CN110206693B

CN110206693B - Fixing support, using method thereof and wind generating set

Info

Publication number: CN110206693B
Application number: CN201910573153.8A
Authority: CN
Inventors: 韩世辉; 李强
Original assignee: Beijing Goldwind Science and Creation Windpower Equipment Co Ltd
Current assignee: Beijing Goldwind Science and Creation Windpower Equipment Co Ltd
Priority date: 2019-06-28
Filing date: 2019-06-28
Publication date: 2022-07-15
Anticipated expiration: 2039-06-28
Also published as: CN110206693A

Abstract

The invention provides a fixing support, a use method thereof and a wind generating set, wherein the fixing support is used for mounting an aviation lamp on a tower barrel, the fixing support comprises a bracket, the aviation lamp is mounted at a first end of the bracket, and a second end of the bracket is fixed on the tower wall of the tower barrel through a through hole formed in the tower wall. According to the fixing support, only the bracket penetrates through the tower wall, and the aviation lamp does not penetrate through the tower wall, so that the through hole formed in the tower wall for the bracket to penetrate through is relatively small, and the strength of the tower barrel can be improved compared with the prior art.

Description

Fixing support, using method thereof and wind generating set

Technical Field

The invention relates to the technical field of wind power generation, in particular to a fixing support, a method for mounting an aviation lamp by using the fixing support and dismounting the aviation lamp mounted by using the fixing support, and a wind generating set.

Background

With the development of the wind power industry, the global installed capacity is continuously increased, the capacity of a single unit is also rapidly increased, and the height of a wind generating set is also increased. Along with the increase of the unit design height, the influence of the wind driven generator set on aviation has gradually attracted attention of people. That is, the aircraft light needs to be installed at the top of the unit, and the aircraft light needs to be installed at the middle section of the tower barrel for the super-high unit.

If a common aviation lamp is installed in the middle section of a tower barrel of the wind generating set, an installation structure needs to be designed on the tower barrel. For example, it is common to provide mounting structures for mounting aircraft lights directly on the tower wall without forming through holes in the tower wall. The scheme does not affect the strength of the tower drum because no through hole is formed in the tower wall, but has the problem of difficult installation and maintenance.

The tower can also be used with an integrated special aviation lamp, so that a through hole needs to be formed in the wall of the tower, and the aviation lamp is extended out of the tower barrel through the through hole. Because the size of aviation lamp is great, consequently set up the size of the through-hole on the tower wall great, so can influence the intensity of a tower section of thick bamboo. Even if the local reinforcing design of the tower barrel is carried out, the load requirement cannot be met, and therefore, the potential safety hazard is large. In addition, the cost of the special aviation lamp is high, thereby leading to an increase in the cost of the wind turbine generator system.

Accordingly, there is a need to develop a mounting assembly for mounting an aircraft light that addresses the above-mentioned problems.

Disclosure of Invention

Therefore, the invention aims to provide a fixing support, a method for mounting an aviation lamp by using the fixing support and a wind generating set, and aims to solve the problems that the existing aviation lamp mounting mode or mounting structure is difficult to mount and maintain, or the strength of a tower barrel is influenced, and the cost is high.

According to an aspect of the invention, there is provided a fixing bracket for mounting an aircraft lamp on a tower, wherein the fixing bracket comprises a bracket, the aircraft lamp being mounted at a first end of the bracket, and a second end of the bracket being fixed to a tower wall of the tower through a through-hole formed in the tower wall. Because only the bracket passes through the tower wall and the aviation lamp does not pass through the tower wall, the through hole which is formed in the tower wall and is used for the bracket to pass through is relatively small, and compared with the prior art, the strength of the tower barrel can be improved.

Preferably, the fixed support can further comprise a limiting block, the limiting block is arranged on the bracket, a clamping groove matched with the limiting block can be formed in the tower wall, and the limiting block is embedded into the clamping groove. The limiting blocks are matched with the clamping grooves, so that the bracket can be prevented from shaking under the action of wind.

Preferably, the bracket may comprise a horizontally extending fixed bar on which the aircraft light is mounted and a mounting bar extending upwardly from a first end of the fixed bar, a second end of the fixed bar passing through the through-hole, wherein the fixed bar and the mounting bar are hollow bars to allow a cable for powering the aircraft light to pass through. Since the fixing rod and the mounting rod are hollow rods which allow the cables for supplying the aircraft lamp to pass through, no further mounting holes for the cables need to be designed.

Preferably, the fixing bracket may further include a pulling ring fixed to the second end of the fixing rod and formed with a cable through-hole through which the cable passes, wherein the pulling ring may include a ring portion fixed on the combining portion and a combining portion fixed to the second end of the fixing rod, the cable through-hole being formed in the combining portion. Through setting up the traction ring, can be convenient for maintainer tie down the direction rope that is used for installing and dismantling the aviation lamp.

Preferably, the fixing bracket may further comprise a lifting ring fixed to the fixing rod and/or the mounting rod and configured such that the central shaft of the fixing rod is in a substantially horizontal position when the aircraft lamp is lifted via the lifting ring. By enabling the central shaft of the fixing rod to be substantially in a horizontal position when the aviation lamp is lifted, maintenance personnel can conveniently enable the second end of the fixing rod to penetrate through the through hole in the tower wall to enter the tower barrel when the aviation lamp is installed.

Preferably, the fixing bracket may further comprise a fixing member for fixing the second end of the fixing rod to the tower wall, wherein the traction ring can be fixed to the second end of the fixing rod through the fixing member. Since the pulling ring can pass through the fixing piece, the pulling ring does not influence the installation and the disassembly of the fixing piece.

According to another aspect of the invention, a method for replacing an aviation lamp mounted on a tower drum by using the fixing bracket is provided, wherein the method comprises a method for disassembling the aviation lamp and a method for mounting the aviation lamp, and the method for disassembling the aviation lamp comprises the following steps: tying a guide rope to the second end of the bracket; separating the second end of the tray from the column wall; pushing the second end of the bracket out of the tower cylinder through the through hole; lowering the bracket to the ground, wherein the method of installing the aviation light comprises: mounting an aviation lamp on the first end of the bracket; tying a guide rope to the second end of the bracket; lifting the bracket to the position of the through hole of the tower wall of the tower barrel; pulling the guide rope to pass the second end of the bracket through the through hole; the bracket is fixed to the tower wall.

Preferably, the fixed bracket may further include a stopper disposed on the bracket, wherein the method of mounting the aviation lamp further includes: before the bracket is fixed, the limiting block is embedded into a clamping groove formed on the wall of the tower.

Preferably, the aviation light is turned upside down in a downward direction during the process of lifting the bracket to the position of the through hole of the tower wall of the tower barrel, wherein the method of installing the aviation light further comprises: before the limiting blocks are embedded into the clamping grooves formed in the tower wall, the aviation lamp is rotated by a preset angle in the upward direction.

Preferably, the fixing bracket may further include a towing ring, and the bracket may include a fixing rod extending horizontally and a mounting rod extending upward from a first end of the fixing rod for mounting the aero light, wherein the towing ring is fixed to the first end of the fixing rod, and the guide rope is tied to the towing ring.

Preferably, the fixing bracket may further comprise a lifting eye fixed to the fixing rod and/or the mounting rod and configured such that the central axis of the fixing rod is in a substantially horizontal position when the aircraft lamp is lifted via the lifting eye.

Preferably, the fixing bracket may further include a fixing member for fixing the second end of the fixing rod to the tower wall and configured to be penetrated by the traction ring.

According to another aspect of the invention, a wind generating set is provided, comprising a tower including a plurality of aviation lights mounted by a plurality of fixing brackets as described above.

Preferably, the tower barrel can be provided with three aviation lamps, the three aviation lamps are arranged at the same height of the tower barrel according to equal angular intervals, and assuming that the radius of a circle of a part of the tower barrel, where the aviation lamps are arranged, is R, and the distance between the aviation lamps and the center of the circle is d, the fixing bracket is constructed so that d is greater than or equal to 1.2R.

Preferably, the wind generating set may further include a GPS receiving module, a coupling device, a power distribution system, and a controller, each of the aviation lamps includes a control panel and a light emitting unit, wherein the GPS receiving module is configured to receive GPS system time information, the controller generates a synchronous clock control signal based on the GPS system time information, the coupling device modulates the synchronous clock control signal into a carrier signal having a predetermined frequency to enter the power distribution system through carrier coupling, the power distribution system transmits the carrier signal to the control panel of each of the aviation lamps, and the control panel of each of the aviation lamps controls the light emitting unit of the corresponding aviation lamp to blink, so that the light emitting units of all the aviation lamps blink synchronously. The GPS receiving module, the coupling device, the power distribution system and the controller can realize synchronous flicker of a plurality of aviation lamps, so that the cost of the wind generating set can be reduced.

Preferably, the wind power generating set may further comprise a fan main controller configured to send a start-stop control signal to the controller to control the plurality of aircraft lights to start and stop operating, wherein, when one or more of the plurality of aircraft lights fails, the control board of the failed one or more aircraft lights sends a fault signal to the power distribution system, the power distribution system sends the fault signal to the controller via the coupling device, and the controller sends the fault signal to the fan main controller by means of the communication interface or the fault feedback contact.

According to the fixing support, only the bracket penetrates through the tower wall, and the aviation lamp does not penetrate through the tower wall, so that the through hole formed in the tower wall for the bracket to penetrate through is relatively small, and the strength of the tower barrel can be improved compared with the prior art. In addition, the fixing bracket can be used for mounting a common aviation lamp, so that compared with the prior art, the cost of the aviation lamp can be reduced, and the cost of the wind generating set can be reduced. In addition, the fixing rod of the fixing bracket adopts an internal left-handed and external right-handed thread structure, so that the field installation operation is more convenient. Furthermore, according to the fixing bracket, the fixing rod and the mounting rod of the present invention are hollow rods that allow the cable for powering the aircraft lamp to pass through, thus eliminating the need for additional mounting holes for the cable. In addition, according to the fixing support provided by the invention, the sealing between the limiting block and the tower barrel can be realized.

In addition, according to the wind generating set, the GPS receiving module, the coupling device, the power distribution system and the controller can achieve synchronous flicker of a plurality of aviation lamps, and therefore the cost of the wind generating set can be reduced. In addition, according to the wind generating set, the fan main controller can control all the aviation lamps to start or stop working, so that energy can be saved relatively.

Drawings

The above and other objects and features of the present invention will become more apparent from the following description of the embodiments taken in conjunction with the accompanying drawings, in which:

fig. 1 and 2 are schematic views respectively showing that an aviation lamp is mounted on a tower tube by a fixing bracket according to an embodiment of the invention.

FIG. 3 is a schematic diagram illustrating an aircraft lamp according to an embodiment of the invention mounted on a fixed bracket.

Fig. 4 is a schematic view showing a partial structure of a fixing bracket according to an embodiment of the present invention.

Fig. 5 is a schematic view illustrating a traction ring of a fixing bracket according to an embodiment of the present invention.

FIG. 6 is a partial schematic view illustrating a tower wall of a tower.

Fig. 7 is a schematic view illustrating a fixing bracket according to another embodiment of the present invention.

FIG. 8 is a schematic diagram illustrating the mounting of an aircraft light on a tower using a fixed support according to an embodiment of the invention.

FIG. 9 is a simplified diagram illustrating a top view of a tower with three aviation lights mounted thereon.

FIG. 10 is a control schematic diagram illustrating controlling the synchronized flashing of a plurality of aviation lights mounted on a tower.

Fig. 11 is a logic block diagram showing a controller.

The reference numbers illustrate:

10, 10': a bracket; 11, 11': a fixing rod; 12, 12': mounting a rod; 20: a fixing member; 30, 30': a limiting block; 40, 40': a hoisting ring; 50: a traction ring; 51: a ring portion; 52: a bonding section; 52 a: a cable through hole; 60: a guide rope; 70: a lifting device; 71: a hook; 72: a guy rope; 80: a tower drum; 81: a tower wall; 81 a: an annular protrusion; 81 b: a through hole; 82: a platform; 90: an aviation lamp.

Detailed Description

Embodiments in accordance with the present invention will now be described in detail with reference to the drawings, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to like elements throughout.

Fig. 1 and 2 are schematic views respectively showing that an aviation lamp is mounted on a tower tube by a fixing bracket according to an embodiment of the invention. In this embodiment, the aviation light 90 may be a conventional aviation light, which is relatively inexpensive compared to a dedicated aviation light of a unitary construction.

As shown in fig. 1 and 2, a fixing bracket according to an embodiment of the present invention includes a bracket 10, and an aero light 90 is installed at a first end of the bracket 10. The second end of the bracket 10 is fixed to the tower wall 81 of the tower 80 through a through hole 81b (see fig. 6) formed in the tower wall 81. That is, only the second end of the cradle 10 passes through the through hole 81b to mount the aero light 90 on the tower wall 81, and the aero light 90 does not pass through the through hole 81 b.

Specifically, the bracket 10 includes a fixing rod 11 extending horizontally and a mounting rod 12 extending upward from a first end of the fixing rod 11. The second end of the fixing rod 11 is formed with external threads (e.g., right-hand threads) and passes through a through hole 81b (see fig. 6) in the tower wall 81 of the tower 80 from outside the tower 80 into the tower 80. The fixing rod 11 and the mounting rod 12 may be integrally formed, or may be separately formed and welded to each other. The end of the mounting rod 12 may be externally threaded and the aircraft light 90 may be correspondingly internally threaded for threaded fastening to the end of the mounting rod 12. Preferably, the fixing bar 11 and the mounting bar 12 may be hollow bars to allow the cables for powering the aircraft light 90 to pass through.

Optionally, the fixing bracket may further include a fixing member 20 for fixing the second end of the fixing rod 11 to the tower wall 81. The fixing member 20 may be a fastening nut to be fitted and fastened on the second end of the fixing rod 11 formed with the external thread and against the inner side of the tower wall 81, thereby fixing the second end of the fixing rod 11 on the tower wall 81. The fixing member 20 is not limited to the fastening nut, and other structures capable of fixing the fixing rod 11 may be used. Of course, the fixing manner of the fixing rod 11 is not limited to the screw-coupling with the fixing member 20, and other fixing manners may be adopted.

Preferably, in order to prevent the fixing lever 11 from shaking due to the wind, a stopper 30 may be provided, and the stopper 30 is engaged with the tower wall 81 to prevent the fixing lever 11 from shaking. For example, the stopper 30 may have a flat key shape and be formed with a through hole to be fitted and fastened on the fixing lever 11. Alternatively, the stopper 30 may be fitted over a portion of the fixing rod 11 on which the external thread is not formed, for example, the stopper 30 may be fastened to the fixing rod 11 by interference fit. Of course, the stopper 30 may be provided on the fixing rod 11 in other forms, for example, a through hole of the stopper 30 may be formed with a screw thread to be fastened to a portion of the external thread of the fixing rod 11 by a screw thread. In addition, the stopper 30 may be integrally formed with the fixing lever 11.

In order to cooperate with the limiting block 30, as shown in fig. 6, an annular protrusion 81a may be formed on the tower wall 81 of the tower 80 to form a slot, and a through hole 81b through which the fixing rod 11 passes is formed in the slot. The shape of the stopper 30 may match the shape of the catching groove to prevent the fixing lever 11 from shaking by being caught to each other. When the limiting block 30 is installed, sealant can be coated on the stop plane (i.e., the side surface) of the limiting block 30 and the limiting block 30 is embedded into the slot, so that the sealing and fixing between the limiting block 30 and the tower wall 81 can be easily realized by the sealant. Of course, the catching groove is not limited to being formed by the annular protrusion 81a, but may also be formed as a groove recessed inward from the tower wall 81. Further, although fig. 1 and 6 show that the catching groove is formed on the outer side of the tower wall 81, it is not limited thereto, and it may be formed on the inner side of the tower wall 81. In the case where the catching groove is formed at the inner side of the tower wall 81, the fixing member 20 may abut against the stopper 30 to fix the fixing lever 11.

Alternatively, in order to further prevent the fixing lever 11 from shaking due to the wind, a plurality of support rods may be arranged at predetermined angular intervals on the outer circumference of the fixing lever 11, first ends of the plurality of support rods being connected to the outer circumference of the fixing lever 11, and second ends of the plurality of support rods abutting on the outer surface of the tower wall 81. This further improves the stability of the bracket 10 by the plurality of support rods.

In addition, the fixing bracket may further include a hanging ring 40, and the hanging ring 40 is fixed to the bracket 10 and is vertically opposite to the navigation light 90, so that the bracket 10 with the navigation light 90 mounted thereon can be hung up to mount the navigation light 90 on the tower tube 80.

Specifically, as shown in fig. 1 to 4, the hanging ring 40 may be an arc-shaped ring, and both ends of the arc-shaped ring may be fixed to the fixing rod 11 and the mounting rod 12, respectively, for example, by welding or the like. Preferably, the hanging ring 40 may be configured such that the central shaft of the fixing rod 11 is in a horizontal position when the aviation light 90 is hung. In this case, when the aviation light 90 is installed, the central axis of the fixing rod 11 of the suspended bracket 10 is always in a horizontal position, and thus, the aerial light can be easily inserted into the tower tube 80 through the through hole 81b of the tower wall 81.

Alternatively, the fixing bracket may further include a traction ring 50 for facilitating the maintenance worker's operation to pass the fixing rod 11 through the through hole 81b, the traction ring 50 being fastened to the second end of the fixing rod 11 and configured to be capable of passing through the fixing member 20. The traction ring 50 may be used to tether the guide rope 60 (see fig. 8) so that a maintenance person may pass the second end of the fixing rod 11 through the through hole 81b by pulling the guide rope 60 within the tower 80.

Specifically, as shown in fig. 5, the traction ring 50 may include a ring portion 51 and a coupling portion 52, and the ring portion 51 is fixed to the coupling portion 52. The coupling portion 52 may be formed with external threads (e.g., left-hand threads), the second end of the fixing rod 11 may be correspondingly formed with internal threads (e.g., left-hand threads), and the coupling portion 52 may be threadedly fastened to the second end of the fixing rod 11. Since the pulling loop 50 can pass through the fixture 20, the pulling loop 50 does not affect the installation and removal of the fixture 20, and the pulling loop 50 can be fastened to the second end of the fixing rod 11 before the fixture 20 is installed. In addition, the joint portion 52 may be formed with a through-hole 52a to facilitate the passing of cables for supplying power to the airline lamp 90.

The specific structure of the fixing bracket according to the embodiment of the present invention is described above with reference to fig. 1 to 5, but the specific structure thereof is not limited thereto, and the respective components thereof may have other structural forms. For example, referring to fig. 7, fig. 7 shows a partial structure of a fixing bracket according to another embodiment of the present invention.

The fixing bracket shown in fig. 7 is identical to the bracket 10, the stopper 30 and the hanging ring 40 of the fixing bracket shown in fig. 1 to 5 except that the bracket 10 ', the stopper 30 ' and the hanging ring 40 ' are different, and the description of the identical components will be omitted.

As shown in fig. 7, in the present embodiment, the bracket 10 'includes a fixing rod 11' extending horizontally and a mounting rod 12 'extending upward from a first end of the fixing rod 11'. Further, the bracket 10 'further includes a tray 13 mounted on an end of the mounting rod 12', and the tray 13 may be formed with a mounting hole 13 a. The tray 13 is provided for mounting an aviation light of a different type (i.e. formed with threads) to the aviation light 90 shown in figures 1 and 2.

In addition, the limiting block 30 ' may be a block shape having a relatively wide middle portion and relatively narrow ends, and accordingly, a shape matching the shape of the limiting block 30 ' may be formed on the tower wall 81 of the tower tube 80 to prevent the fixing rod 11 ' from shaking by engaging with each other. In addition, the hanging ring 40 'may have a U-shape and be fixed to the fixing rod 11'. It should be understood that the structure of the limiting blocks 30 and 30 'is not limited to the illustrated example, and other structures can be adopted as long as the limiting blocks can cooperate with the slots on the tower wall 81 to prevent the fixing rods 11 and 11' from shaking. Similarly, the structure of the slinger 40, 40' is not limited to the illustrated example, and may take other forms so long as the aviation light 90 can be hoisted.

In order to facilitate understanding of the use of the fixing bracket of the present invention, a method of mounting an aviation light on a tower using the fixing bracket and a method of dismounting an aviation light from a tower will be described by taking the fixing bracket in fig. 1 to 5 as an example.

Next, a method for mounting the aviation light on the tower using the fixing bracket will be described.

First, the aero light 90 may be mounted on the first end of the bracket 10.

Specifically, the aero light 90 may be mounted on the mounting rod 12 of the bracket 10. In addition, the stopper 30 may be sleeved and fastened on the fixing rod 11 of the bracket 10, the order of mounting the navigation lamp 90 and the stopper 30 is not limited, and in the case where the stopper 30 is integrally formed with the fixing rod 11, the step of mounting the stopper 30 may be omitted.

The guide line 60 may then be tied to the second end of the carriage 10.

Specifically, the guide string 60 may be directly tied to the second end of the fixing rod 11. In case of providing the traction ring 50, the traction ring 50 may be fastened to the second end of the fixing rod 11 first, and then the guide rope 60 is tied to the ring part 51 of the traction ring 50, or the guide rope 60 may be tied to the ring part 51 of the traction ring 50 first, and then the traction ring 50 is fastened to the second end of the fixing rod 11.

The bracket 10 may then be lifted into position in the through hole 81b of the tower wall 81 of the tower 80.

Specifically, the airline lamp 90 can be hung up by hooking the bracket 10 using the hook 71 of the lifting device 70 provided in the cabin. In the case where the hoist ring 40 is provided, the hook 71 of the lifting device 70 may directly hook the hoist ring 40. Preferably, before lifting the aviation lamp 90 to the position of the through hole 81b, in order to prevent the aviation lamp 90 from colliding with the tower 80, the cable rope 72 may be tied to the hook 71. The tether 72 may hang to the ground and may be pulled or tethered to an external structure by maintenance personnel to keep the airline lights 90 stable.

Then, a maintenance person on the operating platform 82 of the tower 80 may pull the guide rope 60 such that the second end of the bracket 10 passes through the through hole 81b and into the tower 80.

When the hook 71 hooks the hanging ring 40, the central axis of the fixing rod 11 can be always in a horizontal position under the action of gravity, so that the maintenance personnel can conveniently drag the guide rope 60 to enable the second end of the fixing rod 11 to penetrate through the through hole 81b and into the tower 80.

The bracket 10 may then be secured to the tower wall 81.

Specifically, the fixing member 20 is fitted over the second end of the fixing rod 11. Further, since the aero light 90 is inverted in the downward direction during being hoisted, the aero light 90 may be rotated 180 ° as shown in the right side of fig. 8. Of course, the order of rotating the aviation lights 90 and installing the fixture 20 is not limited. After the aviation lamp 90 rotates 180 degrees, the hook 71 can automatically unhook from the hanging ring 40 under the action of gravity.

Then, the limiting member 30 is engaged in the engaging slot of the tower 80, and the fixing member 20 is fastened to abut against the inner side of the tower wall 81, thereby fixing the second end of the fixing rod 11.

The guide cord 60 may then be unwound from the traction ring 50.

Next, a method of removing the aircraft light from the tower will be described.

When the aviation light 90 is disassembled, the guide rope 60 can be firstly tied at the second end of the bracket 10; then, the second end of the tray 10 is separated from the tower wall 81; then, the second end of the bracket 10 is pushed out of the tower 80 through the through hole 81 b; the carriage 10 is then lowered to the ground.

Specifically, the guide rope 60 may be tied to the ring portion 51 of the towing ring 50 first, then the fixing member 20 is removed, and then the bracket 10 (on which the towing ring 50, the limiting block 30 and the hanging ring 40 are disposed) is integrally pushed out to the outside of the tower 80. Under the action of gravity, the aviation light 90 can be slowly lowered to the ground along with the lowering of the guide rope 60.

Of course, the installation and removal of the aircraft light 90 is not limited to the above-described method of operation, and may be carried out using a climbing robot where conditions permit.

Specifically, when the aviation lamp 90 is installed, the bracket 10 with the aviation lamp 90 installed may be carried to the position of the through hole 81b of the tower 80 by using a climbing robot instead of the lifting device 70, and then the second end of the fixing rod 11 is inserted into the tower 80 by the cooperation of the manipulator of the climbing robot and the maintenance personnel, the fixing member 20 is installed, the aviation lamp 90 is rotated by 180 °, the limiting member 30 is engaged in the engaging groove of the tower 80, and the fixing member 20 is fastened, so that the installation of the aviation lamp 90 is achieved.

When disassembling the aircraft light 90, the maintenance personnel remove the fixture 20 within the tower 80 and push the carriage 10 out to the outside of the tower 80 in its entirety, and the climbing robot may carry the carriage 10 with the aircraft light 90 installed slowly to the ground. When the aviation lamp 90 is disassembled, the guide rope 60 can be omitted, and only the bracket 10 provided with the aviation lamp 90 is carried by the climbing robot.

Furthermore, according to aviation standards, at least two aviation lights 90 need to be viewed in either direction for a good warning effect. In the case where three or more aviation lights 90 are installed, all of the aviation lights 90 may be arranged at equal angular intervals. For example, in the case where three aviation lights 90 are installed, the angular interval between the two aviation lights 90 is 120 degrees. In the case of four aviation lights 90 installed, the angular spacing between two aviation lights 90 is 90 degrees.

With four or more aviation lights 90 installed and all aviation lights 90 arranged at equal angular intervals, at least two aviation lights 90 can be viewed in either direction. However, in the case of three aviation lights 90 installed, it is not necessarily possible to view two aviation lights 90 in either direction. As shown in fig. 9, three aviation lights 90 are shown. In the installed state shown in fig. 9, viewing two aviation lights 90 in either direction is not achievable.

For this reason, the distance between the aviation light 90 and the tower 80 needs to meet predetermined conditions to meet aviation standard requirements. In particular, the carrier 10 needs to be designed properly. As shown in FIG. 9, assume that the circle of the tower 80 on which the navigation light 90 is mounted has a radius R and the navigation light 90 is located a distance d from the center of the circle. In order to allow at least two aviation lights 90 to be viewed in either direction, d should be greater than the length of the hypotenuse of the right triangle formed by the line L3 in which R lies, the tangent line L2 to the circle, and the line L1 in which d lies.

The bracket 10 may be configured such that d satisfies

Alternatively, the fixing bracket 10 may be configured such that d satisfies ≧ 1.2R.

Furthermore, along the tower, a plurality of aviation lights are typically provided for one tower. Aviation lamps installed on the same tower tube need to flicker at the same time so as to achieve the best warning effect. At present, the aviation lamp on the market is embedded with a GPS receiving module, and a control panel and a light-emitting unit are further arranged in the aviation lamp. The GPS receiving module receives GPS system time information, the control board generates a synchronous clock control signal based on the GPS system time information and sends the synchronous clock control signal to the control board, and the control board controls the light-emitting unit to synchronously flash. However, the cost of the aviation light embedded with the GPS receiving module is relatively high, resulting in an increase in the cost of the wind turbine generator set.

Therefore, the invention can provide a method for controlling the synchronous flicker of a plurality of aviation lamps, which can be realized by using the aviation lamps without a GPS receiving module, thereby reducing the cost of the wind generating set.

As shown in fig. 10, a plurality of aviation lamps, for example, an aviation lamp 1, an aviation lamp 2, an aviation lamp 3 … …, each of which includes a control panel and a light emitting unit, may be mounted on the tower of the wind generating set through the fixing bracket. The wind generating set comprises a GPS receiving module and a controller (see figure 11) with a central processing unit, the GPS receiving module is used for receiving GPS system time information, the controller generates a synchronous clock control signal based on the GPS system time information and sends the synchronous clock control signal to the control panel, and the control panel controls the light-emitting unit to act.

Specifically, a GPS receiving module for receiving GPS system time information can be installed on the top of the cabin of the wind generating set. The controller may be a synchronous clock controller installed in the cabin and generating a synchronous clock control signal based on GPS system time information provided by the GPS receiving module. Here, the synchronous clock control signal has a specific frequency, and for example, may be a square wave signal that changes between a high level and a low level at a specific frequency. In the embodiment of the invention, the received GPS system time information is used as a standard clock to generate the synchronous clock control signal, so that each aviation lamp is lightened at the same occurrence time of the effective signal edge and is extinguished at the same occurrence time of the ineffective signal edge, and therefore, the synchronous flickering of all the aviation lamps is realized.

In addition, the wind generating set can further comprise a coupling device, and the coupling device modulates the synchronous clock control signal generated by the controller into a carrier signal with a specific frequency so as to be in carrier coupling with a power distribution system of the wind generating set. The power distribution system may transmit a carrier signal to each of the aircraft lights 90.

The control panel of the aviation lamp 90 comprises a power module, a demodulation module and a control module. The power module is used for providing power for the light-emitting units, the demodulation module is used for demodulating clock information in the power distribution system, and the control module is used for controlling the light-emitting units to flicker synchronously according to the clock information and an internal protocol. The power distribution system can send the carrier signal to the demodulation module, the demodulation module demodulates clock information in the power distribution system and sends the clock information to the control panel, and the control panel controls the power supply module to supply power to the light-emitting unit according to the clock information and the internal protocol, so that synchronous flicker of the light-emitting unit is controlled.

Optionally, if the aviation lamp is also installed at the top of the wind generating set, the controller may control the aviation lamp installed at the top of the wind generating set and the aviation lamp installed on the tower to flash synchronously according to GPS system time information received from the GPS receiving module installed on the tower and flashing synchronously. Because only need set up a GPS receiving module at the cabin top and can control all aviation lamps and flash in step, and the aviation lamp need not to set up GPS receiving module, can reduce the cost of aviation lamp from this. Moreover, the controller can also adjust the flicker frequency of the aviation lamp according to the actual requirement so as to deal with different use environments.

Further, to facilitate monitoring of the flashing of the aviation lights 90, the controller may also be configured with fault feedback functionality. As shown in fig. 10, when the aviation lamp 90 has a fault, the control board of the aviation lamp 90 sends a fault signal with a specific frequency to the power distribution system, the power distribution system sends the fault signal to the coupling device, the coupling device converts the fault signal into a clock signal with a specific frequency and sends the clock signal to the central processor of the controller, and the central processor of the controller sends fault information to a wind turbine main controller (PLC) of the wind turbine generator system through a communication interface (such as an RJ45 interface or an RS485 interface) or a fault feedback contact. Maintenance personnel can repair or replace the aviation lamp according to the fault information. Here, the RJ45 interface or the RS485 interface is only an example of a communication interface, and is a mature general interface with good compatibility. The mode of the fault feedback contact directly utilizes an input/output terminal of a fan main controller (PLC) to realize fault detection, and the mode of realization is simpler and has stronger anti-interference capability.

Alternatively, as shown in fig. 11, according to practical application, when the aviation lamp system needs to be controlled to operate or stop, the fan main controller (PLC) may send a start-stop control signal to the central processing unit of the controller, the central processing unit of the controller may send the start-stop control signal to the coupling device, the coupling device modulates the start-stop control signal into a carrier signal with a specific frequency, the carrier signal is coupled into the power distribution system of the wind turbine generator system, the power distribution system transmits the carrier signal to the control panel of each aviation lamp, and the control panel of each aviation lamp may control the light-emitting unit of the corresponding aviation lamp to no longer emit light or to start emitting light. Therefore, the fan main controller (PLC) can control all the aviation lamps to start working or stop working, and energy can be saved relatively. Of course, wired or wireless remote control can also be realized through the existing remote control system of the wind power plant.

In addition, under the condition that a plurality of wind generating sets are arranged in a wind field, each wind generating set is provided with a GPS receiving module, and the GPS system time obtained by the GPS receiving module is consistent, so that all aviation lamps of each wind generating set can synchronously flash based on the GPS receiving module of each wind generating set. Alternatively, if other devices requiring synchronization are present in the wind turbine generator system, the power distribution system may be used to deliver a synchronization clock signal to the other devices requiring synchronization.

According to the fixing support provided by the embodiment of the invention, only the bracket penetrates through the tower wall, and the aviation lamp does not penetrate through the tower wall, so that the through hole formed in the tower wall for the bracket to penetrate through is relatively small, and the strength of the tower barrel can be improved compared with the prior art.

In addition, according to the fixing bracket provided by the embodiment of the invention, the fixing bracket can be used for mounting a common aviation lamp, so that compared with the prior art, the expense of the aviation lamp can be reduced, and the cost of the wind generating set is reduced.

In addition, according to the fixing bracket provided by the embodiment of the invention, the fixing rod adopts an internal left-handed and external right-handed thread structure, so that the field installation operation is more convenient. Furthermore, according to the fixing bracket, the fixing rod and the mounting rod of the embodiment of the invention, the hollow rod allowing the cable for supplying power to the aviation lamp to pass through is adopted, so that other mounting holes for the cable are not required to be designed. In addition, according to the fixing support provided by the embodiment of the invention, the sealing between the limiting block and the tower barrel can be realized.

According to a further embodiment of the invention, a wind power generation assembly may be provided, the wind power generation assembly comprising a tower including a plurality of aircraft lights mounted by a plurality of mounting assemblies as described above. In the wind generating set, a plurality of aviation lamps can synchronously flash through the GPS receiving module and the controller, so that the cost of the wind generating set can be reduced. In addition, in the wind generating set, a fan main controller (PLC) can control the aviation lamp to start working or stop working, and energy can be saved relatively. In addition, in this wind generating set, can adjust the scintillation frequency of aviation lamp according to actual demand to deal with different service environment.

Although the embodiments of the present invention have been described in detail above, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the invention. It will be understood that modifications and variations may occur to those skilled in the art, which modifications and variations may be within the spirit and scope of the embodiments of the invention as defined by the appended claims.

Claims

1. A fixing bracket for mounting an aircraft lamp (90) on a tower (80), characterized in that it comprises a bracket (10, 10 '), said aircraft lamp (90) being mounted at a first end of said bracket (10, 10 '), a second end of said bracket (10, 10 ') being fixed to a tower wall (81) of said tower (80) through a through hole (81 b) formed in said tower wall (81);

the bracket (10, 10 ') includes a horizontally extending fixing rod (11, 11') and a mounting rod (12, 12 ') extending upward from a first end of the fixing rod (11, 11'), the aviation lamp (90) being mounted on the mounting rod (12, 12 '), a second end of the fixing rod (11, 11') passing through the through hole (81 b);

the fixing bracket further includes a pulling ring (50), the pulling ring (50) being fixed to the second end of the fixing rod (11, 11') and formed with a cable through-hole (52 a) through which a cable passes.

2. The fixing bracket according to claim 1, characterized in that it further comprises a stop block (30), said stop block (30) being provided on said bracket (10, 10'),

the tower wall (81) is provided with a clamping groove matched with the limiting block (30), and the limiting block (30) is embedded into the clamping groove.

3. Fixing bracket according to claim 2, characterized in that the fixing rods (11, 11 ') and the mounting rods (12, 12') are hollow rods to allow the passage of cables for supplying the aircraft light (90).

4. The fixing bracket according to claim 3, wherein the pulling ring (50) includes a ring portion (51) and a combining portion (52), the ring portion (51) being fixed on the combining portion (52), the combining portion (52) being fixed to the second end of the fixing rod (11, 11'), the cable through hole (52 a) being formed in the combining portion (52).

5. The fixing bracket according to claim 4, characterized in that the fixing bracket further comprises a lifting eye (40, 40 '), the lifting eye (40, 40') being fixed to the fixing rod (11, 11 ') and/or the mounting rod (12, 12') and being configured such that the central axis of the fixing rod (11, 11 ') is in a substantially horizontal position when the aviation lamp (90) is lifted via the lifting eye (40, 40').

6. A fixing support according to claim 4 or 5, characterized in that it further comprises a fixing piece (20), said fixing piece (20) being used to fix the second end of the fixing rod (11, 11') to the tower wall (81),

wherein the pulling loop (50) is capable of being fixed to the second end of the fixing rod (11, 11') by passing through the fixing member (20).

7. A method of replacing an aircraft light (90) mounted on a tower (80) using a fixing bracket according to claim 1, characterized in that it comprises a method of disassembling the aircraft light (90) and a method of installing the aircraft light (90),

wherein the method of disassembling the aviation lamp (90) comprises: tying a guide rope (60) to the traction ring (50) at the second end of the carriage (10, 10'); separating the second end of the tray (10, 10') from the tower wall (81); pushing the second end of the bracket (10, 10') out of the tower (80) through the through hole (81 b); lowering the carriage (10, 10') to the ground,

wherein the method of installing the aviation light (90) comprises: mounting the aviation light (90) on a first end of the bracket (10, 10'); tying a guide rope (60) to the traction ring (50) at the second end of the carriage (10, 10'); lifting the bracket (10, 10') to the position of the through hole (81 b) of the tower wall (81) of the tower (80); drawing the guide rope (60) to pass the second end of the bracket (10, 10') through the through hole (81 b); -fixing the bracket (10, 10') to the tower wall (81).

8. The method according to claim 7, characterized in that the fixing support further comprises a stop block (30), the stop block (30) being provided on the bracket (10, 10'),

wherein the method of installing the aviation light (90) further comprises: before the bracket (10, 10') is fixed, the stopper (30) is inserted into a slot formed in the tower wall (81).

9. Method according to claim 8, characterized in that during the lifting of the bracket (10, 10') into position in the through-opening (81 b) of the tower wall (81) of the tower (80), the aircraft light (90) is inverted in downward direction,

wherein the method of installing the aviation light (90) further comprises: before the limiting block (30) is embedded into a clamping groove formed in the tower wall (81), the aviation lamp (90) is rotated by a preset angle in the upward direction.

10. The method of claim 9, wherein the fixing bracket further comprises a lifting eye (40, 40 '), the lifting eye (40, 40') being fixed to the fixing rod (11, 11 ') and/or the mounting rod (12, 12') and being configured such that the central axis of the fixing rod (11, 11 ') is in a substantially horizontal position when the aviation light (90) is lifted via the lifting eye (40, 40').

11. The method according to claim 9, wherein the fixing bracket further comprises a fixing piece (20), the fixing piece (20) being used for fixing the second end of the fixing rod (11, 11') on the tower wall (81) and being configured to be penetrated by the pulling loop (50).

12. A wind power plant, characterized in that it comprises a tower (80), said tower (80) comprising a plurality of aeronautical lights (90) mounted by means of a plurality of fixing brackets according to any of claims 1 to 6.

13. Wind park according to claim 12, wherein three aviation lights (90) are mounted on the tower (80), the three aviation lights (90) being arranged at equal angular intervals at the same height of the tower (80),

assuming that the radius of a circle of the tower (80) where the aviation lamp (90) is installed is R, and the distance between the aviation lamp (90) and the center of the circle is d, the fixing bracket is configured to ensure that d is larger than or equal to 1.2R.

14. Wind park according to claim 12, wherein the wind park further comprises a GPS receiving module, a coupling device, a power distribution system and a controller, each aircraft light (90) comprising a control board and a lighting unit,

the GPS receiving module is used for receiving GPS system time information, the controller generates a synchronous clock control signal based on the GPS system time information, the coupling device modulates the synchronous clock control signal into a carrier signal with a preset frequency to enter the power distribution system in a carrier coupling mode, the power distribution system sends the carrier signal to a control panel of each aviation lamp (90), and the control panel of each aviation lamp (90) controls the light emitting unit of the corresponding aviation lamp (90) to flicker, so that the light emitting units of all aviation lamps (90) flicker synchronously.

15. The wind park of claim 14, further comprising a fan main controller configured to send a start-stop control signal to the controller to control the plurality of aviation lights (90) to start and stop operating,

wherein, when one or more of the plurality of aviation lamps (90) fails, the control board of the failed one or more aviation lamps (90) sends a fault signal to the power distribution system, the power distribution system sends the fault signal to the controller via the coupling device, and the controller sends the fault signal to the fan main controller by means of a communication interface or a fault feedback contact.