Patents Examined by Rodney Bonnette
  • Patent number: 10713958
    Abstract: A UAV landing system can include a landing pad defining a landing area including a target point; a plurality of positioning radio transmitters positioned in a spaced apart relation and equidistant from the target point, each radio transmitter transmitting a ranging signal; and a position determination and aircraft navigation system at the incoming UAV to receive the ranging signals; determine a range to each positioning radio using the received ranging signals; compute a position of the UAV relative to the target point; determine a course for the UAV to a point above the target point of the landing pad; fly the UAV to the point above the target point of the landing pad, and cause the aircraft to descend vertically toward the target point when the UAV reaches the point above the target point.
    Type: Grant
    Filed: June 13, 2017
    Date of Patent: July 14, 2020
    Assignee: BENCHMARK ELECTRONICS, INC.
    Inventors: Ronald Hobbs, James Luecke
  • Patent number: 10704312
    Abstract: A door alignment system includes a first alignment member secured to one of a first door or a structure connected to the first door, and a second alignment member secured to the other of the first door or the structure. The first alignment member is configured to couple to the second alignment member when the first door is in a closed position relative to the structure in order to prevent the first door from binding in relation to the structure. The first alignment member is configured to be separated from the second alignment member when the first door is in an open position relative to the structure.
    Type: Grant
    Filed: December 4, 2017
    Date of Patent: July 7, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Guarav Kumar, Tesfaye Tsehayneh Ejigu
  • Patent number: 10709030
    Abstract: An electronic unit comprising a box defining a reception compartment for receiving an electronic module along two mutually opposite directions of an insertion axis, the compartment including electrical power supply means for powering the electronic module and connection means for connecting the electronic unit to the electronic module, these means extending onto a connection face forming part of the reception compartment and extending parallel to the insertion axis. An electronic module for mounting in a compartment of an electronic unit of the invention.
    Type: Grant
    Filed: September 28, 2017
    Date of Patent: July 7, 2020
    Assignee: SAFRAN ELECTRONICS & DEFENSE
    Inventors: François Guillot, Jean-Marc Blineau, Philippe Avignon, Serge Roques, Franck Albero
  • Patent number: 10703465
    Abstract: A mounting system for a vibration isolation device comprises a support structure having an opening disposed therein, the opening having a concave recess; a thin elastomeric component attached to a surface of the concave recess; and a spherical elastomeric bearing disposed in the opening and attached to the thin elastomeric component, the spherical elastomeric bearing having a beveled upper portion, a middle portion and a beveled lower portion configured to engage the vibration isolation devices.
    Type: Grant
    Filed: March 30, 2018
    Date of Patent: July 7, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Michael Smith, Maurice Griffin
  • Patent number: 10689090
    Abstract: An aircraft includes a clearance between an opening and a door. The clearance communicates with a cavity and is oriented in a direction intersecting a flow direction of an air flow to the outside of the aircraft in flight. The aircraft further includes an upstream edge and an upstream outer surface situated in front of the clearance joined by a sharp edge with a bend radius of less than or equal to 1 mm, in order to limit the incidence of aerodynamic noise.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: June 23, 2020
    Assignee: Airbus Operations S.A.S.
    Inventor: David Perez
  • Patent number: 10690058
    Abstract: A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft. The fire seal structure includes: a first seal compressed and elastically deformed between two members of the aircraft; and a second seal pressed against the first seal in a direction intersecting a compression direction in which the first seal is compressed. A wall of the first seal pressed by the second seal includes a bent groove including at least one bent part.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: June 23, 2020
    Assignee: Mitsubishi Aircraft Corporation
    Inventor: Akira Takeuchi
  • Patent number: 10689134
    Abstract: Disclosed is a device for controlled separation of a first so-called stationary part and a second so-called mobile part, the stationary part having a stationary connecting surface opposite a mobile connecting surface of the mobile part, the stationary part having a different thermal expansion coefficient from that of the mobile part, the separation device including: at least one connecting agent arranged in a layer between the stationary connecting surface and the mobile connecting surface, at least one device for heating at least one of the stationary part and the mobile part, and at least one system for controlling the heating device.
    Type: Grant
    Filed: September 19, 2016
    Date of Patent: June 23, 2020
    Assignee: AIRBUS DEFENCE AND SPACE SAS
    Inventors: Robert Oldham, Philippe Mayo, Franck Levallois, Christophe Figus, Daniel Logut
  • Patent number: 10683097
    Abstract: An aircraft strut includes a primary structure which includes: a top stringer, a bottom stringer, at least one transverse frame which links the top stringer to the bottom stringer, a front end wall which links a front end of the top stringer to a front end of the bottom stringer, a rear end wall which links a rear end of the top stringer to a rear end of the bottom stringer, two lateral frames arranged on either side of the transverse frame, each lateral frame having a lattice form. An aircraft includes at least one strut described herein.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: June 16, 2020
    Assignee: Airbus Operations S.A.S.
    Inventors: Eric Bouchet, Mélaine Chaix
  • Patent number: 10676173
    Abstract: An aircraft (102) having a wing assembly (101) including a fixed wing (105) with a wing tip device (103). The wing tip device (103) is moveable between: a flight configuration; and a ground configuration. The outer end of the fixed wing (105) terminates at an outer rib (115), and the inner end of the wing tip device (103) terminates at an inner rib (117). The outer and inner ribs (115, 117) are located on opposing sides of an interface between the fixed wing (105) and the wing tip device (103). The fixed wing-skin (119) terminates inwardly of the interface, but the outer rib (115) has a surface-forming portion (127) forming an extension of the fixed wing-skin towards the interface. The wing tip device-skin (121) terminates outwardly of the interface, but the inner rib has a surface-forming portion (129) forming an extension of the wing tip device-skin towards the interface.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: June 9, 2020
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Robert Ian Thompson, Sylvain Boye, Benjamin Bishop
  • Patent number: 10676379
    Abstract: Systems and methods for extending life of an apparatus, such as a balloon, using electrolysis. A ballast liquid is carried or harvested and, when desired, is electrolyzed using an on-board electrolyzer to generate lift gas, rather than simply being dumped as traditional ballast. However, the ballast liquid may also be dumped, if necessary. A valve may be provided to enable safe dumping of the ballast liquid. The ballast liquid may be water, a water-methanol mixture, or other suitable ballast liquid. The ballast liquid may be stored in a container associated with the balloon prior to launch or may be harvested from the atmosphere while the balloon is in-flight. Features may be provided to maintain the ballast liquid in a liquid state. The lift gas mixture within the balloon is maintained non-flammable.
    Type: Grant
    Filed: June 14, 2017
    Date of Patent: June 9, 2020
    Assignee: Loon LLC
    Inventors: Sergey Vichik, Daniel Bowen, Sherri Goldman, Richard Chad Bruns, Daniel Alex Luebke
  • Patent number: 10676199
    Abstract: A hybrid-electric propulsion system for an aircraft includes a propulsor and a turbomachine. The turbomachine includes a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool. The hybrid electric propulsion system further includes an electrical system including a first electric machine, a second electric machine, and an electric energy storage unit electrically connectable to the first and second electric machines. The first electric machine is coupled to the high pressure spool of the turbomachine and the second electric machine is coupled to the propulsor for driving the propulsor to provide a propulsive benefit for the aircraft. The hybrid electric propulsion system also includes a controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: June 9, 2020
    Assignee: General Electric Company
    Inventors: Robert Charles Hon, Michael Thomas Gansler
  • Patent number: 10669006
    Abstract: An aircraft (102) including a wing (101), having a fixed wing (105) with a wing tip device (103) moveably mounted at the outer end thereof. The wing tip device (103) is moveable between: a flight configuration; and a ground configuration. The wing tip device (103) and the fixed wing (105) are separated along an oblique primary cut plane (113). The wing tip device (103) and the fixed wing (105) meet along an interfacing cut line (135). The interfacing cut line (135) comprises a first length (137) offset from the primary cut plane (113) in a first direction; a second length (141) offset from the primary cut plane (113) in a second direction, opposite to the first direction; and a transition section (139) over which the interfacing cut line (135) transitions from the first length to the second length.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: June 2, 2020
    Assignee: Airbus Operations Limited
    Inventor: Benjamin Bishop
  • Patent number: 10672208
    Abstract: A stowage bin assembly includes a latch that is configured to selectively lock and unlock the stowage bin assembly, and a sensor in communication with the latch. The sensor is configured to be engaged to lock, unlock, open, and/or close the stowage bin assembly without the latch or the sensor being touched.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: June 2, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Richard K. Simms, Stephen G. Dame, Mark L. Cloud, Todd D. Smith
  • Patent number: 10653900
    Abstract: Disclosed is a lifesaving system using a drone and a lifesaving method using the lifesaving system. The lifesaving system includes: a lifesaving drone provided with a parachute, the drone approaching a victim by being remotely controlled and installed in the victim, and assisting rescuing the victim from a high-rise building by operating the parachute; and a disaster management center disposing a rescuing vehicle to a disaster occurrence area and remotely controlling the lifesaving drone when a disaster report is received, or a disaster occurrence area is recognized.
    Type: Grant
    Filed: November 13, 2017
    Date of Patent: May 19, 2020
    Assignee: EDUN-ENG CO., LTD.
    Inventors: Hyeong Ho Kim, Chul Choi
  • Patent number: 10654580
    Abstract: The present invention includes a rotorcraft drive system, method, and aircraft comprising a fixed engine; a rotating spindle that rotates a proprotor gearbox and rotor pylon between a hover and forward flight position, wherein the rotating spindle rotates about a rotation bearings on two inboard ribs of a wing member; and an interconnect drive shaft connected to the fixed engine, wherein the interconnect drive shaft passes through an aft cove of the wing member and connects to the engine via a forward-aft drive shaft, wherein the forward-aft drive shaft is connected to the proprotor gearbox to provide power to a proprotor.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: May 19, 2020
    Assignee: BELL HELIPCOPTER TEXTRON INC.
    Inventors: Brent Chadwick Ross, Daniel B. Robertson
  • Patent number: 10648408
    Abstract: A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft. The fire seal structure includes: a plurality of walls including: a first wall provided on a first partitioning member; and a second wall provided on a second partitioning member. One of the plurality of walls is a spring wall that functions as a spring. The first and the second partitioning members define the fire-prevention region. The plurality of walls forms a labyrinth-shaped gap between the first and the second partitioning members. Each of the plurality of walls contains a refractory material and includes a front end part. When the first and the second partitioning members are stationary with respect to each other, the front end part is not in contact with another member, and the spring wall is disposed closest to a facing member, among the plurality of walls.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: May 12, 2020
    Assignee: Mitsubishi Aircraft Corporation
    Inventor: Akira Takeuchi
  • Patent number: 10647429
    Abstract: A stowage bin assembly is within an interior cabin of a vehicle. The stowage bin assembly includes a weight sensor that is configured to detect the weight of the stowage bin assembly, and a stowage bin control unit in communication with the weight sensor. The stowage bin control unit is configured to automatically close the stowage bin assembly in response to a weight of the stowage bin assembly being within a predetermined range of a maximum weight threshold.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: May 12, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Richard K. Simms, Stephen G. Dame, Mark L. Cloud, Todd D. Smith
  • Patent number: 10647221
    Abstract: A set includes seats, each seat includes a chair and a lateral pedestal arranged laterally on one side of the chair. The chairs and the lateral pedestals are arranged in a staggered configuration in two parallel rows. Each seat has a covering shell determining a rear surface in a rear zone of the chair and determining a front surface in a front zone of the lateral pedestal. A space between a rear surface of a front seat and a front surface of a rear seat forms a passage for an occupant of the rear seat. In a vertical cross section the rear surface and the front surface have convex profiles facing one another, a width of the passage increasing in the direction of decreasing heights from a height of minimum width, and increasing in the direction of increasing heights from the height of minimum width.
    Type: Grant
    Filed: March 29, 2017
    Date of Patent: May 12, 2020
    Assignee: STELIA AEROSPACE
    Inventor: Benoît Trillaud
  • Patent number: 10633079
    Abstract: An aircraft wing system and method comprising: an aircraft wing including upper and lower surfaces, and a leading edge between the upper and lower surfaces; a fairing coupled to the leading edge; and actuation means configured to move the fairing relative to the aircraft wing between a stowed position, a first deployed position, and a second deployed position. The stowed position is when the fairing is in contact with the aircraft wing and serves as a continuation of the aircraft wing. The first deployed position is when the fairing is in contact with the aircraft wing and located below the stowed position. The second deployed position is when the fairing is spaced apart from the leading edge to create a gap between the fairing and the leading edge.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: April 28, 2020
    Assignee: BAE Systems plc
    Inventor: Robert Brown
  • Patent number: 10633076
    Abstract: A method of rotatably couple a wing tip device (4) to a fixed wing (3) by a rotational joint (101) having an outer race (8) and an inner race (9) that is received in the outer race (8) one of the inner and outer races comprises a male member (76) and the other is a two-part assembly comprising a first part (9a) and a second part (9b) that together form a female member (72), the method brings the first and second parts together to form the female member (72) about the male member (76) such that the male member (76) is received in the female member (72) and fixing the first and second parts (9a, 9b) such that the race that is rotationally fixed relative to the wing tip device (4) is axially and radially retained relative to the race that is rotationally fixed relative to the fixed wing (3).
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: April 28, 2020
    Assignee: Airbus Operations Limited
    Inventor: Benjamin Bishop