CN112319816B - Electric power inspection device and inspection method based on FPV and multi-rotor unmanned aerial vehicle - Google Patents
Electric power inspection device and inspection method based on FPV and multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN112319816B CN112319816B CN202011198185.3A CN202011198185A CN112319816B CN 112319816 B CN112319816 B CN 112319816B CN 202011198185 A CN202011198185 A CN 202011198185A CN 112319816 B CN112319816 B CN 112319816B
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- 238000007689 inspection Methods 0.000 title claims abstract description 26
- 238000000034 method Methods 0.000 title description 6
- 230000007246 mechanism Effects 0.000 claims description 13
- 230000003014 reinforcing effect Effects 0.000 claims description 12
- 239000002828 fuel tank Substances 0.000 claims description 10
- 230000005540 biological transmission Effects 0.000 claims description 4
- 230000000295 complement effect Effects 0.000 claims description 3
- 238000010285 flame spraying Methods 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 40
- 239000003921 oil Substances 0.000 description 23
- 238000002485 combustion reaction Methods 0.000 description 6
- 241000712469 Fowl plague virus Species 0.000 description 5
- 238000010330 laser marking Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 238000010030 laminating Methods 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 206010033799 Paralysis Diseases 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003086 colorant Substances 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
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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
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B7/00—Cleaning by methods not provided for in a single other subclass or a single group in this subclass
- B08B7/0035—Cleaning by methods not provided for in a single other subclass or a single group in this subclass by radiant energy, e.g. UV, laser, light beam or the like
- B08B7/0042—Cleaning by methods not provided for in a single other subclass or a single group in this subclass by radiant energy, e.g. UV, laser, light beam or the like by laser
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- 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
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G1/00—Methods or apparatus specially adapted for installing, maintaining, repairing or dismantling electric cables or lines
- H02G1/02—Methods or apparatus specially adapted for installing, maintaining, repairing or dismantling electric cables or lines for overhead lines or cables
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Remote Sensing (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a portable electric power inspection device combining a FPV technology and a multi-rotor unmanned aerial vehicle, and relates to the technical field of electric power inspection unmanned aerial vehicles. The invention is convenient to disassemble and carry, the wings are convenient to fold, the invention is provided with a flame-spraying incineration and auxiliary combustion-supporting device, a wind vane and laser alignment device, and a laser emission head (901) can form a certain included angle with a nozzle of an oil pipe when being positioned, thereby achieving the purpose of improving the flame-spraying hit rate.
Description
Technical Field
The invention relates to the technical field of inspection unmanned aerial vehicles, in particular to an electric inspection device and an inspection method based on FPVs and multi-rotor unmanned aerial vehicles.
Background
In electric power patrols and examines, the electric power workman patrols and examines along the circuit of electric wire mostly, this kind of mode of patrolling and examining is inefficient, the part is patrolled and examined and is accomplished through the unmanned aerial vehicle that is equipped with high definition digital camera and GPS positioning system, unmanned aerial vehicle is independently cruises according to the electric wire netting location, the image is shot in real-time conveying, the image that unmanned aerial vehicle shot can be watched in step or operate unmanned aerial vehicle to the control personnel on the computer, partly special area adopts double principal and subordinate control in addition, patrol and examine and take a picture the record with high definition digtal camera through infrared camera, adopt unmanned aerial vehicle to carry out electric power and patrol and examine not receive the influence of road surface situation, work efficiency has been improved, the reliability of emergency level and power supply.
However, the current parts of patrolling and examining unmanned aerial vehicle are all installed in the casing, lead to unmanned aerial vehicle's occupation space great, are not convenient for dismantle and carry, can not fold at current unmanned aerial vehicle's horn for unmanned aerial vehicle is not convenient for artifical transport and then influences electric power and patrols and examines efficiency.
The foreign matter on the wire of the transmission line becomes a great threat to the safe operation of the power grid, and at present, the operation department often adopts manual removal or laser fixed-point removal in the power failure state. And then for unmanned aerial vehicle flame throwing incineration clearance, make unmanned aerial vehicle flame throwing reverse emergence skew to make in the high altitude flame throwing operation because the influence of high altitude wind-force, adopt artifical the observation in unmanned aerial vehicle flame throwing alignment common adoption, hit efficiency lower, and then cause a certain amount of fuel extravagant, and some remote areas's high-tension line discovers that the adnexed linearity of foreign matter can not in time adopt two kinds of simple and convenient clearance modes in back in electric power patrols and examines, need the manual work to clear away, and the security is lower.
Furthermore, when the weather of sleet congealing appears, the congealing phenomenon can appear in the high-voltage line, causes the power supply system part paralysed and then causes the inconvenience of people's production and life, and current deicing adopts artifical deicing and supplementary flame projecting of unmanned aerial vehicle and the deicing of pulling rope line, to the circuit of some plateau because oxygen content is lower can not effectual burning fuel, influences deicing efficiency.
Disclosure of Invention
In order to solve the problems in the background art, the invention aims to provide an electric power inspection device and an inspection method based on an FPV and a multi-rotor unmanned aerial vehicle.
In order to achieve the purpose, the invention provides the following technical scheme:
the electric power inspection device and the inspection method based on the FPV and the multi-rotor unmanned aerial vehicle comprise the unmanned aerial vehicle, a flame thrower device and a combustion-supporting device, wherein the left side and the right side of the unmanned aerial vehicle are rotatably connected with folding mechanisms, a supporting frame is fixedly clamped on the bottom surface of the unmanned aerial vehicle, the flame thrower device is fixedly connected to the bottom surface of the supporting frame close to the rear end, the combustion-supporting device is fixedly connected to the left side and the right side of the flame thrower device, a camera support is fixedly connected to the bottom surface of the supporting frame close to the front end, an observation head is fixedly connected to the top of the inner wall of a C-shaped groove of the camera support, and a camera is rotatably connected to the bottom surface of the camera support;
the flame sprayer device comprises a fixed support, a fuel tank, an oil pump, an oil pipe, an ignition head and a windshield, wherein the top of the fixed support is fixed on a support frame, the inner side of the bottom of the fixed support is fixedly connected with the fuel tank, the bottom of the fuel tank is fixedly communicated with the oil pump, the front of the oil pump is fixedly communicated with the oil pipe, and the front end of the oil pipe is fixedly connected with the windshield;
the combustion-supporting device comprises a combustion-supporting gas tank, a gas collecting plate and a combustion-supporting gas pipe, the left end and the right end of the fixed support are fixedly connected with the combustion-supporting gas tank, the combustion-supporting gas tanks at the left end and the right end are connected with each other through the gas collecting plate, the bottom of the gas collecting plate is fixedly communicated with the combustion-supporting gas pipe, and one end, away from the combustion-supporting gas tank, of the combustion-supporting gas pipe is fixedly communicated with the conical surface of the wind shield.
As a further scheme of the invention: the folding mechanism comprises a first support, a sliding sleeve, a spring, a second support, a motor, a detachable fan, a first support, a rotating pin, a second support, a reinforcing plate, rotating blocks, a fixed block, a waist-shaped hole, a cylindrical extension spring, a first semi-ring, a support rod and a second semi-ring, wherein the left end and the right end of the unmanned aerial vehicle are respectively fixedly connected with the two rotating blocks, one end of the second support, which is close to the unmanned aerial vehicle, is provided with a boss, the rotating blocks are rotatably connected with the boss at one end, which is close to the unmanned aerial vehicle, of the second support through pins, one end, which is far away from the unmanned aerial vehicle, of the second support is rotatably connected with the bottom of the first support through the rotating pin, the top of the first support is rotatably connected with the fixed block through the pin, the top of the fixed block, which is close to the windshield, is fixedly connected with the first support, the front of the first support is in threaded connection with the back of the second support, the one end that unmanned aerial vehicle was kept away from to support one and support two rotates and is connected with the motor, the top transmission of motor is connected with can dismantle the fan.
As a still further scheme of the invention: the supporting frame comprises a supporting frame I and is characterized in that a square hole is formed in the top of the supporting frame I, a square through hole is formed in the back of the supporting frame I close to the top, waist-shaped holes are formed in the left end and the right end of the supporting frame I and close to the top, a pin is arranged in the waist-shaped hole of the supporting frame I, the pin arranged in the waist-shaped hole of the supporting frame I is rotatably connected to the axis of the bottom of a fixing block, only a cylindrical stretching spring is arranged in the square hole formed in the supporting frame I, the bottom of the cylindrical stretching spring is fixedly connected with the bottom of the square hole of the supporting frame I, and the top of the cylindrical stretching spring is fixedly connected with the bottom of the fixing block in a clamping mode.
As a still further scheme of the invention: the connecting end of the first support frame and the second support frame is in 45-degree inclined plane complementary contact.
As a still further scheme of the invention: the outer surface of the first support close to the front side is provided with a groove towards the axis, a spring is arranged in the groove formed in the first support, the sliding sleeve is connected in the groove formed in the first support in a sliding mode, the inner wall of the sliding sleeve is provided with the spring, the inner wall of the sliding sleeve is close to the front side and provided with a threaded hole, the outer surface of the second support close to the back side is provided with a threaded groove, and the sliding sleeve is in threaded connection with the second support.
As a still further scheme of the invention: the first half ring is fixedly connected to the left end and the right end of the unmanned aerial vehicle, the first half ring is arranged on the rear side of the rotating block, the second half ring is fixedly connected to the back face of the second support frame, the first half ring and the second half ring are connected with each other through the support rod, a T-shaped groove is formed in one end, close to the unmanned aerial vehicle, of the first support frame and the top of the second support frame, and the reinforcing plate is clamped in the T-shaped groove of the first support frame and the second support frame.
As a still further scheme of the invention: the observation head comprises a laser emission head, an observation camera and an observation fixed shell, the left end of the observation fixed shell is provided with the observation camera, and the right end of the observation fixed shell is provided with the laser emission head. The laser emitting head can form a certain included angle with the nozzle of the oil pipe when being positioned.
As a still further scheme of the invention: the outer surface of the middle part of the oil pipe is fixedly connected with a fixed boss, and the top of the fixed boss is rotatably connected with a wind vane.
As a still further scheme of the invention: and one end of the wind direction indicator of the wind vane is painted with bright colors.
As a still further scheme of the invention: the outer surface of the windshield is provided with a through hole, and the ignition head is fixed on the cylindrical surface of the windshield.
Compared with the prior art, the invention has the beneficial effects that:
1. the scheme is that when the folding arm is folded, the reinforcing plate, the semi-ring II and the detachable fan are firstly removed, the sliding sleeve is rotated to enable the threaded connection part of the sliding sleeve and the support II to be separated, then the support I is rotated by 180 degrees by taking the rotating pin as a rotating center, so that the support I and the support II are on the same plane, the square through hole formed in the support I is positioned at one end close to the windshield, the pin arranged in the support I slides in the hole of the waist-shaped hole, the fixing block is rotated by taking the pin as the circle center, so that the support I and the support II are clamped in the square through hole formed in the support I, the support II or the support I is basically attached to one end of the support I and one end of the support II close to the windshield, and finally the support II is rotated by taking the pin in the rotating block as the axis center, so that the support II and the support I are basically attached to the left end and the right end of the unmanned aerial vehicle, and the folding arm is finished, unmanned occupation space that will extend the horn laminating unmanned aerial vehicle fuselage very big shrink.
2. The contact surfaces of the first support frame and the second support frame are inclined planes of 45 degrees, so that the two support frames are in a horizontal or vertical state when rotating 180 degrees, the horizontal state is convenient for folding the arm, the space can be better saved, the vertical state is convenient for improving the horizontal height of the driving part of the unmanned aerial vehicle, and the working space at the bottom of the unmanned aerial vehicle is increased;
3. one end of the supporting rod is clamped in the first half ring of the unmanned aerial vehicle, the other end of the supporting rod is clamped in the second half ring of the second supporting frame, and the reinforcing plate is clamped on the inner side of an included angle formed by the first supporting frame and the second supporting frame in a vertical state, so that the rotating block and the second supporting frame cannot rotate and the first supporting frame and the second supporting frame cannot rotate in a flying state of the unmanned aerial vehicle, the purpose of enhancing the stability of the mechanism is achieved, and the two reinforcing pieces have good fixity and convenient disassembly;
4. the wind vane that sets up is through highlight color mark wind direction indicating head for operating personnel can be through observing the effectual judgement air-out direction of camera, judge the size of wind-force and roughly wind direction and laser emission head can carry out laser marking to burning the point on the basis, can have certain contained angle through spout and burning point that adjustment laser marking point can oil pipe, and the data measurement of highlight color mark wind direction indicating head is passed through to above-mentioned angle. On the basis of reasonable distance from the burning point, the wind influence on flame can be effectively reduced by adjusting the nozzle of the oil pipe and the angle of the burning point, the flame can be pushed to the burning point by wind power, and the probability of hitting the burning point is improved.
5. The combustion-supporting gas tank that sets up can promote the combustible gas content of certain regional ability through in the leading-in wind cap of combustion-supporting gas siphuncle by the gas collection board through combustion-supporting gas to this avoids the fuel that the burning that combustible gas rarefied caused insufficiently to waste and the problem that deicing efficiency is low that the combustion effect is poor to arouse.
Drawings
FIG. 1 is a schematic diagram of the inspection unmanned aerial vehicle structure of the invention;
FIG. 2 is a schematic diagram of the reverse patrol unmanned aerial vehicle structure of the present invention;
FIG. 3 is a front view of the present invention;
FIG. 4 is a left side view of the present invention;
FIG. 5 is a cross-sectional view of the folding mechanism of the present invention;
FIG. 6 is a schematic view of FIG. 5 at area B of the present invention;
FIG. 7 is a schematic cross-sectional view of the folding mechanism of the present invention;
FIG. 8 is a schematic view of FIG. 3 at area A in accordance with the present invention;
fig. 9 is a schematic diagram of the half-folding of the folding mechanism of the inspection unmanned aerial vehicle of the invention;
fig. 10 is a schematic diagram of the folding mechanism of the unmanned aerial vehicle with the reverse structure in a semi-folded state.
In the figure: 1. an unmanned aerial vehicle; 2. a folding mechanism; 201. a first bracket; 202. a sliding sleeve; 203. a spring; 204. a second bracket; 205. a motor; 206. a detachable fan; 207. a first support frame; 208. a rotation pin; 209. a second support frame; 210. a reinforcing plate; 211. rotating the block; 212. a fixed block; 213. a kidney-shaped hole; 214. a cylindrical extension spring; 215. a first half ring; 216. a support bar; 217. a second half ring; 3. a support frame; 4. fixing a bracket; 5. a fuel tank; 6. a combustion-supporting gas tank; 7. a camera head bracket; 8. a camera; 9. an observation head; 901. a laser emitting head; 902. observing the camera; 903. observing the fixed shell; 10. an oil pipe; 11. an ignition head; 12. a combustion-supporting gas pipe; 13. fixing the boss; 14. a wind vane; 15. a windshield; 16. an oil pump; 17. air collecting plate.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings
Referring to fig. 1 to 10, in the embodiment of the invention, an electric power inspection device and an inspection method based on an FPV and a multi-rotor unmanned aerial vehicle include an unmanned aerial vehicle 1, a flame thrower device and a combustion-supporting device, wherein folding mechanisms 2 are rotatably connected to left and right sides of the unmanned aerial vehicle 1, a support frame 3 is fixedly clamped on the bottom surface of the unmanned aerial vehicle 1, the flame thrower device is fixedly connected to the bottom surface of the support frame 3 near the rear end, the combustion-supporting device is fixedly connected to left and right sides of the flame thrower device, a camera bracket 7 is fixedly connected to the bottom surface of the support frame 3 near the front end, an observation head 9 is fixedly connected to the top of the inner wall of a "C" shaped groove of the camera bracket 7, and a camera 8 is rotatably connected to the bottom surface of the camera bracket 7;
the flame thrower device comprises a fixed support 4, a fuel tank 5, an oil pump 16, an oil pipe 10, an ignition head 11 and a windshield 15, wherein the top of the fixed support 4 is fixed on a support frame 3, the inner side of the bottom of the fixed support 4 is fixedly connected with the fuel tank 5, the bottom of the fuel tank 5 is fixedly communicated with the oil pump 16, the front of the oil pump 16 is fixedly communicated with the oil pipe 10, and the front end of the oil pipe 10 is fixedly connected with the windshield 15;
the combustion-supporting device comprises a combustion-supporting gas tank 6, a gas collecting plate 17 and a combustion-supporting gas pipe 12, the left end and the right end of a fixed support 4 are fixedly connected with the combustion-supporting gas tank 6, the combustion-supporting gas tanks 6 at the left end and the right end are mutually connected through the gas collecting plate 17, the bottom of the gas collecting plate 17 is fixedly communicated with the combustion-supporting gas pipe 12, and one end, far away from the combustion-supporting gas tank 6, of the combustion-supporting gas pipe 12 is fixedly communicated with the conical surface of a windproof cover 15.
In fig. 5-7, the folding mechanism 2 includes a first support 201, a sliding sleeve 202, a spring 203, a second support 204, a motor 205, a detachable fan 206, a first support 207, a rotating pin 208, a second support 209, a reinforcing plate 210, a rotating block 211, a fixed block 212, a kidney-shaped hole 213, a cylindrical extension spring 214, a first half ring 215, a support rod 216, and a second half ring 217, two rotating blocks 211 are fixedly connected to the left and right ends of the unmanned aerial vehicle 1, respectively, a boss is provided at one end of the second support 209 close to the unmanned aerial vehicle 1, the rotating block 211 is rotatably connected with the boss at one end of the second support 209 close to the unmanned aerial vehicle 1 through a pin, one end of the second support 209 far away from the unmanned aerial vehicle 1 is rotatably connected with the bottom of the first support 207 through the rotating pin 208, the top of the first support 207 is rotatably connected with the fixed block 212 through a pin, and the second support 204 is fixedly connected with the top of the fixed block 212 close to the windshield 15, the top of a fixing block 212 far away from the windshield 15 is fixedly connected with a first support 201, the front face of the first support 201 is in threaded connection with the back face of a second support 204, one ends of the first support 201 and the second support 204 far away from the unmanned aerial vehicle 1 are rotatably connected with a motor 205, the top of the motor 205 is in transmission connection with a detachable fan 206, the first support 207 is rotated 180 degrees by rotating the first support 207 with a rotating pin 208 as a rotating center, so that the first support 207 and the second support 209 are on the same plane, at the moment, a pin arranged on the first support 207 slides in a hole of a waist-shaped hole 213, the fixing block 212 is rotated with the pin as a circle center, so that the first support 207 is clamped in a square through hole formed in the first support 207, at the moment, the second support 204 or the first support 201 is basically attached to one ends, close to the windshield 15, of the first support 207 and the second support 209, and finally, the second support 209 is rotated with the pin in the rotating block 211 as an axis center, so that the second support 209 and the first support 207 are basically attached to the left end and the right end of the unmanned aerial vehicle 1, the folding of unmanned aerial vehicle horn is accomplished from this, the unmanned occupation space of very big shrink of horn laminating unmanned aerial vehicle fuselage that will extend.
In fig. 5 and 6, a square hole is formed at the top of a first support frame 207, a square through hole is formed at the back of the first support frame 207 close to the top, waist-shaped holes 213 are formed at the left end and the right end of the first support frame 207 close to the top, a pin is arranged in the waist-shaped hole 213 formed in the first support frame 207, the pin arranged in the waist-shaped hole 213 of the first support frame 207 is rotatably connected to the axis of the bottom of a fixed block 212, only a cylindrical tension spring 214 is arranged in the square hole formed in the first support frame 207, the bottom of the cylindrical tension spring 214 is fixedly connected with the bottom of the square hole of the first support frame 207, the top of the cylindrical tension spring 214 is fixedly clamped with the bottom of the fixed block 212, the pin arranged in the first support frame 207 is limited by sliding through the waist-shaped hole 213, the square through hole is convenient for the fixed block 212 to deflect, and a continuous pulling force is applied to the fixed block 212 by the cylindrical tension spring 214 to ensure the firmness of the fixed block 212 before and after deflection, the supporting strength of the wings is improved, and meanwhile, the deflection head convenient to fold is convenient to fold the wings of the unmanned aerial vehicle.
In fig. 6, the link of support frame one 207 and support frame two 209 is the complementary contact of 45 degrees inclined planes for under the state of rotating 180 degrees, two support frames are in level or vertically state, are being convenient for the folding of horn at the horizontality, the saving space that can be better, are making unmanned aerial vehicle drive position level improve being in the vertical state, have increased the workspace of unmanned aerial vehicle 1 bottom.
In fig. 7, a groove towards the axis is formed in the outer surface of the first support 201 close to the front side, a spring 203 is arranged in the groove formed in the first support 201, the sliding sleeve 202 is slidably connected in the groove formed in the first support 201, the spring 203 is arranged on the inner wall of the sliding sleeve 202, a threaded hole is formed in the inner wall of the sliding sleeve 202 close to the front side, a threaded groove is formed in the outer surface of the second support 204 close to the back side, the sliding sleeve 202 is in threaded connection with the second support 204, the first support 201 and the second support 204 are fixed through the threaded connection of the sliding sleeve 202 and the second support 204, meanwhile, the problem that the support connection is loosened due to the work vibration of a motor is effectively reduced due to the elastic action of the spring 203, meanwhile, the first support 201 and the second support 204 are mutually connected, the support strength of the horn is improved, and the horn can stably fly under severe environments.
In fig. 5-7, half ring one 215 fixed connection is at the unmanned aerial vehicle left and right ends, the rear side of turning block 211 is arranged in to half ring one 215, half ring two 217 fixed connection is at the back of support frame two 209, half ring one 215 and half ring two 217 pass through bracing piece 216 interconnect, support frame one 207 is close to unmanned aerial vehicle 1's one end and support frame two 209's top and has seted up "T" shape groove, "reinforcing plate 210 joint is in support frame one 207 and support frame two 209" T "shape inslot, make can turn block 211 and support frame two 209 can not take place to rotate and support frame one 207 and support frame two 209 can not take place to rotate under patrolling and examining unmanned aerial vehicle flight state, with this purpose that reaches reinforcing mechanism stability, two kinds of reinforcements that set up simultaneously have better fixity and convenient to detach's performance.
In fig. 8, the observation head 9 includes a laser emitting head 901, an observation camera 902, an observation fixed casing 903, the left end of the observation fixed casing 903 is provided with the observation camera 902, the right end of the observation fixed casing 903 is provided with the laser emitting head 901, and the laser emitting head 901 can perform laser marking on the incineration point. In fig. 1 and 4, a fixed boss 13 is fixedly connected to the outer surface of the middle portion of the oil pipe 10, a wind vane 14 is rotatably connected to the top of the fixed boss 13, one end of the wind direction indication of the wind vane 14 is colored with a bright color, an operator can judge the direction of wind power by observing the camera 902 effectively, on the basis of judging the size and the approximate wind direction of wind power and the laser marking of the burning point by the laser emitting head, the operator can adjust the laser emitting head 901 to deflect a certain angle, so that the laser emitting head 901 can deflect a certain angle by any known means, for example, the observing head 9 can deflect a certain angle integrally by an electric device or the laser emitting head 901 can deflect a certain angle independently by an electric device, so that a certain included angle is generated between the emitted laser and the oil pipe, and at this time, the laser emitted by the laser emitting head 901 is just positioned at the burning point, like this can be more accurate adjustment oil pipe's spout and the angle of burning the point, at last with burn the reasonable distance of point on, through adjustment oil pipe's spout and the angle of burning the point, utilize wind-force to push flame to burning the point, accurate realization burns burning of point, effectively reduces the wind-force influence that flame received, has improved the probability of hitting burning the point.
In fig. 1 and 2, a through hole is formed in the outer surface of the windshield 15, the ignition head 11 is fixed on the cylindrical surface of the windshield 15, and the combustion-supporting gas tank 6 can promote the content of combustible gas in a certain area through the combustion-supporting gas introduced into the windshield 15 through the combustion-supporting gas pipe 12 by the gas collecting plate 17, so that the problem of low deicing efficiency caused by insufficient combustion and poor combustion effect due to insufficient combustion of the combustible gas is avoided.
The working principle of the invention is as follows: when the folding arm is folded, firstly, the reinforcing plate 210, the half ring II 217 and the detachable fan 206 are detached, the sliding sleeve 202 is rotated to enable the threaded connection part of the sliding sleeve to be separated from the support II 204, then the support I207 is rotated 180 degrees by taking the rotating pin 208 as a rotating center, so that the support I207 and the support II 209 are on the same plane, at the moment, the square through hole formed in the support I207 is positioned at one end close to the windshield 15, the fixing block 212 is pulled to drive the cylindrical stretching spring 214 to stretch, at the moment, the pin arranged in the support I207 slides in the hole of the waist-shaped hole 213, the fixing block 212 is rotated by taking the pin as the circle center, so that the fixing block 212 is clamped in the square through hole formed in the support I207, at the moment, the support II 204 or the support I201 is basically attached to one end of the support I207 and the support II 209 close to the windshield 15, and finally, the support II 209 is rotated by taking the pin in the rotating block 211 as the axis center, therefore, the supporting frame II 209 and the supporting frame I207 are basically attached to the left end and the right end of the unmanned aerial vehicle 1, the contact surface of the supporting frame I207 and the supporting frame II 209 is an inclined plane of 45 degrees, so that the two supporting frames are in a horizontal or vertical state when rotating 180 degrees, the folding of the arm is facilitated when the supporting frames are in the horizontal state, the space can be better saved, the horizontal height of the driving part of the unmanned aerial vehicle is improved when the supporting frames are in the vertical state, the working space at the bottom of the unmanned aerial vehicle 1 is increased, an operator can effectively reduce the wind force influence on flame by adjusting the nozzle direction of the oil pipe 10 to be aligned with the wind direction by observing the wind vane 14 in the camera 902 through a highlight color marking wind direction indicator when carrying out flame spraying and removing adhesion, meanwhile, the laser emitter 901 can carry out laser marking on an incineration point, the flame spraying hit rate of the operator can be effectively improved by the operation and observation of the operator, the combustion-supporting gas tank 6 can promote the combustible gas content of a certain area energy by introducing combustion-supporting gas into the windshield 15 through the gas collecting plate 17 and the combustion-supporting gas pipe 12, so that the problems of fuel oil waste and poor combustion effect caused by insufficient combustion caused by the rarefied combustible gas are solved.
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 are equivalent to or changed within the technical scope of the present invention.
Claims (9)
1. Electric power inspection device based on FPV and many rotor unmanned aerial vehicle, including unmanned aerial vehicle (1), flame thrower device, combustion-supporting device, its characterized in that: the folding mechanism (2) is rotatably connected to the left side and the right side of the unmanned aerial vehicle (1), a supporting frame (3) is fixedly clamped on the bottom surface of the unmanned aerial vehicle (1), a flame thrower device is fixedly connected to the bottom surface of the supporting frame (3) close to the rear end, a combustion-supporting device is fixedly connected to the left side and the right side of the flame thrower device, a camera support (7) is fixedly connected to the bottom surface of the supporting frame (3) close to the front end, an observation head (9) is fixedly connected to the top of the inner wall of a C-shaped groove of the camera support (7), and a camera (8) is rotatably connected to the bottom surface of the camera support (7);
the flame thrower device comprises a fixed support (4), a fuel tank (5), an oil pump (16), an oil pipe (10), an ignition head (11) and a windshield (15), wherein the top of the fixed support (4) is fixed on a supporting frame (3), the inner side of the bottom of the fixed support (4) is fixedly connected with the fuel tank (5), the bottom of the fuel tank (5) is fixedly communicated with the oil pump (16), the front of the oil pump (16) is fixedly communicated with the oil pipe (10), and the front end of the oil pipe (10) is fixedly connected with the windshield (15);
the combustion-supporting device comprises a combustion-supporting gas tank (6), a gas collecting plate (17) and combustion-supporting gas pipes (12), the left end and the right end of the fixed support (4) are fixedly connected with the combustion-supporting gas tank (6), the combustion-supporting gas tanks (6) at the left end and the right end are mutually connected through the gas collecting plate (17), the bottom of the gas collecting plate (17) is fixedly communicated with the combustion-supporting gas pipes (12), and one ends, far away from the combustion-supporting gas tank (6), of the combustion-supporting gas pipes (12) are fixedly communicated with the conical surface of the windproof cover (15);
the folding mechanism (2) comprises a first support (201), a sliding sleeve (202), a spring (203), a second support (204), a motor (205), a detachable fan (206), a first support (207), a rotating pin (208), a second support (209), a reinforcing plate (210), a rotating block (211), a fixed block (212), a waist-shaped hole (213), a cylindrical stretching spring (214), a first half ring (215), a support rod (216) and a second half ring (217), wherein the left end and the right end of the unmanned aerial vehicle (1) are respectively and fixedly connected with the two rotating blocks (211), a boss is arranged at one end of the second support (209) close to the unmanned aerial vehicle (1), the rotating block (211) is rotatably connected with the boss at one end of the second support (209) close to the unmanned aerial vehicle (1) through a pin, one end of the second support (209) far away from the unmanned aerial vehicle (1) is rotatably connected with the bottom of the first support (207) through the rotating pin (208), the top of support frame (207) is connected with fixed block (212) through the round pin rotation, is close to wind cap (15) the top fixedly connected with support two (204) of fixed block (212), keep away from wind cap (15) the top fixedly connected with support one (201) of fixed block (212), the front of support one (201) and the back threaded connection of support two (204), the one end rotation of keeping away from unmanned aerial vehicle (1) of support one (201) and support two (204) is connected with motor (205), the top transmission of motor (205) is connected with detachable fan (206).
2. The FPV and multi-rotor drone based power inspection device according to claim 1, it is characterized in that the top of the first support frame (207) is provided with a square hole, the back of the first support frame (207) close to the top is provided with a square through hole, waist-shaped holes (213) are arranged at the left end and the right end of the first support frame (207) and close to the top, a pin is arranged in a waist-shaped hole (213) formed in the first support frame (207), the pin arranged in the waist-shaped hole (213) of the first support frame (207) is rotatably connected to the bottom axis of the fixed block (212), a cylindrical extension spring (214) is arranged in a square hole formed in the first support frame (207), the bottom of the cylindrical extension spring (214) is fixedly connected with the bottom of the square hole of the first support frame (207), the top of the cylindrical extension spring (214) is fixedly clamped with the bottom of the fixing block (212).
3. The FPV and multi-rotor unmanned aerial vehicle based power inspection device of claim 2, wherein the connection ends of the first support frame (207) and the second support frame (209) are in 45-degree inclined plane complementary contact.
4. The electric power inspection device based on FPV and multi-rotor unmanned aerial vehicle of claim 3, characterized in that the outer surface of the first bracket (201) close to the front is provided with a groove towards the axis, a spring (203) is arranged in the groove formed in the first bracket (201), the sliding sleeve (202) is slidably connected in the groove formed in the first bracket (201), the inner wall of the sliding sleeve (202) is provided with the spring (203), the inner wall of the sliding sleeve (202) is close to the front and is provided with a threaded hole, the outer surface of the second bracket (204) close to the back is provided with a threaded groove, and the sliding sleeve (202) is in threaded connection with the second bracket (204).
5. The FPV and multi-rotor unmanned aerial vehicle-based power inspection device according to claim 4, wherein the first half ring (215) is fixedly connected to the left end and the right end of the unmanned aerial vehicle, the first half ring (215) is arranged on the rear side of the rotating block (211), the second half ring (217) is fixedly connected to the back of the second support frame (209), the first half ring (215) and the second half ring (217) are connected with each other through a support rod (216), a T-shaped groove is formed in one end of the first support frame (207) close to the unmanned aerial vehicle (1) and the top of the second support frame (209), and the reinforcing plate (210) is clamped in the T-shaped groove of the first support frame (207) and the second support frame (209).
6. The FPV and multi-rotor unmanned aerial vehicle-based power inspection device according to claim 5, wherein the observation head (9) comprises a laser emitting head (901), an observation camera (902) and an observation fixed shell (903), the observation fixed shell (903) is provided with the observation camera (902) at the left end, and the laser emitting head (901) is provided at the right end of the observation fixed shell (903).
7. The FPV and multi-rotor unmanned aerial vehicle-based power inspection device according to claim 6, wherein a fixing boss (13) is fixedly connected to the outer surface of the middle of the oil pipe (10), and a wind vane (14) is rotatably connected to the top of the fixing boss (13).
8. The electric power inspection device based on the FPV and the multi-rotor unmanned aerial vehicle as claimed in claim 7, wherein one end of the wind direction indication of the wind vane (14) is painted with a bright color, and based on the wind direction indication of the wind vane (14), the laser emitting head (901) can form a certain included angle with a nozzle of an oil pipe when being positioned.
9. The electric power inspection device based on FPV and multi-rotor unmanned aerial vehicle of claim 8, characterized in that the outer surface of the windshield (15) is provided with a through hole, and the ignition head (11) is fixed on the cylindrical surface of the windshield (15).
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| CN112874759B (en) * | 2021-02-25 | 2023-05-26 | 中国南方电网有限责任公司超高压输电公司贵阳局 | Portable unmanned aerial vehicle for power grid inspection |
| KR102480818B1 (en) * | 2021-03-15 | 2022-12-26 | 주식회사 에어퓨쳐 | Mission Equipment for Anti Hornet Drone |
| CN113173249A (en) * | 2021-06-15 | 2021-07-27 | 南通大学 | Unmanned aerial vehicle laser gun for removing foreign matters from electric power high-voltage overhead transmission line and method thereof |
| CN113581456B (en) * | 2021-08-25 | 2023-02-07 | 广西电网有限责任公司防城港供电局 | Unmanned aerial vehicle mounted laser cutting mechanism for cleaning overhead power supply line |
| CN114162299A (en) * | 2021-11-30 | 2022-03-11 | 大连理工大学 | Trans-medium aircraft based on cycloid propeller |
| CN117775335A (en) * | 2024-02-27 | 2024-03-29 | 利华兴业(大连)新能源有限公司 | Unmanned aerial vehicle panorama camera device |
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