Patents by Inventor Timothy Adam Craychee

Timothy Adam Craychee 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 and apparatus for initial orbit determination using high-precision orbit propagation and maneuver modeling
    Patent number: 8386099
    Abstract: A method of determining an orbit of an orbital object includes computing predicted tracking measurement values based on the orbit computed from the initial conditions factoring in any modeled environmental forces and realistic maneuvers; computing the differences between the actual and predicted tracking measurements; determining an improved estimate of the initial conditions that reduces the measurement errors using a minimization or root finding algorithm; after the algorithm has converged, reviewing the hypothetical maneuvers in the force model, taking each value and determining which values came up as near-zero in the minimized solutions and which values came up as those of measurable thrust; determining overall burn duration using the first and last burn times; determining the thrust profile of the orbital object over the observation period using the integrated thrust values; and determining the actual maneuver based on the observation data.
    Type: Grant
    Filed: February 5, 2010
    Date of Patent: February 26, 2013
    Assignee: Applied Defense Solutions
    Inventors: John Paul Carrico, Jr., Timothy Adam Craychee, Henry Casmir Grabowski, III
  • Method and apparatus for initial orbit determination using high-precision orbit propagation and maneuver modeling
    Publication number: 20110196550
    Abstract: A method of determining an orbit of an orbital object includes computing predicted tracking measurement values based on the orbit computed from the initial conditions factoring in any modeled environmental forces and realistic maneuvers; computing the differences between the actual and predicted tracking measurements; determining an improved estimate of the initial conditions that reduces the measurement errors using a minimization or root finding algorithm; after the algorithm has converged, reviewing the hypothetical maneuvers in the force model, taking each value and determining which values came up as near-zero in the minimized solutions and which values came up as those of measurable thrust; determining overall burn duration using the first and last burn times; determining the thrust profile of the orbital object over the observation period using the integrated thrust values; and determining the actual maneuver based on the observation data.
    Type: Application
    Filed: February 5, 2010
    Publication date: August 11, 2011
    Applicant: APPLIED DEFENSE SOLUTIONS
    Inventors: John Paul Carrico, JR., Timothy Adam Craychee, Henry Casmir Grabowski, III