Rotatable Patents (Class 244/39)
  • Patent number: 10363826
    Abstract: Systems and methods are provided for swapping the battery on an unmanned aerial vehicle (UAV). The UAV may be able to identify and land on an energy provision station autonomously. The UAV may take off and/or land on the energy provision station. The UAV may communicate with the energy provision station. The energy provision station may store and charge batteries for use on a UAV.
    Type: Grant
    Filed: September 9, 2016
    Date of Patent: July 30, 2019
    Assignee: SZ DJI TECHNOLOGY CO., LTD.
    Inventor: Mingxi Wang
  • Patent number: 10301022
    Abstract: Unmanned vehicles can be terrestrial, aerial, nautical, or multi-mode. Unmanned vehicles may efficiently accomplish tasks by autonomously charging or replacing its power source.
    Type: Grant
    Filed: February 6, 2017
    Date of Patent: May 28, 2019
    Assignee: United Services Automobile Association (USAA)
    Inventor: Kade Scott
  • Patent number: 10086951
    Abstract: Described is an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that includes a delivery shroud. The delivery shroud may be maintained in a retracted position while the aerial vehicle is in transit. The delivery shroud reduces the transmission of sound from the aerial vehicle to the delivery area. Likewise, the delivery shroud may also be used to facilitate delivery of a payload from the aerial vehicle to a delivery location within the delivery area.
    Type: Grant
    Filed: August 4, 2017
    Date of Patent: October 2, 2018
    Assignee: Amazon Technologies, Inc.
    Inventors: Brian C. Beckman, Allan Ko
  • Patent number: 10079497
    Abstract: A charge device for a drone includes a base and a covering mechanism. The base has a charge portion. The covering mechanism includes two covers, two first position-limiting components and two second position-limiting components. The two covers are movably disposed on the base. The covers are adapted to move toward each other to become a closed state and cover the charge portion, and the covers are adapted to move away from each other to become an expanded state and expose the charge portion. The first position-limiting components are connected to the covers respectively. Each of the second position-limiting components is connected between the covers. When the covers are in the closed state, the first position-limiting components and the second position-limiting components are located above the charge portion. When the covers are in the expanded state, the first position-limiting components and the second position-limiting components are away from the charge portion.
    Type: Grant
    Filed: January 25, 2017
    Date of Patent: September 18, 2018
    Assignee: Coretronic Intelligent Robotics Corporation
    Inventors: Hsu-Chih Cheng, Ying-Chieh Chen, Chi-Tong Hsieh
  • Patent number: 10023326
    Abstract: In one embodiment, a controller instructs an unmanned aerial vehicle (UAV) docked to a landing perch to perform a pre-flight test operation of a pre-flight test routine. The controller receives sensor data associated with the pre-flight test operation from one or more force sensors of the landing perch, in response to the UAV performing the pre-flight test operation. The controller determines whether the sensor data associated with the pre-flight test operation is within an acceptable range. The controller causes the UAV to launch from the landing perch based in part on a determination that UAV has passed the pre-flight test routine.
    Type: Grant
    Filed: November 30, 2016
    Date of Patent: July 17, 2018
    Assignee: Cisco Technology, Inc.
    Inventors: Charles Calvin Byers, Gonzalo Salgueiro
  • Patent number: 9731839
    Abstract: Described is an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that includes a delivery shroud. The delivery shroud may be maintained in a retracted position while the aerial vehicle is in transit. The delivery shroud reduces the transmission of sound from the aerial vehicle to the delivery area. Likewise, the delivery shroud may also be used to facilitate delivery of a payload from the aerial vehicle to a delivery location within the delivery area.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: August 15, 2017
    Assignee: Amazon Technologies, Inc.
    Inventors: Brian C. Beckman, Allan Ko
  • Patent number: 9708060
    Abstract: Disclosed are embodiments of flow diverting lift elements which, when placed in the proper orientation and propelled through a fluid, produce a lift force with improved lift versus velocity performance. The flow diverting lift elements can produce lift for rotary lift devices such as aircraft. The flow diverting lift devices include an airfoil and a diversion wall extending from an upper surface of the airfoil. The airfoil can be an annular airfoil.
    Type: Grant
    Filed: July 14, 2015
    Date of Patent: July 18, 2017
    Inventor: Derek T. Schwartz
  • Patent number: 9156559
    Abstract: An aircraft wing has a plurality of wing segments mounted on a wing spar by joints that allow relative movement between the spar and the wing segments. Tuning of coefficients of thermal expansion is employed to reduce induced stresses from changes in temperature.
    Type: Grant
    Filed: October 19, 2011
    Date of Patent: October 13, 2015
    Assignee: THE BOEING COMPANY
    Inventors: Robert Erik Grip, Blaine Knight Rawdon
  • Publication number: 20150115097
    Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
    Type: Application
    Filed: April 7, 2014
    Publication date: April 30, 2015
    Applicant: AeroVironment, Inc.
    Inventors: Matthew Todd Keennon, Karl Robert Klingebiel, Alexander Andryukov, Bart Dean Hibbs, John Peter Zwaan
  • Patent number: 8991751
    Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.
    Type: Grant
    Filed: March 23, 2012
    Date of Patent: March 31, 2015
    Assignee: DZYNE Technologies, Inc.
    Inventors: Mark Allan Page, Matthew Robert McCue, Robert Anthony Godlasky
  • Patent number: 8985504
    Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
    Type: Grant
    Filed: June 15, 2012
    Date of Patent: March 24, 2015
    Inventors: Tony Shuo Tao, Nathan Olson, Carlos Thomas Miralles, Robert Nickerson Plumb
  • Patent number: 8946607
    Abstract: Deployment and control actuation mechanisms are incorporated in unmanned aerial vehicles having folding wings and/or folding canards and/or a folding vertical stabilizer. The folding canards and folding vertical stabilizer can be deployed using respective four-bar over-center mechanisms. Elevators pivotably mounted to the folding canards and a rudder pivotably mounted to the folding vertical stabilizer can be controlled by means of respective twist link mechanisms. The folding wings have respective wing roots that are driven by respective gas springs to pivot on bearings about a wing root hub having control servo wire paths.
    Type: Grant
    Filed: December 13, 2011
    Date of Patent: February 3, 2015
    Assignee: The Boeing Company
    Inventor: Jonathan David Gettinger
  • Publication number: 20150028155
    Abstract: The present invention relates to a device for generating aerodynamic lift and in particular an aircraft (100) for vertical take-off and landing. A wing arrangement (110) comprises at least one propulsion unit (111), wherein the propulsion unit (111) comprises a rotating mass which is rotatable around a rotary axis (117). The wing arrangement (110) is mounted to a fuselage (101) such that the wing arrangement (110) is tiltable around a longitudinal wing axis (112) of the wing arrangement (110) and such that the wing arrangement (110) is rotatable with respect to the fuselage (101) around a further rotary axis that differs to the longitudinal wing axis (112). An adjusting mechanism adjusts a tilting angle of the wing arrangement (110) around the longitudinal wing axis (112) under influence of a precession force (Fp) which forces the wing arrangement (110) to tilt around the longitudinal wing axis (112).
    Type: Application
    Filed: February 13, 2013
    Publication date: January 29, 2015
    Inventor: Johannes Reiter
  • Patent number: 8894003
    Abstract: An air vehicle is provided, including a body having a longitudinal axis, a wing arrangement rotatably mounted to the body with respect to the longitudinal axis, a direction control arrangement for controlling the direction of motion of the body, and an actuation mechanism operable for selectively and controllably rotating the wing arrangement with respect to the body through at least a desired first angular displacement about the longitudinal axis. Methods for operating air vehicles are also provided.
    Type: Grant
    Filed: April 13, 2010
    Date of Patent: November 25, 2014
    Assignee: Israel Aerospace Industries Ltd.
    Inventor: Mordechai Shai
  • Patent number: 8640985
    Abstract: The system of the present application represents a rotor hub for a rotorcraft and a rotorcraft incorporating the rotor hub. The rotor hub is represented as having multiple rotor disk assemblies, each rotor disk assembly rotating in the same direction about the same mast axis of rotation. In the preferred embodiment, each rotor disk assembly has three rotor blades. The upper rotor disc assembly and the lower rotor disk assembly are separated by approximately 2.5% of the rotor disk diameter, at least to take advantage of “wake contraction”.
    Type: Grant
    Filed: May 22, 2009
    Date of Patent: February 4, 2014
    Assignee: Textron Innovations Inc.
    Inventor: John E. Brunken, Jr.
  • Patent number: 8509968
    Abstract: Systems and methods for real-time efficiency and aircraft performance monitoring and delta efficiency calculations between various user- or system-selected phases of flight by determining an efficiency messaging index that gets translated into a messaging profile. That messaging profile is then used to obtain necessary flight and other information from multiple sources. The efficiency calculations and deltas can be used to determine real-time or post-processed benefits, which can then be used to optimize flight(s). Additionally, data is post-processed, which allows the calculation, storage and subsequent usage of efficiency coefficients to enhance the accuracy of the efficiency calculations. There are a number of ways to implement the architecture and order of processing.
    Type: Grant
    Filed: March 20, 2012
    Date of Patent: August 13, 2013
    Assignee: The Boeing Company
    Inventors: Gregory T. Saccone, Ryan D. Hale, Nicholas P. G. Impert, Louis J. Bailey
  • Publication number: 20130168493
    Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
    Type: Application
    Filed: June 25, 2012
    Publication date: July 4, 2013
    Inventors: Matthew Todd Keennon, Karl Robert Klingebiel, Alexander Andryukov, Bart Dean Hibbs, John Peter Zwaan
  • Patent number: 8454405
    Abstract: Provided are flying devices and methods of manufacturing and launching same, in particular flying toys or other recreational items that are designed to be thrown through the air by a user participating in any one of a variety of throwing (i.e. “catch”) games. In particular, the concept is directed toward a flying disc having rotatably attached non-rotating (a.k.a. “gliding”) portions that are attached to the disc and provide an optical illusion, wherein the user (and, similarly, an observer) does not notice the spinning of the flying disc, but instead sees a flying craft that appears to have no propulsion, yet flies. While the non-rotating portions alter the airflow associated with a typical flying disc, they do not negatively affect the flight characteristics of the disc itself. Indeed, in certain embodiments, the non-rotating portions (e.g., ailerons) have been observed to improve the flight characteristics of typical flying discs.
    Type: Grant
    Filed: March 23, 2012
    Date of Patent: June 4, 2013
    Inventor: Guy L. Scarborough
  • Patent number: 8292216
    Abstract: A method and apparatus may be present for moving a wing. A plurality of lifting assemblies may be attached to a first plurality of channels in a ring associated with the wing of an aircraft. A plurality of base assemblies may be attached to a plurality of fittings with a second plurality of channels associated with a fuselage of the aircraft. The plurality of lifting assemblies may be moved away from the plurality of base assemblies using a plurality of biasing systems such that the ring may move away from the fuselage.
    Type: Grant
    Filed: December 16, 2009
    Date of Patent: October 23, 2012
    Assignee: The Boeing Company
    Inventor: William Elmer Rumberger, Jr.
  • Patent number: 8286911
    Abstract: A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge.
    Type: Grant
    Filed: February 13, 2009
    Date of Patent: October 16, 2012
    Assignee: Airbus Operations Limited
    Inventors: Jon McAlinden, Kim Sharp
  • Patent number: 8182306
    Abstract: Provided are flying devices and methods of manufacturing and launching same, in particular flying toys or other recreational items that are designed to be thrown through the air by a user participating in any one of a variety of throwing (i.e. “catch”) games. In particular, the concept is directed toward a flying disc having rotatably attached non-rotating (a.k.a. “gliding”) portions that are attached to the disc and provide an optical illusion, wherein the user (and, similarly, an observer) does not notice the spinning of the flying disc, but instead sees a flying craft that appears to have no propulsion, yet flies. While the non-rotating portions alter the airflow associated with a typical flying disc, they do not negatively affect the flight characteristics of the disc itself. Indeed, in certain embodiments, the non-rotating portions (e.g., ailerons) have been observed to improve the flight characteristics of typical flying discs. The non-rotating portions (a.k.a.
    Type: Grant
    Filed: November 20, 2009
    Date of Patent: May 22, 2012
    Inventor: Guy L. Scarborough
  • Publication number: 20120061509
    Abstract: The system of the present application represents a rotor hub for a rotorcraft and a rotorcraft incorporating the rotor hub. The rotor hub is represented as having multiple rotor disk assemblies, each rotor disk assembly rotating in the same direction about the same mast axis of rotation. In the preferred embodiment, each rotor disk assembly has three rotor blades. The upper rotor disc assembly and the lower rotor disk assembly are separated by approximately 2.5% of the rotor disk diameter, at least to take advantage of “wake contraction”.
    Type: Application
    Filed: May 22, 2009
    Publication date: March 15, 2012
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: John E. Brunken, JR.
  • Publication number: 20120018572
    Abstract: An air vehicle is provided, including a body having a longitudinal axis, a wing arrangement rotatably mounted to the body with respect to the longitudinal axis, a direction control arrangement for controlling the direction of motion of the body, and an actuation mechanism operable for selectively and controllably rotating the wing arrangement with respect to the body through at least a desired first angular displacement about the longitudinal axis. Methods for operating air vehicles are also provided.
    Type: Application
    Filed: April 13, 2010
    Publication date: January 26, 2012
    Applicant: Israel Aerospace Industries Ltd.
    Inventor: Mordechai Shai
  • Patent number: 7971823
    Abstract: An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating sine-wave ring is used to activate and move a plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere.
    Type: Grant
    Filed: May 7, 2009
    Date of Patent: July 5, 2011
    Inventor: Herbert Martin
  • Patent number: 7874514
    Abstract: A multi-wing, multi-engine, multi-hull amphibious aircraft is disclosed. In the illustrative embodiment, the aircraft has an open frame structure without a fuselage.
    Type: Grant
    Filed: June 5, 2007
    Date of Patent: January 25, 2011
    Assignee: Lockheed Martin Corporation
    Inventor: Brian R. Said
  • Patent number: 7766274
    Abstract: An unmanned aerial vehicle (UAV) has a payload or body affixed at one end of an elongated airfoil. The entire airfoil/payload combination rotates about a center of mass to define a rotor disk. Thrust is provided by air-augmented rocket engine thrusting tangentially at a location remote from the payload. A control system maintains knowledge of its environment, as by a camera, to produce directional control signals which actuate lift control means in synchronism with the rotational position of the vehicle. A deployable object may be carried. Protection of the stowed vehicle is provided by blister packaging.
    Type: Grant
    Filed: March 13, 2007
    Date of Patent: August 3, 2010
    Assignee: Lockheed Martin Corporation
    Inventors: Stephen M. Jameson, Brian P. Boesch, Edward H. Allen
  • Patent number: 7762495
    Abstract: A solar powered aerial vehicle includes an elongated airframe incorporating lifting and control surfaces, a mechanism for propelling the airframe through the air such that lift developed by the lifting surface is equal to or greater than the weight of the aerial vehicle, a planar solar sail coupled to the airframe and having at least one surface adapted to collect solar energy during the day and to power the propelling mechanism with a first portion of the energy collected, and an apparatus such as a fuel cell/electrolyzer for storing a second portion of the solar energy collected by the solar sail during the day and for powering the propelling mechanism with the second portion of energy during the night. The vehicle is capable of continuous operation at northern latitudes and during the winter months for extended periods without landing or refueling.
    Type: Grant
    Filed: July 25, 2007
    Date of Patent: July 27, 2010
    Assignee: The Boeing Company
    Inventor: Gerald D Miller
  • Publication number: 20100155524
    Abstract: A monomolecular carbon-based film can be placed on an aircraft part, such as the leading edge designed to directly impinge against air during flight, ascent or descent, in order to form a smooth surface having increased lubricity and reduced air friction. The aircraft part may be in the form of a helicopter rotor, wing, propeller, fin, aileron, nose cone, and the like. The monomolecular carbon-based film can be deposited on the aircraft part, for example, using a reactor that includes a bed of silica and through which emissions from a diesel engine are passed. The monomolecular carbon-based film decreases air friction and increased lift of a modified aircraft that includes an aircraft part treated with the film. It also provides a structured shock absorber.
    Type: Application
    Filed: March 3, 2009
    Publication date: June 24, 2010
    Inventor: Thomas C. Maganas
  • Patent number: 7699260
    Abstract: A vertical takeoff and landing aircraft, using for vertical lift and lateral thrust a redundant plurality of essentially similar electrically-powered and electronically-controlled thrust units mounted in a mechanically static or fixed fashion relative to one another in a substantially horizontal plane. The thrust units are situated in this planar array in aerodynamically approximate pairs, such that a complete failure of a single thrust unit would not substantially compromise the ability of the aircraft to maintain flight.
    Type: Grant
    Filed: January 4, 2006
    Date of Patent: April 20, 2010
    Assignee: Hughey Electricopter Corporation
    Inventor: Bradley Ward Hughey
  • Patent number: 7677492
    Abstract: A rotary aircraft has a fuselage with wings and a rotor. The blades of the rotor are twistable about a pitch axis to vary collective pitch. A collective pitch shaft moves in an advancing direction to increase the collective pitch. Weights are mounted to the blades for outward movement along the blades in response to an increase in rotational speed of the blades. A linkage between each of the weights and the collective pitch shaft moves the collective pitch shaft in the advancing direction in response to an increase in rotational speed. A spring acting through a cam mechanism exerts a non linear force in opposition to the outward movement of the blades.
    Type: Grant
    Filed: November 16, 2005
    Date of Patent: March 16, 2010
    Assignee: Cartercopters, L.L.C.
    Inventors: Jay W. Carter, Jr., Jeffrey R. Lewis
  • Publication number: 20090206195
    Abstract: A system and method of constructing a system for delivering cargo by airdrop are provided. In short, the system uses rotor blades to slow the descent of cargo dropped from an aircraft. In one example of one embodiment, a frame is secured to a cargo pallet and at least one rotor blade is secured to the frame. The rotor blade is secured to the frame in a position such that it causes the cargo pallet and the frame to rotate in air when dropped from an elevation. In another embodiment, the rotor blade may be extendable and extend during flight.
    Type: Application
    Filed: December 20, 2006
    Publication date: August 20, 2009
    Applicant: THE BOEING COMPANY
    Inventors: JOSEPH M. COLICH, EDWARD BAROCELA, JAMES LIS
  • Publication number: 20090206208
    Abstract: In an exemplary variable area nozzle, a fixed duct section has an inlet and an outlet oriented approximately perpendicular to the inlet. A controllable nozzle member is disposed adjacent the outlet of the fixed duct section. The controllable nozzle member has an area that is adjustable to maintain a substantially constant nozzle pressure ratio. The controllable nozzle member may include first and second flap doors hinged and pivotable in opposite directions between an open position and a closed position and that also may be hinged and pivotable in a same direction so thrust from gas exiting the nozzle is vectorable. When disposed in rotor tips of an aircraft capable of rotary wing flight and fixed wing flight, the variable area nozzle may maintain a substantially constant nozzle pressure ratio near an optimized nozzle pressure ratio as the aircraft transitions from rotary wing flight to fixed wing flight.
    Type: Application
    Filed: March 22, 2006
    Publication date: August 20, 2009
    Inventors: Dennis K. Kennedy, Neal W. Muylaert, William J. Bigbee-Hansen
  • Patent number: 7552895
    Abstract: The aerodynamics of a floatplane can be improved by providing a wing suitable for mounting on a spreader bar between floats of the floatplane, mounting said wing on the spreader bar between the floats of a floatplane, and preventing the wing from rotating around the spreader bar during flight operations. In one apparatus embodiment, the invention comprises a wing mountable on a spreader bar between floats of the floatplane, a plurality of ribs spaced along the wing's axis, each rib having a recess suitable for accepting the spreader bar, and torque-restraining means to prevent the wing from rotating around the spreader bar.
    Type: Grant
    Filed: October 7, 2005
    Date of Patent: June 30, 2009
    Inventor: Dave From
  • Publication number: 20090095838
    Abstract: A rotor blade assembly for providing vertical lift to an aircraft, having a rotor head and a plurality of blades, with each blade attached to a mechanism such as a cam surface, whereby movement of the mechanism causes the radial distance between the distal tip of the attached blade and the center of the rotor head to alter, decreasing or increasing the length of the lifting surface. The blades are moved from a fully extended position providing maximum lift, to a retracted position in which the blades are removed from the airstream. The pitch of the blades may be controlled by a pitch controller to achieve full helicopter responsiveness. A plurality of bladeletts may be positioned near the outer periphery of the rotor head. When they are moved into the airstream, passing air impacts the bladeletts exerting a pressure, causing rotational movement of the rotor blade assembly.
    Type: Application
    Filed: December 17, 2008
    Publication date: April 16, 2009
    Inventor: Allen J. Gerbino
  • Publication number: 20090008500
    Abstract: Radial Venturi Wing machine, apparatus for improved aircraft flight with a circular wing, a round wing, and a circular fan having its blades affixed at the perimeter of the circle as opposed to its axis. A simple demonstration of this innovation is placing a piece of paper in front of the intake side of a box type fan. The Radial Venturi Wing utilizes this principle by replacing the box around the fan with a circular wing, the paper being pulled toward the fan blade by a, round wing, fan blades by a fan disc. The fan disc draws the air over the surfaces of the two wings causing lift. Air pulled thru the gap between the wings causes a low pressure area under and over the center of the venturi wing causing lift. The downward disc fan thrust causes additional lift. Air pulled thru the gap between the wings causing a venturi effect.
    Type: Application
    Filed: July 6, 2007
    Publication date: January 8, 2009
    Inventor: Phillip Richard Barber
  • Patent number: 7441724
    Abstract: An aircraft includes a fuselage, and first and second freewings. Each of the first and second freewings is separately mounted to the fuselage and independently freely pivotable about respective pivot axes. The aircraft includes an angular rate sensor configured to measure a roll rate of the fuselage and to output a first roll rate signal. The aircraft includes a controller in communication with the angular rate sensor and configured to receive a second roll rate signal from the pilot and to compare the first and second roll rate signals to generate first and second control surface control signals. The aircraft includes at least one control actuator in communication with the controller and configured to actuate a first control surface of the first freewing and a second control surface of the second freewing in response to the first and second control surface control signals, respectively, to control the roll rate of the aircraft.
    Type: Grant
    Filed: September 19, 2005
    Date of Patent: October 28, 2008
    Assignee: Aurora Flight Sciences Corporation
    Inventor: Robert Parks
  • Patent number: 7294036
    Abstract: A circular planform wing includes a contiguous thin central plate having top and bottom surfaces. An outer annular rim encompasses the central plate. The rim has a lower edge defining a lower plane of the wing, and the central plate has an upper zone defining an upper plane of the wing. The rim has a cross-section with a lower rounded corner forming the lower edge, an outer rounded corner, and an upper corner merging with the central plate, the outer corner being located between the upper plane and the lower plane. The rim cross-section has a convex upper curve joining the outer rounded corner to the upper corner, an inside rim surface joining the lower rounded corner to the upper corner, and a convex lower curve joining the outer rounded corner to the lower rounded corner.
    Type: Grant
    Filed: February 11, 2005
    Date of Patent: November 13, 2007
    Inventor: Jonathan Potts
  • Patent number: 7246770
    Abstract: A rotatable leading edge for the fuselage and wings of an aircraft is disclosed. The leading edge may be rotated from an undeflected or retracted position adjacent to the fuselage and wings to a deflected or extended position. In the extended position, the leading edge increases lift of the aircraft at low speeds. In the retracted position, gaps associated with the leading edge are avoided.
    Type: Grant
    Filed: February 25, 2005
    Date of Patent: July 24, 2007
    Assignee: Northrop Grumman Corporation
    Inventor: Allen A. Arata
  • Patent number: 7204454
    Abstract: An articulated leading edge for the fuselage and wings of an aircraft is disclosed. The leading edge may be moved from an undeflected or retracted position adjacent to the fuselage and wings to a deflected or extended position. The leading edge includes fuselage and wing portions which are articulated with respect to each other. The fuselage portion of the leading edge may be rotated around an axis near the nose of the aircraft. When the fuselage portion is rotated, the region between the fuselage portion and wing portion of the leading edge bends and the wing portion is elevated with respect to the wing. In such an extended position, the leading edge increases lift of the aircraft at low speeds. In the retracted position, gaps associated with the leading edge are avoided.
    Type: Grant
    Filed: February 25, 2005
    Date of Patent: April 17, 2007
    Assignee: Northrop Grumman Corporation
    Inventors: Allen A. Arata, David H. Graham
  • Patent number: 7165742
    Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiralling motion without the aircraft rolling. Two fins 6 and 17 are attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The fins 6, 17 are able to rotate in a pivoting manner on the rotatable tube 3 with respect to the rotatable tube 3, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 3. Fin 6 is larger than fin 17. The difference in sizes between the fins makes the larger fin 6 exert a greater force on the rotatable tube 3 than the smaller fin 17 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus causes the rotatable tube 3 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 6, 17 would exert a lateral force on the rotatable tube 3. Thus, as well as forcing the rotatable tube 3 to rotate, the fins 6, 17 would also push the rotatable tube sideways.
    Type: Grant
    Filed: January 20, 2004
    Date of Patent: January 23, 2007
    Inventor: Tom Kusic
  • Patent number: 7131611
    Abstract: Provided is an aerodynamic body having rhomboid wings and internal torsion bars which can be twisted to affect a change in the shape of a wing. Individual or multiple swings can slide relative to the fuselage body to affect a change in sweep angle and aspect ratio. Provided is a method of controlling the aerodynamic properties, in order to affect stability and maneuvering, of an aerodynamic body by warping the wings by twisting one or more torsion bars located internal to one or more wings. Additional control can be exercized by sliding one of more wings relative to the fuselage to change the sweep angle and aspect ratio.
    Type: Grant
    Filed: July 30, 2004
    Date of Patent: November 7, 2006
    Inventor: Marty Allen Ferman
  • Patent number: 7093791
    Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiralling motion without the aircraft rolling. Two fins 6 and 17 are attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The fins 6, 17 are able to rotate in a pivoting manner on the rotatable tube 3a with respect to the rotatable tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 3a. Rotation of the rotatable tube is achieved by using an electric motor 3b turning a wheel 3c. The wheel 3c makes contact with the rotatable tube. When pitched at an angle to the longitudinal axis in unison, both fins 6, 17 would exert a lateral force on the rotatable tube 3a. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion of the aircraft when in flight. The rotation of one fin causes the rotation of another fin.
    Type: Grant
    Filed: January 23, 2004
    Date of Patent: August 22, 2006
    Inventor: Tom Kusic
  • Patent number: 7014142
    Abstract: Rotor/wing aircraft having a low-drag flap are disclosed. In one embodiment, a rotor/wing aircraft includes an elongated blade having a body portion and a flap portion. The body portion has first and second edges and includes a non-symmetric portion proximate the second edge. The flap portion is moveably coupled to the body portion proximate the second edge and is moveable between a rotary flight position and a forward flight position. In the rotary flight position, the flap portion is proximate at least part of the non-symmetric portion to form a second symmetric portion proximate the second edge. In the forward flight position, the flap portion extends away from the non-symmetric portion to form a tapered portion proximate the second edge.
    Type: Grant
    Filed: February 3, 2004
    Date of Patent: March 21, 2006
    Assignee: The Boeing Company
    Inventors: Edward Barocela, Charles N. Vaporean
  • Patent number: 6712313
    Abstract: A constant velocity drive mechanism of a rotary-wing aircraft rotor, comprises a torque splitting differential mechanism, comprising a driving disc integral in rotation with a rotor mast and connected to each of two driven discs either side of the driving disc, by a least one connecting pin hinged to each of the discs by one of three ball joint connections. Each of the driven discs is connected to a hub of the rotor by at least one of two driving devices, each of which is also hinged to the hub, so as to drive the hub in rotation about a geometrical axis which can be inclined in all directions about the axis of rotation of the mast.
    Type: Grant
    Filed: March 20, 2003
    Date of Patent: March 30, 2004
    Assignee: Eurocopter
    Inventors: Elio Zoppitelli, Eric Cornille
  • Patent number: 6708923
    Abstract: An aircraft 1 in the form of an airplane with a spiral inducing assembly 2 which is capable of inducing the airplane to travel in a continuous spiralling motion without rolling. Two fins 3 and 4 are attached to a tube 5 that is able to rotate around the encircled part of the fuselage. The fins 3, 4 are able to rotate in a pivoting manner on the rotatable tube 5 with respect to the rotatable tube 5, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 5. Fin 3 is larger than fin 4. The diferene in sizes between the fins makes the larger fin 3 exert a greater force on the rotatable tube 4 than the smaller fin 4 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus casues the rotatable tube 5 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 3, 4 would exert a lateral force on the rotatable tube 5. Thus, as well as forcing the rotatable tube 5 to rotate, the fins 3, 4 would also push the rotatable tube sideways.
    Type: Grant
    Filed: June 22, 2001
    Date of Patent: March 23, 2004
    Inventor: Tom Kusic
  • Patent number: 6669138
    Abstract: A rotary aeronautical lifting cell having an annular airfoil, airfoil dividers, and a propulsion mechanism. The airfoil dividers separate the annular airfoil into airfoil sections arranged in circular relationship. Upon rotation of the present aeronautical cell, the airfoil sections provide components of lift and propulsion to transportation vehicles attached thereto.
    Type: Grant
    Filed: January 8, 2002
    Date of Patent: December 30, 2003
    Inventor: Francisco A. Arrieta
  • Patent number: 6601795
    Abstract: An air vehicle, such as an aircraft, an unmanned air vehicle, a missile, or an aero bomb that has a fuselage and two main wings each of which has a left side wing and a right side wing. Both of the main wings are rotatably mounted on the fuselage via one or two pivots or hollow turrets so that both of them can be yawed during flight to optimize flying efficiency under various flying conditions.
    Type: Grant
    Filed: August 23, 2002
    Date of Patent: August 5, 2003
    Inventor: Zhuo Chen
  • Patent number: 6513762
    Abstract: A flap actuator system for an airfoil structure including: a flap member for controlling the airfoil structure; a bearing member interconnected with the flap member and the airfoil structure; and an actuator device for rotating the flap member about the bearing member relative to the airfoil structure; the actuator device including an electromagnetic motor segment and a drive mechanism driven by the electromagnetic motor to rotate the flap member about the axis of the bearing member relative to the airfoil structure; the electromagnetic motor being integral with the airfoil structure and the drive mechanism; the electromagnetic motor including a field circuit integral with the drive mechanism and an armature circuit integral with the airfoil structure; the field circuit located within the armature circuit.
    Type: Grant
    Filed: December 5, 2000
    Date of Patent: February 4, 2003
    Assignee: Diversified Technologies, Inc.
    Inventors: David Allan Fink, Marcel Pierre Joseph Gaudreau
  • Patent number: 6497385
    Abstract: A rotor blade has a local geometric twist angle &thgr;=ƒ(r/R), with R being the blade span and r being the distance along the blade span from the axis of rotation. The blade has an inner region between an (r/R)inner=0.20±0.04 and a transition point at (r/R)trams=0.75±0.04, wherein &thgr;inner at (r/R)inner has a positive value and is greater than or equal to &thgr;trans at (r/R)trans. A blade tip region includes a first portion between (r/R)trans and (r/R)min>(r/R)trans, wherein &thgr; continuously decreases from &thgr;trans to &thgr;min at (r/R)min, and &Dgr;&thgr;tip1=|&thgr;min−&thgr;trans|>3°, and a second portion between (r/R)min and the blade tip, wherein &thgr; continuously increases from &thgr;min to &thgr;tip at the tip, and &Dgr;&thgr;tip2=|&thgr;tip−&thgr;min| is at least about 3° and no greater than about 20°.
    Type: Grant
    Filed: November 8, 2001
    Date of Patent: December 24, 2002
    Assignee: Continuum Dynamics, Inc.
    Inventors: Daniel A. Wachspress, Todd R. Quackenbush
  • Patent number: 6457671
    Abstract: A funnel strip is added to a rotary airfoil, which utilizes the Bernoulli principle to increase the velocity of air over the suction side of the rotating airfoil to increase the lift. The device is applicable to thrust-producing devices, such as propellers, as well as to wind-powered devices.
    Type: Grant
    Filed: September 5, 2001
    Date of Patent: October 1, 2002
    Inventor: Norman Sherman