Flexible spacecraft attitude control based on perturbation method analysis

In order to achieve flexible spacecraft high precision attitude control, using the perturbation method, the dynamic equations were divided into the zero order and first order systems. For the zero-order nonlinear time-invariant systems, taking into account the inertia uncertainty and disturbance, the nonlinear direct adaptive control law was improved, and the improvement of the gain adaptation law aimed at the higher precision. Also, the stability proof was given. For the first-order system, the proportional-integral(PI) controller and positive position feedback(PPF) controller were designed to suppression the vibration. The simulation shows that the perturbation analysis and the corresponding controller design can achieve the flexible spacecraft high precision attitude control.