Method and apparatus for contingency guidance of a CMG-actuated spacecraft
Ross, Isaac Michael
MetadataShow full item record
Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CM Gs) 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.
Patent Number: 9,038,958 B1
Showing items related by title, author, creator and subject.
Ross, Issac M.; Proulx, Ronald J.; Greenslade, Joseph M.; Karpenko, Mark (The United States of America as represented by the Secretary of the Navy, Washington, DC (US), 2018-05-29);The disclosure provides a method and apparatus for determination of a control policy for a rigid body system, where the rigid body system comprises a sensor and a plurality of actuators designed to maneuver the rigid ...
Agrawal, B.N. (2005);This paper presents a review of the spacecraft design program at the Naval Postgraduate School. This program is part of the space systems engineering curriculum. In this curriculum, the students take at least one course ...
Karpenko, Mark; Ross, Isaac Michael (United States of America as represented by the Secretary of the Navy, Arlington, VA, 2014-11-04);Methods and apparatus are presented for spacecraft operation in which a control problem is formulated using a control law or steering law as a path constraint or as a dynamic constraint, and the control problem is solved ...