Abstract: A dual mode light assembly for a forward position light of an aircraft includes a base, a visible light source mounted to the base that is configured to emit visible light, a covert light source mounted to the base that is configured to emit covert light, and a light shield mounted to the base. The light shield is configured to restrict transmission of the visible light to a visible light pattern and to restrict transmission of the covert light to a covert light pattern.

Abstract: A light source includes a circular light element having a light source diameter, and a reflector disposed at least partially within the circular light element, the reflector having a first end with a first diameter and a second end with a second diameter, wherein the first diameter is less than the light source diameter and the second diameter is larger than the light source diameter, the second end having a plurality of slits.

Abstract: A device for projecting an image on a projector module screen, comprising an interchangeable disc including at least one image disposed thereon and a light source for illuminating the at least one image. The device further includes a lens for receiving the at least one image from the interchangeable disc and passing the image to the projector module screen, wherein the projector module screen displays the image and a projector module housing enclosing the interchangeable disc, the light source, and the lens.

Abstract: A system and method for estimating a distance between an aircraft and an object is disclosed. An exterior light of the aircraft transmit a test light signal and a parameter the transmitted test light signal is measured. A sensor receives a reflection of the test light signal from the object and the parameter is measured for the reflection test signal. The distance between the aircraft and the object is estimated using the parameter of the reflection and the parameter of the test light signal. The exterior light is generally a light that is built into the aircraft during aircraft construction while the sensor is retrofitted onto the aircraft.

Abstract: A dual mode light assembly for a forward position light of an aircraft includes a base, a visible light source mounted to the base that is configured to emit visible light, a covert light source mounted to the base that is configured to emit covert light, and a light shield mounted to the base. The light shield is configured to restrict transmission of the visible light to a visible light pattern and to restrict transmission of the covert light to a covert light pattern.

Abstract: In a lighting system that emits light of a color within a color specification, the color is controlled by adding light from a single color-correcting light emitting device (light-emitting device) to a primary light-emitting device. In an illustrative embodiment, a color-detecting module can sense the color of the combined light emitted from both the primary and the color-correcting light-emitting devices. The color-control system can generate an amplitude control signal based on a signal indicative of the color sensed by the color-detecting module. A color range of the combined light of the primary and the color-correcting light-emitting devices can intersect a domain of the predetermined color specification, as the generated amplitude control signal spans the domain. Using a single color-correcting light-emitting device to maintain a lighting system's emitted color within a predetermined color specification can advantageously reduce system complexity.

Abstract: An LED light system for an aircraft may comprise a first LED lamp having a first LED array. The first LED array may include at least a first LED and a second LED. A first optical element may be configured to direct light emitted from the first LED in a first beam centered around a first angle and to direct light emitted from the second LED in a second beam centered around a second angle. The LED light system may further comprise a second LED lamp having a second LED array. The second LED array may include at least a third LED and a fourth LED. A second optical element may be configured to direct light emitted from the third LED in a third beam centered around the first angle and to direct light emitted from the fourth LED in a fourth beam centered around the second angle.

Abstract: A device for forming a dynamic image on an aircraft sign includes a plurality of light sources, an input power line, a first timer and a second timer both connected to an enable input and a plurality of delay circuits each connected to a different one of the light sources. The system also includes a counter having a plurality of counter outputs, the counter receiving a counting pulse from the first timer in a dynamic mode of operation and disable signal from the second timer after expiration of a preset time, the expiration of the preset time causing the device to transfer from the dynamic mode to a static mode where each of the plurality of light sources are simultaneously illuminated.

Abstract: A dual mode light assembly for a forward position light of an aircraft includes a base, a visible light source mounted to the base that is configured to emit visible light, a covert light source mounted to the base that is configured to emit covert light, and a light shield mounted to the base. The light shield is configured to restrict transmission of the visible light to a visible light pattern and to restrict transmission of the covert light to a covert light pattern.

Abstract: Light systems having an array of paired visible-light and infrared-light elements, each pair arranged such that a body of each visible-light element obstructs infrared-light emitted from its paired infrared-light element. A lens might be provided to cover the array of paired light elements.

Abstract: A dual-color aviation Anti Collision Light (ACL) has a first set of LEDs that emit a substantially white beam of light and a second set of LEDs that emit a substantially red beam of light. The ACL can be operated in a first mode in which the red LEDs are excited by themselves so that the ACL produces a red beam of light In a second mode, the white LEDs and the red LEDs are excited simultaneously to produce a white beam of light having a chromaticity within the definition of Aviation White. Operating the red LEDs in the white mode has two synergistic effects. First, the red LEDs augment the luminous output of the white LEDs so that fewer white LEDs are required, thus saving cost and space. Second, the red LEDs shift the chromaticity of total light output toward the red region. This has the effect of compensating for the tendency of the white LEDs to become greener with age.

Abstract: A dual-color aviation Anti Collision Light (ACL) has a first set of LEDs that emit a substantially white beam of light and a second set of LEDs that emit a substantially red beam of light. The ACL can be operated in a first mode in which the red LEDs are excited by themselves so that the ACL produces a red beam of light In a second mode, the white LEDs and the red LEDs are excited simultaneously to produce a white beam of light having a chromaticity within the definition of Aviation White. Operating the red LEDs in the white mode has two synergistic effects. First, the red LEDs augment the luminous output of the white LEDs so that fewer white LEDs are required, thus saving cost and space. Second, the red LEDs shift the chromaticity of total light output toward the red region. This has the effect of compensating for the tendency of the white LEDs to become greener with age.

Abstract: An aircraft light, particularly for emitting light onto a runway during takeoff or landing and/or onto the ground during taxi, comprises a light source (30), a reflector (12), a support frame (18) for the reflector (12), and an adjustable bearing arrangement (20) including at least two joints (22) pivotably supporting the reflector (12). The adjustable bearing arrangement (20) comprises at least one extendable and retractable adjustment element (24) guided at the support frame (18) along a movement axis (26). At least one of the two joints (22) is formed as a ball-type joint. The ball-type joint (22), to compensate for a change of the distance (A,A?) between the at least two joints (22) of the bearing arrangement (20) upon movement of the adjustment elements (24) for tilting the reflector (12), slidably engages the reflector substantially orthogonal to the movement axis (26) of the adjustment element.

Abstract: A dual-color aviation Anti Collision Light (ACL) has a first set of LEDs that emit a substantially white beam of light and a second set of LEDs that emit a substantially red beam of light. The ACL can be operated in a first mode in which the red LEDs are excited by themselves so that the ACL produces a red beam of light In a second mode, the white LEDs and the red LEDs are excited simultaneously to produce a white beam of light having a chromaticity within the definition of Aviation White. Operating the red LEDs in the white mode has two synergistic effects. First, the red LEDs augment the luminous output of the white LEDs so that fewer white LEDs are required, thus saving cost and space. Second, the red LEDs shift the chromaticity of total light output toward the red region. This has the effect of compensating for the tendency of the white LEDs to become greener with age.

Abstract: An aircraft light, particularly for emitting light onto a runway during takeoff or landing and/or onto the ground during taxi, comprises a light source (30), a reflector (12), a support frame (18) for the reflector (12), and an adjustable bearing arrangement (20) including at least two joints (22) pivotably supporting the reflector (12). The adjustable bearing arrangement (20) comprises at least one extendable and retractable adjustment element (24) guided at the support frame (18) along a movement axis (26). At least one of the two joints (22) is formed as a ball-type joint. The ball-type joint (22), to compensate for a change of the distance (A,A?) between the at least two joints (22) of the bearing arrangement (20) upon movement of the adjustment elements (24) for tilting the reflector (12), slidably engages the reflector substantially orthogonal to the movement axis (26) of the adjustment element.

Abstract: A wireless communications system suitable for use within an aircraft, such as a part of a wireless emergency lighting system (WELS) is provided. In an aircraft, EXIT signs are located throughout the interior of the aircraft, including the ceiling (general illumination), seats (floor proximity) and EXIT doors (locator/identifier). A wireless communications system uses an integrated lens antenna system that takes advantage of the quantity and location of emergency lights such that any given light will have a direct radio frequency (RF) path to several other lights. A virtual network can be created such that if the path between any two lights becomes disrupted, alternate paths will be constructed under software control.

Abstract: A system for enabling successful use of HID lamps in aircraft, including in particular high power lamps for use as landing lights and taxi lights, utilizes a sealed beam HID lamp which during normal operation has an external temperature considerably lower than the external temperature of a quartz halogen or incandescent sealed beam lamp of equivalent light output. The lower external temperature arises in part from the use of a gas fill in the sealed beam. A detector is provided to monitor the seal integrity of the sealed beam HID lamp and further to provide a response to seal failure resulting in disablement of the lamp. Exemplary ways for accomplishing seal failure detection include radioactive detection, pressure monitoring, and chemical sensing, or other ways wherein detection of a failed seal is followed by an electrical output used to terminate or preclude lamp operation.

Abstract: A recognition light includes a reflector having an axis and first and second annular semi-parabolic reflective surfaces which have respective focal points axially spaced apart from one another, and first and second annular lamps respectively disposed at the focal points. A cover surrounds the reflector and lamps and includes a lens for focusing the light along a plane perpendicular to the axis of the reflector, the lens including first and second Fresnel lens portions each including a convex lens and a prism lens, the convex lenses being disposed adjacent one another and transaxially aligned with the first and second lamps, respectively. A light detector detects light emitted from at least one of the lamps, a monitor circuit provides a fail signal when a characteristic of the light output of at least one of the lamps does not satisfy a specified criteria, and a control circuit first activates the first lamp and then the second lamp in response to receipt of the fail signal of the monitor circuit.