CN207550505U - Small-sized pilotless aircraft - Google Patents
Small-sized pilotless aircraft Download PDFInfo
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- CN207550505U CN207550505U CN201721208651.5U CN201721208651U CN207550505U CN 207550505 U CN207550505 U CN 207550505U CN 201721208651 U CN201721208651 U CN 201721208651U CN 207550505 U CN207550505 U CN 207550505U
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- small
- lower housing
- pilotless aircraft
- upper shell
- propeller
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Abstract
The utility model discloses a kind of small-sized pilotless aircraft, including casing, including the upper surface and the lower surface；And multigroup Ducted propeller on casing is assemblied in, every group of Ducted propeller includes duct housing, fixed seat, force piece and the propeller of both ends perforation；Each duct housing is assemblied on casing and forms the duct chamber of perforation upper and lower surface, and fixed seat is set to duct intracavitary, and force piece is assemblied in fixed seat and is contained in duct intracavitary, and propeller is contained in duct intracavitary and is sequentially connected with force piece.In above-mentioned small-sized pilotless aircraft, by the way that multigroup Ducted propeller is set to be used as the power resources of complete machine, and the propeller being set on every group of Ducted propeller is accommodated in duct intracavitary, it is i.e. stealthy to set rather than be exposed to outside casing, so that small-sized pilotless aircraft is in flight course, it avoids colliding because of propeller and external object, so as to effectively improve the safety and reliability of complete machine.
Description
Technical field
The utility model is related to flying machine technical field, more particularly to a kind of small-sized pilotless aircraft.
Background technology
In recent years, small drone with its simple structure, facilitate manipulation and the features such as higher security performance by more
It is regarded come more multiple, is especially mainly used for taking photo by plane or the pocket unmanned plane of self-timer has attracted large quantities of airplane hobbyists and enthusiast.
Pocket unmanned plane be mainly characterized by it is full-featured, compact portable and easy to operate etc., and among these, portability
It is pocket unmanned plane one of outstanding feature the most.Currently in order to carrying or convenient transportation, the propeller of part pocket unmanned plane
Foldable or detachable form is designed as, reduces the free space of fuselage.But for fuselage size natively small pocket without
For man-machine, the space availability ratio that foldable or dismountable propeller easily leads to whole pocket unmanned plane is not high, the ruler of fuselage
It is very little to be increased.Meanwhile in flight course, the propeller being exposed to outside fuselage is easy to touch periphery object, such as branch
Or people etc., propeller itself is damaged and security performance is not high.
Utility model content
Based on this, it is necessary to which the problem of and security performance big for conventional small unmanned aerial vehicle size be not high provides one kind
The small unmanned aerial vehicle that size is small and reliability is high.
A kind of small-sized pilotless aircraft, including：
Casing, including upper surface and the lower surface opposite with the upper surface；And
The multigroup Ducted propeller being assemblied on the casing, Ducted propeller described in every group include the duct of both ends perforation
Housing, fixed seat, force piece and propeller；
Wherein, each duct housing, which is assemblied on the casing and is formed, penetrates through the upper surface and the lower surface
Duct chamber, the fixed seat is set to the duct intracavitary, and the force piece is assemblied in the fixed seat and is contained in institute
Duct intracavitary is stated, the propeller is contained in the duct intracavitary and is sequentially connected with the force piece.
The Ducted propeller includes four groups in one of the embodiments, and four groups of Ducted propellers are several with the casing
What center symmetric setting is in the casing surrounding.
In one of the embodiments, in Ducted propeller described in every group each propeller include paddle disk and one into
Type is set to six blades of the paddle disk periphery, and each force piece is motor, the stator of each motor with it is described
Fixed seat is fixedly connected, and each paddle disk is fixed on the rotor of each motor.
Each fixed seat is integrally formed, and described with the respective duct housing in one of the embodiments,
Small-sized pilotless aircraft includes damping rubber pad, and the damping rubber pad is set to the surface that the fixed seat installs the force piece.
The casing is including the upper shell with the upper surface and with the lower surface in one of the embodiments,
Lower housing, upper shell connection opposite with the lower housing and enclose the installation cavity for setting and being formed positioned between the two jointly；Institute
It states small-sized pilotless aircraft and includes the rubber plug being set in the installation cavity and the ultrasonic sensor being set in the rubber plug, institute
It states rubber plug to be connected between the upper shell and the lower housing, sound end exposes to the lower casing in the ultrasonic sensor
Body.
The rubber plug includes the cock body of one end formation opening and is set to the cock body periphery in one of the embodiments,
Support feet, the lower housing and the rubber plug corresponding position offer through-hole；The cock body is provided with one end of the opening
It is contained in the through-hole, the other end of the relatively described opening of the cock body is connected to the upper shell towards the lower housing
Surface, the support feet are set to the cock body and are provided with one end of the opening and are fixedly supported to the lower housing towards institute
State the surface of upper shell；Sound end described in the ultrasonic sensor by it is described opening and the through-hole expose to it is described under
Housing.
The small-sized pilotless aircraft includes the sound-absorbing part being contained in the installation cavity, institute in one of the embodiments,
It states sound-absorbing part and is set to the lower housing towards the surface of the upper shell.
The casing is including the upper shell with the upper surface and with the lower surface in one of the embodiments,
Lower housing, upper shell connection opposite with the lower housing and enclose the installation cavity for setting and being formed positioned between the two jointly；Institute
It states small-sized pilotless aircraft and the energy being set in installation cavity offer unit, circuit board, the first heat conductive pad and second is provided
Heat conductive pad, the circuit board are set to the lower housing towards the surface of the upper shell, and the energy provides unit and is set to
On the circuit board, the first heat conductive pad is set between the lower housing and the circuit board, and second heat conductive pad is set to
The energy is provided between unit and the upper shell.
The upper shell and/or the lower housing offer what is connected with the installation cavity in one of the embodiments,
Heat emission hole.
The upper shell and the lower housing are Al-alloy casing in one of the embodiments,.
In above-mentioned small-sized pilotless aircraft, it is used as the power resources of complete machine by setting multigroup Ducted propeller, and is set to
Propeller on every group of Ducted propeller is accommodated in duct intracavitary, i.e., stealthy to set rather than be exposed to outside casing so that small-sized
Unmanned aerial vehicle avoids colliding because of propeller and external object in flight course, so as to effectively improve the safety of complete machine and can
By property.
Description of the drawings
Fig. 1 is the part-structure schematic diagram of the small-sized pilotless aircraft in this preferred embodiment；
Fig. 2 is the structure diagram of another angle of small-sized pilotless aircraft shown in Fig. 1；
Fig. 3 is the structure diagram of Ducted propeller in small-sized pilotless aircraft shown in Fig. 1；
Fig. 4 is the structure diagram of another angle of Ducted propeller shown in Fig. 3；
Fig. 5 is the structure diagram of propeller in Ducted propeller shown in Fig. 3；
Fig. 6 is the perspective view of small-sized pilotless aircraft shown in Fig. 1；
Fig. 7 is the structure diagram of damping rubber pad in small-sized pilotless aircraft shown in Fig. 6；
Fig. 8 is the structure diagram of rubber plug in small-sized pilotless aircraft shown in Fig. 6；
Fig. 9 is the structure diagram of another angle of rubber plug in small-sized pilotless aircraft shown in Fig. 6；
Figure 10 is the structure diagram of sound-absorbing part in small-sized pilotless aircraft shown in Fig. 6.
Specific embodiment
For the ease of understanding the utility model, the utility model is more fully retouched below with reference to relevant drawings
It states.The preferred embodiment of the utility model is given in attached drawing.But the utility model can come in many different forms
It realizes, however it is not limited to embodiment described herein.On the contrary, the purpose for providing these embodiments makes to the utility model
The understanding of disclosure more thorough and comprehensive.
It should be noted that when element is referred to as " being fixed on " another element, it can be directly on another element
Or there may also be elements placed in the middle.When an element is considered as " connection " another element, it can be directly connected to
To another element or it may be simultaneously present centering elements.Term as used herein " vertical ", " horizontal ", " left side ",
" right side " and similar statement are for illustrative purposes only.
Unless otherwise defined, all of technologies and scientific terms used here by the article is led with belonging to the technology of the utility model
The normally understood meaning of technical staff in domain is identical.It is only in the term used in the description of the utility model herein
The purpose of description specific embodiment, it is not intended that in limitation the utility model.Term as used herein " and/or " include
The arbitrary and all combination of one or more relevant Listed Items.
As depicted in figs. 1 and 2, a kind of small-sized pilotless aircraft 100 in this preferred embodiment, including casing 10, Duo Zuhan
Road propeller 20 (such as Fig. 3) and ultrasonic sensor 30.Multigroup Ducted propeller 20 is assemblied on casing 10, for being small-sized
Unmanned aerial vehicle 100 provides power, and ultrasonic sensor 30 is set on casing 10, for playing fixed high work to small drone 100
With.In this embodiment, small-sized pilotless aircraft 100 is the pocket unmanned aerial vehicle that can be accommodated in pocket, is mainly used for
Self-timer, the defeated assistant engineer's tool of the amusement such as take photo by plane.It is to be appreciated that in some other embodiment, small-sized pilotless aircraft 100 also can be used for
Other functions, such as carry out present dispatching etc..
Casing 10 includes upper surface 110 and the lower surface 130 opposite with upper surface 110.Wherein, upper surface 110 is small-sized
The surface of (towards sky) is located above during 100 normal use of unmanned aerial vehicle, lower section is located at when lower surface 130 is normal use
The surface of (towards ground).
Specifically, casing 10 includes upper shell 11 and the lower housing 13 being oppositely arranged with upper shell 11, and upper surface 110 is set
In upper shell 11 backwards to the surface of lower housing 13, lower surface 130 is set to lower housing 13 backwards to the surface of upper shell 11.Meanwhile
Upper shell 11 with lower housing 13 connect and encloses jointly and sets to be formed positioned at installation cavity (not shown) between the two relatively, pacifies for accommodating
Fill other components of small drone 100.
In this embodiment, casing 10 is substantially square platy structure, and in order to reduce the resistance in flight course
It is typically designed with it is certain streamlined, such as square platy structure quadrangle using fillet design etc., be construed as limiting herein.
Meanwhile upper shell 11 and lower housing 13 are made of aluminum alloy material in casing 10, while main screw lift is mitigated, enhancing is whole
The intensity of machine.
Fig. 3 is please referred to, every group of Ducted propeller 20 includes duct housing 21, fixed seat 23, force piece 25 and propeller
27.Each duct housing 21 is assemblied on casing 10 and forms the duct chamber 210 of perforation upper surface 110 and lower surface 130.It is fixed
Seat 23 is set in duct chamber 210, and force piece 25 is assemblied in fixed seat 23 and is contained in duct chamber 210.Propeller 27 is received
It is dissolved in duct chamber 210 and is sequentially connected with force piece 25, by the way that force piece 25 and propeller 27 are contained in duct chamber 210
Design that is interior, being exposed to compared to tradition outside casing 10 avoids touching periphery object in flight course and causing propeller itself
Damage effectively improves the security reliability of complete machine.
Fig. 4 is please referred to, specifically, each duct housing 21 is in the hollow cylindrical of both ends perforation, and fixed seat 23 includes seat
Body 230 and several fixed arms 232 formed are radiated by 230 periphery of pedestal.Pedestal 230 is substantially in the form of annular discs, several fixed arms 232
230 periphery of pedestal is uniformly arranged on, and each fixed arm 232 is connected between the internal chamber wall of pedestal 230 and duct chamber 210.
In this embodiment, fixed arm 232 includes three, and three fixed arms 232 are with 120 degree of angles between the two
Form is uniformly arranged on 230 periphery of pedestal, to ensure the stress equalization of fixed seat 23, to be carried for the force piece 25 being mounted thereon
For balanced support power.In addition, in order to improve the integral strength of fixed seat 23, each fixed seat 23 and respective duct housing 21 1
It is body formed.It is to be appreciated that in some other embodiment, the quantity and structure of fixed arm 232 can as needed depending on, it is and solid
Fixed arm 232 also can use the other manners such as screw, welding to be individually fixedly connected between duct housing 21, not make herein
It limits.
Fig. 5 is please referred to, propeller 27 includes paddle disk 270 and is integrally formed six blades for being set to 270 periphery of paddle disk
272.The hollow cylindrical of the generally both ends perforation of paddle disk 270, six blades 272 are circumferentially disposed along the axis of rotation of paddle disk 270
In the peripheral surface of paddle disk 270.Every blade 272 includes being located at the blade root 2721 of opposite end and blade tip 2723, blade root 2721 with
Paddle disk 270 connects and the central axis of opposite paddle disk 270 tilts at an angle.Every blade 272 from the one of blade root 2721
It holds to one end close to blade tip 2723 and gradually twists, and blade tip 2723 is reversed from lower housing 13 to 11 direction of upper shell.Its
In, the torsional direction all same of six blades 272.
It is to be appreciated that in some other embodiment, the quantity and blade tip 2723 of blade 272 are reversed with respect to blade root 2721
Angle can as needed depending on, be not limited thereto.
Referring again to Fig. 3, each force piece 25 is motor, the stator of each motor and fixation in this embodiment
Seat 23 is fixedly connected, on rotor of each 270 fixing sleeve of paddle disk loaded on each motor, to drive blade 272 under being driven in motor
Synchronous coaxial rotating.
In this embodiment, Ducted propeller 20 includes four groups, and four groups of Ducted propellers 20 are in 10 geometry of casing
The heart is symmetrically disposed on 10 surrounding of casing, to keep balance of the complete machine in flight course.It is to be appreciated that in some other implementation
In example, the quantity of Ducted propeller 20 can as needed depending on, be not limited thereto.
Referring again to Fig. 2, ultrasonic sensor 30 is set in installation cavity, and sound end is exposed to outside lower housing 13,
For being detected.Wherein, ultrasonic wave is that a kind of vibration frequency height that vibration generates occurs under voltage drive by transducing chip
In the mechanical wave of sound wave, notable reflect to form can be generated when encountering impurity or interface and is reflected into echo, and encounter work
Animal physical efficiency generates Doppler effect.Therefore, it is important a member in entire 100 sensing system of small drone.
Fig. 1 and Fig. 6 are please referred to, small-sized pilotless aircraft 100 includes ultrasonic wave anti-interference structure in one of the embodiments,
40, for reducing the interference of flight course China and foreign countries bound pair ultrasonic sensor on the whole, ultrasonic wave is promoted in small drone
100 data stability, so as to promote the flying height of complete machine and attitude stability.
Fig. 7 is please referred to, specifically, ultrasonic wave anti-interference structure 40 includes damping rubber pad 41, and damping rubber pad 41 is set to solid
The surface of force piece 25 is installed in reservation 23, avoids directly contacting firmly between force piece 25 and fixed seat 23.Since force piece 25 exists
During high-speed rotation, noise (making an uproar and the mechanical noise of itself of force piece 25 including wind) and the vibrations of generation, to ultrasonic wave
The validity of 30 numerical value of sensor generates large effect.By this damping rubber pad 41, can buffer with filtration fraction from solid
It is shaken between reservation 23 and force piece 25, changes the propagation medium of noise, reduce influence of the noise to ultrasonic sensor 30.
Fig. 8 and Fig. 9 are please referred to, ultrasonic wave anti-interference structure 40 includes being set to installation cavity in one of the embodiments,
Interior rubber plug 43, rubber plug 43 are connected between upper shell 11 and lower housing 13, and ultrasonic sensor 30 is set in rubber plug 43, and
Sound end exposes to lower housing 13 in ultrasonic sensor 30.
Specifically, rubber plug 43 includes the cock body 430 of one end formation opening 4301 and several support feets 432.Lower housing 13 with
43 corresponding position of rubber plug offers through-hole 132 (as shown in Figure 2), and one end that cock body 430 is provided with opening 4301 is contained in through-hole
In 132, the other end of 430 opposed open 4301 of cock body is connected to upper shell 11 towards the surface of lower housing 13.Several support feets
432, which are set to cock body 430, is provided with the peripheral surface of 4301 one end of opening, and be fixedly supported to lower housing 13 towards upper shell 11
Surface.Ultrasonic sensor 30 is contained in cock body 430, and sound end exposes to lower housing by opening 4301 and through-hole 132
13.In this embodiment, support feet 432 includes three, and three support feets 432 are uniformly arranged on the periphery of cock body 430.It can
To understand ground, in some other embodiment, the quantity of support feet 432 can as needed depending on, and support feet 432 setting
It position also can be as needed, it is only necessary to realize that rubber plug 43 is stably fixed between upper shell 11 and lower housing 13, herein
It is not construed as limiting.
It is installed on lower housing 13, and is set in cock body 430 that is, ultrasonic sensor 30 is indirect, led to
It crosses cock body 430 to be vacantly set between upper shell 11 and lower housing 13 so that ultrasonic sensor 30 and upper shell 11 and lower casing
Body 13 is isolated, and avoids being influenced by upper shell 11 and 13 vibrations of lower housing in flight course, while is also helped filtering and come
The influence made an uproar from the vibrations in 100 flight course of small drone and 25 wind of force piece.Meanwhile ultrasonic sensor 30 is set with
It is damaged in cock body 430, avoiding small drone 100 by extraneous severe impact power.
Figure 10 is please referred to, ultrasonic wave anti-interference structure 40 includes being contained in installation cavity in one of the embodiments,
Sound-absorbing part 45, sound-absorbing part 45 are set to lower housing 13 towards the surface of upper shell 11, flew for changing small drone 100
Influence of the noise to 30 Effective Numerical of ultrasonic sensor is reduced in the route of transmission of noise in journey.In this embodiment, it inhales
Sound part 45 is to be adhered to the lower housing 13 of small drone 100 towards the acoustical cotton on 11 surface of upper shell by gum.It can manage
Solution, in some other embodiment, sound-absorbing part 45 can also be made of other sound-absorbing materials, and the position that sound-absorbing part 45 is set also may be used
It depending on as needed, such as is also provided on upper shell 11, is not limited thereto in addition to being set on lower housing 13.
Please referring again to Fig. 1, small-sized pilotless aircraft 100 includes energy and provides unit 50, electricity in one of the embodiments,
Road plate 60 and radiator structure 70.Circuit board 60 is contained in installation cavity and is set to lower housing 13 towards the table of upper shell 11
Face, energy provides unit 50 and is contained in installation cavity and is set on circuit board 60, for providing electricity for small-sized pilotless aircraft 100
Can, specifically, it is two pieces of lithium batteries being set in installation cavity that energy, which provides unit 50,.Radiator structure 70 includes the first heat conductive pad
71, the first heat conductive pad 71 is set between lower housing 13 and circuit board 60, for providing energy to unit 50 and circuit board 60 produces
Raw heat is conducted to lower housing 13, is radiated through lower housing 13.Wherein, in this embodiment, lower housing 13 is aluminium alloy
Material is made, so as to further enhance the radiating efficiency for providing energy unit 50 and circuit board 60.
Further, radiator structure 70 includes the second heat conductive pad 73, and the second heat conductive pad 73 is set to upper shell 11 and energy
Between unit 50 is provided, conducted for providing energy to the heat that unit 50 and circuit board 60 generate to upper shell 11, through upper casing
Body 11 radiates.Wherein, in this embodiment, lower housing 13 is made of aluminum alloy materials, so as to further enhance to energy
Amount provides the radiating efficiency of unit 50 and circuit board 60.
Wherein, above-mentioned first heat conductive pad, 71 and second heat conductive pad 73 is silica gel heat conductive pad.It is to be appreciated that at some other
In embodiment, the first heat conductive pad 71 and the second heat conductive pad 73 also can be other conductive structures for being conducive to conduction heat, not make herein
It limits.
Still further, radiator structure 70 includes the heat emission hole 75 being opened on upper shell 11 and/or lower housing 13, heat dissipation
Hole 75 is connected with installation cavity, for being discharged to the heat inside complete machine.
In above-mentioned small-sized pilotless aircraft 100, by the way that multigroup Ducted propeller 20 is set to be used as the power resources of complete machine, and set
The propeller 27 being placed on every group of Ducted propeller 20 is accommodated in duct chamber 210, i.e., stealthy to set rather than be exposed to casing
Outside 10 so that small-sized pilotless aircraft 100 avoids colliding because of propeller and external object, so as to effectively improve in flight course
The safety and reliability of complete machine.
The above embodiment only expresses the several embodiments of the utility model, and description is more specific and detailed, but
It should not be interpreted as limiting the scope of the present invention.It should be pointed out that the common skill for this field
For art personnel, without departing from the concept of the premise utility, various modifications and improvements can be made, these are belonged to
The scope of protection of the utility model.Therefore, the protection domain of the utility model patent should be determined by the appended claims.
Claims (10)
1. a kind of small-sized pilotless aircraft, which is characterized in that including：
Casing, including upper surface and the lower surface opposite with the upper surface；And
The multigroup Ducted propeller being assemblied on the casing, Ducted propeller described in every group include the duct shell of both ends perforation
Body, fixed seat, force piece and propeller；
Wherein, each duct housing is assemblied on the casing and forms the culvert for penetrating through the upper surface and the lower surface
Road chamber, the fixed seat are set to the duct intracavitary, and the force piece is assemblied in the fixed seat and is contained in the culvert
Road intracavitary, the propeller are contained in the duct intracavitary and are sequentially connected with the force piece.
2. small-sized pilotless aircraft according to claim 1, which is characterized in that the Ducted propeller includes four groups, four groups
Ducted propeller is symmetrically disposed on the casing surrounding with the casing geometric center.
3. small-sized pilotless aircraft according to claim 1 or 2, which is characterized in that each in Ducted propeller described in every group
The propeller includes paddle disk and is integrally formed six blades for being set to the paddle disk periphery, and each force piece is electricity
Machine, the stator of each motor are fixedly connected with the fixed seat, and each paddle disk is fixed on turning for each motor
On son.
4. small-sized pilotless aircraft according to claim 1, which is characterized in that each fixed seat and the respective culvert
Road housing is integrally formed, and the small-sized pilotless aircraft includes damping rubber pad, and the damping rubber pad is set to the fixed seat peace
Fill the surface of the force piece.
5. small-sized pilotless aircraft according to claim 1, which is characterized in that the casing is included with the upper surface
Upper shell and the lower housing with the lower surface, the upper shell is opposite with the lower housing to be connected and encloses to set jointly to form position
In installation cavity between the two；The small-sized pilotless aircraft includes the rubber plug being set in the installation cavity and is set in the glue
Ultrasonic sensor in plug, the rubber plug are connected between the upper shell and the lower housing, the ultrasonic sensor
Middle sound end exposes to the lower housing.
6. small-sized pilotless aircraft according to claim 5, which is characterized in that the rubber plug includes the plug that one end forms opening
Body and the support feet for being set to the cock body periphery, the lower housing offer through-hole with the rubber plug corresponding position；The plug
One end that body is provided with the opening is contained in the through-hole, and the other end of the relatively described opening of the cock body is connected to described
For upper shell towards the surface of the lower housing, the support feet is set to one end and the fixation that the cock body is provided with the opening
The lower housing is supported in towards the surface of the upper shell；Sound end described in the ultrasonic sensor passes through the opening
The lower housing is exposed to the through-hole.
7. small-sized pilotless aircraft according to claim 5, which is characterized in that the small-sized pilotless aircraft includes being contained in institute
The sound-absorbing part in installation cavity is stated, the sound-absorbing part is set to the lower housing towards the surface of the upper shell.
8. small-sized pilotless aircraft according to claim 1, which is characterized in that the casing is included with the upper surface
Upper shell and the lower housing with the lower surface, the upper shell is opposite with the lower housing to be connected and encloses to set jointly to form position
In installation cavity between the two；The small-sized pilotless aircraft includes the energy being set in the installation cavity and provides unit, circuit
Plate, the first heat conductive pad and the second heat conductive pad, the circuit board are set to the lower housing towards the surface of the upper shell, institute
Energy offer unit to be stated to be set on the circuit board, the first heat conductive pad is set between the lower housing and the circuit board,
Second heat conductive pad is set to the energy and provides between unit and the upper shell.
9. small-sized pilotless aircraft according to claim 8, which is characterized in that the upper shell and/or the lower housing are opened
Equipped with the heat emission hole connected with the installation cavity.
10. small-sized pilotless aircraft according to claim 8, which is characterized in that the upper shell and the lower housing are
Al-alloy casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721208651.5U CN207550505U (en) | 2017-09-20 | 2017-09-20 | Small-sized pilotless aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721208651.5U CN207550505U (en) | 2017-09-20 | 2017-09-20 | Small-sized pilotless aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207550505U true CN207550505U (en) | 2018-06-29 |
Family
ID=62676314
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721208651.5U Expired - Fee Related CN207550505U (en) | 2017-09-20 | 2017-09-20 | Small-sized pilotless aircraft |
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| Country | Link |
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| CN (1) | CN207550505U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499503A (en) * | 2017-09-20 | 2017-12-22 | 湖南基石信息技术有限公司 | Small-sized pilotless aircraft |
-
2017
- 2017-09-20 CN CN201721208651.5U patent/CN207550505U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499503A (en) * | 2017-09-20 | 2017-12-22 | 湖南基石信息技术有限公司 | Small-sized pilotless aircraft |
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Effective date of registration: 20200603 Address after: Room 502, building 19, phase I, Changsha Zhongdian Software Park, No. 39, Jianshan Road, Changsha hi tech Development Zone, Changsha City, Hunan Province Patentee after: Hunan Ou Shi Electronic Technology Co.,Ltd. Address before: 410000 Changsha central power software park headquarters building, 39, pointed mountain road, Changsha hi tech Development Zone, Hunan, A293 Patentee before: Hunan Keyshare Information Technology Co.,Ltd. |
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Granted publication date: 20180629 Termination date: 20200920 |
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