Patents Issued in August 13, 2019
  • Patent number: 10377461
    Abstract: An aircraft structural component having a skin element, including an inner surface, a multitude of transverse stiffening elements, which lie against the inner surface of the skin element, and a multitude of longitudinal stiffening elements, perpendicular to the transverse stiffening elements against the inner surface of the skin element, wherein between a first and a second transverse stiffening element and also between a first and a second longitudinal stiffening element, a first skin section is defined. An aircraft structural component is provided with the quantity of the longitudinal stiffening elements reduced. A first applied reinforcement includes a core layer having a contour line running along the circumference of the skin element, the first applied reinforcement including a face sheet surrounding the core layer on the side thereof which faces away from the skin element, which face sheet is connected to the skin element along the core layer contour line.
    Type: Grant
    Filed: June 23, 2015
    Date of Patent: August 13, 2019
    Assignee: Airbus Operations GmbH
    Inventors: Paul Jörn, Pierre Zahlen, Markus Müller, Ichwan Zuardy, Claus Hanske
  • Patent number: 10377462
    Abstract: A decompression assembly for use in an aircraft comprises a cabin lining element, an opening formed in the element, and an air channel arranged adjacent to a rear face of the element and connected to the opening. The air channel is provided with an air outlet which, during normal operation of the assembly, discharges air exiting a cabin region delimited by the element through the opening into an area located between the element and an aircraft outer skin, a first decompression opening, and a first decompression flap which, during normal operation of the decompression assembly, closes the first decompression opening in the air channel and which, in the event of a rapid decompression, opens the first decompression opening to allow a pressure equalization between the aircraft cabin region and the aircraft area located between the cabin lining element and the aircraft outer skin.
    Type: Grant
    Filed: November 11, 2016
    Date of Patent: August 13, 2019
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Uwe Schneider
  • Patent number: 10377463
    Abstract: An aircraft having a hatch and a fall-protection device includes a structure comprising a roof pierced with an opening, a cover plate, and a lock provided to adopt a locking position, in which the lock holds the cover plate in the closed position in the opening, or, alternatively, an unlocked position, in which the lock does not hold the cover plate. The aircraft further comprises at least one fall-protection device provided so that, when the lock moves into the unlocked position, it is in a first position to allow movement of the cover plate under the influence of gravity from its closed position to an intermediate position, in which the cover plate is suspended from the structure and then moves from the first position into a second position, during which movement the cover plate moves from the intermediate position into an open position, no longer attached to the structure.
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: August 13, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Yannick Chourreau, Loic Challancin
  • Patent number: 10377464
    Abstract: This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection molding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles to close the tool. Further, the injection molding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demolded.
    Type: Grant
    Filed: March 13, 2017
    Date of Patent: August 13, 2019
    Assignee: AIRBUS OPERATIONS, S.L.
    Inventors: Pablo Cebolla Garrofe, Álvaro Calero Casanova, Soledad Crespo Peña, Carlos Garcïa Nieto, Iker Vélez De Mendizábal Alonso, Enrique Guinaldo Fernandez, Francisco Javier Honorato Ruiz, Alvaro Torres Salas
  • Patent number: 10377465
    Abstract: The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The basic structure is a semi rigid airship with movable longerons. Movement of the longerons adjusts the camber of the upper and/or lower surfaces to achieve varying shapes of the lifting-body. This transformation changes both the lift and drag characteristics of the craft to alter the flight characteristics. The transformation may be accomplished while the craft is airborne and does not require any ground support equipment.
    Type: Grant
    Filed: October 15, 2014
    Date of Patent: August 13, 2019
    Assignee: Hyalta Aeronautics, Inc.
    Inventor: Scott R. Kempshall
  • Patent number: 10377466
    Abstract: An unmanned air vehicle (UAV) having a fuselage, a foldable propulsion means to generate thrust leading to the UAV movement, a driving means to drive the propulsion means and a plurality of flight control surfaces actuators are further included. The UAV further includes at least one pair of foldable wings where the rear portion of the wings is pivotally attached to the fuselage. The wings having at least one roll control surface hinged to at least one of the foldable wings. At least a pair of tail stabilizers having ruddervators flight control surfaces hinged to the tail stabilizers. In a fully extended position or in ready to fly state position, each of the foldable wings are deployed perpendicular to one another and perpendicular to the fuselage to form an offset-x shaped wings, and in a stowed position, each of the wings are positioned parallel to one another and positioned parallel to the fuselage.
    Type: Grant
    Filed: August 25, 2016
    Date of Patent: August 13, 2019
    Assignee: UVISION AIR, LTD.
    Inventors: Moshe Kahlon, Amit Morag
  • Patent number: 10377467
    Abstract: A rotating circular aerofoil system that includes a disc body that has an aerofoil shape in cross section. The aerofoil shape has an angle of attack that is symmetrical. The disc body's includes a circular inner edge which forms a circular center opening and the disc body's leading edge. The disc body also includes an outer edge that forms the trailing edge. Intersecting ribs extend across the center opening and include a shaft opening that attaches to a rotating shaft. Formed on the top and bottom surfaces of the disc body are evenly spaced apart, extending T-shaped or L-shaped fins. In one embodiment, an air blower or impeller is attached to a hollow shaft linked to an air pump. When the air pump is activated, air is delivered to the air blower and impeller that distributes the air over the top surface of the disc body to improve lift.
    Type: Grant
    Filed: July 1, 2016
    Date of Patent: August 13, 2019
    Inventors: Thoi H. Huynh, Fuji P. Hynh
  • Patent number: 10377468
    Abstract: A modular brake and rudder control system usable in an aircraft. The modular system mounts atop the flight deck floor without penetrating through the floor when the system is operatively connected to the aircraft's fly-by-wire brake and rudder systems. Pedal assemblies extending from the housing are rotatable and longitudinally moveable relative to the housing. A brake control system fully contained in the housing is connected to the pedal assemblies and provides a signal via an electrical connector to the fly-by-wire brake system upon rotation of the pedals. A rudder control system is fully contained in the housing and is operable independent of the brake control system. The rudder control system detects longitudinal motion of the pedal assemblies and provides a signal via an electrical connector to the fly-by-wire rudder system.
    Type: Grant
    Filed: March 8, 2017
    Date of Patent: August 13, 2019
    Assignee: Mason Electric Company
    Inventors: Fred Carner, Bijan Salamat
  • Patent number: 10377469
    Abstract: An aircraft includes a first structure that includes a first surface and a first coil conformed to, or embedded within, the first surface. The aircraft includes a second structure that includes a second surface and a second coil conformed to, or embedded within, the second surface. The second structure is configured to couple to the first structure such that the first coil is aligned with the second coil to enable inductive coupling between the first coil and the second coil.
    Type: Grant
    Filed: March 4, 2016
    Date of Patent: August 13, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Jonathan B. Vance, Scott R. Johnston
  • Patent number: 10377470
    Abstract: A system and method for providing state comparison of redundant processors used, e.g. to control a rotor craft. A primary microprocessor is configured to receive input data from a position sensor and a flight condition sensor and determine therefrom a first desired control law state, and a secondary microprocessor is configured to receive input data from the position sensor and the flight condition sensor and determine therefrom a second desired control law state. The first desired control law state from the primary microprocessor and the second desired control law state from the secondary microprocessor are compared, and (a) the first desired control law state is entered when the first desired control law state and the second desired control law state match, and (b) a last known control law state is maintained when the first desired control law state and the second desired control law state do not match.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: August 13, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventor: Jillian Samantha Alfred
  • Patent number: 10377471
    Abstract: An apparatus, method and system for combining aerodynamic design with engine power to increase synergy between the two and increase climb performance, engine-out performance, and fuel efficiency for a variety of aircraft or the like.
    Type: Grant
    Filed: August 14, 2017
    Date of Patent: August 13, 2019
    Inventor: David Birkenstock
  • Patent number: 10377472
    Abstract: An airplane including a wing and a wing tip attached to an end of the wing. The wing has a wing leading edge and a wing trailing edge in a wing chord plane. The wing tip includes a winglet and a ventral fin. The winglet has a winglet leading edge continuously transitioning from the wing leading edge, and a winglet trailing edge continuously transitioning from the wing trailing edge. The winglet leading edge may be swept rearward. The winglet includes an adapter section attached to the end of the wing, a transition section attached to the adapter section, a blade section attached to the transition section, the blade section extending above the wing chord plane, and a first tip section attached to the blade section. The ventral fin may be coupled to the winglet at an attachment location adjacent the transition section, and extends below the wing chord plane.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: August 13, 2019
    Assignee: Aviation Partners, Inc.
    Inventor: Louis B. Gratzer
  • Patent number: 10377473
    Abstract: According to one embodiment, a clutch may be coupled between a rotor system and a power train of a rotorcraft. The clutch may be operable to disengage the rotor system from the power train during operation of the power train. A clutch control system in communication with the clutch and include a rotorcraft condition sensor operable to sense an operating condition of the rotorcraft and a control unit operable to prevent the clutch from disengaging the rotor system from the power train if the operating condition of the rotorcraft fails to satisfy a predetermined criterion.
    Type: Grant
    Filed: January 4, 2013
    Date of Patent: August 13, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Ryan T. Ehinger, David Sembritzky, Carlos A. Fenny, Gary A. Cope, Charles J. Kilmain
  • Patent number: 10377474
    Abstract: A blade guard removable structure for an aerocraft has a connecting base, a blade guard and an elastic limiting strip. The blade guard has an insert. The connecting base has a receptacle for allowing the insert to be inserted therein. The limiting strip has an inner end. The inner end is connected to the insert. The limiting strip has a protruded fastener, an extension portion and an outer end. The protruded fastener is disposed on the extension portion. The protruded fastener is located at the outer end. The connecting base has a limiting recess for limiting the protruded fastener. The limiting strip is located in between the blade guard and the limiting recess.
    Type: Grant
    Filed: November 18, 2016
    Date of Patent: August 13, 2019
    Assignee: GUANGDONG SYMA MODEL AIRCRAFT INDUSTRIAL CO., LTD
    Inventor: Jiongliang Xiao
  • Patent number: 10377475
    Abstract: A nozzle for use with a rotor blade for a reaction drive type helicopter includes a first wall, a second wall opposing the first wall, and sidewalls extending between the first wall and the second wall enclosing a cavity having an upstream end and a downstream end. The nozzle includes an inlet section for receiving a gasflow at the upstream end. The distance between the first wall and the second wall reduces to a throat downstream of the inlet section. An expansion section extending from the throat, downstream thereof.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: August 13, 2019
    Assignee: RJ HELICOPTER CORP.
    Inventor: David J. White
  • Patent number: 10377476
    Abstract: A vehicle includes a propulsion system using one or more impellers as opposed to propellers. The impellers impart circumferential and radial velocity components to the working fluid, which may be air or water. The air is deflected by counter-vortex chambers in a shroud to convert the circumferential and radial velocity to an axial velocity aligned with the axis of rotation of the impeller.
    Type: Grant
    Filed: April 3, 2017
    Date of Patent: August 13, 2019
    Assignee: MOHYI LABS, LLC
    Inventor: John Mohyi
  • Patent number: 10377477
    Abstract: According to one embodiment, a pitch link includes a first link, a second link coupled to a first end of the first link, a third link coupled to a second end of the first link opposite the first end, and a first bearing housing having a first bearing and a second bearing housing having a second bearing. The first bearing housing is removably coupled to the second link. The second link separates the first bearing housing from the first link. The second bearing housing is removably coupled to the third link. The third link separates the second bearing housing from the first link.
    Type: Grant
    Filed: November 5, 2012
    Date of Patent: August 13, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Joseph Biser, Clifton B. Day, Frank B. Stamps, Daniel Spivey
  • Patent number: 10377478
    Abstract: The present invention discloses a rotor control system where rapid changes in rotor torque are transferred into moment forces acting about the blade pitch axis of a rotor blade in a thrust-generating rotor, to ultimately control the movements of a rotary wing aircraft. The moment forces acting on the rotor blade are transferred through a carefully adjusted damping member in order to allow rapid changes in rotor torque to create cyclic changes in blade pitch angle, while slow or permanent changes are cancelled out and affects the rotational speed and the thrust generated by the rotor, without permanently affecting the blade pitch angle of individual rotor blades.
    Type: Grant
    Filed: January 20, 2016
    Date of Patent: August 13, 2019
    Assignee: FLIR UNMANNED AERIAL SYSTEMS AS
    Inventors: Petter Muren, Trygve Frederik Marton, Ivar Johnsrud, Päl Hagh Sandberg
  • Patent number: 10377479
    Abstract: The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: August 13, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Thomas Dewey Parsons, Carlos Alexander Fenny, Erik John Oltheten
  • Patent number: 10377480
    Abstract: A variable thrust cross-flow fan system for an aircraft including a rotatable wing member having a first housing member; an actuator assembly operably coupled to the first housing member; and a variable thrust cross-flow fan assembly including a first and second driver plates having a plurality of blades rotatably mounted therebetween. The plurality of blades has a circular path of travel when rotating and includes a control assembly coupled to the plurality of blades to generate a variable thrust force. The control assembly includes a control cam that is substantially non-rotatable relative to the first and second driver plates and a hinge member that is fixedly connected to the control cam and to the first housing member at a hinge axis. Rotation of the first housing member by the actuator assembly imparts rotation of the control cam about the hinge axis, thereby changing the direction of the variable thrust force.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: August 13, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Kirk L. Groninga, Daniel B. Robertson, Matthew E. Louis
  • Patent number: 10377481
    Abstract: Systems and methods to launch an aircraft are disclosed. In one embodiment, a system to launch an aircraft comprises a launch arm comprising at least one load cell, an aircraft coupled to the launch arm, and a release mechanism in communication with the at least one load cell, wherein the release mechanism releases the aircraft when the at least one load cell indicates that a load on the launch arm is below a predetermined threshold. Other embodiments may be described.
    Type: Grant
    Filed: October 26, 2012
    Date of Patent: August 13, 2019
    Assignee: The Boeing Company
    Inventors: James J. Childress, Daniel J. Perron
  • Patent number: 10377482
    Abstract: A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle system which has removable wing sections which allow for re-configuration with different wing section types, allowing for configurations adapted for a particular flight profile. A method of customizing a configuration of an unmanned aerial vehicle based upon flight profile factors such as duration, stability, and maneuverability.
    Type: Grant
    Filed: May 1, 2016
    Date of Patent: August 13, 2019
    Assignee: Transition Robotics, Inc.
    Inventors: Jeffrey Kyle Gibboney, Pranay Sinha
  • Patent number: 10377483
    Abstract: This disclosure describes an aerial vehicle, such as an unmanned aerial vehicle (“UAV”), which includes a plurality of maneuverability propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll). The aerial vehicle may also include a lifting propulsion mechanism that operates to generate a force sufficient to maintain the aerial vehicle at an altitude.
    Type: Grant
    Filed: December 20, 2016
    Date of Patent: August 13, 2019
    Assignee: Amazon Technologies, Inc.
    Inventors: Robert Roy Champagne, Jr., Gur Kimchi, Louis LeRoi LeGrand, III, Nicholas Hampel Roberts, Ricky Dean Welsh
  • Patent number: 10377484
    Abstract: Systems and methods for unmanned aerial vehicle (UAV) positional anchors. Signals may be broadcast via a signal interface of an anchor in a defined space which also includes a UAV. The UAV is at one location within the defined space, and the anchor is at another location within the defined space. A virtual environment may be generated that corresponds to the defined space. The virtual environment may include at least one virtual element, and a location of the virtual element within the virtual environment may be based on the location of the anchor within the defined space. A visual indication may be generated when the UAV is detected within a predetermined distance from the location of the anchor. In some embodiments, a visual element may be generated to augment the anchor where a location of the visual element is based on a location of the anchor within the defined space. The visual element may be changed when the UAV is flown to the location of the anchor within the defined space.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: August 13, 2019
    Assignee: SONY INTERACTIVE ENTERTAINMENT INC.
    Inventors: Michael Taylor, Dennis Dale Castleman, Glenn Black, Javier Fernandez Rico
  • Patent number: 10377485
    Abstract: The invention relates to a system for automatically inspecting a surface of an object such as an aircraft (54), a transport vehicle, a building or an engineering structure, said surface being liable to contain a defect. The system is characterized in that it comprises a fleet comprising at least one flying robot (14a, 14b, 14c), each flying robot comprising a module for acquiring images of at least one portion of the surface to be inspected, and a module for processing the acquired images, which module is suitable for providing information representative of the state of each inspected surface portion, which information is called the processing result.
    Type: Grant
    Filed: June 15, 2016
    Date of Patent: August 13, 2019
    Assignee: DONECLE
    Inventor: Matthieu Claybrough
  • Patent number: 10377486
    Abstract: A drone speaker system is configured to deploy a fleet of drone speaker units. Each drone speaker unit includes a speaker configured to broadcast acoustic signals and a flight system configured to aerially transport a speaker. The drone speaker system initially generates a spatial map of a location where the drone speaker units are to be deployed. The drone speaker system then identifies suitable perching locations for the drone speaker units. Then, the drone speaker system deploys the fleet of drone speaker units to those perching locations to place one or more speakers. Once positioned in this manner, the speakers can generate a sound field. The drone speaker units may also reconfigure the speakers to achieve different sound fields having varying characteristics.
    Type: Grant
    Filed: December 7, 2017
    Date of Patent: August 13, 2019
    Assignee: HARMAN INTERNATIONAL INDUSTRIES, INCORPORATED
    Inventors: Sven Kratz, Joseph Verbeke, Stefan Marti, Adam Boulanger
  • Patent number: 10377487
    Abstract: A display device, configured to display an image photographed by a camera mounted on a remotely controlled mobile object, includes a display part which is mountable on a head of a user and capable of displaying an image, a receiving part configured to receive a photographed image and position information of the mobile object transmitted from the mobile object, a position detection part configured to detect a position of the display part, a direction detection part configured to detect a direction of the display part, and a controller configured to control image displaying on the display part, determine whether the mobile object exists in the direction of the display part and within a particular range with respect to a position of the display part, and switch images to be displayed on the display part depending on whether the mobile object exists within the particular range or not.
    Type: Grant
    Filed: December 22, 2017
    Date of Patent: August 13, 2019
    Assignee: Brother Kogyo Kabushiki Kaisha
    Inventor: Hiromasa Takahashi
  • Patent number: 10377488
    Abstract: A tandem-wing unmanned aircraft system (UAS) includes forward and aft wings mounted to the fuselage by frangible spar elements, the forward wings in a shoulder-wing configuration and the aft wings in a low-wing configuration. The forward and aft wings may incorporate fill-span multifunctional control surfaces on their trailing edges. The wing design prevents interference with airflow over the fuselage into a tail-mounted ducted propeller assembly, which pivots to provide vectored thrust. A nose compartment at the nose end of the fuselage may include a forward-mounted camera with a hemispherical field of view, the nose camera protected by transparent exterior panels. A ventral cargo compartment mounted amidships may include a ventral camera gimbal-mounted to provide an overhead perspective; the ventral camera may be gimbal-mounted for articulation along multiple rotational axes to provide additional views of the UAS exterior.
    Type: Grant
    Filed: May 2, 2017
    Date of Patent: August 13, 2019
    Assignee: Draganfly Innovations Inc.
    Inventors: Garry Reusch, Mark Ter Keurs, Nathan Armstrong, Zenon Dragan
  • Patent number: 10377489
    Abstract: A device for transporting two or more articles to two or more locations comprising: one or more holding units for carrying the two or more articles one or more orifices for loading and/or delivering the articles a controlling unit for directing the movement and operations of the device a flying attachment for transporting the device through air.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: August 13, 2019
    Inventor: Angad Singh Sawhney
  • Patent number: 10377490
    Abstract: A package launch system can be implemented to propel a package from an unmanned aerial vehicle (UAV) in a generally vertically descent trajectory, while the UAV is in motion. The package launch system can apply the force onto the package in a number of different ways. For example, flywheels, coils, and springs can generate the force that establishes the vertical descent path of the package. Further, the package delivery system can also monitor the package during its vertical descent. The package can be equipped with one or more control surfaces. Instructions can be transmitted from the UAV via an RF module that cause the one or more controls surfaces to alter the vertical descent path of the package to avoid obstructions or to regain a stable orientation.
    Type: Grant
    Filed: January 17, 2018
    Date of Patent: August 13, 2019
    Assignee: Amazon Technologies, Inc.
    Inventors: Brian C. Beckman, Menashe Haskin, Michael Rolnik, Yan Vule
  • Patent number: 10377491
    Abstract: A delivery device coupled to a drone can be used to distribute dry powdered materials to a target area. The powdered materials can be stored in a hopper having an auger at the lower end of the hopper. An auger motor can be actuated to transport the powdered material to an aeration chamber where the powdered material is mixed with turbulent air. The aerated powdered materials can then be emitted from the delivery device from a slinger disc onto a target area.
    Type: Grant
    Filed: April 20, 2016
    Date of Patent: August 13, 2019
    Assignee: DROPCOPTER
    Inventors: Adam Fine, Matthew Koball
  • Patent number: 10377492
    Abstract: An illuminating ceiling system for an internal cabin of a vehicle includes a plurality of ceiling panels. Each of the ceiling panels includes a lighting assembly secured to a first portion that overlaps a second portion of adjacent one of the ceiling panels. The lighting assembly is configured to emit light into the internal cabin.
    Type: Grant
    Filed: February 13, 2018
    Date of Patent: August 13, 2019
    Assignee: The Boeing Company
    Inventor: Sunghoon Lee
  • Patent number: 10377493
    Abstract: A mobile galley cart including a wheeled insulated housing having a door configured to open to access to the interior of the housing, a thermoelectric chiller mounted near the bottom of the cart, cold air ducting in fluid communication with the thermoelectric chiller and opening to the interior of the housing, and warm air ducting including a warm air exhaust arranged to exhaust warm air from the mobile galley cart. A mobile galley cart system including a cart configured to dock at a separate service wall to provide service connections therebetween.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: August 13, 2019
    Assignee: Rockwell Collins, Inc.
    Inventor: Peter John Leslie Burd
  • Patent number: 10377494
    Abstract: A divider assembly that includes a main body portion having a lower section and an upper section and a removable panel having front and back surfaces. The upper section tapers in width in an upward direction and the main body portion includes front and back surfaces. The removable panel is removably secured to the upper section on the front surface of the main body portion.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: August 13, 2019
    Assignee: C&D ZODIAC, INC.
    Inventors: Joseph Merrick, Ian Geoffrey Scoley, Eric Heimbach, Jean-Claude Bourgade, Didier Poho
  • Patent number: 10377495
    Abstract: A ram air channel arrangement for ambient air supply into an aircraft comprises a ram air channel which has a ram air inlet channel and a ram air outlet channel arranged downstream of the ram air inlet channel and in fluid communication with the ram air inlet channel. The ram air channel arrangement further comprises a cabin exhaust air line which is adapted to have cabin exhaust air flow therethrough which has been removed from an aircraft cabin and which cabin exhaust air line is connected to the ram air inlet channel and is adapted to lead the cabin exhaust air into the ram air inlet channel.
    Type: Grant
    Filed: September 16, 2016
    Date of Patent: August 13, 2019
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Holger Bammann, Alexander Solntsev, Frank Klimpel, Alexandre Broquet
  • Patent number: 10377496
    Abstract: An airflow control system for use in a vehicle is provided. The airflow control system includes a manifold and a recirculation duct in flow communication with the manifold. The recirculation duct includes a fan and a recirculation valve. The system additionally includes a ventilation duct coupled in flow communication with the recirculation duct between the fan and the recirculation valve. The ventilation duct is in flow communication with an ambient environment surrounding the vehicle and includes at least one ventilation valve.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: August 13, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Luong Hoang Le, George Bates, III, Myles Edward Brown, Brian P. Berryessa, Ryan S. Perham
  • Patent number: 10377497
    Abstract: There is provided an anti-icing system that has a simple structure and makes it possible to exert anti-icing performance by dealing with displacement of a stagnation point without increasing air resistance. The anti-icing system according to the present invention blows heated gas to an inner surface of a wing of an aircraft, and includes: a piccolo tube that includes a flow path through which the heated gas flows in a longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside; and a supply source that supplies the heated gas toward the piccolo tube. The piccolo tube is held to cause positions of the respective ejection holes to be fixed in a gravity direction.
    Type: Grant
    Filed: January 20, 2017
    Date of Patent: August 13, 2019
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Toshiyuki Ishida, Gento Ichikawa, Yoichi Uefuji, Masatoshi Morishita, Kazuhiro Kawai, Satoshi Watanabe, Go Fujita
  • Patent number: 10377498
    Abstract: An aircraft, an aircraft engine and a corresponding method provide for anti-icing based upon energy provided by a fan assembly of the aircraft engine, such as by rotation of a low pressure shaft of the fan assembly. The aircraft includes an aircraft body having wings and an aircraft engine carried by the aircraft body. The aircraft engine includes a core gas turbine engine and a fan assembly coupled to the core gas turbine engine. The fan assembly may include a fan, a low pressure turbine and a low pressure shaft connecting the fan and the low pressure turbine. The aircraft engine also includes an electric anti-icing system that has a variable frequency generator driven by the fan assembly, and one or more resistive heaters carried by the wings. The variable frequency generator is configured to provide electrical energy to the one or more resistive heaters.
    Type: Grant
    Filed: January 21, 2016
    Date of Patent: August 13, 2019
    Assignee: THE BOEING COMPANY
    Inventor: Steve G. Mackin
  • Patent number: 10377499
    Abstract: A restraint arrangement for an evacuation system may comprise a first strap configured to be disposed along a length of the evacuation system, and a second strap configured to be disposed along the length of the evacuation system, wherein the first strap is coupled to the second strap, the first strap is coupled to the evacuation system via a first plurality of attachment members along the length of the evacuation system, the second strap is coupled to the evacuation system via a second plurality of attachment members along the length of the evacuation system, and the first strap is configured to separate from the second strap in response to a predetermined load.
    Type: Grant
    Filed: January 17, 2017
    Date of Patent: August 13, 2019
    Assignee: Goodrich Corporation
    Inventors: Jaro Volny, Drew Hartman
  • Patent number: 10377500
    Abstract: To provide an electrified aircraft, and a method of controlling a regenerative electric power of the electrified aircraft where a path angle and a descending rate can be controlled with a good response independently from a speed while controlling the drag force of the propulsion drive system and where it is possible to maximize safely a generated electric power in each flight status at the time of descent or ascent. The electrified aircraft includes a propeller or a fan for propulsion; an electric drive motor for rotary-driving the propeller or the fan and for generating an electric power by the rotation of the propeller or the fan; and an estimation unit for estimating a drag force of the propeller or the fan or an electric power generation amount of the electric drive motor based on propulsion system parameters of the electric drive motor.
    Type: Grant
    Filed: March 12, 2015
    Date of Patent: August 13, 2019
    Assignee: Japan Aerospace Exploration Agency
    Inventors: Hiroshi Kobayashi, Akira Nishizawa, Tomoko Iijima, Takeshi Tagashira
  • Patent number: 10377501
    Abstract: A rotary wing aircraft having an electrical installation including at least one thermopile for powering at least one piece of electrical load equipment. Technical specifications for the thermopile specify: a usable power for supplying to the load equipment in the range 20 W to 200 kW, a power rise time lapse lying in the range 3 s to 30 s, and a low operating time for usefully supplying a predetermined quantity of electrical energy lying in the range 10 s to 180 s. The invention applies in particular to rotary wing aircraft.
    Type: Grant
    Filed: July 28, 2016
    Date of Patent: August 13, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventor: Matthieu Connaulte
  • Patent number: 10377502
    Abstract: An engine mount assembly for coupling an engine to an airframe. The engine mount assembly includes a torsion bar coupled to the engine and a lateral movement control assembly coupled between the torsion bar and the airframe. The lateral movement control assembly includes a spring having a lateral stiffness. The torsion bar rotates in response to lateral movement of the engine such that the lateral movement of the engine is controllable based on the lateral stiffness of the spring.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: August 13, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Bruce Bennett Bacon, John Elton Brunken, Jr., Michael Edwin Rinehart, Nick Pravanh
  • Patent number: 10377503
    Abstract: An engine assembly comprising an engine and a pod surrounding the engine that is equipped, upstream according to the direction of entry of air into the engine, with a fan provided with blades, the pod having an upstream air intake. The engine assembly also comprises a display unit including at least one light ring arranged in the air intake upstream of the fan, the light ring including at least one row of light-emitting diodes and being configured to emit at least one light beam and to project it on the blades of the fan.
    Type: Grant
    Filed: June 2, 2016
    Date of Patent: August 13, 2019
    Assignee: Airbus Operations SAS
    Inventors: Alain Porte, Frederic Chelin, Wolfgang Rehm, Nathalie Papin, Irene Moreno Gonzalez
  • Patent number: 10377504
    Abstract: A system for controlling aircraft movement includes a platform configured to support the aircraft. The system includes a securing mechanism coupled to the platform to releasably couple the aircraft onto the platform. The system includes a conveying system coupled to the platform. The conveying system configured to, with the aircraft coupled to the platform during take-off of the aircraft, move the platform to accelerate the aircraft. The conveying system configured to, during landing of the aircraft, decelerate the aircraft. The system includes a controller coupled to the securing mechanism and to the conveying system. The controller configured to communicate with the securing mechanism and with the conveying system to control acceleration of the platform during take-off of the aircraft and deceleration of the platform during landing of the aircraft.
    Type: Grant
    Filed: August 14, 2018
    Date of Patent: August 13, 2019
    Assignee: The Boeing Corporation
    Inventors: Brett M Hoffstadt, William A. Harkness, Royal E. Meservy
  • Patent number: 10377505
    Abstract: Passageway including a section that is extendable and retractable, the section including frame, slide track assemblies, and scissor bar assembly. The frame includes upright members on a first side of the frame. The slide track assemblies are disposed proximately to the upright members. Each of the slide track assemblies includes a slide track and a slide block. The slide track has a cavity and a channel. The slide block can ascend, descend, and rotate within the cavity. The slide block includes a guide block that extends from the slide block through the channel. The scissor bar assembly is secured to the upright members and slide blocks of the slide track assemblies such that the upright members are enabled to extend and retract with respect to each other along an arcuate path, wherein the guide block limits rotation of the slide block to rotation of the guide block within the channel.
    Type: Grant
    Filed: March 16, 2018
    Date of Patent: August 13, 2019
    Assignee: East Island Aviation Services, Inc.
    Inventor: James Larson
  • Patent number: 10377506
    Abstract: A braking system for a passenger boarding bridge are provided. The braking system includes a locking member fixedly mounted on the cabin and at least one set of braking assemblies. Each set of the braking assemblies includes an oscillating member rotatably mounted on the cab, an oscillating wheel mounted on the oscillating member and an elastic member having a pre-tightening force. The oscillating wheel cooperates with an outer side of the drive belt to form an abutting force so as to balance the pre-tightening force. The pre-tightening force of the elastic member rotates the oscillating member to a direction of the locking member and cooperates with the locking member in a locking manner to realize braking when the length of the drive belt between the driven wheel and the driving wheel exceeds a preset value or is in a broken state.
    Type: Grant
    Filed: July 15, 2016
    Date of Patent: August 13, 2019
    Assignees: CHINA INTERNATIONAL MARINE CONTAINERS (GROUP) LTD, SHENZHEN CIMC-TIANDA AIRPORT SUPPORT LTD
    Inventors: Feipeng Wei, Wei Xiang, Jianming Huang, Jifang Nie
  • Patent number: 10377507
    Abstract: The invention consists of an actuated box and navigation aid for automatic delivery by unmanned vehicles (UAV) or drones. It also incorporates delivery information via the web linking orders, enclosure status, package specific drone homing signals, delivery confirmations and more. This system incorporates a novel and effective means for providing a standardized and predicable area for safe landing during delivery by functionalized drones. It also secures the package from theft, vandalism, animals and the weather and provides features necessary for air-traffic management.
    Type: Grant
    Filed: June 11, 2016
    Date of Patent: August 13, 2019
    Inventors: Simon Tremblay, Eric Bharucha
  • Patent number: 10377508
    Abstract: Systems and methods are provided for installing fasteners. One exemplary embodiment is a method that includes inserting a fastener into a hole, and gripping ends of the fastener via dies. At least one of the dies includes a permanent coating having a static friction coefficient of less than 0.2 at a surface contacting the fastener. The method further includes plastically deforming the fastener via force from the dies, thereby expanding the fastener into interference with the hole along a length of the fastener such that an amount of interference between the fastener and the hole along the length of the fastener is greater than one and a half thousandths of an inch and less than twenty thousandths of an inch.
    Type: Grant
    Filed: November 29, 2016
    Date of Patent: August 13, 2019
    Assignee: The Boeing Company
    Inventors: William Donald Hood, Donald Brian Peterson, Curtis Leon Hayes, Paul Michael Haworth, Tyler James Kumley
  • Patent number: 10377509
    Abstract: A fully automated method for testing functionality of a spacecraft or aircraft unit under testing (UUT) includes selecting a test station at which to conduct a first functionality test on the UUT. The method also includes coupling a program specific module (PSM) to the UUT. Each PSM is configured to couple to a specific type of UUT to provide power and telemetry to the specific type of UUT. The method further includes a robot arm moving the UUT to the selected test station. The method still further includes conducting the first functionality test on the UUT at the selected test station.
    Type: Grant
    Filed: September 19, 2014
    Date of Patent: August 13, 2019
    Assignee: Raytheon Company
    Inventor: Rigel Quinn Woida-O'Brien
  • Patent number: 10377510
    Abstract: Various enhanced rocket fairings and associated mechanisms are discussed herein for split fairings with two fairing halves. In some implementations, electrically-actuated base clamps are included to deploy the rocket fairing by applying a spring force between a corresponding fairing half and a payload adapter, which directs movement of the fairing halves upwards and away from the payload adapter until release of the fairing halves. In other implementations, electrically-actuated fairing mechanisms are included to hold together a first fairing half and a second fairing half, and separate the first fairing half from the second fairing half using a spring force. In further implementations, one fairing half includes a tab feature configured to overlap a second fairing half. The tab feature can deform inward under a pressure differential between an exterior and a payload envelope to reduce a gap between the two fairing halves.
    Type: Grant
    Filed: November 14, 2018
    Date of Patent: August 13, 2019
    Assignee: Vector Launch Inc.
    Inventors: Brian James Riskas, Robert Duane Hill, Emerald James Adair, Kerry Michael Kugler, Richard William Dalgarno, Mark Edward Bishop, Robert Stewart Skillen