CN108100244A - A kind of dismountable multi-rotor unmanned aerial vehicle - Google Patents
A kind of dismountable multi-rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN108100244A CN108100244A CN201711393304.9A CN201711393304A CN108100244A CN 108100244 A CN108100244 A CN 108100244A CN 201711393304 A CN201711393304 A CN 201711393304A CN 108100244 A CN108100244 A CN 108100244A
- Authority
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- China
- Prior art keywords
- structural slab
- component
- guard circle
- rotor
- structure plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000463 material Substances 0.000 claims description 16
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 9
- 239000004917 carbon fiber Substances 0.000 claims description 9
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical group C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 9
- 229920006231 aramid fiber Polymers 0.000 claims description 8
- 230000001413 cellular effect Effects 0.000 claims description 8
- 230000001681 protective effect Effects 0.000 claims description 5
- 238000012423 maintenance Methods 0.000 abstract description 7
- 238000000034 method Methods 0.000 abstract description 2
- 239000003822 epoxy resin Substances 0.000 description 4
- 239000003292 glue Substances 0.000 description 4
- 229920000647 polyepoxide Polymers 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 230000037396 body weight Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 238000011065 in-situ storage Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229920006351 engineering plastic Polymers 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to unmanned air vehicle technique field more particularly to a kind of dismountable multi-rotor unmanned aerial vehicles.It includes：Unmanned plane body；Multiple structural slab components, the inner end of the structural slab component are connected with the edge of the unmanned plane body；Multiple rotors protect component; each rotor protection component includes guard circle and multiple support arms in guard circle; the first end of each support arm is connected with the edge of guard circle; the second end of each support arm is connected to each other to install the installed part of rotor, and the guard circle is removably connected within two neighboring structural slab component.The present invention is connected by structural slab component with unmanned plane body, and instead of traditional rod-type horn structure, structure is simpler, and volume further reduces；Rotor protects component and structural slab component detachably connected so that the unmanned plane can be disassembled and installed quickly, reduce transportation cost and dismounting and maintenance difficulty.
Description
Technical field
The present invention relates to unmanned air vehicle technique field more particularly to a kind of dismountable multi-rotor unmanned aerial vehicles.
Background technology
The cabinet size of medium-and-large-sized unmanned plane is larger, and horn is longer and can not dismantle, transport and shift it is more not convenient, even if
It is that traditional foldable horn can not still effectively reduce volume, and maintenance cost is higher when breaking down.
In addition, the main material of unmanned plane body on the market is carbon fiber or engineering plastics at present, to meet nothing simultaneously
Man-machine rigidity, the intensity of unmanned plane structure are generally interference, cause overall structure weight larger.
The content of the invention
(1) technical problems to be solved
The present invention is to solve the problem of existing unmanned plane transport and dismounting, maintenance inconvenience.
(2) technical solution
In order to solve the above technical problem, the present invention provides a kind of dismountable multi-rotor unmanned aerial vehicle, including：
Unmanned plane body；
Multiple structural slab components, the inner end of the structural slab component are connected with the edge of the unmanned plane body；
Multiple rotors protect components, and each rotor protection component includes guard circle and multiple is located in guard circle
Support arm, the edge of the first end of each support arm with the guard circle are connected, and the second of each support arm
End is connected to each other to install the installed part of rotor, the guard circle be removably connected to two neighboring structural slab component it
It is interior.
Further, the material of the structural slab component, guard circle and support arm is carbon fiber aramid fiber cellular material, institute
Carbon fiber aramid fiber cellular material is stated as current material.
Further, two adjacent structural slab components are respectively first structure plate component and the second structural slab group
Part, the guard circle are respectively first segment and second segment for the part of the clamping, the first structure plate component and second
The outer end of structural slab component offers left buckling groove and right buckling groove, and the first segment of the guard circle is removably connected in
In the left buckling groove of one structural slab component, the second segment of the guard circle is removably connected in the right card of the second structural slab component
In access slot.
Further, the first structure plate component is included on be connected respectively with the unmanned plane body edges first
Structural slab and the first lower structure plate, there are the first interval between structural slab and the first lower structure plate on described first, and described
Structural slab, the first interval and the first lower structure plate together constitute the left buckling groove of the first structure plate component and right card on one
Access slot；
The second structural slab component include be connected respectively with the unmanned plane body edges second on structural slab and
Second lower structure plate, there are the second interval between structural slab and the second lower structure plate on described second, and structure on described second
Plate, the second interval and the second lower structure plate together constitute the left buckling groove of the second structural slab component and right buckling groove.
Further, the multi-rotor unmanned aerial vehicle further includes the first fastener and the second fastener, first fastener
Structural slab, the first segment of guard circle and the first lower structure plate on described first are sequentially connected, second fastener is by described in
Structural slab, the second segment of guard circle and the second lower structure plate are sequentially connected on second.
Preferably, first fastener and the second fastener are screw.
Further, the structural slab component offer up/down perforation perforation or the structural slab component it is hollow, by
This alleviates the weight of structural slab component.
Further, the installed part is located at the center of the guard circle, and the installed part is equipped with mounting hole, described
Rotor is removably installed in the mounting hole.
Further, the thickness of the structural slab component is 4~4.5mm, and the thickness of the guard circle is 12~13mm, institute
The thickness for stating support arm is 12~13mm.The thickness data is smaller so that the weight of unmanned plane entirety is further subtracted
Gently.
Further, between guard circle there is interval in two wing tips of the rotor, to prevent spin-ended wing rotary course
In touch guard circle.
Further, the bottom of the installed part is sequentially connected the motor that is useful for driving the rotor wing rotation and for pacifying
Fill the motor cabinet of the motor.
Preferably, the motor periphery is equipped with electric motor protecting circle, to be protected to the motor.Preferably, the peace
The bottom of piece installing passes sequentially through motor and motor cabinet described in epoxy resin glue sticking.
Preferably, the first end of the support arm passes through epoxide-resin glue and the marginal adhesion of guard circle.
Further, the top of the unmanned plane body is equipped with protective cover to be protected to unmanned plane body, and bottom is set
There is remote control operation of landing gear, during unmanned plane during flying, by being remotely controlled the folding and unfolding of operation of landing gear described in remote control control, with
Reduce flight resistance.
Preferably, the rotor protection component is six, and each guard circle is in contact with each other；Correspondingly, the rotation
There are six the wing is common.
Preferably, each guard circle is in contact with each other.
(3) advantageous effect
The above-mentioned technical proposal of the present invention has the advantages that：
1st, unmanned plane of the invention, there is provided rotors to protect component, and passes through structural slab component and be connected with unmanned plane body
It connects, instead of traditional rod-type horn structure, structure is simpler, and whole volume further reduces；The rotor protection group
The guard circle of part is removably connected in structural slab component, so that rotor protection component and structural slab component are removably
Connection, so that the unmanned plane can be disassembled and installed quickly, reduces transportation cost and dismounting and maintenance difficulty, carries
High assembled in situ efficiency；Can be individually replaced when rotor protects component and structural slab component to damage, without to complete machine into
Row is repaired, and considerably reduces maintenance cost.
2nd, the present invention is provided with guard circle, and guard circle can be used as horn to conduct while rotor is protected not occur to beat paddle
Lift makes Fabric utilization higher.The present invention is provided with buckling groove between guard circle and the structural slab component of unmanned plane body,
And pass through the fasteners such as screw and can quickly and easily dismount, further improve installation effectiveness.
3rd, the material of structural slab component of the invention, guard circle and support arm is carbon fiber aramid fiber cellular material, on an equal basis
The weight of carbon fiber aramid fiber cellular material under volume is only the 30% of traditional carbon fibres plate, considerably reduces body weight,
So that unmanned plane cruising time is significantly promoted.
Description of the drawings
Fig. 1 is the structure diagram (being free of rotor) of multi-rotor unmanned aerial vehicle described in the embodiment of the present invention；
Fig. 2 is that the top view of multi-rotor unmanned aerial vehicle described in the embodiment of the present invention (schematically illustrates one of rotation
The wing)；
Fig. 3 is the side view of multi-rotor unmanned aerial vehicle described in the embodiment of the present invention；
Wherein, 1, guard circle；2nd, support arm；21st, the first end of support arm；22nd, the second end of support arm；3rd, electric motor protecting
Circle；4th, motor cabinet；5th, structural slab component；51st, structural slab on second；52nd, the second lower structure plate；53rd, perforate；54th, first structure
Plate component；55th, the second structural slab component；6th, protective cover；7th, it is remotely controlled operation of landing gear；8th, mounting hole；9th, carbide reservoir；10th, nobody
Machine body；12nd, installed part；13rd, mounting hole；14th, rotor；15th, left buckling groove；16th, right buckling groove；
Specific embodiment
Embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples.Following embodiment is used for
Illustrate the present invention, but cannot be used for limiting the scope of the invention.
In the description of the present invention, unless otherwise indicated, " multiple " are meant that two or more；Term " on ",
" under ", "left", "right", " interior ", " outer ", " front end ", " rear end ", " head ", the orientation of the instructions such as " afterbody " or position relationship be
Based on orientation shown in the drawings or position relationship, it is for only for ease of the description present invention and simplifies description rather than instruction or dark
Show that signified device or element there must be specific orientation, with specific azimuth configuration and operation, thus it is it is not intended that right
The limitation of the present invention.In addition, term " first ", " second ", " the 3rd " etc. be only used for description purpose, and it is not intended that instruction or
Imply relative importance.
In the description of the present invention, it is necessary to which explanation, unless otherwise clearly defined and limited, term " connected " " connects
Connect " it should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected or be integrally connected；It can be machine
Tool is connected or is electrically connected；It can be directly connected, can also be indirectly connected by intermediary.For this field
For those of ordinary skill, concrete condition can be regarded and understand the concrete meaning of above-mentioned term in the present invention.
As shown in FIG. 1 to 3, in order to solve the above technical problem, the present invention provides a kind of dismountable for the present embodiment
Multi-rotor unmanned aerial vehicle, including：10, six structural slab components 5 of unmanned plane body and six rotor protection components.
The inner end of structural slab component 5 is connected (being welding in the present embodiment) with the edge of unmanned plane body 10；Each rotation
Wing protection component includes the support arms 2 that guard circle 1 and three are located in guard circle 1, the first end 21 of each support arm with
The edge of guard circle 1 is connected, and (in the present embodiment, 21 top of first end of each support arm passes through epoxide-resin glue and guard circle
The bottom at 1 edge is connected), the second end 22 of each support arm is connected to each other to an installed part 12 (institute in the present embodiment
" being connected to each other " is stated to be integrally formed), installed part 12 is located at the center of guard circle 1, and installed part 12 is equipped with mounting hole 13, rotation
The wing 14 is removably installed in mounting hole 13, and wherein two sections of guard circle 1 are removably connected to two neighboring structure respectively
In the outer end of plate component 5；In the present embodiment, formed angle is 120 ° between three support arms 2.
Specifically, two adjacent structural slab components 5 are respectively first structure plate component 54 and the second structural slab component
55, wherein two sections of guard circle 1 are respectively first segment and second segment, first structure plate component 54 and the second structural slab component 55
Outer end offers left buckling groove 15 and right buckling groove 16, and the first segment of guard circle 1 is removably connected in first structure plate group
In the left buckling groove 15 of part 54, the second segment of guard circle 1 is removably connected in the right buckling groove 16 of the second structural slab component 55
It is interior.
Furthermore, first structure plate component 54 includes tying on 10 edge of unmanned plane body be connected respectively first
Structure plate and the first lower structure plate, there are the first interval between structural slab and the first lower structure plate on first, and the structure on first
Plate, the first interval and the first lower structure plate together constitute the left buckling groove 15 of first structure plate component 54 and right buckling groove 16；
Second structural slab component 55 includes 51 and second lower structure of structural slab on be connected respectively with 10 edge of unmanned plane body second
Plate 52, there are the second interval between 51 and second lower structure plate 52 of structural slab on second, and structural slab, second interval on second
The left buckling groove 15 of the second structural slab component 55 and right buckling groove 16 are together constituted with the second lower structure plate.
In the present embodiment, multi-rotor unmanned aerial vehicle further includes the first fastener and the second fastener, and first fastener leads to
Default mounting hole 8 is crossed on first structure plate component 54 by structural slab, the first segment of guard circle 1 and the first lower structure plate on first
It is sequentially connected；Equally, the second fastener by default mounting hole 8 on the second structural slab component 55 by structural slab on second 51,
The second segment of guard circle 1 and the second lower structure plate 52 are sequentially connected.Specifically, in the present embodiment, the first fastener and second
Fastener is screw.
Further, structural slab component 5 offer up/down perforation perforation 53 or the structural slab component 5 it is hollow, with
This mitigates the weight of structural slab component 5.Further to mitigate the weight of entire unmanned plane, structural slab component 5,1 and of guard circle
The material of support arm 2 is carbon fiber aramid fiber cellular material, which is current material；Structural slab component
5 thickness is 4mm, i.e., structural slab on first, the first lower structure plate, on second 51 and second lower structure plate 52 of structural slab thickness
It is 2mm, the thickness of guard circle 1 and support arm 2 is 12mm.
In the present embodiment, there is interval in two wing tips of rotor 14, rotated through to prevent the spin-ended wing 14 between guard circle 1
Guard circle 1 is touched in journey.The bottom of installed part 12 is bonded with to drive what rotor 14 rotated by epoxide-resin glue successively
Motor and the motor cabinet 4 for installing motor, and motor periphery is equipped with electric motor protecting circle 3, to be carried out to the motor
Protection.
In the present embodiment, the top of unmanned plane body 10 is equipped with protective cover 6 to be protected to unmanned plane body 10, bottom
Equipped with carbide reservoir 9 and two remote control operation of landing gear 7.Protective cover 6 is used to protect the winged control being arranged on unmanned plane body 10, GPS
Wait electronic equipments.During unmanned plane during flying, by being remotely controlled the folding and unfolding of operation of landing gear 7 described in remote control control, to reduce
Flight resistance.
In the present embodiment, rotor protection component is six, and each guard circle 1 is in contact with each other；Correspondingly, rotor 14 is also common
There are six.It should be noted that the rotor protection component of the present embodiment can be not limited to six, correspondingly, rotor 14 is also unlimited
In six.
The unmanned plane of the present embodiment, there is provided rotors to protect component, and passes through structural slab component and be connected with unmanned plane body
It connects, instead of traditional rod-type horn structure, structure is simpler, and whole volume further reduces；The rotor protection group
The guard circle of part is removably connected in structural slab component, so that rotor protection component and structural slab component are removably
Connection, so that the unmanned plane can be disassembled and installed quickly, reduces transportation cost and dismounting and maintenance difficulty, carries
High assembled in situ efficiency；Can be individually replaced when rotor protects component and structural slab component to damage, without to complete machine into
Row is repaired, and considerably reduces maintenance cost.
The present embodiment is provided with guard circle, and guard circle can be used as horn to conduct while rotor is protected not occur to beat paddle
Lift makes Fabric utilization higher.The present embodiment is provided with clamping between guard circle and the structural slab component of unmanned plane body
Slot, and pass through the fasteners such as screw and can quickly and easily dismount, further improve installation effectiveness.
The material of the structural slab component of the present embodiment, guard circle and support arm is carbon fiber aramid fiber cellular material, on an equal basis
The weight of carbon fiber aramid fiber cellular material under volume is only the 30% of traditional carbon fibres plate, considerably reduces body weight,
So that unmanned plane cruising time is significantly promoted.
The embodiment of the present invention provides for example and description, and is not exhaustively or by the present invention to limit
In disclosed form.Many modifications and variations are obvious for the ordinary skill in the art.Selection and
Description embodiment is to more preferably illustrate the principle of the present invention and practical application, and enables those of ordinary skill in the art
The present invention is understood so as to design the various embodiments with various modifications suitable for special-purpose.
Claims (10)
1. a kind of dismountable multi-rotor unmanned aerial vehicle, which is characterized in that including：
Unmanned plane body；
Multiple structural slab components, the inner end of the structural slab component are connected with the edge of the unmanned plane body；
Multiple rotors protect component, and each rotor protection component includes guard circle and multiple supports in guard circle
Arm, the edge of the first end of each support arm with the guard circle are connected, the second end of each support arm that
This connects into the installed part for installing rotor, and the guard circle is removably connected within two neighboring structural slab component.
2. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that the structural slab component, guard circle and support
The material of arm is carbon fiber aramid fiber cellular material.
3. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that adjacent two structural slab components difference
For first structure plate component and the second structural slab component, the guard circle is respectively first segment and for the part of the clamping
Two sections, the outer end of the first structure plate component and the second structural slab component offers left buckling groove and right buckling groove, described
The first segment of guard circle is removably connected in the left buckling groove of first structure plate component, and the second segment of the guard circle is removable
It is connected in unloading in the right buckling groove of the second structural slab component.
4. multi-rotor unmanned aerial vehicle according to claim 3, which is characterized in that the first structure plate component include respectively with
The unmanned plane body edges be connected first on structural slab and the first lower structure plate, on described first under structural slab and first
There are the first interval between structural slab, and structural slab, the first interval and the first lower structure plate together constitute institute on described first
State the left buckling groove of first structure plate component and right buckling groove；
The second structural slab component includes structural slab and second on be connected respectively with the unmanned plane body edges second
Lower structure plate, there are the second interval between structural slab and the second lower structure plate on described second, and structural slab, on described second
Two intervals and the second lower structure plate together constitute the left buckling groove of the second structural slab component and right buckling groove.
5. multi-rotor unmanned aerial vehicle according to claim 4, which is characterized in that further include the first fastener and the second fastening
Part, structural slab, the first segment of guard circle and the first lower structure plate on described first are sequentially connected by first fastener, described
Structural slab, the second segment of guard circle and the second lower structure plate on described second are sequentially connected by the second fastener.
6. according to Claims 1 to 5 any one of them multi-rotor unmanned aerial vehicle, which is characterized in that the structural slab component opens up
Perforation or the structural slab component for having up/down perforation are hollow.
7. according to Claims 1 to 5 any one of them multi-rotor unmanned aerial vehicle, which is characterized in that the installed part is located at described
The center of guard circle, and the installed part is equipped with mounting hole, the rotor is removably installed in the mounting hole.
8. according to Claims 1 to 5 any one of them multi-rotor unmanned aerial vehicle, which is characterized in that two wing tips of the rotor
There is interval between guard circle.
9. according to Claims 1 to 5 any one of them multi-rotor unmanned aerial vehicle, which is characterized in that the bottom of the installed part according to
The secondary motor for being connected with to drive the rotor wing rotation and the motor cabinet for installing the motor.
10. according to Claims 1 to 5 any one of them multi-rotor unmanned aerial vehicle, which is characterized in that the top of the unmanned plane body
Portion is equipped with protective cover, and bottom is equipped with remote control operation of landing gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711393304.9A CN108100244A (en) | 2017-12-19 | 2017-12-19 | A kind of dismountable multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711393304.9A CN108100244A (en) | 2017-12-19 | 2017-12-19 | A kind of dismountable multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108100244A true CN108100244A (en) | 2018-06-01 |
Family
ID=62211580
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711393304.9A Pending CN108100244A (en) | 2017-12-19 | 2017-12-19 | A kind of dismountable multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN108100244A (en) |
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| US20150321755A1 (en) * | 2014-04-28 | 2015-11-12 | Arch Aerial, Llc | Collapsible multi-rotor uav |
| CN105366045A (en) * | 2015-12-17 | 2016-03-02 | 湖南云顶智能科技有限公司 | Multi-rotor-wing unmanned aerial vehicle |
| CN106005361A (en) * | 2016-04-07 | 2016-10-12 | 珠海市磐石电子科技有限公司 | Aviation power unit and flight frame and modularization aircraft thereof |
| US20170113800A1 (en) * | 2015-10-23 | 2017-04-27 | Roger Freeman | Unmanned aerial vehicle protective frame configuration |
| CN206231612U (en) * | 2016-12-06 | 2017-06-09 | 中南大学 | A kind of cellular module and the honeycomb fashion multi-rotor aerocraft using the module |
| CN207658048U (en) * | 2017-12-19 | 2018-07-27 | 东汉太阳能无人机技术有限公司 | A kind of dismountable multi-rotor unmanned aerial vehicle |
-
2017
- 2017-12-19 CN CN201711393304.9A patent/CN108100244A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150321755A1 (en) * | 2014-04-28 | 2015-11-12 | Arch Aerial, Llc | Collapsible multi-rotor uav |
| CN104986331A (en) * | 2015-07-27 | 2015-10-21 | 致导科技（北京）有限公司 | Unmanned aerial vehicle rotor wing protection frame and unmanned aerial vehicle |
| US20170113800A1 (en) * | 2015-10-23 | 2017-04-27 | Roger Freeman | Unmanned aerial vehicle protective frame configuration |
| CN105366045A (en) * | 2015-12-17 | 2016-03-02 | 湖南云顶智能科技有限公司 | Multi-rotor-wing unmanned aerial vehicle |
| CN106005361A (en) * | 2016-04-07 | 2016-10-12 | 珠海市磐石电子科技有限公司 | Aviation power unit and flight frame and modularization aircraft thereof |
| CN206231612U (en) * | 2016-12-06 | 2017-06-09 | 中南大学 | A kind of cellular module and the honeycomb fashion multi-rotor aerocraft using the module |
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Application publication date: 20180601 |