Attitude maneuver of a precise-oriented satellite is studied in this paper. The satellite consists of a rigid main body and two symmetrical flexible solar panels. The equations of motion are derived using Lagrange's Formulation, and the finite element method is used to discretized elastic motion of the panels. The satellite is equipped with constant-amplitude torque input to maneuver its attitude. Using fastest time-optimal input, the satellite has poor accuracy after maneuver. Input shaper shows the capability to improve the satellite accuracy in attitude. However, the structural deflection of the panels during transient state in the maneuver process can be very large. The paper proposes the input shaping procedure to maneuver the satellite with excellent attitude accuracy after and small structural deflection during the maneuver process. The performance of procedure is then examined using numerical simulation. © 2016 IEEE.