Having Plural Lifting Rotors Patents (Class 244/17.23)
  • Patent number: 10407162
    Abstract: An aircraft (40a) is provided that includes a plurality of arms (41, 42, 43, 44) with selected arms having the ability to either adjust their length, have arm segments operative to move about an articulated joint in two or three dimensions, or have one arm operative to adjust an angle between the one arm and another arm, or any combination of the foregoing. Thrust generators are repositionably mounted on selected arms, and a control system enables automated, on¬board, or remote control of the thrust generators, repositioning of the thrust generators on the arms, adjustment in the length of the selected arms, the movement of selected arms about the articulated joints, and adjustment of the angle between two or more arms, all while maintaining directional control of the aircraft in flight or on the ground. The aircraft has operational capabilities that exceed existing designs and facilitates manned and unmanned delivery of cargo and transportation of passengers.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: September 10, 2019
    Assignee: ROBODUB INC.
    Inventor: Suvro Datta
  • Patent number: 10407169
    Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of landing members. A pusher propeller extends from the tailboom assembly. In a vertical takeoff and landing mode, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode, rotation of the pusher propeller provides forward thrust and the first and second rotor assemblies are non-rotatable about the fuselage forming a dual wing configuration to provide lift.
    Type: Grant
    Filed: August 30, 2016
    Date of Patent: September 10, 2019
    Assignee: Bell Textron Inc.
    Inventors: Kirk Landon Groninga, Daniel Bryan Robertson, Frank Bradley Stamps
  • Patent number: 10377474
    Abstract: A blade guard removable structure for an aerocraft has a connecting base, a blade guard and an elastic limiting strip. The blade guard has an insert. The connecting base has a receptacle for allowing the insert to be inserted therein. The limiting strip has an inner end. The inner end is connected to the insert. The limiting strip has a protruded fastener, an extension portion and an outer end. The protruded fastener is disposed on the extension portion. The protruded fastener is located at the outer end. The connecting base has a limiting recess for limiting the protruded fastener. The limiting strip is located in between the blade guard and the limiting recess.
    Type: Grant
    Filed: November 18, 2016
    Date of Patent: August 13, 2019
    Assignee: GUANGDONG SYMA MODEL AIRCRAFT INDUSTRIAL CO., LTD
    Inventor: Jiongliang Xiao
  • Patent number: 10370119
    Abstract: A self-stabilizing spherical unmanned aerial vehicle (UAV) camera assembly, including: a stabilizer assembly; a plurality of motors coupled to the stabilizer assembly; a spherical camera mounting cage assembly disposed about and coupled to the stabilizer assembly; and a plurality of cameras coupled to the spherical camera mounting cage assembly. Preferably, the plurality of cameras include a plurality of stereoscopic cameras coupled to an exterior of the spherical camera mounting cage assembly. The self-stabilizing spherical UAV camera assembly is capable of taking/recording 360 degree×180 degree stereoscopic photo/video content. The self-stabilizing spherical UAV camera assembly can also be used with various real-time visualization and control technologies.
    Type: Grant
    Filed: September 19, 2018
    Date of Patent: August 6, 2019
    Inventor: Carl Michael Neely
  • Patent number: 10351236
    Abstract: A remotely navigated aerial vehicle may include a main body and a propulsion system operably coupled to the main body to propel the vehicle in response to an external command. The main body may include a frame and a cover plate coupled to the frame such that the frame and cover plate define an interior cavity in at least a portion of the main body. The frame may include a central body defining a longitudinal axis of the frame, a first arm at a first end portion of the central body, and a second arm at a second end portion of the central body.
    Type: Grant
    Filed: April 6, 2016
    Date of Patent: July 16, 2019
    Assignee: Wing Aviation LLC
    Inventors: Adam Woodworth, Clark Sopper
  • Patent number: 10343785
    Abstract: A hybrid rotary aircraft includes a body having an inner area; a plurality of arms rigidly attached to and extending from the body; a plurality of rotor assemblies pivotally engaged with the plurality of arms; a first gas engine; and a first brushless electric generator rotatably attached to the first gas engine and conductively coupled to each of the brushless electric motors. The plurality of rotor assemblies each having a brushless electric motor; and a rotor blades rotatably attached to the brushless electric motor.
    Type: Grant
    Filed: November 18, 2016
    Date of Patent: July 9, 2019
    Inventors: Isaac Reese, Jacob Brazda
  • Patent number: 10343770
    Abstract: A torque and pitch managed four rotor aircraft includes intersecting blades connected by synchronizing gears. The power for the rotors is provided by individual motors, one for each rotor, the motors preferably electric. Each rotor-motor assembly includes a torque management system including a set of torque sensors mounted on the drive shaft of the rotor-motor, the torque management system configured to balance the load torque presented by the rotors against the torque supplied by the motors. An additional overriding feedback system regulates rotational speed of the rotors. Direction of the aircraft is effected by adjusting the pitch of the individual rotors, and power is supplied through a battery and/or a motor-generator system located in the aircraft.
    Type: Grant
    Filed: March 1, 2016
    Date of Patent: July 9, 2019
    Inventor: Joe H. Mullins
  • Patent number: 10322797
    Abstract: A rotating sealing system includes a non-metallic rotating seal configured to be attached to a rotating shaft. The rotating seal is configured to rotate with the rotating shaft about an axis. The rotating sealing system includes a stationary sealing surface configured to be attached to a stationary housing positioned around the rotating shaft. The stationary sealing surface is substantially parallel to the axis. The rotating seal is configured to seal with the stationary sealing surface as the rotating shaft rotates.
    Type: Grant
    Filed: March 3, 2015
    Date of Patent: June 18, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Travis Jurrell, Timothy Cecil, Scott Poster, Wesley Porter
  • Patent number: 10294923
    Abstract: Embodiments herein describe using a tower damping system to reduce oscillations in a wind turbine. To do so, the dampening system may use a metric that is decoupled from the activation strategy in order to control the blade pitch and avoid or mitigate feedback loops. In one embodiment, the dampening system measures a force on the turbine that is correlated to a fatigue loading on the tower. Furthermore, the turbine may perform a calculation to decouple the force from the activation strategy. That is, the turbine determines the value of the force as if the damping system was not activated or present. In addition, the dampening system uses the current wind speed and a wind distribution to generate a pitch reference value. The dampening system may use both the pitch reference value and the fatigue loading on the tower to reduce the tower oscillations.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: May 21, 2019
    Assignee: VESTAS WIND SYSTEMS A/S
    Inventor: Jacob Krogh Kristoffersen
  • Patent number: 10293932
    Abstract: A multi-mode unmanned aerial vehicle includes an elongated fuselage, a right and left fixed wing extending from a respective right and left side of the elongated fuselage, a right and left tilt wing attached at a first side to a free end of the respective right and left fixed wing, a right and left duct attached to a second side of the respective right and left tilt wing, a right and left winglet attached to the respective right and left duct opposite to the right and left tilt wing, a tilt tail located within a curved guide slot at a rear end of the elongated fuselage, a rear duct attached to the tilt tail, a tilting mechanism, and an integrated autonomous flight control system.
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: May 21, 2019
    Inventor: Saeid A. Alzahrani
  • Patent number: 10287034
    Abstract: A docking station for an aircraft includes a base portion and an alignment system disposed on the base portion configured to orient the aircraft relative to the base portion. The alignment system can include a plurality of protrusions extending away from the base portion in a vertical direction. The plurality of protrusions can extend away from the base portion in both the vertical direction and a horizontal direction such that the protrusions can extend from the base portion at an angle.
    Type: Grant
    Filed: March 2, 2016
    Date of Patent: May 14, 2019
    Assignee: American Robotics, Inc.
    Inventor: Reese A. Mozer
  • Patent number: 10246185
    Abstract: An aircraft having a fixed wing is operative to perform vertical takeoff and landing while positioned in a nose-down orientation. The aircraft has a fixed wing having a leading edge and a trailing edge; a propulsion system operative to selectively provide forward propulsion and rearward propulsion; and a controller operative to control operation of the propulsion system. The propulsion system provides rearward propulsion during takeoff of the aircraft to move the aircraft in a direction of the trailing edge of the fixed wing, and provides forward propulsion during flight of the aircraft to move the aircraft in a direction of the leading edge of the fixed wing. The aircraft maintains the wing substantially vertical with the trailing edge facing upwards during takeoff, and transitions to having the wing substantially horizontal during flight. A vertical landing procedure is also provided.
    Type: Grant
    Filed: June 26, 2017
    Date of Patent: April 2, 2019
    Assignee: PANASONIC INTELLECTUAL PROPERTY MANAGEMENT CO., LTD.
    Inventors: Casey Joseph Carlin, Luca Rigazio, Alexander Joseph Romelfanger
  • Patent number: 10227133
    Abstract: In some embodiments, a transportation method includes coupling a flying frame to a passenger pod assembly; lifting the passenger pod assembly into the air in a vertical takeoff and landing mode with the passenger pod assembly in a generally horizontal attitude; transitioning from the vertical takeoff and landing mode to a forward flight mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; transporting the passenger pod assembly toward a second location in the forward flight mode; transitioning the flying frame from the forward flight mode to the vertical takeoff and landing mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; landing the flying frame at the second location in the vertical takeoff and landing mode; and releasing the passenger pod assembly.
    Type: Grant
    Filed: July 1, 2016
    Date of Patent: March 12, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Patent number: 10214285
    Abstract: In some embodiments, an aircraft includes a flying frame having an airframe with first and second wing members having a plurality of pylons extending therebetween, a distributed propulsion system including a plurality of propulsion assemblies securably attached to the airframe and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode with the wing members disposed in generally the same horizontal plane and a forward flight mode with the wing members disposed in generally the same vertical plane. The flight control system is operable to command the propulsion assemblies responsive to at least one of remote flight control, autonomous flight control and combinations thereof.
    Type: Grant
    Filed: July 1, 2016
    Date of Patent: February 26, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Patent number: 10207805
    Abstract: A drone transport system has a carrier pod adapted for carrying a passenger or parcels with the passenger or parcels enclosed, the carrier pod having a first attachment interface at an uppermost extremity, the attachment interface having one or first physical attachment elements, and a flight-enabled drone having a downward-facing second attachment interface having one or more second physical attachment elements compatible with the first physical attachment elements of the carrier pod. The flight-enabled drone is controllable to approach the carrier pod from above, to align and engage the second physical attachment elements with the first physical attachment elements, to lift and carry the pod from one place to another, and to land and disengage the first and second physical attachment elements, leaving the carrier pod at a new place.
    Type: Grant
    Filed: March 10, 2017
    Date of Patent: February 19, 2019
    Inventor: Michael Steward Evans
  • Patent number: 10150567
    Abstract: A rotor system for a rotorcraft includes a first rotor assembly defining a rotation axis, a second rotor assembly offset from the first rotor assembly along the rotation axis, and a drive system connected to the first and second rotor assemblies. The drive system includes a first electric motor disposed along the rotation axis and operably connected to the first rotor assembly, and a second electric motor disposed along the rotation axis and operably connected to the second rotor assembly to rotate the second rotor assembly about the rotation axis independent of rotation of the first rotor assembly about the rotation axis.
    Type: Grant
    Filed: January 27, 2016
    Date of Patent: December 11, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Timothy Fred Lauder, Patrick Boyle
  • Patent number: 10131423
    Abstract: A multirotor flying vehicle including at least one rotor support frame organized on a geometric grid, with a plurality of rotor assemblies coupled to the at least one rotor support frame. At least one power supply is coupled to and powers the rotor assemblies. A control system is coupled to the rotor assemblies and is configured to operate the vehicle.
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: November 20, 2018
    Inventors: David Geise, John Geise
  • Patent number: 10124888
    Abstract: A rotorcraft having a body and a propulsion system wherein the propulsion system includes a main thrust rotor and multiple control rotors, wherein the main thrust rotor is coupled to the body, whereby the main thrust rotor is driven by a main thrust drive shaft having an axis of rotation maintained in a fixed orientation to the body of the rotorcraft and wherein the multiple control rotors are arranged to control roll, pitch and yaw of the rotorcraft and are driven by respective control drive shafts offset to the axis of rotation of the main thrust drive shaft.
    Type: Grant
    Filed: October 31, 2014
    Date of Patent: November 13, 2018
    Assignee: THE UNIVERSITY OF QUEENSLAND
    Inventor: Paul Edward Ian Pounds
  • Patent number: 10099783
    Abstract: An improved accessory mounting is disclosed for a rotary wing aircraft comprising a frame supporting a plurality of driven propellers. A transceiver is connected to a electronic flight control for directing the flight of the rotary wing aircraft. An accessory frame receives an accessory load to be carried by the rotary wing aircraft. A battery is disposed on the frame for powering the transceiver. A quick change mounting removably mounts the accessory frame to the frame. Preferably, the battery is movable relative to the frame for compensating for different weights of the accessory load secured to the accessory frame to adjust the center of mass for proper flight of the rotary wing aircraft. An integral balance included for adjusting the center of mass assisting of the rotary wing aircraft.
    Type: Grant
    Filed: August 10, 2015
    Date of Patent: October 16, 2018
    Assignee: FPV MANUALS LLC
    Inventor: Tim Nilson
  • Patent number: 10093416
    Abstract: A system and method for efficiently maneuvering a multirotor drone having a control system, an electrical power source, a plurality of rotor assemblies each having a rotor boom, a rotor mast, at least one rotor blade, a rotor assembly adjustment apparatus, a plurality of electric motors, wherein each electric motor is connected to a rotor boom positioned in a substantially horizontal direction and drives a rotor mast positioned in a substantially vertical direction and connected to at least one rotor blade, with the position of said rotor boom automatically adjustable in a substantially horizontal direction by the adjustment apparatus and the control system.
    Type: Grant
    Filed: May 21, 2015
    Date of Patent: October 9, 2018
    Inventor: Khalid Hamad Mutleb Alnafisah
  • Patent number: 10053213
    Abstract: A multi-copter lift body aircraft has a push or pull propeller and a lift body that has a first airfoil shape on a front to rear cross-section and a second airfoil shape on a left to right cross-section. The lift body is made from a top shell and a bottom shell. The lift body has a nose and a tail. Multi-copter propellers are attached to the lift body. The multi-copter propellers provide a lift at low speeds and the lift body provides a lift at high speeds. Avionics can be stored in a hollow cavity of the lift body. The avionics may include a control circuit, batteries, and a radio receiver. The multi-copter has a lift body made from an upper shell and a lower shell. The lift body has an optimum attack angle at a cruising speed, and the lift body provides a combined lift mode.
    Type: Grant
    Filed: May 8, 2017
    Date of Patent: August 21, 2018
    Assignee: Pinnacle Vista, LLC
    Inventor: Haofeng Tu
  • 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: 10017245
    Abstract: A multirotor flying vehicle including at least one rotor support frame organized on a geometric grid, with a plurality of rotor assemblies coupled to the at least one rotor support frame. At least one power supply is coupled to and powers the rotor assemblies. A control system is coupled to the rotor assemblies and is configured to operate the vehicle.
    Type: Grant
    Filed: April 13, 2016
    Date of Patent: July 10, 2018
    Inventors: David Geise, John Geise
  • 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: 10005549
    Abstract: A reliable reduced weight coaxial lifting system includes a reducing gear with two shafts rotating in opposite directions, upper and lower rotor hubs mounted on the respective shafts and upper and lower swashplates connected to one another, which are movable in the axial direction and are kinematically linked to guides of blades positioned on the upper and lower rotor hubs. Guides of the blades are connected to the upper swashplate by rockers mounted on a slide block located above the upper rotor hub and guides of the blades of the lower rotor hub are connected by tie rods directly to the lower swashplate. The lower swashplate is connected to control systems of a collective and a cyclical pitch and the slide block is connected to a control system of a differential pitch of the upper rotor.
    Type: Grant
    Filed: June 22, 2015
    Date of Patent: June 26, 2018
    Assignee: RS Helikopter GmbH
    Inventors: Vitali Brandt, Andrei Alexandrovich Vlasov, Vladimir Yurievich Ivanov
  • Patent number: 9994313
    Abstract: This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back.
    Type: Grant
    Filed: November 26, 2014
    Date of Patent: June 12, 2018
    Assignee: XCraft Enterprises, LLC
    Inventors: Jerry Daniel Claridge, Charles Fischer Manning
  • Patent number: 9981741
    Abstract: Systems and methods are described herein related to an unmanned aerial vehicle, the unmanned aerial vehicle includes: a frame portion, two rear arms extending away from the frame portion, and at least one rear air propulsion device arranged on each of the rear arms at an orthogonal angle relative to a vertical axis. The at least one rear air propulsion device has an axis of rotation for both lift and rotation based on the angle. The unmanned aerial vehicle has two front arms arranged along a horizontal axis. The vertical axis is perpendicular to the horizontal axis. The unmanned aerial vehicle also includes at least one camera arranged on at least one of the front arms. The at least one camera faces a front direction.
    Type: Grant
    Filed: September 18, 2015
    Date of Patent: May 29, 2018
    Assignee: QUALCOMM Incorporated
    Inventor: Donald Bolden Hutson
  • Patent number: 9981744
    Abstract: There is disclosed a drone including a main body comprising a motor, a shaft inserted in the main body vertically, a wing unit rotatable on the shaft by a power generated from the motor, the wing unit comprising a propeller unfolded horizontally and folded vertically, wherein the motor comprises a first motor and a second motor, and the shaft comprises an upper shaft inserted in the main body from a top vertically and a lower shaft inserted in the main body from a bottom vertically, and the wing unit comprises a first wing unit rotated on the upper shaft in a first direction by a power generated from the first motor, and a second wing unit rotated on the lower shaft in a second direction, which is the reverse of the first direction, by a power generated from the second motor.
    Type: Grant
    Filed: July 22, 2015
    Date of Patent: May 29, 2018
    Assignee: LG ELECTRONICS INC.
    Inventors: Zhimin Choo, Chulbae Lee
  • Patent number: 9957045
    Abstract: A drone (2) has an upper coupler (6) that releasably connects to a lower coupler (8) of a second drone (4), interconnecting the drones in a stacked combined flying machine (5A). The couplers index a predetermined rotational relationship between the two drones about a central vertical axis (10). An embodiment (5C) provides coaxial counter-rotating propellers of the respective upper and lower drones. Other embodiments rotationally offset the upper and lower drones to minimize overlap (A1, A2) of the upper and lower propeller disks or to overlap only portions (A1) of the propeller disks that rotate in opposite directions. The couplers may have electrical connectors that integrate control systems (38, 40) that establish a master/slave control relationship.
    Type: Grant
    Filed: September 3, 2017
    Date of Patent: May 1, 2018
    Inventor: Brehnden Daly
  • Patent number: 9914538
    Abstract: A supporting assembly for an unmanned aerial vehicle is disclosed. The supporting assembly includes a base, rotor arms, and rotor shrouds. The rotor arms extend from the base. Each of the rotor arms includes a proximal end secured to the base and a distal end opposite to the proximal end. Each of the rotor shrouds includes a converged end removably engaged with and secured to the distal end, an arc shaped end, and one or more connecting members extending from the arc shaped end to the converged end. An unmanned aerial vehicle and a rotor shroud apparatus are also disclosed.
    Type: Grant
    Filed: November 18, 2016
    Date of Patent: March 13, 2018
    Assignee: ZEROTECH (SHENZHEN) INTELLIGENCE ROBOT CO., LTD.
    Inventor: Wei-Yong Yu
  • Patent number: 9891885
    Abstract: A display device includes a display unit, at least a flight unit connected to the display unit, a position information receiving unit obtaining information on a current position of the display device, a sensor unit obtaining information of a user, a flight control unit automatically controlling a flight of the display device, a posture information obtaining unit obtaining posture information of the display device, a main control unit controlling an overall operation of respective components of the display device, a posture correction unit varying an angle of the display device or the display unit, a vibration system, a voice recognition unit, a communication module, an input member transmitting input information to the communication module, a power source unit, an obstacle detection unit, a joint manipulator connecting the at least one flight unit and the display unit, and a connector connecting the display unit and the display device.
    Type: Grant
    Filed: January 3, 2016
    Date of Patent: February 13, 2018
    Assignee: SAMSUNG DISPLAY CO., LTD.
    Inventor: Beomshik Kim
  • Patent number: 9845149
    Abstract: The embodiments of the present invention disclose a method and a device for driving a rotor. The method comprises: receiving a flight control command; obtaining current rotational states of first motors corresponding to first actuators and the current rotational states of second motors corresponding to second actuators; determining required first rotational states of the first motors according to the flight control command and the current rotational states of the first motors; determining required second rotational states of the second motors according to the flight control command and the current rotational states of the second motors; controlling the first motor to rotate in a corresponding first rotational state so as to drive first blade clamping bodies to twist relative to a lower rotor hub; controlling the second motor to rotate in a corresponding second rotational state so as to drive second blade clamping bodies to twist relative to an upper rotor hub.
    Type: Grant
    Filed: October 23, 2013
    Date of Patent: December 19, 2017
    Assignee: SHENZHEN UNITED AIRCRAFT TECHNOLOGY CO., LTD
    Inventor: Gangyin Tian
  • Patent number: 9823664
    Abstract: A method of positioning an instrument by an unmanned aircraft for measurement purposes relating to a target surface is provided. The method includes coupling the instrument to the unmanned aircraft and moving the unmanned aircraft to position the instrument away from the target surface. The method further includes stabilizing the unmanned aircraft to maintain a constant altitude and a level attitude relative to the target surface and orientating the instrument perpendicular to the target surface. A measurement is conducted by the instrument while the instrument is orientated perpendicular to the target surface. The method also includes transmitting the measurement to a receiver.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: November 21, 2017
    Assignee: A.M.T.S., LLC
    Inventors: Michael L. Krogh, Ed DeMoss
  • Patent number: 9810224
    Abstract: Rotary-wing aircraft or fixed-wing aircraft consisting of one or a plurality of rotors and/or one or a plurality of airscrews being caused to rotate by means of at least one shaft, the said aircraft comprising a distributed electric motor unit configured to ensure the propulsion and/or the lifting of the said aircraft by causing the said shaft to rotate, the motor unit being a distributed electric motor unit connected directly to the rotating shaft, no mechanism for the transmission of movement being interposed between the said unit and the said shaft, the distributed electric motor unit being composed of a plurality of stacked electric motor elements, each said electric motor element being connected directly to the rotating shaft and consisting of at least one fixed stator and at least one moving rotor capable of connection to the said rotating shaft in order to transmit to it a mechanical power of the following kind where: ·Pr=the nominal mechanical power necessary for the propulsion and/or for the lifting
    Type: Grant
    Filed: August 17, 2012
    Date of Patent: November 7, 2017
    Inventors: Eric Chantriaux, Pascal Chretien
  • Patent number: 9764835
    Abstract: This disclosure describes a configuration of a multi-propeller aerial vehicle (MPAV). The components of the MPAV are designed for easy manufacture, assembly, configuration and replacement. Likewise, the configuration of the MPAV is designed for increased flight duration.
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: September 19, 2017
    Assignee: Amazon Technologies, Inc.
    Inventors: Gur Kimchi, Fabian Hensel, Scott A. Green, Daniel Buchmueller
  • Patent number: 9725158
    Abstract: A self-righting aeronautical vehicle comprising a hollowed frame and a lift mechanism. The exterior of the frame and center of gravity are adapted to self-right the vehicle. The frame can include sealed, hollowed sections for use in bodies of water. The frame can be spherical in shape enabling inspection of internal surface of partially or fully enclosed structures. Inspection equipment can be integrated into the vehicle and acquired data can be stored or wirelessly communicated to a server. A controlled or other mass can be pivotally assembled to a pivot axle spanning across the interior of the frame. The pivot axis can rotate about a vertical axis (an axis perpendicular to the elongated axis). The propulsion mechanisms can be adapted for use as a terrestrial vehicle when enclosed in a sealed spherical shell.
    Type: Grant
    Filed: September 6, 2016
    Date of Patent: August 8, 2017
    Inventors: Gaofei Yan, James Dees
  • Patent number: 9725168
    Abstract: According to an embodiment of the present invention, an unmanned aerial vehicle comprises a body, a plurality of arms provided on a periphery of the body, a propeller provided on each of the plurality of arms and driven by a driving motor, and a gripper provided on a bottom of the body to grip an object. The gripper may include a supporting bar extending downward from the bottom of the body and a head provided at a lower end of the supporting bar to grip the object.
    Type: Grant
    Filed: April 12, 2016
    Date of Patent: August 8, 2017
    Inventor: Yong Kuk Kim
  • Patent number: 9463874
    Abstract: A method of regulating the speed of rotation of at least one main rotor of a multi-engined rotorcraft, which rotor is driven at variable speed. In the event of a failure of one of the main engines of the rotorcraft, a control unit generates an NR setpoint that is not less than the nominal drive speed (NRnom) of the main rotor. Thereafter, a calculator acts iteratively to determine a target speed (NRobj) for driving the main rotor to obtain stabilized lift of the rotorcraft by balancing between the torque developed by the main rotor and the rate of increase of its drive speed. The autopilot then causes the pitch of the blades of the main rotor to vary so as to obtain the iteratively calculated target speed (NRobj) until stabilized lift of the rotorcraft is obtained.
    Type: Grant
    Filed: June 30, 2015
    Date of Patent: October 11, 2016
    Assignee: Airbus Helicopters
    Inventors: Jean-Baptiste Vallart, Setareh Taheri
  • Patent number: 9457901
    Abstract: A method and system of printable payload extensions of a quadcopter are disclosed. In one aspect, a quadcopter includes an airframe and a central portion of the airframe having at least one of an upper extender mechanism and a lower extender mechanism. The central portion enables users of the quadcopter to design payload extensions that mechanically couple with the quadcopter using a three-dimensional (3D) printing device as long as the payload extensions have a weight less than a maximum payload capacity of the quadcopter. The quadcopter couples with at a set of payload extensions including a hook assembly, an interlocking building block platform assembly, a DSLR camera assembly, a HD camera assembly, and/or a container assembly through the central portion of the airframe.
    Type: Grant
    Filed: April 22, 2014
    Date of Patent: October 4, 2016
    Assignee: FATDOOR, INC.
    Inventors: Blaise Bertrand, Youenn Colin, Anthony Patron, Vinh Pho
  • Patent number: 9446843
    Abstract: An enhanced performance rotorcraft rotor blade system and methods are presented. A rotor blade comprises an inboard blade portion, and at least one controllable surface coupled to the inboard blade portion. The at least one controllable surface is operable to improve a lift of the inboard blade portion by altering an angle of attack of the inboard blade portion independent of the rotor blade.
    Type: Grant
    Filed: March 27, 2012
    Date of Patent: September 20, 2016
    Assignee: The Boeing Company
    Inventor: David L. Perlman
  • Patent number: 9434462
    Abstract: An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting dome shaped vehicle body has an apex/protrusion preferably at a top of a central vertical axis. The apex/protrusion provides initial instability to begin a self-righting process when the vehicle is inverted on a surface. A lift and stabilization panel extends across an upper portion of said frame to provide lift, drag and/or stability. A propulsion system can be located within a central void of the frame assembly and oriented to provide a lifting force. An electronics assembly is also carried by the self-righting body for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a supporting surface. The body provides self-righting functionality and protection of elements carried therein.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: September 6, 2016
    Inventors: Gaofei Yan, James Dees
  • Patent number: 9388794
    Abstract: Flying electric generator aircraft that include groupings of four rotors mounted to booms extending fore and aft of a fuselage structure wherein the rotors are placed so that when the aircraft is facing the wind, each rotor has a direct path to an undisturbed flow of air, regardless of pitch angle and during all flight maneuvers of the aircraft. The rotors are placed in counter-rotating pairs with the booms preferably angled so that the rotors in the front of the aircraft are spaced at a distance from one another that is different than a spacing of the rotors at the rear of the aircraft.
    Type: Grant
    Filed: August 18, 2015
    Date of Patent: July 12, 2016
    Inventors: Bruce Weddendorf, Colin Austin, Greg Mercier, Robert Austin
  • Patent number: 9365290
    Abstract: An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode.
    Type: Grant
    Filed: August 27, 2015
    Date of Patent: June 14, 2016
    Assignee: Martin UAV, LLC
    Inventor: Stephen Morris
  • Patent number: 9242729
    Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.
    Type: Grant
    Filed: March 5, 2015
    Date of Patent: January 26, 2016
    Assignee: SZ DJI TECHNOLOGY CO., Ltd
    Inventors: Tao Wang, Tao Zhao, Hao Du, Mingxi Wang
  • Patent number: 9233754
    Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.
    Type: Grant
    Filed: August 26, 2015
    Date of Patent: January 12, 2016
    Assignee: SZ DJI TECHNOLOGY CO., LTD
    Inventors: Tao Wang, Tao Zhao, Shaojie Chen, Zhigang Ou
  • Patent number: 9221536
    Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.
    Type: Grant
    Filed: October 15, 2014
    Date of Patent: December 29, 2015
    Assignee: SZ DJI TECHNOLOGY, CO., LTD
    Inventors: Tao Wang, Tao Zhao, Shaojie Chen, Zhigang Ou
  • Patent number: 9187174
    Abstract: The invention is a flight vehicle, and methods of operation thereof, having wings and movable propeller assemblies which can be rotated to provide vertical and/or horizontal thrust. The propeller assemblies are configured to maximize available engine/propeller thrust and to prevent propwash from striking the wings of the aircraft.
    Type: Grant
    Filed: October 6, 2011
    Date of Patent: November 17, 2015
    Inventor: Donald Orval Shaw
  • Patent number: 9156549
    Abstract: A lift device is disclosed that can be used to provide vertical lift to an aircraft or other vehicle. The lift device can include a fan that produces an airflow and a vane box that can direct the airflow. In one form the fan can be oriented at an angle relative to a reference plane in the aircraft. In another form the vane box can be oriented at an angle. The vane box can be structured to provide a maximum flow area between an aft flow vector and a forward flow vector.
    Type: Grant
    Filed: December 29, 2010
    Date of Patent: October 13, 2015
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC.
    Inventors: Daniel Kent Vetters, Andrew Barlow
  • Patent number: 9109575
    Abstract: Flying electric generator aircraft that include groupings of four rotors mounted to booms extending fore and aft of a fuselage structure wherein the rotors are placed so that when the aircraft is facing the wind, each rotor has a direct path to an undisturbed flow of air, regardless of pitch angle and during all flight maneuvers of the aircraft. The rotors are placed in counter-rotating pairs with the booms preferably angled so that the rotors in the front of the aircraft are spaced at a distance from one another that is different than a spacing of the rotors at the rear of the aircraft.
    Type: Grant
    Filed: May 23, 2012
    Date of Patent: August 18, 2015
    Assignee: SKY WINDPOWER CORPORATION
    Inventors: Bruce Weddendorf, Colin Austin, Greg Mercier, Robert Austin