CN113165743A - Unmanned aerial vehicle with rotary-type folding wing - Google Patents
Unmanned aerial vehicle with rotary-type folding wing Download PDFInfo
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- CN113165743A CN113165743A CN201980081520.0A CN201980081520A CN113165743A CN 113165743 A CN113165743 A CN 113165743A CN 201980081520 A CN201980081520 A CN 201980081520A CN 113165743 A CN113165743 A CN 113165743A
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- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
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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
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/293—Foldable or collapsible rotors or rotor supports
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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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 present invention relates to an unmanned aerial vehicle having a rotary-type folding wing, and more particularly, to an unmanned aerial vehicle having a rotary-type folding wing, which can fold wings of an unmanned aerial vehicle (unmanned aerial vehicle) in a folding manner through a simple operation of rotating a handle, simplifies setup and preparation work when using the unmanned aerial vehicle, and thus can reduce a volume while greatly shortening unnecessary time consumed, thereby facilitating carrying and keeping.
Description
Technical Field
The present invention relates to a drone with a rotary-type folding wing, and more particularly, to a drone with a rotary-type folding wing, which can fold wings of a drone (unmanned aerial vehicle) in a folding manner through a simple operation of rotating a handle, simplify setup and preparation work when using the drone, and thus can reduce a volume while greatly reducing unnecessary consumption time, thus being easy to carry and keep.
Background
In recent years, various ultra-light unmanned aerial vehicles have been developed for military use, research use, and other various purposes.
Various kinds of such ultra-light unmanned aerial vehicles have been developed according to the use and are being widely used, but in recent years, products having a hovering function floating on the spot without moving have been developed and widely used as shown in a plurality of prior documents such as patent laid-open No. 10-0812756.
However, as described above, the structure and operation of the aircraft having the hovering function are very complicated, which is not only expensive but also has a problem in that maintenance is difficult.
Therefore, a new method is required to solve these problems.
On the other hand, since currently marketed drones are inconvenient to carry and keep, various manners of drones are being designed to improve these problems.
For example, korean patent laid-open No. 10-1866191 (grant 2018.06.04) "portable foldable drone" discloses a technology of using a link structure of an umbrella and a ball detent so that all propellers can be folded or unfolded at one time, making it easy to carry the drone.
However, since the above-mentioned prior art is a way in which the propeller enters between the link members and is folded in a folded state, an operation of simultaneously folding the plurality of arm guides and the connecting member is very difficult in a state of accurately matching the folding sensitivity of the plurality of propellers, and there is a problem in that the propeller is damaged if the operation is not proper.
Disclosure of Invention
Technical problem to be solved
The present invention has been made to solve the above problems, and an object of the present invention is to provide a drone having a rotary folding wing, which is capable of easily folding a rotary wing of a drone about a rotary shaft so as to be portable, and reducing a partial volume of the drone, thereby easily moving and keeping the drone while securing flight safety.
In addition, another object of the present invention is to provide a drone with a rotary-type folding wing, which is very simple for the preliminary preparation work of flight preparation of the drone, so that the conventional preparation time, which is unnecessarily consumed, can be greatly shortened.
(II) technical scheme
In order to achieve the above object, a drone with a rotary-type folding wing according to the present invention is characterized in that it comprises: a main body part having a predetermined internal space in which a battery and a control device can be installed; a guide support body integrally coupled to an upper end of the main body and having a vertically penetrating screw hole formed at a center thereof; a rotating shaft extending up and down and formed with a screw thread of a predetermined length along an outer circumferential edge so as to penetrate up and down through the inside of the main body part and the guide support body and be screw-coupled and rotatable with at least one of the main body part and the guide support body; an upper cover provided at an upper end of the rotating shaft and axially supported when the rotating shaft rotates; a plurality of ribs, one end parts of which in the length direction are respectively hinged with the upper cover and radially extend for a preset length; a plurality of support ribs each having a lengthwise one-side distal end portion hinge-connected to the guide support and a lengthwise other-side distal end portion hinge-connected to one end portion of the wing rib so as to be folded together with the plurality of wing ribs in parallel with the rotation shaft when descending along with the rotation of the rotation shaft and so as to be folded such that the plurality of wing ribs are radially spread centering on the rotation shaft when ascending; and a plurality of rotary wings provided at a lengthwise end portion of each of the wing ribs to generate a flight thrust.
In addition, the unmanned aerial vehicle with the rotary type folding wing according to the present invention is characterized in that the rotary shaft is composed of a plurality of parts which are assemblably divided by a predetermined length, respectively.
In addition, the drone with a rotary-type folding wing according to the present invention is characterized by further comprising: and a rotation key coupled to a lower end portion of the rotation shaft in a length direction thereof.
(III) advantageous effects
With the above-described structure, the unmanned aerial vehicle having the rotary-type folding wing according to the present invention can easily fold the wing of the unmanned aerial vehicle (unmanned aerial vehicle) in a folding manner through a simple rotating operation of the rotating shaft lever, thus simplifying setup and preparation work when using the unmanned aerial vehicle, reducing the volume while greatly shortening unnecessary consumption time, and thus having advantages of easy carrying and keeping.
In addition, according to the unmanned aerial vehicle with the rotary-type folding wing of the present invention, not only can an unnecessary partial structure be separated during flight to ensure safety of flight, but also a rotary key capable of facilitating manual operation of a rotary shaft can be integrally built in the unmanned aerial vehicle to facilitate folding operation of the rotary wing generating flight propulsion, thereby having an advantage of being very convenient in use.
Drawings
Fig. 1 is a side sectional view illustrating a drone with a rotary-type folding wing according to one embodiment of the present invention.
Fig. 2 is a side sectional view illustrating a folding structure of the drone with the folding wing of the rotary type according to one embodiment of the present invention.
Fig. 3 is a sectional view showing a coupling structure of a rotating shaft of the drone with the rotating-type folding wing according to one embodiment of the present invention.
Fig. 4 is a use state diagram showing a use example of a partial structure of the drone with the rotary-type folding wing according to one embodiment of the present invention.
Description of the reference numerals
1: the unmanned aerial vehicle 10: main body part
20: guide supports 30a, 30 b: rotating shaft lever
31: threaded portion 32: position limiter
33: the cover 34: inner accommodation hole
34 a: first internal thread portion 34 b: second internal screw thread part
40: the upper cover 50: multiple ribs
60: the plurality of support ribs 70: multiple rotary wings
80: the rotation key 81: a first external thread part
82: second external thread portion 83: handle (CN)
Detailed Description
Hereinafter, a drone (hereinafter, referred to as "drone") having a rotary-type folding wing according to the present invention will be described in more detail with reference to embodiments shown in the accompanying drawings.
Fig. 1 is a perspective view showing a drone with a rotary-type folding wing according to one embodiment of the present invention, fig. 2 is a sectional view showing a structure of the drone with the rotary-type folding wing according to one embodiment of the present invention, fig. 3 is a sectional view showing a coupling structure of a rotating shaft of the drone with the rotary-type folding wing according to one embodiment of the present invention, and fig. 4 is a use state view showing a use example of a partial structure of the drone with the rotary-type folding wing according to one embodiment of the present invention.
Referring to the drawings, a drone 1 with a rotary-type folding wing according to one embodiment of the present invention includes a main body 10, a guide support 20, a rotation shaft 30, an upper cover 40, a plurality of ribs 50, a plurality of support ribs 60, and a plurality of rotation wings 70.
The main body part 10 is a structure forming a main body of the unmanned aerial vehicle of the present invention, and in one embodiment of the present invention, the main body part 10 forms an integral weight center in a circular structure, and a lower surface thereof may be formed in the shape of a flat surface, so that the unmanned aerial vehicle in flight can stably land on the ground.
In addition, the main body 10 is provided with a predetermined internal space therein, and a battery, a control device (not shown), and the like for power supply, flight control, and the like may be built in the internal space.
The guide support 20 is configured to function as a rotation guide of the rotation shaft 30, which will be described later, and a screw hole 21 is formed at the center of the guide support 20 to penetrate up and down so that the rotation shaft 30 is coupled to a screw shaft.
In addition, such a guide support 20 may be provided at an upper end of the main body 10, and in one embodiment of the present invention, the guide support 20 may be configured to be integrally coupled to the upper end of the main body 10.
The rotating shaft 30 is configured to function as a threaded shaft of the guide support 20, extends up and down by a predetermined length, forms a threaded portion 31 of a predetermined length along an outer peripheral edge, penetrates up and down through the inside of the main body 10 and the guide support 20, is screw-coupled, and is rotatable about the guide support 20.
At this time, in one embodiment of the present invention, the threaded part 31 of the rotating shaft 30 may be screw-coupled with at least one of the main body part 10 and the guide support 20. That is, a screw hole may be formed in the center of at least one of the main body 10 and the guide support 20.
Therefore, referring to fig. 1 and 2, in one embodiment of the present invention, in a state where the main body 10 and the guide support 20 are stationary, when the rotation shaft 30 is rotationally operated, the main body 10 and the guide support 20 may move up and down in a rotation direction of the rotation shaft 30.
The upper cover 40 is configured such that a length-direction uppermost end portion of the rotation shaft 30 is axially supported when the rotation shaft 30 is rotated from the main body 10 and the guide support 20.
Accordingly, the upper cover 40 is formed at the bottom thereof with a shaft hole 41 having a predetermined depth to be axially coupled to the upper end of the rotating shaft 30, and is formed along the outer circumference with a rim 42 for coupling the plurality of ribs 50, which will be described later.
The plurality of ribs 50 are foldable structures so that the plurality of rotation wings 70, which will be described later, can be folded and unfolded close to or away from the rotation shaft 30.
The plurality of ribs 50 may be formed to have the same shape as a rod extending a predetermined length, and the plurality of ribs 50 may be formed of a light and strong material to be able to sufficiently bear the weight of the plurality of rotary wings 70. For example, it may be formed of titanium, aluminum, or an alloy thereof.
On the other hand, since the longitudinal one-side end portions of the plurality of ribs 50 are hinged along the edge portion 42 of the upper cover 40, that is, the outer peripheral edge of the upper cover 40, the plurality of ribs 50 can be spread out in a state of being radially disposed around the upper cover 40.
The plurality of support ribs 60 and the plurality of ribs 50 are hinge-connected to each other such that the plurality of ribs 50 are radially expanded centering on the rotation shaft 30, and the plurality of support ribs 60 are folded according to the rotation of the rotation shaft 30 to be folded in parallel with the rotation shaft 30.
Therefore, the plurality of support ribs 60 are provided in a number corresponding to the plurality of ribs 50, and each has a lengthwise one-side distal end portion hinge-connected along the outer circumferential edge of the guide support 20 and a lengthwise other-side distal end portion hinge-connected to one end portion of the plurality of ribs 50.
Accordingly, the plurality of support ribs 60 will be folded together with the plurality of ribs 50 in a direction parallel to the rotation shaft 30 as the rotation shaft 30 rotates.
That is, when the rotation shaft 30 is rotated in one direction to lower the guide support 20, the plurality of ribs 50 are lowered together with the guide support 20 and folded in parallel with the rotation shaft 30, and at this time, the plurality of ribs 50 hinge-connected to the other end portion are folded together.
When the rotation shaft 30 is rotated in the opposite direction to raise the guide support 20, the other end portions of the support ribs 60 hingedly coupled to the guide support 20 are spread in the radial direction of the rotation shaft 30, and at this time, the wing ribs 50 hingedly coupled to the other end portions of the support ribs 60 are spread in the radial direction around the rotation shaft 30 together with the support ribs 60.
On the other hand, the rotation shaft 30 is provided with a stopper 32 to prevent the plurality of ribs 50 and the plurality of support ribs 60 from being further folded when being folded to a predetermined position by the guide support 20. Therefore, the stopper 32 is formed to have a step along the outer circumference at a predetermined height of the lower rotating shaft 30b to be described later on the lower end portion side of the rotating shaft 30.
The plurality of rotary wings 70 are a structure for generating a flight thrust of the unmanned aerial vehicle 1 of the present invention, and are provided at the longitudinal end portions of the respective ribs 50.
The plurality of rotary wings 70 are formed at equal intervals in the radial direction around the rotary shaft 30, and in this case, the unmanned aerial vehicle 1 of the present invention may determine the number of the plurality of rotary wings 70 according to the number of propellers of a multi-rotor type such as a quad-rotor type, a hexa-rotor type, and an octa-rotor type. That is, the number of the plurality of ribs 50, the plurality of support ribs 60, and the plurality of rotary wings 70 of the present invention may be determined according to the multi-rotor structure.
On the other hand, such a plurality of rotary wings 70 are preferably disposed such that the plurality of ribs 50 are kept horizontal in a state of being fully deployed in preparation for the flight of the drone 1 of the present invention, at which time the plurality of rotary wings 70 require power for driving motors, and the power connection as described above may be achieved by batteries built in the main body portion 10 and power connection lines 100 electrically connected to the plurality of rotary wings 70, respectively.
Accordingly, in one embodiment of the present invention, such a power connection line 100 is connected in a length direction along the inner hollow of the plurality of ribs 50 so as to extend in a length direction of the rotation shaft 30 and is connected to the inside of the main body 10 or is connected to the inside of the main body 10 in an externally exposed state to prevent interference with the folded structure of the plurality of ribs 50.
In addition, although not shown in the drawings, the unmanned aerial vehicle 1 of the present invention may further include a control receiving section, a communication section, and the like for controlling the flight of the unmanned aerial vehicle, and such a structure is an essential structure for the flight of the unmanned aerial vehicle, and thus a detailed description of a structure generally used for the flight operation of the unmanned aerial vehicle will be omitted. In addition, as described above, such a general structure may be arranged and designed to be built in a predetermined internal space provided in the main body portion 10 to form an appropriate center of gravity.
On the other hand, the rotating shaft 30 of the drone 1 according to one embodiment of the invention may be composed of a plurality of parts that are assemblably divided by predetermined lengths, respectively.
Referring to fig. 3, the rotating shaft 30 is composed of a plurality of rotating shafts 30a, 30b detachably divided in a length direction, and they may be screw-coupled to each other. In preparation for the flight of the unmanned aerial vehicle 1 of the present invention, when the main body 10 is raised to a predetermined height along the rotating shaft 30 to fully deploy the plurality of ribs 50, the unmanned aerial vehicle 1 may be flown in a state where the lower rotating shaft 30b extending downward of the main body 10 is separated.
That is, the unmanned aerial vehicle 1 according to the present invention may remove a portion of the rotating shaft 30 unnecessarily extending downward during flight to improve flight safety, and may prevent the rotating shaft 30 from contacting the ground during landing, and may stably land the main body 10 having a flat bottom surface on the ground.
On the other hand, as described above, in the case where the lower rotating shaft 30b is separated, a cap 33 may be coupled to the separated screw part of the lower rotating shaft 30 b.
In addition, the drone 1 according to one embodiment of the invention is characterized in that it further comprises a rotation key 80 incorporated at the lower end of the length direction of the rotation shaft 30.
The rotation key 80 is configured to function as a simple handle to facilitate a user's operation of rotating the rotation shaft 30.
That is, when the user deploys the plurality of ribs 50 in preparation for flight, the total weight of the plurality of rotary wings 70 makes it not easy to grasp the cylindrical rotary shaft 30 for rotation, and thus in one embodiment of the present invention, the rotary key 80, which functions as a tool like a portable rotary handle, is configured to be detachably built into the drone 1.
Therefore, the rotation key 80 may be built into the body part 10 or the rotation shaft 30, and the rotation key 80 may be provided in a receiving space within a predetermined space designated as a receiving type, but in one embodiment of the present invention, the rotation key 80 may be integrally coupled to a lower end portion of the rotation shaft 30.
For example, the rotary key 80 may be built into the inner receiving hole 34 extending from the lowermost end of the rotary shaft 30 to a predetermined depth in the longitudinal direction.
The inner receiving hole 34 is formed with a narrow space in the depth direction, a wide space is formed at the opening portion of the bottom, a first female screw portion 33a is formed at the wide space, and the rotary shaft 30 is provided with a second female screw portion 33b that is formed to open laterally from the outside of the portion where the inner receiving hole 34 is provided.
In this case, the rotation key 80 may be formed in a rod shape corresponding to the length of the inner receiving hole 34, and when such a rotation key 80 is inserted into the inner receiving hole 34, a first male screw portion 81 is formed along the outer peripheral edge of the portion located in the wide space, and a second male screw portion 82 is formed along the outer peripheral edge of the distal end portion in the longitudinal direction.
Therefore, when the rotary key 80 is rotated in a state where the front end portion is pushed into the inner receiving hole 34 in advance, the first male screw portion 81 of the rotary key 80 is screwed into the first female screw portion 34a of the rotary shaft 30 and is inserted into the inner receiving hole 34 in the wide space.
At this time, the rear end of the rotation key 80 may form a ring-shaped handle 83, and the handle 83 is configured to be easily grasped when the rotation key 80 is removed from the inner receiving hole 34.
The rotary key 80 may be assembled around the lower end of the rotary shaft 30 in a direction crossing the rotary shaft 30 in a state of being removed from the inner receiving hole 33.
That is, the rotary key 80 may be screw-coupled to the second female screw part 32b of the rotary shaft 30, and thus the second female screw part 32b is formed to have an inner diameter corresponding to and screw-coupled to the second male screw part 82 formed at the front end of the rotary key 80, so that the rotary key 80 may be screw-fastened in a direction crossing the rotary shaft 30 and detachably assembled.
Therefore, when the rotation key 80 is taken out from the lower end of the rotation shaft 30 and connected to the rotation shaft 30 according to the user's demand, the rotation key 80 may be used as a handle for adjusting the rotation, and may be replaced into the inner receiving hole 34 after the use is finished, so as to be integrated with the rotation shaft 30, thereby allowing convenient carrying.
With the above configuration, in the unmanned aerial vehicle 1 of the present invention, the plurality of rotary wings 70 disposed on the outermost side with respect to the rotary shaft 30 as the center can be folded close to the rotary shaft 30, so that the unmanned aerial vehicle is not only convenient to carry and store, but also the operation of unfolding the plurality of rotary wings 70 from the folded state in order to use the unmanned aerial vehicle 1 of the present invention can be very easily performed by the rotation adjustment operation of the rotary shaft 30, and since the rotary key 80 can be integrally carried and built in the unmanned aerial vehicle, when the rotary shaft 30 is manually rotated, an effect very convenient in use is produced.
The drone with a rotating type folding wing, described in the foregoing and shown in the accompanying drawings, is only one embodiment for implementing the present invention and should not be construed as limiting the technical idea of the present invention. The scope of the present invention is defined only by the contents described in the claims, and modifications and variations of the embodiments without departing from the gist of the present invention will be apparent to those skilled in the art and are intended to fall within the scope of the present invention.
Industrial applicability
The unmanned aerial vehicle having the rotary-type folding wing of the present invention having the above-described structure is an industrially very useful invention that can easily fold the wing of the unmanned aerial vehicle (unmanned aerial vehicle) in a folding manner through a simple rotating operation of the rotating shaft lever, thus simplifying setup and preparation work when using the unmanned aerial vehicle, reducing the volume while greatly reducing the time unnecessarily consumed, and facilitating carrying and keeping.
Claims (3)
1. An unmanned aerial vehicle with rotary-type folding wing, characterized in that includes:
a main body portion having a predetermined internal space in which a battery and a control device are provided;
a guide support body integrally coupled to an upper end of the main body and having a vertically penetrating screw hole formed at a center thereof;
a rotating shaft extending up and down and formed with a screw thread of a predetermined length along an outer circumferential edge so as to penetrate up and down through the inside of the main body part and the guide support body and be screw-coupled and rotatable with at least one of the main body part and the guide support body;
an upper cover provided at an upper end of the rotating shaft and axially supported when the rotating shaft rotates;
a plurality of ribs, one end parts of which in the length direction are respectively hinged with the upper cover and radially extend for a preset length;
a plurality of support ribs each having a lengthwise one-side distal end portion hinge-connected to the guide support and a lengthwise other-side distal end portion hinge-connected to one end portion of the wing rib so as to be folded together with the plurality of wing ribs in parallel with the rotation shaft when descending along with the rotation of the rotation shaft and so as to be folded such that the plurality of wing ribs are radially spread centering on the rotation shaft when ascending; and
and a plurality of rotary wings provided at a lengthwise end portion of each of the wing ribs to generate a flight thrust.
2. Unmanned aerial vehicle with rotary-type folding wings of claim 1,
the rotating shaft is composed of a plurality of parts which are assemblably divided by predetermined lengths, respectively.
3. Unmanned aerial vehicle with rotating type folding wings according to claim 1 or 2, further comprising:
and a rotation key coupled to a lower end portion of the rotation shaft in a length direction thereof.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR10-2018-0158893 | 2018-12-11 | ||
| KR1020180158893A KR102186048B1 (en) | 2018-12-11 | 2018-12-11 | Drones with rotating folding wings |
| PCT/KR2019/015218 WO2020122433A1 (en) | 2018-12-11 | 2019-11-11 | Drone provided with foldable rotary wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113165743A true CN113165743A (en) | 2021-07-23 |
Family
ID=71075653
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201980081520.0A Pending CN113165743A (en) | 2018-12-11 | 2019-11-11 | Unmanned aerial vehicle with rotary-type folding wing |
Country Status (3)
| Country | Link |
|---|---|
| KR (1) | KR102186048B1 (en) |
| CN (1) | CN113165743A (en) |
| WO (1) | WO2020122433A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911355B (en) * | 2021-07-10 | 2023-06-09 | 山东交通学院 | Portable unmanned aerial vehicle and application method thereof |
| CN113415410A (en) * | 2021-07-31 | 2021-09-21 | 重庆交通大学 | Foldable unmanned aerial vehicle wing assembly |
| CN113859516B (en) * | 2021-10-22 | 2022-11-04 | 哈尔滨工业大学 | Deformation wing parallel guide rail distributed type driving telescopic mechanism |
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- 2018-12-11 KR KR1020180158893A patent/KR102186048B1/en active IP Right Grant
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- 2019-11-11 CN CN201980081520.0A patent/CN113165743A/en active Pending
- 2019-11-11 WO PCT/KR2019/015218 patent/WO2020122433A1/en active Application Filing
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| US20170158320A1 (en) * | 2015-09-20 | 2017-06-08 | Daniel Bosch | Unmanned aerial system |
| KR20170111589A (en) * | 2016-03-29 | 2017-10-12 | 성균관대학교산학협력단 | Transformable drone |
| US20170283035A1 (en) * | 2016-04-05 | 2017-10-05 | Lanping JI | Foldable wing and rotocraft and glider using the same |
| CN206327559U (en) * | 2016-12-13 | 2017-07-14 | 西安昂翼机器人科技有限公司 | A kind of foldable cantilever rotor and its aircraft using the cantilever rotor |
| CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
| CN208021708U (en) * | 2018-03-23 | 2018-10-30 | 张梦杰 | One kind can auto-folder unmanned plane horn |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20200071306A (en) | 2020-06-19 |
| KR102186048B1 (en) | 2020-12-03 |
| WO2020122433A1 (en) | 2020-06-18 |
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