Automatic Or Condition Responsive Control Patents (Class 244/17.13)
  • Patent number: 10537812
    Abstract: Methods for interactive communication between an object and a smart device are provided. Signals can be transmitted from the smart device to the object to control movement of a movable part at the object. Signals can also be transmitted from the smart device to the object to broadcast words and/or songs at a speaker at the object. In addition, in response to a user's touching the object, the object's speaker can broadcast words and/or songs. The signals transmitted from the smart device to the object transceiver can be audio signals so as to create a two-way interactive and live communication. In addition, voice instructions can be spoken into the microphone of the object, and then transmitted from the object to the smart device to initiate an activity at the smart device.
    Type: Grant
    Filed: March 29, 2018
    Date of Patent: January 21, 2020
    Assignee: Future of Play Global Limited
    Inventor: To Sun Wong
  • Patent number: 10538327
    Abstract: In some embodiments, methods and systems of facilitating movement of product-containing pallets include at least one forklift unit configured to lift and move the product-containing pallets, at least one motorized transport unit configured to mechanically engage and disengage a respective forklift unit, and a central computer system in communication with the at least one motorized transport unit. The central computer system is configured to transmit at least one signal to the at least one motorized transport unit. The signal is configured to cause the at least one motorized transport unit to control the at least one forklift unit to move at least one of the product-containing pallets.
    Type: Grant
    Filed: May 2, 2017
    Date of Patent: January 21, 2020
    Assignee: Walmart Apollo, LLC
    Inventors: Donald R. High, Nathan G. Jones, Gregory A. Hicks
  • Patent number: 10533851
    Abstract: An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.
    Type: Grant
    Filed: March 18, 2018
    Date of Patent: January 14, 2020
    Assignee: AeroVironment, Inc.
    Inventors: Christopher E. Fisher, Thomas Robert Szarek, Justin B. McAllister, Pavel Belik
  • Patent number: 10518865
    Abstract: In one embodiment, a horizontal stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a horizontal orientation. The airfoil structure comprises a leading edge, a trailing edge, a top surface, and a bottom surface. Moreover, the airfoil structure is cambered, wherein a camber of the airfoil structure forms a concave slope on the top surface and a convex slope on the bottom surface.
    Type: Grant
    Filed: May 11, 2017
    Date of Patent: December 31, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Brendan P. Lanigan, Joshua R. O'Neil
  • Patent number: 10494121
    Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.
    Type: Grant
    Filed: October 23, 2018
    Date of Patent: December 3, 2019
    Assignee: Tribune Boradcasting Company, LLC
    Inventor: Hank J. Hundemer
  • Patent number: 10479490
    Abstract: A system for video imaging and photographing using an autonomous aerial platform. The system may be a quad rotor system using electrically powered propellers. The aerial platform may be commanded by the user to follow an object of interest. The aerial platform may have multiple configurations for its thrust units such that they are clear of the field of view of the imaging device in a first configuration, such that they protect the imaging device during landing in a second configuration, and that allows for efficient storage in a stowed configuration.
    Type: Grant
    Filed: December 21, 2016
    Date of Patent: November 19, 2019
    Inventors: JoeBen Bevirt, Andy Clark
  • Patent number: 10481615
    Abstract: A method of operating a rotorcraft includes transitioning from a first mode to a second mode when a velocity of the rotorcraft exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time. In the first mode, the translational speed of the rotorcraft is determined based on a pilot stick signal, and in the second mode, an output of an attitude rate controller is proportional to an amplitude of the pilot stick signal.
    Type: Grant
    Filed: March 1, 2017
    Date of Patent: November 19, 2019
    Assignee: Bell Textron Inc.
    Inventor: Sung Kyun Kim
  • Patent number: 10472058
    Abstract: A vertical takeoff and landing (VTOL) fixed-wing aircraft having overlapping propellers and low handing vertical stabilizers disposed on the rear end of the aircraft.
    Type: Grant
    Filed: March 15, 2019
    Date of Patent: November 12, 2019
    Assignee: SHANGHAI AUTOFLIGHT CO., LTD.
    Inventor: Yu Tian
  • Patent number: 10474237
    Abstract: A method for providing haptic feedback to a user of a rotary wing aircraft that includes receiving, by a computing device, a signal indicative of a user input selecting a control system state for a rotary wing aircraft, where, upon selection, the control system state modifies one or more operational parameters of the rotary wing aircraft, and in response to receiving the signal, outputting, by the computing device, a signal to a shaker system coupled to a collective stick, where the signal is configured to cause the shaker system to provide a haptic feedback via the collective stick, and where the haptic feedback includes a signature that indicates that the control system state has been activated.
    Type: Grant
    Filed: July 25, 2017
    Date of Patent: November 12, 2019
    Assignee: Rolls-Royce Corporation
    Inventor: Paul Gush
  • Patent number: 10429843
    Abstract: An automatic piloting system intended for an aircraft comprising an aircraft signals acquisition module, a module for interfacing with the crew, and a module for processing the output signals, comprises: a generic software kernel for automatic piloting aboard the aircraft, comprising several parameterizable elementary cells, a parameterization tool for the generic software kernel, able to transform an operational need of the automatic piloting system, expressed by means of a configuration file in accordance with a predetermined configuration domain DC, into a database of binary parameters DB able to parameterize the generic software kernel; each cell being parameterized by the database DB, and means for loading and storage aboard the aircraft of the database DB.
    Type: Grant
    Filed: April 24, 2013
    Date of Patent: October 1, 2019
    Assignee: THALES
    Inventors: Rodolphe Devaureix, Arnaud Bonnafoux, Jerome Birre
  • Patent number: 10400851
    Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly with an upper blade and a lower rotor assembly with a lower blade. A first antenna in one of upper blade and the lower blade, and a second antenna in the other of the upper blade and the lower blade. An oscillator to apply an excitation signal to the first antenna. A blade proximity monitor to monitor a magnitude of the excitation signal and an output signal from the second antenna to determine a distance between the upper blade and the lower blade.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: September 3, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Maximilian August Koessick, Michael J. Kostoss, Eric Lucien Nussenblatt, Justin Thomas, Christopher Paul Butler, Brandon Michael Cerge
  • Patent number: 10392102
    Abstract: A rotary wing aircraft including a vehicle vibration control system.
    Type: Grant
    Filed: August 30, 2017
    Date of Patent: August 27, 2019
    Assignee: LORD Corporation
    Inventors: Mark R. Jolly, Russell E. Alteri, Askari Badre-Alam, Douglas E. Ivers, Douglas A. Swanson, Daniel Mellinger, Andrew D. Meyers
  • Patent number: 10392105
    Abstract: A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range.
    Type: Grant
    Filed: July 5, 2017
    Date of Patent: August 27, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Joseph M. Schaeffer, Jignesh Patel, Eric O'Neill
  • Patent number: 10384778
    Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.
    Type: Grant
    Filed: September 10, 2018
    Date of Patent: August 20, 2019
    Assignee: Tribune Broadcasting Company, LLC
    Inventor: Hank J. Hundemer
  • Patent number: 10386843
    Abstract: In accordance with an embodiment, a method of operating a rotorcraft includes operating the rotorcraft in a position hold mode by determining whether GPS position data is usable, receiving a position of the rotorcraft from a GPS sensor, determining a position error based on received GPS position data and a held position when the GPS position data is usable, determining the position error based on a rotorcraft velocity when the GPS position data is not usable, and transmitting an actuator command based on the determined position error.
    Type: Grant
    Filed: April 3, 2017
    Date of Patent: August 20, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventor: Robert Earl Worsham, II
  • Patent number: 10370093
    Abstract: Techniques for calculating a sound received at a plurality of distances from an unmanned aerial vehicle (UAV) may be provided. For example, during delivery, the UAV may be associated with a sensor to obtain first sound information that corresponds to the sound generated by the UAV. A sensor associated with a landing marker may obtain second sound information about the sound generated by the UAV during flight and delivery of a payload to a location associated with the landing marker. In embodiments, the first sound information and the second sound information may be utilized to calculate sound metrics for the sound generated by the UAV and determine the sound received at a plurality of distances from the UAV during flight.
    Type: Grant
    Filed: November 16, 2016
    Date of Patent: August 6, 2019
    Assignee: Amazon Technologies, Inc.
    Inventors: Brian C. Beckman, Eric Berlinberg, John Raymond Brodie, Emilia Sorana Buneci
  • Patent number: 10374466
    Abstract: A commercially available vehicle is modified by coupling a beamed-power transmission system to the vehicle's frame. The beamed-power transmission system is arranged to deliver beamed power to a remote device such as an unmanned aerial vehicle (i.e., UAV or drone). The cooling system of the vehicle is used to cool portions of the beamed-power transmission system. An aiming system aims a power beam produced by the beamed-power transmitter toward the remote device, and a stability system coupled to both the vehicle frame and the beamed-power transmission system maintains three-dimensional constancy of the power beam even when the vehicle frame is in motion. The commercially available vehicle may be an electric vehicle, a gas-electric hybrid vehicle, or the like having a power source that includes batteries, a fuel-cells, or a generator.
    Type: Grant
    Filed: August 11, 2016
    Date of Patent: August 6, 2019
    Assignee: LASERMOTIVE, INC.
    Inventors: Claes Olsson, Thomas J. Nugent, Jr.
  • Patent number: 10364797
    Abstract: The invention relates to a method for controlling a wind turbine in partial and full load. In order to avoid disadvantages of switching between partial and full load controllers, the wind turbine control system is configured so that both the partial and full load controller provides control action during partial and full load. For that purpose, the partial and full load controllers are configured with variable gains, wherein gain scheduling is performed so that the gain of partial load controller is larger than the gain of the full load controller during partial load and vice verso so that the gain of the full load controller is larger than the gain of the partial load controller during full load.
    Type: Grant
    Filed: January 27, 2016
    Date of Patent: July 30, 2019
    Assignee: VESTAS WIND SYSTEMS A/S
    Inventors: Fabio Caponetti, Jesper Sandberg Thomsen, Jacob Deleuran Grunnet
  • Patent number: 10359785
    Abstract: A rotary wing aircraft control system includes an airframe, a main rotor assembly supported by the airframe, and a control system arranged in the airframe and operatively connected to the main rotor assembly. The control system includes a flight control computer (FCC), at least one control inceptor device and a touchdown orientation control system. The touchdown orientation control system includes a computer readable program code an FCC to: sense, by a sensor operatively connected to the flight control computer (FCC), an altitude of the rotary wing aircraft relative to a landing surface, determine one of a landing state rearward velocity reference limit value and a landing state lateral velocity reference limit value associated with the altitude, and selectively limit a landing state flight envelope of the rotary wing aircraft to the one of the landing state rearward velocity reference limit value and the landing state lateral velocity reference limit value.
    Type: Grant
    Filed: January 11, 2017
    Date of Patent: July 23, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Anthony Litwinowicz
  • Patent number: 10360737
    Abstract: A method of drive system diagnostics of an aircraft includes capturing high load drivetrain component vibration data at select steady-state and/or high-load transient operating conditions of the aircraft and processing the captured vibration data to improve reliability and/or accuracy of captured vibration data. The processed vibration data is utilized to provide a health assessment of the drivetrain components and achieve earlier detection of incipient faults. A health monitoring system for drivetrain components of an aircraft includes a plurality of vibration sensors positioned at drivetrain components of an aircraft to capture drivetrain component vibration data at transient operating conditions of the aircraft. One or more processing modules process the captured vibration data to improve reliability and/or accuracy of the captured data, and a fault reasoning module calculates a health indicator of the drivetrain components.
    Type: Grant
    Filed: April 2, 2015
    Date of Patent: July 23, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Jeremy Sheldon, David Kasper, Mark W. Davis
  • Patent number: 10351229
    Abstract: A rotor blade is provided. The rotor blade includes a blade portion, a tip cap formed to define a dimple, a fastener and a doubler. The fastener includes a flat-headed shaft and is disposable such that the flat-headed shaft extends through the blade portion and the tip cap at the dimple. The fastener is configured to urge the blade portion toward the tip cap. The doubler includes a dimpled portion disposable between the tip cap and a portion of the flat-headed shaft at the dimple and an exterior portion. The exterior portion is disposable flush with respective exterior surfaces of the blade portion and the flat-headed shaft.
    Type: Grant
    Filed: March 12, 2015
    Date of Patent: July 16, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Richard Joseph Simkulak, Michael J. Shimkus
  • Patent number: 10351225
    Abstract: A method for position hold override control of an aircraft includes determining, by a processor, that a position hold mode is enabled to hold the aircraft at a substantially fixed position with respect to a target. The processor receives a control input indicative of a commanded change in acceleration of the aircraft as an override of the position hold mode. The processor determines an acceleration command based on the commanded change in acceleration. The acceleration command is adjusted as an adjusted acceleration command responsive to a non-linear scheduled translational rate command based on feedback of a commanded velocity of the aircraft. An update to the commanded velocity of the aircraft is generated based on the adjusted acceleration command.
    Type: Grant
    Filed: March 4, 2016
    Date of Patent: July 16, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Steven E. Spoldi, Alex Faynberg, Stephen Kubik, Donald T. Ream, John Rucci, Stephen C. McCulley, Christiaan Corry
  • Patent number: 10349649
    Abstract: An animal trap device is disclosed and includes a base, a circular cover plate, an elastic element and an elastic lasso. The circular cover plate further includes a top portion, and a surrounding portion; wherein the surrounding portion surrounds a circumference of the top portion. The top portion has a support disc and a flange protruding from a side surface of the support disc. The elastic element is configured between the base and the circular cover plate, and adapted to provide the top portion with an upward elastic force. The elastic lasso is wound around the surrounding portion, and positioned below the flange. The elastic lasso will be blocked by the flange and the surrounding portion, retained in an open position until leaving the surrounding portion when the top portion is exerted with a force to move downward.
    Type: Grant
    Filed: May 25, 2017
    Date of Patent: July 16, 2019
    Assignee: CIXI HAOSHENG ELECTRONICS & HARDWARE CO., LTD.
    Inventor: Jin-Jun Cao
  • Patent number: 10351230
    Abstract: According to one aspect, a method of initial rotor state compensation for a rotorcraft includes determining a vehicle attitude of the rotorcraft prior to takeoff of the rotorcraft. A rotor state compensation is computed based on the vehicle attitude. A plurality of rotor servos is commanded to an initial rotor state based on a nominal rotor neutral position value in combination with the rotor state compensation to establish a predetermined takeoff trajectory of the rotorcraft.
    Type: Grant
    Filed: July 17, 2015
    Date of Patent: July 16, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Igor Cherepinsky, Joseph T. Driscoll
  • Patent number: 10343771
    Abstract: A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.
    Type: Grant
    Filed: February 6, 2019
    Date of Patent: July 9, 2019
    Assignee: Kaiser Enterprises, LLC
    Inventors: James Kaiser, William Vatis
  • Patent number: 10338090
    Abstract: An airspeed estimation system of an aircraft includes an electronic airspeed rate modeler unit configured to output an estimated airspeed rate signal indicating an estimated airspeed rate of the aircraft. The estimated airspeed rate signal is based on a longitudinal body acceleration of the aircraft and at least one adaptive parametric airspeed model. The airspeed estimation system further includes an electronic airspeed estimator unit in signal communication with the airspeed rate modeler unit. The airspeed estimator unit is configured to determine an estimated airspeed of the aircraft based on the estimated airspeed rate signal.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: July 2, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Dale R. Bailey, Jr., Antonio Rivera
  • Patent number: 10315758
    Abstract: A propulsion system comprising independent rotor sub-systems producing a thrust force of a desired magnitude in any desired radial direction from the center of the propulsion system, driven from a single driveshaft that may be fixed in its position in the vehicle. When the propulsion system is fitted, for example, to a single-main-rotor helicopter in place of the convention anti-torque tail rotor, the helicopter is thereby equipped with a propulsion system that can produce yaw, pitch, the anti-torque lateral thrust for stability in hover, aft thrust or drag as well as the direct forward thrust that will enable the helicopter to fly at higher speeds. The propulsion system may also be applied in other aeronautical systems as well as to marine and industrial systems to impart energy into a fluid and thereby induce movement in that fluid.
    Type: Grant
    Filed: August 19, 2014
    Date of Patent: June 11, 2019
    Inventor: Martin Leon Adam
  • Patent number: 10317914
    Abstract: An unmanned aircraft includes a forward propulsion system comprising one or more forward thrust engines and one or more corresponding rotors coupled to the forward thrust engines; a vertical propulsion system comprising one or more vertical thrust engines and one or more corresponding rotors coupled to the vertical thrust engines; a plurality of sensors; and a yaw control system, that includes a processor configured to monitor one or more aircraft parameters received from at least one of the plurality of sensors and to enter a free yaw control mode based on the received aircraft parameters.
    Type: Grant
    Filed: April 18, 2016
    Date of Patent: June 11, 2019
    Assignee: LATITUDE ENGINEERING, LLC
    Inventors: Jason Michael K. Douglas, Justin Armer, Carlos Murphy
  • Patent number: 10310498
    Abstract: Various systems and methods for disabling UAVs are presented. An interrogation system may transmit an identifier request message to a UAV. The interrogation system may receive, in response to the identifier request message, a response message that indicates a UAV identifier. The interrogation system may access one or more UAV identifier databases that relate UAV identifiers with airspace definitions. The interrogation system may retrieve from the one or more UAV identifier database systems an airspace definition corresponding to the UAV identifier. The interrogation system may determine that the UAV is to be disabled based on: a location of the UAV, a restricted airspace definition, and the airspace definition corresponding to the UAV identifier. The interrogation system may then transmit a disablement instruction message to the UAV based on the location of the UAV and the airspace definition corresponding to the UAV identifier.
    Type: Grant
    Filed: June 16, 2016
    Date of Patent: June 4, 2019
    Assignee: EchoStar Technologies International Corporation
    Inventor: Edmund Petruzzelli
  • Patent number: 10302736
    Abstract: In one representative embodiment, a method of detecting position relative to a wind turbine can comprise detecting a condor within a detection area, determining a first position of the condor relative to the wind turbine, assigning the condor to a first predetermined zone of a plurality of predetermined zones based on the first position, determining a second position of the condor relative to the wind turbine, assigning the condor to a second predetermined zone of the plurality of predetermined zones based on the second position, predicting a trajectory of the condor based on a relationship between the first position and the second position.
    Type: Grant
    Filed: November 16, 2015
    Date of Patent: May 28, 2019
    Inventors: Christine Sutter, Chuck Grandgent, Amy Parsons, Sara Parsons, Stuart Webster
  • Patent number: 10265855
    Abstract: Disclosed are a wall-climbing aerial robot mechanism and a method of controlling the same. The method of controlling a wall-climbing aerial robot includes allowing the aerial robot to fly towards a structure, allowing the aerial robot to approach the structure and recognize a wall of the structure, allowing the aerial robot to calculate a trajectory for landing on the wall of the structure, approach the wall of the structure after taking an orientation, and be attached on the wall of the structure, and allowing the aerial robot to move along the wall of the structure to perform a task.
    Type: Grant
    Filed: October 27, 2016
    Date of Patent: April 23, 2019
    Assignee: Korea Advanced Institute of Science and Technology
    Inventors: Hyeon Myeong, Wancheol Myeong, Kwang Yik Jung, Yonghun Jeong, Jae-Uk Shin
  • Patent number: 10266259
    Abstract: Systems, methods, and apparatuses for increasing the mechanical energy of an aerial vehicle as part of an Airborne Wind Turbine are disclosed. The aerial vehicle is coupled to a distal portion of a tether and a ground station is coupled to a proximal portion of the tether. A mass possessing a gravitational potential energy is also coupled to the proximal portion of the tether. A connector is configured to releasably hold the mass at an elevation. Release of the mass transfers energy to the aerial vehicle by increasing tension in the tether.
    Type: Grant
    Filed: December 20, 2016
    Date of Patent: April 23, 2019
    Assignee: Makani Technologies LLC
    Inventor: Thomas Van Alsenoy
  • Patent number: 10252812
    Abstract: A system for an aircraft having a first gas turbine engine and a second gas turbine engine includes a first engine controller comprising a first motion sensor. The first motion sensor defines a first orthogonal coordinate system, and is configured for determining first motion sensor data indicating motion of the aircraft along at least one axis of the first orthogonal coordinate system. The system further includes a second engine controller comprising a second motion sensor spaced apart from the first motion sensor. The second motion sensor defines a second orthogonal coordinate system, and is configured for determining second motion sensor data indicating motion of the aircraft along at least one axis of the second orthogonal coordinate system. In addition, the second engine controller is communicatively coupled to the first engine controller such that the first engine controller receives the second motion sensor data.
    Type: Grant
    Filed: September 28, 2016
    Date of Patent: April 9, 2019
    Assignee: General Electric Company
    Inventor: David Allen Gutz
  • Patent number: 10228691
    Abstract: The present invention extends to methods, systems, devices, and apparatus for augmented radar camera view for remotely operated vehicles. A camera and a radar unit are co-located on a remotely controlled aerial vehicle, for example, in a forward looking view. The camera captures images and the radar unit senses reflections from transmitted waves. The images (operator view) and radar returns (radar view) are combined in an augmented view. The augmented view is displayed to an operator (e.g., a pilot) at a control station to provide the operator with an augmented reality sense of obstacles in the environment of the remotely controlled aerial vehicle. Thus, when a remotely controlled aerial vehicle is flying through an environment that may be dark, clouded, foggy, etc., the operator may still be able to detect obstacles from the radar view.
    Type: Grant
    Filed: March 31, 2017
    Date of Patent: March 12, 2019
    Assignee: Olaeris, Inc.
    Inventors: Paul E. I. Pounds, Edward Lindsley
  • Patent number: 10227140
    Abstract: A method detects an impendent situation of an operating aircraft. The method comprises receiving data corresponding to a plurality of parameters related to an operation of the aircraft. It is determined if any of the plurality of parameters is at or beyond at least a first respective threshold by comparing the plurality of parameters with the first respective thresholds. If at least one of the parameters is an outlier parameter at or beyond its first respective threshold, another or others of the plurality of parameters associated to the at least one outlier parameter is identified, the at least one other parameter being selected based on a predetermined combination of parameters representative of an adverse condition. The associated parameters are compared with a stored data combination threshold specific to the associated parameters. A signal indicative of an impending situation is output if the associated parameters are on or beyond the data combination threshold.
    Type: Grant
    Filed: July 14, 2015
    Date of Patent: March 12, 2019
    Assignee: CMC ELECTRONICS INC
    Inventor: David Edward McKay
  • Patent number: 10222792
    Abstract: A device (15) for piloting a drone (10) comprising a touch screen (18) displaying a touch-sensitive area, means for detecting signals emitted by the touch-sensitive area, and means for transforming said detected signals into piloting commands and transmitting said commands to the drone. The device comprises control means, controlled by the touch-sensitive area forming activation/deactivation button, to make the drone piloting mode alternately switch between a mode of activation of the system for holding the last detected commands, mode in which said piloting commands transmitted to the drone result from the transformation of the last detected signals before the switching to the activation mode, and a mode of deactivation of the system for holding the last detected commands, mode in which said piloting commands transmitted to the drone result from the transformation of the current detected signals. The invention also relates to an associated method for controlling a drone.
    Type: Grant
    Filed: October 14, 2016
    Date of Patent: March 5, 2019
    Assignee: Parrot Drones
    Inventor: Martin Line
  • Patent number: 10216187
    Abstract: A vehicle includes a frame, drive elements configured to drive movements of the frame, and a computer configured to receive mission planning and manual commands and to control operations of the drive elements to operate in a safe mode in which mission commands are accepted but manual commands are refused, a manual mode in which mission commands are refused but manual commands are accepted and an enroute mode. The computer is further configured to only allow mode transitions directly between the safe mode and the manual mode and directly between the safe mode and the enroute mode.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: February 26, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Thomas Zygmant, Jesse J. Lesperance, Ira E. Zoock, James A. Kelly
  • Patent number: 10176709
    Abstract: A system and method are disclosed for remotely operating a shut-off valve of a gas meter. The gas meter includes a meter housing having a shut-off valve disposed within. An optical control system enables the shut-off valve to be operated with optical signals input to the meter.
    Type: Grant
    Filed: April 29, 2016
    Date of Patent: January 8, 2019
    Assignee: Honeywell International Inc.
    Inventors: Joshua Jorgensen, Albert Sauer
  • Patent number: 10168601
    Abstract: According to a first aspect of the present invention there is provided an arrangement comprising, a volitant body comprising at least one actuator; a control unit for controlling said actuator; and a mechanical arrangement for operationally connecting said volitant body to a reference point remote from said volitant body. There is further provided a corresponding method for operating such an arrangement.
    Type: Grant
    Filed: September 5, 2017
    Date of Patent: January 1, 2019
    Assignee: Perspective Robotics AG
    Inventors: Markus Waibel, Sergei Lupashin, Markus Hehn, Raffaello D'Andrea
  • Patent number: 10167079
    Abstract: An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe. A flight control computer is configured to control a main rotor rotational speed of the upper and the lower rotor assemblies of the main rotor assembly as a function of airspeed of the aircraft. A method of operating an aircraft includes retrieving a threshold main rotor rotational speed of the dual coaxial main rotor assembly and calculating an actual main rotor rotational speed according to an environment of the aircraft. The actual main rotor rotational speed is maintained to remain at or below the threshold main rotor speed according to an airspeed of the aircraft.
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: January 1, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Steven D. Weiner, William J. Eadie
  • Patent number: 10138002
    Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.
    Type: Grant
    Filed: July 14, 2016
    Date of Patent: November 27, 2018
    Assignee: Tribune Broadcasting Company, LLC
    Inventor: Hank J. Hundemer
  • Patent number: 10113487
    Abstract: A control system for a gas turbine engine is disclosed. The control system may include a computer processor. The control system may also include an outer loop control module programmed into the computer processor to determine a torque request based at least in part on a real-time collective lever angle command. The control system may also include an inner loop control module programmed into the computer processor to receive the torque request from the outer loop control module, to determine fuel flow and inlet guide vane schedules based at least in part on the received torque request, and to send signals to a gas generator of the gas turbine engine in order to control the gas generator according to the determined fuel flow and inlet guide vane schedules.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: October 30, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Chaohong Cai, Timothy J. Crowley, Richard P. Meisner
  • Patent number: 10112709
    Abstract: A rotor system includes a hub assembly, a first, second, and third rotor blade rotatably attached to the hub assembly, a first, second, and third damper pivotally attached to the hub assembly and pivotally attached to the first, second, and third rotor blade, respectively, and a control system operably associated with the first, second, and third damper. A method to control vibratory forces exerted on the hub assembly via the first and second rotor blade includes separately controlling a dynamic spring rate of each of the first and second dampers with the control system.
    Type: Grant
    Filed: September 23, 2014
    Date of Patent: October 30, 2018
    Assignee: Bell Helicopter Textron Inc.
    Inventors: David E. Heverly, II, Frank B. Stamps, Michael Smith
  • Patent number: 10099782
    Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.
    Type: Grant
    Filed: July 14, 2016
    Date of Patent: October 16, 2018
    Assignee: Tribune Broadcasting Company, LLC
    Inventor: Hank J. Hundemer
  • Patent number: 10092849
    Abstract: A hover-control method for multirotor unmanned aerial vehicle (UAV) upcast at any angle to take off is applied to correct at least one tilt angle of the multirotor UAV by dual-feedback schemes. When any of the at least one tilt angle is greater than a corresponding angle limitation, an open feedback scheme is executed to drive a plurality of motors of the multirotor UAV until a predetermined condition is achieved. When all of the at least one tilt angle are not larger than the respective angle limitations, a negative feedback scheme is executed to drive the motors of the multirotor UAV until a hover condition is achieved.
    Type: Grant
    Filed: June 2, 2016
    Date of Patent: October 9, 2018
    Assignee: WISTRON CORPORATION
    Inventors: Zhen-Te Liu, Yu-Yen Chen
  • Patent number: 10086935
    Abstract: A propulsor system for a rotary winged aircraft includes a propeller including having a propeller hub rotatable about a propeller axis and a plurality of propeller blades secured to and extending radially outwardly from the propeller hub. The propeller is oriented on the rotary winged aircraft to provide forward thrust for the rotary winged aircraft when the propeller is rotated about the propeller hub. A plurality of guide vanes non rotatable about the propeller axis are positioned upstream of the plurality of propeller blades. The plurality of guide vanes are positioned to turn an airflow flowing into the plurality or propeller blades, thereby reducing an angle of attack of the plurality of propeller blades relative to the airflow.
    Type: Grant
    Filed: December 9, 2015
    Date of Patent: October 2, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Colman D. Shattuck, Peter F. Lorber, Blake Almy Moffitt, Peter J. Germanowski, Brian E. Wake, Steven D. Weiner
  • Patent number: 10081432
    Abstract: A structure of drone (100) comprises a frame (110) comprising an engagement portion (110?), said engagement portion (110?) being a strip having a predetermined geometry. The structure of drone (100) also comprises a plurality of propulsion elements (120). Each propulsion element (120) is arranged, in use, to be engaged in a removable way to the engagement portion (110?) at a any point of the strip, in such a way to easily change the number and the arrangement of the propulsion elements (120) present on the engagement portion (110?).
    Type: Grant
    Filed: September 5, 2014
    Date of Patent: September 25, 2018
    Assignee: UNIVERSITA DEGLI STUDI DI FIRENZE
    Inventors: Guglielmo Rossi, Sandro Moretti, Nicola Casagli
  • Patent number: 10065734
    Abstract: The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.
    Type: Grant
    Filed: October 1, 2015
    Date of Patent: September 4, 2018
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Robert Earl Worsham, II, John Joseph Schillings, Charles Eric Covington
  • Patent number: 10054955
    Abstract: The system includes a rudder bar configured to be able to be actuated by a pilot of the aircraft, a unit for automatically detecting a position value corresponding to a position of the rudder bar, an auxiliary unit for generating a trim value, a computation unit configured to generate a control value as a function of the position value of the rudder bar and of the trim value. The computation unit is configured to generate the control value according to a nonlinear kinematic relative to the position value of the rudder bar.
    Type: Grant
    Filed: December 11, 2015
    Date of Patent: August 21, 2018
    Assignee: Airbus Operations S.A.S.
    Inventors: Patrice Brot, Sylvain Devineau
  • Patent number: 10040544
    Abstract: A flying vehicle with a fuselage having a longitudinal axis, a cockpit extending substantially from the center of the fuselage, a left front wing extending from the fuselage, a right front wing extending from the fuselage, a left rear wing extending from the fuselage, a right rear wing extending from the fuselage. Each wing contains a rotor rotatably mounted and a direct drive brushless motor providing directional control of the vehicle. A centrally located ducted fan encompasses the cockpit and provides VTOL capabilities. The central location of the cockpit and central ducted fan aid in balance and stability. The central ducted fan is itself a brushless motor with the stator windings encapsulated in the ducted fan housing and rotor magnets within the fan. All motors and rotatable mounts are controlled by a fly-by-wire system integrated into a central computer with avionics allowing for autonomous flight.
    Type: Grant
    Filed: January 4, 2016
    Date of Patent: August 7, 2018
    Inventor: Jesse Antoine Marcel