CN107161320A - Multi-rotor unmanned aerial vehicle horn contracting mechanism - Google Patents
Multi-rotor unmanned aerial vehicle horn contracting mechanism Download PDFInfo
- Publication number
- CN107161320A CN107161320A CN201710295317.6A CN201710295317A CN107161320A CN 107161320 A CN107161320 A CN 107161320A CN 201710295317 A CN201710295317 A CN 201710295317A CN 107161320 A CN107161320 A CN 107161320A
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- CN
- China
- Prior art keywords
- sleeve
- plug
- aerial vehicle
- unmanned aerial
- contracting mechanism
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- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Abstract
The invention discloses a kind of multi-rotor unmanned aerial vehicle horn contracting mechanism, including：First connector, including the first sleeve and the first plug；Second connector, including second sleeve, the second plug and rotating shaft；And 3rd sleeve, under closure connection status, the outer baffle block baffle of second sleeve is on the inside of the internal stop of 3rd sleeve, and the internal thread of 3rd sleeve is connected with the external screw thread of the first sleeve, and the first plug and the second plug are plugged in together.Because the first sleeve and second sleeve are linked together by rotating shaft, and rotating shaft is moveably mounted in slotted eye so that the first sleeve and second sleeve can realize plug simultaneously and fold two kinds of contraction modes, facilitate the expansion and recovery of contracting mechanism；3rd sleeve by internal stop and internal thread respectively with the external screw thread of the first sleeve and outer baffle block of second sleeve is spacing is fixedly connected so that contracting mechanism locking is fastened, and can be realized and be accurately positioned.
Description
Technical field
The present invention relates to unmanned plane equipment technical field, and in particular to a kind of multi-rotor unmanned aerial vehicle horn contracting mechanism.
Background technology
Multi-rotor unmanned aerial vehicle is a kind of rotary wing aircraft having more than two rotor shafts.By the motor of each shaft end
Rotate, drive rotor to produce lifting power.The angle fixation of rotor is variable like that rather than helicopter.By changing not
The moment of torsion of propulsive force can be changed with the relative velocity between rotor, so as to control the running orbit of aircraft.Due to many rotors
Fairly simple stabilization, currently practiced Multi-axis aircraft external form is much smaller with respect to for aircraft, thus be adapted to the sparetime use.Because
Multi-axis aircraft easy to manufacture and control, so being commonly used to make model and remotely-piloted vehicle.It common are four axles, six axles, eight
Axle aircraft.Its small volume, lightweight therefore easy to carry, the various adverse circumstances that can be not easily accessible easily into people.Hair
By now, Multi-axis aircraft can perform the aerial missions such as film of taking photo by plane is found a view, monitored in real time, landform is explored for exhibition.
With the development of multi-rotor unmanned aerial vehicle, the application field of multi-rotor unmanned aerial vehicle is more and more wider, the size of unmanned plane
It is stepped up, in order to facilitate the storage and transport of multi-rotor unmanned aerial vehicle, the horn of part unmanned plane is designed to available plug
Mode dismantle, or with fold mode compress overall dimensions.
Multi-rotor unmanned aerial vehicle horn, which shrinks mode, in the prior art mainly two kinds of contraction modes of folding and plug, two kinds of receipts
Concrete structure and the advantage and disadvantage such as following table of contracting mode：
As can be seen from the above table, the contraction mode of multi-rotor unmanned aerial vehicle horn in the prior art, no matter folding mode or
Pluggable mode has shortcoming.
The content of the invention
The application provides a kind of convenient expansion and the multi-rotor unmanned aerial vehicle horn of recovery, locking fastening and registration shrinks
Mechanism.
A kind of multi-rotor unmanned aerial vehicle horn contracting mechanism is provided in a kind of embodiment, including：
First connector, including the first sleeve and the first plug, one end of the first sleeve is for connecting with unmanned aerial vehicle body
The fixing end connect, the other end is plug folded end, and the plug folded end of the first sleeve is provided with mounting groove, and the both sides of mounting groove are also set
There is axial slotted eye；First plug be arranged on the first sleeve in, and the first plug connection end be located at the first sleeve plug
In folded end；
Second connector, including second sleeve, the second plug and rotating shaft, one end of second sleeve be for unmanned plane machine
The fixing end of arm connection, the other end is plug folded end, and the external diameter of the plug folded end of second sleeve is equal to less than the first sleeve
Plug folded end internal diameter, second sleeve plug folded end be provided with the axial raised mounting blocks with connecting hole, installation
Block is fastened in the mounting groove of the first sleeve, and rotating shaft is located in the connecting hole of mounting blocks, and is movably located in mounting groove
In the slotted eye of both sides；Second plug be arranged on second sleeve in, and the second plug connection end be located at second sleeve plug
In folded end；
And 3rd sleeve, in closure connection status, the 3rd sleeve is set in first sleeve and second sleeve
Splicing position, the two ends of the 3rd sleeve respectively with first sleeve and second sleeve is spacing is fixed together.
Further, the first sleeve and the plug folded end of second sleeve are equipped with the company of the T-shaped structure of axial cross section
Socket part, connecting portion is made up of transverse slat and stringer board, and mounting groove and slotted eye are arranged on the stringer board of connecting portion, and mounting blocks are raised in connection
The stringer board in portion.
Further, the transverse slat lateral surface of the connecting portion of second sleeve is arranged for the inclined plane being fastenedly connected.
Further, the first sleeve is additionally provided with external screw thread, and the external peripheral surface of the first sleeve is provided with raised outer baffle block, the
Three sleeve its one end inner surfaces are provided with internal thread provided with raised internal stop, the other end；Under closure connection status, second sleeve
Outer baffle block baffle on the inside of the internal stop of 3rd sleeve, the internal thread of 3rd sleeve is connected with the external screw thread of the first sleeve,
One plug and the second plug are plugged in together.
Further, the first connector also includes the first plate, and the first plug is fixed on the first sleeve by the first plate
Interior, the second connector also includes the second plate, and the second plug is fixed in second sleeve by the second plate.
Further, the first plate and the second plate are nylon plate.
Further, the first plug is female banana plug, and the second plug is public banana plug.
Further, outer baffle block and internal stop are collar stop.
Further, the first sleeve, second sleeve, 3rd sleeve, the first plug and the second plug are metal material.
Further, the first sleeve, second sleeve and 3rd sleeve are aluminum alloy material, and the first plug and the second plug are
Copper material.
Further, the fixing end of the first sleeve and second sleeve is equipped with mounting hole.
According to the multi-rotor unmanned aerial vehicle horn contracting mechanism of above-described embodiment, because the first sleeve and second sleeve are by turning
Axle is linked together, and rotating shaft is moveably mounted in slotted eye so that the first sleeve and second sleeve can be realized simultaneously
Two kinds of contraction modes of plug and folding, facilitate the expansion and recovery of contracting mechanism；3rd sleeve passes through internal stop and internal thread
Respectively with the external screw thread of the first sleeve and outer baffle block of second sleeve is spacing is fixedly connected so that contracting mechanism locking is fastened, and
And can realize and be accurately positioned.
Brief description of the drawings
Fig. 1 is the structural representation of the open mode of multi-rotor unmanned aerial vehicle horn contracting mechanism；
Fig. 2 is the structural representation of the closure state of multi-rotor unmanned aerial vehicle horn contracting mechanism；
Fig. 3 is the side structure schematic view of the open mode of multi-rotor unmanned aerial vehicle horn contracting mechanism；
Fig. 4 is the sectional view of the open mode of multi-rotor unmanned aerial vehicle horn contracting mechanism.
Embodiment
The present invention is described in further detail below by embodiment combination accompanying drawing.
A kind of multi-rotor unmanned aerial vehicle horn contracting mechanism is provided in the present embodiment, and this contracting mechanism is used for unmanned plane
Horn be arranged on fuselage so that when without flight, horn can shrink stored collapsed, save parking space, convenient
Carry.The contracting mechanism of the present embodiment can be also arranged in other equipment, realize the contraction storage of other equipment.
As shown in Figure 1, Figure 2 and Figure 3, the multi-rotor unmanned aerial vehicle horn contracting mechanism of the present embodiment mainly includes the first connection
Part 1, the second connector 2 and 3rd sleeve 3.First connector 1 is arranged on unmanned aerial vehicle body, and the second connector is arranged on nobody
On machine horn, the first connector 1 and the second connector 2 are plug and folding connection, and 3rd sleeve 3 is used for the first connector 1
It is fixed together with the second connector 2.In other embodiments, the first connector 1 can be also arranged on unmanned plane horn,
Second connector 2 is arranged on the fuselage of unmanned plane.
Specifically, the first connector 1 includes the first sleeve 11, the first plug 12 and the first plate 13 in the present embodiment.The
One end of one sleeve 11 is fixing end, and mounting hole is provided with fixing end, and the first sleeve 11 is installed by the mounting hole of fixing end
On unmanned aerial vehicle body.The other end of first sleeve 11 is the plug folded end for being connected with second sleeve 21, the first sleeve
11 plug folded end is provided with the connecting portion of the T-shaped structure of axial cross section, and T-shaped connecting portion is made up of transverse slat and stringer board, transverse slat
Together with being enclosed with the circumferential wall of the first sleeve 11, stringer board, which is used to fold, to be installed, and mounting groove 111 is provided with the centre of stringer board,
Slotted eye 112 of the both sides of mounting groove 111 provided with symmetrical axial direction.The external peripheral surface of first sleeve 11 is provided with external screw thread 113.
First plug 12 is arranged in the first sleeve 11 by the first plate 13, and the first plug 12 is used to insert with second
The connection ends of first 22 connection are located in the plug folded end of the first sleeve 11, the first plug 12 have in array several, the
One plate 13 is inlayed in the first sleeve 11.
Second connector 2 includes second sleeve 21, the second plug 22, the second plate 23 and rotating shaft 24.Second sleeve 21
One end is fixing end, and mounting hole is provided with fixing end, and second sleeve 21 is arranged on unmanned plane machine by the mounting hole of fixing end
On arm.The other end of second sleeve 21 is the plug folded end for being connected with the first sleeve 11, the plug folding of second sleeve 21
Folded end is again provided with the connecting portion of the T-shaped structure of axial cross section, and T-shaped connecting portion is made up of transverse slat and stringer board, transverse slat and second
The circumferential wall of sleeve 21 is enclosed together, and stringer board, which is used to fold, to be installed, and the external diameter of the plug folded end of second sleeve 21 is equal to or omited
Less than the internal diameter that the first sleeve 11 plugs folded end, second sleeve 21 is as male end, and the first sleeve 11 is female end, during connection, the
The plug folded end of two sleeves 21 is inserted into the plug folded end of the first sleeve 11.The T-shaped connecting portion of second sleeve 21 it is vertical
Plate is provided with connecting hole provided with axially raised mounting blocks 211, mounting blocks 211.As shown in figures 1 and 3, mounting blocks
211 are connected in the mounting groove 111 of the first sleeve 11, and mounting blocks 211 are located in the connecting hole of mounting blocks 211 by rotating shaft 24
Interior, the two ends of rotating shaft 24 are movably located in the slotted eye 112 of the first sleeve 11, and rotating shaft 24 is by the first sleeve 11 and second sleeve
21 removable plugs and linking together of turning folding.Outer baffle block 212 of the external peripheral surface of second sleeve 21 provided with projection,
Outer baffle block 212 is the baffle plate of loop configuration.
In order that must insert it is more close, by the transverse slat lateral surface 213 of the T-shaped connecting portion of second sleeve 21 be arranged to tilt
Face.It is preferred that, as shown in figure 4, the top half of lateral surface 213 is arranged to inclined plane, inclined plane tilts 1 ° vertically, and inclined plane is certainly
Upper and lower continuous increase, the distance of the latter half of lateral surface 213 to center is arrived slightly larger than the correspondence position inner surface of the first sleeve 11
The distance at center, equivalent to one chamfering of inclined plane, for guiding inserting to coordinate, so that second sleeve 21 can be inserted closely
It is attached in the first sleeve 11.
Second plug 22 is arranged in second sleeve 21 by the second plate 23, and the second plug 22 is used to insert with first
The connection end of first 12 connection is located in the plug folded end of second sleeve 21, the quantity of the second plug 22 and position and the first plug
21 is corresponding, and the second plate 23 is inlayed in second sleeve 21.
As shown in figure 4, the first sleeve 11 is equal with the external diameter and internal diameter of second sleeve 21, the internal diameter of 3rd sleeve 3 is more than
The external diameter of first sleeve 11 and second sleeve 21.One end inner surface of 3rd sleeve 3 is provided with internal stop 31, and internal stop 31 is annular
The baffle plate of structure, the external diameter of internal stop 31 is more than the external diameter of the outer baffle block 212 of second sleeve 21 so that outer baffle block 212 can baffle
Firmly internal stop 31, the axial movement of spacing 3rd sleeve 3.The other end inner surface of 3rd sleeve 3 is provided with internal thread 32, internal thread 32
It is adapted with the external screw thread 113 of the first sleeve 11.
As shown in Fig. 2 contracting mechanism is closed again under connection status, 3rd sleeve 3 is enclosed on the first sleeve 11 and second sleeve
21 splicing position, the internal stop 31 of the one end of 3rd sleeve 3 is together with the baffle of outer baffle block 212 of second sleeve 21,3rd sleeve 3
The external screw thread 113 of the internal thread 32 of the other end and the first sleeve 11 links together, so that 3rd sleeve 3 is by the He of the first sleeve 11
Second sleeve 21 is fixed together.When unmanned plane does not perform aerial mission, 3rd sleeve 3 is turned on and exits the first sleeve
11 and the splicing position of second sleeve 21, then second sleeve 21 is extracted out of first sleeve 11, finally rotary folding again, completes to receive
Contracting is folded, as shown in figure 1, now contracting mechanism is in open mode, it is necessary in use, by opposite step by the first sleeve
11 and second sleeve 21 be fixed together.In other embodiments, 3rd sleeve 3 also can be removable by buckle or alignment pin
That unloads is fixed together the first sleeve 11 and second sleeve 21.
The present embodiment is preferred, and the first plug 12 and the second plug 22 are as electrical fitting, for UNICOM's fuselage and machine
Circuit between arm.First plug 12 is female banana plug, and the second plug 22 is public banana plug, is closed under connection status, the
Two plugs 22 are inserted into the first plug 21 and linked together.First plate 13 and the second plate 23 are inserting for nylon material
Plate, installation the first plug 12 and the second plug 22 that can be consolidated, and play a part of insulation.First sleeve 11, second set
Cylinder 21 and 3rd sleeve 3 are the aluminum alloy material of thin-walled, and the first plug 12 and the second plug 22 are copper material, in other realities
Apply in example, the first sleeve 11, second sleeve 21,3rd sleeve 3, the first plug 12 and the second plug 22 can be other metal materials
Matter.
The multi-rotor unmanned aerial vehicle horn contracting mechanism that the present embodiment is provided, by rotating shaft 24 and the combination of slotted eye 112, is realized
The folding of contracting mechanism and the selection for plugging two kinds of functions.When rotating shaft 24 is installed, mechanism can run through " rotation-insert
Enter-go up thread bush " three rapid lockings of step, realize the rapid deployment of unmanned plane horn.When not installing rotating shaft, the 3rd is opened
Sleeve 3 just can extract second sleeve 21 completely from the first sleeve 11, realize the separation of unmanned plane horn and fuselage, convenient
Storage and transport.
First sleeve 21 and second sleeve 22 are fixed together by 3rd sleeve 3 by internal thread 32 and internal stop 31,
Double sleeve load-carrying construction are formed after contracting mechanism locking, make whole mechanism that there is good intensity and rigidity.First sleeve 11,
Two sleeves 21 and 3rd sleeve 3 use thin-wall construction mode, greatly alleviate pts wt.By experiment, in equal chi
Under very little and weights, this contracting mechanism static strength is 7 times of similar engineering plastics mechanism.
First sleeve 11 and the tight fit of second sleeve 21 are realized by the inclined plane of fastening, make motor mounting surface accurate
On the design and installation face of being positioned at, prevent to loosen the generation of phenomenon.
By the first of nylon plug 13 and second plate 23 position the first plug 12 and the second plug 22, banana hair style the
The application of one plug 12 and the second plug 22 realizes circuit and disconnects or connect with the dismounting of contracting mechanism.
Use above specific case is illustrated to the present invention, is only intended to help and is understood the present invention, not to limit
The system present invention.For those skilled in the art, according to the thought of the present invention, it can also make some simple
Deduce, deform or replace.
Claims (10)
1. a kind of multi-rotor unmanned aerial vehicle horn contracting mechanism, it is characterised in that including：
First connector, including the first sleeve and the first plug, one end of first sleeve is for connecting with unmanned aerial vehicle body
The fixing end connect, the other end is plug folded end, and the plug folded end of first sleeve is provided with mounting groove, the mounting groove
Both sides are additionally provided with axial slotted eye；First plug is arranged in first sleeve, and the connection of first plug
End is in the plug folded end of first sleeve；
Second connector, including second sleeve, the second plug and rotating shaft, one end of the second sleeve be for unmanned plane machine
The fixing end of arm connection, the other end is plug folded end, and the external diameter of the plug folded end of the second sleeve is equal to less than described
The internal diameter of the plug folded end of first sleeve, the plug folded end of the second sleeve is provided with axial raised with connecting hole
Mounting blocks, the mounting blocks are fastened in the mounting groove of first sleeve, and the rotating shaft is located in the connection of the mounting blocks
In hole, and movably it is located in the slotted eye of the mounting groove both sides；Second plug is arranged in the second sleeve,
And the connection end of second plug is located in the plug folded end of the second sleeve；
And 3rd sleeve, in closure connection status, the 3rd sleeve is set in inserting for first sleeve and second sleeve
Meet place, the two ends of the 3rd sleeve respectively with first sleeve and second sleeve is spacing is fixed together.
2. multi-rotor unmanned aerial vehicle horn contracting mechanism as claimed in claim 1, it is characterised in that first sleeve and second
The plug folded end of sleeve is equipped with the connecting portion of the T-shaped structure of axial cross section, and the connecting portion is made up of transverse slat and stringer board,
The mounting groove and slotted eye are arranged on the stringer board of the connecting portion, and the mounting blocks are raised in the stringer board of the connecting portion.
3. multi-rotor unmanned aerial vehicle horn contracting mechanism as claimed in claim 2, it is characterised in that the connection of the second sleeve
The transverse slat lateral surface in portion is arranged for the inclined plane being fastenedly connected.
4. multi-rotor unmanned aerial vehicle horn contracting mechanism as claimed in claim 1, it is characterised in that first sleeve is additionally provided with
External screw thread, the external peripheral surface of first sleeve is provided with raised outer baffle block, and the 3rd sleeve its one end inner surface is provided with
Raised internal stop, the other end is provided with internal thread；Under closure connection status, the outer baffle block baffle of the second sleeve is described
On the inside of the internal stop of 3rd sleeve, the internal thread of the 3rd sleeve is connected with the external screw thread of first sleeve, and described first
Plug and the second plug are plugged in together.
5. multi-rotor unmanned aerial vehicle horn contracting mechanism as claimed in claim 1, it is characterised in that first connector is also wrapped
The first plate is included, first plug is fixed in first sleeve by first plate, and second connector is also
Including the second plate, second plug is fixed in the second sleeve by second plate.
6. multi-rotor unmanned aerial vehicle horn contracting mechanism as claimed in claim 4, it is characterised in that first plate and second
Plate is nylon plate.
7. multi-rotor unmanned aerial vehicle horn contracting mechanism as claimed in claim 1, it is characterised in that first plug is female fragrant
Any of several broadleaf plants plug, second plug is public banana plug.
8. multi-rotor unmanned aerial vehicle horn contracting mechanism as claimed in claim 1, it is characterised in that the outer baffle block and internal stop
It is collar stop.
9. multi-rotor unmanned aerial vehicle horn contracting mechanism as claimed in claim 1, it is characterised in that first sleeve, second
Sleeve and 3rd sleeve are aluminum alloy material, and first plug and the second plug are copper material.
10. multi-rotor unmanned aerial vehicle horn contracting mechanism as claimed in claim 1, it is characterised in that first sleeve and
The fixing end of two sleeves is equipped with mounting hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710295317.6A CN107161320A (en) | 2017-04-28 | 2017-04-28 | Multi-rotor unmanned aerial vehicle horn contracting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710295317.6A CN107161320A (en) | 2017-04-28 | 2017-04-28 | Multi-rotor unmanned aerial vehicle horn contracting mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107161320A true CN107161320A (en) | 2017-09-15 |
Family
ID=59812434
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710295317.6A Pending CN107161320A (en) | 2017-04-28 | 2017-04-28 | Multi-rotor unmanned aerial vehicle horn contracting mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107161320A (en) |
Cited By (11)
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| CN107600385A (en) * | 2017-10-18 | 2018-01-19 | 沈阳旋飞航空技术有限公司 | The cantilever fold mechanism of electronic unmanned plane |
| CN107628226A (en) * | 2017-09-25 | 2018-01-26 | 安徽瓦尔特机械贸易有限公司 | The attachment structure of rotor wing unmanned aerial vehicle horn and fuselage |
| CN107672784A (en) * | 2017-11-08 | 2018-02-09 | 沈阳旋飞航空技术有限公司 | The support bar quick-disassembly structure of the dynamic unmanned plane of oil |
| CN107867389A (en) * | 2017-11-08 | 2018-04-03 | 安徽梦之翼无人机科技有限公司 | A kind of plant protection unmanned plane horn structure |
| CN108177759A (en) * | 2017-12-28 | 2018-06-19 | 王开富 | A kind of unmanned plane horn fold mechanism with locking function |
| CN108945391A (en) * | 2018-09-21 | 2018-12-07 | 深圳市翔农创新科技有限公司 | A kind of horn foldable assembly and unmanned plane |
| CN109070990A (en) * | 2017-12-28 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Horn component and unmanned plane |
| CN109278980A (en) * | 2018-11-16 | 2019-01-29 | 华东理工大学 | Unmanned plane horn wide-angle fold mechanism |
| CN109747825A (en) * | 2019-01-22 | 2019-05-14 | 深圳市飞米机器人科技有限公司 | Aircraft |
| CN110325439A (en) * | 2018-07-11 | 2019-10-11 | 深圳市大疆创新科技有限公司 | Folding retractable mechanism, propeller protective device and rotor wing unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107600385A (en) * | 2017-10-18 | 2018-01-19 | 沈阳旋飞航空技术有限公司 | The cantilever fold mechanism of electronic unmanned plane |
| CN107672784A (en) * | 2017-11-08 | 2018-02-09 | 沈阳旋飞航空技术有限公司 | The support bar quick-disassembly structure of the dynamic unmanned plane of oil |
| CN107867389A (en) * | 2017-11-08 | 2018-04-03 | 安徽梦之翼无人机科技有限公司 | A kind of plant protection unmanned plane horn structure |
| CN108177759A (en) * | 2017-12-28 | 2018-06-19 | 王开富 | A kind of unmanned plane horn fold mechanism with locking function |
| CN109070990A (en) * | 2017-12-28 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Horn component and unmanned plane |
| WO2019127217A1 (en) * | 2017-12-28 | 2019-07-04 | 深圳市大疆创新科技有限公司 | Arm assembly and unmanned aerial vehicle |
| CN110325439A (en) * | 2018-07-11 | 2019-10-11 | 深圳市大疆创新科技有限公司 | Folding retractable mechanism, propeller protective device and rotor wing unmanned aerial vehicle |
| WO2020010539A1 (en) * | 2018-07-11 | 2020-01-16 | 深圳市大疆创新科技有限公司 | Folding telescopic mechanism, propeller protection device and rotor unmanned aerial vehicle |
| WO2020057115A1 (en) * | 2018-09-21 | 2020-03-26 | 深圳市翔农创新科技有限公司 | Arm folding assembly and unmanned aerial vehicle |
| CN108945391B (en) * | 2018-09-21 | 2020-04-03 | 深圳市翔农创新科技有限公司 | Arm folding assembly and unmanned aerial vehicle |
| CN108945391A (en) * | 2018-09-21 | 2018-12-07 | 深圳市翔农创新科技有限公司 | A kind of horn foldable assembly and unmanned plane |
| CN109278980A (en) * | 2018-11-16 | 2019-01-29 | 华东理工大学 | Unmanned plane horn wide-angle fold mechanism |
| CN109278980B (en) * | 2018-11-16 | 2022-01-28 | 华东理工大学 | Large-angle folding mechanism for unmanned aerial vehicle arm |
| CN109747825A (en) * | 2019-01-22 | 2019-05-14 | 深圳市飞米机器人科技有限公司 | Aircraft |
| CN109747825B (en) * | 2019-01-22 | 2022-01-18 | 深圳市飞米机器人科技有限公司 | Aircraft with a flight control device |
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