CN219160198U

CN219160198U - Aircraft slide lamp optical structure based on integrated lens

Info

Publication number: CN219160198U
Application number: CN202223086980.0U
Authority: CN
Inventors: 郭长伟; 路建华; 胡康辉; 潘黎明; 吴裕庭
Original assignee: Shanghai Aviation Electric Co Ltd
Current assignee: Shanghai Aviation Electric Co Ltd
Priority date: 2022-11-21
Filing date: 2022-11-21
Publication date: 2023-06-09
Anticipated expiration: 2032-11-21

Abstract

The utility model discloses an integrated lens-based optical structure of an aircraft running light, which comprises the following components: the sliding lamp comprises a sliding lamp panel, an inner ring LED group, an outer ring LED group and a lens surface light edge; the sliding lamp panel is provided with the inner 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 outer ring LED group consists of outer ring LEDs, and the outer ring LEDs are provided with outer ring TIR lenses; the lens surface light edge covers the inner ring TIR lens and the outer ring TIR lens, and the lens surface light edge is used for directional light control. The utility model has the beneficial effects that: the aircraft slide 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 slide lamp optical structure based on integrated lens

Technical Field

The utility model relates to an aircraft slide lamp, in particular to an integrated lens-based optical structure of the aircraft slide lamp.

Background

At present, an LED is adopted as a light source of the aircraft slide lamp, and the light distribution mode is that a reflecting bowl is utilized 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.

In addition, the LED light is in Lambertian distribution, and the LED light can cause great light energy loss when being directly applied to an aircraft running light.

Disclosure of Invention

The utility model provides a novel optical structure of an aircraft sliding lamp based on an integrated lens, and aims to solve the problem that the existing aircraft sliding 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 glide lamp optical structure comprising: the sliding lamp comprises a sliding lamp panel, an inner ring LED group, an outer ring LED group and a lens surface light edge; the sliding lamp panel is provided with the inner ring LED group and the outer ring LED group; the inner ring LED group consists of an inner ring LED and an inner ring TIR lens, and the inner ring LED is provided with the inner ring TIR lens; the outer ring LED group consists of an outer ring LED and an outer ring TIR lens, and the outer ring LED is provided with the outer ring TIR lens; the lens surface light edge covers the inner ring TIR lens and the outer ring TIR lens, and the lens surface light edge is used for directional light control.

As a preferred embodiment of the optical structure of the aircraft running light based on the integrated lens, the inner ring LED is at the focal position of the inner 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 slide lamp based on the integrated lens, the number of the LEDs on the inner ring and the number of the LEDs on the outer ring are 5 and 10 respectively.

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

Compared with the prior art, the utility model has the beneficial effects that: the aircraft slide 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 cross-sectional view of a structure according to an embodiment of the present utility model.

FIG. 4 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. 1-3, an integrated lens-based aircraft glide lamp optical configuration is shown.

The aircraft slide light optical structure comprises: the slide lamp comprises a slide lamp panel 1, an inner ring LED group 2, an outer ring LED group 3, a lens surface light edge 4 and the like.

The sliding lamp panel 1 is provided with the inner ring LED group 2 and the outer ring LED group 3. Wherein the inner ring LED group 2 is arranged at the inner ring, and the outer ring LED group 3 is arranged at the outer ring.

The inner ring LED group 2 consists of an inner ring LED and an inner ring TIR lens. The inner ring LEDs are uniformly arranged along the circumferential direction. The inner ring LED is configured with the inner ring TIR lens. And the inner ring LED is arranged at the focal position of the inner ring TIR lens.

The outer ring LED group 3 is composed of an outer ring LED31 and an outer ring TIR lens 32. The outer ring LEDs 31 are uniformly arranged in the circumferential direction. The outer ring LED31 is provided with the outer ring TIR lens 32. The outer ring LED31 is at the focal position of the outer ring TIR lens 32.

The lens surface light edge 4 is covered on the inner ring TIR lens and the outer ring TIR lens. The lens surface light edge 4 is used for directional light control.

In this embodiment, the number of the inner ring LEDs and the number of the outer ring LEDs are 5 and 10, respectively.

In the embodiment, the inner ring LEDs and the outer ring LEDs are high-power LEDs, so that HB 6441-1990 aviation white color requirements are met, and the color temperature range is 4400K-4600K, so that the LEDs have higher light efficiency while meeting aviation white color requirements.

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

Referring to fig. 4, the aircraft running light described in this embodiment is verified using optical simulation software SPEOS. Wherein, the thermal steady-state central light intensity 100885cd, the horizontal scattering angle reaches 52 degrees, and the vertical scattering angle reaches 11 degrees. It can be seen that the aircraft running 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 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 slide light optical structure, comprising: the sliding lamp comprises a sliding lamp panel, an inner ring LED group, an outer ring LED group and a lens surface light edge; the sliding lamp panel is provided with the inner ring LED group and the outer ring LED group; the inner ring LED group consists of an inner ring LED and an inner ring TIR lens, and the inner ring LED is provided with the inner ring TIR lens; the outer ring LED group consists of an outer ring LED and an outer ring TIR lens, and the outer ring LED is provided with the outer ring TIR lens; the lens surface light edge covers the inner ring TIR lens and the outer ring TIR lens, and the lens surface light edge is used for directional light control.

2. The integrated lens-based aircraft runner optical structure of claim 1 wherein the inner ring LEDs are at the focal position of the inner ring TIR lens and the outer ring LEDs are at the focal position of the outer ring TIR lens.

3. The integrated lens-based aircraft slide light optical structure of claim 1, wherein the number of the inner ring LEDs and the number of the outer ring LEDs are 5 and 10, respectively.

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