CN219623877U

CN219623877U - Aircraft landing lamp optical structure based on integrated lens

Info

Publication number: CN219623877U
Application number: CN202320323660.8U
Authority: CN
Inventors: 郭长伟; 路建华; 张涛; 郑茜元; 吕海慧
Original assignee: Shanghai Aviation Electric Co Ltd
Current assignee: Shanghai Aviation Electric Co Ltd
Priority date: 2023-02-27
Filing date: 2023-02-27
Publication date: 2023-09-01
Anticipated expiration: 2033-02-27

Abstract

The utility model discloses an integrated lens-based aircraft landing light structure, which comprises: landing lamp panel, inner ring LED group, middle ring LED group and outer ring LED group; the landing lamp panel is provided with the inner ring LED group, the middle ring LED group and the outer ring LED group. The utility model has the beneficial effects that: the aircraft landing lamp utilizes the TIR lens to carry out light distribution, so that the light energy utilization rate is high, the universalization degree of the optical element is improved, and the modularized design is realized.

Description

Aircraft landing lamp optical structure based on integrated lens

Technical Field

The utility model relates to an aircraft landing light, in particular to an integrated lens-based aircraft landing light structure.

Background

At present, an LED is adopted as a light source of an aircraft landing lamp, and the light distribution mode is that a reflecting bowl is used for carrying out reflection light distribution. The defects are that: reflective light distribution of the reflector has certain limitations, including but not limited to: the light energy utilization rate is low, the batch difference is large, and the installation mode is complex.

Disclosure of Invention

The utility model provides a novel integrated lens-based optical structure of an aircraft landing lamp, and aims to solve the problem that the existing aircraft landing lamp adopts reflective light distribution.

In order to achieve the above object, the technical scheme of the present utility model is as follows: an integrated lens-based aircraft landing light structure, comprising: landing lamp panel, inner ring LED group, middle ring LED group and outer ring LED group; the landing lamp panel is provided with the inner ring LED group, the middle ring LED group and the outer ring LED group; the inner ring LED group consists of inner ring LEDs, and the inner ring LEDs are provided with inner ring TIR lenses; the middle ring LED group consists of middle ring LEDs, and the middle ring LEDs are provided with middle ring TIR lenses; the outer ring LED group is composed of outer ring LEDs, and the outer ring LEDs are provided with outer ring TIR lenses. The inner ring TIR lens controls the light intensity of 3.5 degrees and part of the central light intensity, the middle ring TIR lens controls the central light intensity, and the outer ring TIR lens controls the light intensity of 7 degrees and part of the central light intensity.

As a preferred solution of the optical structure of the aircraft landing light based on the integrated lens, the inner ring LED is at the focal position of the inner ring TIR lens, the middle ring LED is at the focal position of the middle ring TIR lens, and the outer ring LED is at the focal position of the outer ring TIR lens.

As a preferable scheme of the optical structure of the aircraft landing lamp based on the integrated lens, the number of the inner ring LEDs, the number of the middle ring LEDs and the number of the outer ring LEDs are 5, 10 and 15 respectively.

As a preferable scheme of the optical structure of the aircraft landing lamp based on the integrated lens, the inner ring LEDs, the middle ring LEDs and the outer ring LEDs are all high-power LEDs.

Compared with the prior art, the utility model has the beneficial effects that: the aircraft landing lamp utilizes the TIR lens to carry out light distribution, so that the light energy utilization rate is high, the universalization degree of the optical element is improved, and the modularized design is realized.

Drawings

Fig. 1 is a schematic diagram (2D schematic) of an embodiment of the present utility model.

Fig. 2 is a schematic structural view (3D schematic) of an embodiment of the present utility model.

Fig. 3 is a schematic view of an LED arrangement according to an embodiment of the present utility model.

Fig. 4 is a cross-sectional view (taken along the midline) of the structure of an embodiment of the present utility model.

FIG. 5 is a diagram of simulation results according to an embodiment of the present utility model.

Detailed Description

The utility model will be described in further detail below with reference to the drawings by means of specific embodiments. The description of these embodiments is provided to assist understanding of the present utility model, but is not to be construed as limiting the present utility model. In addition, the technical features of the embodiments of the present utility model described below may be combined with each other as long as they do not collide with each other.

Referring to fig. 1-4, an integrated lens-based aircraft landing light architecture is shown.

The aircraft landing light structure comprises: landing lamp panel 1, inner circle LED group 2, middle circle LED group 3, outer lane LED group 4 etc..

The landing light board 1 is provided with the inner ring LED group 2, the middle ring LED group 3 and the outer ring LED group 4. Wherein the middle ring LED group 3 is arranged between the inner ring LED group 2 and the outer ring LED group 4.

The inner ring LED group 2 is composed of inner ring LEDs 21. The inner ring LEDs 21 are uniformly arranged in the circumferential direction. The inner ring LED21 is configured with an inner ring TIR lens 22. The inner ring LED21 is at the focal position of the inner ring TIR lens 22. The inner ring TIR lens 22 controls the light intensity at an angle of 3.5 DEG and part of the center light intensity.

The middle-turn LED group 3 is composed of middle-turn LEDs 31. The middle-ring LEDs 31 are uniformly arranged in the circumferential direction. The intermediate ring LED31 is provided with an intermediate ring TIR lens 32. The intermediate ring of LEDs 31 is at the focal position of the intermediate ring TIR lens 32. The intermediate ring TIR lens 32 controls the central light intensity.

The outer ring LED group 4 is composed of outer ring LEDs 41. The outer ring LEDs 41 are uniformly arranged in the circumferential direction. The outer ring LED41 is provided with an outer ring TIR lens 42. The outer ring LED41 is at the focal position of the outer ring TIR lens 42. The outer TIR lens 42 controls the intensity of 7 ° and part of the center intensity.

In this embodiment, the number of the inner ring LEDs 21, the number of the middle ring LEDs 31, and the number of the outer ring LEDs 41 are 5, 10, and 15, respectively.

In this embodiment, the inner ring LED21, the middle ring LED31, and the outer ring LED41 are all high-power LEDs.

In this embodiment, the inner ring TIR lens 22, the middle ring TIR lens 32, and the outer ring TIR lens 42 are made of a lens material with high transmittance, high temperature resistance, and high hardness.

Referring to fig. 5, the aircraft landing light described in this embodiment is verified using optical simulation software SPEOS. Wherein the thermal steady-state center light intensity 490000cd, horizontal and vertical scatter angles reach a circular spot of 14.7 °. It can be seen that the aircraft landing light has less light beam loss outside the required scattering angle range, more than about 90% of light beams fall in the effective scattering angle range, the optical utilization rate is high, the light type distribution is continuous, no brightness gradient change and full, the whole light distribution is good, no dark area exists, and the peak light intensity and the angle are far beyond the requirements of GJB 2020A-2012.

The foregoing has outlined rather broadly the more detailed description of the utility model in order that the detailed description thereof herein may be better understood, and in order that the present utility model may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the utility model, which are all within the scope of the utility model. Accordingly, the scope of protection of the present utility model is to be determined by the appended claims.

Claims

1. An integrated lens-based aircraft landing light structure, comprising: landing lamp panel, inner ring LED group, middle ring LED group and outer ring LED group; the landing lamp panel is provided with the inner ring LED group, the middle ring LED group and the outer ring LED group; the inner ring LED group consists of inner ring LEDs, and the inner ring LEDs are provided with inner ring TIR lenses; the middle ring LED group consists of middle ring LEDs, and the middle ring LEDs are provided with middle ring TIR lenses; the outer ring LED group consists of outer ring LEDs, and the outer ring LEDs are provided with outer ring TIR lenses; the inner ring TIR lens controls the light intensity of 3.5 degrees and part of the central light intensity, the middle ring TIR lens controls the central light intensity, and the outer ring TIR lens controls the light intensity of 7 degrees and part of the central light intensity.

2. The integrated lens-based aircraft landing light structure of claim 1, wherein the inner ring LED is at the focal position of the inner ring TIR lens, the middle ring LED is at the focal position of the middle ring TIR lens, and the outer ring LED is at the focal position of the outer ring TIR lens.

3. An integrated lens-based aircraft landing light structure as claimed in claim 1, wherein the inner ring LEDs, the middle ring LEDs and the outer ring LEDs are 5, 10 and 15 respectively.

4. The integrated lens-based aircraft landing light structure of claim 1, wherein the inner ring LED, the middle ring LED and the outer ring LED are all high-power LEDs.