CN113942650A - Device of explosion-proof machine of unmanned aerial vehicle - Google Patents
Device of explosion-proof machine of unmanned aerial vehicle Download PDFInfo
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- CN113942650A CN113942650A CN202111422318.5A CN202111422318A CN113942650A CN 113942650 A CN113942650 A CN 113942650A CN 202111422318 A CN202111422318 A CN 202111422318A CN 113942650 A CN113942650 A CN 113942650A
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- 238000004891 communication Methods 0.000 claims abstract description 7
- 239000000872 buffer Substances 0.000 claims description 18
- 230000035939 shock Effects 0.000 claims description 14
- 230000000712 assembly Effects 0.000 claims description 3
- 238000000429 assembly Methods 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 7
- 238000004880 explosion Methods 0.000 abstract description 5
- 230000003139 buffering effect Effects 0.000 description 8
- 238000013016 damping Methods 0.000 description 6
- 238000001125 extrusion Methods 0.000 description 6
- 238000003860 storage Methods 0.000 description 4
- 230000033001 locomotion Effects 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000006173 Good's buffer Substances 0.000 description 1
- 206010057071 Rectal tenesmus Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 208000012271 tenesmus Diseases 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
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Classifications
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- 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
- B64D17/00—Parachutes
- B64D17/62—Deployment
- B64D17/70—Deployment by springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- 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
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
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- 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
- B64D47/08—Arrangements of cameras
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/06—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs
- F16F15/067—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs using only wound springs
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses an unmanned aerial vehicle anti-explosion device which comprises an unmanned aerial vehicle body, wherein a communicating component is arranged inside the unmanned aerial vehicle body, an expansion component is arranged at the top of the unmanned aerial vehicle body, a control shell is arranged at the bottom of the unmanned aerial vehicle body, a control component is arranged inside the control shell, a camera is arranged at the bottom of the control shell, and supporting components are arranged on two sides of the control shell. According to the invention, through the arrangement of the communication assembly, the driving force control unfolding assembly can be controlled to start when the unmanned aerial vehicle turns on side, the parachute in the unmanned aerial vehicle can be pushed out through the unfolding assembly, the downward falling speed of the unmanned aerial vehicle is effectively reduced through the arrangement of the parachute, the function of preventing the unmanned aerial vehicle from falling is further realized, other sensors are not required to be additionally arranged, the cost of the unmanned aerial vehicle is reduced, and the use effect is improved.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an anti-explosion device for an unmanned aerial vehicle.
Background
The unmanned plane is a non-manned plane operated by radio remote control equipment and a self-contained program control device, is a general name of the unmanned plane, and is an unmanned plane without a cockpit on the plane but provided with an automatic pilot, a program control device and other devices. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, remotely measure and digitally transmit the personnel through equipment such as radar and the like. Since the unmanned aircraft has important significance for future air battles, the research and development work of the unmanned aircraft is carried out in all major military countries in the world.
Among the correlation technique, unmanned aerial vehicle is when normal flight, because the electric wire among the natural environment is more, and the thickness of electric wire is different, when the power cord is thinner, unmanned aerial vehicle is at the in-process of flight, can't detect, and then can't avoid, thereby bump, when unmanned aerial vehicle collides with the external world, the fried machine phenomenon of turning on one's side will appear, thereby cause the tenesmus, the light person causes the crash phenomenon, heavy person injures by a crashing object, do not have good fried machine function, unmanned aerial vehicle's result of use has been reduced.
Disclosure of Invention
The invention aims to solve the defects that the prior art does not have a good anti-explosion function and the using effect of an unmanned aerial vehicle is reduced, and provides an anti-explosion device for the unmanned aerial vehicle.
In order to achieve the purpose, the invention adopts the following technical scheme:
an unmanned aerial vehicle anti-explosion device comprises an unmanned aerial vehicle body, wherein a communication assembly is arranged inside the unmanned aerial vehicle body, an expansion assembly is arranged at the top of the unmanned aerial vehicle body, a control shell is arranged at the bottom of the unmanned aerial vehicle body, a control assembly is arranged inside the control shell, a camera is arranged at the bottom of the control shell, and supporting assemblies are arranged on two sides of the control shell;
through the setting of intercommunication subassembly, the drive force control when can turning on one's side unmanned aerial vehicle expandes the subassembly and starts, through offering of expansion subassembly, can release its inside parachute, through the setting of parachute, the effectual speed that has reduced unmanned aerial vehicle and fall downwards, and then play and prevent exploding quick-witted function, need not additionally set up other sensors moreover, reduced the unmanned aerial vehicle cost, improved the result of use.
The above technical solution further comprises:
the intercommunication subassembly is including seting up in the inside movable groove of unmanned aerial vehicle body, the bottom of activity inslot wall is fixedly connected with battery and wave spring respectively, the fixed surface contact cover in the movable groove, wave spring's top fixedly connected with contact piece, the top of contact piece is run through the contact cover extends to the inside of contact cover, the negative pole port of battery pass through the wire with the contact piece is connected.
The unfolding assembly comprises a movable frame fixed at the top of the unmanned aerial vehicle body, an electric telescopic rod is fixedly connected to one side of the inner wall of the movable frame, a positive port of the storage battery is connected with a positive end of the electric telescopic rod through a wire, and a negative end of the electric telescopic rod is connected with the contact sleeve through a wire.
Sliding connection has the cross between the both sides of expansion frame inner wall, the top of cross is connected with the umbrella face through the rope line, the equal fixedly connected with extrusion spring in both sides of the bottom of cross, two the bottom of extrusion spring all is fixed in the bottom of expansion frame inner wall, the bottom fixedly connected with fixture block of cross, the bayonet socket has been seted up to one side of fixture block, electric telescopic handle's flexible end fixedly connected with is used for inserting the inside lug of bayonet socket.
The top of movable frame all is connected with two apron, two through the rotation of rotation axis the equal fixedly connected with torsional spring in both sides of apron, two sets of torsional springs all with the inner wall fixed connection of movable frame, two sets of the surface of two sets of rotation axes is located to the torsional spring cover respectively.
The control assembly comprises a control groove which is connected with the inside of the control shell in a sliding mode, a damping frame is connected between the two sides of the inner wall of the control groove in a sliding mode, two threaded holes are formed in the damping frame, the top of the damping frame is connected with a circuit board through the two threaded holes, fastening bolts are arranged on the two sides of the circuit board, and the top of the circuit board is fixedly connected with cushion pads through four supporting rods.
Two first slope frames of the equal fixedly connected with in both sides of shock attenuation frame bottom, two the equal sliding connection in inclined plane of first slope frame has the second slope frame, two the equal sliding connection in bottom of second slope frame in the bottom of control groove inner wall, two fixedly connected with damping spring between the second slope frame.
The supporting component comprises a buffer plate which is connected to the side face of the control shell in a sliding mode, the bottom of the buffer plate is fixedly connected with a U-shaped support frame, the outer surface of the U-shaped support frame is fixedly connected with a buffering wear-resistant sleeve, and a buffering spring is fixedly connected between the top of the buffer plate and the bottom of the unmanned aerial vehicle body.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, through the arrangement of the communication assembly, the driving force control unfolding assembly can be started when the unmanned aerial vehicle turns on side, the parachute in the unmanned aerial vehicle can be pushed out through the unfolding assembly, the downward falling speed of the unmanned aerial vehicle is effectively reduced through the arrangement of the parachute, the function of preventing the unmanned aerial vehicle from falling is further realized, other sensors are not required to be additionally arranged, the cost of the unmanned aerial vehicle is reduced, and the using effect is improved.
Drawings
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle explosion-proof machine device provided by the invention;
fig. 2 is a schematic cross-sectional view of the body of the drone of fig. 1;
FIG. 3 is a cross-sectional structural view of the deployment assembly of FIG. 1;
FIG. 4 is a schematic structural view of the cover plate of FIG. 3;
FIG. 5 is a schematic view of the support assembly and control housing assembly of FIG. 1;
FIG. 6 is a schematic structural diagram of the control assembly of FIG. 5;
fig. 7 is a schematic structural view of the shock-absorbing mount of fig. 6.
In the figure: 1. an unmanned aerial vehicle body; 2. a communicating component; 21. a movable groove; 22. a storage battery; 23. a rocking spring; 24. a contact sleeve; 25. a contact block; 3. a deployment assembly; 31. a movable frame; 32. an electric telescopic rod; 33. a cross plate; 34. an umbrella cover; 35. a compression spring; 36. a clamping block; 37. a bump; 38. a cover plate; 39. a torsion spring; 4. a control housing; 5. a control component; 51. a control slot; 52. a shock-absorbing mount; 53. a circuit board; 54. a cushion pad; 55. a first tilt frame; 56. a second tilt frame; 57. a damping spring; 6. a camera; 7. a support assembly; 71. a buffer plate; 72. a U-shaped support frame; 73. a buffering wear-resistant sleeve; 74. a buffer spring.
Detailed Description
The technical solution of the present invention is further explained with reference to the accompanying drawings and specific embodiments.
Example one
As shown in fig. 1-7, the device for the explosion-proof machine of the unmanned aerial vehicle provided by the invention comprises an unmanned aerial vehicle body 1, wherein a communication assembly 2 is arranged inside the unmanned aerial vehicle body 1, a deployment assembly 3 is arranged at the top of the unmanned aerial vehicle body 1, a control shell 4 is arranged at the bottom of the unmanned aerial vehicle body 1, a control assembly 5 is arranged inside the control shell 4, a camera 6 is arranged at the bottom of the control shell 4, and support assemblies 7 are arranged on two sides of the control shell 4;
through the setting of intercommunication subassembly 2, the drive force control when can turning on one's side unmanned aerial vehicle expandes subassembly 3 and starts, through the seting up of expandeing subassembly 3, can release its inside parachute, through the setting of parachute, the effectual speed that has reduced unmanned aerial vehicle and fall downwards, and then play and prevent exploding quick-witted function, need not additionally set up other sensors moreover, reduced the unmanned aerial vehicle cost, improved the result of use.
The above technical solution further comprises:
The unfolding component 3 comprises a movable frame 31 fixed at the top of the unmanned aerial vehicle body 1, one side of the inner wall of the movable frame 31 is fixedly connected with an electric telescopic rod 32, the positive end of the storage battery 22 is connected with the positive end of the electric telescopic rod 32 through a wire, and the negative end of the electric telescopic rod 32 is connected with the contact sleeve 24 through a wire;
through battery 22's positive pole port pass through the wire with electric telescopic handle 32's positive terminal is connected to and electric telescopic handle 32's negative pole end passes through the wire and is connected with contact sleeve 24, make when contact block 25 and contact sleeve 24 contact, battery 22 just can carry out the power supply in a twinkling of an eye to electric telescopic handle 32, and then can control electric telescopic handle 32 and start, have good self-opening function, do not need additionally to set up relevant sensor etc. the effectual unmanned aerial vehicle cost that has reduced, and the production efficiency is improved.
A cross plate 33 is slidably connected between two sides of the inner wall of the movable frame 31, the top of the cross plate 33 is connected with an umbrella cover 34 through a rope, two sides of the bottom of the cross plate 33 are fixedly connected with extrusion springs 35, the bottom ends of the two extrusion springs 35 are fixed at the bottom of the inner wall of the movable frame 31, the bottom of the cross plate 33 is fixedly connected with a clamping block 36, one side of the clamping block 36 is provided with a bayonet, and the telescopic end of the electric telescopic rod 32 is fixedly connected with a lug 37 inserted into the bayonet;
the top of the cross plate 33 is provided with a push rod for pushing the cover plate 38 open, so as to ensure that the cover plate 38 is already in an open state when the umbrella cover 34 moves out of the movable frame 31;
starting through electric telescopic handle 32 can drive lug 37 to the lateral motion, and then lose the chucking to fixture block 36, through the elastic force of extrusion spring 35 self, can extrude cross 33 for cross 33 up-movement, and then shift out adjustable frame 31 with umbrella face 34, the cooperation air current can be effectual opens umbrella face 34, forms the parachute.
The top of the movable frame 31 is rotatably connected with two cover plates 38 through rotating shafts, two torsional springs 39 are fixedly connected to two sides of each cover plate 38, two groups of torsional springs 39 are fixedly connected with the inner wall of the movable frame 31, and the two groups of torsional springs 39 are respectively sleeved on the outer surfaces of the two groups of rotating shafts;
through the setting of two apron 38, can shelter from the top of activity frame 31, through the setting of two torsional springs 39, stability when apron 38 shelters from activity frame 31 can be improved moreover.
In the embodiment, when the unmanned aerial vehicle has a rollover phenomenon when colliding with an external electric wire, the unmanned aerial vehicle rolls over, since the inertia contact block 25 is swung left and right by the swing spring 23, the inertia contact block is connected with the contact sleeve 24 when the inertia contact block 25 is swung, when the contact sleeve 24 is connected with the contact block 25, the storage battery 22 can supply power to the electric telescopic rod 32, so that the electric telescopic rod 32 is opened, and the projection 37 can be driven to move to one side by starting the electric telescopic rod 32, and the clamping of the clamping block 36 is lost, the cross plate 33 can be extruded by the elastic force of the extrusion spring 35, so that the cross plate 33 moves upwards, and then shift out adjustable frame 31 with umbrella face 34, the cooperation air current can be effectual opens umbrella face 34, forms the parachute, has reduced the downward speed of falling of unmanned aerial vehicle.
Example two
As shown in fig. 6 to 7, based on the first embodiment, the control assembly 5 includes a control slot 51 slidably connected inside the control housing 4, a shock absorbing frame 52 is slidably connected between two sides of an inner wall of the control slot 51, two threaded holes are formed in the shock absorbing frame 52, a circuit board 53 is connected to the top of the shock absorbing frame 52 through the two threaded holes, fastening bolts are arranged on two sides of the circuit board 53, and a cushion 54 is fixedly connected to the top of the circuit board 53 through four support rods;
through the setting of blotter 54, can make circuit board 53 and the top of control housing 4 inner wall cushion the contact, further improve shock attenuation buffering effect, and through that fastening bolt's setting in addition for the cooperation screw hole carries out the dismouting with circuit board 53 and shock attenuation frame 52, has good dismouting function, and one side fixedly connected with baffle of control tank 51 is provided with the bolt on the baffle, is used for being connected with control housing 4, has good dismouting function.
Two first inclined frames 55 are fixedly connected to two sides of the bottom of the shock absorption frame 52, second inclined frames 56 are slidably connected to inclined surfaces of the two first inclined frames 55, bottoms of the two second inclined frames 56 are slidably connected to the bottom of the inner wall of the control groove 51, and a shock absorption spring 57 is fixedly connected between the two second inclined frames 56;
in this embodiment, when vibrating from top to bottom through shock attenuation frame 52, can drive two first slope frames 55 and vibrate from top to bottom, through the downward motion of two first slope frames 55, can extrude two second slope frames 56, make two second slope frame 56 relative direction motions, through damping spring 57 self's elastic force, can extrude two second slope frames 56, make two second slope frames 56 move from each other, form reaction force, and then play good buffering shock attenuation effect, when the effectual unmanned aerial vehicle of avoiding weighing down, protect circuit board 53, good shock-absorbing function has, the effectual stability of circuit board 53 damage that appears of fried machine of having solved.
EXAMPLE III
As shown in fig. 5, based on the above-mentioned first or second embodiment, the supporting component 7 includes a buffer plate 71 slidably connected to the side of the control housing 4, a U-shaped supporting frame 72 is fixedly connected to the bottom of the buffer plate 71, a buffer wear-resistant sleeve 73 is fixedly connected to the outer surface of the U-shaped supporting frame 72, and a buffer spring 74 is fixedly connected between the top of the buffer plate 71 and the bottom of the unmanned aerial vehicle body 1.
In this embodiment, through the setting of a U type support frame 72 even, can contact with ground after unmanned aerial vehicle falls, form the support to unmanned aerial vehicle, and through the setting of the wear-resisting cover 73 of buffering, not only play good anti-skidding function, and play certain buffering effect, through the elastic force of buffer spring 74 self, can make buffer board 71 have good buffer capacity, and then gravity when can falling unmanned aerial vehicle offsets, and then improve unmanned aerial vehicle's buffering effect.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111422318.5A CN113942650A (en) | 2021-11-26 | 2021-11-26 | Device of explosion-proof machine of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111422318.5A CN113942650A (en) | 2021-11-26 | 2021-11-26 | Device of explosion-proof machine of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113942650A true CN113942650A (en) | 2022-01-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111422318.5A Withdrawn CN113942650A (en) | 2021-11-26 | 2021-11-26 | Device of explosion-proof machine of unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN113942650A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN120156714A (en) * | 2025-05-14 | 2025-06-17 | 山东南鑫力合智能科技有限公司 | Emergency recovery and landing device for unmanned aerial vehicle |
-
2021
- 2021-11-26 CN CN202111422318.5A patent/CN113942650A/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN120156714A (en) * | 2025-05-14 | 2025-06-17 | 山东南鑫力合智能科技有限公司 | Emergency recovery and landing device for unmanned aerial vehicle |
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Application publication date: 20220118 |