Singular control in minimum time spacecraft reorientationSpacecraft reorientation is investigated numerically for an inertially symmetric rigid spacecraft with three bounded independent control torques aligned with the principal axes. The dynamical system of the spacecraft and the framework of the optimal-control problem are established in order to identify all of the potential strategies. The investigation lists bang-bang solutions and finite-order and infinite-order singular arcs, and the conditions for the finite-order singular arcs are given. Numerical examples are developed for all of the control-logic systems, and the suboptimality of the rest-to-rest maneuvers is proven for principal-axis rotations. The most efficient control technique is the singular control of infinite order, and the vector-valued singular control can be utilized in a derivative of the switching function.
Document ID
19910064997
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Seywald, Hans (NASA Langley Research Center Hampton, VA, United States)
Kumar, Renjith R. (NASA Langley Research Center; Analytical Mechanics Associates, Inc. Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 91-2645
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference