Patents by Inventor Matthieu GALLOT

Matthieu GALLOT 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).

  • Device and method for controlling an auxiliary engine suitable for supplying thrust power to the rotor of a helicopter
    Patent number: 9919806
    Abstract: The invention relates to a device for controlling an auxiliary engine (8) comprising a gas generator and a free turbine suitable for being able to be connected mechanically to the rotor (12) of a helicopter in order to supply it with thrust power, characterised in that said control device comprises a proportional-integral controller (30) having a proportional gain (Kp) and an integral gain (Ki), which are dependent on the rotation speed of said gas generator, said controller (30) being configured to receive an error signal representing a speed error of said free turbine, and to generate a signal (Sc) for correcting the drive speed of said gas generator obtained by adding a signal proportional to said error signal in accordance with said proportional gain (Kp), and an integrated signal (Si) resulting from the addition of a signal proportional to said error signal in accordance with said integral gain (Ki) and a memory signal (Sm), supplied by a feedback loop (31) of said integrated signal (Si), said memory sig
    Type: Grant
    Filed: January 11, 2016
    Date of Patent: March 20, 2018
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Jean Philippe Jacques Marin, Matthieu Gallot, Philippe Etchepare
  • DEVICE AND METHOD FOR CONTROLLING AN AUXILIARY ENGINE SUITABLE FOR SUPPLYING THRUST POWER TO THE ROTOR OF A HELICOPTER
    Publication number: 20170334569
    Abstract: The invention relates to a device for controlling an auxiliary engine (8) comprising a gas generator and a free turbine suitable for being able to be connected mechanically to the rotor (12) of a helicopter in order to supply it with thrust power, characterised in that said control device comprises a proportional-integral controller (30) having a proportional gain (Kp) and an integral gain (Ki), which are dependent on the rotation speed of said gas generator, said controller (30) being configured to receive an error signal representing a speed error of said free turbine, and to generate a signal (Sc) for correcting the drive speed of said gas generator obtained by adding a signal proportional to said error signal in accordance with said proportional gain (Kp), and an integrated signal (Si) resulting from the addition of a signal proportional to said error signal in accordance with said integral gain (Ki) and a memory signal (Sm), supplied by a feedback loop (31) of said integrated signal (Si), said memory sig
    Type: Application
    Filed: January 11, 2016
    Publication date: November 23, 2017
    Inventors: Jean Philippe Jacques MARIN, Matthieu GALLOT, Philippe ETCHEPARE