Abstract
A novel non-singular terminal sliding mode control method is proposed to solve the problem how to design the reaction-jet and aerodynamic compound control law for agile missiles with fast time variability, uncertainty, strong nonlinearity and the initial state of the system far away from the equilibrium point. In order to shorten the time to reach the equilibrium state, a combined non-singular terminal sliding mode surface is designed to improve the convergence speed when the system states are on the sliding mode surface, and an improved double power reaching law is designed to improve the speed when the system states are reaching the sliding mode surface. The extended state observer is used to estimate the internal and external disturbances of the system in real time, which eliminates the disturbance caused by the observation error and suppresses the chattering. Finally, the finite-time convergence property of the proposed method is proved, and the effectiveness of the proposed method is verified by simulation comparison.
| Translated title of the contribution | Novel Non-singular Terminal Sliding Mode Control for Missile's Agile Turn |
|---|---|
| Original language | Chinese (Traditional) |
| Pages (from-to) | 454-464 |
| Number of pages | 11 |
| Journal | Yuhang Xuebao/Journal of Astronautics |
| Volume | 43 |
| Issue number | 4 |
| DOIs | |
| Publication status | Published - 30 Apr 2022 |