Air Speed Or Velocity Measurement Patents (Class 701/7)
  • Patent number: 10659279
    Abstract: A processing method includes acquiring a real-time video captured by a camera disposed on an physical object; acquiring one or more of a moving direction of the physical object, a speed of the physical object, and an acceleration of the physical object; and controlling a display device to display the real-time video corresponding to a first event in response to the first event be triggered according to the one or more of the moving direction of the physical object, the speed of the physical object, and the acceleration of the physical object.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: May 19, 2020
    Assignee: HTC Corporation
    Inventors: Wei-Cheng Chiu, Wei-Chih Kuo
  • Patent number: 10605822
    Abstract: A system and method for estimating a plurality of airspeed parameters of an aircraft is disclosed. The system comprises one or more processors and a memory coupled to the processor. The memory storing data comprising a database and program code that, when executed by the one or more processors, causes the system to receive a plurality of operating parameters that each represent an operating condition of the aircraft. The system is further caused to determine a model based dynamic pressure based on the operating parameters. The model based dynamic pressure is estimated based on steady flight conditions of the aircraft. The system is further caused to determine a bridge based dynamic pressure based on at least a temperature deviation and an inertial speed vector. The bridge based dynamic pressure is estimated for extreme flight conditions of the aircraft.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: March 31, 2020
    Assignee: The Boeing Company
    Inventor: Jia Luo
  • Patent number: 10338089
    Abstract: A method and system for determining a speed of a vehicle based on a GPS speed captured from a Global Positioning System (GPS). A capturing module captures GPS speed Vx and a horizontal accuracy value corresponding to a time stamp Tx. A speed modification module modifies the GPS speed Vx corresponding to the time stamp Tx. A speed correcting module corrects the GPS speed Vx corresponding to the time stamp Tx. The GPS speed may be corrected by filtering an error in the GPS speed by using a Slope dependent averaging (SDA) filter in order to obtain a first corrected speed Vx?. Further, the first corrected speed is corrected by selecting one of a center weight (CW) filter and an edge weight (EW) filter, based upon a pre-defined condition, in order to obtain a second corrected speed Vx? indicating the speed of the vehicle.
    Type: Grant
    Filed: June 26, 2015
    Date of Patent: July 2, 2019
    Assignee: TATA CONSULTANCY SERVICES LIMITED
    Inventors: Tapas Chakravarty, Arijit Chowdhury, Balamuralidhar Purushothaman
  • Patent number: 10261517
    Abstract: A rotorcraft including a flight control computer (FCC) providing a vertical speed hold for the rotorcraft, a collective control, and a collective trim motor connected to the collective control. The collective trim motor moves the collective control according to a collective set command generated by the FCC according to a target vertical speed and when the FCC determines the collective control is in-detent. A collective position sensor is connected to the collective control. The collective position sensor generates, and sends to the FCC, a collective position signal indicating the position of the collective control. A flight control device controls a flight parameter of the rotorcraft in response to a flight control device control signal received from the FCC. The FCC generates the flight control device control signal according to the collective position signal, and sends the flight control device control signal to a flight control device.
    Type: Grant
    Filed: April 11, 2017
    Date of Patent: April 16, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Christopher Mike Bothwell, Sung Kyun Kim, Jillian Samantha Alfred, Robert Earl Worsham, II, Luke Dafydd Gillett, Morganne Cody Klein
  • Patent number: 10147244
    Abstract: A first air data value is generated based on a first set of parameters. A second set of parameters that does not include any of the first set of parameters is processed through an artificial intelligence network to generate a second air data value. The second set of parameters is processed through a plurality of diagnostic artificial intelligence networks to generate a plurality of diagnostic air data values. Each of the plurality of diagnostic artificial intelligence networks excludes a different one of the second set of parameters. One of the second set of parameters is identified, based on the first air data value and the plurality of diagnostic air data values, as a fault source parameter that is associated with a fault condition.
    Type: Grant
    Filed: June 10, 2016
    Date of Patent: December 4, 2018
    Assignee: Simmonds Precision Products, Inc.
    Inventors: Mauro J. Atalla, Thomas G. Wiegele, Kaare Josef Anderson, Michael A. Lynch
  • Patent number: 9625261
    Abstract: A method and apparatus includes strategies for improving required time of arrival reliability by an aircraft comprising determining a speed correction for one of AT speed constraints or an AT or ABOVE speed constraints, wherein the determining is selected from one or more of the mechanisms from the group consisting of continuous RTA speed management between constraints, padding of the AT speed constraints and the AT or ABOVE speed constraints; decelerating proactively; and using a variable guidance margin, wherein the guidance margin is a speed change not reflected in a flight plan prediction.
    Type: Grant
    Filed: September 4, 2014
    Date of Patent: April 18, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Michal Polansky, Erwan Paricaud, Dorothee De Villele, Zdenek Jancik
  • Patent number: 9593962
    Abstract: Systems and methods for attitude fault detection based on integrated GNSS/inertial hybrid filter residuals are provided. In one embodiment, a fault detection system for aircraft attitude measurement system comprises: a sensor monitor coupled to a first inertial measurement unit, the sensor monitor comprising: a navigation error model for the first inertial measurement unit, the model configured to model a plurality of error states including at least an attitude error state vector, an velocity error state vector, and a position error state vector determined from data generated by the first inertial measurement unit; and a propagator-estimator configured to propagate and update error states based on GNSS data; and a residual evaluator configured to input measurement error residual values generated by the propagator-estimator, wherein the residual evaluator outputs an alert signal when the measurement error residual values exceed a threshold.
    Type: Grant
    Filed: December 9, 2014
    Date of Patent: March 14, 2017
    Assignee: Honeywell International Inc.
    Inventors: Mats Anders Brenner, Mark A. Ahlbrecht, John R. Morrison
  • Patent number: 9540005
    Abstract: A method is provided for controlling speed of a vehicle. The method includes determining an arrival time error (ATE) for a required time of arrival (RTA) and a projected trajectory according to a travel plan with a current speed profile having a plurality of regions, each with a respective speed adjustment parameter (SAP) and a respective SAP value relative to a nominal speed profile. The method further includes selecting, when the ATE is greater than a threshold, one of the regions as a selected region for modification based on a priority order of the regions. The method further includes modifying the current speed profile by adjusting the respective SAP value for the selected region according to the respective SAP in order to decrease the ATE; and implementing the modified speed profile.
    Type: Grant
    Filed: March 28, 2016
    Date of Patent: January 10, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Ryan Howe-Veenstra, Benjamin Bochem, Mike Jackson
  • Patent number: 9460622
    Abstract: A method and apparatus is provided for controlling the operation of an autonomous vehicle. According to one aspect, the autonomous vehicle may track the trajectories of other vehicles on a road. Based on the other vehicle's trajectories, the autonomous vehicle may generate a representative trajectory. Afterwards, the autonomous vehicle may change at least one of its speed or direction based on the representative trajectory.
    Type: Grant
    Filed: October 16, 2014
    Date of Patent: October 4, 2016
    Assignee: Google Inc.
    Inventors: David Ian Franklin Ferguson, Dmitri A. Dolgov
  • Patent number: 9308985
    Abstract: A system and method for controlling a deceleration profile of an aircraft, includes a processor and memory that receives a signal indicative of a deceleration command; receives signals indicative of a sensed velocity and a commanded heading rate; determines a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate; determines an estimated deceleration command as a function of the commanded velocity; and determines an actual deceleration command in response to the determining of the estimated deceleration command.
    Type: Grant
    Filed: April 11, 2014
    Date of Patent: April 12, 2016
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Stephen Kubik, Alex Faynberg, Stephen C. Mcculley, John P. Rucci, Christiaan P. Corry, Edward Pavelka
  • Patent number: 9229447
    Abstract: A method for detecting erroneous air data on an aircraft includes determining a current air parameter and a current altitude pressure parameter which collectively define a current point of control for the aircraft. The method also includes verifying whether the current point of control is situated in a characteristic envelope indicating operating limits for the aircraft. When the current point of control is outside the characteristic envelope, then a detection piece of information identifying at least one of the parameters as an erroneous parameter is emitted, which causes that erroneous parameter to be invalidated and an alarm signal to be sent to the crew. Therefore, an erroneous air data parameter is readily addressed and discarded using the method and associated device.
    Type: Grant
    Filed: March 19, 2012
    Date of Patent: January 5, 2016
    Assignee: Airbus Operations (SAS)
    Inventor: Julien Feau
  • Patent number: 9157415
    Abstract: The present subject matter is directed to a system and method for controlling an electrical component, e.g. a power bridge, of a wind turbine using contingency communications. In one embodiment, the method includes receiving, by the electrical component, a standard set of commands for a first time frame. A next step includes receiving, by the electrical component, one or more contingency sets of commands for time frames beyond the first time frame. The method also includes determining if the standard set of commands is received within a start window of the first time frame. A further step includes implementing, by the electrical component, the standard set of commands during the first time frame if the standard set of commands is received within the start window. The method also includes implementing, by the electrical component, one of the contingency sets of commands received during a previous time frame if the standard set of commands is not received within the start window.
    Type: Grant
    Filed: March 21, 2014
    Date of Patent: October 13, 2015
    Assignee: General Electric Company
    Inventors: Robert Allen Seymour, James Michael Nowak, David Smith, Terry Michael Tackman, Allen Michael Ritter
  • Patent number: 9079116
    Abstract: A radio controlled (RC) vehicle includes a receiver that is coupled to receive an RF signal from a remote control device, the RF signal containing command data in accordance with a first coordinate system, wherein the first coordinate system is from a perspective of the remote control device. A motion sensing module generates motion data based on the motion of the RC vehicle. A processing module transforms the command data into control data in accordance with a second coordinate system, wherein the second coordinate system is from a perspective of the RC vehicle. A plurality of control devices control the motion of the RC vehicle based on the control data.
    Type: Grant
    Filed: December 11, 2013
    Date of Patent: July 14, 2015
    Inventors: Katherine C. Stuckman, Michael D. Reynolds
  • Publication number: 20150149000
    Abstract: The drone comprises: a vertical-view camera (132) pointing downward to pick up images of a scene of the ground overflown by the drone; gyrometer, magnetometer and accelerometer sensors (176); and an altimeter (174). Navigation means determine position coordinates (X, Y, Z) of the drone in an absolute coordinate system linked to the ground. These means are autonomous, operating without reception of external signals. They include image analysis means, adapted to derive a position signal from an analysis of known predetermined patterns (210), present in the scene picked up by the camera, and they implement a predictive-filter estimator (172) incorporating a representation of a dynamic model of the drone, with as an input the position signal, a horizontal speed signal, linear and rotational acceleration signals, and an altitude signal.
    Type: Application
    Filed: July 3, 2014
    Publication date: May 28, 2015
    Inventors: MICHAEL RISCHMULLER, LAURE CHEVALLEY, FRANCOIS CALLOU, ETIENNE CALDICHOURY
  • 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: 9037318
    Abstract: Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.
    Type: Grant
    Filed: May 8, 2013
    Date of Patent: May 19, 2015
    Assignee: Honeywell International Inc.
    Inventors: Mark T. Manfred, Thomas A. Ryno
  • Patent number: 9037316
    Abstract: A method for early detection of the vortex ring state in a helicopter includes steps of establishing flight control signals for flight control with regard to the vertical movement axis of the helicopter, detecting resultant movements in the vertical movement axis of the helicopter, and detecting an impending vortex ring state of the helicopter in accordance with a correlation between the flight control signals and the vertical movements in the vertical movement axis.
    Type: Grant
    Filed: July 13, 2011
    Date of Patent: May 19, 2015
    Assignees: Deutsches Zentrum für Luft- und Raumfahrt e.V., Office national d'études et de recherche aérospatiales
    Inventors: Max Abildgaard, Laurent Binet
  • 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
  • Patent number: 9008939
    Abstract: A vehicle control system and method combining control allocation and phase compensation for forming a phase compensated actuator command signal based on a control demand signal. A feedback unit includes a matrix multiplication unit for forming an estimated behavior signal, from a control efficiency matrix and the actuator command signal. The estimated behavior signal is fed to a second summation unit for forming a difference signal. The difference signal is processed by a filter unit for forming a feedback signal which is connected to a first summation unit for forming a modified control demand signal, such that the modified control demand signal is adjusted to always represent a control demand realizable by the vehicle. The modified control demand signal is further connected to the second summation unit and to a control allocator which output is then connected to the matrix multiplier to form a feedback loop.
    Type: Grant
    Filed: February 12, 2008
    Date of Patent: April 14, 2015
    Assignee: SAAB AB
    Inventor: Bengt-Göran Sundqvist
  • Publication number: 20150100184
    Abstract: A system and method are provided for calculating Mach number and true airspeed without reference to data from a pitot static sensor. The true airspeed and Mach number are calculated using the altitude information from GPS, IRS, Radio Altimeter and other onboard sensors other than the air data computer (ADC). The computed true airspeed or Mach number could be used to confirm the ADC information or in lieu of the ADC information when the ADC information is unreliable or unavailable.
    Type: Application
    Filed: December 15, 2014
    Publication date: April 9, 2015
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Visvanathan Thanigai Nathan, Thanga Anandappan
  • Patent number: 9002542
    Abstract: A method for detecting piloting conflicts between the crew and the autopilot of an aircraft. According to the method, an automatic trajectory is programmed by checking whether the actual values of navigation parameters converge on said corresponding desired values within a predetermined convergence period; in the case where at least one of the actual values does not converge, within the convergence period, on the corresponding desired value, a predictive calculation is carried out, at consecutive future moments, of the value of at least one particular parameter selected amongst the navigation parameters; and in the case where the predicted value of the particular parameter is higher than a corresponding predefined threshold, an alarm is emitted for the crew of the aircraft to notify them about a piloting conflict being able to jeopardize the flight safety of the aircraft. A device for implementing the method. An aircraft including the device.
    Type: Grant
    Filed: June 4, 2009
    Date of Patent: April 7, 2015
    Assignee: Airbus Operations (SAS)
    Inventors: Frédéric Dehais, Charles Lesire, Catherine Tessier, Laure Christophe
  • Patent number: 9002616
    Abstract: In one aspect, a digital engine control system for an aircraft engine is provided. The control system includes a selection unit, the selection unit including a monitoring module configured to determine a measurement of the speed of rotation of the engine from the output signal from one or more protection sensors and to compare the or each speed measurement determined by the selection unit with speed measurements supplied by electronic control units to determine an operating state of each electronic control unit.
    Type: Grant
    Filed: November 7, 2012
    Date of Patent: April 7, 2015
    Assignee: Thales
    Inventors: Gilles Genevrier, Claude Bresson
  • Patent number: 8996204
    Abstract: Systems and methods for adjusting target approach speed for use in a “Too Fast” approach to landing condition. An exemplary system stores predefined maximum wind setting and a predefined reference speed and a pilot set bug speed value. A processing device sets a target speed equal to the bug speed, if the bug speed is less than the reference speed plus a value associated with a predefined maximum wind setting, and sets the target speed equal to the reference speed plus the max wind added value, if the manual bug speed is not less than the reference speed plus the max wind added value. An output device outputs an alert if the received aircraft speed is greater than the set target speed plus a predefined error value when the received aircraft location is within a threshold value of a touchdown point.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: March 31, 2015
    Assignee: Honeywell International Inc.
    Inventors: Yasuo Ishihara, Steve Johnson
  • Patent number: 8958932
    Abstract: Systems and methods to mitigate instrument landing system (ILS) overflight interference are disclosed. An example method performing a first measurement of a position of an aircraft relative to a first location based on an instrument landing system, performing a second measurement of the position of the aircraft based on inertial measurements performed over a first time period occurring prior to the first measurement, performing a third measurement of the position of the aircraft based on inertial measurements performed over a second time period greater than the first time period and occurring prior to the first measurement, and generating guidance information based on a selected one of the first, second, or third measurements of the position of the aircraft.
    Type: Grant
    Filed: February 11, 2013
    Date of Patent: February 17, 2015
    Assignee: The Boeing Company
    Inventor: Tim Murphy
  • Patent number: 8958930
    Abstract: Method for dynamically limiting the inclinations of monoblock flight control surfaces (FCS) in an aircraft. Dynamic limitation of the FCS is activated if a stall susceptibility condition is detected in the current aircraft environment. The real-time calibrated airspeed of the aircraft, real-time angle of attack (AOA) of the aircraft, and real-time sideslip angle (AOS) of the aircraft are obtained. The aircraft parameters may be obtained via estimation if the measured values are deemed unsuitable. The real-time local AOA and AOS of the FCS are calculated based on the obtained aircraft parameters. The inclination of each of the FCS relative to the critical values is dynamically limited according to the calculated real-time local AOA and AOS of the FCS. The aircraft may be an unmanned aerial vehicle (UAV) and/or a V-tail aircraft. The stall susceptibility condition may include icy conditions.
    Type: Grant
    Filed: January 30, 2012
    Date of Patent: February 17, 2015
    Assignee: Elbit Systems Ltd.
    Inventor: Dan Malta
  • Patent number: 8954238
    Abstract: An emergency evacuation device of a vehicle that executes an automatic vehicle stop control based on a command of a driver is disclosed. The emergency evacuation device comprises a driver's physiological condition estimation portion that estimates a driver's physiological condition; a driver's command input portion, operated by the driver, that receives a driver's command input and outputs a command of an execution of an automatic vehicle stop control in accordance with the command input; and an automatic vehicle stop control portion that executes the automatic vehicle stop control in response to the command from the driver's command input portion, wherein based on the driver's physiological condition estimated in the driver's physiological condition estimation portion, the structure of the driver's command input portion, for example, the arrangement of receptor(s) of the driver's command input portion receiving the command from the driver is changed.
    Type: Grant
    Filed: July 11, 2011
    Date of Patent: February 10, 2015
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventors: Masumi Kobana, Kazuya Sasaki, Shinya Kawamata
  • Patent number: 8924046
    Abstract: A combined stand-by instrument intended to be fitted to the instrument panel of an aircraft, and a method for calibrating the combined stand-by instrument, comprises anemobarometric sensors, inertial sensors, a magnetic field sensor, a screen and a computer making it possible to determine and to display on the screen an altitude, a speed, an attitude and a current heading of the aircraft on the basis of the sensors and to calibrate the magnetic field sensor. The computer is configured to allow the simultaneous display on the screen of the altitude, of the speed and of the attitude of the aircraft as well as a guide for the calibration of the magnetic field sensor.
    Type: Grant
    Filed: November 22, 2011
    Date of Patent: December 30, 2014
    Assignee: Thales
    Inventors: Damien Gerthoffert, Florent Colliau, Yves Jaulain
  • Patent number: 8914164
    Abstract: A system and method are provided for calculating Mach number and true airspeed without reference to data from a pitot static sensor. The true airspeed and Mach number are calculated using the altitude information from GPS, IRS, Radio Altimeter and other onboard sensors other than the air data computer (ADC). The computed true airspeed or Mach number could be used to confirm the ADC information or in lieu of the ADC information when the ADC information is unreliable or unavailable.
    Type: Grant
    Filed: August 2, 2013
    Date of Patent: December 16, 2014
    Assignee: Honeywell International Inc.
    Inventors: Visvanathan Thanigai Nathan, Thanga Anandappan
  • Publication number: 20140343761
    Abstract: A system and method automatically control an emergency descent of an aircraft to a target altitude. Factors including weather, traffic, terrain, special use airspace, distance to an alternate, time above 10,000 feet, and time airborne are considered in deciding on descent airspeed, aircraft heading, and selection of an alternate. The target altitude may be redefined after activation of a Terrain Advisory and Awareness System. A vertical speed, or rate of descent, may be adjusted after receiving a resolution advisory from a traffic clearance and avoidance system if the maneuver with maximum operating speed generates excessive normal acceleration. Initiation of the emergency descent will be transmitted via radio and data link communication and automatic selection of a mode declaring a state of emergency on the traffic clearance and avoidance system.
    Type: Application
    Filed: May 15, 2013
    Publication date: November 20, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: Peter Pastor
  • Patent number: 8892275
    Abstract: A method and device optimize the vertical trajectory of an aircraft in flight along a predetermined approach trajectory. The method and device include the use of a calculator, which is structured to predict a predicted stabilization altitude at which the aircraft will reach a setpoint approach speed as a function of the current aircraft parameter values, a theoretical vertical trajectory, and predetermined models of aerodynamic efficiency of the aircraft. A comparator is structured to determine absolute value differences between the predicted stabilization altitude and the setpoint stabilization altitude and to compare the differences against a predetermined altitude threshold.
    Type: Grant
    Filed: July 26, 2012
    Date of Patent: November 18, 2014
    Assignee: Airbus Operations SAS
    Inventors: Florian Constans, Mickael Lefebvre
  • Patent number: 8855837
    Abstract: A flight control system includes an Acceleration and Attitude Command/Velocity Hold mode (AACVH) algorithm which blends attitude commands with acceleration commands. This blending determines a trim attitude for a given rotorcraft flight condition.
    Type: Grant
    Filed: December 9, 2013
    Date of Patent: October 7, 2014
    Assignee: Sikorsky Aircraft Corporation
    Inventor: Igor Cherepinksy
  • Patent number: 8831928
    Abstract: Embodiments of the present invention provide a system and method for providing a translation service. The method comprises providing a translation interface accessible via a network. The translation interface receives specialized data associated with a domain from a member. A text string written in a source language is received from the member via the translation interface. A domain-based translation engine is selected. The domain-based translation engine may be associated with a source language, a target language, and a domain. The text string is translated into the target language using, at least in part, the selected domain-based translation engine. The translated text string is transmitted to the member via the Internet. In some embodiments, a translation memory is generated based on the specialized data.
    Type: Grant
    Filed: April 4, 2007
    Date of Patent: September 9, 2014
    Assignee: Language Weaver, Inc.
    Inventors: Daniel Marcu, William Wong, Felix Lung
  • 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: 8825233
    Abstract: A method for estimating airspeed of an aircraft includes receiving values indicative of operating conditions of the aircraft along an axis; estimating a tip path plane (TPP) angle along the axis from at least one of the operating conditions to create an estimated TPP angle; and determining an estimated airspeed as a function of the estimated TPP angle, the determining including referencing a look-up table that indexes the estimated TPP angle with the airspeed.
    Type: Grant
    Filed: May 31, 2012
    Date of Patent: September 2, 2014
    Assignee: Sikorsky Aircraft Corporation
    Inventor: Steven E. Spoldi
  • 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: 8818577
    Abstract: A device includes means for generating and applying to an aircraft protecting orders avoiding a flight with an excessive descent rate. More specifically, the device includes components configured to perform a series of operations including measuring the current vertical speed and the current height of the aircraft and comparing these flight parameters with a safety envelope defining couples of vertical speed and height that are indicative of an excessive descent rate. If the current vertical speed and height are located in the safety envelope, a protection is triggered by generating protecting orders to remove the aircraft from the safety envelope and applying those protecting orders to control surfaces of the aircraft.
    Type: Grant
    Filed: February 9, 2011
    Date of Patent: August 26, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Pascale Louise, Emmanuel Cortet, Erwin Grandperret
  • Patent number: 8798814
    Abstract: A method and apparatus for managing a flight of a rotorcraft. Parameters for the flight of the rotorcraft are identified. A number of regions, above a terrain, to be avoided by the rotorcraft during the flight of the rotorcraft over the terrain are identified using the parameters for the flight of the rotorcraft. Information about the number of regions is displayed on a display device during the flight of the rotorcraft.
    Type: Grant
    Filed: January 27, 2011
    Date of Patent: August 5, 2014
    Assignee: The Boeing Company
    Inventors: William Foulke Spencer, V, Dan M. Wells
  • Patent number: 8788124
    Abstract: Systems and methods for the calculation of the approach speed during air to air refueling maneuvers. The systems comprise: a) capturing means of a sequence of digital photograms of the approach operation scenario calibrated in order to determine the real distance corresponding to a pixel of a photogram; b) computational means configured for obtaining the coordinates of the relative trajectory of the receiver aircraft with respect of the tanker aircraft, by means of a sequence of photograms of the approach operation obtained by said capturing means and calculating the speed difference between receiver aircraft and tanker aircraft based on the trajectory defined by the coordinates recorded in said process b1). The invention also refers to the methods for calculating the approach speed.
    Type: Grant
    Filed: June 4, 2013
    Date of Patent: July 22, 2014
    Assignee: EADS Construcciones Aeronauticas S.A.
    Inventors: Francisca Coll Herrero, Jose Maria Miranda Orte
  • Patent number: 8779945
    Abstract: A flight display for an aircraft includes a virtual ice accretion meter having a liquid water content portion and an ice thickness portion. A method for determining ice accretion includes integrating over a time period a constant K multiplied by a liquid water content (LWC) and true airspeed (TAS).
    Type: Grant
    Filed: March 15, 2011
    Date of Patent: July 15, 2014
    Assignee: Sikorsky Aircraft Corporation
    Inventor: Robert James Flemming
  • 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: 8768556
    Abstract: An apparatus defines a protection envelope in an aircraft, including a processor and at least one sensor, each sensor being coupled with the processor, the processor executing at least one neural network based algorithm. The at least one sensor monitors flight parameters of the aircraft thereby generating monitored flight parameters. The processor divides the performance envelope of the aircraft into predefined flight regimes, wherein for each predefined flight regime, the processor defines and stores a suitable protection envelope. The processor determines an estimated flight regime of the aircraft using the neural network based algorithm based on the monitored flight parameters. The processor selects a respective suitable protection envelope for the aircraft based on the estimated flight regime.
    Type: Grant
    Filed: November 12, 2010
    Date of Patent: July 1, 2014
    Assignee: Elbit Systems Ltd.
    Inventors: Gershon Ben-Arie, Ilana Segall, Asi Dotan
  • Patent number: 8761961
    Abstract: A method for controlling an unmanned aerial vehicle (UAV) using an electronic device obtains movement data of the electronic device detected by an accelerometer of the electronic device, and converts the movement data of the electronic device to control signals. The method further sends the control signals to the UAV, and changes a flight status of the UAV according to the control signals.
    Type: Grant
    Filed: October 20, 2010
    Date of Patent: June 24, 2014
    Assignee: Hon Hai Precision Industry Co., Ltd.
    Inventors: Hou-Hsien Lee, Chang-Jung Lee, Chih-Ping Lo
  • Patent number: 8744670
    Abstract: A method for quickly calculating mileage includes the steps: A, receiving report data from a vehicular terminal and updating data center according to the report data; B, receiving an inquiry request which includes a vehicle number, a first time point which is earlier than a second time point and the second time point which are requested to inquire; C, inquiring the data center to acquire a first total mileage value to which the time point that is proximate to the first time point corresponds and a second total mileage value to which the time point that is proximate to the second time point corresponds; D, obtaining a running mileage L from the first time point to the second time point by subtracting the first total mileage value from the second total mileage value. A system for quickly calculating mileage quickly is also proposed.
    Type: Grant
    Filed: September 8, 2010
    Date of Patent: June 3, 2014
    Assignee: ChinaGps Co., Ltd (Shenzhen)
    Inventors: Jie Zhu, Jialiang Chu, Decheng Huang, Youwen Zhang
  • Patent number: 8744700
    Abstract: A device comprising a processor that detects an autonomously sensed change in a vehicle's operational state from an initial state characterized by a sensed vehicle speed equal to about 0; to an immediately succeeding vehicle state characterized by sensed vehicle speed being greater than about 0 and, verification from a reverse operating mode sensor that longitudinal vehicle speed is in a reverse direction; and presumptively signals the thusly detected change of vehicle operational state as an instance of reverse operation of the associated vehicle.
    Type: Grant
    Filed: April 25, 2012
    Date of Patent: June 3, 2014
    Inventors: Darren Beams, Neil Cawse
  • Patent number: 8744768
    Abstract: A method and device establishes trajectory planning, predictions and guidance so as to obtain the satisfaction of a time constraint (RTA). This objective is achieved by undertaking a computation of a trajectory up to the point where the flypast time constraint applies, on the basis of a profile of altitude and speeds, and then by computing the profile of speeds and altitudes making it possible, throughout the computed trajectory, to comply with the RTA. The method is also a method for readapting the trajectory and the vertical profile when during a mission, the data outside the aeroplane have caused the time predictions to drift and the constraint is no longer complied with under the initial speeds and trajectory assumptions.
    Type: Grant
    Filed: November 29, 2010
    Date of Patent: June 3, 2014
    Assignee: Thales
    Inventors: Manuel Gutierez-Castaneda, Philippe Chaix, Benoît Dacre-Wright
  • Patent number: 8742927
    Abstract: The invention relates to the automatic detection of the presence of non-authorized persons in the vicinity of an apparatus of the aircraft type. To this end, the invention comprises equipping persons with radio transmitters for identifying them as authorized personnel. The aircraft are also fitted, such as at the existing PODs, with a transceiver device of a radio identification system of the RFID type for recognition of the persons wearing the radio transmitters. Only the persons who are not authorized in the vicinity of the aircraft initiate an alarm procedure.
    Type: Grant
    Filed: January 29, 2008
    Date of Patent: June 3, 2014
    Assignee: Airbus Operations SAS
    Inventor: Pujol Olivier
  • Patent number: 8731756
    Abstract: In a method for monitoring the operation of a vacuum pump in a brake system, the vacuum pump is operated between an activation pressure and a deactivation pressure to generate a vacuum, the evacuation period between the activation pressure and the deactivation pressure being measured and compared with a reference period. An error signal is generated if the evacuation period exceeds the reference period.
    Type: Grant
    Filed: October 11, 2010
    Date of Patent: May 20, 2014
    Assignee: Robert Bosch GmbH
    Inventors: Hartmut Krueger, Karl Weidinger, Peter Damm
  • Publication number: 20140129057
    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: Application
    Filed: April 2, 2013
    Publication date: May 8, 2014
    Applicant: Prox Dynamics AS
    Inventor: Prox Dynamics AS
  • Patent number: 8718840
    Abstract: A device for estimating the angle of attack of an aircraft moving through the air comprises means for receiving a measured incidence presented locally by the air relative to the aircraft and means for determining the angle of attack of the aircraft as a function of the measured incidence and information about the airspeed of the aircraft. The means for determining the angle of attack of the aircraft comprise means for reading the angle of attack of the aircraft from a look-up table having at least the measured incidence and the airspeed information as inputs. Corresponding system and a corresponding method are also proposed.
    Type: Grant
    Filed: May 7, 2008
    Date of Patent: May 6, 2014
    Assignees: Airbus Operations S.A.S., Airbus
    Inventors: Thomas Spoerry, Bruno Chauveau
  • Patent number: 8718839
    Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a timer. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated.
    Type: Grant
    Filed: December 3, 2010
    Date of Patent: May 6, 2014
    Assignee: Evolved Aircraft Systems, L.L.C.
    Inventors: Michael Louis Everett, Louis Jackson Everett, Mario Ruiz, Jr.