Abstract
The output feedback control for spacecraft attitude tracking system is investigated in this study. It is assumed that angular velocity measurements are not available for feedback control. A technique named adding power integrator (API) is adopted to estimate the pseudo-angular-velocity. Then we design a finite-time attitude control law, which only utilizes the relative attitude information. The stability analyses of the feedback system are proved as well, which shows the attitude tracking errors will converge into a region of zero even the external disturbances exist. The simulation results illustrate the high precision and robust attitude control performance of the proposed control strategy.
| Original language | English |
|---|---|
| Article number | 8277367 |
| Pages (from-to) | 1174-1185 |
| Number of pages | 12 |
| Journal | Journal of Systems Engineering and Electronics |
| Volume | 28 |
| Issue number | 6 |
| DOIs | |
| State | Published - Dec 2017 |
Keywords
- finite-time control
- output feedback
- spacecraft attitude stabilization
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