Abstract: A method and apparatus for displaying information for an aircraft. Information is identified for the aircraft. An aeronautical chart is displayed on a display system. An envelope is displayed in the aeronautical chart based on the information. The envelope defines a space flyable by the aircraft that meets a number of objectives.

Abstract: A method of approximately correcting a vehicle's guidance system command for the disturbing effects of the medium through which it is moving, without having to sense or estimate the speed and direction of that medium. The correction is determined by taking the ratio of two scalar quantities: the speed of the vehicle relative to the medium, which can be estimated from the known fluid dynamic characteristics of the vehicle, divided by an approximation of inertial speed, which can be obtained using one or more on-board sensors such as a GPS, thus increasing transient performance of the vehicle moving through the fluid medium.

Abstract: Methods and devices for calculating an estimate of a wind vector. A maneuver of a platform may be identified as a steady-straight motion maneuver, a partial turn maneuver, or a full turn maneuver. A preliminary estimate of a wind vector corresponding to a wind condition prevailing near the platform may be calculated by applying a maneuver-specific calculating method. A gain associated with the preliminary estimate of the wind vector may be calculated by applying a state-specific calculation method. A filtered estimate of the wind vector may be updated based, at least in part, on the preliminary estimate of the wind vector and the gain associated with the to preliminary estimate of the wind vector.

Abstract: A monitoring device automatically monitors lateral guidance orders of an aircraft. The device includes a failure monitoring device for implementing comparisons between roll control orders generated by a number of equipments in order to be able to detect a failure of one of the equipments concerning the generation of lateral guidance orders of the aircraft. Additionally, the device includes a failure anticipation comparator device for analyzing inlet parameters of the equipments to determine when a failure of one of the equipments should be anticipated.

Abstract: A method for providing one or more aircraft with weather data during flight includes generating a weather model using a source of weather data. The weather model incorporates flight operations information and performance requirements. The method includes generating a weather message from the weather model. The weather message is generated in a format that is compatible with the aircraft. The method also includes transmitting the weather message to the aircraft during flight of the aircraft.

Abstract: A display system for an aircraft is provided. The system includes a processing unit configured to receive weather information associated with a flight path of a flight plan and to generate display commands based on the weather information. The flight plan includes a first waypoint associated with a first altitude. The system further includes a display device coupled with the processing unit and configured to receive the display commands and to display symbology representing the weather information. The weather information includes first weather information for the first altitude and second weather information at a second altitude, different from the first altitude.

Abstract: A system and method for controlling a display of geographical data on a primary display device to assist in navigating a mobile platform such as an aircraft, ship, train, land-based motor vehicle, etc. The system includes a graphical user interface module (GUI) for receiving a plurality of user inputs, and an image control module. The GUI generates a primary display of the complete route being traveled on the primary display device. If the entire route does not fit on the display device, then the image control module generates data that the GUI uses to generate a context display on the primary display device. The context display presents the entire route as a smaller image on the primary display device, simultaneously with the primary display. The user inputs for the GUI enable the user to zoom, pan and perform other image control operations on either the primary display or the context display.

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: An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.

Abstract: Systems and methods for remotely setting a value for a trigger threshold variable used by a processor unit onboard an aircraft to determine if and when a data message should be transmitted from the aircraft. The method comprises the following steps performed by a computer: (a) obtaining data representing a flight plan or flight trajectory of the aircraft and flight information; (b) obtaining data representing business considerations; (c) computing a value of the trigger threshold variable as a function of at least the flight plan or flight trajectory data and the business considerations data; and (d) constructing a trigger threshold data message containing the computed value of the trigger threshold variable.

Abstract: The present invention relates to a system (1) and an associated method for managing audio warning messages in an aircraft. The system (1) comprises a plurality of monitoring systems (10, 20) capable of detecting the establishment of at least one warning condition (CA), and comprises a central broadcasting module (40), to which each of the monitoring systems is connected and which is capable of broadcasting an audio message (SIG) corresponding to a detected warning condition. In particular, in this system (1), the said central broadcasting module (40) comprises means (402, 420) for determining at least one priority warning condition among the warning conditions detected by the monitoring systems, and means (410, 430) for generating at least one audio message (SIG) corresponding to the at least one determined priority warning condition, in order to broadcast it.

Abstract: A computerized method for transmitting data between a multi core vehicle management system and a vehicle system. The method can include receiving, at a vehicle management system computer, a vehicle system request message from a requesting vehicle management system component. The requesting vehicle management system component can be one of a plurality of vehicle management system components, and the vehicle system request message can have a destination vehicle system component. The method can include generating a sanitized vehicle system request message based on the requesting vehicle management system component and the destination vehicle system component. The sanitized vehicle system request message can be transmitted to said destination vehicle system component.

Abstract: A present novel and non-trivial system, module, and method for presenting clearance-dependent advisory information in an aircraft is disclosed. Clearances include those corresponding to interval management operations and/or trajectory management operations. Data representative of clearance information including data representative of an actual controller intervention threshold (“CIT”) information, ownship information, target information, and alert parameter(s) information is received. The actual CIT information is comprised of the CIT of a clearance assigned to an aircraft and/or an designator from which the CIT of the assigned clearance is determined. A dynamic alerting threshold is determined as a function of the received information.

Abstract: Disclosed is a display system for an aircraft cockpit. The display system includes a plurality of display devices, each of which comprises at least one viewing screen configured to display a display format, and a cursor management unit linked to each display device and configured for moving a cursor over sensitive objects on the viewing screens of the display devices.

Abstract: A system may include a sensor for coupling with a vehicle configured for atmospheric flight. The sensor may be configured for detecting a turbulence event, where the turbulence event is at least one of experienced by the vehicle or occurs proximal to the vehicle during atmospheric flight. The system may also include a transmitter coupled with the sensor. The transmitter may be configured for automatically remotely transmitting data regarding the turbulence event to a ground based entity.

Abstract: An onboard monitor that ensures the accuracy of data representing the calculated position of an airplane during final approach to a runway. This airplane position assurance monitor is a software function that uses dissimilar sources of airplane position and runway data to ensure the accuracy of the respective data from those dissimilar sources. ILS data and GPS or GPS/Baro data are the dissimilar sources of airplane position data used by this function. This function will calculate the airplane's angular deviations from the runway centerline and from the glide slope with onboard equipment and then compares those angular deviations to the ILS angular deviation information.

Abstract: A method and a system are provided for displaying flight information of an aircraft. The system receives at least one user defined airspeed related to flight of the aircraft from a user. A processor calculates the at least one calculated airspeed based on data stored in a memory device. A static position is determined by the processor for the user defined and calculated airspeeds. The difference between the positions developed from the user defined and calculated position is also calculated. A difference indicator is displayed to the user for the difference between each user defined and calculated position.

Abstract: A feathering, flapping and rotor loads indicator for use in a rotorcraft includes a calculation unit configured to calculate (a) a current temperature of a bearing of the rotor assembly using a first calculation model, (b) a projected temperature of the bearing using the first calculation model and (c) a load exerted on a selected component of the rotor assembly using a second calculation model, the first and second calculation models adapted to calculate, respectively, the projected and the current temperatures of the bearing and the load exerted on the selected component based on flight control parameters; and a display unit configured to display on a common scale a movable indicator, the movable indicator being driven by the highest value between the projected temperature of the bearing and the load exerted on the selected component. The display unit displays another movable indicator driven by the current temperature of the bearing.

Abstract: A method for controlling speed of an aircraft in the air. The method compares a variation of the aircraft speed in the air with a variation of the aircraft speed on the ground for an identical period, and detects any significant difference between the variations.

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

Abstract: A system includes an unmanned aerial vehicle (UAV) configured to be equipped with data representing a first UAV flight plan, and a ground station configured to control the UAV. The ground station is operable to receive, at a first time, a first data set representing at least one flight path of at least one aircraft, calculate a second UAV flight plan to avoid the at least one flight path of the at least one aircraft, the second UAV flight plan being based on the data representing the first UAV flight plan and the first data set representing at least one flight path of the at least one aircraft, and transmit data representing the second UAV flight plan to the UAV.

Abstract: An electronic multi-function probe (MFP) is provided for positioning adjacent an aircraft skin. The electronic MFP includes a plurality of pressure sensing ports and an electronics housing. Positioned within the electronics housing are air data processing circuitry and stall protection system processing circuitry. The air data processing circuitry is configured to generate air data parameters, including airspeed and altitude, as a function of pressures at the plurality of pressure sensing ports. The stall protection system processing circuitry of the electronic MFP is configured to detect stall conditions as a function of angle of attack and at least one air data parameter from the air data processing circuitry, and to generate stall protection system outputs indicative of the detected stall conditions.

Abstract: Systems and methods for providing passive crowd-sourced alternate route recommendations. In one embodiment, locations of users of a number of mobile location-aware devices are tracked over time. Upon receiving a request, users of mobile location-aware devices that have traveled from a desired start location to a desired stop location are identified. Location histories for the identified users are analyzed to determine one or more different routes taken from the desired start location to the desired stop location. The one or more different routes, or a select subset thereof, are then returned to the requestor as recommended alternate routes.

Abstract: An aircraft hover system for enabling an aircraft to hover at a target spatial location represented by GPS location coordinates. The hover system includes a display screen rendering a display including live video feed of the terrain below the airborne aircraft, a first mark overlaying the video feed, the first mark representing the current position of the aircraft relative to the terrain, and a perimeter surrounding the first mark, the portion of the terrain within the perimeter being substantially magnified compared to that of the terrain outside of the perimeter. The hover system is configured such that, as the aircraft approaches the target spatial location, the distance between the first mark and a second mark on the display gradually decreases until and finally the first and second marks coincide; the second mark representing the target spatial location.

Abstract: Methods and apparatus for predicting airfoil stall for an aircraft having a control surface. Measurements of forces or moments acting upon an integrated span of the control surface are sensed over a period of time to provided unsteady data. The unsteady data is filtered to remove structural frequencies and input to at least one stall warning detection function, and an output is received. Each of the stall warning detection functions identifies an angle-of-attack that is approximately within a predetermined number of degrees of stall when the received output reaches a threshold. The received output is compared to the threshold to determine whether an angle-of-attack exists that is near stall.

Abstract: The present examples provide circuits, systems, processes, and the like for providing precision course guidance, typically for improved positive course guidance below published minimum descent altitude or decision altitude, including just in time calculations of obstacle free flight paths. The calculated flight path may be presented in the context of a synthetic scene of the environment surrounding the aircraft. To provide precision course guidance, exemplary avionics systems, processes and the like, as described below may be utilized.

Abstract: In a method for stand-alone alignment of an inertial unit for an onboard instrument capable of being mounted in an aircraft, the method includes monitoring the appearance of a movement of the inertial unit during the alignment, suspending the alignment of the inertial unit in the event of the appearance of movement, and resuming the alignment of the inertial unit on the disappearance of the movement.

Abstract: Avionics display system is provided for deployment onboard an aircraft and includes an air traffic data source that provides the avionics display system with data indicative of at least position and velocity of a neighboring aircraft. The system comprises a cockpit display system, and a monitor included within the cockpit display system. The cockpit display system receives and displays position and velocity data pertaining to the neighboring aircraft on the cockpit monitor as a position symbol and a velocity vector graphic. A processor operatively coupled to the monitor is configured to generate an air traffic display on the monitor including symbology indicative of (1) the current position of the neighboring aircraft (2) a velocity of the neighboring aircraft, and (3) the rate-of-change of the velocity of the neighboring aircraft.

Abstract: A method and device for automatically estimating a degradation in fuel consumption and in drag of an aircraft. The device comprises a device for calculating a numerical value of the effect of a degradation in performance on the fuel consumption and/or the drag of the aircraft, and an arrangement for displaying this numerical value on a screen in the cockpit of the aircraft.

Abstract: A procedure and a device for the determination of current airspeeds [13] of a rotorcraft [2] in a stationary flight regime and/or at low speeds. A calculation system [1] incorporates two pairs of polynomial calculation laws [9] [10] that are executable successively by pairs. A pair of first polynomial laws [9] calculates estimated airspeeds [11], consisting respectively of longitudinal and lateral airspeeds, and is constructed through multilinear regression based on parameters relating to simulated flight points [17] defined by means of a flight simulator [18]. A pair of second polynomial laws [10] calculates the current airspeeds based on the estimated airspeeds [11], and is constructed through multilinear regression based on parameters relating to test-flight points defined by means of test flights [25].

Abstract: A method for estimating airspeed of an aircraft includes receiving values indicative of operating conditions of the aircraft along an axis; estimating a tip path plane (TPP) angle along the axis from at least one of the operating conditions to create an estimated TPP angle; and determining an estimated airspeed as a function of the estimated TPP angle, the determining including referencing a look-up table that indexes the estimated TPP angle with the airspeed.

Abstract: A flight control system for an aircraft, controlling a plurality of actuators adapted to actuate control surfaces of the aircraft, including: at least one communications bus; at least one computer situated in the avionics bay of the aircraft, and adapted to calculate flight commands and to transmit them over the bus in the form of command messages; and at least a first remote terminal connected to the bus, adapted to control a control surface actuator, and to acquire the state of the actuator from information provided by at least a first sensor, the first terminal receiving command messages from the computer and transmitting electrical orders to the actuator as a function of the command messages received in this way, and also transmitting messages to the computer, at its request, relating to the state of the actuator as a function of the information provided by the first sensor.

Abstract: A vehicle system for determining an object threat level, includes a display and electronics configured to receive mission context data indicating an operational state of the vehicle. The electronics determines a threat level of the object in response to the mission context data. The electronics determines at least one recommended action in response to the threat level. The electronics provides an indication of the threat level and at least one recommended action to the display.

Abstract: An improved stable approach monitor (SAM) system provides an audible advisory to a pilot when an aircraft is on a final landing approach. More specifically, the SAM system compares a measured airspeed of the aircraft to a predetermined flap placard speed. If the measured airspeed exceeds the predetermined flap placard speed then the improved SAM system provides an audible advisory indicating the airspeed of the aircraft is too fast. Advantageously, this audible advisory should prevent the pilot from attempting to deploy the flaps at an excessive airspeed and in turn focuses the pilot's attention on the problem at hand, which would be to reduce the airspeed of the aircraft. Once the airspeed is equal to or below the predetermined flap placard speed, the improved SAM system may provide another audible advisory informing the pilot to commence deployment of the flaps.

Abstract: A method of selecting weather data for use in at least one of a flight management system (FMS) of an aircraft and a ground station includes selecting a reduced set of weather data points to send to the FMS and taking into account a trajectory of the aircraft when determining what data points to include in the reduced set.

Abstract: The invention relates to a method for transmitting data, characterized in that it includes a step of transmitting in-flight data between a first aircraft and at least a second aircraft, the data transmitted being data stored in at least one black box on board the first aircraft.

Abstract: A method for aiding the management of an aircraft flight according to an active flight plan receiving a control clearance transmitted at a current time includes a step of computing a reception flight plan based on the said control clearance, a step of storing the said reception flight plan in a memory space dedicated to the said reception flight plan. The method also includes, prior to the step of computing a reception flight plan: a step of determining the time, called the recognition time, assumed to have to elapse between the current time and a time at which the said control clearance is assumed to be recognized; a step of attribution, to the said control clearance, of a destination flight plan as a function of the recognition time, the said destination flight plan being the temporary flight plan when the recognition time is included in a first time slot and the destination flight plan being a secondary flight plan when the recognition time is included in a second time slot longer than the first time slot.

Abstract: A method and apparatus for managing a flight of an aircraft. Conditions in an environment around the aircraft are monitored during the flight of the aircraft on a route having a number of target points. In response to detecting a condition requiring a change to the route of the aircraft, current resources for the aircraft are identified. A determination is made as to whether changing the route reduces the number of target points that can be reached based on the current resources for the aircraft. In response to a determination that changing the route reduces the number of target points that can be reached, the route is changed to include a portion of the number of target points using the condition and a policy.

Abstract: A torque based power limit cueing system is provided and includes an engine computer to compile data relating to torque and additional information of each of one or more engines, an active stick by which tactile cueing are provided to a pilot and by which the pilot inputs control commands, a multi-function display (MFD) by which visible cues are provided to the pilot and a flight control computer (FCC) operably coupled to the engine computer, the active stick and the multi-function display, the FCC being configured to receive the data from the engine computer and to output tactile cue commands and visible commands in accordance with the torque and the additional information of each of the one or more engines to the active stick and the MFD, respectively.

Abstract: An asset operational health monitoring system, in which a plurality of sensors are arranged to determine values of asset operation parameters pertaining to an instance of asset operation. One or more processing unit receives data corresponding to said asset operation values and determine a plurality of asset locations at a corresponding plurality of points in time. The one or more processing unit is arranged to receive data indicative of the location of a region of adverse environmental conditions which may impact on the operation of the asset and to compare the determined locations of the asset with the location of said region so as to determine whether one or more of said asset locations fall within said region. An indicator of operational risk associated with the presence of said asset in said region is output which can drive asset operation or maintenance decision making. The system may be used for ash cloud impact monitoring for aircraft, a fleet of aircraft or aircraft engines.

Abstract: An installation for detecting and displaying the failures of the functional systems of an aircraft is described. The installation can include both a general alarm system (4) connected to said functional systems (2) and to the auxiliary alarm detection means (5) originated from said functional systems, and a complementary alarm system (6), connected to said functional systems (2), independently from the general system (4), and able to indicate a breakdown not detected by the general system on the instrument panel of the cockpit.

Abstract: An inclination control method using a torque vectoring system, may include a) detecting a vehicle speed, a steering angle, a yaw rate, and a steering torque of a vehicle, b) determining whether the vehicle may be tending to be inclined according to detected values of the vehicle speed, the steering angle, the yaw rate, and the steering torque, c) determining a torque vectoring duty according to the magnitude of the steering angle and the yaw rate when it may be determined that the vehicle may be tending to be inclined, and d) controlling the torque vectoring system according to the determined torque vectoring duty.

Abstract: An aerodynamic state estimation system includes a real-time actual measurement device, an air data computer, and a plurality of sensors. The measurement device receives laser scatter energy indicative of one or more atmospheric data parameters and outputs one or more truth measurements. The air data computer module receives the one or more truth measurements, calculates one or more state parameter estimations based on a plurality of functional parameters, and outputs at least one of the one or more truth measurements and the one or more state parameter estimations as one or more high accuracy state parameters, The plurality of sensors, located at the air data computer module, measure the plurality of functional parameters.

Abstract: A data collection and distribution system for monitoring aircraft in flight, on the ground and at the gate or terminal for monitoring critical and catastrophic events, managing the emergency during such an event, and for investigating the event. The system generates, transmits and collects critical data generated by monitoring equipment onboard an aircraft or other commercial transport and selectively displays the data on a cockpit display console as well as for downloading, transmitting and displaying data at external monitoring and response stations, including fixed ground stations, roving ground stations and chase aircraft or vehicles. Digital surveillance information is collected, processed, dispatched, and log via remote control and access. The system includes a variety of system appliances such as surveillance cameras, sensors, detectors, and panic buttons and accommodates legacy equipment.

Abstract: A runway indicator is displayed overlying a target runway for providing supplementary guidance to support the pilot's ability to fly a stabilized approach. The highlighted runway position indicator provides cues to verify that the aircraft is continuously in a position to complete a normal landing using normal maneuvering during the instrument segment of an approach and includes a landing threshold, a landing zone on the runway, an approach line leading to the runway, an outline highlighting the sides and ends of the runway, a rectangle larger than and surrounding the runway, and a visual precision path approach indicator.

Abstract: A method for controlling the piloting of an aircraft comprising the steps of receiving at least one first instruction for modification of a current velocity vector of the aircraft, determining a target velocity vector of the aircraft, on the basis of said at least one first instruction received, and determining, on the basis at least of said target velocity vector, at least one actuation command intended for at least one actuator of the aircraft in order to modify the movement of the aircraft according to said at least one first instruction received.

Abstract: A method and hold path computation system for automatically generating a hold path for an aircraft flying in a holding pattern, wherein the holding pattern is defined by one or more orbits within a selectable holding area are provided. The system includes a processor configured to receive a hold departure time indicating a time the aircraft is to leave the hold path to meet a required time of arrival (RTA) at a waypoint, determine a present position of the aircraft within the holding pattern, and determine an amount of time to complete a current hold orbit. The processor is also configured such that if the determined amount of time to complete a current hold orbit is less than or equal to the hold departure time, maintain the aircraft flying in the holding pattern and determine an amount of time by which to shorten the next orbit to exit the holding pattern at the hold departure time.

Abstract: A computer-implemented system and method for the collection, filtering, and transmission of aviation information is disclosed. A plurality of flight information is received over a digital network at various remote locations, and the data is filtered prior to transmission to a central database for presentation and use. The database includes aviation information. The method of filtration is dynamically updated as to information concerning a specific flight based on one characteristic of the flight. As to aircraft being tracked, a determination is made as to which receiver should relay collected data, and that determination is periodically revised, such as to minimize transmission costs and maximize signal quality as aircraft positions change. Once the information is located in the central database, it is suitable for use in responding to user requests for flight tracking information is association with at least one identified flight.

Abstract: The present invention relates to an on-board aeronautic system intended to be dynamically reconfigured, especially an on-board information system, and to an associated method as well as to an aircraft comprising such a system. In particular, the system comprises a plurality of heterogeneous equipment items, at least part of the said equipment items being reconfigurable, and comprises a reconfiguration management center set up to receive state messages from the said plurality of equipment items and to emit reconfiguration messages destined for the said reconfigurable equipment items as a function of at least the said received messages, the said state messages being emitted according to the same format by monitoring means encompassed in each of the said equipment items, the reconfigurable equipment items encompassing reconfiguration means capable of processing at least one of the said reconfiguration messages in order to reconfigure the said associated equipment item.

Abstract: The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations.