A search and landing light for a vehicle includes a light emitting element having an output primarily along a first axis and a canopy surrounding the light emitting element. The search and landing light includes a housing to enclose one or more electrical components associated with the search and landing light. The housing and the canopy extend along a longitudinal axis that is substantially perpendicular to the first axis. The search and landing light includes an actuator coupled between the canopy and disposed in the housing. The actuator is disposed along the longitudinal axis and is configured to rotate the canopy relative to the housing.

An aircraft navigation light, configured to be usable as any of a left forward navigation light, a right forward navigation light, and a tail navigation light of an aircraft, comprises a common support plate which is substantially vertical in the aircraft frame of reference; a first light source arranged on the common support plate for emitting red light; a second light source arranged on the common support plate for emitting green light; a third light source arranged on the common support plate for emitting white light; a driving circuit coupled to the first light source, the second light source and the third light source and configured to supply power to a selected one of the first light source, the second light source, and the third light source; and a blocking element arranged to limit the light output of the aircraft navigation light to one lateral side.

An aircraft light (2) includes a support board (4); a light source (6), arranged on the support board (4); an optical element (8; 8′; 12; 14), arranged over the light source (6); and a kinematic coupling fixture (20), establishing a fixed position of the optical element (8; 8′; 12; 14) with respect to the support board (4).

An aircraft light (2) includes a support board (4); a light source (6), arranged on the support board (4); an optical element (8; 8′; 12; 14), arranged over the light source (6); and a kinematic coupling fixture (20), establishing a fixed position of the optical element (8; 8′; 12; 14) with respect to the support board (4).

A method for controlling an orientation of a searchlight on a vehicle is provided. The method comprises: obtaining a target range to a point of interest (POI) at a target; determining a searchlight position and attitude; calculating a three dimensional position at the POI using searchlight azimuth and tilt actuator angles, the target range, and the searchlight position and attitude, while a searchlight light head continues to point at the 3D target position despite changes in movement or orientation of the vehicle; calculating a desired searchlight orientation including azimuth angle and tilt angle to point the light head at the target through inverting a kinematic relationship between the vehicle and the searchlight; calculating compensatory actuator angles for a plurality of searchlight actuators to achieve the desired searchlight orientation based on error measurements calculated from a current orientation; and commanding the plurality of searchlight actuators to the compensatory actuator angles.

A de-icing light assembly may comprise: a housing; a plurality of lights coupled to the housing; a lens assembly coupled to the housing, the lens assembly comprising: a lens material; an indium tin oxide (ITO) film disposed on the lens material; and a silicon oxide coating disposed on the ITO film.

A de-icing light assembly may comprise: a housing; a plurality of lights coupled to the housing; a lens assembly coupled to the housing, the lens assembly comprising: a lens material; an indium tin oxide (ITO) film disposed on the lens material; and a silicon oxide coating disposed on the ITO film.

A helicopter search light includes a movable light head comprising: at least one light source and at least one optical element, which are configured for emitting a search light beam; at least two radiation sensors arranged in a preset distance (d) from each other. The radiation sensors are configured for detecting electromagnetic radiation and providing corresponding sensor signals. The system also includes an image processing module configured for receiving the sensor signals provided by the at least two radiation sensors and generating enhanced image data from said sensor signals and a controller configured for controlling movement of the movable light head depending on said enhanced image data.

A helicopter search light includes a movable light head comprising: at least one light source and at least one optical element, which are configured for emitting a search light beam; at least two radiation sensors arranged in a preset distance (d) from each other. The radiation sensors are configured for detecting electromagnetic radiation and providing corresponding sensor signals. The system also includes an image processing module configured for receiving the sensor signals provided by the at least two radiation sensors and generating enhanced image data from said sensor signals and a controller configured for controlling movement of the movable light head depending on said enhanced image data.

Systems and methods to combine lights and cameras are disclosed. Exemplary implementations may carry a housing that holds both a lighting component and a video camera; receive instructions to operate the lighting component in at least one of two different lighting modes, including a landing lighting mode and a taxi lighting mode; control the video camera to capture video information at a particular frame rate; and control the lighting component to emit light in a manner that supports at least one particular lighting mode and that includes switching off or turning down the lighting component in synchrony with the particular frame rate to reduce glare and/or otherwise improve the captured video information.