Abstract: A helicopter search light comprises a housing with a mounting portion, which is configured to be mounted to a helicopter, a light source support arranged within the housing and at least one optical system. Each optical system includes a group of at least two light sources with different light emission characteristics, which are arranged on the light source support; and a reflector, which is movable between at least two discrete positions, each position being associated with one of the at least two light sources, with the reflector in each position only reflecting light emitted by the associated light source. The helicopter search light further comprises at least one actuator, which is configured for selectively moving the reflector between the at least two discrete positions.

Abstract: An aircraft beacon light for an aircraft wing with a foldable wing tip includes a housing, a lens cover, and at least one light source arranged between the housing and the lens cover, wherein the aircraft beacon light is configured to emit flashes of red light in operation, and wherein the housing and the lens cover are shaped to embed the aircraft beacon light into a hinge assembly coupling the foldable wing tip to a main wing portion of the aircraft wing.

Abstract: An exterior aircraft light unit includes a housing; a mounting structure, mounted to the housing and extending away from the housing substantially along a first cross-sectional plane; a lens cover, mounted to the housing, surrounding the mounting structure, and defining an inner space of the exterior aircraft light unit, with the mounting structure dividing the inner space of the exterior aircraft light unit into a first partial inner space and a second partial inner space; a plurality of anti-collision light sources, configured to emit respective sequences of warning light flashes in operation.

Abstract: An overhead aircraft passenger service unit, which is configured to be placed above the passenger seats within an aircraft cabin, comprises at least one cavity for housing at least one oxygen mask and at least one removable cover, which at least partially covers an opening of the cavity. The removable cover houses and/or supports at least one functional component.

Abstract: An exterior aircraft light unit comprises a housing, at least one light source, and a heat sink. The heat sink includes at least one first heat sink portion and at least one second heat sink portion. The at least one light source is thermal connected with the at least one first heat sink portion for transferring heat from the at least one light source to the at least one first heat sink portion; and the at least one second heat sink portion is configured to be selectively attachable to the at least one first heat sink portion.

Abstract: An exterior aircraft light for indicating a movement of a foldable wing tip between a folded up position and a laterally extended position includes a light source; and a control unit; wherein the control unit is configured to operate the light source to emit a warning light output in response to a warning light control signal indicative of the movement of the foldable wing tip.

Abstract: An aircraft light for a foldable wing tip of an aircraft includes a first lighting structure, including at least one first light source and a first optical system, with the at least one first light source and the first optical system in operation generating a first light output; a second lighting structure, including at least one second light source and a second optical system, with the at least one second light source and the second optical system in operation generating a second light output; wherein the first light output and the second light output are of the same color and wherein the first light output and the second light output are angled with respect to each other; and wherein the aircraft light is configured to control the at least one first light source and the at least one second light source depending on a wing tip orientation signal, which is indicative of an orientation of the foldable wing tip.

Abstract: An exterior aircraft light includes a housing configured to be mounted to an exterior portion of an aircraft; at least one light source mounted to the housing; a lens cover, cooperating with the housing for forming an inner space of the exterior aircraft light, with light from the at least one light source leaving the exterior aircraft light through the lens cover into an outside environment of the aircraft; and a gasket arranged between the housing and the lens cover, the gasket having at least one flap portion forming at least one check valve for fluid discharge from the inner space of the exterior aircraft light towards the outside environment of the aircraft.

Abstract: An LED light unit comprises a support portion, a light source having at least one LED, the light source being arranged on the support portion and having a source-side light intensity distribution (LISS), and a refractive optical element having an inner surface and an outer surface, with at least one of the inner surface and the outer surface being non-spherical, the refractive optical element being arranged over the light source and being attached to the support 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: An integrated aircraft lighting and display panel includes high-density arrays of micro-scale light-emitting diodes (LED) set into arrays (e.g., linear, two-dimensional, freeform) to form tiles, the LED tiles combined and interconnected to form LED panels conformable to any interior surface within an aircraft cabin. The PCB and LED arrays may be set into structural layers corresponding to overhead panels, side panels, bin panels, divider panels, doorway panels, galley and monument panels, or other interior structural panels of the aircraft. The LED arrays may be activated by an onboard video processor and local panel-level controllers to provide cabin lighting, indicate aircraft signage, display high-resolution image or video graphics, or simultaneously blend any combination thereof, either on command or in response to detected conditions.

Abstract: An aircraft may include a first pair of forward-facing flash position lamps disposed at a first wing tip, the first pair of flash position lamps comprising a first flash position lamp and a second flash position lamp, a second pair of forward-facing flash position lamps disposed at a second wing tip, the second pair of flash position lamps comprising a third flash position lamp and a fourth flash position lamp, and a controller in electronic communication with the first pair of flash position lamps, wherein at least one of the first flash position lamp and the second flash position lamp are configured to flash, while maintaining a combined intensity of the first pair of forward-facing flash position lamps above a desired intensity, to indicate a change in direction of the aircraft.

Abstract: An aircraft passenger service unit kit includes an overhead passenger service unit panel including at least one hinge pin extending along an edge portion of the overhead passenger service unit panel and an elastic fixing element for fixing the overhead passenger service unit panel to an aircraft support structure. The fixing element includes at least one first end, which is configured for rotatably connecting with the at least one hinge pin; and at least one opposing second end, which is configured for engaging with a mounting rail of the aircraft support structure. The overhead passenger service unit panel further includes a forcing element, which is configured for acting onto the fixing element generating a tension within the fixing element for securely fixing the at least one second end of the fixing element to the mounting rail.

Abstract: An integrated aircraft lighting and display panel includes high-density arrays of micro-scale light-emitting diodes (LED) set into arrays (e.g., linear, two-dimensional, freeform) to form tiles, the LED tiles combined and interconnected to form LED panels conformable to any interior surface within an aircraft cabin. The PCB and LED arrays may be set into structural layers corresponding to overhead panels, side panels, bin panels, divider panels, doorway panels, galley and monument panels, or other interior structural panels of the aircraft. The LED arrays may be activated by an onboard video processor and local panel-level controllers to provide cabin lighting, indicate aircraft signage, display high-resolution image or video graphics, or simultaneously blend any combination thereof, either on command or in response to detected conditions.

Abstract: An aircraft head light comprises: a plurality of lighting arrangements, each lighting arrangement comprising a light source and a generally parabolic reflector surrounding the respective light source. The plurality of lighting arrangements are arranged in a side-by-side relationship, with the generally parabolic reflectors of adjacent lighting arrangements having respective reflector contact sections. For at least one adjacent pair of the plurality of lighting arrangements, said adjacent pair comprising a first lighting arrangement and a second lighting arrangement the reflector contact section of the generally parabolic reflector of the first lighting arrangement is parabolic and the reflector contact section of the generally parabolic reflector of the second lighting arrangement is non-parabolic.

Abstract: A combined aircraft take-off and tower signal light unit comprises a mounting portion for mounting the combined aircraft take-off and tower signal light unit to an aircraft, wherein the mounting portion is configured for orienting a horizontal cross-sectional plane (H) of the combined aircraft take-off and tower signal light unit substantially horizontally with respect to the aircraft; and at least one light source. The combined aircraft take-off and tower signal light unit has a take-off light output, which is centered on a take-off light emission axis and which has a take-off light peak intensity, and a tower signal light output, which is centered on a tower light emission axis (B) and which has a tower light peak intensity.

Abstract: An aircraft beacon light includes a mounting plate having a central portion; a plurality of light sources arranged on the mounting plate around the central portion and facing away from the mounting plate; and a lens structure arranged over the plurality of light sources, wherein the lens structure is configured to reflect a first portion of light emitted by the plurality of light sources laterally outwards via total internal reflection; wherein the aircraft beacon light is configured to emit flashes of red light in operation.

Abstract: A cover for an exterior aircraft light includes a lens cover structure, attachable to an exterior aircraft light housing and configured to close the exterior aircraft light housing, wherein the lens cover structure has an inside and an outside and is at least partially made of transparent material; and a wear indicator, attached to the inside of the lens cover structure, the wear indicator having a contrasted pattern visible from the outside of the lens cover structure through the transparent material.

Abstract: A combined aircraft wing scan and runway turn-off light unit includes a housing for mounting the combined aircraft wing scan and runway turn-off light unit to a side portion of a fuselage of an aircraft; at least one light source; and an optical system for shaping a light emission distribution of the combined aircraft wing scan and runway turn-off light unit; wherein the light emission distribution comprises a first illumination region for illuminating a wing region of the aircraft and a second illumination region for illuminating a lateral forward airfield region.

Abstract: A lanyard assembly for an evacuation system may comprise a lanyard body and a pin housing. The lanyard body may comprise an actuator connect portion, a pin housing connect portion, and a center member extending between the actuator connect portion and the pin housing connect portion. The pin housing may be slidably coupled to the pin housing connect portion of the lanyard body.