Patents by Inventor Philip Conway Hirschberg

Philip Conway Hirschberg 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).

  • Pre and post orbit maneuver pulses to reduce flexural oscillations
    Patent number: 10501211
    Abstract: Techniques for performing an orbital maneuver on a spacecraft by firing a thruster include executing a first double pulse, double coast firing (DPDC) sequence with the thruster prior to the orbital maneuver, firing the thruster for a duration of the orbital maneuver, and executing a second DPDC firing sequence with the thruster subsequent to the orbital maneuver.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: December 10, 2019
    Assignee: Space Systems/Loral, LLC
    Inventor: Philip Conway Hirschberg
  • Spacecraft momentum management using solar array
    Patent number: 8868263
    Abstract: Stored momentum on a spacecraft is managed by determining a target profile of stored momentum as a function of time for the spacecraft; measuring a difference between a momentum value actually stored on the spacecraft and a desired momentum value, where the desired momentum value substantially conforms to the target profile at a particular time; reducing the difference by producing a torque on the spacecraft, where the torque results from selectively controlling at least one solar array position offset angle, the offset angle being an offset of at least one solar array of the spacecraft from a nominal sun pointing direction.
    Type: Grant
    Filed: May 25, 2011
    Date of Patent: October 21, 2014
    Assignee: Space Systems/Loral, LLC
    Inventors: Mohammad Saghir Munir, John Hutton Cooper, Philip Conway Hirschberg
  • SPACECRAFT MOMENTUM MANAGEMENT USING SOLAR ARRAY
    Publication number: 20120303185
    Abstract: Stored momentum on a spacecraft is managed by determining a target profile of stored momentum as a function of time for the spacecraft; measuring a difference between a momentum value actually stored on the spacecraft and a desired momentum value, where the desired momentum value substantially conforms to the target profile at a particular time; reducing the difference by producing a torque on the spacecraft, where the torque results from selectively controlling at least one solar array position offset angle, the offset angle being an offset of at least one solar array of the spacecraft from a nominal sun pointing direction.
    Type: Application
    Filed: May 25, 2011
    Publication date: November 29, 2012
    Applicant: SPACE SYSTEMS/LORAL, INC.
    Inventors: Mohammad Saghir Munir, John Hutton Cooper, Philip Conway Hirschberg