Aerodrome lighting device (versions)

FIELD: electricity.

SUBSTANCE: light beam that left the first output face passes along the first channel and gets to the first input surface of the first window. Light beam that left the second output face passes along the second channel and gets to the second input surface of the second window. The light beam is discharged from the device via the first output surface of the first window and the second output surface of the second window. At the same time arrangement of the first window and second window in the form of an optical wedge with mutually perpendicular cylindrical surfaces or in the form of an optical wedge with a diffraction structure with rated relief applied onto the first input surface of the first window and the second input surface of the second window provides for formation of angular divergence of the light beam, which has asymmetric angular dimensions along the vertical line and horizontal line and change of its direction, providing for arrangement of the lower border of the light beam on the surface of a landing strip, and also provision of the specified direction of the axis of maximum brightness of light beam.

EFFECT: simplified design, reduced dimensions and weight of a device and improved technology for assembly into a landing strip surface.

10 cl, 5 dwg

 

The technical field

The invention relates to lighting equipment airfields, heliports, landing sites for aircraft carriers, and is intended for display at night and in low visibility conditions axis and boundaries of a runway or taxi-way, or for indication of the landing area, or other lights which are built into the surface. In addition, this device can be used to indicate the axis and the boundaries of highways.

The level of technology

A device - in-depth fire (RF patent No. 2057274). In-depth fire includes a housing with an internal cavity, which contains the optical elements and at least one lamp. The lamp is connected to the means of supply. On the housing cover mounted with at least one optical window for an output light beam and a reinforced hole for access to the interior of the housing. The lamp base is mounted a means for engagement of the lamp with removable long holder, enter into the housing only when replacing the lamp through is made in the cover in alignment with the lamp and socket specified access hole into the case. The hole is made with dimensions that are necessary and sufficient to accommodate protruding from the cover of the flame holder, and overlapping this holder, and when exp is watachi overlapped installed through the seal removable stopper.

The disadvantages of the known solutions are the large weight and size characteristics, complicating the installation of the device into the surface of the aerodrome; the complexity of the design of fire associated with the presence of electrical devices, the contact elements and additional parts inside the enclosure required for mounting, fixing and replacing the lamp. This device has a low reliability, low manufacturability and maintainability.

The closest technical solution (prototype) is a light emitting device, embedded in the surface (U.S. patent No. 6155703). The lighting device includes in-depth in the surface of the fiber-optic cable, and connected with it the insert comprising a cylindrical body with an internal cavity. The cavity has at least one channel with a window. Inside the cavity is an optical device that generates a luminous flux. Light beam is directed using the built-in mirror with adjustment of its angular position in the window. The connection of the fibre optic cable with inset in the lower part of the body, and the optical axis of the optical-fiber cable perpendicular to the surface of the runway.

The disadvantages of the prototype are enlarged dimensions of the insert due to the vertical connection of fiber-optic to the blanching with the lower part of the body and lengthening when this optical path of the light within the cavity, which leads to an increase in the aperture of the window and the size of the device in cross section perpendicular to the axis of the light flux. In addition, the increased size of the device increases the likelihood of hitting him wheel chassis LA and power load, which must withstand the insert. The disadvantage is the inconvenience of mounting the design of the insert in the runway, due to the need to pre-drill a ring of holes and subsequent atheological remove the inner part of the material (concrete) to obtain a cylindrical cavity in which is mounted a lighting device.

The aim of the invention is to reduce the size and weight of the device and improving the technology of the mounting surface of the runway.

This goal is achieved due to the fact that according to the first embodiment in the airfield lighting device, comprising a housing with above-ground part and an underground part, fiber-optic cable with an input end and an output end, means mounting the optical rotator, the first window with the first input surface and a first output surface, the output end is fixed in the underground part of ensuring the passage of light from a fiber optic cable in optical rotator, the output end is fixed in the underground hour and by means of fastening, in addition, the device performed the first channel from the first input part and the first output part, an optical rotator made in the form of the first rotary prism with a first input line, an additional line is made reflective, and the first output line, and the first rotary prism installed in the underground part, the first channel made in the body of the output light from the first rotary prism through the first output line of the underground part of the outside device through the above-ground part, the first input portion located on the side of the first rotary prism, and the first window installed in the first output portion, the first window is made to ensure forming a predetermined pattern of light distribution, in the particular case at least the first input surface or the first output surface is cylindrical, in another particular case, the first input surface and the first output surface is cylindrical with a mutually perpendicular axis position, in another particular case, at least on the first input surface or the first output surface of the diffraction structure, in another particular case, on the first input line, the first output line, the first input surface and the first output surface is caused to illuminate what their coverage, consistent with the spectrum of a passing light flux; according to the second embodiment in aerodrome lighting device, comprising a housing with above-ground part and an underground part, fiber-optic cable with an input end and an output end, means mounting the optical rotator, the first window with the first input surface and a first output surface, the output end is fixed in the underground part of ensuring the passage of light from the optical fiber cable in the optical rotary device, the output end is fixed in the underground part by means of fastening, in addition to the device through the first channel from the first input part and the first output part, the second window from the second entrance surface and the second output surface, and the device made a second channel from the second input part and the second output part, an optical rotator made in the form of the first rotary prism with a first input line, an additional line and the first output line and the second rotatable prism with the second input line, the second reflecting face and the second output line, and the first rotary prism and the second rotatable prism installed in the underground part, an additional distinction is made with the provision of the reflection spectrum of the luminous flux toward the first you are the one face and passing through the additional edge the other end of the spectrum in the second rotatable prism, the first channel is made in the case with the provision of the light output from the first rotary prism through the first output line of the underground part of the outside device through the above-ground part, the second channel made in the body of the output light from the second rotatable prism through the second output line of the underground part of the outside device through the above-ground part, the first input portion located on the side of the first rotary prism, and the first window installed in the first output part, the second input part is on the side of the second rotary prism, and the second window is set to the second output part, the first window and the second window wypolnenii ensuring the formation of the set beam light distribution, in the particular case at least the first input surface or the first output surface and the second input surface or the output surface is cylindrical, in another particular case, the first input surface and the first output surface is cylindrical with a mutually perpendicular axis position, the second input surface and the second output surface is cylindrical with a mutually perpendicular axis position, in another particular case, at least on the first input surface or the first output surface is made di is Acciona structure, and on the second input surface or the second output surface of the diffraction structure, in another particular case, on the first input line, the first output line, the second input line, the second output line, the first input surface, the first output surface, the second input surface and the second output surface of the deposited antireflective coating, consistent with the spectrum of light passing stream.

Brief description of drawings

The invention is illustrated by drawings (Fig.1-5), where Fig 1 shows the device side partial section view in figure 2 shows the front view of the device, figure 3 shows a top view of the device with the first window, figure 4 shows the direction of movement of the light flux inside the first rotary prism, figure 5 shows the direction of movement of the light flux inside the first rotary prism and the second rotatable prism in the case of using them together.

Disclosure of inventions

In the drawing: runway 1, the first recess 2, the first output surface 3, the first window 4, the first input surface 5, the first output part 6, channel 7, the first input part 8, the optical rotator 9, the above-ground part 10, the underground portion 11, a body 12 tip 13, a fiber optic cable 14, the first output line 15, dopolnitelnye gr is ery 16, the first input line 17, the second reflective face 18, the second input face 19, the second output line 20, the second rotatable prism 21, the first rotary prism 22.

According to the first embodiment, the main elements of the device are the body 12, a fiber optic cable 14, the optical rotator 9 and the first window 4.

The housing 12 is made to enable the installation of the device and protect the inner parts of the device from external impact. The housing 12 is composed of two parts - the underground part 11 and the above-ground portion 10.

The underground portion 11 is made to enable the installation of the device in runway 1. The underground portion 11 is made in the form of a flat plate with a thickness substantially less than the length and height. The underground portion 11 in the particular case in the form of flat monolithic cylindrical segment (semi-circle), i.e. in the form of a plate bounded linear edge and an arcuate edge. In particular, if the thickness of the underground part 11, i.e. the distance between its large surfaces made of 10 mm is the Underground portion 11 during operation is located in the body of a runway 1 perpendicular to its surface or in a position close to perpendicular. This arcuate edge of the underground part 11 facing the inside of the runway 1 in the horon the opposite of the above-ground portion 10. The linear edge of the underground part 11 facing outwards runway 1 in the direction of the aerial part 10. In the underground part 11 in the region of the center of its linear region made a hole for installation of optical rotary device 9. The underground portion 11 is connected with the above-ground part 10 in its linear edge. Optical rotary device 9 is placed in the underground part 11. The underground portion 11 may be made integral with the above-ground part 10, or may be rigidly connected with it. The underground portion 11 may be made of another configuration, for example in the form of a parallelogram.

The aboveground part 10 in particular, if made in the form of a truncated four-sided rectangular pyramid. Other embodiments of the shape of the above-ground part 10, for example dome-shaped, conical, cylindrical, etc. without impairing the functional properties of the device. The height of the aerial part 10 should not exceed the height recommended by the International civil aviation organization (ICAO), i.e., 13 mm Aboveground part 10 is connected with the underground part 11 on the surface of the largest area (the bottom surface ground part 10), for example in the case of performing the above-ground part 10, in the form of a truncated pyramid underground portion 11 attached thereto by a larger base of the truncated pyramid.

In the casing 12 through the first channel 7, before oznaczony for passing light from the optical rotary device 9 through the first window 4 to the outside of the device. The first channel 7 is a narrow hollow space in the shape of a tube, i.e. cylindrical or conical hole made on the location of the optical rotator 9 (the Central part of the linear region of the underground part 11) to the side surface of the above-ground part 10 (in the particular case of one of the side faces of the truncated pyramid). The first channel 7 consists of a first input part 8 and the first output part 6. From the first input part 8 posted optical rotary device 9. From the first output part 6 is the first window 4.

The overground part 10 made the first recess 2. The first recess 2 is located opposite from the first open 4 side with respect to the first channel 7. The first recess 2 is made with the possibility of the location of the lower boundary of the light flux emerged from the first channel 7 through the first window 4, on the surface of the runway 1, after the unit is installed in the runway 1.

Optical rotary device 9 in the first embodiment is made consisting of a first rotary prism 22. The first rotary prism 22 is an optical element that is designed to change the direction of the light flux. The first rotary prism 22 is made of transparent material and is limited to flat polarized what poverhnosti. The first rotary prism 22 is a prism with a base in the form of triangles. The first rotary prism 22 is supplied with the first input face 17, additional edge 16 and the first output line 15.

The first input line 17 is a side face of the prism, located perpendicularly to the first output face 15, and designed to input to the first rotary prism 22 of the light flux. On the first input face 17 of the first rotary prism 22 may be applied ar coating. To the first input face 17 summarized fiber optic cable 14 with a tip 13.

An additional facet 16 is a side face of the prism forming the first input line 17 and the first output line 15 sharp corners. An additional distinction is made reflective, i.e. with the possibility of reflection of at least part of the spectrum of the light flux. Additional face 16 caused the beam splitting coating, for example of the spectral selective reflecting interference coating that reflects up to 100% of the spectrum in the direction of the first output face 15 of the first rotary prism 22.

The first output line 16 is a side face of the prism, located perpendicularly to the first input face 17, and designed for light output from the first rotary prism 22 to the outside device is istwa. On the first output line 15 of the first rotary prism 22 applied ar coating, consistent with the spectrum of a passing light flux and is designed to reduce light loss. The first output face 17 facing the first window 4 that is installed in the first output part 6 of the first channel 7.

Fiber optic cable 14 is one or a group of optical conductors (with a glass or plastic core)enclosed in a common envelope and used to transmit light waves. Fiber optic cable 14 is limited by the input end and the output end. Transmitted light waves are emitted by conventional or laser source type connected to the input end. Fiber-optic cable 14 at the output end provided with fastening means in the form of tip 13.

The tip 13 is designed for coupling a fiber optic cable 14 with the optical rotating device 9, i.e. for leading the light flux to the first input face 17.

The first window 4 is made to ensure the protection optical rotator 9 and the first channel 7 from external influences and dirt. The first window 4 is made with a capability of forming the angular divergence of the light flux, which has an asymmetric angular dimensions vertically and horizontally (see ' Between the national standards and recommended practices. Airfields. Annex 14 to the Convention on international civil aviation (ICAO). Volume 1. The design and operation of aerodromes. Ed. 1 - July 1990, ICAO Appendix 2). The first window 4 is made with the possibility of changing the direction of the light flux, providing the location of the lower boundary of the light flux on the surface of the runway 1. The first window 4 is made with the required direction of the axis of maximum brightness of the light flux. The above features may be provided when performing the first window 4 in the form of an optical wedge (see Reference design opto-mechanical devices. Under the General Ed. Vaganova. 3rd ed., revised and enlarged extra - Leningrad: Mashinostroenie, Leningrad. Department, 1980 - p.192), which is non-parallel surfaces are formed of a cylindrical surface with mutually perpendicular axes of the cylinders parallel to the surfaces of the optical wedge (see ALEXANDER Sulima Production of optical parts. Ed. 2nd, Rev. and extra - M.: Higher. school, 1969. - s.). A similar function is fulfilled by the first window 4 in the form of an optical wedge with a diffractive structure on the first input surface 5 of the first window 4. Diffractive structure is made with an estimated microrelief optical surface, which is formed given the angular divergence of the light flux (see Difrac the ion computer optics. Ed. by V.A. of Soifer - M.: FIZMATLIT, 2007, Chapter 2).

The first window 4 provided with the first input surface 5 and the first exit surface 3. The first input surface 5 facing the first channel 7, i.e. to the first output face 15. The first output surface 3 facing in the direction opposite to the first entrance surface 5, i.e. to the outside of the device.

To reduce the loss of light at the first input surface 5 and the first output surface 3 of the first window 4 antireflection coating is applied.

To ensure the durability of the device to mechanical stress the first window 4 made of a glass having increased strength and resistance to abrasion, for example made of quartz glass or sapphire, or oxynitride aluminum, or other optically transparent materials or compositions.

According to the second embodiment, the main elements of the device are the body 12, a fiber optic cable 14, the optical rotator 9, the first window 4 and the second window.

The housing 12 is made to enable the installation of the device and protect the inner parts of the device from external impact. The housing 12 is composed of two parts - the underground part 11 and the above-ground portion 10.

The underground portion 11 is made to enable the installation of the device in runway 1. Underground is the actu 11 made in the form of a flat plate with thickness much less of its length and height. The underground portion 11 in the particular case in the form of flat monolithic cylindrical segment (semi-circle), i.e. in the form of a plate bounded linear edge and an arcuate edge. In particular, if the thickness of the underground part 11, i.e. the distance between its large surfaces made of 10 mm is the Underground portion 11 during operation is located in the body of a runway 1 perpendicular to its surface or in a position close to perpendicular. This arcuate edge of the underground part 11 facing the inside of the runway 1 in the direction opposite the above-ground parts 10. The linear edge of the underground part 11 facing outwards runway 1 in the direction of the aerial part 10. In the underground part 11 in the region of the center of its linear region made a hole for installation of optical rotary device 9. The underground portion 11 is connected with the above-ground part 10 in its linear edge. Optical rotary device 9 is placed in the underground part 11. The underground portion 11 may be made integral with the above-ground part 10, or may be rigidly connected with it. The underground portion 11 may be made of another configuration, for example in the form of a parallelogram.

The aboveground part 10 in particular, if made in the form of a truncated four-sided rectangular pyramid. Other embodiments of the forms of the above-ground parts 10, for example dome-shaped, conical, cylindrical, etc. without impairing the functional properties of the device. The height of the aerial part 10 should not exceed the height recommended by the International civil aviation organization (ICAO), i.e., 13 mm Aboveground part 10 is connected with the underground part 11 on the surface of the largest area (the bottom surface ground part 10), for example in the case of performing the above-ground part 10, in the form of a truncated pyramid underground portion 11 attached thereto by a larger base of the truncated pyramid.

In the casing 12 through the first channel 7 and the second channel is designed to pass light from the optical rotary device 9 through the first window 4 and the second window to the outside device. The first channel 7 is a narrow hollow space in the shape of a tube, i.e. cylindrical or conical hole made on the location of the optical rotator 9 (the Central part of the linear region of the underground part 11) to the side surface of the above-ground part 10 (in the particular case of one of the side faces of the truncated pyramid). The second channel is identical to the first channel 7. The first channel 7 consists of a first input part 8 and the first output part 6. The second channel comprises a second input part and the second output part. From the first input part 8 and the second input frequent the placed optical rotary device 9. The first output part 6 of the first channel 7 is directed in the direction opposite to the second output of the second channel. From the first output part 6 is the first window 4. From the second output part has a second window.

The overground part 10 made the first recess 2 and the second recess. The first recess 2 is located opposite from the first open 4 side with respect to the first channel 7. The second notch is located opposite to the second window side with respect to the second channel. The first recess 2 and the second recess is made with the possibility of the location of the lower boundary of the light flux, released respectively from the first channel 7 through the first window 4 and the second channel through the second window, on the surface of the runway 1, after the unit is installed in the runway 1.

Optical rotary device 9 according to the second variant is made consisting of a first rotary prism 22 and the second rotatable prism 21. The first rotary prism 22 and the second rotatable prism 21 are optical elements for changing the direction of the light flux. The first rotary prism 22 and the second rotatable prism 21 is made of transparent material and is limited to flat polarized surfaces. The first rotary prism 22 Evora rotary prism 21 are prisms with bases in the form of triangles. The first rotary prism 22 is supplied with the first input face 17, additional edge 16 and the first output line 15. The second rotatable prism 21 is supplied with the second input face 19, the second reflective face 18 and the second output line 20.

The first input line 17 is a side face of the prism, located perpendicularly to the first output face 15, and designed to input to the first rotary prism 22 of the light flux. On the first input face 17 of the first rotary prism 22 may be applied ar coating. To the first input face 17 summarized fiber optic cable 14 with a tip 13.

An additional facet 16 is a side face of the prism forming the first input line 17 and the first output line 15 sharp corners. An additional distinction is made with the possibility of reflection of at least part of the spectrum of the light flux. An additional facet 16 is made also with the possibility of transmission to the second rotatable prism 21, at least part of the spectrum of the light flux. This additional facet 16 caused the beam splitting coating, for example of the spectral selective reflecting interference coating that reflects up to 100% of the spectrum in the direction of the first output face 15 of the first rotary prism 22 and transmits another part of the spectrum is via an additional line 16 to the second rotatable prism 21.

The first output line 16 is a side face of the prism, located perpendicularly to the first input face 17, and designed for light output from the first rotary prism 22 to the outside of the device. On the first output line 15 of the first rotary prism 22 applied ar coating, consistent with the spectrum of a passing light flux and is designed to reduce light loss. The first output face 17 facing the first window 4 that is installed in the first output part 6 of the first channel 7.

The second input face 19 is a side face of the prism that is located perpendicular to the second reflecting face 18, and intended to enter the second rotatable prism 21 of the light flux. The second input face 19 of the second rotatable prism 21 may be applied ar coating. The second input face 19 is located on the extra edge 16, i.e. combined with additional face 16 with the possibility of falling into the second rotary prism 21 through the second input face 19 of the light flux transmitted through the additional edge 16 of the first rotary prism 22.

The second reflective face 18 is a side face of the prism that is located perpendicular to the second input face 19 and is designed to reflect at least part of the spectrum SV is preset flow. On the second reflecting face 19 marked the beam splitting coating, for example of the spectral selective reflecting interference coating that reflects up to 100% of the spectrum, missed more face 16 to the second rotatable prism 21, and the output side of the second face 20 of the second rotatable prism 21.

The second output line 20 is a side face of the prism forming the second input line 19 and the second reflective face 18 sharp corners, and designed for light output from the second rotary prism 21 to the outside of the device. The second output face 20 of the second rotatable prism 21 applied ar coating, consistent with the spectrum of a passing light flux reflected from the second reflective face 18 and is designed to reduce light loss. The second output face 20 facing the second window set to the second output of the second channel.

Fiber optic cable 14 is one or a group of optical conductors (with a glass or plastic core)enclosed in a common envelope and used to transmit light waves. Fiber optic cable 14 is limited by the input end and the output end. Transmitted light waves are emitted by conventional or laser source type connected to the input end. Optical-in the window of the cable 14 at the output end provided with fastening means in the form of tip 13.

The tip 13 is designed for coupling a fiber optic cable 14 with the optical rotating device 9, i.e. for leading the light flux to the first input face 17.

The first window 4 and the second window is made to ensure the protection optical rotator 9, the first channel 7 and the second channel from external influences and dirt. The first window 4 and the second window is made with a capability of forming the angular divergence of the light flux, which has an asymmetric angular dimensions vertically and horizontally (see International standards and recommended practices. Airfields. Annex 14 to the Convention on international civil aviation (ICAO). Volume 1. The design and operation of aerodromes. Ed. 1 - July 1990, ICAO Appendix 2). The first window 4 and the second window is made with the possibility of changing the direction of the light flux, providing the location of the lower boundary of the light flux on the surface of the runway 1. The first window 4 and the second window is made with the required direction of the axis of maximum brightness of the light flux. The above features may be provided when performing the first window 4 and the second window in an optical wedge (see Reference design opto-mechanical devices. Under the General Ed. V. Panov. 3rd ed., revised and enlarged the op. - Leningrad: Mashinostroenie, Leningrad. Department, 1980 - p.192), which is non-parallel surfaces are formed of a cylindrical surface with mutually perpendicular axes of the cylinders parallel to the surfaces of the optical wedge (see ALEXANDER Sulima Production of optical parts. Ed. 2nd, Rev. and extra - M.: Higher. school, 1969. - s.). A similar function is fulfilled by the first window 4 and a second window in an optical wedge with a diffractive structure on the first input surface 5 of the first window 4 and the second input surface of the second window. Diffractive structure is made with an estimated microrelief optical surface, which is formed given the angular divergence of the light flux (see Diffraction computer optics. Ed. by V.A. of Soifer - M.: FIZMATLIT, 2007, Chapter 2).

The first window 4 provided with the first input surface 5 and the first exit surface 3. The first input surface 5 facing the first channel 7, i.e. to the first output face 15. The first output surface 3 facing in the direction opposite to the first entrance surface 5, i.e. to the outside of the device. The second window is supplied with the second input surface and the second output surface. The second input surface facing the second channel, i.e. the second output face 20. The second output surface facing the prot is opposite the second entrance surface, i.e. output device.

To reduce the loss of light at the first input surface 5 and the first output surface 3 of the first window 4 and the second input surface and the second output surface of the second window is applied antireflection coating.

To ensure the durability of the device to mechanical stress the first window 4 and the second window is made of glass of high strength and resistance to abrasion, for example made of quartz glass or sapphire, or oxynitride aluminum, or other optically transparent materials or compositions.

The implementation of the invention

The invention according to the first embodiment is implemented as follows. Manufactured housing 12, an optical rotator 9, consisting of a first rotary prism 22, the first window 4 and a fiber optic cable 14 with a tip 13. Optical rotary device 9 is installed in the housing 12 and the first input part 8 of the first channel 7 with capability of rotation of the light flux from the optical fiber cable 14 with a tip 13 in the direction of the first window 4. At the end of the fiber optic cable 14 is fixed to the handpiece 13.

In the runway 1 carry out the holes for the mounting device to accommodate the underground parts 11 of the housing 12), and the trench for placement of fiber optic cable 14. Done is the underground part 11 of the housing 12 in the form of a flat plate allows to simplify the technology of its mounting surface runway 1 by milling the surface of the runway 1 grooves with depth equal to the height of the underground part 11 of the housing 12. Milling is carried out by means of a diamond cutter with a radius equal to the radius of curvature of the arcuate edge of the underground part 11 of the housing 12 and a width equal to the thickness of the underground part 11. In addition, this technology can be used for cutting trenches for laying in the surface of the runway 1 fiber optic cable 14. In these trenches place fiber optic cable 14.

Fiber-optic cable 14 with a tip 13 is placed in a horizontal plane parallel to the runway 1 or in a position close to him. Fiber-optic cable 14 with a tip 13 is perpendicular to the underground part 11 of the housing 12. Fiber optic cable 14 is fixed in the underground part with the aid of fastening means, in the form of tip 13, ensuring the passage of light from the fiber optic cable 14 in the optical rotating device 9. When this join fiber optic cable 14 to the first input face 17 of the first rotary prism 22. If necessary, the trench in which to place fiber optic cable 14, is closed.

The underground portion 11 of the device is placed in the specified hole. The underground portion 11 is directed linear edge upwards, i.e. in the direction opposite to the direction of the gravity vector. P is jamna part 11 arcuate edge facing down, i.e. in the direction of the gravity vector.

The aboveground part 10 surface, which is made from its connection with the underground part 11, in part based on the surface of the runway 1. The first channel 7 is located at an angle to the horizon, i.e. to the surface of the runway. The surface of the first recess 2 from the underground part 11 is parallel to the runway 1 or in a position close to parallel.

The design of the device with the underground part 11, in the form of flat plates connected to the aerial part 10 ensures that the axis direction of the light flux along the azimuth and elevation after multiple force effects, as opposed to analogue and prototype device cannot be rotated about a vertical axis.

Due to the position of the optical rotary device 9 as close as possible to the surface of the elevated portion 10, which is connected to the underground part 11, reduced its size to several millimeters. In addition, this arrangement made it possible to locate in the horizontal plane of the fiber optic cable 14 with a tip 13, thereby reducing optical losses occurring during the bending of the fiber optic cable 14 and the dimensions of the device as a whole, to reduce the length of the optical path length is Otok and improve the overall strength of the device while reducing its size.

This optical system allows to minimize the size of the first channel 7 and almost eliminated from the structure of the device of the internal cavity, thereby improving the sealing device and its strength characteristics.

When mounting the device to install it with the specified elevation, consistent with the elevation of the runway 1, you can use a wedge-shaped plate mounted between the plane of the runway 1 and aerial part 10 of the housing 12 of the device. It is possible to use additional and more complex devices control the position of the first rotary prism 22 or the first window 4.

The light output from the fiber optic cable 14 by means of the tip 13 is supplied to the first rotary prism 22 through the first input line 17. Luminous flux falls on the additional face 16, which reflects up to 100% of the spectrum in the direction of the first output face 15 of the first rotary prism 22. The reflected portion of the spectrum passes through the first output line 15. On the first input line 17 and the first output line 15 deposited antireflection coatings, consistent with the spectrum passing through the light flux, which increases the efficiency of the device.

The luminous flux emitted from the first output face 15 passes through the first channel 7 and gets to the first input on Ernest 5 of the first window 4. Luminous flux output from the device through the first output surface 3 of the first window 4. Thus the performance of the first window 4 in the form of an optical wedge with mutually perpendicular cylindrical surfaces or in the form of optical wedge coated with the first input surface 5 of the first window 4 diffractive structure with the settlement provides relief forming angular divergence of the light flux, which has an asymmetric angular dimensions vertically and horizontally, and change its direction, providing the location of the lower boundary of the light flux on the surface of the runway 1, and the required direction of the axis of maximum brightness of the light flux. This can be achieved by performing the above-ground part of the device 10 of the first recess 2 from the first window 4, opposite to the first channel 7, having a surface parallel runway 1.

The invention according to the second embodiment is implemented as follows. Manufactured housing 12, an optical rotator 9, consisting of a first rotary prism 22 and the second rotatable prism 21, the first window 4, a second window and a fiber optic cable 14 with a tip 13. Optical rotary device 9 is installed in the housing 12 to enable the chief is the light from a fiber optic cable 14 with a tip 13 in the direction of the first window 4 and the second window. At the end of the fiber optic cable 14 is fixed to the handpiece 13.

In the runway 1 carry out the holes for the mounting device to accommodate the underground parts 11 of the housing 12), and the trench for placement of fiber optic cable 14. The execution of the underground part 11 of the housing 12 in the form of a flat plate allows to simplify the technology of its mounting surface runway 1 by milling the surface of the runway 1 grooves with a depth equal to the height of the underground part 11 of the housing 12. Milling is carried out by means of a diamond cutter with a radius equal to the radius of curvature of the arcuate edge of the underground part 11 of the housing 12 and a width equal to the thickness of the underground part 11. In addition, this technology can be used for cutting trenches for laying in the surface of the runway 1 fiber optic cable 14. In these trenches place fiber optic cable 14.

Fiber-optic cable 14 with a tip 13 is placed in a horizontal plane parallel to the runway 1 or in a position close to him. Fiber-optic cable 14 with a tip 13 is perpendicular to the underground part 11 of the housing 12. Fiber optic cable 14 is fixed in the underground part with the aid of fastening means made in the form of Nikon is cnica 13, ensuring the passage of light from the fiber optic cable 14 in the optical rotating device 9. When this join fiber optic cable 14 to the first input face 17 of the first rotary prism 22. If necessary, the trench in which to place fiber optic cable 14, is closed.

The underground portion 11 of the device is placed in the specified hole. The underground portion 11 is directed linear edge upwards, i.e. in the direction opposite to the direction of the gravity vector. The underground portion 11 arcuate edge directed downwards, i.e. in the direction of the gravity vector.

The aboveground part 10 surface, which is made from its connection with the underground part 11, in part based on the surface of the runway 1. The first channel 7 and the second channel are arranged at an angle to the horizon, i.e. to the surface of the runway. The surface of the first recess 2 and the second grooves from the underground part 11 are parallel runway 1 or in a position close to parallel.

The design of the device with the underground part 11, in the form of flat plates connected to the aerial part 10 ensures that the axis direction of the light flux along the azimuth and elevation after multiple force effects, as opposed to analogue and prototype device cannot regards acuatica relative to the vertical axis.

Due to the position of the optical rotary device 9 as close as possible to the surface of the elevated portion 10, which is connected to the underground part 11, reduced its size to several millimeters. In addition, this arrangement made it possible to locate in the horizontal plane of the fiber optic cable 14 with a tip 13, thereby reducing optical losses occurring during the bending of the fiber optic cable 14 and the dimensions of the device as a whole, to reduce the optical path length of the light flux and to improve the overall strength of the device while reducing its size.

This optical system allows to minimize the size of the first channel 7 and the second channel and virtually eliminate the design of the device cavity, thereby improving the sealing device and its strength characteristics.

Performing optical rotator 9 with two rotating prisms (with the first rotary prism 22 and the second rotatable prism 21) allows to provide the light signals of different colors when applied to the additional face 16 of the first rotary prism 22 spectral selective reflecting interference coatings. Its application allows to obtain in a single device two spectral selective lighting of the indicator with the opposite to what yavleniyami light fluxes, without energy to increase the power of the light stream.

An example of the use of such devices serve as input lights (green) and end lights (red)are located near each other at the ends of runways 1 and emitting the luminous flux of these spectra in opposite directions.

When mounting the device to install it with the specified elevation, consistent with the elevation of the runway 1, you can use a wedge-shaped plate mounted between the plane of the runway 1 and aerial part 10 of the housing 12 of the device. It is possible to use additional and more complex devices control the position of the first rotary prism 22 and the second rotatable prism 21, the first window 4 and the second window.

The light output from the fiber optic cable 14 by means of the tip 13 is supplied to the first rotary prism 22 through the first input line 17. Luminous flux falls on the additional face 16, which reflects up to 100% of the spectrum in the direction of the first output face 15 of the first rotary prism 22 and transmits another part of the spectrum to the second rotatable prism 21. The reflected portion of the spectrum passes through the first output line 15. Passed through an additional facet 16 part of the spectrum enters the second rotatable when the mu 21 through the second input line 19. Last part of the spectrum falls on the second reflecting face 18, which reflects up to 100% of the last part of the spectrum at the output side of the second face 20 of the second rotatable prism 21. On the first input line 17, the second input face 19, the first output line 15 and the second output line 20 deposited antireflection coatings, consistent with the spectrum passing through the light flux, which increases the efficiency of the device.

The luminous flux emitted from the first output face 15 passes through the first channel 7 and gets to the first input surface 5 of the first window 4. The luminous flux emitted from the second output face 20 passes through the second channel and gets on the second input surface of the second window 4. Luminous flux output from the device through the first output surface 3 of the first window 4 and the second output surface of the second window. Thus the performance of the first window 4 and the second window in an optical wedge with mutually perpendicular cylindrical surfaces or in the form of optical wedge coated with the first input surface 5 of the first window 4 and the second input surface of the second window diffractive structure with the settlement provides relief forming angular divergence of the light flux, which has an asymmetric angular dimensions vertically and horizontally, and change it healthy lifestyles the tion, providing the location of the lower boundary of the light flux on the surface of the runway 1, and the required direction of the axis of maximum brightness of the light flux. This can be achieved by performing the above-ground part of the device 10 of the first recess 2 from the first window 4, opposite to the first channel 7 and through the second notch from the side of the second window, opposite the second channel having a surface parallel runway 1.

Thus, the device described above provides a simplified design, reduced size and weight of the device and improving the technology of the mounting surface of the runway.

1. Airfield lighting device, comprising a housing with above-ground part and an underground part, fiber-optic cable with an input end and an output end, means mounting the optical rotator, the first window with the first input surface and a first output surface, the output end is fixed in the underground part of ensuring the passage of light from a fiber optic cable in optical rotator, the output end is fixed in the underground part by means of fastening, in addition, in the device through the first channel from the first input part and the PE the howling output part, wherein the optical rotator made in the form of the first rotary prism with a first input line, an additional line is made reflective, and the first output line, and the first rotary prism installed in the underground part, the first channel made in the body of the output light from the first rotary prism through the first output line of the underground part of the outside device through the above-ground part, the first input portion located on the side of the first rotary prism, and the first window installed in the first output portion, the first window is made to ensure the formation of a predetermined pattern of light distribution.

2. The device according to claim 1, characterized in that at least the first input surface or the first output surface is cylindrical.

3. The device according to claim 1, characterized in that the first input surface and the first output surface is cylindrical with a perpendicular position of the axes.

4. The device according to claim 1, characterized in that at least the first input surface or the first output surface of the diffraction structure.

5. The device according to claim 1, characterized in that the first input line, the first output line, the first input surface and the first output surface on eseni antireflection coating, consistent with the spectrum of light passing stream.

6. Airfield lighting device, comprising a housing with above-ground part and an underground part, fiber-optic cable with an input end and an output end, means mounting the optical rotator, the first window with the first input surface and a first output surface, the output end is fixed in the underground part of ensuring the passage of light from a fiber optic cable in optical rotator, the output end is fixed in the underground part by means of fastening, in addition, in the device through the first channel from the first input part and the first output part, characterized in that it introduced a second window with a second the input surface and the second output surface, and the device made a second channel from the second input part and the second output part, an optical rotator made in the form of the first rotary prism with a first input line, an additional line and the first output line and the second rotatable prism with the second input line, the second reflecting face and the second output line, and the first rotary prism and the second rotatable prism installed in the underground part, an additional distinction is made with the provision of the reflection spectrum of the light flux in the side is from the first output face and passing through the additional edge the other end of the spectrum to the second rotary the prism, the first channel is made in the case with the provision of the light output from the first rotary prism through the first output line of the underground part of the outside device through the above-ground part, the second channel made in the body of the output light from the second rotatable prism through the second output line of the underground part of the outside device through the above-ground part, the first input portion located on the side of the first rotary prism, and the first window installed in the first output part, the second input part is on the side of the second rotary prism, and the second window is set to the second output part, the first window and the second window is made to ensure the formation of the set beam light distribution.

7. The device according to claim 6, characterized in that at least the first input surface or the first output surface and the second input surface or the output surface is cylindrical.

8. The device according to claim 6, characterized in that the first input surface and the first output surface is cylindrical with a mutually perpendicular axis position, the second input surface and the second output surface is cylindrical with a perpendicular position of the axes.

9. The device according to claim 6, characterized in that at least at first the input surface or the first output surface of the diffraction structure, and on the second input surface or the second output surface of the diffraction structure.

10. The device according to claim 6, characterized in that the first input line, the first output line, the second input line, the second output line, the first input surface, the first output surface, the second input surface and the second output surface of the deposited antireflective coating, consistent with the spectrum of a passing light flux.



 

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