CN108622426A - A kind of unmanned plane impact protector equipment - Google Patents
A kind of unmanned plane impact protector equipment Download PDFInfo
- Publication number
- CN108622426A CN108622426A CN201810383742.5A CN201810383742A CN108622426A CN 108622426 A CN108622426 A CN 108622426A CN 201810383742 A CN201810383742 A CN 201810383742A CN 108622426 A CN108622426 A CN 108622426A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- surge bunker
- buffer
- dish type
- fender bracket
- 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
- 230000001012 protector Effects 0.000 title claims abstract description 16
- 230000035939 shock Effects 0.000 claims abstract description 10
- 239000006096 absorbing agent Substances 0.000 claims abstract description 8
- 241000273930 Brevoortia tyrannus Species 0.000 claims description 48
- 230000003139 buffering effect Effects 0.000 claims description 13
- 238000013016 damping Methods 0.000 claims description 8
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 230000004888 barrier function Effects 0.000 description 10
- 238000010586 diagram Methods 0.000 description 5
- 230000006698 induction Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 241000607479 Yersinia pestis Species 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 201000010099 disease Diseases 0.000 description 1
- 208000037265 diseases, disorders, signs and symptoms Diseases 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Current-Collector Devices For Electrically Propelled Vehicles (AREA)
- Vibration Dampers (AREA)
Abstract
The present invention relates to unmanned plane fields,More particularly to a kind of unmanned plane impact protector equipment,The anti-striker being arranged successively along the clockwise direction of the fuselage of unmanned plane including the dish type fender bracket that can be wrapped up the fuselage of unmanned plane and all wings and at least four,All anti-strikers are connect by a shock absorber part with dish type fender bracket,It the bottom of dish type fender bracket being capable of exposed notch equipped with the undercarriage for unmanned plane,The fuselage roof of unmanned plane is fixed with connecting seat,The top of dish type fender bracket is equipped with can be with the bolted support arm of connecting seat,Anti- striker includes surge bunker,The triggering inductor being arranged in surge bunker and the idler wheel part being arranged outside surge bunker,The bottom of dish type fender bracket is equipped with several miniature adjustment fans,This practicality can be effectively to in-flight carrying out Anti-bumping protection without aircraft,And unmanned plane can be compensated due to unbalance after being impacted,It prevents from unmanned plane from turning on one's side in the air to fall.
Description
Technical field
The present invention relates to unmanned plane field, more particularly to a kind of unmanned plane impact protector equipment.
Background technology
UAV is to utilize radio remote-controlled telemetry equipment and the presetting apparatus provided for oneself referred to as " unmanned plane "
The not manned aircraft manipulated.Without cockpit on machine, but be equipped with navigation and flight control, presetting apparatus and power and
The equipment such as power supply.Ground remote control telemetry station personnel are by equipment such as data-links, to it into line trace, positioning, remote control, telemetering sum number
Word transmits.Compared with manned aircraft, it has the characteristics that small, easy to use, a variety of flight environment of vehicle requirements of adaptation, therefore can
It is widely used in air remote sensing, meteorological research, agriculture plant seeds by airplane and the prevention and control of plant diseases, pest control.
Unmanned plane can distinguish plurality of classes, wherein it is multi-rotor unmanned aerial vehicle to have a classification, while can also be called multiaxis without
It is man-machine, according to propeller quantity, and quadrotor, six rotors, eight rotors can be subdivided into etc..It is generally believed that propeller quantity is more,
Flight is more steady, and operation is easier.
Multi-rotor unmanned aerial vehicle is although small, but its manufacturing cost is not low, and common is all thousands of members, expensive
Being being capable of member up to ten thousand;Multi-rotor unmanned aerial vehicle it is daily in-flight, since ground control person to remote barrier and is flying
Distance is grasped bad between capable unmanned plane, if operation is not proper, unmanned plane may strike on the barrier, this
When will damage multiple wings on unmanned plane, body damage is will result in this way, and even if wing does not damage, it is also possible to
Unbalance deviation after touching, the deviation can result in unmanned plane rollover and fall.
Invention content
In view of the above-mentioned deficiencies in the prior art, it is an object of the present invention to provide a kind of unmanned plane impact protector equipment.
To solve the above problems, the present invention provides following technical scheme:
A kind of unmanned plane impact protector equipment, including the dish type that the fuselage of unmanned plane and all wings can be wrapped up
For fender bracket and at least four successively along the anti-striker of the clockwise direction of the fuselage of unmanned plane setting, all anti-strikers pass through one
A shock absorber part is connect with dish type fender bracket, and the bottom of dish type fender bracket exposed can be lacked equipped with the undercarriage for unmanned plane
Mouthful, the fuselage roof of unmanned plane is fixed with connecting seat, and the top of dish type fender bracket is equipped with can be bolted with connecting seat
Support arm, anti-striker includes surge bunker, the triggering inductor being arranged in surge bunker and the idler wheel part being arranged outside surge bunker,
The bottom of dish type fender bracket is equipped with several miniature adjustment fans.
Further, all shock absorber parts include snubber block and cross sliding block, and one end and the dish type of snubber block are protected
The peripheral surface of retaining frame is fixedly connected, and the other end offers cruciform groove, and cross sliding block movable can be arranged cross
In groove, and four ends of cross sliding block are connected by the inner wall elasticity of a damping spring and cruciform groove respectively
It connects.
Further, one end of all surge bunkers is connect with all cross sliding blocks correspondingly respectively, and
The other end of all surge bunkers is open setting.
Further, the orlop in surge bunker is arranged in the triggering inductor, and buffer arm, buffer arm are equipped in surge bunker
One end it is hinged by the roof in torsional spring and surge bunker, buffer arm is hollow structure, being capable of activity in the free end of buffer arm
Be inserted with extension arm, be additionally provided in surge bunker can horizontally toward its open-mouth sliding buffer board, extension arm far from buffering
One end of arm and the top of buffer board connect, and the extension arm one end and the top of buffer board can level be slidably matched.
Further, all idler wheel parts are located at the buffering front edge of board in respective position surge bunker, idler wheel part packet
Two buffer bars are included, two buffer bars are in that horizontal and the two the same end is fixedly connected with buffer board, and two buffer bars are another
One end is hinged, and there are one buffering wheels.
Further, the one end of all buffer boards far from respective position surge bunker open-mouth be all provided with there are one touching
Bar.
Further, the indentation, there be arranged with two can respectively with the bolted fixed strip of undercarriage, dish type
Fender bracket is cell structure.
Further, all miniature adjustment fans are arranged along the clockwise direction of fuselage successively, and all miniature
Fan is adjusted to correspond with all surge bunkers respectively.
Advantageous effect:A kind of unmanned plane impact protector equipment of the present invention, by all triggering inductors and all miniature tune
Rectification campaign fan is connect with the control handle of multi-rotor unmanned aerial vehicle, and wireless module and control mainboard are equipped in control handle, then more
Rotor wing unmanned aerial vehicle flies, after barrier to be contacted, dish type fender bracket preferential contact barrier, and its face or close barrier
The buffering wheel of the surge bunker of object location is hindered to contradict barrier, rotation occurs for buffering wheel, and release portion divides frictional impact dynamics, and should
Impact force makes buffer board carry out horizontal movement in surge bunker by extension arm and buffer arm, that is, towards in the surge bunker
Triggering inductor direction, and the touching bar of the buffer board can touch the induction end of triggering inductor, and signal passes to control
Wireless module in handle processed, then control is carried out by control mainboard and is carried out with the symmetrical miniature adjustment fan of the triggering inductor
Work, caused unbalance due to hitting to compensate with this, the time of the miniature adjustment fan work can be adjusted to 5S-8S in advance,
And buffer board in surge bunker due to hitting in dynamics movement, cross sliding block coordinate damping spring in cruciform groove into
Row is alleviated, and influence of the impact force to unmanned plane is greatly reduced, this practicality can be effectively to in-flight carrying out anticollision without aircraft
Protection, and unmanned plane can be compensated due to unbalance after being impacted, it prevents unmanned plane from turning on one's side in the air and falls.
Description of the drawings
Fig. 1 is the installation condition schematic diagram one of the present invention;
Fig. 2 is the dimensional structure diagram of the present invention;
Fig. 3 is the enlarged drawing at A in Fig. 2;
Fig. 4 is the installation condition schematic diagram two of the present invention;
Fig. 5 is the installation condition schematic diagram three of the present invention;
Fig. 6 is the sectional view of surge bunker;
Fig. 7 is the dimensional structure diagram of unmanned plane;
Reference sign:Dish type fender bracket 1, notch 1a, fixed strip 1b, support arm 1c, anti-striker 2, surge bunker 2a delay
Arm 2b, extension arm 2c, buffer board 2d, buffer bar 2e, buffering wheel 2f are rushed, bar 2g is touched, triggers inductor 2h, shock absorber part 3, damping
Block 3a, cruciform groove 3b, damping spring 3c, cross sliding block 3d, connecting seat 4, unmanned plane 5, wing 5a, undercarriage 5b are micro-
Type adjusts fan 6.
Specific implementation mode
With reference to the accompanying drawings of the specification and embodiment, specific embodiments of the present invention are described in further detail:
A kind of unmanned plane impact protector equipment shown in referring to Figure 1 to Figure 7, including can by the fuselage of unmanned plane 5 and
The dish type fender bracket 1 and at least four that all wing 5a are wrapped up is successively along the setting of the clockwise direction of the fuselage of unmanned plane 5
Anti- striker 2, all anti-strikers 2 are connect by a shock absorber part 3 with dish type fender bracket 1, and the bottom of dish type fender bracket 1, which is equipped with, to be supplied
The undercarriage 5b of unmanned plane 5 can exposed notch 1a, the fuselage roof of unmanned plane 5 is fixed with connecting seat 4, and dish type is protected
The top of retaining frame 1, which is equipped with, to be buffered including surge bunker 2a, setting with 4 bolted support arm 1c of connecting seat, anti-striker 2
Triggering inductor 2h in the 2a of storehouse and the idler wheel part being arranged outside surge bunker 2a, the bottom of dish type fender bracket 1 is equipped with several micro-
Type adjusts fan 6.
All shock absorber parts 3 include one end and the dish type protection of snubber block 3a and cross sliding block 3d, snubber block 3a
The peripheral surface of frame 1 is fixedly connected, and the other end offers cruciform groove 3b, cross sliding block 3d and movable can be arranged in cross
In type groove 3b, and four ends of cross sliding block 3d are respectively by a damping spring 3c and cruciform groove 3b
Wall elastic connection, after anti-striker 2 collides with the external world, impact force is by cross sliding block 3d by damping spring 3c cross
Irregularly shaken in groove 3b and to buffer.
One end of all surge bunker 2a is connect with all cross sliding block 3d correspondingly respectively, and all slow
The other end for rushing storehouse 2a is open setting, and surge bunker 2a gives cross sliding block 3d to transmit extraneous impact force.
The orlop in surge bunker 2a is arranged in the triggering inductor 2h, and buffer arm 2b, buffer arm are equipped in surge bunker 2a
One end of 2b is hinged by the roof in torsional spring and surge bunker 2a, and buffer arm 2b is hollow structure, in the free end of buffer arm 2b
Movable can be inserted with extension arm 2c, be additionally provided in surge bunker 2a can horizontally toward its open-mouth sliding buffer board 2d,
The one end of extension arm 2c far from buffer arm 2b is connect with the top of buffer board 2d, and the one end extension arm 2c is with buffer board 2d's
Top can level be slidably matched, explanation:Under normal conditions, buffer arm 2b and extension arm 2c make buffer board 2d close to slow to torsional spring
It is a large amount of exposed in the external world to rush storehouse 2a openings one end, then exposed part is taking the lead in contacting extraneous buildings, also
It is to bear impact force at first, which makes buffer board 2d make in surge bunker 2a by buffer arm 2b with extension arm 2c
Horizontal movement, the cooperation of extension arm 2c and buffer board 2d top slides give the movement travel of buffer board 2d, and subsequently through
Torsional spring, buffer board 2d can continue to reset, make its front end largely continue it is exposed outside.
All idler wheel parts are located at the front ends buffer board 2d in respective position surge bunker 2a, and idler wheel part includes two
Buffer bar 2e, two buffer bar 2e are in that horizontal and the two the same end is fixedly connected with buffer board 2d, two buffer bar 2e
The other end is hinged, and there are one buffering wheel 2f, preferential to use buffering wheel 2f due to end in contact external world buildings before buffer board 2d,
By buffering wheel 2f rotations, alleviate part impact force.
The one end of all buffer board 2d far from respective position surge bunker 2a open-mouths is all provided with there are one bar 2g is touched, and is delayed
During punching 2d is moved by external impact power, touching bar 2g connected to it is moved therewith, and its end can contradict triggering
In the induction end of inductor 2h.
Be arranged at the notch 1a two can respectively with the bolted fixed strip 1b of undercarriage 5b, dish type protection
Frame 1 is cell structure, and fixed strip 1b is for coordinating support arm 1c to be detachably connected dish type fender bracket 1 and unmanned plane 5, just
In subsequent repair and maintenance, and it is plastic construction that dish type fender bracket 1 is whole, so cooperation fixed strip 1b is installed
When, it opposite can move, fixed strip 1b connect by bolt with undercarriage 5b.
All miniature adjustment fans 6 are arranged along the clockwise direction of fuselage successively, and all miniature adjustment fans 6
It is corresponded respectively with all surge bunker 2a, when the buffering wheel 2f outside a surge bunker 2a in 1 outside of dish type fender bracket strikes
After barrier, symmetrical miniature adjustment fan 6 starts to rotate with surge bunker 2a, is compensated due to after shock with this, relatively
The rolling power of the impingement position other end, that is, hit part and shake upward, the other end shakes downward.
Operation principle:By the control hand of all triggering inductor 2h and all miniature adjustment fans 6 and multi-rotor unmanned aerial vehicle 5
Handle connects, and is equipped with wireless module and control mainboard in control handle, then multi-rotor unmanned aerial vehicle 5 is flown, barrier to be contacted
After hindering object, 1 preferential contact barrier of dish type fender bracket, and the buffering wheel 2f of some surge bunker 2a by opposite Obstacle Position
Barrier, then buffering wheel 2f rotations are contradicted, release portion divides frictional impact, and the impact force makes buffer board 2d by extension
Arm 2c and buffer arm 2b carries out horizontal movement in surge bunker 2a, that is, towards the triggering inductor side 2h in surge bunker 2a
To, and the touching bar 2g of buffer board 2d can touch the induction end of triggering inductor 2h, and signal passes in control handle
Wireless module, then control and symmetrical triggering inductor 2h miniature adjustment wind are carried out by the control mainboard in control handle
Fan 6 works, which can in advance adjust to 5S-8S, is caused since shock is too quickly to compensate unmanned plane 5 with this
It is unbalance, and buffer board 2d in surge bunker 2a due to hitting in dynamics movement, cross sliding block 3d cooperation damping spring 3c
Alleviated in cruciform groove 3b, greatly reduces influence of the impact force to unmanned plane 5.
The above described is only a preferred embodiment of the present invention, not making any limit to the technical scope of the present invention
System, thus it is every according to the technical essence of the invention to any subtle modifications, equivalent variations and modifications made by above example,
In the range of still falling within technical scheme of the present invention.
Claims (8)
1. a kind of unmanned plane impact protector equipment, it is characterised in that:Including can be by the fuselage of unmanned plane (5) and all wings
The dish type fender bracket (1) and at least four that (5a) is wrapped up is successively along the anti-of the clockwise direction of the fuselage of unmanned plane (5) setting
Striker (2), all anti-strikers (2) are connect by a shock absorber part (3) with dish type fender bracket (1), the bottom of dish type fender bracket (1)
Portion be equipped with for unmanned plane (5) undercarriage (5b) can exposed notch (1a), unmanned plane (5) fuselage roof fixation sets
There is connecting seat (4), the top of dish type fender bracket (1) is equipped with can be with connecting seat (4) bolted support arm (1c), anti-striker
(2) include that surge bunker (2a), the triggering inductor (2h) being arranged in surge bunker (2a) and setting are external in surge bunker (2a)
The bottom of idler wheel part, dish type fender bracket (1) is equipped with several miniature adjustment fans (6).
2. a kind of unmanned plane impact protector equipment according to claim 1, it is characterised in that:All shock absorber parts (3)
Include snubber block (3a) and cross sliding block (3d), one end of snubber block (3a) and the peripheral surface of dish type fender bracket (1) are fixed
Connection, the other end offer cruciform groove (3b), and cross sliding block (3d) movable can be arranged at cruciform groove (3b)
It is interior, and four ends of cross sliding block (3d) pass through the inner wall of a damping spring (3c) and cruciform groove (3b) respectively
Elastic connection.
3. a kind of unmanned plane impact protector equipment according to claim 2, it is characterised in that:All surge bunkers (2a)
One end connect correspondingly with all cross sliding blocks (3d) respectively, and the other end of all surge bunkers (2a) is spacious
Mouth setting.
4. a kind of unmanned plane impact protector equipment according to claim 3, it is characterised in that:The triggering inductor (2h)
Orlop in surge bunker (2a) is set, is equipped with buffer arm (2b) in surge bunker (2a), one end of buffer arm (2b) passes through torsional spring
Hinged with the roof in surge bunker (2a), buffer arm (2b) is hollow structure, can be movable in the free end of buffer arm (2b)
It is inserted with extension arm (2c), the buffer board (2d) for capableing of horizontally toward its open-mouth sliding is additionally provided in surge bunker (2a), is extended
The one end of arm (2c) far from buffer arm (2b) is connect with the top of buffer board (2d), and the one end extension arm (2c) and buffer board
The top of (2d) can level be slidably matched.
5. a kind of unmanned plane impact protector equipment according to claim 4, it is characterised in that:All idler wheel part difference
Front end buffer board (2d) in respective position surge bunker (2a), idler wheel part include two buffer bars (2e), two buffer bars
(2e) is in that horizontal and the two the same end is fixedly connected with buffer board (2d), and two buffer bar (2e) other ends are hinged with
One buffering wheel (2f).
6. a kind of unmanned plane impact protector equipment according to claim 5, it is characterised in that:All buffer boards (2d)
Bar (2g) is touched there are one being all provided in one end far from respective position surge bunker (2a) open-mouth.
7. a kind of unmanned plane impact protector equipment according to claim 1, it is characterised in that:It is symmetrical at the notch (1a)
If there are two can be respectively with undercarriage (5b) bolted fixed strip (1b), dish type fender bracket (1) be cell structure.
8. a kind of unmanned plane impact protector equipment according to claim 1, it is characterised in that:All miniature adjustment wind
Fan (6) successively along the clockwise direction of fuselage arrange, and all miniature adjustment fans (6) respectively with all surge bunkers (2a) one
One corresponds to.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201810383742.5A CN108622426B (en) | 2018-04-26 | 2018-04-26 | A kind of unmanned plane impact protector equipment |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201810383742.5A CN108622426B (en) | 2018-04-26 | 2018-04-26 | A kind of unmanned plane impact protector equipment |
Publications (2)
Publication Number | Publication Date |
---|---|
CN108622426A true CN108622426A (en) | 2018-10-09 |
CN108622426B CN108622426B (en) | 2019-11-08 |
Family
ID=63694468
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201810383742.5A Active CN108622426B (en) | 2018-04-26 | 2018-04-26 | A kind of unmanned plane impact protector equipment |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN108622426B (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110015419A (en) * | 2019-04-18 | 2019-07-16 | 广州供电局有限公司 | Distribution network cable corridor inspection device |
CN113650778A (en) * | 2021-09-02 | 2021-11-16 | 浙江图盛输变电工程有限公司温州科技分公司 | Power grid inspection unmanned aerial vehicle adapting to complex environment |
CN113734431A (en) * | 2021-09-24 | 2021-12-03 | 南京拓恒无人***研究院有限公司 | Unmanned aerial vehicle anti-collision structure and using method thereof |
CN114044153A (en) * | 2022-01-11 | 2022-02-15 | 云奕智创航空科技(南通)有限公司 | A special anticollision locking equipment for unmanned aerial vehicle transportation |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104192304A (en) * | 2014-09-17 | 2014-12-10 | 深圳大学 | Rotor robot system for environment and pedestrian safety |
CN205311898U (en) * | 2016-01-21 | 2016-06-15 | 苏州盛世十月软件技术有限公司 | Anticollision unmanned aerial vehicle |
CN106005384A (en) * | 2016-06-20 | 2016-10-12 | 深圳市勤新科技有限公司 | Unmanned aerial vehicle that protective properties is high |
CN206544595U (en) * | 2017-03-11 | 2017-10-10 | 芜湖元一航空科技有限公司 | A kind of crash structure of fire-fighting unmanned plane |
JP6217054B1 (en) * | 2016-11-04 | 2017-10-25 | 株式会社松屋アールアンドディ | Drone with airbag |
CN206750130U (en) * | 2017-05-10 | 2017-12-15 | 深圳市亿联智能有限公司 | A kind of wireless security protection monitoring device for patrol of flying |
CN206766343U (en) * | 2016-09-08 | 2017-12-19 | 厦门九星天翔航空科技有限公司 | One kind collection sample anticollision unmanned plane |
CN107571991A (en) * | 2017-09-07 | 2018-01-12 | 闫淑萍 | Unmanned plane collision avoidance system |
-
2018
- 2018-04-26 CN CN201810383742.5A patent/CN108622426B/en active Active
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104192304A (en) * | 2014-09-17 | 2014-12-10 | 深圳大学 | Rotor robot system for environment and pedestrian safety |
CN205311898U (en) * | 2016-01-21 | 2016-06-15 | 苏州盛世十月软件技术有限公司 | Anticollision unmanned aerial vehicle |
CN106005384A (en) * | 2016-06-20 | 2016-10-12 | 深圳市勤新科技有限公司 | Unmanned aerial vehicle that protective properties is high |
CN206766343U (en) * | 2016-09-08 | 2017-12-19 | 厦门九星天翔航空科技有限公司 | One kind collection sample anticollision unmanned plane |
JP6217054B1 (en) * | 2016-11-04 | 2017-10-25 | 株式会社松屋アールアンドディ | Drone with airbag |
CN206544595U (en) * | 2017-03-11 | 2017-10-10 | 芜湖元一航空科技有限公司 | A kind of crash structure of fire-fighting unmanned plane |
CN206750130U (en) * | 2017-05-10 | 2017-12-15 | 深圳市亿联智能有限公司 | A kind of wireless security protection monitoring device for patrol of flying |
CN107571991A (en) * | 2017-09-07 | 2018-01-12 | 闫淑萍 | Unmanned plane collision avoidance system |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110015419A (en) * | 2019-04-18 | 2019-07-16 | 广州供电局有限公司 | Distribution network cable corridor inspection device |
CN113650778A (en) * | 2021-09-02 | 2021-11-16 | 浙江图盛输变电工程有限公司温州科技分公司 | Power grid inspection unmanned aerial vehicle adapting to complex environment |
CN113734431A (en) * | 2021-09-24 | 2021-12-03 | 南京拓恒无人***研究院有限公司 | Unmanned aerial vehicle anti-collision structure and using method thereof |
CN113734431B (en) * | 2021-09-24 | 2023-09-01 | 南京拓恒无人***研究院有限公司 | Unmanned aerial vehicle anti-collision structure and application method thereof |
CN114044153A (en) * | 2022-01-11 | 2022-02-15 | 云奕智创航空科技(南通)有限公司 | A special anticollision locking equipment for unmanned aerial vehicle transportation |
CN114044153B (en) * | 2022-01-11 | 2022-03-15 | 云奕智创航空科技(南通)有限公司 | A special anticollision locking equipment for unmanned aerial vehicle transportation |
Also Published As
Publication number | Publication date |
---|---|
CN108622426B (en) | 2019-11-08 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN108622426B (en) | A kind of unmanned plane impact protector equipment | |
GB2565569B (en) | Method and system for landing an unmanned aerial vehicle | |
CN209921623U (en) | Scalable collision avoidance device of unmanned aerial vehicle | |
KR101260370B1 (en) | Composite Protection Structure for Flying Robot with Rotary Wings | |
CN205971873U (en) | Many rotor unmanned aerial vehicle prevent crashing | |
CN106218873B (en) | A kind of anti-crash protection structure of unmanned plane | |
CN205707386U (en) | A kind of UAV Intelligent safe recovery device | |
Fujita et al. | Robustness analysis on aerial deployment motion of a Mars aircraft using multibody dynamics simulation: effects of wing-unfolding torque and timing | |
CN208102336U (en) | Rotor protection mechanism in a kind of unmanned plane | |
CN213473501U (en) | Unmanned aerial vehicle collision avoidance device | |
CN110979695A (en) | Automatic parachute throwing condition interpretation method for parachuting recovery unmanned aerial vehicle | |
CN206372523U (en) | Kite aircraft | |
WO2019061386A1 (en) | Unmanned aerial vehicle fall protection device | |
CN210503170U (en) | Plant protection unmanned aerial vehicle based on 5G networking technology | |
CN207328825U (en) | A kind of unmanned vehicle | |
CN213443093U (en) | Bird-driving unmanned aerial vehicle | |
CN211844925U (en) | Unmanned aerial vehicle flight buffer stop | |
CN213354843U (en) | Bird unmanned aerial vehicle is driven to many rotors | |
CN112478186B (en) | Power distribution network inspection unmanned aerial vehicle based on vehicle-mounted system | |
CN109625311A (en) | A kind of production method of Small General Aircraft cargo hold load-carrying mark | |
CN207536123U (en) | A kind of damping tube for preventing unmanned plane undercarriage from bouncing | |
CN205131691U (en) | Be applied to unmanned aerial vehicle's elastic suspension damping device | |
CN211059607U (en) | Target drone avionics system shock absorption and fixing device | |
CN210555562U (en) | Unmanned aerial vehicle shock attenuation undercarriage | |
CN210063380U (en) | Unmanned aerial vehicle with wing protector |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |