INVESTIGATION OF ACQUISITION PROBLEM IN SATELLITE ATTITUDE CONTROL

摘要

The acquisition function of a spacecraft attitude control system consists of properly orienting the vehicle with respect to specified reference directions starting from large initial attitude and rate errors. The resulting control system design problem was examined by establishing suitable mathematical representations, comparing compet¬ing control concepts, developing a practical optimization approach, and evaluating a new technique for applying Lyapunov stability theory to the acquisition problem.nAll potentially practical kinematic representation for specify¬ing rigid body attitude are presented and compared. The bases for comparison are with respect to their applicability for analytic studies and simulation studies. In each case the ease of visualization and interpretation, simplicity of system representation, order of the re¬presentation, as well as the basic characteristics of the representa¬tions themselves are considered.