Patents by Inventor Erez Eller

Erez Eller has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 10443674
    Abstract: A method of controlling noise of an aircraft includes storing a plurality of predefined noise modes; receiving a selection of a selected noise mode from the plurality of predefined noise modes, the selected noise mode identifying at least one operational parameter; and controlling the aircraft in response to the at least one operational parameter.
    Type: Grant
    Filed: July 27, 2015
    Date of Patent: October 15, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Erez Eller, William J. Eadie, Kevin L. Bredenbeck, Steven D. Weiner
  • Patent number: 10329013
    Abstract: A method for controlling a differential rotor roll moment for a coaxial helicopter with rigid rotors, the method including receiving, with a processor, a signal indicative of a displacement command from a controller; receiving, with the processor via a sensor, one or more signals indicative of a longitudinal velocity, an angular velocity of one or more rotors and an air density ratio for the helicopter; determining, with the processor, a ganged collective mixing command in response to the receiving of the displacement command; determining, with the processor, a rotor advance ratio as a function of the longitudinal velocity and the angular velocity; and determining, with the processor, a corrective differential lateral cyclic command for the rigid rotors that controls the differential rotor roll moment to a desired value.
    Type: Grant
    Filed: September 24, 2015
    Date of Patent: June 25, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Cody Fegely, Erez Eller, Kenneth S. Wittmer, Aaron L. Greenfield, John Knag
  • Publication number: 20190084684
    Abstract: An aircraft can include an electrical energy system including at least one battery having a plurality of cells, at least one fuel tank, one or more electrical motors powered by the electrical energy system and configured to drive one or more rotors for providing vertical thrust, and at least one fluid fueled engine operatively connected to the at least one fuel tank to drive a thruster for forward propulsive force.
    Type: Application
    Filed: September 20, 2017
    Publication date: March 21, 2019
    Inventor: EREZ ELLER
  • Publication number: 20190017569
    Abstract: An aircraft includes an airframe having an empennage, a counter rotating, coaxial main rotor assembly located at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the empennage and providing translational thrust to the airframe. At least two control surfaces located at the empennage are independently operable via commands from one or more flight control computers. A method of operating an aircraft includes transmitting a first signal from one or more flight control computers to a first control surface located at a first lateral side of a translational thrust system, and actuating the first control surface to a first position via the first signal. A second signal is transmitted to a second control surface located at a second lateral side opposite the first lateral side, and the second control surface is actuated to a second position via the second signal.
    Type: Application
    Filed: June 18, 2018
    Publication date: January 17, 2019
    Inventors: Erez Eller, Matthew T. Luszcz, William J. Eadie
  • Patent number: 10099777
    Abstract: One aspect is a flight control system for a rotary wing aircraft including a main rotor system and an elevator control system. A flight control computer of the flight control system includes processing circuitry configured to execute control logic. The control logic includes an inverse plant model that produces a main rotor feed forward command based on a pitch rate command, and a load alleviation control filter configured to reduce loads on a main rotor system and produce an elevator command for an elevator control system. A transformed elevator command filter produces a main rotor pitch adjustment command based on the elevator command, and a main rotor command generator generates an augmented main rotor feed forward command for the main rotor system based on the main rotor feed forward command and the main rotor pitch adjustment command.
    Type: Grant
    Filed: April 2, 2014
    Date of Patent: October 16, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Erez Eller, Aaron L. Greenfield, Ole Wulff, Matthew A. White, Matthew T. Luszcz
  • Patent number: 10086932
    Abstract: A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer is operably connected to the one or more sensors and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: October 2, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Erez Eller, John Knag
  • Publication number: 20170349275
    Abstract: An aircraft includes an airframe having an empennage, a counter rotating, coaxial main rotor assembly located at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the empennage and providing translational thrust to the airframe. At least two control surfaces located at the empennage are independently operable via commands from one or more flight control computers. A method of operating an aircraft includes transmitting a first signal from one or more flight control computers to a first control surface located at a first lateral side of a translational thrust system, and actuating the first control surface to a first position via the first signal.
    Type: Application
    Filed: September 30, 2015
    Publication date: December 7, 2017
    Applicant: Sikorsky Aircraft Corporation
    Inventors: Erez Eller, Matthew T. Luszcz, William J. Eadie
  • Publication number: 20170334556
    Abstract: A method for controlling a differential rotor roll moment for a coaxial helicopter with rigid rotors, the method including receiving, with a processor, a signal indicative of a displacement command from a controller; receiving, with the processor via a sensor, one or more signals indicative of a longitudinal velocity, an angular velocity of one or more rotors and an air density ratio for the helicopter; determining, with the processor, a ganged collective mixing command in response to the receiving of the displacement command; determining, with the processor, a rotor advance ratio as a function of the longitudinal velocity and the angular velocity; and determining, with the processor, a corrective differential lateral cyclic command for the rigid rotors that controls the differential rotor roll moment to a desired value.
    Type: Application
    Filed: September 24, 2015
    Publication date: November 23, 2017
    Inventors: Cody Fegely, Erez Eller, Kenneth S. Wittmer, Aaron L. Greenfield, John Knag
  • Publication number: 20170308101
    Abstract: An aircraft includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the air-frame; and a horizontal stabilizer positioned at the extending tail, the horizontal stabilizer having one or more elevators; wherein the aircraft is configured to mix at least two of the main rotor assembly collective pitch, the main rotor assembly cyclic pitch, the elevator deflection, and the translational thrust system thrust to trim the aircraft attitude.
    Type: Application
    Filed: September 30, 2015
    Publication date: October 26, 2017
    Inventors: Matthew T. Luszcz, William J. Eadie, Erez Eller, Adam Leone
  • Publication number: 20170305540
    Abstract: A method of controlling noise of an aircraft includes storing a plurality of predefined noise modes; receiving a selection of a selected noise mode from the plurality of predefined noise modes, the selected noise mode identifying at least one operational parameter; and controlling the aircraft in response to the at least one operational parameter.
    Type: Application
    Filed: July 27, 2015
    Publication date: October 26, 2017
    Inventors: Erez Eller, William J. Eadie, Kevin L. Bredenbeck, Steven D. Weiner
  • Publication number: 20170291702
    Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A horizontal stabilizer with a left elevator and right elevator positioned at the extending tail. A flight control computer to independently control one or more of the main rotor assembly and the elevator through a fly-by-wire control system. The flight control computer is configured to mix a collective pitch of the main rotor assembly and a deflection of the elevator.
    Type: Application
    Filed: September 29, 2015
    Publication date: October 12, 2017
    Inventors: Erez Eller, Matthew A. White, Matthew T. Luszcz
  • Publication number: 20170283045
    Abstract: An aircraft is provided including an airframe, an extending tail, one or more engines supported by the airframe, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail. The translational thrust system providing translational thrust to the airframe. A gearbox configured to transfer power from the engine to the main rotor assembly. A flight control computer to independently control one or more of the engine, the upper rotor assembly, the lower rotor assembly, and the translational thrust system. The flight control computer, in response to at least one control command, engages or disengages the translational thrust system, while maintaining controlled powered flight.
    Type: Application
    Filed: September 28, 2015
    Publication date: October 5, 2017
    Inventors: Todd A. GARCIA, Erez ELLER, William J. EADIE, David H. HUNTER
  • Publication number: 20170277201
    Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. The main rotor assembly and the translational thrust system are configured to provide hover nose down, hover nose up and hover level modes of flight.
    Type: Application
    Filed: September 24, 2015
    Publication date: September 28, 2017
    Inventors: Kevin L. BREDENBECK, Steven D. WEINER, Erez ELLER, Matthew T. LUSZCZ
  • Publication number: 20170274987
    Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A cockpit in the airframe, the cockpit including two seats and a single collective control input positioned between the two seats.
    Type: Application
    Filed: September 30, 2015
    Publication date: September 28, 2017
    Inventors: Kevin L. BREDENBECK, William FELL, Erez ELLER
  • Publication number: 20170274994
    Abstract: An aircraft is provided including an airframe, an extending tail, a counter-rotating, coaxial main rotor assembly having an upper rotor assembly and a lower rotor assembly, and a translational thrust system including a propeller positioned at the extending tail. The translational thrust system is configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state and to generate power when in an autorotation state. A gearbox interconnects the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state. When the aircraft is in autorotation, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.
    Type: Application
    Filed: September 25, 2015
    Publication date: September 28, 2017
    Inventors: Erez Eller, Matthew T. Luszcz, William J. Eadie, Steven D. Weiner
  • Publication number: 20170233068
    Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly composed of a plurality of blades and a lower rotor assembly composed of a plurality of blades. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A flight control system to control the upper rotor assembly and the lower rotor assembly, wherein the flight control system is configured to control lift offset of the upper rotor assembly and the lower rotor assembly.
    Type: Application
    Filed: September 30, 2015
    Publication date: August 17, 2017
    Inventors: Erez Eller, Matthew T. Luszcz, Kenneth C. Arifian, Kevin L. Bredenbeck, Bryan S. Cotton
  • Publication number: 20170217582
    Abstract: An aircraft is provided and includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.
    Type: Application
    Filed: September 29, 2015
    Publication date: August 3, 2017
    Inventors: Kevin L. BREDENBECK, Bryan S. COTTON, Kenneth C. ARIFIAN, Erez ELLER, Matthew T. LUSZCZ
  • Publication number: 20170113790
    Abstract: A rotary-wing aircraft includes an airframe, a first rotor assembly configured to rotate about an axis and a first fairing disposed between the airframe and the first rotor assembly. A sensory system of the rotary-wing aircraft is supported by the first fairing.
    Type: Application
    Filed: October 18, 2016
    Publication date: April 27, 2017
    Inventors: Daniel Bazzani, Erez Eller, Peter J. Germanowski
  • Publication number: 20170029093
    Abstract: One aspect is a flight control system for a rotary wing aircraft including a main rotor system and an elevator control system. A flight control computer of the flight control system includes processing circuitry configured to execute control logic. The control logic includes an inverse plant model that produces a main rotor feed forward command based on a pitch rate command, and a load alleviation control filter configured to reduce loads on a main rotor system and produce an elevator command for an elevator control system. A transformed elevator command filter produces a main rotor pitch adjustment command based on the elevator command, and a main rotor command generator generates an augmented main rotor feed forward command for the main rotor system based on the main rotor feed forward command and the main rotor pitch adjustment command.
    Type: Application
    Filed: April 2, 2014
    Publication date: February 2, 2017
    Applicant: Sikorsky Aircraft Corporation
    Inventors: Erez Eller, Aaron L. Greenfield, Ole Wulff, Matthew A. White, Matthew T. Luszcz
  • Patent number: 9501062
    Abstract: Disclosed is a rotorcraft including a plurality of blades, and a control computer configured to obtain a blade bending measurement from a sensor associated with a one of the plurality of blades, process, by a device comprising a processor, the blade bending measurement to obtain moment data for the rotorcraft, obtain data from an inertial measurement unit (IMU), wherein the data obtained from the IMU pertains to at least one of a pitch of the aircraft and an angular rate, and process, by the device, the moment data and the data from the IMU to generate a command configured to stabilize the aircraft, wherein the command is based on a reference input, and wherein the reference input is based on at least one input provided by a pilot of the aircraft.
    Type: Grant
    Filed: March 21, 2016
    Date of Patent: November 22, 2016
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Erez Eller, Ole Wulff