Abstract: A method and a device for assisting the piloting of a propeller rotorcraft having a rotary wing and at least one propeller. The piloting assistance device comprises a computer configured to display the following on a display: (i) a first scale representing a power consumed by the at least one propeller and carrying a minimum power mark and a maximum power mark, (ii) a second scale graduated in forward speed of the propeller rotorcraft, (iii) an index comprising a power section representing a current power consumed by the at least one propeller, the index comprising a speed section indicating a current forward speed on the second scale.

Abstract: A system and apparatus assists pilots and flight crews in determining the best course of action at any particular point inflight for any category of emergency. The system monitors a plurality of static and dynamic flight parameters including atmospheric conditions along the flight path, ground conditions and terrain, conditions aboard the aircraft, and pilot/crew data. Based on these parameters, the system may provide continually updated information to the pilot or crew about the best available landing sites or recommend solutions to aircraft configuration errors. In case of emergency, the system may provide the pilot with procedure sets associated with a hierarchy of available emergency landing sites (or execute these procedure sets via the autopilot system) depending on the specific nature of the emergency.

Abstract: A computer-implemented method includes receiving a first input associated with an incident location of an incident. A second input associated with a measurement zone surrounding the incident location is received. The method further includes producing, via a display monitor, a set of waypoints associated with a flight path of an unmanned aerial vehicle (UAV) based on the first input and the second input. The set of waypoints is displayed on a satellite aerial map including the incident location.

Abstract: A vehicle location accuracy enhancement system is provided. A digital active phased array radar is configured to generate a profiled terrain including terrain altitude information. A controller is configured to implement operating instructions in memory to conduct profile matching between the generated profiled terrain from the at least one digital active phased array radar and terrain altitude profile information in a terrain database to determine profiled location solutions. The controller is further configured to at least augment sensor location solutions from at least one other location determining system, including a GNSS, with the profiled location solutions to enhance accuracy of the sensor location solutions. The controller is also configured to determine location errors in the GNSS based on the profiled location solution and to broadcast the determined location errors.

Abstract: An avionic system for a rotorcraft includes a data source and an enhanced ground proximity warning system. The data source has terrain data and obstacle data stored therein. The enhanced ground proximity warning system can be selectively switched, by a pilot, to operate in either a normal mode or a desensitized mode. The enhanced ground proximity warning system receives flight data, retrieves terrain data and obstacle data from the data source, evaluates the retrieved terrain data and the obstacle data to determine variations in elevations of terrain and obstacles in predetermined area that is a predetermined distance ahead of the current position and along the flight path, and based at least in part on the determined variations, selectively generate a prompt that suggests that the pilot switch the ground proximity warning system to the desensitized mode.

Abstract: A method includes identifying a first image that is captured at a first time. The method also includes segmenting the first image into a plurality of first image portions. The method also includes identifying a second image that is captured at a second time. The method also includes segmenting the second image into a plurality of second image portions. The method also includes comparing one of the plurality of first image portions and a corresponding one of the plurality of second image portions. The method also includes determining a difference between the first image and the second image based at least partially upon the comparison. The method also includes transforming the first image into a transformed first image based at least partially upon the difference.

Abstract: The present disclosure relates to a method and a device for measuring at least one atmospheric parameter (gas, temperature). The method includes implementing steps of acquiring spectral images in the ultraviolet and/or the visible and/or the infrared range and scanning according to a tomographic principle. The spectral images are acquired using a network of optical systems such as infrared cameras, and are used to estimate the air quality and/or meteorological and/or climate parameters in a geographic area, for example an urban agglomeration.

Abstract: Flight control surface actuation systems including skew detection systems and associated methods. A flight control surface actuation system includes a skew detection system configured to generate a skew detection signal that represents a skew condition of a flight control surface. In some examples, the skew detection system includes a skew lanyard and a detection mechanism assembly (DMA) configured to detect a lanyard displacement of the skew lanyard and to generate an analog lanyard displacement signal. In some examples, the skew detection system includes a hybrid sensing actuator that includes an actuator output and an actuator output position sensor directly coupled to the actuator output. Methods of utilizing a flight control surface actuation system include detecting a skew condition in the flight control surface utilizing DMAs and/or hybrid sensing actuators.

Abstract: Systems, devices and methods for alerting a crew of an aircraft or other mobile platform of a relevant condition associated with the aircraft are disclosed. One exemplary method comprises receiving data indicative of an existence of the relevant condition associated with the aircraft; receiving data indicative of a substantially real-time value of a dynamic parameter associated with the relevant condition; and displaying an awareness-enhancing indication associated with the relevant condition in a display area of the crew alerting system of the aircraft. The awareness-enhancing indication comprises a textual message and a supplemental indication indicative of the substantially real-time value of the dynamic parameter associated with the relevant condition. In various embodiments, the supplemental indication may be textual or graphical. The supplemental indication may also be indicative of a target value of the dynamic parameter.

Abstract: Systems, methods and computer readable storage media provide flexible vehicle status notifications via an instrument cluster displayed on an in-vehicle screen. In some examples, when a non-displayed gauge goes into an out-of-parameter or warning range, the gauge may be dynamically shown in the out-of-parameter or warning state in a container position assigned to the gauge in another display or in a dynamic container position in the instrument cluster. In some examples, a popup notification may be provided to inform the driver of a condition. When there are multiple notifications, they may be grouped into definable severity classifications and prioritized so that a notification determined to be a most important message at the time is presented to the driver in a notification zone central to a driver's field of vision on the instrument cluster that allows for reusing screen space for providing warning and information from a range of data sources.

Abstract: An audio signal processing apparatus in which different pieces of predetermined parameter information regarding acoustic transfer in a head of a listener are retained as preset candidates, a parameter information list including the retained preset candidates is presented, to prompt a user to select parameter information, and an audio signal for the user is generated by using the user-selected parameter information.

Abstract: The invention relates to an electronic device for managing the display of a head-up display system capable of being embarked in a cockpit of an aircraft piloted by at least one pilot and comprising: a display module configured to display a plurality of symbols relative to the operation of the aircraft and its environment in at least two distinct visualization planes, the visualization planes each having a distinct depth along a line of sight from the pilot, a determination module configured to determine a reference visualization plane corresponding to an accommodation plane of the eye of the pilot and a warning module configured to generate a warning to be displayed in the reference visualization plane.

Abstract: There is provided an installation structure for an oil pressure sensor, including: a crankcase in which a main gallery that extends in one direction is formed; and the oil pressure sensor detachably installed on an outer surface of the crankcase. The oil pressure sensor is configured to detect an oil pressure of a branch passage branching from one end of the main gallery. In a bottom view of a vehicle, a connector of the oil pressure sensor is oriented to an outside of the vehicle, and the connector of the oil pressure sensor overlaps with the crankcase.

Abstract: A configuration system (80) arranged to configure an aircraft in a single-pilot mode and a two-pilot mode, comprising: acquisition means (84) and authentication means (83) arranged to acquire and authenticate a configuration order that defines the selected mode and controls the configuration system (80) to configure the aircraft in the selected mode; first activation means (85) arranged to activate equipment dedicated to piloting by a single-pilot on board when the aircraft is configured in single-pilot mode, and to deactivate dedicated equipment when the aircraft is configured in two-pilot mode; verification means (87) arranged to, when the aircraft is configured in the single-pilot mode, verify that single-pilot flight conditions are met and inform the sole pilot on board and a ground station of the results of these checks.

Abstract: Provided is a warning light apparatus for at least one wind turbine including: at least one warning light, at least one sensor for detecting the presence of an object, a presence acquisition device connected to the at least one sensor the presence acquisition device being configured for: triggering the capturing of data through the at least one sensor, analysing the data captured through the at least one sensor for detecting the presence of objects, a warning controller connected to the at least one warning light and the presence acquisition device, the warning controller being configured for: receiving information about the detection of objects from the presence acquisition device, sending function signals depending on the information received from the presence acquisition device for activating or deactivating the at least one warning light.

Abstract: An apparatus may receive first data, in a first data format, from one or more unmanned aircraft system service suppliers comprising first positions of one or more unmanned aircraft systems, receive second data, in a second data format, from one or more communications systems comprising second positions of one or more manned aircraft, transmit third data, in a third data format, comprising the first positions of the one or more unmanned aircraft systems and the second positions of the one or more manned aircraft, receive a first control signal comprising a control command associated with one or more of the unmanned aircraft systems or one or more of the manned aircraft, and transmit a second control signal comprising the control command to one or more of the unmanned aircraft system service suppliers or to one or more of the communications systems.

Abstract: A monitoring system and method are provided for real time monitoring of flaps, landing gears, or tail skids to determine safe taxi, takeoff, and flight readiness. Monitoring units, including scanning LiDAR devices combined with cameras or sensors, mounted in aircraft exterior locations produce a stream of meshed data that is securely transmitted to a processing system to generate a real time visual display of the flaps, landing gears, or tail skid for communication to aircraft pilots to ensure safe aircraft taxi, takeoff, and flight readiness. Actual flap position alignment with optimal flap setting, proper retraction and extension positions of landing gears, and tail skid condition is ensured. Safety of aircraft taxi, takeoff and flight and airport operations are improved when the present system and method are used to prevent incidents related to misaligned flaps and improperly positioned landing gears or tail skids.

Abstract: A gunshot detection system includes gunshot sensor units with microphones for detecting gunshots and capturing audio data depicting the detected gunshots and other ambient sounds, an environmental board with various environmental sensors for generating environmental data indicating environmental conditions. The audio data, environmental data, and position information can be stored locally on local nonvolatile storage of the gunshot sensor unit for later retrieval by law enforcement entities. In one embodiment, the gunshot sensor units include a wired and/or wireless data transfer interface for transferring the audio data, environmental data and/or position information to handheld units of law enforcement entities. The gunshot sensor unit can also stream live captured audio data for live monitoring by a control panel, and might also include speakers for providing audio playback of audio data from the control panel.

Abstract: An aircrew automation system that provides a pilot with high-fidelity knowledge of the aircraft's physical state, and notifies that pilot of any deviations in expected state based on predictive models. The aircrew automation may be provided as a non-invasive ride-along aircrew automation system that perceives the state of the aircraft through visual techniques, derives the aircraft state vector and other aircraft information, and communicates any deviations from expected aircraft state to the pilot.

Abstract: Systems and methods for enabling consistent smooth takeoffs and landings of vertical and/or short-runway takeoff and landing aircraft at sites with gusty conditions. The system includes a network of wind measurement stations deployed around the perimeter of a takeoff/landing site for spatio-temporally characterizing wind fluctuations (e.g., wind gusts) that enter a volume of airspace overlying the site, data processing means for deriving information about the fluctuations from the wind measurements, communication means for transmitting disturbance information to the aircraft, and a flight control system onboard the aircraft that is configured to use the disturbance information to control the aircraft in a manner that compensates for the fluctuations. The wind measurement units may include laser Doppler anemometers, sound detection and ranging systems or other devices capable of simultaneous spatially and temporally resolved wind measurements.

Abstract: A system includes a communication interface configured to receive squitter messages from other aircraft in the vicinity of an ownship aircraft. The system also includes a processor aboard the ownship configured to receive the squitter messages, determine the altitude and position of the other aircraft from the squitter messages, and compare the altitude of the other aircraft to terrain data at the determined position to determine whether any of the other aircraft are operating abnormally. The system also includes a display providing an indication that a first aircraft of the other aircraft is operating abnormally.

Abstract: Flight control unit and flight unit start flight in accordance with a flight plan. Flight history acquisition unit acquires a flight history of drone. Flight plan acquisition unit acquires a flight plan for drone. Inspection timing determination unit calculates a difference between the acquired flight plan and the acquired flight history, and based on the difference, determines an inspection timing for drone. Inspection timing notification unit provides notification of the determined inspection timing.

Abstract: Embodiments of the present disclosure provide an array substrate, a display device and a spatial positioning method of a display device. The display device includes a base substrate, a pixel layer arranged at a side of the base substrate, a light source structure having a same light exit direction as the pixel layer, a processing element. The light source structure emits collimation invisible light, the pixel layer includes a plurality of sub-pixels and at least one sensing pixel arranged between the sub-pixels, the at least one sensing pixel receives reflected light of the collimation invisible light emitted by the light source structure and reflected by an object to be positioned, the processing element is coupled with the sensing pixel and the light source structure, a distance from the object to the display device is calculated according to relevant data information of the collimation invisible light and the reflected light.

Abstract: Systems and methods for a brain-computer interface (BCI) to increase a number of degrees of freedom (DOF) of one or more neural signals that are used to interact with the BCI.

Abstract: A network system for monitoring and storing data of aircraft intelligent windows or windshields to provide useable life of, provide real life performance of, and/or measure characteristics and/or properties of, the windshields forwards the data from sensors mounting the windshield to a window sensing hub having a microprocessor programed to receive and process the data to determine the performance of the windshield and formatting the data in accordance to a preset program, wherein the program includes providing data from the sensors that measures characteristics and properties of the windshield that are active during the period in which the data is taken. An aircraft central maintenance system connected to the window sensing hub receives the formatted information from the window sensing hub and unfiltered or unformatted information, wherein the unfiltered information from the windshield is acted on by the central maintenance system to provide an estimated useable life of the windshield.

Abstract: A device comprises a transcription unit for transcribing an audio message received from the air traffic control into a text message, a processing unit for extracting first indications from the text message, a transcription unit for transcribing, into a restated text message, a restated audio message transmitted by the pilot to the air traffic control after the reception of the audio message, a processing unit for extracting second indications from the restated text message, a comparison unit for comparing the first and second indications and a warning unit for transmitting a warning to the pilot if a difference between the first and second indications is detected, so as to notify the pilot that they have misunderstood the audio message from air traffic control.

Abstract: An information displaying apparatus for a vehicle includes a translucent cover panel, first and second displays which are placed in erect positions located on one side of the cover panel, and imaging optical elements which are placed beside the first and second displays along a surface of the cover panel on the one side of the cover panel, and are configured to form real images of screens of the first and second displays as floating images in a region located on the other side of the cover panel.

Abstract: The present disclosure relates to systems and methods that provide both an image of a scene and depth information for the scene. An example system includes at least one time-of-flight (ToF) sensor and an imaging sensor. The ToF sensor and the imaging sensor are configured to receive light from a scene. The system also includes at least one light source and a controller that carries out operations. The operations include causing the at least one light source to illuminate at least a portion of the scene with illumination light according to an illumination schedule. The operations also include causing the at least one ToF sensor to provide information indicative of a depth map of the scene based on the illumination light. The operations additionally include causing the imaging sensor to provide information indicative of an image of the scene based on the illumination light.

Abstract: A system and apparatus for assisting in determining the best course of action at any point inflight for an emergency. The system may monitor a plurality of parameters including atmospheric conditions along the flight path, ground conditions and terrain, conditions aboard the aircraft, and pilot/crew data. Based on these parameters, the system may provide continually updated information about the best available landing sites or recommend solutions to aircraft configuration errors. In case of emergency, the system may provide a procedure associated with a hierarchy of available emergency landing sites for execution via the autopilot system for landing the aircraft.

Abstract: Methods and systems for combining information from a first image captured of a scene via a first sensor and information from a second image captured of the scene via a second sensor wherein the first image and second image have at least one common field of view (FoV) and wherein the first image comprises pixels that are distributed according to a non-linear image point distribution function. The first image is corrected, before combining, based on said non-linear distribution function.

Abstract: A method 300 for deploying an aircraft landing gear including: receiving an aircraft landing gear deployment signal 310, receiving an aircraft position signal indicative of a distance of the aircraft from an aircraft landing site 320, receiving one or more flight signals indicating one or more dynamic conditions or parameters relating to the flight of the aircraft 330, determining, based at least on the one or more flight signals, a first aircraft position, relative to the aircraft landing site, at which the landing gear deployment should commence 340, and deploying the landing gear (a) when the aircraft reaches the first aircraft position, in the event that the deployment signal is received before the aircraft reaches the first aircraft position, or (b) immediately, in the event that the deployment signal is received when the aircraft has passed the first aircraft position 350.

Abstract: A device includes a control input generator and a neural network trainer. A flight simulator is configured to generate first state data responsive to a first control input from the control input generator and to provide the first state data to a first neural network to generate a candidate second control input. The control input generator is also configured to select, based on a random value, a second control input from between the candidate second control input and a randomized offset control input that is based on a random offset applied to the first control input. The flight simulator is configured to generate second state data responsive to the second control input from the control input generator. The neural network trainer is configured to update weights of the first neural network based, at least in part, on the first state data and the second state data.

Abstract: Computer assistance in interval management may be beneficial in a number of ways. For example, digital communication of interval management instructions or information related to interval management may beneficially be communicated to aircraft with respect to other aircraft. This information may be communicated overlaid on air traffic control (ATC) communications, or otherwise. A method can include, for example, obtaining a spacing goal for an aircraft relative to a target aircraft. The method can also include determining clearance instructions for the aircraft, wherein the speed guidance is based on the spacing goal. The method can further include transmitting the clearance instructions in a computer-readable format to the aircraft. The instructions can be provided by an overlay-modulated signal of a provided modulated ATC signal. The instructions can be configured to enable control of the aircraft to achieve the spacing goal.

Abstract: An automated take-off system for an aircraft includes a processing circuit an automated braking system of the aircraft, the automated braking system configured to cause the aircraft to stop. The processing circuit is configured to determine whether the speed of the aircraft less than a VR speed and an aircraft failure event has occurred and determine whether to abort the takeoff or continue the takeoff in response to determining that the speed of the aircraft is less than the VR speed and that the aircraft failure event has occurred. The processing circuit is configured to cause the automated braking system to stop the aircraft in response to determining to abort the takeoff.

Abstract: A system, method and device for monitoring an aircraft, including activity taking place within an aircraft and conditions of the aircraft, where one or more a percepting component such as a camera, microphone, or other sensor, is situated at a location within the aircraft from which information may be ascertained. Preferably the component is disguised within the surfaces or instrumentation of the aircraft. The percepting component is connected with a communication mechanism to transmit communications from the system resident within the aircraft to a grounds portion of the system through a communication link, such as a satellite communication link. The system may process the information corresponding with the aircraft condition or activity and generate alerts when a trigger is met or exceeded. The system components on the aircraft may monitor conditions and activity without using or interfering with the aircraft instrumentation, the system using only the aircraft power.

Abstract: A situation recognition device (10) including a surveillance processor (1) and an AI system (3). The surveillance processor receives visual and/or acoustic surveillance signals (E) from an aircraft passenger compartment (20) via an input interface (7). The AI system (3) includes an AI processor (4), a rule set generator (5) based on self-learning algorithms, and a reference rule set memory (6). The AI system is in bidirectional data communication with the surveillance processor (1). The AI processor (4) checks, upon a request (Q) from the surveillance processor (1), data patterns in the received visual and/or acoustic surveillance signals (E) for deviations from data patterns in a reference rule set (R) stored in the reference rule set memory (6). The surveillance processor (1) outputs indicator signals (A) via the output interface (8) if deviations determined by the AI processor (4) exceed one or more predefinable deviation threshold values.

Abstract: A system for facilitating the execution of law enforcement duties is disclosed. More particularly, according to one aspect of the invention, an electronic system is configured to facilitate the performance of law enforcement duties by quasi-instantaneously providing actionable intelligence to its users, such as front-line law enforcement officers, in response to a real-time query (e.g., accessing witness, medical, military personnel, law enforcement personnel, and government personnel information). According to another aspect of the invention, a system implements a set of automated status classifications for subjects with suspected or confirmed involvement in criminal and/or terrorist activities. The status classifications specifically and concisely establish the subject's involvement in criminal and/or terrorist activities.

Abstract: In an aspect, a system for vibration monitoring of an electric aircraft. A system include a propulsor. A system includes a sensor coupled to a propulsor. A sensor is configured to measure a vibration datum of a propulsor and transmit the vibration datum to a flight controller. A flight controller is configured to receive a vibration datum from a sensor. A flight controller is configured to generate a throttle datum as a function of a vibration datum. A flight controller is configured to transmit a throttle datum to a propulsor.

Abstract: The invention relates to a device and to a method for the open and closed control of n actuators An, n=1, 2, . . . , N, where N?1, which drive aerodynamic control surfaces of an aircraft.

Abstract: An augmented reality system, includes a first head-mounted see-through optic and a second head-mounted see-through optic each adapted to present digital content viewable by a user and having a transparency that enables the user to see through to the surrounding environment, wherein the first and second optics are separated by a distance such that a user of the first cannot see a user of the second optic, a training simulation system adapted to present digital content to each of the first and second optics, wherein the digital content represents a vehicle operated by the other user, wherein the digital content is presented to the first optic at a geospatial position proximate the first optic and the training simulation system further adapted to move the geospatial position of the digital content to maintain an apparent position relative to the other vehicle based on the other vehicle's movements.

Abstract: A method of generating and managing terrain awareness and warning system (TAWS) alerts including determining a number of warnings relating to terrain near an aircraft flight path, each warning indicating terrain above a threshold elevation and having a position associated with the warning. The method further including generating, for each warning, first alert data configured for display as an alert on a display device. The method further including sending the first alert data to the display device, receiving, from the display device, a user request to inhibit a first alert, the first alert based on the first alert data. The method further including generating second alert data for the first alert, wherein the second alert data is configured to inhibit the first alert, wherein inhibiting the first alert includes modifying a display of the first alert on the display device and sending the second alert data to the display device.

Abstract: A method for detecting damages to a rotor of an aircraft, where the aircraft comprises actuators for active vibration reduction, may comprising one or more of the following steps: determining actuator variables in a reference flight of the aircraft; plotting the actuator variables of respective data range tiles determined in the reference flight of the aircraft in first coordinates of a coordinate system, wherein the coordinate system contains numerous data range tiles; obtaining the number of actuator variables in the reference flight of the aircraft that are located in each data range tile; eliminating the data range tiles that have a number of actuator variables lying below a limit value for this in the reference flight of the aircraft, by means of which a reference flight signature is created; and determining actuator variables for a flight-specific signature.

Abstract: A system, a method, and a computer program embodied on a non-transitory computer-readable medium, the program configured to cause at least one processor to perform steps including gathering observations and forecasts of a plurality of aviation environmental and operational data of a terminal airspace, independently transforming the observations and forecasts into respective terminal airspace risk factors; integrating the terminal airspace risk factors into operational time periods; weighting the integrated terminal airspace risk factors into an overall airspace risk score for each operational time period; categorizing the overall airspace risk score into a terminal airspace risk category based upon at least one predetermined risk score threshold; and displaying the risk categories and selected underlying risk factors data on a map with a plurality of display panes.

Abstract: Systems and methods for vehicle behavior prediction include an imaging device that captures images of a vehicle in traffic. A processing device including policy stored in a memory of the processing device in communication with the imaging device stochastically models future behavior of the vehicle based on the captured images. A policy simulator in communication with the processing device simulates the policy as a reparameterized pushforward policy of a base distribution. An evaluator receives the simulated policy from the policy simulator and performs cross-entropy optimization on the future behavior of the vehicle by analyzing the simulated policy and updating the policy according to cross-entropy error. An alert system retrieves the future behavior of the vehicle and recognizes hazardous trajectories of the future trajectories and generates an audible alert using a speaker.

Abstract: A navigation system includes a navigation database and a route generator. The route generator receives an avoidance, generates a concave polygon representing the avoidance with respect to four-dimensional data of the navigation database, identifies a displacement vector of the avoidance, shifts the concave polygon using the displacement vector, identifies each gap between vertices of the shifted concave polygon, adds an added edge to the to connect vertices across each identified gap, determines, for each edge of the concave polygon, if the edge includes an internal edge, removes each internal edge from the concave polygon, compares the concave polygon to the plurality of cells, identifies one or more cells in which the concave polygon is located, and outputs a navigation alert based on the identified one or more cells.

Abstract: A method and apparatus for assessing performance of an operation for a vehicle. Real-time information is received by a computer system in the vehicle from at least one of a vehicle operator or a group of hardware systems in the vehicle during the operation for the vehicle. The performance of the vehicle operator in performing the operation is determined by from the real-time information. A graphical image of the feedback is displayed in a display system in the vehicle during the operation in which the graphical image provides guidance in operating the vehicle to perform the operation. The graphical image of the feedback comprises a graphical indicium of a corrective action for the correcting operation of the vehicle while carrying out the operation of the vehicle in which the graphical indicium enables improving performance of the operation of the vehicle by the vehicle operator.

Abstract: A cylinder head cover that prevents the gas outlet for the blow-by gas from being cooled by structural improvements so that the gas outlet does not freeze or become clogged in a cold condition. A cylinder head cover includes: a gas passage through which blow-by gas from a crankcase passes; and a gas outlet portion protruding upward from a head cover upper wall. The gas outlet portion includes a protruding case portion bulging upward from the head cover upper wall so as to form an outlet passage through which blow-by gas passes, and an air layer is formed outside the outlet passage in the protruding case portion.

Abstract: There is provided a graphical user interface that displays information on a plurality of different types of content on a single screen. The graphical user interface includes an overview display area and a detail display area. The overview display area displays an overview of the information on the content in chronological order, based on time information for the plurality of the different types of content. The detail display area displays, in greater detail, the information on the content that corresponds to the time information that is selected in the overview display area. Scrolling the information that is displayed in the overview display area causes the information on the content that is displayed in the detail display area to be scrolled.

Abstract: A system for facilitating the execution of law enforcement duties is disclosed. More particularly, according to one aspect of the invention, an electronic system is configured to facilitate the performance of law enforcement duties by quasi-instantaneously providing actionable intelligence to its users, such as front-line law enforcement officers, in response to a real-time query (e.g., accessing warrant, probation, and parolee information). According to another aspect of the invention, a system implements a set of automated status classifications for subjects with suspected or confirmed involvement in criminal and/or terrorist activities. The status classifications specifically and concisely establish the subject's involvement in criminal and/or terrorist activities. According to yet another aspect of the invention, a system is configured to execute an automated query of a database of subject packets that include license plate data from a license plate reader system.

Abstract: A system for determining visibility comprises a particle sensor unit mounted onboard a vehicle, and a processor unit in communication with the particle sensor unit. The particle sensor unit comprises a light source configured to transmit a light beam into an external air region; a set of receive optics configured to collect a scattered portion of the light beam from particles in the air region; and an optical detector configured to receive the collected scattered portion and measure a signal intensity. The processor unit is operative to perform a method for determining visibility that comprises analyzing data received from the particle sensor unit to determine particle distribution in a volume of the air region; performing particle differentiation to determine sizes and types of particles in the distribution; calculating visibility data based on the sizes and types of the particles; and outputting the visibility data to one or more onboard systems.