Abstract: Methods and systems are provided for presenting information pertaining to the health of one or more mechanical components of a vehicle. One exemplary method involves a client device initiating an ad hoc wireless connection with a monitoring system onboard the vehicle, requesting status information for the vehicle from the monitoring system via the ad hoc wireless connection, and receiving the status information for the vehicle from the monitoring system via the ad hoc wireless connection. The monitoring system generates the status information based at least in part on measurement data obtained from one or more sensor systems during operation of the vehicle and provides the status information in response the request. The client device processes the status information present the one or more graphical representations of the current condition of the one or more mechanical components of the vehicle on the client device.

Abstract: To easily grasp a relationship of parameter values which influence a log velocity of a ship, with the log velocity of the ship caused by the parameters, a ship characteristic estimating device is provided, which includes a data outputter configured to output a plurality of parameter data respectively including rotational speed data of a propeller of a ship, and wind velocity vector data of wind force that may act on the ship, and an estimator configured to receive the plurality of parameter data outputted from the data outputter, estimate values corresponding to the respective parameter data to be log velocity vectors of the ship, and output them as first output values. The rotational speed data are same as each other and the wind velocity vector data are different from each other.

Abstract: Systems and methods of an in-cockpit flight trajectory modification system for an aircraft are provided. A receiver is capable of receiving flight-related hazard information. A traffic aware planner (TAP) module is operably connected to the receiver to receive the flight-related hazard information. A user interface device is operably connected to the TAP module on board the aircraft to provide trajectory information associated with the aircraft and to receive user input corresponding to a request for a revised trajectory. A TAP application is capable of calculating one or more revised trajectories for the aircraft based at least on active trajectory information of the aircraft and the flight-related hazard information. The user interface device may be configured to display information related to the one or more revised trajectories, including a graphic display of the active trajectory and at least one revised trajectory in a visualization panel of the user interface device.

Abstract: A method for determining the speed vector ({right arrow over (Vd)}), with respect to the surrounding air, of a rotary wing aircraft (HL) equipped with a beam scanning Doppler laser anemometry device for measuring (Step1) a set of projections (Vm) of said speed vector ({right arrow over (Vd)}) in at least four non-coplanar directions, comprising the following steps: detecting (Step2) any anomaly of at least one element from the set of measured projections (Vm), from a comparison with respect to a first threshold (S1), of a deviation between the measurements (Vm) and the measurements (Vp) predicted from a predetermined model depending on values of beam scanning parameters of the anemometry device; and reducing (Step3) the effect of a detected anomaly by invalidating measurements corresponding to said anomaly and computing the components of the speed vector from valid measurements.

Abstract: A first air data system for providing first aircraft air data parameter outputs is formed by a first electronics channel of a first multi-function probe (MFP) that is electrically coupled with a first static pressure sensor. A second air data system for providing second aircraft air data parameter outputs is formed by a first electronics channel of a second MFP that is electrically coupled with a second static pressure sensor. A third air data system for providing third aircraft air data parameter outputs is formed by a second electronics channel of the first MFP that is electrically coupled with a second electronics channel of the first MFP.

Abstract: Systems and methods for predicting and managing computation derations that may occur in multi-core processors are disclosed. The method may include: determining effects of multi-core contentions on a particular core of a multi-core processor; determining effects of single-core contentions on a particular hosted function hosted on the multi-core processor; determining an adjustment time to a baseline activation time for the particular hosted function, wherein the adjustment time plus the baseline activation time overcome the effects of multi-core contentions and single-core contentions at a predetermined probability goal; and adjusting a computation time requirement of the particular hosted function to include the adjustment time and the baseline activation time.

Abstract: The estimation device comprises an estimation assembly for determining a corrected estimated incidence, with the aid of an estimated incidence which is computed on the basis of aerodynamic parameters and of inertial parameters related to the aircraft and of a measured incidence which is determined on the basis of measurements carried out on the aircraft by at least one incidence probe. This estimation device thus makes it possible to obtain estimations of the speed of the aircraft, of its incidence and of the total temperature, on the basis of aerodynamic and inertial parameters.

Abstract: A method, apparatus and program product utilize a flight recorder having active error detection functionality to proactively detect errors in a computer or a sub-system or component thereof. The active error detection may be based on one or more trends detected in the trace data logged by the flight recorder and reflective of particular types of errors that may be present in a computer during operation, such that an error may be logged, and in some instances, an exception may be triggered.

Abstract: An in aircraft computer renders graphical representations of airfield range marker extensions to a runway extended centerline, even when the runway extended centerline is not rendered. Crossbars of the runway extended centerline are extended as arc segments to the center of the display with chevrons indicating the relative location of the airfield. Distance marker billboards are replicated at the end of the extended arc segments. As the aircraft approaches the airfield, crossbars closer to the airfield are extended. Vertical markers maintain billboards corresponding to range rings around an airfield in a visually prominent location, even when the proximal portion of such range ring is not visible in the display.

Abstract: A system and method are provided for displaying a strategic navigational overview of a vehicle, including a navigational map and a marker icon thereon representing an entity pertinent to navigation of the vehicle. A vertical line contacting the marker icon has, contiguous thereto, a current altitude icon representing the current altitude of the vehicle, and a trending icon indicating a direction of a change in altitude of the vehicle.

Abstract: A service arrangement system coordinates service providers who provide geographical location-based services to users. The location-based services may include transportation of users. For example, a service provider operates a vehicle to transport a user from an origin location to a destination location. To provide an engaging user experience and encourage users to continue using the services, the service arrangement system accurately and expediently determines the origin location and the destination location based on querying available data sources. The service arrangement system can use selection rules for multiplexing, fallback logic, or load-balancing to select a high quality data source from the available data sources.

Abstract: A method of controlling an aircraft in the event of pilot incapacity includes detecting, using at least one sensor, the occurrence of an event relating to a pilot's capacity to control the aircraft, determining whether the event justifies a controlled takeover of the aircraft from the pilot, asserting a controlled takeover of the aircraft from the pilot if it has been determined that a controlled takeover is justified, and executing a controlled landing of the aircraft without assistance of the pilot.

Abstract: The invention concerns a PCMCIA card for downloading flight data remotely via a wireless network to a ground station, the PCMCIA card being designed to be connected to an ACMS system of an aircraft, the ACMS system being designed to generate an ACMS report after at least one predefined condition has been satisfied, and to record flight data.

Abstract: A method and system is provided for determining the compatibility of an approach, to a landing runway, with an angular guidance mode, the approach being compatible with a linear guidance mode, the angular guidance being characterized by a lateral angle of precision, the linear guidance being characterized by a lateral divergence of precision. The method is implemented on a flight management system deployed aboard an aircraft and comprising a first step of determining a first distance representative of a maximum distance of use of the angular guidance, on the basis of the lateral angle of precision and of the lateral divergence of precision.

Abstract: A resource usage graphical overlay for a navigation system is disclosed. For each such resource, a resource exhaustion distance is computed, based on the consumption or lapse rate of the resource, and the vehicle speed. This resource exhaustion distance is scaled for the interactive map display and rendered as a service area on the interactive map so a user can determine what destinations are reachable before resources are completely depleted.

Abstract: The present invention relates to a speed measurement system allowing the relative speed V of a moving body in relation to an ambient air mass to be measured independently of the atmospheric conditions, the moving body being designed to move at least at subsonic and transonic speeds.

Abstract: Systems and methods for updating a terrain awareness and warning system (TAWS) database are disclosed. The systems request, by way of the first wireless communications device communicating by way of an avionics data transfer protocol, an update to the TAWS database, where the request is based upon flight path data, and receive and accept, by way of the first wireless communications device and by way of the avionics data transfer protocol and in response to the request, the update to the TAWS database.

Abstract: A method and system is provided for the recovery of an aircraft energy upset in a time-constrained descent. The system includes a computational unit to assess a number of adjustments involving a combination of speed changes, aerodynamic brake deployment and track miles adjustments that alter the energy dissipation profile whilst allowing the aircraft to maintain a pre-determined time-of-arrival over an incoming waypoint along the original descent path.

Abstract: A system includes a processor having first and second processing units and a memory coupled to the processor. The memory includes processor executable code to implement an application to execute a first process to provide first application output information and to execute a second process to provide second application output information, a selector to provide a first indication that the first process is a critical process and a second indication that the second process is a non-critical process, and an application program interface (API) to run on the first processing unit. The API directs the processor to run the application on the second processing unit, executes the first process to provide first API output information in response to the first indication; determines if the first application output information matches the first API output information, and determines to not execute the second process in response to the second indication.

Abstract: A system method for predicting vehicle mission capability for a vehicle that is propelled by an engine includes collecting engine degradation data for the engine. Location independent engine degradation data are generated from the collected engine degradation data. The location independent engine degradation data are representative of engine degradation that is independent of locations associated with the mission. Predictions of location dependent engine degradation are calculated from the collected engine degradation data and the location independent engine degradation data. The location dependent engine degradation is representative of engine degradation due to movement through locations associated with the mission.

Abstract: Methods, systems, and computer readable media for managing aircraft radiofrequency communications on board an aircraft are disclosed. In some aspects, a method can include determining at least one communication frequency, the at least one communication frequency corresponding to a communication center within a radio horizon of the aircraft, displaying the at least one communication frequency at an interface, and where there is more than one communication frequency displayed on the interface: filtering the more than one communication frequency according to a flight step of the aircraft in order to reduce a number of the more than one communication frequency displayed on the interface, and sorting the more than one communication frequency according to occupation rate in order to prioritize the more than one communication frequency displayed on the interface, and thereby aid in predicting a communication frequency communicated to the aircraft.

Abstract: This disclosure is directed to systems and methods for smart transitioning between aircraft trajectory management modes. In one example, a system is configured to track a speed of a target aircraft in flight ahead of an own aircraft on which the system is positioned. The system is further configured to determine whether the target aircraft has maintained a rate of change in speed within a selected range of variation in change of speed, for a selected period of time. The system is further configured to enable an activation of a merging trajectory management mode of the own aircraft in response to determining that the own aircraft is in a trajectory management mode transition airspace and that the target aircraft has maintained the rate of change in speed within the selected range of variation in change of speed, for the selected period of time.

Abstract: A computer method for determining potential wake turbulence by a first aircraft from wake generated by a second aircraft. The computer method includes receiving a signal generated by the second aircraft at the first aircraft and transforming the signal to a first wake turbulence boundary that represents the wake generated by the second aircraft. An intersection volume, which is representative of a zone of dangerous turbulence interactions, is selected for the first aircraft. Based on a determination of intersection between the first wake turbulence boundary and the intersection volume, issuing a warning flag if an intersection exists or continue generating the first wake turbulence boundary and determining whether interactions exist.

Abstract: A system and method for controlling an aircraft system. An operator interaction with a control is received. The control comprises an image representing a hardware control for controlling the aircraft system. The image representing the hardware control is changed to represent a change in a state of the control in response to receiving the operator interaction. The aircraft system is operated in the manner indicated by the state of the control as represented in the image.

Abstract: A system and method for providing the information contained in instrument procedure charts in a more intuitive and easier to comprehend manner is provided. The provided enhanced instrument procedure visualization system displays a dynamic three-dimensional view of a selected instrument procedure, and incorporates time-relevant information from weather and traffic sources. The provided enhanced instrument procedure visualization system further allows a pilot to scroll forward and backward in time to review and study the complete instrument procedure.

Abstract: A plurality of sensors provide respective output data rates, with a first sensor that has a highest output data rate, while one or more other sensors have output data rates that are submultiples of the aforesaid highest output data rate. The data signals coming from the sensors are stored in a memory, e.g., a FIFO memory, by storing the data signals of the first sensor at the aforesaid highest output data rate, accompanying storage of the data signals coming from said first sensor with storage of the data signals coming from the sensors as supplied by said other sensors at the aforesaid submultiple output data rates, so that the data signals are stored in the memory according to a repeated pattern that is common to the various sensors.

Abstract: A centralized maintenance device installed on-board an aircraft notably carries out the following functions: correlation of data relating to failures, warnings, configurations, operational contexts, flags and the logbook, received by the on-board maintenance system; storage of the data received by the on-board maintenance system in a first database; management of a historical record of the data received and of their correlation; transmission to a man-machine interface of the data received, of their correlation and of a date associated with each item of data; display of the received data, their correlation and the date associated with each item of data, by a man-machine interface of the on-board maintenance system.

Abstract: According to one embodiment, a gauge display prioritization system comprises a priority engine and an output engine. The priority engine is operable to receive a measurement from a first sensor associated with a first aircraft component and a measurement from a second sensor associated with a second aircraft component, select a prioritization criterion based on the received measurements, and select one priority measurement from the received measurements based on the prioritization criterion. The output engine is operable to instruct a gauge disposed within a cockpit to display information representative of the one priority measurement to a pilot.

Abstract: A method for managing navigation of an aircraft. Positions for the aircraft are identified from position information from sensors. Graphical indicators are displayed on a graphical user interface in a display system. The graphical indicators identify the positions for the aircraft. Range rings are displayed around the graphical indicators. The range rings indicate accuracy bounds for the positions.

Abstract: A method of error detection of a flight management system coupled with a guidance of an aircraft according to a flight plan, comprises the steps of: generating a first reference guidance order, monitoring the integrity of the first reference position, when the first reference position is not monitored as being dependable: invalidating the first FMS assembly and the associated guidance system, when the first reference position and the first reference trajectory are monitored as being dependable: generating a first monitoring guidance order, generating a first reference flight control, generating a first monitoring flight control, in monitoring the integrity of the first reference guidance order when the first reference guidance order is not monitored as being dependable: invalidating the first FMS assembly and the associated guidance.

Abstract: A method of preserving rotor speed during a one engine inoperative operation of an rotorcraft, the method can include: detecting a failure of a first engine; monitoring an engine parameter associated with a second engine; using a computer processor to compare the engine parameter to an engine limit; and commanding a decrease collective pitch command when the engine parameter is within a predefined range of the engine limit.

Abstract: A system and method for guided navigation of a mining vehicle are presented. A position sensor is mounted to a haul truck. The position sensor is configured to identify a position of the haul truck. A navigation aid is configured to identify a target destination for the haul truck, calculate a path including the target destination, and use the position sensor to monitor a progress of the haul truck along the path. A user interface is configured to display at least a portion of the path to an operator of the haul truck.

Abstract: A system, device, and method for generating a landing distance indicator (LDI) are disclosed. The LDI generating system may include one or more sources of navigation data, one or more sources of landing distance (LD) factor data, published LD data source, an image generator (IG), and a presentation system. The IG may be configured to navigation data; acquire LD factor data; define LD data; and generate image data as a function of the navigation data and the LD data. The navigation data could include a runway reference point, and the LD data could an LD. The image data could be representative of at least an image of an LDI comprised of a first boundary is based upon a location of the runway reference point, and a second boundary is based upon the runway reference point and the landing distance.

Abstract: An emergency landing control system for an aircraft includes a landing site data source, a performance margin data source, an engine health data source, an aircraft health data source, and a processor. The landing site data source determines, continuously and in real-time, available landing sites. The performance margin data source conducts, continuously and in real-time, continuous performance analysis of an engine. The engine health data source determines, continuously and in real-time, available engine power as a function of time. The aircraft health data source determines, continuously and in real-time, available aircraft life as a function of time. The processor receives data from these data sources and, based on these data, continuously generates landing paths to one or more of the available landing sites, and selectively and continuously adjusts maximum available engine power up to emergency power limits, as needed, during execution of a landing maneuver to a landing site.

Abstract: A method of determining parameters that are characteristics of the operation of a vehicle having a power plant with at least one engine and mechanical transmission means, sensors, and display means. During the method, various items of information about the aircraft, its state and/or its operation and/or its environment are measured, and then, for at least one parameter Pi relating to the state and the operation of the aircraft there are determined a first limit value Pi_lim for the parameter Pi, a second value Pi_X for each parameter Pi to enable the aircraft to perform a predetermined maneuver X, and an instantaneous third value Pi_inst for each parameter Pi. Thereafter, each first, second, and third values Pi_lim, Pi_X, Pi_inst is displayed simultaneously in order to show up the relative position of second and third values Pi_X and Pi_inst relative to a first value Pi_lim for each parameter Pi.

Abstract: Present novel and non-trivial system, device, and method for recording a modification of an existing route plan are disclosed. The disclosed system may be comprised of a flight management system (“FMS”), at least one human-machine interface (“HMI”) device, at least one display unit, and a route modification generator (“RMG”). The disclosed device may be comprised of the RMG configured to perform the disclosed method, where such method may be comprised of receiving a request to modify an existing route plan; retrieving the route plan from the FMS; generating a message data set representative of one or more pre-formatted messages having one or more visually-conspicuous, user-interactive variable fields; updating the message data set in response to a user's selection of each field; sending the updated data set to the display unit; receiving a pilot's authorization to modify the route plan, and sending the accepted, modified flight plan to the FMS.

Abstract: Systems and methods for processing aircraft flight information and flight plan information are described. Specific techniques are described for managing flight data in real time, sharing flight data between a plurality of systems, dynamically managing flight information, generating flight plan information, providing flight plan information to a user, and closing flight plan discontinuities.

Abstract: Systems and methods for updating a scale of a barometric altimeter on aircraft are provided. The method, for example, may include, but is not limited to, receiving, by an aircraft communication system, barometric altimeter scale data corresponding to an atmospheric pressure at an airport, determining, by the processor, if the altitude of the aircraft is below a transition level for the airport, and adjusting, by the processor, the scale of the barometric altimeter based upon the received barometric altimeter scale data when the altitude of the aircraft is below the transition level for the airport.

Abstract: The present disclosure is directed to a method for providing an alert to a pilot. The method includes the step of receiving a plurality of alerts. The method also includes the step of identifying a highest priority alert from the plurality of alerts. An additional step of the method includes determining a current view of the pilot. The method also includes the step of presenting the highest priority alert within the current view of the pilot.

Abstract: A method for producing a connector, in particular for repair, in particular in the field of aviation and aerospace, including the steps of: providing a base layer; attaching a first layer of fiber composite material having a first rigidity to the base layer; attaching a second layer of fiber composite material having a second rigidity to the first layer, offset therefrom, the second rigidity being greater than the first rigidity; and riveting the first layer to the base layer and riveting the second layer to the first layer and to the base layer.

Abstract: Despite pilot training and current safety systems, aircraft accidents continue to occur. It is recognized herein that existing approaches to preventing aircraft accidents lack capabilities. A predictive aircraft recovery control unit can receive flight data from the plurality of data nodes. The flight data can be indicative of at least a speed of the aircraft and a position of the aircraft. In some cases, based on the flight data, the predictive aircraft recovery control unit can determine that the aircraft will enter a stall condition. Furthermore, based on the flight data, the predictive aircraft recovery control unit can determine a time period that will elapse before the aircraft enters the stall condition. In response to determining that the aircraft will enter the stall condition after the time period elapses, the predictive aircraft recovery control until can trigger a recovery sequence before the aircraft enters the stall condition.

Abstract: Systems and methods for attitude fault detection based on air data and aircraft control settings are provided. In one embodiment, a sensor monitor for an aircraft attitude measurement system comprises: an aircraft model configured to model a plurality of states, the plurality of states including at least an aircraft attitude state, an aircraft velocity state, a sink rate error state, and a wind velocity state; a propagator-estimator configured to utilize the plurality of states of the aircraft model to process air data measurements and attitude measurements from a first inertial measurement unit of the aircraft attitude measurement system; and a residual evaluator configured to input residual error values generated by the propagator-estimator, wherein the residual evaluator outputs an alert signal when the residual error values exceed a predetermined statistical threshold.

Abstract: Systems and methods for airspeed estimation using actuation signals are provided. In one embodiment, an on-board avionics airspeed estimation system is provided. The system comprises: a flight control surface for an aircraft; a control surface actuator coupled to the flight control surface, wherein the control surface actuator receives an actuator control output signal from an actuator control system and drives the flight control surface into a position based on the actuator control output signal; a wind estimator coupled to a plurality of aircraft sensors, wherein the plurality of aircraft sensors output a set of aircraft measurements to the wind estimator and wherein the actuator control output signal is further provided to the wind estimator; wherein the wind estimator calculates a wind speed estimate by applying the actuator control output and the set of aircraft measurements to an onboard aircraft model.

Abstract: A user interface for an integrated autopilot and flight management system for an aircraft includes a plurality of tactical parameter controls for operation of the autopilot and a plurality of strategic parameter controls for operation of the flight management system.

Abstract: A system and method for displaying predictive cues on an aircraft display system for executing a landing after an engine failure is provided. The system and method displays the cues for various aircraft configurations, and each cue is displayed in perspective (conformally) on a three dimensional graphical display of the surrounding terrain.

Abstract: A flight instrument that displays the rotational speed of a main rotor of a rotary-wing aircraft, with the flight instrument including display means, a first indicator of a setpoint for the rotational speed of the main rotor, a second indicator of the first current value of the rotational speed of the main rotor, and third and fourth indicators of the limit values of the rotational speed. The setpoint for the rotational speed of the main rotor is variable and the first indicator is stationary on the display means, with the second, third and fourth indicators being movable in relation to the first indicator.

Abstract: A method for determining an orientation of a portable or mobile electronic device includes determining an orientation of the device using at least a first inertial motion sensor (e.g., a gyroscope) with which the portable electronic device is equipped. A correction factor is provided to the orientation of the electronic device using a feedback control signal based on motion data obtained from at least a second inertial motion sensor (e.g. an accelerometer) to reduce drift in motion data obtained from the first inertial sensor. Responsive to a loss of valid motion data from the first inertial motion sensor, a rate at which the correction factor is provided to the orientation of the portable electronic device is increased.

Abstract: In some examples described herein, a runway location is determined based on aircraft state information from at least one aircraft. For example, a processor may determine the coordinates of one or more points of a runway based on aircraft state information generated by one or more aircraft using the runway. In some examples, the processor may aggregate coordinates determined from the aircraft state information provided by a plurality of different aircraft in order to determine the location of the runway. The processor can be located onboard an aircraft providing the state information, onboard a different aircraft, or external to any aircraft.

Abstract: A system and method are disclosed for indicating to an aircrew of an aircraft a normalized runway icon to ensure visualization of a predicted touchdown point, runway length, stopping distance, energy state marking, and threat conditions, where normalization is referenced to typically available length for landing. Indications of present aircraft locations relative to the icons as well as alerts when thresholds are exceeded are provided.

Abstract: A method and apparatus for predicting fuel for an aircraft. Remaining amounts of fuel that will be present for types of fuel use for the aircraft at a destination are predicted. Flight times for the types of fuel use are calculated from the remaining amounts of fuel predicted for the types of fuel use for the aircraft at the destination. Graphical indicators are displayed indicating the types of fuel use and the flight times for the types of fuel use.