CN112758310A - Multi-functional protection undercarriage of unmanned aerial vehicle - Google Patents
Multi-functional protection undercarriage of unmanned aerial vehicle Download PDFInfo
- Publication number
- CN112758310A CN112758310A CN202110282987.0A CN202110282987A CN112758310A CN 112758310 A CN112758310 A CN 112758310A CN 202110282987 A CN202110282987 A CN 202110282987A CN 112758310 A CN112758310 A CN 112758310A
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- CN
- China
- Prior art keywords
- cavity
- main support
- unmanned aerial
- support frame
- aerial vehicle
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Classifications
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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
- B64C25/54—Floats
- B64C25/56—Floats inflatable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- 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
Abstract
The invention relates to the field of accessories of unmanned aerial vehicles and discloses a multifunctional protective undercarriage of an unmanned aerial vehicle, which comprises a main support frame fixed at the bottom of the unmanned aerial vehicle, wherein a main support rod is fixed at the lower side of the main support frame, connecting balls are rotatably arranged at two sides of the main support rod, supporting blocks capable of being detached are symmetrically arranged at two sides of the main support frame, an installation cavity with an opening facing to one side close to the main support frame is arranged in each supporting block, an installation assembly is arranged in each installation cavity, and limiting cavities are communicated in the end walls at the upper side and the lower side of each installation cavity. This multi-functional protection undercarriage of unmanned aerial vehicle can break down when unmanned aerial vehicle is about to fall into the aquatic from the high altitude, through launching the stabilizer plate and aerifing the mode that makes the gasbag inflation expand and expand to the gasbag, makes unmanned aerial vehicle can stably float on the surface of water to avoid unmanned aerial vehicle to intake, and then solved unmanned aerial vehicle and fallen into the fragile problem of aquatic.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle accessories, in particular to a multifunctional protective undercarriage for an unmanned aerial vehicle.
Background
The unmanned aerial vehicle is an unmanned aerial vehicle operated by a radio remote control device and a self-contained program control device, or is completely or intermittently and autonomously operated by an on-board computer, and is generally used for shooting in the civil field, the shooting scene is complex, and the unmanned aerial vehicle can shoot on the water surface, the ground and between jungles.
However because unmanned aerial vehicle's power is provided by the battery, if unmanned aerial vehicle still does not return to when the condition on ground before battery power exhausts, the unmanned aerial vehicle chance drops to ground or aquatic from the high altitude to make unmanned aerial vehicle internal mechanism receive comparatively serious damage, if unmanned aerial vehicle also has probably to drop from the high altitude and make unmanned aerial vehicle damage if mechanical failure appears when normal operating simultaneously.
Disclosure of Invention
The multifunctional protection undercarriage of the unmanned aerial vehicle has the advantage of multifunctional protection, and solves the problem that the unmanned aerial vehicle is damaged due to the fact that the unmanned aerial vehicle falls from high altitude due to the fact that storage battery power is exhausted and mechanical faults.
The invention provides the following technical scheme: a multifunctional protective landing gear of an unmanned aerial vehicle comprises a main support frame fixed at the bottom of the unmanned aerial vehicle, wherein a main support rod is fixed at the lower side of the main support frame, connecting balls are rotatably arranged at two sides of the main support rod, supporting blocks capable of being detached are symmetrically arranged at two sides of the main support frame, an installation cavity with an opening facing to one side close to the main support frame is arranged in each supporting block, an installation assembly is arranged in each installation cavity, limiting cavities are communicated and arranged in the end walls at the upper side and the lower side of each installation cavity, an elastic cavity with an opening facing to one side far away from the main support frame is arranged at the upper side of each limiting cavity, a buffer assembly is arranged in each elastic cavity, a medicament cavity is arranged at one side of each limiting cavity at the lower side, an air bag cavity with an opening facing to one side close to the main support, the downside in medicament chamber is provided with the pressure chamber, the downside of pressure chamber is provided with the opening and keeps away from the stable chamber of main tributary strut one side, be provided with stable subassembly in the stable chamber, the installation cavity is kept away from one side of main tributary strut is provided with the sensor.
Carefully selecting, the buffer component comprises an elastic plate which is arranged in the elastic cavity in a sliding way, an elastic buffer claw is fixed on the end surface of one side of the elastic plate, which is far away from the main support frame, an elastic spring is fixedly connected between the end surface of one side of the elastic plate close to the main support frame and the end wall of one side of the elastic cavity close to the main support frame, the lower side of the elastic cavity is communicated with a sliding cavity, a sliding block capable of moving into the elastic cavity is arranged in the sliding cavity in a sliding manner, an adsorption cavity is communicated with the end wall of one side of the sliding cavity, which is far away from the main support frame, an adsorption plate which is arranged in the adsorption cavity in a sliding manner is fixed on the sliding block, the lower end wall of the adsorption cavity is fixedly provided with an electromagnet which can attract the adsorption plate after being electrified, and a return spring is fixedly connected between the lower end surface of the sliding block and the lower end wall of the sliding cavity.
Carefully, the buoyancy subassembly is including installing gasbag in the gasbag chamber, the opening part fixed mounting in gasbag chamber has the encapsulation board that prevents the foreign matter entering, the medicament chamber with the intercommunication is provided with the air duct between the gasbag, it is provided with the pressure plate to slide in the pressure chamber, be fixed with the upside on the pressure plate and extend to medicament intracavity and downside can move extremely stabilize the closing plate of intracavity, the lower terminal surface of pressure plate with fixedly connected with compression spring between the lower terminal wall of pressure chamber.
Optionally, the sealing plate can separate two sides of the medicament cavity, liquid and gas cannot pass through the medicament cavity, and the space between the two support blocks at the lower side of the main support rod can be filled after the air bag is inflated and deployed.
Carefully, stabilize the subassembly including fixing it is close to stabilize the chamber main tributary strut one side end wall in the stable motor, it keeps away from to stabilize the motor one side power connection of main tributary strut has the steady axle, stabilize the intracavity slide be provided with stabilize axle threaded connection's steadying plate, steadying plate can float in aqueous.
Carefully, the installation component includes that the dead lever is installed sealing washer in the installation cavity, the sealing washer can with the main tributary vaulting pole closely laminates, spacing intracavity slides and is provided with and can move extremely the restriction in the installation cavity connect the gliding stopper of ball in the installation cavity, the stopper is kept away from a side end face of installation cavity with spacing chamber is kept away from fixedly connected with spacing spring between a side end wall of installation cavity.
The main support rod is internally fixed with a switching motor, two sides of the switching motor are dynamically connected with a switching shaft fixedly connected with the connecting ball, a limiting block is fixedly arranged in the end wall of one side of the mounting cavity, which is far away from the main support rod, and a limiting groove which can be matched and connected with the limiting block is arranged in the connecting ball.
The invention has the following beneficial effects:
1. according to the unmanned aerial vehicle, when the unmanned aerial vehicle breaks down and falls into water from the high altitude, the unmanned aerial vehicle can stably float on the water surface by means of unfolding the stabilizing plate and inflating the air bag to expand the air bag, so that the unmanned aerial vehicle is prevented from entering water, and the problem that the unmanned aerial vehicle is easy to damage when falling into water is solved.
2. The device can also rotate through the switching motor when the unmanned aerial vehicle is about to fall from high altitude to land in case of failure, and simultaneously, impact force generated when the unmanned aerial vehicle is in contact with the land is buffered by popping up the buffer claw, so that the unmanned aerial vehicle is prevented from being in direct contact with the ground, and the problem that the unmanned aerial vehicle is damaged when directly falling from high altitude to the ground is solved.
Drawings
The invention is further illustrated with reference to the following figures and examples.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a sectional view of the structure taken along the line A-A in FIG. 1;
FIG. 3 is an enlarged view of the point B in FIG. 1;
FIG. 4 is a perspective view of the seal ring of the present invention;
FIG. 5 is a schematic diagram of the land landing structure of the present invention;
FIG. 6 is a schematic structural diagram of the present invention during landing on water.
In the figure: 10. a support block; 11. a limiting block; 12. an elastic cavity; 13. a connecting ball; 14. a buffer claw; 15. a limiting block; 16. a mounting cavity; 17. a seal ring; 18. an elastic plate; 20. a main supporting frame; 21. a limiting groove; 22. an air bag; 23. a package board; 24. a balloon lumen; 25. a main support bar; 26. a switching shaft; 27. stabilizing the motor; 28. switching the motors; 29. an air duct; 30. a limiting spring; 31. a limiting cavity; 32. a sealing plate; 33. a pressure spring; 34. a pressure plate; 35. a stabilizing shaft; 36. a stabilizing plate; 37. a pressure chamber; 38. a medicament chamber; 39. a sensor; 40. an elastic spring; 41. a slider; 42. a sliding cavity; 43. a return spring; 44. an electromagnet; 45. an adsorption chamber; 46. an adsorption plate; 47. a stability chamber.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-6, a multifunctional protective landing gear of an unmanned aerial vehicle comprises a main support frame 20 fixed at the bottom of the unmanned aerial vehicle, a main support rod 25 is fixed at the lower side of the main support frame 20, connecting balls 13 are rotatably arranged at both sides of the main support rod 25, support blocks 10 capable of being detached are symmetrically arranged at both sides of the main support frame 20, an installation cavity 16 with an opening facing to one side close to the main support frame 20 is arranged in each support block 10, an installation component is arranged in each installation cavity 16, limiting cavities 31 are communicated in the upper and lower end walls of each installation cavity 16, an elastic cavity 12 with an opening facing to one side far away from the main support frame 20 is arranged at the upper side of each limiting cavity 31, a buffer component is arranged in each elastic cavity 12, a medicament cavity 38 is arranged at one side of the lower side of each limiting cavity 31 close to the main support frame 20, an air bag cavity 24 with an opening facing to one side close, a buoyancy assembly is arranged in the air bag cavity 24, a pressure cavity 37 is arranged on the lower side of the medicament cavity 38, a stable cavity 47 with an opening facing away from one side of the main support frame 20 is arranged on the lower side of the pressure cavity 37, a stable assembly is arranged in the stable cavity 47, and a sensor 39 is arranged on one side of the installation cavity 16 away from the main support frame 20.
Wherein, the buffer component comprises an elastic plate 18 arranged in the elastic cavity 12 in a sliding manner, an elastic buffer claw 14 with elasticity is fixed on one side end face of the elastic plate 18 far away from the main support frame 20, an elastic spring 40 is fixedly connected between one side end face of the elastic plate 18 close to the main support frame 20 and one side end wall of the elastic cavity 12 close to the main support frame 20, a sliding cavity 42 is arranged on the lower side of the elastic cavity 12 in a communicating manner, a sliding block 41 capable of moving into the elastic cavity 12 is arranged in the sliding cavity 42 in a sliding manner, an adsorption cavity 45 is arranged on one side end wall of the sliding cavity 42 far away from the main support frame 20 in a communicating manner, an adsorption plate 46 arranged in the adsorption cavity 45 in a sliding manner is fixed on the sliding block 41, and an electromagnet 44 capable of attracting the adsorption plate 46 after being electrified is fixedly arranged on the lower end wall of the adsorption cavity 45, a return spring 43 is fixedly connected between the lower end surface of the sliding block 41 and the lower end wall of the sliding cavity 42.
Wherein, buoyancy module is including installing gasbag 22 in the gasbag chamber 24, the opening part fixed mounting in gasbag chamber 24 has the packaging plate 23 that prevents the foreign matter entering, medicament chamber 38 with the intercommunication is provided with air duct 29 between the gasbag 22, it is provided with pressure plate 34 to slide in the pressure chamber 37, be fixed with the upside on the pressure plate 34 and extend to in the medicament chamber 38 and the downside can move extremely seal plate 32 in the stability chamber 47, the lower terminal surface of pressure plate 34 with fixedly connected with pressure spring 33 between the lower terminal wall of pressure chamber 37.
The sealing plate 32 can separate two sides of the medicament cavity 38, liquid and gas cannot pass through the medicament cavity, and the space between the two support blocks 10 on the lower side of the main support rod 25 can be filled after the air bag 22 is inflated and unfolded.
Wherein, the stabilizing component comprises a stabilizing motor 27 fixed in a stabilizing cavity 47 close to the end wall of one side of the main support frame 20, a stabilizing shaft 35 is dynamically connected to one side of the stabilizing motor 27 far away from the main support frame 20, a stabilizing plate 36 in threaded connection with the stabilizing shaft 35 is arranged in the stabilizing cavity 47 in a sliding manner, and the stabilizing plate 36 can float in water.
Wherein, the installation component includes that the dead lever is installed sealing washer 17 in the installation cavity 16, sealing washer 17 can with the main tributary vaulting pole 25 closely laminates, it can remove to slide to be provided with in the spacing chamber 31 restrict in the installation cavity 16 connect the gliding stopper 15 of ball 13 in the installation cavity 16, stopper 15 is kept away from a side end face of installation cavity 16 with spacing chamber 31 is kept away from spacing spring 30 of fixedly connected with between a side end wall of installation cavity 16.
A switching motor 28 is fixed in the main support rod 25, switching shafts 26 fixedly connected with the connecting balls 13 are dynamically connected to two sides of the switching motor 28, a limiting block 11 is fixed in an end wall of one side of the mounting cavity 16 far away from the main support frame 20, and a limiting groove 21 capable of being connected with the limiting block 11 in a matched manner is arranged in the connecting ball 13.
The working principle is as follows: in an initial state, the supporting block 10 is not connected with the connecting ball 13, the buffer claw 14 is located in the elastic cavity 12, the sliding block 41 limits the elastic plate 18 to slide, the electromagnet 44 is not electrified, chemical reagents which can react with each other to release a large amount of gas are stored in the medicine cavity 38 and are respectively located on two sides of the sealing plate 32, the stabilizing plate 36 is located in the stabilizing cavity 47, if the unmanned aerial vehicle needs to fly on the water surface for a long time, the connecting ball 13 is inserted from an opening of the mounting cavity 16, the stabilizing plate 36 is placed downwards at the moment, so that the sealing ring 17 is in close contact with the main supporting rod 25 to prevent liquid from entering, the connecting ball 13 presses the limiting block 15 into the limiting cavity 31, after the connecting ball 13 crosses the limiting block 15, the limiting block 15 resets and moves to one side close to the main supporting rod 25 under the action of the limiting spring 30 to limit the connecting ball 13, and the limiting block 11 is located in, when the unmanned aerial vehicle runs into the situation of insufficient electric quantity or propeller failure when flying on the water surface and needs to land on the water surface, the sensor 39 controls the stabilizing motor 27 to start, thereby driving the stabilizing shaft 35 to rotate, thereby enabling the stabilizing plate 36 to move towards one side far away from the main support frame 20, thereby hiding the contact area between the large support block 10 and the water surface, thereby improving the stability of the unmanned aerial vehicle after landing, meanwhile, after the stabilizing plate 36 is separated from the sealing plate 32, the pressure plate 34 moves downwards under the action of the pressure spring 33, thereby enabling the two sides of the medicament cavity 38 to be communicated, thereby enabling the two chemical reagents to contact and react, the generated gas is transferred into the air bag 22 through the air duct 29, thereby enabling the air bag 22 to inflate and expand and pop out from the air bag cavity 24, thereby improving the buoyancy of the support block 10, and further ensuring that the aircraft can land on the water surface safely and the unmanned, if the unmanned aerial vehicle flies to land to perform forced landing, the switching motor 28 is started before the forced landing, so that the switching shaft 26 drives the connecting ball 13 to rotate, the supporting block 10 rotates by one hundred eighty degrees by taking the main supporting rod 25 as an axis through the connecting action of the limiting groove 21 and the limiting block 11, then the switching motor 28 stops, when the unmanned aerial vehicle is about to perform the forced landing, the sensor 39 controls the electromagnet 44 to be electrified, so that the adsorption plate 46 moves to one side close to the electromagnet 44, the sliding block 41 moves to the sliding cavity 42, the limitation on the elastic plate 18 is released, the elastic plate 18 is ejected to one side far away from the main supporting frame 20 under the action of the elastic spring 40, so that the buffer claw 14 is moved out of the elastic cavity 12, the buffer claw 14 recovers to a normal state without the limitation of the inner wall of the elastic cavity 12, and when the buffer claw 14 is in contact with the ground, because the buffer claw 14 has elasticity, therefore, the impact force generated by the falling of the airplane can be buffered, and the airplane can be protected from being damaged too much.
The above embodiments are merely illustrative of the technical ideas and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the contents of the present invention and implement the present invention, and not to limit the protection scope of the present invention. All equivalent changes and modifications made according to the spirit of the present invention should be covered within the protection scope of the present invention.
Claims (7)
1. The utility model provides a multi-functional protection undercarriage device of unmanned aerial vehicle, is including fixing main tributary strut (20) in unmanned aerial vehicle bottom, its characterized in that: a main support rod (25) is fixed on the lower side of the main support frame (20), connecting balls (13) are rotatably arranged on two sides of the main support rod (25), supporting blocks (10) which can be disassembled are symmetrically arranged on two sides of the main support frame (20), a mounting cavity (16) with an opening facing to one side close to the main support frame (20) is arranged in each supporting block (10), a mounting assembly is arranged in each mounting cavity (16), limiting cavities (31) are communicated in the end walls of the upper side and the lower side of each mounting cavity (16), an elastic cavity (12) with an opening facing to one side far away from the main support frame (20) is arranged on the upper side of each limiting cavity (31), a buffer assembly is arranged in each elastic cavity (12), a medicament cavity (38) is arranged on one side of the lower side of each limiting cavity (31) close to the main support frame (20), and an air bag cavity (24) with an opening facing to one side close to the main support frame (20), be provided with buoyancy module in gasbag chamber (24), the downside in medicament chamber (38) is provided with pressure chamber (37), the downside of pressure chamber (37) is provided with the opening orientation and keeps away from stable chamber (47) of main tributary strut (20) one side, be provided with stable subassembly in stable chamber (47), installation cavity (16) are kept away from one side of main tributary strut (20) is provided with sensor (39).
2. The multifunctional protective undercarriage for unmanned aerial vehicles of claim 1 further comprising: the buffer assembly comprises an elastic plate (18) arranged in the elastic cavity (12) in a sliding manner, an elastic buffer claw (14) with elasticity is fixed on one side end face of the elastic plate (18) far away from the main support frame (20), an elastic spring (40) is fixedly connected between one side end face of the elastic plate (18) close to the main support frame (20) and one side end wall of the elastic cavity (12) close to the main support frame (20), a sliding cavity (42) is communicated with the lower side of the elastic cavity (12), a sliding block (41) capable of moving into the elastic cavity (12) is arranged in the sliding cavity (42) in a sliding manner, an adsorption cavity (45) is communicated with one side end wall of the sliding cavity (42) far away from the main support frame (20), and an adsorption plate (46) arranged in the adsorption cavity (45) in a sliding manner is fixed on the sliding block (41), the lower end wall of the adsorption cavity (45) is fixedly provided with an electromagnet (44) which can attract the adsorption plate (46) after being electrified, and a return spring (43) is fixedly connected between the lower end surface of the sliding block (41) and the lower end wall of the sliding cavity (42).
3. The multifunctional protective undercarriage for unmanned aerial vehicles of claim 1 further comprising: buoyancy subassembly is including installing gasbag (22) in gasbag chamber (24), the opening part fixed mounting of gasbag chamber (24) has packaging plate (23) that prevents the foreign matter entering, medicament chamber (38) with communicate between gasbag (22) and be provided with air duct (29), it is provided with pressure plate (34) to slide in pressure chamber (37), be fixed with the upside on pressure plate (34) and extend to in medicament chamber (38) and the downside can remove to stabilize closing plate (32) in chamber (47), the lower terminal surface of pressure plate (34) with fixedly connected with pressure spring (33) between the lower terminal wall of pressure chamber (37).
4. The multifunctional protective undercarriage for unmanned aerial vehicles of claim 3 further comprising: the sealing plate (32) can separate two sides of the medicament cavity (38) and prevent liquid and gas from passing through, and the air bag (22) can fill the space between the two support blocks (10) at the lower side of the main support rod (25) after being inflated and unfolded.
5. The multifunctional protective undercarriage for unmanned aerial vehicles of claim 1 further comprising: stabilize the subassembly including fixing stabilize chamber (47) and be close to stabilize motor (27) in main support frame (20) one side end wall, stabilize motor (27) and keep away from one side power connection of main support frame (20) has stabilizing shaft (35), slide in stabilize chamber (47) be provided with stabilizing plate (36) of stabilizing shaft (35) threaded connection, stabilizing plate (36) can float in aqueous.
6. The multifunctional protective undercarriage for unmanned aerial vehicles of claim 1 further comprising: the installation component comprises a fixed rod installed on a sealing ring (17) in an installation cavity (16), the sealing ring (17) can be tightly attached to a main support rod (25), a limiting cavity (31) is internally provided with a sliding block capable of moving to the installation cavity (16) for limiting, a limiting block (15) sliding in the installation cavity (16) is connected with a ball (13), the limiting block (15) is far away from one side end surface of the installation cavity (16) and the limiting cavity (31) is far away from a limiting spring (30) fixedly connected between one side end wall of the installation cavity (16).
7. The multifunctional protective landing gear of an unmanned aerial vehicle of claim 6, wherein: the main support rod (25) is internally fixed with a switching motor (28), two sides of the switching motor (28) are in power connection with a switching shaft (26) fixedly connected with the connecting ball (13), a limiting block (11) is fixed in the end wall of one side of the mounting cavity (16) far away from the main support rod (20), and a limiting groove (21) which can be matched and connected with the limiting block (11) is formed in the connecting ball (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110282987.0A CN112758310A (en) | 2021-03-16 | 2021-03-16 | Multi-functional protection undercarriage of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110282987.0A CN112758310A (en) | 2021-03-16 | 2021-03-16 | Multi-functional protection undercarriage of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112758310A true CN112758310A (en) | 2021-05-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110282987.0A Withdrawn CN112758310A (en) | 2021-03-16 | 2021-03-16 | Multi-functional protection undercarriage of unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN112758310A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114228982A (en) * | 2021-11-30 | 2022-03-25 | 重庆交通大学绿色航空技术研究院 | Unmanned aerial vehicle support |
| CN114542878A (en) * | 2022-02-25 | 2022-05-27 | 重庆三峡学院 | Automatic geological disaster characteristic monitoring device |
| CN114739299A (en) * | 2022-03-25 | 2022-07-12 | 中铁城建集团有限公司 | Plate thickness controller capable of continuously counting and accurately measuring thickness of cast-in-place concrete plate |
-
2021
- 2021-03-16 CN CN202110282987.0A patent/CN112758310A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114228982A (en) * | 2021-11-30 | 2022-03-25 | 重庆交通大学绿色航空技术研究院 | Unmanned aerial vehicle support |
| CN114542878A (en) * | 2022-02-25 | 2022-05-27 | 重庆三峡学院 | Automatic geological disaster characteristic monitoring device |
| CN114739299A (en) * | 2022-03-25 | 2022-07-12 | 中铁城建集团有限公司 | Plate thickness controller capable of continuously counting and accurately measuring thickness of cast-in-place concrete plate |
| CN114739299B (en) * | 2022-03-25 | 2023-09-01 | 中铁城建集团有限公司 | Plate thickness controller capable of continuously counting and accurately measuring plate thickness of cast-in-place concrete |
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Application publication date: 20210507 |