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.
Patent No.: US 8,880,246 B1
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 ...
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 ...