CN203589583U - Pay-off rack used for flight stringing - Google Patents
Pay-off rack used for flight stringing Download PDFInfo
- Publication number
- CN203589583U CN203589583U CN201320690604.4U CN201320690604U CN203589583U CN 203589583 U CN203589583 U CN 203589583U CN 201320690604 U CN201320690604 U CN 201320690604U CN 203589583 U CN203589583 U CN 203589583U
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- Prior art keywords
- pay
- plug
- rack
- socket
- connecting plate
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- Expired - Lifetime
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Abstract
The utility model discloses a pay-off rack used for flight stringing. An upper part of the pay-off rack is connected with an aircraft chassis through a connecting device. The pay-off rack is a frame which is provided with a chassis on the bottom end, and the frame is made of light high-strength tube stock. The pay-off rack on an end of a spool 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 plugged and cooperated in the socket of the chassis of the aircraft. The connecting plate is connected with the top end of the pay-off rack, and the connecting plate and the pay-off rack rotate oppositely. The chassis of the aircraft is provided with a driving mechanism which can separate the plug from the socket. The pay-off is light in weight, accurate in paying off, and can fly for a long distance, and the aircraft is automatically separated from the pay-off rack.
Description
Technical field
The utility model relates to the device of 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 wire erection very large weight to steel tower, the erection method now adopting is generally now Di Nima very thin 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 to import the power supply of supplying with from land be power that motor drives 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 of putting into steel tower hanging wire point of restricting by Di Nima.There is at present the aircraft of 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 multiple 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 wheel carrier entirety depart from aircraft 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, by the throwing device on the telecontrol transmitter emission instruction signal control aircraft on ground, reel and line wheel carrier entirety jettisoning are guaranteed to flight safety to alleviate Aircraft Load.But this wire-binding device complex structure, inevitably will gain in weight, therefore 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.
Utility model content
The utility model technical issues that need to address 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 separation with pay off rack.
For solving the problems of the technologies described above, the technical scheme that the utility model adopts 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, the connecting plate with plug that are fixed on underbody, and the plug of connecting plate is pegged graft and is engaged in the socket of underbody, and connecting plate connects and relative rotation with pay off rack top; On underbody, being also provided with can be by the plug driving mechanism separation with socket.
Further improvement of the utility model 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 utility model 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 utility model 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 utility model 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 utility model is obtained is:
Pay off rack of the present utility model can adopt multiaxis multi-rotor aerocraft as power source, and its flight path is accurate, accurately unwrapping wire.Jockey of the present utility model 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 meeting under emergency and can under remote state or automatically, jockey being opened, make aircraft separation with pay off rack, pay off rack is jettisoninged.Jockey of the present utility model 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 utility model 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 separation 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 separation with socket, can not be subject to the interference of aircraft base and socket.
The framework of pay off rack of the present utility model is made by light-high-strength tubing, the underframe of base of frame, play a supporting role, the utility model can be restricted 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 utility model 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 utility model looks schematic diagram;
Fig. 2 is agent structure side schematic view of the present utility model;
Fig. 3 is the syndeton schematic diagram of aircraft of the present utility model 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 utility model is described in further details.
As shown in Figure 1, 2, flight stringing of the present utility model 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 control to aircraft according to the signal of navigator.
Underbody 13 below by a jockey 4, connect pay off rack 6, pay off rack 6 can be rotated freely and in due course can be separation with underbody 13.
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 the inertia that stops bobbin, rotate, 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. flight stringing pay off rack, 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, the connecting plate with plug (41) that are fixed on underbody (13), 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 driving mechanism (5) separation with socket plug.
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 the main body outside of described plug II (45) protrusion at 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 any one, 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), at the outlet wire clipper (16) that is also provided with Ke Yi Shi Di Nima rope (15) disconnection below of pay off rack (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320690604.4U CN203589583U (en) | 2013-11-05 | 2013-11-05 | Pay-off rack used for flight stringing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320690604.4U CN203589583U (en) | 2013-11-05 | 2013-11-05 | Pay-off rack used for flight stringing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203589583U true CN203589583U (en) | 2014-05-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320690604.4U Expired - Lifetime CN203589583U (en) | 2013-11-05 | 2013-11-05 | Pay-off rack used for flight stringing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203589583U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103594963A (en) * | 2013-11-05 | 2014-02-19 | 国家电网公司 | Pay-off rack for flight stringing |
| CN104332894A (en) * | 2014-11-17 | 2015-02-04 | 国家电网公司 | Vehicle-mounted pay-off rack of unmanned aerial vehicle and unmanned aerial vehicle |
| CN105668350A (en) * | 2016-04-20 | 2016-06-15 | 北京深远世宁科技有限公司 | Automatic take-up and payoff device and method for mooring unmanned aerial vehicle |
-
2013
- 2013-11-05 CN CN201320690604.4U patent/CN203589583U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103594963A (en) * | 2013-11-05 | 2014-02-19 | 国家电网公司 | Pay-off rack for flight stringing |
| CN103594963B (en) * | 2013-11-05 | 2016-01-13 | 国家电网公司 | Flight stringing pay off rack |
| CN104332894A (en) * | 2014-11-17 | 2015-02-04 | 国家电网公司 | Vehicle-mounted pay-off rack of unmanned aerial vehicle and unmanned aerial vehicle |
| CN104332894B (en) * | 2014-11-17 | 2017-09-26 | 国家电网公司 | A kind of unmanned aerial vehicle onboard pay off rack and unmanned plane |
| CN105668350A (en) * | 2016-04-20 | 2016-06-15 | 北京深远世宁科技有限公司 | Automatic take-up and payoff device and method for mooring unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140507 Effective date of abandoning: 20160113 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |