Goodrich Lighting Systems Patente

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An aircraft light (2) comprises: a support element (4), supporting at least one light source (6); an injection molded optical element (8), made of light transmissive silicone rubber; and a layer of light transmissive silicone rubber (12) arranged between at least a portion of the injection molded optical element (8) and at least a portion (4b) of the support element (4). The layer of light transmissive silicone rubber (12) provides adhesion between the injection molded optical element (8) and the support element (4).

A navigation light system (200) for an unmanned aerial vehicle (100), such as a multicopter type unmanned aerial vehicle, includes: a plurality of light emission units (20), wherein each of the plurality of light emission units (20) has a unit-specific light emission direction (24) and is configured to provide a light output (30) around the unit-specific light emission direction (24) and wherein each of the plurality of light emission units (20) includes a multi-color light source (22) capable of emitting red light, green light, and white light; wherein the plurality of light emission units (20) are arranged to jointly provide a navigation light pattern (80) around the unmanned aerial vehicle (100) and wherein the light outputs (30) of adjacent light emission units (20) have an overlap (40); and wherein the navigation light system (200) is configured to operate each of the plurality of light emission units (20) depending on a relation between a momentary flight direction (120) of the unmanned aerial vehicle (100) and the respective unit-specific light emission direction (24), with the navigation light pattern (80) around the unmanned aerial vehicle (100) providing a red sector (82), a green sector (84), and a white sector (86) in accordance with the momentary flight direction (120) of the unmanned aerial vehicle (100) and with the overlap (40) of the light outputs of adjacent light emission units at a border between the red sector (82) and the green sector (84) providing a white flight direction indicator light output (88).

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A method of determining operating conditions of an exterior aircraft light (2) comprising at least one light source (4) includes: operating the at least one light source (4) of the exterior aircraft light (2); repeatedly detecting light with a light detector (12), which is located at the exterior aircraft light (2) and configured for providing light detection values (I); determining a smallest light detection value (I<min>) provided by the light detector (12) within a first period of time, and storing said smallest light detection value (I<min>) as an element of a series of smallest light detection values (I<min>); and evaluating the light detection values (l) and the series of smallest light detection values (I<min>) for detecting erosion of an optical component (8) of the exterior aircraft light (2), for detecting the presence of ambient light (14) and/or for detecting the presence of fog and/or clouds (20) in front of the exterior aircraft light (2).

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A helicopter lighting system (30) comprises a docking station (32), configured to be mounted to a helicopter (10) and configured for allowing an unmanned aerial vehicle (100) to dock to and to separate from the docking station (32); and an unmanned aerial vehicle (100), in particular an unmanned aerial vehicle (100) of a multicopter type, configured for docking to and separating from the docking station (32), the unmanned aerial vehicle (100) including at least one lighting device (120), configured for illuminating at least one target object (300) or area (310) which is visible from the helicopter (10).

Exterior aircraft light (2) comprises a dome-shaped light transmissive cover (4), a light emission assembly (12), and an interface assembly (14). The light emission assembly (12) comprises a light emission tower portion (16), having a cover-facing end (16a) and an opposite aircraft-facing end (16b) and having a hollow channel (22) extending between the aircraft-facing end (16b) and the cover-facing end (16a), a platform portion (17), and at least one light source (18) and at least one optical element (20), arranged on the platform portion (17). The interface assembly (14) extends through the hollow channel (22) of the light emission tower portion (16) and comprises an elevated base (32), which is configured for mechanically supporting and electrically connecting an electric component (34), the electric component (34) being at least one of a data reception component, a data transmission component, and a data generation component. The interface assembly (14) further comprises at least one signal line (52), which extends from the elevated base (32) through the interface assembly (14).

An exterior aircraft light cover (10) with integrated illumination include: a mounting portion (12), configured to be mounted to an exterior aircraft light housing (3); a light transmissive pane (16), supported by the mounting portion (12), wherein the mounting portion (12) and the light transmissive pane (16) are configured to jointly close the exterior aircraft light housing (3); at least one photovoltaic device (26, 28), which is configured for generating electric energy when illuminated; at least one electric storage device (30), which is configured for storing the electric energy generated by the at least one photovoltaic device (26, 28); and at least one ancillary light source (18, 20), which is operable with electric energy supplied by at least one of the at least one photovoltaic device (26, 28) and the at least one electric storage device (30).

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An aircraft passenger cabin light (2) having an elongated shape having a longitudinal direction (L) comprises: a cabin wall illumination assembly (4), which extends along the longitudinal direction (L) of the aircraft passenger cabin light (2) and which is configured for illuminating a portion of a wall (120) of an aircraft passenger cabin (104); and a plurality of personal reading light units (12a, 12b) for providing personal reading light illumination to passengers. The plurality of personal reading light units (12a, 12b) are arranged in an array extending along the longitudinal direction (L) of the aircraft passenger cabin light (2). Said array is arranged along the cabin wall illumination assembly (4).

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An aircraft light (2) comprises a support board (4) and a supporting profile (10). The support board (4) supports at least one electric light source (6), in particular at least one LED. The support board (4) has two lateral edges (5a, 5b), which extend in a longitudinal direction of the support board (4) and which are spaced apart from each other in a transverse direction (T) of the support board (4). The supporting profile (10) comprises a receiving space (12) for receiving and supporting the support board (4). The receiving space (12) is defined by a base (14), extending in a longitudinal direction (L) of the supporting profile (10) and in a transverse direction (T) of the supporting profile (10), and two opposing side walls (16a, 16b) protruding from the base (14). The supporting profile (10) further comprises two undercut sections (20a, 20b), forming opposing slots in the two opposing side walls (16a, 16b) that are dimensioned for accommodating a lateral edge (5a, 5b) of the support board (4), respectively. At least one of the two lateral edges (5a, 5b) of the support board (4) comprises at least one spring element (9) for elastically fixing the support board (4) within the receiving space (12), with the two lateral edges (5a, 5b) of the support board (4) being arranged in opposing slots.

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An aircraft passenger reading light (2), comprises a light source arrangement having a plurality of rows (61, 62, 63) of reading light sources (6), with each of the rows (61, 62, 63) having a plurality of reading light sources (6) for passenger-specific illumination of a plurality of seats (80a, 80b, 80c) of a seating row of an aircraft (100) and with the plurality of rows (61, 62, 63) having different illumination directions in a longitudinal direction (L) of the aircraft (100), wherein each of the plurality of reading light sources (6) comprises a first electrical terminal (7) and a second electrical terminal (9); a first power supply connector (22) and a second power supply connector (24) for coupling the aircraft passenger reading light (2) to an aircraft on-board power supply (21); and a multi-state switching arrangement (20) having a plurality of switching states. The first power supply connector (22) is coupled to the first electrical terminals (7) of the plurality of reading light sources (6). The second power supply connector (24) is coupled to the second electrical terminals (9) of the plurality of reading light sources (6) via the multi-state switching arrangement (20), with each of the plurality of switching states permanently coupling the second electrical terminals (9) of the reading light sources (6) of a single one of the plurality of rows (61, 62, 63) to the second power supply connector (24) and permanently decoupling the second electrical terminals (9) of the reading light sources (6) of the other rows (61, 62, 63) from the second power supply connector (24).

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A combined aircraft navigation and anti-collision light (2), includes: at least one navigation light source (22); a navigation light sensor (30), in operation outputting a light detection signal (38) corresponding to an amount of light detected by the navigation light sensor (30); a first optical system (24), associated with the at least one navigation light source (22), wherein the first optical system (24) is configured for shaping a navigation light output from light emitted by the at least one navigation light source (22) and is configured for directing stray light from the at least one navigation light source to the navigation light sensor (30); at least one anti-collision light source (42); a second optical system (44), associated with the at least one anti-collision light source (42) and configured for shaping an anti-collision light output from light emitted by the at least one anti-collision light source (42); a lens cover (60), arranged over the at least one navigation light source (22), the first optical system (24), the at least one anti-collision light source (42), and the second optical system (44) for passing the navigation light output and the anti-collision light output therethrough, wherein the navigation light sensor (30) is arranged with respect to the lens cover (60) to detect light emitted by the at least one anti-collision light source (42) and diffusely reflected by the lens cover (60); and a controller (62), coupled to the navigation light sensor (30) and configured to determine a state of erosion of the lens cover (60) from a pulsed signal component of the light detection signal (38).

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