# US 12,760,883 B2 · Aircraft tail light, aircraft comprising an aircraft tail light, and method of operating an aircraft tail light > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,760,883 B2 - Document ID: US12760883B2 - Status: Granted - Kind: B2 - Application number: 19/270,205 - Filed: 2025-07-15 - Published: 2026-01-22 - Granted: 2026-10-13 - Earliest claimed: 2024-07-18 - Assignees: Goodrich Lighting Systems GmbH - Applicants: Goodrich Lighting Systems GmbH & Co. KG - Inventors: Anil Kumar Jha; Andre Hessling von Heimendahl; Marion Depta - Web page: https://patentgrep.com/patent/US12760883B2 ## CPC - F21V 29/50: Cooling arrangements (air-treatment systems dissipating or using the heat of lighting fixtures F24F3/056) - B64D 45/00: Aircraft indicators or protectors not otherwise provided for - B64D 47/06: for indicating aircraft presence - B64D 2203/00: Aircraft or airfield lights using LEDs - F21W 2107/30: for aircraft - F21V: FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F21W: INDEXING SCHEME ASSOCIATED WITH SUBCLASSES F21K, F21L, F21S and F21V, RELATING TO USES OR APPLICATIONS OF LIGHTING DEVICES OR SYSTEMS ## Abstract An aircraft tail light for being installed adjacent a hot gas exhaust of an aircraft comprises: at least one light source for generating a light output of the aircraft tail light and a heat transfer structure. The at least one light source is arranged in an aircraft exterior portion of the aircraft tail light. The heat transfer structure comprises a heat receiving portion, thermally coupled with the at least one light source for absorbing heat (H) from the at least one light source, and a heat dispensing portion for dispensing heat (H) from the heat transfer structure. The heat transfer structure extends from the aircraft exterior portion of the aircraft tail light to an aircraft interior portion of the aircraft tail light. ## Claims ### Claim 1 An aircraft tail light for being installed adjacent a hot gas exhaust of an aircraft, the aircraft tail light comprising: at least one light source for generating a light output of the aircraft tail light; and a heat transfer structure comprising a heat receiving portion, thermally coupled with the at least one light source for absorbing heat (H) from the at least one light source, and a heat dispensing portion for dispensing heat (H) from the heat transfer structure; wherein the at least one light source is arranged in an aircraft exterior portion of the aircraft tail light and wherein the heat transfer structure extends from the aircraft exterior portion of the aircraft tail light to an aircraft interior portion of the aircraft tail light, with the heat receiving portion being arranged in the aircraft exterior portion of the aircraft tail light and the heat dispensing portion being arranged in the aircraft interior portion of the aircraft tail light, and wherein the heat transfer structure comprises a plurality of heat transfer ribs extending at least partially into the aircraft exterior portion and at least partially into the aircraft interior portion of the aircraft tail light. ### Claim 2 (depends on 1) The aircraft tail light according to claim 1, further comprising: a mounting structure for fixing the aircraft tail light to an aircraft skin of the aircraft; wherein the mounting structure is configured to fix the aircraft tail light to the aircraft skin with the aircraft exterior portion on an outside of the aircraft skin and with the aircraft interior portion on an inside of the aircraft skin. ### Claim 3 (depends on 1) The aircraft tail light according to claim 1, configured to be installed adjacent the hot gas exhaust of the aircraft with the aircraft interior portion being arranged in an auxiliary power unit bay of the aircraft. ### Claim 4 (depends on 1) The aircraft tail light according to claim 1, wherein the heat dispensing portion is configured for dispensing the heat (H) to an air flow (A), passing the heat dispensing portion within the aircraft. ### Claim 5 (depends on 1) The aircraft tail light according to claim 1, further comprising a mounting portion configured to be attached to a skin of the aircraft, wherein the plurality of heat transfer ribs extend at least partially between the mounting portion and the at least one light source. ### Claim 6 (depends on 1) The aircraft tail light according to claim 1, further comprising a thermal shield for shielding the at least one light source from heat from the hot gas exhaust, to which the aircraft tail light is exposed. ### Claim 7 (depends on 6) The aircraft tail light according to claim 6, wherein the thermal shield comprises a hot mirror, which is reflective for infrared radiation, wherein the hot mirror is in particular substantially more reflective for infrared radiation than for visible light. ### Claim 8 (depends on 6) The aircraft tail light according to claim 6, wherein the aircraft tail light comprises a support structure for supporting the thermal shield, and/or wherein the thermal shield has a flat shape. ### Claim 9 (depends on 6) The aircraft tail light according to claim 6, wherein the aircraft tail light comprises at least one optical element for forming the light output of the aircraft tail light from light emitted by the at least one light source, and wherein the thermal shield is arranged between the at least one optical element and the at least one light source and/or wherein the thermal shield is provided as a reflective layer or coating applied to the at least one optical element, wherein the reflective layer or coating is in particular applied to a surface of the at least one optical element facing the at least one light source. ### Claim 10 (depends on 1) The aircraft tail light according to claim 1, wherein the aircraft tail light comprises a protective cover, which is at least partially formed from a thermally insulating material; wherein the thermally insulating material in particular comprises at least one of PES, PPS, PPSU and PEEK/PEKK. ### Claim 11 (depends on 1) The aircraft tail light according to claim 1, wherein the aircraft tail light is one of an aircraft navigation light, an aircraft anti-collision light, and a combined aircraft navigation and anti-collision light. ### Claim 12 (depends on 1) An aircraft comprising: a hot gas exhaust for discharging hot exhaust gases from the aircraft; an aircraft tail light according to claim 1, installed adjacent the hot gas exhaust, such as to be exposed to hot exhaust gases discharged through the hot gas exhaust; wherein the aircraft tail light is mounted to the aircraft with the heat dispensing portion of the heat transfer structure being arranged in a cavity formed within the aircraft. ### Claim 13 (depends on 12) The aircraft according to claim 12, comprising an auxiliary power unit, wherein the hot gas exhaust is an exhaust of the auxiliary power unit, and wherein the cavity is an auxiliary power unit bay, housing the auxiliary power unit. ### Claim 14 (depends on 12) The aircraft according to claim 12, wherein the cavity is configured such that an air flow (A), in particular a thermally driven air flow (A), passes by the heat dispensing portion of the heat transfer structure; wherein the air flow (A) in particular has a temperature in the range of between 50° C. and 90° C., more particularly a temperature in the range of between 60° C. and 80° C., even more particularly a temperature in the range of between 65° C. and 75° C. ### Claim 15 (depends on 1) A method of operating the aircraft tail light according to claim 1, wherein the method includes: operating the at least one light source for generating the light output of the aircraft tail light; and passing an air flow (A) through a cavity, formed within the aircraft, for dissipating heat (H) from the heat dispensing portion of the heat transfer structure; wherein the air flow (A) has in particular a temperature in the range of between 50° C. and 90° C., more particularly a temperature in the range of between 60° C. and 80° C., even more particularly a temperature in the range of between 65° C. and 75° C. ### Claim 16 (depends on 1) The aircraft tail light according to claim 1, wherein each rib of the plurality of heat transfer ribs extends at least partially into the aircraft exterior portion and at least partially into the aircraft interior portion.