Abstract: A wayfinding device is provided for giving directions to a desired destination within a building having a plurality of wayfinding beacons configured to transmit data using an ultrasound signal. The ultrasound signal can include a plurality of bursts, wherein a sequence of predefined time intervals between consecutive bursts within the plurality of bursts uniquely identifies each wayfinding beacon. The wayfinding device is separate from the wayfinding beacons and includes a wayfinding beacon recognition component configured to identify a wayfinding beacon when the device receives the data through the ultrasound signal from a wayfinding beacon. The device is further programmed to provide directions to a user of the device in a direction toward the desired destination in response to identifying a wayfinding beacon.

Abstract: A method for estimating the effect of environmental conditions on an aircraft, including measuring the motions of an aircraft; estimating the expected motions of the aircraft, wherein the expected motions of the aircraft are estimated using information regarding the aircraft's control inputs and/or control surface positions; and estimating, based on the measured motions of the aircraft and the expected motions of the aircraft, the forces exerted on the aircraft by the environmental conditions, wherein the forces are estimated based on a difference between the measured motions of the aircraft and expected motions of the aircraft.

Abstract: A method and device are provided for automatically adjusting an image of an aircraft navigation screen. The device includes a determining unit for automatically determining, if necessary, a new display configuration making it possible to present on a navigation screen a detected dangerous event, and a display unit for automatically effecting a change of display of the navigation screen by applying this new display configuration.

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

Abstract: One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.

Abstract: A method and system for highlighting a parameter image representative of a flight parameter of an aircraft to a user in a multi-parameter aircraft instrument display, such as a flat panel display. An electronic instrument display is configured to present parameter images, at least one of which includes a first indicator configured to indicate a specific value (e.g., a target value) for a flight parameter and a second indicator configured to indicate an actual flight parameter value that changes according to variations in the flight parameter. A graphics rendering controller is configured to generate the parameter images and to enlarge a portion of the parameter image when the actual flight parameter value is within a predetermined range from the target value.

Abstract: A method for transmitting data and/or information when a scaled environmental condition occurs in a location along a specified path and/or within a predetermined altitude parameter and/or within a predetermined geographic location that satisfies a predetermined display requirement, including receiving at least some data and/or information; determining whether the received data and/or information represents an environmental condition that is in a location along a specified path and/or within a predetermined altitude parameter and/or within a predetermined geographic location that satisfies a predetermined display requirement; preparing, if the received data and/or information represents an environmental condition that is in a location along a specified path and/or within a predetermined altitude parameter and/or within a predetermined geographic location that satisfies the predetermined display requirement, the data and/or information for transmission; and transmitting the prepared data and/or information.

Abstract: A method of monitoring the performance of an aerodynamic surface of an aircraft. The aircraft is operated during a non-perturbed measurement period such that the flow of air over the surface is at least partially laminar. A parameter is measured which is indicative of the drag of the surface during the non-perturbed measurement period to provide non-perturbed drag data. Air flow is perturbed temporarily over the surface in a perturbed measurement period so that it undergoes a transition from laminar flow to turbulent flow. The parameter is also measured during the perturbed measurement period to provide perturbed drag data. The degree of laminar flow during the non-perturbed measurement period can then be estimated in accordance with the difference between the perturbed drag data and the non-perturbed drag data. An ice protection system can be used to perturb the air flow.

Abstract: The invention pertains to optoelectronic devices for aiding the guidance and taxiing of aircraft, comprising a so-called head-up collimator allowing the presentation of information in the pilot's visual field. It applies notably to large-size civil aircraft of the Boeing 747 or Airbus A380 type. The optoelectronic device comprises means for calculating a deviation factor for the actual trajectory of said aircraft relative to a theoretical trajectory on said traffic way, means for generating symbols and at least one head-up collimator comprising means for displaying and superimposing said symbols on the outside landscape. The deviation factor is calculated on the basis of an angle (PÂ?G) and that the means for generating symbols generate a symbol representing said deviation factor, so as to be superimposed on said traffic way.

Abstract: A system and method for selectively alerting a pilot of an aircraft about distance remaining to the end of a runway. A position of the aircraft is received. A position of a runway is retrieved from a runway database. The retrieved position of the runway is compared to the received position of the aircraft to determine if the aircraft is within an alert envelope relative to the retrieved position of the runway. The position of the runway is subtracted from the position of the aircraft to determine a distance to the distal end of the runway. An alert to the pilot is generated based upon the distance to the distal end of the runway.

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

Abstract: Embodiments of a process and a program product are provided suitable for implantation by a flight management system (FMS), which is deployed onboard an aircraft and including a display device and a user interface. The FMS operable in a plurality of non-precision approach modes. In one embodiment, the process includes the steps of: (i) receiving data via the user interface designating an approach in a flight plan; (ii) enabling the pilot to utilize the user interface to select a non-precision approach mode from the plurality of non-precision approach modes if the designated approach is a non-precision approach; and (iii) placing the FMS in the selected non-precision approach mode during the designated approach.

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: A flight recorder includes an information input device, heat sensitive memory device electrically connected to the information input device, and housing enclosing the heat sensitive memory device. The housing is made with a first material and having a plurality of openings made through the housing. A sacrificial material is disposed between the housing and heat sensitive memory device. The sacrificial material having a lower melting temperature than the first material such that the sacrificial material changes state and egresses through the openings in the housing when exposed to heat to create an air gap between the housing and heat sensitive memory device. The first material includes nickel and the sacrificial material includes aluminum. A heat insulating layer is disposed between the sacrificial material and heat sensitive memory device. A second sacrificial material is disposed between the heat insulating layer and heat sensitive memory device.

Abstract: Systems and methods for suppressing an unstable alert when the aircraft is in the process of landing on a temporarily displaced threshold. In an example process, a processor on the aircraft determines the aircraft is on an approach to landing on a runway based on information received from one or more data sources on the aircraft, then retrieves predefined glideslope information for the runway from a memory device that is in signal communication with the processor. Next, the processor determines whether position of the aircraft is above the predefined glideslope by a first threshold amount. If the aircraft is determined to be above the predefined glideslope by the first threshold amount, the processor issues an unstable alert only if a flight path angle of the aircraft is greater than an angle of the predefined glideslope by a second threshold amount.

Abstract: A system for collecting and storing performance data for an engine is provided. The system includes one or more sensors configured to generate sensor data signals representative of one or more engine data performance parameters. The system further includes a data sampling component, a data quantizing component, a data storage sampling rate component, a data encoding component and a data storage component. The data sampling component is configured to sample the sensor data signals at a data sampling rate. The data quantizing component is configured to generate quantized data samples corresponding to the sampled sensor data signals. The data storage sampling rate component is configured to determine a data storage sampling rate for the quantized data samples, based on an analysis of at least a subset of the quantized data samples.

Abstract: Methods and systems for handling aircraft control information are disclosed. A system in accordance with one embodiment of the invention includes a display medium coupleable to a flight manager, with the flight manager configured to receive and direct instructions for automatically controlling aircraft functions at a future time during flight of the aircraft. The system can further include a display controller coupled to the display medium to present at least one operator activatable element at the display medium and update information presented at the display medium when the operator activates the operator activatable element. For example, the operator activatable element can include an icon presented at a computer display screen, and can be activated by a keystroke.

Abstract: An aircraft guidance and piloting system automatically guides and pilots an aircraft in the event a pilot is unable to guide or pilot the aircraft. Upon determining the pilot's inability to control the aircraft, a processor transmits an automatic engagement command to a control unit. The control unit guides and pilots the aircraft to an alternative airport for landing.

Abstract: A computer-implemented function monitors and displays exhaust gas temperatures (EGT) in a plurality of cylinders in an engine. The invention provides an easy way to read exhaust gas temperature on a specific cylinder, and to provide a means for leaning the engine while in a climb. Efficient leaning in a climb reduces fuel consumption and reduces the chance of harmful conditions that can lead to engine failure.

Abstract: The present invention is a method for providing a depiction of an approach path to a landing area and of terrain proximal to the landing area via a flight deck situational awareness system of an aircraft. The method may include providing a vertical reference graphical indicator for indicating a glide path for the landing area. The method may further include providing a plurality of extended graphical indicators which extend from the vertical reference graphical indicator and intercept the depicted terrain. The method may further include connecting the plurality of extended graphical indicators via a horizontal reference graphical indicator which forms an extension of a centerline of the landing area onto the depicted terrain. The vertical reference graphical indicator, the extended graphical indicators, and the horizontal reference graphical indicator may form boundaries of a plurality of transparent panes, which collectively form a transparent approach curtain.

Abstract: Methods and systems for displaying a digital terrain to a user of a vehicle are provided. First, second, and third actual terrain data points are received. The third actual terrain data point is between the first and second actual terrain data points. If the third actual terrain data point is above a line interconnecting the first and second actual terrain data points, the first actual terrain data point is modified such that the third actual terrain data point is not above a line interconnecting said modified first actual terrain data point and the second actual terrain data point. A digital terrain is displayed to the user of the vehicle. The digital terrain includes a first digital terrain data point corresponding to the modified first actual terrain data point.

Abstract: A device and method for managing tasks for the piloting of an aircraft includes a means for detecting alerts of the flight systems and an alerts management means for presenting the alerts and the tasks of the resolution procedures to the crew. The device includes means for recording additional procedures and tasks and modifications of attributes of tasks with respect to the tasks recorded in the first recording means, a means for triggering the additional tasks able to order the alerts management means to present the additional tasks, the triggering means operating according to a mode of asynchronous acquisition of trigger data originating from the flight systems and a means for selecting the recorded additional procedures and additional tasks so as to transmit the modified procedures and the modified attributes of the tasks to the alerts management means.

Abstract: A head-up display system includes an aircraft, a predicted flight path generation component that calculates a predicted flight path over a period of time, and a graphic generation component configured to generate a graphical display and project it onto a combiner configured to combine the graphical display with a visual exterior view. A synthetic vision system includes an aircraft, a predicted flight path generation component that receives one or more state parameters and calculates a predicted flight path over a period of time, and a synthetic terrain generation component configured to generate a synthetic view which is displayed on a display. The graphical display and/or the synthetic view includes a three-dimensional depiction of the predicted flight path over the period of time generated utilizing one or more three-dimensional transforms, one or more graphical images based on flight data, and a three-dimensional graphical depiction of a flight plan.

Abstract: A system for displaying throttle settings to an aircraft operator includes, but is not limited to, a display unit, a data storage unit configured to store aircraft and airport data, an operator input unit configured to receive thrust related information from the aircraft operator, an aircraft sensor configured to detect an aircraft condition, and a processor. The processor is communicatively connected to each of the above components and is configured to obtain therefrom the aircraft data, the airport data, the thrust related information, and the aircraft condition. The processor is also configured to calculate a first thrust requirement based on the aircraft data, the airport data, the thrust related information, and the aircraft condition, and to provide commands to the display unit to display either the first thrust requirement.

Abstract: The Tail Load Monitoring System detects faulty low frequency (e.g. those in the range from 0.1 to 1 Hz) oscillatory conditions caused by Flight Control System malfunctions while the aircraft is in air by means of a continuous assessment of the estimated tail load behavior and data processing. Both estimation and data processing activities are provided by a dedicated architecture featuring a tail load estimation module, a band-pass filter and three independent paths that continuously monitor nuisance fault detection events avoidance, catastrophic events avoidance (addressing a limit load criterion), and structural damage avoidance (addressing fatigue life criteria).

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

Abstract: An electronic display instrument configured to secure in a desired position over multiple pre-existing instrument holes in a dashboard of an aircraft in place of multiple conventional display instruments, each conventional instrument having a conventional readout. The instrument comprises a display screen having a plurality of readouts corresponding to the conventional readouts of the multiple conventional instruments that the electronic display instrument replaces. The instrument further includes a body having a front and a back opposite the front and a top and a bottom opposite the top. The body is positioned adjacent and connected to the display screen. The instrument also includes an electronics module protruding from the back of the body to position in one of the pre-existing instrument holes in the dashboard panel of the aircraft.

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

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

Abstract: Method, device and item of equipment for filtering alarms originating from a windshear detection system embedded in an aircraft being able to emit an alarm. The aircraft has at least one sensor allowing the acquisition of a flight parameter. The device includes: units for the calculation of the second derivative of the flight parameter, units for the calculation of the absolute value of the second derivative of the flight parameter, units for the comparison of the absolute value of the second derivative of the flight parameter with a threshold C1, units for evaluating whether the absolute value of the second derivative of the flight parameter exceeds the threshold C1 over a duration greater than a time threshold T, and units for suppressing the alarm originating from the windshear detection system.

Abstract: A wireless data communications network system for establishing communication between a server and a plurality of containers that are loaded onto a cargo vessel. The system includes a data communications device configured to establish and manage a pre-configured wireless data communications network and to communicate with the server through a local area network, and a plurality of electronic tracking devices each having a wireless transceiver and routing capabilities and configured to be joined to a container and to connect to the wireless data communications network upon being activated. The data communications device is configured to intermittently perform a network scan to locate each tracking device connected to the network and reconfigure the network topology to include each connected tracking devices such that the data communications device maintains mutual communication with each connected tracking device using the routing capabilities of the tracking devices.

Abstract: A display system and method for an aircraft displays, in real-time, the protected airspace associated with a CTL maneuver. The system processes aircraft approach category data and determines the protected airspace based at least in part on the processed aircraft approach category. An image representative of the determined protected airspace is displayed on the aircraft flight deck display system.

Abstract: A diagnostic method for locating a failure in a complex system that includes the steps of detecting operating information using a detector device; verifying a performance of the system based on the operating information; determining an operating status of the system to be one of “operational,” “non-operational” and “degraded” based on the operating information; comparing the operating information with predetermined data when the operation status is one of “operational,” “non-operational” and “degraded;” and generating at least one hypothesis as to a location of the failure of the system.

Abstract: A method of creating and modifying a flight plan using a cursor control device and a display to represent the flight plan in the context of terrain. The method includes inserting waypoints, including origin and destination waypoints, into a flight plan using a cursor control device to position the waypoints in a display and commanding a flight management system (FMS) to connect the waypoints into a flight plan. The flight plan is drawn in the context of terrain on a display where conflicts between the flight plan and terrain are indicated. Selected elements of the flight plan are selected with a cursor control device and the selected elements are dragged to new positions on the display until terrain conflicts are eliminated, thus generating a modified flight plan. The modified flight plan is reviewed in the context of terrain to determine its acceptability and making further modifications thereof if desired.

Abstract: One example embodiment relates to a method of navigating an object. The method includes detecting when the object accelerates through the speed of sound and maneuvering the object based on when the object accelerates through the speed of sound. Another example embodiment relates to a system for navigating an object. The system includes a detector within the object. The detector determines when the object accelerates through mach one. The system further includes a guidance system within the object. The guidance system adjusts the flight of the object based on data received from the detector.

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

Abstract: A system for monitoring the contents of a closed container includes one or more sensors for monitoring the container contents, a signal receiving element positioned, and a processing system. The signal receiving element receives sensor data from the sensors. The processing system has a memory for storing predetermined conditions and a control element for analyzing received sensor data by comparing the received sensor data to stored predetermined conditions. The control element includes capabilities for declaring a security alert based on the comparison. The communications system includes a first transceiver inside the closed container for receiving signals containing sensor data from within the container and for transmitting those signals outside of the container, and a satellite transceiver, physically linked to the first transceiver and disposed outside the closed container, for receiving signals from the first transceiver and for forwarding the received signals via satellite uplink to a remote location.

Abstract: The present invention relates to a method for homogenizing measurement units used for displaying communication messages containing numerical data notably messages exchanged by an aircraft with the air traffic control authority. The choice of the working units of the flight management computer are recovered in the configuration database. The measurement unit of the numerical data item of the displayed message is determined. When the measurement unit of the numerical data item of the message does not form part of the system of measurement units, the numerical data item is connected into a unit forming part of the system of units. The display of the communication message on the onboard screen is formatted.

Abstract: A flight deck display system and related operating methods for an aircraft are provided. The system includes a processor architecture and a display element coupled to the processor architecture. The processor architecture is configured to receive real-time aircraft data and terrain data for the aircraft and, based upon the real-time aircraft data and the terrain data, generate image rendering display commands. The display element receives the image rendering display commands and, in response thereto, renders a primary flight display that includes a conformal view of terrain corresponding to a flight deck viewpoint. The primary flight display also includes a conformal terrain avoidance guidance (TAG) element on the view of terrain. The TAG element includes visual indicia of a desired navigation path that is intended to avoid terrain that obstructs a current flight path of the aircraft.

Abstract: A flight control system is provided that includes a reference system and flight control actuators. The reference system includes one or more sets of gyroscopes and accelerometers. At least one set of the gyroscopes and accelerometers are configured to provide a first output of a first set inertial signals for normal mode flight control and second output of a second different set of inertial signals for backup mode flight control. The flight control actuators are configured to be controlled by one of the first set of inertial signals and the second set of inertial signals.

Abstract: Systems and methods for improving output of weather information. A weather radar system receives weather reflectivity values. A processing device stores the received weather reflectivity values into a three-dimensional buffer, calculates a sum of the reflectivity value stored in a column of cells within the three-dimensional buffer, and assigns a first hazard indication to the cells of the column when the result of the calculation is above a first threshold. A display device generates a weather display based on data stored in the three-dimensional buffer. The weather display includes a display icon associated with the hazard indication when a cell from the three-dimensional buffer has been selected for the weather display.

Abstract: System for detecting wake turbulence (SDWT) of a first aircraft, which can be embedded onboard a second aircraft, comprising: first means (DET1) for determining the roll (Roll2) of the second aircraft; second determination means (DET2) of an envelope (CRollRef) of reference roll curves which is representative of a wake turbulence created by the first aircraft; means (COMP) for comparing, over a sliding window, the roll (Roll2) of the second aircraft and the envelope (CRollRef) of reference roll curves; and alarm means (AL) for forewarning the pilot of the second aircraft of the detection of wake turbulence of the first aircraft when the said comparison is below a resemblance threshold (SS).

Abstract: A method of determining effectiveness of an aircraft braking system on an aircraft during an aircraft landing including generating a scalar deceleration value when a predefined braking event occurs that corresponds to effectiveness of a braking system associated with an aircraft landing operation during occurrence of a predefined braking event on an aircraft; and disseminating the generated scalar deceleration value to downstream users. A system includes a data collection module adapted to collect data relating to braking data associated with each of an associated plurality of segments of deceleration of the aircraft during a predefined braking event; a calculation module adapted to generate a scalar deceleration value based on data obtained; and a communication module in signal communication with the calculation module and with at least one downstream user of the system adapted to communicate the scalar deceleration value to at least one downstream user.

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

Abstract: The device includes a calculation unit to automatically calculate an overall thrust moment of the engines which represents a thrust asymmetry of the engines of a multi-engine aircraft, a determination unit to automatically determine, using this overall moment, a maximum roll rate, and a limiting unit to automatically limit a roll command using this maximum roll rate.

Abstract: A terrain advisory display including a display, a processing circuit coupled to the display and wherein the display is configured to generate a three-dimensional image.

Abstract: A method is present for displaying weather information. A number of weather conditions present within an altitude range along a route of an aircraft is identified from weather data. A type of weather indicator is selected based on a type of weather condition in the number of weather conditions to form a number of weather indicators. A vertical situation display is displayed with the number of weather indicators in a number of locations on a display corresponding to the number of locations for the number of weather conditions.

Abstract: A method of determining a maneuver performed by an aircraft having sensors for monitoring motion data, the method including periodically sampling the sensors to electronically determine segments of motion data of the aircraft; aggregating sequences of the segments of the motion data; comparing the aggregated segments of motion data to models of particular maneuvers; and determining the maneuver performed by the aircraft.

Abstract: The parts of the flight plan of an aircraft corresponding to lateral trajectories at low altitude can comprise passages with limited lateral freedom of deployment because of risks of collision with the ground, or because of obstacles on the ground. The method makes it possible to signal them for the attention of the crew, so that said crew should redouble their attention. To do this it uses the display, on an onboard navigation screen, of a vertical profile of margin of maneuver relating to the navigation band widened to the right and to the left by lateral margins of maneuver, superimposed on the vertical navigation profile relating only to the navigation band.