AVIATION BEACON DEVICE FOR A WIND TURBINE

Abstract

An aircraft beacon device of a wind power installation, to be arranged on a gondola of the wind power installation, comprising at least three omnidirectional emission sections arranged concentrically in a ring around a common mid-axis, each omnidirectional emission section comprising a lens section arranged concentrically in a ring around the mid-axis, with a beam plane defined perpendicularly to the mid-axis, and at least one lighting ring having lighting means arranged concentrically in a ring around the mid-axis in order to emit light through the lens section, wherein each lighting ring is configured in order to emit light with a central emission direction which makes an emission angle with the beam plane, and wherein the emission direction depends on an axial position of the lighting ring with respect to the lens section, wherein at least one omnidirectional emission section comprises at least two lighting rings offset axially with respect to one another for emission with different emission angles.

Claims

1. An aircraft beacon device of a wind power installation, configured to be arranged on a gondola of the wind power installation, the aircraft beacon device comprising: at least three omnidirectional emission sections arranged concentrically in a ring around a common mid-axis, each omnidirectional emission section comprising: a lens section arranged concentrically in a ring around the mid-axis, with a beam plane defined perpendicularly to the mid-axis, and at least one lighting ring having lights arranged concentrically in a ring around the mid-axis in order to emit light through the lens section, wherein each lighting ring is configured to emit light with a central emission direction that makes an emission angle with the beam plane, and wherein the emission direction depends on an axial position of the lighting ring with respect to the lens section, wherein at least one omnidirectional emission section comprises at least two lighting rings offset axially with respect to one another for emission with different emission angles.

2. The aircraft beacon device according to claim 1, wherein the omnidirectional emission sections are arranged in the axial direction with respect to one another.

3. The aircraft beacon device according to one of the claim 1, wherein the lights are LEDs.

4. The aircraft beacon device according to claim 1, wherein at least one of the lights are configured to output light with a first color, and at least one further light is configured in order to output light with a second color.

5. The aircraft beacon device according to claim 1, wherein at least some of the lights are red LEDs and have a minimum intensity with a value from the following list: 10 cd, 20 cd, 25 cd, 30 cd, 32 cd, 50 cd, 70 cd, 100 cd or 200 cd.

6. The aircraft beacon device according to claim 1, wherein at least some of the lights are white LEDs and have a minimum intensity with a value from the following list: 3. 4 cd, 34 cd or 175 cd.

7. The aircraft beacon device according to claim 1, comprising a control unit configured to vary emission characteristic of the aircraft beacon device by selective driving of individual lights or lighting rings.

8. The aircraft beacon device according to claim 1, comprising a control unit configured to adjust or vary an intensity of the lights or lighting rings.

9. The aircraft beacon device according to claim 7, wherein the control unit has emission characteristics that are programmed in a fixed manner.

10. The aircraft beacon device according to claim 7, wherein the control unit is configured to modify the emission characteristic during operation of the installation.

11. An aircraft beacon device comprising: a rod-shaped main body configured to be fed horizontally through a tower of the wind power installation from an inside outwards, wherein the rod-shaped main body is configured to be arranged externally on the tower, and a lighting section for emitting light for warning aircraft, the lighting section being configured in order to illuminate only a region above a horizontal plane in which the aircraft beacon device is arranged.

12. The aircraft beacon device according to claim 11, wherein at least one emission characteristic is implemented in a fixed manner.

13. The aircraft beacon device according to claim 12, wherein at least one emission characteristic implemented in a fixed manner essentially emits only upwards in such a way that the aircraft beacon device does not emit downwards when used as intended on the wind power installation.

14. The aircraft beacon device according to claim 13, wherein at least one emission characteristic implemented in a fixed manner has a lower emission angle of at least −5° the luminous intensity below this lower emission angle being less than 10%, of the maximum luminous intensity of the emission characteristic, and/or in that the luminous intensity below an emission angle of 0° is less than 70% of the maximum luminous intensity of the emission characteristic and decreases further with lower emission angles.

15. The aircraft beacon device according to claim 12, wherein there are at least two emission characteristics implemented in a fixed manner, a first of the at least two emission characteristics is intended for a red night beacon and a second of the at least two emission characteristics is intended for a white daytime beacon.

16. The aircraft beacon device according to claim 1, wherein the lights are infrared lights.

17. A wind power installation comprising: a gondola; and at least one aircraft beacon device according to claim 1 arranged on the gondola.

18. A method for operating an aircraft beacon device according to claim 1 comprising driving the lights in such a way that a predetermined emission characteristic is generated and/or is switched on and/or off in a predetermined sector.

19. The method according to claim 18, wherein properties of the emission of the aircraft beacon device are adjusted or modified during continuous operation by corresponding driving of the lights and/or the lighting rings.

20. The method according to claim 18 wherein a vertical emission characteristic, a horizontal sector for emission and/or an emission intensity is adjusted or modified during continuous operation as a function of an event and/or a period of time or point in time.

21. The method according to claim 18, wherein an emission characteristic is specified by establishing the driving of the lights and the lighting rings, before the aircraft beacon device is put into operation.

22. The method according to claim 18, wherein the aircraft beacon device, when installed on a gondola of a wind power installation, is readjusted as a function of the azimuthal position of the gondola, and an emission characteristic varying in the horizontal direction is adapted according to the azimuthal position of the gondola during continuous operation.

Description

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

[0061] The present invention will now be explained in more detail below by way of example with the aid of exemplary embodiments with reference to the appended figures.

[0062] FIG. 1 shows a schematic representation of a wind power installation.

[0063] FIG. 2 shows a schematic representation of an aircraft beacon device according to one embodiment.

[0064] FIG. 3 shows a schematic representation of emission characteristics of an aircraft beacon device according to one embodiment.

[0065] FIG. 4 schematically shows a wind power installation gondola in plan view.

[0066] FIG. 5 shows by way of example one vertical emission characteristic of an omnidirectional emission section.

[0067] FIG. 6 shows by way of example another vertical emission characteristic of an omnidirectional emission section.

[0068] FIG. 7 schematically shows an emission characteristic only for emission upwards as a comparison.

DETAILED DESCRIPTION

[0069] FIG. 1 shows a wind power installation 100 having a tower 102 and a gondola 104. A rotor 106 having three rotor blades 108 and a spinner 110 is arranged on the gondola 104. During operation, the rotor 106 is set in rotational movement by the wind and thereby drives a generator in the gondola 104. An aircraft beacon device 101 is arranged on the gondola 104, although as an alternative two aircraft beacon devices 101 may for example also be provided.

[0070] FIG. 2 shows an aircraft beacon device 200, which has three omnidirectional emission sections 210, 211 and 212 arranged in a ring and concentrically with respect to one another in the axial direction 202 around a mid-axis 204. The omnidirectional emission sections 210, 211 and 212 respectively comprise a fully circumferential lens section 220, 221 and 222, each of the lens sections 210, 211 and 212 defining a beam plane 230, 231 and 232. The omnidirectional emission sections 210 and 211 have three fully circumferential lighting rings 240, 241 and 242, and 243, 244 and 245, respectively. They have white LEDs 250 arranged in a ring concentrically around the mid-axis 204. The three lighting rings 240, 241 and 242, and 243, 244 and 245, respectively, are axially offset with respect to one another. The lowermost omnidirectional emission section 212 has only one lighting ring 246 of red LEDs 251.

[0071] To this extent, FIG. 2 shows a part of the aircraft beacon device 200 in a partially sectional schematic partial view. The representation of FIG. 2—the same applies for the subsequent FIG. 3—is intended in particular possible emission characteristics in relation to the vertical direction is respectively a central lighting ring 241 or 244 at the height of the relevant beam plane 230 or 231. A lighting ring 240 or 243 is respectively arranged higher, and yet another lighting ring 242 or 245 is respectively arranged lower. The two omnidirectional emission sections 210 and 211 are represented identically in FIG. 2, although different configurations could also be provided. For example, the lens sections 220 and 221 could be formed in a different way. A different number of lighting rings may be provided, for example only two lighting rings in the upper omnidirectional emission section 210. The lighting rings 240, 241 and 242 of the omnidirectional emission section 210, on the one hand, may also have different spacings from one another in comparison with the spacings of the lighting rings 243, 244 and 245 of the omnidirectional emission section 211. In this way, different emission characteristics may respectively be achieved by the two omnidirectional emission sections 210 and 211. In this way, a very large number of different emission characteristics may be characterized by superposition of the emission characteristics of the two omnidirectional emission sections 210 and 211.

[0072] It should also be pointed out that the vertical spacing, i.e., the spacing in the direction of the mid-axis 204, or in the axial direction 202, is no longer relevant for a distant observer, i.e., for example the pilot of an aircraft. Rather, it is much more important that different characteristics can be generated.

[0073] The omnidirectional emission sections 210 and 211 may also be provided in order to satisfy very different requirements for emission characteristics. It is even conceivable for two different regions, or even two different countries, to place different requirements on the emission characteristics such that only the use of one omnidirectional emission section, for example the omnidirectional emission section 210, is envisaged for one region or one country, and only the operation of the omnidirectional emission section 211 is envisaged for the other region or the other country. Often, however, a combination of a plurality of omnidirectional emission sections is conceivable.

[0074] The omnidirectional emission section 212 of the example of FIG. 2 comprises only the one lighting ring 246, which has red LEDs 251. These red LEDs, or the red lighting ring, are intended for nighttime operation and therefore often make do with less flexibility in terms of their emission direction. In particular, such red light-emitting diodes, or in general red lighting, of aircraft beacon devices are less dazzling and can also be seen easily even without a special beam direction because of the dark background. A single lighting ring may therefore be sufficient. This is also presented only for illustration, and in particular to illustrate that an aircraft beacon device may contain a plurality of omnidirectional emission sections 210, 211 and 212, which may be formed in a different way.

[0075] Correspondingly, the representation of FIG. 2 also shows that, it is possible to achieve different emission characteristics by superposition, which, besides emission direction and intensity, also involves a superposition or combination or variation in terms of the light color.

[0076] FIG. 3 shows the emission characteristic 300 of an omnidirectional emission section as represented in FIG. 2. The omnidirectional emission section 310 comprises a lens section 320 and three lighting rings 340, 341 and 342, represented by an LED 350, 351 and 352, respectively. The individual LEDs 350, 351 and 352 are driven selectively and according to requirement by the control unit of the aircraft beacon device 360. Owing to the fact that the lighting rings 340, 341 and 342 are arranged offset axially with respect to one another, the three lighting rings 340, 341 and 342 respectively have a different emission characteristic. This is illustrated by the emission characteristic 301, which shows the omnidirectional emission section 310 after selective driving, only the lighting ring 342, or LED 352, being driven.

[0077] The omnidirectional emission section 310 shown by way of example could, for example, be identical to the omnidirectional emission section 210 of FIG. 2, and correspondingly form a part of an aircraft beacon device as illustrated in FIG. 2.

[0078] FIG. 3 shows this omnidirectional emission section 310 in two drive variants. The upper variant, variant a) or FIG. 3a shows the driving of all three LEDs 350, 351 and 352, which to this extent also stand representatively for the corresponding lighting rings 340, 341 and 342. For illustration, three beam cones 360, 361 and 362 are shown, which come from a light-emitting diode 350, 351 and 352, respectively. These three beam cones 360, 361 and 362 then reach the lens section 320. The position of the light-emitting diodes 350, 351 and 352, respectively, with respect to the lens section 320 then gives an emission range with a central emission direction 370, 371 and 372, respectively, with corresponding emission angles 380, 381 and 382, respectively. In this case, the light-emitting diode 350 is assigned the central emission direction 370 with the emission angle 380. For this upper light-emitting diode 350, this leads to a central emission direction 370 which is directed downwards and therefore has a negative emission angle 380. The central light-emitting diode 351 therefore has a horizontal central emission direction 371, and thus an emission angle 381 which has the value zero. The light-emitting diode 352 arranged further below correspondingly has a central emission direction which is directed upwards with a positive emission angle 382.

[0079] For this case a) or FIG. 3a, there is therefore a widely spread emission characteristic which emits significantly upwards and significantly downwards.

[0080] Variant b) or FIG. 3b drives only the lower light-emitting diode 352, or the corresponding lighting ring, which leads only to the lower emission cone 362 and consequently also only to the upwardly directed central emission direction 372 with the emission angle 382. The emission characteristic of the omnidirectional emission section 310 is therefore directed upwards overall.

[0081] As considered from the outside, or by a remote observer or from a remote observation point, the omnidirectional emission section 310, and when only this omnidirectional emission section of the aircraft beacon device is driven, the entire aircraft beacon device, therefore emits in a wide range. In the lower case, the omnidirectional emission section 310, or the entire aircraft beacon device, only emits upwards.

[0082] The characteristic of the aircraft beacon device can thus be influenced as a whole by correspondingly controlled driving of the lighting, and in particular in a focused fashion by the driving of the lighting rings. This influence by of the driving makes it possible both to specify fixed characteristics, for example in order to satisfy regionally different requirements, and carry out dynamic adjustments. Such dynamic adjustments may, inter alia, be provided for event-dependent adaptations as well as azimuthal readjustment or compensation for azimuthal readjustment of a gondola of a wind power installation. Such a flexibly adjustable aircraft beacon device is suitable in particular for wind power installations because, on the one hand, great flexibility is required. On the other hand, wind power installations currently have the feature that they are not fully standardized, but are substantially standardized and can be installed in very different regions. Similar or almost identical wind power installations can therefore be provided for entirely different regions and also be fitted with the same aircraft beacon devices. This fitting may even be carried out before the region in which the respective wind power installation is to be delivered has been established, that is to say before it has been established which regulations the aircraft beacon device must eventually comply with. This naturally also includes the case that the delivery of a wind power installation to a particular location, and therefore to a particular region, has been established but for unforeseeable reasons a modification is carried out and this wind power installation is suddenly delivered to a different place. For the aircraft beacon device, this is no longer a problem. It merely needs to be adapted accordingly by programming.

[0083] FIG. 4 schematically shows a wind power installation gondola 402 in a plan view with two aircraft beacon devices 400. The aircraft beacon devices 400 are installed on an instrument support 404, which is located above the gondola 402 and is also accessible for maintenance purposes.

[0084] FIG. 4 shows only one of three rotor blades 406 of the gondola 402 for illustration, namely in a 12 o'clock position. The rotor blade 406 together with the spinner 408 is arranged so as to be rotatable with respect to the rest of the gondola 402. Because of the wind, the rotor blade 406 rotates in the rotation direction 410 denoted by an arrow. When an aircraft 412, which is represented in this case only symbolically and at an unrealistically short distance, approaches, one of the aircraft beacon devices 400 may be shadowed by the rotor blade 406. Which of the two is shadowed, if one of them is shadowed at all, depends on the setting of the rotor blade 406 and the position of the observer, i.e., symbolically of the aircraft 412 in this case.

[0085] Such a problem of being covered by the rotor blade 406 arises, however, only for objects which are in front of the wind power installation, i.e., those which are in front of the gondola 402. If such objects lie behind the wind power installation or the gondola 402, they can always see both aircraft beacon devices 400. It is therefore only necessary for the two aircraft beacon devices 400 to emit in the forward direction, i.e., for double illumination to be provided. In the backward direction, double illumination by two aircraft beacon devices 200 is not absolutely necessary. One possibility then consists in each of the aircraft beacon devices emitting 180° in the forward direction, in order to achieve double illumination there because of the problem of the shadowing by the rotor blade 406. In the backward direction, the two aircraft beacon devices may respectively illuminate 90°, so that together they illuminate 180° in the backward direction, but not doubly. In order to illustrate this, an illumination sector 414 and 416, respectively, is indicated for the two aircraft beacon devices. Each illumination sector 414 and 416 therefore illuminates 270°. Likewise, the two aircraft beacon devices correspondingly have a blind sector 418 and 420, respectively, which they do not illuminate.

[0086] The illumination of the illumination sectors 414 and 416 can now be achieved straightforwardly by the lighting or lighting groups of the aircraft beacon devices 400 being driven accordingly.

[0087] FIG. 5 shows by way of example a vertical emission characteristic of an omnidirectional emission section which has four axially separated lighting rings. The luminous intensity in candelas (Cd) is plotted on the ordinate as a function of the vertical angle ranges on the abscissa. The value 0 here denotes the respective beam plane and negative values are in this case upwardly directed directions, although this may also be configured differently.

[0088] Of the four lighting rings, for the vertical emission characteristic shown in FIG. 5, only the second to fourth rings, counted from the bottom, are used, each of which induces one of the second to fourth individual characteristics 502-504 shown. The first ring may be used for a different characteristic. The overall characteristic 505, which is formed by the sum of the individual characteristics, is likewise indicated, as is a predetermined setpoint characteristic 506. It can be seen that the setpoint characteristic 506 can be complied with by the overall characteristic 505, which may also be referred to as the sum characteristic.

[0089] FIG. 6 shows vertical emission characteristics for the same omnidirectional emission section as in FIG. 5, but with different driving. Here, the first to third rings, counted from the bottom, are used. It can be seen that, in comparison with FIG. 5, a different overall characteristic 605 or sum characteristic 605 is obtained, which can comply with the setpoint characteristic 606 shown, which is likewise different here. The overall characteristic 605 or sum characteristic 605 is the sum of the individual characteristics 601 to 603.

[0090] It can also be seen that the individual characteristic 602 of the second ring has a higher intensity in comparison with the individual characteristic 502 of FIG. 5, which was also generated by the second ring.

[0091] It can therefore be seen that the respective overall characteristic or sum characteristic can be influenced or adjusted by selection of the driven rings, i.e., lighting rings, as well as by the intensity of the individual driving.

[0092] Therefore, which does not apply for the embodiments shown, a variable aircraft beacon is provided, which may also be referred to as an obstacle beacon or simply as a beacon.

[0093] Both the light intensity and the emission characteristic of the beacon can be varied.

[0094] This is done, in particular, by switching individual LEDs or LED groups on and/or off, and/or by different driving. By switching the individual LEDs or LED groups on and/or off, the emission characteristic is influenced in particular. In particular, the intensity may be influenced by different driving.

[0095] As the origin of the modification of the beacon properties, it is possible to use a sensor value, an automated specification, for example a timer, or direct instructions, for example via remote control devices.

[0096] One example of use is demand-controlled night identification. The beacons in this case illuminate to the necessary minimum in order not to disturb the residents and to ensure sufficient protection for the aircraft. When an aircraft is detected, the beacon switches to a maximum. This is only an example and it is also conceivable, for example, and is generally proposed as an embodiment, also to modify the intensity and/or emission characteristic during the day as a function of an event, such as the approaching aircraft mentioned by way of example, and in particular to adapt them to the event.

[0097] The utility model is intended to comprise solutions which are produced in a beacon or in a plurality of beacons.

[0098] It is particularly advantageous for the proposed beacon that it can be modified during continued operation. The proposed beacon can always adjust its setting again during normal operation.

[0099] Preferably, 4 omnidirectional emission sections are provided, so as to achieve high flexibility.

[0100] Preferably, respectively 4 lighting rings are provided in at least one omnidirectional emission section, in order to be able to produce even very different emission characteristics.

[0101] FIG. 7 compares a preferred emission characteristic with a previous emission characteristic. The two characteristics are respectively denoted by an upper limit (“max” in dashes) and a lower limit (solid “min”), the respectively bolder lines relating to the new preferred characteristic. Positive values of the vertical emission angle in this case denote emission upwards, negative downwards, and 0° denotes a horizontal plane.

[0102] The specific emission characteristics respectively lie between the upper and lower limits. The previous emission characteristic is therefore distributed substantially uniformly around the horizontal plane, whereas the new preferred emission characteristic lies approximately around the value 5°, while scarcely lying in the negative range, i.e., scarcely emitting downwards. It is essentially limited to the upward range.