Entries |
Document | Title | Date |
20080228333 | METHOD AND DEVICE TO ASSIST IN THE GUIDANCE OF AN AIRPLANE - The device ( | 09-18-2008 |
20080234884 | SYSTEM 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 |
20080243319 | METHOD 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 |
20080249674 | Method 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 h | 10-09-2008 |
20080255714 | METHODS 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 |
20080312781 | Quiet 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 |
20080319591 | System 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 |
20090005920 | METHOD 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 |
20090012663 | DETERMINING 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 |
20090024260 | METHOD 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 |
20090037037 | AUTOMATIC 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 |
20090043432 | Method and device for determining the dynamic stability margin of an aircraft - A method of determining a dynamic stability margin M | 02-12-2009 |
20090055036 | System 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 |
20090055037 | METHOD AND DEVICE FOR AIDING THE PILOTING OF AN AIRCRAFT - Method and device for assisting the piloting of an aircraft. | 02-26-2009 |
20090099713 | Device 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 |
20090112380 | STANDBY 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 |
20090112381 | Method 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 |
20090118876 | DECOMPRESSION 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 |
20090125167 | METHOD 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 |
20090138147 | LOW-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 |
20090177343 | SYSTEM 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 |
20090216393 | DATA-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 |
20090299554 | METHOD 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 |
20090306839 | Aircraft 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 |
20090312893 | PERSPECTIVE 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 |
20090319102 | Flight 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 |
20090319103 | PERSPECTIVE 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 |
20090326745 | AIRCRAFT 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 |
20100004803 | Smart 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 |
20100010695 | HEADING 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 |
20100010696 | ENHANCING 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 |
20100030404 | METHOD 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 |
20100030405 | AIRCRAFT 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 |
20100030406 | DEVICE 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 |
20100042275 | SYSTEMS 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 |
20100049382 | FLIGHT CONTROL METHOD - The invention involves a method comprising the steps of
| 02-25-2010 |
20100057275 | PRESENTING 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 |
20100057276 | Method of Monitoring Atmospheric Areas for an Aircraft - The invention relates to a method and a device for monitoring risky atmospheric areas. | 03-04-2010 |
20100057277 | METHODS 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 |
20100063654 | Locator 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 |
20100076629 | System 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 |
20100076630 | SYSTEM, 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 |
20100094487 | AVIONICS 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 |
20100100262 | Method 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 |
20100131126 | SYSTEM 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 |
20100152932 | SYSTEM 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 |
20100179712 | TRANSPARENT 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 |
20100198433 | Flight 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 |
20100204854 | ARCHITECURE 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 |
20100204855 | METHOD 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 |
20100211237 | SYSTEM 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 |
20100222945 | METHOD 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 |
20100235019 | METHOD 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 |
20100241294 | METHOD 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 |
20100250034 | METHOD OF MANAGING AIRCRAFT WARNINGS, AND A DEVICE FOR IMPLEMENTING SAID METHOD - A method of managing warnings in an aircraft, includes:
| 09-30-2010 |
20100262320 | ACTUATOR MONITORING CIRCUIT, CONTROLLER, AND ACTUATOR UNIT - An actuator monitoring circuit | 10-14-2010 |
20100332056 | SYSTEMS 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 |
20100332057 | FLIGHT 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 |
20110029163 | METHOD 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 |
20110029164 | AVIATION 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 |
20110035081 | METHOD 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 |
20110054721 | VEHICLE 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 |
20110060484 | SYSTEMS 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 |
20110071710 | METHOD 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 |
20110077804 | AIRSPACE 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 |
20110082605 | AIRCRAFT 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 |
20110098871 | METHOD 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 |
20110118908 | METHODS 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 |
20110125348 | Automatic 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 |
20110125349 | Integrated 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 |
20110160940 | Text 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 |
20110184594 | SYSTEMS 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 |
20110196551 | SYSTEM 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 |
20110208375 | DEVICE, 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 |
20110208376 | ON-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 |
20110213514 | AVIATION 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 |
20110238240 | DEVICE 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 |
20110246000 | SYSTEMS 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 |
20110246001 | SYSTEMS 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 |
20110246002 | SYSTEMS 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 |
20110257818 | Dynamically 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 |
20110264310 | Method 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 |
20110282524 | SYSTEM 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 |
20120004794 | Device 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 |
20120029739 | SYSTEMS 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 |
20120095624 | Transportable 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 |
20120109425 | SYSTEMS, 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 |
20120150368 | Method 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 |
20120209458 | SYSTEMS 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 |
20120215388 | AIRCRAFT 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 |
20120253564 | INTEGRATED 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 |
20120296500 | AERODYNAMIC 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 |
20120316705 | OPTIMIZED 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 |
20130006450 | METEOROLOGICAL DATA SELECTION ALONG AN AIRCRAFT TRAJECTORY - A method of selecting weather data for use in at least one of a flight management system (FMS) of an aircraft and a ground station includes selecting a reduced set of weather data points to send to the FMS and taking into account a trajectory of the aircraft when determining what data points to include in the reduced set. | 01-03-2013 |
20130013134 | HEURISTIC 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 |
20130018533 | Method 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 |
20130024053 | RECONFIGURATION 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 |
20130030612 | METHOD 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 |
20130046423 | SYSTEM 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 |
20130054056 | METHOD OF MANAGING OPERATIONAL HEALTH OF ASSETS - An asset operational health monitoring system, in which a plurality of sensors are arranged to determine values of asset operation parameters pertaining to an instance of asset operation. One or more processing unit receives data corresponding to said asset operation values and determine a plurality of asset locations at a corresponding plurality of points in time. The one or more processing unit is arranged to receive data indicative of the location of a region of adverse environmental conditions which may impact on the operation of the asset and to compare the determined locations of the asset with the location of said region so as to determine whether one or more of said asset locations fall within said region. An indicator of operational risk associated with the presence of said asset in said region is output which can drive asset operation or maintenance decision making. The system may be used for ash cloud impact monitoring for aircraft, a fleet of aircraft or aircraft engines. | 02-28-2013 |
20130066487 | FLIGHT 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 |
20130066488 | METHOD AND DEVICE FOR AUTOMATICALLY ESTIMATING AN AIRSPEED OF AN AIRCRAFT - Method and device for automatically estimating an airspeed of an aircraft | 03-14-2013 |
20130073124 | Method 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 |
20130079957 | Aerological 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 |
20130096738 | DISPLAY 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 |
20130116863 | METHOD AND DEVICE FOR DETECTING THE JAMMING OF AN AIRCRAFT CONTROL SURFACE - The detection device includes, but is not limited to a device that is configured to determine a control error corresponding to the difference between a first control instruction and a control surface position, a second device that is configured to calculate the difference between this control error and a second control instruction in such a way as to form a comparison signal, and a third device that is configured to detect a jamming of the control surface if this comparison signal is greater than a threshold value. | 05-09-2013 |
20130131897 | THREE 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 |
20130138272 | INTERACTIVE 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 |
20130158751 | Stand 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 |
20130184902 | PILOTING ASSISTANCE METHOD, A PILOTING ASSISTANCE DEVICE, AND AN AIRCRAFT - A piloting assistance device ( | 07-18-2013 |
20130197725 | METHODS 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 |
20130211635 | INTERACTIVE 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 |
20130218373 | Method 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 |
20130226376 | SYSTEM AND METHOD FOR RENDERING AN AIRCRAFT COCKPIT DISPLAY FOR USE WITH AN IN-TRAIL PROCEDURE (ITP) - A method for rendering symbology on a cockpit display of a host aircraft, relating to a proposed ITP transition, is provided. The method comprises analyzing data to predict an ITP transition that is possible and economical, rendering on the display symbology textually representative of the possible ITP transition, and rendering on the display symbology textually representative of the time before which the ITP transition is possible. | 08-29-2013 |
20130231804 | DEVICE FOR DISPLAY AND CONTROL OF SETPOINTS FOR AUTOMATIC PILOTING FOR AIRCRAFT - The general field of the invention is that of devices for display and control of setpoints for automatic piloting for aircraft, configured to display the setpoints of speed, heading, climb slope and altitude. The various setpoints are displayed in the form of a graphical representation comprising: wheels graduated in speed and in altitude indicating the aircraft setpoint values; a circular heading rose, graduated and centred on a first symbol representing the aircraft, the heading setpoint being indicated by a second symbol representing the heading to be followed by the aircraft and disposed around the perimeter of the heading rose; and a vertical sectional view comprising a graduated semicircle centred on a third symbol representing the aircraft, the slope setpoint being indicated by a fourth symbol representing the slope to be followed by the aircraft and disposed around the perimeter of the semicircle. | 09-05-2013 |
20130238172 | SYSTEMS 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. | 09-12-2013 |
20130245860 | SITUATIONAL AWARENESS PILOT BRIEFING TOOL - Embodiments of the present invention relate to a system and method for better conveying information to a pilot and/or other members of a flight crew present on the flight deck of an aircraft. Embodiments of the invention are of particular use in the briefings that precede various phases of the flight operations of an aircraft (such as start-up of the engines, take-off, ascent to cruise altitude, descent from cruise altitude and landing). The system and method provide a briefing output relevant to the particular phases of a flight in both of a visual form and an audio form, with the briefing output including data of most relevance to the particular flight phase. | 09-19-2013 |
20130253738 | AIRCRAFT SPEED GUIDANCE DISPLAY - The invention relates to systems and methods for displaying flight information representative of a deviation from a specified four-dimensional flight path. Particularly, but not exclusively, the invention relates to a cockpit display for enabling pilots to arrive at a particular location at a particular time and to achieve the necessary changes to aircraft speed to achieve a preferred ground speed. | 09-26-2013 |
20130274964 | FLIGHT DATA MONITORING AND VALIDATION - A computer-implemented flight data monitoring method is provided for monitoring flight data, for example flight data obtained by a flight data recorder or quick access recorder on an aircraft. The method comprises receiving input flight data, performing flight data validation on the input flight data to generate validated flight data, and performing flight data analysis on the validated flight data to detect at least one predetermined type of flight event. The events may be useful for generating an aircraft safety report, for example. By validating the data before performing the analysis, the number of events which are falsely detected based on invalid or unreliable data can be reduced. | 10-17-2013 |
20130282207 | Fully Parametrizable Electronic Alerts and Procedures Management System, Intended for an Aircraft - An alerts and procedures management system for an aircraft comprises a software kernel aboard the aircraft and a parameterization tool for the software kernel, which comprises a conversion module for converting a configuration file describing an operational need of the system into a database of binary parameters which is able to parameterize the software kernel. The software kernel comprises at least four elementary cells: a first cell for acquiring aircraft signals, a second cell for characterizing state variables of the aircraft, a third cell for computing at least one separate event, a fourth cell for scheduling the separate events for communication with the crew; each of the cells comprising a software engine parameterizable by the database. | 10-24-2013 |
20130289804 | SYSTEM AND METHOD FOR ECONOMIC USAGE OF AN AIRCRAFT - The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations. | 10-31-2013 |
20130297103 | SYSTEM AND METHOD FOR COLLECTING REMOTELY LOCATED POSITIONAL DATA - A computer-implemented system and method for the collection, filtering, and transmission of aviation information is disclosed. A plurality of flight information is received over a digital network at various remote locations, and the data is filtered prior to transmission to a central database for presentation and use. The database includes aviation information. The method of filtration is dynamically updated as to information concerning a specific flight based on one characteristic of the flight. As to aircraft being tracked, a determination is made as to which receiver should relay collected data, and that determination is periodically revised, such as to minimize transmission costs and maximize signal quality as aircraft positions change. Once the information is located in the central database, it is suitable for use in responding to user requests for flight tracking information is association with at least one identified flight. | 11-07-2013 |
20130304283 | Method for controlling the piloting of an aircraft - A method for controlling the piloting of an aircraft comprising the steps of receiving at least one first instruction for modification of a current velocity vector of the aircraft, determining a target velocity vector of the aircraft, on the basis of said at least one first instruction received, and determining, on the basis at least of said target velocity vector, at least one actuation command intended for at least one actuator of the aircraft in order to modify the movement of the aircraft according to said at least one first instruction received. | 11-14-2013 |
20130311013 | Measurement Assisted Aerodynamic State Estimator - An aerodynamic state estimation system includes a real-time actual measurement device, an air data computer, and a plurality of sensors. The measurement device receives laser scatter energy indicative of one or more atmospheric data parameters and outputs one or more truth measurements. The air data computer module receives the one or more truth measurements, calculates one or more state parameter estimations based on a plurality of functional parameters, and outputs at least one of the one or more truth measurements and the one or more state parameter estimations as one or more high accuracy state parameters, The plurality of sensors, located at the air data computer module, measure the plurality of functional parameters. | 11-21-2013 |
20130317673 | METHOD AND SYSTEM OF TRANSMITTING AND RECEIVING DATA ORIGINATING FROM AN AIRCRAFT BLACK BOX - The invention relates to a method for transmitting data, characterized in that it includes a step of transmitting in-flight data between a first aircraft and at least a second aircraft, the data transmitted being data stored in at least one black box on board the first aircraft. | 11-28-2013 |
20130325218 | SYNTHETIC ESTIMATION OF ROTORCRAFT AIRSPEED - A method for estimating airspeed of an aircraft includes receiving values indicative of operating conditions of the aircraft along an axis; estimating a tip path plane (TPP) angle along the axis from at least one of the operating conditions to create an estimated TPP angle; and determining an estimated airspeed as a function of the estimated TPP angle, the determining including referencing a look-up table that indexes the estimated TPP angle with the airspeed. | 12-05-2013 |
20130325219 | METHOD AND DEVICE FOR AUTOMATICALLY ESTIMATING A DEGRADATION IN FUEL CONSUMPTION AND IN DRAG OF AN AIRCRAFT - A method and device for automatically estimating a degradation in fuel consumption and in drag of an aircraft. The device comprises a device for calculating a numerical value of the effect of a degradation in performance on the fuel consumption and/or the drag of the aircraft, and an arrangement for displaying this numerical value on a screen in the cockpit of the aircraft. | 12-05-2013 |
20130325220 | PROCEDURE AND DEVICE FOR THE DETERMINATION OF AIRSPEEDS OF A ROTORCRAFT IN STATIONARY FLIGHT AND/OR AT LOW SPEEDS - A procedure and a device for the determination of current airspeeds [ | 12-05-2013 |
20130345910 | DETECTOR FUNCTION AND SYSTEM FOR PREDICTING AIRFOIL STALL FROM CONTROL SURFACE MEASUREMENTS - Methods and apparatus for predicting airfoil stall for an aircraft having a control surface. Measurements of forces or moments acting upon an integrated span of the control surface are sensed over a period of time to provided unsteady data. The unsteady data is filtered to remove structural frequencies and input to at least one stall warning detection function, and an output is received. Each of the stall warning detection functions identifies an angle-of-attack that is approximately within a predetermined number of degrees of stall when the received output reaches a threshold. The received output is compared to the threshold to determine whether an angle-of-attack exists that is near stall. | 12-26-2013 |
20140039733 | METHOD AND APPARATUS FOR PROVIDING IN-FLIGHT WEATHER DATA - A method for providing one or more aircraft with weather data during flight includes generating a weather model using a source of weather data. The weather model incorporates flight operations information and performance requirements. The method includes generating a weather message from the weather model. The weather message is generated in a format that is compatible with the aircraft. The method also includes transmitting the weather message to the aircraft during flight of the aircraft. | 02-06-2014 |
20140039734 | AIRCRAFT SYSTEMS AND METHODS FOR DISPLAYING WEATHER INFORMATION ALONG A FLIGHT PATH - A display system for an aircraft is provided. The system includes a processing unit configured to receive weather information associated with a flight path of a flight plan and to generate display commands based on the weather information. The flight plan includes a first waypoint associated with a first altitude. The system further includes a display device coupled with the processing unit and configured to receive the display commands and to display symbology representing the weather information. The weather information includes first weather information for the first altitude and second weather information at a second altitude, different from the first altitude. | 02-06-2014 |
20140046510 | ESTIMATING A WIND VECTOR - Methods and devices for calculating an estimate of a wind vector. A maneuver of a platform may be identified as a steady-straight motion maneuver, a partial turn maneuver, or a full turn maneuver. A preliminary estimate of a wind vector corresponding to a wind condition prevailing near the platform may be calculated by applying a maneuver-specific calculating method. A gain associated with the preliminary estimate of the wind vector may be calculated by applying a state-specific calculation method. A filtered estimate of the wind vector may be updated based, at least in part, on the preliminary estimate of the wind vector and the gain associated with the to preliminary estimate of the wind vector. | 02-13-2014 |
20140058594 | Aircraft Environmental Sensors and System - According to one embodiment, an aircraft part environmental stress analysis system includes a part failure repository, a part history repository, and a failure analysis engine. The part failure repository is configured to store a plurality of failure records, each failure record identifying a failed aircraft part. The part history repository is configured to store a plurality of part records, each part record storing, for a failed aircraft part, at least one measurement of an aspect of a natural environment of which the failed aircraft part was subject to. The failure analysis engine is operable to compare the plurality of failure records to the plurality of part records and identify at least one potential environmental cause of failure for a plurality of failed aircraft parts based on the comparison. | 02-27-2014 |
20140067171 | SYSTEMS AND METHODS FOR GRAPHICALLY INDICATING AIRCRAFT ASCENT AND DESCENT CAPABILITIES - Systems and methods are operable to present graphical information indicating capability of an aircraft to change altitude. An exemplary embodiment determines an altitude change capability of the aircraft; determines an altitude change capability icon based on the determined altitude change capability of the aircraft, wherein the altitude change capability icon is defined by at least a leading portion, a trailing portion, a top portion, and a bottom portion, wherein a slope of the leading portion of the altitude change capability icon corresponds to the determined altitude change capability of the aircraft, and wherein the leading portion and the trailing portion are separated by at least the top portion and the bottom portion; and communicates the altitude change capability icon to a display for presentation to the crew of the aircraft. | 03-06-2014 |
20140074325 | Flight Deck Touch-Sensitive Hardware Controls - Touch or proximity sensors are integrated into control devices such as knobs, dials or wheels incorporated in a user control panel. A control output processor detects whether any of the sensors are outputting signals indicating that a control device is being touched (or nearly touched) by a user. The control output processor causes an associated display area to be highlighted or otherwise modified on a display screen to indicate to the user which control device is being touched. This feature allows for “no-look” interaction with control panels, and keeps the user's eyes focused on the relevant displays where the control devices produce effects. This allows users to preview and verify that the correct control device is being manipulated prior to taking any (potentially erroneous) control actions. | 03-13-2014 |
20140074326 | METHOD OF DETERMINING A TURBULENT CONDITION IN AN AIRCRAFT - A method of determining a turbulent condition in an aircraft with a handheld device where the handheld device has at least one of a gyroscope, seismometer, and an accelerometer where the method includes receiving an output from the at least one of the gyroscope, seismometer, and accelerometer while the handheld device is located within the aircraft and providing an indication of a turbulent condition. | 03-13-2014 |
20140081483 | FLEET OPERATIONS QUALITY MANAGEMENT SYSTEM AND AUTOMATIC MULTI-GENERATIONAL DATA CACHING AND RECOVERY - A fleet operations quality management system for use with one or more vehicles which includes a data recording unit and separate memory subsystem mounted on each vehicle, a remotely located data collection station to collect, store and pre-process data from multiple vehicles, a centralized data storage and retrieval system designed to accept and assimilate recorded trip data, a web application designed to provide access to and analysis of the recorded trip data, and a graphical software application that can be used to view the recreated trip in a realistic simulated environment. An electronic system comprising a receiver module and a mobile device, whereby the receiver module is capable of receiving data transmissions from a network of ground stations and buffering the data for future use. | 03-20-2014 |
20140088800 | CENTRIPETAL ACCELERATION DETERMINATION, CENTRIPETAL ACCELERATION BASED VELOCITY TRACKING SYSTEM AND METHODS - The flight of an aircraft is characterized in terms of Earth-based reference system data for a first position and a second position of the aircraft that are separated by a time increment. A centripetal acceleration of the aircraft is determined based on the Earth-based reference system data for the positions in conjunction with the time increment. A rate of rotation is established corresponding to the time increment in an aircraft-based reference system. Aircraft airspeed is determined based on the centripetal acceleration and the rate of rotation. A turn can be detected as characterized by a change in track angle from a prior GPS packet compared to a new packet. Aircraft turns can be detected based on a change in track angle in GPS packets. Compensation can be applied to a gyro based on centripetal acceleration such that the gyro more accurately responds to the Earth gravity axis. | 03-27-2014 |
20140100721 | AIRCRAFT VISION SYSTEM WITH RELIEF LINES AND ASSOCIATED METHOD - The vision system for an aircraft according to the invention comprises a display management system, on a display, capable of dynamically displaying synthetic information coming from a synthetic environment generating assembly on the display. The management assembly can control the display, on a first region of the display, of relief lines representative of the terrain situated facing the aircraft, without displaying synthetic surface representations of the terrain in the intermediate areas situated between the relief lines of the first region of the display. The generating assembly includes means for determining the position of the crest lines of the terrain from topographical data present in at least one database, and means for computing the position of the relief lines from the position of the crest lines of the terrain. | 04-10-2014 |
20140100722 | Method and device for displaying flight parameters on an aircraft - The display device comprises display means which highlight on a screen, preferably of PFD type, the information useful to the pilot relating to at least one flight parameter, especially while reducing the corresponding scale on said screen. | 04-10-2014 |
20140121863 | Flight Envelope Display - A method and apparatus for displaying aircraft performance characteristics. A two-dimensional representation of a flight envelope for an aircraft is displayed. The two-dimensional representation of the flight envelope comprises a display of speed versus altitude performance capabilities of the aircraft. A current speed and a current altitude of the aircraft are identified. A performance indication of the current speed and the current altitude is displayed on the two-dimensional representation of the flight envelope. A position of the performance indication on the two-dimensional representation of the flight envelope indicates the current speed and the current altitude with respect to the flight envelope. | 05-01-2014 |
20140142790 | Display system for aircraft cockpit - A system including a switching device for switching an auxiliary display unit between a first state, corresponding to nominal operation, for which a screen of said auxiliary display unit is controlled by a control assembly of a main display unit, and a second, standby state, corresponding to a situation in which the main display unit has broken down, for which state said screen is controlled by a control assembly of said auxiliary display unit. | 05-22-2014 |
20140156116 | ASSISTANCE WITH PILOTING OF AN AIRCRAFT IN A STALL - An intuitive display including a visual representation of a maximum admissible angle of attack on a pitch scale giving the crew of an aircraft a visual recognition of an imminent stall, or of a stall, together with real assistance with piloting during the stall until the aircraft has come out of the stall completely. | 06-05-2014 |
20140172204 | METHOD AND DEVICE FOR SUPPLYING DATA RELATING TO A FLIGHT PLAN ON A HUMAN-MACHINE INTERFACE - A method and a device is provided for supplying, in summary fashion on a single page of a screen for each point, the data relating to a flight plan. The method makes it possible to establish relevant groups of information according to the situation of the flight and to summarize the display of the data in folded-up mode or in an unfolded lateral mode. The unfolded display offers, on one and the same page, a more precise detail of the situation, by ergonomically and intuitively showing in the columns the predictions in relation to a type of constraint. | 06-19-2014 |
20140180508 | Aircraft with a cockpit including a viewing surface for piloting which is at least partially virtual - The invention concerns an aircraft including a cockpit comprising a viewing surface for piloting giving at least one pilot a view of an outside scene comprising the environment of the aircraft extending forward of the aircraft. At least part of said viewing surface for piloting is free of any glazed surface and is formed by display means for a digital image representing at least part of an outside scene comprising the environment of the aircraft extending forward of the aircraft. | 06-26-2014 |
20140207314 | DISPLAY SYSTEM FOR AN AIRCRAFT AND ASSOCIATED METHOD - The system includes additional display means including at least one additional screen and additional graphic interface handling means of the additional screen (able to display on the additional screen, a summary window depending on the operational state of the aircraft. The summary window comprises at least one first pictogram able to be displayed on a first display window of main display means of the aircraft without being displayed on the second window of the main display means, and at least one second pictogram intended to be displayed on the second display window of the main display means without being displayed on the first window of the main display means. | 07-24-2014 |
20140214245 | AIRCRAFT VISION SYSTEM, AND ASSOCIATED VISION METHOD - The system according to the invention comprises a display and a synthetic image dynamic generating assembly. It includes a management assembly for the graphic interface of the display, capable of controlling the dynamic display, on a first region of the display, of a synthetic image and able to maintain, in certain movement configurations of the aircraft, a second region of the display delimited by the edge substantially with no synthetic surface representation of the terrain. The management assembly includes means for dynamically delimiting the edge of the first region. The delimiting means are configured to dynamically compute the position of the edge as a function of a determined visibility distance (D | 07-31-2014 |
20140222256 | A METHOD OF ASSISTING PILOTING AN AIRCRAFT BY ADAPTING THE DISPLAY OF SYMBOLS - The invention relates to a method of assisting piloting an aircraft. The method is performed when the real position of a symbol for display lies outside the display limit of the screen. The symbol is representative of a parameter associated with the dynamic behavior of the aircraft (FPV, . . . ) or liable to influence said behavior (FD, . . . ). The symbol possesses two components, and the first component is to be given precedence on display over the second component. In the method, the display of the symbol depends firstly on the orthogonal projection (FPV-lock) of the real position (FPV) of the symbol onto the axis of the first component, and secondly on the position of said projection relative to the display limit of the screen. Such a display makes it possible to give reliable information to the pilot. | 08-07-2014 |
20140249700 | AIRCRAFT GROSS WEIGHT AND CENTER OF GRAVITY VALIDATOR - A system for validating ground determination of gross weight of aircraft includes sensor(s) that generates information regarding ground determination of gross weight while parked at parking bay; processing device that receives information regarding ground determination of gross weight of the aircraft from sensor(s); and computer memory communicatively coupled to processing device. Processing device determines ground determination based on information regarding ground determination of gross weight generated by sensor. Processing device determines gross weight in air after takeoff based on indicated airspeed, angle of attack, and thrust applied to aircraft. Processing device determines error between ground determination and air determination of gross weight taking into account reduction in gross weight due to fuel consumed since receiving ground determination. Processing device updates information regarding relationship between ground determination and air determination of gross weight. Computer memory stores updated information regarding relationship for use next time aircraft parks at parking bay. | 09-04-2014 |
20140249701 | SYSTEM AND METHOD FOR MANAGING AN INTERVAL BETWEEN AIRCRAFT - A system and method provide situational awareness for a pilot of an ownship in managing the longitudinal interval from an aircraft from which the ownship is following and maintaining the ownship within performance limits by displaying an airspeed bar containing markers representing the ownship minimum and maximum airspeeds, the ownship indicated airspeed, and a commanded interval management airspeed (CIMS) for providing speed situational awareness. A flight management system modifies the CIMS in response to a distance between the aircraft and the ownship. An optional pointer attached to the marker representing the CIMS indicates a trend in the in the CIMS. | 09-04-2014 |
20140309821 | AIRCRAFT FLIGHT MANAGEMENT DEVICES, SYSTEMS, COMPUTER READABLE MEDIA AND RELATED METHODS - Aircraft flight management devices, systems, computer readable media, and related methods are provided. The present subject matter includes devices, systems, computer readable media, and related methods of providing flight management control during abnormal events and/or situations requiring diversion from the present mission. In some aspects, a system for providing flight management may include a computing platform with a processor, a memory, and a flight management application module (FMAM) configured to receive data from multiple servers. The FMAM may also calculate one or more aircraft ranges and/or diversion routes based upon the received data. In some aspects, systems and devices disclosed herein may be configured to provide diversion assistance by selectively displaying information including the map, one or more of the aircraft ranges, a vertical display, and information regarding one or more airports. | 10-16-2014 |
20140324255 | AIRCRAFT EMERGENCY SYSTEM USING ADS-B - A safety system for an aircraft using ADS-B has a touch screen device or switch interfaced with an emergency computer, wherein the emergency computer sends an emergency signal to the ADS-B system in response to a command from the touch screen device or switch. | 10-30-2014 |
20140330459 | OPTICAL PARTICLE DETECTOR - An optical device mounted on the interior of an aircraft for distinguishing the morphology of individual atmospheric particles, identifying them as water droplets, ice crystals, dust particles or volcanic ash, including a source of collimated, polarized light and providing this information to the flight crew to assist them in making informed decisions on conditions that might impact aircraft performance. | 11-06-2014 |
20140343762 | DEVICE AND METHOD TO INCREASE PILOT FOCUS - An interactive task organizer application may encourage a pilot to be more alert and engaged while operating the aircraft, despite that automation has made the job more passive. The interactive task organizer application may have access to flight data, and may use this data to create a virtual environment that encourages pilots to perform flight related tasks and to make visible explicit mission goals at a global and local level. | 11-20-2014 |
20140343763 | METHOD AND DEVICE FOR DISPLAYING THE PERFORMANCE OF AN AIRCRAFT WHEN CLIMBING AND/OR DESCENDING - The display device ( | 11-20-2014 |
20140358333 | AIRSPEED ESTIMATION USING ROTOR VIBRATIONS - Embodiments are directed to determining, by a computing device comprising a processor, at least one parameter associated with a rotorcraft, obtaining, by the computing device, a profile of a vibration associated with the operation of the rotorcraft based on the at least one parameter, determining, by the computing device, an amplitude of the vibration using the profile, and determining, by the computing device, an airspeed of the rotorcraft based on amplitude. | 12-04-2014 |
20140358334 | AIRCRAFT INSTRUMENT CURSOR CONTROL USING MULTI-TOUCH DEEP SENSORS - Aircraft and instrumentation systems are provided. An aircraft includes a display surface, at least one projector, at least one deep sensor, and a controller. The display surface is configured to display images with aircraft information. The at least one projector is oriented to project the images onto the display surface. The at least one deep sensor is configured to generate a signal indicative of a location of an object relative to the display surface. The controller is configured to generate tasks when the signal generated by the at least one deep sensor indicates that the object is touching the display surface. The controller is further configured to generate tasks based on a movement pattern of the object that is indicated by the signal generated by the at least one deep sensor. | 12-04-2014 |
20140358335 | AERIAL REFUELING INDICATION SYSTEM AND METHOD - An indication system and method for detecting and displaying the relative position during fuel transfer. The system comprises a first input device configured to be capable of detecting the extended length from the tanker aircraft of elongated hose and to be capable of sending the detected length of elongated hose to the control module. The control module is operably connected to a display and configured to be capable of receiving an input signal from the input device of hose extension, transforming it into a corresponding output signal of the position of the receiver aircraft inside a refueling range of limit positions and sending the corresponding output signal to the display, which is configured to be capable of displaying information indicating the position of the receiver aircraft inside the refueling range of limit positions. | 12-04-2014 |
20140379177 | TORQUE ESTIMATION APPARATUS FOR VERTICAL TAKE-OFF AND LANDING AIRCRAFT, VERTICAL TAKE-OFF AND LANDING AIRCRAFT, TORQUE ESTIMATION PROGRAM FOR VERTICAL TAKE-OFF AND LANDING AIRCRAFT, AND TORQUE ESTIMATION METHOD FOR VERTICAL TAKE-OFF AND LANDING AIRCRAFT - This invention easily estimates the amount of a utilizable torque in real time based on limited engine performance parameters, regardless of abrupt variations in the engine performance. A torque estimation apparatus ( | 12-25-2014 |
20150012155 | AIRCRAFT COMPRISING A MEASURING PROBE AND METHOD FOR DETERMINING FLIGHT PARAMETERS OF SUCH AN AIRCRAFT - The invention relates to an aircraft including a fuselage and a first measuring probe including means for measuring the local incidence, means for measuring the static pressure, and optionally means for measuring the total pressure. The fuselage includes at least one first zone where the pressure coefficient of the aircraft depends on the unique local incidence irrespective of the sideslip and incidence values of the aircraft, and the first measuring probe is arranged in said first zone | 01-08-2015 |
20150019049 | PASSENGER AIRCRAFT EMERGENCY PROCEDURES - Passenger aircraft includes seats, display screens facing the seats, and oxygen masks. When oxygen masks are deployed, imperative imagery is displayed that urges the passenger to at least don their oxygen mask, then optionally help others, etc. In some of these embodiments, the passenger aircraft further includes input devices. Each passenger can enter an input that indicates they have donned the mask, so as to see further imagery for guidance. These inputs could be stored in the flight data recorder for subsequent analysis. In some embodiments, passengers enter self-reported data using the input devices. The self-reported data can be stored in the flight data recorder for subsequent analysis of situations, such as when oxygen masks have been deployed. | 01-15-2015 |
20150019050 | METHOD AND DEVICE FOR DISPLAYING IN REAL TIME A PITCH INSTRUCTION ON AN AIRCRAFT DURING MANUAL PILOTING - A device comprising a display unit which is configured to display, on a screen of the cockpit of the aircraft, a pitch bar illustrating a pitch order and means for adapting the direct gain of the pitch law used to the effective manual behavior of the pilot in order to obtain a homogeneous response from the aircraft. | 01-15-2015 |
20150066254 | Method and System for Calculating Aircraft Speed Changes - Methods and systems for determining a change of speed of an aircraft for enabling the avoidance of conflicts between aircraft trajectories. The method of determining a change in speed of an aircraft, comprises the steps of: defining a merge point and a tie point; monitoring a first aircraft; determining when the first aircraft passes the tie point; providing trajectory data; predicting a trajectory of a second aircraft using the trajectory data; defining a minimum permissible longitudinal spacing; predicting a longitudinal spacing between the first and second aircraft at the merge point based on the predicted trajectory; and if the minimum permissible longitudinal spacing is greater than the predicted longitudinal spacing then calculating a proposed change in speed of the second aircraft that will result in the longitudinal spacing between the first and second aircraft at the merge point being greater than or equal to the minimum permissible longitudinal spacing. | 03-05-2015 |
20150073628 | HELICOPTER SYSTEM AND METHOD FOR INTEGRATING COLLECTIVE FLIGHT DIRECTOR CUES - A system and method are provided for integrating and displaying the collective cue and the pitch and roll cue of a helicopter display with a flight path marker providing a moving reference showing the aircraft flight path. | 03-12-2015 |
20150088342 | SYSTEM AND METHOD FOR PROCESSING AND DISPLAYING WAKE TURBULENCE - A system and method to display, when within an envelope of an ownship's flight path, a symbol representing wake turbulence from another aircraft based on aircraft type and flight parameters received from the other aircraft, the symbol being formatted to indicate the severity of portions of the wake turbulence. The format is modified periodically in accordance with the aircraft's flight path and a decay rate of the wake turbulence. | 03-26-2015 |
20150120097 | INTEGRATED COMMUNICATION AND APPLICATION SYSTEM FOR AIRCRAFT - A method of transferring aircraft data from an aircraft to a portable electronic device entails receiving at the portable electronic device the aircraft data from a data connection with an aircraft data source without writing data back to the aircraft or from a user interface while being capable of receiving aircraft data via the data connection and executing an application on the portable electronic device using the aircraft data to present new information about the aircraft or its operating environment that is not available for display on a cockpit display but which is displayable on the portable electronic device based on the aircraft data received by the portable electronic device. | 04-30-2015 |
20150134154 | SYSTEM FOR ACTIVATING THE DISTRESS BEACON OF AN AIRCRAFT - A system for activating the distress beacon determines a positional difference between a theoretical position of the aircraft determined from data of the flight plan and a real position of the aircraft determined from the navigation and monitoring equipment installed in the aircraft. This system delivers an instruction to arm the distress beacon when one or more conditions are met, among which is the condition that the positional difference exceeds a predetermined value. | 05-14-2015 |
20150142224 | METHOD AND SYSTEM FOR DISPLAYING METEOROLOGICAL EVENTS ALONG A FLIGHT PLAN OF AN AIRCRAFT - Method and system for displaying meteorological phenomena encountered by an aircraft flying along a flight plan. The display system includes a display device configured to present on a screen a meteorological indicator, the meteorological indicator comprising a time line representing a time scale relating to the duration of the flight of the aircraft along the flight plan and, on this time line, a set of first symbols illustrating meteorological phenomena and a second symbol indicating the current instant. | 05-21-2015 |
20150307203 | VERTICAL AXIS SOFT LANDING CONTROL - Embodiments are directed to obtaining data pertaining to at least: a rate of descent of an aircraft and a measured distance of the aircraft from at least one of an obstacle and the ground, processing, by a processing device, the data to obtain a flight envelope, generating a tactile cue corresponding to the flight envelope, and applying the tactile cue to an inceptor. | 10-29-2015 |
20150307204 | LOW-G ALERT - A warning system alerts a helicopter pilot that a low-G condition is imminent or occurring. The low-G alert employs an accelerometer to detect a vertical acceleration of the aircraft. Higher frequency vibrations in the output of the accelerometer are removed by a filter to provide a clean signal representing vertical acceleration of the aircraft. This signal is processed by a central processing unit (CPU) to perform a threshold detector function. The CPU is configured to detect the possibility of the onset or occurrence of a low-G event. Upon detection, the CPU triggers an audible alert to announce “Low-G. Pull aft.” or the like until the low-G event has been corrected or avoided. | 10-29-2015 |
20150314884 | SYSTEM AND METHOD FOR IMPROVED LOW AIRSPEED WARNING - A method and system are provided for generating a low airspeed warning in an aircraft. This method creates a scale factor that is a factor of engine thrust and aircraft altitude. A low airspeed threshold is determined that varies according to the aircraft altitude with respect to a predetermined altitude band and the engine thrust with respect to a predetermined engine thrust band. A low airspeed alert is generated in response to the determination of the low airspeed threshold. This method provides a pilot with earlier knowledge of low airspeed conditions when the aircraft is in a target altitude band, increasing the pilot's response time and thereby enhancing overall aircraft safety. | 11-05-2015 |
20150323559 | METHOD FOR DETERMINING THE SPEED OF A ROTOCRAFT RELATIVE TO THE SURROUNDING AIR - A method for determining the speed vector ({right arrow over (Vd)}), with respect to the surrounding air, of a rotary wing aircraft (HL) equipped with a beam scanning Doppler laser anemometry device for measuring (Step | 11-12-2015 |
20150325129 | METHOD FOR GEO-LOCATING RAW DATA EXCHANGED DURING AN AIR/GROUND TRANSMISSION AND A CORRESPONDING GEO-LOCATION DEVICE - A method for geo-locating the raw data exchanged between an aircraft and a VHF receiver is provided. Each item of raw data includes an identifier of the aircraft transmitting this item of data. The method includes obtaining position data of the aircraft. In this regard, the position data includes a piece of information which represents the identifier of the aircraft. The method also includes correlating the raw data and the position data by determining the data that has an identical identifier. | 11-12-2015 |
20150325130 | SPACE WEATHER MONITORING SYSTEM FOR POLAR ROUTES - A space weather monitoring system for polar routes includes: a satellite which flies over polar routes; a route-information providing server which receives data collected by the satellite monitoring the polar routes and generates various pieces of information about space weather; a flight vehicle which makes a request for information about the polar routes of the flight to the route-information providing server, and flies over the polar routes based on the received information; and a network which relays data among the satellite, the route-information providing server and the flight vehicle, so that an aurora-distribution map needed for an aircraft flight, an electromagnetic wave absorption map based on the ionosphere, information about space weather, and the situation and forecast of the space weather can be provided to an airline, thereby having effects on allowing the airline to check the information about the space weather in real time and fully considering a user who is unfamiliar to the space weather. | 11-12-2015 |
20150369626 | METHOD OF SIMULATING A REAL-TIME AIRCRAFT SYSTEM INPUT TO AN AVIONICS COMPONENT - A method of simulating a real-time aircraft system input to an avionics component for an aircraft includes receiving the simulation input and providing the simulated input to the avionics component. | 12-24-2015 |
20160019796 | SYSTEM AND METHOD FOR PROVIDING IN-FLIGHT WEATHER INFORMATION TO COMPUTE AN OPTIMIZED VERTICAL FLIGHT PROFILE - A system and method for providing in-flight weather information to compute an optimized vertical flight profile are disclosed. In one embodiment, on-board weather information is obtained from one or more aircraft at regular intervals during flight. Further, weather information is identified for a predicted flight trajectory of an aircraft from the obtained on-board weather information. For example, the aircraft is preceding the at least one aircraft. Furthermore, a subset of the identified weather information is dynamically provided to a flight management system (FMS) in the aircraft, during flight, to compute the optimized vertical flight profile. | 01-21-2016 |
20160019798 | SYSTEM AND METHOD FOR SENDING IN-FLIGHT WEATHER ALERTS - A system and method for sending weather alerts to an aircraft during flight are disclosed. In one embodiment, in-flight weather information is obtained from one or more aircrafts at regular intervals. Further, weather conditions along a predicted flight trajectory of the aircraft are determined using the obtained in-flight weather information. The aircraft is preceding the one or more aircrafts. Furthermore, the weather alerts associated with the weather conditions are sent to a display in the aircraft during flight. | 01-21-2016 |
20160023776 | SYSTEMS AND METHODS FOR AIRSPEED ESTIMATION USING ACTUATION SIGNALS - Systems and methods for airspeed estimation using actuation signals are provided. In one embodiment, an on-board avionics airspeed estimation system is provided. The system comprises: a flight control surface for an aircraft; a control surface actuator coupled to the flight control surface, wherein the control surface actuator receives an actuator control output signal from an actuator control system and drives the flight control surface into a position based on the actuator control output signal; a wind estimator coupled to a plurality of aircraft sensors, wherein the plurality of aircraft sensors output a set of aircraft measurements to the wind estimator and wherein the actuator control output signal is further provided to the wind estimator; wherein the wind estimator calculates a wind speed estimate by applying the actuator control output and the set of aircraft measurements to an onboard aircraft model. | 01-28-2016 |
20160041304 | ICE CRYSTAL ICING ENGINE EVENT PROBABILITY ESTIMATION APPARATUS, SYSTEM, AND METHOD - Described herein is an apparatus that includes an estimation module that estimates a probability of an ice crystal icing engine event based on infrared satellite data, numerical weather prediction data, and empirical data corresponding with at least one actual ice crystal icing engine event. The apparatus also includes a data product module that generates a data product that indicates the estimation of the probability of an ice crystal icing engine event. Additionally, the apparatus includes an output module that communicates the data product to a recipient. | 02-11-2016 |
20160055754 | ROTARY-WING AIRCRAFT EMERGENCY LANDING CONTROL - An emergency landing control system for an aircraft includes a landing site data source, a performance margin data source, an engine health data source, an aircraft health data source, and a processor. The landing site data source determines, continuously and in real-time, available landing sites. The performance margin data source conducts, continuously and in real-time, continuous performance analysis of an engine. The engine health data source determines, continuously and in real-time, available engine power as a function of time. The aircraft health data source determines, continuously and in real-time, available aircraft life as a function of time. The processor receives data from these data sources and, based on these data, continuously generates landing paths to one or more of the available landing sites, and selectively and continuously adjusts maximum available engine power up to emergency power limits, as needed, during execution of a landing maneuver to a landing site. | 02-25-2016 |
20160069274 | ENGINE-INDUCED AIRCRAFT CABIN RESONANCE REDUCTION SYSTEM AND METHOD - A system method of reducing engine induced aircraft cabin resonance in an aircraft includes sensing a parameter representative of current aircraft flight conditions, and sensing a parameter representative of current engine operating conditions of at least one of a first turbofan gas turbine engines or a second turbofan gas turbine engine. In a control system, the parameter representative of current aircraft flight conditions and the parameter representative of current engine operating conditions are processed to supply a variable inlet guide vane (VIGV) offset value. The VIGV offset value is applied to a VIGV reference command associated with one of the first or second turbofan gas turbine engine, to thereby cause the VIGVs of one of the first or second turbofan gas turbine engine to move to a more closed position. | 03-10-2016 |
20160075443 | FAIL SAFE AIRCRAFT MONITORING AND TRACKING - Flight data recorder receives from an aircraft a data stream specifying values for flight data parameters while an aircraft is in flight. The flight data recorder stores the values in a crash survivable non-volatile memory unit of the flight data recorder. The flight data recorder determines an occurrence during flight of an exception condition based on an evaluation of at least one exception parameter. Responsive to determining the occurrence of the exception condition, the flight data recorder wirelessly communicates selected aircraft data to a remote location external of the aircraft using a wireless transmitter under the exclusive control of the flight data recorder. | 03-17-2016 |
20160117930 | Method of Generating and Displaying A Flare Drift Vector Symbol - The present disclosure is generally directed to a method of generating and displaying a parachute flare drift vector symbol on a navigation display of the aircraft capable of deploying a flare relative to a real-time navigation map. The flare drift vector symbol includes a flare ignition forward/aft distance relative to the aircraft deploying the flare, a flare ignition left/right distance relative to the aircraft deploying the flare, a flare burn vector distance, and a flare burn vector direction. The flare drift vector symbol is generating based on the flare parameters, the wind parameters, the flare drift distance, the flare drift direction and the aircraft parameters. | 04-28-2016 |
20160122036 | INTEGRATED COMMUNICATION AND APPLICATION SYSTEM FOR AIRCRAFT - A method of transferring aircraft data from an aircraft to a portable electronic device entails receiving at the portable electronic device the aircraft data from a data connection with an aircraft data source without writing data back to the aircraft or from a user interface while being capable of receiving aircraft data via the data connection and executing an application on the portable electronic device using the aircraft data to present new information about the aircraft or its operating environment that is not available for display on a cockpit display but which is displayable on the portable electronic device based on the aircraft data received by the portable electronic device. | 05-05-2016 |
20160123763 | METHODS AND SYSTEMS FOR DISPLAYING FLIGHT INFORMATION - Avionics systems, controllers, and methods are provided. An avionics system includes a display and a controller. The controller is communicatively coupled with the display. The controller is configured to generate a flight clearance portion of the image including flight clearance information and to generate a flight progress portion of the image including flight progress information. | 05-05-2016 |
20160129992 | ENERGY PROTECTION METHOD AND DEVICE FOR AN AIRCRAFT - An energy protection device comprising an activation unit for, in a low energy situation, automatically activating an energy protection function comprising automatically engaging an autothrust and automatically controlling the engines of the aircraft for the engines to supply a maximum thrust, an auxiliary monitoring unit configured to perform a monitoring to detect an absence of activation of a protection mode by at least one of the engines of the aircraft although an activation command has been transmitted, and a disconnection unit to automatically disconnect the autothrust in case of the detection of such a situation, a disconnection of the autothrust resulting in the triggering of the protection function being stopped. | 05-12-2016 |
20160137289 | METHOD AND A DEVICE FOR CONTROLLING AT LEAST TWO SUBSYSTEMS OF AN AIRCRAFT - A method of controlling subsystems of an aircraft. During a preparation step, at least one global order is stored in a database, each global order including an eligibility condition, and at least one global order including an activation condition, each global order specifying a command sequence comprising at least two actions to be implemented one after another or in parallel by two different members. During an initialization step, an onboard computer determines whether a global order is selected automatically or by a pilot. During an activation step, an onboard computer determines, where appropriate, whether the selected global order is feasible. During an implementation step, and providing the selected global order is feasible, the onboard computer performs the actions specified by the selected global order. | 05-19-2016 |
20160155340 | Weather Avoidance Tool System | 06-02-2016 |
20160171796 | Gas Turbine Engine Anomaly Detections and Fault Identifications | 06-16-2016 |
20160176538 | SMART AVIONICS SYSTEM | 06-23-2016 |
20160185463 | SYSTEM AND METHOD OF INTEGRITY CHECKING DIGITALLY DISPLAYED DATA - System and method of integrity checking digitally displayed data in a display system having a display comprising a pixel array with a viewable area, including rendering a known value into a QR code graphic, generating an image onto the display including drawing the QR code graphic in the viewable area of the pixel array, monitoring the generated image for the drawn QR code graphic and determining the integrity of the drawn graphical information. | 06-30-2016 |
20160196750 | AUTOMATED UN-MANNED AIR TRAFFIC CONTROL SYSTEM | 07-07-2016 |
20160200455 | LINE REPLACEMENT UNIT (LRU) REPLACEMENT PROCESS | 07-14-2016 |
20160252603 | AERO-WAVE INSTRUMENT FOR THE MEASUREMENT OF THE OPTICAL WAVE-FRONT DISTURBANCES IN THE AIRFLOW AROUND AIRBORNE SYSTEMS | 09-01-2016 |
20170236429 | Aircraft Navigation Performance Prediction System | 08-17-2017 |
20170237481 | INTEGRATED COMMUNICATION AND APPLICATION SYSTEM FOR AIRCRAFT | 08-17-2017 |
20190144128 | PERFORMANCE CAPABILITY DETERMINATION FOR AIRCRAFT | 05-16-2019 |
20190147753 | SYSTEM FOR TAKING INTO ACCOUNT MICRO WIND CONDITIONS IN FLIGHT PLANS FOR AERIAL VEHICLES | 05-16-2019 |
20190147755 | METHOD AND SYSTEM FOR OBTAINING AND PRESENTING TURBULENCE DATA VIA COMMUNICATION DEVICES LOCATED ON AIRPLANES | 05-16-2019 |
20220139238 | FLIGHT PATH INSPECTION DISPLAY - A system for rendering flight path specific weather information receives mid-to-long range weather information and one or more flight paths. The weather information corresponding to each of the flight paths is segregated and divided into portions that may be rendered separately on a secondary display, reorganized to be enlarged to occupy the secondary display. Indicators of the aircraft location and destination are maintained on the secondary display with respect to the divided, reorganized flight paths. Each divided, reorganized flight path segment includes an artifice at a peripheral portion indicating where the flight path segments should be rejoined. Multiple flight paths may be processed and rendered to provide a detailed view of each path for pilot consideration. | 05-05-2022 |