Patents Examined by Nicholas McFall
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Patent number: 11964766Abstract: Trailing edge assemblies, couplers and methods for deploying a trailing edge flap of an aircraft wing are disclosed. An exemplary method disclosed herein comprises guiding an aft portion of the trailing edge flap along an elongated track member as the trailing edge flap moves toward the deployed position; guiding a forward portion of the trailing edge flap along the elongated track member as the trailing edge flap moves toward the deployed position; and accommodating transverse movement of the forward portion of the trailing edge flap relative to the elongated track member.Type: GrantFiled: February 25, 2022Date of Patent: April 23, 2024Assignee: BOMBARDIER INC.Inventors: Dmitry Budnitsky, Howard Ian Smith, Thomas Hanson
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Patent number: 11958633Abstract: The present technology relates to an artificial satellite and a control method thereof that enable to ensure quality of a captured image while suppressing battery consumption. An artificial satellite includes: an imaging device configured to perform imaging of a predetermined region on the ground; and a management unit configured to change accuracy of attitude control in accordance with a remaining battery amount at an instructed imaging time, and configured to change an imaging condition in accordance with accuracy of the attitude control. The present technology can be applied to, for example, an artificial satellite or the like that performs satellite remote sensing by formation flight.Type: GrantFiled: May 29, 2020Date of Patent: April 16, 2024Assignee: SONY GROUP CORPORATIONInventors: Satoshi Ezawa, Itaru Shimizu, Naomi Kurahara, Kazuo Ishigame, Tetsu Ogawa
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Patent number: 11958599Abstract: The invention relates to a supporting structure (46) which is positioned in a fluid flow (44) and characterised in that it is configured to be elastically deformed, on at least one portion of the supporting structure (46), between a first idle state in the absence of external stress and a second deformed state in the presence of external stresses caused by the fluid flow (44) due to a change in the orientation of the supporting structure (46) and/or the fluid flow (44). The invention also relates to an aircraft comprising at least one such supporting structure (46).Type: GrantFiled: February 3, 2020Date of Patent: April 16, 2024Inventor: Guilhem Colombiès
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Patent number: 11958629Abstract: Described herein is an elevated unmanned aerial vehicle (UAV) station. The elevated UAV station includes an elevated platform and a conveyance device configured to raise a payload to the elevated platform. The elevated unmanned UAV station may further include a launch device configured to cause a takeoff of a UAV from the elevated platform. The elevated UAV station may further include a recovery device configured to cause a controlled landing of the UAV at the elevated platform. The elevated UAV station may be associated with a payload housing structure to establish a system for payload storage and launch.Type: GrantFiled: July 29, 2021Date of Patent: April 16, 2024Assignee: Zipline International Inc.Inventors: Tyler P. McNish, Stefan C. Aprodu, Keenan A. Wyrobek, William Hetzler, Bijal Mehta, Ryan Alam
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Patent number: 11945577Abstract: Aerial vehicles may be selectively transitioned between a fixed wing flight configuration and a vertical takeoff and landing (VTOL) configuration. In the fixed wing flight configuration, a forward propeller may rotate in a first forward plane, whereas in the VTOL configuration, the forward propeller may be tilted to rotate in a second forward plane. A forward landing arm may extend downward in the VTOL configuration and be configured to be tilted to a stowed position when the aerial vehicle is in the fixed wing flight configuration. The forward landing arm may be coupled to the forward propeller such that tilting of the forward propeller causes corresponding tilting of the forward landing arm. In some examples, a plurality of such landing arms and propellers are tilted during transitioning of the aerial vehicle, such as one or more forward propellers and landing arms and/or one or more aft propellers and landing arms.Type: GrantFiled: May 19, 2022Date of Patent: April 2, 2024Assignee: INSITU, INC., a subsidiary of THE BOEING COMPANYInventor: Ovidiu Cristian Mihai
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Patent number: 11945578Abstract: Apparatus and methods for limiting trailing edge deflection in aircraft folding wing tips are disclosed herein. An example aircraft wing disclosed herein includes a fixed wing portion. The fixed wing portion includes an outboard rib. The aircraft wing also includes a wing tip moveably coupled to the fixed wing portion. The wing tip is moveable between an extended position and a folded position. The wing tip includes an inboard rib that is disposed in a trailing edge section of the wing tip. The wing tip includes a stop plate coupled to the inboard rib. The stop plate extends inboard from the inboard rib such that when the wing tip is in the extended position, the stop plate is disposed below a portion of the outboard rib of the fixed wing portion to limit upward deflection of the trailing edge section of the wing tip relative to the fixed wing portion.Type: GrantFiled: October 18, 2021Date of Patent: April 2, 2024Assignee: The Boeing CompanyInventors: Jeffrey Michael Olds, Eric George Gruner, Billy P. Tung, Eric Dwight Blohm
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Patent number: 11939067Abstract: Briefly, the disclosure relates to apparatuses and methods to enclose electrical contacts for de-icing equipment utilized on fixed-wing aircraft and rotary-wing aircraft, such as helicopters and tiltrotor aircraft. In some implementations, enclosing electrical contacts for a de-ice heater blanket may ensure that high-quality electrical connections are made between conductors of one or more de-icing cables and the electrical contacts of the de-ice heater blanket. Such high-quality electrical connections may be maintained even during aircraft operations conducted in below-freezing ambient environments, rainy and/or wet environments, dusty desert environments, and so forth.Type: GrantFiled: August 29, 2022Date of Patent: March 26, 2024Assignee: TEXTRON INNOVATIONS INC.Inventor: Nicholas Allen Torske
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Patent number: 11939068Abstract: In a hybrid flight vehicle, having multiple rotors attached to a frame, a gas turbine engine to drive the rotors; a generator connected to the gas engine to generate electric power, a battery store the electrical power generated by the generator. multiple first electric motors connected to the rotors to drive the same by the electric power supplied from the battery, a second electric motor connected to the gas turbine engine to motor the engine by the electric power supplied from the battery and a control unit to control flight, wherein the control unit stops supply of the fuel to the engine when a detected residual of the battery is equal to or greater than a predetermined value, and supplies electric power to the second electric motor to motor the engine when a detected temperature of the engine is equal to or higher than a predetermined temperature.Type: GrantFiled: October 22, 2019Date of Patent: March 26, 2024Assignee: Honda Motor Co., Ltd.Inventor: Keisuke Kawai
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Patent number: 11932428Abstract: A projectile-launched aircraft system includes a projectile launcher including a triggering mechanism, a rotary-wing, hover-capable aircraft including a rotor assembly that includes at least one rotor blade, wherein the rotor blade includes a stowed configuration and a deployed configuration that is circumferentially spaced from the stowed configuration about a pivot axis, wherein, upon actuation of the triggering mechanism, the projectile launcher is configured to launch the aircraft along a flightpath.Type: GrantFiled: May 22, 2020Date of Patent: March 19, 2024Assignee: The Texas A&M University SystemInventors: Moble Benedict, Hunter J. Denton, Hao Kang, Vikram Hrishikeshavan
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Patent number: 11919650Abstract: A multi-modal aircraft recovery system is disclosed. In various embodiments, the system includes a first aircraft recovery parachute having a first set of physical attributes optimized for a first set of conditions and a second aircraft recovery parachute having a second set of physical attributes optimized for a second set of conditions different from the first.Type: GrantFiled: August 3, 2022Date of Patent: March 5, 2024Assignee: Kitty Hawk CorporationInventors: Cameron Robertson, Joseph Roop, Todd Reichert, Damon Vander Lind
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Patent number: 11919619Abstract: An aircraft-floor element comprising a first cladding element configure to be swung from a first position to a second position. In the first position, the first cladding element is arranged parallel to a main plane of the aircraft-floor element and on a side of the aircraft-floor element which is directed towards a passenger cabin. In the second position, the first cladding is arranged at an angle to the main plane of the aircraft-floor element, wherein it forms a cladding for a cargo space. An aircraft zone having an aircraft-floor element and an aircraft having such an aircraft zone are also disclosed.Type: GrantFiled: July 12, 2019Date of Patent: March 5, 2024Assignee: AIRBUS OPERATIONS GMBHInventor: Claus-Peter Gross
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Patent number: 11919625Abstract: An aircraft landing gear assembly is disclosed including a landing gear bracket, a fore lever receiving a fore aircraft wheel, an aft lever receiving a rear aircraft wheel, the fore and aft levers being independently moveable, wherein the bracket further comprises a fore lever stop to prevent downwards movement of the fore lever past a lowest rotational position with respect to the bracket at a first angle ?1 forward from the notional bracket axis, and a rear lever stop to prevent downwards movement of the rear lever past a lowest rotational position at a second angle ?2 behind from the notional bracket axis, wherein the first angle is greater than the second angle. An aircraft and a method of landing an aircraft are also disclosed.Type: GrantFiled: February 17, 2021Date of Patent: March 5, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventor: Robert Ian Thompson
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Patent number: 11912404Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.Type: GrantFiled: February 19, 2019Date of Patent: February 27, 2024Assignee: DELOREAN AEROSPACE, LLCInventor: Paul J. DeLorean
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Patent number: 11905011Abstract: An air mobility may include a wing portion extending from a fuselage of the air mobility; a folded portion provided at an edge portion of the wing portion, configured to extend from the wing portion to form a part of the wing portion during unfolding of the folded portion, and configured to move to overlap with the wing portion during folding of the folded portion, so that an area of air resistance in a vertical direction of the wing portion is reduced; an actuator connected to the folded portion and configured to provide power to the folded portion, so that the folded portion is unfolded or folded to the wing portion; and a controller connected to the actuator and configured to control the actuator, so that the folded portion is folded during vertical takeoff or landing of the fuselage, and configured to control the actuator to unfold the folded portion during cruising of the fuselage.Type: GrantFiled: July 17, 2021Date of Patent: February 20, 2024Assignees: Hyundai Motor Company, Kia CorporationInventors: Sang Hyun Jung, Kyu Hoon Cho, Chung Sik Yim, Jae Young Choi
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Patent number: 11897611Abstract: Distributed trailing edge actuation systems and methods for aircraft are described herein. An example aircraft includes a wing, a flap coupled to the wing, the flap movable between a stowed position and a deployed position, and a distributed trailing edge (DTE) actuation system including a flap actuator coupled to the wing to move the flap. The flap actuator includes an integrated hydraulic powered actuator and electric powered actuator. The flap actuator is operable in a hydraulic powered mode in which the hydraulic powered actuator is activated to move the flap, an electric powered mode in which the electric powered actuator is activated to move the flap, and a hybrid mode in which the hydraulic powered actuator and the electric powered actuator are activated simultaneously to move the flap.Type: GrantFiled: August 20, 2021Date of Patent: February 13, 2024Assignee: The Boeing CompanyInventor: Neal V. Huynh
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Patent number: 11897622Abstract: A propeller propulsion unit, comprising at least one kinematic system comprising at least: a heat engine, an electrical energy generator, an electric motor configured to generate a rotary movement as output from the electrical energy generated by the electrical energy generator, a drive and selection device configured to assume a first configuration, in which it is coupled to the output of the electric motor, and a second configuration, in which it is coupled to the main shaft of the heat engine, and a propeller rotated by the drive and selection device. Such a propeller propulsion unit with a hybrid engine allows more power to be provided and facilitates maintenance and ergonomics and is safer.Type: GrantFiled: March 28, 2019Date of Patent: February 13, 2024Assignee: AIRBUS OPERATIONS SASInventors: Patrick Lieven, Jérôme Colmagro
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Patent number: 11891161Abstract: An aircraft includes a fuselage that provides an aircraft passenger cell and a plastically deformable protective body secured on the fuselage. The plastically deformable protective body can be secured on the bottom of the fuselage and/or laterally on the fuselage. The plastically deformable protective body can be secured releasably on the fuselage, for example, via a screw connection.Type: GrantFiled: December 13, 2021Date of Patent: February 6, 2024Assignee: DR. ING. H.C. F. PORSCHE AKTIENGESELLSCHAFTInventor: Stephan Andreas Huebner
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Patent number: 11891187Abstract: An aircraft is described comprising: a support element; a shaft rotating about an axis; a pair of oblique rolling bearings mounted so as to couple the shaft to the support element rotatingly about the axis; the rolling bearings comprising: respective first races cooperating radially in contact with a first component defined by one from the support element and the shaft; respective second races cooperating radially in contact with a second component defined by the other from the support element and the shaft; and respective pluralities of rolling elements adapted to roll on the first and second races; the aircraft further comprises a pair of preloaded elastic members, which couple the first races to the first component respectively, axially and in an elastically yielding manner.Type: GrantFiled: November 28, 2019Date of Patent: February 6, 2024Assignee: LEONARDO S.P.A.Inventors: Daniele Podda, Andrea Gabrielli, Roberto Regonini, Federico Montagna, Stefano Poggi
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Patent number: 11884427Abstract: Stud-propelling mechanisms for securing a launch vehicle to a landing platform, and associated systems and methods, are disclosed. A representative system includes a fastening mechanism carried by a landing support element of a portion of a launch vehicle, the mechanism configured to fasten the landing support element to the landing surface when the launch vehicle portion is on the landing surface. The fastening mechanism can include a barrel structure for propelling a stud and an interference portion positioned to receive the stud upon activation of an energetic material that propels the stud. The stud can bind in the interference portion and in the landing surface to fasten the landing support element to the landing surface. A representative method includes automatically fastening a portion of a launch vehicle to a landing surface using a stud carried by the portion of the launch vehicle.Type: GrantFiled: July 7, 2021Date of Patent: January 30, 2024Assignee: Blue Origin LLCInventors: Brian Riordan, Shane Draney, Rory Arp, Robert E. McMullen
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Patent number: 11885601Abstract: A missile comprises a generally cylindrical body having a distal end and a proximal end; a nosecone having a pointed distal end and a proximal end, wherein the proximal ends of the body and nosecone are oriented toward each other; a forward angled section rotatably attached to the proximal end of the nosecone at its forward edge, the opposite end of the forward angled section having an angled edge perpendicular to the longitudinal axis except for the angle defined by the edge; a rear angled section rotatably attached to the proximal end of the body at its rear edge, the opposite end of the forward angled section having an angled edge matching the angled edge of the forward angled section, the angled edges of the forward angled section and the rear angled section being rotatably attached.Type: GrantFiled: July 13, 2021Date of Patent: January 30, 2024Assignee: United States of America as represented by the Secretary of the Air ForceInventors: Christopher Hoppe, Andrew Ehler, Matthew Snyder