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 status information management system correlates checklist data from all stored checklists to create a holistic, function level representation of aircraft health. Components are associated with defined function level categories. When a component fault is detected, the contextual information management system identifies each function level category that includes that component, and flags that function level category as having a fault. Such flags may be represented on a display where each function level category is displayed. A flight crew member selecting the function level category may see all systems impacted by the component fault. When selecting a function level category, the information management system may render a graphical depiction of the aircraft and the systems included in the function level category. The component fault may be depicted along with an impact criticality to the rendered systems.

Abstract: A control system (10) is suitable for use in one's own motor vehicle (12) and is set up and intended to determine the current driving situation of one's own motor vehicle (12) and other motor vehicles (28, 40) in the surroundings of one's own motor vehicle (12) by means of a surroundings sensor system and to assign the other motor vehicles (28, 40) to specific movement paths or not.

Abstract: A geo-containment system includes at least one unmanned vehicle and an enforcement system that is onboard the unmanned vehicle and configured to limit travel of the unmanned vehicle based, at least in part, on predefined geospatial operational boundaries. Such boundaries may include a primary boundary and at least one secondary boundary that is spaced apart from the primary boundary a minimum safe distance. The minimum safe distance is determined while the unmanned vehicle is traveling. The minimum safe distance is determined using state information of the unmanned vehicle and/or dynamics of the unmanned vehicle. The state information includes at least position and velocity of the unmanned vehicle. The enforcement system is configured to alter and/or terminate operation of the unmanned vehicle if the unmanned vehicle violates the primary geospatial operational boundary and/or the secondary geospatial boundary.

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: An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.

Abstract: A method of management of a flight of an aircraft is provided. The method includes receiving a data stream from an automatic dependent surveillance broadcast (ADS-B) receiver during the flight, and the data stream includes an ADS-B message, a geographic position of the aircraft, and attitude and heading reference system (AHRS) data. The method includes accessing data that indicates a weight of the aircraft, identifying a force event experienced by the aircraft based on the geographic position, the AHRS data, and the weight of the aircraft, and classifying the force event by level of the force event, and by type of the force event as a turbulence event or a non-turbulence event. And the method includes outputting a report that indicates the force event as classified, at least when the force event is classified as a turbulence event.

Abstract: Described are various embodiments of a flight management method and system using same. In one embodiment, a digital flight management system comprises: a digital processing environment comprising instructions to access: flight request data related to a flight plan; aircraft parameter data; a flight risk data source; and geographical data. The instructions are executable to: calculate a predicted flight path; digitally compare the predicted flight path with flight risk data from the flight risk data source to assess a flight risk associated with the predicted flight path; and display via a user interface the predicted fight path in accordance with the flight risk.

Abstract: This disclosure relates to systems and methods for controlling an unmanned aerial vehicle. Boundaries of a user-defined space may be obtained. The boundaries of the user-defined space may be fixed with respect to some reference frame. A user-defined operation associated with the user-selected space may be obtained. Position of the unmanned aerial vehicle may be tracked during an unmanned aerial flight. Responsive to the unmanned aerial vehicle entering the user-defined space, the unmanned aerial vehicle may be automatically controlled to perform the user-defined operation.

Abstract: Methods and systems provide a visual user interface on a display device associated with an aircraft. A Flight Information System (FIS) broadcast report; and an Air Traffic Control (ATC) broadcast message are received. The FIS broadcast report and the ATC broadcast message are transcribed. Ownship data for the aircraft is received. The ownship data concerns at least one of: a state of the aircraft, a flight plan for the aircraft and a state of components of the aircraft. The transcribed FIS broadcast report is analyzed with respect to the ownship data to determine filtered FIS information that is relevant to the ownship. A visual user interface (UI) is rendered to be displayed on the display device. The visual UI includes the transcribed ATC broadcast message and the filtered FIS information.

Abstract: A light system for an evacuation slide may include a readiness indicator light assembly. The readiness indicator light assembly may comprise a first light emitting diode configured to emit a first color and a second light emitting diode configured to emit a second color. The light system may be configured to power the first light emitting diode after initial deployment of the evacuation slide and to power the second light emitting diode after the internal pressure of the evacuation slide is greater than a minimum pressure threshold.

Abstract: Disclosed are methods, systems, and non-transitory computer-readable media for transmitting obstacle information to one or more operator displays associated with an aircraft. For instance, the method may include obtaining aircraft flight information including a current position and altitude; retrieving obstacle information for a flight area; scanning the flight area with environment sensors to identify observed obstacles and generate observed obstacle information.

Abstract: An abnormality warning system provides an abnormality warning for multiple motor systems that drive a motor used correspondingly to each of multiple rotors included in an electric aircraft. The abnormality warning system includes an abnormality determination unit and a warning level setting unit. The abnormality determination unit determines an abnormal one of the motor systems. The warning level setting unit sets a warning level to warn abnormality, based on at least position information of the rotor in the electric aircraft or the usage of the rotor corresponding to a motor system determined to be abnormal by the abnormality determination unit.

Abstract: A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system having an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft; receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust.

Abstract: An autothrottle of an aircraft is configured to reduce engine power of the aircraft such that the aircraft incrementally slows from a prior airspeed to a reduced airspeed by a first increment, and compare the rates of energy consumption at the prior airspeed and the reduced airspeed. In response to the rate of energy consumption at the reduced airspeed being lower than at the prior airspeed as determined the above operations are repeated. In response to the rate of energy consumption at the reduced airspeed not being less than at the prior airspeed, the autothrottle increases the engine power such that the aircraft incrementally speeds up from a prior airspeed to an increased airspeed by a second increment, the increased airspeed corresponding to a more efficient operating point of the aircraft than any prior airspeed.

Abstract: Disclosed are methods, systems, and non-transitory computer-readable media for providing contextual building height information to one or more operators of an aircraft. For instance, the method may include obtaining aircraft flight information including a current position and a current altitude of the aircraft; and retrieving, from a database, building information for one or more buildings located in a flight path area, the flight path area including the current position of the aircraft. The method may further include assigning one or more visual characteristics to each of the one or more buildings located in the flight path area based at least in part on the building information and the current altitude of the aircraft; and displaying, to the one or more operators of the aircraft, the one or more buildings located in the flight path area with the assigned one or more visual characteristics.

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: 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: The present disclosure is generally directed to the use of mixed reality to provide safety information as well as infotainment during flight. Demonstrations of the safety information for the aircraft are augmented in a 3-D way with a virtual representation of the aircraft. The virtual representation provides the safety instructions to the passengers. The mixed reality concept provides the safety information with the help of video-see through mixed reality by way of a head-mounted display worn by the passengers. The safety instructions are provided with a complete working view of locations and operations for the safety jackets, emergency exits, and oxygen passenger service units.

Abstract: An aircraft control surface skew and/or loss detection system including an aircraft wing structure having a fixed part and at least two control surface elements wherein the at least two control surface elements are configured to be moveable relative to the fixed part. The detection system also includes a cable operably connected to each of the at least two control surface elements such that a tensile force is applied to the cable upon skew and/or loss of one of the control surface elements. The detections system has a sensor assembly including a first part and a second part, wherein one of the first and second parts has a sensor and wherein the cable is coupled to the second part such that skew and/or loss of one of the control surface elements causes movement of the second part relative to the first part.

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: 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: 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: 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.