摘要
An attitude stabilization scheme is presented for a rigid satellite. The partial loss of reaction wheel effectiveness is tolerated, and reaction wheel misalignment is also compensated. The Lyapunov stability analysis shows that the closedloop attitude system is guaranteed to be almost asymptotically stable in finite-time. An illustrative example of a satellite is given, and simulation results show the effectiveness of the derived control law.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 1434-1438 |
| 页数 | 5 |
| 期刊 | Kongzhi yu Juece/Control and Decision |
| 卷 | 29 |
| 期 | 8 |
| DOI | |
| 出版状态 | 已出版 - 1 8月 2014 |
| 已对外发布 | 是 |