Patents by Inventor Amer CHPOUN

Amer CHPOUN 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).

  • System for controlling speed transition and thrust vectorisation in a multiple-shaped nozzle by secondary injection
    Patent number: 11661910
    Abstract: A mixing tube with multiple shapes is provided, allowing additional injection of gas in order to keep the flow detached from the second shape in an ascent phase and to bring about, in a descent phase, a controlled detachment as a result of the change of slope between the two shapes. A propulsion nozzle for an engine of a spacecraft or aircraft is provided including such a mixing tube and a method for controlling the speed transition of the propulsion gases in such a nozzle in accordance with the altitude. Also, a method is provided for vectorising the thrust in such a nozzle by radial and asymmetrical injection of gas and a control method which prevents re-attachment of the jet to the second shape of such a propulsion nozzle for an engine of a spacecraft when it is in the take-off or landing phase.
    Type: Grant
    Filed: April 18, 2019
    Date of Patent: May 30, 2023
    Assignees: CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE D'ORLEANS, UNIVERSITE D'EVERY-VAL D'ESSONNE
    Inventors: Luc Leger, Vladeta Zmijanovic, Mohamed Sellam, Amer Chpoun
  • SYSTEM FOR CONTROLLING SPEED TRANSITION AND THRUST VECTORISATION IN A MULTIPLE-SHAPED NOZZLE BY SECONDARY INJECTION
    Publication number: 20210164418
    Abstract: A mixing tube with multiple shapes is provided, allowing additional injection of gas in order to keep the flow detached from the second shape in an ascent phase and to bring about, in a descent phase, a controlled detachment as a result of the change of slope between the two shapes. A propulsion nozzle for an engine of a spacecraft or aircraft is provided including such a mixing tube and a method for controlling the speed transition of the propulsion gases in such a nozzle in accordance with the altitude. Also, a method is provided for vectorising the thrust in such a nozzle by radial and asymmetrical injection of gas and a control method which prevents re-attachment of the jet to the second shape of such a propulsion nozzle for an engine of a spacecraft when it is in the take-off or landing phase.
    Type: Application
    Filed: April 18, 2019
    Publication date: June 3, 2021
    Inventors: Luc LEGER, Vladeta ZMIJANOVIC, Mohamed SELLAM, Amer CHPOUN