Abstract: A method for providing for the optimized regulation of the relative spacing between aircraft is disclosed. This method can be implemented by a system whose physical architecture can rely mainly on existing computers on board most current aircraft. The method includes a main step of determining the changing trend of the relative spacing, in distance or in time, between a target aircraft (C) and a following aircraft (S).

Abstract: A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight

Abstract: Systems and methods for providing vehicle-centric collision avoidance are disclosed. In one embodiment, a method includes determining a first flight trajectory for a first aircraft. The method also includes determining a second flight trajectory for a second aircraft. A distance between the first aircraft and the second aircraft at a first closest point of approach (CPA) is predicted. The predicted closest point of approach is then compared to a separation perimeter layer. The separation perimeter layer is configured to provide a minimum separation distance from the first aircraft to the second aircraft. When the predicted closest point of approach breaches the separation perimeter, the first flight trajectory is altered to provide collision avoidance.

Abstract: The present invention models dynamic behavior of flight vehicles for simulation, analysis, and design. The present invention allows a user to define the complexity of a flight vehicle model, and such models may be simple rigid body models, models of medium complexity, or very complex models including high order dynamics comprising hundreds of structural flexibility modes and variables related to aero-elasticity, fuel sloshing, various types of effectors, tail-wags-dog dynamics, complex actuator models, load-torque feedback, wind gusts, and other parameters impacting flight vehicles. The present invention accommodates and analyzes multiple vehicle and actuator concepts and configurations as defined in flight vehicle input data, which specifies flight vehicle parameters at a steady-state condition for modeling flight vehicle response to dynamic forces and flight control commands with respect to steady state operation.

Abstract: The device for checking speed intended for an aircraft ready to land on deck on a moving vehicle, the aircraft having a current vertical speed, called the first speed, and a threshold value of vertical downward speed relating to the vertical speed of the moving vehicle, called the “low threshold”, the ship having an absolute vertical speed, called the second speed, comprises a display and means for receiving data originating from the aircraft, notably its vertical absolute speed. The device includes a calculator making it possible to generate on the display a graduated speed gauge including a fixed cursor indicating the first vertical speed and a second moving cursor indicating the speed of the ship, a third moving cursor indicating the low threshold, the graduation being centered around the value of the first vertical speed.

Abstract: A system and a method for commanding a spacecraft to perform a three-axis maneuver purely based on “position” (i.e., attitude) measurements. Using an “inertial gimbal concept”, a set of formulae are derived that can map a set of “inertial” motion to the spacecraft body frame based on position information so that the spacecraft can perform/follow according to the desired inertial position maneuvers commands. Also, the system and method disclosed herein employ an intrusion steering law to protect the spacecraft from acquisition failure when a long sensor intrusion occurs.

Abstract: Methods and apparatuses for displaying and receiving tactical and strategic flight guidance information are disclosed. A method in accordance with one aspect of the invention includes displaying at least one first indicator to an operator of the aircraft, with a first indicator corresponding to a first instruction input by the operator for directing a first aircraft behavior and implemented upon receiving an activation instruction from the operator. At least one second indicator corresponding to a second instruction for directing a second aircraft behavior at least proximately the same as the first aircraft behavior is displayed, with the at least one second instruction to be automatically implemented at a future time. The at least one second indicator is at least approximately the same as the at least one first indicator. Indicators can be hierarchically organized to simplify presentation and reduce pilot training time.

Abstract: Embodiments of a process are provided suitable for implementation by an avionics display system deployed on a host aircraft and including a monitor. In one embodiment, the process includes the step of receiving air traffic data indicative of a first flight characteristic pertaining to a neighboring aircraft. The first flight characteristic is selected from the group consisting of: (i) the wake turbulence created by the neighboring aircraft, (ii) the current flight plan of the neighboring aircraft, and (iii) the airspace in which the neighboring aircraft's current detection position should reside to ensure that the neighboring aircraft's actual position resides within the an airspace currently assigned to the neighboring aircraft. A visual representation of the first flight characteristic is generated on the monitor.

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: Disclosed are a method and device for attenuating vertical turbulence encountered by an aircraft during flight. Incorporated into the method and device is a wind determination device, which is used to determine a vertical wind component existing outside the aircraft. A severity level determination unit is used to determine a severity level of the vertical wind component determined by the wind determination device. A control unit calculates at least one control order based on the vertical wind component determined by the wind determination device. In addition, the control unit determines the actual existence of activation conditions determined according to the severity level determined by the severity level determination unit. Upon verifying the activation conditions, the control unit transmits the control order to at least one actuator of the at least one controllable movable member.

Abstract: A method and device control the thrust of a multi-engine aircraft. At least one engine command is determined by a command determining unit, with the determined command commanding each engine that has not failed to deliver a thrust substantially equal to a reduced thrust value. A command application unit is configured to apply the determined command to each aircraft engine that has not failed. The reduced thrust value is determined, by a weight determining device, according to the current weight of the aircraft and according to a reduced thrust value FOEI, which is calculated by a thrust calculation unit.

Abstract: A method and apparatus for managing solar power collection. A position of the sun is identified relative to an aerospace vehicle while the aerospace vehicle is moving along a flight path. A level of power generation is identified by a solar power generation system while the aerospace vehicle moves along the flight path using a threat management module and equivalent radar signature data. The threat management module uses the equivalent radar signature data to identify the level of power generation by the aerospace vehicle from different positions of the sun relative to the aerospace vehicle, and the equivalent radar signature data is based on solar power generation signature data identifying the level of power generation for the different positions of the sun relative to the aerospace vehicle. A change in the flight path that results in a desired level of power generation is identified by the solar power generation system.

Abstract: A method for pointing control of a laser communication terminal on a spacecraft may include measuring a line-of-sight (LOS) error of the laser communication terminal. The method may also include estimating a LOS error of the laser communication terminal based on measurements from a spacecraft gyro and a gimbal gyro onboard the spacecraft. The method may further include switching from a LOS error measurement feedback to a LOS error estimate feedback to control pointing of the laser communication terminal during a power fade condition.

Abstract: A method of providing a relative navigation system by projecting into space from a first object a grid that is repeatedly detected from a second object having a second relative reference frame associated with a second origin point on the second object and using range and attitude between the objects to adjust the attitude or range of at least one of the first and second objects.

Abstract: Technologies are described herein for providing additional yaw control to a multi-engine aircraft experiencing engine thrust asymmetry. A primary flight control system of the aircraft is configured to limit the operational thrust of an operating engine of the aircraft to provide additional yaw control when the aircraft is experiencing thrust asymmetry. The system includes a thrust limit module for calculating the maximum engine thrust limit to be imposed on an operating engine. The maximum engine thrust limit is calculated using inputs corresponding to the sideslip angle and the roll rate of the aircraft. The maximum engine thrust limit is imposed on the operating engine of the aircraft such that the operational thrust generated by the operating engine is limited to the maximum engine thrust limit. By reducing the operational thrust generated by the operating engine, the yawing caused by the thrust asymmetry is likely to be reduced.

Abstract: The inventive flight control assisting device comprises first means (4) for determining the actual aircraft flight conditions, second means (5) for determining, with the aid of said actual flight conditions and a predetermined pattern, a minimum approaching distance corresponding to a minimum distance between projections on the horizontal plane of the aircraft actual position and a touch-down point when said aircraft moves downwards and decelerates according to an optimised approach in such a way that stabilised approaching conditions are attained, and display means (7) for displaying at least said minimum approaching distance on a navigation screen (9) in the form of a first circular arc focused on a position relative to the aircraft which displays the touch-down position.

Abstract: An integrated system for providing a reporting point journey log display in an aircraft and for providing the automatic transfer and installation of a reporting point journey log in a ground retention application. The integrated system includes means for procuring and aggregating reporting point on-board aircraft data from aircraft systems. Means are provided for generating a reporting point cockpit message and readback script from the aggregated reporting point onboard aircraft data. The aggregated reporting point onboard aircraft data is automatically transmitted to a receiving ground application for assembling the data into the form of a reporting point journey log. The reporting point journey log is installed into a ground storage application.

Abstract: The invention relates to a method for determining the speed of an aircraft that is subject to a time constraint. The invention consists no longer in calculating a single CAS/MACH pair during climb/descent but in adapting the speed in a continuous manner to the bounds of curves of minimum Vmin and maximum Vmax speed defining a flight envelope of the aircraft. The calculation of these speeds is carried out on the basis of constant maximum and minimum speed setpoints and of a coefficient taking into account a deviation to the time constraint.

Abstract: A method and apparatus for searching and generating trajectory content in a navigation device are provided. The method includes establishing a predetermined search region from a current position; extracting information about first parcels included in the established search region and information about second parcels including information about links of specific trajectory content; and determining whether the specific trajectory content is included in the established search region by comparing the information about the first parcels with the information about the second parcels.

Abstract: A method for estimating an angle of attack and an angle of sideslip of an aircraft having a plurality of control surfaces each adjustable with respect to an associated reference surface. The method includes measuring quantities representative of the angle formed by each control surface with respect to the associated reference surface, and measuring an effective rolling speed, an effective pitching speed, and an effective yawing speed of the aircraft. A linearized model of a state observer is defined according to the following equations: { ? x .

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: A method of determining environmental data along a trajectory of an aircraft may assist in the evaluation of flight conditions along the trajectory. Environmental data may be at least one of collected, derived, and fused from a plurality of weather sources using at least one processor. The environmental data may be filtered, extrapolated, and fused, using the at least one processor, within at least one selected volume of airspace over a trajectory of the aircraft based on selected weather-applicability time intervals, and on at least one of user-selected parameters and weighted environmental data criteria. The trajectory may comprise at least one of a planned trajectory, a current trajectory, and an intent trajectory of the aircraft. An effect of the filtered, extrapolated, and fused environmental data on the trajectory may be determined using the at least one processor.

Abstract: A method for calculating a safe extraction path from a terrain-challenged airport that does not depend upon published procedures. The method includes the steps of: a) defining at least one containment zone for a circling climb departure path relative to a reference location; b) receiving aircraft performance data from an on-board flight management system; c) receiving air mass parameters from on-board aircraft sensors; d) calculating the maximum allowable climb altitude (MACA) utilizing the at least one containment zone, the received aircraft performance data, and the received air mass parameters; and, e) comparing the MACA to at least one selected safe departure altitude (SDA) to calculate the lowest possible descent altitude that can be achieved while ensuring that at least one safe extraction path exists.

Abstract: Illustrative computer-executable methods, systems, and computer software program products predict cruise orientation of an as-built airplane. In illustrative embodiments, nominal orientation of an as-built airplane is input. Deviation from the nominal orientation of the as-built airplane is automatically computed, and the computed deviation from the nominal orientation of the as-built airplane is applied to the nominal orientation of the as-built airplane.

Abstract: Biodynamic feedthrough in a master control system can be mitigated. An accelerometer is used to measure the acceleration of an environment. In one embodiment, mitigation damping forces can then be determined based on the velocity of an effector of a haptic manipulator and the measured accelerations. The haptic manipulator applies the mitigation damping forces as force feedback. In another embodiment, biodynamic feedthrough can be filtered from the input signal. Parameters for a model can be accessed based on the position of the effector, and the model can be used to predict biodynamic feedthrough from the measured accelerations.

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: Methods and systems for operating an avionics system are provided. A set of data that is representative of traffic advisory information is received. A visual indicator is displayed to a user based on the set of data that is representative of the traffic advisory information. The traffic advisory information may be received by a user through a receiver and manually entered into an interface for viewing. Alternatively, the avionics system may automatically generate the visual indicator based on the traffic advisory information.

Abstract: Provided is an altitude measurement apparatus and method that may measure an altitude of an aircraft without using a separate altimeter. The altitude measurement apparatus may include a camera unit being provided to a vertical takeoff and landing (VTOL) aircraft to collect an image of a circular mark formed on the ground, and a calculation unit to calculate an altitude of the VTOL aircraft based on the collected image. Accordingly, the altitude measurement apparatus may measure the altitude using a simple structure such as the circular mark formed on the ground, and be configured at inexpensive costs.

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: A system for converting audible air traffic control instructions for pilots operating from an air facility to textual format. The system may comprise a processor connected to a jack of the standard pilot headset and a separate portable display screen connected to the processor. The processor may have a language converting functionality which can recognize traffic control nomenclature and display messages accordingly. Displayed text may be limited to information intended for a specific aircraft. The display may show hazardous discrepancies between authorized altitudes and headings and actual altitudes and headings. The display may be capable of correction by the user, and may utilize Global Positioning System (GPS) to obtain appropriate corrections. The system may date and time stamp communications and hold the same in memory. The system may have computer style user functions such as scrollability and operating prompts.

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: A positioning system for aerial refueling of an aircraft provided with a first element for connection with a second element arranged on a tanker plane. The first and second elements are adapted to feed fuel from the tanker plane to the aircraft. A receiver on the aircraft is arranged to receive signals from the second element. A control unit on the aircraft controls the aircraft depending on the signals to steer the aircraft to a position for connecting the first and second elements.

Abstract: Device for servoing graphical representations of the aerial environment for aircraft, an avionics the device including a display, a computer and memory in communication with the computer, the memory storing means for generating images of environmental data, said data being servoed by the first calculation resource and periodically refreshed in a first time interval. The device comprises a calculation resource providing an angle of heading of the aircraft relative to North and its geo-referenced current position, these data being servoed, periodically, in real time in a second time interval. The representation of a part of the environmental data on the viewing screen of the device is servoed and refreshed during the second time interval and positioned and oriented graphically, by the display, according to the last current angle of the position of the aircraft calculated and of the last geo-referenced current position.

Abstract: The device includes means for determining a plurality of successive standard flight sections (S1A, S2A, S3A, S4A) comprising a level and a transition phase for reaching this level, and means for joining together these successive flight sections (S1A, S2A, S3A, S4A) in order to form the vertical profile (PV1) of the flight plan.

Abstract: The method of optimizing the exit of an aircraft traversing for a known duration (D) a holding circuit forming a racecourse comprising two parallel branches of the same distance, the branches being traversed in a first time (t1), and two arcs of the same radius linking respectively the ends of each branch, the two arcs being traversed in a second time (t2), the holding circuit comprising an exit point situated at the end of one of the branches is characterized in that the distance of the branches of the holding circuit for the last two loops performed are adjusted so that the aircraft is substantially in proximity to the exit point when the duration (D) has elapsed.

Abstract: Disclosed is a method and device, which provide an enhanced ability to monitor the navigation of an aircraft during a phase of flight in which the aircraft is close to the ground in which the aircraft uses positional information supplied by a satellite positioning system for the navigation. A display screen is used to display a first characteristic sign representing a selected setpoint value for a height parameter of the aircraft. The display screen also displays a second characteristic sign representing a current auxiliary value expressed in the form of an achievable height parameter. An alert is emitted when the second characteristic sign is determined to be within a predetermined height value of the first characteristic sign, and the alert is shown in visual format on the display screen. An alarm is also emitted following a predetermined time after the alert is emitted, if the setpoint value is not replaced by a new setpoint value.

Abstract: A system and method of controlling a gas turbine engine controller in a rotorwing aircraft includes determining when a fixed collective takeoff (FCTO) of the rotorwing aircraft is being conducted. A control loop gain of the gas turbine engine controller is at least selectively varied when the FCTO is being conducted.

Abstract: A system and method for displaying aircraft traffic information on an onboard display element of a host aircraft are provided. The system obtains current flight status data of the host aircraft and current flight status data of a second aircraft that is near the host aircraft, and processes the current flight status data of the host aircraft and the current flight status data of the second aircraft to determine an in-trail procedure (ITP) opportunity region for the host aircraft. The ITP opportunity region is associated with conditions that satisfy ITP criteria for the host aircraft. The system renders, on the onboard display element, an ITP display comprising graphical representations of the host aircraft and the second aircraft positioned in accordance with the current flight status data of the host aircraft and the current flight status data of the second aircraft. The ITP display further includes a graphical representation of the ITP opportunity region.

Abstract: An autopilot system includes a navigation application for computing angular position and angular turn rate of a pilot line and an autopilot steering application for calculating steering commands for a ship steering device. The pilot line provides directional guidance to a ship and is a vector having one end attached to a point on the ship and a second end pointing to a desired direction. The autopilot steering application receives the computed pilot line angular position and angular turn rate and calculates angular position steering commands for the steering device. The steering commands are calculated by taking into account the difference between the pilot line angular position and the ship's angular position and the difference between the pilot line angular turn rate and the ship's angular turn rate.

Abstract: An inertial system measures the attitude of an aircraft consisting at least in determining the angle of pitch and/or the angle of heading and/or the angle of roll of the aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative. A pair of accelerometers to determine the angle of pitch being are disposed on either side of the centre of gravity along an axis substantially merged with the longitudinal axis of the aircraft. A pair of accelerometers to determine the angle of heading are disposed on either side of the centre of gravity along an axis substantially merged with the transverse axis of the aircraft. A pair of accelerometers to determine the angle of roll are disposed on either side of the centre of gravity along a vertical axis perpendicular to the plane formed by the other axes.

Abstract: A method and apparatus for managing separation between vehicles. A closest point of approach between a first vehicle traveling along a first path and a second vehicle traveling along a second path is predicted. A number of compensation commands for altering the first path of the first vehicle are generated using the closest point of approach and a desired level of separation between the first vehicle and the second vehicle. The number of compensation commands is integrated with a number of control commands for the first vehicle to form a final number of control commands configured to maneuver the first vehicle to substantially maintain the desired level of separation between the first vehicle and the second vehicle. A response of the first vehicle to the final number of control commands is a desired response.

Abstract: An automatic fore/aft detection procedure as described herein may be implemented in connection with an aircraft brake control system that utilizes wheel-mounted accelerometers that detect landing gear acceleration for purposes of antiskid control. The fore/aft detection procedure automatically determines that the aircraft is moving in a forward direction based upon the current wheel speed and rotational direction of the wheels. Once detected, forward direction is assigned to the rotational direction of each wheel (clockwise or counterclockwise) and a fore/aft orientation can be assigned to the accelerometer for each wheel.

Abstract: The invention relates to a database and a method of generating a database containing topographical information on obstacles distributed over a geographic area subdivided into cells. The method includes reading topographical data obtained from heterogeneous sources. Topographical data are generated which relate to pointlike obstacles from the information collected from the topographical data. Topographical data are generated which relate to linear obstacles from the information collected from the topographical data. The obstacle database is created. Each cell contains a link to the obstacles whose coordinates in the geographic area covered by the cell are recorded with an uncertainty value. In particular, the invention applies to the generation of a database on board an aircraft.

Abstract: The electro-optical system for determining the attitude of a mobile part comprises a fixed part and a mobile part, the fixed part being linked rigidly with at least one virtual image plane. The mobile part is linked rigidly with at least one first linear electro-optical device defining a first direction vector, the calculation of the position of the vanishing point of the projection of the straight line comprising the first direction vector in the image plane determining a first direction, representing the direction of the mapping of the first direction vector in the image plane, and a first choice of a first point of the projection in the image plane of the straight line comprising the first direction vector determining a first sense, representing the sense of the mapping of the first direction vector in the image plane.

Abstract: A missile has a pair of systems to provide acceleration information during flight. The primary system is a microelectromechanical systems (MEMS) inertial measurement unit (IMU) that provides accurate rate sensor output, such as providing pitch and yaw rates, at low cost, over a wide range of conditions. However MEMS IMUs are susceptible to temporary incorrect responses when subjected to shocks, such as acoustic-range shocks, for instance in the range of 10-20 kHz. The missile includes a secondary system to temporarily provide acceleration data during the periods following shocks, when the MEMS IMU does not provide valid (reliable or usable) rate sensor output, for use in estimating pseudo pitch and yaw rates. The secondary system may be an accelerometer that does not provide navigation-quality acceleration data, but does provide a sufficiently accurate response in order to maintain stable flight during the post-shock period.

Abstract: The present invention relates to haptic feedback for operating at least one manual flight control device (21) for controlling the cyclic pitch of the blades (5) of a rotary wing (4) of a hybrid helicopter (1) via power assistance (27). Said operations of said control device (21) are defined according to a predetermined damping force relationship (A) that is a function of an instantaneous load factor of the hybrid helicopter (1) in such a manner that the instantaneous load factor is maintained between its minimum and maximum limit values in proportion to a position of a thrust control member (20) between its minimum and maximum thrust values (23, 22).

Abstract: A method of adjusting the trajectory of an aircraft flying a climb circuit, of substantially helical form corresponding to a succession of racetracks, denoted HOLD, the last HOLD, called the exit HOLD, having predefined geometric characteristics and comprising a lock-on point, allowing the aircraft to enter and to exit in the HOLD, the aircraft attaining the setpoint altitude of the climb circuit during the flight of the exit HOLD, comprises at least three steps, including: a step of computing the prediction of the position of the aircraft when the setpoint altitude will be attained; a step of computing the remaining distance to be traveled, between the position of the aircraft when the setpoint altitude will be attained and the lock-on point; and a step making it possible to carry out an adaptation of the form of the exit HOLD so as to minimize the remaining distance to be traveled DELTA.

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: A system for estimating at least one of position, attitude, and heading of a vehicle is disclosed. The system includes at least three gyroscopes configured to output a signal indicative of inertial angular rates around three mutually orthogonal axes of the vehicle and at least three accelerometers configured to output a signal indicative of accelerations along three mutually orthogonal axes of the vehicle. The system further includes a triaxial magnetometer configured to output a signal indicative of a projection of ambient magnetic field on three mutually orthogonal axes of the vehicle. The system also includes a sensor configured to output a signal indicative of vehicle altitude and a differential pressure sensor configured to output a signal indicative of airspeed of the vehicle. The system further includes a device configured to receive the signals and estimate at least of one of position, attitude, and heading of the vehicle.

Abstract: Disclosed is a method and system for managing a convoy of aircraft during taxiing. Taxi management is carried out by exchanging, by a first data transmission unit, information between the aircraft of the convoy concerning aircraft flight parameters of the aircraft within the convoy, and exchanging, between the aircraft of the convoy and at least one control station that manages the convoy collectively, information relating to the collective convoy. The exchange can be carried out by a second data transmission unit, with the ground control station receiving from each aircraft in the convoy information relating to convoy status, centralizing the received information, scheduling the convoy, and transmitting to each aircraft a convoy status table that indicates overall status of the convoy.