Abstract: An aircraft exterior light unit may comprise a magnetically controlled fluid drain valve configured to expel liquid water from the light unit. The valve may include a permanent magnet configured to induce a magnetic flux circuit that generates a magnetic force configured to close the valve. The valve may be configured to open when the pressure inside the light unit exceeds the magnetic force. As the valve opens and expels the water, the pressure within the light unit may decrease, equalizing with that of the external environment. As the magnetic force generated by the magnet increases as the valve is open and the water expelled, the magnet may be configured to close the valve once more. As such, the magnet may be configured to control a self-acting fluid drain valve in an aircraft exterior light.

Abstract: A system is provided for illuminating a winglet cap of a winglet. The system includes the winglet cap, a light source, a total internal reflection (TIR) lens positioned in proximity to the light source, and a prismatic lens positioned between the light source and the winglet cap. In the system, light produced by the light source reflects off a surface of the TIR lens and passes through the prismatic lens. In the system, the prismatic lens bends the light and directs the bent light toward an inside surface of the winglet cap.

Abstract: A system is provided for illuminating a winglet cap of a winglet. The system includes the winglet cap, a light source, a total internal reflection (TIR) lens positioned in proximity to the light source, and a prismatic lens positioned between the light source and the winglet cap. In the system, light produced by the light source reflects off a surface of the TIR lens and passes through the prismatic lens. In the system, the prismatic lens bends the light and directs the bent light toward an inside surface of the winglet cap.

Abstract: An aircraft light unit is disclosed herein. The aircraft light unit includes a housing having a first side and an opposing second side, a light coupled to the first side of the housing, a circuit board assembly coupled to second side of the housing, a thermoelectric cooler coupled to the circuit board assembly and configured to dissipated heat from the circuit board assembly, and a heat sink disposed over the thermoelectric cooler and configured to dissipate heat from the thermoelectric cooler.

Abstract: An aircraft exterior light unit may comprise a magnetically controlled fluid drain valve configured to expel liquid water from the light unit. The valve may include a permanent magnet configured to induce a magnetic flux circuit that generates a magnetic force configured to close the valve. The valve may be configured to open when the pressure inside the light unit exceeds the magnetic force. As the valve opens and expels the water, the pressure within the light unit may decrease, equalizing with that of the external environment. As the magnetic force generated by the magnet increases as the valve is open and the water expelled, the magnet may be configured to close the valve once more. As such, the magnet may be configured to control a self-acting fluid drain valve in an aircraft exterior light.

Abstract: An exterior aircraft light unit according to exemplary embodiments of the invention comprises: a housing including a mounting portion, which is configured for mounting the aircraft light unit to an aircraft; at least one light source; and a heat sink; wherein the heat sink comprises: a first heat sink portion comprising a plurality of cooling ribs being thermally connected with the at least one light source for transferring heat from the at least one light source to the plurality of cooling ribs; and at least one second heat sink portion comprising two heat sink plates and a clamping pin and being configured such that the second heat sink portion is selectively attachable, particularly clampable, to a respective cooling rib of the first heat sink portion.

Abstract: An exterior aircraft light unit according to exemplary embodiments of the invention comprises: a housing including a mounting portion, which is configured for mounting the aircraft light unit to an aircraft; at least one light source; and a heat sink; wherein the heat sink comprises: a first heat sink portion comprising a plurality of cooling ribs being thermally connected with the at least one light source for transferring heat from the at least one light source to the plurality of cooling ribs; and at least one second heat sink portion comprising two heat sink plates and a clamping pin and being configured such that the second heat sink portion is selectively attachable, particularly clampable, to a respective cooling rib of the first heat sink portion.

Abstract: A nano-based device includes a support structure providing a support surface, a second structure providing a second surface angled with respect to the support surface, and at least one nano-emitter provided on the second surface.

Abstract: A nano-based device includes a support structure providing a support surface, a second structure providing a second surface angled with respect to the support surface, and at least one nano-emitter provided on the second surface.