CN208181396U - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
- Publication number
- CN208181396U CN208181396U CN201820594040.7U CN201820594040U CN208181396U CN 208181396 U CN208181396 U CN 208181396U CN 201820594040 U CN201820594040 U CN 201820594040U CN 208181396 U CN208181396 U CN 208181396U
- Authority
- CN
- China
- Prior art keywords
- hatchcover
- unmanned plane
- fuselage
- liner plate
- plane according
- 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.)
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Classifications
-
- 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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
Abstract
A kind of unmanned plane (100), including fuselage (10), the fuselage (10) is equipped with the accommodating chamber (20) for accommodating electric element (90), the opening of the accommodating chamber (20) is removably covered with hatchcover (30), the inner wall of the hatchcover (30) is equipped with liner plate (40), and the liner plate (40) partially protrudes from the hatchcover (30).The liner plate that hatchcover is protruded from by the inner wall setting unit in hatchcover, can increase the connection area between hatchcover and fuselage.After hatchcover is connect with fuselage, the part that liner plate protrudes from hatchcover can be filled in the gap location between hatchcover and fuselage and form backstop, and then guarantee to be detached from fuselage during unmanned plane during flying to avoid hatchcover after mounting without offset between hatchcover and fuselage.
Description
Technical field
The utility model relates to unmanned flight's technical field, in particular to a kind of unmanned plane.
Background technique
Hatchcover can be all arranged in the top of usual unmanned plane, and hatchcover is during unmanned plane during flying due to the deformation meeting of fuselage
Cause the problem of forming biggish offset between hatchcover and body or even being detached from fuselage, be the field long-term existence.
Way more typical at present is that several point installation fasteners are arranged on hatchcover, by fastener by force by hatchcover and machine
Body tightens together.But this way has the disadvantage that: (1) fastener installed can inevitably protrude from body, destroy
The consistency of body surface, influences beauty.(2) fastener protrudes from the aerodynamic arrangement of body breaks down body, influences aircraft
Flying quality.
Utility model content
The utility model provides a kind of unmanned plane, can cross between the hatchcover and fuselage that guarantee unmanned plane after mounting without disconnected
Difference is detached from fuselage during unmanned plane during flying to avoid hatchcover.
Unmanned plane provided by the embodiment of the utility model, including fuselage, the fuselage, which is equipped with, is used for accommodating electric element
Accommodating chamber, the opening of the accommodating chamber is removably covered with hatchcover, and the inner wall of the hatchcover is equipped with liner plate, the liner plate portion
Divide and protrudes from the hatchcover.
Further, the inner wall two sides of the hatchcover be equipped with the symmetrical liner plate, the shape of the liner plate with it is described
The lateral profiles shape of hatchcover is adapted.
Further, the hatchcover is domes, and the middle part of the hatchcover is arched upward outward is formed with arch portion.
Further, the inner wall of the hatchcover is equipped with the first department of assembly, and the liner plate is equipped with and first department of assembly phase
Second department of assembly of cooperation.
Further, first department of assembly is equipped with pin thread/female thread, and second department of assembly is equipped with female thread/pin thread.
Further, first department of assembly is multiple, and the lateral profiles arranged for interval along the hatchcover is in the hatchcover.
Further, the side wall of the accommodating chamber is equipped with first boss portion, and the side of the hatchcover is equipped with and described first
The second boss portion that boss portion matches.
Further, the hatchcover is equipped with locking structure, and the locking structure includes the locking piece with fuselage cooperation.
Further, the locking piece is rotatably dispose in the inner wall of the hatchcover.
Further, the surface of the hatchcover is equipped with through-hole, and the locking structure further includes being arranged in the through-hole
Rotating member, the rotating member can be rotated relative to the through-hole, side and the lock of the rotating member close to the hatchcover inner wall
Determine part connection.
Further, the rotating member is equipped with rotation section close to the side of the hatchcover outer wall.
The unmanned plane of the utility model is protruded from the liner plate of hatchcover by the inner wall setting unit in hatchcover, can increased
Connection area between hatchcover and fuselage.After hatchcover is connect with fuselage, the part that liner plate protrudes from hatchcover can be filled in cabin
Gap location between lid and fuselage forms backstop, and then guarantees between hatchcover and fuselage after mounting without offset, to avoid hatchcover
Fuselage is detached from during unmanned plane during flying.
Detailed description of the invention
Fig. 1 is a kind of stereoscopic schematic diagram of unmanned plane shown in the utility model embodiment.
Fig. 2 is a kind of decomposition diagram of unmanned plane shown in the utility model embodiment.
Fig. 3 is a kind of top view of unmanned plane shown in the utility model embodiment.
Fig. 4 is the hatchcover of unmanned plane shown in Fig. 3 and the enlarged diagram of fuselage.
Fig. 5 is a kind of side view of unmanned plane shown in the utility model embodiment.
Fig. 6 is the decomposition diagram of unmanned plane shown in fig. 5.
Fig. 7 is a kind of front view of unmanned plane shown in the utility model embodiment.
Fig. 8 is the decomposition diagram of unmanned plane shown in Fig. 7.
Fig. 9 is the hatchcover of unmanned plane shown in Fig. 7 and the enlarged diagram of fuselage.
Figure 10 is the partial enlargement diagram of unmanned plane shown in Fig. 9.
Figure 11 is a kind of structural schematic diagram of the locking structure of unmanned plane shown in the utility model embodiment.
Figure 12 is the signal of locking structure when a kind of unmanned plane hatchcover shown in the utility model embodiment is connect with fuselage
Figure.
Figure 13 is the signal of locking structure when a kind of unmanned plane hatchcover shown in the utility model embodiment is separated with fuselage
Figure.
Figure 14 is a kind of structural schematic diagram of the undercarriage of unmanned plane shown in the utility model embodiment.
Figure 15 is a kind of decomposition diagram of the undercarriage of unmanned plane shown in the utility model embodiment.
Specific embodiment
Example embodiments are described in detail here, and the example is illustrated in the accompanying drawings.Following description is related to
When attached drawing, unless otherwise indicated, the same numbers in different drawings indicate the same or similar elements.Following exemplary embodiment
Described in embodiment do not represent all embodiments consistent with the utility model.On the contrary, they be only with such as
The example of the consistent device and method of some aspects be described in detail in the appended claims, the utility model.
It is only to be not intended to be limiting this reality merely for for the purpose of describing particular embodiments in the term that the utility model uses
With novel.In the "an" of the utility model and singular used in the attached claims, " described " and "the"
Most forms are intended to include, unless the context clearly indicates other meaning.It is also understood that term used herein " and/
Or " refer to and include that one or more associated any or all of project listed may combine.
It should be appreciated that " first " " second " and similar word used in present specification and claims
It is not offered as any sequence, quantity or importance, and is used only to distinguish different component parts.Equally, "one" or
The similar word such as " one " does not indicate that quantity limits yet, but indicates that there are at least one.Unless otherwise noted, " front ", " after
The similar word such as portion ", " lower part " and/or " top " is not limited to a position or a kind of sky only to facilitate explanation
Between orient.The similar word such as " comprising " or "comprising" means to appear in element or object before " comprising " or "comprising"
Cover the element for appearing in " comprising " or "comprising" presented hereinafter or object and its equivalent, it is not excluded that other elements or
Object." connection " either the similar word such as " connected " is not limited to physics or mechanical connection, and may include
Electrical connection, it is either direct or indirect.
The utility model provides a kind of unmanned plane, can cross between the hatchcover and fuselage that guarantee unmanned plane after mounting without disconnected
Difference is detached from fuselage during unmanned plane during flying to avoid hatchcover.With reference to the accompanying drawing, the unmanned plane of the utility model is carried out
It is described in detail.In the absence of conflict, the feature in following embodiment and embodiment can be combined with each other.
Referring to shown in Fig. 1 to Fig. 8, the utility model embodiment provides a kind of unmanned plane 100, can be fixed-wing nobody
The model plane equipment such as machine, multi-rotor unmanned aerial vehicle, VTOL fixed-wing unmanned plane, mixing wing unmanned plane.Example shown in the figure
In, unmanned plane 100 is VTOL fixed-wing unmanned plane, and unmanned plane 100 includes fuselage 10 and the fixed-wing for being set to fuselage 10
11 and two horns 12 of fuselage 10 are symmetrically disposed on, multiple rotors 13 and multiple undercarriages 14, machine can be set on horn 12
The tail portion of body 10 is additionally provided with power device of the propeller 15 as fixed-wing 11.Optionally, fixed-wing 11 is removably mounted on
On fuselage 10.
The fuselage 10 is equipped with the accommodating chamber 20 for accommodating electric element 90, and the opening of the accommodating chamber 20 is detachable
Ground is covered with hatchcover 30, and the inner wall of the hatchcover 30 is equipped with liner plate 40, and 40 part of liner plate protrudes from the hatchcover 30.Hatchcover
30 be attached to fuselage 10 after accommodating chamber 20 is covered, electronic component 90 can be enclosed in the inside of fuselage 10.Optionally, it accommodates
Chamber 20 is located at the top of fuselage 10.Electronic component 90 may include battery, GPS module, 4G module, satellite modules, main control module
Equal elements.
The unmanned plane 100 of the utility model protrudes from the liner plate 40 of hatchcover 30 by the inner wall setting unit in hatchcover 30,
The connection area between hatchcover 30 and fuselage 10 can be increased.After hatchcover 30 is connect with fuselage 10, liner plate 40 protrudes from hatchcover
30 part can be filled in the gap location between hatchcover 30 and fuselage 10 and form backstop, so guarantee hatchcover 30 and fuselage 10 it
Between after mounting without offset, fuselage 10 is detached from 100 flight course of unmanned plane to avoid hatchcover 30.
In an optional embodiment, liner plate 40 selects the carbon fiber board of whole 0.5mm thickness to be fixed on the interior of hatchcover 30
Side, the carbon fiber board of 0.5mm thickness can guarantee longitudinal enough flexibilities again while guaranteeing transverse strength, can be easier to
The hatchcover 30 for fitting to solid surface structure on.The part that 40 edge of liner plate protrudes from hatchcover 30 has enough contact surfaces
Product, to guarantee between hatchcover 30 and fuselage 10 to be not in offset.
In conjunction with shown in Fig. 2 and Fig. 4, in an optional embodiment, the inner wall two sides of the hatchcover 30 are equipped with symmetrical
The liner plate 40, the shape of the liner plate 40 is adapted with the lateral profiles shape of the hatchcover 30, to guarantee to be filled up completely
By the gap location between hatchcover 30 and fuselage 10.
Further, as shown in connection with fig. 8, the hatchcover 30 is domes, and arch upward shape outward at the middle part of the hatchcover 30
At there is arch portion 31, make hatchcover 30 that there are round and smooth curved surfaces, full of innervation and there is good aeroperformance.
In the present embodiment, the hatchcover 30 includes middle part 302 and the front end 301 positioned at 302 two sides of middle part
With rear end 303, wherein front end 301 is class square close to the part of middle part 302, middle part 302 and rear end 303
Shape structure, the width of middle part 302 are greater than front end 301 close to the part of middle part 302 and the width of rear end 303, preceding
Part of the end 301 far from middle part 302 is the class pyramidal structure that width is gradually reduced.Two liner plates 40 are symmetricly set on hatchcover
The two sides of 30 front end 301, and the shape of liner plate 40 is adapted with the lateral profiles shape of the front end 301 of hatchcover 30.
In an optional embodiment, the hatchcover 30 be equipped with the first department of assembly 32, the liner plate 40 be equipped with it is described
The second department of assembly 41 that first department of assembly 32 matches.It, will by the mutual cooperation of the first department of assembly 32 and the second department of assembly 41
Hatchcover 30 and liner plate 40 are connected with each other.In example shown in the figure, first department of assembly 32 be it is multiple, along the hatchcover 30
Front end 301 lateral profiles arranged for interval on the hatchcover 30, the quantity of the second department of assembly 41 and the first department of assembly 32
Quantity it is consistent, and be accordingly arranged on liner plate 40 for it, to guarantee the bonding strength between hatchcover 30 and liner plate 40.
Further, first department of assembly 32 is equipped with pin thread/female thread, and second department of assembly 41 is equipped with corresponding mother
Button/pin thread is mutually fastened (that is, structure type of snap fastener) by pin thread and female thread, and then by hatchcover 30 and liner plate 40
It is connected with each other.In the present embodiment, first department of assembly 32 and second department of assembly 41 are through-hole, first assembly
It is installed with pin thread 34 in portion 32, is installed with female thread 42 in second pilot hole 41, pin thread 34 and female thread 42 are mutually fastened, i.e.,
Hatchcover 30 and liner plate 40 can be connected with each other, easy to operate, structure is simple, and the structure type of snap fastener can be utmostly
Ground is flushed with the surface of hatchcover 30, therefore will not exempt to influence the aesthetics and aeroperformance on 10 surface of fuselage.Optionally, snap fastener
Using plastic material, to meet light-weighted requirement.Certainly, the first department of assembly 32 and the second department of assembly 41 can also use other
The connection structure of similar rivet is connected with each other, and this specification compares with no restriction.
Referring to shown in Fig. 9 and Figure 10, in an optional embodiment, the side wall of the accommodating chamber 20 is equipped with first boss
Portion 21, the side of the hatchcover 30 are equipped with the second boss portion 33 matched with the first boss portion 21.Pass through first boss
The cooperation in portion 21 and second boss portion 33 can limit freedom of motion of the hatchcover 30 into accommodating chamber 20.Cooperate liner plate 40 itself
Deformability allow to be fitted in the inside of hatchcover 30 well, limit hatchcover 30 toward being detached from the movement of 10 direction of fuselage
Freely, so that hatchcover 30 be made to can be good at being fitted on fuselage 10.In addition, between first boss portion 21 and second boss portion 33
It is formed by corresponding boss face, sliding slot is also used as and realizes that hatchcover 30 is assembled in a sliding manner on fuselage 10.
Referring to shown in Figure 11 to Figure 13, in an optional embodiment, the hatchcover 30 is equipped with locking structure 50, described
Locking structure 50 includes the locking piece 51 with the fuselage 10 cooperation, and the locking piece 51 is rotatably dispose in the interior of the hatchcover 30
Wall.Wherein, locking piece 51 can be connected directly with fuselage 10 and be cooperated, or is arranged inside fuselage 10 and matched with locking piece 51
Structure.
In the present embodiment, slot can be set in the inside of fuselage 10 and locking piece 51 cooperates.When needing to pacify hatchcover 30
When being attached to the aperture position of accommodating chamber 20 and being connect with fuselage 10, locking piece 51 can be turned to state as shown in figure 12, locked
Determine in the slot that part 51 can be fastened on inside fuselage 10, and then hatchcover 30 and fuselage 10 are fixed to each other.When needing hatchcover
30 with fuselage 10 when separating, and locking piece 51 can be turned to state as shown in fig. 13 that, makes inside locking piece 51 and fuselage 10
Slot be mutually disengaged, and then hatchcover 30 is separated with fuselage 10, hatchcover 30 can be dismantled from fuselage 10.Optionally, it locks
The quantity for determining structure 50 can be multiple, be arranged at intervals on hatchcover 30.In example shown in the figure, the number of locking structure 50
Amount is three, is arranged at intervals on the rear end 303 of hatchcover 30.
Further, the surface of the hatchcover 30 is equipped with through-hole, and the locking structure 50 further includes being arranged in the through-hole
Interior rotating member 52, the rotating member 52 can be rotated relative to the through-hole, and the rotating member 52 is close to 30 inner wall of hatchcover
Side is connect with the locking piece 51, and the rotating member 52 is equipped with rotation section 53 close to the side of 30 outer wall of hatchcover, is passed through
The rotation of 52 opposing through-bores of rotation section may be implemented in rotary motion portion 53, to drive locking piece 51 to rotate.
In other embodiments, it is also provided with the pilot hole along fuselage direction on fuselage 10, bullet is set on hatchcover 30
Property structure, when by hatchcover 30 lock when, pull elastic construction towards heading move so that locking piece 30 put into repacking match
Hole, the elastic construction restore deformation locking.Alternatively, the inside of fuselage 10 can also longitudinally open up pilot hole, the locking structure
50 also may include the elastic component for being set to 30 inner wall of hatchcover and cooperating with the pilot hole, and hatchcover 30 is assembled on fuselage 10 in place
Afterwards, can push hatchcover 30 is fastened on the elastic component in the pilot hole, and then hatchcover 30 and fuselage 10 are fixed to each other.
Referring to shown in Figure 14 and Figure 15, in an optional embodiment, the undercarriage 14 includes: undercarriage ontology
141 and Quick-dismantle component 142, undercarriage 141 and Quick-dismantle component 142 it is detachably connected.Wherein, undercarriage ontology 141 includes master
Body portion 143 and set on the plug division of main part 143 144, Quick-dismantle component 142 includes the first mounting portion for connecting with horn 12
145 and the second mounting portion 146 for connecting with the first mounting portion 145, the second mounting portion 146 is equipped with to be matched with plug division 144
Slot 147 and fixing piece 148.The plug division 144 of undercarriage ontology 141 is inserted in the slot 147 of Quick-dismantle component 142, and is led to
It crosses fixing piece 148 and the second mounting portion 146 is fixed, and then realize and undercarriage 14 is installed on horn 12.
The above is only the preferred embodiment of the utility model, not does in any form to the utility model
Limitation, although the utility model has been disclosed with preferred embodiment as above, is not intended to limit the utility model, any to be familiar with
Professional and technical personnel, in the range of not departing from technical solutions of the utility model, when in the technology using the disclosure above
Hold the equivalent embodiment for being modified or being modified to equivalent variations, but all without departing from technical solutions of the utility model
Hold, any simple modification, equivalent change and modification made by the above technical examples according to the technical essence of the present invention, still
It is within the scope of the technical solutions of the present invention.
This patent document disclosure includes material protected by copyright.The copyright is all for copyright holder.Copyright
Owner does not oppose the patent document in the presence of anyone replicates the proce's-verbal of Patent&Trademark Office and archives or should
Patent discloses.
Claims (11)
1. a kind of unmanned plane, which is characterized in that including fuselage, the fuselage is equipped with the accommodating chamber for accommodating electric element,
The opening of the accommodating chamber is removably covered with hatchcover, and the inner wall of the hatchcover is equipped with liner plate, and the patch portion protrudes from
The hatchcover.
2. unmanned plane according to claim 1, which is characterized in that the inner wall two sides of the hatchcover are equipped with symmetrical described
Liner plate, the shape of the liner plate are adapted with the lateral profiles shape of the hatchcover.
3. unmanned plane according to claim 1, which is characterized in that the hatchcover is domes, the middle part of the hatchcover
It arches upward outward and is formed with arch portion.
4. unmanned plane according to claim 1, which is characterized in that the hatchcover is equipped with the first department of assembly, and the liner plate is set
There is the second department of assembly matched with first department of assembly.
5. unmanned plane according to claim 4, which is characterized in that first department of assembly is equipped with pin thread/female thread, and described the
Two departments of assembly are equipped with female thread/pin thread.
6. unmanned plane according to claim 4, which is characterized in that first department of assembly be it is multiple, along the hatchcover
Lateral profiles arranged for interval is in the hatchcover.
7. unmanned plane according to claim 1, which is characterized in that the side wall of the accommodating chamber is equipped with first boss portion, institute
The side for stating hatchcover is equipped with the second boss portion matched with the first boss portion.
8. unmanned plane according to claim 1, which is characterized in that the hatchcover is equipped with locking structure, the locking structure
Including the locking piece cooperated with the fuselage.
9. unmanned plane according to claim 8, which is characterized in that the locking piece is rotatably dispose in the interior of the hatchcover
Wall.
10. unmanned plane according to claim 9, which is characterized in that the surface of the hatchcover is equipped with through-hole, the locking knot
Structure further includes the rotating member being arranged in the through-hole, and the rotating member can be rotated relative to the through-hole, and the rotating member is close
The side of the hatchcover inner wall is connect with the locking piece.
11. unmanned plane according to claim 10, which is characterized in that the rotating member is close to the side of the hatchcover outer wall
Equipped with rotation section.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820594040.7U CN208181396U (en) | 2018-04-24 | 2018-04-24 | Unmanned plane |
| CN201880017759.7A CN110896622A (en) | 2018-04-24 | 2018-09-17 | Unmanned plane |
| PCT/CN2018/106020 WO2019205457A1 (en) | 2018-04-24 | 2018-09-17 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820594040.7U CN208181396U (en) | 2018-04-24 | 2018-04-24 | Unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208181396U true CN208181396U (en) | 2018-12-04 |
Family
ID=64434858
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820594040.7U Active CN208181396U (en) | 2018-04-24 | 2018-04-24 | Unmanned plane |
| CN201880017759.7A Pending CN110896622A (en) | 2018-04-24 | 2018-09-17 | Unmanned plane |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201880017759.7A Pending CN110896622A (en) | 2018-04-24 | 2018-09-17 | Unmanned plane |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN208181396U (en) |
| WO (1) | WO2019205457A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110896622A (en) * | 2018-04-24 | 2020-03-20 | 深圳市大疆创新科技有限公司 | Unmanned plane |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113071668A (en) * | 2020-04-16 | 2021-07-06 | 灵遥机器人(深圳)有限责任公司 | Unmanned aerial vehicle |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150102159A1 (en) * | 2013-10-15 | 2015-04-16 | Russ Hegarty | Waterproof multi-rotor unmanned flying apparatus |
| CN203666962U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Hatch cover fastening structure for unmanned fixed wing operation aircraft |
| CN203996866U (en) * | 2014-07-08 | 2014-12-10 | 河南科普信息技术工程有限公司 | A kind of for locking device fixing between unmanned plane housing |
| JP6375570B2 (en) * | 2014-07-31 | 2018-08-22 | エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ | Unmanned aerial vehicle base station |
| CN205059987U (en) * | 2015-09-06 | 2016-03-02 | 深圳市道通智能航空技术有限公司 | Casing and aircraft |
| CN205259760U (en) * | 2015-12-25 | 2016-05-25 | 海鹰航空通用装备有限责任公司 | Fast locking device of unmanned aerial vehicle cabin cover |
| FR3046779B1 (en) * | 2016-01-14 | 2018-02-16 | Dassault Aviation | SYSTEM FOR PACKAGING A PACKAGE FROM AN AIRCRAFT, AIRCRAFT AND ASSOCIATED METHOD |
| KR102320197B1 (en) * | 2016-03-03 | 2021-11-01 | 사우스코 인코포레이티드 | Latch mechanism with status indicator |
| CN205418056U (en) * | 2016-03-29 | 2016-08-03 | 零度智控（北京）智能科技有限公司 | Unmanned aerial vehicle of unmanned aerial vehicle shell and applied this unmanned aerial vehicle shell |
| CN206265285U (en) * | 2016-12-02 | 2017-06-20 | 南昌白龙马航空科技有限公司 | Unmanned plane waterproof hatch cover |
| CN207157485U (en) * | 2017-08-05 | 2018-03-30 | 北京海利天梦科技有限公司 | A kind of unmanned plane with the fast locking device of hatchcover |
| CN107444607A (en) * | 2017-08-14 | 2017-12-08 | 北京奇正数元科技股份有限公司 | The rotation fast-open type hatchcover of small-sized unmanned plane |
| CN208181396U (en) * | 2018-04-24 | 2018-12-04 | 深圳市大疆创新科技有限公司 | Unmanned plane |
-
2018
- 2018-04-24 CN CN201820594040.7U patent/CN208181396U/en active Active
- 2018-09-17 CN CN201880017759.7A patent/CN110896622A/en active Pending
- 2018-09-17 WO PCT/CN2018/106020 patent/WO2019205457A1/en active Application Filing
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110896622A (en) * | 2018-04-24 | 2020-03-20 | 深圳市大疆创新科技有限公司 | Unmanned plane |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019205457A1 (en) | 2019-10-31 |
| CN110896622A (en) | 2020-03-20 |
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