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Flight condition indicating system

Subclass of:

701 - Data processing: vehicles, navigation, and relative location

701001000 - VEHICLE CONTROL, GUIDANCE, OPERATION, OR INDICATION

701003000 - Aeronautical vehicle

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Entries
DocumentTitleDate
20130030612METHOD AND DEVICE FOR AN OPTIMAL MANAGEMENT OF THE ENERGY OF AN AIRCRAFT - Method and device for an optimal management of the energy of an aircraft.01-31-2013
20090012663DETERMINING CURRENT METEOROLOGICAL CONDITIONS SPECIFIC TO AN AIRCRAFT - A method of providing meteorological data for aeronautical use. The method includes collecting data from a plurality of data sources, processing the data to determine current meteorological conditions of a current location of an aircraft in an airspace, and providing the current meteorological conditions to the aircraft and other users as appropriate, such as airline operations centers, air navigation service providers, and national weather service providers. Based on current aircraft behavior data and guidance systems design, beneficial wind and meteorological data can be established for a given flight and its cleared route and descent path.01-08-2009
20100152932SYSTEM AND METHOD FOR RENDERING AIRCRAFT TRAFFIC ON A VERTICAL SITUATION DISPLAY - A flight deck display element for a host aircraft is used to render a dynamic vertical situation display (VSD). The VSD includes a graphical representation of the host aircraft, graphical representations of one or more neighboring aircraft, and a graphical representation of a conflict zone surrounding the graphical representation of the host aircraft. The graphical representations of the neighboring aircraft are positioned on the VSD in a manner that indicates the respective altitudes of the neighboring aircraft relative to the host aircraft. They are also positioned on the VSD in a manner that indicates the respective lateral separation of the neighboring aircraft relative to the host aircraft.06-17-2010
20090055036System for acquiring air data during flight - The present invention relates to aviation. The proposed air data system includes pitot pressure probes with sensing ports, anti-icing electric heaters, conduits, pressure transducers, outer air temperature sensors, and computer; the above units and components are incorporated in a single streamlined housing attached to the aircraft and composed of axisymmetric surfaces. The system for air data acquisition is autonomous and interacts with the aircraft and its subsystems through only the information exchange channels and power supply lines via electric connectors.02-26-2009
20110196551SYSTEM AND METHOD FOR SITUATION SPECIFIC GENERATION AND ASSESSMENT OF RISK PROFILES AND START OF SUITABLE ACTION FOR PROTECTION OF VEHICLES - The present invention relates to a vehicle system (08-11-2011
20100076629System and Method for Merging Meteorological Data Predicted and Measured on an Aircraft - The invention consists in merging together the predicted and measured meteorological data to supply them to the flight prediction calculation system so as to smooth the discontinuities brought about in the prior art by the simple update which is carried out. This merging is advantageously done by linear weighting of the data, the weighting coefficient depending upon the positioning in vertical and horizontal distances between the predicted point and the aeroplane in relation to chosen thresholds.03-25-2010
20130079957Aerological Phenomena Alert Device for an Aircraft - An aerological phenomena alert device for an aircraft, which comprises onboard equipment capable of detecting meteorological phenomena, comprises: a module for collecting and storing meteorological data originating from the onboard equipment capable of detecting the meteorological phenomena, a module for creating a report from the collected meteorological data, a module for sending the report, a module for receiving reports sent by surrounding aircraft, a module for processing and consolidating the reports received, and for generating alerts when a report signals an aerological phenomenon, and a module for merging the data originating from aircraft and from meteorological stations, situated in a station on the ground and comprising a ground/air communication module for sending meteorological reports adapted to each aircraft according to its position in relation to an aerological phenomenon.03-28-2013
20130138272INTERACTIVE DIALOG DEVICE BETWEEN AN OPERATOR OF AN AIRCRAFT AND A GUIDANCE SYSTEM OF SAID AIRCRAFT - The dialog device includes a display screen, on which are displayed three graphic representations, which are respectively associated with the three control axes of the aircraft, each of said graphic representations comprising a plurality of portions, each of which is associated with a guidance mode of the associated control axis, so that all the possible guidance modes of the guidance system are thus represented, this representation highlighting the fact that the guidance modes are active exclusively on a given guidance axis.05-30-2013
20100100262Method and Device for the Energy Protection of an Aircraft - According to the invention, an aircraft speed threshold is computed in order to calculate a total power to apply to aircraft engines. When conditions of activation are fulfilled, the current individual power of each aircraft engine in operation controlled by a protection function is gradually modified.04-22-2010
20100042275SYSTEMS AND METHODS FOR GENERATION OF COMPREHENSIVE AIRSPACE WEATHER CONDITION DISPLAY FROM SHARED AIRCRAFT SENSOR DATA - Systems and methods communicate sensor data pertaining to detected weather between aircraft. An exemplary system has at least one sensor on a transmitting aircraft, wherein the sensor is configured to detect weather and configured to output sensor data. The system has a first transceiver on the transmitting aircraft that is configured to transmit a signal with the sensor data. And the system has a second transceiver on a receiving aircraft that is configured to receive the signal containing the sensor data transmitted by the first transceiver. The sensor data of the transmitting aircraft is fused with sensor data of the receiving aircraft for a geographic region of interest to extend the effective sensor coverage and to resolve at least one of a location conflict and a severity conflict between the sensor data of the transmitting aircraft and the receiving aircraft.02-18-2010
20090125167METHOD AND APPARATUS FOR DETECTING ICING CONDITIONS FOR AN AIRCRAFT - A method for detecting icing conditions for an airborne aircraft operating within a zone defined using one or more aircraft-related parameter and one or more environment parameter includes: (a) In no particular order: (1) measuring the aircraft-related parameter(s) to obtain aircraft-related parametric value(s); and (2) measuring the environment-related parameter(s) to obtain environment-related parametric value(s). (b) Employing the aircraft-related parametric value(s) and the environment-related parametric value(s) to determine whether the aircraft is operating within the zone. (c) If the aircraft is operating within the zone, observing elapsed time during which the aircraft is operating within the zone. (d) If the aircraft has operated within the zone for a predetermined elapsed time-in-zone, displaying an alert message for a user to indicate a likelihood of presence of icing conditions.05-14-2009
20100094487AVIONICS DISPLAY SYSTEM AND METHOD FOR GENERATING THREE DIMENSIONAL DISPLAY INCLUDING ERROR-COMPENSATED AIRSPACE - Embodiments of a method are provided that may be carried out by an avionics display system deployed on an aircraft and including a monitor. The avionics display system receives position data indicative of the aircraft's detected position from at least one data source. In one embodiment, the method includes the steps of: (i) attributing an error characteristic to the data source, (ii) identifying an airspace assigned to the aircraft at a given time, and (iii) establishing an error-compensated airspace as a function of the error characteristic and the assigned airspace. The aircraft's actual position remains within the assigned airspace provided that the aircraft's detected position resides within the error-compensated airspace. A visual representation of the outer boundaries of the error-compensated airspace is generated on the monitor.04-15-2010
20100063654Locator Beacon Disposed Internal to an Enclosure of a Flight Data Recorder and Method Therefor - A flight data recorder includes an enclosure and electronic interface within the enclosure. The electronic interface is coupled for receiving data. A crash survivable memory unit is disposed within the enclosure. The crash survivable memory unit includes a memory module electrically coupled to the electronic interface for storing the data. A locator beacon is disposed within the enclosure or within the crash survivable memory unit. The locator beacon is an acoustic resonator which emits ultrasonic pulses. A battery is disposed within the enclosure or within the crash survivable memory unit for providing operating power to the locator beacon. The battery is rechargeable. The battery status is stored in the memory module. A beacon control circuit is disposed within the enclosure or within the crash survivable memory unit for monitoring the battery. A beacon activation device detects a crash event and notifies the beacon control circuit to activate the locator beacon.03-11-2010
20130046423SYSTEM AND METHOD FOR AIRCRAFT THERMAL CAPACITY PREDICTION - A technique for identifying, projecting, displaying, and enhancing the thermal capacity for an aircraft is disclosed wherein the thermal capacity is defined as the amount of time or range the aircraft can continue until a thermal limit is exceeded.02-21-2013
20090043432Method and device for determining the dynamic stability margin of an aircraft - A method of determining a dynamic stability margin M02-12-2009
20090306839Aircraft monitoring equipment - An aircraft monitoring system uses aircraft engine and system transducers to monitor critical engine and aircraft system parameters. Simple controls and graphical user interfaces facilitate the display of different kinds of critical information to the pilot. Such data may also be recorded for later downloading and analysis.12-10-2009
20130073124Method and Device for Protecting an Aircraft - A method and a device for protecting an aircraft in the flight phase, said aircraft exhibiting several configurations of slats and flaps, comprises the following steps: determining, for at least one configuration of slats and flaps, of a limit angle of incidence beyond which the aircraft runs a risk of stalling, determining a gain factor as a function of the normal acceleration of the aircraft, comparing the current angle of incidence of the aircraft—with the limit angle of incidence weighted by the gain factor, and, emission of an alert indicating that the aircraft runs a risk of stalling, if the current angle of incidence of the aircraft is greater than the limit angle of incidence weighted by the gain factor.03-21-2013
20130066487FLIGHT OPERATIONAL CONSEQUENCES SYSTEM - According to an embodiment, a method provides flight operational consequence information by receiving a status indication associated with an aircraft component at a processing device in the aircraft during a flight. The processing device ascertains one or more operational consequences that includes displaying text strings associated with the status indication, wherein each of the one or more operational consequences are associated with one or more flight segments of the flight. At least a subset of the one or more operational consequences are provided on a display associated with the processing devices and an indication is provided on the display of the one or more flight segments associated with the one or more operational consequences.03-14-2013
20130066488METHOD AND DEVICE FOR AUTOMATICALLY ESTIMATING AN AIRSPEED OF AN AIRCRAFT - Method and device for automatically estimating an airspeed of an aircraft03-14-2013
20110282524SYSTEM AND METHOD FOR DETECTING WAKE TURBULENCE OF AN AIRCRAFT - System for detecting wake turbulence (SDWT) of a first aircraft, which can be embedded onboard a second aircraft, comprising: 11-17-2011
20110029163METHOD OF CORRECTING GUIDANCE COMMANDS FOR FLUID MEDIUM - A method of approximately correcting a vehicle's guidance system command for the disturbing effects of the medium through which it is moving, without having to sense or estimate the speed and direction of that medium. The correction is determined by taking the ratio of two scalar quantities: the speed of the vehicle relative to the medium, which can be estimated from the known fluid dynamic characteristics of the vehicle, divided by an approximation of inertial speed, which can be obtained using one or more on-board sensors such as a GPS, thus increasing transient performance of the vehicle moving through the fluid medium.02-03-2011
20090118876DECOMPRESSION VENT LATCHING MECHANISM - A decompression vent latching apparatus, includes a flap placed on a door opening to a first area from a second area, a housing fastened to the flap on the door, a plunger mounted within the housing, having rotational and lateral movement within the housing, a stop block connected to the plunger, a pair of tip blocks having movement restricted by the stop block connected to the plunger when contacting the stop block, the tip blocks being controlled to be a predetermined distance away from the stop block, and a locking unit connected to the pair of tip blocks providing a closed or open position.05-07-2009
20100057277METHODS AND SYSTEMS FOR HEALTH MONITORING FOR AIRCRAFT - A method for health monitoring for an aircraft includes the steps of obtaining vibration data for the aircraft, obtaining navigation data for the aircraft, and determining a measure of health of the aircraft using the vibration data and the navigation data.03-04-2010
20110125349Integrated Bird-Aircraft Strike Prevention System - IBSPS - An airborne apparatus that employs an advanced computer to analyze bird and aircraft positioning data, programmed to issue a warning about an impending strike, thereby creating the ultimate Bird-Aircraft Strike Prevention System. This system will constantly process the bird positioning data gathered by the Radar/Infrared sensors. In case of a bird-aircraft strike danger the system will immediately alert the pilot as well as Air Traffic Control, and, compute the necessary course correction required to avoid the collision. The advantages of the system include the ability to prevent bird strikes and instantaneously compute an alternative course or action necessary to avoid the bird-aircraft impact. Additionally, because the IBSPS is capable of being airborne, the aircraft will be protected from bird-strikes throughout the entire flight, even in absence of ground systems. Furthermore, the ability to integrate all IBSPS equipped airplanes significantly increases area coverage and enhances the safety of Air Traffic System.05-26-2011
20080312781Quiet Climb Crew Interface - 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.12-18-2008
20090299554METHOD AND DEVICE FOR MONITORING THE SPEED OF AN AIRCRAFT - A method for controlling speed of an aircraft in the air. The method compares a variation of the aircraft speed in the air with a variation of the aircraft speed on the ground for an identical period, and detects any significant difference between the variations.12-03-2009
20120296500AERODYNAMIC COEFFICIENT ESTIMATION DEVICE AND CONTROL SURFACE FAILURE/DAMAGE DETECTION DEVICE - A highly reliable aerodynamic coefficient estimate can be computed, and computation of this aerodynamic coefficient estimate enables accurate detection of control surface failure/damage while reducing a discomfort for passengers. A deflection angle command signal generation means (11-22-2012
20110208375DEVICE, SYSTEM AND METHOD OF ESTIMATING THE ANGLE OF ATTACK OF AN AIRCRAFT - A device for estimating the angle of attack of an aircraft moving through the air comprises means for receiving a measured incidence presented locally by the air relative to the aircraft and means for determining the angle of attack of the aircraft as a function of the measured incidence and information about the airspeed of the aircraft. The means for determining the angle of attack of the aircraft comprise means for reading the angle of attack of the aircraft from a look-up table having at least the measured incidence and the airspeed information as inputs. Corresponding system and a corresponding method are also proposed.08-25-2011
20080249674Method and device for determining a maximum stabilization height in the final flight phase of an airplane - The disclosed embodiments relate to a method of determining a maximum stabilization height h10-09-2008
20090319103PERSPECTIVE VERTICAL SITUATION DISPLAY SYSTEM AND METHOD - A display system and method for an aircraft simultaneously displays the terrain under the flight plan, or under the current track of the aircraft, as both a two-dimensional lateral situation view image and as a perspective vertical situation view image. This provides improved tactical flight planning, and that does not erroneously show the flight plan passing through the displayed terrain.12-24-2009
20090319102Flight Recorder Having Integral Reserve Power Supply Within Form Factor of Enclosure and Method Therefor - A flight recorder includes an enclosure having a notch formed on one side or corner of the enclosure. An electronic interface is disposed within the enclosure. The electronic interface is coupled for receiving flight data, video data, and audio data. A memory unit is disposed within the enclosure and electrically connected to the electronic interface for storing the data. The memory unit contains a non-volatile memory device. A reserve power supply is physically disposed within the notch of the enclosure. The reserve power supply contains a rechargeable battery. A clamp secures the reserve power supply to the enclosure to make the reserve power supply removable from the enclosure. The reserve power supply has an electrical connector coupled to the enclosure for providing an operating voltage to the electronic interface and memory unit. The reserve power supply and electrical connector physically reside within a form factor of the enclosure.12-24-2009
20080234884SYSTEM AND METHOD FOR FACILITATING AERIAL REFUELING - A refueling system and method for use with a refueling tanker aircraft. The system and method involves the use of a camera system to provide imaging information concerning a receiver aircraft to the processor. The processor uses the imaging information to derive closure rate and distance information for the receiver aircraft as it approaches a refueling envelope prior to contact with a refueling boom. The processor also makes use of information from a look-up table to generate commands that are tailored to the specific type of aircraft being refueled. The commands are applied to a pilot's director lights display that generates visual commands or signals (e.g., “UP”, “DOWN”, “LEFT”, “RIGHT”) that assist the pilot of the receiver aircraft in guiding his/her aircraft toward and into the refueling envelope at a desired closure rate. The system and method eliminates potential error in the pre-contact phase of a refueling operation by eliminating judgment decisions by a boom operator when generating the commands for the pilot's director lights display.09-25-2008
20110208376ON-BOARD FLIGHT STRATEGY EVALUATION SYSTEM ABOARD AN AIRCRAFT - The invention relates to a process and an on-board system for evaluating flight strategies aboard an aircraft, linked with a flight plan (08-25-2011
20090138147LOW-FREQUENCY FLIGHT CONTROL SYSTEM OSCILLATORY FAULTS PREVENTION VIA HORIZONTAL AND VERTICAL TAIL LOAD MONITORS - 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).05-28-2009
20090005920METHOD AND DEVICE FOR DETECTING NOISE ON A GUIDE SIGNAL OF LOC TYPE RECEIVED BY AN AIRCRAFT - The invention has as an object a method and a device for an aircraft for detecting noise in a signal of LOC type. A first step consists in estimating a first lateral speed (01-01-2009
20090024260METHOD AND DEVICE FOR AUTOMATICALLY ADJUSTING AN IMAGE OF AN AIRCRAFT NAVIGATION SCREEN - Method and device for automatically adjusting an image of an aircaft navigation screen. The device (01-22-2009
20090099713Device And Method For Providing A Flight Status Signal - The present invention provides a device for providing an aircraft flight status signal which indicates whether the aircraft is in the air or on the ground, which device calculates the flight status signal as a function of a number of differently provided flight speed signals, a number of differently provided engine status signals, a number of differently provided evacuation signals, a number of differently provided front undercarriage status signals and a number of differently provided main undercarriage status signals.04-16-2009
20100262320ACTUATOR MONITORING CIRCUIT, CONTROLLER, AND ACTUATOR UNIT - An actuator monitoring circuit 10-14-2010
20100179712TRANSPARENT VEHICLE SKIN AND METHODS FOR VIEWING VEHICLE SYSTEMS AND OPERATING STATUS - Systems and methods for viewing systems and status of a vehicle are provided. One system includes memory configured to store schematic data representing a schematic of the vehicle and a processor coupled to the memory and configured to execute the schematic data. The system further includes a display coupled to the processor and configured to output an image of the schematic, the image providing a transparent direct view of the vehicle and the systems. One method includes the steps of generating an image representing a schematic of the vehicle and the systems, the image providing a transparent direct view of the vehicle and the systems and selectively rotating the image such that a user is capable of viewing the vehicle and the systems from a plurality of angles. Also provided are machine-readable mediums including instructions for executing the above method.07-15-2010
20100241294METHOD AND DEVICE FOR ESTIMATING AT LEAST ONE WIND CHARACTERISTIC ON AN AIRCRAFT - A method and a device for estimating on an aircraft at least one wind characteristic.09-23-2010
20100222945METHOD AND DEVICE FOR DETERMINING AERODYNAMIC CHARACTERISTICS OF AN AIRCRAFT - The present invention provides a device and method for determining aerodynamic characteristics of an aircraft, in particular a pitch moment coefficient at an ascending force of the aircraft without a horizontal tail plane of zero and an aerodynamic neutral point of the aircraft without a horizontal tail plane. In the method according to the invention, forces and mechanical flight parameters on aerofoils and a horizontal tail plane of the aircraft are detected at various detection instants during at least one non-stationary flight manoeuvre of the aircraft. In this case, a linear system of equations is formed, which comprises a pitch movement moment balance equation for each detection instant, the pitch movement moment balance equation having the detected forces and mechanical flight parameters. This linear system of equations is evaluated to calculate the aerodynamic characteristics.09-02-2010
20100211237SYSTEM AND METHOD FOR RENDERING A SYNTHETIC PERSPECTIVE DISPLAY OF A DESIGNATED OBJECT OR LOCATION - A method for displaying information on a flight deck display element of an aircraft begins by obtaining a user interface command that represents a user-entered selection of a designated target. Relevant data is accessed and processed in response to this command, including aircraft status data for the aircraft, terrain data corresponding to terrain proximate the designated target, and graphics data corresponding to the designated target. Then, a target-focused display is rendered on the flight deck display element. The target-focused display includes a real-time synthetic perspective view of the designated target and the terrain proximate the designated target, wherein content of the target-focused display is influenced by the aircraft status data, the terrain data, and the graphics data.08-19-2010
20130218373Method and System For Highlighting a Flight Path Deviation of an Aircraft - A method and system for highlighting a flight path deviation of an aircraft to a user in a multi-parameter aircraft instrument display, such as a flat panel display. A visibility attribute is configured to toggle between a standard state when the actual aircraft position is within a predetermined range of the target aircraft position, and an enhanced state when the actual aircraft position is outside the predetermined range. The electronic display is configured to highlight a flight path deviation when in the enhanced state, such as by displaying deviation scales having an actual aircraft position indicator relative to the target position, and increasing the size or changing the color of certain displayed elements, or displaying/concealing new elements. Such display features aid in focusing the pilot's attention to deviations from optimal flight paths and ensuring navigation accuracy and, therefore, safety.08-22-2013
20090112381Method and apparatus for a crash survivable flight data recorder - Common practice in the aviation industry is to place a single Flight Data Recorder (FDR) in an aircraft for the purpose of aiding an investigation of an aircraft accident or incident. In contrast, a system employing ‘an example’ embodiment of the invention uses multiple flight data recorders by having a primary node or first FDR, and one or more secondary nodes or one or more additional FDRs configured to store flight data. Each FDR is placed in a different location so as to ensure backup of the recorded and stored data. In this way, the invention system provides redundancy of information for an aircraft accident or incident and more reliable data storage.04-30-2009
20130131897THREE DIMENSIONAL AUDITORY REPORTING OF UNUSUAL AIRCRAFT ATTITUDE - A system and method for reporting unusual aircraft attitude to a pilot includes sensing aircraft attitude, and processing the sensed aircraft attitude to determine when the aircraft attitude exceeds an attitude limit. A three-dimensional directional audio alert is generated that, when heard by the pilot, sounds like it is coming from a direction to which the pilot should maneuver the aircraft to correct the aircraft attitude, and includes a verbal instruction that the pilot should follow correct the aircraft attitude.05-23-2013
20090037037AUTOMATIC DOWNLINK MESSAGING DURING EMERGENCY FLIGHT SITUATIONS - According to an example embodiment, a method includes receiving an emergency status signal indicating that an aircraft is in an emergency condition, formatting a downlink message in response to receiving the emergency status signal, the downlink message describing the emergency condition and an autopilot response to the emergency condition, and transmitting the downlink message to a controller of the aircraft.02-05-2009
20100332056SYSTEMS AND METHODS FOR GENERATION OF COMPREHENSIVE AIRSPACE WEATHER CONDITION DISPLAY FROM SHARED AIRCRAFT SENSOR DATA BY A RECEIVING AIRCRAFT - Systems and methods communicate sensor data pertaining to detected weather between aircraft. An exemplary system receives a signal from a remote aircraft that includes at least sensor data acquired from sensors on the remote aircraft. The system fuses the sensor data of the remote aircraft with sensor data of the receiving aircraft to resolve at least one of a location conflict and a severity conflict between the sensor data of the remote aircraft and the receiving aircraft. The system presents weather information on a display corresponding to the fused sensor data of the remote aircraft and the receiving aircraft.12-30-2010
20100332057FLIGHT INFORMATION REMINDER SYSTEM AND METHOD - A flight information reminder system includes a computer system maintaining updated flight information about a flight having a duration. The computer system is adapted to issue messages to individual subscriber units over a wireless network at spaced intervals throughout at least a portion of the duration of the flight, and the subscriber units are each coupled to receive the messages issued from the computer system over the wireless network. The messages each contain the updated flight information about the flight.12-30-2010
20110029164AVIATION YOKE HSI INTERFACE AND FLIGHT DECK CONTROL INDICATOR AND SELECTOR SAFETY SYSTEM - An aviation yoke HSI interface and flight deck control indicator and selector safety system enhances flight safety. The system incorporates a multi-controlled HSI with a yoke heading adjustment control, a yoke VOR radial selector, and a yoke heading centering control positioned on the captain yoke. The system may also incorporate a first officer multi-controlled HSI with a first officer yoke heading adjustment control, a first officer yoke VOR radial selector, and a first officer yoke heading and course centering control positioned on the first officer yoke. An autopilot mode indicator visually indicates whether an autopilot is flying according to a desired heading or according to a VOR radial signal. A side selector-indicator control permits selection of which side controls the flight of the aircraft. A first control unit and a second control unit may be in electrical communication with both sides to fly the aircraft in autopilot.02-03-2011
20110213514AVIATION YOKE HSI INTERFACE AND FLIGHT DECK CONTROL INDICATOR AND SELECTOR SAFETY SYSTEM - An aviation yoke HSI interface and flight deck control indicator and selector safety system enhances flight safety. The system incorporates a multi-controlled HSI with a yoke heading adjustment control, a yoke radial/course selector, and a yoke heading centering control positioned on a yoke, stick, or collective. The system may also incorporate a first officer multi-controlled HSI with a first officer yoke heading adjustment control, a first officer yoke radial/course selector, and a first officer yoke heading and course centering control. An autopilot mode indicator visually indicates whether an autopilot is flying according to a desired heading or according to a navigational aid signal, such as a VOR radial signal. A side selector-indicator control permits selection of which side controls the flight of the aircraft.09-01-2011
20110035081METHOD FOR STAND-ALONE ALIGNMENT OF AN INERTIAL UNIT FOR AN ONBOARD INSTRUMENT CAPABLE OF BEING MOUNTED IN AN AIRCRAFT, AND AN ONBOARD INSTRUMENT BEING ABLE TO USE SUCH A METHOD - In a method for stand-alone alignment of an inertial unit for an onboard instrument capable of being mounted in an aircraft, the method includes monitoring the appearance of a movement of the inertial unit during the alignment, suspending the alignment of the inertial unit in the event of the appearance of movement, and resuming the alignment of the inertial unit on the disappearance of the movement.02-10-2011
20110082605AIRCRAFT PILOTING ASSISTANCE METHOD AND CORRESPONDING DEVICE - An aircraft piloting assistance method and system including determining at least one flyable slope with which the aircraft is assumed to be able to fly, based on a value of at least one flight parameter including the weight of the aircraft. The step for determining said slope or slopes with which the aircraft is able to fly, called flyable slopes is performed by a computer, and presenting the flyable slope to a decision-maker.04-07-2011
20110246001SYSTEMS AND METHODS FOR AIRCRAFT FLIGHT TRACKING AND EMERGENCY LOCATION - Systems and methods are provided for automated collection and analysis of aircraft flight data. In accordance with one aspect, a system for collecting flight data associated with an aircraft is provided to transmit collected flight data to a remote system for storage and processing. In accordance with another aspect, a remote system utilizes received aircraft location data to determine whether an aircraft flight incident has occurred, and to alert appropriate emergency services. In accordance with another aspect, a remote system analyzes received aircraft flight data and quantitatively evaluates performance of a pilot. In yet another aspect, a system is provided for graphical and textual display of collected aircraft flight data and pilot performance evaluation data.10-06-2011
20110246000SYSTEMS AND METHODS FOR AIRCRAFT FLIGHT TRACKING AND DATA COLLECTION - Systems and methods are provided for automated collection and analysis of aircraft flight data. In accordance with one aspect, a system for collecting flight data associated with an aircraft is provided to transmit collected flight data to a remote system for storage and processing. In accordance with another aspect, a remote system utilizes received aircraft location data to determine whether an aircraft flight incident has occurred, and to alert appropriate emergency services. In accordance with another aspect, a remote system analyzes received aircraft flight data and quantitatively evaluates performance of a pilot. In yet another aspect, a system is provided for graphical and textual display of collected aircraft flight data and pilot performance evaluation data.10-06-2011
20090055037METHOD AND DEVICE FOR AIDING THE PILOTING OF AN AIRCRAFT - Method and device for assisting the piloting of an aircraft.02-26-2009
20090312893PERSPECTIVE VERTICAL SITUATION DISPLAY SYSTEM AND METHOD - A display system and method for an aircraft simultaneously displays the terrain under the flight plan, or under the current track of the aircraft, as both a two-dimensional lateral situation view image and as a perspective vertical situation view image. This provides improved tactical flight planning, and that does not erroneously show the flight plan passing through the displayed terrain.12-17-2009
20100131126SYSTEM AND DISPLAY ELEMENT FOR DISPLAYING WAYPOINT MARKERS WITH INTEGRATED ALTITUDE CONSTRAINT INFORMATION - A flight deck display system for an aircraft includes a processor architecture configured to receive aircraft instrument data, waypoint restriction information, and position data for the aircraft and, based upon the received data, generate image rendering display commands. The system also includes a display element configured to receive the image rendering display commands and, in response thereto, to render a display that includes a perspective view of terrain and at least one waypoint marker corresponding to an approaching waypoint. The waypoint marker includes visually distinguishable characteristics that convey waypoint restriction information (e.g., altitude or airspeed constraint information that governs the waypoint).05-27-2010
20090216393DATA-DRIVEN ANOMALY DETECTION TO ANTICIPATE FLIGHT DECK EFFECTS - A method for data-driven anomaly detection may include monitoring a plurality of parameters associated with a plurality of subsystems of a system. The method may also include collecting data corresponding to each of the plurality of parameters from the plurality of subsystems and generating monitoring quantities based on the data. The method may also include determining if any quantities in the monitoring quantities exceed a predetermined limit. A contribution plot may be generated corresponding to each of the parameters in response to any of the quantities exceeding the predetermined limit. The method may further include determining which parameter is likely to cause an effect based on the contribution plot.08-27-2009
20100057275PRESENTING WEATHER INFORMATION ON A DISPLAY - A method is present for presenting weather information. A number of weather conditions for a geographic region is identified from weather data for the geographic region. A geometry is selected for a weather condition based on a type of the weather condition to form a number of geometries. Each geometry within the number of geometries has a level of transparency within a corresponding border allowing another geometry to be identified when displayed in an overlapping manner. A spatial extension is selected for the each geometry within the number of geometries based on an extent of an associated weather condition to form the number of geometries. The number of geometries is displayed on a map of the geographic region in which the number of geometries is displayed in locations on the map corresponding to locations of the number of weather conditions in the geographic region.03-04-2010
20100057276Method of Monitoring Atmospheric Areas for an Aircraft - The invention relates to a method and a device for monitoring risky atmospheric areas.03-04-2010
20110098871METHOD AND APPARATUS FOR UPDATING WINDS ALOFT DISPLAY AS AIRCRAFT ALTITUDE CHANGES - A method and apparatus are provided for displaying wind magnitudes and directions aloft as the aircraft (04-28-2011
20110071710METHOD AND DEVICE FOR DETECTING AN ERRONEOUS SPEED GENERATED BY AN AIR DATA INERTIAL REFERENCE SYSTEM - Method and device for detecting an erroneous speed generated by an air data inertial reference system. The device (03-24-2011
20110077804AIRSPACE AWARENESS ENHANCEMENT SYSTEM AND METHOD - A display system and method for an aircraft renders various airspaces and associated airspace types on an aircraft display device. An image is selectively rendering on the aircraft display device that includes at least an airspace boundary graphic representative of at least a portion of the boundary for the airspace, and a textual airspace type designation label representative of the airspace type of the airspace.03-31-2011
20110060484SYSTEMS AND METHODS FOR HANDLING THE DISPLAY AND RECEIPT OF AIRCRAFT CONTROL INFORMATION - 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.03-10-2011
20100004803Smart recovery system - This invention relates to an intelligence system on board an aircraft that detects an emergency, assesses the situation, and then acts on the situation in a pre-determined manner.01-07-2010
20080243319METHOD FOR UPDATING METEOROLOGICAL INFORMATION FOR AN AIRCRAFT - The present invention relates to a method for updating meteorological information for an aircraft. The FMS computer automatically makes the request for the meteorological data so as to anticipate the updating of the latter as soon as an update is available. This automation allows the crew to have the data ready for display and use without waiting, to reduce and smooth the workload of the crew by anticipating the request and the processing of these data, and to limit the potential confusion associated with the receipt, hitherto verbal, of the ATIS information.10-02-2008
20080319591System For Piloting an Aircraft, at Least For Piloting the Aircraft During an Autonomous Approach For the Purpose of Landing - System for piloting an aircraft, at least for piloting the aircraft during an autonomous approach for the purpose of landing. The piloting system (12-25-2008
20110257818Dynamically Monitoring Airborne Turbulence - A method for monitoring for turbulence. Data is received from a motion sensor system in a portable data processing system in an aircraft while the aircraft is in operation. The portable data processing system is configured to be moved by a single person. A number of pieces of data is identified in the data received from the motion sensor system in which the number of pieces of data indicates a presence of turbulence encountered. Turbulence information is generated using the number of pieces of data. The turbulence information identified is sent to a remote data processing system outside of the aircraft.10-20-2011
20110054721VEHICLE MONITORING SYSTEM - A system to monitor aircraft equipment, having a chassis, defining an interior compartment, an arrangement configured to accept input data of at least one aircraft parameter, the arrangement configured to be placed within an aircraft, crash survivable cockpit voice and flight data recorder, and a power supply arrangement connected to arrangement configured to accept input data and the recorder.03-03-2011
20110264310Method Of Determining A Maneuver Performed By An Aircraft - 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.10-27-2011
20110125348Automatic Emergency Reporting - Technologies are described herein for providing automatic emergency reporting. The technologies are adapted to receive values of aircraft state parameters collected from one or more sensors arranged within an aircraft. The technologies then determine whether the collected values of the aircraft state parameters indicate normal or anomalous operation of the aircraft. Responsive to the determination of whether the aircraft state parameters indicate normal or anomalous operation of the aircraft, the technologies initiate an emergency reporting function. The emergency reporting function may transmit a report containing the collected values of the aircraft state parameters to a ground system via a data-link.05-26-2011
20100030406DEVICE FOR REST MANAGMENT FOR AIRCRAFT PILOT - A device for managing a rest period, in flight, of a pilot in a cockpit of an airplane including parameter acquisition means, for acquiring one input parameter characteristic of a desired rest period by the pilot who wishes to have a rest, calculations means intended for calculating, from the current position of the airplane given by the airplane parameters, a future position of the airplane at the end of the desired rest period along a trajectory programmed from the input parameters and airplane parameters, means for displaying information on the rest period and or on the position of the airplane.02-04-2010
20100030405AIRCRAFT DISPLAY SYSTEMS AND METHODS FOR ENHANCED DISPLAY OF FLIGHT PATH INFORMATION - A display system for a vehicle includes a processing unit configured to receive data representative of flight path information and terrain and to supply display commands associated with the flight path information and the terrain; and a display device coupled the processing unit and configured to receive the display commands and operable to render a three-dimensional view, including symbology representing the flight path information on the terrain.02-04-2010
20100030404METHOD AND DEVICE FOR AIDING THE MANAGEMENT OF SUCCESSIVE FLIGHTS OF AN AIRCRAFT - Method and device for aiding the management of successive flights of an aircraft.02-04-2010
20110118908METHODS AND SYSTEMS FOR MANAGEMENT OF AIRPLANE SPEED PROFILE - Methods and systems for airplane speed profile management are disclosed. A method and system in accordance to one embodiment of the disclosure includes a graphical display of speed segments and constraints as well as controls for managing the speeds and associated constraints. Speed Profile Management System (SPMS) provides an integrated and interactive speed profile management tool where pilots can view, update, or change the speed profile of their airplane's current or subsequent phases of flight.05-19-2011
20090326745AIRCRAFT CRUISE SPEED CONTROL - The present invention provides an alternative to the auto-throttle integrated in an aircraft autopilot by restricting the conditions in which the system operates. The proposed system removes the auto-throttle function from the autopilot system and gives it directly to the Full Authority Digital Engine Control (FADEC). A cruise control mode is available to the pilot only under stable flight conditions.12-31-2009
20090177343SYSTEM AND METHOD FOR SELECTABLE WEATHER OBJECT DISPLAY - Systems and methods for presenting information pertaining to a weather object on a display. A process includes displaying on the aircraft display terrain information, weather reflectivity information, and at least one hazardous weather icon corresponding to the weather, wherein the hazardous weather icon indicates a determined hazard level associated with the weather; receiving a selection to display only the hazardous weather icon; and in response to receiving the selection, continuing display of the hazardous weather icon and suppressing display of the terrain information and the weather reflectivity information.07-09-2009
20120004794Device and Method for Task Management for Piloting an Aircraft - 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.01-05-2012
20090112380STANDBY INSTRUMENT SYSTEM - An augmented air data and inertial reference system (AADIRS) serving as a standby instrument on an aircraft is provided. A secondary air data and inertial reference system (ADIRS) includes a secondary air data module coupled to a secondary inertial reference module. The secondary air data and inertial reference system is configured to derive secondary air data and inertial reference data using the secondary air data module and the secondary inertial reference module. The secondary inertial reference system is further configured to provide the second air data and inertial reference data to a flight control system for use as a backup source of data for control of the aircraft. A graphics module is coupled to the secondary air data and inertial reference system and a display. The graphics module is configured to receive the secondary air data and inertial reference data and process the secondary air and inertial reference data.04-30-2009
20120209458SYSTEMS AND METHODS FOR VERIFYING AN AVAILABLE RUNWAY LENGTH - A system and method for verifying an available runway length is provided. The method may include receiving, by a processor, a digital notice to airmen including an available runway length, receiving, by the processor, takeoff data or landing data including a length of runway needed by an aircraft in any configuration, and verifying, by the processor, and alerting the pilot if that the available runway length is greater than or equal to the length of runway needed by the aircraft in the configuration.08-16-2012
20120109425SYSTEMS, METHODS, AND APPARATUS FOR SENSING FLIGHT DIRECTION OF A SPACECRAFT - Certain embodiments of the invention may include systems, methods, and apparatus for sensing flight direction of a spacecraft. According to an example embodiment of the invention, a method is provided for determining flight direction of a spacecraft. The method includes providing at least one imaging detector associated with a spacecraft; imaging at least a portion of a celestial body onto the at least one imaging detector; acquiring, by the at least one imaging detector, sequential images of at least a portion of the celestial body; and determining the spacecraft flight direction relative to the celestial body based at least in part on processing the sequential images, wherein the processing is performed by one or more computer processors.05-03-2012
20120316705OPTIMIZED TASK PROCESSING METHOD AND DEVICE FOR AN FWS - The subject of the present invention is a method for processing alerts by an avionic system FWS that makes it possible to optimize the processing of these alerts without unnecessarily consuming “processor time”. The method according to the invention is characterized in that it consists in having processed, on each processing cycle of the processor of the FWS, only the operations relating to alerts for which the result has been modified since the preceding processing cycle.12-13-2012
20100250034METHOD OF MANAGING AIRCRAFT WARNINGS, AND A DEVICE FOR IMPLEMENTING SAID METHOD - A method of managing warnings in an aircraft, includes: 09-30-2010
20100204855METHOD AND DEVICE FOR ASSISTING IN THE CONTROL OF THE ON-BOARD SYSTEMS IN A AIRCRAFT - The object of the invention is in particular a method and a device for aiding in the control of systems installed on board an aircraft comprising at least one display device capable of displaying configuration parameters of the said aircraft and at least one associated acquisition device. After the state of the said aircraft has been determined (08-12-2010
20100204854ARCHITECURE WITH OPTIMIZED INTERFACING FOR AN AIRCRAFT HYBRID COCKPIT CONTROL PANEL SYSTEM - A hybrid electronics cockpit control panel system architecture is provided that includes optimized interfacing and partitioning. The architecture includes a digital function block with a digital signal processor and digital communication capabilities. The architecture also includes integrated cockpit control panels that employ a printed circuit board to avoid wire/cable connections for cockpit control panel components beyond the face panel. The architecture provides digital control and communication along a central communication bus that can eliminate the need for dedicated wire connections between the control panel and the electrical components throughout the aircraft, reducing weight and volume. One example aircraft cockpit control panel system includes a control signal processor that receives electrical control signals from pilot operating devices on the control panel and transforms them into digital status signals for communication on a communication bus. In another example aircraft cockpit control panel system, the control signal processor transforms the electrical control signals into digital control signals that are communicated to aircraft components. In another example aircraft cockpit control panel system, signals from a first control signal processor are passed through at least a second control signal processor to provide a redundant circuit path.08-12-2010
20110184594SYSTEMS AND METHODS FOR PROVIDING AIRCRAFT HEADING INFORMATION - Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.07-28-2011
20120215388AIRCRAFT SYSTEMS AND METHODS FOR DISPLAYING VISUAL SEGMENT INFORMATION - A display system and method are provided for an aircraft. The system includes a processing unit configured to determine a visual segment for the aircraft and to generate display commands based on the visual segment; and a display device coupled the processing unit and configured to receive the display commands and to display symbology representing the visual segment as a visual segment marker.08-23-2012
20100049382FLIGHT CONTROL METHOD - The invention involves a method comprising the steps of 02-25-2010
20100010696ENHANCING MOBILE MULTIPLE-ACCESS COMMUNICATION NETWORKS - 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.01-14-2010
20100010695HEADING REFERENCE SYSTEM WITH REMOTE-MOUNTED SENSOR - A navigation system for an aircraft includes one or more wing-mounted sensors whose outputs are effected by the flexing of the wing during flight. The navigation system corrects for these errors using measurements of actual wing flex taken during an initial flight and thereafter assumed to be valid for all subsequent flights and for all aircraft using the same type of airframe. The actual measurements of wing flex define a wing flex correction factor that the navigation system may adjust during flight to reduce or remove residual errors. The wing flex correction factor accounts for all three types of possible wing flex: pitch, roll, and yaw flexing.01-14-2010
20120253564INTEGRATED FLIGHT CONTROL AND COCKPIT DISPLAY SYSTEM - A Human Machine Interface includes a flight control system operable to communicate display data directly to a cockpit display system.10-04-2012
20100235019METHOD OF DETERMINING AND DISPLAYING FLYING INDICATIONS AND A FLIGHT INDICATOR FOR IMPLEMENTING SAID METHOD - The present invention relates to a pilot assistance method for giving assistance in piloting a rotary wing aircraft, the method consisting in using a scale with collective pitch graduations that is movable on a display screen to indicate the position of the collective pitch, in determining the desynchronization pitch, in using a maximum limit value and a minimum limit value for the speed of rotation of the rotor, in transforming the maximum limit value and the minimum limit value in real time and as a function of physical flight parameters respectively into a bottom limit position and a top limit position for the collective pitch, and when a determined difference appears between the real value and the reference value Nr0 for the speed of rotation of the rotor, in displaying at least one item of corrective information about the adjustment of the collective pitch.09-16-2010
20100198433Flight Management System with Optimization of the Lateral Flight Plan - Flight management system for aircraft comprising computation means capable of determining a gain or a loss in terms of flight time remaining to a point of arrival, and in terms of fuel consumption, following the input by an operator of a modification of an initial flight plan using the Direct To function. The computation means are capable of suggesting to the operator a modification of the lateral flight plan that procures an optimum gain. The flight management system also comprises a display interface capable of presenting to the operator the information concerning the gain or the loss in time and/or consumption, and of prompting the operator to accept or refuse the modification.08-05-2010
20130013134HEURISTIC METHOD FOR COMPUTING PERFORMANCE OF AN AIRCRAFT - A method estimates the vertical airspeed and fuel flow of an aircraft at a point along a flight plan using other aircraft parameters for that point. The process uses a database having entries containing sets of actual values of operating parameters obtained during prior aircraft flights. The database is sorted by data set aggregate values that are is calculated from each set of actual values. When the vertical airspeed and fuel flow estimates are needed, a section thereof is identified based on the aggregate values. That section of the database is analyzed to identify the set of actual operating parameters values that best matches the other aircraft parameters for the flight plan point. The vertical airspeed and fuel flow values from that identified set are used as the estimates. This process reduces the amount of the database that has to be analyzed to locate the data to use.01-10-2013
20120150368Method And Device For Automatically Monitoring Lateral Guidance Orders Of An Aircraft - Method and device for automatically monitoring lateral guidance orders of an aircraft.06-14-2012
20130018533Method For Determining The Speed Air Aircraft And Aircraft Equipped With Means For ImplementationAANM Feau; JulienAACI ToulouseAACO FRAAGP Feau; Julien Toulouse FRAANM Francois; HugoAACI Saint-JeanAACO FRAAGP Francois; Hugo Saint-Jean FR - An aircraft is equipped with engines, each engine having at least one pod and one compressor/turbine hitch. The aircraft has at least one data processing unit and at least one system at the engine level. At least one engine is equipped with at least one static pressure probe for measuring the ambient air under the pod. Also, air static pressure probes are arranged at the engine levels, with one pressure probe at the output of the compressor, at least one rotation speed sensor, for example of a blower, and ambient air temperature probes at the air input or in any compression point. The processing unit is able, from measurements performed by such probes at the engine level, to supply to at least one of the systems at the engine level, determination data for the air speed of the aircraft.01-17-2013
20110160940Text Flight Service Station - A method and system (i.e. Text Flight Service Station) to provide up to date weather information, pilot information and flight plan information for small aircraft pilots, particularly, those flying at lower altitudes where radio information is limited or unavailable.06-30-2011
20130024053RECONFIGURATION PROCESS OF AN AIRCRAFT ENVIRONMENT SURVEILLANCE DEVICE - The invention relates to a reconfiguration process for an aircraft environment surveillance device including at least two redundant electronic systems (01-24-2013
20080255714METHODS AND APPARATUS FOR AIRCRAFT TURBULENCE DETECTION - Methods and apparatus for an in-flight air turbulence detection system. In one embodiment, a system includes an air turbulence detector and a transmitter to transmit turbulence information. In another embodiment, a system includes a receiver, a detection processing module, an aircraft ID module, and a route modification module.10-16-2008
20080228333METHOD AND DEVICE TO ASSIST IN THE GUIDANCE OF AN AIRPLANE - The device (09-18-2008
20100076630SYSTEM, METHOD AND COMPUTER PROGRAM PRODUCT FOR REAL-TIME EVENT IDENTIFICATION AND COURSE OF ACTION INTERPRETATION - A system for identifying events includes a memory capable of storing a compressed event table including a number of events, the event table having been compressed by reducing the number of events in the event table without reducing the number of events represented by the event table. Each event of the event table includes a set of state parameters, and may also be associated with an output. The system also includes a processor capable of operating a fast state recognition (FSR) application. The FSR application, in turn, can receive a plurality of inputs, and identify an event of the compressed event table based upon the plurality of inputs and the state parameters of the compressed event table, event being identified in accordance with a state recognition technique.03-25-2010
20130096738DISPLAY APPARATUS, CONTROL SUPPORT SYSTEM, AND DISPLAY METHOD - An FPM and a target attitude relative to air display are displayed on a PFD, which is an integrated indicator. The target attitude relative to air display is a mark indicating a target attitude relative to air representing a target angle-of-attack and a target sideslip angle of the aircraft to achieve a target flight path. The PFD displays the relative difference between the FPM and the target attitude relative to air display and shows that the aircraft is flying in the target traveling direction when the FPM matches (is superposed on) the target attitude relative to air display. Thus, controlling with higher trackability than controlling performed based on a target attitude relative to ground is enabled.04-18-2013
20110246002SYSTEMS AND METHODS FOR AIRCRAFT FLIGHT TRACKING AND ANALYSIS - Systems and methods are provided for automated collection and analysis of aircraft flight data. In accordance with one aspect, a system for collecting flight data associated with an aircraft is provided to transmit collected flight data to a remote system for storage and processing. In accordance with another aspect, a remote system utilizes received aircraft location data to determine whether an aircraft flight incident has occurred, and to alert appropriate emergency services. In accordance with another aspect, a remote system analyzes received aircraft flight data and quantitatively evaluates performance of a pilot. In yet another aspect, a system is provided for graphical and textual display of collected aircraft flight data and pilot performance evaluation data.10-06-2011
20130184902PILOTING ASSISTANCE METHOD, A PILOTING ASSISTANCE DEVICE, AND AN AIRCRAFT - A piloting assistance device (07-18-2013
20110238240DEVICE FOR DISPLAYING THE ENERGY VARIATION OF AN AIRCRAFT, CORRESPONDING METHOD AND SYSTEM FOR DISPLAYING THE ENERGY VARIATION - This device for displaying information relative to a flight configuration of the aircraft provided with at least one propulsion system, able to generate a thrust force on said aircraft comprised in a thrust range, said information comprising information relative to an energy variation of the aircraft, is characterized in that the energy variation of the aircraft is expressed by a size representative of this energy variation and homogenous at a gradient of the aircraft, and in that said device is capable of representing a range of energy variations that can be achieved by said aircraft and a current energy variation of said aircraft. Corresponding method and system for displaying an energy variation.09-29-2011
20130158751Stand Alone Aircraft Flight Data Transmitter - A method and apparatus for transmitting data. An aircraft data transmission system comprises an aircraft flight data transmitter. The aircraft flight data transmitter is configured to be connected to a connector for an on-board flight data recorder system for an aircraft. The aircraft flight data transmitter is further configured to receive data generated by sensors in the aircraft from the on-board flight data recorder system. The aircraft flight data transmitter is further configured to determine whether an undesired condition is present in the aircraft using the data. The aircraft flight data transmitter is further configured to initiate sending of at least a portion of the data received from the on-board flight data recorder system over a wireless communications link in response to a determination that the undesired condition is present in the aircraft.06-20-2013
20120029739SYSTEMS AND METHODS FOR HANDLING THE DISPLAY AND RECEIPT OF AIRCRAFT CONTROL INFORMATION - 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.02-02-2012
20130197725METHODS AND SYSTEMS FOR REQUESTING AND RETRIEVING AIRCRAFT DATA DURING FLIGHT OF AN AIRCRAFT - The disclosed embodiments relate to methods and systems for requesting and retrieving aircraft data during flight of an aircraft. This aircraft data can be used to perform additional monitoring of aircraft sub-systems to detect an abnormal condition, and/or to identify one or more sources that are causing the abnormal condition. In one embodiment, aircraft data for one or more relevant parameters can be requested from the ground, measured on-board the aircraft, and stored in a data file that is then communicated back to personnel on the ground. The real-time aircraft data for one or more relevant parameters can then be analyzed to identify the one or more sources that are causing the abnormal condition.08-01-2013
20120095624Transportable Device for Recording Flight Data - A transportable device for recording flight data obtained from an avionics system in an aircraft is provided. The device includes a case containing a laptop computer. The case limits the electromagnetic disturbances between the laptop and the avionics system. The laptop is connected to the avionics system, so as to receive the flight data to be recorded. The device can be applied to monitoring of flight data.04-19-2012
20130211635INTERACTIVE DIALOG DEVICES AND METHODS FOR AN OPERATOR OF AN AIRCRAFT AND A GUIDANCE SYSTEM OF THE AIRCRAFT - Interactive dialog devices and methods are provided for use by an operator of an aircraft with a guidance system of the aircraft. The dialog devices and methods can include an interaction on a screen that can represent, on the one hand, a playback element indicating the value of a guidance target of the guidance system of the aircraft, and on the other hand, a control element that can be grasped or selected and moved on a display along a path, such as for example a curve, by an operator to modify the value of the guidance target.08-15-2013

Patent applications in class Flight condition indicating system