Stability Analysis for Constrained Principal Axis Slew ManeuversThis paper addresses the problem of reorienting a rigid spacecraft from arbitrary initial conditions to prescribed final conditions with zero angular velocity. The control law analyzed is based on quaternion feedback and leaves the user to choose two gains as functions of position, angular rate, and time. For arbitrary initial states, conditions on the controller gains are identified that guarantee global asymptotic stability. For the special case of rest-to-rest reorientations, the control law reduces to earlier results involving a principal axis rotation. The paper also addresses slew rate constraints, both, in terms of the two and infinity norms.
Document ID
20040105588
Acquisition Source
Langley Research Center
Document Type
Other
Authors
Seywald, Hans (Analytical Mechanics Associates, Inc. Hampton, VA, United States)
Lim, Kyong B. (NASA Langley Research Center Hampton, VA, United States)
Anthony, Tobin C. (NASA Goddard Space Flight Center Greenbelt, MD, United States)