CN112224396A - Six-rotor unmanned aerial vehicle with double-layer staggered arms and capable of being folded transversely - Google Patents
Six-rotor unmanned aerial vehicle with double-layer staggered arms and capable of being folded transversely Download PDFInfo
- Publication number
- CN112224396A CN112224396A CN202011123113.2A CN202011123113A CN112224396A CN 112224396 A CN112224396 A CN 112224396A CN 202011123113 A CN202011123113 A CN 202011123113A CN 112224396 A CN112224396 A CN 112224396A
- Authority
- CN
- China
- Prior art keywords
- horn
- unmanned aerial
- aerial vehicle
- arm
- arms
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
- B64C1/061—Frames
-
- 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
- B64C1/061—Frames
- B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
-
- 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- 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
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Agricultural Machines (AREA)
Abstract
The invention provides a six-rotor unmanned aerial vehicle with arms arranged in a double-layer staggered manner and capable of being folded transversely, which can greatly reduce the volume and weight of the folded six-rotor unmanned aerial vehicle and improve the portability of the six-rotor unmanned aerial vehicle. This six rotor unmanned aerial vehicle includes: the wing comprises a main frame and six wing arms uniformly distributed at intervals along the circumferential direction of the main frame; the six wing arms are divided into an upper layer and a lower layer along the axial direction of the main frame, and the three wing arms positioned on the upper layer and the three wing arms positioned on the lower layer are distributed in a staggered manner; this unmanned aerial vehicle's horn adopts the mode of folding in the plane, and the collapsible long arm of every horn can set for the angle around its butt joint end horizontal rotation with the short armed under the effect of horn folding joint, realizes the folding of horn, when being in fold condition, is in the three horn on the same floor and transversely rotates in its self place horizontal plane and fold into the triangle form, reduces space size area occupied from this under unmanned aerial vehicle packing and the transportation condition.
Description
Technical Field
The invention relates to an unmanned aerial vehicle, in particular to a six-rotor unmanned aerial vehicle with double-layer staggered arms and a transversely foldable arm, and belongs to the technical field of unmanned aerial vehicles.
Background
The folding rotorcraft is a type with a foldable structure for the horn, and aims to reduce the occupied space, facilitate transportation and storage and improve the maneuverability of the folding rotorcraft in use. The six-rotor unmanned aerial vehicle is a common type in practical use, the horn of the six-rotor unmanned aerial vehicle is in a coplanar arrangement mode, a feasible folding mode is upward or downward vertical folding, the outline of the folded six-rotor unmanned aerial vehicle is a regular hexagon cylinder, and the storage and transportation appearance of the six-rotor unmanned aerial vehicle can be regarded as a cylinder with the bottom surface being a regular hexagon circumcircle. In practical use, particularly in special application scenes such as disaster prevention and relief, military affairs, police affairs and the like, the flying and folded external dimensions of the model are expected to be reduced to the greater extent, and the portability of the model is expected to be improved.
Disclosure of Invention
In view of this, the invention provides a six-rotor unmanned aerial vehicle with arms arranged in a double-layer staggered manner and capable of being folded transversely, which can greatly reduce the volume and weight of the folded six-rotor unmanned aerial vehicle and improve the portability of the six-rotor unmanned aerial vehicle.
The double-deck staggered arrangement of horn, six rotor unmanned aerial vehicle that can transversely fold include: the robot comprises a main frame and six arms which are uniformly distributed at intervals along the circumferential direction of the main frame; the six machine arms are divided into an upper layer and a lower layer along the axial direction of the main machine frame, and the three machine arms positioned on the upper layer and the three machine arms positioned on the lower layer are arranged in a staggered manner;
the horn includes: the foldable long arm, the machine arm folding joint and the short arm; one end of the short arm is fixedly connected to the host frame, and the other end of the short arm is connected with one end of the foldable long arm through the arm folding joint; the propeller blades are arranged at the other end of the foldable long arm, and a motor for driving the propeller blades to rotate is arranged on the machine arm;
the foldable long arm can horizontally rotate around the butt joint end of the folding joint of the horn and the short arm, so that the three horns on the same layer transversely rotate in the horizontal plane where the three horns are located to be folded into a triangle.
In a preferred embodiment of the present invention, among the six propeller blades, three propeller blades located at an upper stage are directed upward, and three propeller blades located at a lower stage are directed downward.
In a preferred embodiment of the present invention, when the arm is in the extended state, the propeller blade located at the upper stage and the propeller blade located at the lower stage adjacent thereto have an overlapping portion.
As a preferred aspect of the present invention, the arm folding joint includes: the shaft joint and the locking buckle; one end of the shaft joint is fixedly connected with the foldable long arm, and the other end of the shaft joint is butted with the short arm; one side of two opposite sides of the butt joint end of the shaft joint and the short arm is connected with the short arm through a pin shaft, and the other side of the two opposite sides is connected with the short arm through a locking buckle; when the locking buckle is in a loose state, the shaft joint can rotate around the pin shaft.
In a preferred form of the invention, the main frame is mounted on and secured to the landing gear.
As a preferred mode of the present invention, the host frame has a regular hexagonal frame structure.
As a preferred aspect of the present invention, the host framework includes: six large side plates, six small side plates, a fixing plate and a main supporting beam; the connection relationship is as follows:
the six large side plates surround a regular hexagon frame structure, and two adjacent large side plates are connected through a small side plate; the two fixing plates are respectively arranged at the upper end and the lower end of the regular hexagonal frame, and the two main supporting beams are fixedly arranged at the bottom of the lower fixing plate; the machine arm is connected to the small side plate.
Has the advantages that:
(1) the six-rotor unmanned aerial vehicle adopting the structure greatly reduces the volume and the weight of the folded six-rotor unmanned aerial vehicle, improves the portability, and is particularly suitable for special application scenes with stronger maneuverability, such as disaster prevention and relief, military affairs, police affairs and the like.
(2) Because the upper and lower layering setting of adoption for this unmanned aerial vehicle is whole on two adjacent horn be located upper strata and lower floor respectively, and two adjacent horn during operation from this can overlap by the blade under the condition that does not influence efficiency, thereby can shorten the horn, further reduced the radial dimension under the unmanned aerial vehicle operating condition.
(3) Due to staggering, the machine arm can be transversely folded, and the longitudinal overall dimension of the unmanned aerial vehicle in a storage and transportation state is greatly reduced by more than 40 percent due to the shortening of the machine arm.
(4) Compare in six rotor unmanned aerial vehicle of tradition, owing to shortening of horn, reduced complete machine weight.
Drawings
Fig. 1-2 are schematic structural views of the main body of the unmanned aerial vehicle of the invention after deployment;
fig. 3-4 are schematic structural views of the folded main body of the unmanned aerial vehicle of the invention;
fig. 5 is a perspective view of the entire unmanned aerial vehicle of the present invention.
Fig. 6 is a schematic structural diagram of the host framework in embodiment 2.
Wherein: 1-motor, 2-propeller blade, 3-horn folding joint, 301-locking buckle, 302-shaft joint, 4-main frame, 401-big side plate, 402-small side plate, 403-main supporting beam, 404-connecting piece, 405-fixing plate, 5-foldable long arm, 6-short arm, 7-radial outline of whole machine when unfolded, 8-propeller blade outline, 9-radial outline of whole machine after folded, 10-longitudinal outline of main machine after folded, 11-longitudinal outline of main machine after unmanned plane folded, 12-undercarriage.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
Example 1:
the embodiment provides a but arm double-deck staggered arrangement, horizontal folding six rotor unmanned aerial vehicle, adopts layering, staggered arrangement to arrange, can reduce volume and weight after six rotor unmanned aerial vehicle are folding by a wide margin, improves its portability.
This six rotor unmanned aerial vehicle global design thinking do: divide into two-layer about six horn, three horn of every layer is along the outer circumference even interval distribution of unmanned aerial vehicle host computer frame 4, and six whole also along the outer circumference even interval distribution of host computer frame 4 of horn on upper and lower layer, and every layer of three horn is 120 degrees along unmanned aerial vehicle host computer outer fringe from this, and the adjacent horn of upper and lower layer is 60 staggered arrangement.
As shown in fig. 1-2, the six-rotor drone includes: the device comprises a main frame 4 and six arms uniformly distributed at intervals along the circumferential direction of the main frame 4; the six arms are divided into an upper layer and a lower layer along the axial direction of the main frame 4 (so that the six foldable propeller blades 2 are not completely positioned on the same plane), and the three arms of each layer are arranged at intervals of 120 degrees; and the three machine arms on the upper layer and the three machine arms on the lower layer are uniformly distributed at intervals, so that two adjacent machine arms are respectively positioned on the upper layer and the lower layer on the whole, and the interval between the two adjacent machine arms is 60 degrees.
Six horn lengths equal, connect a propeller blade 2 on every horn, the horn is collapsible, includes: a foldable long arm 5, a horn folding joint 3 and a short arm 6; one end of the short arm 6 is fixedly arranged on the host frame 4, the other end of the short arm is connected with one end of the foldable long arm 5 through the horn folding joint 3, and the foldable long arm 5 is folded in a plane through the horn folding joint 3; the propeller blades 2 are arranged at the other end of the foldable long arm 5; the motor 1 is fixed on the foldable long arm 5 through a motor base, and the power output end of the motor 1 is connected with the propeller blades 2 and used for driving the propeller blades 2 to rotate. When the size structure of the machine arm is designed, the lengths of the foldable long arm 5 and the foldable short arm 6 are determined according to the compact principle that the three machine arms on the same layer are just compatible after being folded.
Among the six propeller blades 2 of the unmanned aerial vehicle, three propeller blades 2 connected with the three arms positioned on the upper layer face upwards, and three propeller blades 2 connected with the three arms positioned on the lower layer face downwards; the six propeller blades 2 adopt three upward and three downward mounting structure forms, so that the larger load can be borne on the premise that the center of gravity of the upper half part of the main frame 4 is positioned at the center of the machine body.
Compare six rotor unmanned aerial vehicle vertical folding's of tradition mode, this unmanned aerial vehicle's horn adopts in the plane folding mode, the collapsible long arm 5 of every horn can be around its butt joint end horizontal rotation settlement angle with short arm 6 under the effect of horn folding joint 3, realize the folding of horn, as shown in fig. 3, when being in fold condition, be in the three horn of same floor and transversely rotate in its self place horizontal plane and fold into the triangle form, reduce space size area occupied under unmanned aerial vehicle packing and transportation condition from this.
The specific comparative analysis is as follows:
the specific structural dimension of this unmanned aerial vehicle in this example is: the diameter a of the overall machine radial outline 7 is 1694mm when the overall machine radial outline is unfolded, the height b of the main machine body longitudinal outline 10 is 0.17a 288mm when the overall machine radial outline is unfolded (or folded), the diameter d of the overall machine radial outline 9 is 0.46a 779mm when the overall machine radial outline is folded, and the arm length c of the foldable long arm 5 is (a-d)/2 is 457 mm. In this example, two adjacent propeller blade contours 8 overlap 20mm in plan view when in operation (i.e., when deployed). Therefore, the occupied area of the unmanned aerial vehicle in the unfolding state is as follows: s ═ pi (a/2)2＝2.254×106mm2＝2.254m2。
As shown in fig. 4, the folded profile of the unmanned aerial vehicle is a cylinder with a bottom diameter and a height d and b, and the volume thereof is: v ═ pi (d/2)2×b＝1.372×108mm3＝0.1372m3。
Compare with the same kind of six rotor unmanned aerial vehicle of traditional vertical folding of specification:
(1) when two adjacent propeller blade contour lines of a traditional vertically-folded six-rotor unmanned aerial vehicle work, the two adjacent propeller blade contour lines cannot be overlapped, and the distance is also considered, if the safety distance is 10mm, the foldable long arm of the six-rotor unmanned aerial vehicle can be extended by 30mm, namely c '═ c +30 ═ 487mm, and when the six-rotor unmanned aerial vehicle is unfolded, the diameter a of the whole machine radial outline contour line 7 can be increased by 60mm, namely a' ═ 1694+60 ═ 1754mm
The floor area of the expanded state is S '═ pi (a'/2) 2 ═ 2.416 × 106 ═ 2.416m2The occupied area of the unmanned aerial vehicle is 1.072 times of that of the unmanned aerial vehicle in the unfolding state.
(2) Because six rotor unmanned aerial vehicle's of tradition horn is folding perpendicularly, the horn length c' after its folding back cylindrical profile highly be the extension, the bottom surface is the same with this embodiment, then folding back appearance profile volume is:
V’＝π(d/2)2×c’＝π(779/2)2×487＝2.321×108＝0.2321m3is 1.69 times of the volume of the folded profile of the unmanned aerial vehicle (or can be understood as adopting the scheme in the embodiment)The volume of the folded same-specification six-rotor unmanned aerial vehicle can be reduced by 41 percent.
(3) Because unmanned aerial vehicle needs extension horn in the present embodiment is compared to traditional six rotor unmanned aerial vehicle of folding perpendicularly, corresponding complete machine weight also increases to some extent.
The same kind of comparison unmanned aerial vehicle folding back main engine body longitudinal shape outline line 11 is shown in fig. 6.
By comparison, the six-rotor unmanned aerial vehicle with the arms arranged in a double-layer staggered manner and capable of being transversely folded can greatly reduce the appearance volume of the same type of foldable six-rotor unmanned aerial vehicle in the storage and transportation state; meanwhile, the weight of the whole machine and the occupied area after the unfolding are also reduced.
Fix this unmanned aerial vehicle host computer frame 4 installation on undercarriage 12, constitute that unmanned aerial vehicle is whole, the whole state of expanding of unmanned aerial vehicle is shown as figure 5.
Example 2:
on the basis of the above embodiment 1, a structural form of the horn folding joint 3 is given.
The foldable long arm 5 realizes the rotary folding in the plane through the arm folding joint 3; the arm folding joint 3 comprises a shaft joint 302 and a locking buckle 301; wherein one end of the shaft joint 302 is fixedly connected with the foldable long arm 5, and the other end is butted with the short arm 6; one side of two opposite sides of the butt joint end of the shaft joint 302 and the short arm 6 is connected with the short arm 6 through a pin shaft, and the other side of the two opposite sides is connected with the short arm 6 through a locking buckle 301; when the locking buckle 301 is in a released state, the shaft joint 302 can rotate around the pin shaft; therefore, when the locking buckle 301 locks the shaft joint 302 on the short arm 6, and the shaft joint 302 and the short arm 6 are in a butt-joint locking state, the machine arm is in an unfolding state as shown in fig. 2; when the locking buckle 301 is released, the shaft joint 302 can rotate around the pin shaft, and the three foldable long arms 5 in the same layer can horizontally rotate and fold into a triangular form, as shown in fig. 3.
Example 3:
on the basis of the above embodiment 1 or embodiment 2, a structural form of the host frame 4 is further given.
As shown in fig. 2, the host frame 4 is used for providing fixed mounting and mechanical connection for other parts of the unmanned aerial vehicle, and the host frame 4 is a hexagonal frame structure, including: six large side plates 401, six small side plates 402, six connecting pieces 404, a fixing plate 405 and a main supporting beam 403; the connection relationship is as follows: the six large side plates 401 are distributed in a hexagon shape, namely the six large side plates 401 surround a hexagonal frame structure, and two adjacent large side plates 401 are connected through a small side plate 402; each small side plate 402 is connected with a horn, the six horns are divided into an upper layer and a lower layer along the axial direction of the main frame 4, and the three horns on the upper layer and the three horns on the lower layer are uniformly distributed at intervals; the installation mode is as follows: the convex grooves on the side edges of the two large side plates 401 are respectively embedded into the grooves on the two opposite side edges of the machine arm and then are connected and fixed through screws and nuts; the small side plate 402 is fixedly connected with the horn through screws, and the connecting piece 404 simultaneously fixedly connects the two large side plates 401 and the horn positioned between the two large side plates 401 through screws, so that six groups of the large side plates are assembled and connected together to form a hexagonal frame after being fixed; then, two fixing plates 405 are respectively installed at the upper end and the lower end of the hexagonal frame, two main supporting beams 403 are respectively and fixedly installed at the bottoms of the lower fixing plates, and the two ends of the main supporting beams 403 are respectively and fixedly connected with the small side plates 402 at the corresponding sides through connecting pieces, thereby forming a six-rotor main frame 4 which provides fixed installation and mechanical connection for other parts.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. Double-deck staggered arrangement of horn, six rotor unmanned aerial vehicle that can transversely fold, its characterized in that: the method comprises the following steps: the device comprises a main frame (4) and six arms which are uniformly distributed at intervals along the circumferential direction of the main frame (4); the six machine arms are divided into an upper layer and a lower layer along the axial direction of the main machine frame (4), and the three machine arms positioned on the upper layer and the three machine arms positioned on the lower layer are arranged in a staggered manner;
the horn includes: a foldable long arm (5), a machine arm folding joint (3) and a short arm (6); one end of the short arm (6) is fixedly connected to the host frame (4), and the other end of the short arm is connected with one end of the foldable long arm (5) through the arm folding joint (3); the propeller blades (2) are arranged at the other end of the foldable long arm (5), and a motor (1) for driving the propeller blades (2) to rotate is arranged on the machine arm;
the foldable long arm (5) can horizontally rotate around the butt joint end of the folding joint (3) of the machine arm and the short arm (6), so that the three machine arms on the same layer transversely rotate in the horizontal plane where the three machine arms are located to be folded into a triangle.
2. The six-rotor unmanned aerial vehicle with double staggered horn arrangement and capable of being folded transversely of claim 1, wherein three propeller blades (2) on the upper tier face upward and three propeller blades (2) on the lower tier face downward in the six propeller blades (2).
3. The six-rotor drone with double staggered horn arrangement and lateral foldability according to claim 1, characterised in that the horn, in the unfolded state, has overlapping portions of the propeller blades (2) situated on the upper level and the propeller blades (2) situated adjacent to it and situated on the lower level.
4. The double-deck staggered, transversely foldable hexa-rotor drone of claim 1, 2 or 3, characterized in that said folding joints of arms (3) comprise: a shaft joint (302) and a locking buckle (301); one end of the shaft joint (302) is fixedly connected with the foldable long arm (5), and the other end of the shaft joint is butted with the short arm (6); one side of two opposite sides of the butt joint end of the shaft joint (302) and the short arm (6) is connected with the short arm (6) through a pin shaft, and the other side of the two opposite sides is connected with the short arm (6) through a locking buckle (301); when the locking buckle (301) is in a loose state, the shaft joint (302) can rotate around a pin shaft.
5. The double-deck staggered, transversely foldable hexarotor drone of claim 1, 2 or 3, characterized in that said main frame (4) is mounted fixed on the undercarriage (12).
6. The double-deck staggered horn, transversely foldable hexa-rotor drone of claim 1, 2 or 3, said main frame (4) being a regular hexagonal frame structure.
7. The six-rotor drone with double staggered horn arrangement and lateral foldability according to claim 6, characterized in that the main frame (4) comprises: six large side plates (401), six small side plates (402), a fixing plate (405) and a main supporting beam (403); the connection relationship is as follows:
the six large side plates (401) surround a regular hexagonal frame structure, and two adjacent large side plates (401) are connected through a small side plate (402); the two fixing plates (405) are respectively arranged at the upper end and the lower end of the regular hexagonal frame, and the two main supporting beams (403) are fixedly arranged at the bottom of the lower fixing plate; the horn is connected to the small side plate (402).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011123113.2A CN112224396A (en) | 2020-10-20 | 2020-10-20 | Six-rotor unmanned aerial vehicle with double-layer staggered arms and capable of being folded transversely |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011123113.2A CN112224396A (en) | 2020-10-20 | 2020-10-20 | Six-rotor unmanned aerial vehicle with double-layer staggered arms and capable of being folded transversely |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112224396A true CN112224396A (en) | 2021-01-15 |
Family
ID=74118949
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011123113.2A Pending CN112224396A (en) | 2020-10-20 | 2020-10-20 | Six-rotor unmanned aerial vehicle with double-layer staggered arms and capable of being folded transversely |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112224396A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113277064A (en) * | 2021-07-02 | 2021-08-20 | 宁波阿瑞斯自动化技术有限公司 | Many rotor unmanned aerial vehicle of emergency rescue |
| CN115834984A (en) * | 2022-11-21 | 2023-03-21 | 国网四川省电力公司达州供电公司 | Portable limited space patrol instrument |
| CN116812185A (en) * | 2023-07-04 | 2023-09-29 | 深圳技术大学 | Eight-axis unmanned aerial vehicle for camera monitoring |
| CN116812184A (en) * | 2023-07-04 | 2023-09-29 | 深圳技术大学 | Six-axis unmanned aerial vehicle for radar mapping |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107082113A (en) * | 2017-06-09 | 2017-08-22 | 四川雷神空天科技有限公司 | Foldable attachment means and the unmanned vehicle applied |
| CN206750132U (en) * | 2017-03-16 | 2017-12-15 | 南京辰茂新材料科技有限公司 | A kind of technical grade multiaxis unmanned aerial vehicle platform |
| CN206856986U (en) * | 2017-05-23 | 2018-01-09 | 河北智飞农业科技有限公司 | One kind can encircle folded form plant protection unmanned plane |
| NO20180080A1 (en) * | 2018-01-17 | 2019-07-18 | Griff Aviation As | An unmanned aerial vehicle having rotating wing lift generating means, advantageously a multicopter with a unitary main fuselage and foldable rotor arms. |
| CN209852579U (en) * | 2019-04-25 | 2019-12-27 | 曜宇航空（深圳）科技有限公司 | Multi-rotor aircraft |
| US20200172226A1 (en) * | 2017-08-04 | 2020-06-04 | Autel Robotics Co., Ltd. | Arm and unmanned aerial vehicle |
-
2020
- 2020-10-20 CN CN202011123113.2A patent/CN112224396A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206750132U (en) * | 2017-03-16 | 2017-12-15 | 南京辰茂新材料科技有限公司 | A kind of technical grade multiaxis unmanned aerial vehicle platform |
| CN206856986U (en) * | 2017-05-23 | 2018-01-09 | 河北智飞农业科技有限公司 | One kind can encircle folded form plant protection unmanned plane |
| CN107082113A (en) * | 2017-06-09 | 2017-08-22 | 四川雷神空天科技有限公司 | Foldable attachment means and the unmanned vehicle applied |
| US20200172226A1 (en) * | 2017-08-04 | 2020-06-04 | Autel Robotics Co., Ltd. | Arm and unmanned aerial vehicle |
| NO20180080A1 (en) * | 2018-01-17 | 2019-07-18 | Griff Aviation As | An unmanned aerial vehicle having rotating wing lift generating means, advantageously a multicopter with a unitary main fuselage and foldable rotor arms. |
| CN209852579U (en) * | 2019-04-25 | 2019-12-27 | 曜宇航空（深圳）科技有限公司 | Multi-rotor aircraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113277064A (en) * | 2021-07-02 | 2021-08-20 | 宁波阿瑞斯自动化技术有限公司 | Many rotor unmanned aerial vehicle of emergency rescue |
| CN115834984A (en) * | 2022-11-21 | 2023-03-21 | 国网四川省电力公司达州供电公司 | Portable limited space patrol instrument |
| CN115834984B (en) * | 2022-11-21 | 2024-01-30 | 国网四川省电力公司达州供电公司 | Portable limited space inspection instrument |
| CN116812185A (en) * | 2023-07-04 | 2023-09-29 | 深圳技术大学 | Eight-axis unmanned aerial vehicle for camera monitoring |
| CN116812184A (en) * | 2023-07-04 | 2023-09-29 | 深圳技术大学 | Six-axis unmanned aerial vehicle for radar mapping |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112224396A (en) | Six-rotor unmanned aerial vehicle with double-layer staggered arms and capable of being folded transversely | |
| CN100548804C (en) | The system of engine strut fixation to wing | |
| CN101481015A (en) | Small-sized foldable multi-wheel multi-column support type landing gear | |
| CN102493654B (en) | Engineering machine | |
| CN103552686B (en) | A kind of compound type duct aerial reconnaissance machine people | |
| CN105857601A (en) | Arm connecting device for unmanned aerial vehicle | |
| ES2759925T3 (en) | Fuselage-mounted landing gear | |
| CN205916328U (en) | Multi -rotor unmanned aerial vehicle | |
| CN105966602A (en) | Novel unmanned aerial vehicle | |
| CN107264771A (en) | Pressure bulkhead device | |
| EP3838750A1 (en) | Multi-rotor aircraft with multi-axis misalignment layout | |
| CN208360493U (en) | A kind of portable aerial survey quadrotor drone | |
| CN115535232B (en) | Flapping wing aircraft with foldable flapping wings | |
| CN103523209A (en) | Retractable main landing frame for small aircrafts | |
| CN210553993U (en) | Aircraft and air-ground amphibious vehicle | |
| CN219008166U (en) | Unmanned aerial vehicle wheeled undercarriage and unmanned aerial vehicle | |
| CN101879943B (en) | Small-size retractable multi-wheel and multi-support undercarriage | |
| CN110697020A (en) | Unmanned aerial vehicle lightweight folding frame | |
| CN211810219U (en) | Aircraft | |
| CN207157488U (en) | A kind of unmanned plane of scalable paddle arm and foot stool | |
| WO2017000528A1 (en) | Driving device assembly including multiple driving devices and application thereof | |
| CN206606348U (en) | A kind of multi-rotor unmanned aerial vehicle | |
| CN113184164A (en) | Folding wing type airplane | |
| CN210011875U (en) | Foldable six-shaft multi-rotor flight body | |
| CN114802733A (en) | Ducted fan and flying device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210115 |