Altitude Or Attitude Control Or Indication Patents (Class 701/4)
  • Patent number: 10319241
    Abstract: Disclosed is a novel system and method for adjusting a flight path of an aircraft. The method begins with computing a flight path of an aircraft from a starting point to an ending point which incorporates predicted weather effects at different points in space and time. An iterative loop is entered for the flight path. Each of the following steps are performed in the iterative loop. First lift data is accessed from a fine-grain weather model associated with a geographic region of interest. The lift data is data to calculate a force that directly opposes a weight of the aircraft. In addition, lift data is accessed from sensors coupled to the aircraft. The lift data is one or more of 1) thermal data, 2) ridge lift data, 3) wave lift data, 3) convergence lift data, and 4) a dynamic soaring lift data. Numerous embodiments are disclosed.
    Type: Grant
    Filed: January 12, 2018
    Date of Patent: June 11, 2019
    Assignee: International Business Machines Corporation
    Inventors: Timothy M. Lynar, Olivia J. Smith, John M. Wagner
  • Patent number: 10287001
    Abstract: A self-adjusting flight control system is disclosed. In various embodiments, an input interface receives an input signal generated by an inceptor based at least in part on a position of an input device comprising the inceptor. A processor coupled to the input interface determines dynamically a mapping to be used to map input signals received from the inceptor to corresponding output signals associated with flight control and uses the determined mapping to map the input signal to a corresponding output signal. The processor determines the mapping at least in part by computing a running average of the output signal over an averaging period and adjusting the mapping at least in part to associate a neutral position of the input device comprising the inceptor with a corresponding output level that is determined at least in part by the computed running average.
    Type: Grant
    Filed: June 15, 2016
    Date of Patent: May 14, 2019
    Assignee: Kitty Hawk Corporation
    Inventors: Todd Reichert, Zachais Vawter, Joseph Roop, Mark Johnson Cutler
  • Patent number: 10266249
    Abstract: An air/ground contact logic management system for use with fly-by-wire control systems in an aircraft. The system includes a first sensor configured to provide an output signal to determine when the aircraft is in a transition region. A logic management system is in communication with the first sensor and is configured to receive and process the output signal and classify a mode of the aircraft. A controller receives signal data from the logic management system and communicates with a control axis actuator to regulate a level of control authority provided to a pilot. The control authority is individually regulated within each integrator as a result of the individual landing gear states.
    Type: Grant
    Filed: February 21, 2017
    Date of Patent: April 23, 2019
    Assignee: Textron Innovations Inc.
    Inventor: Shyhpyng Jack Shue
  • Patent number: 10261505
    Abstract: A critical system comprises a control pathway comprising an actuation unit having a nonlinear behavior, that is able to be controlled by applying an input quantity and whose state is characterized by an output quantity. The behavior of the actuation unit being described by a flat nonlinear model, wherein the system comprises an estimation unit comprising a dynamic inversion linearization module calculating from the measured output quantity, the input quantity of the equivalent linear model; an estimation module estimating a flat output quantity from the input quantity of the equivalent linear model; and a computing module computing a residual based on the estimated flat output quantity and a measured flat output quantity, corresponding to the measured output quantity.
    Type: Grant
    Filed: November 19, 2014
    Date of Patent: April 16, 2019
    Assignee: THALES
    Inventors: Alexandre Bobrinskoy, Olivier Guerineau, Franck Cazaurang, Marc Gatti, Bruno Bluteau
  • Patent number: 10220929
    Abstract: Aspects of the disclosure provide a fill port apparatus for filling high altitude balloons, such as those used in communications networks, with lighter than air lift gasses. For instance, the fill port apparatus includes a tubular body portion having a passageway extending between a first end and a second end of the tubular body portion. The fill port apparatus also includes an attachment structure arranged at the first end of the tubular body portion. This structure is configured to attach to a top plate of a balloon envelope. The fill port apparatus also includes a plurality of energy directing structures arranged on an interior surface of the tubular body portion. These energy directing structures extend into the passageway from the interior surface and are each configured to contact at least one other of the plurality of energy directing structures when the tubular body portion is welded to itself.
    Type: Grant
    Filed: July 30, 2018
    Date of Patent: March 5, 2019
    Assignee: LOON LLC
    Inventors: Daniel Henry Fourie, Kyle Brookes
  • Patent number: 10101173
    Abstract: Systems and methods are provided for indicating a bank limit on an instrument display of an aircraft. In an example implementation, static air pressure measurements, impact air pressure measurements, an acceleration measurement, and an angle of attack may be received from corresponding sensors. A current airspeed and a stick shaker speed are determined. A minimum maneuver speed is determined from the current airspeed and the shaker stick speed. A bank limit indicator is provided on the flight display when the current airspeed is equal to or less than the minimum maneuver speed. A bank angle limit is displayed on the bank limit indicator based on the extent to which the current airspeed is equal to or less than the minimum maneuver speed.
    Type: Grant
    Filed: July 15, 2016
    Date of Patent: October 16, 2018
    Assignee: The Boeing Company
    Inventor: Frederick E. Ludtke, II
  • Patent number: 10071824
    Abstract: A method and apparatus for estimating gyro scale factor during normal spacecraft operations, using small attitude motions that are compliant with mission pointing accuracy and stability requirements and a signal processing method that specifically detects the intentionally induced motions. This process increases operational availability by avoiding the need to take the spacecraft offline for large calibration maneuvers.
    Type: Grant
    Filed: February 8, 2013
    Date of Patent: September 11, 2018
    Inventor: Alan D Reth
  • Patent number: 10054444
    Abstract: The subject matter disclosed herein relates to a system and method for receiving a plurality of signals generated by a plurality of sensors adapted to detect physical movement of a mobile device with respect to a plurality of coordinate axes. A time at which at least one of the received signals is digitized is delayed to provide an output of digitized versions of the received plurality of signals synchronized with respect to a common point in time.
    Type: Grant
    Filed: May 29, 2009
    Date of Patent: August 21, 2018
    Assignee: QUALCOMM Incorporated
    Inventors: Joseph Czompo, Ara Bicakci
  • Patent number: 10049590
    Abstract: A method for autonomous controlling of an aerial vehicle, wherein a flight operator commands the aerial vehicle, comprising the steps of: measuring flight and/or system data of the aerial vehicle; performing an evaluation of a flight condition of the aerial vehicle based on the measured data and based on at least one decision criterion; and, issuing at least one autonomous controlling command, if, as a result of the evaluation of the flight condition, the aerial vehicle is in danger.
    Type: Grant
    Filed: September 23, 2014
    Date of Patent: August 14, 2018
    Assignee: AIRBUS DEFENCE AND SPACE GMBH
    Inventors: Christian Thiele, Winfried Lohmiller, Lars Schoepfer, Hugo Heusinger, Werner Kleih
  • Patent number: 9983009
    Abstract: A method is provided for calculating the estimated navigation performance prediction for a trajectory associated with a list of segments of a flight plan. A method for displaying the navigation performance in a corridor trajectory so as to guarantee compliance with the navigation performance requirements while offering immediate viewing of the navigation latitude in a corridor is also provided.
    Type: Grant
    Filed: July 5, 2017
    Date of Patent: May 29, 2018
    Assignee: THALES
    Inventors: Michel Roger, Christophe Pierre, Hervé Goutelard
  • Patent number: 9933449
    Abstract: A system for calculating airspeed and dynamic pressure comprises a system body, an internal accelerometer, located within the system body, an internal pressure sensor, located in the system body, the internal pressure sensor being not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere, and a processor in reception of the internal accelerometer, and the internal pressure sensor, capable of calculating Mach number via an axial acceleration, and capable of calculating a dynamic pressure and a true airspeed via the Mach number.
    Type: Grant
    Filed: August 5, 2015
    Date of Patent: April 3, 2018
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventors: Robert D. Frey, Jr., David J. Schorr
  • Patent number: 9889932
    Abstract: This disclosure relates generally to Unmanned Aerial Vehicle (UAV), and more particularly to system and a method for landing of an Unmanned Aerial Vehicle (UAV). In one embodiment, the method includes estimating a 3-dimensional (3D) location of at least one media sensor mounted on the UAV relative to a marker representative of a landing location of the UAV. The marker comprises a recursive geometrical pattern. The landing of the UAV on the marker at the landing location is facilitated based on the 3D location of the at least one media sensor mounted on the UAV relative to the marker.
    Type: Grant
    Filed: March 31, 2016
    Date of Patent: February 13, 2018
    Assignee: Tata Consultancy Services Limited
    Inventors: Hrishikesh Sharma, Balamuralidhar Purushothaman
  • Patent number: 9875660
    Abstract: In one embodiment, a method includes receiving flight path data regarding the presence of an unmanned aerial vehicle (UAV) at a location at a future time, detecting the presence of the UAV at the location at the future time, determining radio identity data of the UAV using a radio mode of identification, determining optical identity data of the UAV using an optical mode of identification, and certifying the UAV based on a comparison of the radio identity data and the optical identity data to the flight path data.
    Type: Grant
    Filed: March 28, 2016
    Date of Patent: January 23, 2018
    Assignee: CISCO TECHNOLOGY, INC.
    Inventors: Charles Calvin Byers, Gonzalo Salgueiro, Joseph Michael Clarke
  • Patent number: 9854404
    Abstract: Various methods, apparatuses and/or articles of manufacture are provided which may be implemented using one or more fixed electronic devices to generate a reference data report corresponding to a particular environment. Various methods, apparatuses and/or articles of manufacture are provided which may be implemented using one or more mobile electronic devices to generate an environment report corresponding to a particular environment.
    Type: Grant
    Filed: June 22, 2015
    Date of Patent: December 26, 2017
    Assignee: QUALCOMM Incorporated
    Inventors: Stephen William Edge, Andreas Klaus Wachter, Lionel Jacques Garin, Grant Alexander Marshall
  • Patent number: 9852645
    Abstract: Disclosed is a Global Positioning System (“GPS”) independent navigation system (“GINS”) for a self-guided aerial vehicle (“SAV”). The SAV has a housing, where the housing has an outer surface, a length, a front-end, and a longitudinal axis along the length of the housing. The GINS includes a first optical sensor, a second optical sensor, a storage unit, and a comparator.
    Type: Grant
    Filed: August 17, 2015
    Date of Patent: December 26, 2017
    Assignee: The Boeing Company
    Inventor: Steven A. Wright
  • Patent number: 9834301
    Abstract: A method of increasing the performance of an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly of controlling fluid flow across their surfaces or other surfaces which would benefit from such a method, includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and a method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. Various embodiments provide steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control reduces the power requirements of the aircraft, missile, munition or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices.
    Type: Grant
    Filed: August 9, 2012
    Date of Patent: December 5, 2017
    Assignees: Orbital Research Inc., University of Notre Dame du Lac
    Inventors: Mehul Patel, Tom Corke
  • Patent number: 9816818
    Abstract: An apparatus and method for providing an improved heading estimate of a mobile device in a vehicle is presented. First, the mobile device determines if it is mounted in a cradle attached to the vehicle; if so, inertia sensor data may be valid. While in a mounted stated, the mobile device determines whether it has been rotated in the cradle; if so, inertia sensor data may no longer be reliable and a recalibration to determine a new relative orientation between the vehicle and the mobile device is needed. If the mobile device is mounted and not recently rotated, heading data from multiple sensors (e.g., GPS, gyroscope, accelerometer) may be computed and combined to form the improved heading estimate. This improved heading estimate may be used to form an improved velocity estimate. The improved heading estimate may also be used to compute a bias to correct a gyroscope.
    Type: Grant
    Filed: December 1, 2011
    Date of Patent: November 14, 2017
    Assignee: QUALCOMM Incorporated
    Inventors: Joseph Czompo, Guttorm Ringstad Opshaug, Kumar Gaurav Chhokra, Zoltan Fenene Biacs, Wyatt T. Riley
  • Patent number: 9810536
    Abstract: The subject matter disclosed herein relates to a system and method for receiving a plurality of signals generated by a plurality of sensors adapted to detect physical movement of a mobile device with respect to a plurality of coordinate axes. A time at which at least one of the received signals is digitized is delayed to provide an output of digitized versions of the received plurality of signals synchronized with respect to a common point in time.
    Type: Grant
    Filed: December 8, 2015
    Date of Patent: November 7, 2017
    Assignee: QUALCOMM Incorporated
    Inventor: Joseph Czompo
  • Patent number: 9651931
    Abstract: Safety and/or reliability may he improved in industrial control systems by optimally utilizing integrated circuit elements to reduce the amount of components required and to provide cross monitoring. In one aspect, circuitry that is part of an Integrated Circuit (IC) for controlling a first channel may also be used to monitor and provide safe operation for circuitry for controlling a second channel, and the circuitry for controlling the second channel may similarly be used to monitor and provide safe operation for the circuitry controlling the first channel. Circuitry may include a windowed watchdog circuit which may be used to monitor various events of the other circuitry, and safe operation may be provided by removing power from the other circuitry to provide a safe state.
    Type: Grant
    Filed: March 11, 2015
    Date of Patent: May 16, 2017
    Assignee: Rockwell Automation Technologies, Inc.
    Inventors: Edward C. Hopsecger, Joseph G. Vazach
  • Patent number: 9580186
    Abstract: A helicopter stall warning method includes receiving an airspeed of the helicopter, determining a stall airspeed based on multiple factors associated with the helicopter, the multiple factors comprising ambient temperature near the helicopter, the helicopter's altitude, and the helicopter's gross weight, determining a stall warning threshold derived from the stall airspeed, and providing a tactile warning through a collective helicopter control when the helicopter's airspeed meets or exceeds the stall warning threshold.
    Type: Grant
    Filed: January 25, 2016
    Date of Patent: February 28, 2017
    Assignee: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventor: Randall A. Greene
  • Patent number: 9533752
    Abstract: A method and apparatus for controlling flight control surfaces on an aircraft. Commands are sent onto a data bus system from flight control modules. The flight control modules and actuator control modules determine whether an error is present in the commands sent onto the data bus system. Point-to-point connections between the flight control modules and the actuator control modules are managed based on whether the error is present in the commands sent onto the data bus system.
    Type: Grant
    Filed: July 16, 2014
    Date of Patent: January 3, 2017
    Assignee: THE BOEING COMPANY
    Inventor: Ying Chin Yeh
  • Patent number: 9500478
    Abstract: A method of measuring an altitude in a portable terminal is provided. The method includes receiving a reference altitude from an information providing device fixed and installed at a certain point, measuring a current atmospheric pressure of the certain point, calculating an altitude of the certain position using the measured current atmospheric pressure and a reference atmospheric pressure, and storing a difference between the reference altitude and the calculated altitude of the certain point as an altitude error.
    Type: Grant
    Filed: June 3, 2013
    Date of Patent: November 22, 2016
    Assignee: Samsung Electronics Co., Ltd.
    Inventors: Gyejoong Shin, Dohyoung Chung
  • Patent number: 9457888
    Abstract: According to the invention, high lift leading-edge slats (13) and high lift flaps (14) are simultaneously deployed, when the speed of the aircraft is equal to and less than an AES threshold.
    Type: Grant
    Filed: June 7, 2007
    Date of Patent: October 4, 2016
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Franck Delaplace, Martin Richter, Dieter Lang
  • Patent number: 9415861
    Abstract: A control system for an aircraft high lift device includes a threshold setting unit configured to output one of a plurality of configuration change thresholds as an active output threshold, a threshold deactivation unit coupled to the threshold setting unit and configured to temporarily increase the active output threshold to a deactivation value, a configuration setting unit coupled to the threshold deactivation unit and configured to set the aircraft high lift device from a first configuration to a second configuration, if a measured value of an angle-of-attack of the aircraft exceeds the active output threshold, and a threshold control unit configured to control the threshold deactivation unit to temporarily increase the active output threshold to the deactivation value while the aircraft high lift device is mechanically moving from a first configuration to a second configuration.
    Type: Grant
    Filed: February 25, 2015
    Date of Patent: August 16, 2016
    Assignee: Airbus Operations GmbH
    Inventor: Martin Berens
  • Patent number: 9405312
    Abstract: An active control column transitionable to a fully passive state for an aircraft and methods of use are provided. The control column includes a passive feedback arrangement, a stick and a ground lock mechanism is provided. The passive feedback arrangement is moveable relative to a mechanical ground to adjust a feedback profile provided to the stick. The stick is movable relative to the mechanical ground and the passive feedback arrangement. The ground lock mechanism has a locked state in which the passive feedback arrangement is maintained in a fixed position relative to the mechanical ground. This places the control column in a fully passive state. The ground lock mechanism also has a normal state in which the passive feedback arrangement is permitted to move relative to the mechanical ground such that active feedback can be provided to the stick.
    Type: Grant
    Filed: July 28, 2010
    Date of Patent: August 2, 2016
    Assignee: Woodward MPC, Inc.
    Inventors: Darryl S. Stachniak, Thomas M. Rusak
  • Patent number: 9360869
    Abstract: Systems and methods for controlling aircraft obtain at least one of ground-referenced longitudinal movement data of the aircraft and ground-referenced lateral movement data of the aircraft. A round-referenced heading of the aircraft is obtained and a heading error is calculated based on a difference between the ground-referenced heading and a target heading. A lateral movement error value is generated based on at least one of the ground-referenced longitudinal movement data and ground-referenced lateral movement data, and based on the heading error.
    Type: Grant
    Filed: December 3, 2013
    Date of Patent: June 7, 2016
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Kenneth S. Wittmer, Stephen Kubik
  • Patent number: 9354635
    Abstract: An air/ground contact logic management system for use with fly-by-wire control systems in an aircraft. The system includes a first sensor configured to provide an output signal to determine when the aircraft is in a transition region. A logic management system is in communication with the first sensor and is configured to receive and process the output signal and classify a mode of the aircraft. A controller receives signal data from the logic management system and communicates with a control axis actuator to regulate a level of control authority provided to a pilot. The control authority is individually regulated within each integrator as a result of the individual landing gear states.
    Type: Grant
    Filed: June 5, 2012
    Date of Patent: May 31, 2016
    Assignee: Textron Innovations Inc.
    Inventor: Shyhpyng Jack Shue
  • Patent number: 9316205
    Abstract: A system and method for pressure based load measurement are provided. The system and method measure at least one pressure differential on an airfoil and determine at least one aerodynamic load associated with the at least one pressure differential. The determined at least one load is used to modify characteristics of the airfoil to increase efficiency and/or avoid damage. The determined at least one aerodynamic load may be further utilized to balance and/or optimize loads at the airfoil, estimate a load distribution along the airfoil used to derive other metrics about the airfoil, and/or used in a distributed control system to increase efficiency and/or reduce damage to, e.g., one or more wind turbines.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: April 19, 2016
    Assignee: Frontier Wind, LLC
    Inventors: Jonathon P. Baker, Edward A. Mayda
  • Patent number: 9274529
    Abstract: Method for autonomous safe emergency landing of a powered unmanned aerial vehicle (UAV) in the event of an engine failure. A landing approach trajectory is generated, including a downwind leg, initiating at an initiation point of the trajectory, an upwind leg, terminating at a selected touchdown point, and a U-turn leg, joining between the downwind leg and the upwind leg. The UAV is directed to the initiation point to follow the downwind leg. A glide ratio of the UAV is repeatedly determined based on current flight conditions. A current turning point is repeatedly determined along the downwind leg based on the determined glide ratio, the U-turn leg initiating at the current turning point. When the UAV arrives at the current turning point, the UAV is directed to follow the U-turn leg and the upwind leg, for landing the UAV at the selected touchdown point.
    Type: Grant
    Filed: February 21, 2013
    Date of Patent: March 1, 2016
    Assignee: Elbit Systems, LTD.
    Inventors: Eyal Ben-Shachar, Reuven Godel, Roy Mor
  • Patent number: 9262929
    Abstract: Embodiments described herein may help to automatically create flight plans that incorporate information regarding a number of different societal considerations. An illustrative computer-implemented method may involve receiving societal-consideration data for a plurality of geographic areas over which unmanned aerial vehicles (UAVs) are deployable. For a given geographic area from the plurality of geographic areas, the societal-consideration data may include one or more land-use indications for the geographic area that are indicative of a type of land use in the geographic area. The method may also involve, for each of one or more of the plurality of geographic areas: applying a cost function to the one or more land-use indications for the geographic area to determine a societal-consideration cost of UAV flight over the geographic area; and sending an indication of the determined societal-consideration cost to a computer-based flight planner.
    Type: Grant
    Filed: May 10, 2014
    Date of Patent: February 16, 2016
    Assignee: Google Inc.
    Inventors: Nick Roy, Leila Takayama, Mathias Samuel Fleck, Roger William Graves
  • Patent number: 9260180
    Abstract: A system and method are disclosed for automatic landing of an aircraft on a landing runway, including an on-board video camera intended to take images of the ground, image processor to extract from these images visual features of the landing runway, guidance system determining guidance commands of the aircraft to bring it into a nominal approach plane and to align it with the axis of the landing runway, from the respective positions of the visual features of the landing runway, in at least one of the images, where the guidance commands are supplied to a flight control computer.
    Type: Grant
    Filed: July 23, 2014
    Date of Patent: February 16, 2016
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Guilhem Puyou, Victor Gibert, Fabien Perrin
  • Patent number: 9257050
    Abstract: An onboard monitor that ensures the accuracy of data representing the calculated position of an airplane during final approach to a runway. This airplane position assurance monitor is a software function that uses dissimilar sources of airplane position and runway data to ensure the accuracy of the respective data from those dissimilar sources. ILS data and GPS or GPS/Baro data are the dissimilar sources of airplane position data used by this function. This function will calculate the airplane's angular deviations from the runway centerline and from the glide slope with onboard equipment and then compare those angular deviations to the ILS angular deviation information.
    Type: Grant
    Filed: December 9, 2013
    Date of Patent: February 9, 2016
    Assignee: The Boeing Company
    Inventors: Steven L. Fleiger-Holmes, Timothy Allen Murphy, Jean Marie Crane
  • Patent number: 9207328
    Abstract: Disclosed is a system for determination of attitude for a projectile in flight. The system includes at least one antenna mounted on the projectile. Each antenna is configured to receive Global Positioning System (GPS) signals. Further, the system includes a signal receiving unit communicably coupled to the each antenna to receive the GPS signals and to ascertain the earth referenced velocity vector. The system also includes a plurality of magnetometers for ascertaining a projectile referenced earth's magnetic field vector. Moreover, the system includes a processing unit. The processing unit is configured to utilize a known projectile referenced velocity vector and a stored prediction of the earth referenced earth's magnetic field vector along with the measured earth referenced velocity vector and the measured projectile referenced earth's magnetic field vector to determine the attitude of the projectile. Further disclosed is a method for determination of attitude for a projectile in flight.
    Type: Grant
    Filed: June 21, 2011
    Date of Patent: December 8, 2015
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventor: Robert D. Frey, Jr.
  • Patent number: 9170435
    Abstract: A method of projecting into space, from a first object, a plurality of modulated lines to form a grid defining a first relative reference frame, the method includes projecting polarized light having a first orientation to form a horizontal grid line projecting from the first object and projecting polarized light having a second orientation different than the first orientation to from a vertical grid line projecting from the first object and modulating the horizontal grid line and the vertical grid line to carry first and second grid words, respectively.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: October 27, 2015
    Assignee: GE Aviation Systems LLC
    Inventors: James Gerard Lopez, Jerry Lynne Page
  • Patent number: 9160980
    Abstract: An apparatus and method to enhance dead-reckoning navigation using inertial sensor measurements based on images from a camera are disclosed. A camera build into a mobile device is used to calibrate inertial sensors and rotation matrices. Images from a camera may be used (1) to remove a gravitational element from accelerometer measurements; (2) to set a scaling factor and an offset for a gyrometer; and (3) to set initial and updated values for rotation matrices.
    Type: Grant
    Filed: June 30, 2011
    Date of Patent: October 13, 2015
    Assignee: QUALCOMM Incorporated
    Inventor: Lionel J. Garin
  • Patent number: 9098997
    Abstract: Systems and methods for generating a predicted flight trajectory using a combination of aircraft state data, flight information, environmental information, historical data or derived flight information from aircraft messaging which can be used for the transmission of environmental data. The generated trajectory prediction is assigned a level of confidence based on fidelity, merit or accuracy. The level of predicted accuracy is based on the number of and sources of the specific information, time, distance or flight phase. The predicted trajectory includes pseudo-waypoints at flight transitions not readily available in the flight information and also includes the environmental conditions at all waypoint (including pseudo-waypoint) locations.
    Type: Grant
    Filed: September 30, 2011
    Date of Patent: August 4, 2015
    Assignee: The Boeing Company
    Inventors: Tamara S. Stewart, Louis J. Bailey, Charles J. Tytler
  • Patent number: 9078102
    Abstract: Various methods, apparatuses and/or articles of manufacture are provided which may be implemented using one or more fixed electronic devices to generate a reference data report corresponding to a particular environment. Various methods, apparatuses and/or articles of manufacture are provided which may be implemented using one or more mobile electronic devices to generate an environment report corresponding to a particular environment.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: July 7, 2015
    Assignee: QUALCOMM Incorporated
    Inventors: Stephen William Edge, Andreas Klaus Wachter, Lionel Jacques Garin, Grant Alexander Marshall
  • Patent number: 9053630
    Abstract: A method for providing a minimum safe altitude indication on an aircraft display is described. The method includes utilizing current aircraft heading and position data to generate a location and orientation for an own-ship depiction with respect to an aircraft display, utilizing the current position data, along with terrain data, to generate minimum safe altitude data for an area surrounding the aircraft, and displaying on the aircraft display, about the location for own-ship depiction, the minimum safe altitudes surrounding the aircraft.
    Type: Grant
    Filed: February 17, 2010
    Date of Patent: June 9, 2015
    Assignee: The Boeing Company
    Inventors: Jason W. Clark, Thorsten Wiesemann, Cindy Dorfmann
  • Patent number: 9038961
    Abstract: A method for simulating the movement behavior of a fluid in a closed moving container is provided. The simulation is based on the determination of the potential movement path of the center of gravity of the volume of the fluid as an elliptical trajectory situated in a disturbance plane having certain semi-axes.
    Type: Grant
    Filed: December 9, 2010
    Date of Patent: May 26, 2015
    Assignee: EADS Deutschland GmbH
    Inventor: Ronald Deslandes
  • 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
  • Publication number: 20150142223
    Abstract: A technique is directed to operating a UAV. The technique involves launching (or guiding) the UAV into flight. The technique further involves performing a series of aileron (or other control surface) deflection evaluations while the UAV is in flight. The technique further involves performing a UAV remedial operation in response to the series of aileron deflection evaluations indicating abnormal aileron behavior, e.g., the UAV can send a warning message to a ground control station (GCS), land the UAV at a target location, deploy a chute, and so on. Such operation enables detection of an unexpected change in the UAV's center of gravity, e.g., due to a blocked fuel bladder connection, icing on one side of the UAV, mechanical failure of an aileron, etc.
    Type: Application
    Filed: November 21, 2013
    Publication date: May 21, 2015
    Applicant: AAI Corporation
    Inventor: James M. Barbour
  • 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: 9027888
    Abstract: A method and system are presented for use in determination of the orientation of an aerospace platform with respect to a first rotation axis. A direction of a rotation rate vector of said aerospace platform within a lateral plane intersecting with said first rotation axis is measured and the measured data is analyzed to determine an orientation angle of said aerospace platform about said first rotation axis. While the aerospace platform is in a predetermined-dynamic state movement, a certain direction is determined by measuring a direction of the rotation rate of the aerospace platform within said lateral plane by a sensor assembly mounted on said platform and including at least one rotation rate sensor. An orientation of the platform with respect to said first axis is determined by determining a relation between said certain direction and said known direction within said external reference frame.
    Type: Grant
    Filed: August 4, 2011
    Date of Patent: May 12, 2015
    Assignee: Israel Aerospace Industries Ltd.
    Inventors: Rabin Shaltiel, Allan Kahane
  • Patent number: 9031718
    Abstract: An aircraft is provided with: an attitude control command calculating section which calculates an attitude control command for target attitude on the basis of a control stick operation amount; a gain value generating section which generates a gain value equal to or less than 1 which decreases as the control stick operation amount is larger; a multiplication section which multiplies the attitude control command for target attitude by the gain value; and a addition section which adds a rate damping control command to the attitude control command for target attitude multiplied by the gain value and outputs a result to a subtraction section for calculating an SAS command.
    Type: Grant
    Filed: October 12, 2012
    Date of Patent: May 12, 2015
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Yosuke Higuchi, Takeshi Matsuda
  • Patent number: 9020681
    Abstract: A method of displaying navigation limits for a planned travel route of a vehicle is presented here. The method calculates estimated navigation limits for the vehicle using an onboard subsystem of the vehicle, where the estimated navigation limits represent self-assessed navigation accuracy of the vehicle relative to the planned travel route. Contracted navigation limits are acquired for the vehicle, where the contracted navigation limits represent specified navigation accuracy of the vehicle, relative to the planned travel route, as mandated by a third party navigation controller. A navigation display is rendered on an onboard display element such that it includes graphical representations of the planned travel route, at least one of the estimated navigation limits, and at least one of the contracted navigation limits.
    Type: Grant
    Filed: June 8, 2010
    Date of Patent: April 28, 2015
    Assignee: Honeywell International Inc.
    Inventors: Petr Krupansky, Jiri Vasek, Pavel Kolcarek, Tomas Neuzil, John A. Wise
  • Patent number: 9014880
    Abstract: A trajectory-based sense-and-avoid system for use on an aircraft is provided that utilizes 4-D constructs, such as 4-D trajectories or 4-D polytopes, to maintain separation from other aircraft and/or to avoid collisions with other aircraft. In certain embodiments the trajectory-based sense-and-avoid system utilizes 4-D trajectories provided from an external source and/or 4-D trajectories estimated based on a variety of data sources during operation.
    Type: Grant
    Filed: December 21, 2010
    Date of Patent: April 21, 2015
    Assignee: General Electric Company
    Inventors: Michael Richard Durling, Harold Woodruff Tomlinson, Jr., Nikita Visnevski, Craig Alan Hoover, Glenn Alan Forman, Thomas Baby Sebastian, Mauricio Castillo-Effen, Steven Richard Hansen, Douglas Stuart Abernathy
  • Patent number: 9008872
    Abstract: A system for configuring landing supports of a load to land on uneven terrain includes a terrain sensor configured to detect a terrain characteristic of the uneven terrain. The system further includes landing supports configured to support the load upon landing. The system also includes a support control device operatively coupled to the landing supports, and a landing support control computer that is operatively coupled to the terrain sensor, landing supports, and support control device. The landing support control computer may determine if landing on the uneven terrain is allowable, based on the terrain characteristic and a load characteristic of the load. Upon determining that landing on the uneven terrain is allowable, the support control device configures the landing supports for landing on the uneven terrain.
    Type: Grant
    Filed: October 4, 2012
    Date of Patent: April 14, 2015
    Assignee: The Boeing Company
    Inventors: William Peck Pflug, Charles Briggs Spinelli
  • Patent number: 9008869
    Abstract: A low-altitude altimeter (10) and a method of determining low altitudes for unmanned aerial vehicles (24). The altimeter includes at least two illuminators (12, 14), at least one sensor (16), and a computing device (18). The illuminators (12, 14) emit signals which are received by the sensor (16) in such a way that an angle at which they are received is determinable by the computing device (18). The computing device (18) processes each signal received by the sensor (16), determines the angle at which the sensor (16) received the signal, and, based thereon, determines the altitude of the unmanned aerial vehicle (24). When a first pair of illuminators are arranged along a fuselage axis, and a second pair of illuminators are arranged orthogonally to that axis, the computing device can combine first and second altitude, pitch angle, and roll angle measurements to provide a more refined altitude determination.
    Type: Grant
    Filed: November 1, 2013
    Date of Patent: April 14, 2015
    Assignee: University of Kansas
    Inventors: Christopher T. Allen, Trenton Shuey, Rongqing Hui
  • 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
  • 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