Patents by Inventor Fabien ROZO-QUILLERE

Fabien ROZO-QUILLERE 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).

  • Method of following a transfer orbit or a phase of orbital placement of a space vehicle, in particular an electric propulsion vehicle, and apparatus for the implementation of such a method
    Patent number: 10054449
    Abstract: A method of following a transfer orbit or a phase of orbital placement of a continuous-thrust space vehicle comprises the following steps: a) tracking at least one GNSS signal and using it to determine at least one pseudorange between the space vehicle and one or more GNSS satellites transmitting the signal; b) using an estimation model to jointly estimate a set of state parameters of the space vehicle comprising a plurality of position parameters, a plurality of velocity parameters and at least one thrust error parameter characterizing a discrepancy between an actual thrust force of the space vehicle and a nominal thrust force by taking the pseudorange or pseudoranges as input datum of the estimation model. An apparatus for the implementation of such a method is also provided.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: August 21, 2018
    Assignee: THALES
    Inventors: Thibaud Calmettes, Fabien Rozo-Quillere, Damien Serant
  • METHOD OF FOLLOWING A TRANSFER ORBIT OR A PHASE OF ORBITAL PLACEMENT OF A SPACE VEHICLE, IN PARTICULAR AN ELECTRIC PROPULSION VEHICLE, AND APPARATUS FOR THE IMPLEMENTATION OF SUCH A METHOD
    Publication number: 20150247730
    Abstract: A method of following a transfer orbit or a phase of orbital placement of a continuous-thrust space vehicle comprises the following steps: a) tracking at least one GNSS signal and using it to determine at least one pseudorange between the space vehicle and one or more GNSS satellites transmitting the signal; b) using an estimation model to jointly estimate a set of state parameters of the space vehicle comprising a plurality of position parameters, a plurality of velocity parameters and at least one thrust error parameter characterizing a discrepancy between an actual thrust force of the space vehicle and a nominal thrust force by taking the pseudorange or pseudoranges as input datum of the estimation model. An apparatus for the implementation of such a method is also provided.
    Type: Application
    Filed: February 27, 2015
    Publication date: September 3, 2015
    Inventors: Thibaud CALMETTES, Fabien ROZO-QUILLERE, Damien SERANT