CN103594963A - Pay-off rack for flight stringing - Google Patents

Pay-off rack for flight stringing Download PDF

Info

Publication number
CN103594963A
CN103594963A CN201310539920.6A CN201310539920A CN103594963A CN 103594963 A CN103594963 A CN 103594963A CN 201310539920 A CN201310539920 A CN 201310539920A CN 103594963 A CN103594963 A CN 103594963A
Authority
CN
China
Prior art keywords
pay
rack
plug
socket
connecting plate
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201310539920.6A
Other languages
Chinese (zh)
Other versions
CN103594963B (en
Inventor
董树森
李新
周雪涛
高笑茶
盖志军
郭珊
张哲�
万冀杰
张湘潭
尹泉军
王文义
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
State Grid Corp of China SGCC
State Grid Hebei Electric Power Co Ltd
Hebei Power Transmission and Transformation Co Ltd
Original Assignee
State Grid Corp of China SGCC
State Grid Hebei Electric Power Co Ltd
Hebei Power Transmission and Transformation Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by State Grid Corp of China SGCC, State Grid Hebei Electric Power Co Ltd, Hebei Power Transmission and Transformation Co Ltd filed Critical State Grid Corp of China SGCC
Priority to CN201310539920.6A priority Critical patent/CN103594963B/en
Publication of CN103594963A publication Critical patent/CN103594963A/en
Application granted granted Critical
Publication of CN103594963B publication Critical patent/CN103594963B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Landscapes

  • Storing, Repeated Paying-Out, And Re-Storing Of Elongated Articles (AREA)

Abstract

The invention discloses a pay-off rack for flight stringing. The upper portion of the pay-off rack is connected with a chassis of an aircraft through a connecting device. The pay-off rack is a framework which is provided with an underframe at the bottom end and is made of light high-strength tubes. The pay-off rack at one end of a wire shaft is provided with a damper. The connecting device comprises a socket fixed on the chassis of the aircraft and a connecting plate with a plug. The plug of the connecting plate is inserted in the socket of the chassis of the aircraft in a matching mode. The connecting plate is connected with the top end of the pay-off rack and can rotate relative to the top end of the pay-off rack. The chassis of the aircraft is further provided with a drive mechanism capable of separating the plug from the socket. The pay-off rack of the flight stringing is light in weight, accurate in paying off wires, capable of flying a long distance, and capable of automatically separating the aircraft from the pay-off rack.

Description

Flight stringing pay off rack
Technical field
The device that the present invention relates to the use aircraft traction unwrapping wire in a kind of transmission line stringing process, specifically refers to a kind of pay off rack.
Background technology
Erect power transmission lines in process, need to be by the very large wire erection of weight to steel tower, the erection method now adopting is generally now the very thin Di Nima of very light in weight to be restricted through each steel tower, and then the higher Di Nima rope of the thicker intensity of connection, through connecting wire with steel wire rope, preferably wire is moved on steel tower by hauling machine again.When erecting power transmission lines long distance transmission line, because distance reaches the even tens of kms of thousands of rice, so generally all use at present the aircraft tractions such as model plane while placing first Di Nima rope.If publication number is 10806091 Chinese patent literatures, a kind of electric power helicopter is just provided, be in body, be provided with by its with cable bands import the motor that the power supply supplied with from land is power and drive rotor wing rotation lift-off and advance and retreat to turn to as prime mover.But this device can not be applicable to long-distance flight.Therefore with model plane that can remote control, replacing helicopter traction Di Nima rope is the method for often using in electric stringing.But the control precision of general model plane can not reach the requirement that Di Nima rope is put into steel tower hanging wire point.The aircraft that has at present the many rotors of a kind of multiaxis, if number of patent application is that 20101052963.1 Chinese patent literatures disclose a kind of six axle multi-rotor aerocrafts, it comprises a chassis, on chassis, connect and be fixed with folding bar axle, bar axle is arranged on chassis symmetrically, the end of bar axle is arranged symmetrically with rotor, and the control device of aircraft is arranged on chassis.This aircraft is because it has a plurality of drivings force, so it is had a smooth flight.
In addition; the patent No. is that 201120009726.3 Chinese utility model patent document also discloses a kind of Onboard electric stringing device for unmanned air vehicle; comprise elastic damping device and elastic force overload protective device; it is just rotatable and can't be in rotation under self moment of inertia effect that damper makes line wheel only at certain pulling force, do the used time, prevents from that messenger from being put disorderly to cause uncontrollable winding.This spring slide plate overload protective device is opened and makes reel and the whole aircraft that departs from of wheel carrier under the sudden change pulling force effect between aircraft and messenger, thus the safety of protection aircraft.Between line wheel carrier and aircraft, be also provided with wireless remote control throwing device; when payingoff construction personnel find aircraft flight attitude extremely or occur certain undesired sign; or when having completed one section of unwrapping wire task and need to make a return voyage, the throwing device of controlling on aircraft by the telecontrol transmitter emission instruction signal on ground guarantees flight safety by reel and the whole jettisoning of line wheel carrier to alleviate Aircraft Load.But this wire-binding device complex structure, inevitably will gain in weight, so it also needs to use the such Large Scale Space Vehicle of helicopter just can complete.And the use cost of Large Scale Space Vehicle goes up 100,000 even 1,000,000 yuan easily, from economic benefit and operating efficiency, for construction party improper.
Summary of the invention
The technical issues that need to address of the present invention are to provide a kind of flight stringing pay off rack, and it is lightweight, can use the aircraft such as model plane to carry out long-distance flight, and can automatically make aircraft separated with pay off rack.
For solving the problems of the technologies described above, the technical solution adopted in the present invention is:
Flight stringing pay off rack, in pay off rack, be provided with bobbin, pay off rack top is connected by jockey with underbody, described pay off rack is the framework of being made by light-high-strength tubing, the bottom of framework is provided with the underframe of being made by light-high-strength tubing, on the pay off rack of one end of bobbin, is provided with damper; Described jockey comprises the socket that is fixed on underbody, with the connecting plate of plug, the plug of connecting plate is pegged graft and is engaged in the socket of underbody, connecting plate connects also relative rotation with pay off rack top; On underbody, being also provided with can be by the plug driving mechanism separated with socket.
Further improvement of the present invention is: on the socket on the plug of the connecting plate of described jockey and on underbody, be respectively arranged with corresponding pin-and-hole, a latch that pulled by driving mechanism is set in pin-and-hole.
The further improvement of technique scheme of the present invention is: described connecting plate is horseshoe-shaped structure, described plug is divided into the plug I with pin-and-hole in the middle of the front end that is arranged on horseshoe-shaped structure and is arranged on two plug II of the both sides, rear end of horseshoe-shaped structure, on underbody, be provided with the position socket I corresponding with plug I and plug II and socket II, plug I is connected by latch with socket I, and plug II is inserted in the hole of socket II.
The further improvement of technique scheme of the present invention is: described plug II is protruded the main body outside at connecting plate, above the end of plug II, is provided with slope.
Further improvement of the present invention is: the crown center position of described pay off rack is provided with the suspension ring of guiding Di Nima rope, at the outlet wire clipper that is also provided with the disconnection of Ke Yi Shi Di Nima rope below of pay off rack.
Owing to having adopted technique scheme, the technological progress that the present invention obtains is:
Pay off rack of the present invention can adopt multiaxis multi-rotor aerocraft as power source, and its flight path is accurate, accurately unwrapping wire.Jockey of the present invention is very simple, and multiaxis multi-rotor aerocraft and pay off rack can adopt the light-weight high-strength materials such as carbon fiber to make, and make the overall weight of device light, can carry out long-distance flight.And meet can be under remote state under emergency or automatically make jockey open, make aircraft separated with pay off rack, pay off rack is jettisoninged.Jockey of the present invention makes the base of aircraft can relatively rotate with pay off rack, can guarantee that the Di Nima rope on bobbin is derived smoothly, and the lead that bobbin is restricted facing to Di Nima all the time.
The plug of the connecting plate of jockey of the present invention adopts latch to be connected with the socket of underbody, and when needs are jettisoninged, driving mechanism (as steering wheel) can pull latch, and plug and socket are thrown off, and plug falls in socket, and this action is very fast.When connecting plate is the shape of a hoof, a plug I in the middle of being positioned at connects on underbody in socket I by latch, be positioned at the hole of two socket II of two plug II insertions of both sides, water chestnut rear end, when in plug I, latch is pulled out, plug I is separated with socket I, and plug II also can be deviate from smoothly from socket II.Plug II is protruded in the main body outside of connecting plate and above the end of plug II and is arranged to slope or circular arc, while making connecting plate separated with socket, can not be subject to the interference of aircraft base and socket.
The framework of pay off rack of the present invention is made by light-high-strength tubing, the underframe of base of frame, play a supporting role, the present invention can restrict Di Nima around in bobbin by handle, when unwrapping wire, damper can also prevent that bobbin is because of unlimited freely the rotating of inertia, cause many unwrapping wire, or reverse kinking occurs.Suspension ring outlet wire clipper of the present invention the Ke Yi Shi Di Nima smooth outlet of restricting is set, prevent card line, prevent knotting, and can not continue unwrapping wire under special status time, outlet wire clipper can first be cut off Di Nima rope, thereby with bobbin and pay off rack, make a return voyage safely, avoided directly jettisoninging pay off rack.
Accompanying drawing explanation
Fig. 1 is that overall structure master of the present invention looks schematic diagram;
Fig. 2 is agent structure side schematic view of the present invention;
Fig. 3 is the syndeton schematic diagram of aircraft of the present invention and pay off rack;
Fig. 4 is the syndeton schematic diagram of the plug I socket I of connecting plate;
Fig. 5 is the syndeton schematic diagram of the plug II socket II of connecting plate.
Wherein, 4, jockey, 5, driving mechanism, 6, pay off rack, 7, bobbin, 8, connecting rod, 9, suspension ring, 10, damper, 11, underframe, 12, latch, 13, underbody, 14, transverse slat, 15, Di Nima rope, 16, outlet wire clipper; 41, connecting plate, 42, socket I, 43, socket II, 44, plug I, 45, plug II, 46, bearing, 50, pull bar, 51, bearing pin, 441, pin-and-hole, 451, slope.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further details.
As shown in Figure 1, 2, flight stringing of the present invention is the framework of being made by light-high-strength tubing (as carbon element pipe) by pay off rack main body, and bobbin 7 is installed in framework, is wound with Di Nima rope 15 on bobbin 7.Aircraft can be multiaxis multi-rotor aerocraft.Underbody 13 is provided with the control device of controlling aircraft flight above, and control device can receive the signal controlling aircraft flight that remote control is sent, and also can realize the automatic flight of aircraft is controlled according to the signal of navigator.
Underbody 13 below by a jockey 4, connect pay off racks 6, pay off rack 6 can be rotated freely and in due course can be separated with underbody 13.
Jockey 4 comprises the socket that is fixed on underbody 13, with the connecting plate 41 of plug, the plug of connecting plate 41 is pegged graft and is engaged in the socket on underbody 13.Described socket has three, and the plug of connecting plate 41 also has corresponding three.Described connecting plate 41 is horseshoe-shaped structure, plug I 44 is arranged on the front end centre position of horseshoe-shaped structure, plug I is provided with pin-and-hole 441, and a socket on base is the socket I with pin-and-hole 441, and socket I is comprised of left and right two parts, it between two parts, is the plug I gap of placing connecting plate 41, plug I is placed between socket I, then with latch 12, plug I is connected with socket I, after latch is extracted, plug I comes off in socket I, makes plug I separated with socket I.Both sides, rear end at the connecting plate 41 of horseshoe-shaped structure are provided with two plug II 45, are provided with the position socket II 43 corresponding with plug II 45 positions on underbody 13, and the side of socket II corresponding plug II arranges porose.Two plug II are symmetrical arranged, and plug II is protruded the main body outside at connecting plate 41, and two plugs form a fork-shaped, are provided with slope 451 above the end of plug II 45.Plug II 45 is inserted in the hole of socket II 43.On underbody 13, be also provided with can by plug separated with socket can be controlled the driving mechanism 5 controlled of device.Driving mechanism 5 can be an automatically controlled steering wheel, and latch 12 is connected to the side of the pull bar 50 of steering wheel by a bearing pin 51.When needs make pay off rack separated with aircraft, start driving mechanism 5, pull latch 12, plug I and first separated, the disengagement of socket I, connecting plate rotates, comes off from socket II.The controlled device of driving mechanism 5 is controlled, and realizes the automatically separated of aircraft and pay off rack.
One bearing 46 is set below connecting plate 41, and connecting plate 41 is connected to pay off rack top by bearing 46, and connecting plate 41 by bearing 46, relative rotation can occur with pay off rack.The bottom of framework is provided with the underframe 11 of being made by light-high-strength tubing, underframe 11 can be two carbon element pipes, the two ends of the framework of pay off rack 6 are provided with transverse slat 14, bobbin 7 is arranged between interior two transverse slats 14 of framework of pay off rack 6, and on bobbin 7, being tied with Di Nima rope 15(can also be the rope of other kind certainly).On the transverse slat 14 of the pay off rack of one end of bobbin 7, be provided with the damper 10 being connected with the rotating shaft of pay off rack, for stopping that the inertia of bobbin rotates, the rotating shaft of the other end of bobbin 7 is stretched out outside pay off rack 6 transverse slats 14, the rotating shaft that bobbin 7 stretches out outside pay off rack 6 is connecting rod 8, is useful on and connects coiling handle.The crown center position of pay off rack 6 is provided with the suspension ring 9 of guiding Di Nima rope 15, after pay off rack 6, be also provided with outlet wire clipper 16, Di Nima rope on bobbin 7 enters outlet wire clipper 16 after suspension ring 9, after 16 guidings of outlet wire clipper, and normal unwrapping wire.Outlet wire clipper 16 can be provided with the device (devices that can certainly adopt other can make Di Nima rope 15 disconnect) of the disconnections of Di Nima can being restricted such as scissors, when there are abnormal conditions, control device can also be controlled the action of outlet wire clipper, and Di Nima rope is cut off.

Claims (5)

1. stringing pay off rack flies, in pay off rack (6), be provided with bobbin (7), pay off rack (6) top is connected by jockey (4) with underbody (13), it is characterized in that: described pay off rack (6) is the framework of being made by light-high-strength tubing, the bottom of framework is provided with the underframe (11) of being made by light-high-strength tubing, on the pay off rack (6) of one end of bobbin (7), is provided with damper (10); Described jockey (4) comprises the socket that is fixed on underbody (13), with the connecting plate (41) of plug, the plug of connecting plate (41) is pegged graft and is engaged in the socket of underbody (13), and connecting plate (41) connects and relative rotation with pay off rack top; On underbody (13), being also provided with can be by the plug driving mechanism (5) separated with socket.
2. flight stringing pay off rack according to claim 1, it is characterized in that on the plug of connecting plate (41) of described jockey (4) and be respectively arranged with corresponding pin-and-hole (441) on the socket on underbody (13), a latch (12) that pulled by driving mechanism (5) is set in pin-and-hole (441).
3. flight stringing pay off rack according to claim 2, it is characterized in that described connecting plate (41) is horseshoe-shaped structure, described plug is divided into the plug I (44) with pin-and-hole (441) in the middle of the front end that is arranged on horseshoe-shaped structure and is arranged on two plug II (45) of the both sides, rear end of horseshoe-shaped structure, on underbody (13), be provided with the position socket I (42) corresponding with plug I (44) and plug II (45) and socket II (43), plug I (44) is connected by latch (12) with socket I (42), plug II (45) is inserted in the hole of socket II (43).
4. flight stringing pay off rack according to claim 3, is characterized in that described plug II (45) protrusion, in the main body outside of connecting plate (41), is provided with slope (451) above the end of plug II (45).
5. according to the flight stringing pay off rack described in claim 1～4, it is characterized in that the crown center position of described pay off rack (6) is provided with the suspension ring (9) of guiding Di Nima rope (15), is also provided with the outlet wire clipper (16) that Ke Yi Shi Di Nima rope (15) disconnects after pay off rack (6).
CN201310539920.6A 2013-11-05 2013-11-05 Flight stringing pay off rack Active CN103594963B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201310539920.6A CN103594963B (en) 2013-11-05 2013-11-05 Flight stringing pay off rack

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201310539920.6A CN103594963B (en) 2013-11-05 2013-11-05 Flight stringing pay off rack

Publications (2)

Publication Number Publication Date
CN103594963A true CN103594963A (en) 2014-02-19
CN103594963B CN103594963B (en) 2016-01-13

Family

ID=50084998

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201310539920.6A Active CN103594963B (en) 2013-11-05 2013-11-05 Flight stringing pay off rack

Country Status (1)

Country Link
CN (1) CN103594963B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108190612A (en) * 2017-12-29 2018-06-22 温州新马亚电器有限公司 A kind of actinobacillus device of electric wire

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2409617A1 (en) * 1977-11-18 1979-06-15 Skogsflyg Cassel Aero Installation of overhead power cable using aircraft - from which cable spool is rotatably suspended, to pay out cable as aircraft files along line of poles
SU1403175A1 (en) * 1986-11-10 1988-06-15 Краснодарский филиал Государственного научно-исследовательского института гражданской авиации Device for rolling out cables off spool by a helicopter
CN2677297Y (en) * 2004-03-01 2005-02-09 云南省送变电工程公司 Remote controlled aircraft rope hithcing releasing device
CN201927943U (en) * 2011-01-13 2011-08-10 杨苡 Onboard electric stringing device for unmanned air vehicle
CN202564902U (en) * 2012-04-14 2012-11-28 李斐 Wire stringing device
CN203589583U (en) * 2013-11-05 2014-05-07 国家电网公司 Pay-off rack used for flight stringing

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2409617A1 (en) * 1977-11-18 1979-06-15 Skogsflyg Cassel Aero Installation of overhead power cable using aircraft - from which cable spool is rotatably suspended, to pay out cable as aircraft files along line of poles
SU1403175A1 (en) * 1986-11-10 1988-06-15 Краснодарский филиал Государственного научно-исследовательского института гражданской авиации Device for rolling out cables off spool by a helicopter
CN2677297Y (en) * 2004-03-01 2005-02-09 云南省送变电工程公司 Remote controlled aircraft rope hithcing releasing device
CN201927943U (en) * 2011-01-13 2011-08-10 杨苡 Onboard electric stringing device for unmanned air vehicle
CN202564902U (en) * 2012-04-14 2012-11-28 李斐 Wire stringing device
CN203589583U (en) * 2013-11-05 2014-05-07 国家电网公司 Pay-off rack used for flight stringing

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108190612A (en) * 2017-12-29 2018-06-22 温州新马亚电器有限公司 A kind of actinobacillus device of electric wire
CN108190612B (en) * 2017-12-29 2019-11-19 曹诗晴 A kind of actinobacillus device of wire and cable

Also Published As

Publication number Publication date
CN103594963B (en) 2016-01-13

Similar Documents

Publication Publication Date Title
CN203589584U (en) Power transmission line flying stringing device
CN205076537U (en) Trailing cable laying pay -off of unmanned aerial vehicle
US20210047033A1 (en) System and method for airborne wind energy production
US10329016B1 (en) Remote aerial manipulation platform
US11814167B2 (en) Vertically-tethered multicopters
CN103594962B (en) Transmission line flight wire-binding device
CN203589583U (en) Pay-off rack used for flight stringing
CN105836153A (en) Mooring system of unmanned aerial vehicle
KR20170087340A (en) System and method for connection power line using dron
CN212797290U (en) Centre gripping formula unwrapping wire unmanned aerial vehicle
CN104196684A (en) Aircraft and airship type high-altitude wind power generation device
CN109494628B (en) Electric power paying-off multi-rotor unmanned aerial vehicle and electric power paying-off method
CN106081062B (en) solar energy unmanned plane
CN204967138U (en) Portable aerial [insulated] cable lays auxiliary device
CN103594963B (en) Flight stringing pay off rack
CN112038977B (en) Unmanned aerial vehicle electric power paying-off method
CN102861400B (en) Fire protection system
KR102077470B1 (en) Hybrid Dron and It's control methods
CN109795710B (en) Full-automatic pay-off and take-up system synchronously controlled by tethered unmanned aerial vehicle
CN203582137U (en) Flying pay-off rack connecting device capable of self disengagement
CN207312846U (en) A kind of twisted and released of the cable line apparatus
CN101964502A (en) Method for spreading initial guide rope with remote control fixed wing aircraft
CN212220561U (en) Heavy rotor unmanned aerial vehicle for forestry fire suppression operation
KR102009772B1 (en) Hybrid Dron and It's control methods
CN213185278U (en) Hanging wire tool suitable for unmanned aerial vehicle electric power unwrapping wire

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant