Spin-off maneuver of a flexible satellite using constant-amplitude thrusters is studied in this paper. The satellite consists of a rigid main body and two symmetrical solar panels. The panels are having structural flexibility and their motions are discretized following the finite element method. Under constant-amplitude thrusts, steady-state attitude angle oscillations may occur in large amplitude after the maneuvers. Since in operation the satellite should point to certain area on the earth precisely, these oscillations of course are not acceptable. To reduce the oscillations, proportional derivative (PD) based constant-amplitude input shaping logic is proposed to determine time locations of thruster switching. Then, under such inputs, spin-downs of the satellite are simulated numerically. Results of simulations indicate that the precise orientation of the satellite can be achieved. © (2014) Trans Tech Publications, Switzerland.