CN106143867A - Aircraft fuselage and include its aircraft - Google Patents
Aircraft fuselage and include its aircraft Download PDFInfo
- Publication number
- CN106143867A CN106143867A CN201510163563.7A CN201510163563A CN106143867A CN 106143867 A CN106143867 A CN 106143867A CN 201510163563 A CN201510163563 A CN 201510163563A CN 106143867 A CN106143867 A CN 106143867A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- aircraft
- aircraft fuselage
- battery
- battery case
- 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.)
- Granted
Links
Landscapes
- Pressure Welding/Diffusion-Bonding (AREA)
- Toys (AREA)
Abstract
The present invention provides a kind of aircraft fuselage and includes its aircraft, described aircraft fuselage includes on one fuselage and once fuselage, described upper fuselage and described lower fuselage use ultrasonic bonding to connect, the inside of described aircraft fuselage have a cavity and with at least one open communication on described lower fuselage, a dynamical system is arranged in described cavity via described opening.The present invention uses ultrasonic welding process to connect the fuselage up and down of aircraft, one-shot forming, and yields is high；Using the aircraft fuselage of this welding procedure, upper and lower fuselage seamless link, contact surface stress, intensity obtains bigger raising simultaneously.
Description
Technical field
The present invention be more particularly directed to a kind of aircraft fuselage and include its aircraft.
Background technology
The aircraft of prior art, needs first to install in upper fuselage or lower fuselage dynamical system, to be installed
After more upper and lower fuselage is closed up and is fixedly connected.And use screw connecting mode to connect more and fly
The fuselage up and down of row device, utilizes screw bearing as stress point, but integral body intensity is relatively low.If
Enhancing fuselage intensity increases screw number, can increase too much weight to aircraft again, be unfavorable for flight
The performance of device improves.Meanwhile, use screw connecting mode to assemble difficulty, in large aircraft lock machine body one
As need not of uniform size tens screw, cost of labor is high, and yields is low.
And, general aircraft all can be again by upper and lower fuselage after installing the components and parts of aircraft interior
Closing up connection, the assembling of aircraft is relatively complicated, and processing step is various, both takes time and effort, and the most easily goes out
Existing loading error, may cause the product of assembling to have mass defect.
Summary of the invention
The technical problem to be solved in the present invention is first to install dynamical system in prior art close to overcome
Hold together upper and lower fuselage, and use screw connecting mode to connect the fuselage weight that the fuselage up and down of aircraft is brought
The defects such as weight, fuselage intensity difference, aircraft installation in trouble are laborious, it is provided that a kind of aircraft fuselage and including
Its aircraft.
The present invention is to solve above-mentioned technical problem by following technical proposals:
A kind of aircraft fuselage, its feature is, described aircraft fuselage includes on one fuselage and once machine
Body, described upper fuselage and described lower fuselage use ultrasonic bonding to connect, the inside of described aircraft fuselage
Have a cavity and with at least one open communication on described lower fuselage, a dynamical system is via described opening
It is arranged in described cavity.
The present invention is by making improvement to the structure of aircraft fuselage so that can first upper and lower to aircraft
Fuselage carries out closing up connection, then installs dynamical system, and the assembling of aircraft fuselage is simplified.The present invention
The mode using ultrasonic bonding connects the fuselage up and down of aircraft so that the upper and lower fuselage of aircraft is without seam welding
Connecing, by contact surface stress, instead of contact point stress (screw connection), fuselage intensity is greatly improved,
And integration fuselage weight is relatively light, and facilitate production and processing, be greatly improved production efficiency.
It is preferred that the interface of described upper fuselage is provided with welding bar, the interface of described lower fuselage is provided with weldering
Access slot, described welding bar docks with described welding groove.
Welding bar can embed welding groove so that upper fuselage can be directed at before ultrasonic bonding with lower fuselage
Position, the connection of upper and lower fuselage is more accurate.Meanwhile, during ultrasonic bonding, the weldering of upper fuselage
Connect bar can soften, combine together with welding groove so that fuselage firmly connects up and down, and structural strength increases greatly
Add.
It is preferred that described welding bar around described upper fuselage one circle arrange, described welding groove accordingly around
Described lower fuselage one circle is arranged.
Welding bar and the connection of welding groove of a full circle, adds solder side so that the company of fuselage up and down
Connect more firm.
It is preferred that described dynamical system includes a master control borad and a battery.
For electrically driven (operated) aircraft, dynamical system can be master control borad and battery, and master control borad can drive
Rotor revolution, it is provided that flying power, battery is then powered for master control borad.
It is preferred that described aircraft fuselage is provided with a sensor outer housing fixed mechanism, this aircraft fuselage
Outer surface is provided with one for fixing the draw-in groove of sensor outer housing；This sensor outer housing fixed mechanism also includes:
One for housing the outer cover body of sensor；One with the Access Division of this card slot fit, this Access Division include with
The two side that the line end to end of this fuselage is parallel, the top of this Access Division is provided with an opening；One is located at this
Outer cover body lower end is for the snap-fit engagement portion being connected with this Access Division by this outer cover body；This Access Division with
This snap-fit engagement portion is connected by an axle.
The sensor outer housing fixed mechanism of aircraft just can from aircraft easily without disassembling fuselage
Disassemble, it is simple to change and upgrade.Additionally, due to it may be at being deployed in fuselage and gathering simultaneously
In fuselage the two state, transport of being more convenient for for the sensor outer housing of the most existing aircraft,
It is not easy the most damaged.
It is preferred that described aircraft fuselage is provided with a lampshade fixed mechanism, this lampshade fixed mechanism includes setting
For housing the lamp house of lamp on this aircraft fuselage, and the lampshade coordinated with this lamp house, this lamp house bag
Including an annular sidewall, this annular sidewall is provided with at least two installing hole；This lampshade is provided with and described peace
The buckle that dress hole coordinates is protruding；Described buckle projection includes an extension vertically extended, described
Extension points to the free end of this lamp house and is provided with a boss extended outside this lampshade；Described buckle is protruding
With described installing hole pine timing, the upright side walls contacted with this installing hole is provided with a transition face.
The lampshade fixed mechanism simple in construction of aircraft, dismounting is quick convenient, effectively reduces flight simultaneously
The deadweight of device.
It is preferred that described aircraft fuselage is provided with a battery component, this battery component includes a battery case,
Including at least one piece of battery in this battery case, positive terminal and the negative pole end of described battery lead to respectively
Cross the first charging balanced line and the second charging balanced line and a discharge and recharge interface connects, this discharge and recharge interface bag
Include at least one charging port and an electric discharge port；This discharge and recharge interface is located on this battery case.
The battery component of aircraft and to comprise its Flight Vehicle Structure simple, easy to use, by battery outside
Battery can effectively be protected by shell, simplifies the operating procedure of discharge and recharge simultaneously.
It is preferred that described aircraft fuselage is provided with a undercarriage, this undercarriage includes: a support component, uses
In supporting aircraft；Fixation kit, is positioned on the end face of this support component, and this fixation kit for
This aircraft fuselage snaps connection, when this fixation kit pressurized this fixation kit can in this fuselage quilt
Take out.
The fixation kit of undercarriage snaps connection with the fuselage of aircraft, and can when fixation kit pressurized
Take out in fuselage so that without using special instrument, dismounting side when dismantling this undercarriage from fuselage
Just；Meanwhile, when undercarriage damages, easy independent replacement undercarriage, reduce use cost；In transport
During aircraft, convenient by undercarriage dismounting, thus convenient this aircraft of transport, and save greatly
Save transport space, reduce cost of transportation.
It is preferred that this described aircraft fuselage has a battery case and an inner containment chamber, this battery case is used
In set battery assembly, this inner containment chamber is located at inside this battery case and is positioned at this aircraft fuselage
Portion, this inner containment chamber is for accommodating at least one aircraft interior components, and the opening of this battery case makes this
At least one aircraft interior components is able to enter this inner containment intracavity via this battery case.
Aircraft fuselage can install the assembly such as antenna, battery easily, and battery case and inner containment
The design in chamber makes the intraware such as master control borad etc. of aircraft rearmounted to fixedly mount, and is obviously improved
Ease for operation that aircraft is installed and convenience.
In the present invention, above-mentioned optimum condition on the basis of meeting common sense in the field can combination in any, to obtain final product
The each preferred embodiment of the present invention.
The most progressive effect of the present invention is: the present invention uses ultrasonic welding process to connect aircraft
Fuselage up and down, one-shot forming, yields is high；Use the aircraft fuselage of this welding procedure, up and down simultaneously
Fuselage seamless link, contact surface stress, intensity obtains bigger raising.
Accompanying drawing explanation
Fig. 1 is the structural representation of the aircraft fuselage of the embodiment of the present invention 1.
Fig. 2 is the top view of Fig. 1.
Fig. 3 is the Fig. 2 sectional view along line A-A.
Fig. 4 is the rear structure schematic diagram of the aircraft fuselage of the embodiment of the present invention 1.
Fig. 5 is the axonometric chart at airframe structure one visual angle of the aircraft in the embodiment of the present invention 2.
Fig. 6 is the axonometric chart at another visual angle of airframe structure of the aircraft in the embodiment of the present invention 2.
Detailed description of the invention
Name several preferred embodiment, and combine accompanying drawing and become apparent from intactly illustrating the present invention.
Embodiment 1
Fig. 1 shows a kind of aircraft fuselage 1, and described aircraft fuselage includes on one fuselage 2 and once
Fuselage 3.Described upper fuselage and described lower fuselage use ultrasonic bonding to connect.As shown in Figure 4, described
The inside of aircraft fuselage 1 has a cavity 4 and connects with at least one opening 5 on described lower fuselage.
One dynamical system (not shown) is arranged in described cavity via described opening.
The inside of the aircraft fuselage of the present invention has a bigger cavity, and this cavity is by lower fuselage
Opening is in communication with the outside.So, dynamical system just can be installed to after aircraft fuselage completes again
On fuselage.The dynamical system that opening on lower fuselage is installed after being provides enough spaces.In this enforcement
In example, described dynamical system includes a master control borad and a battery.Master control borad can drive rotor revolution,
Thering is provided flying power, battery is then powered for master control borad.Certainly, the present invention is also not limited to electrically driven (operated)
Aircraft, is also applied for other dynamical systems and provides the aircraft of power.
For the present invention, it is possible to after fuselage integration completes, then master control borad and battery are installed to machine
In body.The motor being positioned at horn end then can be connected with master control borad easily.In order to be more convenient for connecting,
The lower fuselage of the present invention can offer two openings, and a close Vehicle nose, one near aircraft
Afterbody, the most whether two motors of front end, or two motors of rear end, before can passing through one
One latter two opening is connected with master control borad easily.The two opening can install aircraft interior
By on extra cover plate lid after components and parts.It is preferred that can also allow battery while installation puts in place,
The shape design utilizing self carrys out the opening of closed rear end.
The present invention is by making improvement to the structure of aircraft fuselage so that can first upper and lower to aircraft
Fuselage carries out closing up connection, then installs dynamical system, and the assembling of aircraft fuselage is simplified.The present invention
The mode using ultrasonic bonding connects the fuselage up and down of aircraft so that the upper and lower fuselage of aircraft is without seam welding
Connecing, by contact surface stress, instead of contact point stress (screw connection), fuselage intensity is greatly improved,
And integration fuselage weight is relatively light, and facilitate production and processing, be greatly improved production efficiency.
In the present embodiment, as shown in Figure 2,3, the interface of described upper fuselage is provided with welding bar 6, institute
The interface stating lower fuselage is provided with welding groove 7, and described welding bar docks with described welding groove.Welding bar can
To embed welding groove so that upper fuselage can be directed at position, upper and lower machine with lower fuselage before ultrasonic bonding
The connection of body is more accurate.Meanwhile, during ultrasonic bonding, the welding bar of upper fuselage can soften,
Combine together with welding groove so that fuselage firmly connects up and down, and structural strength is greatly increased.Certainly, originally
Invention is not limited to use welding bar and welding groove to realize this mode of ultrasonic bonding, it would however also be possible to employ
Other modes complete ultrasonic bonding.Even if only having upper fuselage and two interfaces of lower fuselage, too
Ultrasonic bonding can be completed.
In the present embodiment, described welding bar is arranged around described upper fuselage one circle, and described welding groove is corresponding
Ground is arranged around described lower fuselage one circle.Welding bar and the connection of welding groove of a full circle, adds weldering
Junction so that the connection of fuselage is more firm up and down.Certainly, the present invention the whole fuselage of non-required one enclose
All use the form of welding bar and welding groove, it is also possible to only use ultrasonic bonding in significant points, at it
Its part still adopts modes such as being screwed.The most in actual applications, for multi-rotor aerocraft,
Owing to horn is near motor, during electric machine rotation, higher, then to stability and horn requirement of strength
Horn just can realize integration form to use ultrasonic bonding, and other positions are then adopted and are screwed.
Additionally, it is solid to be equipped with sensor outer housing on the integrated flight device fuselage of the present embodiment
Determine mechanism, lampshade fixed mechanism, battery component, undercarriage, install very convenient.
Specifically, the outer surface of this aircraft fuselage is provided with one for fixing the draw-in groove of sensor outer housing；
This sensor outer housing fixed mechanism also includes: one for housing the outer cover body of sensor；One with this draw-in groove
The Access Division coordinated, this Access Division includes the two side that the line end to end with this fuselage is paralleled, this clamping
The top in portion is provided with an opening；One is located at this outer cover body lower end for by this outer cover body and this Access Division
The snap-fit engagement portion connected；This Access Division is connected by an axle with this snap-fit engagement portion.
This lampshade fixed mechanism includes being located at for housing the lamp house of lamp on this aircraft fuselage, and with this
The lampshade that lamp house coordinates, this lamp house includes an annular sidewall, and this annular sidewall is provided with at least two and installs
Hole；It is protruding that this lampshade is provided with the buckle coordinated with described installing hole；Described buckle projection includes one along perpendicular
Nogata is to the extension extended, and described extension points to the free end of this lamp house and is provided with one outside this lampshade
The boss extended；Described buckle is protruding with described installing hole pine timing, the vertical side contacted with this installing hole
Wall is provided with a transition face.
This battery component includes a battery case, includes at least one piece of battery, institute in this battery case
State the positive terminal of battery and negative pole end respectively by the first charging balanced line and the second charging balanced line with
One discharge and recharge interface connects, and this discharge and recharge interface includes at least one charging port and an electric discharge port；This fills
Electric discharge interface is located on this battery case.
This undercarriage includes: a support component, is used for supporting aircraft；Fixation kit, is positioned at this support group
On the end face of part, and this fixation kit is for snapping connection with this aircraft fuselage, when this fixation kit is subject to
During pressure, this fixation kit can be removed in this fuselage.
From the above description it is known that the present invention uses ultrasonic welding process to connect the machine up and down of aircraft
Body, one-shot forming, yields is high；Use the aircraft fuselage of this welding procedure simultaneously, upper and lower fuselage without
Seam connects, and contact surface stress, intensity obtains bigger raising.
Embodiment 2
Aircraft in the present embodiment is a telecontrolled aircraft, with reference to (Fig. 5,6 equal shown in Fig. 5 and Fig. 6
The bottom of aircraft fuselage is mainly shown), its airframe structure includes an aircraft fuselage.This aircraft machine
Body has battery case 12, inner containment chamber, an antenna opening, connection jaws 15 and 16, connects at two
Line lid, a baffle plate 13, rise and fall bridge joint mouth 14.
Wherein, this battery case 12 is located at the bottom of this aircraft fuselage and for set battery assembly, should
Inner containment chamber is located at inside this battery case and is positioned at the inside of this aircraft fuselage, and this inner containment chamber is used
In an accommodating master control borad 11 (it is to say, this inner containment chamber is located in Fig. 5 at this master control borad 11),
The opening of this battery case makes this master control borad be able to via this battery case and enters this inner containment intracavity.Or
Saying, the opening of this battery case is sufficiently large, so that master control borad is able to be positioned over this flight by this opening
Device fuselage interior.It should be noted that, this battery case offer so that motor, LED and other one
The connecting line of a little aircraft assemblies directly can be connected to this master control in this inner containment chamber via battery case
Plate 11 so that aircraft is installed more easily or connects these aircraft assemblies.
Specifically, in the present embodiment, LED and motor are arranged on the machine wall of this airframe structure,
The i.e. two ends of the connecting line of LED, motor to master control borad should substantially lay respectively at machine wall and be somebody's turn to do
At inner containment chamber.The machine wall of this airframe structure is being internally formed a machine wall sky while constituting fuselage
Chamber, these connecting lines by LED on machine wall, motor position is set successively through machine wall cavity, electricity
Pond groove and this inner containment chamber arrive this inner containment intracavity, are ultimately connected to connecing accordingly on this master control borad
At Kou, thus realize the connection of LED, motor and master control borad.It means that any one
Connecting line is all not exposed to outside this airframe structure, simultaneously again with in complete airframe structure machine-shaping
After complete the installation of various assembly and connecting line again.This makes installation process extremely convenient flexible.
But, the different settings of interface based on this master control borad 11, be positioned in this inner containment chamber should
The part of interface of master control borad 11 may and be not easy to the connecting line of corresponding aircraft assembly via this electricity
Pond groove is connected to this master control borad 11.Therefore, the present embodiment is additionally provided with the connection jaws below aircraft fuselage
15, the position that arranges of this connection jaws 15 makes it easier to for some assemblies such as gps antenna, fuselage front
The connecting line of motor pass and be connected to the corresponding interface on this master control borad 11, it also can provide external
RF interface.It should be noted that, for the realization only for assembly and the connection of master control borad 11, this wiring
Mouth 15 and 16 is not indispensable.
Connection jaws 16 near the undercarriage interface on the right side being positioned at this aircraft fuselage is relatively small, this
Place's connection jaws 16 can be provided as cradle head control interface and the USB interface of this master control borad.When master control borad 11
Installation and the connection of part aircraft assembly when all completing, here connection jaws 16 can not affect
On the premise of these complete the part installed or connect, it is connected to this master control borad for The Cloud Terrace.Meanwhile, should
Connection jaws 16 be provided as USB interface can greatly facilitate this aircraft software system etc. upgrading more
New and and external equipment between data transmission.
This antenna opening is for being removably inserted into connect for the shell mechanism of an antenna and fixing
This antenna.The surface that this battery case contacts with battery component is provided with at least gathering sill, this at least
The bearing of trend of gathering sill is vertical with the opening direction of this battery case, and the front end of each gathering sill is equipped with
One flaring targeting port.This baffle plate 13 is positioned at this battery case side, for by this at least one aircraft
The connecting line of assembly is separated in outside this battery case.
This wiring lid is used for closing connection jaws, and connection jaws is located at the bottom of this aircraft fuselage, this antenna
Mouth is located at the top of this aircraft fuselage.It should be appreciated that Fig. 5 only schematically shows at two
Connection jaws 15 and 16, but the quantity of connection jaws all can carry out more spirit according to actual needs with arranging position
The setting lived.
This undercarriage interface 14 is positioned at this aircraft fuselage bottom, is used for being removably secured installation together
Fall frame.This undercarriage interface specifically includes on the left and right sides sidewall being opened in this aircraft fuselage bottom
Chute and the locating slot being connected with this chute, this chute is used for connecting fixing group of frame assembly
Part, this locating slot sets this landing gear assembly for card.
Embodiment 3
The present embodiment is a kind of aircraft, and it includes any one described flying in above-described embodiment 1-2
Row device fuselage.
Although the foregoing describing the detailed description of the invention of the present invention, but those skilled in the art should managing
Solving, these are merely illustrative of, and protection scope of the present invention is defined by the appended claims.This
The technical staff in field, can be to these embodiment party on the premise of without departing substantially from the principle of the present invention and essence
Formula makes various changes or modifications, but these changes and amendment each fall within protection scope of the present invention.
Claims (10)
1. an aircraft fuselage, it is characterised in that described aircraft fuselage includes fuselage and on
Lower fuselage, described upper fuselage and described lower fuselage use ultrasonic bonding to connect, described aircraft fuselage
Inside have a cavity and with at least one open communication on described lower fuselage, a dynamical system is via described
Opening is arranged in described cavity.
2. aircraft fuselage as claimed in claim 1, it is characterised in that the docking of described upper fuselage
Face is provided with welding bar, and the interface of described lower fuselage is provided with welding groove, described welding bar and described welding groove
Docking.
3. aircraft fuselage as claimed in claim 2, it is characterised in that described welding bar is around institute
Stating fuselage one circle to arrange, described welding groove is arranged accordingly around described lower fuselage one circle.
4. aircraft fuselage as claimed in claim 1, it is characterised in that described dynamical system includes
One master control borad and a battery.
5. aircraft fuselage as claimed in claim 1, it is characterised in that described aircraft fuselage sets
Having a sensor outer housing fixed mechanism, the outer surface of this aircraft fuselage is provided with one for fixing outside sensor
The draw-in groove of shell；This sensor outer housing fixed mechanism also includes: one for housing the outer cover body of sensor；
One with the Access Division of this card slot fit, this Access Division includes the both sides that the line end to end with this fuselage is paralleled
Wall, the top of this Access Division is provided with an opening；One is located at this outer cover body lower end for by this outer cover body
The snap-fit engagement portion being connected with this Access Division；This Access Division is connected by an axle with this snap-fit engagement portion.
6. aircraft fuselage as claimed in claim 1, it is characterised in that described aircraft fuselage sets
Having a lampshade fixed mechanism, this lampshade fixed mechanism includes being located on this aircraft fuselage for housing lamp
Lamp house, and the lampshade coordinated with this lamp house, this lamp house includes an annular sidewall, and this annular sidewall sets
There is at least two installing hole；It is protruding that this lampshade is provided with the buckle coordinated with described installing hole；Described buckle
Projection includes an extension vertically extended, and described extension points to the free end of this lamp house and is provided with
One boss extended outside this lampshade；Described buckle is protruding with described installing hole pine timing, with this installation
The upright side walls of hole contact is provided with a transition face.
7. aircraft fuselage as claimed in claim 1, it is characterised in that described aircraft fuselage sets
Having a battery component, this battery component includes a battery case, includes at least one piece in this battery case
Battery, the positive terminal of described battery and negative pole end are respectively by the first charging balanced line and the second charging
Balanced line and a discharge and recharge interface connect, and this discharge and recharge interface includes at least one charging port and a discharge end
Mouthful；This discharge and recharge interface is located on this battery case.
8. aircraft fuselage as claimed in claim 1, it is characterised in that described aircraft fuselage sets
Having a undercarriage, this undercarriage includes: a support component, is used for supporting aircraft；Fixation kit, is positioned at
On the end face of this support component, and this fixation kit is for snapping connection with this aircraft fuselage, when this is solid
When determining assembly pressurized, this fixation kit can be removed in this fuselage.
9. aircraft fuselage as claimed in claim 1, it is characterised in that this described aircraft fuselage
Having a battery case and an inner containment chamber, this battery case is used for set battery assembly, this inner containment chamber
Being located at inside this battery case and be positioned at the inside of this aircraft fuselage, this inner containment chamber is for housing at least
One aircraft interior components, the opening of this battery case make this at least one aircraft interior components be able to via
This battery case enters this inner containment intracavity.
10. an aircraft, it is characterised in that it includes as described in any one in claim 1-9
Aircraft fuselage.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510163563.7A CN106143867B (en) | 2015-04-08 | 2015-04-08 | Aircraft fuselage reaches aircraft including it |
| US15/562,802 US20180281919A1 (en) | 2015-04-08 | 2016-04-08 | Aircraft fuselage and aircraft with same |
| PCT/CN2016/078860 WO2016161975A1 (en) | 2015-04-08 | 2016-04-08 | Aircraft fuselage and aircraft with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510163563.7A CN106143867B (en) | 2015-04-08 | 2015-04-08 | Aircraft fuselage reaches aircraft including it |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106143867A true CN106143867A (en) | 2016-11-23 |
| CN106143867B CN106143867B (en) | 2020-10-02 |
Family
ID=57335676
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510163563.7A Active CN106143867B (en) | 2015-04-08 | 2015-04-08 | Aircraft fuselage reaches aircraft including it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106143867B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019242621A1 (en) * | 2018-06-22 | 2019-12-26 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle and body assembly thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202270361U (en) * | 2011-10-10 | 2012-06-13 | 天津市浦杰工贸发展有限公司 | Aeromodel of airbus |
| CN203047531U (en) * | 2012-11-15 | 2013-07-10 | 深圳市大疆创新科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN203127141U (en) * | 2012-12-13 | 2013-08-14 | 深圳市大疆创新科技有限公司 | Multi-rotor wing unmanned aerial vehicle |
| CN103350752A (en) * | 2012-10-29 | 2013-10-16 | 深圳市哈博森科技有限公司 | Four-rotor aircraft |
| CN203309073U (en) * | 2013-06-08 | 2013-11-27 | 无锡隆盛科技股份有限公司 | Ultrasonic welding structure for plastic planetary gearbox |
| US20140231582A1 (en) * | 2012-10-03 | 2014-08-21 | Sean Headrick | Methods and Systems of Constructing a Multi Rotor Aircraft Fuselage |
| CN204674815U (en) * | 2015-04-08 | 2015-09-30 | 优利科技有限公司 | Aircraft fuselage and comprise its aircraft |
-
2015
- 2015-04-08 CN CN201510163563.7A patent/CN106143867B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202270361U (en) * | 2011-10-10 | 2012-06-13 | 天津市浦杰工贸发展有限公司 | Aeromodel of airbus |
| US20140231582A1 (en) * | 2012-10-03 | 2014-08-21 | Sean Headrick | Methods and Systems of Constructing a Multi Rotor Aircraft Fuselage |
| CN103350752A (en) * | 2012-10-29 | 2013-10-16 | 深圳市哈博森科技有限公司 | Four-rotor aircraft |
| CN203047531U (en) * | 2012-11-15 | 2013-07-10 | 深圳市大疆创新科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN203127141U (en) * | 2012-12-13 | 2013-08-14 | 深圳市大疆创新科技有限公司 | Multi-rotor wing unmanned aerial vehicle |
| CN203309073U (en) * | 2013-06-08 | 2013-11-27 | 无锡隆盛科技股份有限公司 | Ultrasonic welding structure for plastic planetary gearbox |
| CN204674815U (en) * | 2015-04-08 | 2015-09-30 | 优利科技有限公司 | Aircraft fuselage and comprise its aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019242621A1 (en) * | 2018-06-22 | 2019-12-26 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle and body assembly thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106143867B (en) | 2020-10-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106005361B (en) | Aviation power unit and flight frame and modularization aircraft thereof | |
| CN203047531U (en) | Multi-rotor unmanned aerial vehicle | |
| CN205971879U (en) | Unmanned aerial vehicle | |
| TWM567744U (en) | Shareable energy module replacement system for unmanned aerial vehicle | |
| JP2018505818A (en) | Unmanned air transport means with a three-way wing configuration | |
| CN103350752A (en) | Four-rotor aircraft | |
| CN110444707A (en) | Battery assembly, battery assembly and disassembly system and method | |
| CN207045661U (en) | Eight rotor plant protection unmanned planes and its flying wing arm knob are disassembled | |
| CN204802064U (en) | Aircraft and fuselage structure thereof | |
| US20180281919A1 (en) | Aircraft fuselage and aircraft with same | |
| CN110800129A (en) | Battery and agricultural unmanned aerial vehicle with same | |
| CN107097928A (en) | A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure | |
| CN111056030B (en) | Automatic charging platform of unmanned aerial vehicle | |
| CN204674815U (en) | Aircraft fuselage and comprise its aircraft | |
| CN106143867A (en) | Aircraft fuselage and include its aircraft | |
| CN106081059A (en) | A kind of many rotor wing unmanned aerial vehicles | |
| CN209023111U (en) | Multi-rotor unmanned aerial vehicle | |
| CN209071753U (en) | A kind of novel electric vehicle AC charging socket | |
| CN206125405U (en) | Fin reaches fixed wing uavs including it | |
| CN203921205U (en) | Multi-axis aircraft electric motor mounting structure | |
| CN208620526U (en) | A kind of air-conditioning electric control box, automatically controlled cartridge mount assembly and air conditioner | |
| CN205902271U (en) | Mounting panel and have security protection equipment of this mounting panel | |
| CN209351594U (en) | A kind of rotor wing unmanned aerial vehicle | |
| CN207759062U (en) | A kind of integrated four cameras oblique photograph cradle head structure | |
| CN210912849U (en) | Unmanned vehicles's fuselage and unmanned vehicles who has it |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |