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This paper presents a development of component synthesis vibration suppression (CSVS) method for maneuvering flexible spacecrafts. The proposed method eliminates unwanted flexible vibrations while achieving the desired rigid body attitude motion. The robustness to uncertainties of dynamic modeling parameters is analyzed. Unlike traditional input shaping in which a numerical optimization is utilized, design for CSVS commands is based on analytic methodology and is relative easy to implement. A case study is performed on a time-fuel optimal control strategy using constant amplitude reaction thrusters. Both simulation and experimental results validate the effectiveness of the proposed approach.