Patents Issued in September 15, 2020
  • Patent number: 10773770
    Abstract: A bicycle control apparatus is basically provided with a controller. The controller includes a processor, a memory, and an I/O interface. The controller is arranged to communicate with an assist mechanism of a bicycle. The assist mechanism includes an assist motor arranged to impart a supplemental drive force to the bicycle to supplement a manual drive force of the bicycle. The controller is programmed to alternately set a first control state or a second control state. The controller controls the assist motor such that an output state of the assist motor with respect to a manual drive force of the bicycle is different in the first control state than in the second control state.
    Type: Grant
    Filed: January 22, 2018
    Date of Patent: September 15, 2020
    Assignee: Shimano Inc.
    Inventors: Yusuke Nishikawa, Yasuhiro Tsuchizawa, Makoto Usui, Satoshi Shahana
  • Patent number: 10773771
    Abstract: A bicycle includes an electrical auxiliary drive, including an electric motor, a battery for storing electrical energy, which battery is connected to the electric motor, a crank mechanism having pedal cranks, which are mounted on a pedal crankshaft disposed about a crank axis, so as to be able to rotate, and a planetary gear for driving the bicycle both by the electric motor and by the muscle power of a driver, the planetary gear and the electric motor being disposed about the pedal crankshaft of the crank mechanism.
    Type: Grant
    Filed: July 19, 2017
    Date of Patent: September 15, 2020
    Assignee: Robert Bosch GmbH
    Inventors: Peter Kimmich, Mario Kustosch, Philipp Kohlrausch
  • Patent number: 10773772
    Abstract: A bicycle sprocket assembly is basically provided that includes a sprocket support member, a first sprocket, a second sprocket that is a separate member from the first sprocket, and a third sprocket that is a separate member from the first and second sprockets. The sprocket support member is configured to support at least one of the first, second and third sprockets. The sprocket support member includes a plurality of sprocket support portions extending radially outwardly from a central cylindrical portion. A first reinforcement member is attached to at least one of the first and second sprockets, and extends between the first and second sprockets. A second reinforcement member is attached to at least one of the second and third sprockets, and extends between the second and third sprockets. Each of the first and second reinforcement members is disposed between an adjacent pair of the plurality of sprocket support portions.
    Type: Grant
    Filed: April 12, 2017
    Date of Patent: September 15, 2020
    Assignee: Shimano Inc.
    Inventors: Tsuyoshi Fukumori, Hiroshi Fujita
  • Patent number: 10773773
    Abstract: An electrical bicycle derailleur is basically provided with a base member, a movable member, at least one link member, a motor unit and a wireless unit. The base member is configured to be mounted to a bicycle frame. The movable member is movably arranged relative to the base member. The at least one link member movably connects the base member and the movable member. The motor unit is disposed on one of the base member, the movable member, and the at least one link member. The motor unit includes a motor configured to move the at least one link member. The wireless unit includes a wireless receiver configured to receive a wireless signal, the wireless unit being disposed on the at least one link member.
    Type: Grant
    Filed: June 7, 2017
    Date of Patent: September 15, 2020
    Assignee: Shimano Inc.
    Inventors: Atsushi Komatsu, Shingo Sakurai
  • Patent number: 10773774
    Abstract: A snow vehicle is disclosed comprising a vehicle frame, a propulsion unit coupled to the frame, and at least one front ski steered by a steering mechanism. The front of the vehicle includes a first front suspension and a second front suspension coupled to the ski. The rear suspension includes a bumper assembly preventing bottoming out of the rear suspension. The rear suspension is coupled to the vehicle frame such that the longitudinal spacing between the vehicle frame and rear suspension is adjustably controllable.
    Type: Grant
    Filed: February 4, 2019
    Date of Patent: September 15, 2020
    Assignee: Polaris Industries Inc.
    Inventors: Allen M. Mangum, Justin R. York
  • Patent number: 10773775
    Abstract: The present invention is a dual-purpose mounting system for attaching removable hydrofoils along a rideable board. The dual-purpose mounting system reduces repetitive stress exerted on the hull of the rideable board by foil bending and torsion, therefore prolonging the hull life of the rideable board. The dual-purpose mounting system is a solid one-piece constructed foil strongbox having a mounting body that is installed into a surfboard hull. A mounting receptacle is positioned within the mounting body to receive a tuttle style hydrofoil mount through a first hydrofoil aperture at a mounting surface of the mounting body. A pair of second hydrofoil apertures traverses into the mounting surface to further facilitate attachment of a plate style hydrofoil. A plurality of fastener sleeves traverses into the mounting body opposite the mounting receptacle enable attachment of the mounting body to the surfboard hull.
    Type: Grant
    Filed: October 25, 2019
    Date of Patent: September 15, 2020
    Inventor: Robert A. Stehlik
  • Patent number: 10773777
    Abstract: The invention relates to an auxiliary floating system for the installation, transport or maintenance of an offshore structure, said structure comprising at least one essentially vertical shaft, wherein said auxiliary floating system comprises: at least one floating element that remains semi-submerged during the process of installing the offshore structure; at least one coupling structure connected to said floating element; and guide elements secured to the coupling structure and in sliding contact with the shaft. Advantageously, the sliding contact between the auxiliary floating system and the shaft is such that it allows essentially horizontal relative movement between the auxiliary floating system and said shaft, such that during the process of installing the offshore structure, said structure sinks while the auxiliary floating system remains at essentially the same level on the surface.
    Type: Grant
    Filed: May 12, 2017
    Date of Patent: September 15, 2020
    Assignee: ESTEYCO S.A.
    Inventors: José Salustiano Serna García-Conde, Miguel Ángel Fernández Gómez
  • Patent number: 10773778
    Abstract: The LED lights for a surfboard is a safety device. The LED lights for a surfboard is configured for use with a surfboard. The surfboard is a floating structure. The surfboard is a roughly disk shaped structure. The surfboard comprises a superior face and an inferior face. The LED lights for a surfboard illuminates when the LED lights for a surfboard is placed in water. The illumination of the LED lights for a surfboard discourages predators in the water from attacking the LED lights for a surfboard. The LED lights for a surfboard comprises a housing, an illumination circuit and the surfboard. The housing contains the illumination circuit. The housing mounts on the inferior face of the disk structure of the surfboard. The illumination circuit automatically illuminates when the LED lights for a surfboard is placed in water.
    Type: Grant
    Filed: October 15, 2019
    Date of Patent: September 15, 2020
    Inventors: Homer Shaffer, Michele Walter
  • Patent number: 10773779
    Abstract: A liquid-ingress control device, comprising a casing having an interior and an exterior, and optionally, a liquid-activated trigger positioned in the casing interior, the casing comprising an exterior liquid entry control surface defined by a perimeter in sealing relationship with an edge of a cap, the cap having an interior cap surface formed to define a cap space between the interior cap surface and the liquid entry control surface; the liquid entry control surface comprising a liquid entry port comprising a tube extending between the exterior and interior of the casing through an aperture formed in the entry control surface, the tube optionally comprising a flange positioned exterior to the casing; the cap comprising at least two flow apertures positioned such that liquid contained within the cap space is capable of egress under gravity from the cap space, independently of the orientation of the device.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: September 15, 2020
    Inventor: Jeffrey Birkin
  • Patent number: 10773780
    Abstract: An unmanned underwater vehicle having one, some, or all of an integrated communication control fin, a ballast and trim control, a reusable trigger mechanism for a drop weight, and a visual hull display. Furthermore, associated methods are also provided.
    Type: Grant
    Filed: June 22, 2017
    Date of Patent: September 15, 2020
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventors: Jeffrey M. Smith, Samuel D. Godin, Leonard M. Baker, Dani Goldberg, William H. Key, Jr.
  • Patent number: 10773781
    Abstract: A paddle assistance and propulsion system for use with personal watercraft is disclosed. The paddle assistance and propulsion system may include different mounting techniques that allow a propulsion device (e.g., a motor) to be coupled to various types of personal watercraft. Some mounting techniques may include the use of magnets to couple a motor-side mount to a boat-side mount. The paddle assistance and propulsion system may also utilize a variety of sensors in combination with control systems to provide various types of paddle assistance and different types of paddle assistance modes for the user of the personal watercraft.
    Type: Grant
    Filed: May 31, 2019
    Date of Patent: September 15, 2020
    Assignee: Detekt Biomedical, LLC.
    Inventors: Damon Vincent Borich, Karen Borich, Andrea Grbavac, Zwckxally Obregon
  • Patent number: 10773782
    Abstract: An interior component carrier system comprises a first and second installation rail. Each rail includes at least one connecting portion connectable to an associated primary structure component to fasten the rail to the component, and a carrier portion extending from the connecting portion in a direction along a longitudinal axis of the system. The system further comprises a first carrier element having a first end connected to a first carrier rod extending in a direction along the longitudinal axis and a second end connectable to a first interior component, wherein the first carrier rod is fastened to the carrier portion of the first rail, and a second carrier element having a first end connected to a second carrier rod extending in the longitudinal axis direction and a second end connected to the first carrier element, wherein the second carrier rod is fastened to the second rail carrier portion.
    Type: Grant
    Filed: June 30, 2017
    Date of Patent: September 15, 2020
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Martin Metten, Hermann Benthien, Marcus Hinrichs, Michael Telkamp, Florian Mueller, Tancredi Tincani
  • Patent number: 10773783
    Abstract: A vehicle body may have an internal skeleton, and a skin formed over the internal skeleton. The skin may include a matrix material, and a plurality of continuous fibers encased within the matrix material. At least one of the plurality of continuous fibers is in tension and has differing levels of tension along its length.
    Type: Grant
    Filed: August 22, 2017
    Date of Patent: September 15, 2020
    Assignee: Continuous Composites Inc.
    Inventors: Ryan C. Stockett, Kenneth L. Tyler
  • Patent number: 10773784
    Abstract: A floor module for an aircraft cargo hold including a cover element and a floor element which is spaced apart from the cover element at least in some segments and which is attached to an underside of the cover element. The cover element includes receiving openings for receiving ball elements. The cover element and the floor element can be formed as a hybrid composite part.
    Type: Grant
    Filed: March 21, 2016
    Date of Patent: September 15, 2020
    Assignee: Telair International GmbH
    Inventors: Thomas Huber, Richard Holzner
  • Patent number: 10773785
    Abstract: An unmanned aerial vehicle includes a plurality of propellers and an airframe. The airframe includes a body having a hollow portion, and a plurality of through holes connected to the hollow portion and formed on an outer peripheral surface of the body. The airframe also includes a plurality of arms supporting the plurality of propellers, and each arm of the plurality of arms includes a base end portion disposed at a body side in a longitudinal direction of the respective arm. The base end portion is inserted in a corresponding through hole of the plurality of through holes and supported by the body. Each arm of the plurality of arms is configured to be stored in the hollow portion of the body by being retracted into the body via the through hole, and expanded out of the body by being pulled out of the body via the through hole.
    Type: Grant
    Filed: September 19, 2019
    Date of Patent: September 15, 2020
    Assignee: PRODRONE CO., LTD.
    Inventors: Kiyokazu Sugaki, Kazuo Ichihara
  • Patent number: 10773786
    Abstract: An aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The strut comprises a strut inboard end portion and a strut outboard end portion. The strut inboard end portion is coupled to and extends from the body and the strut outboard end portion is coupled to and extends from the intermediate portion of the wing. The strut outboard end portion of the strut is configured to generate a download acting on the strut outboard end portion of the strut when the aircraft is in flight.
    Type: Grant
    Filed: June 6, 2017
    Date of Patent: September 15, 2020
    Assignee: The Boeing Company
    Inventors: Anthony J. Sclafani, Adam D. Grasch, Christopher K. Droney, Neal A. Harrison
  • Patent number: 10773787
    Abstract: Wing-to-fuselage joints and aircraft including the same. An aircraft includes a fuselage with an outer fuselage skin that at least partially defines an outer surface of the fuselage and a wing assembly operably coupled to the fuselage via a wing-to-fuselage joint. The wing assembly includes a left wing region with a lower left-wing-region skin and an upper left-wing-region skin, a right wing region with a lower right-wing-region skin and an upper right-wing-region skin, and a center wing region with a lower center-wing-region skin and an upper center-wing-region skin. The upper center-wing-region skin is coextensive with at least one of the upper left-wing-region skin and the upper right-wing-region skin.
    Type: Grant
    Filed: June 14, 2017
    Date of Patent: September 15, 2020
    Assignee: The Boeing Company
    Inventors: Kenneth H. Griess, Gary E. Georgeson
  • Patent number: 10773788
    Abstract: A fairing assembly for an aerial vehicle having a tank that forms a body of the vehicle and a wing coupled to the tank is provided. The fining assembly includes a substructure configured to couple with a tank skin of the tank, a thermal protection system coupled to the substructure, and a seal assembly coupled to the substructure, the seal assembly being configured to overlap at least a portion of an edge of the wing.
    Type: Grant
    Filed: August 15, 2017
    Date of Patent: September 15, 2020
    Assignee: The Boeing Company
    Inventors: Michael J. Best, Jonathan D. Embler, John S. Kruse, Thomas R. Pinney, Drew L. Smallwood
  • Patent number: 10773789
    Abstract: A wing or stabilizer of an aircraft. The wing or stabilizer comprises a box portion, comprising at least one spar and an outer skin coupled to the at least one spar. The wing or stabilizer also comprises at least one panel, comprising an outer face-sheet and an inner face-sheet. In a fore-aft direction the outer face-sheet terminates at an outer free edge. In the fore-aft direction the inner face-sheet terminates at an inner free edge. The at least one panel also includes a core sandwiched between the outer face-sheet and the inner face-sheet. The inner face-sheet comprises a cantilevered portion. The cantilevered portion defines the inner free edge. The cantilevered portion is fastened to the outer skin of the box portion.
    Type: Grant
    Filed: July 7, 2017
    Date of Patent: September 15, 2020
    Assignee: The Boeing Company
    Inventors: Young L. Zeon, Gerfried R. Achtner
  • Patent number: 10773790
    Abstract: An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material layer is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.
    Type: Grant
    Filed: December 15, 2017
    Date of Patent: September 15, 2020
    Assignee: Airbus Operations S.L.
    Inventors: Edouard Menard, Esteban Martino González, Fernando Iniesta Lozano
  • Patent number: 10773791
    Abstract: An aircraft with stealth double wings comprises a main body and stealth double wings. The main body has two main wings respectively having a surface into which a space is formed. The stealth double wings respectively are located in the spaces and include a first and a second rotating shaft, a link rod, a first and a second wing. The link rod has two ends respectively connected with the two rotating shafts. The two rotating shafts respectively have another end connected with the first and second wings. Thereby, when the first wing is moved to cover and enclose the space's opening, the second wing is driven to be located within the space, and when the first wing is moved upwardly away from the space, the second wing is driven to cover and enclose the space's opening, so as to keep the surface intact.
    Type: Grant
    Filed: July 24, 2018
    Date of Patent: September 15, 2020
    Inventor: Shih-Ping Lee
  • Patent number: 10773792
    Abstract: An air flow channeling yaw control device includes a vane cover, a vane array, and an actuator. The vane array includes a plurality of vanes, each of the plurality of vanes comprising a first edge and a second edge, the first edge being hingedly coupled to the vane cover and the second edge being hingedly coupled to a wing of an aircraft. The wing includes a leading edge and a trailing edge. The actuator is configured to move the plurality of vanes from a retracted position into a deployed position. The plurality of vanes, when moved into the deployed position, are configured to direct a flow of air flowing over the leading edge of the wing through channels created by the plurality of vanes. The plurality of vanes, when moved into the retracted position, are configured to retract within the wing.
    Type: Grant
    Filed: March 2, 2018
    Date of Patent: September 15, 2020
    Assignee: Lockheed Martin Corporation
    Inventor: Mark D. Buchholz
  • Patent number: 10773793
    Abstract: A rotor blade locking assembly for locking a rotor blade in a deployed position. The rotor blade locking assembly comprises a locking mechanism configured to be coupled to a blade grip. The locking mechanism comprises a latch and an actuator configured to cause the latch to move between an unlocked position and a locked position. The assembly comprises a locking plate configured to be coupled to the rotor blade. The locking plate comprises a bearing surface configured to bear against a contact surface of the latch, when the latch is in the locked position.
    Type: Grant
    Filed: August 5, 2018
    Date of Patent: September 15, 2020
    Assignee: Textron Innovations Inc.
    Inventors: Kyle Thomas Cravener, Tyler Wayne Baldwin, Jared Mark Paulson
  • Patent number: 10773794
    Abstract: A dynamic rotor-phasing unit can phase rotors in-flight for dynamic rotor tuning and in an idle state for aircraft storage. The input and output shafts can be clocked (e.g., rotated) from 0 degrees apart to in excess of 360 degrees apart or from 0 degrees apart to 140 degrees apart. Such rotation can minimize the footprint of an aircraft for stowing purposes, as the rotor blades can be folded to fit within a smaller area without disconnecting the drive system. Additionally, the unit can allow tiltrotor blades to be clocked during flight, which can allow the live-tuning of the aircraft's rotor dynamics. A fail-safe rotary actuator can rotate a stationary planet carrier to clock the input shaft and the output shaft. Alternatively, an actuator can position a slider housing to clock the input shaft and the output shaft.
    Type: Grant
    Filed: January 10, 2019
    Date of Patent: September 15, 2020
    Assignee: Bell Textron Inc.
    Inventors: Colton Gilliland, Tyson Henry
  • Patent number: 10773795
    Abstract: An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.
    Type: Grant
    Filed: September 24, 2018
    Date of Patent: September 15, 2020
    Assignee: THE BOEING COMPANY
    Inventor: Mark S. Good
  • Patent number: 10773796
    Abstract: A wing-lip arrangement couplable with a wing of an aircraft includes a connection region for coupling or integration with the wing end region, at least one tip, at least one upper surface and at least one lower surface, which extend between a leading edge and a trailing edge of the wing-tip arrangement from the connection region to the at least one tip, and at least one vortilon. The local dihedral of the wing-tip arrangement changes between the at least one tip and the connection region, such that at least a part of the wing-tip arrangement projects at an angle relative to the wing. The at least one vortilon includes a vortilon base and a vortilon tip. The vortilon base is attached to at least one of the at least one lower surface of the wing-tip arrangement. The vortilon tip faces in an upstream direction.
    Type: Grant
    Filed: August 15, 2017
    Date of Patent: September 15, 2020
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Ian Roy Whitehouse, Thomas Ehlers
  • Patent number: 10773797
    Abstract: A method is provided that enhances wheel drive assembly acceleration, heat reduction, and energy efficiency performance during ground travel in aircraft equipped with landing gear wheel-mounted drive assemblies to move aircraft on the ground without reliance on the aircraft's engines or external tow vehicles. Inflation pressure levels of tyres on the landing gear wheels are monitored with pressure and/or temperature sensors to determine and maintain an optimum defined high inflation pressure level for the specific kind of aircraft tyre or the aircraft. A clutch-activated drive assembly may be prevented from transferring torque and driving the aircraft when the optimum high inflation pressure levels are not present in the tyres during ground travel. Tyre pressures may be manually or automatically adjusted in response to processed sensor information to maintain the optimum high inflation pressure level in all tyres as the aircraft is driven with the drive assemblies or with engine thrust.
    Type: Grant
    Filed: February 15, 2017
    Date of Patent: September 15, 2020
    Assignee: Borealis Technical Limited
    Inventors: Jan Vana, Isaiah W. Cox, Joseph J. Cox, Jonathan S. Edelson, Nechama Cox
  • Patent number: 10773798
    Abstract: An aircraft rotor assembly has a yoke and a plurality of rotor blade assemblies coupled thereto. Each of the rotor blade assemblies include a rotor blade, a bearing, and a blade grip coupling the rotor blade to the bearing. Each of the rotor blades is rotatable about a lead-lag axis, flap axis, and a pitch change axis, wherein all the axes intersect within the bearing. Adjacent pairs of rotor blade assemblies are coupled together via a damper assembly that is coupled to the pitch change axis of each of the rotor blade assemblies.
    Type: Grant
    Filed: September 29, 2017
    Date of Patent: September 15, 2020
    Assignee: Bell Textron Inc.
    Inventors: Andrew Paul Haldeman, Dalton T. Hampton, Bryan Marshall, Frank Bradley Stamps
  • Patent number: 10773799
    Abstract: A system includes a higher unmanned multicopter, a lower unmanned multicopter, and a flexible connector. The flexible connector connects the higher unmanned multicopter and the lower unmanned multicopter. The VTM system is configured to carry a payload, including by having the higher unmanned multicopter fly above the lower unmanned multicopter with the flexible connector taut such that both the higher unmanned multicopter and the lower unmanned multicopter contribute to carrying the payload.
    Type: Grant
    Filed: January 19, 2018
    Date of Patent: September 15, 2020
    Assignee: Kitty Hawk Corporation
    Inventors: Sebastian Thrun, Damon Vander Lind
  • Patent number: 10773800
    Abstract: An unmanned aerial vehicle subsystem includes a vehicle-mountable light bar. The light bar includes a periphery and a plurality of lights configured to illuminate through at least a portion of the periphery. The light bar further defines a volume within which is positioned an unmanned aerial vehicle pad and a tether extension and retraction mechanism. The subsystem further includes an unmanned aerial vehicle having at least one camera. A tether is operable with the tether extension and retraction mechanism and extendable from the tether extension and retraction mechanism to the unmanned aerial vehicle. The tether is configured to, during flight of the unmanned aerial vehicle, transmit power to the unmanned aerial vehicle and transmit data signals to and from the unmanned aerial vehicle.
    Type: Grant
    Filed: June 4, 2019
    Date of Patent: September 15, 2020
    Assignee: RSQ-Systems SPRL
    Inventors: Mathieu Buyse, Jean Marc Coulon
  • Patent number: 10773801
    Abstract: Using a trick flight control process, a pilot may fly an aircraft while having control over two axes of orientation while the aircraft may be rotating automatically about a third axis of orientation. The pilot may continue to fly the aircraft during an automated trick rather than relinquishing control completely to the aircraft's electronics.
    Type: Grant
    Filed: July 24, 2017
    Date of Patent: September 15, 2020
    Assignee: TRAXXAS LP
    Inventors: Wesley Ronald Erhart, Thomas Michael Kawamura
  • Patent number: 10773802
    Abstract: The present disclosure provides an aircraft system in the tilt-rotor category with four propulsion units where the tilt angle and thrust of each unit is controlled independently of the other units. The tilt angle for each unit can be adjusted anywhere from below horizontal, to fully forward, and to greater than 180 degrees (i.e. tilted backwards). As a result, the system enables greater control during all phases of flight. Due to continuous, independent tilt control of the angle and thrust of each rotor, the present aircraft can avoid stalls much easier than traditional fixed-wing aircraft and other VTOL designs, as thrust vectors can at any moment be adjusted to compensate for loss of wing lift, making the aircraft safer to use.
    Type: Grant
    Filed: June 25, 2018
    Date of Patent: September 15, 2020
    Assignee: Forward Robotics Inc
    Inventors: Tamara Jean Finlay, Meng Wei
  • Patent number: 10773803
    Abstract: An automatic degradable sphere distributing device for an unmanned aerial vehicle, relating to the technical field of plant protection mechanism. Said distributing device comprises a ranking portion, an adjustment portion and a distributing portion. The ranking portion consists of a rotating shaft (2), blades (1a, 1b), a rolling bearing (12), a sphere cabinet (3), a coupling (9b), a motor support (11b) and a motor (10b). The adjustment portion consists of a housing (501), a bevel gear transmission group (502, 503) and adjustment sheets (504a, 504b, 504c). The distributing portion consists of circular wheels (8a, 8b), a spur gear group (6a, 6b), a guide rod (13), a coupling (9a), a motor support (11a) and a motor (10a). Said distributing device may rank the degradable spheres vertically in sequence, being adaptable to spheres of different volumes, being highly universal, and being capable of distributing the spheres at intervals, with high precision and automation degree.
    Type: Grant
    Filed: November 10, 2015
    Date of Patent: September 15, 2020
    Assignee: JIANGSU UNIVERSITY
    Inventors: Baijing Qiu, Xiang Tong
  • Patent number: 10773804
    Abstract: A seating arrangement for a cabin of a passenger aircraft that includes 5-abreast passenger accommodation suites, each including a privacy wall and a seat movable between a seating position and a lie-flat bed position, and adapted to be laterally positioned in the aircraft cabin in respective adjacent outboard, middle and inboard positions. Three of the suites are adapted to be positioned in a longitudinally-offset position in relation to each other and defining respective ingress/egress paths to a cabin aisle extending along a longitudinal axis of the aircraft cabin adjacent the third suite. Two of the suites are positioned in a longitudinally-offset position in relation to each other and defining respective ingress/egress paths on the opposite side of the cabin aisle. At least some of the suites define an angular offset relative to the longitudinal axis of the cabin aisle.
    Type: Grant
    Filed: April 25, 2017
    Date of Patent: September 15, 2020
    Assignee: B/E AEROSPACE, INC.
    Inventors: Javier Valdes De La Garza, Glenn A. Johnson, Daniel I. Udriste, Alexander N. Pozzi, Mark B. Dowty
  • Patent number: 10773805
    Abstract: Described is a breakover mechanism for a passenger seat that includes a frame member with a rear portion attached to two opposing sides of a seat back of the passenger seat wherein the frame member is at least partially disposed under a seat pan of the passenger seat, at least one moving portion attached to a forward portion of the frame member, a carriage portion fixedly attached to the seat pan; and a single point mechanism attached to the carriage portion. Once a threshold loading condition occurs, the single point mechanism changes states to facilitate movement of the moving portion relative to the carriage portion.
    Type: Grant
    Filed: December 19, 2018
    Date of Patent: September 15, 2020
    Assignee: Safran Seats USA LLC
    Inventors: Girish J. Malligere, Nahum Madrid, Michael T. Murray, Michael Willey
  • Patent number: 10773806
    Abstract: Systems and methods are described for controlling seat actuation and other controls using an in-flight entertainment system of an aircraft or other vehicle. The system can include an electronic control unit configured to send commands to actuate a passenger seat based on input received via a passenger controlled device. The electronic control unit or a related peripheral component is configured to receive a flight phase notification. If the flight phase notification indicates a taxi, take-off or landing phase, the electronic control unit sends a command to disable actuation of the passenger seat. Such command could also be sent if the flight phase notification is not received for a predefined time period.
    Type: Grant
    Filed: April 6, 2018
    Date of Patent: September 15, 2020
    Inventor: Matthew Gledich
  • Patent number: 10773807
    Abstract: An airplane is provided. The airplane includes a compressing device. The compressing device includes a turbine with a first inlet and a second inlet. The turbine provides energy by expanding mediums. The first inlet is configured to receive a first medium of the mediums. The second inlet is configured to receive a second medium of the mediums. The compressing device includes a compressor and a motor. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode. The motor provides a supplementary energy to the compressor.
    Type: Grant
    Filed: May 24, 2017
    Date of Patent: September 15, 2020
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventors: David E. Hall, Louis J. Bruno, Harold W. Hipsky
  • Patent number: 10773808
    Abstract: An airplane is provided. The airplane includes an environmental control system that provides a pressurized medium to a chamber of the airplane. The airplane also includes a bleed system. The bleed system includes a plurality of ports, each of which can provide a bleed medium from an engine of the airplane to the environmental control system. The plurality of ports includes at least a first port, a second port, and a third port. The first port is selected for an idle condition. The second port is selected for a hot day cruise condition. The third port is selected for a standard operating condition. The bleed system can operate in a first mode, a second mode, or a third mode to provide the bleed medium to the environmental control system from the first port, the second port, or the third port respectively.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: September 15, 2020
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventor: Louis J. Bruno
  • Patent number: 10773809
    Abstract: The present invention provides a dewatering device for an air-conditioning system of a plane, comprising: one or more filter plates disposed within a mixing cavity of an air-conditioning system of a plane, for filtering liquid-state water in mixed air in the mixing cavity, wherein the filter plates are configured to be inclinable relative to an axis of the mixing cavity, and an inclination angle thereof is adjustable so as to change a filtering amount of the mixed air.
    Type: Grant
    Filed: September 22, 2015
    Date of Patent: September 15, 2020
    Assignees: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD, COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE
    Inventors: Xuede Sun, Geping Li, Xizhong Jian, Xudong Yan, Zhan Cheng
  • Patent number: 10773810
    Abstract: An aircraft turbojet engine low-pressure compressor or booster, comprising an inlet structure de-iced by a pressurized hot fluid circulation coming from the high-pressure compressor. The de-icing structure comprises a deformable membrane through the thickness of which the pressurized fluid circulation passes. When there is a build-up of ice on the membrane, the pressurized fluid circulation is blocked, resulting in its pressure deforming the membrane in such a manner as to crack the build-up of ice.
    Type: Grant
    Filed: May 14, 2018
    Date of Patent: September 15, 2020
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Nicolas Raimarckers
  • Patent number: 10773811
    Abstract: A window heating system for providing current to a heating element includes a first sensor, a second sensor, and a sensor selection module configured to determine a state of the first and the second sensors. The sensor selection module includes a first comparator associated with the first sensor and configured to determine whether a condition of the first sensor is satisfied. The window heating system also includes a controller configured to control current to the heating element based on the second sensor when the first comparator determines the condition of the first sensor is not satisfied.
    Type: Grant
    Filed: December 6, 2017
    Date of Patent: September 15, 2020
    Assignee: THE BOEING COMPANY
    Inventor: Scott D. Maxwell
  • Patent number: 10773812
    Abstract: An aspect includes a battery charging system for a hybrid electric aircraft. The battery charging system includes a generator, a battery system, and a controller. The controller is operable to charge the battery system up to a first charge level based on receiving a first charging current at a power input. An operational status of a gas turbine engine of the hybrid electric aircraft is monitored. The battery system is charged at a second charging current received from the generator driven by the gas turbine engine responsive to determining that the gas turbine engine is in a taxi state, where the second charging current is less than the first charging current. Charging of the battery system is halted based on detecting a transition of the gas turbine engine from the taxi state to an off-idle throttle state.
    Type: Grant
    Filed: August 17, 2018
    Date of Patent: September 15, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Neil Terwilliger, David A. Golfin
  • Patent number: 10773813
    Abstract: The present invention relates to an aircraft comprising a fuselage (1) and a propulsion unit at the rear of the fuselage, the propulsion unit comprising at least one fan rotor (7, 8), a nacelle (14) fairing the fan and at least one connection means (15) connecting the nacelle to the fuselage, the fan being rotated by the energy supplied by at least one gas-turbine gas generator (2a, 2b) housed in the fuselage, said gas generator comprising auxiliary equipment cooled by a cooling circuit. The aircraft is characterised in that said cooling circuit comprises at least one heat exchanger exchanging heat with the ambient air housed in one of said connection means (15) and/or in said nacelle (14). The cooling circuit optionally comprises also a heat exchanger exchanging heat with the ambient air, housed in the tail unit.
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: September 15, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nils Edouard Romain Bordoni, Antoine Jean-Philippe Beaujard, Nicolas Jerome Jean Tantot
  • Patent number: 10773814
    Abstract: A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the engine control unit, an engine operation control system, and a pilot interface including pilot controls. The engine operation control system includes a processor that initiates a health check of the in-flight engine restart system to determine an in-flight engine restart system status. The engine operation control system processes engine mode of operation commands to establish an engine mode of operation, and delivers commands to aspects of the in-flight engine restart system including the engine control unit based on processing of the engine mode of operation commands. The engine operation control system reports the in-flight engine restart system status and results of the engine mode of operation commands to the flight control computer.
    Type: Grant
    Filed: July 20, 2016
    Date of Patent: September 15, 2020
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Michael Peter Strauss, Michael Joseph DeVita, Mark Denton Bystry, Jr., Joseph Lawrence Simonetti, Carl A. Palmer
  • Patent number: 10773815
    Abstract: A computer-implemented method, system, and/or computer program product optimizes an operation of an aerial drone. A drone on-board computer on an aerial drone receives sensor readings from sensors on the aerial drone, where the sensor readings detect a change in flight conditions while the aerial drone is flying between a first location and a second location. In response to the sensors on the aerial drone detecting a change in the flight conditions while the aerial drone is flying between the first location and the second location, the drone on-board computer disengages an electric motor from propellers on the aerial drone and engages an internal combustion engine to the propellers.
    Type: Grant
    Filed: June 8, 2018
    Date of Patent: September 15, 2020
    Assignee: International Business Machines Corporation
    Inventors: Ahamed Jalaldeen, Chivukula V. L. Narayana
  • Patent number: 10773816
    Abstract: Embodiments of a single lever turboprop control method and system are provided, which utilize torque-based and/or power-based scheduling to achieve a desired (e.g., substantially proportional) relationship between control lever position and the power output of a turboprop engine. In one embodiment, the method includes the step or process of monitoring, at an Engine Control Unit (ECU), for receipt of a Power Lever Angle (PLA) signal from a single lever control device. When a PLA control signal received at the ECU, a target torque or power output is established as a function of at least the PLA control signal. A first engine setpoint, such as a blade angle setpoint or an engine rotational speed setpoint, is determined utilizing the target torque output. An operational parameter of the turboprop engine is then adjusted in accordance with the first engine setpoint.
    Type: Grant
    Filed: July 20, 2018
    Date of Patent: September 15, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Dave Looper, Scot Coffey, Yufei Xiong
  • Patent number: 10773817
    Abstract: A ram air system for an aircraft having an engine and a fuselage with an outer mold line. The ram air system includes an engine air pathway having an opening in the outer mold line defining an engine inlet. The engine air pathway is configured to supply operating air for combustion in the engine. An auxiliary air pathway includes a first intake disposed inside the outer mold line in the engine inlet and a second intake disposed externally to the engine air pathway. The auxiliary air pathway is configured to draw in cooling air to cool ancillary aircraft components from at least one of the first intake and the second intake based on the airspeed of the aircraft.
    Type: Grant
    Filed: March 8, 2018
    Date of Patent: September 15, 2020
    Assignee: NORTHROP GRUMMAN SYSTEMS CORPORATION
    Inventors: Peter A. Brennen, Chris K. Lee, Peter Schmidt
  • Patent number: 10773818
    Abstract: A cooling system includes a first heat exchanger for cooling a refrigerant, an expander configured to receive the refrigerant from the first heat exchanger at least one compressor configured to compress the refrigerant, an ejector configured to receive the refrigerant from the expander as a motive stream that evacuates and compresses the refrigerant from an evaporator, and a liquid separator coupled to an output of the ejector and configured to provide liquid refrigerant to an evaporator loop and vapor refrigerant to the at least one compressor. The evaporator loop includes an expansion device positioned to expand the liquid refrigerant from the liquid separator, and the evaporator configured to receive the refrigerant from the expansion device, heat the refrigerant from a heat load, and pass the refrigerant to the ejector.
    Type: Grant
    Filed: December 29, 2014
    Date of Patent: September 15, 2020
    Assignee: Rolls Royce Corporation
    Inventor: Igor Vaisman
  • Patent number: 10773819
    Abstract: A tank assembly is provided and includes a housing which has a housing volume and which is chargeable with a volume of a first fluid, a bladder disposed within the housing and chargeable with a second fluid such that the bladder has a minimal volume in an uncharged state and a flow system. The flow system includes a portion thereof which is coupled to the bladder and which has a second volume within the housing. The flow system is configured to at least charge the bladder with a volume of the second fluid which is equal to or less than a difference between the housing volume less a sum of the minimal volume and the second volume and the volume of the first fluid.
    Type: Grant
    Filed: August 21, 2017
    Date of Patent: September 15, 2020
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventor: Christoph Haugstetter
  • Patent number: 10773820
    Abstract: A liquid tank system comprises a main liquid tank, an outlet communicating between a fluid circuit and the main liquid tank, an inlet communicating between the fluid circuit and the main liquid tank, and an auxiliary cavity. First vent passage and second vent passage(s) communicate between the main liquid tank and the auxiliary cavity and allows liquid and gas to flow from the main liquid tank to the auxiliary cavity. The second vent passage has a flow control device regulating flow through the second vent passage and having a set point at which it allows liquid and gas to flow from the main liquid tank to the auxiliary cavity only when a pressure in the main liquid tank is beyond a threshold.
    Type: Grant
    Filed: May 2, 2018
    Date of Patent: September 15, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sebastien Bergeron, Pierre Gauvin, Johnny Vinski, Genevieve McMurray