Method and apparatus for determining spacecraft maneuvers
Ross, Isaac Michael
MetadataShow full item record
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 to provide a guidance command trajectory for use in operating spacecraft control momentum gyroscopes to guide the spacecraft from an initial state to a desired final state.
RightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
Showing items related by title, author, creator and subject.
Ross, Isaac Michael; Lee, Donghun; Karpenko, Mark (United States of America as represented by the Secretary of the Navy, Washington, DC (US), 2015-05-26);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 ...
Romano, M.; Agrawal, B. (2004);The dynamics equations of a spacecraft consisting of two bodies mutually rotating around a common gimbal axis are derived by the use of the Newton–Euler approach. One of the bodies contains a cluster of single-gimbal var ...
Bang, H.; Agrawal, B.N. (1994);A new approach for spacecraft maneuver based upon constraint dynamics and tracking control laws is presented in this paper. For high precision pointing requirement on spacecraft maneuver, a desired trajectory is prescribed ...