چكيده لاتين :
In this paper. muiitruun and near-minimum time optimal control laws are
developed and compared forי a rigid space platforn: with flc:Tible links duriru] an
orientating nuuieuuer with a Imי.gr; angle of rotation. The control conuiuuid«
mיe considered as typical l!!Lng-bang with muliip!« symmetrical suntclies, the
time optimal control solution for the Tigid-body mode is obtained as a bangbang
function and applied to the .fle:rible system after smoothening the control
inpnt.s to avoid stimulation of the .flexilile modes. This will also reflect practical
limitations in erertuu; bang-I)(lT/,g actuatorי jorces/torques due to delays and
non-zero time constants of eiisiiru; actuation elements. The smoothness of
the uiuut. commasul is obtained by ncshaping its profile based on consuieration
of addiiion.a! derioaiiue constraints. the optimal control problem is converted
into parameter optimization problem. The steps of tlu solution procedure and
numerical algorithm. to obt.aiti the time optinuil control input are discussed
next: The developed control law is applied to a given satellite duriiu; a
slewing maueuuer. The simulation results show that the couirol input with
just a few switching times can significantly lessen the vibrating motion of the
jieribie appendage. which reneols the merits of the developed control law. The
modified realistic optimal input compared to the liang-bang solution goes well
with the practical Iiniitations and alleviates the vibrating motion of the flexible
appendage. which reveals therneriis of the new developed control law.
