Abstract: A lighting system for air mobility may include a light emitting unit provided on a boom or a propeller of the air mobility and configured to emit light toward a ground surface so that the light is projected onto a point directed toward the ground surface from the propeller or the boom; and a control unit electrically connected to the light emitting unit and configured to control light emitting modes of the light, emitted by the light emitting unit, based on operating modes of the air mobility or operating modes of the propeller.

Abstract: A collision avoidance system includes a sensor adapted to detect at least one vehicle in the vicinity of a predetermined area and generate target data relating to the at least one vehicle. An awareness engine receives the target data and evaluates the target data for a threat of a collision. An alerting system is adapted to alert the at least one vehicle in the event of a threat of a collision, the alerting system being activated by the awareness engine.

Abstract: A method of aiding viewing position for autostereoscopic displays having a suggested viewing zone or optimal viewing position. The method detects a position of a viewer using a detection sensor associated with the display and determines if the viewer is within the suggested viewing zone. If the viewer is not within the suggested viewing zone, the method provides feedback to the viewer, such as visual cues on the display, indicating how the viewer should move in order to be within the suggested viewing zone. The method can continuously provide the feedback in order to indicate how the viewer is moving with respect to the suggested viewing zone and when the viewer has moved into the suggested viewing zone.

Abstract: A method and apparatus for managing a programmable control panel for a vehicle. A number of first level control functions is assigned to the programmable control panel for the vehicle. A number of second level control functions is assigned to the programmable control panel based on a health of programmable control panels in the vehicle.

Abstract: Control and monitoring of airfield lighting from a control tower and other maintenance/supervisory locations uses double loop self healing fiber optic communications circuits to enhances speed of operation even with large and complex airfield lighting system requirements, and significantly increased reliability and operating lifetime thereof. A plurality of local light control and monitoring groups are used, wherein each group has at least one fiber optic communications concentrator that independently communicates with light controllers within the group and the remote supervisory control and monitoring systems in the control tower and other locations. This allows faster control response of the lamps in each of the airfield light fixtures, and monitoring concentration of operational data within each group.

Abstract: The present invention consists of a device especially configured for enabling locating an aircraft quickly which due to an accident has fallen in an area where the search for the remains is especially difficult, such as the sea or mountainous areas. It is made up of a container (1) with an automated lock (7) divided internally into two chambers (2 and 3) in which metal sheets (4) and hollow spheres (5) are introduced; an attached beacon (6), a memory circuit (14); and it is operated by means of an automated control. All these elements form an assembly as a result of a protective and waterproof shell (8) joining them together. It also has an anchor (10) joining it to the outer part of the aircraft where it is arranged, which allows automating the release of the device as the result of a signal indicating the imminence of an accident.

Abstract: An arrangement for cross monitoring two independent signals. The arrangement a calculator configured to calculate a value depending upon a signal value, a drift value and a feedback value, and a determining unit configured to determine a larger of the calculated value and a first predetermined value. The arrangement also includes a comparing unit configured to compared the determine larger value with a second predetermined value and a delaying unit configured to delay the determined larger value and change status of the larger value to become an updated feedback value to be provided to the calculator. The arrangement is characterized in that the signal value includes information about an absolute value of a difference between the two independent generated signals.

Abstract: A system for preventing light pollution includes one or more radar units that monitor for vehicles in a volume surrounding or containing one or more obstructions having one or more obstruction lights. A master radar detection processing unit receives sensed radar detection information from the one or more radar units with associated radar signal processing units and determines whether a vehicle is present within the monitored volume. A plurality of obstruction light controller units are interconnected in a network, such as a wireless network. Each obstruction light controller unit turns on an obstruction light when a vehicle enters the monitored volume or a failure condition exists, and turns off the obstruction light when the vehicle has vacated the monitored volume and no failure condition exists. The one or more radar units can transmit sensed radar detection information to a master radar detection processing unit via the network.

Abstract: A safety light apparatus includes a first light source to emit a first light beam and a first light modulator to modulate the first light beam to project a first light image resembling a left boundary of a bike lane. A second light source emits a second light beam, and a second light modulator modulates the second light beam to project a second light image resembling a right boundary of a bike lane. A housing supports the first and second light sources and the first and second light modulators. A mounting device is provided for mounting the housing to a bicycle.

Abstract: In a method for aiding aircraft landing using a GPS and an MLS within the context of a computed axial approach, the method uses coordinates of an azimuth antenna and/or of an elevation antenna as a reference point for the computation of a position of the aircraft in a reference frame centered on the landing runway. This position of the aircraft is thereafter used to determine an angle of azimuth between a longitudinal axis of the landing runway and the aircraft.

Abstract: Disclosed is a method and device, which provide an enhanced ability to monitor the navigation of an aircraft during a phase of flight in which the aircraft is close to the ground in which the aircraft uses positional information supplied by a satellite positioning system for the navigation. A display screen is used to display a first characteristic sign representing a selected setpoint value for a height parameter of the aircraft. The display screen also displays a second characteristic sign representing a current auxiliary value expressed in the form of an achievable height parameter. An alert is emitted when the second characteristic sign is determined to be within a predetermined height value of the first characteristic sign, and the alert is shown in visual format on the display screen. An alarm is also emitted following a predetermined time after the alert is emitted, if the setpoint value is not replaced by a new setpoint value.

Abstract: The device (1) comprises means (5) for calculating a controlled speed enabling the aircraft to observe a longitudinal separation relative to an aircraft of the convoy that precedes it.

Abstract: Systems and methods for anti-collision lights on a UAV. A method for passive anti-collision lights on a Micro-Aerial Vehicle (“MAV”) including determining a location of the MAV using a flight management computer configured to fly the MAV on a programmed path using data from a global positioning system and an inertial navigation system. The flight management system transmits light activation data and selectively activates at least one navigation light located on a visible surface of the MAV using the light activation data from the flight management computer.

Abstract: The invention provides a sensor for determining when a latch for securing an engine cowl on an aircraft is secured by detecting the proximity of a latch hook and a latch pin. The sensor includes a resonant circuit configured and adapted to transmit a status signal when the latch is in a secured state. The sensor also includes a means for conveying status information of the latch to a location remote from the latch based on the status signal, the conveying means being operably connected to the resonant circuit. The invention also provides a method of determining when a latch is open or secured by detecting the proximity of a latch hook and a latch pin.

Abstract: The present invention relates to an emergency assistance beacon signal methodology for law enforcement, emergency and military personnel by which such personnel who encounter an imminent need for assistance or rescue while on duty in a vehicle, may utilize such methodology to invite the assistance or rescue of other such personnel. Upon a first personnel determining that assistance or rescue is needed, the first personnel activate a powerful light element attached to a such that the powerful light directs a beam of light upwardly and non-horizontally from the vehicle. Upon a second personnel recognizing the beam of light, travels to a general area of the beam of light to locate the first and provides first personnel assistance or rescue.

Abstract: An aircraft communications system is located on an aircraft. The aircraft communications system comprises a set of eyewear units, an aircraft data processing system, and a wireless system. Each eyewear unit has a set of sensors and a display. The set of eyewear units is capable of receiving user input and is capable of presenting information to a set of users of the set of eyewear units. The aircraft data processing system is capable of receiving the user input and sending the information to the set of eyewear units in response to receiving the user input from the set of eyewear units. The wireless system is located proximate to the cabin of the aircraft and is capable of sending the user input from the set of eyewear units to the aircraft data processing system and sending the information to the set of eyewear units.

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: According to a first broad aspect of the present invention, there is provided a method and system for indicating a status of a subsystem controlled by a switch provided on a steering wheel of a marine vehicle. The method and system comprise: providing a switch for the subsystem on the steering wheel of the marine vehicle; providing a status indicator for the switch; detecting an activation of the switch; transmitting a command to the subsystem in the marine vehicle in response to the activation; detecting an operation status of the subsystem in response to the command; and activating the status indicator to indicate information of the operation status.

Abstract: A group multiplexed output (208) operably couples to each unique intermediate frequency received signal output as corresponds to a plurality of aviation radio frequency receiver front ends (502). By one approach, this can comprise, in particular, multiplexing, in frequency, each of the discrete received signal outputs for each of the plurality of aviation radio frequency receiver front ends with one another. By one approach, each such aviation radio frequency receiver front end is configured and arranged to receive radio frequency signals for a corresponding different radio frequency platform (as may each correspond, for example, to a different aviation operational purpose).

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 helmet mounted tracking system for target designation includes an airplane azimuth sensor, a helmet mounted azimuth sensor, an airplane pitch sensor, a helmet mounted pitch sensor, and a processor. The airplane azimuth sensor determines an azimuth heading for an airplane. The helmet mounted azimuth sensor determines an azimuth heading for a helmet that is worn by a pilot. The airplane pitch sensor determines a pitch for the airplane. The helmet mounted pitch sensor determines a pitch for the helmet that is worn by the pilot. The processor is in operative communication with the airplane azimuth sensor, the helmet mounted azimuth sensor, the airplane pitch sensor, and the helmet mounted pitch sensor and the processor is processes instructions from each of the sensors to determine a target pitch and a target azimuth.

Abstract: a plurality of bi-color lights is mounted to the stern of a ship such as an aircraft carrier. The lights are arranged so that they are visible from an escort ship that is following the aircraft carrier while attempting to maintain a selected range and angular position relative to the aircraft carrier. The lights are arranged such that the number of lights of each color that are visible from the escort ship depends upon the angular position of the escort ship relative to the aircraft carrier.

Abstract: An apparatus for a portable aircraft landing light system. The system has three modalities that can be controlled manually or remotely. The modalities are visible light, infrared light and FLIR emission. A ballast and battery provide constant power supply to each of the three modalities.

Abstract: A dual mode light source unit is configured so that it can be secured into a conventional incandescent bulb socket on the aircraft. The light source has a connector portion that fits in the socket and receives the electrical current supplied thereto by the aircraft electrical system. The unit also comprises electric circuitry connected with the connector portion and a visible light source and an IR light source. The electric circuitry processes the input current from the socket and, based thereon, operates in either a civilian, visible mode or a covert IR mode. Where the current is in one electrical state, such as for example a certain voltage, the electric circuit sends power to the visible light source. When the current is in a different electrical state, e.g., a different voltage level, the circuitry sends power only to the IR source, and no visible light is emitted.

Abstract: A light source in the form of a light emitting diode (LED) cluster module suitable for use as an aircraft forward position light source. The light source comprises multiple LED components mounted on a base structure together with supporting electronic components to regulate the function of the LED components. The LED components are configured on the base structure in a manner so as to be capable of complying with the Federal Aviation Regulations minimum light intensities or candela requirements and color specifications while in a preferred implementation using a traditional aircraft 28-volt power supply. Furthermore, the preferred implementations are capable of meeting stringent dimensional design criteria and therefore are suitably adaptable as replacement light sources for existing aircraft forward position light housings.

Abstract: A lamp, in particular a position lamp for a motor vehicle, has a housing in which at least one light source is arranged, with the housing having a light pane covering an opening of the housing, with the light source being structured as a plurality of light-emitting diodes. A light field formed by a plurality of similar first light-emitting diodes to produce a basic light-intensity distribution and at least one additional second light-emitting diode to produce a preferred light-intensity distribution is provided so that a predetermined total light-intensity distribution is obtained by superpositioning, or overlapping, of the basic light-intensity distribution and the preferred light-intensity distribution.

Abstract: A signal system 10 for a vessel such as an aircraft, incorporates nodes 16A, B, C arranged in a hierarchy. Low level nodes 16C are associated with plant 14 of the aircraft. Mid-level nodes 16B can communicate with groups of low level nodes 16C, grouped by proximity. A top level node 16A can communicate with all mid-level nodes 16B. Decision making capability is built into nodes 16, to allow decisions to be taken at the lowest hierarchical level at which all of the necessary information is available.

Abstract: A power-line carrier airport facilities monitor system, comprising a host station and respective terminal for monitoring individually the object facilities via a rubber transformer are connected in series to a power line derived from a fixed current generator, wherein the host station and respective terminal create a control command for respective terminal/monitoring signal of the object facilities as text data and, on the other hand, injections said text data to the power line by FSK modulation based on the zero cross detection of the power line power source waveform.

Abstract: Pose estimation of a camera is facilitated by including in the scene a space fiducial, an object that has the property that its appearance as viewed by the camera uniquely determines the direction from which it is viewed.

Abstract: Apparent object motion is created to stimulate rapid M cell response in an observer's visual system. In one embodiment, first and second pairs of lights, spaced apart about 1 to 60 minutes of visual angle at the viewing distance, are operated such that the innermost of each pair is activated for duration T1, and after a duration T2, the outermost of each pair is activated for the duration of a warning event. T1 is determined by luminous energy intensity from the innermost light pair, while duration T2 is selected to preclude an overlap in the observer's visual system between response to the end of the first-activated light, and the response commencing with the start of the second-activated light. An observer rapidly perceives the lights as looming closer, due to the inward-to-outward sweeping visual image that enhances salience. Because the observer's M cells appear to be primarily stimulated by the luminous energy, the observer can react more rapidly to the warning event than to conventional warning lights.

Abstract: Apparatus for determining position within a beam, comprising pulses of energy transmitted in coded patterns, is achieved by processing the signals received from the beam to generate a value indicative of coarse position within the beam and by interpolation within the coarse position to generate a value resolving fine position within the coarse position.

Abstract: A system for illuminating parts of an aircraft, such as a helicopter, including three low-intensity position lights (10) mounted on the aircraft, with two of the position lights mounted in a forward location and spaced laterally from the center of the aircraft and a third position light mounted in an aft location centrally positioned on the aircraft. The three position lights provide a triangular light formation that indicates the position of the aircraft during tactical, covert operations. The position lights include a chemiluminescent light source (12) and a housing (22) for carrying the chemiluminescent light source. Each housing is secured to a part of the aircraft by means of a bracket (52) and a pair of band clamps (60). The chemiluminescent light source is visible from within the housing within a limited range of the aircraft. Preferably, the chemiluminescent light source creates an infrared light that is detectable by means of night vision goggles worn by pilots of nearby flying aircraft.

Abstract: An intermediate voltage or cable marker with a gas filled lamp with reflectively enhanced conspicuity comprising an inner conductive coating in an opaque shell; the shell being mountable on an the intermediate voltage line and having one end of the gas filled lamp electrically connected to the intermediate voltage line or grounded cable and the other end electrically connected to a electrical coil in series with the conductive inner shell coating; the gas filled tube being mounted in a reflective chamber shaped to increase both lateral and vertical conspicuity.

Abstract: A traffic signal made up of a conventional stop and go configuration of lamps and switching means with an improved lamp control and improved lamps. The lamps are of the incandescent type, preferably having two filaments. The filaments are connected to a source of electrical current. The current is supplied through an electronic circuit providing electrical current of a first polarity alternately to one of the filaments and electrical current a second polarity alternately to the second filament. It has been discovered that this alternate energizating of the filaments gives a scanning effect that is more conspicuous and has greater attention getting qualities under all viewing conditions.

Abstract: A solar-powered beacon comprises a water-tight caisson housing a battery for storing electricity produced by solar cells atop the beacon. An electronic circuit within the caisson controls operation of the beacon. The caisson material acts as a heat sink for the solar cells, and insulation is provided below the cells to further protect the electronic components.

Abstract: An apparatus for guiding the occupants of a structure along a path of travel within the structure is provided. The apparatus is comprised of modular floor covering units which are abuttingly arranged to cover the floor of the structure, with some of the units being signal units having a light-transmissive housing positioned in an opening therein, and having light-emitting means positioned in the housing. Power means are provided to energize the light-emitting means, and thereby provide a visually discernable pathway on the floor. The floor covering units preferably comprise carpet tiles, the light-transmissive housings are preferably formed of molded plastic and the light-emitting means are preferably light-emitting diodes.

Abstract: Disclosed is a system for aligning elements in azimuth, in particular guns of artillery batteries. A prior system of this type uses an omnidirectional xenon beacon which produces pulses to indicate rotation of a reference unit, a double pulse indicating a reference director. A receiver counts pulses until it detects a directional laser beam from the reference unit, the number of pulses given a reading of what is known as a reciprocal bearing. The xenon and laser pulses are optically separated in the receiver. The prior system is not as reliable as desired, mainly because of scintillation effects. The present invention overcomes this problem by identifying different pulses by the pattern of their arrival times. A detector unit generates and stores numbers each having a magnitude proportional to their time of arrival. The numbers are processed by a microprocessor to determine the angle through which the laser beam travels between a reference direction and the direction of the detector unit.