CN110380358A - Installation, method for dismounting and the dismantling device of fault detector - Google Patents
Installation, method for dismounting and the dismantling device of fault detector Download PDFInfo
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- CN110380358A CN110380358A CN201910739945.8A CN201910739945A CN110380358A CN 110380358 A CN110380358 A CN 110380358A CN 201910739945 A CN201910739945 A CN 201910739945A CN 110380358 A CN110380358 A CN 110380358A
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- fault detector
- installation tool
- power line
- accommodating chamber
- installation
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- 238000009434 installation Methods 0.000 title claims abstract description 191
- 238000000034 method Methods 0.000 title claims abstract description 29
- 230000007246 mechanism Effects 0.000 claims abstract description 139
- 230000007257 malfunction Effects 0.000 claims abstract description 8
- 210000000078 claw Anatomy 0.000 claims description 59
- 230000009471 action Effects 0.000 claims description 12
- 230000033001 locomotion Effects 0.000 claims description 9
- 230000004888 barrier function Effects 0.000 claims 1
- 238000001514 detection method Methods 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 10
- 230000000694 effects Effects 0.000 description 6
- 230000005611 electricity Effects 0.000 description 5
- 125000006850 spacer group Chemical group 0.000 description 5
- 238000000354 decomposition reaction Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/02—General constructional details
- G01R1/04—Housings; Supporting members; Arrangements of terminals
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
-
- 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
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N7/00—Television systems
- H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
- H04N7/183—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a single remote source
- H04N7/185—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a single remote source from a mobile camera, e.g. for remote control
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Multimedia (AREA)
- Signal Processing (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Automation & Control Theory (AREA)
- Electric Cable Installation (AREA)
Abstract
The present invention relates to power line failure indicating equipment technical fields, more particularly to a kind of installation of fault detector, method for dismounting and dismantling device.The installation method includes: that the electricity-fetching mechanism of fault detector is made to be maintained at open position, and control flight instruments take off, to carry installation tool and fault detector close to power line；When power line enters in the opening of the electricity-fetching mechanism of fault detector, control flight instruments fly towards power line side, so that installation tool driving malfunction indicator is installed on power line；When fault detector is clamped on power line, control flight instruments fly towards the direction far from power line, so that installation tool is detached from fault detector.Installation tool is carried using flight instruments and cooperates fault detector, and fault detector is clamped on power line to carry out that electro-detection is taken to operate by realization, easy to operate.Flight instruments can carry installation tool and be detached from fault detector to carry out the installation operation of next fault detector simultaneously, reduce costs.
Description
Technical field
The present invention relates to power line failure indicating equipment technical field, more particularly to a kind of fault detector installation,
Method for dismounting and dismantling device.
Background technique
Fault detector is suitable for distribution line, for acquiring every phase load electric current, voltage-to-ground, can carry out short circuit, connect
Earth fault detection, electrification instruction, on the spot indicating fault.CN201611245841.4 discloses a kind of removable flight electric power acquisition
Terminal and acquisition method, including rack, multiple wings, master control borad and take electric clip connection device and indicating fault at flight steering engine
Device takes electric clip connection device and fault detector to be respectively provided on the rack.Electric snapping machine will be taken by controlling flight steering engine by master control borad
Structure is articulated on high-tension cable, and is acquired data and be sent to master control borad.Master control borad carries out fault verification to acquisition data simultaneously, and
Failure is indicated by fault detector.After data acquire, electric fastening structure is taken to be detached from bus, whole frame flies fall downwards
Ground.In this way, improving the installation and recycling safety to acquisition terminal, and operate conveniently.But program higher cost is relatively applicable in
In the acquisition terminal frequently mounted and dismounted.And for needing to be fixed on the fault collection device of high voltage cable for a long time, at
This is higher.
Summary of the invention
Based on this, it is necessary to be set for the unmanned flight's device and fault detector modularization of traditional electric power acquisition equipment
Meter scheme problem at high cost provides installation, method for dismounting and the dismantling device of a kind of fault detector.
A kind of installation method of fault detector, comprising the following steps:
The electricity-fetching mechanism of fault detector is set to be maintained at open position, control flight instruments take off, to carry installation tool
And fault detector is close to power line；
Judge whether power line enters the opening of the electricity-fetching mechanism of fault detector；
When in the opening for the electricity-fetching mechanism that judgement power line enters fault detector, flight instruments are controlled towards power line
Side flight, so that installation tool driving malfunction indicator is installed on power line；
Judge whether the thread clamping mechanism of fault detector clamps with power line；
When the thread clamping mechanism and power line that determine fault detector clamp, flight instruments are controlled towards the side far from power line
To flight, so that installation tool is detached from fault detector.
Control flight instruments fly towards power line side in one of the embodiments, so that installation tool driving malfunction
Indicator is installed to the step on power line
It controls flight instruments to fly towards power line side, so that power line presses fault detector, so that failure
The thread clamping mechanism of indicator is detached from the restriction of the touch buckle of installation tool and presss from both sides under the action of the stored energy mechanism of installation tool
The electricity-fetching mechanism of tight power line, simultaneous faults indicator moves to closed position；
The step of making electricity-fetching mechanism be maintained at open position in one of the embodiments, includes:
Fault detector is placed in the accommodating chamber of installation tool, the thread clamping mechanism of fault detector is opened, and makes to pacify
The touch buckle of holding tool catches on the thread clamping mechanism of fault detector, so that the electricity-fetching mechanism of fault detector is maintained at open position
It sets.
In one of the embodiments, before the step in the accommodating chamber that fault detector is placed in installation tool,
It is further comprising the steps of:
It opens the driving claw of installation tool and makes that claw is driven to be maintained at opening using the position limiting structure of installation tool
Position；
The limit lock tongue of installation tool is adjusted to retracted state.
The step of the thread clamping mechanism of fault detector is caught in the touch buckle for making installation tool in one of the embodiments,
It is further comprising the steps of after rapid:
Limit of the position limiting structure of installation tool to driving claw is released, is moved so that driving claw has to closed position
Trend.
In one of the embodiments, before the step of electricity-fetching mechanism for making fault detector is maintained at open position,
It is further comprising the steps of:
Installation tool is connect with flight instruments；
The image acquisition device of flight instruments is fixed on to the predeterminated position of the drone body of flight instruments.
A kind of method for dismounting of fault detector, comprising the following steps:
Installation tool is set to be maintained at opening state, control flight instruments take off, to carry installation tool close to indicating fault
Device；
Judge whether fault detector is aligned with the opening of the accommodating chamber of installation tool；
When determining that fault detector is aligned with the opening of the accommodating chamber of installation tool, flight instruments are controlled towards indicating fault
The direction of device is flown, so that fault detector enters in accommodating chamber；
Judge whether the locking mechanism of fault detector releases the locking to the wire clamp of fault detector；
When the locking mechanism for determining fault detector has released the locking to the wire clamp of fault detector, erector is judged
Whether the limit lock tongue of tool pops up and is connected to the surface of fault detector；
When the limit lock tongue for determining installation tool pops up and is connected to the surface of fault detector, flight instruments court is controlled
Direction far from power line is flown, so that fault detector is detached from power line with installation tool together.
The step of making installation tool be maintained at opening state in one of the embodiments, includes:
It opens the driving claw of installation tool and makes that claw is driven to be maintained at opening using the position limiting structure of installation tool
Position.
It further include following step in one of the embodiments, after the step of making installation tool be maintained at opening state
It is rapid:
The limit lock tongue of installation tool is adjusted to elastic stretching state.
A kind of dismantling device of fault detector, including installation tool, installation tool are removably connect with flight instruments,
And it can ascend to heaven under the drive of flight instruments to overhead transmission line so that fault detector to be installed on power line；
Installation tool is equipped with accommodating chamber for accommodating fault detector, fault detector can be contained in accommodating chamber or
Person deviates from out of accommodating chamber, and when fault detector is contained in accommodating chamber, installation tool can carry fault detector close to electricity
The line of force, and driving malfunction indicator clamps power line, when fault detector clamps power line, installation tool can be filled in flight
Disengaging fault detector under the drive set.
Installation tool, which is equipped with, in one of the embodiments, touches buckle, touches buckle for clasping fault detector
Thread clamping mechanism, so that the electricity-fetching mechanism of fault detector is in an open position.
Installation tool is equipped with stored energy mechanism in one of the embodiments, and stored energy mechanism is for the folder with fault detector
Line mechanism cooperation, to drive thread clamping mechanism to clamp power line.
Stored energy mechanism includes driving claw and the first elastic component in one of the embodiments, and driving claw has separate
The closed position of the open position of the opening of accommodating chamber and the opening close to accommodating chamber, the first elastic component are used to mention to driving claw
For the elastic restoring force moved towards closed position, when driving claw in an open position, driving claw merges out accommodating chamber
Opening drives claw in the first elastic component when fault detector is installed to accommodating chamber and drives claw in the close position
Effect is lower to drive thread clamping mechanism to clamp power line.
Position limiting structure is additionally provided in installation tool in one of the embodiments, position limiting structure is used to refer in receiving failure
When showing device, make that claw is driven to be maintained at open position.
Installation tool further includes the second elastic component in one of the embodiments, is mounted in accommodating chamber, the second elastic component
For providing the elastic force of abjection accommodating chamber to fault detector when fault detector is installed to accommodating chamber.
Limit lock tongue is additionally provided in installation tool in one of the embodiments, limit lock tongue is located at the opening of accommodating chamber
Locate, limit lock tongue has retracted state and elastic stretching state, and when limit lock tongue is in retracted state, limit lock tongue is merged out
The opening of accommodating chamber, when limiting lock tongue in elastic stretching state, limit lock tongue can be abutted with the surface of fault detector,
Fault detector to be locked in accommodating chamber.
Flight instruments include drone body in one of the embodiments, and the figure being arranged in drone body
As collector and controller, installation tool is removably attached in drone body, and image acquisition device is connect with controller, figure
It is used to acquire picture signal as collector and picture signal is sent to controller, controller is for receiving picture signal and basis
The movement of picture signal control drone body.
The dismantling device of fault detector further includes remote control device in one of the embodiments, is connect with controller, distant
Control device is used to receive and the image of display controller feedback, while the movement of drone body is controlled by controller.
Beneficial effects of the present invention include at least:
The installation method of above-mentioned fault detector carries installation tool using flight instruments and cooperates fault detector, so that
Fault detector can be reliably mounted on the acquisition that electric power data is carried out on power line, easy to operate.Work as fault detector
When being reliably mounted on power line, flight instruments can carry installation tool and be detached from fault detector.To flight instruments and peace
Holding tool can operate the installation of next fault detector, the very big cost for having saved electric power acquisition.
The method for dismounting of above-mentioned fault detector carries installation tool using flight instruments and cooperates fault detector, so that
Fault detector can be disassembled smoothly from power line, easy to operate, conducive to the safe retrieving of fault detector.
The dismantling device of above-mentioned fault detector accommodates fault detector by installation tool, and entirety can be filled in flight
It ascends to heaven under the drive set to high-altitude, while passing through the cooperation of installation tool and fault detector, realization clamps fault detector
To carry out that electro-detection is taken to operate on power line.And after fault detector and power line clamp fasten, flight instruments can also
It enough carries installation tool and is detached from fault detector, so that flight instruments and installation tool are able to carry out next fault detector
Installation operation.In this way, an installation tool and flight instruments can be suitable for multiple fault detectors installation and
Subsequent disassembling section not only operates conveniently fast, but also significantly reduces cost.
Detailed description of the invention
Fig. 1 is the structural decomposition diagram of the dismantling device for the fault detector that one embodiment of the invention provides；
Fig. 2 is the structural decomposition diagram of the fault detector in structure shown in Fig. 1；
Fig. 3 is the structural decomposition diagram of the installation tool in structure shown in Fig. 1；
Fig. 4 is the structural decomposition diagram of the limit lock tongue in structure shown in Fig. 3；
Fig. 5 is flight instruments, installation tool and the fault detector assembling schematic diagram of structure shown in Fig. 1；
Fig. 6 is the schematic diagram of the opening for the electricity-fetching mechanism that power line enters the fault detector in structure shown in Fig. 5；
Fig. 7 is the schematic diagram in the close position of the electricity-fetching mechanism in structure shown in Fig. 6；
Fig. 8 is that flight instruments carry the schematic diagram that installation tool is detached from fault detector in structure shown in Fig. 7；
Fig. 9 is that the flight instruments carrying installation tool in structure shown in Fig. 8 close to fault detector and accommodates indicating fault
The schematic diagram of device；
Figure 10 is the schematic diagram of the installation tool and fault detector disengaging power line in structure shown in Fig. 9；
Figure 11 is the flow chart of the installation method for the fault detector that one embodiment of the invention provides.
Description of symbols:
100- flight instruments；
110- drone body；120- image acquisition device；
200- installation tool；
210- accommodating chamber；The second elastic component of 211-；
220- touches buckle；
230- stored energy mechanism；231- drives claw；The first elastic component of 232-；
240- position limiting structure；241- limit base；242- limits knob；243- limiting slot；
250- limits lock tongue；
251- lock tongue；252- lock tongue bracket；2521- retraction slot；2522- pops up slot；
253- latch bolt spring；254- knob main shaft；
300- fault detector；
310- electricity-fetching mechanism；311- first coil group；The second coil group of 312-；313- dynamic clamping head and quiet clamping head；
320- thread clamping mechanism；
321- wire clamp；
322- locking mechanism；3221- pawl；3222- ratchet；3223- locking pressure spring；
400- remote control device；
500- tool holder；
600- power line.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, by the following examples, it and combines attached
Figure, is further elaborated the installation of fault detector of the invention, method for dismounting and dismantling device.It should be appreciated that
Described herein specific examples are only used to explain the present invention, is not intended to limit the present invention.
It is herein component institute serialization number itself, such as " first ", " second " etc., is only used for distinguishing described object,
Without any sequence or art-recognized meanings.And " connection ", " connection " described in the application, unless otherwise instructed, include directly and
It is indirectly connected with (connection).In the description of the present invention, it is to be understood that, term " on ", "lower", "front", "rear", " left side ",
The orientation of the instructions such as " right side ", "vertical", "horizontal", "top", "bottom", "inner", "outside", " clockwise ", " counterclockwise " or position are closed
System is merely for convenience of description of the present invention and simplification of the description to be based on the orientation or positional relationship shown in the drawings, rather than indicates
Or imply that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore cannot understand
For limitation of the present invention.
In the present invention unless specifically defined or limited otherwise, fisrt feature in the second feature " on " or " down " can be with
It is that the first and second features directly contact or the first and second features pass through intermediary mediate contact.Moreover, fisrt feature exists
Second feature " on ", " top " and " above " but fisrt feature be directly above or diagonally above the second feature, or be merely representative of
First feature horizontal height is higher than second feature.Fisrt feature can be under the second feature " below ", " below " and " below "
One feature is directly under or diagonally below the second feature, or is merely representative of first feature horizontal height less than second feature.
It is shown in Figure 1, the dismantling device for the fault detector that one embodiment of the invention provides, including installation tool
200, installation tool 200 is removably connect with flight instruments 100, and can be ascended to heaven under the drive of flight instruments 100 to aerial
Route is fault detector 300 to be installed on power line 600.Installation tool 200 is equipped with for accommodating fault detector 300
Accommodating chamber 210, fault detector 300 can be contained in accommodating chamber 210 or deviate from out of accommodating chamber 210.Work as indicating fault
When device 300 is contained in accommodating chamber 210, installation tool 200 can carry fault detector 300 close to power line 600, and drive event
Hinder indicator 300 and clamps power line 600.When fault detector 300 clamps power line 600, installation tool 200 can fly
Disengaging fault detector 300 under the drive of device 100.
The dismantling device of the fault detector of the present embodiment accommodates fault detector 300, and two by installation tool 200
Person can integrally ascend to heaven under the drive of flight instruments 100 to high-altitude, while pass through installation tool 200 and fault detector 300
Fault detector 300 is clamped on power line 600 to carry out that electro-detection is taken to operate by cooperation, realization.And in fault detector 300
After being fixedly clamped with power line 600, flight instruments 100 can also carry installation tool 200 and be detached from fault detector 300, from
And flight instruments 100 and installation tool 200 are able to carry out the installation operation of next fault detector 300.In this way, an installation
Tool 200 and a flight instruments 100 can be suitable for installation and the subsequent disassembly behaviour of multiple fault detectors 300
Make, not only operates conveniently fast, but also significantly reduce cost.
It is appreciated that installation tool 200 and the detachably connected mode of flight instruments 100 can there are many.Referring to figure
1, in one embodiment, the dismantling device of fault detector includes tool holder 500, and tool holder 500 is for connecting installation
Tool 200 and flight instruments 100.Between tool holder 500 and installation tool 200 and tool holder 500 and flight instruments
The mode that screw connection can be used between 100 achieves a fixed connection.Certainly, between tool holder 500 and installation tool 200,
And other can also be used between tool holder 500 and flight instruments 100 and be equal to fixed form realization connection.
Flight instruments 100 are mainly the installation and removal for carrying installation tool 200 and removing cooperation fault detector 300.Referring to
Fig. 1, as a kind of enforceable mode, flight instruments 100 include drone body 110, and are arranged in drone body 110
On image acquisition device 120 and controller (not shown).Installation tool 200 is removably attached in drone body 110.Figure
Picture collector 120 is connect with controller, and image acquisition device 120 is for acquiring picture signal and picture signal being sent to control
Device, controller are used to receive picture signal and control the movement of drone body 110 according to picture signal.Image acquisition device 120
High-definition camera etc. can be used, image acquisition device 120 is mainly used for acquiring video image, for whether judging power line 600
Into the opening of the electricity-fetching mechanism 310 of fault detector 300, and judge fault detector 300 thread clamping mechanism 320 whether with
Power line 600 clamps.Simultaneously be also used to judge fault detector 300 whether the opening pair with the accommodating chamber 210 of installation tool 200
Standard, and judge whether locking mechanism 322 releases the locking to wire clamp 321 and judge to limit whether lock tongue 250 pops up and abut
On the surface etc. of fault detector 300.
Further, the dismantling device of fault detector further includes remote control device 400 connected to the controller.Remote control device
400 image for receiving and display controller is fed back, while passing through the movement that controller controls drone body 110.Remote control
Device 400 may include display screen and key operation module.Connection between remote control device 400 and controller is mainly wirelessly transferred
Connection.In this way, the state of flight of drone body 110 can remotely be monitored by remote control device 400, and according to circumstances to unmanned plane
The flare maneuver of ontology 110 is adjusted and controls.
Installation tool 200 is for cooperating with fault detector 300, to realize the installation and removal of fault detector 300
's.Referring to Fig. 1, as a kind of enforceable mode, installation tool 200, which is equipped with, touches buckle 220 and stored energy mechanism 230, touches
Buckle 220 is for clasping the thread clamping mechanism 320 of fault detector 300, so that at the electricity-fetching mechanism 310 of fault detector 300
In open position.Stored energy mechanism 230 is used to cooperate with the thread clamping mechanism 320 of fault detector 300, to drive thread clamping mechanism 320
Clamp power line 600.The structurally and functionally mode for buckling 220 and stored energy mechanism 230 is touched by combination failure indicator 300 rear
It is specifically described in detail in text.
Illustratively, the fault detector 300 in the embodiment of the present invention is equipped with for surrounding power line 600 to carry out
Take the electricity-fetching mechanism 310 of electricity and detection, and the thread clamping mechanism 320 for clamping power line 600.Wherein, electricity-fetching mechanism 310 has
There is the closed position to be formed and carry out signal acquisition by the open position of the opening of power line 600 and around power line 600.Clamp
Mechanism 320 is for driving electricity-fetching mechanism 310 to move between the open and the closed positions.Electric power is clamped in thread clamping mechanism 320
When line 600, electricity-fetching mechanism 310 is in the close position.Referring to Fig. 1 and Fig. 2, in one embodiment, electricity-fetching mechanism 310 may include
First coil group 311 and the second coil group 312, the second coil group 312 can be rotated relative to first coil group 311.Electricity-fetching mechanism
310 it is in an open position when, the second coil group 312 relative to first coil group 311 open, between the two formed pass through power line
600 opening.When electricity-fetching mechanism 310 is in the close position, the second coil group 312 is closed relative to first coil group 311, the two
Between formed around power line 600 clamping opening, first coil group 311, the second coil group 312 and power line 600 can be formed at this time
Take electrical circuit.Thread clamping mechanism 320 can drive the second coil group 312 to rotate, so that electricity-fetching mechanism 310 is in open position and closure
It is moved between position.
Further, dynamic clamping head and quiet clamping head 313 is additionally provided between first coil group 311 and the second coil group 312.Elastic reset
Part 312 is used to provide the reset force of closure to the second coil group 312.Illustratively, dynamic clamping head and quiet clamping head 312 includes torsional spring, is arranged
On the articulated shaft that first coil group 311 is connected with the second coil group 312.The wherein side torque arm of torsional spring is supported relatively fixedly
It connects in first coil group 311, the other side torque arm of torsional spring is connected in the second coil group 312.In the present embodiment, the second coil
Group 312 can be closed relative to first coil group 311 automatically under the effect of the reset force of dynamic clamping head and quiet clamping head 312, without behaviour manually
Make, to easily facilitate the use of fault detector 10.
Referring to Fig. 1 and Fig. 2, in one embodiment, thread clamping mechanism 320 includes wire clamp 321 and locking mechanism 322, takes electricity
Mechanism 310 and wire clamp 321 link, and wire clamp 321 is for driving electricity-fetching mechanism 310 to move between the open and the closed positions.
In conjunction with Fig. 5, when touch buckle 220 clasps wire clamp 321, electricity-fetching mechanism 310 is maintained at open position.In conjunction with Fig. 6 and Fig. 7, when
When wire clamp 321 is detached from touch buckle 220, wire clamp 321 clamps power line 600 under the action of stored energy mechanism 230, so that taking
Motor structure 310 moves to closed position.And locking mechanism 322 is used for when wire clamp 321 clamps power line 600, locks wire clamp 321
Position, with prevent power line 600 deviate from, to ensure that the stability for taking electric process.
In the present embodiment, flight instruments 100 carry installation tool 200 and fault detector 300 are loaded on power line 600
Before, as shown in figure 5, fault detector 300 is installed in the accommodating chamber 210 of installation tool 200, and make to touch buckle 220
Wire clamp 321 is clasped, so that wire clamp 321 drives the second coil group 312 to open relative to first coil group 311, in first coil
The opening for passing through power line 600 is formed between group 311 and the second coil group 312.Referring to Fig. 6, flight instruments 100 carry peace later
Holding tool 200 and fault detector 300 are close to power line 600, when power line 600 enters first coil group 311 and the second line
When position between circle group 312, as shown in fig. 7, power line 600 squeezes fault detector 300, it is detached from wire clamp 321 and touches card
Button 220, so that wire clamp 321 drives the second coil group 312 to close relative to first coil group 311 under the action of stored energy mechanism 230
It closes.At this time first coil group 311, the second coil group 312 and between the two power line 600 formation take electrical circuit.It locks simultaneously
Mechanism 322 can lock the position of wire clamp 321, so that power line 600 is reliably clamped in first coil group 311 and second
Between coil group 312, being reliably connected for fault detector 300 and power line 600 when taking electricity is realized.Referring to Fig. 8, flight is filled later
The disengaging fault detector 300 of installation tool 200 can be carried by setting 100.
Fault detector 300 after hours, by flight instruments 100 carry installation tool 200 from power line 600
Unload fault detector 300.Referring to Fig. 9, when the opening of the accommodating chamber 210 of installation tool 200 is directed at fault detector 300,
It operates flight instruments 100 to fly towards the direction of fault detector 300, so that fault detector 300 slowly enters accommodating chamber 210
In.After fault detector 300 enters accommodating chamber 210 to a certain degree, the side wall of accommodating chamber 210, which applies locking mechanism 322, to be made
Firmly, locking of the locking mechanism 322 to wire clamp 321 is relieved.As shown in Figure 10, flight instruments 100 can pass through erector later
Tool 200 carries fault detector 300 and flies towards the direction far from power line 600, under the opposite effect of power line 600, wire clamp
321 and electricity-fetching mechanism 310 open, fault detector 300 can with power line 600 smoothly be detached from.Failure is referred to realize
Show the safe retrieving of device 300.
In this way, locking mechanism 322 only need to be released to wire clamp when installing fault detector 300 and installation tool 200
321 locking, that is, openable wire clamp 321, and wire clamp 321 is fixed with buckle 220 is touched, without referring to as traditional failure
Show that device 300 will overcome biggish elastic force that could open wire clamp 321 like that.So that fault detector 300 is easier for installation,
It operates simpler laborsaving.And when unloading fault detector 300, also only locking mechanism 322 need to be released by installation tool 200
Fault detector 300 and power line 600 may make to be detached from the locking of wire clamp 321, uninstall process also simpler convenience, behaviour
Make more friendly.
The structure type of locking mechanism 322 can be a variety of.Referring to fig. 2, in one embodiment, locking mechanism 322 is
Ratchet locking mechanism.Ratchet locking mechanism may include pawl 3221 and ratchet 3222, and pawl 3221 is arranged in wire clamp 321 and failure
In the one of them of the shell of indicator 300, the corresponding pawl 3221 of ratchet 3222 is arranged in wire clamp 321 and fault detector 300
Shell another one on, pawl 3221 and the cooperation of ratchet 3222 are with the backstop wire clamp 321 when wire clamp 321 clamps power line 600.
Illustratively, pawl 3221 includes the trigger unit and locking part for being located at both ends, and the middle part of pawl 3221 is rotatably coupled
On the shell of fault detector 300, trigger unit and locking part are around the counter motion each other of the middle part of pawl 3221.Ratchet 3222 can
It is connected on wire clamp 321 relatively fixedly, locking part is used to cooperate with ratchet 3222, with latch ratchet 3222 or release ratchet
3222.Locking mechanism 322 may also include the locking pressure spring 3223 being arranged between trigger unit and the shell of fault detector 300,
Locking pressure spring 3223 is used to provide the reset force of the shell far from fault detector 300 to trigger unit.
Under normal condition, under the action of locking pressure spring 3223, locking part contacts pawl 3221 with ratchet 3222, wire clamp
321 positions are locked.When needing to open wire clamp 321, it is only necessary to apply certain external force to trigger unit, accordingly locking part will
It is disengaged with ratchet 3222, so as to arbitrarily rotate wire clamp 321.Therefore, when needing wire clamp 321 to clamp power line 600, make
Locking part is contacted with ratchet 3222 with latch ratchet 3222, thus realize under the interaction of pawl 3221 and ratchet 3222,
So that wire clamp 321 can not be opened.Fault detector 300 after hours, need from Tear Down Deficiency indicator on power line 600
When 300, it is only necessary to which the accommodating chamber 210 of installation tool 200 is directed at fault detector 300 to accommodate fault detector 300.Together
When during receiving, the side wall of accommodating chamber 210 can squeeze trigger unit so that locking part be detached from ratchet 3222, to release
Locking to wire clamp 321, and then smoothly remove fault detector 300.In this way, flight instruments 100, which are more easily utilized, carries peace
Holding tool 200 dismantles fault detector 300, easy to operate, without being strictly directed at clamping-line structure solution as tradition
Lock direction.
Stored energy mechanism 230 generally refers to the drive of stored energy mechanism 230 for driving thread clamping mechanism 320 to clamp power line 600
Wire clamp 321 clamps power line 600.The structure type of stored energy mechanism 230 can be a variety of.Referring to Fig. 3, as a kind of enforceable
Mode, stored energy mechanism 230 include driving claw 231 and the first elastic component 232, and driving claw 231 has far from accommodating chamber 210
The closed position of the open position of opening and the opening close to accommodating chamber 210, the first elastic component 232 are used for driving claw 231
The elastic restoring force moved towards closed position is provided.When driving claw 231 in an open position, driving claw 231 is merged out
The opening of accommodating chamber 210 is driven when the installation of fault detector 300 to accommodating chamber 210 and driving claw 231 in the close position
Dynamic claw 231 drives wire clamp 321 to move towards the side for clamping power line 600 under the action of the first elastic component 232.
In the present embodiment, before fault detector 300 is installed to installation tool 200, make that claw 231 is driven to be in open position
It sets, so that fault detector 300 can be smoothly installed in accommodating chamber 210 by the opening of accommodating chamber 210.Work as indicating fault
After the installation to accommodating chamber 210 of device 300, wire clamp 321 is clasped using buckle 220 is touched, so that electricity-fetching mechanism 310 is maintained at open position
It sets.It is worth noting that may make fault detector 300 in accommodating chamber when fault detector 300 is installed in accommodating chamber 210
There is certain elastic floating in 210.In this way when installation tool 200 carries fault detector 300 close to power line 600, electricity
The line of force 600 can extrude fault detector 300, break off relations so that touching buckle 220 with wire clamp 321.And then drive claw 231 can
It is moved under the action of the first elastic component 32 to closed position, to drive wire clamp 321 to move, so that electricity-fetching mechanism 310 is transported
It moves to closed position.
Referring to Fig. 3, in one embodiment, the dismantling device of fault detector further includes the second elastic component 211, is mounted on
In accommodating chamber 210.When second elastic component 211 is used in the installation to accommodating chamber 210 of fault detector 300, to fault detector
300 provide the elastic force of abjection accommodating chamber 210.Second elastic component 211 can be helical spring.Or second elastic component 211
It can be elastic slice, the structures such as butterfly spring.
In conjunction with Fig. 5, when fault detector 300 is installed in accommodating chamber 210 and wire clamp 321 is touched buckle 220 and clasps,
Fault detector 300 is had the tendency that deviating from outward by the elastic force effect of the second elastic component 211, and driving claw 231 is by the first elasticity
The elastic restoring force effect of part 232 has the tendency that wire clamp 321 is pushed to move towards the position for clamping power line 600, while touching card
Button 220 catches on wire clamp 321, prevent wire clamp 321 towards the position for clamping power line 600 from moving.Finally, fault detector 300
Can be relatively fixed in the accommodating chamber 210 of installation tool 200, and electricity-fetching mechanism 310 is maintained at open position, consequently facilitating will
Fault detector 300 is installed on power line 600.In the present embodiment, by the way that the second elastic component 211 is arranged, failure may make to refer to
When showing that device 300 is housed in accommodating chamber 210, fault detector 300 can have certain elasticity floating relative to installation tool 200
It is dynamic, it is broken off relations with making to touch buckle 220 for fault detector 300 when being loaded on power line 600 with wire clamp 321.
Referring to Fig. 1 and Fig. 3, as a kind of enforceable mode, it is additionally provided with position limiting structure 240 in installation tool 200, limits
Structure 240 is used for when accommodating fault detector 300, makes that claw 231 is driven to be maintained at open position.By the way that position limiting structure is arranged
240, when can unload fault detector 300 when fault detector 300 is packed into installation tool 200 or from power line 600
The position of fixed driving claw 231 avoids driving claw 231 from hindering to the receiving of fault detector 300 into accommodating chamber 210.
In one embodiment, position limiting structure 240 includes limit base 241, limit knob 242 and limiting slot 243.Limit base
241 are arranged on the bracket of installation tool 200.Knob 242 is limited rotationally through setting on limit base 241, and is limited
One end of knob 242 can be stretched out from inside to outside from limit base 241, or be retracted into limit base 241.The corresponding limit of limiting slot 243
Position knob 242 setting driving claw 231 on, when drive claw 231 it is in an open position when, limit knob 242 one end from
Limit base 241 is stretched out from inside to outside and is fastened in limiting slot 243.Illustratively, as shown in figure 3, limit base 241 is hollow knot
Structure, opposite two side walls offer through-hole.The side of limit base 241 is respectively equipped with deep trouth and shallow slot, deep trouth and shallow slot
It is for, deep trouth refers to that the deeper slot of the depth relative to shallow slot, shallow slot refer to the depth relative to deep trouth
Shallower slot.Limit knob 242 include main body axis, main body axis be equipped with limited post, limited post for be fastened on respectively deep trouth or
In person's shallow slot.Spring and two limit films are additionally provided on main body axis, one of limit film is fixedly connected on main body axis, another
A limit film is movably set on main body axis, and spring is located between two limit films.When limit knob 242 is installed to limit
When on seat 241, two limit films are abutted with the inside of the two side walls equipped with through-hole of limit base 241 respectively, and limited post card is set
In deep trouth or shallow slot.When rotating knob makes limited post be fastened on deep trouth, the end of knob 242 is limited from limit base 241
It stretches out from inside to outside, so that limiting slot 243 can be caught in by limiting the end of knob 242, with the rotation of backstop driving claw 231.When
When rotation knob makes limited post be fastened on shallow slot, the end of limit knob 242 is retracted into limit base 241.
Referring to Fig. 1 and Fig. 3, as a kind of enforceable mode, limit lock tongue 250, limit are additionally provided in installation tool 200
Lock tongue 250 is located at the opening of accommodating chamber 210, and limit lock tongue 250 has retracted state and elastic stretching state.When limit lock tongue
250 when being in retracted state, and limit lock tongue 250 merges out the opening of accommodating chamber 210, stretches out when limit lock tongue 250 is in elasticity
When state, limit lock tongue 250 can be abutted with the surface of fault detector 300, and fault detector 300 is locked in accommodating chamber
In 210.In the present embodiment, limit lock tongue 250 mainly when unload fault detector 300, by fault detector 300 and
Installation tool 200 is reliably fixed, to realize that flight instruments 100 carry installation tool 200 smoothly by fault detector 300 from electric power
It is unloaded on line 600.
Referring to fig. 4, illustratively, limit lock tongue 250 includes lock tongue 251, lock tongue bracket 252 and latch bolt spring 253, and
Knob main shaft 254.Lock tongue bracket 252 is used to be fixed on the opening of accommodating chamber 210, and knob main shaft 254 is mounted on lock tongue bracket
On 252.Lock tongue 251 is connect with one end of knob main shaft 254, and knob main shaft 254 can be rotated relative to lock tongue 251, but two
Person can not relatively move in the axial direction along knob main shaft 254.The setting of lock tongue bracket 252 retraction slot 2521 and pop-up slot 2522,
Spacer pin is fixed on knob main shaft 254, spacer pin is for being fastened in retraction slot 2521 or pop-up slot 2522.Lock tongue bullet
Spring 253 is set on knob main shaft 254, and between lock tongue 251 and spacer pin.When spacer pin is arranged in lock tongue bracket 252
Retraction slot 2521 in when, lock tongue 251 is in retracted state, and lock tongue 251 can merge out the opening of accommodating chamber 210 at this time, thus
Convenient for fault detector 300 to be accommodated to the accommodating chamber 210 into installation tool 200.When spacer pin is arranged in the bullet of lock tongue bracket 252
Out when slot 2522, lock tongue 251 is in elastic stretching state, i.e. limit lock tongue 250 is in elastic stretching state.
In this way, making limit lock tongue 250 be in elasticity when needing to unload fault detector 300 from power line 600 and stretching out
State.When fault detector 300 initially enters accommodating chamber 210, the circumferential side wall of fault detector 300 can squeeze lock tongue 251,
Lock tongue 251 is flexibly contracted in lock tongue bracket 252.When fault detector 300 enters accommodating chamber 210 to a certain degree, lock
Tongue 251 stretches out under the action of latch bolt spring 253 to the inside of accommodating chamber 210, and lock tongue 251 can be with fault detector 300
Upper surface abut, realization fault detector 300 is locked in accommodating chamber 210.In this way, installation tool 200 can be reliably
Fault detector 300 is unloaded from power line 600.
Referring to Figure 11, one embodiment of the invention additionally provides a kind of installation method of fault detector, comprising the following steps:
S100: making the electricity-fetching mechanism 310 of fault detector 300 be maintained at open position, and control flight instruments 100 take off,
To carry installation tool 200 and fault detector 300 close to power line 600.In one embodiment, make fault detector
It further include connecting installation tool 200 with flight instruments 100 before the step of 300 electricity-fetching mechanism 310 is maintained at open position
The step of.It ascends to heaven to overhead transmission line to which flight instruments 100 can carry installation tool 200 to install fault detector 300
In on power line 600.It and include the unmanned plane sheet that the image acquisition device 120 of flight instruments 100 is fixed on to flight instruments 100
The step of predeterminated position of body 110.To which image acquisition device 120 can be collected for controlling the movement of drone body 110
Reference picture.
In one embodiment, electricity-fetching mechanism 310 is made to be maintained at open position, specific operation process may include referring to failure
Show that device 300 is placed in the accommodating chamber 210 of installation tool 200, open the thread clamping mechanism 320 of fault detector 300, and makes to install
The touch buckle 220 of tool 200 catches on the thread clamping mechanism 320 of fault detector 300, so that fault detector 300 takes motor
Structure 310 is maintained at open position.More specifically, in the accommodating chamber 210 that fault detector 300 is placed in installation tool 200
In step before, first open the driving claw 231 of installation tool 200, and made using the position limiting structure of installation tool 200 240
Claw 231 must be driven to be maintained at open position.
Illustratively, make a kind of implementation for driving claw 231 to be maintained at open position can by position limiting structure 240
To be, by limit knob 242 torsion to the state of stretching, so that the end of limit knob 242 is fastened on the limit of driving claw 231
In slot 243, so that claw 231 be driven to be maintained at open position.Limit lock tongue 250 is reversed to retracted state simultaneously.Then, such as
Shown in Fig. 5, fault detector 300 is placed in the accommodating chamber 210 of installation tool 200, opens the wire clamp of fault detector 300
321, so that touch buckle 220 is caught on wire clamp 321, keeps electricity-fetching mechanism 310 in open position.Later, it is right to release position limiting structure 240
The limit of claw 231, such as rotary stopper knob 242 are driven, so that the end of limit knob 242 is retracted into limit base 241,
So that driving claw 231 has the trend moved to closed position.
S200: judge whether power line 600 enters the opening of the electricity-fetching mechanism 310 of fault detector 300.In the step,
The location drawing picture of fault detector 300 and power line 600 is acquired specifically by the image acquisition device 120 of flight instruments 100,
Thus judge whether power line 600 enters the opening of electricity-fetching mechanism 310.
S300: when in the opening for the electricity-fetching mechanism 310 that judgement power line 600 enters fault detector 300, control flies
Luggage sets 100 and flies towards 600 side of power line, so that 200 driving malfunction indicator 300 of installation tool is installed to power line 600
On.In one embodiment, control flight instruments 100 fly towards 600 side of power line, so that 200 driving malfunction of installation tool
The detailed process that indicator 300 is installed on power line 600 includes: that control flight instruments 100 fly towards 600 side of power line,
So that power line 600 presses fault detector 300, so that thread clamping mechanism 320 is detached from the restriction for touching buckle 220 and is storing up
Power line 600 can be clamped under the action of mechanism 230, the electricity-fetching mechanism 310 of simultaneous faults indicator 300 moves to closed position.
In the step, referring to Fig. 6 and Fig. 7, the specific can be that power line 600, which presses fault detector 300, leads to wire clamp
321 are detached from touch buckle 220, so that claw 231 be driven to drive wire clamp 321 electric towards compressing under the action of the first elastic component 232
The position of the line of force 600 moves, while electricity-fetching mechanism 310 moves to closed position, and wire clamp 321 is by 322 locking bit of locking mechanism
It sets.It is appreciated that when in the opening for the electricity-fetching mechanism 310 that judgement power line 600 does not enter fault detector 300, adjustment
The flight position of flight instruments 100, until power line 600 enters in the opening of electricity-fetching mechanism 310.
S400: judge whether the thread clamping mechanism 320 of fault detector 300 clamps with power line 600.In the step, judgement
Whether the thread clamping mechanism 320 of fault detector 300 clamps with power line 600, specifically can be the image by flight instruments 100
Collector 120 acquires the ratchet 3222 of locking mechanism 322 and the location drawing picture of pawl 3221, thus judges fault detector 300
Thread clamping mechanism 320 it is whether tight with the folder 321 of power line 600.When the locking part of pawl 3221 and ratchet 3222 contact, event is determined
The thread clamping mechanism 320 and power line 600 for hindering indicator 300 clamp.Otherwise, it is determined that the thread clamping mechanism 320 of fault detector 300 with
Power line 600 does not clamp.It is appreciated that when the thread clamping mechanism 320 for determining fault detector 300 is not pressed from both sides with power line 600
When tight, the flight position of flight instruments 100 is adjusted, until the locking part of pawl 3221 is contacted with ratchet 3222.
S500: when the thread clamping mechanism 320 and power line 600 that determine fault detector 300 clamp, flight instruments are controlled
100 fly towards the direction far from power line 600, so that installation tool 200 is detached from fault detector 300.In the step, such as Fig. 8
Shown, when the thread clamping mechanism 320 and power line 600 that determine fault detector 300 clamp, control flight instruments 100 are towards separate
It flies in the direction of power line 600.At this point, driving claw 231 rotates under the opposite effect of power line 600, to install
Tool 200 can be detached from fault detector 300.In this way, fault detector 300 is left on power line 600, and failure can be started
Detect work.And flight instruments 100 can carry installation tool 200 and make a return voyage, flight instruments 100 and installation tool 200 can go to grasp
Make the installation of next fault detector 300, to be effectively saved the cost of electric power acquisition.
Referring to Fig. 9 and Figure 10, one embodiment of the invention additionally provides a kind of method for dismounting of fault detector, including following
Step:
S100: installation tool 200 is made to be maintained at opening state, control flight instruments 100 take off, to carry installation tool
200 close to fault detector 300.In one embodiment, the step of making installation tool 200 be maintained at opening state may include,
The driving claw 231 of installation tool 200 is opened, and makes that claw 231 is driven to protect using the position limiting structure of installation tool 200 240
It holds in open position.In addition, reversing limit lock tongue 250 to elastic stretching state.Wherein, to drive by position limiting structure 240
Dynamic claw 242 is maintained in one embodiment of open position, can be limit knob 242 torsion to stretching state, so that
The end of limit knob 242 is fastened in the limiting slot 243 of driving claw 231, so that driving claw 231 is maintained at opening
Position.
S200: judge whether fault detector 300 is aligned with the opening of the accommodating chamber 210 of installation tool 200.The step
In, the location drawing of fault detector 300 and accommodating chamber 210 is acquired particular by the image acquisition device 120 of flight instruments 100
Picture, thus judges whether fault detector 300 is aligned with the opening of the accommodating chamber 210 of installation tool 200.
S300: when determining that fault detector 300 is aligned with the opening of the accommodating chamber 210 of installation tool 200, control flight
Device 100 flies towards the direction of fault detector 300, so that fault detector 300 enters in accommodating chamber 210.It is appreciated that
When determining that the opening of accommodating chamber 210 of fault detector 300 and installation tool 200 is not aligned with, adjustment flight instruments 100
Flight position, until fault detector 300 is aligned with the opening of the accommodating chamber 210 of installation tool 200.
S400: judge whether the locking mechanism 322 of fault detector 300 releases to the wire clamp 321 of fault detector 300
Locking.In the step, particular by the pawl 3221 and ratchet of 120 locking mechanism 322 of image acquisition device of flight instruments 100
3222 location drawing picture, thus judges whether locking mechanism 322 releases the locking to wire clamp 321.When the locking part of pawl 3221
When being detached from ratchet 3222, determine that locking mechanism 322 has released the locking to wire clamp 321.Otherwise, it is determined that locking mechanism 322 does not have
Release the locking to wire clamp 321.It is appreciated that when determining that locking mechanism 322 does not release the locking to wire clamp 321, adjustment
The flight position of flight instruments 100, until the locking part of pawl 3221 is detached from ratchet 3222.
S500: when the locking mechanism 322 for determining fault detector 300 has been released to the wire clamp 321 of fault detector 300
When locking, judge whether the limit lock tongue 250 of installation tool 200 pops up and be connected to the surface of fault detector 300.The step
In, the location drawing picture on 300 surface of fault detector is acquired particular by the image acquisition device 120 of flight instruments 100, is thus sentenced
Whether disconnected limit lock tongue 250 pops up and is connected to the surface of fault detector 300.It is appreciated that when determining that limiting lock tongue 250 does not have
When having pop-up and being connected to the surface of fault detector 300, the flight position of flight instruments 100 is adjusted, until limit lock tongue 250
Pop up and be connected to the surface of fault detector 300.
S600: when the limit lock tongue 250 for determining installation tool 200 pops up and is connected to the surface of fault detector 300,
Control flight instruments 100 towards far from power line 600 direction fly so that fault detector 300 with installation tool 200 together
It is detached from power line 600.In the step, when flight instruments 100 towards when the direction flight far from power line 600, wire clamp 321 is in electric power
It rotates under the action of line 600 and electricity-fetching mechanism 310 is driven to move towards open position, when the second coil of electricity-fetching mechanism 310
When 312 opening angles of group reache a certain level, fault detector 300 can be smoothly detached from from power line 600.To the dress that flies
Installation tool 200 and the return of fault detector 300 ground can be carried by setting 100, realize the safe retrieving of fault detector 300.
Each technical characteristic of embodiment described above can be combined arbitrarily, for simplicity of description, not to above-mentioned reality
It applies all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, all should be considered as described in this specification.
The embodiments described above only express several embodiments of the present invention, and the description thereof is more specific and detailed, but simultaneously
It cannot therefore be construed as limiting the scope of the patent.It should be pointed out that coming for those of ordinary skill in the art
It says, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to protection of the invention
Range.Therefore, the scope of protection of the patent of the invention shall be subject to the appended claims.
Claims (18)
1. a kind of installation method of fault detector, which comprises the following steps:
The electricity-fetching mechanism (310) of fault detector (300) is set to be maintained at open position, control flight instruments (100) is taken off, to take
Band installation tool (200) and fault detector (300) are close to power line (600)；
Judge whether power line (600) enters the opening of the electricity-fetching mechanism (310) of fault detector (300)；
When in the opening for the electricity-fetching mechanism (310) that judgement power line (600) enters fault detector (300), control flight
Device (100) flies towards power line (600) side, so that installation tool (200) driving malfunction indicator (300) is installed to electric power
On line (600)；
Judge whether the thread clamping mechanism (320) of fault detector (300) clamps with power line (600)；
When the thread clamping mechanism (320) and power line (600) that determine fault detector (300) clamp, control flight instruments (100)
It flies towards the direction far from power line (600), so that installation tool (200) is detached from fault detector (300).
2. the installation method of fault detector according to claim 1, which is characterized in that the control flight instruments
(100) it flies towards power line (600) side, so that installation tool (200) driving malfunction indicator (300) is installed to power line
(600) step on includes:
It controls flight instruments (100) to fly towards power line (600) side, so that power line (600) presses fault detector
(300), so that the touch that the thread clamping mechanism (320) of fault detector (300) is detached from installation tool (200) buckles (220)
Restriction and under the action of the stored energy mechanism of installation tool (200) (230) clamp power line (600), simultaneous faults indicator
(300) electricity-fetching mechanism (310) moves to closed position.
3. the installation method of fault detector according to claim 1, which is characterized in that described to make electricity-fetching mechanism (310)
The step of being maintained at open position include:
Fault detector (300) is placed in the accommodating chamber (210) of installation tool (200), fault detector (300) are opened
Thread clamping mechanism (320), and the touch of installation tool (200) is made to buckle the thread clamping mechanism that (220) catch on fault detector (300)
(320), so that the electricity-fetching mechanism (310) of fault detector (300) is maintained at open position.
4. the installation method of fault detector according to claim 3, which is characterized in that described by fault detector
(300) it is placed in front of the step in the accommodating chamber (210) of installation tool (200), further comprising the steps of:
It opens the driving claw (231) of installation tool (200) and to drive using the position limiting structure (240) of installation tool (200)
Dynamic claw (231) are maintained at open position；
The limit lock tongue (250) of installation tool (200) is adjusted to retracted state.
5. the installation method of fault detector according to claim 4, which is characterized in that make installation tool described
It (200) further include following step after the step of touch buckle (220) catches on thread clamping mechanism (320) of fault detector (300)
It is rapid:
Limit of the position limiting structure (240) of installation tool (200) to driving claw (231) is released, so that driving claw (231) tool
The trend of oriented closed position movement.
6. the installation method of fault detector according to claim 1, which is characterized in that make fault detector described
(300) further comprising the steps of before the step of electricity-fetching mechanism (310) is maintained at open position:
Installation tool (200) is connect with flight instruments (100)；
The image acquisition device (120) of flight instruments (100) is fixed on the pre- of the drone body (110) of flight instruments (100)
If position.
7. a kind of method for dismounting of fault detector, which comprises the following steps:
Installation tool (200) is set to be maintained at opening state, control flight instruments (100) is taken off, leaned on to carry installation tool (200)
Nearly fault detector (300)；
Judge whether fault detector (300) is aligned with the opening of the accommodating chamber (210) of installation tool (200)；
When determining that fault detector (300) are aligned with the opening of the accommodating chamber (210) of installation tool (200), control flight dress
It sets (100) to fly towards the direction of fault detector (300), so that fault detector (300) enters in accommodating chamber (210)；
Judge whether the locking mechanism (322) of fault detector (300) releases to the wire clamp (321) of fault detector (300)
Locking；
When the locking mechanism (322) for determining fault detector (300) has been released to the wire clamp (321) of fault detector (300)
When locking, judge whether the limit lock tongue (250) of installation tool (200) pops up and be connected to the surface of fault detector (300)；
When the limit lock tongue (250) for determining installation tool (200) pops up and is connected to the surface of fault detector (300), control
Flight instruments (100) processed are flown towards the direction far from power line (600), so that fault detector (300) is with installation tool
(200) power line (600) are detached from together.
8. the method for dismounting of fault detector according to claim 7, which is characterized in that described to make installation tool (200)
The step of being maintained at opening state include:
It opens the driving claw (231) of installation tool (200) and to drive using the position limiting structure (240) of installation tool (200)
Dynamic claw (231) are maintained at open position.
9. the method for dismounting of fault detector according to claim 7, which is characterized in that make installation tool described
(200) further comprising the steps of after the step of being maintained at opening state:
The limit lock tongue (250) of installation tool (200) is adjusted to elastic stretching state.
10. a kind of dismantling device of fault detector, which is characterized in that including installation tool (200), the installation tool
(200) it removably connect, and can be ascended to heaven under the drive of the flight instruments (100) to overhead line with flight instruments (100)
Road is fault detector (300) to be installed on power line (600)；
The installation tool (200) is equipped with the accommodating chamber (210) for accommodating the fault detector (300), and the failure refers to
Show that device (300) can be contained in the accommodating chamber (210) or deviate from out of the accommodating chamber (210), when the failure refers to
When showing that device (300) is contained in the accommodating chamber (210), the installation tool (200) can carry the fault detector (300)
Close to power line (600), and the fault detector (300) is driven to clamp power line (600), when the fault detector
(300) when clamping power line (600), the installation tool (200) can be detached from institute under the drive of the flight instruments (100)
State fault detector (300).
11. the dismantling device of fault detector according to claim 10, which is characterized in that the installation tool (200)
(220) are buckled equipped with touching, the thread clamping mechanism for touching buckle (220) and being used to clasp the fault detector (300)
(320), so that the electricity-fetching mechanism (310) of the fault detector (300) is in an open position.
12. the dismantling device of fault detector according to claim 10, which is characterized in that the installation tool (200)
Equipped with stored energy mechanism (230), the stored energy mechanism (230) is used to match with the thread clamping mechanism (320) of the fault detector (300)
It closes, to drive the thread clamping mechanism (320) to clamp power line (600).
13. the dismantling device of fault detector according to claim 12, which is characterized in that the stored energy mechanism (230)
Including driving claw (231) and the first elastic component (232), driving claw (231) has far from the accommodating chamber (210)
The open position of opening and close to the accommodating chamber (210) opening closed position, first elastic component (232) be used for
Driving claw (231) provides the elastic restoring force moved towards closed position, when the driving claw (231) is in open position
When setting, driving claw (231) merges out the opening of the accommodating chamber (210), when the fault detector (300) are installed extremely
When the accommodating chamber (210) and the driving claw (231) in the close position, the driving claw (231) is described first
The thread clamping mechanism (320) are driven to clamp power line (600) under the action of elastic component (232).
14. the dismantling device of fault detector according to claim 13, which is characterized in that the installation tool (200)
On be additionally provided with position limiting structure (240), the position limiting structure (240) be used for when accommodate fault detector (300), make described in
Driving claw (231) is maintained at open position.
15. the dismantling device of fault detector according to claim 10, which is characterized in that the installation tool (200)
Further include the second elastic component (211), be mounted in the accommodating chamber (210), second elastic component (211) is used in the event
When barrier indicator (300) installation is interior to the accommodating chamber (210), Xiang Suoshu fault detector (300) provides the receiving
The elastic force of chamber (210).
16. the dismantling device of fault detector according to claim 10, which is characterized in that the installation tool (200)
On be additionally provided with limit lock tongue (250), limit lock tongue (250) is located at the opening of the accommodating chamber (210), the limiting lock
Tongue (250) has retracted state and elastic stretching state, when the limit lock tongue (250) is in retracted state, the limit
Lock tongue (250) merges out the opening of the accommodating chamber (210), when the limit lock tongue (250) is in elastic stretching state, institute
Stating limit lock tongue (250) can abut with the surface of the fault detector (300), and the fault detector (300) are locked
It is scheduled in the accommodating chamber (210).
17. the dismantling device of fault detector according to claim 10, which is characterized in that the flight instruments (100)
Including drone body (110), and the image acquisition device (120) and controller that are arranged on drone body (110), it is described
Installation tool (200) is removably attached on the drone body (110), described image collector (120) and the control
Device connection processed, described image collector (120) are described for acquiring picture signal and picture signal being sent to the controller
Controller is used to receive described image signal and controls the movement of the drone body (110) according to described image signal.
18. the dismantling device of fault detector according to claim 17, which is characterized in that further include remote control device
(400), it is connect with the controller, the remote control device (400) is used to receive and show the image of the controller feedback, together
When the movement of the drone body (110) is controlled by the controller.
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| CN201910739945.8A CN110380358A (en) | 2019-08-12 | 2019-08-12 | Installation, method for dismounting and the dismantling device of fault detector |
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| CN201910739945.8A CN110380358A (en) | 2019-08-12 | 2019-08-12 | Installation, method for dismounting and the dismantling device of fault detector |
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| CN112222806A (en) * | 2020-09-23 | 2021-01-15 | 青岛鼎信通讯股份有限公司 | Remote-controllable electric fault indicator assembling and disassembling tool |
| CN112509300A (en) * | 2020-11-17 | 2021-03-16 | 青岛鼎信通讯股份有限公司 | Remote control method for fault indicator installation tool |
| CN113067283A (en) * | 2021-03-31 | 2021-07-02 | 艾斯佩特(武汉)科技有限公司 | Indirect operation and tool transmission method for power transmission and transformation equipment |
| CN113160528A (en) * | 2021-02-24 | 2021-07-23 | 郑州龙华机电工程有限公司 | Power equipment fault monitoring alarm device |
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