Patents by Inventor Michael Allen Walker

Michael Allen Walker 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).

  • GNSS ephemeris with graceful degradation and measurement fusion
    Patent number: 9075140
    Abstract: A method for providing an extended propagation ephemeris model for a satellite in Earth orbit, the method includes obtaining a satellite's orbital position over a first period of time, applying a least square estimation filter to determine coefficients defining osculating Keplarian orbital elements and harmonic perturbation parameters associated with a coordinate system defining an extended propagation ephemeris model that can be used to estimate the satellite's position during the first period, wherein the osculating Keplarian orbital elements include semi-major axis of the satellite (a), eccentricity of the satellite (e), inclination of the satellite (i), right ascension of ascending node of the satellite (?), true anomaly (?*), and argument of periapsis (?), applying the least square estimation filter to determine a dominant frequency of the true anomaly, and applying a Fourier transform to determine dominant frequencies of the harmonic perturbation parameters.
    Type: Grant
    Filed: September 23, 2010
    Date of Patent: July 7, 2015
    Assignee: Purdue Research Foundation
    Inventors: James Levi Garrison, Michael Allen Walker
  • GNSS Ephemeris with Graceful Degradation and Measurement Fusion
    Publication number: 20110071808
    Abstract: A method for providing an extended propagation ephemeris model for a satellite in Earth orbit, the method includes obtaining a satellite's orbital position over a first period of time, applying a least square estimation filter to determine coefficients defining osculating Keplarian orbital elements and harmonic perturbation parameters associated with a coordinate system defining an extended propagation ephemeris model that can be used to estimate the satellite's position during the first period, wherein the osculating Keplarian orbital elements include semi-major axis of the satellite (a), eccentricity of the satellite (e), inclination of the satellite (i), right ascension of ascending node of the satellite (?), true anomaly (?*), and argument of periapsis (?), applying the least square estimation filter to determine a dominant frequency of the true anomaly, and applying a Fourier transform to determine dominant frequencies of the harmonic perturbation parameters.
    Type: Application
    Filed: September 23, 2010
    Publication date: March 24, 2011
    Applicant: PURDUE RESEARCH FOUNDATION
    Inventors: James Levi Garrison, Michael Allen Walker