Abstract: An unmanned aerial system (UAS) adapted to measure one or more atmospheric conditions has a frame and a plurality of motorized rotors suspended on arms extending outward from the frame. The UAS further includes a flight control module that includes a computer programmable flight control board and a sensor package that has an air sampling scoop, a first sensor positioned inside the air sampling scoop, and a ducted fan inside the air sampling scoop. The ducted fan is configured to draw air through the air sampling scoop in contact with the first sensor. The ducted fan can be configured to operate only when the UAS is above a predetermined altitude. The UAS may also be configured to operate in a “wind vane” mode in which wind speed and direction is determined based on the pitch and heading of the UAS.

Abstract: Methods are described for generating encrypted messages and unicast/multicast transmitting the encrypted messages to one or more aircraft using Automatic Dependent Surveillance-Broadcast (ADS-B) transmission. Corresponding system for communicating messages to an aircraft using ADS-B link is also provided.

Abstract: A system and method of displaying an Engine Failure Awareness Chart (EFAC) for aircraft with at least one engine out is shown and described herein. The EFAC may display lines and zones indicative of levels of risk of obstacles on the ground. The obstacles may be either man-made or natural structures. The EFAC may update continuously providing the pilot with a real-time awareness of the risks around the aircraft during an engine failure. Using the EFAC the pilot may navigate the aircraft to a landing area or back to the airport for landing.

Abstract: Proximity detection systems and proximity detections methods are disclosed herein. In one aspect of the disclosure the systems and methods include measuring and analyzing the vector components of a generated magnetic field. In another aspect of the present disclosure, the results of the vector component measurements are used to take safety actions which may result in an alert to an operator or pedestrian, and/or automatic action by a vehicle or machine.

Abstract: Orientation and position sensing methods and devices are disclosed. The described methods and devices are based on implementing magneto-electric-quasi-static fields for position and orientation sensing in lossy-dielectric, conducting, or metallic non-line-of-sight environments, where obstructions or occlusions or nearby objects exists that are lossy in nature and that typically perturb radio or electromagnetic wave signaling. Detailed experimental results highlighting the performance of the disclosed methods are also presented.

Abstract: Orientation and position sensing methods and devices are disclosed. The described methods and devices are based on implementing magneto-electric-quasi-static fields for position and orientation sensing in lossy-dielectric, conducting, or metallic non-line-of-sight environments, where obstructions or occlusions or nearby objects exists that are lossy in nature and that typically perturb radio or electromagnetic wave signaling. Detailed experimental results highlighting the performance of the disclosed methods are also presented.

Abstract: A system and method for estimating an orientation of a traffic participant. In one example, the system includes a sensor configured to detect a traffic participant and an electronic controller configured to receive a signal from the sensor, compare a location of the vehicle to a map of expected orientation of traffic participants to estimate an orientation of the traffic participant, perform a calculation based upon the signal from the sensor to estimate an orientation of the traffic participant if an expected orientation is not determined by the comparison of the location of the vehicle to the map of expected orientation of traffic participants, and generate a notification based upon the estimated orientation of the traffic participant.

Abstract: Aspects of the present disclosure provide systems and methods for determining an estimated orientation and/or position of a user's head using worn ear pieces and leveraging the estimated head orientation and/or position to provide information to the user. In one exemplary method, first and second spatial positions of respective first and second ear pieces worn by a user may each be determined. Based at least in part on the first and second spatial positions of the respective first and second ear pieces, an estimated orientation of the user's head may be determined. The method may further include requesting information to be provided to the user based at least in part on the estimated orientation of the user's head and providing contextual information to the user responsive to the request.

Abstract: A restricted airspace monitoring system and method include a restricted airspace monitoring control unit that is configured to determine if a restricted airspace is active through monitored positions of a plurality of aircraft within an airspace that includes the restricted airspace and/or restriction notice information.

Abstract: A method for automatically calculating a trajectory for an aircraft to re-join a reference route of the aircraft executed iteratively, in particular when the aircraft is no longer locked onto its reference route, each iteration comprising a step of detection of deviation from the active segment of the route; if the deviation from the active segment of the route is detected, the method comprises a step of selection of a route segment to be re-joined, a step of calculation of a re-joining trajectory between a starting point and the route segment to be re-joined, and a step of validation of the trajectory of the route segment to be re-joined. Where this trajectory is validated, the method comprises a step of assignment of the re-joining trajectory for the segment to the re-joining trajectory for the route. Otherwise, it comprises a step of verification of the existence of a next route segment fulfilling a selection condition.

Abstract: Unmanned aerial vehicles include a processor to determine whether a first location of an unmanned vehicle and a second location of a virtual event is within a threshold distance; and a game experience controller to: control the unmanned vehicle based on a first command associated with a non-augmented state of the unmanned vehicle in response to the first location of the unmanned vehicle and the second location of the virtual event being outside of the threshold distance; and in response to the first location of the unmanned vehicle and the second location of the virtual event being within the threshold distance, control the unmanned vehicle based on a second command associated with an augmented state of the unmanned vehicle to simulate the unmanned vehicle being affected by the virtual event.

Abstract: An aid method for piloting an aircraft including acquiring an instruction intended to alter the flight plan, determining an applicability period of the instruction made up of a plurality of applicability moments of the instruction in which the application of the instruction is compatible with the operational capabilities of the aircraft and with the constraints of the flight plan, for each applicability moment of the instruction, determining an altered flight plan in case of application of the instruction at this applicability moment and calculating values of the operational parameters associated with this flight plan, and selecting an optimal applicability moment based on values of the operational parameters associated with the altered flight plan and operational parameters associated with the current flight plan.

Abstract: A method for the three-dimensional representation of the trajectory of an aircraft in flight implemented in a navigation system of an aircraft is provided. The flight plan of the aircraft comprises imposed georeferenced trajectories and predicted non-georeferenced trajectories. When the trajectory of the aircraft is dependent on a non-georeferenced flight setpoint, the three-dimensional representation method is an iterative process comprising the following steps: computing a predicted trajectory arising from at least one computed trajectory extending over a determined distance or duration; computing a smoothed trajectory from the predicted trajectory in order to obtain a resulting trajectory; computing a displayed trajectory, the trajectory being equal to the resulting trajectory corrected for constant deviations or deviations depending on the application of setpoints from the flight director; and displaying the displayed trajectory.

Abstract: A system and method for displaying a current state and a future state of a vehicle on a display associated with the vehicle are provided. The method includes: receiving flight plan data for a selected flight plan and a plurality of legs associated with the selected flight plan from a source of flight plan data; determining, with a processor, a current state of the vehicle with respect to one of the plurality of legs based on sensor data; determining, with the processor, a current target state for the vehicle with respect to one of the plurality of legs based on the flight plan data; determining a divergence of the current state based on a difference between the current state and the current target state; and generating a user interface for display that illustrates the divergence of the current state with respect to the one of the plurality of legs.

Abstract: A landing receiving apparatus for aircraft landing, and a control method thereof are provided, in which the landing receiving apparatus includes a flight management system (FMS) which is inputted with, by a user, destination airport, destination runway, and a receiver mode, a data storage portion which stores approach path data for landing of the aircraft; a receiver portion which calculates aircraft position information by using Global Navigation Satellite System (GLASS) signals and Satellite-Based Augmentation System (SBAS) signals transmitted from an antenna portion, when a receiver mode inputted by a user is a GNSS/SBAS combination mode, and a landing guidance information generating portion which generates landing guidance information by using approach path data corresponding to a destination airport and a destination runway inputted by the user, and the aircraft position information, and transmits the generated landing guidance information to the FMS.

Abstract: In the field of satellite global navigation, a method is provided for estimating the level of error in global navigation satellite measurements and for ensuring the reliability of these estimations, implemented by a global navigation device in which local errors are detected by said global navigation device and errors associated with the satellites are detected by a ground segment.

Abstract: Systems and methods for averaging satellite sigmas and readmitting excluded satellite measurements into differential corrections and integrity monitors are provided. In one embodiment, a method comprises: calculating a first RFI based averaged sigma and a second RFI based averaged sigma, wherein the first RFI based averaged sigma includes a sigma for the excluded satellite measurement and wherein the second RFI based averaged sigma does not include the sigma for the excluded satellite measurement; and, readmitting the excluded satellite measurement into either a differential correction broadcast or a respective integrity monitor when the first RFI based averaged sigma is less than or equal to the second RFI based averaged sigma.

Abstract: The present invention provides a system and mobile device for providing geographic information to a user. The system includes a mobile device that is wirelessly connected to a geographic database. The mobile device includes a plurality of sensors for determining a first location and a first direction. A controller is adapted to provide information requested based on local queries and distal queries. In addition, the controller can respond to thematic queries of each variety, wherein the database search is limited to objects, entities or features that fit within a selected theme. Finally, the controller is adapted to select and order query results based upon two- and three-dimensional query windows.

Abstract: A method for generating a flight route includes receiving an unconfirmed flight route of a drone, displaying a visually observable area based on a position of an observer who visually observes the drone, confirming, if the unconfirmed flight route is entirely included in the visually observable area, the unconfirmed flight route as a confirmed flight route, and displaying, if at least a part of the unconfirmed flight route is not included in the visually observable area, a warning message indicating that the unconfirmed flight route is not confirmed.

Abstract: A display apparatus for a vehicle includes a virtual image display device, a detection device, and a picture control device. The virtual image display device emits predetermined light to permit a windshield or a combiner to reflect the predetermined light towards an eye of a driver. The emitted predetermined light is to display a picture. The virtual image display device displays the picture in a displayed area as a virtual image; the picture appears ahead of the vehicle. The detection device detects a target that is an obstacle or an intersection. The picture control device displays the picture to appear below the target in the displayed area, and then moves the picture to a position corresponding to the target apparently while decreasing at least a width of the picture.

Abstract: Provided is an apparatus for monitoring a malfunctioning state of a global positioning system (GPS) satellite, the apparatus comprising: an orbit computing unit to compute an orbit of a geostationary satellite; a data receiver to receive GPS data from the GPS satellite; a data correction unit to correct an error in a clock error value of the GPS data; a first computing unit to compute a data pseudorange between the GPS satellite and a base station based on the corrected GPS data; a second computing unit to compute a geographical distance between the GPS satellite and the base station; and a determining unit to determine a malfunctioning state of the GPS satellite by comparing the data pseudorange and the geographical distance.

Abstract: A method and device are disclosed for automatically managing a flight path change on an aircraft, in particular for a low-level flight. The method determines a first deviation between the current position and a current path of the aircraft and a second deviation between this current position and a new path of the aircraft and changes the flight path by replacing the current path by the new path, if at least the absolute value of the difference between this first deviation and this second deviation is less than or equal to a maximal allowed distance during at least a predefined time period.

Abstract: An aircraft display system includes a processor configured to receive a heading-based leg and to generate display signals based on the heading-based leg; and a display device including a horizontal situation indicator coupled to the processor. The horizontal situation indicator receives the display signals from the processor and displaying symbology representing the heading-based leg.

Abstract: The present invention provides a system and mobile device for providing geographic information to a user. The system includes a mobile device that is wirelessly connected to a geographic database. The mobile device includes a plurality of sensors for determining a first location and a first direction. A controller is adapted to provide information requested based on local queries and distal queries. In addition, the controller can respond to thematic queries of each variety, wherein the database search is limited to objects, entities or features that fit within a selected theme. Finally, the controller is adapted to select and order query results based upon two-and three-dimensional query windows.

Abstract: A method for detecting piloting conflicts between the crew and the autopilot of an aircraft. According to the method, an automatic trajectory is programmed by checking whether the actual values of navigation parameters converge on said corresponding desired values within a predetermined convergence period; in the case where at least one of the actual values does not converge, within the convergence period, on the corresponding desired value, a predictive calculation is carried out, at consecutive future moments, of the value of at least one particular parameter selected amongst the navigation parameters; and in the case where the predicted value of the particular parameter is higher than a corresponding predefined threshold, an alarm is emitted for the crew of the aircraft to notify them about a piloting conflict being able to jeopardize the flight safety of the aircraft. A device for implementing the method. An aircraft including the device.

Abstract: A head-up display system includes an aircraft, a predicted flight path generation component that calculates a predicted flight path over a period of time, and a graphic generation component configured to generate a graphical display and project it onto a combiner configured to combine the graphical display with a visual exterior view. A synthetic vision system includes an aircraft, a predicted flight path generation component that receives one or more state parameters and calculates a predicted flight path over a period of time, and a synthetic terrain generation component configured to generate a synthetic view which is displayed on a display. The graphical display and/or the synthetic view includes a three-dimensional depiction of the predicted flight path over the period of time generated utilizing one or more three-dimensional transforms, one or more graphical images based on flight data, and a three-dimensional graphical depiction of a flight plan.

Abstract: This disclosure relates to a system for preventing collisions with a terrain. The system includes a detecting means for detecting risks of collision with the terrain after a predetermined forecasting delay. The system further includes a determining means for determining, based on a trajectory followed by the aircraft, a possible limit point for success of the vertical terrain avoidance maneuver. The system further includes indication means for giving indications on azimuth clearance sections, around the direction in which the aircraft is moving, suitable for success of the vertical terrain avoidance maneuver. The system further includes means for estimating a free-travel distance in each azimuth clearance sector on a straight distancing trajectory with constant gradient and over a distance correspond to more than one minute of flight, the free-travel distance being free of potential conflicts with the terrain.

Abstract: A method of operating an aircraft comprising a cockpit with a flight deck having at least one flight display, a pilot's seat facing the flight deck, and a synthetic vision system producing a synthetic image for displaying on the at least one flight display.

Abstract: A device for verifying guidance orders includes a passivation device for implementing comparisons between guidance orders from at least three different equipments in order to generate a passivated guidance order. For example, one of the guidance orders may be an auxiliary guidance order used to compare to the other two primary guidance orders so that the primary guidance order that is closest to the auxiliary guidance order is selected as the passivated guidance order. The passivated (e.g., validated) guidance order is transmitted to a flight control system of the aircraft.

Abstract: Present novel and non-trivial systems and methods for positioning a heading-based image within a track-based image and for generating steering commands for a forward-looking image capture device of an enhanced vision system (“EVS”). The positioning system is comprised of a source of navigation data, a source of first image data representative of a track-based image, a source of second image data representative of a heading-based image, and an avionics system processor (“ASP”) configured to receive the navigation data, the first image data, and the second image data, determine image positioning data, and merge the first image data with the second image data as a function of the image positioning data. The steering commands generating system is comprised of a source of navigation data, the ASP configured to generate steering command data commensurate to a wind correction angle, and the EVS configured to receive the steering data.

Abstract: Systems and methods are disclosed for displaying the current trends (i.e., turning or going straight) or the future positions of vehicles of interest on a traffic display unit. The position, orientation and geometry of the displayed symbology is a function of parametric information broadcast by the vehicles of interest and processed by a computer system that controls the traffic display unit. In particular examples disclosed herein, the traffic display unit is a navigation display on an aircraft or a traffic display unit at a traffic controller's station. However, the methods disclosed herein have application to vehicular traffic other than aircraft, such as boats or ships.

Abstract: An apparatus for displaying terrain on a display apparatus of an airborne vehicle is provided. The apparatus includes a synthetic vision system having a terrain and obstruction database, an enhanced vision system with sensors for recording terrain data, a height and position sensor for determining the flight state data, a display apparatus, a processor for fusion of the data from the synthetic vision system and from the enhanced vision system. The height information that is produced by the synthetic vision system and the enhanced vision system is stored as pixels in a two-dimensional grid network. The fusion processor uses an error function for insertion of a pixel into the two-dimensional grid network. The error function provides an estimate of the size of the respective cell in which the pixel is stored, from the distance between the pixel and the sensor position.

Abstract: A method for selecting and displaying a flight path for an aircraft on a display of a flight deck of the aircraft that allows a user to input a selected flight path on a map displayed on the display. A final flight path will be displayed on the display of the flight deck that is based on the input of the selected flight path.

Abstract: This device for displaying information relative to a flight configuration of the aircraft provided with at least one propulsion system, able to generate a thrust force on said aircraft comprised in a thrust range, said information comprising information relative to an energy variation of the aircraft, is characterized in that the energy variation of the aircraft is expressed by a size representative of this energy variation and homogenous at a gradient of the aircraft, and in that said device is capable of representing a range of energy variations that can be achieved by said aircraft and a current energy variation of said aircraft. Corresponding method and system for displaying an energy variation.

Abstract: A vehicle display system diminishes specified display features when in a taxi mode. EV images, SV images, and avionics symbology are displayed, with certain of the images and symbology being diminished when in a taxi mode. Additionally, guidance to the runway centerline is displayed in the taxi mode.

Abstract: A method and module for displaying a munition release envelope.

Abstract: The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring an actual along-track position and an actual vertical position of the aircraft relative to corresponding desired positions on the predetermined flight path. Throttle commands are generated based on deviations of the actual vertical position of the aircraft from the desired vertical position. Elevator commands are generated based on the deviation of the actual along-track position from the desired along-track position and on the deviation of the actual vertical position from the desired vertical position.

Abstract: A method for presenting the current drift values of an aircraft on a display device in which the drift values are presented in a vector presentation. The length of the drift vector above a predefined threshold value is presented in a manner proportional to the current drift velocity, and the length of the drift vector below the threshold value is presented in a manner disproportionate to the current drift velocity. There is a continuous transition between the two ways of presentation at the threshold value.

Abstract: A method for determining location such as vehicle location receives data at a predetermined frequency, validates the received data, stores the received data based on the validation and computes a location based on the stored data. The validation includes verifying a presence of particular data substrings within the received data, verifying a presence of a plurality of data fields within each data substring, computing a parameter based on information contained in two of the plurality of data fields and comparing the computer parameter with a pre-defined threshold.

Abstract: A present novel and non-trivial system, device, and method for presenting course deviation information on an aircraft display unit are disclosed. Lateral/vertical boundaries are established based upon lateral/vertical navigation data provided by one or more navigation data sources. Lateral/vertical deviation symbology data set(s) representative of lateral/vertical deviation scale(s) are generated and adapted to the lateral/vertical navigation data. The adapted lateral/vertical deviation symbology data set(s) representative of adapted lateral/vertical deviation scale(s) are provided to a display unit, whereby symbology(ies) of such adapted scale(s) are presented on a screen of the display unit. Each adapted scale is comprised of a desired course indicator and at least one deviation indicator, where the desired course indicator corresponds to a desired course and each deviation indicator corresponds to one navigation boundary.

Abstract: A device for aiding flight for an aircraft includes means for locating the localities situated in the operational area for rescue missions. The device is able to present to the crew a landmark of the positions of the localities in relation to the position of the aircraft, this landmark also indicating information connected with navigation and to flight regulations for each of the localities. The device relates to operations aircraft and more particularly rescue helicopters.

Abstract: A novel and non-trivial radar-based system, module, and method for presenting steering symbology on an aircraft display unit are disclosed. Hazard information acquired from a forward-looking aircraft radar system may be presented as hazard data to a symbology generating processor. A plurality of minimum turn angles may be determined based upon the boundary tangents of the hazard data. Data representative of steering symbology corresponding to a one or more minimum turn angles may be generated, where the symbology may take the form of textual symbology and/or non-textual symbology. Then, the steering symbology data may be provided to a presentation system for depiction of steering symbology on a tactical display unit and/or strategic display unit.

Abstract: A method and a device for activating an automatic piloting mode of an aircraft are disclosed. The device can include means for engaging an automatic pilot mode, when (i) the current distance of the aircraft with respect to a reference position on the ground belongs to a determined distance range, and (ii) the current height of the aircraft is at most equal to a reference height associated to the automatic pilot mode.

Abstract: Methods for flying multiple aircraft in a predetermined formation in which a relative navigation grid is emitted from at least one of the aircraft, a spatial relationship is calculated based on the emitted relative navigation grid, and a relative position of at least one aircraft is altered to position the aircraft in the predetermined formation when the spatial relationship does not conform with the predetermined formation.

Abstract: A display system comprises first and second LED panels for displaying first and second priority aviation data, a power supply, a modulator, a processor and a logic gate. The modulator generates a modulated voltage for the second LED panel, where the second priority data are displayed at a modulated brightness. The processor controls the modulator, and generates a status signal indicating a failure condition of the modulated voltage. The logic gate switches the first LED panel from the modulated voltage to the unmodulated voltage based on the status signal, where the first priority data default from the modulated brightness level to full brightness based on the failure condition.

Abstract: A visual display system is provided for an aircraft having a flight plan with a plurality of flight plan pages. The system includes a display unit configured to display at least one of the flight plan pages; an input device configured to receive an input from a user corresponding to a selected flight plan page from the plurality of flight plan pages; and a processor coupled to the monitor and the input device. The processor is configured to receive the input from the input device and provide the selected flight plan page to the display unit for display based on the input.

Abstract: An assistance method and device for lateral control of an aircraft upon an approach phase is disclosed. The device (1) comprises means (25) to predict in flight a risk of runway lateral excursion and means (20) to advise the pilot of the aircraft about the existence of such a risk.

Abstract: Disclosed is a method and device for assisting guidance of an aircraft. A flight management system is used to determine guidance instructions that include speed instructions having at least one flight time constraint to guide the aircraft to a check-point. An accuracy level for complying with the flight time constraint and at least one error level for at least one flight parameter are generated by an accuracy generating unit. An operating margin for at least one second parameter is determined from the determined accuracy and error levels, with the operating margin being representative of air speed criterion values of the aircraft. A range determining unit is used to determine whether the range of air speed criterion values is within an air speed envelope of the aircraft, and the speed instructions are modified when the range of air speed criterion values is not within the air speed envelope.

Abstract: Systems and methods are disclosed for displaying the current trends (i.e., turning or going straight) or the future positions of vehicles of interest on a traffic display unit. The position, orientation and geometry of the displayed symbology is a function of parametric information broadcast by the vehicles of interest and processed by a computer system that controls the traffic display unit. In particular examples disclosed herein, the traffic display unit is a navigation display on an aircraft or a traffic display unit at a traffic controller's station. However, the methods disclosed herein have application to vehicular traffic other than aircraft, such as boats or ships.

Abstract: A method of operating an aircraft comprising a cockpit with a flight deck having at least one flight display, a pilot's seat facing the flight deck, and a synthetic vision system producing a synthetic image for displaying on the at least one flight display.