Compensation For Environmental Conditions Patents (Class 701/10)
  • 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: 8818705
    Abstract: In general, a method performed on a vehicle includes determining that the vehicle is located within a predetermined range of a beacon, the beacon being associated with a beacon identification, navigating the vehicle to a first location based on determining that the vehicle is located with the predetermined range, generating a first report based on determining that the vehicle is located at the first location, the generating including: specifying the beacon identification, recording navigation data that includes an altitude, a distance from the beacon, and a bearing relative to the beacon, and recording environmental data. The method further includes transmitting the first report from the vehicle to a base station, the first report including the beacon identification, the navigation data, and the environmental data.
    Type: Grant
    Filed: April 20, 2012
    Date of Patent: August 26, 2014
    Assignee: Accenture Global Services Limited
    Inventor: Gregory P. Spata
  • Patent number: 8786467
    Abstract: A method and a system for displaying an airport or runway moving map with traffic information on a display screen in the cockpit or flight deck of an aircraft. Symbology representing surface and near-surface aircraft and surface vehicle traffic and associated traffic data are filtered to prevent or limit clutter on the display screen. Traffic symbology is automatically and manually filtered to display only relevant traffic. Traffic data is selectively displayed and displayed as/when relevant or needed. The displayed traffic information may be derived from automatic dependent surveillance-broadcast, traffic information system-broadcast, automatic dependent surveillance-rebroadcast, traffic collision avoidance system or other source.
    Type: Grant
    Filed: March 18, 2011
    Date of Patent: July 22, 2014
    Assignee: The Boeing Company
    Inventors: Samuel T. Clark, Roglenda R. Bowe, Stephen Bernard Ortman, Jean Marie Crane
  • Patent number: 8788188
    Abstract: The different advantageous embodiments provide a system comprising a weather band selection process and a processor unit. The processor unit is configured to run the weather band selection process. The weather band selection process identifies a flight trajectory associated with an aircraft, identifies weather information for the flight trajectory, and identifies a weather band selection for the aircraft using the flight trajectory, aircraft information and the weather information.
    Type: Grant
    Filed: April 16, 2012
    Date of Patent: July 22, 2014
    Assignee: The Boeing Company
    Inventor: Louis J. Bailey
  • 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: 8774987
    Abstract: A method for vertical gust suppression due to turbulence for an aircraft having at least one of direct lift control surfaces or pitch control surfaces. The method includes sensing atmospheric turbulence, measuring the sensed atmospheric turbulence to generate turbulence data, generating a command based on the turbulence data, and applying the command to aircraft controls to actuate the direct lift control surfaces or the pitch control surfaces based on the turbulence data. Therefore, an aircraft response to the actuation of the direct lift control surfaces or the pitch control surfaces reduces a vertical acceleration, a pitch acceleration, a pitch rate, a pitch attitude or a structural load of the aircraft due to the turbulence. Thus, the method reduces the effects of vertical gusts of wind on the aircraft, improves the comfort level for aircraft passengers and crew, and reduces diversions the aircraft may take to avoid the turbulence.
    Type: Grant
    Filed: December 17, 2007
    Date of Patent: July 8, 2014
    Assignee: The Boeing Company
    Inventors: Vincent M. Walton, Christopher J. Borland, Tze L. Siu, Kioumars Najmabadi, Edward E. Coleman, David P. Marquis, Dianne L. McMullin, Kevin H. Milligan
  • 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
  • Patent number: 8768598
    Abstract: An engine control system having an engine, a digital engine control, and a gain logic disposed within the digital engine control for use with an aircraft. The digital engine control is configured to receive and process inputs from systems within the aircraft. Gain logic uses the inputs to generate command data to regulate the performance of the engine so as to allow rotor speed deviations from a set point.
    Type: Grant
    Filed: December 26, 2011
    Date of Patent: July 1, 2014
    Assignee: Textron Innovations Inc.
    Inventor: James M. McCollough
  • Patent number: 8751070
    Abstract: Disclosed is a method and system for aiding the piloting of an aircraft to climb to a safety altitude situated above an existing low-height flight trajectory comprised of a lateral trajectory and a vertical trajectory, in which the safety altitude is the altitude of the aircraft that avoids collision of the aircraft with surrounding terrain. The aircraft is guided along the existing lateral trajectory of the low-height flight trajectory in a horizontal plane; and the aircraft is brought to the safety altitude by subjecting the aircraft to a climb mode in a vertical plane, which causes the aircraft to climb according to a climb slope which is greater than or equal to a maximum slope according to the existing vertical trajectory of the low-height flight trajectory.
    Type: Grant
    Filed: February 13, 2007
    Date of Patent: June 10, 2014
    Assignee: Airbus Operations SAS
    Inventors: Fabien Silly, Pascale Louise-Babando, Vincent Markiton
  • Patent number: 8725322
    Abstract: A method and device are provided for determining a target altitude for an emergency descent of an aircraft that is to be reached by the end of the emergency descent. The device determines an updated target altitude which takes into account variations of barometric pressure and which is able to replace the target altitude that must be reached at the end of the emergency descent. The method includes determining an initial target altitude representative of the initial position of the aircraft and then repeatedly determining a current target altitude along a reference horizontal distance. The current target altitude is compared to the initial target altitude and is used to update the emergency descent if the current target altitude is lower than the initial target altitude.
    Type: Grant
    Filed: July 15, 2011
    Date of Patent: May 13, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Paule Botargues, Erwin Grandperret, Lucas Burel, Thierry Bourret
  • Patent number: 8725321
    Abstract: A system and method for controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces.
    Type: Grant
    Filed: February 18, 2010
    Date of Patent: May 13, 2014
    Assignee: Textron Innovations Inc.
    Inventors: Steven G. Hagerott, James L. Hammer, Philippe A. Ciholas, Mark W. Palmer
  • Patent number: 8718870
    Abstract: A vehicle control system includes an actuator capable of adjusting a behavior of a vehicle, a temperature detecting device configured to detect a temperature of a tire on a wheel of the vehicle, and a control device configured to control the actuator according to the temperature of the tire detected by the temperature detecting device so as to change a degree of suppressing a behavior change of the vehicle by the actuator. Therefore, the vehicle control system can suppress a variation in a driving feeling.
    Type: Grant
    Filed: September 3, 2010
    Date of Patent: May 6, 2014
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventor: Masashi Igarashi
  • Patent number: 8706321
    Abstract: In one embodiment of a method to reduce vertical position errors of an aircraft, a disturbance input acting on the aircraft may be determined. The magnitude of the disturbance may be converted into a delta lift command if the magnitude of the disturbance is outside a criteria. The delta lift command may be post processed. The delta lift command may be converted into symmetric lateral surface position commands for control surfaces. The symmetric lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the symmetric lateral surface position commands.
    Type: Grant
    Filed: August 23, 2012
    Date of Patent: April 22, 2014
    Assignee: The Boeing Company
    Inventors: Brian K. Rupnik, Sean J. Flannigan
  • Patent number: 8700317
    Abstract: A method of calculating Federal Aviation Administration (FAA) published or FAA Air Traffic Control assigned aeronautical holding patterns, comprising the steps of: defining navigational way points using their latitude and longitude coordinates; displaying the latitude and longitude that define the point for an inbound turn; defining four posts of a holding pattern; and showing the actual holding space dimensions along with the non-protected airspace. The method may be performed by a stand-alone electronic device or an electronic device having other functions. The latitude and longitude that define the point for an inbound turn can be displayed as a bearing, and/or as a distance along a radial. The inbound turning point can be calculated using a global positioning or flight management system. A turn may be commanded using an automatic flight control system or flight director.
    Type: Grant
    Filed: March 11, 2013
    Date of Patent: April 15, 2014
    Assignee: Epoch Flight Systems LLC
    Inventors: Bruce Gary Wilder, Otto Charles Wilke
  • Patent number: 8698654
    Abstract: A vehicle display system diminishes specified display features when in a taxi mode. EV images, SV images, and avionics symbology are displayed, with certain of the images and symbology being diminished when in a taxi mode. Additionally, guidance to the runway centerline is displayed in the taxi mode.
    Type: Grant
    Filed: December 28, 2011
    Date of Patent: April 15, 2014
    Assignee: Honeywell International Inc.
    Inventor: Gang He
  • Patent number: 8700306
    Abstract: Autonomous collision avoidance systems for unmanned aerial vehicles are disclosed. Systems illustratively include a detect and track module, an inertial navigation system, and an auto avoidance module. The detect and track module senses a potential object of collision and generates a moving object track for the potential object of collision. The inertial navigation system provides information indicative of a position and a velocity of the unmanned aerial vehicle. The auto avoidance module receives the moving object track for the potential object of collision and the information indicative of the position and the velocity of the unmanned aerial vehicle. The auto avoidance module utilizes the information to generate a guidance maneuver that facilitates the unmanned aerial vehicle avoiding the potential object of collision.
    Type: Grant
    Filed: January 4, 2013
    Date of Patent: April 15, 2014
    Assignee: L-3 Unmanned Systems Inc.
    Inventors: Davis S. Duggan, David A. Felio, Craig S. Askew
  • Patent number: 8676404
    Abstract: In a centralized navigation information management system installed on board an aircraft which is in a current position at a current time, the aircraft having a warning management system and a route management system with means for creating a route plan, the route plan having a future route plan corresponding with the part of the route plan beginning at the current position and at the current time, the system includes: means for creating a task comprising at least one task parameter relating to an item of navigation information, including a task variable corresponding to a condition of execution of the said task, the means for creating a task having means for determining a predicted time meeting the execution condition; and means for detecting a possible inconsistency between the created task and the route plan or the future route plan and for transmitting, when an inconsistency is detected, a message relating to the inconsistency to a first display means of a centralized warning management system to display
    Type: Grant
    Filed: December 28, 2010
    Date of Patent: March 18, 2014
    Assignee: Thales
    Inventors: Nicolas Marty, François Coulmeau, Fabien Guilley
  • Patent number: 8656162
    Abstract: A method to facilitate securing of air-to-ground communications for an aircraft is provided. The method includes receiving security management information at the aircraft via at least one broadband data link prior to takeoff of the aircraft. The security management information is received for ground entities that can be communicatively coupled with the aircraft traveling on a flight path. The method of securing avionics also includes validating the security management information for the ground entities, and storing the validated security management information for the ground entities in the aircraft. The validating and storing of security management information occur prior to takeoff of the aircraft.
    Type: Grant
    Filed: October 22, 2009
    Date of Patent: February 18, 2014
    Assignee: Honeywell International Inc.
    Inventors: Aloke Roy, Michael L. Olive
  • Patent number: 8645007
    Abstract: An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.
    Type: Grant
    Filed: June 8, 2012
    Date of Patent: February 4, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Burkhard Gölling, Rudibert King, Ulrich Notger Heinz, Wolfgang Nitsche
  • Publication number: 20140018980
    Abstract: Systems and methods for flight management are provided. One flight control system is provided that includes a flight management system configured to manage aircraft flight control including at least one of a flight path or an altitude for an aircraft. The flight control system also includes a flight parameter selection module configured to determine a Cost Index (CI) and cruising altitude for use by the flight management system to manage the aircraft flight control, wherein the determination is based on a flight cost and predicted weather along the flight path.
    Type: Application
    Filed: July 12, 2012
    Publication date: January 16, 2014
    Applicant: General Electric Company
    Inventors: Srinivas Bollapragada, Ana Del Amo
  • Patent number: 8629788
    Abstract: A system may include a sensor for coupling with a vehicle configured for atmospheric flight. The sensor may be configured for detecting a turbulence event, where the turbulence event is at least one of experienced by the vehicle or occurs proximal to the vehicle during atmospheric flight. The system may also include a transmitter coupled with the sensor. The transmitter may be configured for automatically remotely transmitting data regarding the turbulence event to a ground based entity.
    Type: Grant
    Filed: August 10, 2010
    Date of Patent: January 14, 2014
    Assignee: Rockwell Collins, Inc.
    Inventors: William T. Greenleaf, Richard S. Dove, Scott F. Bauler, Randy H. Jacobsen, Kirschen A. Seah
  • Patent number: 8600587
    Abstract: A vehicle system for determining an object threat level, includes a display and electronics configured to receive mission context data indicating an operational state of the vehicle. The electronics determines a threat level of the object in response to the mission context data. The electronics determines at least one recommended action in response to the threat level. The electronics provides an indication of the threat level and at least one recommended action to the display.
    Type: Grant
    Filed: September 16, 2010
    Date of Patent: December 3, 2013
    Assignee: Rockwell Collins, Inc.
    Inventors: Kirschen A. Seah, Kevin M. Kronfeld, Jeffery A. Finley
  • Patent number: 8594889
    Abstract: An inclination control method using a torque vectoring system, may include a) detecting a vehicle speed, a steering angle, a yaw rate, and a steering torque of a vehicle, b) determining whether the vehicle may be tending to be inclined according to detected values of the vehicle speed, the steering angle, the yaw rate, and the steering torque, c) determining a torque vectoring duty according to the magnitude of the steering angle and the yaw rate when it may be determined that the vehicle may be tending to be inclined, and d) controlling the torque vectoring system according to the determined torque vectoring duty.
    Type: Grant
    Filed: November 30, 2011
    Date of Patent: November 26, 2013
    Assignee: Hyundai Motor Company
    Inventor: Hee Young Jo
  • Patent number: 8560203
    Abstract: Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.
    Type: Grant
    Filed: July 26, 2011
    Date of Patent: October 15, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Salvatore Calandra, Frederic Giroux, Mark Iacobacci, Martin Chabot, Simon Hartropp, Yusuf Syed, Dariusz Chmiel, Adrienne Bajaj
  • Patent number: 8554392
    Abstract: A method and device for assisting in driving a vehicle in motion along an initial trajectory, in an environment containing at least one obstacle, assistance is carried out by checking, by a trajectory checking unit, during movement of the vehicle, the existence of at least one condition for modifying the initial trajectory to avoid the obstacle. A criteria determining unit is used to determine a criterion CR by which to avoid the obstacle, and an avoidance trajectory determining unit is used to determine an avoidance trajectory according to a derivative of the criterion CR. The vehicle is assisted along the determined avoidance trajectory by a driving assist device.
    Type: Grant
    Filed: June 29, 2009
    Date of Patent: October 8, 2013
    Assignee: Airbus Operations SAS
    Inventor: Xavier Dal Santo
  • Publication number: 20130226375
    Abstract: Systems and methods for updating a scale of a barometric altimeter on aircraft are provided. The method, for example, may include, but is not limited to, receiving, by an aircraft communication system, barometric altimeter scale data corresponding to an atmospheric pressure at an airport, determining, by the processor, if the altitude of the aircraft is below a transition level for the airport, and adjusting, by the processor, the scale of the barometric altimeter based upon the received barometric altimeter scale data when the altitude of the aircraft is below the transition level for the airport.
    Type: Application
    Filed: February 28, 2012
    Publication date: August 29, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Wesley Peter, Sabu Mathew
  • Patent number: 8521365
    Abstract: The invention relates to a device including elements for automatically controlling an aircraft on the ground along the lateral axis, by a dissymmetrical use of the engines and/or brakes of the aircraft.
    Type: Grant
    Filed: March 6, 2009
    Date of Patent: August 27, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Dominique Chatrenet, Fabrice Villaumé, Céline Bourissou, Pierre Scacchi, Louis-Emmanuel Romana
  • Patent number: 8498759
    Abstract: An apparatus determines a condition and relative location of an inner tire and an outer tire of a tire pair. Each tire has an associated tire-based sensor assembly that senses a tire condition, senses acceleration, and transmits, in response to its associated acceleration signal, having a unique tire identification and associated sensed tire condition. A tire rotation sensor senses rotation of the tire pair during vehicle movement and provides a tire rotation signal indicative thereof. A vehicle-based controller associates each of the unique identification signals with one of the inner tire location and the outer tire location responsive to a phase relationship between the received transmitted signals from the tire-based sensor assemblies and the tire rotation signal.
    Type: Grant
    Filed: February 20, 2012
    Date of Patent: July 30, 2013
    Assignee: TRW Automotive U.S. LLC
    Inventor: David L. Juzswik
  • Patent number: 8489279
    Abstract: A damping force control apparatus includes a damping force control device controlling a damping force of a shock absorber provided between a sprung mass and an unsprung mass of each wheel of a vehicle, a detection device detecting at least an acceleration of the sprung mass in an up-down direction and a relative displacement between the sprung mass and the unsprung mass, a damping coefficient calculation device calculating a damping coefficient to be applied to the damping force control by the damping force control device based on detected results of the detection device, a sensed acceleration increment calculation device calculating a sensed acceleration increment corresponding to an increment of sense according to the Weber Fechner law on the basis of the detected results of the detection device, and a modification device modifying the damping coefficient in accordance with a sensed acceleration increment calculated by the sensed acceleration increment calculation device.
    Type: Grant
    Filed: October 26, 2009
    Date of Patent: July 16, 2013
    Assignee: Aisin Seiki Kabushiki Kaisha
    Inventors: Seiji Hidaka, Akihito Yamamoto
  • Publication number: 20130166113
    Abstract: 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. 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: Application
    Filed: May 22, 2012
    Publication date: June 27, 2013
    Applicant: Optical Air Data Systems, LLC
    Inventors: Elizabeth A. Dakin, Priyavadan Mamidipudi, Philip L. Rogers
  • Patent number: 8473117
    Abstract: A flight control system and method for controlling the flight of a fixed-wing model aircraft is disclosed. The flight control system may actively sense the condition when the wings of the model aircraft are not level to the horizon. The flight control system may then command the servo(s) to control movement about the roll and the yaw axes of the aircraft in order to level the wings to the horizon. In addition, the flight control system may limit the maximum bank angle that can be achieved even when full roll control is commanded by the operator. The flight control system in accordance with the present disclosure may allow inexperienced operators to fly model aircraft successfully by eliminating/mitigating adverse effects that may cause the operators to lose control.
    Type: Grant
    Filed: May 10, 2011
    Date of Patent: June 25, 2013
    Assignee: Horizon Hobby, Inc.
    Inventor: Michael J. McConville
  • Patent number: 8463466
    Abstract: A method, apparatus and software is disclosed for controlling the heading of an aircraft travelling on the ground in which veering is detected and compensatory steering commands generated so as to automatically maintain a reference heading.
    Type: Grant
    Filed: February 6, 2008
    Date of Patent: June 11, 2013
    Assignee: Airbus Operations Limited
    Inventors: Anthony Venios, Stephan Mongereau, Sanjiv Sharma, Gianluca Verzichelli, Andrew Hebborn, Xavier Guery
  • Patent number: 8442707
    Abstract: The present invention relates to continuous descent approaches that ensure the greatest certainty in arrival time. The continuous descent approach is flown by maintaining an aerodynamic flight path angle, thereby allowing a ground speed to be followed with greater accuracy. An improvement is described that accounts for turns made during continuous descent approaches that may otherwise cause a drift away from the desired ground speed, and hence arrival time. A correction to the aerodynamic flight path angle is used that produces a compensatory change in the potential energy of the aircraft upon completing the turn to balance the anticipated drift in kinetic energy.
    Type: Grant
    Filed: February 11, 2010
    Date of Patent: May 14, 2013
    Assignee: The Boeing Company
    Inventors: Ramon Gomez Ledesma, David Garrido-Lopez
  • Patent number: 8442704
    Abstract: A method for dynamically computing an equi-distance point (EDP) for an aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency, determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by a flight management system (FMS) of the aircraft, and generating the EDP for the aircraft by locating a point on the remaining flight path which is equidistant from the at least two reference points.
    Type: Grant
    Filed: July 19, 2010
    Date of Patent: May 14, 2013
    Assignee: Airbus Engineering Centre India
    Inventors: Veeresh Kumar Masaru Narasimhulu, Dinesh Kumar Kushwaha
  • Patent number: 8433506
    Abstract: A method of providing weather information for an aircraft trajectory to a flight management system (FMS) includes selecting a unique subset of temperature data points from weather data points along an aircraft trajectory and sending corresponding weather data points to the FMS.
    Type: Grant
    Filed: June 30, 2011
    Date of Patent: April 30, 2013
    Assignee: General Electric Company
    Inventors: Frank Saggio, III, Ana Isabel Del Amo Blanco
  • Patent number: 8401736
    Abstract: Traveling environment information, which is information on a traveling environment around a vehicle, is obtained. If the automation level of the vehicle, which is set according to the traveling environment information, is decreased, the driving assistance level is decreased in a stepwise manner to execute a driving assistance control.
    Type: Grant
    Filed: June 19, 2009
    Date of Patent: March 19, 2013
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventors: Shinya Kawamata, Kenichi Kitahama
  • Patent number: 8392037
    Abstract: A flight control system includes a fly by wire system operable to provide predictive termination point symbology overlaid on a synthetic imagery displayed by a display system in response to a control system and a sensor system. A method to facilitate a VTOL aircraft approach to a terminal point includes integrating a flight director mode with a control system to provide a stabilized approach path to a termination point.
    Type: Grant
    Filed: August 18, 2008
    Date of Patent: March 5, 2013
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Vineet Sahasrabudhe, Lorren Stiles, Margaret A. Macisaac, John H. Judge, Alex Faynberg
  • Patent number: 8392038
    Abstract: The method of generating a secure flight plan portion in the event of depressurization corresponding to a time-conditioned descent profile that may include a succession of levels, comprises: a step of defining a first point of the flight plan, called non-return point, denoted NRP, and a second point of the flight plan, called EOZ, the two points delimiting a portion of the flight plan plotted above an area identified as “with risks”; a step of defining two radials in the horizontal plane respectively passing through the first and the second points; a step of determining a first flight plan portion comprising the definition of a lateral offset angle from the original flight plan; a step of determining a vertical descent profile; a step of displaying time markers indicating the exhaustion of the oxygen reserve.
    Type: Grant
    Filed: December 10, 2009
    Date of Patent: March 5, 2013
    Assignee: Thales
    Inventors: Christophe Caillaud, Jérôme Sacle
  • Patent number: 8392039
    Abstract: An aircraft display system (100) for illustrating a suggested crab angle has a processor (104) adapted to receive data representative of a desired ground tract (214) and representative of a ground tract deviation, and is configured upon receipt of these data to supply a ground tract rendering display command. A display device (116) coupled to receive the ground tract image rendering display commands is operable to render an icon (222) representative of the desired aircraft heading to maintain the desired ground tract (214). The method of how to maneuver an aircraft to correct for crosswind includes determining (306) a difference between a current ground track (224) and a current heading (218), determining a desired heading to maintain the desired ground track (214) based on the difference, and rendering on a display an aircraft icon (222) that is representative of the desired heading.
    Type: Grant
    Filed: May 29, 2008
    Date of Patent: March 5, 2013
    Assignee: Honeywell International Inc.
    Inventors: Gang He, Ivan Sandy Wyatt
  • Patent number: 8386097
    Abstract: Disclosed is a method and device for assisting guidance of an aircraft. A flight management system is used to determine guidance instructions that include speed instructions having at least one flight time constraint to guide the aircraft to a check-point. An accuracy level for complying with the flight time constraint and at least one error level for at least one flight parameter are generated by an accuracy generating unit. An operating margin for at least one second parameter is determined from the determined accuracy and error levels, with the operating margin being representative of air speed criterion values of the aircraft. A range determining unit is used to determine whether the range of air speed criterion values is within an air speed envelope of the aircraft, and the speed instructions are modified when the range of air speed criterion values is not within the air speed envelope.
    Type: Grant
    Filed: March 11, 2008
    Date of Patent: February 26, 2013
    Assignee: Airbus Operations SAS
    Inventors: Jean-Louis de Menorval, Fabrice Lucas, David Gerasimovic
  • Patent number: 8380425
    Abstract: Autonomous collision avoidance systems for unmanned aerial vehicles are disclosed. Systems illustratively include a detect and track module, an inertial navigation system, and an auto avoidance module. The detect and track module senses a potential object of collision and generates a moving object track for the potential object of collision. The inertial navigation system provides information indicative of a position and a velocity of the unmanned aerial vehicle. The auto avoidance module receives the moving object track for the potential object of collision and the information indicative of the position and the velocity of the unmanned aerial vehicle. The auto avoidance module utilizes the information to generate a guidance maneuver that facilitates the unmanned aerial vehicle avoiding the potential object of collision.
    Type: Grant
    Filed: September 13, 2010
    Date of Patent: February 19, 2013
    Assignee: L-3 Unmanned Systems, Inc.
    Inventors: David S. Duggan, David A. Felio, Craig S. Askew
  • Patent number: 8373579
    Abstract: A monitoring system for alerting pilots of aircraft or operators of vehicles when the aircraft or vehicle is approaching a geographical feature of interest, such as a runway, includes a database including at least one geo-referenced chart; a processor; a positioning system configured to identify at least one of the position, heading, track and velocity of the vehicle, and transmit such data to the processor; and a display unit configured to display the present position of the aircraft on the at least one geo-referenced chart. After receiving the position, heading, track and/or velocity data, the processor determines whether the aircraft has entered a containment area associated with a geographical feature of interest, and if so, provides a visible notification to the pilot or operator, which may comprise a change in display of the geographical feature of interest.
    Type: Grant
    Filed: December 6, 2006
    Date of Patent: February 12, 2013
    Assignee: Universal Avionics Systems Corporation
    Inventors: Joachim Laurenz Naimer, Frank Hummel, John Jorgensen, Patrick Krohn
  • Patent number: 8359130
    Abstract: Disclosed are a method and device for attenuating vertical turbulence encountered by an aircraft during flight. Incorporated into the method and device is a wind determination device, which is used to determine a vertical wind component existing outside the aircraft. A severity level determination unit is used to determine a severity level of the vertical wind component determined by the wind determination device. A control unit calculates at least one control order based on the vertical wind component determined by the wind determination device. In addition, the control unit determines the actual existence of activation conditions determined according to the severity level determined by the severity level determination unit. Upon verifying the activation conditions, the control unit transmits the control order to at least one actuator of the at least one controllable movable member.
    Type: Grant
    Filed: October 9, 2006
    Date of Patent: January 22, 2013
    Assignee: Airbus Operations SAS
    Inventors: Alexandre Colomer, Xavier Dal Santo
  • Patent number: 8359128
    Abstract: A method and apparatus for managing solar power collection. A position of the sun is identified relative to an aerospace vehicle while the aerospace vehicle is moving along a flight path. A level of power generation is identified by a solar power generation system while the aerospace vehicle moves along the flight path using a threat management module and equivalent radar signature data. The threat management module uses the equivalent radar signature data to identify the level of power generation by the aerospace vehicle from different positions of the sun relative to the aerospace vehicle, and the equivalent radar signature data is based on solar power generation signature data identifying the level of power generation for the different positions of the sun relative to the aerospace vehicle. A change in the flight path that results in a desired level of power generation is identified by the solar power generation system.
    Type: Grant
    Filed: July 13, 2011
    Date of Patent: January 22, 2013
    Assignee: The Boeing Company
    Inventors: Matthew Jonathan Segal, Kevin Andrew Wise
  • Patent number: 8340840
    Abstract: A method and device for reducing on an aircraft lateral effects of a turbulence. The device (1) includes means (2, 3, 5, 7, A1, A2) for calculating and applying a roll control command and a yaw control command enabling the side effects generated by a turbulence event to be attenuated on the aircraft.
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: December 25, 2012
    Assignee: Airbus Operations (SAS)
    Inventor: Stéphane Puig
  • Patent number: 8340896
    Abstract: A road shape recognition device includes: distance and height detecting means for detecting distance data having a distance and height in real space regarding a road surface where a vehicle is traveling at multiple mutually different points; approximation line calculating means for dividing the plurality of distance data into near and far groups as viewed from the vehicle to calculate an approximation line of the distance data for each group each time the distance data of the boundary portion between the two groups is transferred from one of the groups to the other; statistics calculating means for calculating statistics from the corresponding approximation line for each group where the distance data is transferred; and road shape model generating means for selecting one out of combinations of the approximation lines to generate a road shape model using the selected combination.
    Type: Grant
    Filed: May 18, 2010
    Date of Patent: December 25, 2012
    Assignee: Fuji Jukogyo Kabushiki Kaisha
    Inventor: Toru Saito
  • Patent number: 8332084
    Abstract: A method of determining environmental data along a trajectory of an aircraft may assist in the evaluation of flight conditions along the trajectory. Environmental data may be at least one of collected, derived, and fused from a plurality of weather sources using at least one processor. The environmental data may be filtered, extrapolated, and fused, using the at least one processor, within at least one selected volume of airspace over a trajectory of the aircraft based on selected weather-applicability time intervals, and on at least one of user-selected parameters and weighted environmental data criteria. The trajectory may comprise at least one of a planned trajectory, a current trajectory, and an intent trajectory of the aircraft. An effect of the filtered, extrapolated, and fused environmental data on the trajectory may be determined using the at least one processor.
    Type: Grant
    Filed: June 23, 2009
    Date of Patent: December 11, 2012
    Assignee: The Boeing Company
    Inventors: Louis J. Bailey, Gregory T. Saccone
  • Patent number: 8321075
    Abstract: Biodynamic feedthrough in a master control system can be mitigated. An accelerometer is used to measure the acceleration of an environment. In one embodiment, mitigation damping forces can then be determined based on the velocity of an effector of a haptic manipulator and the measured accelerations. The haptic manipulator applies the mitigation damping forces as force feedback. In another embodiment, biodynamic feedthrough can be filtered from the input signal. Parameters for a model can be accessed based on the position of the effector, and the model can be used to predict biodynamic feedthrough from the measured accelerations.
    Type: Grant
    Filed: February 24, 2009
    Date of Patent: November 27, 2012
    Assignee: SRI International
    Inventors: Thomas Low, Kevin Hufford
  • Patent number: 8311686
    Abstract: A method for monitoring airplane noise and emissions may include receiving a predetermined set of engine performance data for an airplane and receiving a predetermined set of airplane flight data for the airplane. The method may also include predicting at least one of a noise level and an emissions level from the airplane at each of a plurality of ground based noise and emissions monitoring stations based on the predetermined set of engine performance data and the predetermined set of airplane flight data. Each of the plurality of ground based noise and emissions monitoring stations is located at a predetermined geographic location along an expected flight path of the airplane.
    Type: Grant
    Filed: August 20, 2009
    Date of Patent: November 13, 2012
    Assignee: The Boeing Company
    Inventors: William H. Herkes, Kevin A. Burnside, Ronald F. Olsen
  • Patent number: 8306679
    Abstract: The present invention relates to a method of protecting an aircraft in approach by signalling against the risks of collision with the terrain in steep-sided environments, in order to avoid unwanted warnings emanating from the clearance sensors of the onboard TAWS system while protecting the aircraft when it fails to observe the published procedure, and this equally in a landing procedure and in a take-off procedure. The method includes conferring an additional function on the conventional TAWS functions, specific to the detection of the potential risks of collision of the aircraft with the terrain when following procedures of reduced protection corridor type, and this without modifying either the logics or the characteristics of the clearance sensor or sensors as currently defined in the TAWSs of the state of the art.
    Type: Grant
    Filed: November 13, 2008
    Date of Patent: November 6, 2012
    Assignee: Thales
    Inventors: Hugues Meunier, Nicolas Marty, Aurélie Sallier