CN206914622U - A kind of folding multi-rotor unmanned aerial vehicle - Google Patents
A kind of folding multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN206914622U CN206914622U CN201720789399.5U CN201720789399U CN206914622U CN 206914622 U CN206914622 U CN 206914622U CN 201720789399 U CN201720789399 U CN 201720789399U CN 206914622 U CN206914622 U CN 206914622U
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- fuselage
- horn
- aerial vehicle
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- rotor unmanned
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- 230000005611 electricity Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
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- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
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Abstract
The utility model discloses a kind of folding multi-rotor unmanned aerial vehicle, including fuselage, horn and undercarriage, fuselage includes fuselage upper casing and fuselage lower casing, and the GPS supports for installing GPS navigation device are provided with fuselage upper casing；Multiple horns to the folded piece between fuselage upper casing and fuselage lower casing by being uniformly hinged on around fuselage；Undercarriage includes at least three support bars being independently arranged and is arranged on the hinge part of supporting bar top, and support bar is evenly distributed on around fuselage and is hinged by hinge part with horn；Meanwhile the length of support bar be more than horn from hinge part to horn on motor installation end length.Horn is realized by folded piece and folded, undercarriage is realized by hinge part and folded, so as to which whole unmanned plane can be in transport or stored collapsed when not in use, simultaneously, by set support bar length be more than horn from hinge part to horn on motor installation end end length, they sup-port still can be used when unmanned plane is in folded state.
Description
Technical field
The utility model is related to the design field of unmanned plane, specifically, be related to a kind of folding more rotors without
It is man-machine.
Background technology
In recent years, unmanned air vehicle technique has the development advanced by leaps and bounds.Because its cost is low, mobility is good, survival ability
By force, the advantages that risk that no one was injured, unmanned plane occupies extremely important status in modern military war, in civil area
Have boundless prospect, at present take photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster relief, observation it is wild dynamic
The occasions such as thing, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance obtain widely should
With having expanded the purposes and value of unmanned plane in itself significantly.
Current unmanned plane mainly includes fixed-wing unmanned plane and rotor wing unmanned aerial vehicle, and multi-rotor unmanned aerial vehicle is increasingly becoming nobody
The Developing mainstream of aircraft.The horn extending space of in general multi-rotor unmanned aerial vehicle is larger, not readily transportable and dismounting.
Publication No. is that CN106477024A patent document discloses a kind of folding eight rotor wing unmanned aerial vehicle, including electricity
Machine, propeller, horn, fuselage upper casing, fuselage lower casing, undercarriage cross bar, undercarriage montant, battery case and electricity adjust box；On fuselage
Shell closing connection fuselage lower casing, fuselage upper casing is smooth streamlined curved surface；Fuselage upper casing is connected with eight horns, and horn includes the
Cut with scissors by rotary shaft the lower end of one horn connector and the second horn connector, the first horn connector and the second horn connector
Connect, in addition to horn stay；Outer end connection motor, propeller and the electricity of horn adjust box；The upper end of undercarriage montant is connected to
The bottom sides of fuselage lower casing, undercarriage cross bar are connected to the lower end of undercarriage montant by three-way piece.
The invention is by setting the first horn connector and the second horn connector to realize the folding of horn, but the Foldable square
Formula appoint horn can not so be folded completely, and by undercarriage cross bar and undercarriage montant landing gear structure it is cumbersome, can not fold,
Cause the unmanned plane of the invention to fold descendant and occupy larger space.
Utility model content
For the purpose of this utility model to provide a kind of folding multi-rotor unmanned aerial vehicle, the undercarriage of the unmanned plane can same machine
Arm folds together, realizes that whole unmanned plane folds to greatest extent, convenience in transport and carrying.
To achieve these goals, the collapsible unmanned plane of more rotors provided by the utility model includes fuselage, horn and risen
Fall frame, fuselage includes fuselage upper casing and fuselage lower casing, the GPS supports for installing GPS navigation device are provided with fuselage upper casing；It is more
Individual horn to the folded piece between fuselage upper casing and fuselage lower casing by being uniformly hinged on around fuselage；Undercarriage is included extremely
Few three support bars being independently arranged and the hinge part for being arranged on supporting bar top, support bar are evenly distributed on around fuselage and led to
Hinge part is crossed to be hinged with horn；Meanwhile the length of support bar be more than horn from hinge part to horn on motor installation end length.
In above-mentioned technical proposal, fuselage is divided into fuselage upper casing and fuselage lower casing is easily installed and dismantled.
Horn realizes and folded that undercarriage is realized by hinge part and folded by folded piece, so as to which whole unmanned plane can transported
Defeated or stored collapsed when not in use, meanwhile, by set the length of support bar be more than horn from hinge part to horn on motor pacify
The length at end is filled, they sup-port still can be used when unmanned plane is in folded state.
Specific scheme is that folded piece includes the fixture that is connected between fuselage upper casing and fuselage lower casing and solid with this
Determine the movable part that part is flexibly connected by rotary shaft；Movable part is provided with the sleeve for being used for connecting horn；Between fixture and movable part
Provided with the first retaining mechanism that movable part is fixed when movable part drives horn to be in open configuration；Set on fuselage lower casing
Have for the second relief portion for movable part activity.
Horn folded piece is arranged between fuselage upper casing and fuselage lower casing so that whole horn can fold around fuselage, together
When, fixation of the horn in stretching, extension is realized by the first retaining mechanism.The folded piece is simple in construction, is applicable to various types of
Unmanned plane.Space is provided for the activity of rotating part by the second relief portion of fuselage lower casing, avoids bumping against fuselage.
Further specific scheme is that fixture includes two interval settings and touched respectively under fuselage upper casing and fuselage up and down
The fixed plate of shell, and it is overlapped on the connecting plate on two fixed plate tops；Movable part is arranged between two fixed plates, and rotary shaft is by fixing
The bottom of plate passes through.
Further specific scheme is that the first retaining mechanism includes being arranged far from the movable part of rotary shaft one end
Latch segment, a screwed hole is offered on the latch segment, a through hole corresponding with the screwed hole is offered on connecting plate；Fuselage upper casing
It is provided with the first relief portion for twisting nail.Screw is coordinated by the screwed hole on the through hole and latch segment on connecting plate, realizes lock
Tight function, so as to realize fixation of the horn in stretching, extension.By the first relief portion of fuselage upper casing, when to the first retaining mechanism
Screw can avoid fuselage when being tightened.
Another specific scheme is for hinge part including the retainer ring for being set on horn, for installing retainer ring
Mounting blocks and the moving block being flexibly connected with mounting blocks by rotary shaft, and moving block side is provided with and is used to install support bar
Sleeve；Moving block is fixed when moving block drives support bar to be in holding state the is provided between moving block and mounting blocks
Two retaining mechanisms.
By the support bar for being arranged to be hinged with horn by undercarriage, relative horn can be achieved and folded, meanwhile, horn
Also foldable, horn is folded simultaneously with support bar, and smaller space is occupied during transport or carrying.Support bar and horn
Be hinged hinge part is simple in construction, it is easy to accomplish the folding of support bar, moving block is locked by retaining mechanism, makes to rise and fall
The structure of frame is more stable.
Further specific scheme is to be provided with a cavity in moving block；Second retaining mechanism includes being slidably mounted in cavity
And the locking member provided with buckle, and be arranged on and be used for the clamping block for blocking buckle on mounting blocks.
Further specific scheme is that the spring of support locking member is provided with cavity, and the both sides of cavity, which are set, coordinates buckle
The guide groove of slip；The clamping slot of buckle can be accommodated by being offered on clamping block；Locking member has the press section extended to outside cavity.
When needing support bar to open, the press section of locking member is pinned, while rotates moving block, support bar is in vertical
State, the press section of locking member is then unclamped, pushed out under the elastic force effect of spring, buckle is caught in clamping along guide groove
In groove, now support bar opens and locked.When needing to collapse support bar, the same press section for pressing locking member, make buckle
Exited along clamping slot, then along rotary shaft rotary supporting rod, fold it and collapse.
Preferable scheme is that support bar vertically has outside angle in holding state, and its bottom is provided with a bottom
Face is the cushion block on inclined-plane, and a wedge for keeping the angle is provided between retainer ring and mounting blocks.The design causes support more
It is stable.
Another specific scheme be GPS supports include be fixed on fuselage upper casing chassis, be vertically set on chassis
Pole and be installed on pole top and for installing the mounting disc of GPS navigation device；Chassis is diametrically offering use
In the mounting groove of installation pole；Pole is up-narrow and down-wide trapezoidal, and bottom has the mounting bar being fixed in mounting groove, and top is set
There is the screwed hole for installing mounting disc, and pole is provided with to mitigate some hollow outs of own wt；The bottom of mounting disc is set
There is boss, be provided with fixing groove in boss, bottom land offers through hole corresponding with screwed hole.
The GPS supporting structures are stable, are not easy to be influenceed by weather, to the firm supporting of GPS navigation device, so that GPS navigation
The signal transmission of device is more stable.
Further specific scheme is that chassis is used to fix and adjust the arcuate socket in itself direction provided with some；Arcuate socket
It is interior to be provided with the step for being easily installed screw；The middle part of mounting groove is provided with the positioning hole with raised rotary shaft contraposition on fuselage, both ends
Screwed hole provided with fastening mounting bar；The edge of mounting disc is provided with the surrounding edge for being used for installing and protect GPS navigation device, the surrounding edge
On offer breach for leading to line.
By setting positioning hole and the rotary shaft coordinated with positioning hole to further increase the stability of GPS supports.
Compared with prior art, the beneficial effects of the utility model are：
The utility model is folded with by the horn to unmanned plane and undercarriage, make its transport and deposit when
It is more convenient to wait, and can be applied to each unmanned plane field, including agriculture unmanned plane or industrial unmanned plane etc..
Brief description of the drawings
Fig. 1 is the front view of the utility model embodiment；
Fig. 2 is the top view of the utility model embodiment；
Fig. 3 is the stereogram of the utility model embodiment；
Fig. 4 is the stereogram that the utility model embodiment omits a wherein horn；
Fig. 5 is the front view of the horn folded piece of the utility model embodiment；
Fig. 6 is the stereogram of the horn folded piece of the utility model embodiment；
Fig. 7 is the front view of the undercarriage hinge part of the utility model embodiment；
Fig. 8 is the stereogram of the undercarriage hinge part of the utility model embodiment；
Fig. 9 is the front view of the gear support bar one of which embodiment of the utility model embodiment；
Figure 10 is the front view of the gear support bar another embodiment of the utility model embodiment；
Figure 11 is the front view of the GPS supports of the utility model embodiment；
Figure 12 is the stereogram of the GPS supports of the utility model embodiment；
Figure 13 is the stereogram on the chassis of the GPS supports of the utility model embodiment；
Figure 14 is the stereogram of the pole of the GPS supports of the utility model embodiment；
Figure 15 is the stereogram of the mounting disc of the GPS supports of the utility model embodiment.
Embodiment
With reference to embodiments and its accompanying drawing the utility model is described in further detail.
Embodiment
Referring to Fig. 1 to Fig. 3, folding multi-rotor unmanned aerial vehicle includes fuselage 1, horn 2, undercarriage 3 and GPS supports 4.Machine
Body 1 is disc, including fuselage upper casing 11 and fuselage lower casing 12.Multiple horns 2 are distributed on around discoidal fuselage 1, and with
Fuselage 1 is be hinged by horn folded piece 5.Undercarriage 3 includes the support bar 31 of more than three and support bar 31 is hinged on into machine
Hinge part 32 on arm 2 or fuselage 1, in the present embodiment, support bar 31 is hinged on horn 2 by hinge part 32 respectively, every
The bottom of support bar 31 is provided with cushion block 33.GPS supports 4 are arranged on the top of fuselage 1, and the top of GPS supports 4 is provided with GPS and led
Navigate device.
The present embodiment is provided with eight horns 2 and three support bars 31 altogether, and three support bars 31, which are respectively separated, is hinged on
On one, the 3rd and the 6th horn, approaches uniformity arrangement, to ensure stability of the unmanned plane when rising and falling.Meanwhile support
The length of bar 31 is more than the length of the motor installation end from hinge part 32 to horn of horn 2, be so designed that be in order in horn 2 and
Undercarriage still can play a part of support to whole unmanned plane during 3 rounding state of undercarriage.In addition, in order to reduce whole nothing
Man-machine weight, fuselage 1, horn 2 and support bar 31 are made using carbon fiber, and on fuselage upper casing 11 and fuselage lower casing 12
It is equipped with hollow out.
Referring to Fig. 3 to Fig. 6, the horn folded piece 5 between horn 2 and fuselage 1 includes fixture 51 and movable part 52, fixture
51 and movable part 52 be flexibly connected by rotary shaft 53, and the first retaining mechanism is provided between fixture 51 and movable part 52.
Fixture 51 includes two and is arranged at intervals and touch the fixed plate of fuselage upper casing 11 and fuselage lower casing 12 respectively up and down
511, and the connecting plate 512 on the top of two fixed plate 511 is overlapped on, fixed plate 511 is fixed by screws in the He of fuselage upper casing 11
Between fuselage lower casing 12.Movable part 52 is arranged between two fixed plates 511, and rotary shaft 53 is passed through by the bottom of fixed plate 511.In machine
Body lower casing 12 is provided with the second relief portion 14 being used for for the activity of movable part 52.
Movable part 52 includes the bottom plate 521 and buck plate 522 of L-shaped connection, and rotary shaft 53 is arranged on remote on bottom plate 521
The side of buck plate 522, the side plate face of buck plate 521 are provided with the sleeve 54 for being used for connecting horn 2.In horn 2 and sleeve
Screwed hole is equipped with 54 side face and is used for mounting screw, so that one end of horn 2 is fixed in sleeve 54, horn 2 it is another
One end is provided with propeller.In order to reduce the weight of whole unmanned plane, multiple hollow outs are provided with fixture 51 and movable part 52
Portion 55.
Retaining mechanism includes the latch segment 56 for being fixed on the top of buck plate, and the latch segment is provided with screwed hole 57, connected
One and the 57 corresponding through hole of screwed hole are offered on plate 512.When movable part 52 drives horn 2 to rotate to open configuration, lock
Tight block 56 is inserted in fixture 51, and screwed hole 57 is aligned with through hole 58, and lock-screw is sequentially inserted into through hole 58 and screwed hole 57
Tightened, the first relief portion 13 for twisting nail is provided with fuselage upper casing 11.
Referring to Fig. 7 to Fig. 9, hinge part 32 includes retainer ring 321, mounting blocks 322 and moving block 323.Retainer ring 321 is used
Mounting blocks 322 are arranged on wherein in one side in fixed horn, and by screw.Between the another side of moving block 323 and mounting blocks 322
It is flexibly connected by rotary shaft 324, moving block 323 is provided with the set for being used for installing support bar 31 in the side away from mounting blocks 322
Cylinder 325, the side face of sleeve 325 are provided with the holding screw 326 for being used for fixing support bar 31.Moving block 323 and mounting blocks 322
Between be provided with the second retaining mechanism that moving block 323 is fixed when moving block 323 drives support bar 31 to be in holding state.
A cavity is provided with moving block 323, retaining mechanism includes being slidably mounted in the cavity and provided with buckle 329
Locking member 328, and be arranged on and be used for the clamping block 3221 for blocking buckle 329 on mounting blocks 322, meanwhile, it is provided with cavity
Support the spring 327 of locking member 328, the both sides of cavity set the guide groove 3231 for coordinating buckle 329 to slide, on clamping block 3221
The clamping slot 3222 of buckle 329 can be accommodated by offering.To adapt to the shape of spring 327, locking member 328 is hollow cylindrical,
The press-side of locking member 328 is provided with the press section for adapting to finger.
When needing support bar 31 to open, the press section of locking member 328 is pinned, while rotates moving block 323, makes support bar
31 are in vertical state, then unclamp locking member 328, are pushed out under the elastic force effect of spring 327, make buckle 329 along leading
It is caught in groove 3231 in clamping slot 3222, now support bar 31 opens and locked.When needing to collapse support bar 31, equally press
The press section of latch segment 328 is pressed, buckle 329 is exited along clamping slot 3222, then along the rotary supporting rod 31 of rotary shaft 324,
It is folded to collapse.
Bar 31 supported above is in vertical state when opening, in order that support bar 31 is more stable when opening, can incite somebody to action
Support bar 31 tilts certain angle and set, and referring to Figure 10, the bottom surface of cushion block 33 is arranged into inclined-plane, at the same retainer ring 321 with
A correcting wedge is provided between mounting blocks 322, mounting blocks 322 is relatively fixed ring 321 and vertically tilts certain angle.When rise
When falling the opening of frame 3, three support bars 31 tilt to surrounding so that support is more stable.
Referring to Figure 11 to Figure 15, GPS supports 4 include chassis 41, pole 42 and mounting disc 43, and pole 42 is vertically fixed on
On chassis 41, mounting disc 43 is fixed on the top of pole 42, for installing GPS navigation device.
Chassis 41 is provided with some arcuate sockets 411, is provided with step in arcuate socket 411, is easily installed screw, screw leads to successively
The screwed hole crossed on arcuate socket 411 and fuselage upper casing, which is tightened, makes chassis 41 be fixed on fuselage, meanwhile, can by arcuate socket 411
Rotation adjusts the angle of whole GPS supports 4, so as to adjust the receiving side signal of GPS navigation device to find optimum orientation.
Chassis 41 is diametrically offering the mounting groove 412 for installing pole 42, the middle part of mounting groove 412 be provided with fuselage
The positioning hole 413 of raised rotary shaft contraposition, screwed hole 414 is additionally provided with the both ends of mounting groove 412, and screwed hole 414 is used to fasten
Pole 42.
Pole 42 is up-narrow and down-wide trapezoidal, and for its thickness between 5~8mm, bottom has the peace coordinated with mounting groove 412
Bar 421 is filled, mounting bar 421 is provided with through hole 422 corresponding with screwed hole 414.The top of pole 42, which is provided with, to be used to install installation
The screwed hole 423 of disk 43.Pole 42 is provided with some hollow outs, to mitigate own wt, for visual appearance, and all hollow outs edges branch
The center line of bar 42 is arranged symmetrically.
The bottom of mounting disc 43 is provided with boss 431, and the fixing groove for accommodating and fixing the top of pole 42 is provided with boss 431
432, bottom land offers through hole 433, and the through hole 433 is corresponding with screwed hole 423.The edge of mounting disc 43 be provided be used for install and
The surrounding edge 434 of GPS navigation device is protected, the breach 435 for leading to line is offered on surrounding edge 434.
The folding multi-rotor unmanned aerial vehicle of the present embodiment can be applied to each unmanned plane field, including agriculture unmanned plane and work
Industry unmanned plane etc..Meanwhile preferable implementation example of the present utility model is the foregoing is only, the utility model is not limited to,
It is all the utility model spirit and principle within, any modification, equivalent substitution and improvements made etc., should be included in this practicality
Within new protection domain.
Claims (10)
1. a kind of folding multi-rotor unmanned aerial vehicle, including fuselage, horn and undercarriage, it is characterised in that：
The fuselage includes fuselage upper casing and fuselage lower casing, and the GPS for installing GPS navigation device is provided with the fuselage upper casing
Support；
Multiple horns to the folded piece between the fuselage upper casing and the fuselage lower casing by being uniformly hinged on institute
State around fuselage；
The undercarriage includes at least three support bars being independently arranged and is arranged on the hinge part of the supporting bar top, described
Support bar is evenly distributed on around fuselage and is hinged by the hinge part with the horn；
The length of the support bar is more than length of the horn from the hinge part to motor installation end on horn.
2. multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：
Described folded piece includes being connected to the fixture between the fuselage upper casing and the fuselage lower casing and fixing with this
The movable part that part is flexibly connected by rotary shaft；
The movable part is provided with the sleeve for being used for inserting the horn；
It is provided between the fixture and the movable part when the movable part drives the horn to be in open configuration to described
The first retaining mechanism that movable part is fixed；
The fuselage lower casing is provided with the second relief portion being used for for movable part activity.
3. multi-rotor unmanned aerial vehicle according to claim 2, it is characterised in that：
Described fixture includes two and is arranged at intervals and touch the fixation of the fuselage upper casing and the fuselage lower casing respectively up and down
Plate, and it is overlapped on the connecting plate on two fixed plate tops；
Described movable part is arranged between two fixed plates, and rotary shaft is passed through by the bottom of fixed plate.
4. multi-rotor unmanned aerial vehicle according to claim 3, it is characterised in that：
The first described retaining mechanism includes the latch segment being arranged far from the movable part of described rotary shaft one end, the latch segment
On offer a screwed hole, a through hole corresponding with the screwed hole is offered on described connecting plate；
Described fuselage upper casing is provided with the first relief portion for twisting nail.
5. multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：
Described hinge part include be used for be set on the horn retainer ring, for the mounting blocks of the retainer ring are installed with
And the moving block being flexibly connected with the mounting blocks by rotary shaft, and described moving block side is provided with and is used to install the branch
The sleeve of strut；
It is provided between the moving block and the mounting blocks when the moving block drives the support bar to be in holding state to institute
State the second retaining mechanism that moving block is fixed.
6. multi-rotor unmanned aerial vehicle according to claim 5, it is characterised in that：
A cavity is provided with described moving block；
The second described retaining mechanism includes being slidably mounted in cavity and the locking member provided with buckle, and is arranged on the peace
It is used for the clamping block for blocking the buckle on dress block.
7. multi-rotor unmanned aerial vehicle according to claim 6, it is characterised in that：
The spring for supporting the locking member is provided with described cavity, the both sides of cavity set the guiding for coordinating the buckle to slide
Groove；
The clamping slot of the buckle can be accommodated by being offered on described clamping block；
Described locking member has the press section extended to outside cavity.
8. according to the multi-rotor unmanned aerial vehicle described in claim 5 to 7 any claim, it is characterised in that：
Described support bar vertically has outside angle in holding state, and its bottom is provided with a bottom surface as inclined-plane
Cushion block, a wedge for keeping the angle is provided between the retainer ring and the mounting blocks.
9. multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：
Chassis that described GPS supports include being fixed on the fuselage upper casing, the pole that is vertically set on the chassis with
And it is installed on the pole top and the mounting disc for installing GPS navigation device；
The chassis is diametrically offering the mounting groove for installing the pole；
For the pole to be up-narrow and down-wide trapezoidal, bottom has the mounting bar being fixed in the mounting groove, and top, which is provided with, to be used for
The screwed hole of the mounting disc is installed, and the pole is provided with to mitigate some hollow outs of own wt；
The bottom of the mounting disc is provided with boss, and fixing groove is provided with boss, and bottom land offers corresponding with the screwed hole logical
Hole.
10. multi-rotor unmanned aerial vehicle according to claim 9, it is characterised in that：
Described chassis is provided with some for fixing and adjusting the arcuate socket in itself direction；
The step for being easily installed screw is provided with the arcuate socket；
The middle part of the mounting groove is provided with the positioning hole with raised rotary shaft contraposition on fuselage, and both ends, which are provided with, fastens the mounting bar
Screwed hole；
The edge of the mounting disc is provided with the surrounding edge for being used for installing and protect GPS navigation device, is offered on the surrounding edge for leading to line
Breach.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720789399.5U CN206914622U (en) | 2017-06-30 | 2017-06-30 | A kind of folding multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720789399.5U CN206914622U (en) | 2017-06-30 | 2017-06-30 | A kind of folding multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206914622U true CN206914622U (en) | 2018-01-23 |
Family
ID=61335429
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720789399.5U Expired - Fee Related CN206914622U (en) | 2017-06-30 | 2017-06-30 | A kind of folding multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206914622U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107336826A (en) * | 2017-06-30 | 2017-11-10 | 浙江大学 | A kind of collapsible unmanned plane of more rotors |
-
2017
- 2017-06-30 CN CN201720789399.5U patent/CN206914622U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107336826A (en) * | 2017-06-30 | 2017-11-10 | 浙江大学 | A kind of collapsible unmanned plane of more rotors |
| CN107336826B (en) * | 2017-06-30 | 2023-08-15 | 浙江大学 | Many rotor folding unmanned aerial vehicle |
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