CN107000834A - Many rotor unmanned aircrafts - Google Patents
Many rotor unmanned aircrafts Download PDFInfo
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- CN107000834A CN107000834A CN201680003994.XA CN201680003994A CN107000834A CN 107000834 A CN107000834 A CN 107000834A CN 201680003994 A CN201680003994 A CN 201680003994A CN 107000834 A CN107000834 A CN 107000834A
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- horn
- many rotor
- rotor unmanned
- unmanned aircrafts
- fuselage
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- 238000013461 design Methods 0.000 description 13
- 238000005516 engineering process Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
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Classifications
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
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- Refuge Islands, Traffic Blockers, Or Guard Fence (AREA)
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Abstract
A kind of many rotor unmanned aircrafts, including：Fuselage (1), multiple horns (2), is collapsibly arranged on fuselage (1), and when horn (2) is in extended configuration, horn (2) is extended around towards fuselage (1)；When horn (2) is in folded state, horn (2) is folded towards the both sides of fuselage (1).Many rotor unmanned aircrafts that the present invention is provided, by being arranged at multiple horns (2) are folding on fuselage (1), when unmanned vehicle be in it is to be used or when using, horn (2) can be in extended configuration, when needing to assemble unmanned vehicle and transported, horn (2) can be set to folded state, so that unmanned vehicle is in long and narrow strip structure, so that the shape of unmanned vehicle is adapted with the shape of conveying arrangement, it is convenient that unmanned vehicle after folding is arranged in conveying arrangement, significantly reduce the transport difficulty to unmanned vehicle, improve the practicality of unmanned vehicle.
Description
Technical field
The present invention relates to vehicle technology field, more particularly to a kind of many rotor unmanned aircrafts.
Background technology
With developing rapidly for science and technology, unmanned air vehicle technique development is more and more ripe, and the field of application is also more and more wider
It is general, for example：The field such as military affairs, scientific research, civilian, specifically can be used for photographing, explores, communicates, preventing and reducing natural disasters, border patrol etc.
Deng.
For large-scale multi-rotor unmanned aerial vehicle, for convenience of assembling and transporting, use folded wing more, however, in the prior art,
The shape of wing after folding is mostly irregular, and then improves the difficulty assembled and transported to multi-rotor unmanned aerial vehicle.
The content of the invention
The invention provides a kind of many rotor unmanned aircrafts, for be not easy to present in prior art to many rotors without
People's aircraft transported, is improved and multi-rotor unmanned aerial vehicle is assembled and the problem of transport difficulty.
The present invention is to provide for a kind of many rotor unmanned aircrafts, including：
Fuselage,
Multiple horns, are collapsibly arranged on the fuselage；
When the horn is in extended configuration, the horn is extended around towards the fuselage；
When the horn is in folded state, the horn is folded towards the both sides of the fuselage.
Many rotor unmanned aircrafts that the present invention is provided, by being arranged at multiple horns are folding on fuselage, work as nothing
When people's aircraft is in during to be used or use, horn can be in extended configuration, when needing to unmanned vehicle
When being assembled and being transported, horn can be set to folded state so that unmanned vehicle is in long and narrow strip structure so that
The shape of unmanned vehicle is adapted with the shape of conveying arrangement, further facilitates the unmanned vehicle after folding being arranged at fortune
In defeated device, the transport difficulty to unmanned vehicle is significantly reduced, and improves the practicality of unmanned vehicle, favorably
Popularization and application in market.
Brief description of the drawings
Fig. 1 is the three-dimensional knot that a kind of horn of many rotor unmanned aircrafts provided in an embodiment of the present invention is in extended configuration
Structure schematic diagram；
Fig. 2 is the main view that a kind of horn of many rotor unmanned aircrafts provided in an embodiment of the present invention is in extended configuration
Figure；
Fig. 3 is the side view that a kind of horn of many rotor unmanned aircrafts provided in an embodiment of the present invention is in extended configuration
Figure；
Fig. 4 is that a kind of horn of many rotor unmanned aircrafts provided in an embodiment of the present invention is regarded in the vertical of folded state
Figure；
Fig. 5 is the main view that a kind of horn of many 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 many rotor unmanned aircrafts provided in an embodiment of the present invention is in folded state.
In figure：
1st, fuselage；2nd, horn；
3rd, adjustment part；31st, connecting portion；
311st, fixed sub-portion；312nd, adjusting sub-section；
3121st, it is raised；313rd, sub-portion is connected；
3131st, axle；32nd, tight lock part.
Embodiment
To make the purpose, technical scheme and advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
A part of embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
In the present invention, the term such as term " installation ", " connection ", " fixation " is broadly understood, for example, " connection " can be with
It is to be fixedly connected or be detachably connected, or is integrally connected.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 invention, term " first ", " second " are only used for the different portion of convenient description
Part, and it is not intended that indicating or implying ordinal relation, relative importance or the implicit number for indicating indicated technical characteristic
Amount.Thus, " first " is defined, at least one this feature can be expressed or be implicitly included to the feature of " second ".
Unless otherwise defined, all of technologies and scientific terms used here by the article is with belonging to technical field of the invention
The implication that technical staff is generally understood that is identical.Term used in the description of the invention herein is intended merely to description tool
The purpose of the embodiment of body, it is not intended that in the limitation present invention.
Below in conjunction with the accompanying drawings, some embodiments of the present invention are elaborated.Do not conflict between each embodiment
In the case of, the feature in following embodiments and embodiment can be mutually combined.
Embodiment one
Fig. 1 is the solid that a kind of horn 2 of many rotor unmanned aircrafts provided in an embodiment of the present invention is in extended configuration
Structural representation；Fig. 2 is the master that a kind of horn 2 of many rotor unmanned aircrafts provided in an embodiment of the present invention is in extended configuration
View；Fig. 4 is the elevation view that a kind of horn 2 of many rotor unmanned aircrafts provided in an embodiment of the present invention is in folded state；
Refer to the attached drawing 1-2,4 are understood, present embodiments provide a kind of many rotor unmanned aircrafts, including：
Fuselage 1,
Multiple horns 2, are collapsibly arranged on fuselage 1；
When horn 2 is in extended configuration, horn 2 is extended around towards fuselage 1；
When horn 2 is in folded state, horn 2 is folded towards the both sides of fuselage 1.
The present embodiment is not limited for the concrete shape structure of fuselage 1, and those skilled in the art can be according to specific
Design requirement is configured, for example：Fuselage 1 can be set to square structure, polygonized structure etc., it is more preferred, can
So that fuselage 1 is set into rectangular configuration；In addition, the number for horn 2 is not limited, those skilled in the art can be according to tool
The design requirement of body is configured, for example, could be arranged to 2,4,6 or 8 etc., it is more preferred, nobody is flown
It is set to include at least four horns 2 on row device.
When horn 2 is in extended configuration, horn 2 is extended around towards fuselage 1, at many rotor unmanned aircrafts now
During to be used or use, now, because horn 2 is extended around towards fuselage 1 so that the horizontal chi of unmanned vehicle
Very little and longitudinal size is larger.
When horn 2 is in folded state, horn 2 is folded towards the both sides of fuselage 1, specifically, can be by the two of fuselage 1
Side is set to include：The heading of unmanned vehicle and the tail direction of unmanned vehicle；And then cause horn 2 in rugosity
During state, the set multiple horns 2 being placed on fuselage 1 are respectively facing heading and tail direction carries out folding operation, now
Unmanned vehicle be in it is to be assembled or to be transported during.By the way that horn 2 is provided towards into heading and tail direction
Folded, efficiently reduce 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 strip structure is mutually fitted with the shape of conveying arrangement that is used to ship unmanned vehicle
Match somebody with somebody, wherein, conveying arrangement can include：Strip knapsack, suitcase, square box etc., so that convenient enter to unmanned vehicle
Luggage is matched somebody with somebody and transported, and significantly reduces the transport to unmanned vehicle and mobile difficulty.
Many rotor unmanned aircrafts that the present embodiment is provided, by being arranged at multiple horns 2 are folding on fuselage 1,
When unmanned vehicle is in during to be used or use, horn 2 can be in extended configuration, it is winged to nobody when needing
When row device is assembled and transported, horn 2 can be set to folded state so that unmanned vehicle is in long and narrow bar shaped knot
Structure so that the shape of unmanned vehicle is adapted with the shape of conveying arrangement, is further facilitated the unmanned vehicle after folding
It is arranged in conveying arrangement, 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 above-described embodiment, understand, make to further improve unmanned vehicle with continued reference to accompanying drawing 1-2,4
The length of the horn 2 folded towards heading is less than to enter towards tail direction by reliability, the present embodiment
The length for the horn 2 that row is folded.
The present embodiment is not limited for the specific length dimension of horn 2, and those skilled in the art can be according to specific
Design requirement is configured；It should be noted that when setting 2 length dimension of horn, it is more preferred, will be towards heading
The length of horn 2 be set smaller than the length of horn 2 towards tail direction, be achieved in that in the power point by unmanned vehicle
The heart is disposed proximate to tail direction, so that the power dot center moved afterwards 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 many rotor unmanned aircrafts provided in an embodiment of the present invention is in extended configuration
Figure；On the basis of above-described embodiment, understood with continued reference to accompanying drawing 1-4, when each horn 2 is in extended configuration, each
The axis of horn 2 is respectively formed an identical predetermined angle between a preset plane, wherein, preset plane is flown by nobody
The plane that yaw axis and roll axle on row device are constituted.
Wherein, predetermined angle is pre-set, and the present embodiment is not limited for the specific angular range of predetermined angle,
Those skilled in the art can be configured according to specific design requirement, for example, can be set to predetermined angle to include
It is 10 °, 30 °, 60 °, 100 °, 120 ° or 150 ° etc., more preferred, predetermined angle is set to obtuse angle.
It should be noted that the axis of each horn 2 forms a predetermined angle, and each machine with preset plane
The axis of arm 2 is equal with the predetermined angle that preset plane is formed, so that the unmanned vehicle in extended configuration
For symmetrical structure, the convenient running status to unmanned vehicle is adjusted and controlled.
Example IV
Fig. 5 is the main view that a kind of horn 2 of many 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 many rotor unmanned aircrafts provided in an embodiment of the present invention is in folded state；
On the basis of above-described embodiment, understood with continued reference to accompanying drawing 1-6, the present embodiment is by each horn 2 around a default axle
3131 are folded, and each axle 3131 is respectively formed an identical predetermined angle between a preset plane, wherein, preset plane
It is the plane that yaw axis and roll axle on unmanned vehicle are constituted.
Wherein, predetermined angle is pre-set, and the present embodiment is not limited for the specific angular range of predetermined angle,
Those skilled in the art can be configured according to specific design requirement, for example, can be set to predetermined angle to include
It is 10 °, 30 °, 60 °, 100 °, 120 ° or 150 ° etc., more preferred, predetermined angle is set to acute angle；By by preset angle
Degree is set to acute angle, so as to reduce the longitudinal size between the horn 2 of folded state and fuselage 1, further reduces nothing
The space-consuming of people's aircraft.
It should be noted that each axle 3131 with preset plane one predetermined angle of formation, and each axle 3131 with it is pre-
If the predetermined angle that plane is formed is equal, so that the unmanned vehicle in extended configuration is symmetrical structure, convenient
Unmanned vehicle in folded state is assembled and transported.
Embodiment five
On the basis of above-described embodiment, understand that the present embodiment is foldable for multiple horns 2 with continued reference to accompanying drawing 1-6
The specific implementation that ground is arranged on fuselage 1 is not limited, and those skilled in the art can enter according to specific design requirement
Row is set, more preferred, and unmanned vehicle is set to also to include：Multiple adjustment parts 3, each adjustment part 3 is connected to fuselage 1
Between corresponding horn 2, when horn 2 is in extended configuration, the axis and the axis of adjustment part 3 of horn 2 overlap；
When horn 2 is in folded state, in a default angle between the axis of horn 2 and the axis of adjustment part 3.
Wherein, the number of adjustment part 3 is identical with 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 is not limited for the concrete shape structure of adjustment part 3, those skilled in the art
It can be configured according to specific design requirement, it is more preferred, adjustment part 3 is set to include：Connecting portion 31, with fuselage
1 is connected with horn 2, for realizing switching of the horn 2 between extended configuration and folded state.
In addition, the present embodiment is not limited for the concrete shape structure of connecting portion 31, those skilled in the art can root
Be configured according to specific design requirement, it is more preferred, connecting portion 31 can be set to it is columnar structured, so by setting
The connecting portion 31 put, have effectively achieved switching of the horn 2 between extended configuration and folded state, specifically, when in horn 2
During in extended configuration, the axis and the axis of adjustment part 3 of horn 2 overlap, the axis of adjustment part 3 now and company
The axis of socket part 31 overlaps；When horn 2 is in folded state, between the axis of horn 2 and the axis of adjustment part 3
In a default angle；Wherein, the default angle formed between the axis of horn 2 and the axis of adjustment part 3 is to set in advance
Put, those skilled in the art can be configured according to specific design requirement, more preferred, and default angle is set to
Acute angle.
The foldable connection of multiple horns 2 and fuselage 1 is have effectively achieved by multiple adjustment parts 3 of setting, by adjusting
One integral piece 3 realizes horn 2 and may be at extended configuration or folded state, is effectively improved 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 above-described embodiment, understood with continued reference to accompanying drawing 1-6, in order to ensure the stabilization of unmanned vehicle operation
Reliability, adjustment part 3 is set to also to include：
Tight lock part 32, is detachably connected with connecting portion 31, for when horn 2 is in extended configuration, with the phase of connecting portion 31
Connection；And when horn 2 is in folded state, be separated with connecting portion 31.
Wherein, the concrete shape structure for tight lock part 32 is not limited, and those skilled in the art can be according to its realization
Function any setting is carried out to it, it is more preferred, tight lock part 32 is set to columnar structured；Specifically, in machine
When arm 2 is in extended configuration, tight lock part 32 is connected with connecting portion 31, and tight lock part 32 now can be by horn 2 and fuselage 1
Connection status is locked, so as to improve the reliability that horn 2 is connected with fuselage 1, it is ensured that unmanned vehicle is run
Reliability；And when horn 2 is in folded state, tight lock part 32 is separated with connecting portion 31, tight lock part 32 now
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
Unmanned vehicle after folding is in rectangular configuration, convenient that unmanned vehicle is assembled and transported.
, can be by tight lock part 32 in order to preferably realize that tight lock part 32 is locked to the connection status of horn 2 and fuselage 1
It is set to be set in the outside of horn 2, and the internal diameter size of tight lock part 32 is more than the outside dimension of horn 2, and then cause locking
Portion 32 can be moved freely on horn 2；In addition, what the present embodiment was detachably connected for tight lock part 32 and connecting portion 31
Specific implementation is not limited, and those skilled in the art can be configured according to specific design requirement, for example：Will connection
The outside in portion 31 is provided with external screw thread, and the inner side of tight lock part 32 is provided with internal thread, and connecting portion 31 passes through outer spiral shell with tight lock part 32
Line is connected with the cooperation of internal thread；The detachable of tight lock part 32 and connecting portion 31 so can be realized by rotation lock portion 32
Connection；Or, the outside of connecting portion 31 can also be provided with to projection 3121, the inner side of tight lock part 32 is provided with and projection 3121
The groove being engaged, connecting portion 31 is detachably connected with tight lock part 32 by projection 3121 with groove.Certain, art technology
Personnel can also realize being detachably connected for connecting portion 31 and tight lock part 32 using other modes, will not be repeated here.
By the tight lock part 32 being detachably connected with connecting portion 31 of setting, it is effectively guaranteed to be in horn 2 and stretches
The reliability that horn 2 during state is connected with fuselage 1, and then improve the security reliability that unmanned vehicle is used.
Embodiment seven
On the basis of above-described embodiment, understood with continued reference to accompanying drawing 1-6, specific shape of the present embodiment for connecting portion 31
Shape structure is not limited, and those skilled in the art can be configured according to specific design requirement, more preferred, will connect
Portion 31 is set to include：
Fixed sub-portion 311, is fixedly connected with fuselage 1；
Adjusting sub-section 312, rotates with fixed sub-portion 311 and is connected, and be fixedly connected with horn 2；
Horn 2 drives adjusting sub-section 312 to be rotated relative to fixed sub-portion 311 according to the power provided, to cause
Horn 2 switches to folded state by extended configuration.
Wherein, because fixed sub-portion 311 is fixedly connected with fuselage 1, adjusting sub-section 312 is rotated with fixed sub-portion 311 and is connected,
So as to manufacture, can be respectively arranged at fixed sub-portion 311 with adjusting sub-section 312 to connecting portion 31 for convenience
The outer wall both sides of horn 2, adjusting sub-section 312 now is fixedly connected with horn 2, so that horn 2 is in the presence of external force
Adjusting sub-section 312 can be driven to be rotated relative to fixed sub-portion 311, realize horn 2 by extended configuration and folded state
Handover operation.
In addition, the present embodiment is not limited for the concrete shape structure of fixed sub-portion 311 and adjusting sub-section 312, ability
Field technique personnel can be configured according to specific design requirement, in order to ensure horn 2 extended configuration and folded state it
Between handover operation reliability, it is more preferred, be in semicircular arc structure by fixed sub-portion 311 and adjusting sub-section 312,
The connecting portion 31 constituted is in cylindrical structure；Now, when horn 2 is in extended configuration, fixed sub-portion 311 and adjusting sub-section
312 lateral surface with horn 2 is abutted against, and connecting portion 31 now is set on the lateral surface of horn 2, and locking now
Portion 32 can be abutted against with being connected sub-portion 313；And when horn 2 is in folded state, the axis of horn 2 and fixed sub-portion
Default angle is formed between 311, and predetermined angle is acute angle；The default angle is used to limit the progress folding operation journey of 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.
Do not limited in addition, the present embodiment rotates the specific implementation being connected for adjusting sub-section 312 with fixed sub-portion 311
Fixed, those skilled in the art can be configured according to specific design requirement, more preferred, can be by fixed sub-portion 311
It is hinged with adjusting sub-section 312 by connecting sub-portion 313, it is necessary to illustrate, axle 3131 is provided with connection sub-portion 313,
Adjusting sub-section 312 can carry out rotating operation along the axle 3131, so as to realize horn 2 between extended configuration and folded state
Switching.
Finally it should be noted that：Various embodiments above is merely illustrative of the technical solution of the present invention, rather than its limitations；To the greatest extent
The present invention is described in detail with reference to foregoing embodiments for pipe, it will be understood by those within the art that：Its according to
The technical scheme described in foregoing embodiments can so be modified, or which part or all technical characteristic are entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the present invention technology
The scope of scheme.
Claims (22)
1. a kind of many rotor unmanned aircrafts, it is characterised in that including：
Fuselage,
Multiple horns, are collapsibly arranged on the fuselage；
When the horn is in extended configuration, the horn is extended around towards the fuselage；
When the horn is in folded state, the horn is folded towards the both sides of the fuselage.
2. many rotor unmanned aircrafts according to claim 1, it is characterised in that the both sides of the fuselage include：It is described
The tail direction of the heading of unmanned vehicle and the unmanned vehicle.
3. many rotor unmanned aircrafts according to claim 2, it is characterised in that folded towards the heading
The length of the horn be less than the length of the horn folded towards the tail direction.
4. many rotor unmanned aircrafts according to claim 1, it is characterised in that when the horn is in folded state
When, the unmanned vehicle is in long and narrow strip structure.
5. many rotor unmanned aircrafts according to claim 1, it is characterised in that be in stretching in each horn
During state, the axis of each horn is respectively formed an identical predetermined angle between a preset plane, wherein, it is described
Preset plane is the plane that yaw axis and roll axle on the unmanned vehicle are constituted.
6. many rotor unmanned aircrafts according to claim 5, it is characterised in that the predetermined angle is obtuse angle.
7. many rotor unmanned aircrafts according to claim 1, it is characterised in that each horn is pre- around one
If axle folded, each axle is respectively formed an identical predetermined angle between a preset plane, wherein, it is described pre-
If plane is the plane that yaw axis and roll axle on the unmanned vehicle are constituted.
8. many rotor unmanned aircrafts according to claim 7, it is characterised in that the predetermined angle is acute angle.
9. many rotor unmanned aircrafts according to claim 1, it is characterised in that also including 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 configuration, the horn
Axis and the axis of the adjustment part overlap；When the horn is in folded state, the axis of the horn
In a default angle between the axis of the adjustment part.
10. many rotor unmanned aircrafts according to claim 9, it is characterised in that the adjustment part includes：
Connecting portion, is connected with the fuselage and horn, for realizing the horn between extended configuration and folded state
Switching.
11. many rotor unmanned aircrafts according to claim 10, it is characterised in that the adjustment part also includes：
Tight lock part, is detachably connected with the connecting portion, for when the horn is in extended configuration, with the connecting portion phase
Connection；And when the horn is in folded state, be separated with the connecting portion.
12. many rotor unmanned aircrafts according to claim 11, it is characterised in that the tight lock part is set in the machine
The outside of arm, and outside dimension of the internal diameter size more than the horn of the tight lock part.
13. many rotor unmanned aircrafts according to claim 11, it is characterised in that be provided with the outside of the connecting portion
Internal thread is provided with the inside of external screw thread, the tight lock part, the connecting portion passes through the external screw thread and institute with the tight lock part
The cooperation for stating internal thread is connected.
14. many rotor unmanned aircrafts according to claim 11, it is characterised in that be provided with the outside of the connecting portion
The groove being engaged with the projection is provided with the inside of projection, the tight lock part, the connecting portion passes through with the tight lock part
It is described raised to be detachably connected with the groove.
15. many rotor unmanned aircrafts according to claim 11, it is characterised in that the connecting portion includes：
Fixed sub-portion, is fixedly connected with the fuselage；
Adjusting sub-section, rotates with the fixed sub-portion and is connected, and be fixedly connected with the horn；
The horn drives the adjusting sub-section to be rotated relative to the fixed sub-portion according to the power provided, to cause
The horn switches to folded state by extended configuration.
16. many rotor unmanned aircrafts according to claim 15, it is characterised in that the fixed sub-portion and the adjustment
Sub-portion is respectively arranged at the outer wall both sides of the horn.
17. many rotor unmanned aircrafts according to claim 16, it is characterised in that the fixed sub-portion and the adjustment
Sub-portion is in semicircular arc structure, and the connecting portion constituted is in cylindrical structure.
18. many rotor unmanned aircrafts according to claim 15, it is characterised in that be in folded state in the horn
When, the default angle is formed between the axis of the horn and the fixed sub-portion.
19. many rotor unmanned aircrafts according to claim 18, it is characterised in that the predetermined angle is acute angle.
20. many rotor unmanned aircrafts according to claim 15, it is characterised in that the fixed sub-portion passes through connexon
Portion is hinged with the adjusting sub-section.
21. many rotor unmanned aircrafts according to claim 20, it is characterised in that be in extended configuration in the horn
When, the tight lock part is abutted against with the connection sub-portion.
22. many rotor unmanned aircrafts according to any one in claim 1-21, it is characterised in that many 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 true CN107000834A (en) | 2017-08-01 |
| CN107000834B 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) | KR102184640B1 (en) |
| CN (1) | CN107000834B (en) |
| WO (1) | WO2018103026A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018103026A1 (en) * | 2016-12-07 | 2018-06-14 | 深圳市大疆创新科技有限公司 | Multi-rotor 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 |
| CN110382353A (en) * | 2018-04-28 | 2019-10-25 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle rack and unmanned plane |
| 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 |
| CN113859513A (en) * | 2021-11-10 | 2021-12-31 | 复旦大学 | Collapsible horn and many rotor unmanned aerial vehicle |
| CN113911355A (en) * | 2021-07-10 | 2022-01-11 | 山东交通学院 | Portable unmanned aerial vehicle and using method thereof |
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| KR102282857B1 (en) * | 2019-11-26 | 2021-07-29 | 선문대학교 산학협력단 | High efficiency drone with a low gravity center |
| CN112793759A (en) * | 2021-03-16 | 2021-05-14 | 复旦大学 | Can dismantle horn and unmanned aerial vehicle can be dismantled to horn |
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Also Published As
| Publication number | Publication date |
|---|---|
| KR20190029745A (en) | 2019-03-20 |
| KR20200137021A (en) | 2020-12-08 |
| KR102306463B1 (en) | 2021-09-28 |
| WO2018103026A1 (en) | 2018-06-14 |
| CN107000834B (en) | 2019-05-24 |
| KR102184640B1 (en) | 2020-11-30 |
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