Abstract: Aiming at improving the attitude control precision and stability for the flexible spacecraft, an accurate compensation method combining the nonlinear observation with inertia identification is proposed in the paper to improve the attitude control performance. The nonlinear full state observer is designed to estimate the modal of the flexible structures in order to compensate the disturbance torque caused by the flexible vibration. The Lipschtiz convergence condition for the nonlinear full state observer is proved. The inertia identification method based on the spacecraft angular rate polynomial fitting is designed to achieve better attitude maneuver performance. The numerical simulation comparison results illustrate that the proposed method can reduce the attitude maneuver time affected by the flexible vibration and inertia moment inaccurate. This method is correct and effective for the flexible spacecraft attitude maneuver.

Key words: Attitude maneuver, Accurate compensation, Lipschitz observer, Identification of the moment of inertia