Abstract
This paper deals with the controller design of the attitude control system of spacecraft. The sliding mode controller was proposed to avoid the influence of parameters' uncertainty and the external disturbance. The delay factor was introduced in the reaching-law to reduce the control torque required by the system, which could save on the payload of the spacecraft. The simulation results are illustrated to verify the designed controller. The effect of improving the stability of the controller is also verified by using the sign function.
| Original language | English |
|---|---|
| Pages (from-to) | 1198-1202 |
| Number of pages | 5 |
| Journal | Beijing Ligong Daxue Xuebao/Transaction of Beijing Institute of Technology |
| Volume | 31 |
| Issue number | 10 |
| Publication status | Published - Oct 2011 |
Keywords
- Attitude control
- Robust control
- Sliding mode control
- Spacecraft
- Uncertainty