CN107000834B - More rotor unmanned aircrafts - Google Patents
More rotor unmanned aircrafts Download PDFInfo
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- CN107000834B CN107000834B CN201680003994.XA CN201680003994A CN107000834B CN 107000834 B CN107000834 B CN 107000834B CN 201680003994 A CN201680003994 A CN 201680003994A CN 107000834 B CN107000834 B CN 107000834B
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- horn
- rotor unmanned
- unmanned aircrafts
- fuselage
- interconnecting piece
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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
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/50—Foldable or collapsible UAVs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
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- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
A kind of more rotor unmanned aircrafts, it include: fuselage (1), multiple horns (2) are collapsibly set on fuselage (1), when horn (2) is in extended state, horn (2) is extended around towards fuselage (1)；When horn (2) is in folded state, horn (2) is folded towards the two sides of fuselage (1).More rotor unmanned aircrafts provided by the invention, by being set to multiple horns (2) are folding on fuselage (1), when unmanned vehicle is in be used or uses, horn (2) can be in extended state, when needing to assemble unmanned vehicle and transported, folded state can be set by horn (2), so that unmanned vehicle is in long and narrow strip structure, so that the shape of unmanned vehicle is adapted with the shape of transport device, facilitate and folded unmanned vehicle is set in transport device, significantly reduce the transport difficulty to unmanned vehicle, improve the practicability of unmanned vehicle.
Description
Technical field
The present invention relates to vehicle technology field more particularly to a kind of more rotor unmanned aircrafts.
Background technique
With the rapid development of science and technology, unmanned air vehicle technique development is more and more mature, and the field of application is also increasingly wider
It is general, such as: the fields such as military affairs, scientific research, civilian specifically can be used for photographing, explore, communicate, prevent and reduce natural disasters, border patrol etc.
Deng.
Folded wing is mostly used for convenience of assembling and transporting for large-scale multi-rotor unmanned aerial vehicle, however, in the prior art,
The shape of folded wing is mostly irregular, and then improves the difficulty assembled and transported to multi-rotor unmanned aerial vehicle.
Summary of the invention
The present invention provides a kind of more rotor unmanned aircrafts, for it is existing in the prior art be not easy to more rotors without
People's aircraft transports, improves and assembles to multi-rotor unmanned aerial vehicle and the problem of transport difficulty.
The present invention is to provide for a kind of more rotor unmanned aircrafts, comprising:
Fuselage,
Multiple horns are collapsibly set on the fuselage；
When the horn is in extended state, the horn is extended around towards the fuselage；
When the horn is in folded state, the horn is folded towards the two sides of the fuselage.
More rotor unmanned aircrafts provided by the invention work as nothing by being set to multiple horns are folding on fuselage
When people's aircraft is in be used or use process, horn can be in extended state, when needing to unmanned vehicle
When being assembled and being transported, folded state can be set by horn, so that unmanned vehicle is in long and narrow strip structure, so that
The shape of unmanned vehicle is adapted with the shape of transport device, further facilitates folded unmanned vehicle being set to fortune
In defeated device, the transport difficulty to unmanned vehicle is significantly reduced, and improves the practicability of unmanned vehicle, favorably
In the popularization and application in market.
Detailed description of the invention
Fig. 1 is the three-dimensional knot that a kind of horn of more rotor unmanned aircrafts provided in an embodiment of the present invention is in extended state
Structure schematic diagram；
Fig. 2 is the main view that a kind of horn of more rotor unmanned aircrafts provided in an embodiment of the present invention is in extended state
Figure；
Fig. 3 is the side view that a kind of horn of more rotor unmanned aircrafts provided in an embodiment of the present invention is in extended state
Figure；
Fig. 4 is the vertical view that a kind of horn of more rotor unmanned aircrafts provided in an embodiment of the present invention is in folded state
Figure；
Fig. 5 is the main view that a kind of horn of more rotor unmanned aircrafts provided in an embodiment of the present invention is in folded state
Figure；
Fig. 6 is the side view that a kind of horn of more rotor unmanned aircrafts provided in an embodiment of the present invention is in folded state
Figure.
In figure:
1, fuselage；2, horn；
3, adjustment part；31, interconnecting piece；
311, fixed sub-portion；312, adjusting sub-section；
3121, raised；313, sub-portion is connected；
3131, axis；32, tight lock part.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art
Every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
In the present invention, the terms such as term " installation ", " connection ", " fixation " are broadly understood, for example, " connection " can be with
It is to be fixedly connected, may be a detachable connection, or is integrally connected.It for the ordinary skill in the art, can be with
The concrete meaning of above-mentioned term in the present invention is understood as the case may be.
It should be noted that in the description of the present invention, term " first ", " second ", which are only used for facilitating, describes different portions
Part is not understood to indicate or imply ordinal relation, relative importance or the number for implicitly indicating indicated technical characteristic
Amount." first " is defined as a result, the feature of " second " can explicitly or implicitly include at least one of the features.
Unless otherwise defined, all technical and scientific terms used herein and belong to technical field of the invention
The normally understood meaning of technical staff is identical.Term as used herein in the specification of the present invention is intended merely to description tool
The purpose of the embodiment of body, it is not intended that in the limitation present invention.
With reference to the accompanying drawing, it elaborates to some embodiments of the present invention.Do not conflict between each embodiment
In the case of, the feature in following embodiment and embodiment can be combined with each other.
Embodiment one
Fig. 1 is the solid that a kind of horn 2 of more rotor unmanned aircrafts provided in an embodiment of the present invention is in extended state
Structural schematic diagram；Fig. 2 is the master that a kind of horn 2 of more rotor unmanned aircrafts provided in an embodiment of the present invention is in extended state
View；Fig. 4 is the elevation view that a kind of horn 2 of more rotor unmanned aircrafts provided in an embodiment of the present invention is in folded state；
With reference to attached drawing 1-2,4 it is found that present embodiments providing a kind of more rotor unmanned aircrafts, comprising:
Fuselage 1,
Multiple horns 2, are collapsibly set on fuselage 1；
When horn 2 is in extended state, horn 2 is extended around towards fuselage 1；
When horn 2 is in folded state, horn 2 is folded towards the two sides of fuselage 1.
The present embodiment for fuselage 1 concrete shape structure without limitation, those skilled in the art can be according to specific
Design requirement is configured, such as: square structure, polygonized structure etc. can be set by fuselage 1, it more preferably, can
To set rectangular configuration for fuselage 1；In addition, for horn 2 number without limitation, those skilled in the art can be according to tool
The design requirement of body is configured, for example, can be set to 2,4,6 or 8 etc., more preferably, nobody is flown
It is set as including at least four horns 2 on row device.
When horn 2 is in extended state, horn 2 is extended around towards fuselage 1, at more rotor unmanned aircrafts at this time
In to be used or use process, at this point, since horn 2 is extended around towards fuselage 1, so that the lateral ruler of unmanned vehicle
Very little and longitudinal size is larger.
When horn 2 is in folded state, horn 2 is folded towards the two sides of fuselage 1, specifically, can be by the two of fuselage 1
Side be set as include: unmanned vehicle heading and the tail direction of unmanned vehicle；So that horn 2 is in rugosity
When state, the set multiple horns 2 being placed on fuselage 1 are respectively facing heading and tail direction carries out folding operation, at this time
During unmanned vehicle is in be assembled or to be transported.By the way that horn 2 is provided towards heading and tail direction
It is folded, efficiently reduces the longitudinal size of unmanned vehicle, so that unmanned vehicle is in long and narrow strip structure, bar shaped
Structure is relatively conventional structure, and the shape of the strip structure and the transport device for shipping unmanned vehicle is mutually fitted
Match, wherein transport device may include: strip knapsack, suitcase, square box etc., thus it is convenient to unmanned vehicle into
Luggage is matched and is transported, and transport and mobile difficulty to unmanned vehicle are significantly reduced.
More rotor unmanned aircrafts provided in this embodiment, by being set to multiple horns 2 are folding on fuselage 1,
When unmanned vehicle is in be used or use process, horn 2 can be in extended state, it is winged to nobody when needing
When row device is assembled and transported, folded state can be set by horn 2, so that unmanned vehicle is in long and narrow bar shaped knot
Structure further facilitates so that the shape of unmanned vehicle is adapted with the shape of transport device by folded unmanned vehicle
It is set in transport device, significantly reduces the transport difficulty to unmanned vehicle, and improve the reality of unmanned vehicle
With property, be conducive to the popularization and application in market.
Embodiment two
On the basis of the above embodiments, with continued reference to attached drawing 1-2,4 it is found that making to further increase unmanned vehicle
Reliability, the present embodiment by the length of the horn 2 folded towards heading be less than towards tail direction into
The length for the horn 2 that row folds.
The present embodiment for horn 2 specific length dimension without limitation, those skilled in the art can be according to specific
Design requirement is configured；It should be noted that when 2 length dimension of horn is arranged, it more preferably, will be towards heading
2 length of horn be set smaller than 2 length of horn towards tail direction, be achieved in the power point by unmanned vehicle
The heart is disposed proximate to tail direction, so that the power dot center moved back can balance the center of gravity of unmanned vehicle, has
Improve to effect the security and stability of unmanned vehicle operation.
Embodiment three
Fig. 3 is the side view that a kind of horn 2 of more rotor unmanned aircrafts provided in an embodiment of the present invention is in extended state
Figure；On the basis of the above embodiments, with continued reference to attached drawing 1-4 it is found that when each horn 2 is in extended state, each
The central axes of horn 2 are respectively formed an identical predetermined angle between a preset plane, wherein preset plane is flown by nobody
The plane that yaw axis and roll axis on row device are constituted.
Wherein, predetermined angle be it is pre-set, the present embodiment for predetermined angle specific angular range without limitation,
Those skilled in the art can be configured according to specific design requirement, for example, predetermined angle can be set to include
10 °, 30 °, 60 °, 100 °, 120 ° or 150 ° etc., more preferably, obtuse angle is set by predetermined angle.
It should be noted that the central axes of each horn 2 form a predetermined angle, and each machine with preset plane
The central axes of arm 2 are formed by predetermined angle with preset plane and are equal, so that the unmanned vehicle in extended state
It is convenient that the operating status of unmanned vehicle is adjusted and is controlled for symmetrical structure.
Example IV
Fig. 5 is the main view that a kind of horn 2 of more rotor unmanned aircrafts provided in an embodiment of the present invention is in folded state
Figure；Fig. 6 is the side view that a kind of horn 2 of more rotor unmanned aircrafts provided in an embodiment of the present invention is in folded state；?
On the basis of above-described embodiment, with continued reference to attached drawing 1-6 it is found that each horn 2 is surrounded a preset axis by the present embodiment
3131 are folded, and each axis 3131 is respectively formed an identical predetermined angle between a preset plane, wherein preset plane
It is by the yaw axis and the plane that is constituted of roll axis on unmanned vehicle.
Wherein, predetermined angle be it is pre-set, the present embodiment for predetermined angle specific angular range without limitation,
Those skilled in the art can be configured according to specific design requirement, for example, predetermined angle can be set to include
10 °, 30 °, 60 °, 100 °, 120 ° or 150 ° etc., more preferably, acute angle is set by predetermined angle；By by preset angle
Degree is set as acute angle, so as to the longitudinal size reduced between the horn 2 of folded state and fuselage 1, further reduces nothing
The occupied space of people's aircraft.
It should be noted that each axis 3131 forms a predetermined angle with preset plane, and each axis 3131 and pre-
If plane is formed by predetermined angle and is equal, so that the unmanned vehicle in extended state is symmetrical structure, convenient
Unmanned vehicle in folded state is assembled and transported.
Embodiment five
On the basis of the above embodiments, with continued reference to attached drawing 1-6 it is found that the present embodiment is foldable for multiple horns 2
Ground is set to the specific implementation on fuselage 1 without limitation, those skilled in the art can according to specific design requirement into
Row setting, more preferably, sets unmanned vehicle to further include: multiple adjustment parts 3, each adjustment part 3 are connected to fuselage 1
Between corresponding horn 2, when horn 2 is in extended state, the central axes of horn 2 and the central axes of adjustment part 3 overlap；
It is in a default angle between the central axes of horn 2 and the central axes of adjustment part 3 when horn 2 is in folded state.
Wherein, the number of adjustment part 3 is identical as the number of horn 2；I.e. each horn 2 by adjustment part 3 realize with
The foldable connection of fuselage 1；And the present embodiment for adjustment part 3 concrete shape structure without limitation, those skilled in the art
It can be configured according to specific design requirement, more preferably, set adjustment part 3 to include: interconnecting piece 31, with fuselage
1 is connected with horn 2, for realizing switching of the horn 2 between extended state and folded state.
In addition, the present embodiment for interconnecting piece 31 concrete shape structure without limitation, those skilled in the art can root
It is configured according to specific design requirement, more preferably, can set columnar structured for interconnecting piece 31, in this way by setting
The interconnecting piece 31 set has effectively achieved switching of the horn 2 between extended state and folded state, specifically, when in horn 2
When in extended state, the central axes of horn 2 and the central axes of adjustment part 3 overlap, the central axes of adjustment part 3 at this time and company
The central axes of socket part 31 overlap；When horn 2 is in folded state, between the central axes of horn 2 and the central axes of adjustment part 3
In a default angle；Wherein, it is to set in advance that default angle is formed by between the central axes of horn 2 and the central axes of adjustment part 3
It sets, those skilled in the art can be configured according to specific design requirement, more preferably, set default angle to
Acute angle.
The foldable connection that multiple horns 2 and fuselage 1 are had effectively achieved by multiple adjustment parts 3 of setting, passes through tune
One integral piece 3, which realizes horn 2, may be at extended state or folded state, effectively improves and carries out folding operation to horn 2
Reliability, further ensure the convenient, fast property assembled and transported to unmanned vehicle.
Embodiment six
On the basis of the above embodiments, with continued reference to attached drawing 1-6 it is found that in order to guarantee unmanned vehicle operation stabilization
Reliability sets adjustment part 3 to further include:
Tight lock part 32 is detachably connected with interconnecting piece 31, is used for when horn 2 is in extended state, with 31 phase of interconnecting piece
Connection；And when horn 2 is in folded state, separated with 31 phase of interconnecting piece.
Wherein, without limitation for the concrete shape structure of tight lock part 32, those skilled in the art can be according to its realization
Function any setting is carried out to it, more preferably, set columnar structured for tight lock part 32；Specifically, in machine
When arm 2 is in extended state, tight lock part 32 is connected with interconnecting piece 31, and tight lock part 32 at this time can be by horn 2 and fuselage 1
Connection status is locked, to improve the reliability that horn 2 is connect with fuselage 1, ensure that unmanned vehicle is run
Reliability；And when horn 2 is in folded state, tight lock part 32 is separated with 31 phase of interconnecting piece, tight lock part 32 at this time
The locking to horn 2 and the connection status of fuselage 1 is released, so that horn 2 carries out folding operation relative to fuselage 1, so that
Folded unmanned vehicle is in rectangular configuration, convenient that unmanned vehicle is assembled and transported.
It, can be by tight lock part 32 in order to preferably realize that tight lock part 32 locks horn 2 and the connection status of fuselage 1
It is set as being set in the outside of horn 2, and the internal diameter of tight lock part 32 is greater than the outer diameter of horn 2, so that locking
Portion 32 can be moved freely on horn 2；In addition, what the present embodiment was detachably connected tight lock part 32 and interconnecting piece 31
Without limitation, those skilled in the art can be configured specific implementation according to specific design requirement, such as: it will connect
The outside in portion 31 is provided with external screw thread, and the inside of tight lock part 32 is provided with internal screw thread, and interconnecting piece 31 and tight lock part 32 pass through outer spiral shell
Line is connected with the cooperation of internal screw thread；The detachable of tight lock part 32 and interconnecting piece 31 may be implemented by rotation lock portion 32 in this way
Connection；Alternatively, the outside of interconnecting piece 31 can also be provided with to protrusion 3121, the inside of tight lock part 32 is provided with and protrusion 3121
The groove matched, interconnecting piece 31 are detachably connected by protrusion 3121 with groove with tight lock part 32.Of course, art technology
Personnel can also realize being detachably connected for interconnecting piece 31 and tight lock part 32 using other modes, and details are not described herein.
By the tight lock part 32 of setting being detachably connected with interconnecting piece 31, it is effectively guaranteed and is in stretching, extension in horn 2
The reliability that horn 2 when state is connect with fuselage 1, and then improve the security reliability that unmanned vehicle uses.
Embodiment seven
On the basis of the above embodiments, with continued reference to attached drawing 1-6 it is found that the present embodiment for interconnecting piece 31 specific shape
Without limitation, those skilled in the art can be configured shape structure according to specific design requirement, more preferably, will connect
Portion 31 is set as
Fixed sub-portion 311, is fixedly connected with fuselage 1；
Adjusting sub-section 312 is rotatablely connected with fixed sub-portion 311, and is fixedly connected with horn 2；
Horn 2 drives adjusting sub-section 312 to be rotated relative to fixed sub-portion 311 according to provided power, so that
Horn 2 switches to folded state by extended state.
Wherein, it being fixedly connected due to fixed sub-portion 311 with fuselage 1, adjusting sub-section 312 and fixed sub-portion 311 are rotatablely connected,
To manufacture, fixed sub-portion 311 can be respectively arranged at adjusting sub-section 312 to interconnecting piece 31 for convenience
The outer wall two sides of horn 2, adjusting sub-section 312 at this time is fixedly connected with horn 2, so that horn 2 is under the effect of external force
Adjusting sub-section 312 can be driven to be rotated relative to fixed sub-portion 311, realize horn 2 by extended state and folded state
Handover operation.
In addition, the present embodiment for fixed sub-portion 311 and adjusting sub-section 312 concrete shape structure without limitation, ability
Field technique personnel can be configured according to specific design requirement, in order to guarantee horn 2 extended state and folded state it
Between the reliability of handover operation be in more preferably semicircular arc structure by fixed sub-portion 311 and adjusting sub-section 312,
The interconnecting piece 31 constituted is in cylindrical structure；At this point, when horn 2 is in extended state, fixed sub-portion 311 and adjusting sub-section
312 lateral surface with horn 2 abuts against, and interconnecting piece 31 at this time is set on the lateral surface of horn 2, and locking at this time
Portion 32 can be abutted against with sub-portion 313 is connect；And when horn 2 is in folded state, the central axes of horn 2 and fixed sub-portion
Default angle is formed between 311, and predetermined angle is acute angle；The default angle carries out folding operation journey for limiting horn 2
The angle maximum magnitude that the limited angular of degree, i.e. horn 2 carry out folding movement is above-mentioned default angle.
In addition, the specific implementation that the present embodiment is rotatablely connected adjusting sub-section 312 with fixed sub-portion 311 does not limit
Fixed, those skilled in the art can be configured according to specific design requirement, more preferably, can be by fixed sub-portion 311
It is hinged by connection sub-portion 313 with adjusting sub-section 312, it should be noted that it is provided with axis 3131 in connection sub-portion 313,
Adjusting sub-section 312 can carry out rotation operation along the axis 3131, to realize horn 2 between extended state and folded state
Switching.
Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent
Pipe present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: its according to
So be possible to modify the technical solutions described in the foregoing embodiments, or to some or all of the technical features into
Row equivalent replacement；And these are modified or replaceed, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (21)
1. a kind of more rotor unmanned aircrafts characterized by comprising
Fuselage,
Multiple horns are collapsibly set on the fuselage；
When the horn is in extended state, the horn is extended around towards the fuselage；
When the horn is in folded state, the horn is folded towards the two sides of the fuselage；It wraps the two sides of the fuselage
It includes: the tail direction of the heading of the unmanned vehicle and the unmanned vehicle；
The forearm of the horn is folded towards the heading, and the postbrachium of the horn is folded towards the tail direction.
2. more rotor unmanned aircrafts according to claim 1, which is characterized in that folded towards the heading
The length of the horn be less than the length of the horn folded towards the tail direction.
3. more rotor unmanned aircrafts according to claim 1, which is characterized in that when the horn is in folded state
When, the unmanned vehicle is in long and narrow strip structure.
4. more rotor unmanned aircrafts according to claim 1, which is characterized in that be in stretching, extension in each horn
When state, the central axes of each horn are respectively formed an identical predetermined angle between a preset plane, wherein described
Preset plane is by the yaw axis and the plane that is constituted of roll axis on the unmanned vehicle.
5. more rotor unmanned aircrafts according to claim 4, which is characterized in that the predetermined angle is obtuse angle.
6. more rotor unmanned aircrafts according to claim 1, which is characterized in that each horn surrounds one in advance
If axis folded, each axis is respectively formed an identical predetermined angle between a preset plane, wherein described pre-
If plane is by the yaw axis and the plane that is constituted of roll axis on the unmanned vehicle.
7. more rotor unmanned aircrafts according to claim 6, which is characterized in that the predetermined angle is acute angle.
8. more rotor unmanned aircrafts according to claim 1, which is characterized in that further include multiple adjustment parts, Mei Gesuo
Adjustment part is stated to be connected between the fuselage and the corresponding horn, when the horn is in extended state, the horn
Central axes and the central axes of the adjustment part overlap；When the horn is in folded state, the central axes of the horn
It is in a default angle between the central axes of the adjustment part.
9. more rotor unmanned aircrafts according to claim 8, which is characterized in that the adjustment part includes:
Interconnecting piece is connected with the fuselage and horn, for realizing the horn between extended state and folded state
Switching.
10. more rotor unmanned aircrafts according to claim 9, which is characterized in that the adjustment part further include:
Tight lock part is detachably connected with the interconnecting piece, is used for when the horn is in extended state, with the interconnecting piece phase
Connection；And when the horn is in folded state, mutually separated with the interconnecting piece.
11. more rotor unmanned aircrafts according to claim 10, which is characterized in that the tight lock part is set in the machine
The outside of arm, and the internal diameter of the tight lock part is greater than the outer diameter of the horn.
12. more rotor unmanned aircrafts according to claim 10, which is characterized in that be provided on the outside of the interconnecting piece
External screw thread, internal screw thread is provided on the inside of the tight lock part, and the interconnecting piece and the tight lock part pass through the external screw thread and institute
The cooperation for stating internal screw thread is connected.
13. more rotor unmanned aircrafts according to claim 10, which is characterized in that be provided on the outside of the interconnecting piece
Protrusion is provided with groove matched with the bulge on the inside of the tight lock part, and the interconnecting piece passes through with the tight lock part
The protrusion is detachably connected with the groove.
14. more rotor unmanned aircrafts according to claim 10, which is characterized in that the interconnecting piece includes:
Fixed sub-portion, is fixedly connected with the fuselage；
Adjusting sub-section is rotatablely connected with the fixed sub-portion, and is fixedly connected with the horn；
The horn drives the adjusting sub-section to be rotated relative to the fixed sub-portion according to provided power, so that
The horn switches to folded state by extended state.
15. more rotor unmanned aircrafts according to claim 14, which is characterized in that the fixed sub-portion and the adjustment
Sub-portion is respectively arranged at the outer wall two sides of the horn.
16. more rotor unmanned aircrafts according to claim 15, which is characterized in that the fixed sub-portion and the adjustment
Sub-portion is in semicircular arc structure, and the interconnecting piece constituted is in cylindrical structure.
17. more rotor unmanned aircrafts according to claim 14, which is characterized in that be in folded state in the horn
When, the default angle is formed between the central axes of the horn and the fixed sub-portion.
18. more rotor unmanned aircrafts according to claim 17, which is characterized in that the predetermined angle is acute angle.
19. more rotor unmanned aircrafts according to claim 14, which is characterized in that the fixed sub-portion passes through connexon
Portion is hinged with the adjusting sub-section.
20. more rotor unmanned aircrafts according to claim 19, which is characterized in that be in extended state in the horn
When, the tight lock part is abutted against with the connection sub-portion.
21. more rotor unmanned aircrafts described in any one of -20 according to claim 1, which is characterized in that more rotors
Unmanned vehicle includes at least four horns.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2016/108952 WO2018103026A1 (en) | 2016-12-07 | 2016-12-07 | Multi-rotor unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107000834A CN107000834A (en) | 2017-08-01 |
| CN107000834B true CN107000834B (en) | 2019-05-24 |
Family
ID=59431253
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680003994.XA Active CN107000834B (en) | 2016-12-07 | 2016-12-07 | More rotor unmanned aircrafts |
Country Status (3)
| Country | Link |
|---|---|
| KR (2) | KR102306463B1 (en) |
| CN (1) | CN107000834B (en) |
| WO (1) | WO2018103026A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107000834B (en) * | 2016-12-07 | 2019-05-24 | 深圳市大疆创新科技有限公司 | More rotor unmanned aircrafts |
| WO2019205139A1 (en) * | 2018-04-28 | 2019-10-31 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle frame, and unmanned aerial vehicle |
| CN110065616A (en) * | 2019-05-31 | 2019-07-30 | 山东久天智能技术有限公司 | A kind of rotatable folding locking handware and unmanned plane |
| CN110341930B (en) * | 2019-07-16 | 2023-10-24 | 安徽天德无人机科技有限公司 | High-strength folding horn and plant protection unmanned aerial vehicle |
| KR102282857B1 (en) * | 2019-11-26 | 2021-07-29 | 선문대학교 산학협력단 | High efficiency drone with a low gravity center |
| CN113911355B (en) * | 2021-07-10 | 2023-06-09 | 山东交通学院 | Portable unmanned aerial vehicle and application method thereof |
| CN113815839A (en) * | 2021-10-20 | 2021-12-21 | 合肥翼飞特电子科技有限公司 | Two-degree-of-freedom folding mechanism suitable for plant protection unmanned aerial vehicle and plant protection unmanned aerial vehicle |
| CN114013623A (en) * | 2021-10-22 | 2022-02-08 | 合肥翼飞特电子科技有限公司 | Four-six-shaft shared plant protection unmanned aerial vehicle body frame adaptable to various batteries |
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| CN105000165A (en) * | 2015-07-23 | 2015-10-28 | 致导科技（北京）有限公司 | Locking device for folding type unmanned aerial vehicle arm |
| CN205554560U (en) * | 2016-02-22 | 2016-09-07 | 深圳市大疆创新科技有限公司 | Unmanned vehicles and frame thereof |
| CN205633056U (en) * | 2016-05-17 | 2016-10-12 | 南京奇蛙智能科技有限公司 | Foldable unmanned aerial vehicle horn latching device |
| CN205738052U (en) * | 2016-07-05 | 2016-11-30 | 山东翔鸿电子科技有限公司 | Unmanned plane folds horn |
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| WO2008147484A2 (en) * | 2007-02-16 | 2008-12-04 | Donald Orval Shaw | Modular flying vehicle |
| WO2015109322A1 (en) * | 2014-01-20 | 2015-07-23 | Robodub Inc. | Multicopters with variable flight characteristics |
| KR101661942B1 (en) * | 2014-12-15 | 2016-10-05 | 한국항공우주연구원 | Drone for saving a life on the sea |
| CN107000834B (en) * | 2016-12-07 | 2019-05-24 | 深圳市大疆创新科技有限公司 | More rotor unmanned aircrafts |
| CN206255184U (en) * | 2016-12-07 | 2017-06-16 | 深圳市大疆创新科技有限公司 | Many rotor unmanned aircrafts |
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- 2016-12-07 KR KR1020207033776A patent/KR102306463B1/en active IP Right Grant
- 2016-12-07 WO PCT/CN2016/108952 patent/WO2018103026A1/en active Application Filing
- 2016-12-07 KR KR1020197005970A patent/KR102184640B1/en active IP Right Grant
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105000165A (en) * | 2015-07-23 | 2015-10-28 | 致导科技（北京）有限公司 | Locking device for folding type unmanned aerial vehicle arm |
| CN205554560U (en) * | 2016-02-22 | 2016-09-07 | 深圳市大疆创新科技有限公司 | Unmanned vehicles and frame thereof |
| CN205707290U (en) * | 2016-02-22 | 2016-11-23 | 深圳市大疆创新科技有限公司 | The frame of unmanned vehicle and unmanned vehicle |
| CN205633056U (en) * | 2016-05-17 | 2016-10-12 | 南京奇蛙智能科技有限公司 | Foldable unmanned aerial vehicle horn latching device |
| CN205738052U (en) * | 2016-07-05 | 2016-11-30 | 山东翔鸿电子科技有限公司 | Unmanned plane folds horn |
Also Published As
| Publication number | Publication date |
|---|---|
| KR102306463B1 (en) | 2021-09-28 |
| CN107000834A (en) | 2017-08-01 |
| KR20200137021A (en) | 2020-12-08 |
| WO2018103026A1 (en) | 2018-06-14 |
| KR20190029745A (en) | 2019-03-20 |
| KR102184640B1 (en) | 2020-11-30 |
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