Method and apparatus for contingency guidance of a CMG-actuated spacecraft

  • US Patent No. 9038958
  • Issued: May 26, 2015
  • Status: Active
Military Technology

Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CMGs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.

Do you have questions or need more information on a specific technology? Let's talk.

Contact Us