Patents Examined by Richard G Davis
  • Patent number: 10053211
    Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.
    Type: Grant
    Filed: June 29, 2017
    Date of Patent: August 21, 2018
    Assignee: THE BOEING COMPANY
    Inventors: Terrence S. Birchette, Akif O. Bolukbasi
  • Patent number: 10046859
    Abstract: A bleed air pressure regulation system for an aircraft anti-icing system comprises a first, upstream pressure regulating valve and a second, downstream pressure regulating valve arranged in series in a bleed airflow path. The respective pressure regulating valves each have a regulating pressure chamber in fluid communication with a respective pressure setting valve. Each pressure setting valve is in fluid communication with a bleed air inlet upstream of the first, upstream pressure regulating valve. The first, upstream pressure regulating valve is set to regulate the pressure of the bleed air to a first pressure and the second, downstream pressure regulating valve is set to regulate the pressure of the bleed air to a second pressure which is higher than the first pressure.
    Type: Grant
    Filed: January 14, 2016
    Date of Patent: August 14, 2018
    Assignee: GOODRICH ACTUATION SYSTEMS LIMITED
    Inventor: Tony Jones
  • Patent number: 10039388
    Abstract: A mattress wherein a plurality of independent yarn based fire barrier fabrics encases a plurality of distinct and unattached interior core structures. The plurality of interior core structures include at least a detached and internally flippable upper comfort layer assembly with a plurality of non-homogeneous foams or filling materials encased in a yarn-based fire barrier fabric and a lower, interiorly disposed support core structure with resilient filling materials encased in a yarn-based fire barrier fabric and a fabric cover. The detachable and internally flippable upper comfort layer assembly may be contained in a user accessible compartment that is fashioned into an outer cover assembly.
    Type: Grant
    Filed: May 25, 2017
    Date of Patent: August 7, 2018
    Assignee: KICKBALL CONCEPTS, LLC
    Inventors: Harrison Robert Murphy, Juraj Michal Daniel Slavik, II
  • Patent number: 10035596
    Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: July 31, 2018
    Assignee: Top Flight Technologies, Inc.
    Inventors: Long N. Phan, Sanjay Emani Sarma, Cody Miles Wojcik, Eli M. Davis, Benjamin Arthur Sena, Julian Lemus
  • Patent number: 10035581
    Abstract: A multi-rotor UAV comprises a body and a plurality of rotor arms extending radially from the body. A rotor assembly is connected to an outside end of each rotor arm. An attachment interface is connected to the body and provides rotor arm attachment points for attaching the rotor arms to the body and pivoting the rotor arms from an unfolded operating position, to a folded position wherein the rotor arms are pivoted such that an outer arm portion of each rotor arm is enabled to cross the pivot end and an inner arm portion of an adjacent rotor arm.
    Type: Grant
    Filed: January 12, 2016
    Date of Patent: July 31, 2018
    Assignee: Draganfly Innovations, Inc.
    Inventor: Zenon Dragan
  • Patent number: 10035597
    Abstract: An unmanned aerial system (UAS) including a sonotube deployable multicopter (SDM) having a plurality of rotors for propulsion, a plurality of extension arms, and a central pivot device. Each extension arm supports at least one of the plurality of rotors. The central pivot device supports the plurality of extension arms radially extending from the central pivot device. Pivotal movement of a first arm-support structure of the central pivot device relative to a second arm-support structure of the central pivot device rotates a first pair of the plurality of extension arms in unison relative to a second pair of the plurality of extension arms. The pivotal movement is biased to rotate the plurality of extension arms from a compact configuration to an expanded configuration while the UAS is airborne. The SDM configured to be held inside a sonoshell in the compact configuration.
    Type: Grant
    Filed: August 16, 2016
    Date of Patent: July 31, 2018
    Inventors: Douglas Desrochers, David Desrochers
  • Patent number: 10029789
    Abstract: Systems and methods for controlling an unmanned aerial vehicle within an environment are provided. In one aspect, a system comprises one or more sensors carried by the unmanned aerial vehicle and configured to provide sensor data and one or more processors. The one or more processors can be individually or collectively configured to: determine, based on the sensor data, an environment type for the environment; select a flight mode from a plurality of different flight modes based on the environment type, wherein each of the plurality of different flight mode is associated with a different set of operating rules for the unmanned aerial vehicle; and cause the unmanned aerial vehicle to operate within the environment while conforming to the set of operating rules of the selected flight mode.
    Type: Grant
    Filed: November 1, 2016
    Date of Patent: July 24, 2018
    Assignee: SZ DJI TECHNOLOGY CO., LTD
    Inventors: Ang Liu, Xiao Hu, Guyue Zhou, Xuyang Pan
  • Patent number: 10023301
    Abstract: A system including a load factor control module for calculating a deflection order on manual actuation of a control column by a pilot of the aircraft and transmitting that deflection order to at least one elevator of the aircraft, a longitudinal attitude control module for maintaining the longitudinal attitude of the aircraft at a target attitude in the event of absence of manual actuation of the control column by the pilot during a flight, and a transition management module for determining and storing a present longitudinal attitude value of the aircraft at a recording moment and transmitting that longitudinal attitude value to the longitudinal attitude control module for the longitudinal attitude control module to use the longitudinal attitude value as the target attitude.
    Type: Grant
    Filed: April 12, 2016
    Date of Patent: July 17, 2018
    Assignee: Airbus Operations SAS
    Inventors: Mathieu Carton, Pierre Debusschere, Laurent Albugues
  • Patent number: 10017278
    Abstract: A gyroscopic orbiter with vertical takeoff and vertical landing capabilities can transition between different functional modes while in-flight. The orbiter typically includes a fuselage, a front boom, a front propulsion unit, a rear boom, and a rear propulsion unit. The front boom is mounted at two pivot points to a bow of the fuselage by the front boom. The rear boom is mounted at two pivot points to a stern of the fuselage by the rear boom. One functional mode is the vertical takeoff and landing mode, wherein the propulsion units are oriented parallel to each other and are directed upward. Another functional mode is the shuttle mode, wherein the propulsion units are oriented at an angle with each other, and the front propulsion unit is directed forward. Another functional mode is the high speed mode, wherein the propulsion units are oriented collinear with a roll axis of the fuselage.
    Type: Grant
    Filed: June 16, 2016
    Date of Patent: July 10, 2018
    Inventor: Thomas Norman Hesse
  • Patent number: 10017237
    Abstract: Embodiments described herein relates to an Unmanned Aerial Vehicle (UAV) having vibration dampening and isolation capabilities, the UAV including a first frame portion, a second frame portion, and a third frame portion. Each of the first frame portion, the second frame portion, and the third frame portion is separated from one another. At least one first support member inelastically coupling the first frame portion and the third frame portion. At least one second support member elastically coupling the second frame portion and one or more of the first frame portion or the third frame portion to isolate the first frame portion and the third frame portion from vibration of the second frame portion.
    Type: Grant
    Filed: May 3, 2016
    Date of Patent: July 10, 2018
    Assignee: QUALCOMM Incorporated
    Inventors: Donald Bolden Hutson, Clayton Dumstorff, Jonathan Paul Davis, Paul Stewart Ferrell, Charles Wheeler Sweet, III, Travis Van Schoyck, Ross Eric Kessler, Aleksandr Kushleyev, Daniel Warren Mellinger, III
  • Patent number: 10011349
    Abstract: A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a generally vertical orientation in a vertical takeoff and landing mode and a generally horizontal orientation in a forward flight mode. The rotor assembly includes a proprotor operable to produce a generally vertical slipstream in the vertical takeoff and landing mode and a generally horizontal slipstream in the forward flight mode. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.
    Type: Grant
    Filed: August 31, 2016
    Date of Patent: July 3, 2018
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Steven Ray Ivans, Nathan Gabriel Wu
  • Patent number: 10009518
    Abstract: A detachable aerial photographic apparatus includes a carrier, an aircraft, a take-off delaying device and a trigger. The aircraft includes a main body disposed on the carrier, at least one propeller is pivotally furnished in the main body and a camera disposed on the main body. The take-off delaying device includes a movable member disposed on the carrier and at least one stopper connected to the movable member. The stopper is detachably connected to the aircraft for prevent the aircraft from taking off. The movable member is for detaching the stopper from the aircraft for releasing the aircraft. The trigger is electrically connected to the aircraft and the take-off delaying device. The trigger is for triggering the propeller and the movable member. A first time point when the propeller is triggered by the trigger is earlier than a second time point when the stopper is detached from the aircraft.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: June 26, 2018
    Assignee: INDUSTRIAL TECHNOLOGY RESEARCH INSTITUTE
    Inventors: Wei-Ying Tai, Chan-Ru Chang, Chun-Wen Tang
  • Patent number: 10005547
    Abstract: The invention relates to an aircraft undercarriage comprising: a strut (1) for connecting to the aircraft, a slide rod (3) slidably engaged in leaktight manner in the strut via the bottom opening, which rod carries at least one wheel at its bottom end, a diaphragm (7) carried by a support (8) attached to the top wall of the strut to cooperate in leaktight manner with an inside wall of the slide rod so as to define a first chamber (C1) under the diaphragm inside the rod and completely filled with hydraulic fluid, and a second chamber (C2) above the diaphragm and partially filled with hydraulic fluid, a throttle needle (10) secured to the slide rod and penetrating into a calibrated orifice (12) in the diaphragm so as to define a calibrated fluid passage between the first and second chambers, and angular connection means for imposing an angular position on the slide rod relative to the strut.
    Type: Grant
    Filed: May 11, 2016
    Date of Patent: June 26, 2018
    Assignee: MESSIER-BUGATTI-DOWTY
    Inventors: Jerome Fraval, David Frank
  • Patent number: 10000280
    Abstract: A device for mounting an aircraft tail wheel includes a support plate having, on the one hand, an articulation shaft with an arm and, on the other hand, an articulation shaft with a fork receiving the freely rotating tail wheel, while the articulation shaft of the plate is positioned near a rotation shaft of the tail wheel.
    Type: Grant
    Filed: July 17, 2014
    Date of Patent: June 19, 2018
    Assignee: Beringer Aero
    Inventor: RĂ©mi Beringer
  • Patent number: 10000279
    Abstract: The present disclosure describes systems and methods for retractable landing gear. A landing gear arrangement may comprise: a trailing arm; a shock strut; a link rotatably coupled to a first end of the shock strut and rotatably coupled to the trailing arm, the link including a pivot; a rotatable latch rotatably coupled to the link; and an actuator coupled between the rotatable latch and the trailing arm, the rotatable latch configured to rotate about the pivot, the pivot located between a first end and a second end of the rotatable latch, the rotatable latch configured to rotate in a first direction in response to the actuator extending and configured to rotate in a second direction in response to the actuator compressing.
    Type: Grant
    Filed: January 20, 2016
    Date of Patent: June 19, 2018
    Assignee: Goodrich Corporation
    Inventor: William E. Luce
  • Patent number: 10000282
    Abstract: An aircraft landing gear assembly includes a mechanical structural linkage having a shock absorber and a linkage abutment which are biased apart by a mechanical spring. The force required to deform the spring sufficiently to place the linkage abutment at a predefined distance with respect to the shock absorber abutment is less than the breakout force of the shock absorber.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: June 19, 2018
    Assignee: Safran Landing Systems UK Ltd
    Inventor: Robert Kyle Schmidt
  • Patent number: 10000278
    Abstract: The invention relates to a landing gear (1) of an aircraft (5), comprising: a strut assembly (10) including a first end (10a) designed to be mounted on the aircraft (5) and a second end (10b) opposite the first end (10a); a rod (14) slidably mounted on the second end (10b) of the strut assembly (10), said rod (14) being translationally movable in relation to the strut assembly (10); and at least one obstacle detector (2) secured to the landing gear (1), the landing gear (1) being characterized in that the obstacle detector (2) is secured in a zone adjacent to the second end (10b) of the strut assembly (10).
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: June 19, 2018
    Assignees: SAFRAN ELECTRONICS AND DEFENSE, SAFRAN LANDING SYSTEMS
    Inventors: Carlo Necci, Jacques Lacourie
  • Patent number: 10000283
    Abstract: Elastomeric bearings exhibit a reactive positive spring effect, i.e., they produce an opposing torque or force when angular displacement or translation is applied upon them, due to shear stress developed within their elastomer parts. The present invention incorporates a device that exhibits an increasingly strong torque or force in the same direction as the displacement, i.e., a negative spring, under similar conditions of movement. When properly calibrated, the subject type of device can be used in paralleled motion with the ordinary reactive elastomeric bearing to produce a combined effect in which at least a part of the torque or force of the elastomeric bearing is compensated or minimized over a range of movement, particularly in helicopter rotor blade retention applications.
    Type: Grant
    Filed: January 28, 2016
    Date of Patent: June 19, 2018
    Inventor: William L. Hinks
  • Patent number: 9995355
    Abstract: An exemplary cone brake device includes a brake drum and a thermal sprayed coating deposited and bonded to the outer surface. The thermal sprayed coating is configured to engage a friction lining when one of the brake drum and the friction element is moved toward the other of the brake drum and the friction element, so as to decrease the speed of an aerospace propeller.
    Type: Grant
    Filed: January 8, 2016
    Date of Patent: June 12, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Kyle A. Hassler, Sean Warrenburg, Joseph A. Swift, Kevin Mock, Mark Winely
  • Patent number: 9988154
    Abstract: An apparatus, method for making, and product by process for a parachute, the parachute having a conductive network and a set of fabrics; the conductive network including a set of conductive elements and a set of devices; wherein a first subset of conductive elements of the set of conductive elements is incorporated with a second subset of fabrics of the set of fabrics and third subset of devices of the set of devices incorporated is incorporated with a fourth subset of fabrics of the set of fabrics.
    Type: Grant
    Filed: April 29, 2017
    Date of Patent: June 5, 2018
    Inventor: Joseph John D'Angelo, Jr.