Abstract: A rotationally symmetrical anti-collision light (100, 200) for an aircraft utilizing light-emitting diodes (LEDs) is mounted to the fuselage of an aircraft. The LEDs (10, 10?, 20, 20?) may be configured in one or more concentric rings. The anti-collision light includes a reflector (30, 30?) configured to redirect the light emitted by at least one of the rings, so that the light pattern satisfies predetermined specifications.

Abstract: An aircraft rear position light device (1) has a modular configuration. The device utilizes solid-state light sources. In an exemplary embodiment, the light sources are side-emitting light-emitting diodes (LEDs) (40), which are attached to a heat sink (30). A reflector (200) is positioned next to each of the LEDs. The device further includes an outer lens (10) with an integrated cut-off shield (110) and optical treatments (120). The configuration of LEDs and reflectors, in conjunction with the cut-off shield and optical treatments, allows the emitted light to satisfy predetermined minimum and maximum angular intensity requirements. An electronics module (50) is also attached to the heat sink to connect the LEDs to a power source in the aircraft. Electronic updates may be made by replacing the electronics module.

Abstract: A system (10) and method for monitoring the operational life and/or performance of one or more light-emitting diodes (LEDs) (20) based on sensed parameters are disclosed. The remaining life of each LED may be predicted by counting the clock cycles during which the LED-based light is activated. LED current and/or temperature measurements may be used to control the clock signal and, thus, to compensate the predicted life value. Furthermore, operational characteristics of the LED-based light may be monitored based on LED current and/or voltage measurements. Such characteristics may include performance (e.g., intensity) and failure conditions (e.g., open or short circuits).

Abstract: An aircraft forward position lighting device (1) has a modular configuration, including a mounting module (20) containing solid-state light sources, e.g., light-emitting diodes (LEDs) (210, 230). The mounting module also includes reflectors 220. The pattern of light emanating from the light sources and reflectors satisfy Federal Aviation Regulations (FARs) regarding minimum light intensity. The device includes a cut-off shield module (10) configured to provide angular cut-offs to the pattern of light, so that the device satisfies FARs regarding overlap between position lights. The device may also include a base assembly module (30) that contains electronic circuitry connecting the light sources to a power source in the aircraft. Electronic updates may be performed by replacing the base assembly module.

Abstract: A lighting device (1) includes one or more diode light sources (32), which are configured to emit light into the peripheral edges of a light guide (20). The light guide (20) includes a set of diffusing elements (22) for scattering the emitted light in a plurality of directions out of the front surface of the light guide (20). The diffusing elements (22) are distributed on the light guide (20) so that the scattered light achieves a particular characteristic, e.g., improved uniformity.

Abstract: A quick attachment device for use in the repeated testing of diode light sources (30) includes a quick attachment module (10) having a fixed location with respect to a testing position (150) for the diodes (30), and a mounting assembly (20) on which each diode (30) is mounted during testing. The quick attachment module (10) includes a quick disconnect fastener and two locating pins (120a and 120b) for securing the mounting assembly (20) for testing, where the two locating pins (120a and 120b) have a locational transition fit connection with the mounting assembly (20). The mounting assembly (20) may further include a thermal-electric cooling device (260) for cooling the diode light sources (30) during testing.

Abstract: A multi-mode visible and infrared lighthead (100) for use as a landing light or searchlight. The multi-mode lighthead incorporates a modular design wherein at least one visible light source (200) and at least one infrared diode (302) are mounted into the rear sector (128) of a housing (102). Visible or infrared light is emitted out of the front sector (122) of the housing (102). Lenses (308) are installed onto the front sector (122) of the housing (102) and sealed to protect the interior of the lighthead (100) from the elements. Alternatively, and in combination, an imaging module (1), and infrared laser (400) and/or a fixed-position searchlight with rangefinder and positioning capability is provided in the multi-mode lighthead(100).

Abstract: The present invention is directed to an infrared light assembly (10, 30, 80, 90). A preferred embodiment of the light assembly (10, 30, 80, 90) may be used on aircraft or other vehicles for landing, taxi mode, or search operations. The light assembly (10, 30, 80, 90) preferably only requires about 10 to 20 watts of power. The light assembly (10, 30, 80, 90) may include a housing (12, 32, 82), a base (14, 34, 50), an IR diode (16, 36, 60), and an aspheric lens (18, 38). The base (14, 34, 50) is preferably connected to the bottom portion (22) of the housing(12, 32, 82), and the aspheric lens (18, 38) is preferably connected to the top portion (24) of the housing (12, 32, 82). The IR diode (16, 36, 60) may be mounted on the base (14, 34, 50). The housing (12, 32, 82) and the base (14, 34, 50) preferably have high thermal conductivity, and they preferably act as heat sinks.

Abstract: A lighting device (1) includes one or more diode light sources (32), which are configured to emit light into the peripheral edges of a light guide (20). The light guide (20) includes a set of diffusing elements (22) for scattering the emitted light in a plurality of directions out of the front surface of the light guide (20). The diffusing elements (22) are distributed on the light guide (20) so that the scattered light achieves a particular characteristic, e.g., improved uniformity.

Abstract: An infrared LASER diode based high intensity light (100) for use as an aircraft landing light or searchlight in conjunction with night vision imaging systems. The high intensity light (100) uses infrared LASER diodes (110) installed into a heat sink (112) for temperature stability. The infrared light emitted from the LASER diodes (110) is transmitted to an optical positioning plate (106) by optical transmission means (108). The optical positioning plate (106) combines the emissions of the individual LASER diodes (110) to a single infrared light beam, which is collimated by an aspheric lens (102).

Abstract: A dual mode visible and infrared lighthead (100) for use as a landing light or searchlight. The dual mode lighthead incorporates a modular design wherein at least one visible light source (200) and at least one infrared diode (302) are mounted into the rear sector (128) of a housing (102). Visible or infrared light is emitted out of the front sector (122) of the housing (102). Lenses (308) are installed onto the front sector (122) of housing (102) and sealed to protect the interior of the lighthead (100) from the elements.

Abstract: A multi-mode visible and infrared lighthead (100) for use as a landing light or searchlight. The multi-mode lighthead incorporates a modular design wherein at least one visible light source (200) and at least one infrared diode (302) are mounted into the rear sector (128) of a housing (102). Visible or infrared light is emitted out of the front sector (122) of the housing (102). Lenses (308) are installed onto the front sector (122) of the housing (102) and sealed to protect the interior of the lighthead (100) from the elements. Alternatively, and in combination, an imaging module (1), and infrared laser (400) and/or a fixed-position searchlight with rangefinder and positioning capability is provided in the multi-mode lighthead(100).

Abstract: An LED strobe light is disclosed. The strobe light (600) uses light emitting diodes (402) arranged about the circumference of an electrically insulative, thermally conductive disk (404) to form an LED light ring (400). LED Light rings (400) may be stacked as desired, with electrically conductive rings (502) placed between light rings (400). A control circuit (614) conditions voltage and current to a level with the LEDs and regulates the on-off timing of the LEDs.

Abstract: An LED strobe light is disclosed. The strobe light (600) uses light emitting diodes (402) arranged about the circumference of an electrically insulative, thermally conductive disk (404) to form an LED light ring (400). LED Light rings (400) may be stacked as desired, with electrically conductive rings (502) placed between light rings (400). A control circuit (614) conditions voltage and current to a level compatible with the LEDs and regulates the on-off timing of the LEDs.

Abstract: A dual mode visible and infrared lighthead (100) for use as a landing light or searchlight. The dual mode lighthead incorporates a modular design wherein at least one visible light source (200) and at least one infrared diode (302) are mounted into the rear sector (128) of a housing (102). Visible or infrared light is emitted out of the front sector (122) of the housing (102). Lenses (308) are installed onto the front sector (122) of housing (102) and sealed to protect the interior of the lighthead (100) from the elements.

Abstract: An infrared LASER diode based high intensity light (100) for use as an aircraft landing light or searchlight in conjunction with night vision imaging systems. The high intensity light (100) uses infrared LASER diodes (110) installed into a heat sink (112) for temperature stability. The infrared light emitted from the LASER diodes (110) is transmitted to an optical positioning plate (106) by optical transmission means (108). The optical positioning plate (106) combines the emissions of the individual LASER diodes (110) to a single infrared light beam, which is collimated by an aspheric lens (102).

Abstract: The present invention is directed to an infrared light assembly (10, 30, 80, 90). A preferred embodiment of the light assembly (10, 30, 80, 90) may be used on aircraft or other vehicles for landing, taxi mode, or search operations. The light assembly (10, 30, 80, 90) preferably only requires about 10 to 20 watts of power. The light assembly (10, 30, 80, 90) may include a housing (12, 32, 82), a base (14, 34, 50), an IR diode (16, 36, 60), and an aspheric lens (18, 38). The base (14, 34, 50) is preferably connected to the bottom portion (22) of the housing(12, 32, 82), and the aspheric lens (18, 38) is preferably connected to the top portion (24) of the housing (12, 32, 82). The IR diode (16, 36, 60) may be mounted on the base (14, 34, 50). The housing (12, 32, 82) and the base (14, 34, 50) preferably have high thermal conductivity, and they preferably act as heat sinks.

Abstract: An electronically controlled, programmable searchlight (1), particularly useful for mounting on helicopters. The searchlight (1) uses a digital electronic control circuit (30) in conjunction with rotary potentiometers (32), (34) to control movement of the searchlight (1). Adjustable trimpots (22) are employed to provide the searchlight (1) with preset positions, each preset position having an easily alterable operating envelope. The searchlight (1) may have light sources (50, 52) of varying type, which may also be controlled by the electronic control circuit (30).