Naval Postgraduate School
Method and apparatus for determining spacecraft maneuvers
NPS-S8880246B1.pdf (1.148Mb)Abstract
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.
Description
Patent No.: US 8,880,246 B1
Collections
Related items
Showing items related by title, author, creator and subject.
-
Method and apparatus for contingency guidance of a CMG-actuated spacecraft
(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 ... -
Attitude Dynamics/Control of Dual-Body Spacecraft with Variable-Speed Control Moment Gyros
(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 ... -
Application of Constraint Dynamics for Spacecraft Maneuver
(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 ...
