Patents by Inventor Régis Rossotto

Régis Rossotto 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: 10748441
    Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.
    Type: Grant
    Filed: October 11, 2016
    Date of Patent: August 18, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventors: Guillaume Dumur, Regis Rossotto, Hilario Vieira
  • Patent number: 10144528
    Abstract: A power plant comprising two engine groups and a main power transmission gearbox. Each engine group drives the main gearbox mechanically in order to rotate a main rotor of an aircraft at a frequency of rotation NR. A first engine group comprising two main engines is regulated on a first setpoint NR* for the frequency of rotation NR, while a second engine group comprising a secondary engine is regulated on a second setpoint W2* for power of the second engine group. In addition, each engine operates with margins relative to operating limits. The second setpoint W2* for power is determined so that each secondary engine operates with a lowest second margin that is equal to the lowest first margin of the first engine group.
    Type: Grant
    Filed: June 15, 2016
    Date of Patent: December 4, 2018
    Assignee: AIRBUS HELICOPTERS
    Inventor: Regis Rossotto
  • Patent number: 10112723
    Abstract: A method of stopping a turboshaft engine in flight. During a power reduction step, a current power of the engine for stopping is reduced to reach zero power, and a current speed of rotation of the gas generator of the engine for stopping is reduced to reach a predetermined intermediate speed when the current power becomes zero. During a temperature stabilization step, the current speed of rotation remains equal to the intermediate speed. During a shutdown step, the current speed of rotation is reduced to reach zero speed.
    Type: Grant
    Filed: March 29, 2016
    Date of Patent: October 30, 2018
    Assignee: Airbus Helicopters
    Inventors: Regis Rossotto, Jean-Francois Piccone
  • Patent number: 10106268
    Abstract: A power plant comprising two engine groups and a main power transmission gearbox. Each engine group drives the main gearbox mechanically in order to rotate a main rotor of an aircraft at a frequency of rotation NR. A first engine group comprising two main engines is regulated on a first setpoint NR* for the frequency of rotation NR, while a second engine group comprising a secondary engine is regulated on a second setpoint W2* for power. The second setpoint W2* for power is determined so that each secondary engine operates only when a flight power Wvol necessary for the flight of the aircraft is greater than the sum of the main maximum powers WMax1 from each main engine.
    Type: Grant
    Filed: June 7, 2016
    Date of Patent: October 23, 2018
    Assignee: AIRBUS HELICOPTERS
    Inventor: Regis Rossotto
  • Patent number: 9914536
    Abstract: A method of driving rotation of a rotor of an aircraft, said aircraft having at least two fuel-burning engines and an electric motor suitable for driving rotation of said rotor. Said rotor is driven by using said engines together. An authorization is generated only during at least one predetermined stage of flight, said authorization authorizing the use of the electric motor in order to drive said rotor in rotation. While said authorization is valid and if one of said engines has failed, then an operation order is generated to require said electric motor to operate. While said operation order is valid, said rotor is driven by each engine that has not failed together with said electric motor.
    Type: Grant
    Filed: May 12, 2016
    Date of Patent: March 13, 2018
    Assignee: Airbus Helicopters
    Inventor: Regis Rossotto
  • Patent number: 9666051
    Abstract: A method of detecting that an aircraft is flying in icing conditions. A processor unit determines a real power developed by the turboshaft engine and a theoretical power that the engine can develop in theory, the theoretical power being determined using a theoretical model supplying a power as a function at least of a speed of rotation of a gas generator of the engine. The processor unit determines a difference between the real power and the theoretical power. The processor unit generates a warning to indicate the presence of icing conditions when the power difference is greater than a predetermined power threshold for a length of time longer than a time threshold, and when a temperature outside the aircraft lies between a low temperature threshold and a high temperature threshold.
    Type: Grant
    Filed: July 27, 2015
    Date of Patent: May 30, 2017
    Assignee: Airbus Helicopters
    Inventors: Regis Rossotto, Emmanuel Camhi
  • Publication number: 20170066541
    Abstract: A power plant comprising two engine groups and a main power transmission gearbox. Each engine group drives the main gearbox mechanically in order to rotate a main rotor of an aircraft at a frequency of rotation NR. A first engine group comprising two main engines is regulated on a first setpoint NR* for the frequency of rotation NR, while a second engine group comprising a secondary engine is regulated on a second setpoint W2* for power. The second setpoint W2* for power is determined so that each secondary engine operates only when a flight power Wvol necessary for the flight of the aircraft is greater than the sum of the main maximum powers WMax1 from each main engine.
    Type: Application
    Filed: June 7, 2016
    Publication date: March 9, 2017
    Inventor: Regis ROSSOTTO
  • Patent number: 9586691
    Abstract: A power plant (1) having two engine groups (10, 20) and a main gearbox (MGB) (2), and a rotary wing aircraft (30) having such a power plant (1). Each engine group (10, 20) drives said MGB (2) mechanically to rotate a main outlet shaft (3) and, consequently, a main rotor (31) of said aircraft (30) at a frequency of rotation NR. A first engine group (10) has two main engines (11, 12) and is by a first setpoint NR* for said frequency of rotation NR, while a second engine group (20) has one secondary engine (21) and is regulated by a second setpoint W1* for power from said second engine group (20). The first engine group (10) is also regulated by a third setpoint W2f* for anticipating power such that said first engine group (10) and said second engine group (20) deliver the power needed at said main rotor (31).
    Type: Grant
    Filed: July 17, 2014
    Date of Patent: March 7, 2017
    Assignee: Airbus Helicopters
    Inventors: Regis Rossotto, Hanno Boie
  • Publication number: 20170025032
    Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.
    Type: Application
    Filed: October 11, 2016
    Publication date: January 26, 2017
    Applicant: AIRBUS HELICOPTERS
    Inventors: Guillaume DUMAR, Regis ROSSOTTO, Hilario VIEIRA
  • Patent number: 9542855
    Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch maneuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.
    Type: Grant
    Filed: April 8, 2014
    Date of Patent: January 10, 2017
    Assignee: AIRBUS HELICOPTERS
    Inventors: Guillaume Dumur, Regis Rossotto, Hilario Vieira
  • Publication number: 20160375994
    Abstract: A method of driving rotation of a rotor of an aircraft, said aircraft having at least two fuel-burning engines and an electric motor suitable for driving rotation of said rotor. Said rotor is driven by using said engines together. An authorization is generated only during at least one predetermined stage of flight, said authorization authorizing the use of the electric motor in order to drive said rotor in rotation. While said authorization is valid and if one of said engines has failed, then an operation order is generated to require said electric motor to operate. While said operation order is valid, said rotor is driven by each engine that has not failed together with said electric motor.
    Type: Application
    Filed: May 12, 2016
    Publication date: December 29, 2016
    Inventor: Regis ROSSOTTO
  • Publication number: 20160376017
    Abstract: A power plant comprising two engine groups and a main power transmission gearbox. Each engine group drives the main gearbox mechanically in order to rotate a main rotor of an aircraft at a frequency of rotation NR. A first engine group comprising two main engines is regulated on a first setpoint NR* for the frequency of rotation NR, while a second engine group comprising a secondary engine is regulated on a second setpoint W2* for power of the second engine group. In addition, each engine operates with margins relative to operating limits. The second setpoint W2* for power is determined so that each secondary engine operates with a lowest second margin that is equal to the lowest first margin of the first engine group.
    Type: Application
    Filed: June 15, 2016
    Publication date: December 29, 2016
    Inventor: Regis ROSSOTTO
  • Publication number: 20160311547
    Abstract: A method of stopping a turboshaft engine in flight. During a power reduction step, a current power of the engine for stopping is reduced to reach zero power, and a current speed of rotation of the gas generator of the engine for stopping is reduced to reach a predetermined intermediate speed when the current power becomes zero. During a temperature stabilization step, the current speed of rotation remains equal to the intermediate speed. During a shutdown step, the current speed of rotation is reduced to reach zero speed.
    Type: Application
    Filed: March 29, 2016
    Publication date: October 27, 2016
    Inventors: Regis ROSSOTTO, Jean-Francois PICCONE
  • Publication number: 20160035203
    Abstract: A method of detecting that an aircraft is flying in icing conditions. A processor unit determines a real power developed by the turboshaft engine and a theoretical power that the engine can develop in theory, the theoretical power being determined using a theoretical model supplying a power as a function at least of a speed of rotation of a gas generator of the engine. The processor unit determines a difference between the real power and the theoretical power. The processor unit generates a warning to indicate the presence of icing conditions when the power difference is greater than a predetermined power threshold for a length of time longer than a time threshold, and when a temperature outside the aircraft lies between a low temperature threshold and a high temperature threshold.
    Type: Application
    Filed: July 27, 2015
    Publication date: February 4, 2016
    Inventors: Regis ROSSOTTO, Emmanuel CAMHI
  • Patent number: 9217375
    Abstract: A control method for controlling an overspeed safety system (5) of an aircraft (1) having at least a first engine (10) and a second engine (20), during which method an engine is shut down when a monitoring parameter of that engine exceeds a first threshold, and another engine distinct from this engine is shut down when the monitoring parameter for said other engine exceeds a second threshold, said second threshold being greater than said first threshold.
    Type: Grant
    Filed: September 13, 2012
    Date of Patent: December 22, 2015
    Assignee: Airbus Helicopters
    Inventors: Régis Rossotto, Hilario Vieira
  • Publication number: 20150028153
    Abstract: A power plant (1) having two engine groups (10, 20) and a main gearbox (MGB) (2), and a rotary wing aircraft (30) having such a power plant (1). Each engine group (10, 20) drives said MGB (2) mechanically to rotate a main outlet shaft (3) and, consequently, a main rotor (31) of said aircraft (30) at a frequency of rotation NR. A first engine group (10) has two main engines (11, 12) and is by a first setpoint NR* for said frequency of rotation NR, while a second engine group (20) has one secondary engine (21) and is regulated by a second setpoint W1* for power from said second engine group (20). The first engine group (10) is also regulated by a third setpoint W2f* for anticipating power such that said first engine group (10) and said second engine group (20) deliver the power needed at said main rotor (31).
    Type: Application
    Filed: July 17, 2014
    Publication date: January 29, 2015
    Inventors: Regis ROSSOTTO, Hanno BOIE
  • Publication number: 20140302461
    Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.
    Type: Application
    Filed: April 8, 2014
    Publication date: October 9, 2014
    Applicant: AIRBUS HELICOPTERS
    Inventors: Guillaume DUMUR, Regis ROSSOTTO, Hilario VIEIRA
  • Publication number: 20130247577
    Abstract: A control method for controlling an overspeed safety system (5) of an aircraft (1) having at least a first engine (10) and a second engine (20), during which method an engine is shut down when a monitoring parameter of that engine exceeds a first threshold, and another engine distinct from this engine is shut down when the monitoring parameter for said other engine exceeds a second threshold, said second threshold being greater than said first threshold.
    Type: Application
    Filed: September 13, 2012
    Publication date: September 26, 2013
    Applicant: EUROCOPTER
    Inventors: Regis Rossotto, Hilario Vieira
  • Patent number: 8442740
    Abstract: In order to regulate a power plant (105) having a gas generator (1) and a free turbine (3) to drive a rotary wing, a first speed of rotation (NTL) of the free turbine (3) is regulated on a first setpoint value (NTL*) equal either to a regulation term (NRc) or to a predetermined setpoint threshold (NTL*). The regulation term (NRc) is a function of a third speed of rotation (NR) of said rotary wing in accordance, where NRc=NR*(1?d), “d” representing a non-zero constant lying in the range 0 to 1.
    Type: Grant
    Filed: April 5, 2012
    Date of Patent: May 14, 2013
    Assignee: Eurocopter
    Inventor: Régis Rossotto
  • Publication number: 20120277969
    Abstract: In order to regulate a power plant (105) having a gas generator (1) and a free turbine (3) to drive a rotary wing, a first speed of rotation (NTL) of the free turbine (3) is regulated on a first setpoint value (NTL*) equal either to a regulation term (NRc) or to a predetermined setpoint threshold (NTL*). The regulation term (NRc) is a function of a third speed of rotation (NR) of said rotary wing in accordance, where NRc=NR*(1?d), “d” representing a non-zero constant lying in the range 0 to 1.
    Type: Application
    Filed: April 5, 2012
    Publication date: November 1, 2012
    Applicant: EUROCOPTER
    Inventor: Régis Rossotto