Aircraft Propulsion Patents (Class 244/62)
  • Patent number: 10968833
    Abstract: A gas turbine engine arrangement includes an accessory gearbox which is mounted so as to be aligned in an axial direction along the engine. The accessory gearbox may be recessed at least partly into a casing of the engine.
    Type: Grant
    Filed: October 2, 2017
    Date of Patent: April 6, 2021
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Uwe Minkus
  • Patent number: 10906643
    Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.
    Type: Grant
    Filed: July 22, 2019
    Date of Patent: February 2, 2021
    Assignee: AUTEL ROBOTICS CO., LTD.
    Inventors: Dongdong Luo, Feng Ni, Hang Lv, Wenbing Su
  • Patent number: 10766627
    Abstract: According to the present invention there is provided an aerial vehicle that is operable to fly, the aerial vehicle having at least a first and second subsystem that are operably connected, wherein the first subsystem comprises a first flight module, first one or more effectors that are selectively operable to generate a first force sufficient to cause the aerial vehicle to fly; and the second subsystem comprises a second flight module, second one or more effectors that are selectively operable to generate a second force sufficient to cause the aerial vehicle to fly; such that the first or second subsystem can be selectively used to fly the aerial vehicle not relying on the one or more effectors of the other subsystem. There is further provided a corresponding method for controlling an aerial vehicle.
    Type: Grant
    Filed: May 27, 2016
    Date of Patent: September 8, 2020
    Assignee: Verity Studios AG
    Inventors: Markus Hehn, Markus Waibel, Luca Gherardi, Raffaello D'Andrea
  • Patent number: 10618633
    Abstract: A counter rotating propeller system comprises a structure configured to control the front propeller outer slipstream and prop wash. Specifically disclosed is a structure configured to vary the effective hub-tip radius ratio of the rear propeller.
    Type: Grant
    Filed: July 27, 2016
    Date of Patent: April 14, 2020
    Inventor: Richard P. Johnston
  • Patent number: 10526067
    Abstract: The invention relates to a propeller ring (10) of a turbomachine (1), with variable-pitch blades (P), the propeller ring (10) comprising a substantially coaxial annular body (11) with a main axis (A) and a plurality of radial housings (12) uniformly distributed around the main axis (A), each radial housing (12) being designed to receive a bearing (13) for a root (14) of a blade (P) so as to allow the variable pitch of the blade (P), the radial housings (12) having a substantially ovoid cross-section in a plane (T) tangential to the annular body (11).
    Type: Grant
    Filed: October 30, 2015
    Date of Patent: January 7, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sebastien Emile Philippe Tajan, Charles-Henri Michel Marie Derrez, Anthony Lafitte, Cyril Roger Yves Le Pecheur
  • Patent number: 10486811
    Abstract: The present invention extends to methods, systems, devices, and apparatus for remotely operated aerial vehicle with reduced cross-section area during forward flight. In one aspect, a remotely operated aerial vehicle is a rotor based Unmanned Aerial Vehicle (UAV) having a plurality of rotors. A remotely operated aerial vehicle includes a frame, a power source, a plurality of motors, and a corresponding plurality of fixed rotors. The frame includes a top surface. Each fixed rotor in the plurality of fixed rotors is mounted to a corresponding motor from among the plurality of motors. The corresponding motor controls the rotation of the fixed rotor. Each of the plurality of fixed rotors is mounted at a specified angle relative to the top surface. Mounting the fixed rotors at the specified angle minimizes the cross-sectional area of the frame when the remotely operated aerial vehicle flies in a specified direction.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: November 26, 2019
    Assignee: Olaeris, Inc.
    Inventor: Paul E. I. Pounds
  • Patent number: 10407171
    Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.
    Type: Grant
    Filed: March 1, 2019
    Date of Patent: September 10, 2019
    Assignee: AUTEL ROBOTICS CO., LTD.
    Inventors: Dongdong Luo, Feng Ni, Hang Lv, Wenbing Su
  • Patent number: 10266264
    Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.
    Type: Grant
    Filed: June 8, 2018
    Date of Patent: April 23, 2019
    Assignee: AUTEL ROBOTICS CO., LTD.
    Inventors: Dongdong Luo, Feng Ni, Hang Lv, Wenbing Su
  • Patent number: 9843250
    Abstract: An Electro Hydro Dynamic, EHD, thruster (105) comprising a first set of electrodes (210), a second set of electrodes (220) and a supporting structure (103) for supporting the first set of electrodes (210) and the second set of electrodes (220). The EHD thruster (105) is configured to generate airflow of ionized air for cooling a heat sink (101). Further, the EHD thruster (105) is electrically isolated from the heat sink (101).
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: December 12, 2017
    Assignee: Huawei Technologies Co., Ltd.
    Inventors: Vadim Tsoi, Yake Fang
  • Patent number: 9481904
    Abstract: Electrokinetic methods are described with the purpose of collecting assayable agents directed by creation of an electrokinetic potential well. Environmental agents such as biowarfare agents, pathogens, allergens or pollutants are collected autonomously. The dielectric fluid medium, such as air, is sampled by electrokinetic propulsion. A further embodiment for collection of pathogen samples entails exposing the sample to an electric plasma in the neighborhood of a high voltage electrode or electrodes, further transported through a potential well created at a sample collection device conductive liquids, such as oils may be sampled for the presence of contaminants, contaminating organisms or bio-degrading organisms.
    Type: Grant
    Filed: January 23, 2013
    Date of Patent: November 1, 2016
    Assignee: Inspirotec, Inc.
    Inventors: Julian Gordon, Prasanthi Gandhi
  • Patent number: 9287840
    Abstract: A method of producing accelerations without ejecting any material exhaust which relies on inducing mass fluctuations in conventional electrical circuit components and combining them with a mechanically coupled periodic thrust to produce propulsive forces without the ejection of any propellant. Ferroelectric force transducers, in particular, piezoelectric transducers, are driven by at least two phase-locked voltage waveforms so that the rest mass fluctuation and mechanical excursion needed to produce a stationary thrust are both produced in the transducer itself. Parametric amplification is used to achieve high amplitude, correctly phase-locked voltages of correct frequencies to activate the transducer by the simple addition of a DC voltage to the AC voltage of a single frequency driving signal. The driving voltage waveforms may be pulsed to maximize the thrust and reduce the duty cycle of the active components of the system.
    Type: Grant
    Filed: September 2, 2014
    Date of Patent: March 15, 2016
    Assignee: Space Studies Institute
    Inventor: James F. Woodward
  • Publication number: 20150144742
    Abstract: An aircraft (40). The aircraft (40) comprises a propulsion system comprising a pair of internal combustion engines (10) each driving an electrical power generator (56), each electrical power generator (56) being electrically coupled to a plurality of electrically driven propulsors (46). The propulsors (46) are located forward of a leading edge (45) of the wings (44) such that an airstream generated by the propulsors flows over the wings (44) in use. Each internal combustion engine (10) and electrical generator (56) is mounted on a respective wing (44) outboard of a centre of thrust (70) of the propulsors (46) on that wing (44).
    Type: Application
    Filed: November 10, 2014
    Publication date: May 28, 2015
    Inventor: Matthew MOXON
  • Publication number: 20140367510
    Abstract: An aircraft with an electric propulsion arrangement which includes a fuselage, a wing system attached to the fuselage, and a tail unit attached to a rear part of the fuselage. The electric propulsion arrangement is arranged on each side of the fuselage, an electrical energy generator and electricity storage and supply devices are arranged substantially along a longitudinal axis of symmetry of the fuselage. The aircraft thus incorporates a hybrid motorization.
    Type: Application
    Filed: June 13, 2014
    Publication date: December 18, 2014
    Inventors: Stéphane Viala, Jason Zaneboni, Bruno Saint-Jalmes
  • Patent number: 8899516
    Abstract: A landing gear for an aircraft has a pair of spaced wheels, and a drive and steering arrangement operable to drive each of the wheels in either rotational direction. The drive and steering arrangement includes two permanent magnet rotors, with each of the permanent magnet rotors connected to rotate with one of the wheels. A single stator is positioned to drive both of the rotors. The drive and steering arrangement is mounted between the pair of wheels.
    Type: Grant
    Filed: April 5, 2012
    Date of Patent: December 2, 2014
    Assignee: JHamilton Sundstrand Corporation
    Inventors: Lubomir A. Ribarov, Jacek F. Gieras
  • Publication number: 20140061376
    Abstract: A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.
    Type: Application
    Filed: November 26, 2012
    Publication date: March 6, 2014
    Applicant: AeroVironment Inc
    Inventor: AeroVironment Inc
  • Patent number: 8662441
    Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.
    Type: Grant
    Filed: February 7, 2012
    Date of Patent: March 4, 2014
    Assignee: Sparton Corporation
    Inventors: David Powell, Earl Mark, John T. Houck, Keith Huber
  • Patent number: 8615335
    Abstract: A method is presented for controlling thrust generated by aircraft engines. Engine thrust is controlled based on aircraft groundspeed and airspeed during the initial part of takeoff. Limiting thrust at low groundspeed during the initial phase of takeoff has significant benefits that reduce engine stress during this brief but critical phase leading to flight. Logical elements combine both groundspeed and airspeed in such a way that the operator perceives a smooth progressive thrust increase consistent with normal engine operation.
    Type: Grant
    Filed: September 17, 2008
    Date of Patent: December 24, 2013
    Assignee: The Boeing Company
    Inventors: Lyle M. Couey, Keith D. Parsons
  • Patent number: 8511613
    Abstract: An aircraft comprises an airframe, an electric propulsion system, a number of battery pods, and an engagement system. The number of battery pods has a physical connector system. The engagement system is attached to the airframe and is capable of engaging the physical connector system to connect the number of battery pods to the airframe.
    Type: Grant
    Filed: June 15, 2012
    Date of Patent: August 20, 2013
    Assignee: The Boeing Company
    Inventor: Christopher K. Droney
  • Patent number: 8393580
    Abstract: An aircraft comprises an airframe, an electric propulsion system, a number of battery pods, and an engagement system. The number of battery pods has a physical connector system. The engagement system is attached to the airframe and is capable of engaging the physical connector system to connect the number of battery pods to the airframe.
    Type: Grant
    Filed: September 12, 2008
    Date of Patent: March 12, 2013
    Assignee: The Boeing Company
    Inventor: Christopher K. Droney
  • Publication number: 20130020433
    Abstract: A system and methods for reducing flow field velocity into a propeller is disclosed. An aerodynamic structure is enhanced to provide a reduced velocity flow field region, and a propeller is positioned in the reduced velocity flow field region.
    Type: Application
    Filed: July 24, 2011
    Publication date: January 24, 2013
    Inventor: Zachary C. Hoisington
  • Patent number: 8356774
    Abstract: Flexible and resilient masts are connected by flexible and resilient inner and outer spars, and flexible cords radially connect the spars. A flexible material is attached to the cords. The assembly is wrapped around a rotatable cylindrical drum in the structure's stored configuration. Each mast is flexible only about an axis lying parallel to the axis of rotation of the drum, and is otherwise rigid. Each mast is linear when extended and has a bending stress when deformed into a non-linear configuration, such as when wrapped around the drum. When the structure is in its stored configuration, a restraining device opposes the bending stress and another prevents the drum from rotating. Upon disengagement of the restraining devices, the stored bending strain energy forces the drum to rotate and the masts to extend into the deployed configuration and thereby unfurl the flexible material.
    Type: Grant
    Filed: April 21, 2008
    Date of Patent: January 22, 2013
    Assignee: The United States of America as Represented by the Secretary of the Air Force
    Inventors: Jeremy A. Banik, Thomas W. Murphey
  • Patent number: 8321119
    Abstract: A method for assembling a gas turbine engine to prevent rotor over-speeding is described. The method includes serially coupling a first fuel system interface to a second fuel system interface, such that at least one of the first fuel system interface and the second fuel system interface is coupled to the gas turbine engine. The method also includes coupling a control system to the first fuel system interface and to the second fuel system interface. The control system is configured to identify an occurrence of an over-speed condition. The method also includes programming the control system to discontinue fuel flow to the engine when both the first fuel system interface and the second fuel system interface indicate an over-speed condition has occurred.
    Type: Grant
    Filed: July 10, 2008
    Date of Patent: November 27, 2012
    Assignee: General Electric Company
    Inventors: David R. Van Vactor, Bertram S. Noyes, Jr.
  • Publication number: 20120160958
    Abstract: A vehicle is described having an engine to provide motive transportation and a work producing device used to provide power and thermal conditioning to a payload aboard the vehicle. In one form the work producing device provides power to the payload separate from a network powered by the engine that provides motive transportation. The payload can be a directed energy device in one embodiment. The vehicle can take the form of an aircraft which can be configured to receive the work producing device in a cargo bay/payload bay and/or a pod.
    Type: Application
    Filed: December 22, 2011
    Publication date: June 28, 2012
    Inventor: Gregory D. Stewart
  • Patent number: 8180341
    Abstract: A communication system for supporting communications with a target market area. The system includes one or more solar-powered aircraft maintained in, or successively passing through, flight stations or flight patterns around the market area. Each of the aircraft targets limited beamwidth communication antennas on a substantial portion of the target market area. The control system is configured to fly selective flight patterns depending on the aircraft characteristics and the flight conditions. The flight patterns may emphasize high-power-generation patterns such as flying away from the sun for aircraft with wing-mounted solar cells.
    Type: Grant
    Filed: April 30, 2009
    Date of Patent: May 15, 2012
    Assignee: AeroVironment Inc.
    Inventors: Bart D. Hibbs, Earl C. Cox
  • Publication number: 20120018571
    Abstract: A solar-powered airship with a hull configured to contain a gas and at least one propulsion assembly with a propulsion device and electric motors configured to drive the propulsion device. The airship may also include a power supply system including solar panels operatively coupled to the electric motors and configured to supply power to the electric motors. The power supply system may also include batteries operatively coupled to the solar panels and configured to receive and store electrical energy supplied by the solar panels, the batteries being further operatively coupled to the electric motors and configured to supply power to the electric motors. The batteries may each be located within an outer envelope of the airship defined by the hull of the airship in a position selected to provide ballast. The solar-powered airship may also include a cargo system configured to contain passengers or freight.
    Type: Application
    Filed: July 14, 2011
    Publication date: January 26, 2012
    Inventor: John Goelet
  • Patent number: 7886544
    Abstract: A propeller or propeller drive, the propeller being carried by a support shaft (3) which projects from the body (53) of the missile or vehicle and about which the propeller rotates, the drive unit for the propeller being situated in front of the propeller (23) in the propulsion direction or in the propeller spinner (1). According to the invention it is provided that the drive unit has at least one gas turbine (55), optionally a multiple-stage gas turbine, which is secured to the drive shaft and which drives it or jointly rotates with it, and that the drive shaft (6) is traversed by the support shaft (3) or is mounted thereon in a rotating manner and drives the propeller (23), optionally by way of a gear mechanism (14) situated between the turbine (55) and the propeller (23).
    Type: Grant
    Filed: April 24, 2006
    Date of Patent: February 15, 2011
    Inventor: Christian Koenig
  • Publication number: 20100294881
    Abstract: The invention relates to an electrolysis system. Said system can be utilized in a nuclear fusion process, on roof of a ferromagnetic aircraft in preferred embodiment. Said electrolysis system will utilize electric energy produced by said aircraft at no cost. Said energy will be provided to an array of electrodes to electrolyze water or seawater to produce protons and electrons, and with B-11 isotope ions, vaporized out of source on board craft, a fusion spherical plasma can be produced on roof of said aircraft, for a nuclear fusion reaction. Stored energy produced by electrolysis system, can also be used for other purposes. Said fusion spherical plasma is produced at essentially no cost, other than cost of electrolysis system and aircraft. Three aircraft will be utilized in preferred embodiment, all three craft utilizing an electrolysis system, though only one craft, the ferromagnetic craft alone, producing the B-11 isotope ion.
    Type: Application
    Filed: March 19, 2010
    Publication date: November 25, 2010
    Inventor: Gary Richard Gochnour
  • Patent number: 7825359
    Abstract: An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.
    Type: Grant
    Filed: July 17, 2009
    Date of Patent: November 2, 2010
    Inventor: Tom Kusic
  • Patent number: 7812294
    Abstract: An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.
    Type: Grant
    Filed: July 20, 2009
    Date of Patent: October 12, 2010
    Inventor: Tom Kusic
  • Publication number: 20100243796
    Abstract: This invention relates to a plasma gun utilized in a plasma based aircraft maintained in a flight mode by rotating plasma vortices located above and beneath said aircraft. Plasma produced by aircraft is utilized by said plasma gun to facilitate initial take off of craft, and also to accelerate aircraft speed, or, within an emergency, as needed. Said aircraft can also eject plasma through aircraft central shaft or within any direction from sides of said craft, for escape, evasion or normal accelerated flight. Preferred embodiment for said plasma gun, is a coaxial plasma gun, utilizing the large capacitance potential of aircraft, the large supply of aircraft produced plasma off said capacitors, or from uninsulated conducting wires, and also utilizing the strong Lorentz force existing within craft. The plasma produced by ionization within craft strong magnetic field, will enable this craft to rapidly avoid impediments to flight, or oncoming dangers.
    Type: Application
    Filed: March 19, 2010
    Publication date: September 30, 2010
    Inventor: Gary Richard Gochnour
  • Publication number: 20100206982
    Abstract: An air vehicle propulsion system incorporates an engine core with a power shaft to drive an outer blade row. The power shaft is extends through and is supported by a counter rotation transmission unit which drives an inner blade row in counter rotational motion to the outer blade row. The counter rotation transmission unit exchanges power from the engine core with the shaft. An actuator engages the shaft for translation from a first retracted position to a second extended position.
    Type: Application
    Filed: February 13, 2009
    Publication date: August 19, 2010
    Applicant: THE BOEING COMPANY
    Inventors: Matthew D. Moore, Kelly L. Boren, Robin B. Langtry
  • Publication number: 20100176248
    Abstract: A propulsion method employing gyroscopes (1,2) with electric motors (4) which are being moved along a closed path in the spacecraft. Rotation axis of the gyroscopes are rotated periodically relative to movement direction so that gyroscopic effect is only obtained during movement in one direction. Thereby a gyroscopic resistance difference is obtained and used as a propulsion force. Another application is to use gyroscopes connected to generators in order to decelerate a spacecraft, transforming the moment created in gyroscope during deceleration into the electrical energy, distribute it to the space as heat transfer by means of radiation through the heat resistant panels.
    Type: Application
    Filed: September 28, 2008
    Publication date: July 15, 2010
    Inventor: Mehmet Terziakin
  • Publication number: 20100147998
    Abstract: An apparatus and method for transmitting a rotary input into counter-rotating outputs is disclosed herein. An exemplary apparatus for performing the method includes a planetary gear set having a sun gear rotatable by a rotary input, a plurality of planet gears in meshed engagement with the sun gear, a carrier coupling the plurality of planet gears together, and a ring gear encircling and in meshed engagement with the plurality of planet gears. The exemplary apparatus also includes a first shaft member coupled to the carrier for transmitting motion in a first rotational direction. The exemplary apparatus also includes a second shaft member coupled to the ring gear for transmitting motion in a second rotational direction opposite the first rotational direction. The first shaft member at least partially encircles the second shaft member.
    Type: Application
    Filed: March 18, 2009
    Publication date: June 17, 2010
    Inventors: DANIEL K. VETTERS, Robert W. Cedoz
  • Patent number: 7735601
    Abstract: In order to provide noise suppression, bumps or undulations are provided on a nozzle surface in order to vary the convergent-divergent ratio between that surface and an opposed nozzle surface. By such an approach, a circumferential variation in the shock cell pattern is created and the flow is deflected so as to enhance turbulent mixing thereby suppressing noise.
    Type: Grant
    Filed: March 3, 2006
    Date of Patent: June 15, 2010
    Assignee: Rolls-Royce PLC
    Inventors: Rory D. Stieger, Kevin M. Britchford, Paul J. R. Strange
  • Publication number: 20100116927
    Abstract: The present invention pertains to a solar cell module comprising at least one photovoltaic element encapsulated between a front layer on its light receiving surface side and a back layer, said front layer comprising at least one layer comprising a tetrafluoroethylene (TFE) polymer [polymer (F)], said polymer (F) comprising: recurring units derived from TFE; and from 15 to 25% wt of recurring units derived from at least one perfluoromonomer [monomer (CM)] chosen among: (i) perfluoroalkylvinylethers complying with formula CF2?CFORf1, in which Rf1 is a C1-C6 perfluoroalkyl, e.g. —CF3, —C2F5, —C3F7; and/or (ii) perfluoro-oxyalkylvinylethers complying with formula CF2?CFOX0, in which X0 is a C1-C12 perfluorooxyalkyl having one or more ether groups, like perfluoro-2-propoxy-propyl; and (iii) mixtures thereof. Still objects of the invention are a process for the manufacture of the solar cell module as above defined and its use for producing current to external sources, e.g. for powering a fixed-wing aircraft.
    Type: Application
    Filed: April 4, 2008
    Publication date: May 13, 2010
    Applicant: SOLVAY SOLEXIS S.P.A.
    Inventors: Paolo Toniolo, Padmanabhan Srinivasan, Alessio Marrani, Giambattista Besana, Vincenzo Arcella
  • Publication number: 20100090057
    Abstract: An apparatus which exhibits properties allowing it to levitate and travel utilizing magnetic energy.
    Type: Application
    Filed: October 15, 2008
    Publication date: April 15, 2010
    Inventor: Regina B. Liska
  • Publication number: 20100059624
    Abstract: An aircraft including a longitudinal fuselage, at least two lateral wings connected symmetrically one on each side of the fuselage and at least one engine pod fixed to each lateral wing via an engine support pylon. At least one profiled bearing rod is positioned on each of the engine support pylons so as to generate a propulsive resultant force under action of an oblique air flow.
    Type: Application
    Filed: May 11, 2007
    Publication date: March 11, 2010
    Applicant: AIRBUS FRANCE
    Inventors: Thierry Fol, Majorie Defos
  • Publication number: 20100051755
    Abstract: An exemplary embodiment of the present invention sets forth an exemplary bi-plane air vehicle. The air vehicle may include, a plurality of wings coupled to one another in substantially a box configuration, wherein the bi-plane air vehicle has no tail.
    Type: Application
    Filed: August 26, 2008
    Publication date: March 4, 2010
    Applicant: DarkStar LLC
    Inventors: David C. Nichols, Robert Nichols
  • Patent number: 7665689
    Abstract: Integrated propulsion systems and methods for blended wing aircraft are disclosed. In one embodiment, a propulsion system at least one engine operatively disposed within an engine flow duct having an engine inlet and an engine exhaust aperture, and at least one fan operatively disposed within a fan flow duct having a fan inlet and a fan exhaust aperture. The engine and fan rotational axes extending at least approximately along a lengthwise direction of the aircraft, the fan flow duct being separate from the engine flow duct. A transmission assembly is operatively coupled between the at least one engine and the at least one fan, the transmission assembly being configured to transmit a rotary output from the at least one engine to rotate the at least one fan.
    Type: Grant
    Filed: November 24, 2006
    Date of Patent: February 23, 2010
    Assignee: The Boeing Company
    Inventor: James G. McComb
  • Publication number: 20100001143
    Abstract: A flying craft has an aerodynamic aircraft fuselage structure preferably disc shaped. A pair of coaxial electrokinetic motor-generators are mounted concentrically, and preferably centered within the disc shaped structure of the craft. Each of the motors is toroidal in configuration, providing a ring-shaped stator and rotor portions. The rotor portions of the motors drive counter rotating fans which are electro-magnetically levitated. The structure is open to the fans so that air may be drawn into the structure and expelled downward providing vertical lift to the aircraft. By use of auxiliary air braking flaps and electrokinetic thrusters, the craft may be tilted so as to develop a desired horizontal thrust. By impulse breaking one of the fans through tracking solenoids at different points around the stator, the aircraft may be made to rotate about its own vertical axis for changing direction. By a series of sudden braking of the motors the craft may be made to move by inertial reaction.
    Type: Application
    Filed: August 8, 2008
    Publication date: January 7, 2010
    Inventor: Dumitru Bojiuc
  • Patent number: 7642491
    Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is smaller than another ramjet on the right side of the tube 3. The difference in size between the ramjets makes the ramjet 6b exert a weaker force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. A fin 6c is also able to cause the rotate-able tube 3 to rotate during flight. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.
    Type: Grant
    Filed: March 19, 2007
    Date of Patent: January 5, 2010
    Inventor: Tom Kusic
  • Patent number: 7637453
    Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.
    Type: Grant
    Filed: November 29, 2006
    Date of Patent: December 29, 2009
    Inventor: Tom Kusic
  • Patent number: 7635104
    Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3a with respect to the rotate-able tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3a. Ramjet 6b is rotated as is another ramjet on the right side of the tube 3a. The rotate-able tube 3a is rotated by means of an electric motor 3b rotating a wheel 3c. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3a than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3a to rotate.
    Type: Grant
    Filed: November 20, 2006
    Date of Patent: December 22, 2009
    Inventor: Tom Kusic
  • Publication number: 20090294582
    Abstract: A lighter-than-air aircraft is propelled via a bending-rotating tail whip. Two actuating areas located on opposite sides in a rear area of a lifting gas body are shortened by activated actuators. A vertical plane of symmetry of the lifting gas body and thus, the lifting gas body itself, are pivoted in an area of bending zones about angles a and ?. An activated state exists when the actuator performs work for propelling the aircraft. Propulsion can be provided by deformation of the lifting gas body. Changes in direction can also be effected by asymmetrical sequences of movements.
    Type: Application
    Filed: April 7, 2006
    Publication date: December 3, 2009
    Inventors: Silvain Michel, Gabor Kovacs, Patrick Lochmatter
  • Patent number: 7624942
    Abstract: An engine system for an aircraft capable of operating in a helicopter-type flight mode and a fixed-wing flight mode and is capable of transitioning between those flight modes while in-flight includes first and second engines, and a ducting assembly. The ducting assembly includes a first exhaust subassembly in fluid communication with the first engine and a second exhaust subassembly in fluid communication with the second engine. The first exhaust subassembly permits fluid transfer substantially independent of fluid transfer within the second exhaust subassembly.
    Type: Grant
    Filed: June 20, 2006
    Date of Patent: December 1, 2009
    Assignee: United Technologies Corporation
    Inventor: Gary D. Roberge
  • Patent number: 7549603
    Abstract: Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing in their side walls 22,28 gas injection slits 23,30 oriented in oblique directions 24,26 relative to the gas stream 11, and controlled means for the adjustable closure of these slits 23,30.
    Type: Grant
    Filed: March 23, 2006
    Date of Patent: June 23, 2009
    Assignee: SNECMA
    Inventors: Bruno Albert Beutin, Jeremy Edmond Fert
  • Publication number: 20090127383
    Abstract: The invention relates to a plasma based aircraft possessing a magnetic field, and, a huge plasma vortex. Said craft is tubular in shape. Said craft has a vast array of capacitors. The craft has a proton accelerator, plasma guns, diversion devices. Said craft will approach the speed of light. Said craft obtains fuel direct from an atmosphere or a radiation produced atmosphere in space, at no cost. This craft can travel to a g k star for only the cost of construction of craft. This invention is comparable to the discovery of fire insofar as man's future is concerned, particularly in view of our climate change, and a recent near impact from an asteroid—which would have put us within an ice age. The craft has three on-board escape craft. The craft is capable of producing plasma vortices within an electromagnetic field approaching the speed of light. Said field is an inhomogeneous, diamagnetic, orbiting plasma field with a magnetohydrodynamic electrically conducting plasma current.
    Type: Application
    Filed: November 14, 2008
    Publication date: May 21, 2009
    Inventor: Gary Gochnour
  • Publication number: 20090072084
    Abstract: The present invention describes lighter-than-air vehicles. An exemplary embodiment of the present invention provides a lighter-than-air vehicle having a payload module, the payload module including an engine. Furthermore, the lighter-than-air vehicle includes a non-rigid envelope in communication with the payload module. The lighter-than-air vehicle also provides a propulsion system that includes a plurality of thrusters, the thrusters positioned substantially near the equatorial plane of the non-rigid envelope. In an alternative exemplary embodiment, the present invention provides a lighter-than-air vehicle comprising a payload module and a non-rigid envelope in communication with the payload module. Furthermore, the lighter-than-air vehicle includes a hydraulic propulsion system in communication with the non-rigid envelope and the payload module.
    Type: Application
    Filed: September 19, 2008
    Publication date: March 19, 2009
    Applicant: Blackwater Airships, LLC
    Inventor: Richard Hankinson
  • Publication number: 20090026309
    Abstract: The invention relates to an aircraft having a first propulsion unit with an air inlet above the fuselage of the aircraft and a second propulsion unit with an air inlet below the fuselage of the aircraft, the fuselage of the aircraft having recesses for receiving the propulsion units which are arranged such that the first and the second propulsion unit are arranged above one another in the plane set by the longitudinal and vertical axis of the aircraft. The propulsion unit comprises an engine, a housing having an air inlet, devices for the releasable fastening of the propulsion unit to the fuselage of the aircraft as well as devices for establishing a releasable connection of electric supply and data lines as well as fuel lines between the propulsion unit and the fuselage of an aircraft.
    Type: Application
    Filed: March 27, 2008
    Publication date: January 29, 2009
    Applicant: EADS Deutschland GmbH
    Inventor: Michael SCHWARZ
  • Publication number: 20070295010
    Abstract: A device for producing a net force against a base comprising a mass change object, an accelerator, a power source operatively connected to the mass change object and configured to selectively apply to the mass change object (1) a mass-increasing waveform, characterized in that the time rate of change of the power of the mass-increasing waveform is positive, and (2) a mass-decreasing waveform, characterized in that the time rate of change of the power of the mass-decreasing waveform is negative; the power source being configured to apply the mass-increasing waveform to the mass change object when the acceleration of the mass change object has at least a component opposite to the net force direction, and to apply the mass-decreasing waveform to the mass change object when the acceleration of mass change object has at least a component in the net force direction; wherein the mass-increasing waveform is a different waveform, as a function of time, than the mass decreasing waveform.
    Type: Application
    Filed: January 31, 2007
    Publication date: December 27, 2007
    Applicant: Varim Technologies Inc.
    Inventor: Malcolm B. Stephens