With Indication Or Control Of Take-off Patents (Class 701/15)
  • Patent number: 10293951
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a control unit to command the gas turbine engine to perform one of a rolling takeoff procedure and an unrestricted takeoff procedure. The control unit is configured command the gas turbine engine to perform the rolling takeoff procedure when information required to determine whether the unrestricted takeoff procedure can be performed is unavailable to the control unit.
    Type: Grant
    Filed: March 17, 2016
    Date of Patent: May 21, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew R. Feulner, Ronald S. Walther
  • Patent number: 10281913
    Abstract: An example method for predictive take-off rejection (TOR) of an aircraft includes receiving, at a computing device on the aircraft and at a time before the aircraft takes off for a current flight, outputs from a plurality of sensors positioned on the aircraft, comparing the outputs received from the plurality of sensors for the current flight to reference flight data, based on comparing the outputs received from the plurality of sensors for the current flight to the reference flight data the computing device making a determination of whether to initiate a TOR procedure before the aircraft reaches a takeoff speed on a runway, and based on determining to initiate the TOR procedure, the computing device sending a signal to a control device on the aircraft to initiate the TOR procedure.
    Type: Grant
    Filed: August 14, 2017
    Date of Patent: May 7, 2019
    Assignee: The Boeing Company
    Inventors: Jian Dong, Naveed Moayyed Hussain
  • Patent number: 10266162
    Abstract: The present disclosure relates to a method of controlling the braking of an aircraft equipped with a landing gear bearing braked wheels, the aircraft being propelled by jet engines and equipped with a thrust reversal system, the method involving the steps of estimating the grip/adhesion of the braked wheels and activating the thrust-reversal system or modulating the reverse-thrust generated by the thrust-reversal system if this system is already activated, based on the estimated grip/adhesion.
    Type: Grant
    Filed: June 18, 2018
    Date of Patent: April 23, 2019
    Assignees: Safran Nacelles, Safran Landing Systems
    Inventors: Patrick Gonidec, Hakim Maalioune, François Taillard, Denis Jontef, Marie-Laure De-Crescenzo, Jean-François Hammann
  • Patent number: 10109208
    Abstract: A system and method for determining the distance between at least one point on a vehicle and at least one projected area off of the vehicle includes receiving, with a processor, sensor signals indicative of LIDAR data for the projected area off the vehicle; applying, with the processor, a linear estimation algorithm to filter out noise within the LIDAR data and define a surface plane for the projected area; evaluating, with the processor, the LIDAR data against a vehicle state model; determining, with the processor, the distance between the at least one point on the vehicle and the at least one projected area off the vehicle; and commanding a response in the vehicle controls.
    Type: Grant
    Filed: October 27, 2016
    Date of Patent: October 23, 2018
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Igor Cherepinsky, Jason C. Derenick, Joshua M. Leland, Christopher Stathis, Brigid A. Blakeslee
  • Patent number: 10001776
    Abstract: An onboard system for controlling flight of an unmanned aerial vehicle. The system comprises: a flight management system configured for controlling flight of the unmanned aerial vehicle; a mission control module configured to send commands to the flight management system for guiding the unmanned aerial vehicle to perform a mission; a safety module configured to communicate commands to the flight management system for guiding the unmanned aerial vehicle to fly in a safe mode; a communication control component which is switchable between a mission state in which the flight management system receives commands from the mission control module and a safety state in which the flight management system receives commands from the safety module; and a monitor module configured to determine whether a trigger condition warranting a change in mode is present or not and to cause the communication control component to switch from the mission state to the safety state when the trigger condition is present.
    Type: Grant
    Filed: March 21, 2016
    Date of Patent: June 19, 2018
    Assignee: The Boeing Company
    Inventor: Murali Rangarajan
  • Patent number: 9926078
    Abstract: A method for automatically delivering a physical mail includes receiving, by an unmanned aerial vehicle from an unmanned aerial vehicle management system, a delivery information, the delivery information includes information about a first secure mailbox and information about a second secure mailbox, the first secure mailbox being related to a first target user, delivering the physical mail to the first secure mailbox, and rerouting the unmanned aerial vehicle carrying the physical mail from the first secure mailbox to the second secure mailbox in response to the physical mail being delivered to the first secure mailbox.
    Type: Grant
    Filed: November 4, 2015
    Date of Patent: March 27, 2018
    Assignee: International Business Machines Corporation
    Inventors: Simone Bonazzoli, Marco Borgianni, Claudio Falcone, Alessio Fioravanti, Giuseppe Longobardi, Silvano Lutri, Luigi Presti, Paolo Salerno, Alessandro Tomasi, Francesca Ziantoni
  • Patent number: 9749540
    Abstract: There is provided a control device including an image display unit configured to acquire, from a flying body, an image captured by an imaging device provided in the flying body and to display the image, and a flight instruction generation unit configured to generate a flight instruction for the flying body based on content of an operation performed with respect to the image captured by the imaging device and displayed by the image display unit.
    Type: Grant
    Filed: March 27, 2014
    Date of Patent: August 29, 2017
    Assignee: SONY CORPORATION
    Inventors: Kohtaro Sabe, Yasunori Kawanami, Kenta Kawamoto, Tsutomu Sawada, Satoru Shimizu, Peter Duerr, Yuki Yamamoto
  • Patent number: 9738401
    Abstract: Visual landing aids including a series of contrasting circles and polygons for unmanned aerial vehicles that are capable of being accurately detected over a wide range of angles and distances by an unmanned aerial vehicle equipped with a camera and shape detection capabilities. The visual landing said may be implemented using contrasting colors for the pattern which reflect visible and/or UV or infrared light, or by light emitting elements. In some examples, the landing aids includes a secondary smaller version of the landing aid shape pattern that is embedded within the larger pattern, to enable greater detection range while facilitating close-in precision guidance. In still further examples, light emitting elements may be pulsed at a rate that is synchronized with the camera shutter on the unmanned aerial vehicle to further enhance accurate detection.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: August 22, 2017
    Inventors: Jordan Holt, Jeremy Sarao, Alex Barchet
  • Patent number: 9728092
    Abstract: A method of determining the speed of the wind to be taken into account for determining a maximum authorized takeoff weight of an aircraft. A measured speed TASmes of the local wind is calculated from at least one current speed TASinst of the local wind and an observed speed TASobs of the local wind on the basis of weather observations and on the basis of a heading value. The measured speed TASmes is compared with the observed speed TASobs in order to determine a calculated speed TASperfo of the local wind while also making use of at least one instability criterion of the local wind as supplied by the weather observations and weather forecasts. The calculated speed TASperfo is then for taking into account in order to optimize the maximize authorized takeoff weight of the aircraft.
    Type: Grant
    Filed: January 14, 2016
    Date of Patent: August 8, 2017
    Assignee: AIRBUS HELICOPTERS
    Inventors: Etienne Poudrai, Nicolas Certain, Bernard Spinosi
  • Patent number: 9676488
    Abstract: A system and method for controlling a tail-sitter aircraft, includes determining a mode of operation for the aircraft; operating each of a large turbine engine and a small turbine engine to provide total aircraft power during hover or high-power mode of operation; and selectively providing aircraft power from the small turbine engine to a plurality of rotors during a long-range endurance cruise mode of operation.
    Type: Grant
    Filed: June 9, 2015
    Date of Patent: June 13, 2017
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Mark R. Alber
  • Patent number: 9443434
    Abstract: Systems and methods for processing aircraft flight information and flight plan information are described. Specific techniques are described for managing flight data in real time, sharing flight data between a plurality of systems, dynamically managing flight information, generating flight plan information, providing flight plan information to a user, and closing flight plan discontinuities.
    Type: Grant
    Filed: September 30, 2014
    Date of Patent: September 13, 2016
    Assignee: The Boeing Company
    Inventors: Ryan D. Hale, Louis J. Bailey
  • Patent number: 9327842
    Abstract: A method for sensing a takeoff of an aircraft includes receiving a rate of change in vertical motion of the aircraft, determining whether the rate of change in vertical motion of the aircraft exceeds a first threshold, integrating the rate of change in vertical motion of the aircraft and outputting a virtual altitude signal, responsive to receiving the indication that a portion of the aircraft is contacting a surface, delaying the virtual altitude signal through a discrete low pass filter and outputting a delayed virtual altitude signal, subtracting the delayed virtual altitude signal from the virtual altitude signal to output an altitude perturbation signal, determining whether the altitude perturbation signal exceeds a second threshold value, and outputting an indication that the portion of the aircraft is not contacting the surface responsive to the rate of change in the vertical motion of the aircraft and the altitude perturbation signal.
    Type: Grant
    Filed: April 8, 2015
    Date of Patent: May 3, 2016
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Karim Khial, James J. Howlett, Vineet Sahasrabudhe, Naji S. Yakzan
  • Patent number: 9280904
    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: Grant
    Filed: March 15, 2013
    Date of Patent: March 8, 2016
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Thierry Bourret, Pascale Louise, Claire Ollagnon, Nicolas Chauveau, Sebastien Giuliano, Sebastien Drieux
  • Patent number: 9254926
    Abstract: To provide a warning system that can issue a stall warning taking a flight environment into account. The warning system according to the present invention is a warning system for an aircraft, for issuing a warning in the case where there is a possibility of the aircraft stalling, and includes a selecting section for selecting one of two or more calculation criteria based on an icing state of the aircraft, a calculating section for calculating a stall angle based on the selected calculation criterion, and a warning section for comparing the calculated stall angle with a current angle of attack of the aircraft and issuing a stall warning if the current angle of attack exceeds the stall angle.
    Type: Grant
    Filed: February 27, 2014
    Date of Patent: February 9, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Naoto Maeda, Masaya Miyoshi
  • Patent number: 9056669
    Abstract: The present disclosure endeavors to provide systems, methods and apparatus for ensuring aircraft compliance with governmental guidelines, such as, for example, Missile Technology Control Regime (MTCR) Category II compliance. A hardware-based system may be employed to reduce range and/or payload below predetermined ranges and a payload capacities. Also provided herein are hardware-based systems, methods, and apparatus for restricting a system's range to predetermined range and/or the payload to a predetermined limit using, for example, an Application-Specific Integrated Circuit (ASIC) installed in the flight control system.
    Type: Grant
    Filed: October 1, 2012
    Date of Patent: June 16, 2015
    Assignee: Aurora Flight Sciences Corporation
    Inventors: Tom Washington, Thorsten Hisam, Martin Gomez
  • Patent number: 9031720
    Abstract: A method and system for the prediction of aircrafts vertical trajectory, in particular for Air Traffic Management, using the following flight calculation modules: Take-off; Climb; Cruise; Descent; and Landing, corresponding to the relevant flight phases, in which: the calculation of the predicted aircraft trajectory is effected by using a set of TEM equations using, as output variables, the vertical rate of climb or descent, the true air speed, the energy share factor, the thrust and the drag, the mass of the aircraft modeled as point-mass, and using, as input variables, the Mach number depending on true air speed and temperature and altitude, the gravity acceleration, and the fuel flow, and the flight path angle; the calculation of the predicted aircraft trajectory for Cruise phase, wherein only the mass is varies, is performed by using the following analytical solution to said set of TEM equations.
    Type: Grant
    Filed: December 13, 2011
    Date of Patent: May 12, 2015
    Assignee: Selex Sistemi Integrati S.p.A.
    Inventors: Domenico Accardo, Antonio Moccia, Michele Grassi, Urbano Tancredi, Lucio Caminiti, Luigi Fiorillo, Alberto Leardi, Giuseppe Maresca
  • Patent number: 9026274
    Abstract: An apparatus is described comprising: at least one processor; and memory storing instructions that, when executed by the at least one processor, cause the apparatus to: regulate an operation of a motor based at least in part on a control imposed on an output torque of the motor and a rate of change of a speed of the motor.
    Type: Grant
    Filed: August 31, 2012
    Date of Patent: May 5, 2015
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Jonathan Hartman, Timothy Fred Lauder, Russell L. Halstead, Christopher L. Winslow, Michael L. Hardy
  • Patent number: 9020666
    Abstract: The taking-off and landing target instrument 2 to be used in an automatic taking-off and landing system, comprising a target 37 having as many light emitting elements 44 as required for displaying patterns and a target control unit 38 for controlling light emission of the light emitting elements, wherein the light emitting elements are provided on a taking-off and landing surface of the target and are arranged so that a target mark 43 having the center of pattern under all turned-on status is formed, and wherein the target control unit controls a light emission so as to display firstly all turned-on patterns where all of the light emitting elements are turned on, and next, so as to display the light emitting elements in a predetermined pattern.
    Type: Grant
    Filed: April 23, 2012
    Date of Patent: April 28, 2015
    Assignee: Kabushiki Kaisha TOPCON
    Inventors: Fumio Ohtomo, Kazuki Osaragi, Hitoshi Otani
  • 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: 8996206
    Abstract: An aircraft power plant (2) having at least two engines (3, 4), each co-operating with respective control means (5) including respective memories (6), each memory (6) containing information for causing said engine (3, 4) to operate with a plurality of distinct utilization envelopes at iso-damage. Said power plant (2) includes determination means (10) for determining a first utilization envelope (101) for application during a takeoff stage of flight and a second utilization envelope (102) for application during a cruising stage of flight following the takeoff stage of flight, and a third utilization envelope (103) for application during a landing stage of flight following the cruising stage of flight.
    Type: Grant
    Filed: January 9, 2013
    Date of Patent: March 31, 2015
    Assignee: Airbus Helicopters
    Inventors: Jean Philippe Evrard, Alban Corpron
  • 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: 8983687
    Abstract: 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: Grant
    Filed: March 13, 2012
    Date of Patent: March 17, 2015
    Assignee: The Boeing Company
    Inventors: Stephan G. Hunter, Steven James Churchill
  • Patent number: 8977413
    Abstract: Methods of illustrating one or more derated takeoffs of an aircraft on a runway where such illustrations are on a flight display in a cockpit of the aircraft and are based on various information and may allow pilots to make more accurate decisions related to derated takeoffs and full thrust takeoffs of the aircraft.
    Type: Grant
    Filed: March 7, 2012
    Date of Patent: March 10, 2015
    Assignee: GE Aviation Systems LLC
    Inventors: Timothy Donal Paul Burns, Aaron James Gannon, Dashiell Matthews Kolbe, Darrin Walter Wargacki, Gerhard Walter Moeller
  • Patent number: 8948937
    Abstract: Method and device for an optimal management of the energy of an aircraft. The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state and according to a management strategy, optimal commands of means (S1,S2, S3, S4, S5, S6) for controlling the energy of the aircraft, which allow the aircraft to reach a given point of a trajectory in a given operational state.
    Type: Grant
    Filed: July 26, 2012
    Date of Patent: February 3, 2015
    Assignee: Airbus Operations SAS
    Inventors: Florian Constans, Mickael Lefebvre
  • 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: 20140379178
    Abstract: A method for fine positioning of a vertical takeoff and landing (VTOL) vehicle comprises: receiving a command to execute a bump, wherein a bump is a movement of the vehicle by a bump distance in a singular direction, wherein the bump distance is a pre-determined distance moved by the vehicle in a bump; generating a control signal based on the command to execute a bump, wherein the control signal causes a vertical takeoff and landing (VTOL) vehicle to move a bump distance.
    Type: Application
    Filed: June 24, 2013
    Publication date: December 25, 2014
    Inventors: Emray Rein Goossen, Katherine Goossen
  • Patent number: 8909395
    Abstract: A system and method for aircraft performance predictions for climb flight phase is disclosed. In one embodiment, a method of aircraft performance predictions for climb flight phase in a flight management system (FMS) includes determining current predicted aircraft state using a total energy of the aircraft. Further, excess energy available in an engine of the aircraft is computed. Furthermore, a change of speed of the aircraft is computed at a given point in the climb flight phase. Kinetic energy (KE) change required is then computed for the computed speed change. Remaining energy available is then computed based on the computed KE change. The aircraft performance predictions for the climb flight phase are then computed using the determined current predicted aircraft state.
    Type: Grant
    Filed: April 28, 2012
    Date of Patent: December 9, 2014
    Assignee: Airbus Engineering Centre India
    Inventors: Veeresh Kumar Mn, Dinesh Kumar Kushwaha, Chaitanya Pavan Kumar
  • Patent number: 8897933
    Abstract: Methods and systems disclosed herein relate to using a rotating flywheel battery in a balloon in a high-altitude balloon network. An example method could include converting, in a balloon, first electrical energy into kinetic mechanical energy. The balloon includes a flywheel battery configured to rotate about a spin axis. The kinetic mechanical energy includes a rotation motion of the flywheel battery. The method could further include storing the kinetic mechanical energy for a finite period of time. Further, the method could include performing, using the flywheel battery, at least one of: i) converting at least a portion of the stored kinetic mechanical energy into second electrical energy; ii) stabilizing at least one motion of the balloon based on the rotational motion of the flywheel battery; and iii) rotating the balloon substantially about a balloon axis substantially perpendicular to the ground surface of the earth.
    Type: Grant
    Filed: May 14, 2012
    Date of Patent: November 25, 2014
    Assignee: Google Inc.
    Inventors: Eric Teller, Richard Wayne DeVaul, Clifford L. Biffle
  • Patent number: 8886402
    Abstract: Methods and apparatus are provided for an actively variable shock absorbing system for actively controlling the load response characteristics of a shock absorbing strut. In one embodiment the shock absorbing system comprises a controllable valve adapted for actively varying a load response characteristic of the shock absorbing strut. The shock absorbing system further comprises an electronic control system comprising an input for receiving a signal from a sensor, an algorithm adapted to determine an optimal position for the controllable valve in view of the sensor signal, and an output for sending a control signal to the controllable valve to place the valve in the optimal position.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: November 11, 2014
    Assignee: Armorworks Enterprises LLC
    Inventor: Ken-An Lou
  • Patent number: 8886450
    Abstract: The present invention is directed to a system and method for identifying maneuvers for a vehicle in conflict situations. A plurality of miss points are calculated for the vehicle and as well as object conditions at which the vehicle will miss an impact with the at least one other object by a range of miss distances. The miss points are displayed such that a plurality of miss points at which the vehicle would miss impact by a given miss distance indicative of a given degree of conflict is visually distinguishable from other miss points at which the vehicle would miss impact by greater miss distances indicative of a lesser degree of conflict. The resulting display indicates varying degrees of potential conflict to present, in a directional view display, a range of available maneuvers for the vehicle in accordance with varying degrees of conflict.
    Type: Grant
    Filed: February 20, 2007
    Date of Patent: November 11, 2014
    Assignee: Commonwealth Scientific and Industrial Research Organisation
    Inventors: David John Gates, Elliot Ashley Gates, Mark Westcott, Neale Leslie Fulton
  • Patent number: 8868264
    Abstract: A power plant (2) having at least one engine (3, 4) and control means (5) for controlling said engine (3, 4). The control means (5) include a memory (6), said memory (6) containing information for operating said engine (3, 4) in accordance with at least two distinct utilization envelopes during a maximum number of flying hours, the two envelopes comprising an envelope enabling takeoff from a platform and another envelope enabling takeoff from takeoff zones not including platforms, each utilization envelope comprising at least two distinct utilization ratings each defined by a developed power and by a utilization duration for said developed power.
    Type: Grant
    Filed: October 17, 2011
    Date of Patent: October 21, 2014
    Assignee: Airbus Helicopters
    Inventor: Emmanuel Camhi
  • Patent number: 8868265
    Abstract: An aircraft system and method provide visual input to a pilot during takeoff roll. A runway centerline line vector is determined from a captured image, a displacement of the aircraft from the centerline line vector and an aircraft line vector are determined from the image based on the knowledge of sensor characteristics. The runway centerline line vector and the aircraft line vector are displayed to indicate a direction in which the pilot may change heading to maintain the aircraft on the runway.
    Type: Grant
    Filed: November 30, 2011
    Date of Patent: October 21, 2014
    Assignee: Honeywell International Inc.
    Inventors: Ondrej Koukol, Tomas Beda, Jan Lukas
  • Patent number: 8855838
    Abstract: The invention relates to an automatic takeoff method for an aircraft with a flexible airfoil, comprising a carriage suspended by rigging lines from an airfoil. According to said method: —said carriage is provided with an autopilot controlling actuators that control said rigging lines; —said airfoil is provided with an airfoil attitude sensor, comprising a biaxial accelerometer and a biaxial rate gyro, capable of defining the position of an airfoil reference frame in relation to the ground, and means for communicating with said autopilot; —during takeoff, information is received from said airfoil attitude sensor and transmitted to said autopilot for the purpose of controlling said actuators. The invention also relates to an airfoil for the implementation of said method, comprising an airfoil attitude sensor with an inertial unit with a biaxial accelerometer and a biaxial rate gyro, and means for communicating with an autopilot. The invention further relates to an aircraft comprising such an airfoil.
    Type: Grant
    Filed: October 28, 2009
    Date of Patent: October 7, 2014
    Assignee: Swissavia SA
    Inventor: Bernard Berthier
  • Patent number: 8849477
    Abstract: 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.
    Type: Grant
    Filed: October 14, 2008
    Date of Patent: September 30, 2014
    Assignee: Honeywell International Inc.
    Inventor: Ron Brinkman
  • Patent number: 8849476
    Abstract: The present invention relates to a method of updating an ATC flight plan of an aircraft in real time to take account of the flight directives. A reference flight plan is designated. In tandem with the receipt of the flight directive messages originating from the ground, then verifying validity of the flight directive messages, if the message is validated in the affirmative, the messages are applied successively to the reference flight plan and stored. Managing, in real time, the complete list of these flight directives and the ATC flight plan.
    Type: Grant
    Filed: December 14, 2007
    Date of Patent: September 30, 2014
    Assignee: Thales
    Inventor: François Coulmeau
  • Patent number: 8849481
    Abstract: Systems and methods for navigation of a vehicle may carry out one or more operations including, but not limited to: obtaining coordinates of a vector connecting two points in space using carrier phase measurements from global navigation system satellites (GNSS); setting the vector as an intended path of a vehicle; storing carrier phase signals from a GNSS receiver received at a first position of the vehicle; receiving carrier phase signals from a GNSS receiver at a second position of the vehicle; and determining a position of the vehicle relative to the intended path from one or more carrier phase signals received at the second position and one or more stored carrier phase signals received at the first position.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: September 30, 2014
    Assignee: Rockwell Collins, Inc.
    Inventors: Vladislav Gavrilets, Patrick Hwang, Gary McGraw
  • Patent number: 8843254
    Abstract: Systems and methods are disclosed for detection of dragging brakes for use in, for example, an aircraft. A method is provided comprising calculating, by a brake controller, a slip ratio based upon an aircraft speed and a speed of an aircraft wheel, determining, by the brake controller, that the slip ratio is above a threshold value, and sending, by the brake controller and in response to the slip ratio being above the threshold value, a dragging brake signal to an aircraft component.
    Type: Grant
    Filed: July 11, 2012
    Date of Patent: September 23, 2014
    Assignee: Goodrich Corporation
    Inventors: Eric D. Cahill, Dale Prentice
  • Patent number: 8825234
    Abstract: A method and apparatus for managing a touch screen system. Data generated by an acceleration detector about acceleration of the touch screen system is received. The acceleration detector is located within the touch screen system. An action is initiated by an input manager when the acceleration of the touch screen system reduces usability of the touch screen system.
    Type: Grant
    Filed: October 15, 2012
    Date of Patent: September 2, 2014
    Assignee: The Boeing Company
    Inventors: Jeffrey L. Williams, Susan Anne Foster, Jason W. Clark, Samantha Ann Schwartz, Aaron Daniel Pilcher
  • Patent number: 8812223
    Abstract: System and methods are provided alerting an aircraft crew member of a runway assignment for an aircraft takeoff sequence from a runway of an airport having a plurality of runways. In an embodiment, the method includes transmitting data comprising data relating to the runway assignment and data relating to an open status or a closed status for each airport runway to an aircraft data receiver, and transmitting an audio signal indicating the runway assignment to an aircraft audio receiver. In another embodiment, the method includes receiving an audio signal indicating the runway assignment from a control tower audio transmitter, receiving data comprising data relating to the runway assignment and data relating to an open status or a closed status of each of the airport runways from a control tower data transmitter, processing the received data, and displaying the received data relating to the runway assignment on a display.
    Type: Grant
    Filed: January 23, 2007
    Date of Patent: August 19, 2014
    Assignee: Honeywell International Inc.
    Inventors: Billy J. Durham, Brian J. Smith
  • Publication number: 20140214246
    Abstract: Systems and methods for verifying that the flight crew has not made an error in entering takeoff flight performance data into the flight management system (FMS) using the electronic flight bag (EFB). The EFB includes a user interface that receives basic flight plan information and a processor. The processor automatically receives calculated takeoff performance data based on a previously entered basic flight plan, automatically receives user-entered takeoff performance data from a flight management system (FMS) located on a host aircraft, automatically compares the calculated takeoff performance data to the received takeoff performance data, and generates an entry error indication, if the comparison indicates that at least a portion of the entered takeoff performance data does not match the calculated takeoff performance data. An output device outputs the generated entry error indication.
    Type: Application
    Filed: January 28, 2013
    Publication date: July 31, 2014
    Applicant: HONEYWELL INTERNATIONALL INC.
    Inventors: Steve Johnson, Yasuo Ishihara, Kevin J. Conner, Robert A. Champion
  • Patent number: 8793040
    Abstract: The Climb-Optimized Takeoff System is an aircraft functionality aimed at improving the takeoff performance. The improvement is obtained by allowing the airplane to rotate to an optimized pitch attitude at and after VR, while ensuring that the minimum required takeoff climb gradients and the geometric limitations of the airplane are being respected. The optimum takeoff performance is obtained by granting that the airplane pitch attitude, instead of being limited by a single takeoff constraint (such as a given pitch to avoid tail strike) is being tracked to its instantaneous, most constraining limit during the air transition phase (d2).
    Type: Grant
    Filed: June 10, 2011
    Date of Patent: July 29, 2014
    Assignee: Embraer S.A.
    Inventors: Patrice London Guedes, Ricardo Wallach, Guilherme Maximiliano Verhalen, Salvador Jorge da Cunha Ronconi
  • Patent number: 8773289
    Abstract: A method and apparatus are present for monitoring a runway. Data is received about the runway from a number of sensors associated with an aircraft while the aircraft performs an operation on the runway. A number of conditions are identified for the runway using the data received from the number of sensors.
    Type: Grant
    Filed: March 24, 2010
    Date of Patent: July 8, 2014
    Assignee: The Boeing Company
    Inventors: Jeanne C. Maggiore, Wayne R. Majkowski, Kevin L. Swearingen
  • Publication number: 20140163784
    Abstract: A system and method for graphically creating an approach course on a navigation display is provided. A processor operatively coupled to a display and is configured to generate an approach course by (1) generating a graphical representation of at least one terminal area procedure, (2) selecting the at least one terminal area procedure on the display, and (3) displaying the approach course including the at least one terminal area procedure. The approach course is then accepted and inserted into a flight plan.
    Type: Application
    Filed: December 7, 2012
    Publication date: June 12, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: Sudarshan Parthasarathy
  • Patent number: 8736633
    Abstract: A method and system is described for enhancing ground situational awareness to an aircrew via the display of an airport moving map within an own-ship, including determining the position of the own-ship and an aircraft on one of a taxiway, a runway, or an apron, displaying each of the own-ship and the aircraft on an airport moving map by displaying for each a first symbol that indicates the location on the airport moving map; and displaying a second symbol that changes in transparency in proportion to the range of the airport moving map.
    Type: Grant
    Filed: November 9, 2011
    Date of Patent: May 27, 2014
    Assignee: Honeywell International Inc.
    Inventor: Saravanakumar Gurusamy
  • Patent number: 8731745
    Abstract: A method of generating a test sequence diagram includes: linking a first action of the plurality of actions with a second action of the plurality of actions and generating a test sequence diagram which maintains the linking.
    Type: Grant
    Filed: July 1, 2008
    Date of Patent: May 20, 2014
    Assignee: Aerojet Rocketdyne of DE, Inc.
    Inventors: Steven C. Fisher, Tim Brodeur
  • Patent number: 8732233
    Abstract: An electronic flight bag apparatus includes an electronic flight bag (EFB) system installed in an aircraft and which interfaces with a ground network, and a portable EFB device connectible with the EFB system via a trusted secure connection. This apparatus makes it possible for a flight crew member to remove the portable device from the aircraft, enter flight information into the device in a convenient manner, and transfer the information to the installed EFB system. Auxiliary crew members may use the portable device during flight to assist the flight crew.
    Type: Grant
    Filed: July 13, 2005
    Date of Patent: May 20, 2014
    Assignee: The Boeing Company
    Inventor: David L. Allen
  • Patent number: 8712744
    Abstract: A method and apparatus for simulating effects of threats to aircraft communications. A simulation of an aircraft environment is run with the aircraft communications in an aircraft communications network in the aircraft environment. A number of conditions is introduced. The number of conditions comprises a threat configured to affect the aircraft communications in the aircraft communications network in an undesired manner. A change in traffic flow of aircraft in an airspace in the aircraft environment is identified in response to the number of conditions.
    Type: Grant
    Filed: May 12, 2011
    Date of Patent: April 29, 2014
    Assignee: The Boeing Company
    Inventors: Radhakrishna G. Sampigethaya, Radha Poovendran
  • Patent number: 8700236
    Abstract: Flight entries in a flight logbook maintained on a flight server are automatically generated using a remote location-aware mobile device. The remote location-aware device automatically detects aircraft takeoff and landing. The flight server posts designated flight information from the flight logbook to a plurality of social networks.
    Type: Grant
    Filed: January 18, 2012
    Date of Patent: April 15, 2014
    Inventor: Eric R. Berman
  • 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: 8688363
    Abstract: A system is provided for controlling the speed of an aircraft during a deceleration segment between a first state associated with a first speed and a first time and a second state associated with a second speed and a second time. The system includes a navigation system configured to determine the first state; a guidance system configured to determine the second state; and an active deceleration system coupled to the navigation system and the guidance system and configured to construct the deceleration segment between the first state and the second state with at least one intermediate speed between the first speed and the second speed.
    Type: Grant
    Filed: April 27, 2011
    Date of Patent: April 1, 2014
    Assignee: Honeywell International Inc.
    Inventors: Jiri Svoboda, Mike Jackson, Michal Polansky, Erwan Paricaud