Aircraft beacon light and aircraft comprising the same

Patent metadata

Field	Value
Publication number	US-11072437-B2
Application number	US-201816168861-A
Country	US
Kind code	B2
Filing date	Oct 24, 2018
Priority date	Oct 24, 2017
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

An aircraft beacon light is provided for emitting flashes of red light into an environment around an aircraft. The aircraft beacon light includes a support plate having a central portion; a plurality of LEDs, arranged on the support plate around the central portion and facing away from the support plate; an annular light splitting element, having a proximate side arranged over and facing the plurality of LEDs, wherein the proximate side has reflective portions and transmissive portions; and at least one light conditioning element for redirecting light having passed through the transmissive portions of the proximate side of the annular light splitting element.

First claim

The invention claimed is:

1. An aircraft beacon light for emitting flashes of red light into an environment around an aircraft, comprising:
a support plate having a central portion;
a plurality of LEDs, arranged on the support plate around the central portion and facing away from the support plate;
an annular light splitting element, having a proximate side arranged over and facing the plurality of LEDs, wherein the proximate side has reflective portions and transmissive portions,
wherein the annular light splitting element is rotationally symmetric around an axis of rotation,
wherein the reflective portions of the proximate side of the annular light splitting element are metallized portions of the annular light splitting element and wherein the transmissive portions of the proximate side of the annular light splitting element are non-metallized dots of the annular light splitting element, and
wherein the non-metallized dots of the annular light splitting element are arranged in a regular pattern and increase in size for an increase in distance with respect to the axis of rotation; and
at least one light conditioning element for redirecting light having passed through the transmissive portions of the proximate side of the annular light splitting element.

2. The aircraft beacon light according to claim 1 , wherein the plurality of LEDs are arranged on the support plate in a substantially circular arrangement.

3. The aircraft beacon light according to claim 1 , wherein the reflective portions of the proximate side of the annular light splitting element are shaped to reflect light from the plurality of LEDs towards light output directions parallel to the support plate.

4. The aircraft beacon light according to claim 1 , wherein the proximate side of the annular light splitting element has, in cross-section, a first substantially parabolic light collimation section, with light reflected from the first substantially parabolic light collimation section in particular being collimated substantially parallel to the support plate.

5. The aircraft beacon light according to claim 4 , wherein the proximate side of the annular light splitting element has, in cross-section, a second substantially parabolic light collimation section, with light reflected from the second substantially parabolic light collimation section in particular having an angle of between 5° and 15° with respect to the support plate.

6. The aircraft beacon light according to claim 5 , wherein the at least one light conditioning element comprises a refractive surface and wherein the refractive surface forms part of a distal side of the annular light splitting element.

7. The aircraft beacon light according to claim 1 , wherein the at least one light conditioning element comprises an additional reflector.

8. The aircraft beacon light according to claim 7 , wherein the additional reflector has, in cross-section, a third substantially parabolic light collimation section.

9. The aircraft beacon light according to claim 7 , further comprising:
a support arm, extending from the support plate;
wherein the additional reflector is part of or is attached to the support arm.

10. The aircraft beacon light according to claim 7 , wherein at least part of the transmissive portions of the proximate side of the annular light splitting element are arranged over the central portion of the support plate and wherein the additional reflector is arranged to reflect light having passed through the transmissive portions over the central portion of the support plate.

11. The aircraft beacon light according to claim 1 , wherein the annular light splitting element has a circumferential end that extends laterally outwards beyond the plurality of LEDs and wherein a light output direction from the plurality of LEDs to the circumferential end of the annular light splitting element has an angle (a) of between 20° and 50° with respect to the support plate.

12. The aircraft beacon light according to claim 1 , wherein the reflective portions cover between 50% and 95% of the proximate side of the annular light splitting element.

13. An aircraft comprising:
an upper aircraft beacon light in accordance with claim 1 mounted to an upper portion of a fuselage of the aircraft, and
a lower aircraft beacon light in accordance with claim 1 , mounted to a lower portion of a fuselage of the aircraft.

Assignees

• Goodrich Lighting Systems Gmbh

Inventors

• Jha Anil Kumar

Classifications

• F21S10/066

  by selectively switching fixed light sources · CPC title

• F21V7/06

  with parabolic curvature · CPC title

• F03D80/10

  Arrangements for warning air traffic · CPC title

• F21S43/14

  Light emitting diodes [LED] · CPC title

• F21V23/005

  the substrate is supporting also the light source · CPC title