US 11,851,208 B2
Aircraft anti-collision light, aircraft comprising an aircraft anti-collision light, and method of operating an aircraft anti-collision light
Marion Depta, Lippstadt (DE); Carsten Pawliczek, Lippstadt (DE); Andreas Ueberschaer, Guetersloh (DE); and Bjoern Schallenberg, Geseke (DE)
Assigned to GOODRICH LIGHTING SYSTEMS GMBH & CO. KG, Lippstadt (DE)
Filed by Goodrich Lighting Systems GmbH & Co. KG, Lippstadt (DE)
Filed on Mar. 22, 2022, as Appl. No. 17/700,772.
Claims priority of application No. 21165080 (EP), filed on Mar. 25, 2021.
Prior Publication US 2022/0306317 A1, Sep. 29, 2022
Int. Cl. B64D 47/06 (2006.01); F21V 5/00 (2018.01); F21Y 105/18 (2016.01); F21Y 113/10 (2016.01)
CPC B64D 47/06 (2013.01) [F21V 5/007 (2013.01); F21Y 2105/18 (2016.08); F21Y 2113/10 (2016.08)] 17 Claims
OG exemplary drawing
 
1. An aircraft anti-collision light comprising:
a first group of light sources arranged in a first annular configuration around an axis (A);
a second group of light sources arranged in a second annular configuration, wherein the first group of light sources is surrounded by the second group of light sources;
a first lens structure, which is configured for generating a first light output from light emitted by the first group of light sources;
a second lens structure, which is configured for generating a second light output from light emitted by the second group of light sources; and
a light transmissive cover, which is arranged over the first lens structure and the second lens structure and which passes the first light output and the second light output for emitting a total light output;
wherein the total light output has its peak light intensity (I100) in an angular range of between 80° and 90° with respect to the axis (A);
wherein the first lens structure is provided as a first lens structure ring, and
wherein the second lens structure is provided as a second lens structure ring surrounding the first lens structure ring;
wherein the light transmissive cover is shaped to form a third lens structure, which modifies the first and second light outputs for generating the total light output from the first and second light outputs;
wherein the aircraft anti-collision light has a first dimension (H) in a direction of the axis (A) and a second dimension (D) in a direction perpendicular to the axis (A);
wherein the first dimension (H) is in the range of between 5% and 15% of the second dimension (D);
wherein the first dimension (H) is in the range of between 5 mm and 15 mm; and
wherein the second dimension (D) is in the range of between 50 mm and 150 mm.