火星稀薄大气进入过程伞舱组合体振荡阻尼方法研究

In a Mars landing exploration mission, the stability of the parachute system is a prerequisite for ensuring the safety of the entry, descent, and landing process and the reliability of the equipment operation. The large oscillation of the attitude is currently the main threat to the safety of the descent and landing process. This paper proposes an active damping control method that is based on proportional feedback for the attitude oscillation problem of the parachute system with high dynamic coupling force shock. This method performs elimination of the attitude angle deviation as the goal of the control law design. The attitude oscillation suppression method under the limited control capability of the aeroshell is introduced, and the Lyapunov stability analysis method is used to strictly prove the uniform convergence of the proposed method. Finally, this paper separately addresses the problems of attitude oscillation after parachute deployment and after heat shield separation via numerical simulation analysis with and without active damping. The results demonstrate that the parachute system can be stabilized in a short time and verify the effectiveness of the proposed method in attitude stabilization.