Abstract: Methods and systems for generating a vertical situation display for a noise abatement departure procedure (NADP). Other NADP relevant displays are also disclosed including display of NADP parameters on altitude tape and primary flight displays, an NADP bug on an engine display and NADP status annunciations. The methods and systems include receiving NADP parameters entered into a flight management system (FMS) on a user interface of the aircraft system. The NADP parameters include: an initial altitude at which take-off thrust should be reduced to NADP thrust, an acceleration altitude at which the aircraft should begin accelerating to a final take-off speed whilst maintaining the NADP thrust, a climb excitement altitude at which a speed target is changed to the final take-off speed whilst maintaining the NADP thrust, and an end altitude at which the NADP should be exited.

Abstract: A system for aircraft recommendation for an electric aircraft is presented. The system includes a computing device, wherein the computing device is configured to, receive an aircraft datum, receive a flight plan, generate a model of at least a flight phase as a function of the aircraft datum and the flight plan, generate an aircraft recommendation as a function of the flight plan and aircraft datum, wherein generating the aircraft recommendation further comprise identifying a tunable parameter of the at least a flight phase, tuning the tunable parameter as a function of the model of the at least a flight phase and at least an objective constraint, and generating the aircraft recommendation as a function of the tuning. The system further includes a user device, wherein the user device is configured to display the aircraft recommendation.

Abstract: A method for determining a flight path for an aircraft system, for example an unmanned aircraft system (UAS) comprises analysing an intensity map relating to a three dimensional space. The intensity map comprises an array of voxels, each voxel defining a volume in the three dimensional space, and each voxel having a related traffic intensity value based on historical flight data through that voxel. The method comprises determining a probability of an encounter for a preferred flight path between a start point and an end point via one or more voxels in the three dimensional space, based on traffic intensity values of the one or more voxels along the preferred flight path. The preferred flight path is selected if the probability of encounter is less than a first threshold value.

Abstract: The present disclosure provides an air line displaying method and a ground station. The method includes: displaying a first air line view, the first air line view including height information of at least one waypoint in an air line; when detecting a first operation performed by a user on a waypoint of the at least one waypoint, adjusting height information of the waypoint; and sending adjusted height information of the waypoint to an aircraft. By adjusting the air line view through human-computer interaction, the air line view displayed by the ground station can be edited. This makes it convenient for the user to adjust the air line and further enables the aircraft to receive a new air line in time, thereby facilitating flight of the aircraft.

Abstract: An embodiment includes an apparatus that supports a user to make planning decisions of fuel efficiency of an aircraft versus time of arrival of the aircraft along a flight path. An embodiment of the apparatus accepts input data related to the aircraft. The input data may include (i) flight plan data that includes a flight path of the aircraft, (ii) state of the aircraft along the flight path, (iii) environmental data, and (iv) an aircraft performance model of the aircraft. The apparatus calculates aircraft performance and an objective function for a range of altitudes and speeds as a function of the input data. The apparatus causes a user interface to display aircraft performance contour boundaries and a vertical routing path that meets the objective function to provide graphical representations to support a user's planning decisions.

Abstract: Provided is an unmanned aerial vehicle that broadcasts a route and future location information of the unmanned aerial vehicle within preset coverage based on sensing data and current location information of the unmanned aerial vehicle. The unmanned aerial vehicle includes a calculator configured to calculate a predicted route and second location information of the unmanned aerial vehicle corresponding to a preset period of time based on first location information and sensing data; and a transmitter configured to periodically broadcast a first notification signal that includes the first location information, the predicted route, and the second location information.

Abstract: A system and method for reducing a psychoacoustic penalty of acoustic noise emitted by an aircraft, including a plurality of propulsion assemblies coupled to the aircraft, wherein each of the plurality of propulsion assemblies includes a motor, and a plurality of blades defined by a propeller, wherein the plurality of blades can define an asymmetric blade spacing; a control subsystem coupled to the aircraft and communicatively coupled to the motor of each of the plurality of propulsion assemblies, wherein the control subsystem is operable to rotate each of the plurality of propulsion assemblies at a different frequency to modulate the acoustic power distribution of the emitted acoustic signature.

Abstract: A landing control method includes detecting whether a landing indication signal is received, and controlling an aircraft to automatically land in a pre-set landing mode if the landing indication signal is received. A takeoff control method comprises detecting whether a takeoff indication signal is received, and controlling an aircraft to automatically take off in a pre-set takeoff mode if the takeoff indication signal is received.

Abstract: A process displays a data visualization user interface on a computing device. Using the user interface, a user selects a data set and a set of configuration parameters. The parameters selected include (i) a first data field from the data set to define a first axis of a two-dimensional data visualization and (ii) a second data field to define a second axis of the data visualization. When the user selects the first axis, the interface displays an axis configuration window. The user selects the symmetric log axis scaling option for the first axis. The device retrieves the data set from a database according to the configuration parameters. The device then generates and displays the data visualization according to the configuration parameters, including scaling the first axis of the data visualization using a symmetric log transformation function and displaying axis tick marks on the first axis according to the scaling.

Abstract: An air data computer configured to be installed on an aircraft includes an inertial sensor assembly having a plurality of accelerometers and a plurality of rate gyroscopes. The air data computer is configured to: determine a pressure altitude of the aircraft based on measured pressure of the airflow about the exterior of the aircraft; determine an estimated attitude of the aircraft based on rotational rate sensed by the plurality of rate gyroscopes; and determine a vertical acceleration of the aircraft based on the estimated attitude of the aircraft and the acceleration sensed by the plurality of accelerometers. The air data computer is further configured to blend the vertical acceleration and the pressure altitude using a complementary filter to produce a blended altitude rate that is output to consuming systems.

Abstract: A system, computer-readable medium, and a method including receiving flight data engine measurements for at least one engine of the specific aircraft asset; receiving flight data aerodynamics measurements for the specific aircraft asset; combining a physics based parametric aerodynamic performance model tuned for the specific aircraft asset using the flight data aerodynamics measurements and a physics based engine model tuned for the specific aircraft asset using the flight data engine measurements; calculating, based on the combined tuned aerodynamic performance model and the tuned engine model, a performance model for the specific aircraft asset as a whole; and storing a record of the calculated performance model for the specific aircraft asset for a future deployment.

Abstract: An interactive speed profile bar that enables crew awareness of the overall planned flight trajectory speed profile. The speed profile bar will have a graphical depiction (e.g., virtual buttons having alphanumeric symbology) of some or all of the speed segments of the speed profile. Each graphical element (e.g., virtual button) includes symbology identifying the applicable speed mode and corresponding target speed change. Each speed segment will start at the inflection point where the speed change will occur in the flight plan, and will continue until the next trajectory speed change. The speed profile bar will be interactive, allowing the flight crew to select the speed segment to change, in response to which selection the system displays graphical user interface elements showing a menu of the available speed segment options. Each individual speed segment is represented by an individual virtual button that can be selected by touching the screen or other input device.

Abstract: A control system includes at least one lever configured to receive an operator input, a bellcrank coupled to the at least one lever and configured to rotate when the operator input exceeds a threshold, a support structure of the bellcrank which movably holds the bellcrank, and at least one magnet which forms a magnetic field which forms a positive detent between the bellcrank and the support structure of the bellcrank.

Abstract: A system and method for airborne oblique image collection provides a dense diversity of view aspects of a subtended scene. An onboard camera of an aircraft collects a highly overlapped set of oblique images that are well suited for preparing three dimensional meshes that model complex scenes with significant vertical relief. The aircraft is flown in a radial trajectory over a targeted observable area in order to collect the images. The radial trajectory is optimized using parameters including an altitude, a field-of-view angle, an aft edge angle, and a forward edge angle of the onboard camera, as well as an expected velocity of the aircraft. A flight management system is also employed, wherein the flight management system computes a predicted location for the aircraft using location data and a current velocity of the aircraft. The predicted location being compared to an expected location, ensuring proper navigation of the radial trajectory.

Abstract: A method and system for continuously re-planning a vehicle's path, in the face of stationary and moving obstacles, dynamically calculates a new path in real time which is both efficient and maintains minimum safety clearances relative to obstacles. Repulsion signals emanating from obstacles and propagating through delineated sections of a grid representing a geographic space are summed along with values representing the relative distance of the sections from the vehicle origin and vehicle destination. The grid sections having optimal values according to a predetermined criteria represent an efficient and safe travel path between the vehicle origin and destination.

Abstract: A monitoring system is disclosed for use with a mobile platform being operated by an operator. The system may make use of a database for containing operational information and procedures relating to the operation of the mobile platform by the operator. A processor may also be used that communicates with the database and with at least one subsystem of the mobile platform for monitoring operational information concerning operation of the mobile platform against stored information contained in the database. The processor may determine if the operation of the mobile platform is proceeding in accordance with predetermined standards.

Abstract: Various methods, apparatuses and articles of manufacture are provided which may be used in determining an altitude of a mobile device. For example, an electronic device may select a subset of reporting mobile devices located within a particular environment, estimate a reference parameter that is indicative, at least in part, of a reference altitude within the particular region, e.g., based, at least in part, on one or more altitude measurements for one or more of the reporting mobile devices, and initiate transmission of the reference parameter to at least a target mobile device. In another example, a mobile device may obtain such a reference parameter, and estimate its altitude based, at least in part, on the reference parameter.

Abstract: A method and a system for controlling an emergency descent of an aircraft. The system (1) includes a unit (2) for detecting an emergency situation, a unit (11) for calculating a usual emergency descent command, a unit (12) for calculating a limited emergency descent command, a selection unit (14) configured for selecting the usual emergency descent command or, if application conditions are met and if the limited descent command is less than said usual emergency descent command and greater than a regulation emergency descent command, selecting the limited emergency descent command, and a unit (4) for application, to the aircraft, of the selected emergency descent command.

Abstract: This disclosure relates to unmanned aerial vehicles with parallax disparity detection offset from horizontal. The unmanned aerial vehicles use two optical elements, which are arranged to be separated by a horizontal distance and a vertical distance when the unmanned aerial vehicles operate leveled with respect to ground, to determine parallax disparity of an object.

Abstract: This disclosure describes a system and method for operating an automated aerial vehicle wherein influences of a ground effect may be utilized for sensing the ground or other surfaces. In various implementations, an operating parameter of the automated aerial vehicle may be monitored to determine when a ground effect is influencing the parameter, which correspondingly indicates a proximity to a surface (e.g., the ground). In various implementations, the ground effect based sensing techniques may be utilized for determining a proximity to the ground, as a backup for a primary sensor system, for determining if a landing location is uneven, etc.

Abstract: A mixed mode compensation circuit for a power converter generate a digital signal according to a reference signal and a feedback signal which is related to the output voltage of the power converter, convert the digital signal into a first analog signal, offset the first analog signal with a variable offset value to generate a second analog signal, and filter out high-frequency components of the second analog signal to generate a third analog signal for stable output voltage of the power converter. The mixed mode compensation does not require large capacitors, and thus the circuit can be integrated into an integrated circuit.

Abstract: A method and device for automatically determining a speed profile with speed levels for an aircraft. The device includes a calculation unit which is configured for determining a speed profile (P1) which is such that, from upstream to downstream, the speed (V) is maintained at a speed constraint (V1) imposed at a waypoint (B1), up to said waypoint (B1), then a deceleration (T2) is performed from this waypoint (B1) up to an optimum speed (Vopt), said optimum speed (Vopt) being maintained up to another deceleration (T4) ending directly at a downstream speed limit (V2) reached at a given altitude level (A2).

Abstract: A method of constructing a behavior model (32) of an airplane engine, in particular in order to track the operation of the engine, the method comprising a training step (12) of training at least one statistical regression function on the basis of a generic database (14) containing data from a plurality of airplane engines in order to establish a generic behavior model (10) of the airplane engines, and an additional step of resetting the generic behavior model from data in a database (24) specific to the above-mentioned airplane engine, in order to establish a behavior model (32) that takes account of features specific to that engine.

Abstract: A method and apparatus for identifying and analyzing an aircraft landing site during flight is provided. The method includes the steps of using image capture means such as an infrared camera to capture in-flight images of the ground in the region of a possible landing site, using a database of computer modelled images of possible aircraft landing sites mapped to a global co-ordinate reference frame to compare the in-flight images with a modelled image of the possible landing site and optimizing correspondence between the two images to obtain an in-flight image optimally mapped to the global co-ordinate reference frame. Thereafter, the landing site which corresponds to the optimally mapped in-flight image is analyzed to ascertain the presence of any obstructions such as life forms, vehicles or newly erected buildings thereon.

Abstract: The present disclosure relates to an unmanned aerial vehicle (UAV) able to harvest energy from updrafts and a method of enhancing operation of an unmanned aerial vehicle. The unmanned aerial vehicle with a gliding capability comprises a generator arranged to be driven by a rotor, and a battery, wherein the unmanned aerial vehicle can operate in an energy harvesting mode in which the motion of the unmanned aerial vehicle drives the rotor to rotate, the rotor drives the generator, and the generator charges the battery. In the energy harvesting mode regenerative braking of the generator reduces the forward speed of the unmanned aerial vehicle to generate electricity and prevent the unmanned aerial vehicle from flying above a predetermined altitude.

Abstract: The present invention discloses a control stick for controlling an UAV formed by a bar with buttons on the bar head and a GUI displaying airplane like icons providing feedback of current steering control status of a UAV.

Abstract: A system for use in generating a command trajectory for an aircraft is provided. The system includes a natural frequency determining module configured to determine a closure rate of the aircraft to a selected flight path, compare the closure rate of the aircraft to a threshold closure rate, and calculate a natural frequency based on whether the closure rate is below the threshold closure rate. The system further includes a command processor coupled to the natural frequency determining module and configured to receive the calculated natural frequency from the natural frequency determining module, and generate a command trajectory using the calculated natural frequency.

Abstract: An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector heading across a ground surface. The aircraft includes a control system in data communication with a model, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The model decouples the directional movement of the aircraft into a lateral equation of motion and a longitudinal equation of motion. The lateral control architecture utilizes the lateral equation of motion to control the aircraft in the lateral direction, while the longitudinal control architecture utilizes the longitudinal equation of motion to control the aircraft in the longitudinal direction. The initialization command logic selectively activates the lateral control architecture and the longitudinal control architecture.

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 of flying an aircraft, where the aircraft has an associated performance envelope, along a flight path based determining an altitude profile for a cruise-climb along the flight path based on the performance envelope of the aircraft and flying the aircraft along the flight path to approximate the altitude profile.

Abstract: Systems and methods for flight management are provided. One flight control system is provided that includes a flight management system configured to manage aircraft flight control including at least one of a flight path or an altitude for an aircraft. The flight control system also includes a flight parameter selection module configured to determine a Cost Index (CI) and cruising altitude for use by the flight management system to manage the aircraft flight control, wherein the determination is based on a flight cost and predicted weather along the flight path.

Abstract: Methods and apparatus are provided for transmitting incursion alerts to a plurality of in-flight aircraft in accordance with preconfigured pilot preferences. The apparatus comprises a data store module containing data sets against which the pilot preferences are evaluated during flight, including weather, airspace and flight restrictions, ground delay programs, and air traffic information. The apparatus further includes a flight path module containing route and position information for each aircraft. An incursion alert processing module evaluates the flight path, data store, and pilot preferences and generates incursion alerts which are transmitted to each aircraft during flight, either directly or via ground based dispatchers or flight operations personnel.

Abstract: A method of flying an aircraft, where the aircraft has an associated performance envelope, along a flight path based determining an altitude profile for a cruise-climb along the flight path based on the performance envelope of the aircraft and flying the aircraft along the flight path to approximate the altitude profile.

Abstract: Present novel and non-trivial system, device, and method for generating altitude data and/or height data are disclosed. A processor receives navigation data from an external source such as a global positioning system (“GPS”); receives navigation data from multiple internal sources; receives object data representative of terrain or surface feature elevation; determines an instant measurement of aircraft altitude as a function of these inputs; and generates aircraft altitude data responsive to such determination. In an additional embodiment, the processor receives reference point data representative of the elevation of the stationary reference point (e.g., a landing threshold point); determines an instant measurement of aircraft height as a function of this input and the instant measurement of aircraft altitude; and generates aircraft height data responsive to such determination.

Abstract: A method and device for servocontrolling an aircraft speed-wise in an approach phase. The device can adapt to the estimated time of passage of the aircraft at a particular point of the approach trajectory, the position of the start of deceleration of the aircraft in the approach phase.

Abstract: An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector across a ground surface. The aircraft includes a control system in data communication with control actuators, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The lateral control architecture controls the aircraft in the lateral direction, while the longitudinal control architecture controls the aircraft in the longitudinal direction. The initialization command logic automatically activates the lateral control architecture and the longitudinal control architecture to maintain a constant vector across the ground whenever a directional control input is made at low speed.

Abstract: Present novel and non-trivial system, device, and method for generating altitude data and/or height data are disclosed. A processor receives navigation data from an external source such as a global positioning system (“GPS”); receives navigation data from multiple internal sources; receives object data representative of terrain or surface feature elevation; determines an instant measurement of aircraft altitude as a function of these inputs; and generates aircraft altitude data responsive to such determination. In an additional embodiment, the processor receives reference point data representative of the elevation of the stationary reference point (e.g., a landing threshold point); determines an instant measurement of aircraft height as a function of this input and the instant measurement of aircraft altitude; and generates aircraft height data responsive to such determination.

Abstract: Systems and methods for differential altitude estimation utilizing spatial interpolation of pressure sensor data are provided. In one embodiment, a method for mobile navigation comprises: measuring a horizontal location of a mobile navigation unit to generate two-dimensional horizontal coordinate data; measuring a barometric pressure at the mobile navigation unit with a sensor to obtain local pressure data; processing information representative of pressure data derived from a network of a plurality reference stations to obtain a correction factor; performing a calculation using the two-dimensional horizontal coordinate data, the local pressure data, and the correction factor to calculate an altitude coordinate; and determining an altitude of the mobile navigation unit from the altitude coordinate.

Abstract: The invention describes a method and device for preventing useless alarms generated by an anticollision system on board an airplane and according to which the duration (dcap) of a phase of capture of a setpoint altitude (Zc) by the airplane is between a predetermined minimum execution deadline (dmin) and a predetermined maximum execution deadline (dmax).

Abstract: An automatic takeoff and landing apparatus for an aircraft for realizing a takeoff run and performing an ascending flight of the aircraft up to a target altitude at takeoff; and for realizing an approaching flight and performing a landing run of the aircraft at landing.

Abstract: A method and device are provided for determining a target altitude for an emergency descent of an aircraft that is to be reached by the end of the emergency descent. The method includes determining an initial target altitude representative of the initial position of the aircraft and then repeatedly determining a current target altitude along a reference horizontal distance. The current target altitude is compared to the initial target altitude and is used to update the emergency descent if the current target altitude is lower than the initial target altitude. Each target altitude is selected as the larger of a predetermined threshold altitude and a security altitude that ensures any obstructions along a remaining horizontal distance are avoided.

Abstract: The device (1) comprises means (10) for determining, in the case of the loss of a speed information, control parameters which are used on at least one automatic pilot of the aircraft, instead of said speed information.

Abstract: An altitude profile representative of the terrain overflown by an aircraft is established. Thereafter, an altitude limit curve which comprises an intersection with the altitude profile upon the engagement of a terrain avoidance maneuver is determined. As soon as there is no longer any intersection of the limit curve with the altitude profile, the terrain avoidance maneuver is interrupted.

Abstract: An automatic landing apparatus for an aircraft includes: an altitude sensor; an airspeed sensor; an attitude angle sensor; a direction sensor; a position sensor; a landing command inputting section; and a control device, including: an approaching flight control section for realizing an approaching flight along a predetermined path by controlling a propulsion device and a control surface, in response to a landing command; a flare control section for controlling the propulsion device to provide a minimum output and controlling the control surface to perform a flare when the altitude of the aircraft becomes less than a predetermined landing altitude; and a landing run control section for realizing a landing run by controlling the propulsion device to maintain the minimum output and controlling the control surface to maintain the attitude angle and the traveling direction of the aircraft when the airspeed of the aircraft becomes less than a predetermined landing speed.

Abstract: The invention relates to a method for calculating an approach trajectory of an aircraft (200) to an airport The aircraft is slaveable in terms of trajectory, thrust and/or speed. The aircraft is able to advance at reduced engine revs. The airport has a runway The approach trajectory terminates in an impact point (205) on the runway and has a high-altitude descent segment (217) and an intermediate geometric segment (207), to which the aircraft is slaved in terms of trajectory and speed. A step of calculating a final approach segment (208) at reduced engine revs and a landing segment is performed with a greater thrust than the reduced revs so as to prepare a possible go-around (209), to which the aircraft is slaved in terms of thrust and speed.

Abstract: In accordance with an embodiment, a method includes displaying information corresponding to automatically controlled engine thrust levels during a reduced engine thrust period of flight of an aircraft. The information corresponds to one or more parameters associated with a flight control computer of the aircraft. In an alternate aspect, the displayed information includes alphanumeric information formatted in accordance with a sequential order of the automatically controlled engine thrust levels. In a further aspect, the alphanumeric information corresponds to first, second and third engine thrust levels.

Abstract: A vehicle guidance system comprising: a measurement system; a processor arranged to receive information from the measurement system and convert said information into at least one time-to-contact based parameter; and a control system arranged to receive the at least one time-to-contact based parameter from the processor and use the at least one time-to-contact based parameter to either automatically guide the vehicle or to provide vehicle guidance information to a pilot.

Abstract: An aircraft piloting method and device for picking up a vertical profile of a flight plan. The device combines a manual piloting device that enables a pilot to control the start of the picking-up of a vertical profile and an automatic piloting device for automatically ending the vertical profile picking-up and following the vertical profile.

Abstract: A method and device for aiding the piloting of an airplane includes: (1) determining current values of flight parameters of the airplane, (2) determining, with the aid of the current values, an approach distance that corresponds to a distance in a horizontal plane between the current position of the airplane and a position of contact with the ground, and (3) presenting the approach distance on a screen.

Abstract: A system and method for presenting an image of terrain threats are disclosed. Substantially transparent terrain symbols (color or monochrome) are depicted where each symbol is representative of a level of threat. Terrain symbols may overlay a weather image without a loss in information. A system is disclosed which comprises a navigation system, a terrain database, an image processor, and an indicating system. The navigation system acquires navigation data representative of aircraft position and direction; the database stores data of a plurality of cells; and the indicating system receives image data and presents symbols representative of the terrain image. The image processor receives navigation data defines a range of elevations of threat levels based upon the aircraft altitude, receives terrain data from the terrain database, determines the terrain threat of each cell, and provides an image representing the threat level and locations to the display.