Truncated Elastic Modes Coupling Effects Minimization Method by Using Special Attitude Control Scheme

摘要

An adaptive scheme is applied to minimize the truncated modes coupling effects for the attitude controlled spacecraft. The basic idea for the scheme is to nullify the accumulated effect of the truncated modes by using a correction in the control, such as to induce the physical system to have a behavior close to the model of work used in the synthesis and implementation of the control. This nullification provides the decoupling of the truncated modes from the work model. It is the decoupling that makes the truncated modes associated eigenvalues be identical for the controlled and constrained model. The importance of the result is that the eigenvalues for the constrained model are stable and frequently present a reasonable damping time. The proposed scheme is very easy to be implemented in on board control. The procedure was tested for the attitude control of a flexible spacecraft and the obtained results are presented.