Electric Course Control Patents (Class 244/175)
  • Patent number: 11181934
    Abstract: The present disclosure provides systems and methods for predicting ground effects along a flight plan. The systems and methods provide a processor executed process including the steps: receiving a flight plan for a vertical take-off and landing (VTOL) aircraft; receiving terrain and obstacles geospatial data for the flight plan from the database; determining weight of the VTOL aircraft along the flight plan; determining temperature of the environment along the flight plan; determining ground effect data along the flight plan based on the temperature and the weight; based on the terrain and obstacles data, the ground effect data and the flight plan, predict where, along the flight plan, the VTOL aircraft will traverse a ground effect region, thereby providing prediction data; and generating one or more commands to control a system of the VTOL aircraft based on the prediction data.
    Type: Grant
    Filed: July 2, 2020
    Date of Patent: November 23, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Sriram P R, Lisa Fern, Sivakumar Kanagarajan
  • Patent number: 11176007
    Abstract: A redundant processing fabric in an autonomous vehicle may include processing, by a first processing unit of a plurality of processing units, sensor data from a first sensor of a plurality of sensors, where the plurality of processing units are coupled to the plurality of sensors via a switched fabric, wherein the plurality of processing units and plurality of sensors are included in the autonomous vehicle; determining a failure in processing the sensor data by the first processing unit; and redirecting, via the switched fabric, sensor data from the first sensor a redundant processing unit.
    Type: Grant
    Filed: April 12, 2019
    Date of Patent: November 16, 2021
    Assignee: GHOST LOCOMOTION INC.
    Inventors: John Hayes, Volkmar Uhlig
  • Patent number: 11089208
    Abstract: The disclosure describes systems and methods for a stabilization mechanism. The stabilization mechanism may be used in conjunction with an imaging device. The method may be performed by a control system of the stabilization mechanism and includes obtaining a device setting from an imaging device. The method may also include obtaining a configuration of the stabilization mechanism. The method includes determining a soft stop based on the device setting, the configuration, or both. The soft stop may be a virtual hard stop that indicates to the stabilization mechanism to reduce speed as a field of view of the imaging device approaches the soft stop. The method may also include setting an image stabilization mechanism parameter based on the determined soft stop.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: August 10, 2021
    Assignee: GoPro, Inc.
    Inventors: Joseph A. Enke, Kielan C. Crow, Pascal Gohl
  • Patent number: 10960971
    Abstract: An automatic yaw enhancement method for an aircraft having at least one propeller includes providing to a flight controller a pilot command from a pilot interface and avionic data for an airspeed, an angle of attack, and a thrust. A P-factor compensation is determined based on one or more of the airspeed, the angle of attack, and the thrust. A command to a trim device is determined based on a P-factor compensation. When a rudder bias persists, the command to the trim device is repeatedly updated until a rudder force input is nullified. The methods provide automatic pilot assistance for controlling yaw during asymmetric flight conditions and automatic turn coordination while allowing intentional side-slip for facilitating crosswind landings.
    Type: Grant
    Filed: September 11, 2018
    Date of Patent: March 30, 2021
    Assignee: Textron Innovation Inc.
    Inventors: Steven G. Hagerott, Philippe A. Ciholas
  • Patent number: 10814842
    Abstract: A braking system and method utilizing a simplified estimate of a distance between two locations on the earth based on spherical geometry. A braking system utilizing the aforementioned simplified estimate does not require computationally intensive calculations and is more efficient and better equipped to handle real-time generation of distance estimates for braking needs and variable conditions. In the present invention, geodesics evaluations are not used; rather, a modified Haversine formula that simplifies computations is used, including a one-time computation of the cosine of latitude coordinate.
    Type: Grant
    Filed: December 22, 2017
    Date of Patent: October 27, 2020
    Assignee: Hydro-Aire, Inc.
    Inventor: Andrew Brett Slatkin
  • Patent number: 10692389
    Abstract: Methods and systems may allow for automatic initiation of a contingency maneuver, to prevent mid-air collisions between an aerial vehicle and another aircraft or other obstacle, without requiring input from an operator. Generally, a processing unit on board the aerial vehicle detects potential conflicts via a navigation system on board the aerial vehicle. Said navigation system may receive, for example, automatic dependent surveillance-broadcast (ADS-B) signals and global positioning system (GPS) data. Disclosed systems automatically initiate one or more contingency maneuvers to change the flight (e.g., speed, position, direction, and/or altitude) of the aerial vehicle to avoid close calls or colliding with a potential conflict in the surrounding airspace. Such contingency maneuvers provide an automatic flight modification that may occur independently from any operator input.
    Type: Grant
    Filed: July 20, 2018
    Date of Patent: June 23, 2020
    Assignee: Aurora Flight Services Corporation, a subsidiary of The Boeing Company
    Inventor: Jason Solomon Fine
  • Patent number: 10691140
    Abstract: In accordance with an embodiment, 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.
    Type: Grant
    Filed: August 22, 2018
    Date of Patent: June 23, 2020
    Assignee: TEXTRON INNOVATIONS, INC.
    Inventor: Sung Kyun Kim
  • Patent number: 10665115
    Abstract: A method, device, framework, and system provide the ability to control an unmanned aerial vehicle (UAV) to avoid obstacle collision. Range data of a real-world scene is acquired using range sensors (that provide depth data to visible objects). The range data is combined into an egospace representation (consisting of pixels in egospace). An apparent size of each of the visible objects is expanded based on a dimension of the UAV. An assigned destination in the real world scene based on world space is received and transformed into egospace coordinates in egospace. A trackable path from the UAV to the assigned destination through egospace that avoids collision with the visible objects (based on the expanded apparent sizes of each of the visible objects) is generated. Inputs that control the UAV to follow the trackable path are identified.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: May 26, 2020
    Assignee: CALIFORNIA INSTITUTE OF TECHNOLOGY
    Inventors: Anthony T. S. Fragoso, Larry H. Matthies, Roland Brockers, Richard M. Murray
  • Patent number: 10656642
    Abstract: A method for providing mode data during operation of a Flight Management System (FMS) using a Vertical Navigation (VNAV) Autopilot Mode, is provided. When the FMS has disengaged a Lateral Navigation (LNAV) Autopilot Mode, the method detects a changed aircraft position indicating divergence from a flight path, wherein the changed aircraft position comprises a current aircraft position; calculates a future aircraft position for VNAV Autopilot Mode disengagement, based on the changed aircraft position, a predicted cross-track error, and the divergence from the flight path; and presents the changed aircraft position and the future aircraft position when operating in the VNAV Autopilot Mode, via a display device. When the future aircraft position is not on the flight path, the method disengages the VNAV Autopilot Mode, based on the changed aircraft position and the future aircraft position; calculates a descent path for the aircraft, after disengagement; and presents the descent path.
    Type: Grant
    Filed: November 21, 2017
    Date of Patent: May 19, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventor: Kiran Mancheiah Venkataramana
  • Patent number: 10642284
    Abstract: An unmanned aerial vehicle (UAV) may navigate to place a ground structure, having a known location, into a field of view of a camera and capture imagery of the ground structure. Algorithms may be used to identify the ground structure to determine its known location. Ground structures may include identifiers that provide the known location and/or other information to enable determination of the known locations. Algorithms may determine an offset distance of the UAV from the ground structure to enable determination of a location of the UAV. For example, the images may be used to determine a distance and angle(s) from the ground structure when the ground structure is shown in a perspective view and has features that indicate orientation. In some embodiments, the UAV may transmit its location to other UAVs, and/or may create and/or transmit a corrected GPS location based on the location determined by the ground structure.
    Type: Grant
    Filed: June 8, 2018
    Date of Patent: May 5, 2020
    Assignee: Amazon Technologies, Inc.
    Inventor: Gideon Barazovsky
  • Patent number: 10586460
    Abstract: Disclosed are a method and system for operating an unmanned delivery device. One embodiment of the method includes setting at least one sampling section with respect to a travel path to a destination of at least one delivery item, determining a type of the sampling section based on location information and altitude information of the sampling section, setting a traveling range including the at least one sampling section based on the type of the sampling section, generating route information including the at least one traveling range, and providing the route information to the unmanned delivery device.
    Type: Grant
    Filed: March 28, 2018
    Date of Patent: March 10, 2020
    Assignee: Electronics and Telecommunications Research Institute
    Inventor: Moon Sung Park
  • Patent number: 10583845
    Abstract: Systems and methods are disclosed for detecting security threats during vehicle operations. For instance, retrieving a route plan for a route of a vehicle from a database of the vehicle; identifying either a portion of the route or a portion of the route plan as a security threat based on an analysis of the route plan; and in response to identifying the portion of the route or the portion of the route plan as the security threat, transmitting an alert of the security threat.
    Type: Grant
    Filed: October 30, 2018
    Date of Patent: March 10, 2020
    Assignee: Honeywell International Inc.
    Inventors: James Alexander Nicholls, John Stokely, Dereck Clark, Yasuo Ishihara
  • Patent number: 10577081
    Abstract: A vehicle may include a sensor and a proactive vehicle controller that is capable of proactively altering one or more vehicle operating parameters in response to detecting a force caused by an environmental event that will be exerted on a chassis of the vehicle. The sensor has a field-of-view that includes the direction of travel of the vehicle. The sensor may detect objects in the field-of-view and, based at least in part on the behavior of the objects in the field-of-view, predicts the force exerted on the object by an environmental event. Based on the predicted force, the proactive vehicle controller proactively adjusts one or more vehicle operating parameters to minimize the effect of the force that will be exerted on the vehicle by the environmental event.
    Type: Grant
    Filed: March 24, 2016
    Date of Patent: March 3, 2020
    Assignee: Intel Corporation
    Inventors: Jim S. Baca, Alec Iverson, Rita H. Wouhaybi
  • Patent number: 10539421
    Abstract: An inertial measurement system (200) for a longitudinal projectile, comprising a first, roll gyro to be oriented substantially parallel to the longitudinal axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: January 21, 2020
    Assignee: ATLANTIC INERTIAL SYSTEMS, LIMITED
    Inventors: John Keith Sheard, Nicholas Mark Faulkner
  • Patent number: 10536630
    Abstract: The disclosure describes systems and methods for a stabilization mechanism. The stabilization mechanism may be used in conjunction with an imaging device. The method may be performed by a control system of the stabilization mechanism and includes obtaining a device setting from an imaging device. The method may also include obtaining a configuration of the stabilization mechanism. The method includes determining a soft stop based on the device setting, the configuration, or both. The soft stop may be a virtual hard stop that indicates to the stabilization mechanism to reduce speed as a field of view of the imaging device approaches the soft stop. The method may also include setting an image stabilization mechanism parameter based on the determined soft stop.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: January 14, 2020
    Assignee: GoPro, Inc.
    Inventors: Joseph A. Enke, Kielan C. Crow, Pascal Gohl
  • Patent number: 10495288
    Abstract: The present invention includes a first frame attached to an aerial vehicle or a mounting plate attached to the aerial vehicle, and a second frame attached to an aimable device moveably connected to the aerial vehicle or the mounting plate. The first frame and the second frame are configured to collectively provide a hard stop that prevents the aimable device from pointing at the aerial vehicle.
    Type: Grant
    Filed: April 12, 2018
    Date of Patent: December 3, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventor: Francis Turgeon
  • Patent number: 10495483
    Abstract: A method and system for initializing a sensor fusion system is disclosed, wherein the sensor fusion system includes a base system and at least one correction system. Measured values are captured by the base system and by the correction system, and the measured values directly or indirectly describing physical quantities are afflicted with error values. The error values describe deviations of the measured values from the described physical quantities, and at least the physical quantities indirectly described in the measured values of the base system and the error values of the physical quantities cannot be determined during initialization. The measured values are continuously fused into a fusion data set after initialization. For at least one of the physical quantities associated with the measured values of the base system and the error values of the physical quantities, starting values are determined from the measured values of the correction system.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: December 3, 2019
    Assignee: Continental Automotive Systems, Inc.
    Inventor: Nico Steinhardt
  • Patent number: 10490088
    Abstract: A Geo-containment system includes at least one unmanned aircraft and a control system that is configured to limit flight of the unmanned aircraft based, at least in part, on predefined Geo-spatial operational boundaries. These boundaries may include a primary boundary and at least one secondary boundary that is spaced apart from the primary boundary a minimum safe distance. The minimum safe distance is determined while the unmanned aircraft is in flight utilizing state information of the unmanned aircraft and dynamics and dynamics coefficients of the unmanned aircraft. The state information includes at least position and velocity of the unmanned aircraft. The control system is configured to alter or terminate operation of the unmanned aircraft if the unmanned aircraft violates the primary Geo-spatial operational boundary or the secondary Geo-spatial boundary.
    Type: Grant
    Filed: December 21, 2016
    Date of Patent: November 26, 2019
    Assignee: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASA
    Inventors: Evan T. Dill, Kyle M. Smalling, Steven D. Young, Cuong C. Quach, Kelly J. Hayhurst, Anthony J. Narkawicz
  • Patent number: 10392124
    Abstract: Combined modality hover drift cueing methods, systems and computer readable media are disclosed. For example, some implementations can include a system comprising one or more sensors, and a combined modality hover drift cueing controller coupled to the one or more sensors and configured to determine hover drift and to control a plurality of indicators in response to determined hover drift. The system can also include a mode selector coupled to the combined modality hover drift cueing controller and configured to provide an indication of mode selection between one of a first mode, a second mode and a third mode, wherein the first mode is a combined modality mode. The system can further include a peripheral vision hover drift indicator coupled to the controller and mounted on an inside surface of an aircraft cockpit, and a tactile feedback indicator coupled to the controller.
    Type: Grant
    Filed: June 29, 2016
    Date of Patent: August 27, 2019
    Assignee: Lockheed Martin Corporation
    Inventor: Steven D. Colby
  • Patent number: 10355853
    Abstract: Embodiments of the invention are directed to a multilayered obstructed brokered network routing and data repackaging system, sometimes referred to as a MOB HUB. The MOB HUB is configured to communicate with a mission computer on a vehicle. At least one mobile computer is configured to communicate with the MOB HUB.
    Type: Grant
    Filed: August 25, 2016
    Date of Patent: July 16, 2019
    Assignee: The United States of America as Represented by the Secretary of the Navy
    Inventors: Jonathan L. Surmi, Alvin L. Quintana, Mark Miliano, Anthony R. Kunkel
  • Patent number: 10335678
    Abstract: A screen generation process is provided that generates a game screen having disposed thereon multiple selectable objects that a player is allowed to select; an acceptance process that accepts the selection operation input on said selectable objects when the pointing location initially arrives at the location of a selectable object disposed on the game screen while the movement of the pointing location on the game screen is maintained by the player's operations, and said acceptance process accepts the selection operation input in a sequential manner, starting with the selectable object at which the pointing location arrives the earliest; and a special effect generation process that generates special effects in the course of a game driven by the player's operations based on the moment when the pointing location initially arrives at the location of the selectable object, and/or the order of acceptance of the selection operation input on the selectable objects.
    Type: Grant
    Filed: September 23, 2015
    Date of Patent: July 2, 2019
    Assignee: DENA CO., LTD.
    Inventors: Kenichi Takahashi, Miyako Shoji, Shiina Suzuki
  • Patent number: 10338585
    Abstract: An aircraft flight control system includes at least two flight control computers at least one of which is utilized at any one time to control aircraft flight, each of the at least two flight control computers having at least two processors, each processor being responsive to an aircraft input signal indicative of at least one of a plurality of aircraft flight parameters and being responsive to control laws to provide a control output command signal indicative of a desired control of an aircraft flight control surface. Also, at least one of the at least two processors for each of the at least two flight control computers comprises an abnormal response monitor that is responsive to at least one aircraft input signal indicative of at least one of a plurality of aircraft flight parameters to determine whether the control output command signal is within an acceptable value.
    Type: Grant
    Filed: August 18, 2014
    Date of Patent: July 2, 2019
    Assignees: BOMBARDIER INC., C SERIES AIRCRAFT LIMITED PARTNERSHIP
    Inventor: Gregory Burte
  • Patent number: 10330493
    Abstract: Systems and methods for displaying position sensitive datalink messages on avionics displays are provided. In one embodiment, a flight deck instrument display system for an aircraft comprises: a flight plan display screen that displays a graphical representation of at least a part of an aircraft's planned flight path together with symbology representing a position of the aircraft with respect to the aircraft's planned flight path; wherein the flight plan display screen further displays at least one symbol positioned along the graphical representation of at least a part of the aircraft's planned flight path that indicates a point of applicability for a received uplink datalink message.
    Type: Grant
    Filed: December 3, 2014
    Date of Patent: June 25, 2019
    Assignee: Honeywell International Inc.
    Inventors: Raghu Shamasundar, Prasad Rao Piradi, Thomas D. Judd, David Pepitone, Abhishek Gupta, Adib Bouanani, Prashanth Ramanna
  • Patent number: 10323906
    Abstract: An autonomous flight termination system for terminating vehicle flight after the vehicle is launched from an aircraft includes a global positioning system (GPS) receiver; a termination unit selected from a cut-off switch connected to terminate vehicle flight when actuated, and a switch connected to detonate an explosive on the vehicle; a system controller for receiving a first signal indicating separation of the vehicle from the aircraft and a second signal from the GPS receiver to calculate an actual vehicle trajectory, and for sending a third signal to actuate the termination unit to terminate the flight of the vehicle when the actual vehicle trajectory is determined to be outside the safety bounds of a mission-planned flight trajectory; and a failsafe controller connected to receive operational data of the system controller, and to actuate the termination unit when the operational data indicates that the system is in an error state.
    Type: Grant
    Filed: September 30, 2016
    Date of Patent: June 18, 2019
    Assignee: The Boeing Company
    Inventor: Michelle V. DeJong
  • Patent number: 10304344
    Abstract: Methods and systems are provided for generating a route that facilitates navigating a vehicle to a diversion destination while satisfying applicable safety thresholds or other constraints, such as a maximum landing weight. One exemplary method of facilitating an aircraft landing at a diversion airport involves obtaining a current position of the aircraft, identifying a landing threshold influenced by a characteristic of the aircraft, obtaining one or more constraints associating with diverting to the diversion airport, and determining a route from the current position to the diversion airport based at least in part on the landing threshold and the one or more constraints. The route satisfies the constraints and results in a predicted value for the aircraft, e.g., a predicted aircraft landing weight, that satisfies the landing threshold. A graphical representation of the route is displayed on a display device onboard the aircraft.
    Type: Grant
    Filed: February 9, 2016
    Date of Patent: May 28, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Zdenek Moravek, David Kunes, Filip Magula, Robert Sosovicka, Katerina Sprinarova
  • Patent number: 10217368
    Abstract: A flight path setting apparatus includes a display unit, a selector, a range calculator, and a display controller. The display unit displays a flight path of an aircraft. The flight path includes a plurality of points. The selector selects a first point on the basis of an operation performed by a user. The first point is any one of the points displayed by the display unit. The range calculator calculates a non-settable range on the basis of a flight performance and a surrounding environment of the aircraft. The non-settable range is a region that is around the first point and in which a second point is not settable. The second point is subsequent to the first point on the flight path. The display controller causes the display unit to display the non-settable range that relates to the first point and is calculated by the range calculator.
    Type: Grant
    Filed: June 14, 2017
    Date of Patent: February 26, 2019
    Assignee: Subaru Corporation
    Inventors: Shinichi Harada, Satoshi Kuroyanagi, Yukinobu Tomonaga
  • Patent number: 10209691
    Abstract: Nutritional substance systems and methods are disclosed enabling the tracking and communication of changes in nutritional, organoleptic, and aesthetic values of nutritional substances, and further enabling the adaptive storage and adaptive conditioning of nutritional substances.
    Type: Grant
    Filed: August 2, 2016
    Date of Patent: February 19, 2019
    Assignee: Iceberg Luxembourg S.A.R.L.
    Inventor: Eugenio Minvielle
  • Patent number: 10183738
    Abstract: A control augmentation system for high aspect ratio aircraft has aileron/flaperon and throttle position sensors; spoiler and flap controls; a mode switch with manual, and landing modes; and a controller driving left and right spoiler and flap servos, the controller including at least one processor with memory containing firmware configured to: when the mode switch is in manual mode, drive both spoiler servos to a symmetrical position according to the spoiler control; when the mode switch is in landing mode, drive the left spoiler to a position dependent on aileron and throttle position, and the right spoiler to a position dependent on aileron and throttle position, the left and right spoiler positions differing whenever ailerons are not centered, and an average of spoiler positions is more fully deployed when the throttle position is at a low-power setting than when the throttle position is at a high-power setting.
    Type: Grant
    Filed: April 2, 2015
    Date of Patent: January 22, 2019
    Inventor: Marc Arnold
  • Patent number: 10173775
    Abstract: Disclosed herein is one embodiment of a thrust system that includes at least one modular thrust unit and at least one control module. The at least one modular thrust unit includes a base that is made from structural members that are inter-connectable in a plurality of different structural configurations. The at least one modular thrust unit further includes at least one thrust generator coupleable to the base in a thrust configuration and at least one power source operable to deliver power to the at least one thrust generator. The at least one control module is coupleable to the at least one modular thrust unit and operable to control at least one of the at least one thrust generator and the at least one power source.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: January 8, 2019
    Assignee: The Boeing Company
    Inventors: Anthony Samaritano, Daniel I. Newman, Michael J. Duffy
  • Patent number: 10154096
    Abstract: A method for integrating a new navigation service is implemented in an avionics onboard system comprising a DAL+ core computer and a DAL? peripheral computer for managing the application. The method of integration determines an optimal functional and physical distribution of the elementary functions FU(i) of the new service within the onboard avionics system over the set of possible distributions which minimizes a global cost criterion CG, dependent on several parameters, including at least the additional development cost of the elementary functions integrated within the digital DAL+ core computer, and carries out the integration of the new service.
    Type: Grant
    Filed: July 5, 2016
    Date of Patent: December 11, 2018
    Assignee: THALES
    Inventors: François Coulmeau, Laurent Deweerdt
  • Patent number: 10134292
    Abstract: In one example, a method to guide and navigate the aircraft during a complete engine failure is disclosed. Nearby airport data is obtained based on aircraft current location upon detecting the complete aircraft engine failure. Minimum and maximum glide distances of the aircraft are computed based on the current aircraft state parameters and environmental parameters. Candidate reachable airports are determined using the obtained nearby airport data for safe landing based on the computed minimum and maximum glide distances. A glide path for each candidate reachable airport is determined. The aircraft is navigated and guided to a selected one of the candidate reachable airports using an associated glide path.
    Type: Grant
    Filed: December 6, 2016
    Date of Patent: November 20, 2018
    Assignee: AIRBUS GROUP INDIA PRIVATE LIMITED
    Inventor: Dinesh Kumar Kushwaha
  • Patent number: 10112722
    Abstract: A method of controlling an engine for a propeller-driven aircraft, including setting an initial maximum power limit, wherein the initial maximum power limit is associated with a maximum allowable thrust for an aircraft, receiving an indication that a predetermined aircraft condition is satisfied, and setting an updated maximum power limit.
    Type: Grant
    Filed: January 11, 2016
    Date of Patent: October 30, 2018
    Assignee: Unison Industries LLC
    Inventors: Mark Wayne McWaters, Scott Richard Nielsen
  • Patent number: 9910445
    Abstract: A method and apparatus for processing aerodynamic angles for an aircraft. A first rate of change in an inertial aerodynamic angle is calculated using data received from an inertial measurement system for the aircraft. Further, a second rate of change in an externally measured aerodynamic angle is calculated. Yet further, a filtered aerodynamic angle is generated during a flight of the aircraft using the first rate of change in the inertial aerodynamic angle and the second rate of change in the externally measured aerodynamic angle. Still further, a contribution of the first rate of change in the inertial aerodynamic angle used in generated the filtered aerodynamic angle is changed based on a difference between the first rate of change in the inertial aerodynamic angle and the second rate of change in the externally measured aerodynamic angle, enabling controlling the flight of the aircraft using the filtered aerodynamic angle.
    Type: Grant
    Filed: May 18, 2016
    Date of Patent: March 6, 2018
    Assignee: THE BOEING COMPANY
    Inventor: Jia Luo
  • Patent number: 9870000
    Abstract: Systems, methods and apparatus are provided for translating an alert signal into an auto flight system (AFS) maneuver. The system comprises a first module. The first module is configured to receive an alert signal and to construct one or more AFS mode commands associated with the alert signal. The system also comprises a second module. The second module is configured to read and to execute the one or more AFS mode commands that when executed manipulate two or more standard AFS modes that implement the AFS maneuver. The system further comprises a state machine, which couples the first module to the second module and is configured to coordinate the construction of the one or more AFS mode commands by the first module with an execution of the one or more AFS mode commands by the second module.
    Type: Grant
    Filed: March 28, 2011
    Date of Patent: January 16, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventor: Kent Stange
  • Patent number: 9852642
    Abstract: One embodiment provides a method comprising receiving a flight plan request for a drone. The flight plan request comprises a drone identity, departure information, and arrival information. The method further comprises constructing a modified flight plan for the drone based on the flight plan request, wherein the modified flight plan represents an approved, congestion reducing, and executable flight plan for the drone, and the modified flight plan comprises a sequence of four-dimensional (4D) cells representing a planned flight path for the drone. For each 4D cell of the modified flight plan, the method further comprises attempting to place an exclusive lock on behalf of the drone on the 4D cell, and in response to a failure to place the exclusive lock on behalf of the drone on the 4D cell, rerouting the modified flight plan around the 4D cell to a random neighboring 4D cell.
    Type: Grant
    Filed: March 8, 2016
    Date of Patent: December 26, 2017
    Assignee: International Business Machines Corporation
    Inventors: Eric K. Butler, Anca A. Chandra, Pawan R. Chowdhary, Susanne M. Glissmann-Hochstein, Thomas D. Griffin, Divyesh Jadav, Sunhwan Lee, Hovey R. Strong, Jr.
  • Patent number: 9835470
    Abstract: Systems and methods for filtering a micro-electromechanical system sensor rate signal with error feedback are provided. In one example, a micro-electromechanical system sensor rate signal is provided. Next, a feedback signal from a feedback loop is subtracted from the micro-electromechanical system sensor rate signal to produce a first combined signal. The first combined signal is then filtered to produce a filtered rate output. The micro-electromechanical system sensor rate signal is then subtracted from the filtered rate output to produce an error signal, wherein the error signal is used in the feedback loop to generate a feedback signal for a future time step.
    Type: Grant
    Filed: March 27, 2014
    Date of Patent: December 5, 2017
    Assignee: Honeywell International Inc.
    Inventor: Jens M. Henrickson
  • Patent number: 9836065
    Abstract: Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.
    Type: Grant
    Filed: January 9, 2017
    Date of Patent: December 5, 2017
    Assignee: SUNLIGHT PHOTONICS INC.
    Inventors: Sergey V. Frolov, John Peter Moussouris, Michael Cyrus
  • Patent number: 9791278
    Abstract: One embodiment is directed towards a method of navigating a body. The method includes determining a respective measured direction of each of a plurality of celestial objects with respect to the body based on an output of one or more star tracking sensors mounted to the body. Calculating an expected direction of at least one of the plurality of celestial objects with respect to the body based on a current navigation solution for the body. Calculating an updated navigation solution for the body based on the expected direction of the at least one celestial object, the measured direction of the plurality of celestial objects, and an output of one or more inertial sensors mounted to the body.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: October 17, 2017
    Assignee: Honeywell International Inc.
    Inventors: Robert C. McCroskey, Wesley J. Hawkinson, Steven J. Sanders, Lawrence Charles Vallot
  • Patent number: 9778013
    Abstract: An apparatus for measuring a bending angle between two portions of a workpiece in a bending machine includes at least a motion sensor unit provided with a gyroscope sensor, a processing unit connected with the gyroscope sensor and a coupling device for connecting the motion sensor unit with a portion of the workpiece to be bent. During a bending operation of the workpiece the gyroscope sensor measures at least one angular velocity and a related rotation angle of the portion according to an axis and the processing unit receives data from the gyroscope sensor regarding the rotation angle in order to calculate the bending angle as a function of the rotation angle.
    Type: Grant
    Filed: September 19, 2014
    Date of Patent: October 3, 2017
    Assignee: Salvagnini Italia S.p.A.
    Inventor: Enzo Gesuita
  • Patent number: 9754498
    Abstract: A system for navigating an aircraft includes a first aircraft with a first communication unit and a second aircraft with a second communication unit. The first aircraft is adapted for determining coordinates of a position of a waypoint. The first communication unit is adapted to transmit the coordinates of the position of the waypoint to the second communication unit. The second aircraft is adapted to navigate to the position of the waypoint. Several waypoints can be provided in this manner such that a flight trajectory is established along which the second aircraft may follow the first aircraft. In addition, the second aircraft may be adapted to follow the first aircraft based on a received identification signal. In certain embodiments, the system can be used such that the second aircraft can follow the first aircraft in case of a failure of systems of the second aircraft.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: September 5, 2017
    Assignee: Airbus Defence and Space GmbH
    Inventors: Joy Bousquet, Thomas Vitte
  • Patent number: 9751621
    Abstract: Control of aircraft steering during ground travel is provided in an aircraft equipped with an engines-off wheel drive system controllable to move the aircraft autonomously on the ground without reliance on the aircraft's main engines or external tow vehicles. The wheel drive system is designed to interact with the aircraft's nose wheel hydraulic steering system to augment or replace the hydraulic steering system with the operation of the wheel drive system at taxi speeds, particularly at very low taxi speeds and even when the aircraft is stopped, to steer the aircraft as it maneuvers through turns during ground travel between landing and takeoff and at other times.
    Type: Grant
    Filed: July 25, 2014
    Date of Patent: September 5, 2017
    Assignee: Borealis Technical Limited
    Inventor: Isaiah W. Cox
  • Patent number: 9691287
    Abstract: A method. The method includes receiving user input data from a user interface system. The user input data includes user gesture data, wherein the user gesture data is associated with one or more detected user gestures. The method also includes manipulating one or more graphical flight path elements based at least upon received user gesture data. The method further includes performing at least one flight path modification operation based at least upon one or more factors and the received user gesture data. The method additionally includes outputting updated graphical data to the user interface system, wherein the updated graphical data includes updated graphical flight path element data and updated graphical flight path data.
    Type: Grant
    Filed: September 26, 2013
    Date of Patent: June 27, 2017
    Assignee: Rockwell Collins, Inc.
    Inventors: Geoffrey A. Shapiro, Laura Maxine Smith-Velazquez, Timothy J. Etherington, Nicholas M. Lorch
  • Patent number: 9682769
    Abstract: A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: June 20, 2017
    Assignee: Airbus Operations GmbH
    Inventor: Martin Richter
  • Patent number: 9676502
    Abstract: An aiming assembly comprising an instrument and aiming device, the aiming device comprises: a frame, a mobile part comprising a plate, the instrument being fixed onto the plate, the mobile part and the instrument having a centre of gravity, the mobile part being rotationally mobile relative to the frame on a first axis of rotation, and comprising a support configured to cooperate with the plate to allow the plate to be rotationally mobile relative to the frame about a second axis of rotation at right angles to the first axis of rotation, and rotationally mobile relative to the frame on the first axis, the first and second axes of rotation intersecting at a point of intersection. The point of intersection coincides with the centre of gravity of the mobile part and of the instrument, and the support comprises a flexible part configured to compensate for the differential expansions on the second axis of rotation between the frame and the plate.
    Type: Grant
    Filed: January 7, 2016
    Date of Patent: June 13, 2017
    Assignee: THALES
    Inventors: Yannick Baudassé, Stéphane Vézain, Paul Mouille, Didier Stanek
  • Patent number: 9658040
    Abstract: Methods involve using a guided munition (e.g., a mortar round or a grenade) that utilizes deployable flow effectors, activatable flow effectors and/or active flow control devices to extend the range and enhance the precision of traditional unguided munitions without increasing the charge needed for launch. Sensors such as accelerometers, magnetometers, IR sensors, rate gyros, and motor controller sensors feed signals into a controller which then actuates or deploys the flow effectors/flow control devices to achieve the enhanced characteristics.
    Type: Grant
    Filed: June 21, 2016
    Date of Patent: May 23, 2017
    Assignee: Orbital Research Inc.
    Inventors: Srikanth Vasudevan, Paul Suchy, Matthew C. Birch
  • Patent number: 9650129
    Abstract: A controllable aircraft taxi system is provided that enables the simultaneous control of aircraft autonomous ground movement and direction of aircraft autonomous ground movement. Independently controlled non-engine drive means capable of driving an aircraft landing gear wheel to move an aircraft autonomously on the ground without reliance on the aircraft's main engines are mounted to provide driving torque to aircraft a selected number of main landing gear wheels. The aircraft nose landing gear steering system is provided with steering angle detection and measurement means adapted to communicate with main landing gear wheel non-engine drive means, enabling simultaneous control over both autonomous aircraft ground travel and direction of autonomous aircraft ground travel. The present invention overcomes steering challenges presented by using non-engine drive means on main landing gear wheels to drive aircraft autonomously during taxi.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: May 16, 2017
    Assignee: Borealis Technical Limited
    Inventors: Rodney T. Cox, Isaiah W. Cox
  • Patent number: 9646505
    Abstract: A method of controlling the flight of an aircraft by automatically controlling the descent phase of an aircraft using a Flight Management System and Flight Guidance System (FMS & FGS) to control the air speed of the air craft and respond to an over speed condition.
    Type: Grant
    Filed: December 23, 2014
    Date of Patent: May 9, 2017
    Assignee: GE AVIATION SYSTEMS LLC
    Inventors: Sherif Fouad Ali, Mark Lawrence Darnell
  • Patent number: 9646506
    Abstract: A method for managing a premature descent envelope during descent of an aircraft is provided. The method receives glideslope deviation data by an instrument landing system (ILS) onboard the aircraft; compares, by the ILS, the glideslope deviation data to an acceptable band of glideslope deviation values; and when the glideslope deviation data is within the acceptable band, expands, by a terrain awareness and warning system (TAWS), the premature descent envelope to produce an increased premature descent envelope for the aircraft.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: May 9, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Yasuo Ishihara, C Don Bateman, Steve Johnson
  • Patent number: 9630707
    Abstract: The invention relates to a method for managing an electric motor (6) intended to drive rotationally a wheel (4) of an aircraft (1), the method comprising the step of short-circuiting the phases of the electric motor (6) when the aircraft (1) is in a period of deactivation of the motor (6) during which it is envisaged not using the electric motor (6).
    Type: Grant
    Filed: June 23, 2015
    Date of Patent: April 25, 2017
    Assignee: MESSIER-BUGATTI-DOWTY
    Inventors: Sylvain Jaber, Raffi Cekic
  • Patent number: 9536433
    Abstract: A method determines the optimal turn direction of an aircraft among two directions, right and left, following a lateral trajectory to join an arrival straight charted by an angle of arrival, based on a departure point and angle of departure defining a departure straight oriented along movement of the aircraft, the direction defined by a respectively positive or negative optimal turn sign, comprising: determining a conventional departure sign of the departure point; determining a center value of an angle of change of course equal to the difference between the angle of arrival and angle of departure referred back between ?180° and +180°, the center value exhibiting a logical sign corresponding to the center value sign of the angle of change of course; determining the sign of the optimal turn based on comparison between the departure sign and the logical sign, the sign of the optimal turn defining optimal turn direction.
    Type: Grant
    Filed: June 3, 2015
    Date of Patent: January 3, 2017
    Assignee: Thales
    Inventors: Vincent Savarit, François Hoofd, Emmanuel Dewas