Profile Of Descent Patents (Class 701/18)
  • Patent number: 10437691
    Abstract: The disclosed computer-implemented method for caching in an erasure-coded system may include partitioning data into data chunks and storing the data chunks across at least two data storage devices. The method may also include encoding the data chunks into at least one parity chunk and storing the at least one parity chunk on at least one parity storage device. The method may further include caching (parity and/or data functions) to at least one storage device, when a threshold value is reached. The method may include detecting a storage failure on one of the data storage devices and subsequent thereto, prioritizing the caching of certain functions over those of others. Various other methods, systems, and computer-readable media are also disclosed.
    Type: Grant
    Filed: March 29, 2017
    Date of Patent: October 8, 2019
    Assignee: Veritas Technologies LLC
    Inventors: Deodatta Barhate, Sushrut Gajbhiye, Aniruddha Gokhale
  • Patent number: 10388171
    Abstract: Cockpit display systems and methods are provided for generating energy management symbology on cockpit displays, which aid pilot decision-making when evaluating and executing direct approaches. In an embodiment, the cockpit display system includes a cockpit display device on which a first cockpit display, such as a vertical situation display or a horizontal navigation display, is generated. A controller is operably coupled to the cockpit display device and configured to: (i) identify a direct approach (DA) path to a configuration point located over a destination airfield; (ii) calculate a first DA energy estimate for the aircraft to fly the DA path under engine idle conditions and arrive at the configuration point with an airspeed less than a configuration airspeed; and (iii) generate symbology on the first cockpit display indicative of the first DA energy estimate.
    Type: Grant
    Filed: February 15, 2017
    Date of Patent: August 20, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Aric Charles Liberman, Barbara Holder
  • Patent number: 9646503
    Abstract: Cockpit display systems and methods for generating navigation displays including landing diversion symbology are provided. In one embodiment, the cockpit display system includes a cockpit monitor and a controller coupled to the cockpit monitor. The controller is configured to assess the current feasibility of landing at one or more diversion airports in a range of an aircraft on which the cockpit display system is deployed. The controller is further configured to assign each diversion airport to one of a plurality of predetermined landing feasibility categories, and generate a horizontal navigation display on the cockpit monitor including symbology representative of the feasibility category assigned to one or more of the diversion airports.
    Type: Grant
    Filed: February 11, 2015
    Date of Patent: May 9, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Amit Nishikant Kawalkar, Rajesh Chaubey, Rajeev Mohan
  • Patent number: 9382016
    Abstract: According to an aspect, a method of monitoring landing of an aircraft includes determining whether the aircraft is in a landing phase to maneuver the aircraft to a landing zone. Either or both of a landing profile monitor and a pattern matcher can set a landing instability indicator. The landing profile monitor compares aircraft sensor data indicative of a current state of the aircraft to a landing profile of the aircraft and sets the landing instability indicator based on the landing profile. The pattern matcher identifies a pattern associated with the landing zone in perception sensor data indicative of current conditions at the landing zone, monitors the pattern for a change indicative of landing zone instability, and sets the landing instability indicator based on detecting the change indicative of landing zone instability. Landing abort logic is triggered to abort landing based on determining that the landing instability indicator is set.
    Type: Grant
    Filed: June 8, 2015
    Date of Patent: July 5, 2016
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: George Nicholas Loussides, Harshad S. Sane, Christopher Stathis
  • Patent number: 9268702
    Abstract: A method for storage input/output (I/O) path configuration in a system that includes at least one storage device in network communication with at least one computer processor; the method comprising providing in the I/O path into at least: (a) a block-based kernel-level filesystem, (b) an I/O cache module controlling an I/O cache implemented on a first computer readable medium, (c) a journaling module, and (d) a storage cache module controlling a storage cache implemented on a second computer readable medium, the second computer readable medium having a lower read/write speed than the first computer readable medium. Furthermore, the steps of translating by the filesystem, based on computer executable instructions executed by the at least one processor, a file I/O request made by an application executed by the at least one computer processor into a block I/O request and fulfilling by the at least one processor the block I/O request from one of the I/O cache and the storage cache complete the I/O operation.
    Type: Grant
    Filed: April 11, 2013
    Date of Patent: February 23, 2016
    Assignee: Institute of Computer Science (ICS) of the Foundation for Research and Technology—Hellas (FORTH)
    Inventors: Angelos Bilas, Konstantinos Chasapis, Markos Fountoulakis, Stelios Mavridis, Spyridon Papageorgiou, Manolis Marazakis, Yannis Sfakianakis
  • Patent number: 9205915
    Abstract: A method for the guidance of a rotorcraft (1) in relation to a landing point (Pp) in accordance with a landing procedure. An approach route (R) is identified and an approach trajectory (T) is calculated in accordance with a ground slope (S) imposed by the approach route (R). An upstream segment (Sam) of the approach trajectory (T) is calculated through the application of a typical trajectory, as defined in accordance with the ground slope (S), the current mass of the rotorcraft (1), and a low-noise or noise-abatement criterion relating to the noise discomfort generated by the rotorcraft (1), taking into consideration a wind model (V) that represents the change in the wind between a current position of the rotorcraft (1) and the landing point (Pp).
    Type: Grant
    Filed: March 4, 2014
    Date of Patent: December 8, 2015
    Assignee: Airbus Helicopters
    Inventors: Pierre Feyzeau, Etienne Poudrai
  • Patent number: 9058743
    Abstract: An automatic landing method and device for an aircraft on a runway with strong slope. The device includes means to automatically transmit, a runway slope value to an automatic piloting system of the aircraft, and said automatic piloting system uses the slope value to automatically manage the flare phase upon landing.
    Type: Grant
    Filed: October 24, 2012
    Date of Patent: June 16, 2015
    Assignee: Airbus Operations (SAS)
    Inventors: Thierry Bourret, Jean Muller, Mathieu Galy
  • Publication number: 20150149002
    Abstract: This relates to a method and device for constructing a vertical profile for an aircraft descent and/or approach. The construction device comprises a data-capture unit configured to provide, for at least one of a plurality of parameters, a value relating to a user strategy. A construction unit is configured to automatically construct a vertical profile for an aircraft descent and/or approach, using the value thus provided.
    Type: Application
    Filed: November 21, 2014
    Publication date: May 28, 2015
    Inventors: Jaouad BERRAJAA, Virginie LE GALL, Alexandre BUISSON
  • Patent number: 9041560
    Abstract: 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: Grant
    Filed: April 24, 2012
    Date of Patent: May 26, 2015
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Sadguni Venkataswamy, Prashant Prabhu, Ravindra Jayaprakash, Anil Kumar Songa, Mallikarjuna Narala
  • Patent number: 9031719
    Abstract: 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: Grant
    Filed: April 2, 2013
    Date of Patent: May 12, 2015
    Assignee: Prox Dynamics AS
    Inventors: Alexander Philip Hall, Trygve Frederik Marton, Petter Muren
  • Publication number: 20150120100
    Abstract: A method for aiding navigation for an aircraft between a descent start point and a computation end point, comprises the computation steps of: collecting a flight plan consisting of a succession of waypoints and of the associated vertical constraints; determining a corridor consisting of a floor trajectory and of a ceiling trajectory defining the minimum and maximum altitudes permitted to the aircraft; splitting the corridor into several cells defined between two waypoints furthest apart and between which the ceiling trajectory is distinct from the floor trajectory; determining for at least one cell a vertical trajectory complying with the altitude constraints and comprising the longest possible IDLE segment; and a step consisting in determining and displaying maneuvering points of the aircraft making it possible to follow the target vertical trajectory.
    Type: Application
    Filed: October 23, 2014
    Publication date: April 30, 2015
    Inventors: Jerome SACLE, Johan BOYER, Francois COULMEAU
  • Patent number: 9008873
    Abstract: 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: Grant
    Filed: October 7, 2013
    Date of Patent: April 14, 2015
    Assignee: The Boeing Company
    Inventors: Thomas J. Phillips, Jean M. Crane
  • Patent number: 8996207
    Abstract: A method for autonomous landing of an unmanned aerial vehicle (UAV) comprising: obtaining sensor data corresponding to one or more objects outside of the aircraft using at least one onboard sensor; using the sensor data to create a three dimensional evidence grid, wherein a three dimensional evidence grid is a three dimensional world model based on the sensor data; combining a priori data with the three dimensional evidence grid; locating a landing zone based on the combined three dimensional evidence grid and a priori data; validating an open spots in the landing zone, wherein validating includes performing surface condition assessment of a surface of the open spots; generating landing zone motion characterization, wherein landing zone motion characterization includes characterizing real time landing zone pitching, heaving, rolling or forward motion; processing the three dimensional evidence grid data to generate flight controls to land the aircraft in one of the open spots; and controlling the aircraft acco
    Type: Grant
    Filed: June 24, 2013
    Date of Patent: March 31, 2015
    Assignee: Honeywell International Inc.
    Inventors: Emray Rein Goossen, Yunqian Ma
  • Patent number: 8989921
    Abstract: 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: Grant
    Filed: June 10, 2010
    Date of Patent: March 24, 2015
    Assignee: Agustawestland S.p.A.
    Inventors: Fabio Nannoni, Pierre Abdel Nour, Marco Cicale′
  • Patent number: 8983689
    Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a step of calculation of an anticipated deviation of the aircraft, expressed linearly or angularly, projected to a time DT, characteristic of a reaction time of the aircraft, and of a statistical error distribution associated with this anticipated deviation; and a step of calculation of a probability of exceeding a predetermined target deviation, by means of the anticipated deviation and of the statistical error distribution. The method also comprises a crew alert when the probability is above a predetermined threshold.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: March 17, 2015
    Assignee: Thales
    Inventors: Guilhem Putz, Christophe Caillaud, Francois Coulmeau
  • Patent number: 8948939
    Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a calculation step for converting an angular deviation into an equivalent linear deviation, and, conversely, converting a linear deviation into an equivalent angular deviation. The method comprises a step of graphic representation, called unified monitoring, intended for the crew, of a deviation of the aircraft, on a lateral deviation axis and a vertical deviation axis; each of the deviations, lateral and vertical, being able to be represented on a linear scale, an angular scale or a mixed scale.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: February 3, 2015
    Assignee: Thales
    Inventors: Guilhem Putz, Christophe Caillaud, Francois Coulmeau
  • Patent number: 8933957
    Abstract: Methods and systems for visually organizing aviation or aeronautical charts with color emphasis and de-emphasis features selected by a user.
    Type: Grant
    Filed: August 18, 2008
    Date of Patent: January 13, 2015
    Assignee: The Boeing Company
    Inventor: Brian B. Kennedy
  • Publication number: 20140379179
    Abstract: A method for autonomous landing of an unmanned aerial vehicle (UAV) comprising: obtaining sensor data corresponding to one or more objects outside of the aircraft using at least one onboard sensor; using the sensor data to create a three dimensional evidence grid, wherein a three dimensional evidence grid is a three dimensional world model based on the sensor data; combining a priori data with the three dimensional evidence grid; locating a landing zone based on the combined three dimensional evidence grid and a priori data; validating an open spots in the landing zone, wherein validating includes performing surface condition assessment of a surface of the open spots; generating landing zone motion characterization, wherein landing zone motion characterization includes characterizing real time landing zone pitching, heaving, rolling or forward motion; processing the three dimensional evidence grid data to generate flight controls to land the aircraft in one of the open spots; and controlling the aircraft acco
    Type: Application
    Filed: June 24, 2013
    Publication date: December 25, 2014
    Inventors: Emray Rein Goossen, Yunqian Ma
  • Patent number: 8917191
    Abstract: A system for controlling an image displayed on a display unit of an aircraft is shown and described. The system includes an enhanced vision system that detects elements of an approach lighting system for display on the display unit. The system also includes a synthetic vision system that uses a database of navigation information and a determined aircraft location to generate synthetic display elements representing the approach lighting system. Display electronics of the system cause the detected elements from the enhanced vision system to be simultaneously displayed on the display unit within a same scene as the generated synthetic display elements from the synthetic vision system. Advantageously, the simultaneous display allows a pilot viewing the display unit to check for whether information provided by the enhanced vision system matches information provided by the synthetic vision system.
    Type: Grant
    Filed: September 22, 2011
    Date of Patent: December 23, 2014
    Assignee: Rockwell Collins, Inc.
    Inventors: Carlo L. Tiana, Kenneth A. Zimmerman, Robert B. Wood
  • Patent number: 8903572
    Abstract: In one embodiment an aircraft landing evaluation system comprises a first sensor to detect at least one landing trigger condition in an aircraft landing environment and a second sensor to detect at least one touchdown trigger condition in the aircraft landing environment. The system further comprises a processor coupled to the first sensor and the second sensor, and a memory module coupled to the processor. The memory module comprises logic instructions stored in a computer readable medium which, when executed, configure the processor to collect a plurality of flight parameters associated with the aircraft landing, and to collect a one or more additional flight parameters associated with the aircraft landing. A subset of the plurality of flight parameters are stored in a computer readable memory module coupled to the processing device, and may be presented on a display device coupled to the processing device.
    Type: Grant
    Filed: August 11, 2009
    Date of Patent: December 2, 2014
    Assignee: The Boeing Company
    Inventors: Jack S. Hagelin, Jonathan R. Lepere, Richard J. Reuter, Michael R. Anderegg
  • Publication number: 20140350755
    Abstract: A method and system for aiding piloting when selecting a trajectory of approach of an airport or airfield, implemented on at least one processor, includes a first step of selecting a landing airport or airfield, and a second step of determining, for said landing airport or airfield, all or part of the possible trajectories of approach associated with a landing runway, on the basis of a database of the airports or airfields. A third step determines, for at least one of the possible approaches, whether or not said approach is compatible with an angular guidance mode, by geometrical analysis of the approach; and a fourth step displays all of said possible approaches, for said landing airport or airfield, and of displaying the compatibility with said angular guidance mode for the approaches analyzed.
    Type: Application
    Filed: May 22, 2014
    Publication date: November 27, 2014
    Inventors: Christophe CAILLAUD, Jerome SACLE
  • Publication number: 20140343765
    Abstract: A system and apparatus for assisting pilots and flight crews in determining the best course of action at any particular point inflight for any category of emergency. The system monitors a plurality of static and dynamic flight parameters including atmospheric conditions along the flight path, ground conditions and terrain, conditions aboard the aircraft, and pilot/crew data. Based on these parameters, the system may provide continually updated information to the pilot or crew about the best available landing sites or recommend solutions to aircraft configuration errors. In case of emergency, the system may provide the pilot with procedure sets associated with a hierarchy of available emergency landing sites (or execute these procedure sets via the autopilot system) depending on the specific nature of the emergency.
    Type: Application
    Filed: December 27, 2013
    Publication date: November 20, 2014
    Inventors: Sean Patrick Suiter, Richard Andrew Kruse
  • Publication number: 20140343766
    Abstract: Method and device for automatically determining an optimized approach profile for an aircraft. The device provides for a flexible configuration change speed which is not limited to the standard single predetermined configuration change speed in order to prevent segments which are not authorized, in particular segments which are too steep, the following configuration (Ci+1) being able to be maintained during a configuration change in an upstream direction until the corresponding speed profile reaches a maximum speed.
    Type: Application
    Filed: May 16, 2014
    Publication date: November 20, 2014
    Inventors: Virginie LE GALL, Alexandre BUISSON, Pierre-Xavier CATINAT, Valentin VINCENT
  • Patent number: 8880339
    Abstract: A schematic display for presenting vertical navigation (VNAV) data is disclosed. A planned route such as a flight plan is divided into a series of VNAV legs, and only a VNAV schematic that corresponds to the active VNAV leg is displayed. The VNAV schematic in accordance with the present disclosure is a profile-view schematic for the active VNAV leg, providing a visual representation indicating the locations of the upcoming Top of Climb (TOC) or Top of Descent (TOD). Additional VNAV data may also be presented to provide content context. Since the schematic display in accordance with the present disclosure only displays VNAV data relevant to the active VNAV leg at a given time, the complexities associated with displaying the VNAV schematic is reduced, making the VNAV data easy to read and understand.
    Type: Grant
    Filed: August 21, 2012
    Date of Patent: November 4, 2014
    Assignee: Rockwell Collins Inc.
    Inventors: Seth A. Cooper, David A. Gribble, David L. Leedom, Geoffrey A. Shapiro, Daniel E. Russell, James E. Winfield
  • Patent number: 8880247
    Abstract: A method and computer program product for planning a landing approach of an aircraft based on an actual position or first nominal position of the aircraft during its approach for landing on a runway, including providing a stabilization flight path section and stabilization region and/or stabilization point defined by an altitude profile by at least one configuration change point in the stabilization flight path section with a change of the overall profile configuration of the airfoils and with a predetermined final approach flight status of the aircraft, and checking or changing position of the at least one configuration change measure in a change and/or the addition of an additional configuration change measure to the stabilization flight path section and by changing a speed profile along the stabilization flight path section so that the aircraft reaches the predetermined final approach flight status in the stabilization region or at the stabilization point.
    Type: Grant
    Filed: January 23, 2013
    Date of Patent: November 4, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Robert Luckner, Matthias Lauterbach, Björn Dorr
  • Patent number: 8843250
    Abstract: A vertical situation display system for use in a vehicle such as, for example, an aircraft, is provided. A side view of an intended route of flight may be shown with altitude restrictions, airspace and instrument approach information, a projected flight path and range to airspeed symbol. The system may show terrain, weather, and traffic information along the intended route of flight. The system may be used in conjunction with a navigational display to enhance situational awareness. The system includes a computer, an electronic display device, an electronic entry device, a memory and a database. The database may contain terrain, airspace and flight planning data and may be updatable.
    Type: Grant
    Filed: August 13, 2010
    Date of Patent: September 23, 2014
    Assignee: The Boeing Company
    Inventors: Michael J. Tucker, Sherwin S. Chen, John Wiedemann, Jason L. Hammack
  • Publication number: 20140277857
    Abstract: Methods, systems, and computer readable media are disclosed for direct arming aircraft runway approach guidance modes, for example and without limitation, for aircraft operational. In some aspects, a method for directly arming a runway approach guidance mode of an aircraft includes displaying on a display unit an airport, selecting the airport and selecting an active runway for final approach, displaying an path toward the selected final approach runway, selecting the final approach runway, displaying on the display unit at least one symbol associated with at least one runway approach guidance mode, and arming at least one of the at least one runway approach guidance mode.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventors: Thierry BOURRET, Pascale LOUISE, Claire OLLAGNON, Nicolas CHAUVEAU, Sebastien GIULIANO, Sebastien DRIEUX
  • Patent number: 8831799
    Abstract: Methods, systems, and computer-readable media are described herein for providing flight director guidance throughout a flare maneuver during landing operations. A pre-flare flight path to a runway may be received, and a flare engage altitude calculated. A flare command path may be calculated having a slope associated with a desired descent rate at a desired touchdown location on a runway. An aircraft flare trajectory may be calculated that transitions the aircraft from the flare engage altitude on the pre-flare flight path to the flare command path at the desired touchdown location. A flight director command may be provided during the flare maneuver that aligns a current flight path with the aircraft flare trajectory.
    Type: Grant
    Filed: April 4, 2013
    Date of Patent: September 9, 2014
    Assignee: The Boeing Company
    Inventors: Benjamin David Levine, Steven Barry Krogh
  • Publication number: 20140249704
    Abstract: A flight control system can achieve a relatively steep descent (using drag devices such as flight spoilers) at relatively low speeds while retaining good airplane handling qualities from the pilot's point of view. The system and method optimize the drag device's positioning used to perform steep approach to improve performance.
    Type: Application
    Filed: December 4, 2013
    Publication date: September 4, 2014
    Applicant: Embraer S.A.
    Inventors: Daniel Paulo DE TARSO FERREIRA, Mauricio Faustino OLIVEIRA, Fabricio Reis CALDEIRA
  • Patent number: 8818582
    Abstract: A method for guiding an aircraft during its final approach to a landing runway, whereby the aircraft is guided during its approach by aircraft position information obtained from an GNSS satellite navigation system, wherein: prior to the start of the final approach a first time tFAF is determined corresponding with the start of said final approach and a second time tTD corresponding with the landing of the aircraft on said runway, then a set of satellites is determined of the satellite navigation system for excluding from the calculation of said aircraft position information during at least a part of the time interval comprised between said first and second times; and during the final approach, the aircraft position information is determined while excluding the information corresponding with all the satellites of said set of satellites and the aircraft is guided along its final approach path by said position information.
    Type: Grant
    Filed: September 17, 2012
    Date of Patent: August 26, 2014
    Assignees: Airbus Operations S.A.S., Ecole Nationale de l'Aviation Civile (E.N.A.C.)
    Inventors: Pierre Neri, Laurent Azoulai, Jean Muller, Christophe Macabiau
  • Patent number: 8818576
    Abstract: The different advantageous embodiments provide a system for generating trajectory predictions for a flight comprising a flight object manager and a trajectory predictor. The flight object manager is configured to generate flight information using a number of flight plans, a number of flight schedules, and flight status information. The trajectory predictor is configured to receive flight information from the flight object manager and use the flight information to generate the trajectory predictions.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: August 26, 2014
    Assignee: The Boeing Company
    Inventors: Christie Marie Maldonado, Ferdinando Dijkstra, Robert W. Mead, Suzanne Elise Meador, Gregory T. Saccone
  • Patent number: 8798819
    Abstract: A monitor on-board an aircraft which uses radio altitude measurements as the basic observable altitude during runway approach. The basic concept utilizes the aircraft's navigation system, which includes means to store and retrieve radio altitude thresholds as a function of the distance along the desired path from the runway thresholds. These threshold functions are determined in advance based on a radio altitude reference which is defined as the expected radio altimeter measurement that would be made if the airplane were exactly on the desired reference path. Vertical containment monitoring is achieved by comparing the radio altitude measurement to computed thresholds for both too high and too low. During the approach, an annunciation message can be generated if the radio altitude measurement is above or below the threshold limits.
    Type: Grant
    Filed: June 18, 2013
    Date of Patent: August 5, 2014
    Assignee: The Boeing Company
    Inventor: Timothy Allen Murphy
  • Patent number: 8788128
    Abstract: In the examples described the forward-looking radar generated real-time terrain model (or in an alternative example in combination with a terrain database), can allow the use of a radio altimeter to compute aircraft vertical position relative to the runway threshold. Such a system typically provides improved accuracy for precision landings.
    Type: Grant
    Filed: August 1, 2008
    Date of Patent: July 22, 2014
    Assignee: Rockwell Collins, Inc.
    Inventor: Patrick D. McCusker
  • Patent number: 8781653
    Abstract: The present invention provides a method of modifying the pitch attitude of an aircraft during landing, comprising: commanding the flaps to move to a landing setting; providing a current value for a flight condition parameter; providing a current flaps setting; comparing said current value to at least one threshold value; if said current value exceeds said threshold, determining a new flaps setting capable of producing an improvement in at least one of a selected aft body contact margin and a selected nose gear contact margin for the aircraft; and adjusting the flaps to said new flaps setting.
    Type: Grant
    Filed: January 11, 2012
    Date of Patent: July 15, 2014
    Assignee: The Boeing Company
    Inventors: Robert E. Buchholz, Monte R. Evans, Jonathan P. Lee, Timothy G. Overton, Adam M. Thoreen
  • Patent number: 8781654
    Abstract: The device includes elements of a processing unit which determine a limit trajectory representing a flight trajectory which is compatible with the aircraft performance during the approach and which shows the limits for the flight of the aircraft. For example, a vertical profile and a horizontal trajectory are determined, with the horizontal trajectory being non-linear so that the energy of the aircraft can be sufficiently dissipated before final approach along an approach axis, while also avoiding obstacles. Thus, a flight trajectory is determined even when the aircraft has deviated from a flight plan and approach axis.
    Type: Grant
    Filed: December 2, 2011
    Date of Patent: July 15, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Andrea Giovannini, Thomas Pastre
  • Patent number: 8768540
    Abstract: There is provided an avionics system that provides several avionics functions within a single LRU. In one embodiment, the system comprises a software-configurable RF assembly, one or more processor assemblies that are configured to provide multiple TAWS/TCAS/Mode S/ADS-B/ATC functions, interfaces to allow connections to aircraft electronics and data loaders, and multipurpose antennas. In one embodiment, a common processor architecture allows generic avionics processors to be configured to operate a number of TAWS/TCAS/Mode S/ADS-B/ATC functions without the need for multiple LRUs, and software-defined RF functions allow RF circuitry that interfaces to the processors to handle current and future communication needs.
    Type: Grant
    Filed: April 10, 2007
    Date of Patent: July 1, 2014
    Assignee: L-3 Communications Corporation
    Inventors: Cyro A. Stone, James R. Troxel, Gregory T. Stayton
  • Publication number: 20140114506
    Abstract: A method for assisting in the piloting of an aircraft during a landing on a landing area on the ground. The method includes the following steps: (1) during a landing phase, while the landing area on the ground is visible from the aircraft: displaying, on a screen of the cockpit of the aircraft, a target corresponding to this landing, overlaid on a view outside the aircraft; receiving from a pilot a command to modify this target and displaying the duly modified target; and receiving a command to validate a value of the target by a pilot; (2) automatically determining an aircraft flight trajectory as a function of the aircraft's current position and of the value of the target validated by the pilot and storing this trajectory; and (3) guiding the aircraft along the stored trajectory. Also a piloting assistance system suitable for implementing this method is disclosed.
    Type: Application
    Filed: October 21, 2013
    Publication date: April 24, 2014
    Inventors: Guilhem Puyou, Fabien Perrin, Matthias Eberle, Matthieu Barba
  • Patent number: 8700234
    Abstract: A method of an aircraft communicating a current position status, a current movement status, a current intent, and/or an intended future path, position, or intent of the aircraft may include the aircraft generating explicit first ownship information related to the current position status and/or the current movement status, or current intent of the aircraft, and/or a flight management or other aircraft system of the aircraft generating information related to the intended future path, position, or intent of the aircraft. The aircraft may transmit the explicit first ownship information and/or the second information using an automatic dependent surveillance broadcast system transmitter. An airborne and/or ground receiver may receive the transmitted information related to the explicit first ownship information and/or the second information.
    Type: Grant
    Filed: May 20, 2008
    Date of Patent: April 15, 2014
    Assignee: The Boeing Company
    Inventors: Syed Taji Shafaat, Samuel T. Clark
  • Patent number: 8676405
    Abstract: A method of controlling the flight of a rotorcraft in a feed-forward/feedback architecture includes utilizing an aircraft plant model to control the rotorcraft performance; determining when an external load is coupled to the rotorcraft; and modifying an inverse plant when the external load is present.
    Type: Grant
    Filed: January 20, 2011
    Date of Patent: March 18, 2014
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Stephen Kubik, Vineet Sahasrabudhe, Alex Faynberg
  • Patent number: 8660722
    Abstract: A target vertical speed, to be applied to the aircraft upon the initiation of the aircraft's flaring phase, is defined in relation to the ground. An optimized ground slope associated with an approach path to be tracked during the landing, is then determined as a function of the determined target vertical speed and of at least one outside parameter. This optimized ground slope is at least equal to a predefined ground slope. Upon interception by the aircraft with the approach path, the aircraft is guided to track the determined optimized ground slope associated with the approach path and reach the target vertical speed upon initiation of the flaring phase.
    Type: Grant
    Filed: March 6, 2012
    Date of Patent: February 25, 2014
    Assignees: Airbus (SAS), Airbus Operations (SAS)
    Inventors: Anne Dumoulin, Martin Scheuermann
  • Patent number: 8630754
    Abstract: The present invention relates to a method for replacing legs in an air navigation procedure described as a series of legs, the legs forming part of an initial family of legs. The method includes: a step of determining a restricted family of legs included in the initial family of legs, so that each leg not belonging to the restricted family corresponds to a combination of legs belonging to the restricted family: The method also includes: a step of replacing in the navigation procedure the legs not belonging to the restricted family with combinations of legs belonging to the restricted family.
    Type: Grant
    Filed: December 5, 2007
    Date of Patent: January 14, 2014
    Assignee: Thales
    Inventors: François Coulmeau, François Hoofd
  • Publication number: 20130325222
    Abstract: The present invention relates to an automatic recovery method for an unmanned aerial vehicle (UAV), and more particularly to a vision-based automatic recovery method for an unmanned aerial vehicle (UAV) using a reference trajectory, in which information from a front vision camera and information from navigation equipment embedded in the unmanned aerial vehicle are combined by a weighting method. The vision-based automatic recovery method using a reference trajectory for an unmanned aerial vehicle includes a reference trajectory generating step of generating the reference trajectory connecting an align point and a recovery point on an on-board based on the recovery point given to the unmanned aerial vehicle through wireless communication; an image processing step of taking an image containing a symbol (e.g.
    Type: Application
    Filed: December 22, 2010
    Publication date: December 5, 2013
    Applicant: KOREA AIR LINES CO., LTD.
    Inventor: Eun Jung Roh
  • Patent number: 8565940
    Abstract: A method of transferring and processing flight data of an aircraft including recording the aircraft flight data in an onboard avionics system in a digital format so as to obtain digital data, the flight data including safety impact flight data and flight data having no recognized effect on safety. The method further includes recording at least the safety impact flight data in the onboard avionics system in an additional format dissimilar to the digital format so as to obtain additional flight data, storing the digital data and the additional flight data separately, transferring the digital data and the additional flight data to a monitoring computer on the ground, displaying the digital data on a screen in the form of display digital data, and transferring the digital data and the additional flight data to a complementary interpretation unit so as to generate one of display data and print data relating to the additional flight data.
    Type: Grant
    Filed: November 3, 2009
    Date of Patent: October 22, 2013
    Assignee: Eurocopter
    Inventors: Carine Roquelaure, Florent Daizé, Mathieu Gester
  • Patent number: 8560150
    Abstract: 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: Grant
    Filed: July 5, 2011
    Date of Patent: October 15, 2013
    Assignee: The Boeing Company
    Inventors: Thomas J. Phillips, Jean M. Crane
  • Patent number: 8548653
    Abstract: A system for aiding piloting of an airplane during a final approach includes current roll angle sensors that measures a current roll angle of the airplane, and a maximum roll angle calculation device that calculates a limit roll angle corresponding to a maximum roll angle at which an end point of the airplane will not strike the ground. The system also includes a display for automatically presenting on a single screen a first characteristic sign illustrating the current roll angle and a second characteristic sign illustrating the limit roll angle. If a potential ground collision is presented by too high of a current roll angle, an alarm may be emitted or automatic control of the airplane may occur to correct the roll angle.
    Type: Grant
    Filed: May 24, 2012
    Date of Patent: October 1, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Stéphane Puig, Martin Delporte, Jérôme Gauvain
  • Patent number: 8543264
    Abstract: A method and aircraft system are provided for determining an optimal gliding speed that maximizes gliding distance of the aircraft upon engine failure, and comprises calculating the optimal gliding speed from a speed polar curve, true airspeed, heading, and vertical wind speed. The polar curve may be constructed with consideration of the aircraft center of gravity and weight. The calculated gliding speed, which may be restricted to a threshold, is provided to the pilot and optionally to an autopilot. The method is repeated periodically, or if the wind vertical or horizontal velocities exceed a threshold for a predetermined period of time.
    Type: Grant
    Filed: April 18, 2012
    Date of Patent: September 24, 2013
    Assignee: Honeywell International Inc.
    Inventor: Jan Tomas
  • Publication number: 20130245861
    Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a calculation step for converting an angular deviation into an equivalent linear deviation, and, conversely, converting a linear deviation into an equivalent angular deviation. The method comprises a step of graphic representation, called unified monitoring, intended for the crew, of a deviation of the aircraft, on a lateral deviation axis and a vertical deviation axis; each of the deviations, lateral and vertical, being able to be represented on a linear scale, an angular scale or a mixed scale.
    Type: Application
    Filed: March 12, 2013
    Publication date: September 19, 2013
    Applicant: THALES
    Inventors: Guilhem PUTZ, Christophe CAILLAUD, Francois COULMEAU
  • Publication number: 20130245862
    Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a step of calculation of an anticipated deviation of the aircraft, expressed linearly or angularly, projected to a time DT, characteristic of a reaction time of the aircraft, and of a statistical error distribution associated with this anticipated deviation; and a step of calculation of a probability of exceeding a predetermined target deviation, by means of the anticipated deviation and of the statistical error distribution. The method also comprises a crew alert when the probability is above a predetermined threshold.
    Type: Application
    Filed: March 12, 2013
    Publication date: September 19, 2013
    Applicant: THALES
    Inventors: Guilhem PUTZ, Christophe CAILLAUD, Francois COULMEAU
  • Publication number: 20130204470
    Abstract: A method and computer program product for planning a landing approach of an aircraft based on an actual position or first nominal position of the aircraft during its approach for landing on a runway, including providing a stabilization flight path section and stabilization region and/or stabilization point defined by an altitude profile by at least one configuration change point in the stabilization flight path section with a change of the overall profile configuration of the airfoils and with a predetermined final approach flight status of the aircraft, and checking or changing position of the at least one configuration change measure in a change and/or the addition of an additional configuration change measure to the stabilization flight path section and by changing a speed profile along the stabilization flight path section so that the aircraft reaches the predetermined final approach flight status in the stabilization region or at the stabilization point.
    Type: Application
    Filed: January 23, 2013
    Publication date: August 8, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Patent number: 8498761
    Abstract: A system allows conventional, unprepared fixed-wing aircraft to land safely on very small, unprepared areas, enabling an aerodynamic capacitance in which the airplanes can fly in a controlled manner against coherent air current, being assisted by a combined system including both the air current control mechanisms and the automatic flight control system of the aircraft.
    Type: Grant
    Filed: July 16, 2010
    Date of Patent: July 30, 2013
    Assignee: Universidad Politecnica de Madrid
    Inventors: José Patricio Gómez Pérez, Ignacio Gómez Pérez, Antonio Monteagudo López De Sabando