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: The invention in particular has as an object a method and a device for centralized management of warnings in an aircraft comprising a centralized system for management of warnings (405) and a plurality of warning presentation interfaces (220?, 225?), each interface being adapted for presenting at least one warning to a user. After having determined at least one warning in the said centralized system for management of warnings according to at least one alarm activation signal received, the said determined warning is presented by a first interface (220?). The said determined warning is filtered and, in response to this step of filtering, the said determined warning is presented or not by a second interface (225?), separate from the first interface, According to a specific embodiment, the said step of presentation of the said determined warning by the said first interface comprises a step of filtering to determine whether or not the said determined warning should be presented by the said first interface.

Abstract: A method and a device (D) for detecting and signaling the approach to a vortex domain by a rotorcraft, the device includes: first elements (1) for measuring the instantaneous vertical speed v of a rotorcraft; second elements (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; third elements (3) constituting a database BDD relating to representing at least one instantaneous vortex domain; fourth elements (4) connected via first, second, and third connections (l1, l2, l3) respectively to the first, second, and third elements, the fourth elements being designed to detect the approach to a vortex domain by the rotorcraft; and fifth elements (5) for signaling the approach to a vortex domain by the rotorcraft, the fifth elements being connected to the fourth elements (4) via a connection (l4).

Abstract: A system and method of at least reducing the likelihood of a rotor lock in an aircraft gas turbine engine is provided. A determination is made that each propulsion gas turbine engine on an aircraft has experienced a flameout. The rotational speed of each propulsion gas turbine engine is compared to a predetermined threshold rotational speed and, if the rotational speed of each propulsion gas turbine engine is below the predetermined threshold rotational speed, a warning is supplied to a flight crew.

Abstract: Method and device for ensuring the safety of a low-altitude flight of an aircraft. The device (1) comprises a recording means (8) corresponding to an operation critical instrument for recording, during a low-altitude flight, one part at least of the lateral trajectory of the flight trajectory situated ahead of the current position of the aircraft, a monitoring means (11) for monitoring, during a low-altitude flight, the availability at least of said lateral trajectory, and a guidance system (3) for taking the aircraft up to a safe altitude, taking into account said part of the trajectory recorded by said recording means (8), when said monitoring means (11) has detected a loss of said lateral trajectory.

Abstract: A device includes a computer for computing the difference between at least two items of control information that are generated by at least two different flight management systems of an aircraft, and a system for generating a warning signal if the difference is greater than a threshold value.

Abstract: According to the invention, as a function of the altitude, the vertical speed and the heading of the aircraft, as well as of the deviation of the actual trajectory of the aircraft with respect to the automatic trajectory, a time interval (T) is determined, during which it is tolerable for said aircraft to be able to fly without any control command, both on the part of the stick (1) and on that of said automatic pilot (2) and an alert is emitted for the attention of the crew in the case where it is noted that the absences of manual piloting and of automatic piloting extend simultaneously over a duration at least equal to said tune interval (T).

Abstract: Presented is a system and method for detecting clear air turbulence comprising an image capturing element, a lens having focal length adapted to focus a scene onto the image capturing element such that the combination of the lens and array of pixels are capable of optically resolving any visual distortions of features in the scene that are caused by turbulent air, and a processor. The processor compares the image with a subsequent image, or a stored image of the scene, to detect a change in refraction of light received from the feature in the scene that is due to turbulence and produces an indication of the area of turbulence in the scene.

Abstract: A system and method for determining when a LED-based position light is nearing its end of life by providing to maintenance personnel visible indication that end of life is approaching. An example system includes a controller, a main LED light, an indicator LED light, a first elapsed time counter, a second elapsed time counter, and an oscillator. The first elapsed time counter recognizes when a first time threshold is exceeded, causing the indicator LED light to flash and triggering the second elapsed time counter to start counting. The second elapsed time counter recognizes when a second time threshold is exceeded, disabling both the indicator LED light and the main LED lights, thereby notifying maintenance personnel that the main LED lights have reached their end of life.

Abstract: A method of displaying, for a system for anti-collision monitoring of an aircraft, the limits of flight margins in relation to obstructions located in a flight zone, and a device for displaying the limits of operational flight margins and the limits of alert zones, is provided. The operational flight margins in the flight zones not initially envisaged, and the limits of the alert zones around the trajectory of the aircraft, are presented.

Abstract: A method identifies turbulence information from turbulence data generated by a set of remote aircraft based on a request to form identified turbulence information. The turbulence information is identified in response to the request received at an aircraft to view the turbulence information. The identified turbulence information is displayed on a display device in the aircraft.

Abstract: The invention relates to a method for managing an anti-collision system for aircraft, said system comprising means of detecting collision with a threat and at least one head-up viewing device. The symbol system comprises two display modes dedicated to collision detection which are: on the one hand an “action” mode: a potential collision is detected by the system, the symbol system comprises at least one symbol representative of the limits of the disengagement path of the aircraft to avoid the collision and enabling the pilot to engage his avoidance maneuver, and on the other hand a “control” mode: this mode is displayed when the avoidance maneuver is engaged and the collision avoided, the symbol system comprises at least the symbol representative of the limits of the disengagement path of the aircraft and a plan view representing the air space around the aircraft and including at least one representation of the threat.

Abstract: A method of detecting obstacles on board an aircraft while in the vicinity (44) of a touchdown point (27, 42), includes the following operations: selecting/determining a path (41) to be followed by the aircraft overflying the touchdown point; the aircraft overflying the touchdown point following the overflight path, and during the overflight recording signals/data delivered by an on-board rangefinder observing a portion of space extending below the aircraft; analyzing the rangefinder data to detect the presence of obstacles and to determine their positions in a terrestrial frame of reference, where appropriate to determine their dimensions; and recording the detected obstacle position data, and dimensions, if any, in a memory.

Abstract: An onboard system for a rotary wing aircraft detects a limit cycle oscillation in the tail mast and provides a timely indication of the limit cycle oscillation to an aircrew before serious damage to the airframe is likely to occur.

Abstract: A method for detecting and localizing a fuel leakage in the engine of a multi-engine aircraft consisting in determining a fuel consumption for each aircraft engine, in comparing the consumption of each engine with the other aircraft engines, in determining the engine exhibiting the greater fuel consumption ratio, in determining the excess consumption ratio of the aforementioned engine with respect to the other engines, in checking whether the excessive consumption is caused by a leakage and in triggering an alarm if the step is checked. A system for detecting and localizing a fuel leakage in the engine of a multi-engine aircraft including an airborne computer for carrying out the aforementioned method is also disclosed.

Abstract: A method is provided for indicating the boundaries of a required navigational performance (RNP) corridor on an aircraft's map display. The method includes the steps of producing an aircraft leg segment symbol on the map display, establishing an RNP value, and scaling the RNP value to the map display field of view. The method further includes the step of generating an RNP corridor boundary graphic on the map display offset from the aircraft leg segment symbol by the scaled RNP value.

Abstract: The process according to the invention is one of identifying the landing runway for which an aircraft is heading, wherein on the basis of on-board information and at least one database relative to the configuration of the landing airport zone, it is possible to dynamically evaluate the aircraft touchdown point on the ground to identify the runway for which the aircraft is heading.

Abstract: Systems and methods for handling information from wireless nodes, including nodes for communication with aircraft, are disclosed. A system in accordance with one aspect of the invention includes a sensor configured to sense information corresponding to a characteristic of a wireless node. The wireless node can be one of a plurality of wireless nodes configured to transmit and receive wireless signals. The wireless nodes can also be linked to a non-wireless network portion. The system can further include a transmitter configured to transmit the information via the network, and a receiver operatively coupled to the transmitter to receive the information via the network. Accordingly, the system can be used to automatically identify and track diagnostic information corresponding to the state of one or more wireless nodes.

Abstract: A system and method are provided for managing mobile platform fault data. The method includes automatically collecting raw fault data regarding at least one fault that occurs onboard the mobile platform utilizing a central maintenance computer (CMC) onboard the mobile platform. The raw fault data is automatically transmitted from the CMC to an onboard computer system (OCS) of the mobile platform and to a central computer system (CCS) located remotely from the mobile platform. The method additionally includes automatically generating at least one electronic mobile platform cabin (MPC) draft fault report from the raw data utilizing a first portion of an electronic logbook function (ELB1) of the OCS. Execution of the ELB1 additionally generates a MPC draft fault report notification message viewable on an OCS display and is automatically downloaded to the CCS.

Abstract: A vertical situation display system for use in a vehicle such as, for example, an aircraft, is provided. A side view of an intended route of flight may be shown with altitude restrictions, airspace and instrument approach information, a projected flight path and range to airspeed symbol. The system may show terrain, weather, and traffic information along the intended route of flight. The system may be used in conjunction with a navigational display to enhance situational awareness. The system includes a computer, an electronic display device, an electronic entry device, a memory and a database. The database may contain terrain, airspace and flight planning data and may be updatable.

Abstract: Method and device for ensuring the safety of a low-altitude flight of an aircraft. A device (1) for ensuring the safety of a low-altitude flight comprises information sources (5) able to determine current flight conditions, a monitoring unit (6) for realizing, with the aid of said current flight conditions, a function for global and autonomous monitoring of said low-altitude flight of the aircraft, making it possible to preserve the integrity of said aircraft during said flight, and means (13) for presenting the results of the monitoring function realized by said monitoring unit (6) to an operator.

Abstract: A method and device that assist a pilot of a follower aircraft during a patrol flight, by presenting on a viewing screen an indicator that provides information as to the possibility of engagement of an automatic pilot during a patrol flight.

Abstract: Methods and systems for a position indicating display system for an aircraft are provided. The system includes a map display unit configured to display a map representative of an area being traversed by the aircraft, and an overlay comprising an own ship depiction, said overlay displayed on the map for a period of time in response to an input from at least one of a user and an aircraft sensor.

Abstract: A method of transitioning from a complex response flight state to a ground operation control state. Pilot intent is determined through collective position information to control the transition. An independent cockpit switch activates an emergency surface contact transition function for use with a fly-by-wire (FBW) flight control system. Once the surface contact transition function is active, FBW control laws transition from a fully augmented flight state, through an augmentation deactivation state and into the surface contact state.

Abstract: An avionics display is disclosed. A synthetic rendering of terrain is created using stored terrain data. A horizon line is overlaid upon the synthetic rendering of terrain. The horizon line represents zero degrees pitch attitude in a direction of travel of an aircraft in which the avionics display is installed. The horizon line is configured to move in response to attitude-changing movement of the aircraft. An attitude cue is overlaid upon the synthetic rendering of terrain and depicted on first and second sides of the horizon line such that the synthetic rendering of terrain remains substantially visible. The attitude cue has a first appearance on the first side of the horizon line and a second appearance on the second side of the horizon line. The first appearance is visually contrasted from the second appearance.

Abstract: An aircraft lightning event detector includes a sensor mounted to an aircraft. The sensor determines whether a lightning event has struck the aircraft or induced a possibly damaging current into the aircraft. A threshold mechanism determines whether the sensed lightning event is greater than a predetermined size. A memory stores a record of the sensed lightning event for post-flight maintenance analysis when the lightning event is greater than the predetermined size.

Abstract: An airspace awareness and warning system (“AAWS”) provides input to an airspace alert (“AA”) processor from at least one real-time aircraft system or sensor, a navigation system, and an airspace database containing three-dimensional delineations of defined airspace; the processor determines an airspace clearance surface and an aircraft airspace alert surface, and if one surface penetrates the other, the processor generates an alert signal and provides an alert signal to a crew alerting system. The two surfaces are determined by the processor by executing an algorithm(s) embedded in software containing the disclosed embodiments and methods. At least one criterion used to define an aircraft airspace alert surface is programmed to include real-time and/or static input factor data provided by at least one system or sensor input from an aircraft. Such input factor could be used to define an airspace clearance surface.

Abstract: A vehicle operator interface is disclosed. The vehicle operator interface comprises a visual display device. A first indicator which is representative of a vehicle energy target, a second indicator representative of a vehicle energy vector and a third indicator representative of a vehicle capability zone are on the display.

Abstract: A method for monitoring the flight of an aircraft consisting in triggering a warning representative of hazardous meteorological conditions liable to face the aircraft while the navigation screen is displaying the terrain-following information.

Abstract: The invention relates to onboard failure warning management systems on aircraft, or flight warning systems (FWS). Traditionally, the logic of these systems refers to procedures to be executed by the crew in response to warnings. Modifications, however minor, to the procedures involve a new development that can be installed on the airplane computer only as part of a costly maintenance procedure, given notably the need to carry out exhaustive tests on the application. The invention introduces the concept of tasks defined by a set of variables, notably the warning and the procedure in which the task is executed, its category, its priority level and its status. Thus, the computer programs can be organized in modules that call the tasks to be executed, the parameters of said tasks being defined in a configuration table that can be updated as the procedures change during simple operation maintenance procedures.

Abstract: A method and a system for indicating a target idle running speed, a predicted core speed, a predicted time to running, current engine state or automation modes of an operating aircraft engine, and indicating that the current core speed of the aircraft engine is less than a target idle running speed or is abnormally decreasing towards a target idle running speed. The indicators may be visual or aural. The visual indicators may include graphical or numeric symbols indicating the target idle running speed, the direction of core speed change, the predicted core speed at some future time, or current engine state or automation mode.

Abstract: A circuit for a display used on an aircraft causes the display to display a composite terrain image. The composite terrain image can be formed from first terrain data from a terrain database and second terrain data from a radar system. A display control circuit can generate a display signal for the composite terrain image. The display signal is received by the display. The composite terrain image can be viewed by a pilot.

Abstract: A transponder module for vehicles. The module has a substantially universal vehicle sensor input interface capable of receiving sensor input from different types of vehicle sensors and from different types of vehicles. One or more processors and memory, in real time, receive vehicle sensor input data via the input interface. Based on a vehicle type stored in the memory, the processor(s) use the sensor input data to determine conditions of subsystems the vehicle. Based on the determined conditions, the processor(s) determine performance capabilities of the vehicle. The transponder module outputs information as to the stored vehicle type, determined conditions, and vehicle performance capabilities.

Abstract: The system contains a receiver in communication with a programmable device. The receiver receives a first horizontal distance from the aircraft to a threshold of the runway, an angle of a glide path, and a threshold crossing height. The programmable device determines a projected ground distance from the aircraft to the threshold. The programmable device determines a projected ground distance from the threshold to a glide path intercept point. The programmable device determines a vertical value along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point. The programmable device determines a synthetic altitude above runway for the aircraft.

Abstract: The invention relates to a method for producing an audible warning when an aircraft autopilot (2) is deactivated consisting: a) in transmitting a first sound in the aircraft cockpit during a time ranging from a first predetermined value (d1) and a second predetermined value (d2) and b) in transmitting a second sound in the aircraft cockpit. Said invention also relates to an audible warning device (1) comprising first means (10) for monitoring the deactivation of the aircraft autopilot (2) and means (12) for emitting an audible warning in the cockpit, wherein said second means is constructed in such a way that it activates the first sound emission whose length ranges from the first predetermined value (d1) and a second predetermined value (d2) and a second sound when the first means detects the deactivation of the autopilot.

Abstract: Methods and systems are provided which warn a pilot or flight crew to prevent navigation of an aircraft into an unapproved region of operation. A boundary of an approved region of operation for the aircraft is identified. A position of the aircraft relative to the boundary of the approved region of operation is determined. Then, a warning is generated if the determined position of the aircraft relative to the boundary of the approved region of operation satisfies a predetermined criteria.

Abstract: A method for supporting low-level aircraft flights in which a warning is provided for the pilot upon a reliable recognition of wire-like obstacles, even during extreme environmental influences, such as clutter, or even when such obstacles are seen against the sky. The method is performed upon the collection of information on the topography of the surrounding terrain by at least one sensor located on the aircraft, such information representing raw data, based upon which an image-like representation is calculated, such representation including a pixel quantity with pixels P(i, j) in columns j and lines i, which image-like representation is evaluated by calculating altitude values in a geodetic coordinate system using the flight condition from the aircraft, evaluating pixel quantity by comparing each pixel P(l, j) to threshold values or ranges of values, evaluating the image-like representation and highlighting each pixel as a picture element if any of various cases is present.

Abstract: The present invention provides a method and system for displaying critical navigational data on a primary flight display to a pilot of an aircraft. The method includes providing an image representative of weather information on a primary fight display and superimposing an image representative of a terrain warning indicator over at least part of the image representative of weather information.

Abstract: In some embodiments, a search and rescue communication may include one or more of the following features: (a) a rescue terminal, (b) a main terminal operably connected to said rescue terminal across a communication network, said main terminal sends an emergency notification message across said communication network to said rescue terminal, and (c) a survival terminal associated with an ejection seat, said survival terminal being in communication with said main terminal, wherein said emergency notification message is delivered by said main terminal when said ejection seat is ejected.

Abstract: The present invention relates to a standby instrument fitted to the instrument panel of an aircraft detecting overloads. The standby instrument includes a processor to calculate and display flight information based on data provided by associated sensors integrated into a standby system. It additionally includes a module for detecting overload of the aircraft on the basis of the data provided to display the flight information. The invention applies to the detection of overloads during a heavy landing. More generally, it applies to the detection and indication of overloads of an aircraft in various types of environment.

Abstract: After deactivation of the presentation of weather information on a radar weather display, systems and methods re-trigger when weather conditions change so that the crew is advised of the changed weather conditions. An exemplary embodiment monitors at least one condition of the weather and in response to the monitored weather condition meeting a re-triggering criteria, presents an advisory to a crew member of the aircraft indicating at least presence of the weather.

Abstract: Method and system for analyzing and processing information on one or more aircraft flight paths, using a four-dimensional coordinate system including three Cartesian or equivalent coordinates (x, y, z) and a fourth coordinate ? that corresponds to a distance estimated along a reference flight path to a nearest reference path location corresponding to a present location of the aircraft. Use of the coordinate ?, rather than elapsed time t, avoids coupling of along-track error into aircraft altitude and reduces effects of errors on an aircraft landing site. Along-track, cross-track and/or altitude errors are estimated and compared with a permitted error bounding space surrounding the reference flight path.

Abstract: The present invention relates to an alarm management system intended to be carried onboard an aircraft. More precisely, the invention is aimed at improving the certainty level relating to the integrity of the announcements of faults or information intended for the pilot and based on voice syntheses. For this purpose, the present invention proposes a device and a method for detecting the digital origin of an analog signal providing a validity signal (VAL) enabling the voice announcements made to the pilot to be rendered secure.

Abstract: A method, system and computer program product to detect and indicating TFR zone violations, potential TFR zone violations or TFR zones in vicinity of an aircraft and indicating measures to avoid or exit a TFR zone are provided. TFR zone information and an aircraft's position information are received. The aircraft's position information is processed to determine the aircraft's current heading. A TFR zone violation is determined based on the aircraft's current position. A potential TFR violation is determined based on whether the aircraft's current heading intersects a TFR zone. The presence of a TFR zone in the vicinity of the aircraft is determined based on the aircraft's current position and heading. Indicators of a TFR violation, potential TFR violation, no TFR violation or TFR zones in the vicinity are provided. If a TFR violation, or possible TFR violation or TFR zone in the vicinity are found, measures are indicated to exit the TFR zone or change the aircraft's current heading to avoid the TFR zone.

Abstract: A terrain awareness and warning system includes electronics for receiving radar returns and providing terrain and/or obstacle alerts or warnings in response to the radar returns. The electronics receives information from a database and the information is utilized to suppress false alerts or warnings.

Abstract: The device relates to the signaling, to the pilot of a craft, of the risks that it incurs due to obstacles placed in its zone of deployment. This device determines, on the zone of deployment of the craft, the contours of several types of risk region as well as the contours of two lateral regions of tight deployment tied to the craft and produces alarms as a function of the types of zones at risk found in the lateral regions of tight deployment.

Abstract: Systems and methods for assisted recovery. An example method receives at least one of a directional or pitch command signal. Localizer or glide slope signals are generated based on the received signal. The localizer or glide slope signals are wirelessly transmitted via a predefined frequency over a transmitter and received at receivers of a navigation system. The vehicle is controlled based on the received signals. A proximity warning device generates an alert when the aircraft is within an alert distance from at least one of terrain, obstacle or special use airspace and an assisted recovery component generates the directional and pitch command signals based on the generated alert and a time delay.

Abstract: A method for transmitting one or more messages over a secure communications network is disclosed. The method involves receiving the one or more messages from a plurality of message sources at a management unit within the secure communications network, the one or more messages protected with information security and authorizing each message for display at a display point. The method further involves transmitting each of the messages to a plurality of communication end points throughout the secure communications network and relaying at least one response through the management unit.

Abstract: A method for displaying data on a portable electronic device first displays graphical data on a graphical display. An event that is independent of the graphical data is received at the device. Responsive to the event, an event type is selected from a list that associates each of at least two event types with one of at least two display formats. A notifier of the event, in the selected format, is then displayed on the graphical display simultaneously with the graphical data. The formats are specific to the event types so that a user can decide whether to continue viewing the graphical data and not respond to the event notifier, or terminate the graphical data being displayed and respond to the event. Examples of events include an alarm from a locally stored user calendar, an incoming phone call, an SMS message, and an email. A computer program and a device are also detailed.

Abstract: An aircraft flight risk measuring system for analyzing risks related to a flight of an aircraft. A user of the risk measuring system can be a flight dispatcher, an owner/operator, a pilot and other interested parties. The risk measuring system includes a risk management server system computer. The system computer has a two-way communication with a user computer operated by the user. An accident history database is connected to the system computer for providing accident reports related to the aircraft and other accident data. Also, a navigation database is connected to said system computer for providing airspace data, radio navigation aids, preferred routes, elevation data, geographic data and information related to a destination airport. Further, a non-static database is connected to the system computer for providing live information related to weather forecasts and data related to the aircraft's flight.