Patents Examined by Philip J Bonzell
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Patent number: 11548637Abstract: An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.Type: GrantFiled: April 24, 2019Date of Patent: January 10, 2023Inventor: Thomas W. Melcher
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Patent number: 11542002Abstract: Systems and methods for an unmanned aerial vehicle (UAV) and control are provided. A UAV may include a swashplateless and hinged propulsion system, and a rotating payload system including an ISR device, a wind sensor, explosive charge and an atmospherics and/or CBRN sensor. A UAV flight controller may include a motion, compass, visual and gyroscopic (MCVG) or other gravitational forces sensor, a communications module configured to communicate with a UAV, and a flight module. The flight module may be configured to receive flight data from the UAV and generate flight control instructions based at least on the flight data and data received from the MCVG sensor. The flight control instructions may be operable to pilot the UAV based on movement of the UAV flight controller in 3D space.Type: GrantFiled: November 30, 2021Date of Patent: January 3, 2023Assignee: KNIGHTWERX INC.Inventors: Daniel Baumgartner, Henry Won
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Patent number: 11542031Abstract: Embodiments of the present invention provide a fuel tank communication system. The communication system includes a main body (30) used to connect two fuel bladder flanges (12, 20) to one another. The communication system provides two separate, independent locking features (42, 60) that can secure fuel bladders to one another.Type: GrantFiled: July 11, 2018Date of Patent: January 3, 2023Assignee: SAFRAN AEROSYSTEMSInventors: Philippe Bulard, Christophe Mendes, Loïc Boissy, Hichem Amara
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Patent number: 11530026Abstract: The present disclosure provides a structural member for a vehicle. The structural member comprises a plurality of finned spar members interlocked with one another, wherein each of the finned spar members include a main body, a plurality of web members extending from a flange, a circuit board formed on the main body, and a bus bar formed on the main body, wherein a compartment is formed between adjacent web members, each compartment being sized to receive a battery.Type: GrantFiled: June 11, 2019Date of Patent: December 20, 2022Assignee: THE BOEING COMPANYInventor: Roger D. Bernhardt
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Patent number: 11524766Abstract: An unmanned rotorcraft includes an airframe, rotor blades that are coupled to the airframe for rotation therewith, a propulsion unit having a propeller, and an actuator that is coupled to the airframe and adapted to temporarily reorient the propulsion unit such that an axis of the propeller moves out of alignment with an axis of the rotor blades. Rotation of the propeller causes counter-rotation of the airframe and rotor blades. The rotor blades and blades of the propeller are adapted to deploy from collapsed positions when flight of the rotorcraft is initiated. A method of operation by the rotorcraft includes, when it is determined that a current heading does not correspond to a determined flight path, causing the actuator to temporarily reorient the propulsion unit in accordance with an angular orientation of the actuator relative to the current heading.Type: GrantFiled: June 1, 2020Date of Patent: December 13, 2022Assignee: Textron Innovations Inc.Inventor: Kip Gregory Campbell
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Patent number: 11527387Abstract: A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.Type: GrantFiled: January 31, 2021Date of Patent: December 13, 2022Assignee: MOMENTUS SPACE LLCInventors: Jason Hummelt, Joel Sercel, Philip Mainwaring, James Small, Matthew Parman
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Patent number: 11524798Abstract: A ducted fan unmanned aerial vehicle (UAV) docking station is provided. The docking station comprises: a guide sized to receive a ducted fan UAV; and a housing communicatively coupled to the guide. The housing comprises: a storage assembly comprising: at least one compartment sized to store the UAV; and at least one dampening system coupled to the at least one storage compartment for cushioning the UAV.Type: GrantFiled: August 29, 2017Date of Patent: December 13, 2022Inventor: Armin Strobel
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Patent number: 11524771Abstract: The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion.Type: GrantFiled: May 10, 2019Date of Patent: December 13, 2022Assignee: AIRBUS OPERATIONS LIMITEDInventor: Arnaud Didey
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Patent number: 11518503Abstract: A hydroelastic damper comprising at least a first resilient assembly that is provided with a first inner strength member engaged at least in part in a first outer strength member, a first resilient member providing resilient return for the first outer strength member and the first inner strength member towards a rest position (POSREP). The hydroelastic damper comprises at least one hydraulic assembly provided with a first hydraulic chamber and a second hydraulic chamber in communication with each other via a connection provided in a first wall of the hydraulic assembly. A first floating piston is movable at least in translation along the longitudinal axis relative to the first inner strength member and to the first outer strength member, the first hydraulic chamber being defined at least by the first floating piston and the first wall in order to protect the first resilient member.Type: GrantFiled: May 29, 2019Date of Patent: December 6, 2022Assignee: AIRBUS HELICOPTERSInventors: Jean-Romain Bihel, Damien Sequera, Jean-Pierre Jalaguier
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Patent number: 11518499Abstract: An aircraft defines a longitudinal direction and includes a fuselage extending between a forward end and an aft end along the longitudinal direction of the aircraft. An aft engine is mounted to the aft end of the fuselage. The aft engine further includes a nacelle including a forward section. An airflow duct extends at least partially through the nacelle of the aft engine and defines an outlet on the forward section of the nacelle for providing an airflow to the forward section of the nacelle.Type: GrantFiled: August 7, 2020Date of Patent: December 6, 2022Assignee: General Electric CompanyInventors: Kishore Ramakrishnan, Trevor Howard Wood
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Patent number: 11511869Abstract: A parachute system includes a payload support configured to operably support a payload below a parachute and an azimuth control device mounted to the payload support and/or the payload. The azimuth control device is configured to operably impart a yaw rotation to the payload in order to adjust an azimuth of the payload. The azimuth control device may include a thrust producing fluid jet device, a thrust producing propeller device, and/or a manipulatable control surface, among others.Type: GrantFiled: December 15, 2021Date of Patent: November 29, 2022Inventor: Roy L. Fox, Jr.
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Patent number: 11505314Abstract: The present disclosure relates to a vertical takeoff and landing (VTOL) aircraft (100) and a propulsion system (600) thereof. The propulsion system (600) comprises a primary rotor (108) configured to couple to an airframe (102) and oriented to generate a vertical thrust relative to the airframe (102), a drivetrain (626) operably coupled to an engine (602) and configured to mechanically drive the primary rotor (108), and a plurality of tiltable secondary rotor assemblies (114) configured to be disposed about the primary rotor (108). The primary rotor (108) comprises a plurality of collective-only variable-pitch blades. Each of the plurality of tiltable secondary rotor assemblies (114) may have a secondary rotor (116) and an electric motor (608) to drive the secondary rotor (116). An electric generator (606) operably coupled to the engine (602) or to the drivetrain (626) may be configured generate electric power for each electric motor (608) of the plurality of tiltable secondary rotor assemblies (114).Type: GrantFiled: July 22, 2019Date of Patent: November 22, 2022Assignee: Aurora Flight Sciences CorporationInventor: Tony Shuo Tao
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Patent number: 11509259Abstract: A plate folding and unfolding device and a solar panel structure are provided. The plate folding and unfolding device includes a cam fixed with first plate piece, and a rotating shaft is disposed inside the cam in an axial direction of the cam; a connecting rod, where the connecting rod includes a first end and a second end that are opposite to each other, the first end is connected vertically to the rotating shaft, and the second end is fixed to a second plate piece; a positioning shaft, where the positioning shaft is disposed, on the connecting rod; and an elastic piece, where the elastic piece is disposed on the connecting rod, one end of the elastic piece is connected to the positioning shaft, where a groove that accommodates the positioning shaft is disposed at at least one location of the outer peripheral surface of the cam.Type: GrantFiled: April 29, 2019Date of Patent: November 22, 2022Assignee: SHENZHEN KUANG-CHI SPACE TECH. CO., LTD.Inventors: Ruopeng Liu, Lin Luan, Junjie Liao
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Patent number: 11498670Abstract: A gearbox system includes a first drive gear rotatable about an axis of rotation and a second drive gear disposed coaxial with the first drive gear and rotatable about the axis of rotation. An input shaft provides a first torque and includes an input gear. Driving pinions are operably connected to the input gear and positioned between the first drive gear and the second drive gear compliantly along a direction parallel to the axis of rotation. Each driving pinion drives the first drive gear in a first direction about the axis of rotation and drives the second drive gear in a second direction opposite the first direction about the axis of rotation. Each driving pinion transfers an equal second torque to the first drive gear and the second drive gear.Type: GrantFiled: August 2, 2016Date of Patent: November 15, 2022Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Thomas L. Sbabo, David A. Darrow, Jr.
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Patent number: 11498683Abstract: The invention provides a kit of parts for assembling an aircraft seat unit, comprising a frame with a slot, a panel for forming a shell of the aircraft seat unit and defining a footprint of the aircraft seat unit, having a first end and a second opposite end, the first end configured to be slid in and out of the frame slot to provide a variable dimension from the frame to second opposite end of the panel, and a fixing mechanism for fixing the panel within the frame slot, in a configuration providing a desired value of aircraft seat unit variable dimension. The invention also provides a plurality of such kits of parts, an aircraft seat unit and an aircraft cabin comprising a plurality of such aircraft seat units or made from such kit of parts, and methods of installing an aircraft seat unit.Type: GrantFiled: December 13, 2019Date of Patent: November 15, 2022Assignee: Safran Seats GB LimitedInventors: Paul Wills, James Woodington
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Patent number: 11498664Abstract: A landing gear system includes a wheel rotatably coupled to an axle about an axis. A torque tube is rotatably mounted to the axle about the axis such that the axle extends through a central portion of the torque tube. A rotor is fixed in rotation about the axis relative to the wheel, and a stator is fixed in rotation about the axis relative to the torque tube. The landing gear assembly further includes a clutch assembly selectively reciprocal between an engaged state and a disengaged state. The stator is fixed in rotation about the axis relative to the torque tube when the clutch assembly is in an engaged state. When the clutch assembly is in a disengaged state, the stator is rotatably about the axis relative to the torque tube.Type: GrantFiled: July 10, 2020Date of Patent: November 15, 2022Assignee: SAFRAN LANDING SYSTEMS CANADA INC.Inventor: Robert Kyle Schmidt
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Patent number: 11498090Abstract: An unmanned aerial vehicle (UAV) includes a sprayer configured to generate a pressurized fluid flow and a nozzle configured to receive the pressurized fluid from the sprayer and to generate a spray fan to apply the fluid to a surface. The UAV includes sensors and a control unit to control both flight of the UAV and spraying by the sprayer. The fluid can be stored onboard the UAV in a reservoir or can be remotely stored and pumped to the UAV. The UAV control unit can be preloaded with a spray plan and a flight plan, or the UAV can be controlled by a user.Type: GrantFiled: January 17, 2018Date of Patent: November 15, 2022Assignee: Graco Minnesota Inc.Inventors: David J. Thompson, Dale D. Johnson
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Patent number: 11498672Abstract: An exemplary clamp system for securing a proprotor blade in a stowed position includes a clamp having a pair of opposing pads operable between an open position to receive a portion of a proprotor blade between the pair of opposing pads and a closed position to grip the portion of the proprotor blade with the pair of opposing pads and a rotary actuator in connection with the clamp to operate the clamp between the open and the closed position.Type: GrantFiled: September 27, 2019Date of Patent: November 15, 2022Assignee: Textron Innovations Inc.Inventor: Christopher Edward Foskey
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Patent number: 11492129Abstract: An inflatable slide may comprise a ramp portion and a slide portion having a head end attached to the ramp portion and a toe end opposite the head end. A safety gate readiness indicator may be located between the head end of the slide portion and an entrance of the ramp portion. The safety gate readiness indicator may be configured to translate between a transverse position and an erect position.Type: GrantFiled: January 17, 2020Date of Patent: November 8, 2022Assignee: Goodrich CorporationInventors: Timothy C. Haynes, Drew Hartman, Ryan Schmidt
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Patent number: 11485481Abstract: An aircraft includes a fuselage extending between a forward end and an aft end; a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor comprising an outer nacelle, the outer nacelle defining an inlet to the propulsor; and a deployable assembly attached to at least one of the fuselage or the outer nacelle and moveable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position. The propulsor further comprises a tail cone, wherein the outer nacelle defines an exhaust with the tail cone, and wherein the plurality of nacelle panels are movable generally along the axial centerline to a position at least partially aft of the exhaust of the outer nacelle when in the engaged position.Type: GrantFiled: February 19, 2019Date of Patent: November 1, 2022Assignee: General Electric CompanyInventors: Lawrence Chih-Hui Cheung, Nikolai N. Pastouchenko, Kishore Ramakrishnan