Goodrich Lighting Systems Patente

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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The present invention is directed to a device for generating oxygen, comprising at least one oxygen source, at least one ionic liquid, and at least one metal salt, wherein the oxygen source comprises a peroxide compound, the ionic liquid is in the liquid state at least in a temperature range from -10°C to +50°C, and the metal salt has an organic and/or an inorganic anion, and comprises one single metal or two or more different metals. The present invention also relates to charge components for filling or refilling the devices, and to the use of ionic liquids as dispersants or solvents for the reaction participants.

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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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Systems and methods for deicing an aircraft landing light may include a metal mesh (212) conductor coupled to a lens (210) of a landing light (202). The systems and methods may include a power supply (418), a temperature sensor (414), a deicing control unit (416), an aircraft light having a lens (210), and a mesh (212) coupled to the lens (210). The temperature sensor (414) may be a microwave resonator sensor configured to sense the temperature of the landing light (202) and send signals to the deicing control unit (416). The signals may be configured to instruct the deicing control unit (416) to either apply an electric current to the mesh (212), or cease applying an electric current to the mesh (212), depending on the landing light temperatures. The deicing control unit (416) may receive landing pulses from a flight control system. The pulses may indicate that the aircraft is landing or has landed.

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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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An interior aircraft light (2) includes a mounting structure (10) for mounting the interior aircraft light (2) to an aircraft seat (80); a UV radiation source (14); and an optical system, configured to direct UV radiation from the UV radiation source (14) towards a floor portion (116) underneath the aircraft seat (80).

An aircraft light unit (4) includes a mounting portion (42), which is configured for mounting the light unit (4) to an aircraft (2); and at least one light source (40a, 40b), which is configured for emitting light. The light unit (4) is configured to emit at least one first output of white light into a predefined first spatial sector (10) and to emit at least one second output of white light into a predefined second spatial sector (12). The light of the at least one first output of white light comprises a first percentage of radiation having a wavelength that is shorter than a predefined threshold, and the light of the at least one second output of white light comprises a second percentage of radiation having a wavelength that is shorter than the predefined threshold, wherein the first percentage of radiation is smaller than the second percentage of radiation.

An aircraft vertical stabilizer illumination light (2), configured for being arranged in a rotatable horizontal stabilizer (102) of an aircraft (100) and for being oriented towards a vertical stabilizer (104) of the aircraft (100) for illuminating the vertical stabilizer (104), includes a LED group (4), having a plurality of LEDs; an optical system (6), having at least one optical element (8, 9), the optical system (6) being associated with the LED group (4) for shaping a light output from the light emitted by the LED group (4); an image generator (18), arranged within the aircraft vertical stabilizer illumination light (2) for being oriented towards the vertical stabilizer (104), the image generator (18) being configured to provide image data of the vertical stabilizer (104); and a controller (14), coupled to the image generator (18) for receiving the image data; wherein the controller (14) is configured to operate the aircraft vertical stabilizer illumination light (2) in a plurality of operating modes, with different sets of the plurality of LEDs being switched on in the plurality of operating modes and with different light outputs (120, 130, 140, 146) being emitted by the aircraft vertical stabilizer illumination light (2) in the plurality of operating modes, and wherein the controller (14) is configured to select a particular operating mode in response to the image data received.

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