Patents Examined by Richard R Green
  • Patent number: 11148828
    Abstract: Embodiments relate to aircraft arresting systems that use a net or a cable that extends across a section of a runway. Ends of the net or cable are secured to an elongated tape, which is secured to and forms a part of an energy absorbing brake system. The elongated tape is secured around a tape reel and is allowed to reel out (or “pay out”) once the aircraft is engaged. Described is a system for adjusting the height of the tape such that its elevation can be altered between the point at which it leaves the energy absorbing brake system and when it reaches the aircraft runway.
    Type: Grant
    Filed: March 1, 2019
    Date of Patent: October 19, 2021
    Assignee: ENGINEERED ARRESTING SYSTEMS CORPORAITON
    Inventor: Christopher Levesque
  • Patent number: 11148816
    Abstract: An adjustable leg restraint for an ejection seat may be configured to translate between an extended state and a nonextended state. The adjustable leg restraint may include a leg located proximate a side panel of the ejection seat. An extension flange may be coupled to the leg guard. The extension flange may be configured to translate the leg guard relative to the side panel of the ejection seat.
    Type: Grant
    Filed: December 12, 2018
    Date of Patent: October 19, 2021
    Assignee: Goodrich Corporation
    Inventors: Matthew D. Salois, Jeff Benjamin
  • Patent number: 11148829
    Abstract: An arresting cable retraction mechanism for use across an aircraft runway. The retraction mechanism functions to extend a cable across a runway (for capture by a tailhook of an aircraft) without causing the cable to recede below the runway surface during an aircraft rollover/deflection event. The arresting cable retraction mechanism is also designed to help prevent damage to a retraction motion actuator due to high speed aircraft rollover. The disclosed system separates components related to retraction vs. deflection due to rollover, such that rollover events do not affect or load the motion actuator used for retraction.
    Type: Grant
    Filed: May 3, 2019
    Date of Patent: October 19, 2021
    Assignee: ENGINEERED ARRESTING SYSTEMS CORPORATION
    Inventors: Kirk F. Schneider, Justin S. Agren, Travis L. Chaney, Christopher J. Levesque, Scott A. Smith, Kenneth J. Neeld, Isaac Arroyo-Marquez, Craig H. Scott
  • Patent number: 11148820
    Abstract: One variation of a system for generating thrust at an aerial vehicle includes: a primary electric motor; a rotor coupled to the motor; an internal-combustion engine; a clutch interposed between the motor and an output shaft of the internal-combustion engine; an engine shroud defining a shroud inlet between the rotor and the internal-combustion engine, extending over the internal-combustion engine, and defining a shroud outlet opposite the rotor; a cooling fan coupled and configured to displace air through the engine shroud; and a local controller configured to receive a rotor speed command specifying a target rotor speed, adjust a throttle setpoint of the internal-combustion engine according to the target rotor speed and a state of charge of a battery in the aerial vehicle, and drive the primary electric motor to selectively output torque to the rotor and to regeneratively brake the rotor according to the target rotor speed.
    Type: Grant
    Filed: December 28, 2020
    Date of Patent: October 19, 2021
    Assignee: Parallel Flight Technologies, Inc.
    Inventors: Joshua Resnick, David Adams, Robert Hulter, Seth McGann, Brian Eiseman
  • Patent number: 11148799
    Abstract: A rotorcraft that utilizes both a main compound rotor and a plurality of tiltrotors is disclosed. The main rotor and the thrusters can provide vertical lift for vertical take-off and landing of the rotorcraft. The thrusters of the rotorcraft can articulate to a horizontal position to facilitate horizontal flight. The main rotor of the rotorcraft can continue to provide vertical lift for the rotorcraft in horizontal flight, as well as operate in an autorotation mode. In the event of a failure of the main power source of the rotorcraft, the main rotor in autorotation mode can safety land the rotorcraft. In the autorotation mode, the main rotor can create electrical energy that is stored in a battery and can be used to power the plurality of thrusters. The rotorcraft can also be configured in an anti-torque mode, where the thrusters cancel out the torque of the main rotor.
    Type: Grant
    Filed: November 26, 2018
    Date of Patent: October 19, 2021
    Assignee: Textron Innovations Inc.
    Inventors: Daniel Robertson, Kirk Groninga, Matthew Louis
  • Patent number: 11148807
    Abstract: A hovering aerial vehicle is provided, comprising an airborne unit and an auxiliary unit. The airborne unit is configured to carry the auxiliary unit during flight and comprises a flight system configured to facilitate providing aerodynamic lift to facilitate hovering of the vehicle. The auxiliary unit comprises an electrical power source in electrical communication with the flight system to provide electrical power for its operation. The hovering aerial vehicle further comprises a decoupling system configured to facilitate selectively switching the vehicle between a detached configuration thereof wherein the airborne and auxiliary units are remote from each other, and an attached configuration thereof wherein the airborne and auxiliary units are secured to one another, and to maintain the electrical communication when the vehicle is in its detached configuration.
    Type: Grant
    Filed: November 2, 2016
    Date of Patent: October 19, 2021
    Assignee: ISRAEL AEROSPACE INDUSTRIES LTD.
    Inventor: Daniel Marom
  • Patent number: 11148806
    Abstract: [Problem] To provide an aerial vehicle wherein the flight efficiency can be improved. [Solution] An aerial vehicle according to the present invention relates in particular to a aerial vehicle having a loading section whereon a payload and the like can be loaded. The aerial vehicle is capable of traveling at least forward and backward, is provided with lift generation sections, arm sections for holding the lift generation sections, a loading section disposed on the arm sections and positioned posterior to the center of gravity of the aerial vehicle, and a maintaining means for maintaining the aerial vehicle at least in the horizontal attitude, and the loading section has a first connection part for maintaining a loaded object at least in the horizontal attitude. On the basis of the above mentioned, the payload can be prevented from entering slipstream regions created by propellers, improving flight efficiency.
    Type: Grant
    Filed: June 4, 2017
    Date of Patent: October 19, 2021
    Assignee: AERONEXT INC.
    Inventor: Yoichi Suzuki
  • Patent number: 11148815
    Abstract: A suspension line assembly for a parachute may comprise a first set of suspension lines bound together to form a first riser, and a second set of suspension lines bound together to form a second riser. A confluence may be formed by the first set of suspension line and the second set of suspension line. The confluence may comprise interior confluence suspension lines and exterior confluence suspension lines that alternate circumferentially along a perimeter of a parachute canopy.
    Type: Grant
    Filed: January 11, 2019
    Date of Patent: October 19, 2021
    Assignee: Goodrich Corporation
    Inventors: Jaro S. Volny, Kassidy L. Carson
  • Patent number: 11142305
    Abstract: An aircraft undercarriage having a leg for mounting to move on an aircraft structure between a deployed position and a retracted position is provided. The undercarriage generally includes a brace member arranged between the structure of the aircraft and the leg in order to stabilize the leg in the deployed position, and a drive actuator for moving the leg from the deployed position to the retracted position. The brace member includes a strut arm having a proximal end that is designed to be hinged on the structure of the aircraft. The arm presents a longitudinal slot extending until the slot reaches a distal end in order to terminate in a bend and having slidably engaged therein a finger that is secured to the leg, the drive actuator being coupled to the strut arm.
    Type: Grant
    Filed: February 1, 2019
    Date of Patent: October 12, 2021
    Assignee: SAFRAN LANDING SYSTEMS
    Inventors: Daniel Moine, Hervé Rolinat
  • Patent number: 11142325
    Abstract: The invention relates to a device (1) for ejecting a parachute, comprising a housing (2) with an ejection opening (3), wherein the housing (2) is suitable for at least partially accommodating the parachute. In order to enable a robust and repeated ejection of the parachute with a low weight of the device (1), according to the invention a movable base (4) is arranged within the housing (2), which base (4) is connected to the housing (2) via at least one spring element, wherein the base (4) can be releasably fixed in place within the housing (2) using a fixing means (5), wherein the device (1) is configured such that if a parachute is arranged within the housing (2), the base (4) is accelerated by the spring element when the fixing means (5) is released, so that the parachute is ejected through the ejection opening (3) by means of the base (4). Furthermore, the invention relates to a method for ejecting a parachute.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: October 12, 2021
    Assignee: DRONE RESCUE SYSTEMS GMBH
    Inventor: Markus Manninger
  • Patent number: 11142312
    Abstract: A truss for a flying vehicle supports a pair of wings in a manner which facilitates pivoting of the wings between a deployed configuration and a retracted configuration. The truss includes parallel top and bottom plates with the gap therebetween. The wings have wing brackets affixed thereto with the wing brackets pivotably supported by hinge assemblies to the top plate and bottom plate of the truss. Latch assemblies can be selectively actuated to secure the wing brackets and associated wings to the truss in either the deployed configuration or the retracted configuration, so that loads between the wings and the truss are primarily carried through the latch assemblies rather than through the hinge assemblies. A hinge position on the truss and on the wing brackets is selected to maximize wing length tip to tip while minimizing an outline required for the vehicle when the wings are fully retracted.
    Type: Grant
    Filed: May 17, 2019
    Date of Patent: October 12, 2021
    Assignee: TUDOR CROSSFELT, LP
    Inventor: Samuel Hall Bousfield
  • Patent number: 11142299
    Abstract: An aircraft wing has a flap arrangement with an inboard flap configured to move in a chordwise extension direction relative to the wing, the inboard flap having an outboard side, and an outboard flap adjacent to the inboard flap and configured to move in the chordwise extension direction relative to the wing, the outboard flap including an inboard side. A flap interconnect between the inboard flap and outboard flap has a roller mounted to a pin extending from the outboard side of the inboard flap and a guide track extending from the inboard side of the outboard flap. The guide track engages the roller on the inboard flap to limit deflection of the outboard flap relative to the inboard flap during movement of the inboard flap in the chordwise extension direction and movement of the outboard flap in the chordwise extension direction, to provide relative alignment of the inboard flap and outboard flap.
    Type: Grant
    Filed: May 31, 2019
    Date of Patent: October 12, 2021
    Assignee: The Boeing Company
    Inventors: Kevin R. Tsai, Kyle A. Johnson
  • Patent number: 11136111
    Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: October 5, 2021
    Assignee: Airbus Operations GmbH
    Inventors: Bernhard Schlipf, Florian Lorenz
  • Patent number: 11136115
    Abstract: An aircraft comprises a fuselage, one or more support structures connected to the fuselage, one or more engines or motors disposed within or attached to the one or more support structures or the fuselage, and a distributed propulsion system. The distributed propulsion system comprising two or more propellers symmetrically distributed in an array along the one or more support structures with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation, and a summation of horizontal force vectors created by the tilted plane of rotation of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust magnitude. Movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.
    Type: Grant
    Filed: June 20, 2018
    Date of Patent: October 5, 2021
    Assignee: TEXTRON INNOVATIONS INC.
    Inventors: Carlos Alexander Fenny, Jouyoung Jason Choi
  • Patent number: 11136122
    Abstract: The disclosure relates to an arrangement comprising a flyable unmanned transporting device and a movable catch arm, which is provided at a ground station, for holding the transporting device at the ground station, wherein at least one recess is provided on the transporting device, and the catch arm, at its end facing away from the ground station, has at least one expansion element which can be introduced into the at least one recess and, in the introduced state, can be expanded in order to produce a form fit between the at least one recess and the at least one expansion element.
    Type: Grant
    Filed: January 21, 2019
    Date of Patent: October 5, 2021
    Assignee: Deutsche Post AG
    Inventors: Felix Vorwerk, Matthäus Pruski, Paul Muller
  • Patent number: 11136128
    Abstract: An aircraft seat kit with one aircraft seat, and an aircraft seat and cabin arrangement with at least two aircraft seats for being mounted one after the other onto a seat rail are described. The seat rail provides a grid with a pre-determined grid pitch for mounting the at least two aircraft seats. Each of the at least two aircraft seats includes: a seating structure, a support for supporting the seating structure, and one of two types of seat rail adapters for mounting the support onto the seat rail. The two types of seat rail adapters differ from each other in that they configure at least one aircraft seat with a different distance in a longitudinal direction between a seat reference point and a reference mounting position, respectively.
    Type: Grant
    Filed: November 7, 2017
    Date of Patent: October 5, 2021
    Inventor: Jörg Weifenbach
  • Patent number: 11130562
    Abstract: Device and method for reducing gust loads acting on control surfaces of an aircraft. Each control surface is movable by at least one actuator, and a flight control system provides reference variables Xsoll and {dot over (X)}soll to actuate the actuator of each control surface. Xsoll indicates a target position, force, or moment of the actuator, and {dot over (X)}soll indicates a time derivative of Xsoll. The device includes: a first sensor system identifying a position, force, or moment, indicated by variable Fext,Boe, as produced by gusts acting from outside on the control surface; and a regulator regulating the actuator of the control surface based on Fext,Boe, Xsoll and {dot over (X)}soll, and XA and {dot over (X)}A, resulting from the actuator acting on the control surface and detected by a second sensor system, wherein regulation of the actuator by the regulator enables compensation of the position, force, or moment produced by gusts acting on the control surface.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: September 28, 2021
    Assignee: Deutsches Zentrum für Luft- und Raumfahrt e.V.
    Inventor: Franciscus van der Linden
  • Patent number: 11124318
    Abstract: Spacecraft servicing devices and related methods may include a propellant tank configured to store a propellant and to be placed into fluid communication with a portion of the target spacecraft.
    Type: Grant
    Filed: July 20, 2018
    Date of Patent: September 21, 2021
    Assignee: Northrop Grumman Systems Corporation
    Inventors: James Garret Nicholson, Thomas Fred Meyer, Daniel Guadagnoli
  • Patent number: 11124293
    Abstract: A bracket manifold for a landing gear assembly is disclosed. In various embodiments, the bracket manifold includes a mounting plate having a central portion and a first wing portion extending from the central portion; and a first manifold section integrated monolithically into at least one of the central portion and the first wing portion of the mounting plate.
    Type: Grant
    Filed: April 23, 2019
    Date of Patent: September 21, 2021
    Assignee: Goodrich Corporation
    Inventors: Bradley William Baird, Hiran S. Mistry
  • Patent number: 11124306
    Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan driven by the power source; and a wing extending from the fuselage. The vertical thrust electric fan is positioned on or within the wing, the wing including a diffusion assembly movable between a first position and a second position and positioned at least partially downstream of the vertical thrust electric fan when in the second position, the diffusion assembly including a first member and a second member, the second member movable generally along the vertical direction relative to the first member such that the first member and second member together define at least in part an exhaust flowpath for the first vertical thrust electric fan when the diffusion assembly is in the second position.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: September 21, 2021
    Assignee: General Electric Company
    Inventors: Kurt David Murrow, Darek Tomasz Zatorski