Flight Condition Indicating System Patents (Class 701/14)
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Patent number: 9366761Abstract: A radio signal processing system includes a first antenna; a second antenna; a first receiver communicatively coupled to the first antenna; a second receiver communicatively coupled to the second antenna; a first processing unit communicatively coupled to the first receiver and configured to receive a first signal from at least one of the first antenna and the second antenna when the system is operating in a first mode; a second processing unit communicatively coupled to the second receiver and configured to receive a second signal from the second antenna when the system is operating in a first mode; and wherein the first processing unit is further configured to receive a third signal from both the first antenna and the second antenna when the system is operating in a second mode.Type: GrantFiled: August 8, 2012Date of Patent: June 14, 2016Assignee: Honeywell International Inc.Inventor: Alfonso Malaga
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Patent number: 9368036Abstract: A method for calculating a flight plan used by a flight management system of an aircraft in a runway approach phase comprises: loading an initial procedure ending at a first end point not corresponding to a threshold of the runway and a first associated missed approach procedure; determining an additional procedure and a second associated missed approach procedure; concatenating the initial procedure and the additional procedure in order to generate a continuous concatenated flight plan comprising the initial procedure, the first missed approach procedure, the additional procedure and the second missed approach procedure; loading the concatenated flight plan into an active flight plan; selecting a second procedure from a set comprising the first missed approach procedure and the additional procedure; activating the selected second procedure.Type: GrantFiled: June 26, 2014Date of Patent: June 14, 2016Assignee: ThalesInventors: François Coulmeau, Jérôme Sacle, Emmanuel Dewas
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Patent number: 9334063Abstract: An aircraft avionics system including an aircraft interface device configured to communicate with an aircraft avionics system and a tablet interface module configured to communicate with the aircraft interface device and with one or more tablets. The aircraft avionics system includes a plurality of sensors for an aircraft and the tablet interface module provides the one or more tablets with information received from the aircraft interface device.Type: GrantFiled: September 10, 2012Date of Patent: May 10, 2016Assignee: ROSEMOUNT AEROSPACE, INC.Inventors: William J. Baumgarten, Michael J. Haukom, Thomas J. Horsager, Daniel L. McDowell
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Patent number: 9327841Abstract: Methods and systems for providing event driven vehicle position reporting are disclosed. For example, if a conventional communication system normally utilized by the vehicle for position reporting is turned off, behaving abnormally or otherwise disabled, methods and systems in accordance with the present disclosure may provide supplemental means and capabilities to continue vehicle position reporting. Furthermore, in certain embodiments, the supplemental reporting systems are configured so that they cannot be turned off or disabled.Type: GrantFiled: May 12, 2014Date of Patent: May 3, 2016Assignee: Rockwell Collins, Inc.Inventor: Lori Talbott
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Patent number: 9293051Abstract: Methods and systems are provided for presenting procedure information for a vertical profile on a display device associated with an aircraft. A method comprises displaying a first segment of the plurality of segments comprising a vertical profile with a first vertical scale and a first horizontal scale, wherein the first horizontal scale is based on a first distance associated with the first segment. The method further comprises displaying a second segment of the plurality of segments with the first vertical scale and a second horizontal scale, wherein the second horizontal scale is based on a second distance associated with the second segment. The first horizontal scale and the second horizontal scale are not equal. In this manner, the vertical profile has a nonuniform horizontal scale and a uniform vertical scale across segments.Type: GrantFiled: April 21, 2009Date of Patent: March 22, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Blake Wilson, Roger W. Burgin, Michael Chytil
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Patent number: 9205916Abstract: Methods, systems, and apparatus for tab-pane-based flight plan management interface are disclosed. The tab-pane-based flight management interface system (FMIS) is optimally Layered and Multi-Indexed (LMI) such that the management of flight management (FM) functions and associated parameters that affect the airplane's flight are easily and efficiently operable by pilots. The LMI-FMIS provides a flexible tab-pane-based architecture that allows pilots to start a flight plan modification, proceed to engage in other tasks not related to the modification, and return to the pending modification to continue the modification process. The LMI-FMIS also provides task-oriented menu structures that provide pilots tailored options or menus applicable to the task at hand thus efficiently guiding pilots to complete a task while maintaining easy access to information that was displayed prior to the commencement of the task.Type: GrantFiled: March 10, 2014Date of Patent: December 8, 2015Assignee: The Boeing CompanyInventors: Daniel J. Boorman, Randall J. Mumaw, Victor A. Riley
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Patent number: 9199744Abstract: A method and a device (50) for issuing a terrain avoidance warning for a rotary wing aircraft (100) during which at least one bundle (N1, N2) of possible avoidance trajectories for said aircraft (100) is prepared in order to avoid a collision between said aircraft (100) and the relief (70) being overflown. A warning is then triggered as soon as said relief (70) being overflown is found to be at a distance from any one of said bundles (N1, N2) of possible avoidance trajectories that is less than a predetermined distance (Mv). Said avoidance trajectories are determined on the basis of a predetermined avoidance maneuver and on the basis of states of said aircraft (100), said predetermined avoidance maneuver being performed at a predetermined maximum power of said aircraft (100).Type: GrantFiled: July 9, 2014Date of Patent: December 1, 2015Assignee: Airbus HelicoptersInventor: Jean-Paul Petillon
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Patent number: 9193478Abstract: The present disclosure relates to a flight recorder, having a memory, a control device, which is coupled to the memory and which is configured to record flight data during the flight of an aircraft and to store said flight data in the memory, a transceiver device, which is coupled to the control device and which is configured to accept stored flight data signals from the control device and to convert them into acoustic signals, and an acoustic transducer, which is coupled to the transceiver device and which is configured to emit the acoustic signals of the transceiver device into a body of water, the control device being configured to receive control signals via the transceiver device and, depending on the control signals, to retrieve partial data areas of the stored flight data from the memory and to transfer them to the transceiver device.Type: GrantFiled: March 19, 2014Date of Patent: November 24, 2015Assignee: Airbus Operations GmbHInventors: Maurice Girod, Uwe Bartels
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Patent number: 9193442Abstract: A method and related system may construct predictable 4-D flight profiles for fuel-efficient Optimized Profile Descents (OPD) in compliance with a Required Time of Arrival (RTA) constraint at a metering waypoint. The method may determine a feasible RTA window at the 95% confidence level enabling pilot awareness to accept or reject the RTA clearance. These methods may eliminate path unpredictability while retaining OPD benefits using constant flight path angle segments during descent. Thus, the vertical descent profile is clearly defined and, therefore, predictable to both pilots and air traffic control.Type: GrantFiled: May 21, 2014Date of Patent: November 24, 2015Assignee: Rockwell Collins, Inc.Inventors: Shih-Yih Young, Kristen M. Jerome
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Patent number: 9135793Abstract: Force feedback elements are incorporated at various points in a flight helmet. An onboard computer system identifies critical events and translates such events into a force feedback pulse applied to one or more of the force feedback elements, warning the pilot of the critical event while at the same time suppressing more conventional critical event warnings that may distract a pilot. Additionally, force feedback elements are incorporated into a vest, bodysuit or body armor. A mobile, personal computer system applies a force feedback pulse to one or more of the force feedback elements to indicate an event that might otherwise require an audible signal.Type: GrantFiled: June 3, 2013Date of Patent: September 15, 2015Assignee: Rockwell Collins, Inc.Inventors: Adam W. Pfab, Nicholas A. Barbaro, Andrew J. LeVake
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Patent number: 9097799Abstract: An object of the present invention is to provide a method for preventing turbulence-induced accidents that can expand a detection range to about 20 km without increasing the size of a device or increasing the energy consumption, can perform planar distribution monitoring of turbulence when the turbulence is detected in the flight direction and also can output a signal for autopilot steering input that decreases the fuselage shaking when the turbulence is difficult to avoid, as well as to provide a device having those functions.Type: GrantFiled: November 12, 2010Date of Patent: August 4, 2015Assignee: JAPAN AEROSPACE EXPLORATION AGENCYInventor: Hamaki Inokuchi
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Patent number: 9096354Abstract: 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 (DV), taken relative to the aircraft.Type: GrantFiled: October 1, 2013Date of Patent: August 4, 2015Assignee: DASSAULT AVIATIONInventors: Olivier Baudson, Arnaud Turpin
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Patent number: 9096327Abstract: According to one embodiment, a system for assessing health of an aircraft includes a receiver, a flight spectrum analyzer, and a health assessment analyzer. The receiver receives, from an aircraft, a plurality of measurements associated with two or more flight parameters. The plurality of measurements includes measurements spanning at least one period of time. The flight spectrum analyzer determines, based on a comparison of the plurality of measurements to a plurality of flight spectrum definitions, an amount of time the aircraft spent in each flight spectrum of a plurality of flight spectrums during the at least one period of time. The health assessment analyzer assesses a change in health of the aircraft over the at least one period of time based on the determination of the amount of time the aircraft spent in each flight spectrum and a plurality of spectrum health profiles.Type: GrantFiled: February 19, 2013Date of Patent: August 4, 2015Assignee: Bell Helicopter Textron Inc.Inventors: Brian E. Tucker, Stephen R. Johnston
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Patent number: 9096329Abstract: A method and device for displaying the performance of an aircraft when climbing and/or descending. The device includes devices for data capture, calculation and generating images for a display screen. The calculation device is configured to calculate a maximum slope that the aircraft can adopt depending on current data received from a data capture device. A display device presents images of the maximum slope superimposed with altitudes of a projected flight plan.Type: GrantFiled: May 14, 2014Date of Patent: August 4, 2015Assignee: Airbus Operations SASInventors: Thomas Koebel, Boris Kozlow, Maxime Wachenheim
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Patent number: 9046369Abstract: Methods and systems are provided for presenting information on a display device associated with an aircraft. A method comprises displaying a navigational map in a viewing area on the display device with initial display settings, identifying selection of a first category of information, and identifying content associated with the first category resulting in a first set of content. The method further comprises automatically updating display settings for the navigational map in response to identifying selection of the first category, wherein the display settings are updated based on the first set of content. The method further comprises displaying the first set of content on the navigational map based on the updated display settings.Type: GrantFiled: April 29, 2009Date of Patent: June 2, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Michael Chytil, Pavel Kolcarek, Blake Wilson, Roger W. Burgin
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Patent number: 9041560Abstract: A system and method are described for receiving a NOTAM and storing information relating to the distance of a temporarily displaced threshold for a runway. When that runway is selected for approach and landing, the temporarily displaced threshold and new aiming point are automatically displayed. The change made to the display using NOTAM data can be indicated to the pilot by distinct symbology or particular color, or by using an icon or an annunciation.Type: GrantFiled: April 24, 2012Date of Patent: May 26, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Sadguni Venkataswamy, Prashant Prabhu, Ravindra Jayaprakash, Anil Kumar Songa, Mallikarjuna Narala
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Patent number: 9043054Abstract: 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.Type: GrantFiled: July 10, 2012Date of Patent: May 26, 2015Assignees: Airbus (S.A.S.), Airbus Operations (S.A.S.)Inventors: Julien Feau, Hugo Francois
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Patent number: 9043055Abstract: 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.Type: GrantFiled: December 19, 2012Date of Patent: May 26, 2015Assignee: GE Aviation Systems LLCInventor: Frazer Leslie Pereira
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Publication number: 20150142224Abstract: 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.Type: ApplicationFiled: November 14, 2014Publication date: May 21, 2015Inventors: Pau LATORRE-COSTA, Adrien JARRY, François BOUNAIX
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Patent number: 9037319Abstract: 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.Type: GrantFiled: September 24, 2013Date of Patent: May 19, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Kevin J Conner, Yasuo Ishihara, Ray Berry
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Patent number: 9035802Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.Type: GrantFiled: December 22, 2010Date of Patent: May 19, 2015Assignee: Textron Innovations Inc.Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
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Patent number: 9037410Abstract: A method of creating at least one flight plan of an aircraft includes entering a creation objective which illustrates a type and general characteristics of the flight plan to be created, automatically generating a flight plan outline, automatically generating a targeted request for information relating to missing parameters, entering the requested information relating to the missing parameters, and supplementing automatically the flight plan outline and automatically deleting any discontinuities to create, in a definitive manner, the flight plan.Type: GrantFiled: October 17, 2008Date of Patent: May 19, 2015Assignee: AIRBUS OPERATIONS SASInventors: Daniel Ferro, Veronique Roan, Philippe Haas, Fulgence Rollet
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Patent number: 9037318Abstract: 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.Type: GrantFiled: May 8, 2013Date of Patent: May 19, 2015Assignee: Honeywell International Inc.Inventors: Mark T. Manfred, Thomas A. Ryno
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Patent number: 9037317Abstract: A system and method for collecting and analyzing data generated by at least one mobile platform (such as a train, ship, aircraft or automobile). The system includes a source of at least one user input, and a data interface control module that collects at least one type of data from the mobile platform, based on the user input, with the data related to the operation of the mobile platform. The system also comprises an analysis control module that analyzes the data collected by the data interface control module and generates analysis data based on the user input.Type: GrantFiled: December 21, 2006Date of Patent: May 19, 2015Assignee: The Boeing CompanyInventors: Robert W. Mead, Kelly J. Griswold
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Patent number: 9037320Abstract: Described herein is an apparatus that includes a disruption severity module and flight recommendation module. The disruption severity module calculates a disruption severity index value associated with an unscheduled maintenance event of an aircraft. The disruption severity index value is calculated based on a plurality of flight operation factors affected by the unscheduled maintenance event. The flight recommendation module recommends one of resolving the unscheduled maintenance event of the aircraft before a subsequent flight of the aircraft or flying the aircraft without resolving the unscheduled maintenance event of the aircraft based on the disruption severity index value.Type: GrantFiled: January 29, 2014Date of Patent: May 19, 2015Assignee: The Boeing CompanyInventors: Paul Kesler, Kevin Arrow
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Patent number: 9037391Abstract: An unmanned aircraft, unmanned aviation system and method for collision avoidance during the flight operation of an unmanned aircraft are provided. The unmanned aircraft includes a lift and propulsion system and a flight control system having a flight control unit, a navigation system and an actuator system. The flight control unit has an autopilot unit. The flight control unit calculates control commands using data from the navigation system and/or the autopilot unit, which can be conveyed to the actuator system for actuating the lift and propulsion system. A collision warning system is connected with the flight control system, the collision warning system detects a collision situation and makes collision avoidance data available. A connection between the collision warning system and the autopilot unit is provided, in order to initiate an obstacle avoidance maneuver by the autopilot unit with the help of the collision avoidance data.Type: GrantFiled: February 6, 2012Date of Patent: May 19, 2015Assignee: EADS Deutschland GmbHInventors: Joerg Meyer, Matthis Goettken, Christoph Vernaleken, Simon Schaerer
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Publication number: 20150134154Abstract: 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.Type: ApplicationFiled: November 6, 2014Publication date: May 14, 2015Inventor: Michel Colin
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Patent number: 9031719Abstract: Local wind fields can be predicted if both the airspeed and the ground speed of the helicopter are known. An aircraft that uses an inertial navigation unit, autopilot and estimator allows a measure of ground speed to be known with good certainty. The embodiments herein extends this system to allow an estimate of the local wind field to be found without actively using an airspeed sensor, but instead combining the measurements of an accelerometer and a drag force model and a model of controlled aerodynamics of the aircraft to estimate the airspeed, which again can be used to estimate the local wind speed.Type: GrantFiled: April 2, 2013Date of Patent: May 12, 2015Assignee: Prox Dynamics ASInventors: Alexander Philip Hall, Trygve Frederik Marton, Petter Muren
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Patent number: 9026279Abstract: A plurality of wireless engine sensors each sense an engine parameter as engine data and transmits wirelessly the engine data regarding the sensed engine parameters and receives data regarding a sampling rate. An engine monitoring module is mounted at the aircraft engine and a wireless sensor transceiver is configured to receive the engine data regarding sensed engine parameters from the wireless engine sensors. A first wireless transmitter is carried by the housing. A memory is carried by the housing. A processor is coupled to the memory, sensor transceiver and the first wireless transmitter and collects and stores in the memory engine data relating to engine parameters and transmits the engine data via the first wireless transmitter.Type: GrantFiled: June 6, 2012Date of Patent: May 5, 2015Assignee: Harris CorporationInventor: James J. Ziarno
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Patent number: 9026278Abstract: A method of using LIDAR on an airborne vehicle is described. A beam of radiation is transmitted to target areas at least one of above, below, and in front of the airborne vehicle, the target areas including particles or objects. Scattered radiation is received from the target areas. Respective characteristics of the scattered radiation are determined. An air turbulence factor or characteristics are determined from the respective characteristics. The airborne vehicle is controlled based on the air turbulence factor, such that turbulence experienced by the airborne vehicle is minimized. Alternatively, the airborne vehicle is controlled based on the characteristics to avoid colliding with the one or more objects. In another example, the airborne vehicle is controlled based on the characteristics to reduce headwind or increase tailwind, and substantially reduce a carbon footprint of the aircraft.Type: GrantFiled: May 22, 2012Date of Patent: May 5, 2015Assignee: Optical Air Data Systems, LLCInventors: Elizabeth A. Dakin, Priyavadan Mamidipudi, Philip L. Rogers
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Patent number: 9026275Abstract: A on-aircraft computer device predicts aircraft states (e.g., altitude, speed, flight path angle, and fuel consumption) at any given time, while utilizing a Deterministic Genetic Algorithm to search 4-D flight path candidates that can comply with all path constraints to produce a feasible 4-D path candidate as a final OPD flight path to arrive at a metering waypoint in a specified time window.Type: GrantFiled: July 24, 2013Date of Patent: May 5, 2015Inventors: Shih-Yih Young, Kristen M. Jerome
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Publication number: 20150120097Abstract: 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.Type: ApplicationFiled: October 30, 2013Publication date: April 30, 2015Inventor: David Hathaway
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Patent number: 9019127Abstract: A method to develop a system for management of warnings and electronic procedures for an aircraft, comprising a database of parameters relating to the warnings and to logic and procedures, the aircraft comprising ATA equipment, comprises definition and calculation of maturity criteria for development of the system, which comprises, in order: A) verification of warnings in the database with respect to predefined lists of warnings and calculation of a maturity criterion, B) if the criterion of A>predetermined threshold, verification of the coherence of the logic for the warnings then definition and calculation of a maturity criterion, C) if the criterion of B>predetermined threshold, verification of the existence of the procedures and, for each warning, analysis of its logic with respect to its procedure, then definition and calculation of a maturity criterion, the system being fully set up when the latter criterion>predetermined threshold.Type: GrantFiled: April 23, 2013Date of Patent: April 28, 2015Assignee: ThalesInventors: Didier Gautheron, Chris Deseure, Xavier Chazottes, Patrick Serrot
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Patent number: 9019128Abstract: A method and apparatus for providing assistance to a flight crew during flight. An image of a group of instruments on a flight deck of an aircraft is generated with an image sensor in a data processing system. Assistance information configured to assist the flight crew from flight information displayed by the group of instruments in the image is generated. The assistance information is displayed on a display device in the data processing system.Type: GrantFiled: May 21, 2013Date of Patent: April 28, 2015Assignee: The Boeing CompanyInventor: Guen Il Kim
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Patent number: 9020665Abstract: A present novel and non-trivial system, device, and method for presenting winds aloft symbology on an aircraft display unit are disclosed. Symbology image data representative of a plurality of sets of winds aloft symbologies may be generated as a function of flight plan data and weather data; flight plan data representative flight plan comprised of a plurality of waypoints may be received along with weather data representative of winds aloft data corresponding to each waypoint. Each set of winds aloft symbologies may be comprised of winds aloft symbology corresponding to each waypoint of the flight plan at a single altitude and symbolize winds aloft at that altitude. When provided to a display unit, each set of winds aloft symbologies represented in the symbology image data may be presented in a series of increasing or decreasing altitudes, where the series is presented sequentially or simultaneously.Type: GrantFiled: June 26, 2013Date of Patent: April 28, 2015Assignee: Rockwell Collins, Inc.Inventors: Michael G. Espenes, Mark W. Volner
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Patent number: 9014882Abstract: A device aiding the flight management of an aircraft during a phase of landing on an airport includes means for automatically determining an adaptive aiming point that is shifted along the runway in the downstream direction and which can be used by different usual landing aid means of the aircraft.Type: GrantFiled: May 3, 2013Date of Patent: April 21, 2015Assignee: Airbus Operations SASInventors: Anne Dumoulin, Marc Locheron
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Patent number: 9014878Abstract: The present invention relates to a method for detecting the performance of the aircraft comprising: collecting data reflecting operation status of the aircraft; generating the customized message based on the collected data, wherein, the customized message is configured to include one or more main parameters related to the operation status of the aircraft; storing or transmitting the customized message; and detecting the performance of the aircraft based on the customized message.Type: GrantFiled: July 26, 2012Date of Patent: April 21, 2015Assignee: Air China LimitedInventors: Zhuping Gu, Jiaju Wu, Fengliang Zheng, Lei Huang, Minjie Tang
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Patent number: 9008873Abstract: Methods and systems for a go/no-go Landing Decision Point (LDP) are disclosed. The methods and systems provide a graphical LDP on a cockpit display that pilots can use to determine whether to continue the landing or execute a go-around. The methods and systems may be implemented in embodiments having an onboard portion, an off-board portion, or both operatively coupled to provide an LDP in a preview/planning mode and real time mode.Type: GrantFiled: October 7, 2013Date of Patent: April 14, 2015Assignee: The Boeing CompanyInventors: Thomas J. Phillips, Jean M. Crane
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Patent number: 9002543Abstract: A system and method for assisting flight crew recovery in the aftermath of an unexpected event is provided. A processor is used to detect that an unexpected event has occurred in an aircraft and, in response to detecting that the unexpected event has occurred, state data are stored in memory. The processor is also used to detect that the unexpected event has been resolved and, in response to detecting that the unexpected event has been resolved, the processor retrieves the state data from the memory, generates an aftermath plan that includes prompts to guide the flight crew to complete the aftermath plan, and continuously updates the aftermath plan until the aftermath plan is completed.Type: GrantFiled: December 20, 2012Date of Patent: April 7, 2015Assignee: Honeywell International Inc.Inventors: Michael Christian Dorneich, Chris Hamblin, William Rogers, Stephen Whitlow
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Patent number: 8996201Abstract: A method and a device are disclosed for exchanging data between a technical management system of an aircraft and a mission management system of the aircraft, in order to permit one of the systems to determine the consequences of an event detected in the other of the systems. After at least one event has been detected in one of the technical management and mission management systems of the aircraft, at least one information item pertaining to the detected event is transmitted to the other of the technical management and mission management systems of the aircraft. The consequences of the event detected in the other of the technical management and mission management systems of the aircraft are then determined. The adaptation of at least one datum of the other of the technical management and mission management systems of the aircraft is evaluated in response to the determination.Type: GrantFiled: August 11, 2009Date of Patent: March 31, 2015Assignee: Airbus Operations SASInventor: Jean-Sebastien Vial
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Patent number: 8996205Abstract: A method for regulating an actuator for a control surface is provided, which actuator has an angular position controlled by an autopilot on an aircraft with mechanical flight control. When the value of the torque exerted by the actuator is less than a threshold torque value, the actuator is regulated in terms of position and the maximum speed of movement of the control surface is limited to a value that is dependent on the torque value. When the value of the torque exerted by the actuator is greater than the threshold torque value, the actuator is regulated in terms of torque.Type: GrantFiled: July 23, 2013Date of Patent: March 31, 2015Assignee: ThalesInventors: Romain Pierre, Arnaud Bonnaffoux, Caroline Adamski
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Publication number: 20150088342Abstract: 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.Type: ApplicationFiled: September 24, 2013Publication date: March 26, 2015Applicant: Honeywell International Inc.Inventors: Kevin J Conner, Yasuo Ishihara, Ray Berry
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Patent number: 8989925Abstract: An improved Horizontal Situation Indicator (HSI) module for use with an aircraft, wherein the HSI module is adapted for accepting Bank Angle Commands or waypoint data from the GPS flight module and for using the same to determine a heading error. The HSI module is further adapted for outputting the heading error to the Flight Director module where it can be used to create a Roll Command for output to the Auto-Pilot, whereby the Auto-Pilot can be commanded to follow a turn using the HSI and the Flight Director without requiring an additional module be added to the aircraft to create the heading error for use by the Flight Director. The waypoint data can be of the “flyover” type or the “flyby” type.Type: GrantFiled: March 12, 2013Date of Patent: March 24, 2015Assignee: L-3 Communications CorporationInventor: James Eugene Strickling
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Patent number: 8989998Abstract: A visual/graphical air traffic display tool to aid flight crews in determining future heading/track and position of ownship based on current climb rate, bank angle and groundspeed under current meteorological conditions. The tool displays symbols which indicate the predicted future position and heading/track of ownship on a traffic display unit. The tool is also capable of using ownship's predicted position and information received from surrounding traffic to identify a future conflict at ownship's predicted position and then display a future conflict warning on the traffic display unit. In one embodiment, the future conflict warning takes the form of a change in the coloration of the ownship position and heading/track indicator being displayed.Type: GrantFiled: March 27, 2013Date of Patent: March 24, 2015Assignee: The Boeing CompanyInventors: Minh-Tri Le, Syed Tahir Shafaat, Kim A. Nguyen
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Patent number: 8989923Abstract: A method of formulating a specification for temporal and vertical required navigation performance is described. The method assesses various flight management guidance systems methods and allows a specification to be set for an airport. The specification may be used to increase aircraft traffic into the airport. The specification sets limits on deviations in time and altitude, for example, on approach into arrivals at the airport. The method comprises: calculating temporal and vertical deviations from a reference trajectory for one or more flight management guidance methods for one or more aircraft types; and comparing the temporal and vertical deviations with operational requirements of the airport. The deviations from a reference trajectory may result from uncertainties affecting trajectory prediction, such as wind and temperature prediction accuracy.Type: GrantFiled: November 26, 2013Date of Patent: March 24, 2015Assignee: The Boeing CompanyInventors: Johan L. De Prins, Ramon Gomez
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Patent number: 8989921Abstract: An electronic flight control system for an aircraft capable of hovering and having at least one rotor. The flight control system is configured to operate in a manual flight control mode, in which the flight control system controls rotor speed in response to direct commands from the pilot; and in at least two automatic flight control modes corresponding to respective flight modes of the aircraft, and in which the flight control system controls rotor speed automatically on the basis of flight conditions. The flight control system is also configured to memorize, for each automatic flight control mode, a respective flight table relating different speed values of the rotor to different values of at least one flight quantity; and to automatically control rotor speed in the automatic flight control modes on the basis of the respective flight tables.Type: GrantFiled: June 10, 2010Date of Patent: March 24, 2015Assignee: Agustawestland S.p.A.Inventors: Fabio Nannoni, Pierre Abdel Nour, Marco Cicale′
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Patent number: 8983686Abstract: The invention relates to a device aboard an aircraft comprising output means configured to restore information relating to the aircraft status from aircraft systems, the device including a module providing interface between said output means and said aircraft systems, said module being configured to synthesize information from aircraft systems depending on predetermined behavior rules and to transmit said information thus synthesized to said output means.Type: GrantFiled: May 17, 2011Date of Patent: March 17, 2015Assignee: AIRBUS Operations S.A.S.Inventors: Alexandre Broquet, Yannick Deleris, Raphael Andre, Fabien Pascal
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Patent number: 8981968Abstract: A method and apparatus for displaying aircraft information. A selection of a piece of dynamic information is detected about an aircraft on a first display on a user interface. The piece of dynamic information is used to operate the aircraft and changes during operation of the aircraft. The piece of dynamic information selected from the first display is added to a custom display on the user interface. The custom display is displayed on the user interface on a display system for the aircraft.Type: GrantFiled: November 22, 2011Date of Patent: March 17, 2015Assignee: The Boeing CompanyInventors: Cindy Chi-Lan Huang, Eduardo Raul Cajavilca
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Patent number: 8983688Abstract: 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 centered 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 centered 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.Type: GrantFiled: March 1, 2013Date of Patent: March 17, 2015Assignee: ThalesInventors: Xavier Servantie, Yannick Le Roux
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Patent number: 8983687Abstract: A system and method for identifying a recommended configuration for operating an aircraft in wind shear conditions. A processor unit receives information associated with an operation to be performed by the aircraft. The processor unit receives an indication that wind shear may be present during the operation. Responsive to receiving the indication that the wind shear may be present during the operation, the processor unit identifies the recommended configuration for the aircraft to perform the operation using the information associated with the operation to be performed by the aircraft and rules for operating the aircraft in the wind shear conditions.Type: GrantFiled: March 13, 2012Date of Patent: March 17, 2015Assignee: The Boeing CompanyInventors: Stephan G. Hunter, Steven James Churchill