A dual sided aircraft light assembly includes a mount structure, a plurality of first light emitters, a plurality of first optics, a plurality of second light emitters, and a plurality of second optics. The first light emitters are disposed such that, upon being energized, each emits light in a first direction that is at an acute angle relative to a reference line that extends in a reference direction. The first optics are configured to focus the light emitted from the first light emitters into a first light beam directed in the first direction. The second light emitters are disposed such that, upon being energized, each emits light in a second direction that is at an obtuse angle relative to the reference line and reference direction. The second optics focus the light emitted from the second light emitters into a second light beam directed in the second direction.

An aircraft and method of deterring avian species from the aircraft include a lighting system including a lighting assembly coupled to the exterior. The lighting assembly includes an ultraviolet (UV) light-emitting element that emits UV light outside of the aircraft.

A wingtip device 1 including an upwardly extending winglet 2 and a downwardly extending winglet 4. The downwardly extending winglet 4 is connected to the upwardly extending winglet 2 at a join 6. An aircraft light 10 is located at the join 6 between the upwardly extending winglet 2 and the downwardly extending winglet 4.

A runway-embedded flash lighting device includes, a body configured for embedding in a runway, a ceiling member with a flash emission window, a bottom cover member, a light guide member disposed in the flash emission window, and two or more flash emission windows. The light guide member is disposed in each of the flash emission windows and an inner surface of the ceiling member is provided with a site to be disposed with a LED flash light source below the flash emission window. The LED flash light source includes, an LED module, a frame-shaped attaching plate; and a lens member. The lens member is attached to a hollow portion in a frame of the frame-shaped attaching plate, and is configured to allow an emission surface of the flash emitted from the LED module to have a uniform illuminance distribution.

Stability of an unmanned aerial vehicle is sought by using a flight controller of an unmanned aerial vehicle control system for controlling flying by an unmanned aerial vehicle based on an instruction from a first operator. A determiner is used to determine whether a second operator visually recognizes the unmanned aerial vehicle based on a predetermined determination method. A switcher is used to switch, based on a result of the determination obtained by the determiner, from a first state, in which the unmanned aerial vehicle flies in accordance with an instruction from the first operator, to a second state, in which the unmanned aerial vehicle flies in accordance with an instruction from the second operator.

A navigation light system for an unmanned aerial vehicle, such as a multicopter type unmanned aerial vehicle, includes: a plurality of light emission units. E of the plurality of light emission units has a unit-specific light emission direction and is configured to provide a light output around the unit-specific light emission direction. Each of the plurality of light emission units includes a multi-color light source capable of emitting red light, green light, and white light. The plurality of light emission units are arranged to jointly provide a navigation light pattern around the unmanned aerial vehicle and wherein the light outputs of adjacent light emission units have an overlap the navigation light system is configured to operate each of the plurality of light emission units depending on a relation between a momentary flight direction of the unmanned aerial vehicle and the respective unit-specific light emission direction.

Rotorcraft lighting equipment includes a plurality of lighting devices configured to be mounted to an exterior of a rotorcraft, wherein each of the lighting devices comprises a plurality of individually controllable lighting modules which are configured for emitting light into different spatial directions; and a lighting control device configured for individually controlling the operation of the plurality of lighting modules for generating a desired light distribution of the light emitted by the plurality of lighting modules.

The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft; a cabin located within the main body and a transitional portion of the blended wing body; and a plurality of transparent panels in a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.

A method may comprise: commanding, by a processor, a lighting system to generate a first desired effect in accordance with a first spectral weighting mode; determining, by the processor, a first optimized predetermined variable within a first predetermined domain to generate the desired effect based on the first spectral weighting mode; commanding, by the processor, the lighting system to transition from the first desired effect to a second desired effect, the second desired effect in accordance with a second spectral weighting mode; and determining by the processor, a second optimized predetermined variable within a second predetermined domain to generate the second desired effect based on the second spectral weighting mode, the first optimized predetermined variable being different from the second optimized predetermined variable.