Abstract
An attitude tracking control algorithm based on non-singular terminal sliding mode surface is proposed for a launch vehicle with unknown external disturbance and actuator stuck fault. Firstly, a multi-input multi-output (MIMO) system model of a launch vehicle attitude control system considering disturbance and actuator stuck fault is established. Then, a model of the launch vehicle attitude tracking system is established, and a non-singular terminal sliding mode surface is designed for the defined model, so that the system can track the reference signal accurately in the event of actuator fault. Based on the Lyapunov function, the stability and finite-time convergence characteristics of the launch vehicle attitude tracking control system are proved. The numerical simulations verify the effectiveness of the attitude tracking control algorithm based on non-singular terminal sliding mode for launch vehicle.
| Translated title of the contribution | Non-Singular Terminal Sliding Mode Fault-Tolerant Control of Launch Vehicle with Actuator Fault |
|---|---|
| Original language | Chinese (Traditional) |
| Pages (from-to) | 1553-1560 |
| Number of pages | 8 |
| Journal | Yuhang Xuebao/Journal of Astronautics |
| Volume | 41 |
| Issue number | 12 |
| DOIs | |
| State | Published - 30 Dec 2020 |
Fingerprint
Dive into the research topics of 'Non-Singular Terminal Sliding Mode Fault-Tolerant Control of Launch Vehicle with Actuator Fault'. Together they form a unique fingerprint.Cite this
- APA
- Author
- BIBTEX
- Harvard
- Standard
- RIS
- Vancouver