CN203784830U - LED (Light Emitting Diode) lens used for aircraft front navigation light - Google Patents
LED (Light Emitting Diode) lens used for aircraft front navigation light Download PDFInfo
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- CN203784830U CN203784830U CN201420091007.4U CN201420091007U CN203784830U CN 203784830 U CN203784830 U CN 203784830U CN 201420091007 U CN201420091007 U CN 201420091007U CN 203784830 U CN203784830 U CN 203784830U
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Abstract
The utility model discloses an LED (Light Emitting Diode) lens used for an aircraft front navigation light. The LED lens comprises an internal total reflection system and an optical prism system, wherein the internal total reflection system is used for collecting light rays which are emitted by an LED light source, carrying out total reflection on the light rays and enabling the light rays to be emergent in a small angle; the optical prism system is used for adjusting the emergent light ray direction and the optical distribution of the small-angle emergent light rays of the internal total reflection system; the internal total reflection system is provided with a groove used for receiving the light rays which are emitted by the LED light source. According to the LED lens, the light distribution requirement of the aircraft front navigation light is met, the implementation mode is simple, the integral molding is realized, the installation is simpler, the cost is lower, the maintenance difficulty and the maintenance hidden danger are also reduced, the application of the LED light source in the aircraft front navigation light is favorably generalized, and the LED lens can be widely applied to the aircraft front navigation light.
Description
Technical field
The utility model relates to a kind of LED lens, particularly a kind of LED lens for aircraft forward position light.
Background technology
LED light source is entering lighting field fast as a kind of new lighting source, and than conventional light source, LED light source has the advantages such as high light efficiency, low energy consumption, long-life, high reliability, at lighting field, has distinct advantage.
Along with the development of LED technology, LED illumination also, progressively to the infiltration of special lighting field, is widely applied in fields such as automobile, railway, boats and ships and space flight at present.In space industry, position light for when night flying, causes the attention at other aircraft of same space flight, bumps avoiding between aircraft.In traditional position light, main use is incandescent lamp, itself limited in service life, and in severe flight environment of vehicle, its life-span further shortens, and the situation of the frequent replacing navigation lights bringing because of navigation lights life problems, not only cause high maintenance cost, when serious, also can cause postponements of flights, therefore LED light source being applied in is important and urgent in position light.Therefore the light sending due to LED light source has good controllability, can design the light that different lens send it and redistribute, to meet application requirements.
But, concerning aircraft forward position light, because its optical profile has specific requirement, as depicted in figs. 1 and 2, Fig. 1 is the light distribution requirements schematic diagram of the horizontal cross-section of the right front navigation lights of aircraft, it is asymmetric light distribution, take aircraft flight direction of advance as 0 ° of angle, the right wing forward position light in 0 degree angular direction to the minimum of a value of the light intensity in clockwise 10 ° of deflections be 40cd, 10 ° of deflections to the minimum of a value of the light intensity in the deflection of clockwise 20 ° is 30cd, and 20 ° of deflections are to the minimum of a value 5cd of the light intensity in clockwise 110 ° of deflections.The light distribution requirements of the horizontal cross-section of the left front navigation lights of aircraft of left side wing and the symmetry in Fig. 1.Fig. 2 is the light distribution requirements schematic diagram above water of the vertical cross-section of aircraft forward position light, using aircraft direction of advance as 0 ° of deflection, in the deflection of 0 ° of deflection up to 5 °, the minimum of a value of light intensity should be before aircraft forward position light on line direction peaked 0.9 times, in the deflection of 5 ° of deflection up to 10 °, the minimum of a value of light intensity is before aircraft forward position light on line direction peaked 0.8 times, in the deflection of 10 ° of deflection up to 15 °, the minimum of a value of light intensity is before aircraft forward position light on line direction peaked 0.7 times, in the deflection of 15 ° of deflection up to 20 °, the minimum of a value of light intensity is before aircraft forward position light on line direction peaked 0.5 times, in the deflection of 20 ° of deflection up to 30 °, the minimum of a value of light intensity is before aircraft forward position light on line direction peaked 0.3 times, in the deflection of 30 ° of deflection up to 40 °, the minimum of a value of light intensity is before aircraft forward position light on line direction peaked 0.1 times.Light distribution requirement in the angle of horizontal plane following (0 ° of deflection down) and Fig. 2 are distributed symmetrically.The current lens for LED light source generally can only be gathered light or diffusion etc. simply; cannot meet the light distribution requirements of the aircraft forward position light in Fig. 1 and Fig. 2; therefore may need to adopt a plurality of LED light sources in conjunction with the mode of a plurality of lens or adopt the mode of supplementing illumination to realize forward position light scheme; scheme is complicated, cost is high; and install loaded down with trivial details; maintenance hidden danger is also large, is unfavorable for the application of LED light source in aircraft forward position light.
Utility model content
In order to solve above-mentioned technical problem, the purpose of this utility model is to provide a kind of LED lens for aircraft forward position light.
The utility model solves the technical scheme that its technical problem adopts:
A kind of LED lens for aircraft forward position light, comprising for collecting the light that LED light source sends and it being carried out to total reflection makes it be the inner full-reflection system of low-angle outgoing, and for adjusting the light direction of low-angle light and the optical prism system of optical profile of the outgoing of inner full-reflection system, described inner full-reflection system is provided with for collecting the groove of the light that LED light source sends.
Further, described inner full-reflection system comprises the first fully reflecting surface, the second fully reflecting surface, light refraction face and exit facet, the light that described LED light source sends incides in inner full-reflection system by light refraction face, passes through exit facet outgoing after the first fully reflecting surface and/or the second fully reflecting surface total reflection.
Further, described optical prism system comprises the plane of incidence, refraction reflecting surface, the first exiting surface and the second exiting surface, the light of the exit facet outgoing of inner full-reflection system incides optical prism system and incides on refraction reflecting surface from the plane of incidence, wherein a part of light outgoing after the refraction of refraction reflecting surface, at refraction reflecting surface place, there is total reflection in residual ray, then a part of total reflection light is via the rear outgoing of the first exiting surface refraction, and remaining total reflection light is via the rear outgoing of the second exiting surface refraction.
Further, described refraction reflecting surface comprises first refractive reflecting surface and the second refraction reflecting surface, at first refractive reflecting surface place, there is the light of total reflection via the rear outgoing of the first exiting surface refraction, and outgoing after the light of the second refraction reflecting surface place generation total reflection reflects via the second exiting surface.
Further, described the first exiting surface comprises refraction exiting surface one and refraction exiting surface two, and described refraction exiting surface one is plane or curved surface, and described refraction exiting surface two is curved surface.
Further, described first refractive reflecting surface, the second refraction reflecting surface and the second exiting surface are plane or curved surface.
Further, described the first fully reflecting surface, the second fully reflecting surface, light refraction face and exit facet are plane or curved surface.
Further, described inner full-reflection system and optical prism system adopt optical plastic or optical glass.
The beneficial effects of the utility model are: a kind of LED lens for aircraft forward position light of the present utility model, comprising for collecting the light that LED light source sends and it being carried out to total reflection makes it be the inner full-reflection system of low-angle outgoing, and for adjusting the light direction of low-angle light and the optical prism system of optical profile of the outgoing of inner full-reflection system, described inner full-reflection system is provided with for collecting the groove of the light that LED light source sends, this LED lens are by rationally arranging the structure of inner full-reflection system and optical prism system, can meet the light distribution requirements of aircraft forward position light, implementation is simple, and can be one-body molded, install comparatively simple, cost is lower, maintenance difficulty and maintenance hidden danger have also been reduced, contribute to promote the application of LED light source in aircraft forward position light.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the utility model is described in further detail.
Fig. 1 is the light distribution requirements schematic diagram of the horizontal cross-section of the right front navigation lights of aircraft;
Fig. 2 is the light distribution requirements schematic diagram above water of the vertical cross-section of aircraft forward position light;
Fig. 3 is the first schematic diagram of a kind of LED lens for aircraft forward position light of the present utility model;
Fig. 4 is the second schematic diagram of a kind of LED lens for aircraft forward position light of the present utility model;
Fig. 5 is the 3rd schematic diagram of a kind of LED lens for aircraft forward position light of the present utility model;
Fig. 6 is the 4th schematic diagram of a kind of LED lens for aircraft forward position light of the present utility model;
Fig. 7 carries out the first schematic diagram of ray tracing to a kind of LED lens for aircraft forward position light of the present utility model;
Fig. 8 carries out the second schematic diagram of ray tracing to a kind of LED lens for aircraft forward position light of the present utility model;
Fig. 9 is the schematic diagram of luminous intensity distribution for the first time of specific embodiment of the utility model;
Figure 10 is the schematic diagram of luminous intensity distribution for the second time of specific embodiment of the utility model;
Figure 11 is the schematic diagram of luminous intensity distribution for the third time of specific embodiment of the utility model.
The specific embodiment
With reference to Fig. 3 and Fig. 4, the utility model provides a kind of LED lens for aircraft forward position light, comprising for collecting the light that LED light source 11 sends and it being carried out to total reflection makes it be the inner full-reflection system 12 of low-angle outgoing, and for adjusting the light direction of low-angle light and the optical prism system 13 of optical profile of 12 outgoing of inner full-reflection system, described inner full-reflection system 12 is provided with for collecting the groove of the light that LED light source 11 sends.
Be further used as preferred embodiment, with reference to Fig. 5, described inner full-reflection system 12 comprises the first fully reflecting surface 121, the second fully reflecting surface 122, light refraction face 123 and exit facet 124, the light that described LED light source 11 sends incides in inner full-reflection system 12 by light refraction face 123, passes through exit facet 124 outgoing after the first fully reflecting surface 121 and/or the second fully reflecting surface 122 total reflections.
Be further used as preferred embodiment, described optical prism system 13 comprises the plane of incidence 130, refraction reflecting surface 131, the first exiting surface 132 and the second exiting surface 133, the light of exit facet 124 outgoing of inner full-reflection system 12 incides optical prism system 13 and incides on refraction reflecting surface 131 from the plane of incidence 130, wherein a part of light outgoing after 131 refractions of refraction reflecting surface, at refraction reflecting surface 131 places, there is total reflection in residual ray, then a part of total reflection light is via the rear outgoing of the first exiting surface 132 refraction, remaining total reflection light is via the rear outgoing of the second exiting surface 133 refraction.
Be further used as preferred embodiment, with reference to Fig. 6, described refraction reflecting surface 131 comprises first refractive reflecting surface 1311 and the second refraction reflecting surface 1312, at first refractive reflecting surface 1311 places, there is the light of total reflection via the rear outgoing of the first exiting surface 132 refraction, and outgoing after the light of the second refraction reflecting surface 1312 places generation total reflection reflects via the second exiting surface 133.
Be further used as preferred embodiment, described the first exiting surface 132 comprises refraction exiting surface 1 and refraction exiting surface 2 1322, and described refraction exiting surface 1 is plane or curved surface, and described refraction exiting surface 2 1322 is curved surface.
Be further used as preferred embodiment, described first refractive reflecting surface 1311, the second refraction reflecting surface 1312 and the second exiting surface 133 are plane or curved surface.
Be further used as preferred embodiment, described the first fully reflecting surface 121, the second fully reflecting surface 122, light refraction face 123 and exit facet 124 are plane or curved surface.
Be further used as preferred embodiment, described inner full-reflection system 12 and optical prism system 13 adopt optical plastic or optical glass.
Below in conjunction with the specific embodiment, the utility model is described further, with reference to Fig. 3 ~ Figure 11, the utility model provides a kind of LED lens for aircraft forward position light, as shown in Figure 3 and Figure 4, comprising for collecting the light that LED light source 11 sends and it being carried out to total reflection makes it be the inner full-reflection system 12 of low-angle outgoing, and for adjusting the light direction of low-angle light and the optical prism system 13 of optical profile of 12 outgoing of inner full-reflection system, inner full-reflection system 12 is provided with for collecting the groove of the light that LED light source 11 sends, as shown in Figure 3, a groove is set on full reflected system 12, when LED light source 11 is installed, the light-emitting area of LED light source 11 is arranged in groove, therefore can collect more light makes it enter full reflected system 12, improve light utilization.
With reference to Fig. 5, inner full-reflection system 12 comprises the first fully reflecting surface 121, the second fully reflecting surface 122, light refraction face 123 and exit facet 124, the light that LED light source 11 sends incides in inner full-reflection system 12 by light refraction face 123, passes through exit facet 124 outgoing after the first fully reflecting surface 121 and/or the second fully reflecting surface 122 total reflections.Optical prism system 13 comprises the plane of incidence 130, refraction reflecting surface 131, the first exiting surface 132 and the second exiting surface 133, the light of exit facet 124 outgoing of inner full-reflection system 12 incides optical prism system 13 and incides on refraction reflecting surface 131 from the plane of incidence 130, wherein a part of light outgoing after 131 refractions of refraction reflecting surface, at refraction reflecting surface 131 places, there is total reflection in residual ray, then a part of total reflection light is via the rear outgoing of the first exiting surface 132 refraction, and remaining total reflection light is via the rear outgoing of the second exiting surface 133 refraction.
With reference to Fig. 6, refraction reflecting surface 131 comprises first refractive reflecting surface 1311 and the second refraction reflecting surface 1312, as shown in Figure 7, at first refractive reflecting surface 1311 places, there is the light of total reflection via the rear outgoing of the first exiting surface 132 refraction, and the light that total reflection occurs at the second refraction reflecting surface 1312 places is via the rear outgoing of the second exiting surface 133 refraction, shown in Fig. 8.The first exiting surface 132 comprises refraction exiting surface 1 and refraction exiting surface 2 1322, and refraction exiting surface 1 is plane or curved surface, and refraction exiting surface 2 1322 is curved surface.Therefore, by the light of outgoing after the refraction of refraction exiting surface 2 1322, will there is larger refraction angle, be reflected in and in Fig. 7, show as the exit direction edge run-out of turning right.By angle of inclination or the shape of appropriate design first refractive reflecting surface 1311 and the second refraction reflecting surface 1312, can control shooting angle and the direction of total reflection light, can also control from the ratio of first refractive reflecting surface 1311 and the second light of reflecting away of refraction reflecting surface 1312, and reflect exiting surface 1 and the angle of inclination or the shape that reflect exiting surface 2 1322 by appropriate design, can control from shooting angle and the direction of the light of this LED lens outgoing, by controlling the size and dimension of the second exiting surface 133, can control ratio and direction by the light of outgoing after the second exiting surface 133 refractions, in the present embodiment, the optical profile of adjusting light refers to adjusts light in the ratio of the light of all directions outgoing.Generally speaking, the optical prism system 13 of this LED lens is for adjusting light direction and the optical profile of light, thereby makes the light of last outgoing meet the lighting requirement of aircraft forward position light.
First refractive reflecting surface 1311, the second refraction reflecting surface 1312, the second exiting surface 133, the first fully reflecting surface 121, the second fully reflecting surface 122, light refraction face 123 and exit facet 124 are plane or curved surface, and each above face all can be made into plane or curved surface.Curved surface in the present embodiment refers to free form surface, and its concrete curve form, size and detail parameters change according to the difference of the LED light source 11 of its use.
Inner full-reflection system 12 and optical prism system 13 adopt the optical materials such as optical plastic or optical glass.
The present embodiment is mainly that the LED lens for the right front navigation lights of aircraft are example, aircraft forward position light is mounted in wing, left side wing is installed red light source, the right wing is installed green light source, therefore the LED light source that the left front navigation lights of aircraft is used is red-light LED, and the LED light source that the right front navigation lights of aircraft is used is green light LED, because the light source colour on both sides is different, refractive index is different, and the design parameter that is therefore applied in the LED lens on passing light and right navigation lights is slightly different.
The operation principle of this LED lens is described below in conjunction with the variation of concrete luminous intensity distribution.
The light that LED light source 11 sends carries out after total reflection through inner full-reflection system 12, it is low-angle outgoing, this is luminous intensity distribution for the first time, now the distribution curve flux 201 of emergent ray as shown in Figure 9, in figure, the position relationship of coordinate system and aircraft 14 can be found out, the Y direction of the rectangular coordinate system in figure is the navigation direction of aircraft 14, in the present embodiment, the lighting angle 202 of distribution curve flux 201 is 40 degree, in practical application, lighting angle 202 is not done to any restriction, as long as can meet the angle of the light distribution requirements of the vertical interface of aircraft forward position light in Fig. 2 is all fine.
From the low-angle light of inner full-reflection system 12 outgoing, from the plane of incidence 130 of optical prism system 13, incide optical prism system 13 and incide on refraction reflecting surface 131, wherein a part of light outgoing after 131 refractions of refraction reflecting surface, at refraction reflecting surface 131 places, there is total reflection in residual ray, this is luminous intensity distribution for the second time, now the distribution curve flux 301 of the light after the 131 places total reflection of refraction reflecting surface as shown in figure 10, similar with the position relationship of coordinate system in Fig. 9 and aircraft 14, the Y direction of the rectangular coordinate system in figure is the navigation direction of aircraft 14, the point of the largest light intensity value of distribution curve flux 301 and the Y-axis of rectangular coordinate system form angle 302, the large I of angle 302 is adjusted according to the light distribution requirements of aircraft forward position light, in the present embodiment, by adjustment, reflect the inclination angle of first refractive reflecting surface 1311 and the second refraction reflecting surface 1312 of reflecting surface 131, angle 302 is adjusted to 16 degree.
Shown in Figure 11, same, similar with the position relationship of coordinate system in Fig. 9 and aircraft 14, the Y direction of the rectangular coordinate system in figure is the navigation direction of aircraft 14.At refraction reflecting surface, 131 places occur after total reflection, part total reflection light is via the rear outgoing of the first exiting surface 132 refraction, the distribution curve flux of this part emergent light is the distribution curve flux 401 in Figure 11, remaining total reflection light is via the rear outgoing of the second exiting surface 133 refraction, form the distribution curve flux 402 in Figure 11, be luminous intensity distribution for the third time here.Distribution curve flux 402 in Figure 11 meets 20 ° of deflections in Fig. 1 to the light intensity value in clockwise 110 ° of deflections.Therefore, this LED lens meet the light distribution requirements of aircraft forward position light, directly in conjunction with LED light source, with this LED lens, can construct aircraft forward position light, implementation is simple, and can be one-body molded, installs comparatively simple, convenient, cost is lower, also reduce maintenance difficulty and maintenance hidden danger, contributed to promote the application of LED light source in aircraft forward position light, there is important dissemination.
More than that better enforcement of the present utility model is illustrated, but the invention is not limited to embodiment, those of ordinary skill in the art also can make all equivalent variations or replacement under the prerequisite without prejudice to the utility model spirit, and the modification that these are equal to or replacement are all included in the application's claim limited range.
Claims (8)
1. LED lens for aircraft forward position light, it is characterized in that, comprising for collecting the light that LED light source (11) sends and it being carried out to total reflection makes it be the inner full-reflection system (12) of low-angle outgoing, and for adjusting the light direction of low-angle light and the optical prism system (13) of optical profile of inner full-reflection system (12) outgoing, described inner full-reflection system (12) is provided with for collecting the groove of the light that LED light source (11) sends.
2. a kind of LED lens for aircraft forward position light according to claim 1, it is characterized in that, described inner full-reflection system (12) comprises the first fully reflecting surface (121), the second fully reflecting surface (122), light refraction face (123) and exit facet (124), the light that described LED light source (11) sends incides in inner full-reflection system (12) by light refraction face (123), passes through exit facet (124) outgoing after the first fully reflecting surface (121) and/or the second fully reflecting surface (122) total reflection.
3. a kind of LED lens for aircraft forward position light according to claim 2, it is characterized in that, described optical prism system (13) comprises the plane of incidence (130), refraction reflecting surface (131), the first exiting surface (132) and the second exiting surface (133), the light of exit facet (124) outgoing of inner full-reflection system (12) incides optical prism system (13) and incides on refraction reflecting surface (131) from the plane of incidence (130), wherein a part of light outgoing after refraction reflecting surface (131) refraction, residual ray locates to occur total reflection at refraction reflecting surface (131), then a part of total reflection light is via the rear outgoing of the first exiting surface (132) refraction, remaining total reflection light is via the rear outgoing of the second exiting surface (133) refraction.
4. a kind of LED lens for aircraft forward position light according to claim 3, it is characterized in that, described refraction reflecting surface (131) comprises first refractive reflecting surface (1311) and the second refraction reflecting surface (1312), the light of locating total reflection occurs at first refractive reflecting surface (1311) is via the rear outgoing of the first exiting surface (132) refraction, and the light of locating total reflection occurs at the second refraction reflecting surface (1312) is via the rear outgoing of the second exiting surface (133) refraction.
5. a kind of LED lens for aircraft forward position light according to claim 4, it is characterized in that, described the first exiting surface (132) comprises refraction exiting surface one (1321) and refraction exiting surface two (1322), described refraction exiting surface one (1321) is plane or curved surface, and described refraction exiting surface two (1322) is curved surface.
6. a kind of LED lens for aircraft forward position light according to claim 4, is characterized in that, described first refractive reflecting surface (1311), the second refraction reflecting surface (1312) and the second exiting surface (133) are plane or curved surface.
7. a kind of LED lens for aircraft forward position light according to claim 2, is characterized in that, described the first fully reflecting surface (121), the second fully reflecting surface (122), light refraction face (123) and exit facet (124) are plane or curved surface.
8. a kind of LED lens for aircraft forward position light according to claim 1, is characterized in that, described inner full-reflection system (12) and optical prism system (13) adopt optical plastic or optical glass.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420091007.4U CN203784830U (en) | 2014-02-28 | 2014-02-28 | LED (Light Emitting Diode) lens used for aircraft front navigation light |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420091007.4U CN203784830U (en) | 2014-02-28 | 2014-02-28 | LED (Light Emitting Diode) lens used for aircraft front navigation light |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203784830U true CN203784830U (en) | 2014-08-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420091007.4U Withdrawn - After Issue CN203784830U (en) | 2014-02-28 | 2014-02-28 | LED (Light Emitting Diode) lens used for aircraft front navigation light |
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|---|---|
| CN (1) | CN203784830U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103868022A (en) * | 2014-02-28 | 2014-06-18 | 深圳市九洲光电科技有限公司 | LED (Light Emitting Diode) lens for front navigation lamp of airplane |
-
2014
- 2014-02-28 CN CN201420091007.4U patent/CN203784830U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103868022A (en) * | 2014-02-28 | 2014-06-18 | 深圳市九洲光电科技有限公司 | LED (Light Emitting Diode) lens for front navigation lamp of airplane |
| CN103868022B (en) * | 2014-02-28 | 2016-05-11 | 深圳市九洲光电科技有限公司 | A kind of LED lens for aircraft forward position light |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140820 Effective date of abandoning: 20160511 |
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| C25 | Abandonment of patent right or utility model to avoid double patenting |