Abstract: A method and systems for controlling a speed of a vehicle are provided. The control system includes an input device configured to receive a required time of arrival (RTA) at a waypoint and a processor communicatively coupled to said input device, said processor programmed to automatically determine a dynamically adjustable range for an autothrottle control using an RTA error and a speed control tolerance, the RTA error representing a difference between an estimated time of arrival (ETA) and the RTA, the speed control tolerance representing a tolerance range about the vehicle speed profile. The control system also includes an output device communicatively coupled to said processor, said output device is configured to transmit at least one of a thrust control signal and a drag control signal to a speed control system of the vehicle.

Abstract: Methods for evaluating and implementing air traffic management tools and approaches for managing and avoiding an air traffic incident before the incident occurs. A first system receives parameters for flight plan configurations (e.g., initial fuel carried, flight route, flight route segments followed, flight altitude for a given flight route segment, aircraft velocity for each flight route segment, flight route ascent rate, flight route descent route, flight departure site, flight departure time, flight arrival time, flight destination site and/or alternate flight destination site), flight plan schedule, expected weather along each flight route segment, aircraft specifics, airspace (altitude) bounds for each flight route segment, navigational aids available. The invention provides flight plan routing and direct routing or wind optimal routing, using great circle navigation and spherical Earth geometry.

Abstract: The invention relates to a device for formulating a flight plan ensuring sufficient safety margins for a duration of a few minutes in relation to the set of flight constraints that could arise and comprising means for: detecting the surrounding moving objects (aircraft or meteorological phenomena), evaluating their type and the danger that they represent, formulating a reconfiguration flight plan ensuring a separation with these phenomena and taking best account of the constraints of the initially followed flight plan, avoiding prohibited or regulated airspaces and avoiding the surrounding relief with ad hoc operational margins.

Abstract: The invention relates to a method for calculating a flight path avoiding a collision with the ground when an aircraft dives towards the ground. The method includes receiving signals including information of a dive angle of the aircraft in relation to the imaginary ground plane, and a present roll angle of the aircraft, and calculating a flight path that avoids collision with the ground on the basis of the information. The calculation includes calculating a need for rolling the aircraft based on the present roll angle, and calculating a need for changing the direction of the velocity vector of the aircraft so that the change has a component in an upward direction in relation to the reference frame of the aircraft.

Abstract: A method and a device for an aircraft for detecting noise in a signal of LOC type. A first step includes estimating a first lateral speed of the aircraft according to a first set of parameters. Concurrently, at least one second lateral speed of the aircraft is estimated according to at least one second set of parameters, among which at least one parameter is of different nature from each parameter of the first set of parameters. A second step includes comparing the first lateral speed and the at least one second lateral speed according to a threshold. If the difference between the first lateral speed and the at least one second lateral speed is greater than the threshold, the presence of noise in the signal of LOC type is detected.

Abstract: Disclosed is a method and device for attenuating lateral effects on an aircraft due to turbulence encountered by the aircraft during flight. The lateral effects are attenuated by applying a roll control order to control a first controllable movable member that acts on aircraft roll and minimizes aircraft roll-wise disturbances due to wind, and a yaw control order that controls a second controllable movable member to act on aircraft yaw. The roll and yaw control orders are calculated based on a sideslip value of the aircraft, while the yaw control order is calculated as a function of the roll control order to compensate for aircraft lateral effects due to turbulence, as well as lateral effects due to application of the roll control order to the first movable member.

Abstract: The speed of the wind during operation of a UAV is estimated. In one example the speed of the wind is estimated by modeling an acceleration of an unmanned aerial vehicle (UAV) based on a measured ground speed of the UAV, determining an actual acceleration of the UAV with one or more sensors, and estimating the speed of the wind as an integral of a difference between the modeled acceleration and the actual acceleration.

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: The method for generating an integrated guidance law for aerodynamic missiles uses a strength Pareto evolutionary algorithm (SPEA)-based approach for generating an integrated fuzzy guidance law, which includes three separate fuzzy controllers. Each of these fuzzy controllers is activated in a unique region of missile interception. The distribution of membership functions and the associated rules are obtained by solving a nonlinear constrained multi-objective optimization problem in which final time, energy consumption, and miss distance are treated as competing objectives. A Tabu search is utilized to build a library of initial feasible solutions for the multi-objective optimization algorithm. Additionally, a hierarchical clustering technique is utilized to provide the decision maker with a representative and manageable Pareto-optimal set without destroying the characteristics of the trade-off front. A fuzzy-based system is employed to extract the best compromise solution over the trade-off curve.

Abstract: A method and apparatus for building, creating, or otherwise specifying an airport ground taxi navigation route for an aircraft from an input of the route is disclosed. The apparatus includes a keypad, voice recognition device, or other entry device, a processor, a display screen, and a navigation map database. A crewmember on the aircraft uses the entry device to enter all or part of the ground navigation taxi route. The entry device converts the received route information into an input text string, either with or without delimiters. The system parses the input text string by extracting characters or substrings from the input text string. A database lookup component searches the map database to find a route component that matches the character or substring. If the system finds a matching route component, it determines if the matching route component is continuous with the taxi route. The system adds the matching route component to the taxi route and displays any discontinuity.

Abstract: Disclosed is a method and device of guiding an aircraft along a flight trajectory to comply with a time constraint for arriving at a required arrival time at a waypoint of the flight trajectory. Speed setpoints are determined according to a speed profile that complies with the required arrival time at the waypoint, based on estimated values of parameters relating to the flight of the aircraft, and by taking account of an upper limit for a maximum speed at which the aircraft flies along the flight trajectory. The determined speed setpoints are applied to the aircraft during guidance of the aircraft along the flight trajectory.

Abstract: Disclosed is a system for generating a controlled speed for an aircraft along a ground trajectory. The system provides for receiving a ground trajectory of the aircraft and the speed profile of the aircraft. An interpolated speed of the aircraft is calculated on the basis of the ground trajectory, the speed profile and the current position; a weighting factor is calculated from an angular deviation, which is calculated from a measured current aircraft heading and the ground trajectory; an auxiliary speed is determined from the calculated interpolated speed; and the determined auxiliary speed is multiplied by the weighting factor to generate the controlled speed.

Abstract: A device and method for assisting in the management of an engine failure on an aircraft. The device automatically determines when an engine failure is detected, vectoring settings including speed, thrust and altitude settings designed to be implemented on the aircraft in such a manner as to allow it to fly to a particular airport.

Abstract: A method and device for aiding the piloting of an aircraft while respecting a time of arrival constraint at a first waypoint during a phase of descent. The method includes calculating an instant of arrival of the aircraft at an intermediate waypoint, in such a way that an estimated latest time of arrival at the first waypoint, corresponding to a minimum speed profile, occurs later by a predetermined first margin than the time of arrival constraint; determining a first speed profile between a current position of the aircraft and the intermediate waypoint, such that the intermediate waypoint is crossed at the calculated instant of arrival; determining a second speed profile, such that the first waypoint is crossed within the time of arrival constraint, starting from the intermediate waypoint at the calculated instant of arrival; and piloting the aircraft according to the first and then second speed profiles.

Abstract: Disclosed is a method and device for generating an aircraft ground path for piloting an aircraft along the ground of an airport domain. Geographical coordinates of reference points corresponding to a series of elements of the airport domain that the aircraft is to successively follow are obtained and converted to a metric frame. Points of intersection of the successive elements are then determined, as well as an auxiliary path for the aircraft to follow, based on the converted geographical coordinates. A turn at each of the intersection points is next determined, and the aircraft ground path is generated from each of the determined turns.

Abstract: An unmanned aerial vehicle comprises a housing, a rotor that is rotated to propel the housing, a pressure sensor that generates a signal indicative of an air pressure proximate a bottom surface of the housing, and a processor configured to determine, based on the signal, when an increase in air pressure proximate the bottom surface is greater than or equal to a threshold value associated with the ground effect of the rotor, wherein the processor controls the rotor to cease rotating or decrease rotational speed to land the unmanned aerial vehicle upon determining that the increase in pressure is greater than or equal to the threshold value.

Abstract: The present invention relates to a method and a device for monitoring the minimum flying altitude of an aircraft.

Abstract: There is provided an information processing apparatus capable of communicating with an information management apparatus storing service information including place information, service content information, and start time information; the information processing apparatus including a communication portion; a position measurement portion for generating positional information; a data acquiring portion for acquiring, based on an input search condition, service information satisfying the search condition from the information management apparatus; and a list generating portion for generating a presentation list recorded with information on a service providing place capable of receiving the service at a provision start time based on the positional information, the place information and the start time information of the acquired service information, and time information defining a time the positional information is generated.

Abstract: The invention relates to a method for controlling the formation flight of at least two aircraft (1,2). The first aircraft (1) includes means of transmitting its position, its velocity and its flight plan. The flight plan has predictions of altitude, velocity and time for at least one next waypoint (WPT). The second aircraft (2) includes means of receiving the information transmitted by the first aircraft (1). According to the invention, the second aircraft (2) determines its future flight plan as a function of the information received from the first aircraft (1) in order to maintain a constant separation (T) from the first aircraft (1).

Abstract: A system for controlling flight of an aircraft has sensors, a receiver, and a digital control system, all of which are carried aboard the aircraft. The sensors determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver receives transmitted data communicating the position and movement of a reference vehicle relative to the earth. The control system calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors and the receiver and then commands flight control devices on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

Abstract: The disclosed embodiments concerns a system for monitoring anemobaroclinometric parameters in an aircraft, including a primary detection circuit having at least one measurement channel. The measurement channel includes a device for measuring static air pressure, a device for measuring a side-slip angle of the aircraft, a device for measuring a dynamic pressure, a total air temperature and a angle of attack of the aircraft, and a data-processing device capable of determining anemobaroclinometric parameters from the measurements of static pressure, side-slip angle, dynamic pressure, total air temperature and angle of attack, a least one laser anemometer to measure at least one true airspeed parameter of the aircraft.

Abstract: Method and device for assisting the piloting of an aircraft. The device (1) comprises means (4) for determining, using a roll instruction and measured current values of external characteristics and of flight characteristics of the aircraft, a predicted path which is a flight path having a constant roll angel, taking account of the effect of the wind.

Abstract: Methods and systems for displaying assistance messages to aircraft operators are disclosed. A method in accordance with one embodiment includes receiving an input from an aircraft operator at an aircraft flight deck, comparing a characteristic of the input to at least one target value for the characteristic, and, if the characteristic of the input differs from the at least one target value for the characteristic by at least a threshold amount, displaying an assistance message to the aircraft operator. The assistance message can include a complying input and/or an instruction for creating a complying input. The input and the assistance message can be displayed simultaneously.

Abstract: A method and device automatically engage an emergency descent function of an aircraft as a function of pressure variation measured in the cabin of the aircraft.

Abstract: A method for estimating engine thrust values of an aircraft is disclosed, the method comprising calculating estimated thrust value of an engine based on an equation of longitudinal motion, aircraft data measured during flight and calibrated drag/lift models, and a method for determining the thrust of an aircraft engine, based on information available from tracking the aircraft air-speed, acceleration, and position, the method comprising calculating the thrust, using the following equation: Thrust=mg{dot over (H)}/V+m{dot over (V)}+Drag.

Abstract: A vertical profile for an in-trail procedure can provide a pilot with enhanced situational awareness. Such a vertical profile may be able to provide a graphical indication of a clearance window for change in altitude procedures, as well as the underlying bases for such a window. A method can include providing, in a hardware display, a graphical vertical profile displaying an aircraft to a pilot of the aircraft. The method can also include providing, in the vertical profile, an indication of the relative speed of at least one other aircraft and a graphical indication of a clearance window for vertical maneuvers for the aircraft of the pilot.

Abstract: A system for controlling flight of an aircraft has sensors, a receiver, and a digital control system, all of which are carried aboard the aircraft. The sensors determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver receives transmitted data communicating the position and movement of a reference vehicle relative to the earth. The control system calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors and the receiver and then commands flight control devices on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

Abstract: The device (1) comprises means for registering, in case of detection of a ground taxiing of the aircraft, the last value of static pressure corrected from induced aerodynamic effects.

Abstract: A vertical take-off and landing aircraft that includes AC motors, which drive fans that propel the aircraft, and a control device for controlling the AC motors adaptively based on a thrust control amount from an attitude controller. In particular, the drive controller performs switching to convert DC from a power source to three-phase AC at a predetermined frequency to be supplied to the AC motors. The drive controller reduces the control frequency of the three-phase AC to be applied to the AC motor to reduce the control resolution when the flight mode is switched from a vertical flight control mode to a horizontal flight control mode, in which the control amount to correct the external forces is smaller. Therefore, it is possible to reduce the power loss in the controller and thus the power consumption compared to conventional vertical take-off and landing aircrafts, in which the control resolution is always constant.

Abstract: A positioning device that detects a position of a mobile body with a radio navigation positioning unit includes: first and second autonomous sensors obtaining behavioral information on the mobile body; a position detecting unit obtaining an estimated position and an estimated direction by updating a detection result based on the behavioral information from the first autonomous sensor; a map data positioning unit that refers to a map data storage unit based on the estimated position and obtains a map data linked position at a predetermined distance away from a link; a direction detecting unit obtaining a cumulative estimated direction by updating the detection result based on the behavioral information from the second autonomous sensor; and a most probable position estimating unit estimating the position of the mobile body from the estimated positions and directions using the Kalman filter.

Abstract: An in-vehicle communication system includes a control unit which locates coupling points of each one of active speaker units to in-vehicle network. The plurality of the active speaker units includes a plurality of acoustic characteristics set data and programs for determining their own addresses. The respective active speaker units thus can be coupled to in-vehicle network without changing their software, and acoustic characteristics values in response to their coupling points in the vehicle can be established.

Abstract: This method facilitates the joining, by an aircraft, of a secure zone, without constraint of deployment in the horizontal plane, in particular when the latter is threatened by a risk of collision with the ground or by a risk of penetration into a forbidden zone which cannot be resolved by a purely vertical avoidance maneuver. It consists in selecting a point for joining a zone of free lateral deployment by means of a criterion of minimum cost of the initial maneuver of turning at the start of the trajectory for joining the possible points of access to the zones of free lateral deployment.

Abstract: A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.

Abstract: A system for controlling flight of an aircraft has sensors (37, 43), a receiver (45), and a digital control system (57), all of which are carried aboard the aircraft. The sensors (37, 43) determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control system (57) calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors (37, 43) and the receiver (45) and then commands flight control devices (33) on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

Abstract: Methods and a system for a vehicle control system using a reference time profile including an upper control bound and a lower control bound are provided. The system includes an input device configured to receive a required time of arrival at a waypoint and a processor communicatively coupled to said input device wherein the processor is programmed to generate a reference time profile using a first speed profile up to an intermediate control point and a second speed profile between the intermediate control point and an RTA waypoint. The system also includes an output device communicatively coupled to the processor wherein the output device is configured to transmit a speed control signal based on the reference time profile to a vehicle speed control system.

Abstract: Methods and systems for operating an avionics system on-board an aircraft are provided. A plurality of signals representative of a current state of the aircraft are received. A future state of the aircraft is calculated based on the plurality of signals representative of the current state of the aircraft. An indication of the future state of the aircraft is generated with the avionics system on-board the aircraft.

Abstract: A device detects an air disturbance and controls the deflection of aircraft control surfaces when the disturbance is detected.

Abstract: An avionics system comprising a primary airspeed data source and a flight management computer is provided. The primary airspeed data source is configured to calculate a primary airspeed. The flight management computer is configured to use airspeed as an aid to control an aircraft, wherein the flight management computer is further configured to determine an alternative airspeed for use by the flight management computer as an aid to control an aircraft when the primary airspeed is unavailable.

Abstract: An avionic aviation system including: a ground station that is linked to an aircraft via a wireless interface; wherein the ground station includes, a receiver that receives, via a wireless interface, a transmission from a detection device integrated in avionics of the aircraft, said transmission including a parameter regarding at least one of takeoff and landing of the aircraft, and a counter module that increments a value based on the parameter regarding at least one of takeoff or landing for the aircraft.

Abstract: An inertial navigation system which includes a first control system and a second control system is described. The first control system is configured to estimate a vertical velocity based in part on received vertical acceleration data. The second control system is configured to receive the estimated vertical velocity from the first control system and determine a compensated vertical velocity utilizing the estimated vertical velocity and airspeed.

Abstract: This invention relates to a system for estimating the position, velocity and orientation of a vehicle, by determining the components of two noncollinear constant unit vectors b,b according to vehicle body axes; and determining the components of the noncollinear constant unit vectors {right arrow over (g)}t,{right arrow over (e)}t according to Earth's axes.

Abstract: A method for estimating inertial acceleration bias errors including obtaining uncorrected acceleration measurements on board a vehicle; obtaining independent position and independent velocity data of the vehicle; transforming the uncorrected acceleration measurements into a reference frame of the independent position and independent velocity data; blending the transformed acceleration measurements with the independent position and the independent velocity data to produce feedback errors; transforming the feedback errors into the reference frame of the acceleration measurements; multiplying the feedback errors by a gain and integrating to estimate the acceleration measurement bias errors.

Abstract: Systems and methods are disclosed that monitor movement of a person, or of a vehicle ridden by the person, to determine speed, distance traveled and/or airtime of the person or vehicle. Accelerometer-based sensors, pressure sensors or Doppler sensors may be employed in these systems and methods. A liquid crystal display may attach to the person to display speed, distance traveled and/or airtime.

Abstract: A method and a device for obtaining a predictive vertical speed of a rotorcraft, the device constituting a predictive vertical speed indicator (1) that includes at least: first elements (1?) for measuring the instantaneous vertical speed v of a rotorcraft; second elements (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; and third elements (3) for calculating the predictive vertical speed vAP of a rotorcraft, the third elements being connected firstly to the first and second elements via respective first and second connections (l1, l2) and containing in memory predetermined values for the minimum-power speed VY and a characteristic constant k that are constants relating to the rotorcraft of a given type of rotorcraft.

Abstract: A method of measuring the state of flow above an airfoil using an estimation of the velocity field based on a combination of Particle Image Velocimetry PIV and multiple surface pressure measurements processed through a POD/mLSE algorithm. Integral to the POD/mLSE algorithm is the estimation of the global POD coefficients. The utility of these time dependent coefficients, which are estimated from surface pressure only, are demonstrated in a simple proportional feedback loop (as the time series to drive the actuators) to keep the flow attached. This method requires realistic feedback flow control since surface measurements and not inflow measurements are required for practical applications. The estimation method works well with dynamic strain on flexible bodies and is not limited to estimation from pressure only.

Abstract: A flight control system includes a collective position command module for a lift axis (collective pitch) which, in combination with an active collective system, provides a force feedback such that a pilot may seamlessly command vertical speed, flight path angle or directly change collective blade pitch. The collective position command module utilizes displacement of the collective controller to command direct collective blade pitch change, while a constant force application to the collective controller within a “level flight” detent commands vertical velocity or flight path angle. The “level flight” detent provides a tactile cue for collective position to reference the aircraft level flight attitude without the pilot having to refer to the instruments and without excessive collective controller movement.

Abstract: Systems and methods for aircraft guidance using a localizer capture criteria for rectilinear displacement data are disclosed. In one embodiment, the method includes determining a rectilinear deviation D between a current aircraft location and a final defined path (FDP) of an aircraft and determining a location at which the aircraft should begin a reposition maneuver based on the rectilinear deviation D. The method starts a reposition maneuver of the aircraft at a location determined based on a relationship between D and characteristics of the aircraft during the reposition maneuver. In some embodiments, the characteristics of the aircraft may include a velocity of the aircraft with respect to ground, an aircraft track angle, a heading of the FDP of the aircraft, a maximum allowed bank angle of the aircraft during a reposition maneuver, and a time allowance for aircraft rollup and rollout.

Abstract: Embodiments of the present invention provide methods, computer programs, and apparatus for adjusting a speed target of an aircraft. In particular, the adjustment of the speed target of the aircraft may allow that aircraft to maintain merging and spacing constraints with respect to a leading aircraft. According to one embodiment of the present invention, the speed target of an aircraft may be adjusted by obtaining a speed target, obtaining own ship track data for the aircraft, obtaining lead ship track data for a leading aircraft, and calculating a speed target adjustment based on the speed target, the own ship track data, the lead ship track data and merging and spacing constraints.

Abstract: The TAWS system, in addition to an FTLA function for detecting the risk of collision with the terrain, has an end-of-conflict announcement function COT which is activated after the cessation of a warning or alarm concerning the risk of collision with the ground originating from the FTLA function. This COT function, when activated, checks that the aircraft (A) is observing minimum vertical and lateral safe distances, and estimates the lower vertical speed margin with which a new ground collision risk warning will not be retriggered. After confirming the observance of the minimum safe distances, the COT function has an end-of-conflict message (“Clear of terrain”) sent with a lower vertical speed margin indication.

Abstract: A portable communication device detects a current speed of travel of the portable communication device independent of any vehicle temporarily transporting the portable communication device. A speed based setting controller of the portable communication device compares the current speed to at least one threshold value set at the portable communication device. Responsive to the current speed exceeding the threshold value, the speed based setting controller automatically assigns a separate speed based setting to a current setting for each feature assigned to the threshold value, wherein each current setting for each feature designates the operability of that feature within the portable communication device, such that the current setting for each feature adjusts with a speed of travel as detected by the portable communication device.