Patents Examined by Assres H Woldemaryam
  • Patent number: 10196129
    Abstract: Two element aerofoils are provided, having an aerofoil chord, a primary element having a first leading edge and a first trailing edge, a secondary element having a second leading edge and a second trailing edge, a gap between the primary element and the secondary element, and an axial overlap between the first trailing edge and the second leading edge. The secondary element is deflectable with respect to the primary element about a fixed hinge point by a flap deflection angle. The secondary element is configured to operate in airbrake mode when deflected by a respective the flap deflection angle corresponding to a design airbrake deflection angle wherein to generate an airbrake drag. In at least some examples, the axial overlap is numerically greater than ?0.5% of the aerofoil chord, at least for the design airbrake deflection angle. Also disclosed are methods for operating air vehicles, and methods for designing two-element aerofoils.
    Type: Grant
    Filed: June 8, 2014
    Date of Patent: February 5, 2019
    Assignee: ISRAEL AEROSPACE INDUSTRIES LTD.
    Inventors: Michael Shepshelovich, Danny Abramov
  • Patent number: 10183738
    Abstract: A control augmentation system for high aspect ratio aircraft has aileron/flaperon and throttle position sensors; spoiler and flap controls; a mode switch with manual, and landing modes; and a controller driving left and right spoiler and flap servos, the controller including at least one processor with memory containing firmware configured to: when the mode switch is in manual mode, drive both spoiler servos to a symmetrical position according to the spoiler control; when the mode switch is in landing mode, drive the left spoiler to a position dependent on aileron and throttle position, and the right spoiler to a position dependent on aileron and throttle position, the left and right spoiler positions differing whenever ailerons are not centered, and an average of spoiler positions is more fully deployed when the throttle position is at a low-power setting than when the throttle position is at a high-power setting.
    Type: Grant
    Filed: April 2, 2015
    Date of Patent: January 22, 2019
    Inventor: Marc Arnold
  • Patent number: 10179648
    Abstract: An airborne drone launch and recovery apparatus for selectively launching drones located on the underside of a carrier aircraft or recovering drones following flight of the drones, the airborne launch and recovery apparatus has an extensible stinger slidable along the length of a stinger sheath between a retracted position proximal the rear portion of the carrier aircraft and an extended position in front of the carrier aircraft, and a catcher shuttle carried on the forward part of the stinger for extending into the non-turbulent air in front of the carrier aircraft when the stinger is in the extended position. The carrier shuttle includes a launch/recovery assembly for selectively either having a locked condition for the recovery guide of a drone prior to the positioning of the catcher shuttle in a selected for the launch of the drone, and having an open condition for receiving the recovery guide of a drone at the termination of the flight of the drone to terminate the flight.
    Type: Grant
    Filed: June 8, 2016
    Date of Patent: January 15, 2019
    Inventors: Howard Martin Chin, Kimberly A. Carraha
  • Patent number: 10160549
    Abstract: An ice detecting apparatus comprising: a body including at least one ice detector mounted thereon and having an ice detecting surface and a scraping member so mounted relative to said body as to allow their movement one relative to the other and configured for scraping ice from said detecting surface during said movement.
    Type: Grant
    Filed: January 27, 2015
    Date of Patent: December 25, 2018
    Assignee: ISRAEL AEROSPACE INDUSTRIES LTD.
    Inventors: Michael Levkovitch, Yehuda Kalman, Maayan Dermer, Michaela Alon, Nachum Levi, Dov Davidor, Evgeny Vadrovnik
  • Patent number: 10144521
    Abstract: A method and system providing an airflow to a wing anti-ice system includes receiving an airflow from an outside air supply, compressing the airflow via an electric compressor, controlling a temperature of the airflow from the electric air compressor via a heat exchanger in fluid communication with the electric compressor and the wing anti-ice system, and providing the airflow to the wing anti-ice system via the heat exchanger.
    Type: Grant
    Filed: August 4, 2015
    Date of Patent: December 4, 2018
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Robert M. DeRoy
  • Patent number: 10144523
    Abstract: An ice resistant structure is provided which includes a self-supporting, structural platform, a retaining, protective layer and a subsurface anti-icing (AI) and/or de-icing (DI) layer. The retaining, protective layer is disposed over the self-supporting, structural platform. The subsurface anti-icing (AI) and/or de-icing (DI) layer is located between the self-supporting, structural platform and the retaining, protective layer. The subsurface Al and/or DI layer is a functional layer such that an Al and/or DI agent is released to a surface of the retaining protective layer by an activation mechanism responsive to a change in an environmental condition.
    Type: Grant
    Filed: October 30, 2017
    Date of Patent: December 4, 2018
    Assignee: Sunlight Products Inc.
    Inventors: Allan James Bruce, Michael Cyrus, Sergey Frolov
  • Patent number: 10144496
    Abstract: An atmospheric balloon includes an upper apex and a lower apex and a balloon membrane. The balloon membrane includes a plurality of balloon gores. The balloon gores extend between the upper and lower apexes. One or more of the balloon gores includes upper straight line gore edges and lower straight line gore edges. The upper and lower straight line gore edges are coupled along one or more corresponding upper and lower straight line gore edges of adjacent balloon gores of the plurality of balloon gores. The one or more balloon gores are formed with cutting the gore material along a straight line cutting edge to form the upper and lower straight line gore edges.
    Type: Grant
    Filed: August 19, 2015
    Date of Patent: December 4, 2018
    Assignee: Raven Industries, Inc.
    Inventors: Michael Scott Smith, Michael William Zimmerman
  • Patent number: 10137989
    Abstract: A construction kit for a housing structure of a monument for a cabin of a vehicle, in particular of an aircraft includes a plurality of integrally formed sandwich panels which each have two cover panels, which surround a core, and are formed with panel connecting structures which are each formed as a plug region or as a mating plug region. The mating plug region is formed so as to be complementary to the plug region in such a way that a plug region of a sandwich panel can be plugged into the mating plug region of another sandwich panel to connect the sandwich panels.
    Type: Grant
    Filed: April 12, 2016
    Date of Patent: November 27, 2018
    Assignee: Airbus Operations GmbH
    Inventors: Tim Von Ahlen, Daniel Hiebing, Ansgar Josef Fennen, Falk Bajorat, Christian L├╝bbering
  • Patent number: 10137995
    Abstract: A one-time flare mechanism system for use with an aerial payload system is described which uses minimal actuation force to produce a reliable flare with minimal shock to the payload, parafoil and rigging.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: November 27, 2018
    Assignee: Earthly Dynamics, LLC
    Inventors: Mark F Costello, Michael Brian Ward, Edward James Scheuermann
  • Patent number: 10137975
    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: April 6, 2016
    Date of Patent: November 27, 2018
    Assignee: The Boeing Company
    Inventors: Cory M. Hitchcock, Thomas S. Perkins, Erik Ivar Wiman, Gregory A. Tubbs
  • Patent number: 10137978
    Abstract: The invention relates to a locking mechanism for a folding wing tip. The locking mechanism has a locked configuration, in which a first part is received in a second part such that the first part may not be withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part may be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configuration and the unlocked configuration by rotation of at least one of the first part or second part around the longitudinal axis of the locking mechanism.
    Type: Grant
    Filed: May 12, 2016
    Date of Patent: November 27, 2018
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: Matt Harding
  • Patent number: 10118708
    Abstract: According to various embodiments, disclosed is a beam structure comprising a four-point cross section for an inflatable article comprising an inflatable slide. The beam structure has greater beam strength and provides greater structural support than an inflatable beam having a traditional circular cross section.
    Type: Grant
    Filed: October 19, 2015
    Date of Patent: November 6, 2018
    Assignee: GOODRICH CORPORATION
    Inventors: Drew Hartman, Jaro S. Volny
  • Patent number: 10112696
    Abstract: An aircraft assembly is disclosed and includes a fuselage including a turbine engine mounted within the aft fuselage. A burst zone is defined about the turbine engine and a tail is disposed at least partially with the burst zone. The tail includes primary control surfaces and sacrificial control surfaces. The sacrificial control surfaces can break away in a defined manner to maintain integrity of the primary control surfaces outside of the burst zone.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: October 30, 2018
    Assignee: United Technologies Corporation
    Inventors: Jesse M. Chandler, Gabriel L. Suciu
  • Patent number: 10112700
    Abstract: A multi-mode mobility micro air vehicle (MAV) accomplishes ground locomotion by hopping on a retractable leg. The hopping is translated into forward locomotion when aided by the forward thrust of propellers, and the orientation of locomotion is directed by aerodynamic controls like ailerons, rudders, stabilators, or plasma actuators. The foot of the leg is convexly curved so as to produce hopping that is statically and passively dynamically stable. The MAV is also equipped for vertical takeoff so that it may conduct multiple idling missions in sequence and may return home for recovery and reuse. Structural integration of power storage and photovoltaic generation systems into the aerodynamic surface of the MAV lightens the weight of the MAV while also providing a strong structure and permitting the MAV to harvest its own energy.
    Type: Grant
    Filed: July 19, 2011
    Date of Patent: October 30, 2018
    Assignee: Orbital Research Inc.
    Inventors: Matthew C. Birch, Richard Kolacinski
  • Patent number: 10106241
    Abstract: Under constraints on the space and the weight of an aircraft, the present invention aims to protect structural members from a heat generation part. An aircraft includes: a fuselage; an air conditioning pack installed on the outside of a lower part of the fuselage; a fairing covering the air conditioning pack; an outer heat insulation material disposed in a region of the fuselage, which corresponds to the air conditioning pack, from the outside of the fuselage; and an inner heat insulation material disposed around the region on the inside of the fuselage.
    Type: Grant
    Filed: December 8, 2015
    Date of Patent: October 23, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Nobuhide Hara, Osamu Yamada
  • Patent number: 10099779
    Abstract: A flexible wheel drive for aircraft onboard taxi systems is provided. In association with an aircraft wheel assembly there is provided a drive gear assembly that is adapted to be driven by a motor mounted to an aircraft. A flexible drive flange is secured about an inboard rim of the aircraft wheel assembly and a flexible ring is interconnected between the drive gear assembly and the flexible drive flange. Preferably, the flexible ring is made of a metal textile or high-temperature composite and the drive flange is of a high-strength stainless steel.
    Type: Grant
    Filed: April 6, 2016
    Date of Patent: October 16, 2018
    Assignee: Meggitt Aircraft Braking Systems Corporation
    Inventors: Kurt Burkhalter, Michael P. Osburn
  • Patent number: 10099783
    Abstract: An improved accessory mounting is disclosed for a rotary wing aircraft comprising a frame supporting a plurality of driven propellers. A transceiver is connected to a electronic flight control for directing the flight of the rotary wing aircraft. An accessory frame receives an accessory load to be carried by the rotary wing aircraft. A battery is disposed on the frame for powering the transceiver. A quick change mounting removably mounts the accessory frame to the frame. Preferably, the battery is movable relative to the frame for compensating for different weights of the accessory load secured to the accessory frame to adjust the center of mass for proper flight of the rotary wing aircraft. An integral balance included for adjusting the center of mass assisting of the rotary wing aircraft.
    Type: Grant
    Filed: August 10, 2015
    Date of Patent: October 16, 2018
    Assignee: FPV MANUALS LLC
    Inventor: Tim Nilson
  • Patent number: 10086937
    Abstract: A observation device includes an aircraft and an observation unit attached to the aircraft that observes a target within a predetermined view angle. The aircraft includes a base, at least two thrusters that generate a propulsion force including lift, actuators that change a direction of the propulsion force generated by the thrusters with respect to the base, an inertial measurement unit (IMU) that detects an orientation of the base with respect to a ground surface, and a controller that controls the thrusters and the actuators based on the orientation of the base detected by the IMU. The observation unit is fixedly attached to the base and the aircraft is configured to fly in any arbitrary orientation with respect to the ground surface through a combination of a magnitude of the propulsion force and the direction of the propulsion force of each of the thrusters.
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: October 2, 2018
    Assignees: DENSO CORPORATION, SOKEN, INC., THE UNIVERSITY OF TOKYO
    Inventors: Takenori Matsue, Koji Kawasaki, Michihiro Matsuura, Masami Kurosaka, Masayuki Inaba
  • Patent number: 10087902
    Abstract: A method of operating an electrical system of an aircraft is provided. The method includes initiating a cross-start action for cross-starting a non-operative engine using a generator of an operative engine, entering a power limiting mode of a generator control unit (GCU) of the operative engine, remaining in the power limiting mode for a duration of the cross-start action and returning to the non-power limiting mode of the GCU of the operative engine upon completion of the cross-start action.
    Type: Grant
    Filed: May 11, 2016
    Date of Patent: October 2, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Mark P. Eisenhauer, Frederick L. Bourne, Matthew Fogarty
  • Patent number: 10081432
    Abstract: A structure of drone (100) comprises a frame (110) comprising an engagement portion (110?), said engagement portion (110?) being a strip having a predetermined geometry. The structure of drone (100) also comprises a plurality of propulsion elements (120). Each propulsion element (120) is arranged, in use, to be engaged in a removable way to the engagement portion (110?) at a any point of the strip, in such a way to easily change the number and the arrangement of the propulsion elements (120) present on the engagement portion (110?).
    Type: Grant
    Filed: September 5, 2014
    Date of Patent: September 25, 2018
    Assignee: UNIVERSITA DEGLI STUDI DI FIRENZE
    Inventors: Guglielmo Rossi, Sandro Moretti, Nicola Casagli