Abstract: A method of indicating a flight direction of an aerial vehicle, having a vehicle body and a plurality of rotors supported by the vehicle body, includes: on the basis of a momentary flight direction of the aerial vehicle, controlling a matrix of light sources, in particular a matrix of LEDs, which are mounted to the vehicle body of the aerial vehicle, to provide an illumination pattern to an observer of the aerial vehicle, with the illumination pattern comprising a flight direction indication, indicative of the momentary flight direction of the aerial vehicle.

Abstract: A composition, method, and article of manufacture are disclosed. The microcapsule includes a polymer shell encapsulating a core component. The polymer shell includes light upconversion molecules. The article of manufacture includes the microcapsule. The method includes obtaining light upconversion molecules having sidechains with reactive functional groups, and forming a microcapsule. The microcapsule includes a polymer shell encapsulating a core component. The polymer shell includes light upconversion molecules. The article of manufacture includes the microcapsule.

Abstract: Techniques for guided placement of a wireless device are described herein. In an example embodiment, a wi-fi wireless device comprises a radio frequency (RF) transceiver coupled to a baseband processor. The RF transceiver is configured to receive an RF signal transmitted over a wireless channel and to convert the RF signal to a modulated digital signal. The baseband processor is configured to receive the modulated digital signal from the RF transceiver, extract a wireless packet from the modulated digital signal, and compute an Exponential Effective SNR Mapping (EESM) value based on the preamble of the wireless packet, where the computed EESM value indicates the quality of the wireless channel at the current location of the wireless device. The baseband processor is further configured to provide a quality indicator based on the EESM value for the current location of the wireless device.

Abstract: A light assembly includes a base, an annular reflector, and a retainer. The base includes one or more light sources mounted thereto. The annular reflector comprises a first radially outward surface and a first radially inward surface. The annular reflector also defines a central longitudinal axis, with the first radially outward surface including a reflective surface. The retainer is coupled to the base and comprises a second radially outward surface. The second radially outward surface of the retainer seats against the first radially inward surface of the annular reflector to retain the annular reflector in a desired position relative to the light source mounted to the base, according to various embodiments.

Abstract: A landing strobe is provided having an optical emitter configured to emit an optical signal. An input device can be coupled to the optical emitter for setting the optical signal to a signature strobe output unique to the landing strobe. A landing zone designation system is also provided having a landing strobe configured to emit a signature strobe output unique to the landing strobe. An aircraft spaced from the landing strobe can include a detector for optically receiving the signature strobe output to determine the landing zone is proper to land the aircraft if the signature strobe output matches an expected signature strobe output.

Abstract: A beacon system is disclosed. The beacon system includes a case that defines a compartment and a lid. Also, the beacon system includes a ground plane mount that is pivotally coupled to the case, a monopole antenna carried by the ground plane mount, and an ADS-B transmitter. In that regard, the ADS-B transmitter is disposed within the compartment and electrically coupled to the monopole antenna.

Abstract: A dynamic exterior aircraft light unit, mounted to an aircraft for illuminating an aircraft environment, includes an LED group with a plurality of LEDs, and an optical system with at least one optical element. The optical system being associated with the LED group for shaping an output light intensity distribution from the light emitted by the LED group and the LED group and the optical system are stationary within the dynamic exterior aircraft light unit.

Abstract: An at least partially transparent exterior aircraft light cover includes at least one protrusion provided at a lateral end of the exterior aircraft light cover, wherein the at least one protrusion is configured to be introduced into a corresponding reception provided at an exterior aircraft light casing and wherein the protrusion is formed for allowing the cover to pivot, with the protrusion providing a fulcrum, when the protrusion is introduced into the reception. The at least partially transparent exterior aircraft light cover further includes at least one fixing device, which is provided in a pivotable portion of the cover and which is configured for removably fixing said pivotable portion to the casing for preventing a pivoting motion thereof.

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 ground illumination aircraft light unit has an operating light emission distribution for illuminating a ground area below an aircraft, wherein the ground illumination aircraft light unit is configured to be mounted to an underside of an aircraft fuselage, and wherein the operating light emission distribution includes a straight downward emission direction normal to the ground area and covers a solid angle of illumination around the straight downward emission direction, wherein the solid angle of illumination is at least 1.3 ? sr.

Abstract: This device for projecting luminous beams for exterior lighting for aircraft comprises a luminous source adapted to be mounted on the aeroplane so as to project the said beam onto an exterior lighting surface. The luminous source comprises a video image projector (2).

Abstract: A strobe light includes a base, a mounting post, a plurality of light emitting diode (LED) lights, a control system, and a lens. The mounting post extends vertically from the base. The plurality of LED lights are mounted around a periphery of the mounting post. The control system is coupled to the plurality of LED lights and operable to independently control each LED light to produce at least one of a 360° strobe light pattern and a rotating beacon light pattern. The lens is connected to the base and covers the plurality of LED lights.

Abstract: An aeronautical safety device which seeks to improve landing and take-off operations of aircraft, having a simple device which, by means of light means and push buttons or actuators indicating the instructions received, allow reflecting the instructions received from the control tower on a panel or in any other enabled point or by the senior cabin crew members themselves. The device has a casing on which at least two display indicators are arranged. One of them would serve for indicating that permission for takeoff or landing has been received, while the other light indicator would exclusively serve to indicate that the cabin is secure. The display indicators indicating that the instruction to initiate takeoff or landing has been received can range from light indicators to simple hinged flaps.

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: The invention refers to a base station (BTS) and a method for a BTS, for a cellular communication system comprising a user equipment (UE) onboard an aircraft, when at a predetermined altitude, and a terrestrial network. The invention is characterised in that the BTS is arranged to be an airborne onboard BTS comprising a screening device generating a first signal (S1) matched to screen a second signal (S2) from the terrestrial network at a predetermined altitude. The onboard BTS also comprises a signal generator generating a third signal (S3) stronger than both the first signal (S1) and the second signal (S2), the onboard BTS arranged to establish a communication link with the UE via the third signal (S3).

Abstract: The invention concerns a method of controlling the flight lighting arrangement of a wind park by means of acoustic monitoring or wind park comprising one or more wind power installations, wherein the wind park has an acoustic monitoring device having a microphone arrangement, wherein the microphone arrangement records sound signals, noises or the like from the environment of the wind park and said sound signals are processed in a signal processing device connected to the microphone arrangement, wherein there is provided a switching device for switching on a flight lighting arrangement of at least one wind power installation of the wind park and the switching device is coupled to and controlled by the signal processing device so that the signal processing device causes the switching device to switch on the flight lighting arrangement if a sound signal of a flying object, for example an aircraft or a helicopter, is detected by means of the acoustic monitoring device, and/or a predetermined sound signal (for exa

Abstract: An anti-collision aircraft light comprises at least one LED and a control unit for operating the at least one LED in a pulsed manner. In this anti-collision aircraft light, the control unit comprises an ambient temperature sensor for sensing the ambient temperature and an adjustable current control for setting an LED operating current depending on the sensed ambient temperature. The control unit further includes a light intensity sensor for sensing the intensity of the light emitted from the at least one LED, an integrator connected to the light sensor for integrating the sensed light intensity, and a comparator for comparing the integrated light intensity to a threshold value. The operating current for the at least one LED is interrupted as soon as the integrated light intensity is equal to the threshold value.

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: A terminal data loading device on a mobile platform includes a media unit for receiving a transportable media element containing media data and outputting a media signal to a control processor unit. The control processor unit outputs an information signal to a wireline communication unit. The wireline communication unit outputs a wireline signal to a network on the mobile platform.

Abstract: A solar powered device and a method of operating such a device to allow it to receive and store information about its physical location, from which it can determine the minimum expected solar energy levels that will be available to it. Based on the minimum expected levels, the device then limits its configurable settings to preferably enable only those configurations having maximum energy demands that can be met or exceeded by the minimum expected energy levels.

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 system and method for non-real-time validation of an electronically signed message transmitted via an asynchronous communications link is provided. The method includes creating an electronic message comprising an electronically signed data entry created by executing a secure data application first portion (SDA1) module hosted by a mobile system. The method additionally includes passing the message to a communications management function first portion (CMF1) module via a synchronous interface. The CMF1 module is hosted by the mobile system. The method further includes transmitting the message from the CMF1 module to a communications management function second portion (CMF2) module in a temporally delayed manner using an asynchronous communications link. The CMF2 module is hosted by a central computer system (CCS) located remotely from the mobile system. The method further yet includes validating the electronically signed entry in a temporally delayed manner utilizing a user database.

Abstract: An anti-collision light for aircraft comprising two illuminating modules each comprising a number of LEDs disposed along a ring and coplanar to a plane, a first reflector facing the LEDS and a second reflector surrounding the LEDS; the first and the second reflector are so configured as to reflect the light emitted by LEDs toward angles between 0 and 75° above or below said plane. An additional module providing infra-red radiation is may be provided; the additional module comprising number of infra red LEDs disposed along a ring and coplanar to a plane and a reflector facing the infra red LEDs.

Abstract: A flight information communication system has a plurality of RF direct sequence spread spectrum ground data links that link respective aircraft-resident subsystems, in each of which a copy of its flight performance data is stored, with airport-located subsystems. The airport-located subsystems are coupled by way communication paths, such as land line telephone links, to a remote flight operations control center. At the flight operations control center, flight performance data downlinked from plural aircraft parked at different airports is analyzed. In addition, the flight control center may be employed to direct the uploading of in-flight data files, such as audio, video and navigation files from the airport-located subsystems to the aircraft.

Abstract: Disclosed is to an aircraft radiofrequency communication system. The system includes at least one at least one radiofrequency transceiver device that is configured to transmit and receive data according to a VDL mode 3 standard and to receive status information that relates to at least one radio link of the radiofrequency transceiver device and includes the status concerning the possibility of transmitting on a particular, selected frequency. In one embodiment, a man/machine interface unit is configured to display configuration information and at least a portion of the status information. In an alternative embodiment, at least one radiofrequency transceiver device is configured to further determine status information that represents a possibility of using the radiofrequency transceiver device in transmission.

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: The invention refers to a base station, BTS, (BTS) and a method for a BTS, for a cellular communication system comprising a user equipment, UE, (UE) onboard an aircraft (1) being at a predetermined altitude and a terrestrial network. The invention is characterized in that the base station (BTS) is arranged to be an airborne onboard BTS (BTS) comprising a screening device (2) generating a first signal (S1) being matched to screen a second signal (S2) from the terrestrial network at a predetermined altitude. The onboard BTS (BTS) also comprises a signal generator (3) generating a third signal (S3) being stronger than both the first signal (S1) and the second signal (S2), the onboard BTS (BTS) being arranged to establish a communication link with the UE (UE) via the third signal (S3).

Abstract: The navigation lighting device for an aircraft, in particular a military aircraft and preferably a fighter aircraft is provided with several navigation light units with navigation lights, a power supply unit for the navigation tight units, and a central actuation unit for the actuation of the navigation light units in each one of several modes of operation. The navigation light units can be actuated for operation in a mode of operation by the central actuation unit sequentially in a predetermined sequence and thus with a time offset. Each navigation light unit comprises a control unit connected to the actuation unit for the actuation of its navigation light in the operation mode predetermined by the central actuation unit. The control units of the navigation light units comprise time-delay elements for the temporal delay of the actuation of the navigation lights on the receipt of an actuation signal of the central actuation unit.

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: A method, apparatus and system for monitoring an emergency frequency at a ground station for detection of an emergency signal and, upon detecting an emergency signal, determining whether the emergency signal represents an emergency event. If an emergency event is detected, the emergency event is reported. Determining whether the emergency signal represents an emergency event may include testing validity of the emergency signal to eliminate false positives. Reporting the emergency event may include sending an emergency event message to a remote server. The emergency event message may include time information and signal strength information associated with the detected emergency event and location information associated with the ground station.

Abstract: An emergency beacon includes a housing fitted with a connector for connecting the beacon to an antenna that is external to the housing. Inside the housing, the beacon includes an incident sensor, a transmitter, a detection and control member connected to the sensor and transmitter and arranged to trigger operation of the transmitter when an incident is detected. The beacon further includes, inside the housing, an incorporated antenna, a changeover switch interposed between the transmitter and the connector and also interposed between the transmitter and the incorporated antenna, and a sensitive member sensitive to the electromagnetic power conveyed towards the connector and to the electromagnetic power returned by the connector. The sensitive member is connected to the control member which is connected to the changeover switch and is programmed to deliver the signals from the transmitter to the external or incorporated antenna, depending on the state of the sensitive member.

Abstract: Systems and methods for direct communication between aircraft for one or more embodiments are adapted to receive tactical and strategic information related to proximate aircraft for improved flight planning. The systems and methods presented herein may be implemented, for example, in a first aircraft having a data link component adapted to process information, a storage component adapted to store information related to the first aircraft, and a communication interface component adapted to directly communicate with a second aircraft via a communication link. The first aircraft may include a user interface component adapted to interact with the data link component to retrieve information related to the first aircraft from the storage component, generate a request message with the information related to the first aircraft, and communicate with the communication interface component to directly transmit the generated request message to the second aircraft via the communication link.

Abstract: Systems and methods for handling information from wireless nodes, including nodes for communication with aircraft, are disclosed. A system in accordance with one aspect of the invention includes a sensor configured to sense information corresponding to a characteristic of a wireless node. The wireless node can be one of a plurality of wireless nodes configured to transmit and receive wireless signals. The wireless nodes can also be linked to a non-wireless network portion. The system can further include a transmitter configured to transmit the information via the network, and a receiver operatively coupled to the transmitter to receive the information via the network. Accordingly, the system can be used to automatically identify and track diagnostic information corresponding to the state of one or more wireless nodes.

Abstract: A flight information communication system has a plurality of RF direct sequence spread spectrum ground data links that link respective aircraft-resident subsystems, in each of which a copy of its flight performance data is stored, with airport-located subsystems. The airport-located subsystems are coupled by way communication paths, such as land line telephone links, to a remote flight operations control center. At the flight operations control center, flight performance data downlinked from plural aircraft parked at different airports is analyzed. In addition, the flight control center may be employed to direct the uploading of in-flight data files, such as audio, video and navigation files from the airport-located subsystems to the aircraft.

Abstract: An aircraft, the aircraft including a whole-aircraft ballistic parachute that is coupled to the aircraft. The aircraft determines if a pre-activation action needs to be performed before activation of the whole-aircraft ballistic parachute. The aircraft also receives a whole-aircraft ballistic parachute activation request. The aircraft then issues a command to perform the pre-activation action and then activates the deployment of the whole-aircraft ballistic parachute. The aircraft then issues a command to perform a post-activation action.

Abstract: A system for optically detecting an object comprises a light source associated with the object and operated to produce a temporal pattern of emissions and a detector, synchronized to the operation of the light source by signals from a global positioning system, to identify light emissions according to the temporal pattern.

Abstract: An device, method, and aircraft are provided for illuminating an in-flight operation, the device, method, and aircraft generating an electromagnetic radiation within the far-violet and ultraviolet spectrum, and thus being imperceptible to the naked eye, compatible with night vision equipment, and undetectable by night vision equipment.

Abstract: An aircraft, in particular a helicopter, has light elements which are in the form of strips and are fitted to the edge of at least a number of windows. The light elements are provided with photoluminescent material.

Abstract: Optical device for indicating the glide angle for aircraft, comprising at least one unit (10) for generating a light ray with a predefined colour, at least one unit (20) for transmitting said light ray and creating a light image, and at least one unit (30) for remotely projecting said light image, characterized in that said generating unit (10) comprises at least one light source consisting of an LED (11) and said unit (20) for transmitting the light ray and creating a light image is of the optical fibre type (21, 22).

Abstract: Flashing lights powered by a common wild frequency power source (40) are synchronized with respect to flash rate and duration. Each lighthead includes a power supply device (1), which includes a timing signal generator (30) and a synchronization device (5). The timing signal generator (30) includes a precision clock (310), which generates a timing signal to regulate the flashing operation of the corresponding light. The synchronization device recurrently causes the timing signal to be reset in accordance with the wild frequency power source signal. By recurrently resetting the timing signal of each light according to a common wild frequency source, the flashing of the lights can be synchronized without transferring synchronization signals between the lights.

Abstract: Systems and methods for handling information from wireless nodes, including nodes for communication with aircraft, are disclosed. A system in accordance with one aspect of the invention includes a sensor configured to sense information corresponding to a characteristic of a wireless node. The wireless node can be one of a plurality of wireless nodes configured to transmit and receive wireless signals. The wireless nodes can also be linked to a non-wireless network portion. The system can further include a transmitter configured to transmit the information via the network, and a receiver operatively coupled to the transmitter to receive the information via the network. Accordingly, the system can be used to automatically identify and track diagnostic information corresponding to the state of one or more wireless nodes.

Abstract: A white anti-collision light mounted on an aircraft utilizes a set of high-power light-emitting diodes (LEDs) and dedicated reflectors to distribute the light in a particular pattern that satisfies predetermined intensity requirements along a horizontal coverage area. The anti-collision light may include heat pipes for transferring heat from the LEDs to a set of cooling fins. Also, the LEDs may be electrically connected and controlled to provide redundancy and mitigate the effects of LED failures.

Abstract: The invention relates to a portable helicopter landing area and to the use method thereof. The inventive device comprises two cases (1, 2) which can be carried by the person on the ground (X) and which are intended to be disposed on the selected surface or area (H). Moreover, two units (A, B) can be removed from the aforementioned two cases respectively. The visual positioning unit (A) comprises: a light which produces four successive white flashes (7) and which is visible from a distance of at least forty kilometers by an aircraft pilot, and a high-frequency current generator unit.

Abstract: An emergency lighting arrangement preferably includes plural emergency light units connected to an on-board power supply network of an aircraft, and plural emergency current sources that each include at least one capacitor. Each emergency light unit includes an emergency light emitting element and a control unit that automatically connects the capacitor of the emergency current source to the emergency light emitting element upon the failure of the on-board power supply network. Preferably, the emergency current source including the capacitor is integrated into the emergency light unit. The emergency light unit may further include normal operation light emitting elements selectively connected by the control unit to the on-board power supply network. The control unit switches between normal operation of the normal light emitting elements and charging of the capacitor, and emergency operation in which the capacitor discharges through the emergency light emitting element.

Abstract: Red, green and white colored lights are emitted from navigation orientation indicating light emitting devices mounted within a helicopter rotor blade near its tip. The light emissions from such devices are under control to respectively indicate passage of the rotor blade through limited arcuate portions of the travel path of the rotor blade end tip. Operational control over the light emitting devices is effected by data processing of outputs from air-speed responsive sensors on the blade end tip.

Abstract: Anti collision light for an aircraft includes a number of light emitting diodes (LEDs) arranged on a common plane. A reflecting arrangement is located above the plane and reflects the light emitted by the diodes in a sidewards direction. A surrounding reflecting arrangement can be provided around the diodes and an additional reflecting arrangement in form of a layer on the plane may also be utilized. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

Abstract: An integrated radio tower light controller and alarm reporting device is described that is made up of solid-state current sensing modules that monitor the AC current distributed to the various lights/beacons and report various alarm modes. In addition, a solid-state flasher module is used to flash the radio tower beacons at the FAA/FCC specified rate along with reporting various alarm modes. Two mechanical relays are also included for reporting failures with the flasher module and AC power failure. Connecting terminals and testing switches are included to connect to various power leads, alarm leads, and to test the various functions of the device.

Abstract: A field unit for warning of a danger of collision between an aircraft and an obstacle, in particular a topographical ground obstacle or an obstacle formed by a mast, building or aerial cable structure, comprises a multi-part tubular mast having devices for fixing a solar panel and a radar antenna; an elongate radar antenna in an environment-protective casing, which, with an electronics unit, forms a radar system for synthesized radar detection of an aircraft in a radar coverage area; a central processing unit for identifying on the basis of information from the radar system an aircraft which is in a zone of the radar coverage area and which on the basis of radar information such as direction, distance and/or speed computes a collision danger area; and a high-intensity light system and radio transmitter system that can be activated by the central processing unit upon detection of an aircraft in a collision danger area.

Abstract: A field unit for warning of a danger of collision between an aircraft and an obstacle, in particular a topographical ground obstacle or an obstacle formed by a mast, building or aerial cable structure, comprises a multi-part tubular mast having devices for fixing a solar panel and a radar antenna; an elongate radar antenna in an environment-protective casing, which, with an electronics unit, forms a radar system for synthesized radar detection of an aircraft in a radar coverage area; a central processing unit for identifying on the basis of information from the radar system an aircraft which is in a zone of the radar coverage area and which on the basis of radar information such as direction, distance and/or speed computes a collision danger area; and a high-intensity light system and radio transmitter system that can be activated by the central processing unit upon detection of an aircraft in a collision danger area.

Abstract: A field unit for warning of a danger of collision between an aircraft and an obstacle, in particular a topographical ground obstacle or an obstacle formed by a mast, building or aerial cable structure, comprises a multi-part tubular mast having devices for fixing a solar panel and a radar antenna; an elongate radar antenna in an environment-protective casing, which, with an electronics unit, forms a radar system for synthesized radar detection of an aircraft in a radar coverage area; a central processing unit for identifying on the basis of information from the radar system an aircraft which is in a zone of the radar coverage area and which on the basis of radar information such as direction, distance and/or speed computes a collision danger area; and a high-intensity light system and radio transmitter system that can be activated by the central processing unit upon detection of an aircraft in a collision danger area.