Attitude Control of Linear System by Using Feed- Forward Constant-Amplitude Inputs

Attitude control of a linear system equipped by
constant amplitude inputs are studied. The inputs to be given
to the system are feed-forward inputs, and the input shaping
method is used to form time optimal inputs in small residual
oscillation of its attitude angles. As a study, attitude
maneuvers of a flexible satellite are studied. The satellite
consists of a rigid main body and two flexible solar panels. In
the modeling, the finite element method is used to discret the
flexible displacement of solar panels. Under constantamplitude
control inputs, results indicate that the maneuver
induces an undesirable motion of the satellite as well as
vibration of the solar panels. Then, time-optimal shaped
inputs are applied to maneuver the satellite. By using shaped
inputs, those reduce vibrations at large-amplitude natural
frequencies, the expected pointing precision of the satellite
can be satisfied.