Patents by Inventor Paul Eglin

Paul Eglin 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: 11794886
    Abstract: A rotorcraft including a first power plant, at least one main rotor participating at least in providing lift for the rotorcraft in the air, and at least one tail rotor carried by a tail boom, the first power plant including at least one engine. In accordance with the invention, the rotorcraft includes: at least one pusher or puller propeller independent from the at least one main rotor, the at least one pusher or puller propeller participating at least in providing propulsion or traction for the rotorcraft; a second power plant including at least one electric motor; and at least one control member configured to generate a control setpoint or instruction for controlling the at least one electric motor.
    Type: Grant
    Filed: November 16, 2020
    Date of Patent: October 24, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Olivier Barais, Paul Eglin, Jerome Geneix
  • Patent number: 11713112
    Abstract: A method of reducing the noise generated in-flight by a vortex wake caused by each first blade of a main rotor of a hybrid helicopter. The hybrid helicopter includes a main rotor, at least two wings and at least one propeller. The method enables a stabilized flight phase on the level or with a non-zero aerodynamic slope to be implemented by determining a first value of the pitch of the second blades of each propeller and an angle of incidence of the main rotor as function of the flight conditions, then by applying the first pitch value to each propeller and by applying the angle of incidence to the main rotor so as to direct the vortex wake to limit the noisy interactions between the vortex wake and the other first blades and/or the second blades.
    Type: Grant
    Filed: March 10, 2021
    Date of Patent: August 1, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Frederic Guntzer, Paul Eglin
  • Patent number: 11673680
    Abstract: The present invention relates to a control method in case of engine failure of a hybrid helicopter having a power plant connected to at least one lift rotor and to at least one propeller, said lift rotor having a plurality of first blades and said at least one propeller having a plurality of second blades. The method comprises the following steps: (i) measuring a forward speed of the hybrid helicopter, (ii) on condition that said forward speed is greater than a first speed threshold and that each engine has failed, automatically implementing a first emergency piloting mode comprising a step for automatic reduction by an automatic piloting system of a pitch of said second blades toward an objective pitch making said at least one propeller produce a motive power which is transmitted to the lift rotor.
    Type: Grant
    Filed: December 4, 2020
    Date of Patent: June 13, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Paul Eglin, Remy Huot, Antoine Conroy
  • Patent number: 11634209
    Abstract: A method for optimizing the operation of at least one first propeller and of at least one second propeller of a hybrid helicopter. The method comprises the following step during a control phase: deflection, with an autopilot system, of at least one aerodynamic stabilizer member into a setpoint position having, with respect to a reference position, a target deflection angle that is a function of a setpoint deflection angle, the setpoint deflection angle being calculated by the autopilot system in order to compensate for a torque exerted by the lift rotor at zero sideslip.
    Type: Grant
    Filed: March 11, 2021
    Date of Patent: April 25, 2023
    Assignee: AIRBUS HELICOPTER
    Inventors: Paul Eglin, Remy Huot, Antoine Conroy
  • Patent number: 11608165
    Abstract: A method of providing torque protection and/or thrust protection for the or each propeller of a hybrid helicopter. The hybrid helicopter includes a control system connected to the blades of each propeller and a thrust control configured to generate an order for modifying a pitch of the blades, which order is transmitted to the control system, the propeller(s) being driven in rotation by a mechanical transmission system of the hybrid helicopter. The method includes a step of having the control system keep the pitch of the blades of a propeller within at least one control envelope relating to a thrust generated by the propeller or to a torque exerted in the mechanical transmission system. In this way, the pitch of the blades of each propeller is kept between a lower limit and an upper limit of the control envelope.
    Type: Grant
    Filed: February 8, 2021
    Date of Patent: March 21, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Paul Eglin, Remy Huot
  • Patent number: 11608166
    Abstract: A method of controlling at least a first pitch of a first propeller and a second pitch of a second propeller of a hybrid helicopter, the hybrid helicopter having a thrust control and a yaw control that are configured to generate orders for modifying respectively a mean pitch component and a differential pitch component of the first pitch and of the second pitch, the hybrid helicopter having a collective pitch control for modifying a collective pitch component of main blades of the lift rotor. The method includes a step of: keeping with the control system the first pitch and the second pitch within a control domain that varies as a function of information relating to the collective pitch component.
    Type: Grant
    Filed: February 17, 2021
    Date of Patent: March 21, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Paul Eglin, Remy Huot
  • Patent number: 11604481
    Abstract: A method for controlling a hybrid helicopter having at least one lifting rotor, at least one forward-movement propeller and an empennage provided with at least one moveable empennage surface. The method includes the following steps: using a main sensor to determine a current value of a rotor parameter conditioning a current power drawn by the lifting rotor, using an estimator to determine a current setpoint of the rotor parameter, adjusting a position of the moveable empennage surface using a deflection controller as a function of the current value and of current setpoint.
    Type: Grant
    Filed: December 2, 2021
    Date of Patent: March 14, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Paul Eglin, Remy Huot, Martin Embacher, Antoine Conroy
  • Publication number: 20220380033
    Abstract: An aircraft comprising two half-wings extending to either side of an airframe. The aircraft comprises at least one propeller arranged in the rear part of the airframe. The aircraft comprises a rotary wing provided with two synchronized counter-rotating rotors carried respectively by the half-wings. The aircraft comprises a power plant comprising at least one engine and a mechanical interconnection system connecting the power plant permanently to the rotors except in the event of failure and during training, and to the at least one propeller.
    Type: Application
    Filed: May 16, 2022
    Publication date: December 1, 2022
    Applicant: AIRBUS HELICOPTERS
    Inventor: Paul EGLIN
  • Patent number: 11447240
    Abstract: A method of protecting a margin for controlling the yaw attitude of a hybrid helicopter that includes a lift rotor as well as at least one first propeller and at least one second propeller. A thrust control is configured to generate at least a first order issued to increase a first pitch of first blades of the first propeller and a second pitch of second blades of the second propeller. After a first order has been issued, the method includes an inhibition step for having a control computer inhibit the first order when a yaw attitude control margin, with regard to an envelope delimiting a flight control domain, is and/or will be less than or equal to a threshold.
    Type: Grant
    Filed: February 11, 2021
    Date of Patent: September 20, 2022
    Assignee: AIRBUS HELICOPTERS
    Inventors: Remy Huot, Paul Eglin
  • Publication number: 20220187849
    Abstract: A method for controlling a hybrid helicopter having at least one lifting rotor, at least one forward-movement propeller and an empennage provided with at least one moveable empennage surface. The method includes the following steps: using a main sensor to determine a current value of a rotor parameter conditioning a current power drawn by the lifting rotor, using an estimator to determine a current setpoint of the rotor parameter, adjusting a position of the moveable empennage surface using a deflection controller as a function of the current value and of current setpoint.
    Type: Application
    Filed: December 2, 2021
    Publication date: June 16, 2022
    Applicant: AIRBUS HELICOPTERS
    Inventors: Paul EGLIN, Remy HUOT, Martin EMBACHER, Antoine CONROY
  • Patent number: 11292589
    Abstract: A method of automatically adjusting lift in a hybrid rotorcraft, the hybrid rotorcraft including a fuselage and at least two half-wings on either side of the fuselage, the at least two half-wings including at least one left half-wing having a left fixed structure secured to the fuselage and at least one left flap mounted to move relative to the left fixed structure, and at least one right half-wing having a right fixed structure secured to the fuselage and at least one right flap mounted to move relative to the right fixed structure. The method determines at least one first deflection angle setpoint ?w1 by which the at least one left flap is to be deflected relative to the left fixed structure and at least one second deflection angle setpoint ?w2 by which the at least one right flap is to be deflected relative to the right fixed structure.
    Type: Grant
    Filed: February 10, 2021
    Date of Patent: April 5, 2022
    Assignee: AIRBUS HELICOPTERS
    Inventors: Paul Eglin, Remy Huot
  • Patent number: 11225316
    Abstract: A method of improving a blade and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.
    Type: Grant
    Filed: February 13, 2019
    Date of Patent: January 18, 2022
    Assignee: AIRBUS HELICOPTERS
    Inventors: Raphael Fukari, Paul Eglin
  • Patent number: 11148794
    Abstract: A method of determining an initial leading edge circle for airfoils of a blade and of improving a blade, and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is determined and then increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.
    Type: Grant
    Filed: February 12, 2019
    Date of Patent: October 19, 2021
    Assignee: AIRBUS HELICOPTERS
    Inventors: Raphael Fukari, Paul Eglin
  • Publication number: 20210291969
    Abstract: A method and to a system of reducing the noise generated in-flight by a vortex wake caused by each first blade of a main rotor of a hybrid helicopter. The hybrid helicopter includes a main rotor, at least two wings and at least one propeller. The method enables a stabilized flight phase on the level or with a non-zero aerodynamic slope to be implemented by determining a first value of the pitch of the second blades of each propeller and an angle of incidence of the main rotor as function of the flight conditions, then by applying the first pitch value to each propeller and by applying the angle of incidence to the main rotor so as to direct the vortex wake to limit the noisy interactions between the vortex wake and the other first blades and/or the second blades.
    Type: Application
    Filed: March 10, 2021
    Publication date: September 23, 2021
    Applicant: AIRBUS HELICOPTERS
    Inventors: Frederic GUNTZER, Paul EGLIN
  • Publication number: 20210291974
    Abstract: A method of protecting a margin for controlling the yaw attitude of a hybrid helicopter that includes a lift rotor as well as at least one first propeller and at least one second propeller. A thrust control is configured to generate at least a first order issued to increase a first pitch of first blades of the first propeller and a second pitch of second blades of the second propeller. After a first order has been issued, the method includes an inhibition step for having a control computer inhibit the first order when a yaw attitude control margin, with regard to an envelope delimiting a flight control domain, is and/or will be less than or equal to a threshold.
    Type: Application
    Filed: February 11, 2021
    Publication date: September 23, 2021
    Applicant: AIRBUS HELICOPTERS
    Inventors: Remy HUOT, Paul EGLIN
  • Publication number: 20210291976
    Abstract: A method of controlling at least a first pitch of a first propeller and a second pitch of a second propeller of a hybrid helicopter, the hybrid helicopter having a thrust control and a yaw control that are configured to generate orders for modifying respectively a mean pitch component and a differential pitch component of the first pitch and of the second pitch, the hybrid helicopter having a collective pitch control for modifying a collective pitch component of main blades of the lift rotor. The method includes a step of: keeping with the control system the first pitch and the second pitch within a control domain that varies as a function of information relating to the collective pitch component.
    Type: Application
    Filed: February 17, 2021
    Publication date: September 23, 2021
    Applicant: AIRBUS HELICOPTERS
    Inventors: Paul EGLIN, Remy HUOT
  • Publication number: 20210291975
    Abstract: A method of providing torque protection and/or thrust protection for the or each propeller of a hybrid helicopter. The hybrid helicopter includes a control system connected to the blades of each propeller and a thrust control configured to generate an order for modifying a pitch of the blades, which order is transmitted to the control system, the propeller(s) being driven in rotation by a mechanical transmission system of the hybrid helicopter. The method includes a step of having the control system keep the pitch of the blades of a propeller within at least one control envelope relating to a thrust generated by the propeller or to a torque exerted in the mechanical transmission system. In this way, the pitch of the blades of each propeller is kept between a lower limit and an upper limit of the control envelope.
    Type: Application
    Filed: February 8, 2021
    Publication date: September 23, 2021
    Applicant: AIRBUS HELICOPTERS
    Inventors: Paul EGLIN, Remy HUOT
  • Publication number: 20210291970
    Abstract: A method of controlling at least one first propeller of a hybrid helicopter, the hybrid helicopter having a thrust control for controlling a first pitch of the first blades of the first propeller. The thrust control includes a movable control member. The method includes the following steps: the thrust control continuously transmitting a control signal carrying a control setpoint to the control system; the control system transforming the control setpoint into a pitch setpoint; and the control system controlling the first pitch by applying the pitch setpoint.
    Type: Application
    Filed: February 16, 2021
    Publication date: September 23, 2021
    Applicant: AIRBUS HELICOPTERS
    Inventor: Paul EGLIN
  • Publication number: 20210284326
    Abstract: A method for optimizing the operation of at least one first propeller and of at least one second propeller of a hybrid helicopter. The method comprises the following step during a control phase: deflection, with an autopilot system, of at least one aerodynamic stabilizer member into a setpoint position having, with respect to a reference position, a target deflection angle that is a function of a setpoint deflection angle, the setpoint deflection angle being calculated by the autopilot system in order to compensate for a torque exerted by the lift rotor at zero sideslip.
    Type: Application
    Filed: March 11, 2021
    Publication date: September 16, 2021
    Applicant: AIRBUS HELICOPTERS
    Inventors: Paul EGLIN, Remy HUOT, Antoine CONROY
  • Publication number: 20210284331
    Abstract: A method of automatically adjusting lift in a hybrid rotorcraft, the hybrid rotorcraft including a fuselage and at least two half-wings on either side of the fuselage, the at least two half-wings including at least one left half-wing having a left fixed structure secured to the fuselage and at least one left flap mounted to move relative to the left fixed structure, and at least one right half-wing having a right fixed structure secured to the fuselage and at least one right flap mounted to move relative to the right fixed structure. The method determines at least one first deflection angle setpoint ?w1 by which the at least one left flap is to be deflected relative to the left fixed structure and at least one second deflection angle setpoint ?w2 by which the at least one right flap is to be deflected relative to the right fixed structure.
    Type: Application
    Filed: February 10, 2021
    Publication date: September 16, 2021
    Applicant: AIRBUS HELICOPTERS
    Inventors: Paul EGLIN, Remy HUOT