Aircraft light unit and aircraft having such aircraft light unit

Patent metadata

Field	Value
Publication number	US-9745079-B2
Application number	US-201414554580-A
Country	US
Kind code	B2
Filing date	Nov 26, 2014
Priority date	Dec 17, 2013
Publication date	Aug 29, 2017
Grant date	Aug 29, 2017

Abstract

An aircraft light unit ( 2 ), has a support portion ( 4 ), a light source having at least one LED ( 6 ), the light source being arranged on the support portion ( 4 ) and in operation emitting light with a source-side light intensity distribution, and an optical element ( 8 ) for transforming the source-side light intensity distribution into an output light intensity distribution. The optical element ( 8 ) has at least two transformation segments ( 10, 20, 30 ), covering different angular ranges of the source-side light intensity distribution in a first cross-sectional plane. The at least two transformation segments ( 10, 20, 30 ) include a first transformation segment ( 10 ), with the light from the light source experiencing total internal reflection within the optical element ( 8 ) in the first transformation segment ( 10 ) and being bundled in a peak region of the output light intensity distribution, and at least one further transformation segment ( 20, 30 ), with the light from the light source experiencing refraction only in the at least one further transformation segment ( 20, 30 ).

First claim

The invention claimed is:

1. An aircraft, comprising:
an aircraft light unit, wherein the aircraft light unit comprises:
a support portion,
a light source having at least one LED, the light source being arranged on the support portion and in operation emitting light with a source-side light intensity distribution, and
an optical element for transforming the source-side light intensity distribution into an output light intensity distribution,
wherein the optical element has at least two transformation segments, covering different angular ranges of the source-side light intensity distribution in a first cross-sectional plane, the at least two transformation segments comprising:
a first transformation segment, having a first light entry surface, a total internal reflection surface and a first light exit surface, with the light from the light source experiencing total internal reflection within the optical element at the total internal reflection surface in the first transformation segment and being bundled in a peak region of the output light intensity distribution, wherein the first transformation segment covers an angular range of between 20° and 40° of the source-side light intensity distribution in the first cross-sectional plane and wherein said peak region in the output light intensity distribution has an opening angle of between 5° and 15° in the first cross-sectional plane, and
at least one further transformation segment, having at least one further light entry surface and at least one further light exit surface, with the light from the light source experiencing refraction only in the at least one further transformation segment,

wherein the aircraft light unit is disposed in a wing tip region of the aircraft; and
wherein the aircraft light unit is arranged in such a way that a principal light emission direction of the light source is at an angle of between 20° and 40° with respect to the longitudinal direction of the aircraft body.

2. The aircraft according to claim 1 , wherein the at least one further transformation segment of the aircraft light unit comprises a second transformation segment, having a second light entry surface and a second light exit surface, with the light from the light source experiencing refraction at the second light entry surface and refraction at the second light exit surface in the second transformation segment.

3. The aircraft according to claim 2 , wherein the second light entry surface of the optical element of the aircraft light unit is convex, when viewed from the light source, in the second transformation segment.

4. The aircraft according to claim 3 , wherein the second transformation segment of the aircraft light unit covers an angular range of between 30° and 70° of the source-side light intensity distribution in the first cross-sectional plane.

5. The aircraft according to claim 4 , wherein the at least one further transformation segment of the aircraft light unit comprises a third transformation segment, having a third light entry surface and a third light exit surface, with the light leaving the second transformation segment contributing partially to the peak region of the output light intensity distribution and partially to a medium intensity region of the out-put light intensity distribution and with the light leaving the third transformation segment forming a low intensity region of the output light intensity distribution.

6. The aircraft according to claim 3 , wherein the second transformation segment of the aircraft light unit covers an angular range of between 40° and 60° of the source-side light intensity distribution in the first cross-sectional plane.

7. The aircraft according to claim 3 , wherein the second transformation segment of the aircraft light unit covers an angular range of about 50° of the source-side light intensity distribution in the first cross-sectional plane.

8. The aircraft according to claim 1 , wherein said peak region in the output light intensity distribution of the aircraft light unit has an opening angle of about 10° in the first cross-sectional plane.

9. The aircraft according to claim 1 , wherein the first transformation segment of the aircraft light unit covers an angular range of around 30° of the source-side light intensity distribution in the first cross-sectional plane.

10. The aircraft according to claim 1 , wherein the light source of the aircraft light unit is one single LED.

11. The aircraft according to claim 1 , wherein a space between the light source and the optical element of the aircraft light unit is free of shutters and reflectors.

12. The aircraft according to claim 1 , wherein the aircraft light unit further comprises a LED performance detection sensor arranged outside of the optical element, wherein the LED performance detection sensor is adapted to receive stray light not reflected in the first transformation segment and to evaluate the intensity of the stray light in order to assess the strength of the at least one LED.

13. The aircraft according to claim 1 , wherein the aircraft light unit is arranged in such a way that a principal light emission direction of the light source is at an angle of about 30° with respect to the longitudinal direction of the aircraft body.

14. The aircraft according to claim 1 , wherein the first cross-sectional plane is a horizontal plane.

15. Method of replacing a used light unit in an aircraft with an aircraft light unit according to claim 1 , the method comprising the steps of:
disconnecting the used light unit from a power source, and
connecting the aircraft light unit according to claim 1 to the power source.

Assignees

• Goodrich Lighting Systems Gmbh

Inventors

• Jha Anil Kumar

Classifications

• H05B45/58

  involving end of life detection of LEDs · CPC title

• H05B47/20

  Responsive to malfunctions or to light source life; for protection · CPC title

• F21W2107/30

  for aircraft · CPC title

• F21V5/04

  of lens shape · CPC title

• F21Y2115/10

  Light-emitting diodes [LED] · CPC title