CN207523953U - Unmanned plane with buffer structure - Google Patents
Unmanned plane with buffer structure Download PDFInfo
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- CN207523953U CN207523953U CN201721574946.4U CN201721574946U CN207523953U CN 207523953 U CN207523953 U CN 207523953U CN 201721574946 U CN201721574946 U CN 201721574946U CN 207523953 U CN207523953 U CN 207523953U
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- unmanned plane
- buffer
- stabilizer blade
- antenna
- host computer
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Abstract
The utility model discloses a kind of unmanned planes with buffer structure, including cabin and wing, further include Mini SAR modules, Mini SAR modules include radar host computer and the antenna being connect with radar host computer signal, and radar host computer is arranged in cabin and is connected by the data-link host of data line and unmanned plane；Antenna includes a reception antenna and a transmitting antenna, and is installed in below wing；Undercarriage 3 includes nose-gear and rear undercarriage, and nose-gear includes two stabilizer blades positioned at fuselage both sides, and feet bottom is equipped with wheel；Each stabilizer blade is correspondingly arranged a gas spring connecting rod, and one end of gas spring connecting rod is connected on stabilizer blade 3, and the other end is connected on fuselage, and forms acute triangle region between gas spring connecting rod corresponding to stabilizer blade, stabilizer blade and fuselage.Wherein bolster plays the role of buffering, prevents from UAV Landing or breaks down to cause the damage of radar host computer when shaking, influence the work of radar host computer.
Description
Technical field
The utility model is related to unmanned plane fields, and in particular to the unmanned plane with buffer structure.
Background technology
Unmanned plane is with its advantage such as flexible, fast and convenient, it has also become land mapping, emergency disaster relief, economic construction etc.
The important way of aspect data acquisition.Traditional unmanned plane, which measures, is generally optical photography, and optics boat takes the photograph system climate, time
Limit it is larger, airborne synthetic aperture radar it is emergent still not extensively.SAR is mainly mounted in satellite, has on the equipments such as man-machine, application
In space flight, ocean, military detection and monitoring, feature is high resolution, and energy all weather operations can efficiently identify camouflage and penetrate
Cloak.Obtained high azimuth resolution is equivalent to the azimuth resolution that a wide aperture antenna can be provided.
Utility model content
The purpose of this utility model is to provide a kind of unmanned planes with buffer structure, solve unmanned plane loading SAR systems
After system, host is directly installed in cabin not over buffer structure and is given a shock the problem of being easily damaged.
To solve the technical issues of above-mentioned, the utility model uses following technical scheme：
A kind of unmanned plane with buffer structure including cabin and wing, further includes Mini-SAR modules, the Mini-
SAR modules include radar host computer and the antenna being connect with radar host computer signal, and the radar host computer is arranged in cabin and passes through
The data-link host of data line and unmanned plane connects；The antenna includes a reception antenna and a transmitting antenna, and pacifies
Below wing；
The undercarriage includes nose-gear and rear undercarriage, and the nose-gear includes two branch positioned at fuselage both sides
Foot, the feet bottom are equipped with wheel；Each stabilizer blade is correspondingly arranged a gas spring connecting rod, and the gas spring connects
One end of extension bar is connected on stabilizer blade, and the other end is connected on fuselage, and gas spring connecting rod and machine corresponding to stabilizer blade, stabilizer blade
Acute triangle region is formed between body.
Four mounting holes fixations may be used for radar host computer and in cabin, antenna includes reception, each one of transmitting antenna,
Antenna long side is asked to be in same level, electromagnetic horn rear portion is there are four mounting hole, and respectively there are one auxiliary mounting holes for both sides.Thunder
Upper no metal is directed toward up to antenna installation requirement antenna main beam to block, therefore antenna is positioned over below wing.Radar antenna is pacified
Assembling structure part and wing needs are customized according to wing, the size of antenna and setting angle.
After SAR system is loaded on unmanned plane, it to be just correspondingly arranged reception antenna and transmitting antenna under the wings of an airplane, it is original
Unmanned plane undercarriage height it is relatively low, so wing below do not leave the enough spaces of antenna for, for ensure antenna safety, should
Liftoff more than the 10CM of antenna is ensured, so needing the height of increase undercarriage.But improved unmanned aerial vehicle body weight increases,
The strength bigger that undercarriage is born during landing, along with can be inherently easily damaged after the height increase of undercarriage, so need pair
Undercarriage is reinforced.
Undercarriage in the application is tail wheel type landing gear, and wherein nose-gear is main landing gear, using aluminium alloy plus
Composite material is reinforced；Damping device is installed on undercarriage, damping device connects undercarriage using gas spring connecting rod
It is good to unload power effect for lower part and fuselage.
As preference, the long side of the reception antenna and transmitting antenna is in same level.In order to same with specification
The transmitting and reception of one polarized wave H or V, ordered record polarization radar signal.
As preference, the interface of the Mini-SAR modules and unmanned plane include power supply interface, data transmission interface and
Electromagnetic interface.
As preference, the power supply interface is connect with power supply, the supply voltage of the power supply is 20-28V, maximum output
Electric current is 5.35-7.5A, capacity ＞ 60Wh.
Mini-SAR systems maximum power dissipation is less than 150W, and power supply voltage range is 24V ± 4V.When system imaging works, put down
Equal power consumption is less than 90W.The requirement of system stream time is more than 0.5 hour.Using on machine during battery powered, it is desirable that provided on machine
Remote-controlled power switch.
As preference, the control interface of Mini-SAR modules uses the PWM of 5V to match with unmanned plane output interface
Control.
As preference, the data transmission interface form is RS485 differential interfaces or two-way RS232 interface.
The Mini-SAR of real time imagery function is equipped with, 8Mbps is more than to the bandwidth requirement of data transmission, interface form is
RS485 differential interfaces, data format are self-defining data form, and common definition is required according to Data transfer system.
If SAR system uses two-way RS232 interface, realize that ground faces the control of airborne equipment, code check 9600bps.
As preference, the reception antenna and transmitting antenna are located on same wing and two center of antenna spacing ＞
60cm is configured with the counterweight antenna with its shape, size and weight all same on another wing.
Counterweight antenna auxiliary keeps the balance of unmanned plane.
As preference, the radar host computer is fixed on cabin bottom by bolster, wherein,
The bolster into spherical shape, including upper buffer part fixed with radar host computer and with the fixed lower buffering in cabin bottom
Portion, the upper buffer part and lower buffer part are flexibly connected by the protrusion and groove being adapted, and the protrusion and groove are in slow
Rush portion's shape；
Spring is equipped between the upper buffer part and lower buffer part, the spring one end is fixed on the flat of buffer part bottom
On face, in the plane at the top that the other end is fixed on lower buffer part.
Bolster is connected and composed by upper buffer part and lower buffer part by spring, has certain cushioning effect, especially
Cushioning effect on vertical direction.In addition, the buffer part shape protrusion being adapted is additionally provided between upper buffer part and lower buffer part
And groove, the upper relative displacement that may have horizontal direction between buffer part and lower buffer part when exposed to external forces, due to protrusion and
Groove is buffer part shape, can relatively rotate and play cushioning effect in non-vertical direction.
As preference, the distance between the lower surface of the upper buffer part and the upper surface of lower buffer part are along bolster
Radially gradually increase.
When upper buffer part and lower buffer part relatively rotate, edge will not mutually be hit, and enhance cushion performance, no
It can influence the work of radar host computer.
As preference, the fuselage is equipped with connection sheet with stabilizer blade junction, the connection sheet rear end is turned under curved
Into at an acute angle between fixed part and the connection sheet and fixed part, the stabilizer blade stabilizer blade and fixed part integrated molding.
Fuselage and nose-gear junction are reinforced, increase the contact area of undercarriage and fuselage using connection sheet,
Disperse stress.In addition, at an acute angle between connection sheet and fixed part and have certain toughness, during landing, cushioning effect can be played,
Have no effect on the pneumatic property of unmanned plane.
As preference, buffer bar is provided between the connection sheet and fixed part, the buffer bar, connection sheet and fixation
Delta-shaped region is formed between portion.
When unmanned plane break down can not stable landing when, undercarriage can be anti-by bigger impact force during landing
Only connection sheet and fixinig plate are broken by greater impact, set buffer bar.
As preference, the buffer bar both ends are both provided with spherical parts, and connection sheet and fixed part are connect with buffer bar
Place is both provided with cavity, and the size and shape of the cavity is adapted with the size and shape of spherical parts.
After fixinig plate and connection sheet are by impact force, angle therebetween can change, and buffer bar can also be generated
Certain torque, so being connected between buffer bar and connection sheet, fixed part by spherical parts with cavity, spherical parts can be in cavity
Inside it is freely rotated.
Compared with prior art, the beneficial effects of the utility model are at least one of following：
MINI-SAR is applied on unmanned plane, traditional unmanned plane is overcome and takes the photograph system climate, time using optics boat
Limit the problem of larger.
MINI-SAR described in the utility model develops control interface, and the interface and the load of unmanned plane autopilot control
Low and high level interface standard is consistent, is connected by the interface with unmanned plane autopilot.
Bolster plays the role of buffering, prevents from UAV Landing or break down to cause the damage of radar host computer when shaking
It is bad, influence the work of radar host computer.
The application increases the height of undercarriage, and there is provided the gas spring connecting rods being adapted with undercarriage, unload power effect
Fruit is good.
There is provided connection sheets, increase undercarriage and the area of fuselage junction, can play the role of disperseing stress.
Buffer bar both ends are connected by spherical parts and cavity with fixinig plate, connection sheet, and spherical parts can be in cavity freely
Rotation.
Description of the drawings
Fig. 1 is the structure diagram of unmanned plane of the utility model with buffer structure.
Fig. 2 is the utility model radar host computer and cabin bottom connection diagram.
Fig. 3 is the structure diagram of the utility model bolster.
Fig. 4 is the sectional view of unmanned plane of the utility model with buffer structure.
Fig. 5 is the connection diagram of the utility model nose-gear and fuselage.
Specific embodiment
In order to make the purpose of the utility model, technical solutions and advantages more clearly understood, below in conjunction with attached drawing and implementation
Example, the present invention is further described in detail.It should be appreciated that specific embodiment described herein is only used to explain
The utility model is not used to limit the utility model.
Embodiment 1：
A kind of unmanned plane with buffer structure is present embodiments provided, as shown in Figure 1, including cabin 1 and wing 2, also
Including Mini-SAR modules, the Mini-SAR modules include radar host computer 4 and the antenna 3 being connect with 4 signal of radar host computer, institute
Radar host computer 4 is stated to be arranged in cabin 1 and connect by the data-link host of data line and unmanned plane；The antenna 3 includes one
A reception antenna and a transmitting antenna, and it is installed in 2 lower section of wing；
The undercarriage 63 includes nose-gear and rear undercarriage 63, and the nose-gear includes two positioned at fuselage both sides
A stabilizer blade 61,61 bottom end of stabilizer blade are equipped with wheel；Each stabilizer blade 61 is correspondingly arranged a gas spring connecting rod 62,
One end of the gas spring connecting rod 62 is connected on stabilizer blade 61, and the other end is connected on fuselage, and stabilizer blade 61, stabilizer blade 61 pair
Acute triangle region is formed between the gas spring connecting rod 62 and fuselage answered.
Four mounting holes fixations may be used for radar host computer 4 and in cabin 1, antenna 3 includes reception, transmitting antenna each one
It is a, it is desirable that 3 long side of antenna is in same level, and 3 rear portion of electromagnetic horn is there are four mounting hole, and respectively there are one assist admittedly for both sides
Determine hole.3 installation requirement antenna of radar antenna, 3 main beam is directed toward upper no metal and blocks, therefore antenna 3 is positioned over 2 lower section of wing.
3 mounting structure of radar antenna and wing 2 need to be customized according to wing 2, the size of antenna 3 and setting angle.
Mini-SAR modules in the present embodiment are appointed by radar host computer on machine 4, antenna 3, Inertial Measurement Unit, radar load
Business control software, radar data are downloaded several parts such as software and are formed.Radar host computer 4 is located in cabin 1, and antenna 3 is mounted on machine
2 lower section of the wing, other parts are the conventional arrangements carried out according to the prior art.The highest of X service bands is differentiated in the present embodiment
Rate 0.3m, is worked using band pattern, has two kinds of single polarization, complete polarization HH, VV, HV, VH operating modes, can be round-the-clock to mesh
It marks region and carries out effective microwave imaging, image should be clearly without apparent noise.Important technological parameters are as shown in the table：
| Frequency range | X wave bands | Flying height | 50- 3000 m |
| Operating distance | 0.1 - 6 km | Operating mode | Band |
| Resolution ratio | 0.3 m | Angular field of view | Fixed viewpoint 30o ~ 60o |
| Strip width | 0.15– 3 km | Power consumption | <120 W |
| Supply voltage | 28 V | Central electronic equipment size | 160 * 150 * 35 mm |
| Weight | < 2kg |
The present embodiment uses -1 mapping type UAV flight's Mini-SAR hosts of Kaiyang using plan, and technical parameter is as follows
Table：
| Size | 3250*2550mm | Bare machine weight | 16kg |
| Maximum fuel amount | 12L | Load-carrying | 6kg |
| Maximum take-off weight | 34kg | Mission module size | 400*240*320mm |
| Oil consumption | 2.5L/h | Cruising speed | 90—160km/h |
| Voyage | 480km | Communication distance | 30km |
| Ceiling | 5500m | Wind resistance | 6 grades |
After SAR system is loaded on unmanned plane, it to be just correspondingly arranged reception antenna and transmitting antenna under the wings of an airplane, it is original
Unmanned plane the height of undercarriage 6 it is relatively low, so do not leave the enough spaces of antenna for below wing, to ensure antenna safety,
It is ensured that liftoff more than the 10CM of antenna, so needing the height of increase undercarriage 6.But improved unmanned aerial vehicle body weight increases
Add, the strength bigger that undercarriage 6 is born during landing, along with can be inherently easily damaged after the height increase of undercarriage 6, so
Undercarriage 6 need to be reinforced.
Undercarriage 6 in the application is tail wheel type landing gear 6, and wherein nose-gear is main landing gear 6, using aluminium alloy
Composite material is added to be reinforced；Damping device is installed on undercarriage 6, damping device is risen and fallen using the connection of gas spring connecting rod
6 lower part of frame and fuselage, it is good to unload power effect.
Embodiment 2：
The present embodiment further defines on the basis of embodiment 1：The long edge position of the reception antenna and transmitting antenna
In same level.In order to the transmitting and reception with the same polarized wave H or V of specification, ordered record polarization radar signal.
Embodiment 3：
The present embodiment further defines on the basis of embodiment 1：The interface of the Mini-SAR modules and unmanned plane
Including power supply interface, data transmission interface and electromagnetic interface.
Embodiment 4：
The present embodiment further defines on the basis of embodiment 3：The power supply interface is connect with power supply, the electricity
The supply voltage in source is 20-28V, maximum output current 5.35-7.5A, capacity ＞ 60Wh.
Mini-SAR systems maximum power dissipation is less than 150W, and power supply voltage range is 24V ± 4V.When system imaging works, put down
Equal power consumption is less than 90W.The requirement of system stream time is more than 0.5 hour.Using on machine during battery powered, it is desirable that provided on machine
Remote-controlled power switch.Requirement of the unmanned plane of the application to power supply is as shown in the table：
| Supply voltage | Maximum output current | Continuous power-on time | Capacity |
| 20V | 7.5A | 0.5h | ＞ 60Wh |
| 24V is preferentially selected | 6.25A | 0.5h | ＞ 60Wh |
| 28V | 5.35 | 0.5h | ＞ 60Wh |
Embodiment 5：
The present embodiment further defines on the basis of embodiment 3：The data transmission interface form is poor for RS485
Tap mouth or two-way RS232 interface.
The Mini-SAR of real time imagery function is equipped with, 8Mbps is more than to the bandwidth requirement of data transmission, interface form is
RS485 differential interfaces, data format are self-defining data form, and common definition is required according to Data transfer system.
If SAR system uses two-way RS232 interface, realize that ground faces the control of airborne equipment, code check 9600bps.
Embodiment 6：
The present embodiment further defines on the basis of embodiment 2：The reception antenna and transmitting antenna are located at same
On a wing 2 and two antennas, 3 center spacing ＞ 60cm, it is configured with and its shape, size and weight all same on another wing 2
Counterweight antenna.
Counterweight antenna auxiliary keeps the balance of unmanned plane.
Embodiment 7：
The present embodiment further defines on the basis of embodiment 1：The radar host computer 4 is fixed on by bolster 5
1 bottom of cabin, as shown in Fig. 2, wherein,
The bolster 5 is fixed including upper buffer part 51 fixed with radar host computer 4 and with 1 bottom of cabin into spherical shape
Lower buffer part 52, the upper buffer part 51 and lower buffer part 52 are flexibly connected by the protrusion 53 and groove being adapted, described prominent
Rise 53 and groove be in buffer part shape；
Spring 54 is equipped between the upper buffer part 51 and lower buffer part 52, described 54 one end of spring is fixed on buffer part
In the plane of 51 bottoms, in the plane at the top that the other end is fixed on lower buffer part 52.
Bolster 5 is connected and composed by upper buffer part 51 and lower buffer part 52 by spring 54, has certain cushioning effect,
Cushioning effect especially on vertical direction.In addition, be additionally provided between upper buffer part 51 and lower buffer part 52 be adapted it is slow
Portion's shape protrusion 53 and groove are rushed, it is upper when exposed to external forces to have the opposite of horizontal direction between buffer part 51 and lower buffer part 52
Displacement since protrusion 53 and groove are buffer part shape, can relatively rotate and play cushioning effect in non-vertical direction.
Embodiment 8：
The present embodiment further defines on the basis of embodiment 7：The lower surface of the upper buffer part 51 and lower buffering
The distance between the upper surface in portion 52 is gradually increased along the radial direction of bolster 5, as shown in Figure 3.
When upper buffer part 51 and lower buffer part 52 relatively rotate, edge will not mutually be hit, and enhance resiliency
Can, do not interfere with the work of radar host computer 4.
Embodiment 9：
The present embodiment further defines on the basis of embodiment 3：The control interface of Mini-SAR modules uses and nothing
The PWM controls for the 5V that man-machine output interface matches.
Embodiment 9：
The present embodiment further defines on the basis of embodiment 3：The fuselage is equipped with company with 61 junction of stabilizer blade
Contact pin 64,64 rear end of connection sheet are bent downwardly to form between fixed part 66 and the connection sheet 64 and fixed part 66 in sharp
Angle, the stabilizer blade stabilizer blade are integrally formed with fixed part.
Fuselage and nose-gear junction are reinforced, increase the contact area of undercarriage 6 and fuselage using connection sheet,
Disperse stress.In addition, at an acute angle between connection sheet and fixed part and have certain toughness, during landing, cushioning effect can be played,
Have no effect on the pneumatic property of unmanned plane.
Embodiment 9：
The present embodiment further defines on the basis of embodiment 3：It is set between the connection sheet 64 and fixed part 66
There is buffer bar 65, delta-shaped region is formed between the buffer bar 65, connection sheet 64 and fixed part 66.
When unmanned plane break down can not stable landing when, undercarriage 6 can be anti-by bigger impact force during landing
Only connection sheet and fixinig plate are broken by greater impact, set buffer bar.
Embodiment 9：
The present embodiment further defines on the basis of embodiment 3：65 both ends of buffer bar are both provided with spherical parts
67, and connection sheet 64 and fixed part 66 are both provided with cavity, the size and shape and ball of the cavity with 65 junction of buffer bar
The size and shape of shape part 67 is adapted.
After fixinig plate and connection sheet are by impact force, angle therebetween can change, and buffer bar can also be generated
Certain torque, so being connected between buffer bar and connection sheet, fixed part by spherical parts with cavity, spherical parts can be in cavity
Inside it is freely rotated.
Although reference be made herein to the utility model is described in multiple explanatory embodiments of the utility model, still,
It should be understood that those skilled in the art can be designed that a lot of other modifications and embodiment, these modifications and embodiment
It will fall within spirit disclosed in the present application and spirit.More specifically, it discloses in the application, drawings and claims
In the range of, a variety of variations and modifications can be carried out to the building block and/or layout of theme combination layout.In addition to building block
And/or outside the modification and improvement of layout progress, to those skilled in the art, other purposes also will be apparent.
Claims (10)
1. a kind of unmanned plane with buffer structure, including cabin（1）, wing（2）And undercarriage（6）, it is characterised in that：Also wrap
Mini-SAR modules are included, the Mini-SAR modules include radar host computer（4）With with radar host computer（4）The antenna of signal connection
（3）, the radar host computer（4）It is arranged on cabin（1）It is interior and pass through the data-link host of data line and unmanned plane connect；The day
Line（3）Including a reception antenna and a transmitting antenna, and it is installed in wing（2）Lower section；
The undercarriage（6）Including nose-gear and rear undercarriage（63）, the nose-gear is including positioned at the two of fuselage both sides
A stabilizer blade（61）, the stabilizer blade（61）Bottom end is equipped with wheel；Each stabilizer blade（61）A gas spring is correspondingly arranged to connect
Extension bar（62）, the gas spring connecting rod（62）One end be connected to stabilizer blade（61）On, the other end is connected on fuselage, and stabilizer blade
（61）, stabilizer blade（61）Corresponding gas spring connecting rod（62）Acute triangle region is formed between fuselage.
2. the unmanned plane according to claim 1 with buffer structure, which is characterized in that the reception antenna and transmitting day
The long side of line is in same level.
3. the unmanned plane according to claim 1 with buffer structure, which is characterized in that the Mini-SAR modules and nothing
Man-machine interface includes power supply interface, data transmission interface and electromagnetic interface；The power supply interface is connect with power supply, the power supply
Supply voltage be 20-28V, maximum output current 5.35-7.5A, capacity ＞ 60Wh；The data transmission interface form
For RS485 differential interfaces or two-way RS232 interface.
4. the unmanned plane according to claim 3 with buffer structure, which is characterized in that the control of Mini-SAR modules connects
Mouth is controlled using the PWM of the 5V to match with unmanned plane output interface.
5. the unmanned plane according to claim 2 with buffer structure, which is characterized in that the reception antenna and transmitting day
Line is located at same wing（2）Upper and two antennas（3）Center spacing ＞ 60cm, another wing（2）On be configured with its shape,
The counterweight antenna of size and weight all same.
6. the unmanned plane according to claim 1 with buffer structure, which is characterized in that the radar host computer（4）Pass through
Bolster（5）It is fixed on cabin（1）Bottom, wherein,
The bolster（5）Including with radar host computer（4）Fixed upper buffer part（51）With with cabin（1）Bottom is fixed lower slow
Rush portion（52）, the upper buffer part（51）With lower buffer part（52）Pass through the protrusion being adapted（53）It is flexibly connected with groove, institute
State protrusion（53）It is hemispherical with groove；
The upper buffer part（51）With lower buffer part（52）Between be equipped with spring（54）, the spring（54）One end is fixed on slow
Rush portion（51）In the plane of bottom, the other end be fixed on lower buffer part（52）Top plane on.
7. the unmanned plane according to claim 6 with buffer structure, which is characterized in that the upper buffer part（51）Under
Surface and lower buffer part（52）The distance between upper surface along bolster（5）Radial direction gradually increase.
8. the unmanned plane according to claim 1 with buffer structure, which is characterized in that the fuselage and stabilizer blade（61）Even
The place of connecing is equipped with connection sheet（64）, the connection sheet（64）Rear end is bent downwardly to form fixed part（66）And the connection sheet（64）
With fixed part（66）Between at an acute angle, the stabilizer blade and fixed part（66）It is integrally formed.
9. the unmanned plane according to claim 8 with buffer structure, which is characterized in that the connection sheet（64）With fixation
Portion（66）Between be provided with buffer bar（65）, the buffer bar（65）, connection sheet（64）And fixed part（66）Between form triangle
Shape region.
10. the unmanned plane according to claim 9 with buffer structure, which is characterized in that the buffer bar（65）Both ends
It is both provided with spherical parts（67）, and connection sheet（64）And fixed part（66）With buffer bar（65）Junction is both provided with cavity, institute
State the size and shape and spherical parts of cavity（67）Size and shape be adapted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721574946.4U CN207523953U (en) | 2017-11-22 | 2017-11-22 | Unmanned plane with buffer structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721574946.4U CN207523953U (en) | 2017-11-22 | 2017-11-22 | Unmanned plane with buffer structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207523953U true CN207523953U (en) | 2018-06-22 |
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| CN201721574946.4U Expired - Fee Related CN207523953U (en) | 2017-11-22 | 2017-11-22 | Unmanned plane with buffer structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112259948A (en) * | 2020-12-22 | 2021-01-22 | 南京钢果电子科技有限公司 | Integrated antenna for unmanned aerial vehicle |
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2017
- 2017-11-22 CN CN201721574946.4U patent/CN207523953U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112259948A (en) * | 2020-12-22 | 2021-01-22 | 南京钢果电子科技有限公司 | Integrated antenna for unmanned aerial vehicle |
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Granted publication date: 20180622 Termination date: 20211122 |