CN108983037A

CN108983037A - A kind of modified power grid monitoring device

Info

Publication number: CN108983037A
Application number: CN201810133118.XA
Authority: CN
Inventors: 董岳良
Original assignee: Individual
Current assignee: Individual
Priority date: 2018-02-09
Filing date: 2018-02-09
Publication date: 2018-12-11

Abstract

The invention discloses a kind of modified power grid monitoring devices, including fuselage body and it is arranged in intracorporal first vestibule of the fuselage, the fuselage body bottom end face is fixedly installed with bottom plate, the vertex of the bottom base plate end face four is fixedly installed with rubber mat, intercommunication is equipped with the second vestibule in the inner wall of first vestibule left end, intercommunication is equipped with third vestibule in the first vestibule right end inner wall, the third vestibule right end runs through the fuselage body right end end face, the 4th vestibule positioned at first chamber bottom is equipped in the fuselage body, first hole is intracavitary to be equipped with lock bracket, the lock bracket bottom is fixedly connected with the first steering shaft that front and back is expanded, expansion end is rotatably assorted with inner wall before and after first vestibule connect respectively before and after first steering shaft, first vestibule is equipped with positioned at the lock bracket right end and is mutually clamped therewith Lock hook；The configuration of the present invention is simple, it is easy to operate, improve the effect and practicability of information-based malfunction elimination.

Description

A kind of modified power grid monitoring device

Technical field

The present invention relates to field of electrical equipment, specifically a kind of modified power grid monitoring device.

Background technique

Power grid is the entirety of the electric substation of various voltages and transmission of electricity distribution line composition in electric system, composed structure Complexity, it is most important for the line service of power grid, when breaking down in electric power network, pass through electric power maintenance work at present People checks, and troubleshooting procedure is cumbersome, needs to expend a large amount of manpower and time, quickly checks therefore, it is necessary to one kind Power network monitoring equipment.

Summary of the invention

Technical problem to be solved by the invention is to provide a kind of modified power grid monitoring devices, are able to solve above-mentioned existing In the art the problem of.

The present invention is achieved through the following technical solutions: a modification of the present invention type power network monitoring device, including In intracorporal first vestibule of the fuselage, the fuselage body bottom end face is fixedly installed with bottom plate, described for fuselage body and setting The vertex of bottom base plate end face four is fixedly installed with rubber mat, and intercommunication is equipped with the second hole in the inner wall of first vestibule left end Chamber, intercommunication is equipped with third vestibule in the first vestibule right end inner wall, and the third vestibule right end runs through the fuselage body right end End face, interior the 4th vestibule being equipped with positioned at first chamber bottom of the fuselage body, first hole is intracavitary to be equipped with lock bracket, The lock bracket bottom is fixedly connected with the first steering shaft that front and back is expanded, expanded before and after first steering shaft end respectively with Inner wall is rotatably assorted connection before and after first vestibule, and first vestibule, which is equipped with, to be located at the lock bracket right end and mutually block therewith The lock hook connect, the lock hook are equipped with the second steering shaft that front and back is expanded, expanded before and after second steering shaft end with Inner wall is rotatably assorted connection before and after first vestibule, and the volume positioned at the lock hook rear end is arranged in second steering shaft Tight piece, is fixedly connected with the operating stick expanded to the right on the lock hook, second hole is intracavitary be equipped with to the locking The conductive winding that frame is connected by power, intracavitary be equipped in second hole are electrically connected with lock bracket left end end face and control expansion Current protection silk, is equipped with the electric controller positioned at second vestibule left end in the end face of fuselage body left end, the electric controller with The current protection silk and conductive winding electrical connection, the 4th hole is intracavitary equipped with the third steering shaft expanded up and down, and described the Expansion end is rotatably assorted with the 4th vestibule top inner wall at the top of three steering shafts connect, and third steering shaft bottom is expanded End has been connected by power first motor, be arranged in sequence from top to bottom in the third steering shaft the first different deflection wheel of corner, Second deflection wheel, third deflection wheel and the 4th deflection wheel are slidably connected with difference in the inner wall of the 4th vestibule left end To connect with the first deflection wheel, the second deflection wheel, third deflection wheel and the 4th deflection wheel pushing tow and head to the left One accident checks bar, the second accident investigation bar, third accident investigation bar and the 4th accident and checks bar, the first accident investigation Bar, the second accident investigation bar, third accident investigation bar and the 4th accident are checked and are designed with recovery device on bar, in the fuselage body Equipped with the 5th vestibule for being located at the first motor right end and being located at immediately below the third vestibule, the 5th hole is intracavitary to be equipped with Device for opening is additionally provided with hand lift device on the fuselage body.

Preferably technical solution, the recovery device include being arranged in the 4th vestibule left end and by described first Accident checks bar, the second accident investigation bar, third accident investigation bar and the 4th accident and checks perforative 6th vestibule of bar, and described the The intracavitary pushing tow in six holes is equipped with the first spring element, and the first spring element right end and first accident investigation bar, the second accident are arranged Bar, third accident investigation bar and the 4th accident investigation bar is looked into be fixedly connected.

Preferably technical solution, the device for opening include that the intracavitary supply arm in the 5th hole is arranged in and sets The power connecting arm on the 5th chamber bottom inner wall is set, supply arm left end end and the 5th vestibule left end inner wall rotate It is cooperatively connected, pushing tow is connected with the second spring element, the confession between the 5th vestibule top inner wall at the top of the supply arm Electric arm bottom end face be equipped with to power connecting arm electrical connection and the third spring element that connect of pushing tow, the 5th vestibule and The implementation bar expanded up and down is slidably connected between the third vestibule in inner wall, expands end at the top of the implementation bar It is intracavitary to protrude into the third hole, the implementation bar bottom expand end protrude into the 5th hole it is intracavitary and with the supply arm pushing tow Connection.

Preferably technical solution, the fuselage body right end end face are equipped with alarm lamp, the fuselage body right end end face It is preceding in the fuselage body right end inner wall to be equipped with information system, the information equipped with the liquid crystal display positioned at the alarm lamp rear end System is electrically connected with first accident investigation bar, the second accident investigation bar, third accident investigation bar and the 4th accident investigation bar, The liquid crystal display is electrically connected with the information system.

Preferably technical solution, the hand lift device include the hand lift for being fixedly mounted on the fuselage body top end surface Frame, front and back perforation is equipped with hand and lifts hole in the carrying trestle.

The beneficial effects of the present invention are: since equipment of the invention is when no investment detects in investigation work, the lock Determine frame utmostly counter-clockwise swing, make the conductive winding right end and the lock bracket, the operating stick is in a horizontal position And carry out bar described in pushing tow, supply arm described in the implementation bar pushing tow connect third spring element with power connecting arm, consequently facilitating area The operating status of separating device and the maintenance of early period.

When in equipment investment detection investigation work of the invention, by device integral installation in the required network system used In, current protection silk one end is connect with main power source and the lock hook is electrically connected with the input terminal of required electricity consumption, this When, electric controller starts the conductive winding automatically rotates clockwise the lock bracket, when the lock bracket is completely into described When first hole is intracavitary, the body of rod described in manually handle rotates counterclockwise the lock hook to the lock bracket and is clamped, meanwhile, The implementation bar moves up, and the supply arm is far from the power connecting arm, to keep normal work, to realize conjunction when normal operation Work is checked in the detection of reason, improves device practicability.

When network system failure needs present device to run, the electric controller detects the current protection silk Electric current irregular working or when being blown, starting the conductive winding rotates counterclockwise the lock bracket rapidly to first Beginning position, the lock hook get rid of and are driven the body of rod up time rapidly by the elastic force effect for rolling tightly piece after the lock bracket Needle is swung, and described move down from implementation bar described in body of rod pushing tow is electrically connected the supply arm with the power connecting arm, at this point, institute First motor starting is stated, the first motor drives the first deflection wheel, the second deflection wheel, third deflection wheel and the 4th deflection Periodic rotary is taken turns, the first accident investigation bar, the second accident investigation bar, third accident investigation bar and the 4th accident investigation are made Bar detects respectively and checks failure, meanwhile, the reason checked is conveyed to the information system, the information system is timely Failure cause is shown on the liquid crystal display to while being controlled the alarm lamp flashing, operator is prompted, to realize information The malfunction elimination of change improves the practicability and high efficiency of malfunction elimination

Device structure of the invention is simple, easy to operate, improves the quality of Intelligent detection circuit, to reach the information of high quality Detection investigation work, while typing information is cooperated using malfunction elimination system and information system, it timely feedbacks, improves information Change the effect and practicability of malfunction elimination.

Detailed description of the invention

The present invention is described in detail by following specific embodiments and drawings for ease of explanation,.

Fig. 1 is a modification of the present invention type power network monitoring device overall structure diagram；

Fig. 2 is the structural schematic diagram of A in Fig. 1；

Fig. 3 is the left view structural representation in Fig. 1.

Specific embodiment

As shown in Figure 1, Figure 2 and Figure 3, a modification of the present invention type power network monitoring device, including fuselage body 100 and set The first vestibule 105 in the fuselage body 100 is set, 100 bottom end face of fuselage body is fixedly installed with bottom plate 201, described Bottom plate 201 bottom end face, four vertex are fixedly installed with rubber mat 202, intercommunication in the 105 left end inner wall of the first vestibule Equipped with the second vestibule 103, intercommunication is equipped with third vestibule 107, the third vestibule 107 in the 105 right end inner wall of the first vestibule Right end runs through the 100 right end end face of fuselage body, and the positioned at 105 bottom of the first vestibule is equipped in the fuselage body 100 Four vestibules 121, first vestibule 105 is interior to be equipped with lock bracket 104, and 104 bottom of lock bracket is fixedly connected with front and back and expands The first steering shaft 128, end is expanded before and after first steering shaft 128 and is turned respectively with the 105 front and back inner wall of the first vestibule Dynamic to be cooperatively connected, first vestibule 105 is equipped with the lock hook 106 for being located at 104 right end of lock bracket and being mutually clamped therewith, institute State lock hook 106 and be equipped with the second steering shaft 133 that front and back is expanded, expand before and after second steering shaft 133 end with it is described First vestibule, 105 front and back inner wall is rotatably assorted connection, is arranged with after the lock hook 106 in second steering shaft 133 End rolls tightly piece 134, is fixedly connected with the operating stick 108 expanded to the right on the lock hook 106, in second vestibule 103 Equipped with the conductive winding 102 to be connected by power with the lock bracket 104, it is equipped with and the locking in second vestibule 103 104 left end end face of frame is electrically connected and the current protection silk 129 of left and right expansion, is equipped with and is located in the 100 left end end face of fuselage body The electric controller 101 of second vestibule, 103 left end, the electric controller 101 and the current protection silk 129 and conductive winding 102 Electrical connection, the 4th vestibule 121 is interior to be equipped with the third steering shaft 120 expanded up and down, expands at the top of the third steering shaft 120 End is rotatably assorted with 121 top inner wall of the 4th vestibule and connect, and 120 bottom of third steering shaft is expanded end power and connected It is connected to first motor 119, the first different deflection wheel 110 of corner, is arranged in sequence in the third steering shaft 120 from top to bottom Two deflection wheels 111, third deflection wheel 112 and the 4th deflection wheel 113 are slidably matched in the 121 left end inner wall of the 4th vestibule Be connected with respectively to the first deflection wheel 110, the second deflection wheel 111, third deflection wheel 112 and the 4th deflection wheel 113 Pushing tow connection and the first accident investigation bar 127, the second accident investigation bar 126, third accident investigation bar 125 and the of head to the left Four accidents check bar 124, first accident investigation bar 127, the second accident investigation bar 126, third accident investigation bar 125 and the Be designed with recovery device on four accidents investigation bar 124, be equipped in the fuselage body 100 positioned at 119 right end of first motor and The 5th vestibule 114 immediately below the third vestibule 107, the 5th vestibule 114 is interior to be equipped with device for opening, the fuselage Hand lift device is additionally provided on body 100.

Valuably, the recovery device includes that setting is checked in 121 left end of the 4th vestibule and by first accident Bar 127, the second accident investigation bar 126, third accident investigation bar 125 and the 4th accident check perforative 6th vestibule of bar 124 123, pushing tow is equipped with the first spring element 122,122 right end of the first spring element and first thing in the 6th vestibule 123 Therefore investigation bar 127, the second accident investigation bar 126, third accident investigation bar 125 are fixedly connected with the 4th accident investigation bar 124, just Restore in detection device, reason can be checked one by one.

Valuably, the device for opening includes described in the supply arm 116 being arranged in the 5th vestibule 114 and setting In power connecting arm 118 in 5th vestibule, 114 bottom interior wall, the 116 left end end of supply arm and 114 left end of the 5th vestibule Wall is rotatably assorted connection, and pushing tow is connected with the second bullet between 116 top of supply arm and 114 top inner wall of the 5th vestibule Power part 117,116 bottom end face of supply arm are equipped with the third to be electrically connected with the power connecting arm 118 and pushing tow is connect Spring element 115 is slidably connected with expansion up and down in inner wall between the 5th vestibule 114 and the third vestibule 107 Implementation bar 109, end is expanded at the top of the implementation bar 109 and is protruded into the third vestibule 107,109 bottom of implementation bar It expands end to protrude into the 5th vestibule 114 and connect with 116 pushing tow of supply arm, realizes and break down in network system When, detection investigation reason is automatically begun at the first time.

Valuably, the 100 right end end face of fuselage body is equipped with alarm lamp 130, sets on the 100 right end end face of fuselage body Have a liquid crystal display 131 positioned at 130 rear end of alarm lamp, in the 100 right end inner wall of fuselage body before be equipped with information system 132, The information system 132 and first accident investigation bar 127, the second accident investigation bar 126, third accident investigation bar 125 and 4th accident is checked bar 124 and is electrically connected, and the liquid crystal display 131 is electrically connected with the information system 132, is convenient for automatic input failure Information is simultaneously shown in time, is conducive to artificial investigation.

Valuably, the hand lift device includes the carrying trestle 160 for being fixedly mounted on 100 top end surface of fuselage body, institute It states front and back perforation in carrying trestle 160 and is equipped with hand lift hole 150, so that convenient move the present apparatus.

When equipment of the invention is when no investment detects in investigation work, the lock bracket 104 is utmostly counterclockwise Swing, make 102 right end of conductive winding and the lock bracket 104, the operating stick 108 be in a horizontal position and pushing tow described in Carry out bar 109, supply arm 116 described in 109 pushing tow of implementation bar connect third spring element 115 with power connecting arm 118.

When in equipment investment detection investigation work of the invention, by device integral installation in the required network system used In, described 129 one end of current protection silk is connect with main power source and the lock hook 106 and the input terminal of required electricity consumption are electrically connected It connects, rotates clockwise the lock bracket 104 at this point, electric controller 101 starts the conductive winding 102 automatically, when the locking When frame 104 is completely into first vestibule 105, the body of rod 108 described in manually handle turns the lock hook 106 counterclockwise It moves to the lock bracket 104 and is clamped, meanwhile, the implementation bar 109 moves up, and the supply arm 116 is far from the power connecting arm 118, to keep normal work.

When network system failure needs present device to run, the electric controller 101 detects that the electric current is protected 129 electric current irregular working of thread protector or when being blown, starting the conductive winding 102 makes the lock bracket 104 rapidly It rotates counterclockwise to initial position, the lock hook 106 is got rid of after the lock bracket 104 by the elastic force for rolling tightly piece 134 Effect drives rapidly 108 clockwise oscillation of the body of rod, and described move down from implementation bar 109 described in 108 pushing tow of the body of rod makes institute It states supply arm 116 to be electrically connected with the power connecting arm 118, at this point, the first motor 119 starts, the first motor 119 is driven The first deflection wheel 110, the second deflection wheel 111, third deflection wheel 112 and 113 periodic rotary of the 4th deflection wheel make described First accident is checked bar 127, the second accident investigation bar 126, third accident investigation bar 125 and the 4th accident investigation bar 124 and is distinguished Failure is detected and checks, meanwhile, the reason checked is conveyed to the information system 132, the information system 132 is timely Failure cause is shown on the liquid crystal display while controlling the alarm lamp 130 and is flashed, operator is prompted.

The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any The change or replacement expected without creative work, should be covered by the protection scope of the present invention.Therefore, of the invention Protection scope should be determined by the scope of protection defined in the claims.

Claims

1. a kind of modified power grid monitoring device, including fuselage body and setting are in intracorporal first vestibule of the fuselage, spy Sign is: the fuselage body bottom end face is fixedly installed with bottom plate, and the vertex of the bottom base plate end face four is fixedly installed with Rubber mat, intercommunication is equipped with the second vestibule in the inner wall of first vestibule left end, and intercommunication is set in the first vestibule right end inner wall There is a third vestibule, the third vestibule right end runs through the fuselage body right end end face, is equipped in the fuselage body and is located at described the 4th vestibule of one chamber bottom, first hole is intracavitary to be equipped with lock bracket, and the lock bracket bottom is fixedly connected with front and back and opens up First steering shaft of exhibition expands end before and after first steering shaft and is rotatably assorted respectively with inner wall before and after first vestibule company It connects, first vestibule is equipped with the lock hook for being located at the lock bracket right end and being mutually clamped therewith, before the lock hook is equipped with The second steering shaft expanded afterwards expands inner wall before and after end and first vestibule before and after second steering shaft and is rotatably assorted company It connects, the piece that rolls tightly positioned at the lock hook rear end is arranged in second steering shaft, is fixedly connected on the lock hook oriented The operating stick of right expansion, the intracavitary conductive winding being equipped with to be connected by power with the lock bracket in second hole, described second Hole is intracavitary equipped with the current protection silk being electrically connected with lock bracket left end end face and left and right is expanded, fuselage body left end end face The interior electric controller being equipped with positioned at second vestibule left end, the electric controller are electrically connected with the current protection silk and conductive winding It connects, the 4th hole is intracavitary equipped with the third steering shaft expanded up and down, and end and described the are expanded at the top of the third steering shaft Four vestibule top inner walls are rotatably assorted connection, and third steering shaft bottom expands end and has been connected by power first motor, described The first different deflection wheel of corner, the second deflection wheel, third deflection wheel and the 4th is arranged in sequence in third steering shaft from top to bottom Deflection wheel, be slidably connected in the inner wall of the 4th vestibule left end respectively to the first deflection wheel, second partially Tiltedly wheel, third deflection wheel and the connection of the 4th deflection wheel pushing tow and the first accident of head to the left check bar, the second accident checks bar, Third accident checks bar and the 4th accident checks bar, the first accident investigation bar, the second accident investigation bar, third accident investigation It is designed with recovery device on bar and the 4th accident investigation bar, is equipped with positioned at the first motor right end and is located in the fuselage body The 5th vestibule immediately below the third vestibule, the 5th hole is intracavitary to be equipped with device for opening, is additionally provided on the fuselage body Hand lifts device.

2. a kind of modified power grid monitoring device according to claim 1, it is characterised in that: the recovery device includes setting It sets in the 4th vestibule left end and by first accident investigation bar, the second accident investigation bar, third accident investigation bar and the Four accidents check perforative 6th vestibule of bar, and the intracavitary pushing tow in the 6th hole is equipped with the first spring element, and first spring element is right End is fixedly connected with first accident investigation bar, the second accident investigation bar, third accident investigation bar and the 4th accident investigation bar.

3. a kind of modified power grid monitoring device according to claim 1, it is characterised in that: the device for opening includes setting The power connecting arm on the intracavitary supply arm in the 5th hole and setting the 5th chamber bottom inner wall is set, the supply arm is left End end is rotatably assorted with the 5th vestibule left end inner wall to be connect, the supply arm top and the 5th vestibule top inner wall Between pushing tow be connected with the second spring element, the supply arm bottom end face is equipped with to be electrically connected with the power connecting arm and pushing tow The third spring element of connection is slidably connected with expansion up and down in inner wall between the 5th vestibule and the third vestibule Implementation bar, end is expanded at the top of the implementation bar and protrudes into that the third hole is intracavitary, and implementations bar bottom expansion end is protruded into 5th hole is intracavitary and connect with the supply arm pushing tow.

4. a kind of modified power grid monitoring device according to claim 1, it is characterised in that: the fuselage body right end end face It is equipped with alarm lamp, the fuselage body right end end face is equipped with the liquid crystal display positioned at the alarm lamp rear end, the machine right body Information system is equipped with before holding in inner wall, the information system and first accident investigation bar, the second accident check bar, third thing Therefore investigation bar and the investigation bar electrical connection of the 4th accident, the liquid crystal display are electrically connected with the information system.

5. a kind of modified power grid monitoring device according to claim 1, it is characterised in that: the hand lift device includes solid Dingan County is mounted in the carrying trestle of the fuselage body top end surface, and front and back perforation is equipped with hand and lifts hole in the carrying trestle.