, and the flight stability of the unmanned aerial vehicle is improved.
In some embodiments, as shown in fig. 1, the first balance ring 3 has two first rotating shafts 31, each of the two first rotating shafts 31 is a cylinder, one end of each first rotating shaft 31 is connected to the protective casing 1, and the axes of the two first rotating shafts 31 are arranged in a collinear manner and pass through the center of the first balance ring 3. From this, can guarantee that first stabilizer ring 3 can stabilize and smooth and easy relative protective housing 1 rotates to indirect assurance unmanned aerial vehicle can not take place crooked at flight in-process screw subassembly 2.
In some embodiments, as shown in fig. 1, the second balance ring 4 has two second rotating shafts 41, each of the two second rotating shafts 41 is a cylinder, one end of each second rotating shaft 41 is connected to the first balance ring 3, and the axes of the two second rotating shafts 41 are arranged in a collinear manner and pass through the center of the second balance ring 4. From this, can guarantee that second gimbal 4 can stabilize and smooth and easy relative first gimbal 3 rotates to indirect assurance unmanned aerial vehicle can not take place crooked at flight in-process screw subassembly 2.
In some embodiments, the protective case 1 is a carbon fiber piece. From this, protective housing 1 adopts the carbon fiber to support and subtracts the aircraft dead weight under the prerequisite of guaranteeing the intensity maximize, reduces the resistance of flight in-process. Of course, the protective casing 1 can also be made of other materials.
Example 1:
the structure of a coaxial twin-oar unmanned aerial vehicle according to an embodiment of the present invention is described below with reference to fig. 1.
The utility model discloses coaxial double-oar unmanned aerial vehicle includes protective housing 1, screw subassembly 2, first stabilizer ring 3, second stabilizer ring 4, installation pole 5, drive assembly 6 and control surface subassembly 7, and protective housing 1 is fretwork honeycomb, and screw subassembly 2 is established in protective housing 1, and this screw subassembly 2 includes two screws of coaxial setting, the direction of rotation of two screws is opposite. The first balance ring 3 and the second balance ring 4 are circular rings, and the diameter of the first balance ring 3 is equal to that of the second balance ring 4. The first balance ring 3 is provided with two first rotating shafts 31, each of the two first rotating shafts 31 is a cylinder, one end of each first rotating shaft 31 is connected with the protective shell 1, and the axes of the two first rotating shafts 31 are arranged in a collinear manner and pass through the circle center of the first balance ring 3. As shown in fig. 1, the second balance ring 4 has two second rotating shafts 41, each of the two second rotating shafts 41 is a cylinder, one end of each second rotating shaft 41 is connected to the first balance ring 3, and the axes of the two second rotating shafts 41 are arranged in a collinear manner and pass through the center of the second balance ring 4. Both ends of installation pole 5 all rotationally link to each other with second gimbal 4 and the length of installation pole 5 equals the diameter of second gimbal 4, and drive assembly 6 is established on installation pole 5, and drive assembly 6 links to each other with propeller component 2 and rotates with drive propeller component 2, and control surface component 7 links to each other with the control panel, and control surface component 7 connects below the control panel, and control surface component 7 is configured as the flight gesture of the unmanned aerial vehicle of adjustment coaxial double oar. The control surface assembly 7 comprises a crossbar 71 and control surfaces 72, the crossbar 71 being connected to the control panel, the crossbar 71 comprising two bars arranged crosswise, the crossing centre of the two bars being on the extension of the rotation axis of the propeller assembly 2, the number of control surfaces 72 being four, and two rotatable control surfaces 72 being provided on each bar.
The advantages of the coaxial twin-bladed drone of the present embodiment are as follows:
1. the coaxial double-oar aircraft has stable and reliable performance and wide application range, is different from the traditional aircraft in layout, adopts spherical appearance, the driving component 6 is positioned in a hollow sphere, and can adapt to and meet different use environments by utilizing the full symmetry characteristic of a spherical structure and the non-toppling characteristic of an internal gyroscope;
2. meanwhile, vertical take-off and landing are supported, and the take-off and landing maneuverability is fast because a runway is not needed, the take-off field can be quickly switched according to a specific task place at any time, the position is fast to move, and the use cost of the unmanned aerial vehicle is greatly reduced;
3. the unmanned aerial vehicle has the advantages that the operation is simple, the use safety is high, the propeller assembly 2, the driving assembly 6 and the control panel can be protected by the protective shell 1, the damage of the unmanned aerial vehicle to people or objects in the flight collision process is reduced, and the damage of the unmanned aerial vehicle is also reduced;
4. the universal components all use national standard, so that the unmanned aerial vehicle is more convenient and faster to mount and dismount;
5. the coaxial double-oar aircraft of this embodiment only has a basketball size to the light volume of quality is easily carried, small, easily carries of complete machine quality, and protective housing 1 adopts the fretwork design.
In the description herein, references to the description of "some embodiments," "other embodiments," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The above description is only for the preferred embodiment of the present invention, and for those skilled in the art, there are variations on the detailed description and the application scope according to the idea of the present invention, and the content of the description should not be construed as a limitation to the present invention.
Claims (9)
1. An unmanned aerial vehicle of coaxial double-oar, its characterized in that includes:
the protective shell (1), the protective shell (1) is of a hollow honeycomb structure;
the propeller assembly (2) is arranged in the protective shell (1) and comprises two coaxially arranged propellers, and the rotating directions of the two propellers are opposite;
a first balancing ring (3), wherein the first balancing ring (3) is rotatably connected to the protective shell (1);
a second balancing ring (4), the second balancing ring (4) being rotatably connected to the first balancing ring (3);
the two ends of the mounting rod (5) are rotatably connected with the second balance ring (4);
the driving assembly (6) is arranged on the mounting rod (5), and the driving assembly (6) is connected with the propeller assembly (2) to drive the propeller assembly (2) to rotate;
a control surface assembly (7), the control surface assembly (7) being connected to the mounting bar (5) and located below the drive assembly (6), the control surface assembly (7) being configured to adjust the flight attitude of the coaxial twin-bladed drone.
2. The coaxial twin-bladed drone according to claim 1, further comprising a control board connected to the mounting bar (5), the control surface assembly (7) being connected below the control board.
3. The coaxial twin-bladed drone according to claim 2, characterized in that the control surface assembly (7) comprises:
a cross-bar (71), said cross-bar (71) comprising two bars arranged crosswise, the crossing center of the two bars being on the extension of the rotation axis of the propeller assembly (2);
the number of the control surfaces (72) is four, and two rotatable control surfaces (72) are arranged on each rod piece.
4. The coaxial, twin-bladed drone of claim 3, wherein the angle between the two bars is 90 °.
5. Coaxial twin-bladed drone according to claim 1, characterised in that the first gimbal ring (3) and the second gimbal ring (4) are circular rings, the diameter of the first gimbal ring (3) being equal to the diameter of the second gimbal ring (4).
6. Coaxial twin-bladed drone according to claim 5, characterised in that the length of the mounting bar (5) is equal to the diameter of the second gimbal ring (4), the rotation axis of the propeller assembly (2) passing through the centre of gravity of the mounting bar (5).
7. The coaxial twin-oar unmanned aerial vehicle of claim 5, wherein the first gimbal (3) has two first rotating shafts (31), the two first rotating shafts (31) are both cylinders, one end of each first rotating shaft (31) is connected with the protective shell (1), and the axes of the two first rotating shafts (31) are arranged in a collinear way and pass through the circle center of the first gimbal (3).
8. The coaxial twin-oar unmanned aerial vehicle of claim 5, wherein the second gimbal (4) has two second rotating shafts (41), both of the two second rotating shafts (41) are cylindrical, one end of each of the second rotating shafts (41) is connected with the first gimbal (3), and the axes of the two second rotating shafts (41) are arranged in a collinear way and pass through the center of the second gimbal (4).
9. Coaxial twin-bladed drone according to any of claims 1 to 8, characterised in that the protective casing (1) is a carbon fibre piece.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921775222.5U CN211468768U (en) | 2019-10-22 | 2019-10-22 | Unmanned aerial vehicle with coaxial double propellers |
| PCT/CN2020/122913 WO2021078204A1 (en) | 2019-10-22 | 2020-10-22 | Unmanned aerial vehicle having dual coaxial propellers |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921775222.5U CN211468768U (en) | 2019-10-22 | 2019-10-22 | Unmanned aerial vehicle with coaxial double propellers |
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| Publication Number | Publication Date |
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| CN211468768U true CN211468768U (en) | 2020-09-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921775222.5U Active CN211468768U (en) | 2019-10-22 | 2019-10-22 | Unmanned aerial vehicle with coaxial double propellers |
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| Country | Link |
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| CN (1) | CN211468768U (en) |
| WO (1) | WO2021078204A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021078204A1 (en) * | 2019-10-22 | 2021-04-29 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle having dual coaxial propellers |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101934858A (en) * | 2010-07-08 | 2011-01-05 | 王泽峰 | Miniature electric ducted propeller type intelligent unmanned aerial vehicle |
| US10112694B2 (en) * | 2010-07-23 | 2018-10-30 | Gaofei Yan | Self-righting aeronautical vehicle and method of use |
| CN109367762B (en) * | 2018-10-17 | 2021-12-28 | 江西洪都航空工业集团有限责任公司 | Auxiliary control surface control device of tilting ducted aircraft |
| CN209225393U (en) * | 2018-11-27 | 2019-08-09 | 青岛歌尔机器人有限公司 | A kind of unmanned plane during flying device |
| CN110203386A (en) * | 2019-05-31 | 2019-09-06 | 上海大学 | A kind of new coaxial unmanned machine of configuration omnidirectional |
| CN110194259B (en) * | 2019-06-17 | 2023-03-31 | 西北工业大学 | Intelligent cage-shaped rotor unmanned aerial vehicle |
| CN211468768U (en) * | 2019-10-22 | 2020-09-11 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle with coaxial double propellers |
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2019
- 2019-10-22 CN CN201921775222.5U patent/CN211468768U/en active Active
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2020
- 2020-10-22 WO PCT/CN2020/122913 patent/WO2021078204A1/en active Application Filing
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021078204A1 (en) * | 2019-10-22 | 2021-04-29 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle having dual coaxial propellers |
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| WO2021078204A1 (en) | 2021-04-29 |
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