Patents Examined by Assres H Woldemaryam
  • 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
  • Patent number: 10450046
    Abstract: Aspects of the disclosure relate to terminating flight of a balloon that may include separating a connection between a balloon envelope and a payload of the balloon. In one example, a payload separation apparatus includes a first shaft configured to attach to the envelope, a second shaft configured to attach to the payload, a pair of arms, and a bracket arranged to secure the pair of arms to the first shaft. In another example, a system includes a flight termination assembly having a cutting edge configured to cut an opening in the envelope and a payload separation apparatus. The apparatus includes a first shaft configured to attach to the envelope, a second shaft configured to attach to the payload, a pair of arms, and a bracket configured to secure the pair of arms to the first shaft. The system also includes a controller configured to activate the cutting edge.
    Type: Grant
    Filed: July 24, 2018
    Date of Patent: October 22, 2019
    Assignee: Loon LLC
    Inventors: Michael Hall-Snyder, Kyle Brookes
  • Patent number: 10450067
    Abstract: A cover panel for a core panel of a structural aircraft component includes a protection cover having an outer shape corresponding to the outer shape of the core panel and including at least one cutout aperture, and at least one fabric panel mounted to the protection cover and covering the at least one cutout aperture.
    Type: Grant
    Filed: November 29, 2016
    Date of Patent: October 22, 2019
    Assignee: Airbus Operations GmbH
    Inventors: Bastian Schaefer, Stefan Holst, Anna Wengorra
  • Patent number: 10450056
    Abstract: Systems and methods are provided for a hydraulic stabilizer trim actuator (HSTA). The HSTA may operate one or more movable control surfaces. The HSTA operate responsive to commands issued by the pilot and/or by a controller and may include hydraulic architecture that minimizes the probability of an un-commanded movement or movement in the opposite direction of such commands.
    Type: Grant
    Filed: July 19, 2016
    Date of Patent: October 22, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Derek M. Joseph, Kevin B. Eck, Christopher D. Feet, Yonas T. Meshesha, Timothy J. Soderquist, Barry D. Hance
  • Patent number: 10450057
    Abstract: An electromechanical actuator includes an actuator that is translatable along an axis relative to a case and that is made up of a deployed part and a non-deployed part, which are following one another along the axis and which are respectively deployed and not deployed outside the case. The axial span of the deployed part varies proportionally opposite that of the non-deployed part as a function of the translated position of the actuator. The actuator also includes an electric motor for translating the actuator, which is supported by the case and is connected to the non-deployed part of the actuator by a transmission. The case defines an inner volume inside which the non-deployed part of the actuator, the motor and the transmission are arranged. The inner volume is, during operation of the actuator, pressurized while being filled with a gaseous medium.
    Type: Grant
    Filed: May 18, 2016
    Date of Patent: October 22, 2019
    Assignee: LORD SOLUTIONS FRANCE
    Inventors: Bastien Roussey, Pierre Bettini
  • Patent number: 10443675
    Abstract: An aircraft includes an airframe having an extending tail, and a counter rotating, coaxial main rotor assembly located at the airframe including an upper rotor assembly and a lower rotor assembly. A translational thrust system is positioned at the extending tail and providing translational thrust to the airframe. An active vibration control (AVC) system is located and the airframe and includes a plurality of AVC actuators configured to generate forces to dampen aircraft component vibration, and an AVC controller configured to transmit control signals to the plurality of AVC actuators thereby triggering force generation by the plurality of AVC actuators. A method of damping vibration of an aircraft includes receiving a vibration signal at an AVC controller, communicating a control signal from the AVC controller to a plurality of AVC actuators, generating a force at the AVC actuators, and damping vibration of the aircraft via the generated force.
    Type: Grant
    Filed: August 6, 2015
    Date of Patent: October 15, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: William A. Welsh, Steven D. Weiner, Robert H. Blackwell, Jr.
  • Patent number: 10442534
    Abstract: An aircraft comprises a weapons bay, the weapons bay comprising a cavity having an opening through which stores may be deployed, and a door assembly for exposing/closing the opening of the cavity. A first store is held in the cavity via a launcher and a first structure is disposed inside the cavity, for controlling the aero-acoustic environment. The first structure for controlling the aero-acoustic environment is removeably mounted in the weapons bay, such that if the first store is exchanged for a second, different, store, the structure for controlling the aero-acoustic environment may be unmounted from the weapons bay and removed, to be exchanged for a second, different, structure for controlling the aero-acoustic environment.
    Type: Grant
    Filed: December 26, 2017
    Date of Patent: October 15, 2019
    Assignee: MBDA UK Limited
    Inventors: Nigel John Taylor, Benjamin James Newby
  • Patent number: 10442518
    Abstract: A moisture diversion system of an aircraft for capturing moisture from at least one internal aircraft structure or at least one gap, the moisture diversion system comprising: a drip shield with an upper surface having a concave shape, at least one moisture channel disposed in the upper surface of the drip shield, the drip shield being in a moisture capturing orientation under the at least one internal aircraft structure or the at least one gap.
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: October 15, 2019
    Assignee: THE BOEING COMPANY
    Inventor: Mark Lennart Larson
  • Patent number: 10442535
    Abstract: In a preferred embodiment, an aircraft monument is adapted for being mounted against an aft-facing bulkhead of the aircraft. The monument may have an aisle-accessible compartment that includes comestible item dispensers and lower footwell regions to accommodate the passengers seated immediately aft of the monument. The monument may also include an aft-facing wall that is readily removal during a maintenance operation so as to facilitate servicing of a heater or chiller unit disposed inside the monument.
    Type: Grant
    Filed: April 3, 2017
    Date of Patent: October 15, 2019
    Assignee: B/E Aerospace, Inc.
    Inventor: Jefferey McKee
  • Patent number: 10435139
    Abstract: A gurney flap arrangement comprises: an airfoil with an opening in a surface of the airfoil; a gurney flap having a first position in which at least a portion of the gurney flap extends through the opening and projects outwardly from the airfoil surface, and a second position in which the gurney flap does not project from the airfoil surface or projects outwardly from the airfoil surface to a lesser extent; and a seal disposed about the opening to seal a gap in the opening between the gurney flap and the airfoil.
    Type: Grant
    Filed: March 31, 2017
    Date of Patent: October 8, 2019
    Assignee: CLAVERHAM LTD.
    Inventors: Suat Bekircan, Paul Brewer
  • Patent number: 10435145
    Abstract: A tension lifting wing wheel assembly includes a peripheral rim located concentrically with a hub supported by a plurality of spokes, each spoke extending therebetween. A series of wings, each wing having an aerodynamically lifting shape extending between a leading edge and a trailing edge. Each wing of the series of wings is assembled to the tension wheel assembly by coupling an area of the wing proximate the leading edge to a leading edge spoke and an area of the wing proximate the trailing edge to a trailing edge spoke. The wings are arranged having a gap provided between the wing trailing edge of each forward located wing and the wing leading edge of each trailing located wing. The tension lifting wing wheel assembly can be employed as a propulsion and/or lifting device integrated into a vehicle, such as an airplane, a helicopter, a tandem rotor helicopter, etc.
    Type: Grant
    Filed: March 26, 2017
    Date of Patent: October 8, 2019
    Inventor: Alfred Finnell
  • Patent number: 10427805
    Abstract: The invention relates to a space wing, produced by means of a diaphragm forming a polygonal surface provided with an inflatable structure which includes ribs extending over the diaphragm along diagonals of the diaphragm and passing through a central point of the diaphragm. The inflatable structure includes at least one film strip, the perimeter of which adheres onto the diaphragm such as to form an inflatable space with the diaphragm.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: October 1, 2019
    Assignee: ARIANEGROUP SAS
    Inventors: Guillaume Cecchini, Hervé Guenat, Claude-Emile Mahy
  • Patent number: 10427808
    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 center 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 center 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 center-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.
    Type: Grant
    Filed: May 19, 2015
    Date of Patent: October 1, 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: 10414480
    Abstract: Systems and methods are provided for securing aircraft sidewall. One embodiment comprises a hanger for supporting sections of sidewall for an aircraft. The hanger includes an elongated vertical member that attaches to a frame of the aircraft, and sets of keyholes that are each arranged in a vertical pattern along the member and that are each configured to support a corresponding section of sidewall of the aircraft. Each keyhole includes a receptacle dimensioned to receive a fitting from a section of sidewall, and a slot dimensioned to slidably accept the fitting via the receptacle to secure the fitting in place. The slot size of keyholes in each set varies from one end of the vertical pattern to another end of the vertical pattern.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: September 17, 2019
    Assignee: The Boeing Company
    Inventors: Cory M. Hitchcock, Thomas S. Perkins, Erik Ivar Wiman, Gregory A. Tubbs
  • Patent number: 10414518
    Abstract: Attitude of a vehicle may be controlled using movable mass. The movable mass may move inside a vehicle or its outline, outside of the vehicle or its outline, inside-to-outside and/or outside-to-inside of the vehicle or its outline, or any combination thereof. The movable mass may be a solid, liquid, and/or gas. When the center-of-mass of the vehicle is moved relative to the line-of-action of applied forces such as thrust, drag, or lift, a torque can be generated for attitude control or for other purposes as a matter of design choice. In the case of external movable masses that extend from the vehicle or its outline, when operating in endoatmospheric flight, or general travel through a fluid, aerodynamic forces from the atmosphere or general fluid forces may further be leveraged to control the attitude of the vehicle (e.g., aerodynamic flaps).
    Type: Grant
    Filed: November 7, 2016
    Date of Patent: September 17, 2019
    Assignee: The Aerospace Corporation
    Inventors: Kevin L Zondervan, Jerome K Fuller
  • Patent number: 10407171
    Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.
    Type: Grant
    Filed: March 1, 2019
    Date of Patent: September 10, 2019
    Assignee: AUTEL ROBOTICS CO., LTD.
    Inventors: Dongdong Luo, Feng Ni, Hang Lv, Wenbing Su
  • Patent number: 10399660
    Abstract: A decompression panel assembly for use in an aircraft includes a frame including a first surface and an opposing second surface, wherein the frame defines a grille opening and at least partially defines a flow path opening. The decompression panel assembly also includes a face panel having a first surface retained against the frame second surface such that the face panel at least partially covers the grille opening. A retention mechanism is coupled to the face panel and is configured to retain the face panel against the frame in a closed position.
    Type: Grant
    Filed: June 6, 2016
    Date of Patent: September 3, 2019
    Assignee: The Boening Company
    Inventors: Douglas Alan Brown, Adam Robert Weston, Brian Tatsuo Imada
  • Patent number: 10399668
    Abstract: An actuator drive disconnection system comprises a housing and a drive coupling mounted in the housing, the drive coupling coupling a drive motor to an actuator drive train. A manually operable drive disconnection mechanism selectively moves the drive coupling from a first position in which the motor and actuator drive train are coupled and a second position in which the motor and actuator drive train are disconnected. The drive disconnection mechanism comprises an operating element which is manually extended from the housing to move the drive coupling from the first position to the second position.
    Type: Grant
    Filed: May 20, 2016
    Date of Patent: September 3, 2019
    Assignee: GOODRICH ACTUATION SYSTEMS SAS
    Inventor: Laurent Schwartz