Robust component synthesis vibration suppression for maneuver of flexible spacecrafts

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