Patents Examined by Assres H Woldemaryam
  • Patent number: 10532819
    Abstract: Apparatus and methods for supporting human external cargo from the hoist of a hoist-equipped helicopter are provided. The apparatus has at least one personal harness for supporting a user; and at least one harness segment with a top end point attachable to the helicopter hoist through an attachable fitting and at least one bottom end point directly or indirectly attachable to the personal harness. The harness segment, and the personal harness externally support the user from the helicopter hoist and allows the user to be safely suspended from the helicopter in order for work or rescue operations to be administered by the user.
    Type: Grant
    Filed: June 23, 2015
    Date of Patent: January 14, 2020
    Assignee: Ascent Aerospace Ltd.
    Inventor: Trent Lemke
  • Patent number: 10526086
    Abstract: An improved drone with 4 flat wings reciprocating up and down, complete with motor and electronics. Appendages on each wing's surface allow air to pass across it during the up-motion, and block it in the down-motion; this creates lift and permits flight and manoeuvres. The drone resembles either a flying bird or an insect, depending on wing motion and on passive attachments appropriate for the respective resemblance, making for inconspicuousness. The drone can execute complex work, either as solitary or in a team, either in flight or at rest in various places, after approaching and adhering expertly.
    Type: Grant
    Filed: October 27, 2014
    Date of Patent: January 7, 2020
    Inventor: Ioannis Micros
  • Patent number: 10526074
    Abstract: A system for the control of the door assemblies of a bay of a landing gear of an aircraft, that is retractile and is able to be deployed, the opening of the bay for the landing gear being able to be closed by a forward door assembly and an aft door assembly, comprises a coupling mechanism of the forward door assembly and the aft door assembly, that is configured such that the aft door assembly is not completely closed, but is ajar, as soon as the forward door assembly is opened during the deployment of the landing gear and the aft door assembly is completely closed at the complete closing of the forward door assembly when the landing gear is retracted.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: January 7, 2020
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Christian Cros, Jérôme Phalippou, Christophe Mialhe, Jacques Peres
  • Patent number: 10518905
    Abstract: A device is provided. The device includes a first pillar. The first pillar includes a bottom portion having an opening. The first pillar further includes a top portion coupled to the bottom portion by a middle portion. The top portion includes a plurality of shelves stacked along a common axis intersecting the bottom portion. Each of the shelves has a respective recess. The first pillar further includes a plurality of clamps. Each of the shelves has a respective clamp of the clamps. Each respective clamp and respective recess of the shelves forms an airfoil cross-sectional shape. The first pillar further includes a plurality of locks. Each of the shelves has a respective lock of the locks. Each of the locks has a first locking portion on respective shelves and a second locking portion on respective clamps of the shelves.
    Type: Grant
    Filed: July 10, 2017
    Date of Patent: December 31, 2019
    Assignee: TEXTRON INNNOVATIONS INC.
    Inventors: Kevin Matthew Knott, Dominic Michael Przano
  • Patent number: 10513329
    Abstract: A signal line protection assembly connecting to a propulsion system of an aerial vehicle includes a foot stand and a protection sleeve. The foot stand includes a foot stand sleeve including a bearing member and a receiving portion. The bearing member has a first side and a second side that is opposite to the first side. The first side is configured to bear the propulsion system, and the receiving portion is arranged at the second side. The protection sleeve is configured to receive a signal line. At least a portion of the protection sleeve is received in the receiving portion.
    Type: Grant
    Filed: March 8, 2019
    Date of Patent: December 24, 2019
    Assignee: SZ DJI TECHNOLOGY CO., LTD.
    Inventor: Di Ou
  • Patent number: 10513354
    Abstract: There is disclosed a Payload Ejection System (PES) able to store any set of payloads for launch and eject that set of payloads at a controlled speed with a low tumble rate while accommodating any offset centre of mass within a restricted volume. The need for ballasting or balancing is eliminated thus freeing up the design space for these payloads. Insensitivity to centre of mass location is enabled by the use of a deployment hinge assembly arrangement which uses two or more non-parallel folding hinge arrangements that allow for linear motion of the output link in one direction while restricting the motion all other directions. One embodiment of the current PES concept uses four (4) hinge panel assemblies, selected to provide optimal stiffness around the entire mechanism. The stiffness of the PES is integral to managing offset centre-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.
    Type: Grant
    Filed: July 12, 2019
    Date of Patent: December 24, 2019
    Assignee: MACDONALD, DETTWILER AND ASSOCIATES INC.
    Inventors: Tej Singh Sachdev, John Douglas Lymer, Richard Andrew Bryan, Branko Francetic, Paul Robert Peacock, Peter Panagiotis Krimbalis
  • Patent number: 10507940
    Abstract: A method for building an aerodynamic structure, an aerodynamic structure, and a vehicle that includes the aerodynamic structure are provided. The method includes providing a structure with at least one substantially-flat exterior surface. The method also includes attaching blocks of rigid fibrous insulation to the at least one substantially-flat outer surface of the structure. Outward-facing surfaces of the blocks of rigid fibrous insulation extend past a target outer mold line of a final aerodynamic shape. The method also includes machining the outward-facing surfaces of the attached blocks to the outer mold line.
    Type: Grant
    Filed: March 28, 2017
    Date of Patent: December 17, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Moises Nevarez, Robert J. Perez, Stephanie C. Klimczak, Jonathan D. Embler
  • Patent number: 10501187
    Abstract: In providing an aircraft lavatory unit capable of suppressing cost and time for installation in a case where a lavatory unit and an ascending/descending unit are to be installed on the aircraft, the present invention provides an aircraft lavatory unit in which a lavatory area and an ascending/descending area are integrally formed, wherein an ascending/descending mechanism which connects to an upper floor or a ceiling space of the aircraft lavatory unit inside the ascending/descending area is provided on a wall surface dividing the lavatory area and the ascending/descending area.
    Type: Grant
    Filed: April 6, 2015
    Date of Patent: December 10, 2019
    Assignee: JAMCO CORPORATION
    Inventors: Kouichi Ooi, Yoshihisa Tsutsui
  • Patent number: 10501201
    Abstract: Actuator systems and methods for controlling aerodynamic control surfaces of aircraft including a first actuator receiving a first input and a first linear translation element that moves based thereon, the first linear translation element operably connected to a first portion of the control surface. A first sensor assembly is disposed relative to the first actuator that generates an output based on a displacement of the first translation element. A second actuator receives a second input and a second linear translation element moves based on the second input, the second linear translation element operably connected to a second portion of the control surface. A second sensor assembly is disposed relative to the second actuator that generates a second sensor output based on a displacement of the second translation element. A controller generates the inputs and receives the sensor outputs to determine if an error condition exists for the system.
    Type: Grant
    Filed: March 27, 2017
    Date of Patent: December 10, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Erik Harrington, Christian Miller, Yuniya S. Bishop
  • Patent number: 10501172
    Abstract: An aircraft landing gear assembly including structural members coupled via a coupling including a bearing. The bearing has a body defining a first bearing surface arranged to contact a first counter-face of the coupling. The first bearing surface is defined by a first tubular layer of fibre reinforced polymer of a first type having an axis and containing synthetic fibres of a first type wound around and along the axis of the bearing. The bearing body further has a second tubular layer of fibre reinforced polymer of a second type containing synthetic fibres of a second type wound around and along the axis of the bearing.
    Type: Grant
    Filed: April 3, 2017
    Date of Patent: December 10, 2019
    Assignee: Safran Landing Systems UK LTD
    Inventors: Nicholas Foster, Sam Evans
  • Patent number: 10494083
    Abstract: Aerodynamic drag associated with a flap hinge assembly used to pivotally mount a flap to the trailing edge of an aircraft wing can be reduced when the cross-sectional area of the hinge fairing which surrounds the flap hinge assembly is reduced in size. The reduction in cross-sectional area of the hinge fairing is enabled when the flap hinge assembly attachment footprint to the underside of the flap box is also reduced. The flap hinge assembly has an internal support rib positioned between spars of the flap box structure internal to the skin, a hinge fitting exhibiting an actuation point and a hinge point positioned proximate a front spar of the flap box structure external to the skin, and a link passing through an aperture in the lower skin of the flap and coupling the internal support rib to the hinge fitting.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: December 3, 2019
    Assignee: The Boeing Company
    Inventors: Andrew S. Currie, Tony Sanders
  • Patent number: 10496107
    Abstract: A drone aircraft for personal assistance or protection. When a driver's car is located in a parking lot at night, the driver can summon a drone stored in the vehicle which flies to the driver and leads the driver to the vehicle by projecting a spot of light onto the ground. The drone makes a video recording of events occurring at this time and transmits the recording to a remote storage location.
    Type: Grant
    Filed: January 17, 2017
    Date of Patent: December 3, 2019
    Assignee: Valeo North America, Inc.
    Inventors: Mark Anthony Pattison, Gavin Francis Warner, John Steven Orisich
  • Patent number: 10479471
    Abstract: An aircraft is provided. The aircraft includes truss elements configured to form a space frame fuselage, and skin panels connected with the truss elements and configured to form a skin over said space frame fuselage. The skin panels are movable relative to one another so as to prevent loading of the space frame fuselage from inducing loading in the skin. The aircraft includes a fitting. The fitting includes a first intermediate portion, a first outer portion, and a first inner portion. The first outer and inner portions are spaced apart from each other and interconnected by the first intermediate portion. The skin panels include first and second skin panels that are adjacent to each other. The first skin panel has a first end portion that is adjacent to a second end portion of the second skin panel. The fitting is positioned between the first and second skin panels such that the first and second end portions of the skin panels extend between the first inner and outer portions.
    Type: Grant
    Filed: November 30, 2016
    Date of Patent: November 19, 2019
    Assignee: The Boeing Company
    Inventors: Angelina M. Conti, Robert E. Grip, Ted K. Rothaupt
  • Patent number: 10479530
    Abstract: An aircraft high-lift device comprising a kinematic chain connected to flaps, the kinematic chain comprising a plurality of shafts connected by coupling systems. This high-lift device comprises at least one differentiated coupling system different from the non-differentiated coupling systems, the differentiated coupling system being configured to be coupled to an adapter and comprising at least one poka-yoke feature. Another subject of the disclosure is an aircraft which comprises at least one high-lift device.
    Type: Grant
    Filed: February 10, 2017
    Date of Patent: November 19, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Deniz Keskin
  • Patent number: 10479508
    Abstract: A jumpseat having a carrier structure comprising at least one seat pan. The jumpseat comprises a mounting structure provided with at least two arms having at least one degree of freedom to move in rotation about a stowage axis, said carrier structure being hinged to each arm by a pivot arrangement, said pivot arrangement being hinged to each arm about a folding axis, the folding and stowage axes being parallel to each other, said pivot arrangement giving the carrier structure at least one degree of freedom to move in rotation relative to the arms about an elevation axis.
    Type: Grant
    Filed: July 7, 2017
    Date of Patent: November 19, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventor: Jean-Francois Joffre
  • Patent number: 10479521
    Abstract: A noncombustible gas distribution method includes distributing noncombustible gas to a center wing tank throughout a continuous, first flight period and, as a result, reducing flammability exposure time during the first flight period or during a subsequent flight period. The method includes not distributing noncombustible gas to left and right main wing tanks while the noncombustible gas is distributed to the center wing tank throughout the first flight period and while the left and right main wing tanks are non-flammable. A noncombustible gas distribution system includes a noncombustible gas source and distribution tubing from the gas source to left and right main wing tanks and a center wing tank. A distribution mechanism yields a greater proportion of gas flow per tank unit volume distributed to an outboard section of the left and right main wing tanks compared to an inboard section during a climb phase of the aircraft's flight.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: November 19, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Ivana Jojic, Alan Grim, Bill F. Lin, Kristopher Vaughan
  • Patent number: 10472046
    Abstract: An internal wing control surface linkage system comprising: an actuator arm configured to rotate around a first rotation axis within an airfoil body. A linking arm is mounted within the airfoil body. The linking arm comprises a linking tube and a linkage rod slideably received within the linking tube. The linking tube comprises a hinged end pivotally coupled to the actuator arm about a first pivot axis parallel to the first rotation axis to cause deflection of a control surface coupled to the airfoil body during rotation of the actuator arm. The linkage rod comprising a hinged end coupled to a clevis about a second pivot axis of the control surface. A spherical bearing swivelly coupling the linking arm and providing a fixed swivel pivot which swivels the linking arm, as the linking tube simultaneously slides within the spherical bearing and, in combination, the rod simultaneously slides within the linking tube.
    Type: Grant
    Filed: December 22, 2016
    Date of Patent: November 12, 2019
    Assignee: LOCKHEED MARTIN CORPORATION
    Inventors: Steven J. Ellzey, James C. Copp
  • Patent number: 10472075
    Abstract: A pneumatic parachute deployment system is disclosed. In various embodiments, a pneumatic parachute deployment system as disclosed herein includes a bladder configured to control a parachute's expansion in at least one dimension, and an inflation mechanism configured to inflate the bladder. The bladder is inflated when the parachute is deployed, and in various embodiments may be used to speed deployment of the parachute and/or restrict the parachute to opening at least initially only to a limited extent.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: November 12, 2019
    Assignee: Kitty Hawk Corporation
    Inventor: Damon Vander Lind
  • Patent number: 10457373
    Abstract: An aircraft with a composite tail boom that comprises at least partly a tubular tail boom cone with an outer skin and an inner skin, wherein the inner skin delimits a hollow interior of the composite tail boom, wherein a plurality of rod-shaped stiffening elements and a plurality of ring-shaped stiffening elements are arranged between the outer skin and the inner skin, the plurality of rod-shaped stiffening elements being oriented in longitudinal direction of the composite tail boom and the plurality of ring-shaped stiffening elements being distributed along the longitudinal direction in the tubular tail boom cone.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: October 29, 2019
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Axel Fink
  • Patent number: 10450083
    Abstract: Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of sensing three dimensional (3D) airflow by an aircraft includes: collecting measurements characterizing airflow near the aircraft; analyzing the collected measurements; creating, by a processor, a computer model predicting one or more 3D airflow patterns parameter values based on the analyzing; obtaining one or more additional measurements characterizing airflow near an aircraft of the plurality of aircraft, and evaluating an error between an airflow parameter value predicted by the computer model and the one or more additional measurement.
    Type: Grant
    Filed: June 13, 2018
    Date of Patent: October 22, 2019
    Assignee: SUNLIGHT AEROSPACE INC.
    Inventors: Sergey V. Frolov, Michael Cyrus, Allan J. Bruce, John P. Moussouris