Abstract
This paper examines attitude synchronization and tracking problems with model uncertainties, external disturbances, actuator failures and control torque saturation. Two decentralized sliding mode control laws are proposed and analyzed based on algebraic graph theory. Using Barbalat's Lemma, it is shown that the control laws guarantee each spacecraft approaches the desired time-varying attitude and angular velocity while maintaining attitude synchronization among the other spacecraft in the formation. The first controller is designed in the presence of model uncertainties, external disturbances, and actuator failures. The results are extended to the case with control input saturation in the second controller. Both control laws do not require online identification of failures. Numerical simulations are presented to show the effectiveness of the proposed attitude synchronization and tracking approaches.
| Original language | English |
|---|---|
| Pages (from-to) | 333-343 |
| Number of pages | 11 |
| Journal | Acta Astronautica |
| Volume | 105 |
| Issue number | 1 |
| DOIs | |
| State | Published - Dec 2014 |
Keywords
- Attitude control
- Attitude synchronization
- Attitude tracking
- Fault tolerant
- Sliding mode control
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