Journal of Applied Sciences1812-56541812-5662Asian Network for Scientific Information10.3923/jas.2012.2519.2526ParmanSetyamartanaAri-WahjoediBambangHalawaEdwardMachmudahAffiani1220121224Attitude maneuvers of a Communication Technology Satellite
(CTS)-like spacecraft using constant-amplitude thrusters is of great importance.
The spacecraft consists of a rigid main body and two symmetrical solar panels.
When the panels are large, they cannot be treated as rigid bodies anymore. They
are supposed to behave structural flexibility. To discrete their motion, the
finite element method is followed. Under constant-amplitude thrusts, steady-state
attitude angle oscillations may occur in large amplitude after the maneuvers.
Since, the spacecraft should point to the earth precisely, these oscillations
must be reduced into small permissible values. To reduce residual attitude angle
oscillations, Proportional Derivative (PD) based constant-amplitude input shaping
logic is proposed to determine time locations of thruster switching. Then, under
such inputs, attitude maneuvers of the spacecraft are simulated numerically.
Results of simulations show that the precise orientation of the satellite can
be achieved.]]>Hwangbo, H.,1992Liu, Q. and B. Wie,1992Pao, L.Y. and W.E. Singhose,1995Rogers, K. and W.P. Seering,1996Parman, S. and H. Koguchi,1998Parman, S. and H. Koguchi,1999Parman, S. and H. Koguchi,1999Parman, S. and H. Koguchi,2000Smith, I.M. and D.V. Griffiths,2005